Tdr94 94d Instruction Book 2z2w29
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Collins TDR-94/94D ATC/Mode S Transponder System instruction book
Collins General Aviation Division
June 15, 1995
TO:
HOLDERS OF THE TDR-94/94D ATC/MODE S TRANSPONDER SYSTEM INSTRUCTION BOOK (523-0775652)
7TH EDITION HIGHLIGHTS The attached pages complete replace the existing instruction book. bars in the margin of the page.
All changes are identified by black
This new material incorporates changes and new material previously published via Addendums and various material found necessary during the review effort. Principle among these changes are the Acceptance Test Procedures in tables 5-11, 5-12, and 5-13.
PUBLICATIONS DEPARTMENT
1/2
523-0775652-00711A 7th Edition, 15 June 1995
Collins TDR-94/94D ATC/Mode S Transponder System
instruction book This publication includes: General Information Operation Theory of Operation Maintenance
Collins General Aviation Division Rockwell International Corporation Cedar Rapids, Iowa 52498 Printed in the United States of America ©Rockwell International 1995
523-0775653 523-0775655 523-0775656 523-0775657
WARNING INFORMATION SUBJECT TO EXPORT CONTROL LAWS This document may contain information subject to the International Traffic in Arms Regulation (ITAR) or the Export istration Regulation (EAR) of 1979 which may not be exported, released, or disclosed to foreign nationals inside or outside of the United States without first obtaining an export license. A violation of the ITAR or EAR may be subject to a penalty of up to 10 years imprisonment and a fine of up to $1,000,000 under 22 U.S.C.2778 of the Arms Export Control Act of 1976 or section 2410 of the Export istration Act of 1979. Include this notice with any reproduced portion of this document.
Caution The material in this publication is subject to change. Before attempting any maintenance operation on the equipment covered in this publication, that you have complete and up-to-date publications by referring to the applicable Publications and Service Bulletin Indexes.
SOFTWARE COPYRIGHT NOTICE Copyright, 1989, 1990, 1991, 1992, 1993, 1994, 1995 Rockwell International Corporation All software resident in this equipment is protected by copyright.
We welcome your comments concerning this publication. Although every effort has been made to keep it free of errors, some may occur. When reporting a specific problem, please describe it briefly and include the publication part number, the paragraph or figure number, and the page number. Send your comments to:
Publications Department MS 106-124 Collins General Aviation Division Rockwell International Corporation Cedar Rapids, Iowa 52498 or by Internet E-Mail to: [email protected]
SPECIFIC ADVISORIES FOR THE <EQ TYPE> Warning Rockwell International does not take the responsibility for certification of the TDR-94/94D when used with equipment other than those covered by the Rockwell International Collins Avionics safety analysis. Warning Electronic control systems, such as autopilots, engine controls, fuel controls, temperature sensors, etc, used for aircraft control can be susceptible to transmissions from communications transceivers, DME’s, transponders, etc, that can interfere with aircraft operations. If such a situation occurs, discontinue transmission or select a different frequency. If necessary, turn off the radio. Warning Service personnel are to obey standard safety precautions, such as wearing safety glasses, to prevent personal injury while installing or doing maintenance on this unit. Warning Use care when using sealants, solvents, and other chemical compounds. Do not expose to excessive heat or open flame. Use adequate ventilation. Avoid prolonged breathing of vapors and avoid prolonged with skin. Observe all cautions and warnings given by the manufacturer. Warning Remove all power to the unit before disassembling it. Disassembling the unit with power connected is dangerous to life and may cause voltage transients that can damage the unit. Warning This unit may have components that contain materials (such as beryllium oxide, acids, lithium, radioactive material, mercury, etc) that can be hazardous to your health. If the component enclosure is broken, handle the component in accordance with OSHA requirements 29CFR 1910.1000 or superseding documents to prevent personal with or inhalation of hazardous materials. Since it is virtually impossible to determine which components do or do not contain such hazardous materials, do not open or disassemble components for any reason. Warning This unit exhibits a high degree of functional reliability. Nevertheless, s must know that it is not practical to monitor for all conceivable system failures and, however unlikely, it is possible that erroneous operation could occur without a fault indication. The pilot has the responsibility to find such an occurrence by means of cross-checks with redundant or correlated data available in the cockpit. Caution Turn off power before disconnecting any unit from wiring. Disconnecting the unit without turning power off may cause voltage transients that can damage the unit.
i
Caution This unit contains electrostatic discharge sensitive (ESDS) components and ESDS assemblies that can be damaged by static voltages. Although most ESDS components contain internal protection circuits, good procedures dictate careful handling of all ESDS components and ESDS assemblies. Obey the precautions given below when moving, touching, or repairing all ESDS components and units containing ESDS components. a. Deenergize or remove all power, signal sources, and loads used with the unit. b. Place the unit on a work surface that can conduct electricity (is grounded). c. Ground the repair operator through a conductive wrist strap or other device using a 470-kΩ or 1-MΩ series resistor to prevent operator injury. d. Ground any tools (and soldering equipment) that will the unit. with the operator’s hand is a sufficient ground for hand tools that are electrically isolated. e. All ESDS replacement components are shipped in conductive foam or tubes and must be stored in their shipping containers until installed. f. ESDS devices and assemblies, that are removed from a unit, must immediately be put on the conductive work surface or in conductive containers. g. Place repaired or disconnected circuit cards in aluminum foil or in plastic bags that have a layer of, or are made with, conductive material. h. Do not touch ESDS devices/assemblies or remove them from their containers until they are needed. Failure to handle ESDS devices as described above can permanently damage them. This damage can cause immediate or premature device failure.
ii
ROCKWELL COLLINS INSTRUCTION BOOK TDR-94/94D, PART NO 622-9352/622-9210 RECORD OF TEMPORARY REVISIONS Note: Insert this page following Specific Advisories page ii. TEMPORARY REV NO
PAGE NUMBER
DATE ISSUED
1
1-11
Aug 15/00 Rockwell Collins
2
1-2
Nov 22/02 Rockwell Collins
BY
DATE REMOVED
BY
NOTICE INFORMATION SUBJECT TO EXPORT CONTROL LAWS This document contains technical data that may be restricted for export under the International Traffic in Arms Regulations (ITAR) or the Export istration Regulations (EAR). Violations of these export laws may be subject to fines and penalties under the Arms Export Control Act (22 U.S. C. 2778).
Temporary Revision 2 523-0775652-02711A
RTR-1/RTR-2 Nov 25/02
523-0775653-006118 6th Edition, 15 June 1995
TDR-94/94D ATC/Mode S Transponder System General Information
table of contents
Paragraph
Page
1.1 INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1-1
1.2 PURPOSE OF EQUIPMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1-1
1.3 EQUIPMENT REQUIRED BUT NOT SUPPLIED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1-1
1.4 RELATED PUBLICATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1-2
1.5 STORAGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1-12
1.6 RELATED SERVICE BULLETINS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1-12
NOTICE: This section replaces fifth edition dated 5 May 1993.
List of Effective Pages Page
*The asterisk indicates pages changed, added, or deleted by the current change.
Issue
*Title . . . . . . . . . . . . . . *List of Effective pages 1-1 thru 1-5 . . . . . . . . . 1-6 thru 1-9 . . . . . . . . . 1-10 thru 1-13 . . . . . . . 1-14 Blank . . . . . . . . . .
. . . . . .
. . . . . .
. . . . . .
. . . . . .
. . . . . .
15 Jun 15 Jun . 5 May 15 Jun . 5 May . 5 May
95 95 93 95 93 93
Record of Revisions INSERTION DATE/BY
RETAIN THIS RECORD IN THE FRONT OF THE MANUAL. ON RECEIPT OF REVISIONS, INSERT REVISED PAGES IN THE MANUAL, AND ENTER DATE INSERTED AND INITIALS.
REV / ED NO
REVISION DATE
SB NUMBER INCLUDED
0/1
4 Apr 89
None
0/2
4 Apr 90
None
0/3
29 Apr 91
None
0/4
6 Jan 92
None
0/5
5 May 93
See Table 1-6
0/6
15 Jun 95
See Table 1-6
REV / ED NO
REVISION DATE
INSERTION DATE/BY
SB NUMBER INCLUDED
I
section general information 1.1 INTRODUCTION This publication provides all the specifications, principles of operation, and information necessary to test and troubleshoot the TDR-94 and TDR-94D Mode S Transponder System in the airplane. The information includes a bench testing procedure to the performance capability before installation of a new or newly repaired transponder. Refer to table 1-1 for a list of equipment covered in this manual and table 1-2 for the TDR-94/94D
Comm/Nav/Pulse System Installation Manual for a listing of the various CTL-92/92A, RTU-870A/T and other controls available for use with the TDR94/94D. The TDR-94D Transponder is a Diversity version; i.e., it is capable of transmitting and receiving on either of two antennas. The TDR-94 is a non-diversity model. The TDR-94D is fully compatible with TCAS II system installations requiring antenna diversity. Either of two antenna types can be used with the TDR-94/94D as shown in table 1-1. 1.2 PURPOSE OF EQUIPMENT
TDR-94/94D Mode S Transponder Figure 1-1
specifications. Table 1-3 is a listing of environmental requirements for DO-160B. Table 1-4 is a listing of publications related to the TDR-94/94D. Table 1-6 is a listing of Service Bulletins and Service Information Letters that have been released up to the date of this manual edition. Figure 1-1 is an overall view of the TDR-94/94D.
The TDR-94/94D is an integral part of the Air Traffic Control Radar Beacon System (ATCRBS). The TDR-94/94D operates in mode A by responding to normal beacon radar interrogations. This mode provides identification of transponderequipped airplanes on the ground controller’s plan position indication (PPI). If the installation is equipped with a compatible altitude encoder, it can operate in mode C and provide altitude data long with the normal reply. In the mode S scheme, each airplane is assigned a unique identification code which allows automatic and unique interrogation and display of a specific airplane. The airplane identification is assigned at installation and is based on the identification (tail) number. The unique identifier is required in TCAS operation. In addition, the TDR-94/94D can receive and send data link messages that are required for ATC automation. The added data link capability allows the transponder to perform additional air traffic control and airplane separation assurance (ASA) functions.
1.1.1 General Description The TDR-94/94D Transponder is a solid-state, airborne, air traffic control (ATC) transponder. The TDR-94 or TDR-94D Transponder is normally mounted in a MMT-150 Modular Mounting Tray and controlled by an ATC control like the the CTL-92/92A Control. Refer to the Pro Line II
5/5/1993
1.3 EQUIPMENT REQUIRED BUT NOT SUPPLIED Table 1-4 lists the equipment required for proper operation of the TDR-94/94D but is not supplied with the unit. Equivalent equipment may be substituted.
1-1
general information 523-0775653 1.4 RELATED PUBLICATIONS Table 1-5 lists publications related to TDR-94/94D operation. Table 1-1. Equipment Covered. COLLINS EQUIPMENT
DESCRIPTION
PART NUMBER
TDR-94
Mode A, C, and S ATC Transponder
622-9352-003
ANT-42
L-band antenna for transponder or DME. Uses ac signal coupling to radiating. element.
622-6591-001
MMT-150
Mounting Tray for TDR-94/94D
622-9672-003
FOR INSTALLATIONS USING CSDB TUNING CTL-92
Pro Line II, ATC Control (uses CSDB data format). Refer to Pro Line II Comm/NAV/Pulse Installation Manual for available options.
622-6523-XXX
CTL-92T
Transponder and TCAS Control, used in conjunction with CTL-92/92A to add TCAS control functions. Refer to TCAS-94 Traffic Alert and Collision Avoidance System Installation Manual for available options.
622-9614-XXX
FOR INSTALLATIONS USING ARINC 429 TUNING RTU-870A
Remote Tuning Unit, gives centralized control and display of the frequency/ATC code and modes of the Collins -4XX series of General Aviation equipment. Refer to Pro Line II Comm/NAV/Pulse Installation Manual for available options.
622-9346-XXX
RTU-870T
Remote Tuning Unit, same as RTU-870A except includes TCAS control capability. Refer to Pro Line II Comm/NAV/Pulse Installation Manual for available options.
622-9856-XXX
ALTERNATE MODELS AVAILABLE TDR-94D
Same as TDR-94 except with diversity capability
622-9210-003
TDR-94
Same as TDR-94 -003 except without TCAS compatibility features. Can be used in installations without TCAS and where diversity is not required.
622-9352-002
TDR-94D
Same as TDR-94D -003 except without TCAS compatibility features. Can be used in installations without TCAS and where diversity is needed.
622-9210-002
TDR-94/94D
This model is no longer ed. All existing -001 units should be upgraded to at least -002.
622-9352-001 622-9210-001
CTL-92A
Same as CTL-92 except with enhanced display capability Refer to Pro Line II Comm/NAV/Pulse Installation Manual for available options.
622-8740-XXX
237Z-1
Similar to ANT-42 except uses dc coupling to radiating element.
522-2632-001
TTC-920G
Transponder/TCAS Control. Dedicated control for TCAS and Mode S Transponder. Refer to TCAS-94 Traffic Alert and Collision Avoidance System Installation Manual for available options.
822-0078-XXX
5/5/1993
1-2
ROCKWELL COLLINS INSTRUCTION BOOK TDR-94/94D, PART NO 622-9352/622-9210 TDR-94/94D ATC/Mode S Transponder System INSTRUCTION BOOK (523-0775652, 7TH EDITION, DATED JUN 15/95)
TEMPORARY REVISION NO. 02 Insert facing page 1-2. Subject: Elementary Surveillance (Flight ID) Installation Guidelines Flight ID capability is one of the functions required by Elementary (Basic) Surveillance. Elementary Surveillance is a subset of Enhanced Surveillance. The -007 version of the TDR-95/94D s both Elementary and Enhanced Surveillance requirements. Details of the requirements for Enhanced Surveillance will be covered in a future Service Information Letter. Existing versions of the TDR-94/94D can be updated to Elementary/Enhanced Surveillance functionality as shown below. UNIT
PRIOR PART NUMBER
SERVIE BULLETINS REQUIRED
NEW PART NUMBER*
TDR-94
622-9352-003
13, 501
622-9352-007
TDR-94D
622-9210-003
13, 501
622-9352-007
*The new TDR-94/94D part numbers (-007 status) are covered in associated TDR-94/94D component maintenance manual (523-0778502). Refer to the Pro Line II Installation Manual (523-0772719) for TDR94/94D installation requirements, and to TDR-94/94D SIL 1-02 for additional system operation and
aircraft installation information. If converting a TDR-94/94D -003 status, additional wiring changes will be required. Refer to SIL 1-96 on the TDR-94/94D for additional information on the applicable changes.
Temporary Revision 2 523-0775652-02711A
Page 1 of 1 Nov 25/02
general information 523-0775653
Table 1-2. Equipment Specifications. CHARACTERISTIC
SPECIFICATION
Certification TSO FAA
TSO-C112, class 2A
RTCA
D0-181, D0-144
Software
DO-178A, level 2
EUROCAE
ED-12A
Deutsche Bundespost FTZ
A44652010
ICAO
Annex 10
Environmental FAA
DO-160B, refer to table 1-3 for additional information
EUROCAE
ED-12A
Height
84.6 mm (3.33 in)
Width
124.5 mm (4.90 in)
Length
317.5 mm (12.50 in)
Weight
3.6 kg (8.5 lb)
Physical Size
Mounting
MMT-150; 1/2 ATR, short, dwarf ( Refer to Pro Line II Comm/NAV/Pulse Installation Manual for additional information.)
Mating Connector
Thinline II, qty 2, 60-pin (Kits: N: 628-8661-001/002 or 628-8660-001/002) ( Refer to Pro Line II Comm/NAV/Pulse Installation Manual for additional information.)
Time between overhaul
On condition of failure or as required by Federal Regulations (see below)
Regulatory requirement for flightline test
FAR 91.413 ATC TRANSPONDER TESTS AND INSPECTIONS. "(a) No person may use an ATC transponder that is specified in Part 125 §91.24 (a), §121.345, §127.123 (b), or §135.143 (c) of this chapter unless, within the preceding 24 calendar months, that ATC transponder has been tested and inspected and found to comply with Appendix F of Part 43 of this chapter; and following any installation or maintenance on an ATC transponder where data correspondence error could be introduced, the integrated system has been tested, inspected, and found to comply with paragraph Appendix E of Part 43 of this chapter."
Power requirements
27.5 ±2.5 V dc at 28 watts nominal, 30 watts maximum
Transmitter Frequency
1090 MHz, ±1 MHz
Power output
250 watts min, 625 watts maximum
Load impedance
50Ω nominal
VSWR
1.5:1 service max., 3:1 survival
5/5/1993
1-3
general information 523-0775653
Table 1-2. Equipment Specifications. (cont’d) CHARACTERISTIC
SPECIFICATION
Receiver Frequency
1030 MHz nominal
IF
60 MHz
Sensitivity
-77 dBm ±3 dBm
Reply modes
ATCRBS mode A ATCRBS mode C ATCRBS mode A/Mode S All Call ATCRBS mode C/Mode S All Call ATCRBS mode A only All Call ATCRBS mode C only All Call Mode S, short (56-bit) Mode S, long (112-bit)
Reply rate ATCRBS
500 15-pulse replies/sec 1200 15-pulse replies in 100 ms
Mode S
34 short and 16 long replies in 1 sec 12 short and 6 long replies in 100 ms 4 short and 4 long replies in 25 ms 2 short and 2 long in 1.6 ms
ATCRBS side lobe suppression Max of 10%l replies and sls initiated
P1 pulse is MTL + 3 dB to -21 dBm and P2 equal to or greater than P1
Max of 10% replies and sls may be initiated
P1 pulse is MTL to MTL + 3 dB and P2 equal to or greater than P1
Minimum of 90% replies and no sls
P1 pulse is MTL +3 dB to -21 dBm, and P1 pulse is min 9 dB greater than P2 No P2 pulse occurs at 2.0 ±0.7 µs after leading edge of P1, or P2 pulse duration is less than 0.3 µs
Mode S side lobe suppression
Max of 10%
Electrical Primary power (P1-58)
27.5, ±2.5, V dc (+), 28 watts nominal, 100 watts peak
Primary power common (P1-60)
27.5 V dc (-)
5/5/1993
1-4
general information 523-0775653
Table 1-2. Equipment Specifications. (cont’d) CHARACTERISTIC
SPECIFICATION
Data bus: CSDB Structure
8-bits/byte, 6-bytes/block
Rate
12.5 Baud, 10-block/sec nominal, 18 max
Data blocks
(all labels are in hexadecimal form) A5: sync; input A0: altitude data; input 1E: ATC code/altitude; input or output 1F: ATC data; output F3: diagnostic data; output
ARINC 429 Structure
8-bits/byte, 4-bytes/word
Rate
5-words/sec min
Data labels
(all labels are in octal form) *013: TDR and TCAS control; input/output *015: Altitude select limits, input/output *016: Mode S control; input/output *031: ATC Transponder Control, input/output *200: Gillham altitude encoder data; input/output *203: TDR altitude data to TCAS; input/output 204: TDR corrected barometric altitude to TCAS; output 272: TCAS coordination data, part 1; output 273: TCAS data for downlink message formats 16, 20, 21; input 274: TCAS coordination data, part 2; output 274: TCAS data for downlink message formats 0 and 16; input 275: TCAS control, part 1; output 275: TCAS acknowledge; input 276: TCAS control, part 2; output 277: TCAS acknowledge; input 277: Diagnostic data request; input 350: Maintenance data; output 371: Equipment ident; output * These labels are normally echoed, and/or ed through to the TCAS, as received except for the SSM which may be different depending on the state of the transponder.
Tuning inputs
Monitored only if Burst Mode (P2-59) is not selected; i.e., P2-59 is open
P2-31 P2-32
CSDB, A CSDB, B
P2-17 P2-18
ARINC 429, A (tune input port A) ARINC 429, B (tune input port A)
P2-13 P2-14
ARINC 429, A (tune input port B) ARINC 429, B (tune input port B)
P2-21 P2-22
ARINC 429, A (tune input port C) ARINC 429, B (tune input port C)
Altitude inputs P2-33 P2-34
CSDB, A (altitude input port A) CSDB, B (altitude input port A)
P2-35 P3-36
CSDB, A (altitude input port B) CSDB, B (altitude input port B)
5/5/1993
1-5
general information 523-0775653
Table 1-2. Equipment Specifications. (cont’d) CHARACTERISTIC
SPECIFICATION
Input/Output Altitude inputs (cont’d) P2-25 P2-26
ARINC 429/575, A (altitude input port A) ARINC 429/575, B (altitude input port A)
P2-29 P2-30
ARINC 429/575, A (altitude input port B) ARINC 429/575, B (altitude input port B)
Data outputs P2-23 P2-24
CSDB, A (Bus 1) CSDB, B (Bus 1)
P2-27 P2-28
CSDB, A (Bus 2) CSDB, B (Bus 2)
P2-15 P2-16
ARINC 429, A (Port A) ARINC 429, B (Port A)
P2-19 P2-20
ARINC 429, A (Port B) ARINC 429, B (Port B)
Peripheral data P2-1 P2-2
ARINC 429, A (Comm A/B input) ARINC 429, B (Comm A/B input)
P2-3 P2-4
ARINC 429, A (Comm A/B output) ARINC 429, B (Comm A/B output)
P2-5 P2-6
ARINC 429, A (Comm C/D input) ARINC 429, B (Comm C/D input)
P2-7 P2-8
ARINC 429, A (Comm C/D output) ARINC 429, B (Comm C/D output)
P2-9 P2-10
ARINC 429, A (TCAS coord data input) ARINC 429, B (TCAS coord data input)
P2-11 P2-12
ARINC 429, A (TCAS coord data output) ARINC 429, B (TCAS coord data output)
Discrete inputs P1-1 P1-2 P1-3 P1-4 P1-5 P1-6 P1-7 P1-8 P1-9 P1-10 P1-11 P1-12
B4, ARINC 572 altitude input B2, ARINC 572 altitude input B1, ARINC 572 altitude input A4, ARINC 572 altitude input A2, ARINC 572 altitude input A1, ARINC 572 altitude input D4, ARINC 572 altitude input D2, ARINC 572 altitude input C4, ARINC 572 altitude input C2, ARINC 572 altitude input C1, ARINC 572 altitude input Common, ARINC 572 altitude input
Mode S address discretes P1-32 P1-33 P1-34
6/15/1995
Common B1 B2
1-6
general information 523-0775653
Table 1-2. Equipment Specifications. (cont’d) CHARACTERISTIC
SPECIFICATION
Input/Output (continued) Mode S address discretes (cont’d) P1-35 P1-36 P1-37 P1-38 P1-39 P1-40 P1-41 P1-42 P1-43 P1-44 P1-45 P1-46 P1-47 P1-48 P1-49 P1-50 P1-51 P1-52 P1-53 P1-54 P1-55 P1-56
B3 B4 B5 B6 B7 B8 B9 B10 B11 B12 B13 B14 B15 B16 B17 B18 B19 B20 B21 B22 B23 B24
Single discrete straps P2-51
Antenna, dual/single select (gnd = single)
P2-56
CSDB/ARINC 429 control select (gnd = CSDB)
P2-60
ADLP installed (gnd = ADLP included in installation)
P1-13
TCAS installed (gnd = TCAS included in installation) Note: There is no provision for TCAS control in CSDB. Therefore, the TDR-94D will not report TCAS capability in its replies to interrogations when CSDB is enabled (P2-56 grounded) even if TCAS is selected (P1-13 grounded) and dual antenna enabled (P2-51 open).
Discrete I/O P2-55
Standby discrete (gnd = in standby)
P1-28 (-003)
Automatic altitude select (gnd = auto alt select enabled)
P1-14
Control Altitude Select (See Combination Discretes below) (gnd = port A altitude data supplied on control port, port B same as open), (open = ports A and B altitude selectable via altitude type select discretes, P2-41/42)
P2-53
Air/ground discrete (gnd = WOW)
P2-48
Reporting altitude port select (gnd = port B)
P2-59
Burst tune enable (gnd = burst) Note: In Burst Tune mode the control port strapping (P2-57/58) is ignored. Burst tune data is accepted on ports A, B, and C as 30 ARINC-429 words spaced over an interval of 1.5 seconds with 500 msec dwell time on each port and the dwell time suspended when data is present. Continuous data is always accepted if available.
6/15/1995
1-7
general information 523-0775653
Table 1-2. Equipment Specifications. (cont’d) CHARACTERISTIC
SPECIFICATION
Discrete I/O (continued) P1-15 P1-30
Cross-side input (connected to opposite TDR P1-30, gnd input = command to standby) Cross-side output (connected to opposite TDR P1-15, gnd output = active mode) (These connections are used in dual burst-tune TDR installations to ensure that only one transponder is operating at a time)
P1-31
Fault monitor output (28 V dc = valid, 200 mA max)
P1-29
Suppression input/output (connected to all other L-band equipment)
P1-16 (-003)
SPI (remote ident) input
Maintenance specific: P2-38
Self-test inhibit (gnd = inhibited) (for maintenance purposes only)
P2-54
Self-test discrete (gnd = self-test on) (for bench test/maintenance purposes only)
Combination discrete straps P2-41, P2-42, and P1-14
P1-14
P2-41
P2-42
Altitude Type Selected
open open open open gnd
gnd open gnd open gnd
gnd gnd open open gnd
gnd
open
gnd
gnd
gnd
open
gnd
open
open
ARINC 429 on ARINC ports A and B CSDB on CSDB ports A and B ARINC 575 on ARINC ports A and B ARINC 572 (Gillham) on the Gillham parallel port Port A altitude on the selected control bus (either ARINC 429 or CSDB) and port B altitude type ARINC 429 on ARINC port B. Port A altitude on the selected control bus (either ARINC 429 or CSBB) and port B altitude type CSDB on CSDB port B. Port A altitude on the selected control bus (either ARINC 429 or CSDB) and port B altitude type ARINC 575 on ARINC port B. Port A altitude on the selected control bus (either ARINC 429 or CSDB) and port B altitude type Gillham on the Gillham parallel port.
P2-43, P2-44, P2-45
Max airspeed programming (gnd to P2-49) P2-43 P2-44 P2-45 Definition open open open none selected gnd open open 0 to 75 knots open gnd open 75 to 150 knots gnd gnd open 150 to 300 knots open open gnd 300 to 600 knots gnd open gnd 600 to 1200 knots open gnd gnd more than 1200 knots gnd gnd gnd (not defined)
P2-46, P2-47
SDI input (gnd to P2-50) P2-46 P2-47 Definition open open (not used) open gnd side 1 gnd open side 2 gnd gnd (not used)
6/15/1995
1-8
general information 523-0775653
Table 1-2. Equipment Specifications. (cont’d) CHARACTERISTIC
SPECIFICATION
Discrete I/O (continued) Combination discrete straps (continued) P2-57, P2-58
Control port select (gnd to P2-52) P2-57 P2-58 Definition gnd open Port A selected open open Port B selected open gnd Port C selected gnd gnd (not defined) Table 1-3. DO-160B Environmental Qualifications.
CHARACTERISTIC
DO-160B PARA NO
QUALIFICATION LEVEL
Temperature and Altitude
4.0
Category F2:
Low Operating Temp High Operating Temp Low Storage Temp High Storage Temp
4.5.1 4.5.3 4.5.1 4.5.2
-55 °C (-67 °F) +70 °C (+158 °F) -55 °C (-67 °F) +85 °C (+185 °F)
Altitude
4.6.1
Category A2: Certified for installation in a controlled temperature locations where pressures are no lower than an altitudes equivalent to 4600 m (15 000 ft) msl. Category E1: Certified for installation in a nonpressurized and noncontrolled temperature locations in an airplane that is operated at altitudes up to 21 300 m (70 000 ft) msl.
Temperature Variation
5.0
Category B:
Certified for installation in a controlled or noncontrolled temperature location in the airplane.
Humidity
6.0
Category B:
Certified for a Severe Humidity Environment - Level I.
Shock Operational Crash Safety
7.0 7.2 7.3
Tested at 6 g peak Tested at 15 g (11 ms duration)
Vibration
8.0
Category J: Category Y:
Certified for fuselage mounting in a fixed wing turbojet or turbofan airplane. Certified for fuselage mounting in a piston or turbojet rotary wing airplane.
Explosion Proofness
9.0
Category E1: Certified for installation in a location where an explosive atmosphere may occur as a result of leakage or spillage.
Waterproofness
10.0
Category X:
No test required. Certified for installation in locations not subject to falling water (including condensation), rain water, or sprayed water.
Fluids Susceptibility
11.0
Category X:
No test required. Certified for installation in locations not exposed to fluid contamination from fuel, hydraulic fluids, oil, solvents, etc.
Sand and Dust
12.0
Category X:
No test required. Certified for installation in locations not subject to blowing sand and dust.
Fungus Resistance
13.0
Category X:
Fungus resistance test not performed.
Salt Spray
14.0
Category X:
Salt spray test not performed.
6/15/1995
1-9
general information 523-0775653
Table 1-3. DO-160B Environmental Qualifications.
CHARACTERISTIC
DO-160B PARA NO
QUALIFICATION LEVEL
Magnetic Effect
15.0
Category Z:
Unit causes a 1° deflection of an uncompensated com at a distance less than 0.3 m (1.0 ft).
Power Input
16.0
Category Z:
Certified for use on airplane electrical systems not applicable to any other category. For example, a dc system from a variable range generator where a small capacity or no battery is floating on the dc bus.
Voltage Spike
17.0
Category A:
Certified for installation in systems where a high degree of voltage spike protection is required.
Audio Frequency Susceptibility
18.0
Category Z:
Certified for use on aircraft electrical systems not applicable to any other category. For example, a dc system from a variable range generator where a small capacity or no battery is floating on the dc bus.
Induced Signal Susceptibility
19.0
Category Z:
Certified for operation in systems where interference-free operation is required.
RF Susceptibility
20.0
Category Z:
Certified for operation in systems where interference-free operation is required.
Emission of RF Energy
21.0
Category Z:
Certified for operation in systems where interference-free operation is required.
Lightning
22.0
Category L:
Long and short wave (750 volts) Damped sinusoidal wave (600 volts)
5/5/1993
1-10
BUSINESS AND REGIONAL SYSTEMS INSTRUCTION BOOK TDR-94/94D, PART NO 622-9352/622-9210 TDR-94/94D ATC/Mode S Transponder System INSTRUCTION BOOK (523-0775652, 7TH EDITION, DATED JUN 15/95)
TEMPORARY REVISION NO. 01 Insert facing page 1-11 Subject:Add BA609 Connector Kit and Mount A new version of the MMT-150 Modular Mounting Tray and TDR-94/94D Connector Kit has been created for BA609 aircraft installations. MMT-150 622-9672-004 and Connector Kit 628-8660-003 are added to Table 1-4. P/O Table 1-4. Equipment Required But Not Supplied. EQUIPMENT
TYPE OR DESCRIPTION
QTY
**
MMT-150 Mount
½ ATR, short, dwarf mount (N: 622-9672-004) for BA609 installations
1
**
60-pin, Thinline II connector, qty 2 each, (Kit N 628-8661-001/002 or 628-8660-001/002 or 628-8660-003 for BA609 installations) (Refer to Pro Line II Installation Manual, for additional details.)
1-kit
Connector Kit
**
Refer to TDR-94/94D installation section in Pro Line II Comm/Nav/Pulse System Installation Manual for additional mount and mating connector information.
Temporary Revision 1 523-0775652-01711A
Page 1 of 1 Aug 15/00
general information 523-0775653
Table 1-4. Equipment Required But Not Supplied. EQUIPMENT
TYPE OR DESCRIPTION
QTY
**MMT-150 Mount
1/2 ATR, short, dwarf mount (N: 622-9672-003)
1
**Connector Kit
60-pin, Thinline II connector, qty 2 each, (Kit N: 628-8661-001/002, or 6288660-001/002) (Refer to Pro Line II Installation Manual, for additional details)
1-kit
**Crimp s
For wires with: up to 0.050 in. insulation dia (372-2514-110), or 0.050 to 0.080 in. insul dia (372-2514-180)
* 105 used, 15 spares
L-band antenna
Collins ANT-42, N: 622-6591-001, or Collins 237Z-1, N: 522-2632-001; qty 1 for TDR-94, qty 2 for TDR-94D
AR
ATC Control
CSDB data format: Collins CTL-92/92A ATC Control, with Collins CTL-92T if TCAS is used, ARINC 429 data format: Collins RTU-870A Radio Tuning Unit, or Collins RTU-870T TCAS/ATC Radio Tuning Unit, or Collins TTC-920G TCAS/ATC Control, or Gables model 816
Altitude data source
Collins ADS-85 Air Data System (Refer to ADS-85 Air Data System Installation Manual)
Air Data Link Message Processor
TBA (not available at time of this publication)
Traffic Alert and Collision Avoidance System
Collins TCAS-94 System (Refer to TCAS-94 Installation Manual)
*Quantity required for typical installation **Refer to installation section for additional mount and mating connector information Table 1-5. Related Publications. PUBLICATION
ATA NUMBER
COLLINS PART NUMBER
Collins Avionics Standard Shop Practices, Instruction Manual
none
523-0768039
TDR-94/94D ATC/Mode S Transponder, Component Maintenance Manual
34-50-91
523-0775997
Collins Pro Line II Comm/Nav/Pulse System, Installation Manual
none
523-0772719
TCAS-94 Traffic Alert and Collision Avoidance System, Installation Manual
none
523-0775833
CTL-92T TCAS Control
34-40-84
523-0776595
RTU-870A/870T Radio Tuning Unit, Component Maintenance Manual
23-80-80
523-0774068
CTL-X2/X2A Controls, Instruction Book (Repair Manual)
23-80-10
523-0772495
Collins TDR-94 Mode S Transponder, Pilot’s Guide
none
523-0776370
5/5/1993
1-11
general information 523-0775653
1.5 STORAGE The TDR-94/94D should be stored in its original packing materials and shipping container. If the unit is to be stored for a long period of time, put the unit in an airtight plastic bag with sufficient desiccant to absorb moisture. At no time should the ambient temperature of the storage area fall below -55 °C (-67 °F) or rise above +85 °C (+185 °F). The relative humidity should never exceed 95 percent. If the unit is stored for an extended period of time, retest the unit prior to returning it to service to ensure that possible component degradation has not affected performance.
5/5/1993
1.6 RELATED RELATED SERVICE SERVICE BULLETINS AND SERVICE SERVICE INFORMATION INFORMATION LETTERS Table 1-6 is a listing of the Service Bulletins and Service Informtion Letters issued and applicable to the TDR-94/94D Mode S Transponder as of the date of this manual. You will notice that many of these have direct application to unit performance in the airplane. It may be helpful to review this listing whenever there is a failure report to determine whether a particular modification may have application to the reported symptom. This implies, of course, that you must determine the modification status of the unit in question.
1-12
general information 523-0775653
Table 1-6. Related Service Bulletins. SERVICE BULLETIN NUMBER, TITLE AND DESCRIPTION
PUBLICATION DATE
SB 1: Convert TDR-94’s and TDR-94D’s to -002 status (Converts -001 to -002 status). The modifications in this service bulletin upgrade the TCAS interface performance. This service bulletin adds altitude input via the control bus and improves the burst control interface.
Rev 1: May 23, 1991
SB 2: Improve Burst Tuning Interface, Self-Test Performance, and EMI Compatibility. Installation of this service bulletin protects transmitter power output transistor during self-test, corrects burst tuning cross-side standby operation, and improves EMI compatibility.
Jan 18, 1991
SB 3: Prevent Corruption of Mode A/C Replies. ATC may report loss of reply or incorrect reply code. Several minutes to several hours may elapse before this malfunction occurs. Once precipitated, the condition will persist until primary power is cycled.
Jan 18, 1991
SB 4: Prevent Occasional Loss of Transponder Function. Reception of certain combinations of transponder interrogations can cause the TDR-94 and TDR-94D not to reply to subsequent interrogations. Once this occurs power must be cycled to restart transponder operation.
Mar 5, 1991
SB 5: A7U301 or A7U304 Replacement. In some units, when A7U301 or A7U304 are replaced, one or both channels may fail the DPSK related test. This service bulletin should be installed when replacing IC A7U301 or A7U304.
Rev 1: Jun 10, 1993
SB 6: Convert TDR-94’s and TDR-94D’s to -003 Status (Converts -002 status to -003 status). Installation of this service bulletin updates the TDR-94/94D to include changes to the Mode S transponder requirements by RTCA. Installation configuration options are expanded and enhancements to its diagnostic and maintenance performance is implemented.
Rev 2: Sep 22, 1992
SB 7: A6U105 or A6U120 PROM Replacement. If A6U105, on the -002/102 Video Processor Card or A6U120 on the -003/103 Video Processor Card, requires replacement, the new PROM may exhibit different parameters which affect the performance of the transponder. If this service is not installed when changing A6U105 or A6U120, the transponder may not reply to interrogations. This service bulletin compensates for the parameter changes.
Rev 1: Sep 17, 1992
SB 8: Replacement of A7U500 or A7U502. The current IC U500 (circuit card assembly A7, N 687-0727-002/102) or U502 (circuit card assembly A7, N 687-0727-001/101) has exhibited some cold start problems. The new U500 or U502 performs better over temperature but requires some changes to accommodate the new IC. This service bulletin should be installed only if U500 or U502 requires replacement.
Rev 1: Sep 22, 1992
SB 9: Prevent Possible Intermittent Operation. A rare combination of events can cause the TDR94/94D to be intermittent. If a specific memory location is corrupted and the unit tries to report a diagnostic, intermittent operation can occur.
Rev 3: Apr 22, 1993
SB 10: Improve Operation of Remote Ident Input. In aircraft which utilize the remote ident input (P1-16), the active transponder may squawk ident if power is removed from the inactive transponder.
Oct 2, 1992
SB 11: Improve Power-On Initialization. To ensure that the TDR-94/94D powers up in less than two seconds and initializes the air/ground Mode S status to the correct reporting position.
Feb 5, 1993
SB 12: Add Diode Isolation to Strap Inputs. In aircraft which parallel the CSDB and ARINC 429 Control select and Burst Enable inputs to other systems, removal of transponder power may cause unrequested activation of the function in another system.
Aug 2, 1993
SB A: Same as SB 3.
Dec 11, 1990
SB B: Improve Start-Up Compatibility With The Gulfstream G-IV Gables 6969 TCAS Control Adapter. Installations utilizing the Gables 6969 TCAS control adapter may power up in the standby mode regardless of the mode the system was powered down in.
Sep 29, 1992
SIL A-90: Connector Plate Inspection (N 629-8657-001/002. Some connector plates used with the TDR-94/94D mounting rack may exhibit one or more discrepancies. This connector plate is available individually and is included as part of connector kits, N 628-8660-001/002 and N 628-8661001/002. All connector plates "REV A" through "REV C" that do not have "A-90" marked on them should be inspected and adjusted if found discrepant. Connector plates "REV D" or later are inspected during manufacture.
Oct 22, 1990
5/5/1993
1-13
523-0775655-103118 3rd Edition, 29 April 1991 1st Revision, 15 June 1995
TDR-94/94D ATC/Mode S Transponder System Operation
Table of Contents
Paragraph
Page
3.1 3.1.1 3.1.2
TDR-94/94D TRANSPONDER OPERATING INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-1 Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-1 CTL-92/92A Control, Controls and Indicators . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-1
3.2 3.2.1 3.2.2 3.2.3 3.2.4 3.2.5 3.2.6 3.2.6.1
OPERATING INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . Operating Instructions for Installations Using a CTL-92/92A Control Equipment Turn On . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Code Selection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Code Storage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Normal Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Self-Test . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CTL-92/92A ATC Control, Diagnostic Codes . . . . . . . . . . . . . . . . . . .
. . . . . . . .
. . . . . . . .
. . . . . . . .
. . . . . . . .
. . . . . . . .
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. . . . . . . .
. . . . . . . .
. . . . . . . .
. . . . . . . .
NOTICE: This section replaces third edition dated 29 April 1991. Only the Title Page has changed in this revision.
. . . . . . . .
. . . . . . . .
. . . . . . . .
. . . . . . . .
. . . . . . . .
3-1 3-1 3-1 3-1 3-2 3-2 3-3 3-5
List of Effective Pages Page
*The asterisk indicates pages changed, added, or deleted by the current change.
Issue
*Title . . . . . . . . . . . . . . *List of Effective pages 3-1 thru 3-4 . . . . . . . . . 3-5 . . . . . . . . . . . . . . . 3-6 Blank . . . . . . . . . .
. . . . .
. . . . .
. . . . .
. . . . .
. . . . .
15 Jun 15 Jun . 4 Apr 29 Apr . 4 Apr
95 95 90 91 89
Record of Revisions INSERTION DATE / BY
RETAIN THIS RECORD IN THE FRONT OF THE MANUAL. ON RECEIPT OF REVISIONS, INSERT REVISED PAGES IN THE MANUAL, AND ENTER DATE INSERTED AND INITIALS.
REV / ED NO
REVISION DATE
SB NUMBER INCLUDED
0/1
4 Apr 89
None
0/2
4 Apr 90
None
0/3
29 Apr 91
None
1/3
15 Jun 95
See Table 1-6
REV / ED NO
REVISION DATE
INSERTION DATE/BY
SB NUMBER INCLUDED
,,
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523-0775656-102118 2nd Edition, 4 April 1990 1st Revision, 15 June 1995
TDR-94/94D ATC/Mode S Transponder System Theory of Operation
Table of Contents
Paragraph
Page
4.1 TDR-94/94D Transponder System theory of Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-1 4.1.1 General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-1 4.1.2 Physical Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-1 4.2
Purpose of Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-2
4.3 4.3.1 4.3.2 4.3.3 4.3.4 4.3.5
Background . . . . . . . . . . . . . . . Introduction . . . . . . . . . . . . . . . . Radar Systems . . . . . . . . . . . . . . ATCRBS Interrogation Modes . . SSR Radiation Patterns and SLS ATC Transponder 4096 Replies .
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4.4 4.4.1 4.4.2 4.4.3 4.4.4
ATCRBS and Mode S . . . . . . . . . . . . . Introduction . . . . . . . . . . . . . . . . . . . . . . Mode S Interrogation Modes . . . . . . . . . Mode S SSR Radiation Pattern and SLS Mode S Transponder Replies . . . . . . . . .
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4.5 4.5.1 4.5.2 4.5.3 4.5.4
TDR-94/94D Theory of Operation . . . . . . . . . Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . Installation Strapping Options . . . . . . . . . . . . . . Typical Configurations . . . . . . . . . . . . . . . . . . . . TDR-94/94D Block Diagram Theory of Operation
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4-18 4-18 4-18 4-19 4-23
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NOTICE: This section replaces second edition dated 4 April 1990. Only the Title Page has changed in this revision.
4-2 4-2 4-2 4-5 4-5 4-5
List of Effective Pages Page
*The asterisk indicates pages changed, added, or deleted by the current change.
Issue
*Title . . . . . . . . . . . . . List of Effective pages 4-1 . . . . . . . . . . . . . . . 4-2 thru 4-4 . . . . . . . . 4-5 . . . . . . . . . . . . . . 4-6 thru 4-7 . . . . . . . . 4-9 . . . . . . . . . . . . . . . 4-10 thur 4-18 . . . . . . 4-19 thru 4-24 . . . . . .
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15 Jun 4 Apr 4 Apr 4 Apr 4 Apr 4 Apr 4 Apr 4 Apr 4 Apr
95 90 90 90 89 90 89 90 90
Record of Revisions INSERTION DATE/BY
RETAIN THIS RECORD IN THE FRONT OF THE MANUAL. ON RECEIPT OF REVISIONS, INSERT REVISED PAGES IN THE MANUAL, AND ENTER DATE INSERTED AND INITIALS.
REV / ED NO
REVISION DATE
SB NUMBER INCLUDED
0/1
4 Apr 89
None
0/2
4 Apr 90
None
1/2
15 Jun 95
See Table 1-6
REV / ED NO
REVISION DATE
INSERTION DATE/BY
SB NUMBER INCLUDED
section
IV
theory of operation 4.1 TDR-94/94D TRANSPONDER SYSTEM THEORY OF OPERATION 4.1.1 General The TDR-94/94D Mode S Transponder is a solid-state, airborne, air traffic control (ATC) transponder that responds to ATCRBS (air traffic control radar beacon system) mode A and mode C interrogations and mode select (mode S) interrogations. The mode S transponder differs from earlier ATCRBS transponders in operation in that it is capable of discrete addressing. That is, in mode S each transponder acquires a unique identity and responds when interrogated according to that identity. In addition, mode S includes the capability of sending and receiving
data link messages. Diversity-equipped mode S transponders are also capable of receiving and transmitting on two antennas. These are usually mounted one on top and the other on the bottom of the fuselage. This provides for more reliable air-to-air surveillance and communications. 4.1.2 Physical Description Figure 4-1 is a view of the TDR-94/94D Mode S Transponder. The unit dimensions are 5 inches wide, by 3 ¾ inches high, by 14 inches long. It weighs about 7.5 pounds. All electrical connectors are at the rear of the unit. These include two 60-pin Thinline connectors and either one (for TDR-94) or two (for TDR-94D) antenna connectors. The unit is normally mounted in a MMT-150 Modular Mounting Tray.
CTL-92/92A Control, Controls and Indicators Figure 3-1
Revised 4 April 1990
4-1
operation 523-0775656 4.2 PURPOSE OF EQUIPMENT The TDR-94/94D transponder is the airborne transponder for the ATCRBS. The TDR-94/94D provides mode A, mode C, and special identification replies to ATCRBS interrogators for tracking, identification, and altitude reporting. In addition, the TDR94/94D is capable of receiving and sending mode S messages that will be required by TCAS II and TCAS III (Traffic Alert and Collision Avoidance System), It also includes the data link capability necessary for aircraft separation assurance (ASA) function.
consisting mainly of a large rotating radar antenna that can be seen at or near most air terminals. This system uses conventional radar to locate all aircraft within its range in of range and azimuth. It transmits a burst of energy and then measures the time to an echo.* The direction in which the antenna is pointing at the time the echo is detected establishes the azimuth to the reflecting target. This target information is displayed on the air traffic controller’s PPI (plan position indicator) (see figure 4-3).
4.3 BACKGROUND 4.3.1 Introduction The air traffic control radar beacon system (ZTCRBS) is a surveillance system in wide use that locates and identifies aircraft within an airspace. However, because of increasing air traffic, this system is being expanded to include additional facilities for airborne collision avoidance. To gain a good understanding of mode S transponder operation, it is necessary to understand the operation of the existing air traffic control (ATC) system. If this is your first with the ATCRBS and related equipment, this paragraph will give you an overall description of the present ATCRBS and then expand that understanding into the new mode S operation. 4.3.2 Radar Systems Refer to figure 4-2. The ATCRBS consists of a primary surveillance radar (PSR) and a secondary surveillance radar (SSR). The PSR can be visualized as
4.3.3 ATCRBS Interrogation Modes
The SSR system interrogates the aircraft transponder for aircraft identity and altitude. The interrogations are in the form of either of two modes: mode A for aircraft identity and mode C, which is used to request altitude information.**
All pulses are 0.8 us wide. The interrogations from the ground station are at a frequency of 1030 MHz. The transponder replies at a frequency of 1090 MHz. The signal received from the airborne transponder is decoded by the round system so that it can be displayed on the ATC radar screen (see figure 4-3). The replies produce either a single or double slash target display on the controller screen. The controller can also elect to display the aircraft identification number (as selected by the aircrew) and the aircraft altitude.
*The time is easily converted into range. The propagation velocity of radio energy is known. The mathematical formula for distance is: D = velocity x (multiplied by) time. However, radio propagation velocity is usually expressed as 12.359 us per radar mile. Notice that this is the inverse of what is necessary for the distance formula, which must have velocity expressed as a measure of distance per unit of time (eg, miles per hour). Therefore, the distance formula must be modified slightly: D = time / (divided by) propagation velocity. **In the original definition of ATC modes, two other modes were defined: mode B and mode D. These also differ only in of pulse spacing, with mode B pulses spaced 17 us and mode D pulses spaced 25 us. For a time, mode D was widely used in Great Britain, but in recent years most of the aviation industry has settled on mode A for ATCRBS operation and mode C for altitude reporting, and modes B and D have been largely abandoned. In US military applications, a system similar to ATCRBS is used; it is known as IFF (identification friend or foe). As this name implies, it has to do with mission security. Three modes are defined: modes 1, 2, and 3. Mode 3 is common to the civil mod A, with a pulse spacing of 8 us. This allows air traffic control visibility of all aircraft, both civil and military. 4 April 1989
4-2
operation 523-0775656
ATC, PSR and SSR System Figure 4-2
4 April 1989
4-3
operation 523-0775656
Air Traffic Presentation on the ATC Radarscope Figure 4-3
4 April 1989
4-4
operation 523-0775656 4.3.4 SSR Radiation Patterns and SLS Refer to figures 4-4 and 4-5. The SSR uses a rotating directional antenna to transmit two pulses, which are identified as P1 and P3. The spacing of these pulses determines the mode. In mode a the pulses are spaced 8 us, while in mode C the pulses are spaced 21 us. The SSR also uses an omnidirectional antenna to transmit a third pulse, designated P2. This pulse is transmitted 2 us after the P1 pulse and provides a reference for side-lobe suppression (sls). The amplitude of the P2 pulse is about the same as the peak sidelobe of the directional antenna. Typically, this is about 18 dB below the peak of the directional (main) beam. Refer to figure 4-4. Notice the two aircraft on the drawing. Aircraft A is shown as being within the main lobe of the directional antenna. The amplitude of the P1 and P3 pulses will be substantially greater here than that of the P2 pulse radiated from the omnidirectional antenna. Therefore, this aircraft transponder will interpret this interrogation as valid. Aircraft B, however, is outside the main lobe and within one of the sidelobes. The P1 and P3 pulses detected here will be the result of side-lobe radiation. Recall that the P2 pulse is transmitted by an omnidirectional antenna and is about equal in amplitude to that of the peak sidelobe. Therefore, the P2 pulse detected by aircraft B will be at least as great in amplitude as the P1, P3 pulses. The transponder in aircraft B will detect this relationship in pulses and discard the interrogation as invalid, because the P2 pulse is not substantially less than the P1, P3 pulses. As a further safeguard against replies to possible late-arriving echoes to this invalid interrogation, the
Revised 4 April 1990
transponder suppresses replies to all interrogations for an additional 25 to 45 ms. In addition, the receiver is desensitized for reception of P1, P3 pulses. The rationale here is that if the sidelobes are detectable, then the main lobe must be much greater, increasing the likelihood of echo reception. 4.3.5 ATC Transponder 4096 Replies The ATCRBS transponder 4096 reply signal is shown in figure 4-6. Notice that the signal can consist of from 2 to 15 pulses (the X pulse is not used). The two framing pulses, F1 and F2, are always present and spaced 20.3 us. An identification pulse may be transmitted 4.35 us after the last framing pulse, F2. The intervening pulses, C1 through D4 on the figure, make up the coded reply. The coded reply consists of four digits ranging from 0 through 7. The digits are formed by the sum of the suffix numbers ranging from 0 through 7. The A group (A1, A2, and A4) makes up the first digit, the B group makes up the second digit, etc. (On the figure, a pulse outlined with a solid line indicates that the pulse is present. A pulse outlined with dashed lines indicates the position for that pulse when it is present.) The pulse configuration on the figure indicates a reply code of 1324. The first digit, 1, is formed y the presence of only the A1 pulse. The second digit, 3, is formed by the presence of B1 and B2 (1 + 2 = 3). A digit 7 is formed when all three pulses of the group are present (1 + 2 + 4 = 7). Therefore, a reply sequence with all pulses present constitutes a code 7777. The X pulse is not defined in ATCRBS replies. This combination of four digits, each ranging from 0 through 7, makes possible 4096 different codes, which explains the reason for calling it the 4096 code.
4-5
operation 523-0775656
ATCRBS, SSR Antenna Radiation Pattern Figure 4-3
4 April 1989
4-6
operation 523-0775656
ATCRBS, Interrogator Pulse Spacing Figure 4-5
ATCRBS and Mode S, Transponder 4096 Reply Code, Signal Format Figure 4-6
4 April 1989
4-7
operation 523-0775656 4.4 ATCRBS AND MODE S (Refer to figure 4-7) 4.4.1 Introduction Mode S substantially enhances the capability of the ATCRBS by adding data link and discrete interrogation features. The data link capability includes air-to-air information exchange, ground-to-air (data uplink or comm A), air-to-ground (data downlink or comm B), and multiple ground stations message protocol. The mode S transponder can also function as part of an airborne separation assurance (ASA) system when interfaced with a Traffic Alert and Collision Avoidance System (TCAS). 4.4.2 Mode S Interrogation Modes (Refer to figures 4-8, 4-9, and 4-10) There are eight different formats of interrogation used in mode S. These eight formats can be summarized in of three basic types. These are shown in figures 4-8 and 4-9. Figure 4-10 is a summary of all eight. This variety of interrogation capability gives the ground controller the flexibility of addressing only those aircraft of immediate interest, as opposed to processing replies from all aircraft. All eight of the interrogation modes are summarized in figure 4-10. The various fields are described in the following paragraphs. These descriptions are largely as provided in Document RTCA/DO-181, with minor changes to clarify the text. a. Address/Parity (AP) Field: The 24-bit* AP field contains the parity overlaid on the address and appears at the end of all transmissions for uplink interrogations and downlink replies, except for downlink format (DF) number 11. b. Acquisition Special (AQ) Field: The 1-bit AQ field designates uplink format (UF) numbers 0 and 16 as acquisition transmissions and is repeated as received by the transponder in DF numbers 0 and 16. *In the RTCA document, some graphic material refers to these as chips. For this description, the are regarded as synonymous.
Revised 4 April 1990
c.
Designator Identification (DI) Field: The 3-bit DI field identifies the coding contained in the special designator (SD) field in IF numbers 4, 5, 20, and 21. The codes are defined as follows: DI 0 1 2-6 7
DEFINITION Not used SD contains multisite information Not assigned SD contains extended data readout request
d. Interrogator Identification (II) Field: The 4-bit II field identifies the interrogator and appears in UF number 11 (mode S only all-call). e. Message, Comm A (MA) Field: The 56-bit MA field contains messages directed to the aircraft (UF numbers 20 and 21). This field also contains the 8-bit comm A definition subfield (ADS). ADS defines the content of the MA message field, of which it is a part. f. Message, Comm C (MC) Field: The 80-bit MC field contains one segment of a sequence of segments transmitted to the transponder in the extended length message (ELM) (112 bits) mode. The field contains an 8-bit comm C definition subfield (CDS) that defines the message to be sent to the transponder and is included in segment zero of the ELM uplink sequence. g. Message, Comm U (MU) Field: The 80-bit MU field contains information used in air-to-air message exchanges. h. Number of C-Segment (NC) Field: The 4-bit NC field provides the number of a segment transmitted in an uplink ELM message and is part of the comm C interrogation, UF number 24. i. Protocol (PC) Field: The 3-bit PC field contains the operating commands to the transponder. The code description is as follow: DI 0 1 2-3 4 5 6 7
DEFINITION No changes in transponder state Nonselective all-call lockout Not assigned Cancel B Cancel C Cancel D Not assigned
4-8
operation 523-0775656
Mode S, PSR and SSR System Figure 4-7
Revised 4 April 1990
4-9
operation 523-0775656
Mode S, All-Call and Discrete Addressing, Interrogation Format Figure 4-8
Mode S, Discrete Addressing, Pulse P6 Definition Figure 4-9
Revised 4 April 1990
4-10
operation 523-0775656
ATCRBS, SSR Antenna Radiation Pattern Figure 4-10
Revised 4 April 1990
4-11
operation 523-0775656 j.
Probability of Reply (PR) Field: The 4-bit PR field contains commands to the transponder to specify the reply probability to the mode S only all-call interrogation, IF number 11. The code description is as follows: PR 0 1 2 3 4 5-7 8 9 10 11 12 13-15
DEFINITION Reply with probability = 1 Reply with probability = 1/2 Reply with probability = ¼ Reply with probability = 1/8 Reply with probability = 1/16 No reply Disregard lockout, reply with probability = 1 Disregard lockout, reply with probability = ½ Disregard lockout, reply with probability = ¼ Disregard lockout, reply with probability = 1/8 Disregard lockout, reply with probability = 1/16 Do not reply
After receiving a mode S only all-call containing a PR code other that 0 through 8, the transponder will execute a random process and make a reply decision for this interrogation in accordance with the command probability. Random occurrence of replies enables the interrogator to acquire closely spaced aircraft that might otherwise synchronously garble the transponder replies.
Revised 4 April 1990
k. Reply Control (RC) Field: The 2-bit RC field designates the transmitted segment as initial (0), intermediate (1), or final (3). An RC field (3) is used to request a comm d downlink by the transponder. RC is part of the comm C interrogation, UF number 24. l.
Reply Length (RL) Field: The 1-bit RL field commands a reply (DFO) if the bit is 0 and a reply in DF number 16 if the bit is 1.
m. Reply Request (RR) Field: The 5-bit RR field describes the length and content of the information requested (MB - see reply field descriptions below ) by the interrogator. The code description is as follow.: RR
REPLY LENGTH
0-15 16 17 18 19-31
Short Long Long Long Long
MB CONTENT Air initiated comm B Extended capability Flight identification Not assigned
If the first bit of the RR code is logic 1, then the decimal equivalent of the last four bits designates the requested source. n. Special Designator (SD) Field: The 16-bit SD field contains control codes affecting the transponder protocol. The content is specified by the DI field. A subfield, IIS, is contained within the SD field and specifies the interrogator identifier.
4-12
operation 523-0775656 4.4.3 Mode S SSR Radiation Pattern and SLS (Refer to figure 4-11) The mode S interrogation is transmitted through a technique known as binary differential phase-shift keying (DPSK). This technique is described graphically in figure 4-9. A chip is an unmodulated interval of 0.25 us that may be preceded by a phase reversal (pr). If a chip is preceded by a pr, it represents a logic 1. If it is not preceded by a pr, it represents a logic 0. In mode S, the omnidirectional antenna transmits pulse P5 as the sls reference pulse. The P5 pulse occurs within the P6 pulse and is timed 0.4 us before the spr (sync phase reversal). Thus, if the amplitude of P5 is sufficient to blank the spr of P6, the interrogation is most likely from a sidelobe and not from the main love. In this case, the spr is hidden from the transponder, so the reply is suppressed. The SSR mode S interrogation pulse spacing and identification is different from that of the earlier ATCRBS. Figures 4-8, 4-9, and 4-10 show these configurations. Notice that the rotating beam transmits two different pulse combination. For all-call interrogations, the transmitted pulses are P1, P3 , and P4. In these interrogations the sls reference pulse, P2, is transmitted by the omnidirectional antenna as in conventional ATCRBS. The P1-to-P3 pulse spacing is either 8 µs (for mode A) or 21 µs (for mode C), also as in ATCRBS. The P4 pulse follows the P3 pulse by 2 µs and can be either 0.8 µs (the same as P1 and P3) or 1.6 µs. The pulse width of P4 determines the all-call objective as follow (all times are in microseconds): P1-P2
PULSE SPACING P1-P3 P3-P4
P4
2±0.15 2±0.15 2±0.15
8±0.2 21±0.2 8±0.2
2 ±0.05
None None Long
2±0.15
21±0.2
2 ±0.05
Long
2±0.15
8±0.2
2 ±0.05
Short
2±0.15
21±0.2
2 ±0.05
Short
INTERROGATION TYPE
ATCRBS Mode A ATCRBS Mode C ATCRBS Mode A/Mode S all-call ATCRBS Mode C/Mode S all-call ATCRBS Mode A-only all-call ATCRBS Mode C-only all-call
Where P4 long pulse width is 1.6 ±0.1 µs and P4 short pulse width is 0.8 ±0.1 µs.
A 0.8-µs pulse is only for non-mode S transponders, while the 1.6-µs pulse is for both ATCRBS and mode S transponders.
Revised 4 April 1990
The mode S discrete addressing interrogation takes yet another form. For this interrogation, the rotating beam antenna transmits pulses P1, P2, and P6. P6 is in reality a series of either 56 or 112 bits identified as chips that define the data. At 1.25 µs after the start of P6, the spr occurs. This spr must be detected in order to enable a reply response. The final chip is followed by a 0.5-µs guard interval. This prevents the trailing edge of P6 from interfering with the demodulation process. The P2 pulse follows the P1 pulse by 2 µs. P6 begins about 1.5 µs after P2. The ground mode S interrogator system uses a monopulse processing scheme to determine the azimuth bearing to the aircraft., This scheme requires only a single reply from an airborne transponder, as opposed to the two replies necessary in the earlier ATCRBS system, to establish the azimuth to the aircraft.* The address (derived from the reply) and location (azimuth and range) of the mode S aircraft is entered into a roll-call file. This file can be visualized as a list of the mode S transponder equipped aircraft within its assigned airspace. On a later scan, the mode S aircraft is discretely addressed. This discrete address contains a command field that is used to desensitize the mode S transponder to further mode S all-call interrogations. This desensitization is called mode S lockout. The ATCRBS-only transponders are not affected by this lockout technique and mode S transponders continue to reply to ATCRBS interrogations. When a mode S transponder equipped aircraft moves from one assigned airspace into another, the first ground interrogator can communicate with the next interrogator and aircraft information to that second interrogator. This communication link can be via ground lines or radio link. If this method is used, the mode S lockout is not disabled on the affected aircraft and the second interrogator will schedule discrete roll-call interrogations for that aircraft as needed. This technique makes it possible to increase the aircraft handling capacity of the ground interrogator. *In this scheme, the monopulse system generates two separate patterns: a single (sum) pattern and a dual lobe (difference) pattern. The ratio of the energy received by the sum pattern to the energy received by the difference pattern determines the bearing of the aircraft from the antenna beam center line.
4-13
operation 523-0775656 In regions where mode S interrogators are not connected via ground or radio link, the protocol for the transponder allows it to be in mode S lockout only for those interrogators that have the aircraft on the rollcall list. This enables a second ground interrogator to acquire an aircraft into its assigned airspace using the all-call technique as previously described. 4.4.4 Mode S Transponder Replies Typically, the ground-based interrogator tracks an aircraft throughout its assigned airspace. The mode S transponder equipped aircraft responds to mode S interrogations with the ATCRBS 4096 code and the mode S reply format. During each scan, the SSR interrogations are in both mode A and mode C. The mode S transponder reply uses a technique known as pulse-position modulation (PPM). This is described graphically in figure 4-12. A pulse transmitted in the first half of the interval represents a logic 1, while a pulse transmitted in the second half represents a logic 0. The mode S reply format is described in the following paragraphs. 4.4.5 Mode S Reply Description The reply waveform is shown in figure 4-12. The reply data block is formed by PPM encoding of the reply data, as previously described. The first preamble pulse occurs 128 µs after the start of the P4 interrogation pulse or the spr. The ATCRBS reply to an ATCRBS interrogation is identical to the reply transmitted by an non-mode S transponder (see figure 4-6). All reply formats are summarized in figure 4-13. The fields are described in the following paragraphs. Address, Announced (AA) Field: The 24-bit AA field contains the aircraft address (uncoded) and is used in the all-call reply. b. Altitude Code (AC) Field: The 13-bit AC field contains the altitude code. The encoded altitude is coded as shown in figure 4-6. The M bit has been redefined for mode S; it was the X bit shown in figure 4-6. In mode S the M bit may be used in the future for encoding the altitude in metric units. Zero is transmitted in each of the 13 bits if altitude information is not available. c. Address/Parity (AP) Field: The 24-bit AP field contains the parity overlaid on the address and appears at the end of all transmissions on both uplink and downlink, except for DF number 11. d. Capability, Transponder (CA) Field: The 3-bit CA field reports transponder capability. The code description is as follows:
CA 0
No communications capability (surveillance only) Comm A and comm B capability Comm A, comm B, and downlink ELM capability Comm A, comm B, uplink ELM, and downlink ELM capability Not assigned
1 2 3 4-7
If the transponder CA code is 1, 2, or 3, the data link capability report is used to indicate the specific data link capabilities of the overall airborne installation. e.
Downlink Request (DR) Field: The 5-bit DR field is used to request extraction of downlink messages from the transponder by the interrogator. The code description is as follow: DESCRIPTION
DR 0 1 2-15 16-31
a.
Revised 4 April 1990
DESCRIPTION
No downlink request Request to send comm B message Not assigned Request permission to send extended length message (ELM’s) of n-segments. The code inserted into the DR field corresponds to 15 + n. Downlink ELM’s are transmitted only after authorization by the interrogator. The segments are transmitted on comm D replies. On receipt of the authorization, the transponder sends a segment every 136 Ts. After receipt of all segments, the interrogator replies with a closeout transmission to indicate that all segments have been received and allow the DR field to be reset. The closeout transmission is contained in a surveillance or comm A interrogation.
f. Flight Status (FS) Field: The 3-bit FS field reports the flight status of the aircraft. The code description is as follows: FS
ALERT
SPI
AIRBORNE/ON THE GROUND
0 1 2 3 4 5
No No Yes Yes Yes No
No No No No Yes Yes
Airborne On the ground Airborne On the ground Either Either 4-14
operation 523-0775656 g. Identification (ID) Field: The 13-bit ID field contains the 4096 identification code as selected by the pilot. h. ELM Control (KE) Field: The 1-bit KE field defines the content of the ND and MD fields in comm D replies. The transponder acknowledges receipt of a final segment with a comm D transmission with KE = 1. The MD field contains a transmission acknowledgement subfield (TAS). The information contained in the TAS subfield is continuously updated as segments are received and is cleared when a closeout occurs or a new initializing segment is received. i. Message Comm B (MF) Field: The 56-bit MD field contains the message transmitted to the interrogator. The field contains an 8-bit subfield (BDS) that defines the contents of the comm B message. j. Message Comm D (MD) Field: The 80-bit MD field contains one segment of a sequence of segments transmitted by the transponder in the ELM mode. It also may contain a summary of the received MC segments of an uplink ELM. An 8-bit subfield (DDS) defines the message to be transmitted and is included in segment 0 of the ELM downlink. k. Message Comm V (MV) Field: The 56-bit MV field contains information used in the air-toair exchanges between mode S transponders. l. Number of D-Segment (ND) Field: The 4-bit ND field provides the number of the segment transmitted in a downlink ELM and is part of the comm D reply. m. Parity/Interrogator Identity (PI) Field: The 24bit PI field contains the parity overlaid on the interrogator identity code.
Revised 4 April 1990
n. Reply Information (RI) Field: The 4-bit RI field reports the airspeed capability and type of reply to the interrogating aircraft. The code description is as follows: RI
DESCRIPTION
0-7
Indicates that downlink is the reply to an air-to-air acquisition interrogation Indicates that downlink is an acquisition reply as follows: No maximum airspeed data is available Airspeed is up to 75 knots Airspeed is between 75 and 150 knots Airspeed is between 150 and 300 knots Airspeed is between 300 and 600 knots Airspeed is between 600 and 1200 knots Airspeed is more than 1200 knots Not assigned
8-15 8 9 10 11 12 13 14 15 o.
Utility Message (UM) Field: The 6-bit UM field contains transponder status readouts. p. Vertical Status (VS) Field: The 1-bit VS field indicates that the aircraft is airborne (VS = 0) or on the ground (VS = 1). q. Free and Unassigned Coding Space Fields: Free coding space contains all logic level 0, as transmitted by the interrogator or transponder. Unassigned coding space that exists within fields is reserved for possible future use.
4-15
operation 523-0775656
Mode S, SSR Antenna Radiation Pattern Figure 4-11
Revised 4 April 1990
4-16
operation 523-0775656
Mode S, Transponder Reply Code Pulse Spacing Figure 4-12
Mode S, Transponder Reply Code Summary Figure 4-13
Revised 4 April 1990
4-17
operation 523-0775656 4.5 TDR-94/94D THEORY OF OPERATION 4.5.1 Introduction This paragraph gives you an overview of the TDR94/94D operating environment. If you are familiar with the various installation configurations and options, you can skip over this paragraph. 4.5.2 Installation Strapping Options The TDR-94 and TDR-94D ATC/Mode S Transponders offer a wide range of installation options. First you should recognize the difference between the TDR-94 and the TDR-94D; the TDR94 is for single
antenna installations, while the TDR-94D is for antenna diversity (dual antenna) installations. You are likely to find the TDR-94D in most TCAS installations because dual antennas are required in TCAS. Both transponders can accept control data in CSDB or ARINC 429 format; this is set at installation by means of special external straps. The following paragraphs and accompanying diagrams describe the various installation configurations. Figure 4-14 shows the various strapping options that must be considered for all installations. You should understand that these strapping options can apply to all installations.
TDR-94/94D ATC/Mode S Transponder Strapping Options Figure 4-14
Revised 4 April 1990
4-18
operation 523-0775656 4.5.3 Typical Configurations Figure 4-15 shows a TDR-94 installation with a CTL-92/92A CSDB transponder control unit and an encoding altimeter. This type of encoder typically supplies altitude data in Gillham code (ARINC 572)
format. The encoded data can be supplied to the CTL-92/92A or directly to the TDR-4. Installers should choose the connection that involves the shortest wire run.
TDR-94 ATC/Mode S Transponder With CTL-92/92A Transponder Control Unit and Altitude Encoder, Typical Figure 4-14
Revised 4 April 1990
4-19
operation 523-0775656 Figure 4-16 shows a similar installation except it uses a central air data computer (CADC) for altitude data. In each of these cases, external strapping is required according to the type of altitude data that is being used. An alternate Installation configuration is
possible using ARINC 429 code selection. In this case, an ARINC 429 source, such as an FMS, would be shown in place of the CTL-92/92A, with appropriate strapping as shown in figure 4-14.
TDR-94 ATC/Mode S Transponder With CTL-92/92A Transponder Control Unit and CADC Altitude Source, Typical Installation Diagram Figure 4-16
Revised 4 April 1990
4-20
operation 523-0775656 Figure 4-17 shows a TDR-94D in a TCAS installation with a CSDB control and dual antennas. If the transponder is operated with only a single antenna, a special strap is required. The diagram also shows a CADC for altitude data. This can be an encoder as shown in figure 4-15. Either way, appropriate
strapping is required. The CTL-92T is required for TCAS control and is connected between the TDR94D and CTL-92/92A. In this installation, transponder control data is entered on the CTL92/92A and the TCAS control data is added to the data word in the CTL-92T.
TDR-94D ATC/Mode S Transponder, Data Link, and TCAS Installation With CSDB Control and CADC Altitude Data Source, Typical Installation Diagram Figure 4-17
Revised 4 April 1990
4-21
operation 523-0775656 Figure 4-18 shows an installation similar to that of figure 4-17. This can be seen as a typical TCAS and
data link installation using an ARINC 429 control for code selection and transponder/TCAS control.
TDR-94D ATC/Mode S Transponder, Data Link, and TCAS Installation With ARINC 429 Transponder Control and CADC Altitude Data Source, Typical Installation Diagram Figure 4-18
Revised 4 April 1990
4-22
operation 523-0775656 4.5.4 TDR-94/94D Block Diagram Theory of Operation 4.5.4.1 Introduction The TDR-94/94D ATC/Mode S Transponder is the airborne portion of the SSR system. It is capable of operating with ATCRBS and mode S interrogators. The TDR-94D can operate with two antennas for improved air-to-air surveillance. This capability is required in TCAS installations. The TDR94/94D also provides data link message capability. 4.5.4.2 Overall Functional Block Diagram Theory of Operation (Refer to figure 4-19) The TDR-94/94D consists of seven major subassemblies numbered A1 through A7. These are described in the following paragraphs. The transponder interrogations and uplink messages are received by either one or both of the antennas. This received signal is routed through the receive signal detector in module A2 to the IF amplifier in module A7. If the transponder is a diversity (dual antenna) unit, the IF amplifier operates on both the top and bottom signals independently. The IF amplifier ensures that the interrogation is a valid signal and processses that signal into the level required by the video processor in module 6. Module A7 also contains the DPSK detector, which detects the presence of a differential phase reversal in a mode S interrogation. The video processor evaluates the video data from the IF amplifier to determine whether the interrogation is an ATCRBS or mode S interrogation. The
Revised 4 April 1990
processor also determines whether a response is appropriate. Depending on certain criteria, the processor also determines which antenna should be used for reply, top or bottom. This data is supplied to modulator A3, where the proper diode drive signals are generated. These diode drive signals control the diversity switch in module A2. The video processor also supplied the proper reply data to the modulator. The modulator controls the bracket drive signals which drive the power amplifer. The response pulse train is formed in the power amplifier. This pulse train is switched through the diversity switch and low- filter and is radiated by the appropriately selected antenna. The U and I/O module contains most of the circuits involved in the digital input and output signals. The discrete inputs include a number of strapping options, like TCAS select and control format select (CSDB or ARINC 429). The digital inputs include altitude and communications data. The digital outputs include communication, TCAS, and altitude data. A few of the discrete inputs, like TCAS select, the altitude digitizer inputs, and the mode S identification strapping inputs, enter the unit on the A6 module. The synthesizer generates the 1090-MHz CW signal that is used to drive the power amplifier. The modulator effectively switches the power amplifier on and off to create the output pulse train that becomes the reply or downlink transmission. The diversity switch directs the power amplifier output to the top or bottom antenna. The modulator controls the diversity switch in response to control signals from the video processor.
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operation 523-0775656
TDR-94/94D Mode S Transponder Overall Block Diagram Figure 4-19
Revised 4 April 1990
4-24
523-0775657-005118 5th Edition, 15 June 1995
TDR-94/94D ATC/Mode S Transponder System Maintenance
Table of Contents
Paragraph
Page
5.1 GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-1 5.2 MAINTENANCE SCHEDULE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-1 5.3 TEST EQUIPMENT AND POWER REQUIREMENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-1 5.4 TESTING AND TROUBLESHOOTING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-1 5.5 MAINTENANCE DIANOSTIC DATA TREIEVAL AND ANALYSIS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-132 5.6 NUMBER SYSTEM CONVERSION AND DATA WORD DESCRIPTIONS . . . . . . . . . . . . . . . . . . . . . . . 5-148 5.7 GILLHAM CODE DESCRIPTION WITH ENCODING AND DECODING INSTRUCTIONS . . . . . . . . . 5-155 5.8 ACCEPTANCE TEST, TEST ASSEMBLY INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-158 5.9 FLIGHTLINE TEST, TEST ASSEMBLY INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-175
NOTICE: This section replaces fourth edition dated 5 May 1993.
List of Effective Pages Page
*The asterisk indicates pages changed, added, or deleted by the current change.
Issue
*Title . . . . . . . . . . . . . . . . . . . 15 Jun 95 *List of Effective pages . . . . . 15 Jun 95 5-1 thru 5-8 . . . . . . . . . . . . . . . 5 May 93 *5-9 . . . . . . . . . . . . . . . . . . . 15 Jun 95 5-10 thru 5-36 . . . . . . . . . . . . 5 May 93 *5-37 . . . . . . . . . . . . . . . . . . 15 Jun 95 5-38 thru 5-42 . . . . . . . . . . . . . 5 May 93 *5-43 thru 5-132 . . . . . . . . . . 15 Jun 95 5-133 thru 5-152 . . . . . . . . . . . 5 May 93 *5-153 thru 5-154.1 . . . . . . . 15 Jun 95 *5-154.2 . . . . . . . . . . . . . . . . . . . Blank *5-155 thru 5-158 . . . . . . . . . 15 Jun 95 5-159 thru 5-162 . . . . . . . . . . . 5 May 93 *5-163 thru 5-169 . . . . . . . . . 15 Jun 95 5-170 thru 5-187 . . . . . . . . . . . 5 May 93 *5-188 thru 5-189 (deleted) . . . 5 May 93 *5-200 thru 5-201 (deleted) . . . 5 May 93 *5-188 thru 5-197 (page numbers15only) Jun 95
Record of Revisions INSERTION DATE/BY
RETAIN THIS RECORD IN THE FRONT OF THE MANUAL. ON RECEIPT OF REVISIONS, INSERT REVISED PAGES IN THE MANUAL, AND ENTER DATE INSERTED AND INITIALS.
REV / ED NO
REVISION DATE
SB NUMBER INCLUDED
1st Ed
4 Apr 90
None
2nd Ed
29 Apr 91
None
3rd Ed
6 Jan 92
None
4th Ed
5 May 93
See Table 1-6
5th Ed
15 Jun 95
See Table 1-6
REV / ED NO
REVISION DATE
INSERTION DATE/BY
SB NUMBER INCLUDED
V
section maintenance 5.1 GENERAL
5.2 MAINTENANCE SCHEDULE
This section provides on board maintenance procedures and limited bench checkout procedures for the TDR-94/94D ATC/Mode S Transponder. The test procedures are for use in:
Collins has no requirement for periodic maintenance of the TDR-94/94D Mode S Transponder.
a. Checking a transponder system on the bench before installation to ensure that it is functioning properly, or b. Exercising the transponder system on board the airplane through a systematic routine for fault isolation to a defective LRU. The bench procedures use a special test described in paragraph 5.9. The Flightline Fault Isolation procedures use a similar, but less complex, test which is described in paragraph 5.9. In both cases, data is provided to allow local fabrication, or purchase from a supplier such as Avionics Specialists Inc, or JcAIR.
5.3 TEST EQUIPMENT AND POWER REQUIREMENTS 5.3.1 Test Equipment Table 5-1 lists the test equipment required to perform the test procedures found in this section. Equivalent test equipment can be substituted in place of the listed items. 5.3.2 Power Requirements All power required to perform the flightline system tests and LRU fault isolation procedures is provided by the airplane in which the system is installed.
Fault isolation procedures should include a check of the airplane installation and wiring with special attention to conditions that can contribute to a failure of the transponder system.
A bench 28-V dc supply, with at least 5-A peak current output, is needed for the bench procedure.
On board airplane fault isolation most often assumes that a self-test can be performed. A system that is totally non-responsive is usually best evaluated on the bench.
Note
The TDR-94/94D performs a full self-test automatically upon unit power-up. It then performs extensive background testing to bus status and the condition of critical functions for diagnostic purposes. Use the TEST button on the control head to initiate a self-test.
5/5/1993
5.4 TESTING AND TROUBLESHOOTING
The following test procedures assume that the airplane interconnect wiring has been verified and is correct. Test procedures in table 5-2 provide an operational test of the TDR-94/94D Mode S Transponder. If any of these tests fail, or if there is reason to suspect a failure, then the Fault Isolation Procedures in Table 5-5 and can be used to help isolate a defective unit.
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Table 5-1. Test Equipment Required.
EQUIPMENT
MANUFACTURER
CHARACTERISTIC
FUNCTION
Fluke 8010A, Dvm
John Fluke Mfg. Co., Inc. Suite 113 1380 Corporate Center Curve Eagan, MN 55121-1200 (612) 452-4264
Portable, 3-1/2 digit accuracy
Measure ac and dc voltages; for use on ramp for wiring checkout and with Flightline Test or on bench for Acceptance Testing
Tektronix 455, 2235, 2236, Oscilloscope
Tektronix 5350 Keystone Court Rolling Meadows, IL 60008 (708) 259-7580
Portable, dc to 10 MHz
Measure serial logic levels; for use with Flightline Test or on bench for Acceptance Testing
ATC-601 Ramp Test Set
IFR. Inc., 4053 Navajo Lane Wichita, KS 67210 (316) 522-4981
Portable ATCRBS transponder Ramp Test Set. Capable of broadcast and direct-connection testing of normal transponder operation in modes A, C, and Mode S, as well as all defined and applicable uplink / downlink formats.
For ATCRBS and Mode S ground station simulation in flightline or bench testing procedures.
RF load
M/A-COM Omni Spectra, Inc. 21 Continental Blvd Merrimac, NH 03054-9979
50-Ω at 1090 MHz TNC or BNC with adapter
RF termination of unused antenna output (TDR-94D only). Needed on flightline only when using direction connection method.
Diversity Boot
Locally fabricated (included with ATC-601)
Rf opaque for diversity testing. Ideally, it should have an adhesive base.
To isolate antenna ports for broadcast diversity testing on the flightline.
DataTrac 400H * DataTrac 400 * DataTrac 200 **
Atlantic Instruments, Inc. P.O. Box 021466 Melbourne, FL 32902 (407) 951-2542
Portable, battery operable, *ARINC 429 bus simulation and analysis, ** ARINC 429 and CSDB bus simulation and analysis
Control head simulation and data bus analysis; for use on ramp with Flightline Test or on bench for Acceptance Testing
JcAIR 429E
JcAIR 400 Industrial Parkway Industrial Airport, KS 66031 (913) 764-2452
ARINC 429 bus simulation and analysis
Control head simulation and data bus analysis; for use on ramp with Flightline Test or on bench for Acceptance Testing
Acceptance Test, Test
Locally fabricated according to data in paragraph 5.8 at the end of this section. This paragraph also lists the various cables needed.
Bench test
To provide input/output control and unit/test equipment interface for bench testing.
Flightline Test
Locally fabricated according to data in paragraph 5.9 at the end of this section. This paragraph also lists the various cables needed.
Portable test device
To provide access to signals between control and transponder unit
5/5/1993
5-2
maintenance 523-0775657 5.4.1 Diagnostic Information The procedures in table 5-6 provide for the retrieval of diagnostic data that is stored in non-volatile memory in the TRD-94/94D transponder. This data can be helpful in diagnosing certain type of failures especially those of a more transient nature. Refer to table 5-3 for a description of the diagnostic codes and the recommended troubleshooting procedure. Table 5-4 provides additional information for proper interpretation of the diagnostic codes.
Most transponder ramp testers can be used in direct-connect or broadcast operating modes. At times both methods are useful in isolating a transponder malfunction between the antenna / antenna cables and the transponder unit. For example, if in the broadcast method the test shows a low power output or low sensitivity. Switching to the direct-connection method can effectively isolate the problem to the transmitter/receiver or the antenna system.
5.4.2 Test Equipment Installation and Power Application For Flightline Testing Using A Ramp Tester
If you use the direct connection method and you are using a test set other than the IFR ATC-601, be sure it has the proper attenuation in the RF link to prevent damage to the transponder receiver. The IFR ATC-601 has the proper attenuation built into its rf port. If another type of tester is being used, check the manual to be sure it provides adequate protection. Be sure that the injected signal level is not greater than -20 dBm.
5.4.2.1 Preliminary Instructions Refer to table 5-2 for the transponder system flightline testing and fault isolation procedures. These procedures use the test setup shown in figure 5-1 and provide for a quick initial check to determine whether or not the transponder system is functional. If this check shows that a fault exists, refer to the procedures in table 5-5 for more detailed fault isolation. A test and data bus reader are needed for these procedures. 5.4.2.2 Bus Reader Selection Any one of the four bus readers listed in table 5-1 can be used. However, of those listed only the Atlantic Instruments DataTrac 200 is capable of receiving and transmitting either the CSDB or the ARINC 429 bus format. The others are ARINC 429 only. Therefore, if the installation includes a CTL-92/92A control, only the DataTrac 200 can be used to simulate that control. 5.4.2.3 Ramp Tester Selection and Use The IFR ATC-601 was used in the development of the procedures in this manual. It is possible that other instruments, i.e., instruments provided by other manuafacturers, have comparably and acceptable features. You should feel free to use your choice of instruments. However, be sure that it is capable of testing the transponder operating items listed at the end of this paragraph.
5/5/1993
Most transponder ramp test sets allow operation inside a hanger. Be aware, however, that the glossy (and often painted) floor surfaces found in most hangers can result in substantial signal reflection. This can have an effect on power output and receiver sensitivity tests. Moving the sense antenna above or below the transponder antenna usually produces different results and demonstrates the effect of signal reflection. It is for this reason that you should try a few different sense antenna heights, distances, and airplane parking locations to gain a basis for test result interpretation and evaluation. Be guided by the antenna placement requirements of the test set manufacturer. Locate the ramp tester sense antenna at the proper distance from the airplane transponder antenna. The best distance and height may be specified by the manufacturer. Mode s diversity transponder installations may require shielding of one antenna for diversity testing. An RF opaque boot of nearly any design is acceptable for this purpose. It should fit completely over the antenna and provide good base grounding. An adhesive base may be best for easy installation and removal.
5-3
maintenance 523-0775657 The IFR ATC-601 features a special automatic test sequence that significantly reduces the time required for the test. Using the automatic sequence or an equivalent manual sequence is largely a matter of personal choice. However, if a particular test fails in the automatic sequence, it might be advisable to repeat that test manually to help in isolating the fault. Follow the test set operating procedures as provided. At least the following transponder operating items should be tested. The order is not critical.: 1. Mode A response. 2. Mode C response with altitude if available. 3. Mode S all-call response, 4. Mode S lockout. 5. Transmitter frequency. 6. Transponder power output. 7. Receiver frequency discrimination. 8. Receiver sensitivity. 9. Receiver interrogation pulse spacing discrimination (all modes). This involves altering the pulse spacing from normal and testing the transponder’s reply or lack of reply. 10. Individual pulse-width discrimination (all modes). This is the same type of test as 9. except that the pulse width is changed instead of the pulse spacing. 11. SLS (side lobe suppression). This involves changing the P2 pulse amplitude with respect to the P1/P3 pulses and testing the transponder’s response. 12. Transponder response to invalid address interrogations. 13. SPR on/off. 14. Mode S, UF0 (uplink format 0). 15. Mode S, UF4. 16. Mode S, UF5. 17. Mode S, UF11. 18. Mode S, UF16. 19. Mode S, UF20. 20. Mode S, UF21. 21. Diversity isolation (TDR-94D, operating with dual antennas only). 22. Transponder squitter. 23. Airplane identification code.
5/5/1993
5.4.2.4 Transponder System Inspection If the nature of the transponder failure report is such that it may be caused by antenna cables or antennas, inspect these for possible physical damage or deteriorated installation integrity. The condition of the transponder antenna, antenna cable(s), and cable connectors can have a significant effect on transponder operation. Therefore, an occasional visual inspection of these components is advisable. However, do not disassemble the airplane to inspect antenna cables unless you have good reason to suspect a cable or connector problem. 5.4.2.5 Transponder System Ground Test Enable Some transponder installations use a weight-onwheels transponder inhibit mechanism to prevent response to interrogations while the airplane is on the ground. It is necessary to disable this inhibit feature for testing. This is unique to each airplane therefore you must consult the airplane manual for the necessary instructions. It may also be necessary to condition the altitude data system for test purposes. 5.4.3 Flightline Test Procedures Transponder system testing procedures, for use on the flightline, are shown in table 5-2. These procedures will that the system is functional. If a failure is detected or suspected because of pilot complaint or other evidence, the fault isolation procedures in table 5-5 provide more detailed testing and LRU performance analysis.
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Table 5-2. Transponder System, Flightline Test Procedures.
TEST
1.
PROCEDURE
Setup:
DESIRED RESULT
TROUBLESHOOTING INSTRUCTIONS
Prepare the airplane and transponder system for testing as required. As a minimum this will require: • Be sure that the air/ground test inhibit, if used, is functional. P2-53 must be grounded to allow a manual self-test. • Set altimeter system(s) for a test altitude (consult airplane manual for necessary procedures) especially as may be required for TCAS if used. • Setup IFR ATC-601 Ramp Tester and perform the necessary preliminary tests for it. • If the broadcast method of testing will be used with the ATC-601 (or equivalent) ramp tester and the installation consists of a TDR-94D diversity transponder install an rf boot over the top antenna. If the direct connection is being used, disconnect both antenna cables from the transponder mount, connect the ATC-601 to the lower antenna connector and install an rf load on the upper connector. Note: If the transponder installation makes the direct connection method quite difficult, the broadcast method should be seen as preferred unless initial tests suggest an advantage in favor of direct connection.
2.0
Inspection:
Before applying power to the transponder system, make a visual inspection of the transponder antenna(s), ATC control, and the r/t. Be sure the r/t is firmly seated in its mount and there are no obvious signs of a dysfunctional installation. If it is possible, check the antenna cable connections on the back of the transponder for tightness and the wire harness for obvious signs of broken wires or dislodged connector pins.
3.0
Power application: Apply power to the transponder system. Enter an appropriate code into the control and set for normal operation.
Normal operation: In the case of the IFR ATC-601, the INTERR and REPLY indicators should both be lit.
5/5/1993
If the installation is equipped with a CTL-92/92A -2XX control, "diAG" may be displayed in the lower window if a diagnostic is detected. It is necessary, then, to press TEST to display the diagnostic code.
If the broadcast method of testing is being used with the ATC-601, avoid use of an emergency ident code (consult the airplane manual if you are unsure). If the INTERR lamp does not light, the ramp tester is not functioning properly. If the REPLY lamp does not light, the transponder is not responding. Check for possible ground operation inhibits.
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maintenance 523-0775657
Table 5-2. Transponder System, Flightline Test Procedures.
TEST
4.0
PROCEDURE
Self Test: Press the ATC TEST button on the ATC control. Note: The installation may feature a remote ATC TEST button in which case use it instead.
DESIRED RESULT
TROUBLESHOOTING INSTRUCTIONS
If the installation uses an ATC control head other than the CTL-92/92A or RTU-870A/T, you may need to consult the airplane manual to determine where the ATC self test results are displayed and in what format any diagnostics are disclosed. Test results should not show any diagnostic other than 00 (no faults detected). In the case of the CTL-92/92A , the diagnostics are displayed on the control.
See table 5-3 for an interpretation of the diagnostic code.
A normal indication on the CTL-92/92A is: • The active code display intensity modulates from minimum to maximum. • On all CTL-92/92A controls: • "AL" is displayed in the upper window and the altitude in thousands of feet in 100-foot increments is displayed in the lower window. • If a diagnostic condition is detected, the upper window shows "dIAG" and the two-digit diagnostic code is displayed in the lower window. Refer to table 5-3 for a listing of the codes, and table 5-4 for an interpretation and explanation of each. 5.0
Auto Test: Select AUTO TEST on the IFR ATC-601 and press RUN.
All AUTO TEST items should indicate ED. This test takes about 30 seconds to complete. Note: It is possible that tests 13, 14, and 15 indicate FAILED. These items are a function of datalink capabilities and may not be implemented in which case you can ignore this failure indication.
Successful completion of tests ing these items, and no other indication of failure (like pilot or ATC complaints), indicates a functional transponder.
If there is a substantial difference in receiver sensitivity and/or power output, it may be caused by a faulty antenna, antenna cable, or connector installation. In this case, inspection and repair of the antennas, cables, or cable connectors is needed.
Otherwise, a failure of any one or more of the items, may indicate a performance problem. In this case, consider removing the transponder for additional analysis and repair on the bench.
6.0
Opposite antenna test: If the direct connection method is being used, switch the test set cable to the other antenna port. If the broadcast method is being used, move the rf boot to the top (or opposite) antenna connector and repeat the test.
The test results should be approximately equivalent between the two antenna test.
7.0
Equipment removal and restoration:
Restore all equipment to its normal ground operating configuration. Return the test set to its normal storage location. Careful handling and storage of all ramp test equipment prolongs the service life and reduces maintenance costs.
5/5/1993
5-5-6
maintenance 523-0775657
Table 5-3. TDR-94/94D Diagnostic Codes
PRIMARY CODE
SECONDARY CODE
DESCRIPTION
DIAGNOSTIC DISPLAY
TI
F/W
00
No fault found
10
Power supply diagnostics
(1)
(1)
11
+5 V dc
Yes
Yes
12
+70 V dc
No
No
13
+35 V dc
No
No
14
LVPS
No
No
Transmitter/modulator diagnostics
(2)
(2)
21
Final stage, overcurrent
Yes
Yes
22
Top antenna, low power output
No
No
23
Bottom antenna low power output
No
No
24
Transmitter overtemperature
No
No
Synthesize diagnostics
No
No
31
Synthesizer lock detect
No
No
32
Synthesizer low power detect
No
No
Receiver/IF diagnostics
No
No
41
Top receiver channel
No
No
42
Bottom receiver channel
No
No
43
Top DPSK demodulator
No
No
44
Bottom DPSK demodulator
No
No
Program memory (ROM) diagnostics
Yes
Yes
51
High-byte ROM
Yes
Yes
52
Low-byte ROM
Yes
Yes
53
Both ROM chips
Yes
Yes
Volatile memory (RAM) diagnostics
Yes
Yes
High-byte RAM
Yes
Yes
20
30
40
50
60 61
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maintenance 523-0775657
PRIMARY CODE
60 (cont’d)
SECONDARY CODE
DESCRIPTION
DIAGNOSTIC DISPLAY
TI
F/W
62
Low-byte RAM
Yes
Yes
63
Both RAM chips
Yes
Yes
64
Cache RAM
Yes
Yes
65
Cache RAM and high-byte RAM
Yes
Yes
66
Cache RAM and low-byte RAM
Yes
Yes
67
Cache RAM and both RAM chips
Yes
Yes
68
Dual port RAM
Yes
Yes
70
Nonvolatile memory (NVRAM)diagnostics
No
No
80
Serial input control bus diagnostics
(4)
No
81
ARINC 429 control UART
(4)
No
82
ARINC 429 control port A inactive
(4)
No
83
ARINC 429 control port B inactive
(4)
No
84
ARINC 429 control port C inactive
(4)
No
85
CSDB control input port A inactive
(4)
No
Serial altitude input diagnostics
No
No
91
ARINC 429/575 altitude UART
No
No
92
ARINC 429/575 input port A inactive
No
No
93
ARINC 429/575 input port B inactive
No
No
94
CSDB altitude input port A inactive
No
No
95
CSDB altitude input port B inactive
No
No
ADLP communication diagnostics
No
No
A1
ADLP comm A/B UART
No
No
A2
ADLP comm A/B bus inactive
No
No
A3
ADLP comm C/D UART
No
No
A4
ADLP comm C/D bus inactive
No
No
TCAS communication diagnostics
No
No
B1
TCAS UART
No
No
B2
TCAS unit
-
-
B3
TCAS bus inactive
No
No
B4
TCAS protocol error
No
No
Squitter diagnostics
No
Yes
C1 (TDR-94D only)
Top channel squitter
No
Yes
C2 (TDR-94D only)
Bottom channel squitter
No
Yes
90
A0
B0
C0
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maintenance 523-0775657
PRIMARY CODE D0
SECONDARY CODE
DESCRIPTION
DIAGNOSTIC DISPLAY TI
F/W
Diversity diagnostic
No
Yes
Message processor diagnostics
No
No
E1 (TDR-94D only)
Top channel message processor, soft failure
No
No
E2
Bottom channel message processor, soft failure
No
No
E3
Top channel message processor, hard failure
Yes
Yes
E4
Bottom channel message processor, hard failure
Yes
Yes
Configuration diagnostics
No
No
F1
Mode S discrete address changed
No
No
F2
TCAS selection changed
No
No
F3
Altitude units selection changed
No
No
F4
Max airspeed program selects changed
No
No
F5
Port selects changed
No
No
F6
SDI selects changed
No
No
F7
Single antenna selection changed
No
No
F8
ADLP selection changed
No
No
F9-FE
(not assigned)
FF
Unacceptable mode s address selected (address lines are all 0 or all 1)
Yes
Yes
(TDR-94D only)
E0
F0
Notes: (1) (2) (3) (4) (5)
1
Except for 00, 70, and D0, primary diagnostics are not displayed. Transmitter is inhibited (TI) and failure warn (F/W1) output (P1-31) is set only if a diagnostic code 11 is detected. Transmitter is inhibited and F/W1 discrete is set only if a diagnostic code 21 is detected. Transmitter is inhibited and TDR-94/94D is set to standby only if all selected control inputs are nonfunctional. Transmitter is inhibited and TDR-94/94D is set to standby only if the control bus failure is detected on the selected control bus. Transmitter is inhibited and TDR-94/94D is set to standby only if serial control is selected and all serial inputs are nonfunctional.
"F/W set" here refers to: a. TDR-94/94D fault monitor discrete output, P1-31, set to high level, b. TDR-94/94D CSDB data word label 1F, byte-1, bit-7, set to logic 0, and c. TDR-94/94D ARINC 429 SSM and other data bits related to diagnostics set to the appropriate fault level.
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Table 5-4. TDR-94/94D Diagnostic Code Description and LRU Disposition
Diagnostic Code
Title
Description and LRU Disposition
For purposes of this diagnostic code interpretation and for the sake of brevity, the following fault levels are defined: Level 1: A level 1 fault is defined as one in which the TDR-94/94D should be removed for further testing or fault isolation on the bench. Level 2: A level 2 fault is defined as one in which the TDR-94/94D is demonstrating a failure which may not prevent it from performing continued but temporary service. That is, a diagnostic which indicates a failure in a peripheral function. For example, a diagnostic code A? indicating an ADLP fault. If an ADLP is not being used in the installation the transponder may operate normally in its other functions. Level 3: A level 3 fault is defined as one in which the TDR-94/94D has experienced a change in the installation, i.e., external to the TDR-94/94D. In this case, further analysis is needed to correct or restore the installation as needed. For example, a diagnostic code F4 indicating a change in the max airspeed strapping. This strongly suggests an airplane wiring problem. Reference to a failure warning indication should be understood to be the flag. 00
No fault found
This code indicates that no failure was detected during the most recent self test routine.
11
+5 V dc
Level 1. This diagnostic code is typically accompanied by a failure warning indication. It is caused by a out-of-tolerance condition in the +5 V dc power supply.
12
+70 V dc
Level 1. Same as 11 except that it applies to the +70 V dc supply on hvps module A1.
13
+35 V dc
Level 1. Same as 11 except that it applies to the +35 V dc supply on hvps module A1.
14
LVPS
Level 1. Same as 11 except that it applies to the low voltage power supply on module A7.
21
Transmitter/modulator, final stage, overcurrent
Level 1. This diagnostic code is typically accompanied by a failure warning indication. It is caused by a sensed high current condition in the final transmitter stage. This may be accompanied by a diagnostic code 24.
22
Top antenna low power output
Level 1 if verifiable, otherwise level 2. This diagnostic code is typically not accompanied by a failure warning indication. It is caused by a sensed low power output condition at the top antenna output final stage. This may be verifiable in the ATC-601 test. This diagnostic will not occur on a TDR-94 (non-diversity) unit.
23
Bottom antenna low power output
Same as 22 except that it applies to the bottom antenna output port.
24
Transmitter over temperature
Level 1. The same as 21 except that it is caused by a high temperature condition.
31
Synthesizer lock detect
Level 1. This diagnostic code is typically not accompanied by a failure warning condition and occurs when the synthesizer output frequency does not agree with the processor command. This condition may be verifiable in the ATC-601 test as a transmitter off frequency failure.
32
Synthesizer low power detect
Level 1. Much the same as 31 except that it applies to the synthesizer output level. A sufficiently low output may prevent the modulator, and hence the transmitter or receiver, from operating.
Top receiver channel
Level 2. This diagnostic code is typically not accompanied by a failure warning condition and occurs when the top receiver channel does not respond properly to a simulated test signal generated by the bottom channel receiver. It is possible that the bottom channel may still be functional. Neither diagnostic 41, 42 or 43 occur on a TDR-94. * See the note 1 at the end of this table
41 *
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Table 5-4. TDR-94/94D Diagnostic Code Description and LRU Disposition
Diagnostic Code 42 *
Title
Description and LRU Disposition
Bottom receiver channel
Level 2. Same as 41 except that the channel roles are reversed. See note 1 at the end of this table.
43
Top DPSK demodulator
Level 1. This diagnostic code is typically not accompanied by a failure warning condition and occurs when the top DPSK demodulator does not respond properly to a simulated mode s test signal. It is possible that the unit may still respond properly to ATCRBS (mode A and C) interrogations. * See the note at te end of this table.
44
Bottom DPSK demodulator
Level 1. Same as 43 except that it applies to the bottom channel.
51
High-byte ROM
Level 1. This diagnostic code is typically accompanied by a failure warning condition. During self-test the microprocessor executes a memory modulo 64K summation of all memory locations and compares that result against a stored check-sum value. This diagnostic indicates that the high-byte ROM failed that comparison test.
52
Low-byte ROM
Level 1. Same as 51 except that the low-byte ROM failed the test.
53
Both ROM chips
Level 1. Same as 51 except that both ROMs failed the test.
61
High-byte RAM
Level 1. This diagnostic code is typically accompanied by a failure warning condition. During self-test the microprocessor executes a read/write test on all available volatile RAM locations using AAAAH and 5555H data. This diagnostic indicates that one or more high-byte RAM device failed this test.
62
Low-byte RAM
Level 1. Same as 61 except that the low-byte RAM device failed the test.
63
Both RAM
Level 1. Same as 61 except that both RAM device failed the test.
64
Cache RAM
Level 1. Same as 61 except that the cache RAM failed the test.
65
Cache and highbyte RAM
Level 1. Same as 61 except that both the high-byte RAM (61) and cache RAM (64) failed the test.
66
Cache and low-byte RAM
Level 1. Same as 61 except that both the low-byte RAM (62) and cache RAM (64) failed the test.
67
Cache and both RAM
Level 1. Same as 61 except that both RAM (63) and cache RAM (64) failed the test.
68
Dual port RAM
Level 1. Same as 61 except that the dual port RAM failed the test.
70
NVRAM
Level 1. This diagnostic code is typically not accompanied by a failure warning condition. During power-up the microprocessor executes a read/write test on the last 16 bytes of the NVRAM to proper operation. This diagnostic indicates that the NVRAM failed that test.
81
ARINC 429 UART
Level 1. This diagnostic code is typically not accompanied by a failure warning condition. During self-test, the microprocessor forces the output from all serial control UARTs to to the input. The microprocessor verifies that the UART processes this ARINC word properly. This diagnostic indicates that the ARINC 429 UART failed this test.
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Table 5-4. TDR-94/94D Diagnostic Code Description and LRU Disposition
Diagnostic Code
Title
Description and LRU Disposition
82
ARINC 429 control port A inactive
Level 2. This diagnostic code is typically not accompanied by a failure warning condition. During normal non-burst mode operation, the microprocessor periodically monitors the selected serial ports for bus activity. During burst mode, this test is not performed because there is no way of predicting the arrival of control data. This diagnostic code indicates that ARINC 429 control port A has no bus activity for at least 1-second.
83
ARINC 429 control port B inactive
Level 2. Same as 82 except that it applies to ARINC 429 control port B.
84
ARINC 429 control port C inactive
Level 2. Same as 82 except that it applies to ARINC 429 control port C.
85
CSDB control port A inactive
Level 2. Same as 82 except that it applies to CSDB control port A. Monitor time is extended to 2-seconds.
86
CSDB control port B inactive
Level 2. Same as 85 except that it applies to CSDB control port B.
91
ARINC 429/575 altitude UART
Level 2. Same as 81 except that it applies to the ARINC 429/575 altitude UART.
92
ARINC 429/575 altitude input port A
Level 2. This diagnostic code is typically not accompanied by a failure warning condition. During normal operation, the microprocessor periodically monitors the selected altitude input ports for bus activity. This diagnostic code indicates that ARINC 429/575 altitude input port A has no bus activity for at least 2-seconds.
93
ARINC 429/575 altitude input port B
Level 2. Same as 92 except that it applies to ARINC 429/575 altitude input port B.
94
CSDB altitude input port A
Level 2. Same as 92 except that it applies to CSDB altitude input port A.
95
CSDB altitude input port B
Level 2. Same as 92 except that it applies to CSDB altitude input port B.
A1
ADLP comm A/B UART
Level 2. This diagnostic code is typically not accompanied by a failure warning condition. During power-on self-test and whenever a comm A/B bus failure is suspected, the microprocessor forces the UART output to to the input and verifies that the UART processes the data properly. This diagnostic code indicates that ADLP comm A/B UART failed the test.
A2
ADLP comm A/B input port
Level 2. This diagnostic code is typically not accompanied by a failure warning condition. The determination of a failure in this function involves a highly complicated exchange between data link transmitters and receivers involving data word check-sums and parity checks. This diagnostic code results after repeated attempts to establish a reliable communications link fail. The failure should be verifiable in the ATC-601 tests 9 through 15.
A3
ADLP comm C/D UART
Level 2. Same as A1 except that it applies to ADLP comm C/D UART.
A4
ADLP comm C/D input port
Level 2. Same as A2 except that it applies to ADLP comm C/D input port.
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Table 5-4. TDR-94/94D Diagnostic Code Description and LRU Disposition
Diagnostic Code
Title
Description and LRU Disposition
B1
TCAS UART
Level 2. This diagnostic code is typically not accompanied by a failure warning condition. Whenever a TCAS is selected and a bus failure is suspected, the microprocessor forces the UART output to to the input and verifies that the UART processes the data properly. This diagnostic code indicates that TCAS UART failed the test.
B2
TCAS unit failure
Level 3. This diagnostic code is typically not accompanied by a TDR-94D failure warning condition. This diagnostic code indicates that TCAS operation is selected and a TCAS unit failure warning has been received. The TCAS unit should be indicating a failure warning.
B3
TCAS bus inactive
Level 2. This diagnostic code is typically not accompanied by a failure warning condition. When TCAS is selected, the microprocessor periodically monitors the TCAS input port for bus activity. This diagnostic code indicates that the TCAS input port is inactive, or fails to meet certain parity, rate, and status conditions, for a time exceeding the normal update rate which varies according to the type of data to be exchanged.
TCAS protocol error
Level 2. This diagnostic code is typically not accompanied by a failure warning condition. This diagnostic code indicates that the TCAS data being received does not comply with the required protocol. * See the note 2 at the end of this table.
C1
Top channel squitter (TDR-94D only)
Level 1. This diagnostic code is typically accompanied by a failure warning condition and indicates that the top channel squitter function is not functioning properly.
C2
Bottom channel squitter
Level 1: Same as C1 except that it applies to the bottom channel.
D0
Diversity (TDR94D only)
Level 1. This diagnostic code is typically accompanied by a failure warning condition and indicates an inability to exchange data between the top and bottom channel as described for diagnostic 41 and 42 and others below.
E1
Top channel message processor
This diagnostic code without an accompanying E3 diagnostic code is typically not accompanied by a failure warning condition. During self test the bottom channel PAM is preloaded to generate an ATCRBS or mode s interrogation which is injected into the top channel for processing. If the message is not properly processed an E1 diagnostic code is recorded and the process is repeated. If the failure occurs on three consecutive attempts, an E3 diagnostic code is recorded. An E3 diagnostic code is typically accompanied by a failure warning condition. Therefore, an E1 diagnostic code without an accompanying E3 diagnostic code can be ignored unless a pattern is detected which may indicate a marginal condition.
E2
Bottom channel message processor
Same as E1 except that it applies to the bottom channel message processor.
E3
Top channel hard message processor
Level 1. See E1 above.
E4
Bottom channel hard message processor
Level 1. Same as E3 except that it applies to the bottom channel message processor.
B4 *
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Table 5-4. TDR-94/94D Diagnostic Code Description and LRU Disposition
Diagnostic Code
Title
Description and LRU Disposition
F1
Mode s discrete address changed
Level 3. This diagnostic code is typically not accompanied by a failure warning condition and indicates that one or more of the mode s address straps has changed since the previous power-up. These straps are monitored only during power-up. If the straps change during a flight leg, the condition will not be detected until the next power-up.
F2
TCAS selection changed
Level 3. Same as F1 except that it applies to the TCAS selection strap.
F3
Altitude units selection changed
Level 3. Same as F1 except that it applies to the altitude units (metric or decimal ) selection strap. (At the time of this publication, this function has not been implemented.)
F4
Max airspeed programs selects changed
Level 3. Same as F1 except that it applies to the max airspeed straps.
F5
Control port selects changed
Level 3. Same as F1 except that it applies to the control port select straps.
F6
SDI selects changed
Level 3. Same as F1 except that it applies to the SDI select straps.
F7
Single antenna select strap changed
Level 3. Same as F1 except that it applies to the single antenna select strap.
F8
ADLP selection changed
Level 3. Same as F1 except that it applies to the ADLP select strap.
FF
Unacceptable address
Level 3. This diagnostic code occurs when an unacceptable mode s address strapping is detected; e.g., all straps open or all straps shorted to ground. This can occur if the strapping plug is removed or the common line has opened.
Note 1: Several of these diagnostic codes may be seen in a diagnostic data . In most cases they can be ignored. If, however, one remains for an extended period (more than 1 or 2 seconds) during manual self-test, the unit should undergo more detailed testing. Explanation: During self-test (automatic and manual) a simulated interrogation signal is generated in one receiver (call this the sending receiver) and is injected into the opposite receiver (call this the target receiver). If the target receiver does not return a proper response, the appropriate diagnostic is recorded. Scenario: If a valid interrogation arrives in the target receiver at the same time as or slightly ahead of the test signal, it will respond to the valid interrogation and therefore fail the test evaluation. Because the test signal is automatically generated at least once per second, the probability of this scenario occurring is rather high and increases as a function of the interrogation rate. If the valid interrogation arrives at the sending or target receiver during the time this test sequence is in process, the unit will simply not respond to the interrogation. This will most likely be unnoticed. Note 2: The B4 diagnostic may be seen repeatedly in a diagnostic data . From the point of view of the transponder and if it is not accompanyed by a TCAS FAIL on the TCAS display, it can be ignored. Explanation: The B4 diagnostic can occur because of an incompatibility between the TCAS and transponder protocols as defined in the respective MOPS (Minimum Operating Performance Standards).
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maintenance 523-0775657 5.4.4 Flightline Fault Isolation Procedures This paragraph provides procedures for isolating a transponder equipment malfunction to a particular LRU. The procedures in table 5-5 require the use of a test , ramp tester, dvm, and a data bus reader/simulator.
Table 5-1 lists the various units which can be used. Other similar units may become available which also can be used provided the capabilities are similar to those listed. Refer to figure 5-1 for the test setup diagram.
Flightline Fault Isolation, Test Setup Diagram Figure 5-1
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Table 5-5. Transponder System, Flightline Fault Isolation Procedures.
TEST
1.0
PROCEDURE
Setup: If this is a continuation of table 5-2, skip to step 7.
DESIRED RESULT
TROUBLESHOOTING INSTRUCTIONS
Prepare the airplane and transponder system for testing as required. As a minimum this will require: • Be sure that the air/ground test inhibit, if used,is functional. P2-53 must be grounded to allow a manual self-test. • Set altimeter system(s) for a test altitude (consult airplane manual for necessary procedures) especially as may be required for TCAS, if used. • Setup IFR ATC-601 Ramp Test Set (or equivalent) and perform the necessary preliminary tests for it. • If the broadcast method of testing will be used with the ATC-601 Ramp Test Set, and the installation consists of a TDR-94D diversity transponder, install an rf boot over the top antenna. If the direct connection is being used, disconnect both antenna cables from the transponder mount, connect the ATC-601 to the lower antenna connector and install a load on the upper connector. Note: If the transponder installation restricts use of the direct connection method, the broadcast method should be used unless or until tests indicate the need for direct connection.
2.0
Inspection:
Before applying power to the transponder system, make a visual inspection of the transponder antenna(s), ATC control, and the r/t. Be sure the r/t is firmly seated in its mount and there are no obvious signs of loose or damaged system components. If it is possible, check the antenna cable connections on the back of the transponder for tightness and the wire harness for obvious signs of broken wires or dislodged connector pins.
3.0
Power application: Apply power to the transponder system. Enter an appropriate code into the control and set for normal operation.
At power-up, you may see diAG along with a diagnostic code number. These random indications should be ignored. You should be concerned primarily with those diagnostics that persist.
4.0
Self Test:
If the installation uses an ATC control head other than the CTL-92/92A, you may need to consult the airplane manual to determine where the ATC self test results are displayed and in what format any diagnostics are disclosed. Test results should not show any diagnostic other than 00 (no faults detected). In the case of the CTL-92/92A units, the diagnostics are displayed on the control.
4.1.a.
Self-test display on CTL92/92A: Press the ATC TEST button on the ATC control. Note: The installation may feature a remote ATC TEST button in which case use it instead. If the CTL-92/92A has a 1/2 switch (dual transponder control), set the 1/2 switch to 2 and repeat the test.
A normal indication on the CTL-92/92A is: • The active code display intensity modulates from minimum to maximum. • On any CTL-92/92A controls with N ending in other than -2XX: • If an altitude encoder is connected to the control and operating, "AL" is displayed in the upper window and the altitude in thousands of feet in 100-foot increments is displayed in the lower window. • If altitude data is not being supplied to the control, "AL" is displayed in the upper window and the lower window remains "-------". • If a diagnostic condition is detected, the upper window shows "dIAG" and the two-digit diagnostic code is displayed in the lower window. Refer to table 5-3 for a listing of the codes, and table 5-4 for an interpretation and explanation of each.
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See table 5-3 for an interpretation of the diagnostic codes and table 5-4 for disposition of LRU.
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Table 5-5. Transponder System, Flightline Fault Isolation Procedures.
TEST
PROCEDURE
DESIRED RESULT
TROUBLESHOOTING INSTRUCTIONS
4.1.b.
Self-test display on RTU870A/T: Select the ATC page and press the ATC test key.
A normal indication on the RTU-870/870A is (top to bottom): • Upper window: ON ALT • Second window: XXXXX FT • Third window: (not used) • Fourth window: TST • Lower window: (ATC code)* RTN
4.1.c.
ATC self-test display for systems using the TTC-920G, CTL-92T, or other type of ARINC 429 transponder / TCAS control. Press the TEST button on the control.
Consult the airplane manual for the location and format of transponder and TCAS self-test display, especially the display of any possible ATC diagnostics.
5.0
Setup the ATC-601 for AUTO TEST and select RUN.
All AUTO TEST items should indicate ED. This test takes about 30 seconds to complete. Note: It is possible that tests 13, 14, and 15 indicate FAILED. These items are a function of datalink capabilities and may not be implemented in which case you can ignore this failure indication.
Otherwise, a failure of any one or more of the items, may indicate a performance problem. In this case, consider removing the transponder for additional analysis and repair on the bench.
6.0
Opposite antenna test: If the direct connection method is being used, switch the test set cable to the other antenna port. If the broadcast method is being used, move the rf boot to the top (or opposite) antenna connector and repeat the test.
The test results should be approximately equivalent between the two antenna test.
If there is a substantial difference in receiver sensitivity and/or power output, it may be caused by a faulty antenna, antenna cable, or connector installation. In this case, inspection and repair of the antennas, cables, or cable connectors is needed.
Successful completion of all tests to this point verifies a functional transponder system unless there are other indications of failure (like pilot or ATC complaints). If any test(s) failed or if you need added assurance, continue with the fault isolation procedures below. These procedures will help you isolate a failure between the control(s) and the transponder unit. The steps that follow require the use of a flightline test and bus reader. This allows access to the data busses for detailed fault isolation and data analysis. The test is described in paragraph 5.9. Refer to figure 5-1 for a diagram of the setup needed for this procedure. If you choose to continue in this series, you should feel free to pick any or all of the tests as seems necessary depending on the suspected failure. The sequence of tests given is not important. For example, if the self-test test failed to produce any results, you should perform the Self-test switch test 9.2.1. to be sure that self-test is being commanded properly.
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Table 5-5. Transponder System, Flightline Fault Isolation Procedures.
TEST
PROCEDURE
7.0
LRU fault isolation:
7.1 Setup
IF POWER IS ON, TURN POWER OFF TO THE TRANSPONDER (AND TCAS SYSTEM IF USED) Remove the control from its location and install the flightline test and appropriate cable. Connect the control to the test mating connector. Set all test data bus switches to MON. Connect the compatible data bus reader RX terminals to the test OUT terminals. If your bus reader has a second RX port, connect it to the test IN terminals. Set the ATC-601 for ATCRBS REPLY TEST
8.0 Code verification
Normal operation test: Turn power on to the system, and set the control for 2150 or any ATCRBS code (avoid the emergency codes). Set for normal operation. Read the appropriate label as shown ---->.
DESIRED RESULT
TROUBLESHOOTING INSTRUCTIONS
Flightline Test installation: • If you are connecting the test between a CTL-92/92A and the airplane wiring (with no CTL-92T; i.e., a non-TCAS installation) you will need a CSDB reader/simulator like the DataTrac 200. • If you are connecting the test between the CTL-92/92A and the airplane wiring which uses a CTL-92T (i.e., a TCAS installation), you will need a CSDB reader/simulator like the DataTrac 200 to monitor/simulate the CSDB data between the CTL-92/92A and the CTL-92T, and the CSDB data from the TDR-94D. • If you are connecting the test between the Gables 816 Control, the CTL-92T Transponder/TCAS Control, TTC-920G Transponder/TCAS Control, or an RTU-870A/T Radio Tuning Unit and the airplane wiring, you will need an ARINC 429 reader/simulator. Note: Do not connect the bus reader TX port to the test OUT terminals while the control is also connected and operating, unless you set the corresponding test switch to EXT INPUT. The test IN and OUT bus terminal labeling is with reference to the control. That is, OUT is data being transmitted OUT from the control, while IN is data being received by/into the control. Placing the corresponding switch to the EXT INPUT position disconnects the source so that external data can be injected without interference. You can always connect the bus reader RX to either the IN or OUT terminals to monitor the source of that particular data (test switch in the MON position). Note that the bus reader shows the correct data. Control
Word Format/Label
CTL-92/92A CSDB/1E CTL-92T ARINC 429/031 RTU-870A/T ARINC 429/031 TTC-920G ARINC 429/031 X = any octal character
Bus Reader ATC-601 RX 1 (Note 1) CODE= 2150 (Note 1) CODE= 2150 (Note 1) CODE= 2150 (Note 1) CODE= 2150
Bus Reader RX 2 (Note 2) (Note 2) (Note 2) (Note 2)
Note 1: This is the data being transmitted by the control. ( , the CTL-92/92A input/output is CSDB data. In all other controls the data is ARINC 429.) CSDB (CTL-92/92A): DataTrac 200: ARINC 429: DataTrac (all): JcAIR 429E:
LBL 7-STAT-0 1E 00011111
HEX-XMT-DATA 21 50 24 10
MSEC 0100
LBL SI 29-HEX-XMT-11 SM P MSEC 031 01 21 50 XX XX 00 1 0100 031 01 142211 00
Note 2: This is data being returned by the transponder. CSDB : DataTrac 200:
LBL 7-STAT-0 1F 00011111
HEX-RCV-DATA 21 50 24 11
ARINC 429: DataTrac (all): LBL SI 29-HEX-RCV-11 031 01 21 50 XX X JcAIR 429E:
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MSEC 0100
SM P MSEC 11 1 0100
031 01 142211 11
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Table 5-5. Transponder System, Flightline Fault Isolation Procedures.
TEST
8.1 Ident
PROCEDURE
ATC code test: Press IDENT on the control head or on the test .
DESIRED RESULT
TROUBLESHOOTING INSTRUCTIONS
A normally operating transponder should transmit the IDENT code for about 18 seconds (18 ± 1 s) and then stop. During that time the ATC-601 shows CODE=ID2150; the CODE preceded by "ID". If the CODE being displayed on the ATC-601 is not the same as the code you entered on the control head recheck your setup to be certain of the code that you are supplying. The code being supplied and displayed is entirely a software function and therefore is highly unlikely of failure.
Note: When the TDR-94/94D first begins transmitting the IDENT code, the ATC-601 displays: CODE=ID2150. After about 18 seconds (18 ± 1) the ID portion disappears but the code number remains. If IDENT was last commanded by way of a digital word it is necessary to transmit a new digital word with the IDENT bit reset (bit 13 = 0) before IDENT can be commanded again either by way of the digital word or by a discrete command. If you use the IDENT button on the control head, the unit will be automatically reset. 9.0
Altitude Test: Altitude information can be supplied to the transponder in a number of formats: a. ARINC 429, b. ARINC 575, c. CSDB, or d. ARINC 572 (Gillham code); paragraph 5.7 provides encoding and decoding information for Gillham code. In a TCAS installation and if the altitude source is a system using the Gillham code, two sources of altitude data are required. One source is connected directly to the transponder while the other is connected to the CTL-92/92A control. In the control the Gillham data is converted to CSDB and supplied to the CTL-92T where it is converted to ARINC 429 and supplied to the transponder. In the transponder the two sources are compared. If they do not agree within 500-ft, the transponder will set the altitude word SSM output to NCD (No Computed Data). If the altitude system is one of the first three listed, the data is supplied directly to the transponder. One or two altitude sources may be used. In either case they are connected directly to the transponder. In non-TCAS installations using a CTL-92/92A control, i.e., no CTL-92T, typically the altitude data is supplied directly to the transponder. It is possible, however, that the Gillham code can also be supplied to the CTL-92/92A. In this case it is supplied to the transponder as CSDB altitude data.
10.0
Power Test: Connect the dvm to the appropriate power terminals on the test .
11.0
Self-test switch verification: Self-test can be initiated in the transponder with either of two inputs; discrete or digital. In most installations the discrete input to the transponder is not used. In step 4.0 above, self-test was initiated digitally. Therefore, if step 4.0 was successful, there is very little to be gained by performing this step. If it failed, however, step 11.1 below provides instructions for verification of the self-test switch by monitoring the control internal switching function. If the control does not have a discrete self-test input/output, or if it does not have a self-test switch, step 11.1 cannot be performed.
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The TTC-920G uses 115 V ac , 400 Hz, power, all others use +28 V dc. Allow ± 10% for 115 Vac or ± 15% for 28 V dc.
If the power is not correct, repair airplane wiring or power source as needed.
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Table 5-5. Transponder System, Flightline Fault Isolation Procedures.
TEST
11.0 (cont ’d)
PROCEDURE
DESIRED RESULT
TROUBLESHOOTING INSTRUCTIONS
Step 11.2 is using the bus simulator to monitor the digital output from the control and then to generate a digital self-test command. If step 4.0 above failed, you can perform step 11.2. If the control output is not correct (i.e., the test bits do not change) the probable cause of failure is in the control. If the transponder still does not respond correctly when a simulated self-test word is injected, the failure appears to be in the transponder. Step 11.2 also provides instructions to monitor the from the transponder to the control. In the case of CSDB data, the word label is 1F. In ARINC 429 the word label is the same as the control word label; 031. When the transponder is replying to interrogations, the SSM is set to 11. Otherwise it is the same as the control word.
11.1
Self-test switch test. Connect the dvm to the TEST terminal on the test [ref to COMM or 28V (-)]. Press TEST on the control (or remote switch if used - not the switch on the test .)
Dvm shows +5 Vdc (± 1) when no TEST switch (either on the control, test , or elsewhere), is pressed. Dvm shows less than +3 V dc when any TEST switch is pressed.
11.2
Control output test: With the bus reader RCV connected to the test OUT terminals and the corresponding switch set to MON, you should see the test bits change when you press the TEST switch. Self-test using bus simulator: If there is no response, connect the bus reader XMT to the OUT terminals on the test . Set the corresponding test switch to EXT INPUT and set the bus reader as shown --->.
CSDB (CTL-92/92A): DataTrac 200: ARINC 429: DataTrac (all) *
JcAIR 429E: (TX)
If +5 V dc voltage is not correct, or is correct but does not change when the switch is pressed, the fault appears to be in the control and it should be removed for further testing on the bench.
LBL 7-STAT-0 HEX-XMT-DATA 1E 10000101 21 50 24 10 |<---test bit LBL SI 29-HEX-XMT-11 031 01 21 50 XX X1
MSEC 0100
SM P MSEC 01 1 0100 ||<--test command
031 01 142211 01 ||<--test command
* Recognize that the column headers are slightly different between the DataTrac 200 and the DataTrac 400/400H.
In the first part of this test, the control output should be as shown above. In the second part of this test, the transponder should respond to the simulated self-test command. Be sure to set the data back to normal (non-test) after the self-test sequence. As a further verfication of inter-unit communication, you can connect the bus reader RCV to the test IN terminals and set the corresponding switch to MON. This will allow you to monitor the data from the transponder to the control. You should see the test bits change when you press the test switch when the self-test command is transmitted. If so, this verifies that the transponder is receiving the command properly. It is highly unlikely, however, that the transponder can provide a proper without properly executing a self-test command.
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Table 5-5. Transponder System, Flightline Fault Isolation Procedures.
TEST
PROCEDURE
DESIRED RESULT
TROUBLESHOOTING INSTRUCTIONS
Note: The remainder of this procedure consists of explanatory information that may be useful for troubleshooting. The test test points labeling reflects the signal or voltage that is found at that point. In most cases, that signal or voltage depends on certain installation options. Therefore, you will need to consult the airplane manual to determine which of those options are active or inactive in your installation. Then use the following procedures to the correctness of the installation. The procedures are separated according to the control present in the installation. CTL92 /92A discretes and etc
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Use a multimeter at the following test test points, connect the reference lead to COMM (P1-s): • DUAL select (P1-m) (-2XX controls only):
Selected = ground Not selected = near +5-V dc (pull-up resistor to +5 V dc internal).
When this pin is grounded the no. 2 CSDB input port is defined as the no. 2 TDR port.
• REMOTE select (P1-K)
Selected = ground Not selected = near +5-V dc (pull-up resistor to +5-V dc internal).
This pin is typically connected to a remote switch labeled REMOTE (or similar). When grounded the CTL-92/92A: • controls are inoperative, • display shows RMT, and • code is determined by the remote tuning device.
• XPDR STBY No. 1 and No. 2 (P1-W and P1-X) (applies only to CTL-92/92A units with 1/2 switch)
P1-W is at ground when 1/2 switch on CTL is in the No. 2 position. Near + 5-V dc when 1/2 switch is in the No.1 position. P1-X is always opposite of P1W.
These pins may be used to operate a relay which controls power to either or both transponders. In this case, the high voltage may be near +28-V.
• XPDR ON/OFF, No. 1 and No.2 (P1-B and P1-C).
These two pins are identical and at ground when the CTL function switch is at OFF and open otherwise.
These pins are typically connected to the XPDR ON/OFF; no. 1 to the no. 1 transponder, and no. 2 to no.2, in dual installations.
• SW 28 V DC OUT, No. 1 and No. 2 (P1-k and P1-j).
These two pins provide switch +28 V dc output through the control. The outputs are identical and high in all CTL control switch positions other than OFF.
These outputs may be used to switch power to the transponders through an external relay.
• DATA BUS SHIELDS (P1D, P1-L, P1-P, P1-T, and P1V)
Pin P1-D is typically connected to chassis ground. The other are connected to an associated data bus shield. All of these pins are internally connected (within the CTL) to 28-V dc common.
It is important that these pins are properly isolated from either of the two associated data bus lines.
• TEST (P1-E) and IDENT (P1-b)
Both of these pins should reflect a TTL high (near + 5-V dc) when none of the associated switches are depressed and a short to ground when the switch is depressed.
In both cases, the function is activated at the low level. A constant ground (even when the switch is not pressed) should be seen as a failure and will disallow the function.
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Table 5-5. Transponder System, Flightline Fault Isolation Procedures.
TEST
CTL92T discretes and etc
PROCEDURE
DESIRED RESULT
TROUBLESHOOTING INSTRUCTIONS
Use a multimeter at the following test test points, connect the reference lead to COMM (P1/2-32). Strapping Options 1 through 6.
• No. 1 (P1-53):
The airplane manual should reveal those strapping options selected. In all cases, the selected strap should show a short-to-ground while those not selected (open strap) should show a TTL high (near +5-V dc). open = All traffic display, grounded = RA/TA only display selected.
• No. 2: (P1-49) Range select strap:
5/5/1993
• On units with pushbuttons and N ending in 0XX:
• Open = 5/10/20 nmi ranges enabled • Ground = 6/12 nmi ranges enabled
• On units with pushbuttons and N ending in 1XX:
• Open = 40/20/10/5/3 ranges enabled • Ground = 6/12 nmi ranges enabled
• On units without pushbuttons and N ending in 0XX:
• Open = 20 nmi range selected • Ground = 12 nmi range selected
• On units without pushbuttons and N ending in 1XX:
• Open = 5 nmi range selected • Ground = 12 nmi range selected
• No. 3: (P1-52) Relative / Absolute intruder altitude display select:
• Open = intruder altitude displayed as relative to own • Ground = intruder altitude displayed as absolute
• No. 4: (P1-51)
Not used
• No. 5 (P1-47) Serial / Parallel Transponder Control Select
• Open = Serial control selected (CTL-92/92A or ARINC 429) • Ground = Parallel control selected (CTL-90)
• No. 6: P1-24)
Not used
Control Functions:
The airplane manual should reveal the control functions which are active in your installation. Most control functions are intended for use with a parallel ATC control head like the CTL-90.
• ATC SEL IN, No. 1 (P1-19) and No. 2 (P1-18)
P1-18 open open gnd gnd
P1-19 open gnd gnd open
ATC Active or Standby No. 1 & No. 2 in standby No. 1 is active No. 1 is active No. 2 is active
• SW 28 V DC OUT No. 1 (P1-25)
Operable only on units with OFF control switch position. Provides switched +28 V dc output when switch is other than OFF; 1.5 A max, open in OFF position.
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Table 5-5. Transponder System, Flightline Fault Isolation Procedures.
TEST
CTL92T discretes and etc (cont ’d)
PROCEDURE
DESIRED RESULT
TROUBLESHOOTING INSTRUCTIONS
Control Functions (cont’d): • Reply Lamp Hi (P1-33) and Lo (P1-41)
Provides a constant +5 V dc high and switched low output to drive the CTL-90 reply lamp. The lamp lights while the transponder is replying to interrogations.
• ALT REP (Altitude Reporting) (P1-20)
Provides a switched low output to drive the CTL-90 altitude reporting indicator.
• GRAY CODE TUNING (From CTL-90)
These 12 lines are the Gray code tuning lines from the CTL-90. These parallel inputs are translated into ARINC 429 and become the label 031 tuning control output to the transponder (ARINC TO XPDR), P1-5/4 and P1-6/7.
SERIAL DATA INPUT/OUTPUT: • When used with the CTL-92/92A ATC Control
In this application, the inter-unit communication formats are: To CTL-92/92A CSDB
• When used with the CTL-90 ATC Control
From CTL-92/92A To XPDR(s) CSDB ARINC 429
From XPDR(s) ARINC 429
In this application, the inter-unit communication formats are: To CTL-90 *
From CTL-90 **
To XPDR(s) ARINC 429
From XPDR(s) ARINC 429
* Data to the CTL-90 is in the form of discretes: • Reply lamp switching • Altitude reporting lamp switching ** Data from the CTL-90 is in the form of discretes: • Test • Ident • ATC Select, No. 1 and No. 2 • Gray code • When used with an ARINC 429 Control
In this application, the inter-unit communication formats are: To ATC Control ARINC 429
From ATC Control ARINC 429
To XPDR(s) ARINC 429
From XPDR(s) ARINC 429
If all tests ed successfully, restore all equipment to its normal ground operating configuration. Return the test set to its normal storage location. Careful handling and storage of all ramp test equipment prolongs the service life and reduces maintenance costs.
5/5/1993
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Table 5-5. Transponder System, Flightline Fault Isolation Procedures.
TEST
RTU870A/T, power and lighting
RTU870A/T, discretes
5/5/1993
PROCEDURE
DESIRED RESULT
TROUBLESHOOTING INSTRUCTIONS
Use a multimeter at the following test test points. Connect the reference lead to the appropriate "L" test point for power measurements, or COMM (P1-53) for signal checks. Discrete ON/OFF: Connect meter + to ON/OFF, meter - to 28 V DC POWER IN L (No. 1 or No. 2)
This input must be low (ground) to enable the RTU. A cross-side switch may be used to select to enable the unit.
28 V dc power input: Connect meter + to: a. 28 V DC POWER IN, NO. 1, H b. 28 V DC POWER IN, NO 2, H
+28 V dc ±5
The No. 1 and No. 2 power inputs are combined (or’d) internally. Therefore, the unit will operate on either.
115 v ac lighting bus: Connect meter + to 115 V AC LIGHTING BUS H and - to L.
115 V ac ± 15
Check 115 V ac lighting supply
28 V dc dimming input: Connect meter + to DIM, - to COMM
28 V dc ± 15, max, depending on dim control setting. If dimming is manually controllable, adjust the DIM control and note that brightness range appears correct.
Check 28 V dimming supply
Discretes:
Note: With the exception of ON/OFF, those test points labeled DISCRETES are all strapping or switching options. You will need to check the airplane manual to determine which options have been selected. In most cases, a high reading is the result of an internal pullup to + 12 V dc and indicates the option is not selected or enabled.
• X-SIDE
This is an output to a cross-side RTU A low output indicates the on-side RTU is on. A high (near + 12 V dc) indicates the cross-side RTU is enabled.
Check RTU
• EDAT (Engine Data Select, RTU-870A only)
This is a reversionary input from an external switch. This should be low (ground) when Engine Data is selected and high (near +12 V dc) otherwise. Engine data information can be monitored at the ARINC 429 ENGINE DATA No. 1 and No. 2, A/B test points.
Check external switch or RTU
• MB (Marker Beacon Sensitivity Select)
This input is normally connected to an external MKR BCN switch. In the HI (high) position this input should be high. In the LO position this input should be low (ground).
Check external switch or RTU.
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Table 5-5. Transponder System, Flightline Fault Isolation Procedures.
TEST
RTU870A/T, discretes (cont ’d)
RTU870A/T, Strappin options
5/5/1993
PROCEDURE
Discretes (cont’d): • ATC 1 (transponder no. 1)
DESIRED RESULT
This input is normally connected to an external ATC (select) switch. A low (near ground) input indicates that transponder no. 1 is selected. A high (+12 V dc pull-up) indicates, no. 2 is selected.
TROUBLESHOOTING INSTRUCTIONS Check external switch or RTU.
• RTU 2
A ground at this point designates this RTU as the no. 2 (co-pilot’s) RTU. An open (near +12 V dc) is no. 1 (pilot’s side).
• REM (remote)
If remote tuning is available, this pin is used to enable the remote tune function. The external REMOTE TUNE switch supplies 28 V dc to this pin when remote tune is enabled. A ground indicates disable.
Check external switch or RTU.
Strapping options: • TST EN (Self test enable)
A switched ground at this input causes the RTU to turn on all display segments and indicators (DME HOLD and REPLY). It also transmits the following data word on the ARINC 429 data bus: 1. Diagnostic label 350, 2. Dim bus word label 351, and 3. Self test word label 352 (RTU-870T only). You will need an ARINC 429 bus reader, connected to any one of the ARINC 429 OUT test jacks if you want to this.
Check airplane wiring or RTU
• N TST (Nav test)
A ground at this point disables the NAV test function. "TEST" is removed from the VOR or MLS subpages.
Check airplane wiring or RTU
• MLS 1 and MLS 2
A ground at these points configures the RTU to display MLS 1/2 on the top line of the main menu. This is used only on installations equipment with a microwave landing system (or systems). If the installed MLS is on same side as the RTU, the MLS control words are added to its ARINC output bus and to the top line of the VOR subpage.
Check airplane wiring or RTU
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Table 5-5. Transponder System, Flightline Fault Isolation Procedures.
TEST
RTU870A/T Strappin options (cont ’d)
5/5/1993
PROCEDURE
DESIRED RESULT
TROUBLESHOOTING INSTRUCTIONS
• DME (No DME2)
A ground at this point causes the pilot’s RTU to transmit only the channel 1 ARINC 429 tuning word to the DME. A ground at this point on the copilot’s RTU causes that RTU to transmit only the channel 2 ARINC 429 tuning word to the DME. The copilot’s RTU transmits channel 3 data only when the copilot’s RTU receives channel 3 data from the remote tuning source. With this pin at ground, only SDI 01 is transmitted.
Check airplane wiring or RTU
• ADF (No ADF 2)
A ground at this point indicates there is no ADF on the copilot’s side. This causes the RTU to transmit tune data only for the pilot’s ADF.
Check airplane wiring or RTU
• UHF 1 (RTU-870T only)
An open at this point selects vhf 1 COMM 1 as the left-side COMM. A ground selects UHF 1 as the left side COMM.
Check airplane wiring or RTU
• UHF 2 (RTU-870T only)
Same as UHF 1 except as it applies to the copilot’s side and no. 2 systems.
Check airplane wiring or RTU
• TCN 1 (TACAN No. 1) (RTU-870T only)
A ground at this point selects the TACAN transceiver for the left-side DME transceiver. TCN is shown on the display. An open selects the left-side DME transceiver .
Check airplane wiring or RTU
• TCN 2 (TACAN No. 2) (RTU-870T only)
Same as TCN 1 except as it applies to the copilot’s side.
Check airplane wiring or RTU
• TCAS (RTU-870T only)
There should be a ground at this point if a TCAS is installed on this airplane. Open if no TCAS is installed.
Check airplane wiring or RTU
• ADF X (ADF extended frequency range) (RTU870T only)
A ground at this point configures the RTU to use the 2091 kHz ADF extended tuning frequency range with or in place of the 2081 kHz extended range.
Check airplane wiring or RTU
• INV TC (Inverse TACAN) (RTU-870T only)
A ground at this point disables the inverse TACAN function. An open enables.
Check airplane wiring or RTU
• C EXT (COMM frequency extension)
A ground at this point selects the extended frequency range (above 135.95 MHz).
Check airplane wiring or RTU
• N EXT (NAV frequency extension)
A ground at this point enables the NAV frequencies up to 135.00 MHz.
Check airplane wiring or RTU
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Table 5-5. Transponder System, Flightline Fault Isolation Procedures.
TEST
RTU870A/T Strappin options (cont ’d) RTU870A/T Data Buses
PROCEDURE
• A EXT (ADF frequency extension)
DESIRED RESULT
TROUBLESHOOTING INSTRUCTIONS
A ground at this point enables the ADF emergency frequency, 2182 kHz.
Check airplane wiring or RTU
Data Buses
The RTU-870A/T can receive and transmit ARINC 429 data on three data buses, labeled A, B, and C. This is in addition to the engine data input buses described below. A data bus reader can be used to read the data. Typical labels seen here are (update rate): • 016*: ATC mode S (5/s), • 030: VHF COMM frequency (10/s), • 031: ATC control code (5/s), • 032: ADF tune frequency (5/s), • 034: VHF NAV tune frequency (5/s), • 035: DME tune frequency (30/s), • 036: MLS channel echo (5/s), • 051*: UHF frequency and control (5/s), • 053*: TACAN tune frequency and control (5/s), • 154: MLS max select GP angle (5/s), • 157: Basic data word 2 (5/s), • 166*: DPU mode W and 1 (5/s), • 203: ATC altitude code (5/s), • 254: FCC mode word 3 (10/s), • 270: FMC mode (5/s), • 301: VHF COMM frequency (burst), • 302: VHF NAV frequency (burst), • 303: DME frequency X3 (burst), • 304: ADF frequency (burst), • 305: ATC code (burst), • 320*: Heading word, • 376*: UHF frequency (burst), and • 377*: TACAN channel (burst). * = RTU-870T only
If the installation is nontypical, consult airplane manual to determine the buses active and the information that each can be expected to reveal.
Engine Data Buses:
Typically the labels seen here are (update rate): • 340: Torque (percent of max) (10/s), • 344: Propeller RPM (10/s), • 345: Inner turbine temperature (10/s), and • 346: Turbine speed (percent of max in RPM) (10/s).
If all tests ed successfully, restore all equipment to its normal ground operating configuration. Return the test set to its normal storage location. Careful handling and storage of all ramp test equipment prolongs the service life and reduces maintenance costs.
5/5/1993
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Table 5-5. Transponder System, Flightline Fault Isolation Procedures.
TEST
TTC920G, power and lighting
TTC920G, manual controls, tests
PROCEDURE
DESIRED RESULT
TROUBLESHOOTING INSTRUCTIONS
Note: You can skip any tests that have been performed earlier as part of this test sequence. Check the airplane manual to determine the strapping and switching functions used in your installation. These procedures assume all functions are active which may not be true in all cases. For example, you will never find an installation that uses both 28 V and 5 V lighting. Power Test: Connect multimeter to 115 VAC POWER IN, NO. 1 and NO. 2 test points.
Measure aircraft power at both sets of test points. Allow 10% tolerance.
Check aircraft power source(s).
Lighting and Dimming Control Test: Connect multimeter to LIGHTING power test points; either 28V or 5 V, as applicable. If a manual dimming control is used, adjust it.
Measure lighting power. Note that dimming control works and intensity appears correct. Note that all switch and control legends are properly illuminated. It may be necessary to block the cockpit light, especially if this is being done outdoors.
Check lighting and dimming source. If any legends are not properly lit, remove TTC for bench repair.
Monitor Lamp Power test: Connect multimeter (+) to MON LMP PWR point and (-) to COMM (J1-6)
Measure the monitor lamp power input. This may be 28 V or 12 V. Allow 10% tolerance.
Check power source.
Note an open when the switch is not pressed and a short when the switch is pressed.
Check TTC.
Note an open when the switch is not pressed and a short when the switch is pressed.
Check TTC.
Connect multimeter, set for resistance measurement: (+) to No. 1, (-) to COMM (J1-6)
Note an open when the XPDR switch is at position 2 and a short when the switch is at position 1.
Check TTC.
Connect multimeter, set for resistance measurement: (+) to No. 2, (-) to COMM (J2-6)
Note an open when the XPDR switch is at position 1 and a short when the switch is at position 2.
Check TTC.
Self Test Switch tests: Connect multimeter, set for resistance measurement: (+) to SELF TEST, (-) to COMM (J1-6). Fault Monitor Lamp Test Switch tests: Connect multimeter, set for resistance measurement: (+) to MON, (-) to COMM (J1-6). ANTENNA SELECT Switch tests:
5/5/1993
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Table 5-5. Transponder System, Flightline Fault Isolation Procedures.
TEST
PROCEDURE
TTC920G, manual controls, tests (cont’d)
XPDR IN STBY Switch tests:
DESIRED RESULT
TROUBLESHOOTING INSTRUCTIONS
Connect multimeter, set for resistance measurement: (+) to No. 1, (-) to COMM (J1-6)
Note an open when the XPDR switch is at position 2 and a short when the switch is at position 1.
Check TTC.
Connect multimeter, set for resistance measurement: (+) to No. 2, (-) to COMM (J2-6)
Note an open when the XPDR switch is at position 1 and a short when the switch is at position 2.
Check TTC.
Connect multimeter, set for resistance measurement: (+) to NO. 1, (-) to COMM (J1-6)
Note an open when the switch is at position 2 and a short when the switch is at position 1.
Check TTC.
Connect multimeter, set for resistance measurement: (+) to NO. 2, (-) to COMM (J2-6)
Note an open when the switch is at position 1 and a short when the switch is at position 2.
Check TTC.
Connect multimeter, set for resistance measurement: (+) to NO. 1 IN, (-) to COMM (J1-6) (NO. 1 OUT is identical)
Note: This input is normally connected to an airplane strut switch. With weight on wheels this point should show a short to chassis ground (CHAS GND, J1-8 or J2-8). If this function has been defeated for test purposes, it should show an open.
Check airplane wiring
Connect multimeter, set for resistance measurement: (+) to NO. 2 IN, (-) to COMM (J1-6) (NO. 2 OUT is identical)
Note: This input is normally connected to an airplane strut switch. With weight on wheels this point should show a short to chassis ground. If this function has been defeated for test purposes, it should show an open.
Check airplane wiring
28 V dc at either of these points indicates that no detected failure exists in the applicable transponder. If this voltage is low, you may need to use an ARINC 429 data bus reader to determine the diagnostic condition - see Diagnostic Code Retrieval Procedures below.
Note: Not all diagnostic conditions produce a failure warn (flag) output. Refer to tables 5-3 and 5-4.
This is an inverted failure warn output. If either of the two transponder fail inputs are low, this point should be high. If both inputs are high, this point should be low.
Check TTC.
REP ALT SEL (Reporting Altitude Select) Switch tests:
TTC920G, discretes tests, (cont’d)
AIR/GRD Tests:
Transponder Fail I/O Tests: TTC920G, Xpdr fail warn tests
Connect multimeter, set for dc voltage measurement: (+) to TRANSPONDER FAIL, 1-IN, (-) to COMM (J1-6) Connect multimeter, set for dc voltage measurement: (+) to TRANSPONDER FAIL, 2-IN, (-) to COMM (J2-6) Connect multimeter, set for dc voltage measurement: (+) to TRANSPONDER FAIL, OUT, (-) to COMM (J1-6)
5/5/1993
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Table 5-5. Transponder System, Flightline Fault Isolation Procedures.
TEST
TTC920G, data bus output tests
PROCEDURE
DESIRED RESULT
Connect an ARINC 429 bus reader to the ARINC 429 OUT NO. 1 jack. Select transponder no. 1.
TROUBLESHOOTING INSTRUCTIONS
Set the bus reader to read ARINC 429 word labels 13, 15, or 16. The words are defined as follows:
Label 013: Bit(s) 0-7 8, 9 10 11, 12 13 14 - 20 21 - 28 29, 30 31
Definition Label (in octal): bits 0,1 = MSB, 2-4 = second digit, 5-7 = LSB, SDI (source destination (or data) identifier), Intruder altitude (ABS/REL), ABS = 1 Altitude select, bits 12/11: 00 = normal, 10 = above, 01 = below, 11 = unrestricted Display: all traffic/threat traffic, all = 0 (not used) TCAS range (see below) SSM (see below) Parity bit
Label 015: Bit(s) 0-7 8, 9 10 - 16 17 - 23 24 - 28 29, 30 31
Definition Label (in octal): bits 0,1 = MSB, 2-4 = second digit, 5-7 = LSB, SDI (source destination (or data) identifier), Altitude A limits (see airplane manual) Altitude B limits (see airplane manual) (not used) SSM (see below) Parity bit
Label 016: Bit(s) 0-7 8, 9 10 11 12, 13 14 - 16 17 - 19 20 - 22 23 - 25 26 - 28 29, 30 31
Definition Label (in octal): bits 0,1 = MSB, 2-4 = second digit, 5-7 = LSB, SDI (source destination (or data) identifier), Altitude reporting, on/off, 1 = off, Ident mode Display control Sensitivity control Digit 4 code Digit 3 code Digit 2 code Digit 1 code SSM (see below) Parity bit
TCAS range bit definition: bit 21 = 0.5 nmi bit 22 = 1.0 nmi bit 23 = 2.0 nmi bit 24 = 4.0 nmi bit 25 = 8.0 nmi bit 26 = 16.0 nmi bit 27 = 32.0 nmi bit 28 = 64.0 nmi
5/5/1993
SSM definition (bits 30/29): 00 = normal operation 01 = NCD (no computed data) 10 = Functional test 11 = Failure warn
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Table 5-5. Transponder System, Flightline Fault Isolation Procedures.
TEST
TTC920G (cont’d)
PROCEDURE
DESIRED RESULT
TROUBLESHOOTING INSTRUCTIONS
If all tests ed successfully, restore all equipment to its normal ground operating configuration. Return the test set to its normal storage location. Careful handling and storage of all ramp test equipment prolongs the service life and reduces maintenance costs.
Table 5-6. Transponder System, Diagnostic Data Retrieval Procedures.
TEST NO and DATA TITLE
BUS READER, TX SETUP
RESULTS and COMMENTS
1.0 Introduction
Note: These procedures apply only to installations using the CTL-92T or the RTU-870A/T. Diagnostic information is available only on the ARINC 429 data bus. Installations using a TTC920G or a CTL-90, do not return this bus to the control. Installations using a CTL-92/92A only use the CSDB bus which does not carry diagnostic data beyond the current diagnostic code which is displayed on the CTL-92/92A during self test. Refer to paragraph 5.5 for added information on Diagnostic Data Retrieval and Interpretation.
2.0 Setup
These procedures use the same setup as used for the procedures in table 5-5, shown on figure 5-1. In all cases, the XMT word label is 277 and the response word label is 351. Note: Throughout these procedures be sure the SSM is always set to 11. If you are using the DataTrac 400/400H you need change only digits 5 and 6 of the data fields; digit 1 (e.g., the 6 in step 3.0) is always set automatically. This bit is set by data word bits 29 through 32. On the DataTrac 200 you set the SI field. For the sake of simplicity, the column headers are not shown on the DataTrac display examples below.
3.0 Soft-ware Rev Status
Data request: DataTrac 400/400H XMT: 277 00 00 00 00 FD 00 1 0100 DataTrac 200 XMT: 277 00 00000 00 1 0100 JcAIR 429E TX, label 277: E00000
Response form (data may differ): DataTrac 400/400H RCV: 351 10 90 26 92 97 00 1 0100 DataTrac 200 RCV: 351 10 81348 00 1 0100 JcAIR 429E RX, label 351: 902692 This shows a SRS = 10-26-92
4.0 Total PwrOn Cycle Counter
Data request: DataTrac 400/400H XMT: 277 01 E0 00 01 FD 11 1 0100 DataTrac 200 XMT: 277 01 00000 11 1 0100 JcAIR 429E TX, label 277: E00001
Six-digit data field displays count in decimal form. DataTrac 400/400H RCV: 351 00 60 02 00 97 11 1 0100 DataTrac 200 RCV: 351 00 00100 11 1 0100 JcAIR 429E RX, label 351: 600200 This shows a POCC = 200.
5.0 Total Fault Counter
Data request: DataTrac 400/400H XMT: 277 10 E0 00 02 FD 11 1 0100 DataTrac 200 XMT: 277 10 00000 11 1 0100 JcAIR 429E TX, label 277: 600002
Six-digit data field displays count in decimal form. DataTrac 400/400H RCV: 351 00 60 02 08 97 11 1 0100 DataTrac 200 RCV: 351 00 00104 11 1 0100 JcAIR 429E RX, label 351: 600208 This shows a TFC = 208.
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Table 5-6. Transponder System, Diagnostic Data Retrieval Procedures.
TEST NO and DATA TITLE
BUS READER, TX SETUP
RESULTS and COMMENTS
6.0 Total Pwr-on Timer (Hrs)
Data request: DataTrac 400/400H XMT: 277 11 60 00 03 FD 11 1 0100 DataTrac 200 XMT: 277 11 00000 11 1 0100 JcAIR 429E TX label 277: 600003
7.0 Total Pwr-on Timer (Min)
Note: If you watch this data item for a minute or less you will see the data increment. Data request: DataTrac 400/400H XMT: 277 00 E0 00 04 FD 11 1 0100 DataTrac 200 XMT: 277 00 00002 11 1 0100 JcAIR 429E TX label 277: 600004
Six-digit data field displays count in decimal form. DataTrac 400/400H RCV: 351 11 60 00 11 97 11 1 0100 DataTrac 200 RCV: 351 11 00008 11 1 0100 JcAIR 429E RX, label 351: 600011 This shows a TPOTM = 11.
8.0 Last Pwron Cycle Fault Cntr
Data request: DataTrac 400/400H XMT: 277 01 60 00 05 FD 11 1 0100 DataTrac 200 XMT: 277 01 00002 11 1 0100 JcAIR 429E TX label 277: 600005
Six-digit data field displays count in decimal form. DataTrac 400/400H RCV: 351 10 E0 00 02 97 11 1 0100 DataTrac 200 RCV: 351 10 00000 11 1 0100 JcAIR 429E RX, label 351: 600002 This shows a LPOCFC = 2.
9.0 Last Maintenance Date
Data request: DataTrac 400/400H XMT: 277 11 60 00 07 FD 11 1 0100 DataTrac 200 XMT: 277 11 00002 11 1 0100 JcAIR 429E TX label 277: 600007
Six-digit data field displays in the form MMDDYY. Six-digit data field displays count in decimal form. DataTrac 400/400H RCV: 351 11 E6 29 93 97 11 1 0100 DataTrac 200 RCV: 351 11 314C8 11 1 0100 JcAIR 429E RX, label 351: E62993 This shows a LMD = 6-29-93 (June 29, 1993)
10.0 Last Pwr-on Cycle Fault Data
Note: In this sequence you must watch the label 351 word carefully. The UUT may transmit several words, each with a different diagnostic code, at 5-second intervals. The first transmission is the contents of the current Total Power-on Cycle count buffer (see step 4.0; above). This is followed, in 5-seconds intervals, with a transmission of each of the secondary diagnostic codes encountered during the most recent power-on cycle (auto self-test). This sequence is automatic and noninterruptable. If you are using the JcAIR 429E, be prepared to write down the data as it appears. The DataTrac units will retain the data. The final label 351 word is likely to be a word similar to XXXEOF which translates into "End of File".
5/5/1993
Six-digit data field displays count in decimal form. DataTrac 400/400H RCV: 351 11 60 00 77 97 11 1 0100 DataTrac 200 RCV: 351 11 0003A 11 1 0100 JcAIR 429E RX, label 351: 600077 This shows a TPOTH = 77.
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Table 5-6. Transponder System, Diagnostic Data Retrieval Procedures.
TEST NO and DATA TITLE
BUS READER, TX SETUP
RESULTS and COMMENTS
10.0 Last Pwr-on Cycle Fault Data (cont’d)
Data request: DataTrac 400/400H XMT: 277 00 60 00 10 FD 11 1 0100 DataTrac 200 XMT: 277 00 00008 11 1 0100 JcAIR 429E TX, label 277: 600010
11.0 Continue (prior) Pwr-on Cycles Fault Data
Note: This step can be seen as an extension of the previous step by retrieving diagnostic data stored during earlier power-on cycles. Data delivery and interpretation is the same as step 10.0. The most recent 16 power-on cycle sequences are stored and are read by incrementing data field bit 6 (bit 5 on the DataTrac 200) 1 through F (Hex). Data request: DataTrac 400/400H XMT: 277 00 60 00 11 FD 11 1 0100 DataTrac 200 XMT: 277 01 00008 11 1 0100 JcAIR 429E TX, label 277: 600011
12.0 Fast Data
Same as step 10.0 except one set of data for each interrogation. A convenient Record Chart is provided, following paragraph 5.5.14.2, for manually entering the data.
Note: This step is for those with access to an automated means of requesting, capturing, and analyzing the data. Such facilities are available from sources other than Collins. For example, Atlantic Instruments supplies hardware and software, operating with the DataTrac 400/400H, for automated ing of the captured data on a PC for detailed analysis and storage. For manual (slower) data , use step 13.0 below. Data request: DataTrac 400/400H XMT: 277 00 60 00 50 FD 11 1 0100 DataTrac 200 XMT: 277 00 00028 11 1 0100 JcAIR 429E TX, label 277: 600050
13.0 Slow Data
Six-digit data field displays count in decimal form. DataTrac 400/400H RCV: 351 00 E0 02 00 97 11 1 6800 351 10 60 00 82 97 11 1 6800 351 11 E0 0E 0F 97 11 1 6800 DataTrac 200 RCV: 351 00 00100 11 1 4999 351 10 00040 11 1 4999 351 11 00706 11 1 4999 JcAIR 429E RX, label 351: E00200 600082 E00E0F
Refer to paragraph 5.5.13.2 for a detailed description of the data that is transmitted here. If you are retrieving data manually, e.g., with the JcAIR 429E, use step 13.0 instead. In this step, step 12.0, the data is transmitted to quickly to be read manually. See note below.
Note: This step is essentially the same as the previous step, step 12.0. Here, however, the data output rate is slower; each sequence is transmitted for a 5-second period, separated by a break transmission 0FFFFH. Data request: DataTrac 400/400H XMT: 277 00 60 00 51 FD 11 1 0100 DataTrac 200 XMT: 277 01 00028 11 1 0100 JcAIR 429E TX, label 277: 600051
Same as step 12.0 except the data is transmitted at 5--second interval.
Note: The DataTrac 400/400H units have a Break Data Review feature which can be effectively used here to capture the data. Consult the applicable manual for the necessary operating procedures. Return the test set to its normal storage location. Careful handling and storage of all ramp test equipment prolongs the service life and reduces maintenance costs.
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maintenance 523-0775657 5.4.5 ACCEPTANCE TEST PROCEDURES 5.4.5.1
Introduction
The Acceptance Test Procedures (ATP) should be used to that the equipment is operational; that no shipping damage has occurred. ing equipment operation before installation helps to isolate most problems discovered after installation. The procedures in this paragraph can also be seen as a Return to Service Test (RTS). In this scenario a the pilot complaint and the flightline test is not conclusive. Thus the unit is removed from an airplane and tested on the bench to isolate a malfunction between the unit or the airplane installation. If the unit performs properly on the bench using the RTS, it can be returned to service. The procedures in this paragraph must not be seen as the equivalent of a Final Performance Test (FPT). An FPT must be performed after any repair operation and is considerably more detailed than this ATP. The FPT is provided in the TDR-94/94D Component Maintenance Manual.
item. A refers to the abbreviated shown schematically in figure 5-4. E is the enhanced version shown in figures 5-3 and 5-5. TE items keyed A and E can be used with either . TE items keyed A only can be used only with the abbreviated version; items keyed E are for use only on the enhanced version. 5.4.5.3 Test Options Table 5-7 shows two test s. Option 1A is the enhanced version and will allow use of a databus reader and various controls and control simulators in addition to a number of altitude sources. The details of this are included in paragraph 5.8 Option 1B is the abbreviated version mentioned in paragraph 5.4.5.2. It is expected that the abbreviated test is assembled locally. The enhanced version can also be locally assembled or purchased from a number of suppliers. Those known suppliers are included in the vendor listing in table 5-8.
The procedures are provided in four different procedures. The procedure chosen depends on equipment available and on the extent to which testing is to be performed. The first procedure uses the CTL-92/92A CSDB control and an abbreviated version of the test . This procedure satisfies a minimum level of acceptance testing by ing that the UUT is able to respond to CSDB tuning data and report any internal diagnostics that may exist.
The abbreviated test , when used with the automatic test capability of the ATC601, satisfies the requirements of ADVISORY CIRCULAR NO 43.13-6A, dated 11/11/77; Subject: Automatic Pressure Altitude Encoding Systems and Transponder Maintenance and Inspection Practices. The IFR ATC-601 Test Set, or equivalent, can be used with either of the two versions.
The remaining procedures utilize the enhanced version of test and provide a greater level of I/O testing capability. These procedures differ only in the particular data bus analyzer being used.
If you are using a test built according to instructions in an earlier version of this manual, it may need to be updated. Refer to paragraph 5.8.1 for update information.
5.4.5.2
ATP Setup Description
Table 5-7 is a list of the equipment required for this ATP. The equipment includes an IFR ATC-601 Mode S Test Set. If an other test set is used, you should be sure that it is capable of performing the tests as defined in these procedures and as listed in paragraph 5.4.2. The right hand column in table 5-7 identifies the test required for the use of that TE 5/5/1993
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maintenance 523-0775657 Table 5-7. Equipment Required for ATP
Item
Manufacturer
Mfg Part Number
Purpose
A/E
Test Option 1A
Locally fabricated
See figure 5-3 and 5-5
To interconnect equipment for ATP
E
Test Option 1B
Locally fabricated
See figure 5-4
To interconnect equipment for ATP
A
ATC/Mode S Test Set
IFR Systems, Inc. Wichita, KS
ATC-601
For rf testing
A,E
ARINC Bus Reader Option 2A
Atlantic Instr. Melbourne, FL
DataTrac 200, Data Trac 400, or DataTrac 400H
For bus monitor and simulation
E
ARINC Bus Reader Option 2B
JcAIR Industrial Airport, KS
429E ARINC 429 Transmitter / Receiver
For bus monitor and simulation
E
Transponder Control Option 3A
Collins
CTL-92 or CTL-92A Transponder Control
Transponder control
A,E
Interconnect cable for option 3A
Same as test
See figure 5-6
For CTL-92/92A interface to test
A,E
Transponder Control Option 3B
Collins
RTU-870A or RTU-870T Radio Tuning Unit
Transponder or transponder/TCAS control
E
Interconnect cable for option 3B
Same as test
See figure 5-7
For RTU-870/870A interface to test
E
Transponder Control Option 3C
Collins
TTC-920G TCAS / Transponder Control
Transponder control
E
Interconnect cable for option 3C
Same as test
See figure 5-8
For TTC-920G interface to test
E
RF load
Omni-Spectra
3101-6100-00
RF termination of unused antenna port
A,E
Interconnect cables for Bus Readers and control simulators
Locally fabricated or the same as test
See figure 5-9
To connect bus reader and control / altitude simulator to test
E
28 V dc power supply
any
5 A minimum capability
For test setup power
A,E
Scope
any
any
For suppression test
A,E
Table 5-8. Equipment Suppliers
Supplier
Address
Product
IFR Systems, Inc.
10200, West York Street Wichita, KS 67215
ATC-601 Ramp Test Set
Atlantic Instruments, Inc.
P.O. Box 021466 Melbourne,FL 32902
DataTrac 400 DataTrac 400H and DataTrac 200 Databus Analyzers
JcAIR
400 Industrial Parkway, Industrial Airport, KS 66031
AcceptanceTest , Flightline Test , and 429E ARINC 429 Transmitter/Receiver
Avionics Specialist, Inc
3833 Premier Ave. Memphis, TN 38118
Acceptance Test and Flightline Test
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maintenance 523-0775657 The enhanced version of test , also satisfies these requirements, and offers additional capabilities for more complete I/O testing as follows: Gillham altitude simulation, Gillham altitude switching for direct or through CTL testing, Mode S address code selection, Control type selection, Control input port selection, Digital altitude type selection; ARINC 429, ARINC 575, or CSDB, TCAS i/o bus verification, Digital altitude and control port selection, Manual ident, Crossfeed switching, Side 1/Side 2 switching, Output port selection, and Use of a data bus analyzer. The control interface cables, shown in figures 5-6, 5-7, and 5-8 can be used with either . 5.4.5.4 Control Options Some type of transponder control is required with either test . The abbreviated version uses the CTL-92/92A Control. The enhanced version can use any of the currently available controls or a simulator. If you have a databus receiver/transmitter, like the DataTrac 400, DataTrac 400H, or DataTrac 200, by Atlantic Instruments, it can be used to simulate an ARINC 429 control. The DataTrac 200 can also simulate a CSDB control. If you plan to used the TTC-920G TCAS control, be aware that it requires 115 Vac, 400 Hz, power which is not provided in the test . The interconnect cable, figure 5-8, has a patch provision for 115 Vac power input. Table 5-8 is a listing of suppliers for the various test equipment items as well as the test .
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5.4.5.5
Gillham Code Simulator
The TDR-94/94D Mode S Transponder Acceptance Test used here includes a built-in Gillham code (ARINC 572) simulator. The Gillham Code Altitude Tests in this section include a listing of a number of altitudes and corresponding Gillham code switch settings. Set the corresponding switch down (SEL) for an active code selection, and set the switch up (OFF) for an inactive selection. 5.4.5.6
ATC Setup Description
If you are using this setup for the first time, check that 28 volts appears only on the correct pins. Use the schematic diagram shown in figure 5-4 or 5-5 as applicable to the you are using. WARNING: Do not use a standard multimeter probe when making continuity tests to the ProLine II UUT mating connector. These types of probes have been known to cause the forks to break resulting in unreliable operation. It is far better to fabricate one or two test probes using a short length of flexible 22 or 26 AWG wire, terminated at one end with a mating blade like those used in the UUT connector. Terminate the other end with a small alligator clip or tip jack to connect to the multimeter lead.
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maintenance 523-0775657 Interconnect the equipment as shown in figure 5-2. The data bus readers are not used with the abbreviated test . Be sure that the rf connections to the antenna connectors are fully inserted and that the i/o mating connectors are firmly seated before applying power. Terminate the unused antenna port with a TNC 50Ω rf termination as identified in table 5-1 and table 5-7. Turn on the ATC-601 Test Set, or equivalent, and exercise the self test routine. If the test set is operational continue with the test. Otherwise, repair the test set. If you are using the test shown on figure 5-5, set the switches as follows: The abbreviated has only the UUT POWER and EXT STBY switches. If you are using a test built according to instructions in an earlier version of this manual, it may require modification. Refer to paragraph 5.8.1.
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SWITCH
POSITION
UUT POWER: OFF EXT STBY: STBY XFEED: OUT SELF TEST: EN TCAS/NO TCAS: NO TCAS SDI: SIDE 1 AIR: AIR ANT: DL AUTO ALT: OFF REP ALT SEL: PA DATA LINK SEL: A/B BURST TUNE: OFF DATALINK: NO ADLP CONTROL DATA SELECT: ARINC PORT: PA OUTPUT PORT SELECT: ARINC 429 PORT A ARINC 572 ALT IN: TO TDR ALT TYPE SELECT: ARINC 429 SOURCE SELECT: SEL ARINC 572 ALT IN: TO TDR Gillham Code switches: All OFF except C2 and B1 to SEL (2, 500 ft) MAX AIRSPEED: All OFF MODE S ADDRESS SELECT: All OFF except: P1-35, 36, 37, 39, 41, 42, 46, 51, 56. (Hex code: 3AC421, Octal: 16542041)
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maintenance 523-0775657
Acceptance Test, Test Setup Diagram Figure 5-2
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maintenance 523-0775657 5.4.5.7 Minimum Acceptance Test, Using a CSDB Control and the Abbreviated Test The procedures in table 5-9 use a CSDB control like the CTL-92/92A to provide transponder control and the abbreviated version of test
for equipment interconnection. Successful completion of these procedures verifies the performance of the UUT by providing reasonable assurance of the functional integrity of the transmitter, receiver, the CSDB control input, and internal data handling.
Table 5-9. Minimum Acceptance Test Procedures, Using a CSDB Control and the Abbreviated Test
STEP
TITLE
PROCEDURE
DESIRED RESULTS
1.0
Setup
If not already done, connect equipment as shown in figure 5-2. • Connect the CTL-92/92A using the cable shown in figure 5-6. • Connect the ATC-601 (or equivalent) to the UUT bottom antenna connector. • Connect and rf termination to the top antenna connector. • Connect power to the power jacks - observe proper polarity. • Be sure POWER switch is OFF and EXT STBY switch is at STBY. • The bus reader is not needed in this setup.
2.0
Initial Test
Power application Set test POWER switch to ON Set CTL to any valid ATC code; e.g. 1234
3.0
UUT Self Test
Set CTL switch to STBY
ATC-601 REPLY lamp is off; no replies.
Set CTL switch to OPR
No change.
Set EXT STBY switch to OPR
ATC-601 REPLY lamp lights; UUT is replying to the interrogations.
Press the TEST button; either on the test or on the CTL. Notice any diagnostic code that may be displayed on the CTL. If diAG and a diagnostic code is displayed, refer to table 5-3 and 5-4 for an interpretation. If a code from 10 to 70 (inclusive), C(), or D0 is displayed, the UUT should be rejected. Any other code may not be indicative of an equipment failure but rather the result of an inactive data bus. As a general rule in testing a UUT with N ending in -002, those diagnostic conditions accompanied by an extinguished FLT MON (fault monitor) lamp on test , should be seen as cause for unit rejection. Others may be the result of the an incomplete equipment complement and may not be indicative of an equipment failure.
4.0
Test Set, Auto Test
Follow the instructions in the Test Set operation manual for the Auto Test mode and execute the test.
Ensure that all tests . See note below.
Set the test POWER switch to Off Switch the RF connector on the UUT from top to bottom (or bottom to top) Repeat the Auto Test sequence.
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Ensure that all tests . See note below.
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maintenance 523-0775657 Table 5-9. Minimum Acceptance Test Procedures, Using a CSDB Control and the Abbreviated Test (Cont).
STEP
TITLE
PROCEDURE
DESIRED RESULTS
This completes the minimum test requirement. -------------------------------------------------------------------------------Note. The AUTO TEST sequence will indicate FAILED even when certain tests result in a NO REPLY condition. The NO REPLY conditions are the result of no ADLP (Airborne Data Link Processor) data being supplied in this setup. This same condition is likely to occur when using the ATC-601 as a ramp tester when testing an installation not equipped with an ADLP. It is also possible that the AUTO TEST fails because the UUT sensitivity is more than -77.0 dBm. If you find this to be the case, recognize that Collins prefers that a sensitivity (MTL) greater than 77.0 be seen as acceptable. Obviously, an MTL approaching -80 dBm tends to indicate a problem with test equipment calibration. To that the test can be seen as successful, proceed as follows: • When the test sequence is completed and the ATC-601 stops (as indicated by no INTERR lamp off, you will see a screen as follows: ** AUTO TEST - FAILED ** MODES TESTED - A,C,S FREQ: 1089.92 MHz MODES ED - A,C.S ERP: 55 dBm MODES FAILED -> MTL: -77 dBm DIVERSITY ISOLATION: >40 dB Press RUN to start
the test results as follows: Use the SELECT up arrow or down arrow key to scroll through the following list of tests performed. If you use the up arrow, you will see the sequence as listed from top to bottom. If you use the down arrow, you will see the sequence is reverse order. 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. 13. 14. 15. 16. 17. 18. 19.
** ** ** ** ** ** ** ** ** ** ** ** ** ** ** ** ** ** **
MTL DIFFERENCE TEST - ED ** DIVERSITY TEST - ED ** FREQUENCY TEST - ED ** SQUITTER TEST - ED ** MODE S UF21 TEST - NO REPLY ** MODE S UF20 TEST - NO REPLY ** MODE S UF16 TEST - NO REPLY ** MODE S UF11 TEST - ED ** MODE S UF5 TEST - ED ** MODE S UF4 TEST - ED ** MODE S UF0 TEST - ED ** SPR ON/OFF TEST - ED ** INVALID ADDRESS TEST - ED ** MODE S ALL-CALL TEST - ED ** ATC ONLY ALL-CALL TEST - ED ** SLS LEVEL TEST - ED ** ATCRBS REPLY TEST - ED ** REPLY JITTER TEST - ED ** REPLY DELAY TEST - ED **
At this point, another press of the arrow key will redisplay the first item; either 1. or 19., depending which arrow was used. In each case, the screen also shows the particular test parameter and the test result. If the test has failed, this value can be compared to the required value to gain more definitive insight into the reason for the failure.
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maintenance 523-0775657 5.4.5.8 Minimum Acceptance Test, Using a ARINC 429 Control and the Abbreviated Test The procedures in table 5-10 use an ARINC 429 control like the RTU-870A/T to provide transponder control and the abbreviated version of test for equipment interconnection. Successful
completion of these procedures verifies the performance of the UUT by providing reasonable assurance of the functional integrity of the transmitter, receiver, the ARINC 429 control input, and internal data handling.
Table 5-10. Minimum Acceptance Test Procedures, Using an ARINC 429 Control and the Abbreviated Test
STEP
TITLE
PROCEDURE
DESIRED RESULTS
1.0
Setup
If not already done, connect equipment as shown in figure 5-2. • Connect the ARINC 429 control using the cable shown in figure 5-7 or 5-8. • Connect the ATC-601 (or equivalent) to the UUT bottom antenna connector. • Connect and rf termination to the top antenna connector. • Connect power to the power jacks - observe proper polarity. • Be sure POWER switch is OFF and EXT STBY switch is at STBY. • The bus reader is not needed in this setup.
2.0
Initial Test
Power application Set test POWER switch to ON Set CTL to any valid ATC code; e.g. 7777
3.0
UUT Self Test
Set CTL switch to STBY
ATC-601 REPLY lamp is off; no replies.
Set CTL switch to OPR
No change.
Set EXT STBY switch to OPR
ATC-601 REPLY lamp lights; UUT is replying to the interrogations.
Press the TEST button; either on the test or on the control. Notice any diagnostic code that may be displayed. If a diagnostic code is displayed, refer to table 5-3 and 5-4 for an interpretation. If a code from 10 to 70 (inclusive), C(), or D0 is displayed, the UUT should be rejected. Any other code may not be indicative of an equipment failure but rather the result of an inactive data bus. As a general rule in testing a UUT with N ending in -002, those diagnostic conditions accompanied by an extinguished FLT MON (fault monitor) lamp on test , should be seen as cause for unit rejection. Others may be the result of the an incomplete equipment complement and may not be indicative of an equipment failure.
4.0
Test Set, Auto Test
Follow the instructions in the Test Set operation manual for the Auto Test mode and execute the test.
Ensure that all tests . See note below.
Set the test POWER switch to Off Switch the RF connector on the UUT from top to bottom (or bottom to top) Repeat the Auto Test sequence.
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Ensure that all tests . See note below.
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maintenance 523-0775657 Table 5-10. Minimum Acceptance Test Procedures, Using an ARINC 429 Control and the Abbreviated Test (Cont).
STEP
TITLE
PROCEDURE
DESIRED RESULTS
This completes the minimum test requirement. -------------------------------------------------------------------------------Note. The AUTO TEST sequence will indicate FAILED even when certain tests result in a NO REPLY condition. The NO REPLY conditions are the result of no ADLP (Airborne Data Link Processor) data being supplied in this setup. This same condition is likely to occur when using the ATC-601 as a ramp tester when testing an installation not equipped with an ADLP. It is also possible that the AUTO TEST fails because the UUT sensitivity is more than -77.0 dBm. If you find this to be the case, recognize that Collins prefers that a sensitivity (MTL) greater than 77.0 be seen as acceptable. Obviously, an MTL approaching -80 dBm tends to indicate a problem with test equipment calibration. To that the test can be seen as successful, proceed as follows: • When the test sequence is completed and the ATC-601 stops (as indicated by no INTERR lamp off, you will see a screen as follows: ** AUTO TEST - FAILED ** MODES TESTED - A,C,S FREQ: 1089.92 MHz MODES ED - A,C.S ERP: 55 dBm MODES FAILED -> MTL: -77 dBm DIVERSITY ISOLATION: >40 dB Press RUN to start
the test results as follows: Use the SELECT up arrow or down arrow key to scroll through the following list of tests performed. If you use the up arrow, you will see the sequence as listed from top to bottom. If you use the down arrow, you will see the sequence is reverse order. 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. 13. 14. 15. 16. 17. 18. 19.
** ** ** ** ** ** ** ** ** ** ** ** ** ** ** ** ** ** **
MTL DIFFERENCE TEST - ED ** DIVERSITY TEST - ED ** FREQUENCY TEST - ED ** SQUITTER TEST - ED ** MODE S UF21 TEST - NO REPLY ** MODE S UF20 TEST - NO REPLY ** MODE S UF16 TEST - NO REPLY ** MODE S UF11 TEST - ED ** MODE S UF5 TEST - ED ** MODE S UF4 TEST - ED ** MODE S UF0 TEST - ED ** SPR ON/OFF TEST - ED ** INVALID ADDRESS TEST - ED ** MODE S ALL-CALL TEST - ED ** ATC ONLY ALL-CALL TEST - ED ** SLS LEVEL TEST - ED ** ATCRBS REPLY TEST - ED ** REPLY JITTER TEST - ED ** REPLY DELAY TEST - ED **
At this point, another press of the arrow key will redisplay the first item; either 1. or 19., depending which arrow was used. In each case, the screen also shows the particular test parameter and the test result. If the test has failed, this value can be compared to the required value to gain more definitive insight into the reason for the failure.
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5.4.5.9 Procedures using the DataTrac 400 or DataTrac 400H Databus Analyzer Table 5-11 Acceptance Test Procedures, Using the DATATRAC 400 or DATATRAC 400H Databus Analyzer STEP
TITLE
PROCEDURE
DESIRED RESULTS
1.0
Setup
Note: If you are using a Test built according to instruction provided in a previous edition of this manual, it may be necessary to upgrade the . Refer to paragraph the Special Tools and Fixture Section. If not already done, connect equipment as shown in figure 5-2. • Connect DATATRAC as follows using cables shown in figure 5-9. • XMT 1 to test DIGITAL CONTROL port, • Parallel connect XMT 1 to test PRIMARY DIGITAL ALTITUDE PORT, • RCV 1 to test DATA BUS READER port. • Connect the ATC-601 to the UUT bottom antenna connector. • Connect an rf termination to the TOP antenna port. • Connect power to test power jacks - observe proper polarity. • Preset the switches as shown in paragraph 5.4.4 above. Be sure POWER switch is OFF and EXT STBY switch is at STBY. On test , set the MODE S ADDRESS switches to any combination except all OFF or all to SEL. If all switches are set OFF or all set SEL, a diagnostic code FF will result.
1.1
Setup
Turn the DATATRAC ( ) on and set the RCV 1, and XMT 1 screen ----->
-----------------RCV 1--(ALL)---12.5 KHz Lbl SDI 32-Hex Data-1 SSM Par msec ... no data present ...
(See notes 1 and 2 that follow test step 1.2)
-ON-------------XMT 1 ----------12.5 KHz Lbl SDI 32-Hex Data-1 SSM Par msec 031 01 15 66 C1 98 00 1 0100 203 01 64 00 01 C1 11 1 0100
Turn on TDR-94/94D
On test : • Set POWER switch to ON Monitor current. If OK: • Set EXT STBY switch to OPR Monitor current.
If the unit has been in service and there is a possibility of an over-current condition, monitor the power supply current output. The setup should draw no more than 1.5 A. Typically it draws about 0.9 to 1.1 A when the UUT is transmitting.
Setup (power-up)
Turn the ATC-601 on and press SELECT for the screen -------------->
** ATCRBS REPLY TEST - NOT RUN **
(lines 2-4 are irrelevant) CODE=
See Note in next cell below. 1.2
ARINC 429 tuning test
On the ATC-601, press RUN ATC-601 screen ---------> Note: When power is applied and proper control data is supplied, the TDR-94/94D should turn on the XFEED OUT lamp almost immediately. The FAULT MON lamp may be off for a few seconds and then turn on. A lighted FAULT MON lamp should generally be seen as a no-fault indication. See table 5-3. The DATATRAC ( ) RCV 1 display becomes --------->
ALT= Press RUN to start
[
]
UUT responds to interrogations as indicated by a lighted XFEED OUT lamp on the test and a lighted REPLY lamp on the ATC-601. ** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE=5263 *****
ALT=32,800 FT [1344] TEST RUNNING *****
To change the CODE, see note 1 below. To change the ALT, see note 2 below. -----------------RCV 1--(ALL)---12.5 KHz Lbl SDI 32-Hex Data-1 SSM Par msec 203 01 64 00 01 C1 11 1 0200 031 01 F5 66 81 98 00 1 0200 350 01 60 00 01 17 11 1 0200 ... no data present ...
Note: Any other labels displayed are irrelevant to this test. Use the down arrow key to scroll the display. See Note 3 below.
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maintenance 523-0775657 Table 5-11 Acceptance Test Procedures, Using the DATATRAC 400 or DATATRAC 400H Databus Analyzer (Cont).
STEP
TITLE
PROCEDURE
DESIRED RESULTS
Note 1. You can change the (octal) CODE=XXXX display by changing data bits 18 through 29 in the label 031 data word (XMT 1 field of the DATATRAC ( )) as follows: ATC-601 digit: First Second Third Bit: 32 31 30 29 28 27 26 25 Data: Par SSM |<-----Data -------> Hex value: 8 4 2 1 8 4 2 1 DATATRAC (Hex): | 1 | | 5 Binary: 0 0 0 1 0 1 0 1 Octal value: 4 2 1 4 2 Produces CODE: 5 2 Bits 11 through 17, of the label 031 control DATATRAC Hex bits: 5th Bit: 16 15 14 13 Bit values: 8 4 2 1 Assignment:
| Pad
| Pad
Fourth 22 21
24
23
8 | 0 1
4 | 1 4
2
20
1
8 | 0 4
6 1 2 6
19 18 17 ----->| Pad 4 2 1 | 6 1 1 2 1 3
0 1
|
word, are assigned the following functions: 6th 12 8 Pad
11 10 9 4 2 1 | |<- |<--SDI |<--Altitude reporting, 1 = OFF
| | | | | |<--Ident, 1 = ON |<--Altitude port select, 1 = B
Note 2: You can set the XMT 1 label 203 data field bits 12 through 28 to any combination of 1 and 0. The RCV 1 label 203 word data field will reflect the XMT 1 word while the ATC-601 will show the altitude to the nearest 100 feet. The label 203 word data bit values are as follows: DATATRAC Hex *: | 2nd Hex value: 8 4 2 Bit: 29 28 27 26 Alt value:(sign bit; 0 = +) 65536 32768 16384 (in feet) DATATRAC Hex *: | 4th | | Hex value: 8 4 2 1 8 Bit: 20 19 18 17 16 Alt value 256 128 64 32 16 (in feet) Determine the altitude by totaling the bit value of all bits set to
| 1 25 8192
| 8 24 4096
5th 4 15 8
2 14 4
3rd 4 23 2048 | 1 13 2
| 8 12 1
| 1 21 512
2 22 1024 6th 4 11 **
2 10 **
| 1 09 **
1.
* The left-most Hex Data bit (bit 1) is determined by the parity bit 32, the SSM bits 31 and 30, and sign bit 29. Since bit 29 must always be a 0, this Hex bit must always be an odd number. The right-most bits (bits 7 and 8) are determined by the label. **= Not used Note 3: You will see a label 371 data word. This is the ARINC 429 Specific Equipment Identification word which is structured the same as other ARINC 429 words but conveys the following information: Bits 11 through 18 identify the equipment type. The code for ATC transponders is 18 therefore bits 14 and 15 are 1; the others are 0. Bits 19 through 24 convey a binary code identifying the equipment manufacturer. Collins’ is 6. Therefore bits 20 and 21 are 1; all others are 0. Bits 24 through 29 are reserved for purposes to be defined. When ARINC 572 altitude data is active, you will see a label 200 data word. This word reflects the ARINC 572 (Gillham code) altitude data. This word is structured the same as other ARINC 429 words, except bits 9 and 10 are part of the data field; i.e., there is no SDI. Bits 9,10, and 11 reflect the D1, D2, and D4 code bits respectively. Bits 13, 14, and 15 reflect the C-bits, bits 17, 18, and 19 reflect the B-bits, and 21, 22, and 23 reflect the A-bits.
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maintenance 523-0775657 Table 5-11 Acceptance Test Procedures, Using the DATATRAC 400 or DATATRAC 400H Databus Analyzer (Cont).
STEP
TITLE
2.0
Test set, Auto Test
PROCEDURE On ATC-601: • Press RUN/STOP to stop • Press AUTO TEST • Press RUN to start Note: This test requires a few seconds to run. It will stop automatically.
DESIRED RESULTS Ensure that all tests . See note below.
On test : • Set EXT STBY switch to STBY • Set POWER switch OFF On UUT: • Move the test set rf cable to the UUT top antenna connector and the rf termination to the bottom. On test : • Set POWER switch ON • Set EXT STBY switch to OPR On ATC-601: • Repeat the AUTO TEST
Ensure that all tests . See note below.
Note. The AUTO TEST sequence will indicate FAILED even when certain tests result in a NO REPLY condition. The NO REPLY conditions are the result of no ADLP (Airborne Data Link Processor) data in this setup. This same condition is likely to occur when using the ATC-601 as a ramp tester when testing an installation not equipped with an ADLP. To that the test can be seen as successful, proceed as follows: • When the test sequence is completed and the ATC-601 stops, as indicated by INTERR and REPLY lamps off, you will likely see a screen as follows: ** AUTO TEST - FAILED ** MODES TESTED - A,C,S FREQ: MODES ED - A,C,S ERP: MODES FAILED -> MTL: DIVERSITY ISOLATION: >40 dB Press RUN to start
1089.92 Mhz 55 Dbm -77 Dbm
(The FREQ, ERP, and MTL values can vary from UUT to UUT and to a lesser degree on UUT temperature.) the test results as follows: On the ATC-601, use the SELECT 6th up arrow or down arrow key to scroll through the following list of tests performed; the numbers are for reference purposes only and do not appear on the test set screen. If you use the down arrow, you will see the list in the order shown; from test 1 through test 19. If you use the up arrow key, you will see the list in reverse order, starting at test 19. You will likely notice that all tests ed except tests 13, 14, and 15 which had a NO REPLY. NO.
TEST NAME AND RESULT
1.0
**
REPLY DELAY TEST - ED
2.0
**
REPLY JITTER TEST - ED
TEST SPECIFICATION / DESCRIPTION **
**
MODE S: 128.00 (±0.25) µs ITM A: 128.00 (±0.25) µs (All others): 3.00 (±0.50) µs MODE S: =< 0.05 µs ITM: =< 0.06 µs
(All others): =< 0.1 µs 3.0
**
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ATCRBS REPLY TEST - ED
**
F1 TO F2 SPACING: 20.3 (±0.1) µs All PULSE WIDTH: 0.45 (±0.1) µs
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maintenance 523-0775657 Table 5-11 Acceptance Test Procedures, Using the DATATRAC 400 or DATATRAC 400H Databus Analyzer (Cont).
STEP
TITLE
NO.
TEST NAME AND RESULT
4.0
**
5.0
** ATC ONLY ALL-CALL TEST - ED **
The TDR-94/94D should not reply to this mode a and mode c only interrogation. ED indicates a correct (NO) response.
6.0
** MODE S ALL-CALL TEST - ED **
The TDR-94/94D should reply to this interrogation. ED indicates a correct response. UUT address previously determined in mode s interrogation, is sent to UUT in UF4 (Uplink Format 4) and verified in DF4 (Downlink Format 4) reply.
7.0
** INVALID ADDRESS TEST - ED **
UUT is interrogated with two addresses, both of which are different from the correct address. ED indicates UUT did not reply to interrogation.
8.0
** SPR ON/OFF TEST - ED **
UUT is interrogated first with SPR ON and verifies a proper reply, then with SPR OFF and verifies no reply. ED indicates UUT responded correctly.
9.0
**
MODE S UF0 TEST - ED
**
UUT is interrogated with mode S UF0, ing correct altitude as compared to previous mode c reply, correct address as compared to DF11 address, and correct format. ED indicates correct UUT response.
10.0
**
MODE S UF4 TEST - ED
**
UUT is interrogated with UF4, ing correct altitude as compared to previous mode c reply, correct address as compared to DF11 reply, and correct format. ED indicates correct UUT response.
11.0
**
MODE S UF5 TEST - ED
**
UUT is interrogated with UF5, ing the correct ID code as compared to previous mode a reply, correct address as compared to DF11 reply, and correct format. ED indicates correct UUT response.
12.0
**
MODE S UF11 TEST - ED
13.0
**
MODE S UF16 TEST - NO REPLY
**
(See test 15.)
14.0
**
MODE S UF20 TEST - NO REPLY
**
(See test 15.)
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PROCEDURE
DESIRED RESULTS
SLS LEVEL TEST - ED
TEST SPECIFICATION / DESCRIPTION UUT is interrogated with F2 (SLS) pulse at 9 dB below F1. UUT should reply to this interrogation. Then UUT is interrogated with F2 equal to F1. UUT should not reply. ED indicates correct response to both tests.
**
UUT is interrogated with UF11, ing correct address as compared to previous response, and correct format. ED indicates correct UUT response.
**
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maintenance 523-0775657 Table 5-11 Acceptance Test Procedures, Using the DATATRAC 400 or DATATRAC 400H Databus Analyzer (Cont).
STEP
TITLE
PROCEDURE
DESIRED RESULTS OR SETUP SCREEN
NO.
TEST NAME AND RESULT
15.0
**
MODE S UF21 TEST - NO REPLY
16.0
**
SQUITTER TEST - ED
17.0
**
FREQUENCY TEST - ED
**
Freq: 1090 (±1) MHz
18.0
**
DIVERSITY TEST - ED
**
ATC-601 monitors squitter pulses on active antenna port (as in test 16) and then monitors for intervening squitter pulses that are not greater than 20 dB below the active squitter. This test will always fail when the UUT is a TDR-94 (non diversity) because squitter is transmitter every second on the same antenna port. If you are testing a TDR-94D and the DL ANT/SGL ANT switch is set to SGL ANT, the test will also fail because this causes the unit to operate like a TDR-94. ED indicates a correct response from a TDR-94D.
19.0
**
MTL DIFFERENCE TEST - ED
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TEST SPECIFICATION / DESCRIPTION **
UUT is interrogated with UF16, UF20, and UF21. These formats are all related to the airborne data link function. This function has not been implemented. The TDR-94/94D will not reply to these interrogation formats. NOT REPLY should not be seen as a failure. When set for dual antenna operation, the TDR-94D transmits a squitter pulse once each second, alternating between top and bottom antenna ports. The ATC-601 verifies that one squitter pulse is received every 1.6 to 2.4 seconds. The test ANT SGL/DL switch must be in the DL position. When set for single antenna operation, or when testing a TDR-94, only the bottom antenna port is used. In this case the ATC-601 verifies that one squitter pulse is received every 0.6 to 1.4 seconds. When you change the ANT SGL/DL switch, you must cycle power to the UUT in order for it to take effect. ED indicates a correct UUT response.
**
**
ATC-601 verifies that the MTL difference between mode a and mode c responses is < 1.0 dB. At this point, another press of the arrow key will display the first item; either 1.0 or 18.0, depending on which arrow was used.
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maintenance 523-0775657 Table 5-11 Acceptance Test Procedures, Using the DATATRAC 400 or DATATRAC 400H Databus Analyzer (Cont).
STEP 3.0
TITLE Power output and Rcvr Sensi-tivity Test
PROCEDURE
DESIRED RESULTS OR SETUP SCREEN
On test select: • Set EXT STBY switch to STBY • Set POWER switch OFF On ATC-601: • Select POWER TEST • Press RUN to indicate TEST RUNNING ------>
** POWER TEST - Top Antenna ANTENNA UNITS ERP MTL *****
TEST RUNNING
** STATUS NO REPLY
*****
Note: If necessary, press SELECT (or SLEW) to select Top Antenna. Be sure that the ATC-601 rf cable is connected to the top antenna port and the rf termination is connected to the bottom port. On DATATRAC ( ): set screen ------>
-----------------RCV 1--(ALL)---12.5 KHz Lbl SDI 32-Hex Data-1 SSM Par msec ... no data present ... -ON-------------XMT 1 ----------12.5 KHz Lbl SDI 32-Hex Data-1 SSM Par msec 031 01 15 66 C1 98 00 1 0100 203 01 64 00 01 C1 11 1 0100
On test : • Set POWER switch ON • Set EXT STBY switch to OPR
** POWER TEST - Top Antenna ANTENNA UNITS ERP MTL Top dBm 55.7 -76.0
** STATUS ED
***** TEST RUNNING *****
After a few seconds, the ATC-601 shows ----> On ATC-601: Press RUN/STOP to stop the test. If the UUT is a TDR-94, skip this step. On test : • Set EXT STBY switch to STBY • Set POWER switch OFF • On TDR-94D mount: Swap the rf cable connection and termination on the UUT antenna ports. (Rf cable to bottom port and termination to top antenna port.) On test : • Set POWER switch to ON • Set EXT STBY switch to OPR On ATC-601: • Press RUN to indicate TEST RUNNING Wait a few seconds then press RUN/STOP to stop the test.
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If a failure is detected, a small arrow will be shown to the left of the offending parameter(s). Make a note of the test results, if a record is needed, and label it as applicable to the UUT bottom antenna port. The data displayed here will be overwritten on the next test. You should see a similar display on the ATC-601 except this data is applicable to the top antenna port. The data can be slightly different. See below for test tolerances and an explanation of a possible failure indication due to high sensitivity. Note: You may also select bottom antenna screen on the ATC-601. Note: You may see a marginal test failure if the UUT is relatively cold. In this case allow the unit to warm up a few minutes and then repeat the test.
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maintenance 523-0775657 Table 5-11 Acceptance Test Procedures, Using the DATATRAC 400 or DATATRAC 400H Databus Analyzer (Cont).
STEP 3.0 (cont’d)
TITLE Power output and Rcvr Sensi-tivity Test (cont’d)
PROCEDURE
DESIRED RESULTS OR SETUP SCREEN
The test tolerances are: ERP: > 48.5 dBm and < 57.0 dBm MTL: -73.0 (±4.0) dBm The ATC-601 will indicate that the UUT has FAILED if the MTL is more than -77.0 dBm or less than 71 dBm. Collins prefers, however, that a FAILURE should be reported only if the MTL is less than 71 dBm. Therefore, if you have a unit displaying an MTL of -77.1 or more, you should see that value as acceptable. Obviously, an MTL indication approaching -80 dBm or more may be cause for suspecting a problem with test set calibration. You may also see a failure because the ERP, Effective Radiated Power or Peak Pulse Power , is more than 57 dBm. Power measurements taken with a ramp tester can be confusing. The various test equipment manufacturers use different dimensions for displaying the test results, the test specifications are not always clear on how the test is to be performed to produce the specified result, and the test method; direct or radiation, yields different results. As in the case of MTL, an ERP slightly greater than 57 dBm ( e.g., 59 dBm max), using the direction connection method, should not be seen as cause for unit rejection. DO-181 specifies the transponder power output at the antenna. Testing a unit on the bench by direct connection to the antenna port yields a power reading at the transmitter output. The difference is, of course, antenna cable and connector losses. DO-181 specifies transponder power output in watts and dBW. The IFR ATC-601 displays power in dBm (ERP). The TIC-48/-49 displays power in watts. The following chart may be useful for proper test evaluation:
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Watts
dBW
dBm
50 70 100 125 150 200 250 300 350 400 450 500
16.99 18.45 20.00 20.97 21.76 23.01 23.98 24.77 25.44 26.02 26.53 26.99
46.99 48.45 50.00 50.97 51.76 53.01 53.98 54.77 55.44 56.02 56.53 56.99
TDR-94/94D Spec
(Min for airplanes limited to 15 000 ft and 175 kts.) Minimum at antenna (ramp testing)
Minimum direct (on bench)
Maximum at antenna
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maintenance 523-0775657 Table 5-11 Acceptance Test Procedures, Using the DATATRAC 400 or DATATRAC 400H Databus Analyzer (Cont).
STEP 4.0
TITLE Gillham Altitude Test
PROCEDURE On ATC-601: select
DESIRED RESULTS OR SETUP SCREEN ** ATCRBS REPLY TEST **
ATCRBS REPLY TEST ----------->
(lines 2-4 are irrelevant) CODE=
ALT=
[
]
Press RUN to start
On test select: • ALT TYPE SELECT: ARINC 572 • ARINC 572 ALT IN: TO TDR On DATATRAC ( ): • Set XMT 1 label 203 word to OFF • Set RCV 1 and XMT 1 screen ------>
-----------------RCV 1--(ALL)---12.5 KHz Lbl SDI 32-Hex Data-1 SSM Par msec ... no data present ...
On test : • Set all ARINC 572 switches to OFF: Then set A4, C2, C4, and B4 to SEL. • Set POWER to ON • Set EXT STBY switch to OPR
The XFEED OUT lamp turns on. The ATC-601 REPLY lamp indicates that UUT is responding to interrogations.
DATATRAC ( ) RCV 1 screen shows: ------------------->
----------------RCV 1--(ALL)---12.5 Lbl SDI 32-Hex Data-1 SSM Par 203 01 E0 B8 61 C1 11 1 031 01 F5 66 81 98 11 1
-ON-------------XMT 1 ----------12.5 KHz Lbl SDI 32-Hex Data-1 SSM Par msec 031 01 15 66 C1 98 00 1 0100
KHz msec 0200 0200
(ignore any other displayed labels) On ATC-601: • Press RUN. Screen shows: -------------------->
** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE=5263 *****
ALT=5900 FT TEST RUNNING
[4460] *****
(The CODE 5263 depends on your selection in the 031 XMT 1 word. See note 1 under step 1.2 above) At this step you are asked to toggle each of the ARINC 572 switches and the altitude display. You should also watch the RCV 1 data word on the DATATRAC ( ) display. By cycling each switch between OFF and SEL you should see the ATC601 display and the DATATRAC ( ) 203 data word change. If the displays do not change for a particular switch, this would indicate either an open or a shorted code line. If the wrong altitude is shown, this would suggest that the code line is affecting another line; i.e., causing two or more inputs to change simultaneously. In either case the UUT, the test , or the interconnecting cable needs repair. Set each switch as shown in the listing below to the (position) shown, and back, and the altitude display at both positions. The altitude display should always revert to the initial display when the switch is returned to its original position. There is no serious need to the correctness of the RCV word as long as the ATC-601 display is correct. SWITCH Initial A1 (SEL) A2 (SEL) A4 (OFF) C1 (SEL) C2 (OFF)
DISPLAYED ALTITUDE 5,900 FT [4460] 23,600 FT [5460] 7,600 FT [6460] -400 FT (0460] none (blank; this is invalid) 5,800 FT [4440]
SWITCH C4 (OFF) B1 (SEL) B2 (SEL) B4 (OFF) D2 (SEL) D4 (SEL)
DISPLAYED ALTITUDE 6,000 FT [4420] 3,600 FT [4560] 5,600 FT [4660] 6,600 FT [4060] 119,600 FT [4462] 55,600 FT [4464]
For addtional information on Gillham code structure, refer to paragraph 5.7 in this section.
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maintenance 523-0775657 Table 5-11 Acceptance Test Procedures, Using the DATATRAC 400 or DATATRAC 400H Databus Analyzer (Cont).
STEP 5.0
TITLE CSDB tuning test
PROCEDURE
This test cannot be performed using a DATATRAC 400/400H because these instruments are not capable of transmitting or receiver CSDB data. However, as an acceptable alternative, you can use a CTL-92/92A, connected to the test using the cable shown in figure 907. • Turn power off and connect CTL-92/92A to test . Be sure CTL-92/92A mode knob is set to OFF. • Turn power on and set the CTL-92/92A mode knob to ALT. On the CTL: • Set the CTL-92/92A to 5263 or any desired ident code.
5.1
CSDB altitude test
DESIRED RESULTS OR SETUP SCREEN
** ATCRBS REPLY TEST **
(lines 2-4 are irrelavent) CODE=5263 *****
ALT=32 800 FT [1344] TEST RUNNING *****
On test : • Set CONTROL DATA SELECT to CSDB • Set OUTPUT PORT SELECT to CSDB PORT 1 • Set ALT TYPE SELECT to CSDB • Set ARINC 572 ALT IN to TO CTL • Set SOURCE SELECT to CTL
The CODE 5263 depends on your selection on the CTL92/92A code select knobs. See note 1 under step 1.2 above. The ALT display depends on the altitude selection on the test ARINC 572 ALT IN switches.
On the test : • Set OUTPUT PORT SELECT to CSDB PORT 2
Be sure that the ACT display, on the CTL-92/92A, does not flash. A flashing ACT at either port selection indicates that output port has failed. If both ports flash, there may be a problem with the test wiring or the CTL input.
Be sure that the ACT display, on the CTL-92/92A does not flash. A flashing ACT indicates that the control label 1F data, from the TDR, does not agree with the CLT-92/92A output label 1E data to the TDR. Only one of the two data CTL input ports is being used; pins U/V.
In this altitude test configuration, Gillham altitude data is being supplied to the CTL (ARINC 572 ALT IN to CTL). The CTL converts this data to CSDB and supplies it to the TDR via the CSDB data output port (only 1 port is used; pins S/R). The CSDB altitude data is being read on the control bus input (SOURCE SELECT to CTL). You can this by setting the CTL mode switch to ON. If you suspect a problem with the altitude data, check the following:
On the test : • Set ARINC 572 ALT IN to TO TDR • Set ALT TYPE SELECT to ARINC 572 • Set SOURCE SELECT to SEL
The ATC-601 ALT display should be the same as above since the ultimate source of altitude information is the same in both tests. If it is different here, suspect a problem with one or more of the altitude discrete inputs to the CTL. If you encounter such a problem, you can identify the defective discrete by returning these three switches to the settings above and then performing the ARINC 572 switching sequence shown following step 4.0 above.
On test : • Set power to OFF • Disconnect the CTL-92/92A from the test • Set CONTROL DATA SELECT ARINC PORT to PA • Set OUTPUT PORT SELECT to ARINC 429 PORT A
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maintenance 523-0775657 Table 103. Acceptance Test Procedures, Using the DATATRAC 400 or DATATRAC 400H Databus Analyzer (Cont).
STEP 6.0
TITLE ARINC 429 Altitude Test
PROCEDURE On ATC-601: select ATCRBS REPLY TEST and press RUN to indicate TEST RUNNING --------->
DESIRED RESULTS OR SETUP SCREEN ** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE= *****
ALT= [ ] TEST RUNNING *****
On test : • Set EXT STBY switch to STBY • Set POWER switch to OFF • ALT TYPE SELECT: ARINC 429 • OUTPUT PORT SELECT: ARINC 429 PORT A On DATATRAC ( ): • Set XMT 1 to ON • Setup screen ------>
-----------------RCV 1--(ALL)---12.5 KHzLbl SDI 32-Hex Data-1 SSM Par msec ... no data present ...
On test : • Set POWER to ON • EXT STBY to OPR
The XFEED OUT lamp turns on. The ATC-601 REPLY lamp indicates that UUT is responding to interrogations.
The ATC-601 screen shows: --->
-ON-------------XMT 1 ----------12.5 KHz Lbl SDI 32-Hex Data-1 SSM Par msec 031 01 15 66 C1 98 00 1 0100 203 01 64 00 01 C1 11 1 0100
** ATCRBS REPLY TEST **
(lines 2-4 are irrelavent) CODE=5263 *****
ALT=32 800 FT [1344] TEST RUNNING *****
(The CODE 5263 depends on your selection in the 031 XMT 1 word. See note 1 under step 1.2 above.) DATATRAC ( ) RCV 1 screen shows: ------>
-----------------RCV 1--(ALL)---12.5 KHz Lbl SDI 32-Hex Data-1 SSM Par msec 203 01 64 00 01 C1 11 1 0200
(ignore any other displayed labels)
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maintenance 523-0775657 Table 103. Acceptance Test Procedures, Using the DATATRAC 400 or DATATRAC 400H Databus Analyzer (Cont).
STEP 6.1
TITLE ARINC Control Discretes Tests (cont’d)
PROCEDURE On the test : • Be sure the SOURCE SELECT switch is set to SEL. On the test : • Set the REP ALT SEL switch to PB
DESIRED RESULTS OR SETUP SCREEN ** ATCRBS REPLY TEST **
(lines 2-4 are irrelavent) CODE=5263 *****
ALT=32 800 FT [1344] TEST RUNNING *****
Notice that the ATC-601 altitude display blanks. Note: At this point the UUT is configured to report altitude data from port B. There is none so the display blanks.
On the test : • Move the parallel connection from the PRIMARY DIGITAL ALTITUDE SOURCE jack to the ALTERNATE DIGITAL ALTITUDE SOURCE jack.
Notice that the ATC-601 altitude display returns.
On the test : • Set the REP ALT SEL switch to PA
Notice that the ATC-601 altitude display blanks.
Note: This verifies that UUT is configured to report altitude data being supplied on port B.
Note: UUT is returned to port A. This series of steps has verified that the Reporting Altitude discrete is switchable.
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On the test : • Set the SOURCE SELECT switch to CTL
Notice that the ATC-601 altitude display returns.
On the test : • Disconnect the parallel connection from the ALTERNATE DIGITAL ALTITUDE SOURCE jack. (Wait about 5 seconds)
Notice that the ATC-601 altitude display remains.
On DATATRAC ( ): • Set the SOURCE SELECT switch to SEL.
Notice that the ATC-601 altitude display blanks.
On test : • Reconnect the parallel connection to the ALTERNATE DIGITAL ALTITUDE SOURCE jack.
Notice that the ATC-601 altitude display remains blanked.
Note: This switches the UUT to the altitude data supplied on the control port.
Note: This verifies the previous step; that altitude is being drawn from the control port; all other sources are disconnected.
Note: This verifies that the Source Select Discrete is switchable.
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maintenance 523-0775657 Table 103. Acceptance Test Procedures, Using the DATATRAC 400 or DATATRAC 400H Databus Analyzer (Cont).
STEP
TITLE
6.1 (cont’d)
ARINC Control Discretes Tests (cont’d)
PROCEDURE
DESIRED RESULTS OR SETUP SCREEN
On test : • Set the AUTO ALT switch to SEL (-003 UUT units only)
Notice that the ATC-601 altitude display returns.
On test : • Set the AUTO ALT switch to OFF (-003 UUT units only)
Notice that the ATC-601 altitude display blanks.
On the DATATRAC: • Set the XMT 1 label 031 word to -------->
-ON-------------XMT 1 ----------12.5 KHz Lbl SDI 32-Hex Data-1 SSM Par msec 031 01 95 66 E1 98 00 1 0100
Note: This enables the automatic altitude port select feature and verifies that the UUT does switch to alternate port B even though port A is the selected port.
Note: This enables the AUTO ALT discrete is switchable.
Notice that the ATC-601 altitude display returns. Note: This digitally switches the UUT to port B. If this test is correct while the earlier test of port B altitude failed, suspect a problem with the Reporting Altitude Select discrete. If both tests failed, suspect a problem with the altitude data receivers. On test : • Set EXT STBY switch to STBY. • Set the POWER switch OFF. • Set the AUTO ALT switch to OFF. On DATATRAC ( ): • Set the XMT 1 label 031 word to ------>
-ON-------------XMT 1 ----------12.5 KHz Lbl SDI 32-Hex Data-1 SSM Par msec 031 01 15 66 C1 98 00 1 0100
If you wish, you can set the XMT 1 label 203 data field bits 12 through 28 to any combination of 1 and 0. The RCV 1 label 203 word data field will follow the XMT 1 word exactly while the ATC-601, set to the ATCRBS REPLY TEST mode, will show the altitude to the nearest 100 feet. When set to the MODE UF0 TEST, the ATC-601 displays altitude to the nearest 25
feet. The label 203 bit values are shown in note 2 following step 1.2. To 1. 2. 3. 4. 5. 6.
simulate any altitude up to about 131,000 feet: Select the desired altitude. Find the data bit with the maximum bit value less than the selected altitude. Make a note of that bit number. Subtract that bit value from your selected value. Find the next bit with the maximum bit value less than the remainder. Make a note of that bit number. Subtract that bit value from your remainder. Repeat steps 4 and 5 until the remainder is 0.
In the XMT 1 label 203 data word, set all noted bits to 1. You should see your selected altitude, to the nearest 100 feet, displayed on the ATC-601. 7.0
ARINC 575 Altitude Test
On test : • SOURCE SELECT: SEL • ALT TYPE SELECT: ARINC 429 On DATATRAC ( ): • Set screen ------> Note: The binary data format is retained here to emphasize the similarity between ARINC 429 and ARINC 575. If you are more comfortable with the Hex data format, feel free to use it instead.
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-----------------RCV 1--(ALL)---12.5 KHz Lbl SDI 29--Binary Data--11 SSM Par msec ... no data present ... -ON--------------XMT 1----------12.5 KHz Lbl SDI 29--Binary Data--11 SSM Par msec 031 01 0000000111011111011 00 1 0100 203 01 0010001010101010100 00 1 0100
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maintenance 523-0775657 Table 103. Acceptance Test Procedures, Using the DATATRAC 400 or DATATRAC 400H Databus Analyzer (Cont).
STEP 7.0 (cont’d)
TITLE ARINC 575 Altitude Test (cont’d)
PROCEDURE
DESIRED RESULTS OR SETUP SCREEN
On test : • Connect parallel control cable to PRIMARY DIGITAL ALTITUDE SOURCE jack. • Set POWER switch to ON. • Set EXT STBY switch to OPR. On ATC-601: • Select ATCRBS REPLY TEST and press RUN to indicate TEST RUNNING. ATC-601 screen --------> On test : • Set ALT TYPE SELECT switch to ARINC 575 On DATATRAC: • Set XMT 1 label 203 word --------> (just change the SSM to 00) ATC-601 screen -------->
** ATCRBS REPLY TEST **
(lines 2-4 are irrelavent) CODE=5263 *****
-ON--------------XMT 1----------12.5 KHz Lbl SDI 29--Binary Data--11 SSM Par msec 203 01 0010001010101010100 00 1 0100
** ATCRBS REPLY TEST **
(lines 2-4 are irrelavent) CODE=5263 *****
DATATRAC screen --------->
ALT=35,500 FT [5524] TEST RUNNING *****
ALT=17,700 FT [3740] TEST RUNNING *****
-----------------RCV 1--(ALL)---12.5 KHz Lbl SDI 29--Binary Data--11 SSM Par msec 203 01 0001000101010101010 11 1 0100 | | | | | | | / / / / / / / | | | | | | | -ON--------------XMT 1----------12.5 KHz Lbl SDI 29--Binary Data--11 SSM Par msec 203 01 0010001010101010100 00 1 0100
In addition to testing the altitude type select discrete, this test illustrates the differences between ARINC 429 and ARINC 575 data. Notice that the bits in the RCV 1 label 203 word (above) are offset to the right by one bit from the XMT 1 label 203 word and the SSM code is 11 as opposed to the 00 in the XMT 1 word. In ARINC 575, the LSB is bit 13; in ARINC 429 the LSB is bit 12. In ARINC 575, bits 30 and 31 determine the sign; 00 being positive. Notice also, that the altitude displayed on the ATC-601 corresponds to the code in the RCV 1 word; not the XMT 1 word. This is also due to the UUT being configured for ARINC 575 and thus the bit values are offset by 1 bit position which has the effect of changing the altitude by a factor of 1/2. On test : • Set ALT TYPE SELECT switch to ARINC 429 On DATATRAC: • Set XMT 1 label 203 word ----> ATC-601 screen:
-ON--------------XMT 1----------12.5 KHz Lbl SDI 29--Binary Data--11 SSM Par msec 203 01 0010001010101010100 11 1 0100
** ATCRBS REPLY TEST **
(lines 2-4 are irrelavent) CODE=5263 *****
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ALT=35,500 FT [5524] TEST RUNNING *****
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maintenance 523-0775657 Table 5-11 Acceptance Test Procedures, Using the DATATRAC 400 or DATATRAC 400H Databus Analyzer (Cont).
STEP 8.0
TITLE Mode S Address Discretes Test
PROCEDURE
DESIRED RESULTS OR SETUP SCREEN
On the test : • Set POWER switch OFF • Set all test mode s address switches to SEL except switch P1-56; set it to OFF. • Set POWER switch ON On ATC-601: • Set for MODE S ALL CALL TEST ------->
** MODE S ALL CALL TEST - NO REPLY ALL CALL ADDRESS = [ NUMBER = Press RUN to start
On ATC 601: • Press RUN • Note screen ----->
** MODE S ALL CALL TEST ALL CALL ADDRESS = FFFFFE TAIL NUMBER =
** ]
TAIL
ED ** [77777776]
****** TEST RUNNING *****
The remainder of this step should be seen as optional unless you have reason to suspect a failure in one or more of the address discrete lines. The procedure will require a few minutes because of the delay involved in cycling power between each switch setting.
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On test : • Set POWER switch OFF. • Set each triad of address switches for an octal digit 6. • Set POWER switch ON.
After a few seconds, UUT begins to reply and shortly thereafter the ATC-601 screen shows the following address:
On test : • Set POWER switch OFF. • Set each triad of address switches for an octal digit 4. • Set POWER switch ON.
After a few seconds, UUT begins to reply and shortly thereafter the ATC-601 screen shows the following address:
On test : • Set POWER switch OFF. • Set each triad of address switches for an octal digit 0, except the eighth triad which is set to 1. • Set POWER switch ON.
After a few seconds, UUT begins to reply and shortly thereafter the ATC-601 screen shows the following address:
ALL CALL ADDRESS = DB6DB6
ALL CALL ADDRESS = 924924
ALL CALL ADDRESS = 000001
[66666666]
[44444444]
[00000001]
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maintenance 523-0775657 Table 5-11 Acceptance Test Procedures, Using the DATATRAC 400 or DATATRAC 400H Databus Analyzer (Cont).
STEP 9.0
TITLE TCAS / NO TCAS Discrete Select and TCAS Bus Test
PROCEDURE
DESIRED RESULTS
On test : • Set POWER switch OFF On DATATRAC ( ): • Same setup as STEP 1.1. ATC-601 is not needed for this test but can be left on. On test : • Set POWER switch ON
After a few seconds the RCV 1 portion of the DATATRAC ( ) screen shows:
After data appears on the RCV 1 display, press RCV and then ENT and use the down arrow key to scroll the words so that you can see the 350 word.
-----------------RCV 1--(ALL)---12.5 KHz Lbl SDI 32-Hex Data-1 SSM Par msec 350 01 00 00 01 17 11 1 0200
On test : • Set POWER switch to OFF • Set TCAS/NO TCAS switch to TCAS On DATATRAC ( ): • Press RCV and then ENT On test : • Set POWER switch to ON
After a few seconds the RCV 1 portion of the DATATRAC ( ) screen shows: (use down arrow key to scroll words) -----------------RCV 1--(ALL)---12.5 KHz Lbl SDI 32-Hex Data-1 SSM Par msec 350 01 68 B3 01 17 11 1 0200 |<---diagnostic code B3
This display shows a diagnostic B3 which is interpreted: TCAS Bus Inactive. This verifies that the discrete properly configures the unit for operation with a TCAS. However, no TCAS data is being supplied in this step, therefore, the unit declares a B3 diagnostic.
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maintenance 523-0775657 Table 5-11 Acceptance Test Procedures, Using the DATATRAC 400 or DATATRAC 400H Databus Analyzer (Cont).
STEP 9.0 (cont’d)
TITLE TCAS Bus Test, XPDR to TCAS
TCAS to XPDR Bus Test
PROCEDURE
DESIRED RESULTS
Connect the DATATRAC RCV 1 to the TCAS OUT jack. that the data word labels are detectable as shown -->.
-----------------RCV 1--(ALL)----100 KHz Lbl SDI 32-Hex Data-1 SSM Par msec 275 00 80 00 00 BD 00 1 0150 276 10 80 F8 02 7D 00 1 0150 350 01 68 B3 01 17 11 1 0150
Note: Except for the diagnostic code in the label 350 data word, the data content is not important. It is quite likely that the data will be different. The presence of the data word labels shown verifies that the TCAS data bus output is active and appears to be normal.
Notice the higher speed. Other labels may also be present.
Note: In this step you need the capability of transmitting data to two separate input ports simultaneously and at different speeds; the 031 control word must be low speed (12.5-kbps) while the TCAS label 274 data words must be high speed (100-kbps). All DATATRAC instruments, as well as the JC Air 429E, can transmit at either of these speeds but only the DATATRAC 400 can do so on two separate ports simultaneously. Otherwise, you will need two simulators. If you do not have this capability, you may not be able to the integrity of the TCAS bus input port. If you are using a DATATRAC 400, or have access to a second bus simulator, connect your second transmitter port or data bus simulator to the TCAS IN and setup as shown -------->:
-ON-------------XMT 2 -----------100 KHz Lbl SDI 32-Hex Data-1 SSM Par msec 274 00 18 00 00 3D 00 1 0100
On bus reader RCV display:
After a few seconds, the 350 word shows:
Note: The objective is to that the UUT recognizes a valid TCAS label 274 word and declares this by removing the diagnostic B3.
-----------------RCV 1--(ALL)---12.5 KHz Lbl SDI 32-Hex Data-1 SSM Par msec 350 01 68 00 01 17 11 1 0150 |<---diagnostic code 00
On the bus reader: Set the XMT 2 word to OFF
After a few seconds, notice that the B3 diagnostic returns.
Note: Be sure to set the higher speed.
Note: Disconnect XMT 2 from the TCAS IN jack and reconnect RCV 1 to the DATA BUS OUTPUT port. Final step in this test, all setups
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On test : • Set POWER switch to OFF • Set TCAS/NO TCAS switch to NO TCAS On DATATRAC ( ): • Press RCV and then ENT On test : • Set POWER switch to ON
After a few seconds, the original 350 word returns: -----------------RCV 1--(ALL)---12.5 KHz Lbl SDI 32-Hex Data-1 SSM Par msec 350 01 00 00 01 17 11 1 0200
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maintenance 523-0775657 Table 5-11 Acceptance Test Procedures, Using the DATATRAC 400 or DATATRAC 400H Databus Analyzer (Cont).
STEP 10.0
TITLE Side 1/ Side 2 Discrete Test
PROCEDURE
DESIRED RESULTS
On test : • Set POWER switch OFF • Be sure SIDE 1/SIDE 2 switch is set to SIDE 1. On DATATRAC ( ): • Same setup as STEP 9.0. On ATC-601: • Set for ATCRBS REPLY TEST screen -->
On test : • Set POWER switch ON
** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE= *****
ALT= TEST RUNNING
[ *****
]
After a few seconds, X FEED OUT and ATC-601 REPLY lamps light and the ATC-601 shows: ** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE=5263 ALT=32,800 FT [1344] ***** TEST RUNNING *****
On test : • Set POWER switch to OFF • Set SIDE 1/SIDE 2 switch to SIDE 2 • Set POWER switch to ON
Note that unit does not reply (X FEED OUT lamp and REPLY lamps are off and no altitude is displayed on ATC-601). Wait about 10 seconds. Note: UUT does not respond because the SDI and side strapping do not agree. Note: Be sure to allow adequate time for the U to reinitialize properly between power off and power on. The SIDE 1/2 strap is one of several that are monitored only at processor initialization. Therefore, if this tests fails, cycle power again but allow more time between power off and power on.
On DATATRAC ( ): • On XMT 1, label 031 word, set the SDI to 10 and press ENTER
Notice that unit begins to reply almost immediately (XFEED OUT lamp turns on and ATC-601 REPLY lamp lights). Note: UUT responds because the SDI and side strapping agree.
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On DATATRAC ( ): • On XMT 1, label 031 word, set SDI to 01 and press ENTER.
Notice that unit stops replying (X FEED OUT lamp and ATC-601 REPLY lamps turn off).
On test : • Set POWER switch OFF • Set SIDE 1/SIDE 2 switch to SIDE 1 • Set POWER switch ON
After a few seconds, X FEED OUT and ATC-601 REPLY lamps light and the ATC-601 shows that the UUT is replying.
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STEP 11.0
TITLE AIR/ GND Discrete Test
PROCEDURE
DESIRED RESULTS
On test : • Set POWER switch OFF • TDR ALT SOURCE: EXT DIRECT • ALT TYPE SELECT: ARINC 429 On DATATRAC ( ): • Same setup as STEP 9.0. On ATC-601: • Set for MODE S UF4 TEST screen ----->
** MODE S UF4 TEST - NO REPLY ** DF FS= ADDRESS= *****
On test : • Set POWER switch ON ATC-601 screen shows ----->:
DR=
UM=
TEST RUNNING
AC= *****
After a few seconds, X FEED OUT and ATC-601 REPLY lamps light and the ATC-601 shows: ** MODE S UF4 TEST - ED ** DF 4 FS=0 DR=00 UM=00 ADDRESS=000001 *****
TEST RUNNING
AC=32,775 FT *****
Note: Initially the screen will show FS=2 for about 2 seconds and then change to FS=0. On test : • Set AIR/GND switch to GND
After a few seconds, the ATC-601 shows: ** MODE S UF4 TEST - ED ** DF 4 FS=1 DR=00 ADDRESS=000001 *****
UM=00 AC=32,775 FT
TEST RUNNING
*****
Of particular significance here is the FS (flight status) indication. For a detailed description of each of these message fields, refer to the Theory of Operation section. On test : • Set AIR/GND switch to AIR
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After a few seconds, notice that the ATC-601 FS field again shows 0.
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maintenance 523-0775657 Table 5-11 Acceptance Test Procedures, Using the DATATRAC 400 or DATATRAC 400H Databus Analyzer (Cont).
STEP 12.0
TITLE DL ANT/ SGL ANT Discrete Test (TDR-94D only)
PROCEDURE
DESIRED RESULTS
On test : • Set POWER switch OFF On DATATRAC ( ): • Same setup as STEP 9.0. On ATC-601, set for SQUITTER TEST screen -----> Be sure the ATC-601 is connected to the top antenna port. On test : • Set DL ANT/SGL ANT switch to DL ANT • Set POWER switch ON You can watch the PERIOD display for a time.
** SQUITTER TEST - NO REPLY ** PERIOD = SECONDS TAIL NUMBER = SQUITTER ADDRESS= [ *****
TEST RUNNING
]
*****
After a few seconds, the ATC-601 screen shows: See note below. ** SQUITTER TEST - ED PERIOD = 2.00 SECONDS TAIL NUMBER = SQUITTER ADDRESS= [ *****
TEST RUNNING
** ]
*****
See the note at the end of this step for test tolerances. On test : • Set POWER switch OFF • Set DL ANT/SGL ANT switch to SGL ANT • Set POWER switch ON
After a few seconds, the ATC-601 screen shows: ** SQUITTER TEST - FAILED PERIOD = SECONDS TAIL NUMBER = SQUITTER ADDRESS= [ *****
TEST RUNNING
** ]
*****
Note: This test is intended to fail. When the UUT is set for single antenna operation, there is no transmission from the top antenna port. Therefore, if this test indicates ED, recheck all switch settings or suspect a problem with the SGL/DL ANT select strap. It should not . On test : • Set POWER switch OFF On ATC-601: • Press RUN to stop the test. • Remove rf terminator from bottom antenna connector • Connect ATC-601 cable to bottom antenna connector • Connect rf terminator to top antenna connector
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maintenance 523-0775657 Table 5-11 Acceptance Test Procedures, Using the DATATRAC 400 or DATATRAC 400H Databus Analyzer (Cont).
STEP 12.0
TITLE DL ANT /SGL ANT Discrete Test (cont’d) (TDR-94D only)
PROCEDURE On test : • Set POWER switch ON On ATC-601: • Press RUN to start the test.
DESIRED RESULTS After a few seconds, the ATC-601 screen shows: See note below. ** SQUITTER TEST - ED PERIOD = 1.00 SECONDS TAIL NUMBER = SQUITTER ADDRESS= [ *****
On test : • Set POWER switch OFF • Set DL ANT/SGL ANT switch to DL ANT • Set POWER switch ON
TEST RUNNING
** ]
*****
After a few seconds, the ATC-601 screen shows: See note below. ** SQUITTER TEST - ED PERIOD = 2.00 SECONDS TAIL NUMBER = SQUITTER ADDRESS= [ *****
TEST RUNNING
** ]
*****
Note: The PERIOD value tends to vary somewhat in all cases. When the UUT is set for dual antenna operation and the ATC-601 is monitoring the top or the bottom antenna port, the value can vary from 1.6 to 2.4. When the TDR-94D is set for single antenna operation, or the UUT is a TDR-94, there is no transmission from the top antenna port and and the transmission PERIOD from the bottom antenna port can vary from 0.6 to 1.4. 13.0
Burst Tune and CrossFeed In Discrete Test
On test : • Set POWER switch OFF • Set CONTROL DATA SELECT to PA • Set ALT TYPE SELECT to ARINC 429 • Set SOURCE SELECT to SEL On DATATRAC ( ): • Same setup as STEP 1.1. On ATC-601, set for SQUITTER TEST screen -----> If necessary, reconnect ATC-601 to top antenna connector, with terminator on bottom connector.
** SQUITTER TEST - NO REPLY ** PERIOD = SECONDS TAIL NUMBER = SQUITTER ADDRESS= [ ] *****
TEST RUNNING
*****
On test : • Set POWER switch ON
After a few seconds, the test X FEED OUT and the ATC-601 REPLY lamps light indicating that the unit is replying. The ATC-601 screen data indicates ED.
On test : • Set X FEED IN/OUT switch to IN
Notice that both X FEED lamps are lighted.
On DATATRAC ( ): • Set XMT 1 to OFF
Notice that the X FEED OUT and ATC-601 REPLY lamps turns off (X FEED IN stays on).
(With the cursor on the 1, press ENT)
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maintenance 523-0775657 Table 5-11 Acceptance Test Procedures, Using the DATATRAC 400 or DATATRAC 400H Databus Analyzer (Cont).
STEP 13.0 (cont’d)
14.0
TITLE Burst Tune and CrossFeed In Discrete Test (cont’d)
Output Port Discrete Test
PROCEDURE
DESIRED RESULTS
On DATATRAC ( ): • Set XMT 1 to ON
Notice that the X FEED IN and OUT and REPLY lamps are lighted.
On test : • Set X FEED IN/OUT switch to OUT • Set BURST TUNE switch to ON On DATATRAC ( ): • Set XMT 1 to OFF
Notice that UUT continues to reply. Watch the unit for a few seconds.
On test : • Set BURST TUNE switch to OFF
Notice that UUT stops replying (X FEED OUT and REPLY lamps turn off).
On test : • Set BURST TUNE switch to ON
Notice that UUT does not reply (X FEED OUT and REPLY lamps do not light).
On DATATRAC ( ): • Set XMT 1 to ON
Notice that UUT replys (X FEED OUT and REPLY lamps are on).
On test : • Set BURST TUNE switch to OFF On DATATRAC ( ): • Set XMT 1 to OFF
Notice that UUT stops replying (X FEED OUT and REPLY lamps are off).
On test : • Set BURST TUNE switch to ON On DATATRAC ( ): • Set XMT 1 to ON
X FEED OUT lamp flashes while XMT 1 is on .
On test : • Set XMT 1 to OFF
X FEED OUT lamp remains off when XMT is OFF.
On test : • Set BURST TUNE switch to OFF • Set SOURCE SELECT switch to SEL • ALT TYPE SELECT: ARINC 429 • CONTROL DATA PORT SEL: PA • OUTPUT PORT SELECT: ARINC 429 PORT A On DATATRAC ( ): • The same as STEP 1.1 • Set XMT 1 to ON On ATC-601, set for SQUITTER TEST screen ----->
** SQUITTER TEST - NO REPLY ** PERIOD = SECONDS TAIL NUMBER = SQUITTER ADDRESS= [ *****
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TEST RUNNING
]
*****
On test : • Set POWER switch ON
After a few seconds, the test X FEED OUTand the ATC-601 REPLY lamps light indicating that the unit is replying. The ATC-601 screen data indicates ED.
On test : • Set OUTPUT PORT SELECT switch to ARINC 429 PORT B
Notice that there is no change in the test result; X FEED OUT and REPLY lights are on and ATC-601 display does not change.
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maintenance 523-0775657 Table 5-11 Acceptance Test Procedures, Using the DATATRAC 400 or DATATRAC 400H Databus Analyzer (Cont).
STEP 15.0
TITLE Control Data Input Port Select Discrete Test
PROCEDURE
DESIRED RESULTS
On test : • Set POWER switch OFF • Set SOURCE SELECT switch to SEL • ALT TYPE SELECT: ARINC 429 • CONTROL DATA SELECT: ARINC PORT PA On DATATRAC ( ): • Same setup as for STEP 9.0. On ATC-601, set for SQUITTER TEST screen ----->
** SQUITTER TEST - NO REPLY ** PERIOD = SECONDS TAIL NUMBER = SQUITTER ADDRESS= [ ] *****
16.0
Manual STBY Discrete Test
TEST RUNNING
*****
On test : • Set POWER switch ON
After a few seconds, the test X FEED OUTand the ATC-601 REPLY lamps light indicating that the unit is replying. The ATC-601 screen data indicates ED.
On test : • Set CONTROL DATA SELECT switch to ARINC PORT PB
Notice that there is no change in the test result; X FEED OUTand REPLY lights are on and ATC-601 display does not change.
On test : • Set CONTROL DATA SELECT switch to ARINC PORT PC
Notice that there is no change in the test result; X FEED OUT and REPLY lights are on and ATC-601 display does not change.
On test : • Set EXT STBY switch to STBY • Set POWER switch OFF • Set CONTROL DATA SELECT switch to ARINC PORT PA On DATATRAC ( ): • Same setup as for STEP 9.0. On ATC-601: • Set for ATCRBS REPLY TEST screen ---------->
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** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE= *****
ALT= [ ] TEST RUNNING *****
On test : • Set POWER switch ON • Set EXT STBY switch to OPR
After a few seconds, the test X FEED OUTand the ATC-601 REPLY lamps light indicating that the unit is replying. The ATC-601 screen data indicates ED.
On test : • Set EXT STBY switch to STBY
Note that X FEED OUT lamp and ATC-601 REPLY lamps turn off and ATC-601 indicates NO REPLY. See note below.
On test : • Set EXT STBY switch to OPR
Note that X FEED OUT lamp and ATC-601 REPLY lamps light almost immediately and ATC-601 indicates ED.
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STEP 17.0
TITLE Max Airspeed Test
PROCEDURE
DESIRED RESULTS
On test : • Set POWER switch OFF • ALT TYPE SELECT: ARINC 429 • Be sure that all three MAX AIRSPEED switches are set to OFF. On DATATRAC ( ): • Same setup as for STEP 9.0. (The DATATRAC is used here only for tuning data.) On ATC-601: • Set for MODE S UF0 TEST screen >
** MODE S UF0 TEST - NO REPLY ** DF
VS= ADDRESS= *****
On test : • Set POWER switch ON
RI=
AC=
TEST RUNNING
*****
After a few seconds, the test X FEED OUT lamp and the ATC-601 REPLY lamps light indicating that the unit is replying.
Note the ATC-601 screen ----------->
** MODE S UF0 TEST - ED ** DF 0 VS=0 RI=8 ADDRESS=000001 *****
AC= 32,775 FT
TEST RUNNING
*****
Exercise the MAX AIRSPEED switches on the test and the correct RI indication as shown in the following list. Cycle power and allow about 2 or 3 seconds of OFF time and about 5 seconds for processor initialization and ATC-601 response time between each switch setting. MAX AIRSPEED SWITCH BIT 15 BIT 16 BIT 17 OFF OFF OFF SEL OFF OFF OFF SEL OFF SEL SEL OFF OFF OFF SEL SEL OFF SEL OFF SEL SEL SEL SEL SEL
RI VALUE 8 9 A B C D E F (not an assigned configuration)
It is worth noting that in this test mode the ATC-601 displays the altitude to the nearest 25 feet.
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maintenance 523-0775657 Table 5-11 Acceptance Test Procedures, Using the DATATRAC 400 or DATATRAC 400H Databus Analyzer (Cont).
STEP 18.0
TITLE Ext Suppression Test
PROCEDURE
DESIRED RESULTS
On test : • ALT TYPE SELECT: ARINC 429 On DATATRAC ( ): • Same setup as for STEP 9.0. On ATC-601: • Set for ATCRBS REPLY TEST screen -----> • Connect scope channel A to the test SUPPR test points. • Connect scope channel B to the REPLY VIDEO BNC connector on the ATC-601. • Set the scope to display both channels
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** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE= *****
ALT= [ ] TEST RUNNING *****
Note a (approx) 30µs pulse on channel A. Note a reply waveform on channel B. If your scope is able, you will see the individual reply code pulses on channel B. You may also see the occasional squitter transmission which appears as a much longer series of pulses at about 1 transmission every 2 sec. Of particular importance, however, is that the channel A (suppression) pulse is about 30 µs long during ATCRBS reply, and brackets the 21 µs ATCRBS reply. During squitter transmission, the suppression pulse extends to bracket the squitter transmission. The squitter transmission is a DF11 reply about 72 µs long.
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maintenance 523-0775657 Table 5-11 Acceptance Test Procedures, Using the DATATRAC 400 or DATATRAC 400H Databus Analyzer (Cont).
STEP 19.0
TITLE ADLP Select, Discrete Strap Test
PROCEDURE
DESIRED RESULTS
On test : • Be sure DATALINK switch is set to NO ADLP. On DATATRAC ( ): • Same setup as for STEP 9.0. DATATRAC RCV 1 screen ------> Note: The ATC-601 is not needed for this test but it can remain connected and operating. On test : • Set POWER switch to OFF • Set DATALINK switch to ADLP. • Be sure DATALINK SELECT switch is set to A/B. • Set POWER switch to ON.
-----------------RCV 1--(ALL)---12.5 KHz Lbl SDI 32-Hex Data-1 SSM Par msec 350 01 60 00 01 17 11 1 0100
-----------------RCV 1--(ALL)---12.5 KHz Lbl SDI 32-Hex Data-1 SSM Par msec 350 01 64 A2 01 17 11 1 0100 |<---diagnostic code A2
Note: The diagnostic A2 identifies an inactive ADLP bus. This test verifies that the ADLP enable discrete is functional.
DATATRAC RCV 1 screen ------> On test : • Set POWER switch to OFF. • Set DATALINK switch to NO ADLP. • Set POWER switch to ON.
-----------------RCV 1--(ALL)---12.5 KHz Lbl SDI 32-Hex Data-1 SSM Par msec 350 01 60 00 01 17 11 1 0100 |<---diagnostic code 00
DATATRAC RCV 1 screen ------> Note: The Airborne Datalink system is not fully implemented at this time. If and when an ADLP (Airborne DataLink Processor) becomes available and operational, suitable procedures will be provided to the integrity of the ADLP input/output ports. At this point, therefore, verification of the ADLP SELECT strap is seen as sufficient to prevent nuisance diagnostics that can occur if the select input should be defective. You will notice that the DATALINK SELECT A/B, C/D function is also not tested.
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maintenance 523-0775657 Table 5-11 Acceptance Test Procedures, Using the DATATRAC 400 or DATATRAC 400H Databus Analyzer (Cont).
STEP 20.0
TITLE Remote IDENT Discrete Test
PROCEDURE
DESIRED RESULTS
On test : • Same as initial setup On DATATRAC ( ): • Same setup as for STEP 9.0. On ATC-601: • Setup for ATCRBS REPLY test
** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE= *****
On test : • Press and release the REMOTE IDENT switch. On DATATRAC ( ): • Note RCV screen ----->:
On ATC-601: • Notice the ID display. ID should display for about 18 seconds.
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ALT= [ ] TEST RUNNING *****
-----------------RCV 1--(ALL)---12.5 KHz Lbl SDI 32-Hex Data-1 SSM Par msec 031 01 75 66 91 98 11 1 0200 |<----Ident bit
Note: The 9 should appear in the data field only while the switch is being pressed. This, together with the ID display on the ATC-601, verifies that the REMOTE IDENTdiscrete input is functional. ** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE=ID5263 ALT= 32,800 FT [1344] |<----ID display ***** TEST RUNNING *****
On Datatrac ( ): • Set the label 031 XMT 1 word:
-ON--------------XMT 1--(ALL)---12.5 KHz Lbl SDI 32-Hex Data-1 SSM Par msec 031 01 15 66 91 98 00 1 0100
On DATATRAC RCV 1 and on ATC-601 screens:
You should see the same displays as immediately above. If the test failed using the REMOTE IDENT switch, but succeeds here, then suspect a failure in the discrete input or the test .
On Datatrac ( ): • Set the label 031 XMT word:
-ON--------------XMT 1--(ALL)---12.5 KHz Lbl SDI 32-Hex Data-1 SSM Par msec 031 01 95 66 81 98 00 1 0100
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STEP 21.0
TITLE Self Test
PROCEDURE
DESIRED RESULTS
On test : • Set POWER switch OFF • ALT TYPE SELECT: ARINC 429 • AIR/GND: AIR • SELF TEST: ENABLE: OFF On DATATRAC ( ): • Same setup as for STEP 9.0. On ATC-601: • Set for ATCRBS REPLY TEST ---------->
** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE= *****
ALT= [ ] TEST RUNNING *****
On test : • Set POWER switch ON
After a few seconds, the test X FEED OUT lamp and the ATC-601 REPLY lamps light indicating that the unit is replying. The ATC-601 screen indicates ED.
On DATATRAC ( ): screen shows: --------->
-----------------RCV 1--(ALL)---12.5 KHz Lbl SDI 32-Hex Data-1 SSM Par msec 031 01 F5 66 81 98 11 1 0200 203 01 64 00 01 C1 11 1 0200 350 01 60 00 01 17 11 1 0200 (You may need to press INC to display all three labels.)
In the next few steps, watch the DATATRAC RCV screen carefully. On the test : • Press and hold the SELF TEST pushbutton for about 1 sec.
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After a few seconds, notice that the DATATRAC ( ) and ATC-601 screens do not change except that the DATATRAC briefly shows *’s to the left of the 0200 time displays in the RH column. (The test TEST lamp lights while you hold the switch but otherwise there is no change.)
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maintenance 523-0775657 Table 5-11 Acceptance Test Procedures, Using the DATATRAC 400 or DATATRAC 400H Databus Analyzer (Cont).
STEP 21.0
TITLE Self Test (cont’d)
PROCEDURE
DESIRED RESULTS
On test : • Set the AIR/GND switch to GND • Set the SELF TEST/ENABLE switch to ON • Press and hold the SELF-TEST button for about 1 s
Self-test Displays: After a few seconds, notice that the X FEED OUT lamp turns off briefly while the ATC-601 screen shows +’s or -’s in most of the data fields, followed by blank fields.
Note: The test TEST lamp lights while you hold the switch. This has no bearing on UUT operation, however. If the lamp does not light, check the test . On the DATATRAC ( ), press RCV (either once or twice) to return to the setup screen, followed by ENT, to clear the screen of any extraneous labels.
After a few seconds, notice that the X FEED OUT lamps turns on again and the ATC-601 screen returns to the normal display. On the DATATRAC ( ), notice that the SSM’s change to 10 and then back to 11.You should try to be especially watchful of the 350 data word and try to catch any diagnostic codes that may be displayed during the selftest sequence.
On the test : • Set the SELF TEST/ENABLE switch to OFF. • Press and hold the SELF TEST button for about 1 s.
Notice that the self-test displays as described above do not appear..
On the test : • Set the SELF TEST/ENABLE switch to ON. • Set the AIR/GND switch to AIR. • Wait about 5 seconds *. • Press and hold the SELF TEST button for about 1 s.
Notice that the self-test displays as described above do not appear..
Note: This verifies that self test is properly inhibited by the self-test inhibit discrete.
Note: This verifies that self test is properly inhibited by the AIR/GND discrete.
*Note: The U must be allowed sufficient time to complete at least one software cycle in order to recognize the change in the AIR/GND discrete. If you press the SELF TEST switch in less than about 3 seconds of setting the AIR/GND switch to AIR, the unit may execute self-test as though it were not inhibited. This should be seen as normal. On the test : • Set the SELF TEST/ENABLE switch to ON. • Set the AIR/GND switch to GND. • Press and hold the SELF TEST button for about 1 s.
Notice the self-test displays as described above reappear. Note: This verifies that the self-test inhibit and AIR/GND discretes are switchable.
This completes this test sequence. Successful completion of this series provides reasonable assurance that the unit is operational. However, this test does not satisfy the requirements of a Final Performance Test which must be performed after any repair operation. Turn off all power, disconnect the equipment, and return it to its normal storage location. Return the UUT to its original shipping container, or equivalent, if it is to remain in storage. Otherwise, prepare it for installation.
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maintenance 523-0775657 5.4.5.10 Procedures Using The Atlantic Instruments DataTrac 200 Databus Analyzer Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer STEP
TITLE
PROCEDURE
DESIRED RESULTS
1.0
Setup
Note: If you are using a Test built according to instruction provided in a previous edition of this manual, it may be necessary to upgrade the . Refer to the Special Tools and Fixtures Section. If not already done, connect equipment as shown in figure 5-2. • Connect DATATRAC 200 as follows and using cables shown in the Special Tools and Fixtures paragraph. • ARINC 429 XMT to test DIGITAL CONTROL port, • Parallel connect XMT to test PRIMARY DIGITAL ALTITUDE PORT, • ARINC 429 RCV to test DATA BUS READER port. • Connect the ATC-601 to the UUT bottom antenna connector. • Connect an rf termination to the top antenna port. • Connect power to test power jacks - observe proper polarity. • Preset the switches as shown in paragraph 5.4.5.6. above. Be sure POWER switch is OFF and EXT STBY switch is at STBY.
1.1
Setup
Turn the DATATRAC 200 on, intialize for ARINC 429, and set the RCV, and XMT screen ----->
Lbl SI 29-Hex RCV-11 SM P MSEC >> NO DATA RECEIVED Lbl SI 29-HEX XMT-11 031 01 55980 203 01 20000
SM P MSRC 00 1 100 11 1 100
(See notes 1 and 2 that follow test step 1.2) On test , set switches as shown in paragraph 5.4.4. above.
1.2
Turn on TDR-94/94D
On test : • Set POWER switch to ON Monitor current. If OK: • Set EXT STBY switch to OPR Monitor current.
Setup (power-up)
Turn the ATC-601 on and press SELECT for the screen -------------->
UUT power on and ARINC 429 tuning test
ATC-601 screen --------->
If the unit has been in service and there is a possibility of an over-current condition, monitor the power supply current output. The setup should draw no more than 1.5 A. Typically it draws about 0.9 to 1.1 A when the UUT is transmitting. ** ATCRBS REPLY TEST - NOT RUN **
(lines 2-4 are irrelevant) CODE=
ALT= Press RUN to start
[
]
** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE=5263 *****
ALT=32,800 FT [1344] TEST RUNNING *****
To change the CODE, see note 1 below. To change the ALT, see note 2 below. The DATATRAC 200 RCV display becomes --------->
Lbl 031 203 350
SI 01 01 01
29-Hex RCV-11 559A0 20000 00000
SM 11 11 11
P 1 1 1
MSEC 0200 0200 0200
Note: Any other labels displayed are irrelevant to this test. Use the INC key to scroll the display. See Note 3 below. On the ATC-601, press RUN
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UUT responds to interrogations as indicated by a lighted XFEED OUT lamp on the test and a lighted REPLY lamp on the ATC-601.
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP
TITLE
PROCEDURE
DESIRED RESULTS
Note 1. You can change the (octal) CODE=XXXX display by changing data bits 18 through 29 in the label 031 data word (XMT field of the DATATRAC 200) as follows: ATC-601 octal digit: Bit: 32 31 30 Data: Par SSM DATATRAC Hex Bits: 8 DATATRAC Hex value: DATATRAC (Hex): Binary: 0 0 0 Octal value: Produces an ATC-601 CODE:
First Second 29 28 27 26 25 24 |<-----Data ------->
First 4
2 0 2 5
21
Second 1
8
4
2
5 1 4
Third 22
23
Fourth 19 18 ----->|
20
Third
1
8
4
2
5 1 1
0 4
1 2 2
0 1
17 Pad
16 Pad
Fourth 1
8
4
2
9 1 4
1 2 6
0 1
0 4
15 Pad 1
8 1 2 3
1 1
0
0
0
Bits 11 through 17, of the label 031 control word, are assigned the following functions: DATATRAC Hex bits: Fifth Bit: 14 13 12 11 10 9 Bit values: 8 4 2 1 8 4 2 1 DATATRAC (Hex): 0 Assignment:
| | Pad | |<- |<--SDI | | |<--Altitude reporting, 1 = OFF | |<--Ident, 1 = ON |<--Altitude port select, 1 = B
Note 2: You can set the XMT label 203 data field bits 12 through 28 to any combination of 1 and 0. The RCV label 203 word data field will reflect the XMT word while the ATC-601 will show the altitude to the nearest 100 feet. The label 203 word data bit values are as follows: lst | DATATRAC (Hex) *: | Hex value: 8 4 2 1 Bit: 29 28 27 26 Alt value:(sign bit; 0 = +) 65536 32768 16384 (in feet) DATATRAC (Hex) *: | 3rd | | Hex value: 8 4 2 1 8 4 Bit: 21 20 19 18 17 16 Alt value 512 256 128 64 32 16 (in feet) Determine the altitude by totaling the bit value of all bits set to
| 8 25 8192
2nd 4 24 4096
4th 2 15 8
| 1 14 4
| 1 22 1024
2 23 2048 | 8 13 2
5th 4 12 1
2 11 **
| 1 10 **
09 **
1.
* The first (lst) Hex Data bit sets data bits 26 through 29. Since bit 29 must always be a 0, this Hex bit must not be set to a hex number greater than 7. The fifth (5th) bit includes part of the SI, bit 10, therefore you will see it change whenever the SI is set to any value other than 01. ** Bits 9, 10, and 11 are not used in the altitude definitions. Note 3: You will see a label 371 data word. This is the ARINC 429 Specific Equipment Identification word which is structured the same as other ARINC 429 words but conveys the following information: Bits 11 through 18 identify the equipment type. The code for ATC transponders is 18 therefore bits 14 and 15 are 1; the others are 0. Bits 19 through 24 convey a binary code identifying the equipment manufacturer. Collins’ is 6. Therefore bits 20 and 21 are 1; all others are 0. Bits 24 through 29 are reserved for purposes to be defined. When ARINC 572 altitude data is active, you will see a label 200 data word. This word reflects the ARINC 572 (Gillham code) altitude data. This word is structured the same as other ARINC 429 words, except bits 9 and 10 are part of the data field; i.e., there is no SDI. Bits 9,10, and 11 reflect the D1, D2, and D4 code bits respectively. Bits 13, 14, and 15 reflect the C-bits, bits 17, 18, and 19 reflect the B-bits, and 21, 22, and 23 reflect the A-bits.
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP
TITLE
2.0
Test set, Auto Test
PROCEDURE
DESIRED RESULTS
On ATC-601: • Press RUN/STOP to stop • Press AUTO TEST • Press RUN to start Note: This test requires a few seconds to run. It will stop automatically.
Ensure that all tests . See note below.
On test : • Set EXT STBY switch to STBY • Set POWER switch OFF On UUT: • Move the test set rf cable to the UUT top antenna connector and the rf termination to the bottom. On test : • Set POWER switch ON • Set EXT STBY switch to OPR On ATC-601: • Repeat the AUTO TEST
Ensure that all tests . See note below.
Note. The AUTO TEST sequence will indicate FAILED even when certain tests result in a NO REPLY condition. The NO REPLY conditions are the result of no ADLP (Airborne Data Link Processor) data in this setup. This same condition is likely to occur when using the ATC-601 as a ramp tester when testing an installation not equipped with an ADLP. To that the test can be seen as successful, proceed as follows: • When the test sequence is completed and the ATC-601 stops, as indicated by INTERR and REPLY lamps off, you will likely see a screen as follows: ** AUTO TEST - FAILED ** MODES TESTED - A,C,S FREQ: MODES ED - A,C,S ERP: MODES FAILED -> MTL: DIVERSITY ISOLATION: >40 dB Press RUN to start
1089.92 Mhz 55 Dbm -77 Dbm
(The FREQ, ERP, and MTL values can vary from UUT to UUT and to a lesser degree on UUT temperature.) the test results as follows: On the ATC-601, use the SELECT up arrow or down arrow key to scroll through the following list of tests performed; the numbers are for reference purposes only and do not appear on the test set screen. If you use the down arrow, you will see the list in the order shown; from test 1 through test 19. If you use the up arrow key, you will see the list in reverse order, starting at test 19. You will likely notice that all tests ed except tests 13, 14, and 15 which had a NO REPLY. NO.
TEST NAME AND RESULT
1.0
**
REPLY DELAY TEST - ED
2.0
**
REPLY JITTER TEST - ED
TEST SPECIFICATION / DESCRIPTION **
**
MODE S: 128.00 (±0.25) µs ITM A: 128.00 (±0.25) µs (All others): 3.00 (±0.50) µs MODE S: =< 0.05 µs ITM: =< 0.06 µs
(All others): =< 0.1 µs 3.0
**
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ATCRBS REPLY TEST - ED
**
F1 TO F2 SPACING: 20.3 (±0.1) µs All PULSE WIDTH: 0.45 (±0.1) µs
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP
TITLE
NO.
TEST NAME AND RESULT
4.0
**
5.0
** ATC ONLY ALL-CALL TEST - ED **
The TDR-94/94D should not reply to this mode a and mode c only interrogation. ED indicates a correct (NO) response.
6.0
** MODE S ALL-CALL TEST - ED **
The TDR-94/94D should reply to this interrogation. ED indicates a correct response. UUT address previously determined in mode s interrogation, is sent to UUT in UF4 (Uplink Format 4) and verified in DF4 (Downlink Format 4) reply.
7.0
** INVALID ADDRESS TEST - ED **
UUT is interrogated with two addresses, both of which are different from the correct address. ED indicates UUT did not reply to interrogation.
8.0
** SPR ON/OFF TEST - ED **
UUT is interrogated first with SPR ON and verifies a proper reply, then with SPR OFF and verifies no reply. ED indicates UUT responded correctly.
9.0
**
MODE S UF0 TEST - ED
**
UUT is interrogated with mode S UF0, ing correct altitude as compared to previous mode c reply, correct address as compared to DF11 address, and correct format. ED indicates correct UUT response.
10.0
**
MODE S UF4 TEST - ED
**
UUT is interrogated with UF4, ing correct altitude as compared to previous mode c reply, correct address as compared to DF11 reply, and correct format. ED indicates correct UUT response.
11.0
**
MODE S UF5 TEST - ED
**
UUT is interrogated with UF5, ing the correct ID code as compared to previous mode a reply, correct address as compared to DF11 reply, and correct format. ED indicates correct UUT response.
12.0
**
MODE S UF11 TEST - ED
13.0
**
MODE S UF16 TEST - NO REPLY
**
(See test 15.)
14.0
**
MODE S UF20 TEST - NO REPLY
**
(See test 15.)
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PROCEDURE
DESIRED RESULTS
SLS LEVEL TEST - ED
TEST SPECIFICATION / DESCRIPTION UUT is interrogated with F2 (SLS) pulse at 9 dB below F1. UUT should reply to this interrogation. Then UUT is interrogated with F2 equal to F1. UUT should not reply. ED indicates correct response to both tests.
**
UUT is interrogated with UF11, ing correct address as compared to previous response, and correct format. ED indicates correct UUT response.
**
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP
TITLE
STEP
TEST NAME AND RESULT
15.0
**
MODE S UF21 TEST - NO REPLY
16.0
**
SQUITTER TEST - ED
17.0
**
FREQUENCY TEST - ED
**
Freq: 1090 (±1) MHz
18.0
**
DIVERSITY TEST - ED
**
ATC-601 monitors squitter pulses on active antenna port (as in test 16) and then monitors for intervening squitter pulses that are not greater than 20 dB below the active squitter. This test will always fail when the UUT is a TDR-94 (non diversity) because squitter is transmitter every second on the same antenna port. If you are testing a TDR-94D and the DL ANT/SGL ANT switch is set to SGL ANT, the test will also fail because this causes the unit to operate like a TDR-94. ED indicates a correct response from a TDR-94D.
19.0
**
MTL DIFFERENCE TEST - ED
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PROCEDURE
DESIRED RESULTS TEST SPECIFICATION / DESCRIPTION
**
UUT is interrogated with UF16, UF20, and UF21. These formats are all related to the airborne data link function. This function has not been implemented. The TDR-94/94D will not reply to these interrogation formats. NOT REPLY should not be seen as a failure. When set for daul antenna operation, the TDR-94D transmits a squitter pulse once each second, alternating between top and bottom antenna ports. The ATC-601 verifies that one squitter pulse is received every 1.6 to 2.4 seconds. The test ANT SGL/DL switch must be in the DL position. When set for single antenna operation, or when testing a TDR-94, only the bottom antenna port is used. In this case the ATC-601 verifies that one squitter pulse is received every 0.6 to 1.4 seconds. When you change the ANT SGL/DL switch, you must cycle power to the UUT in order for it to take effect. ED indicates a correct UUT response.
**
**
ATC-601 verifies that the MTL difference between mode a and mode c responses is < 1.0 dB. At this point, another press of the arrow key will display the first item; either 1.0 or 18.0, depending on which arrow was used.
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP 3.0
TITLE Power output and Rcvr Sensitivity Test
PROCEDURE
DESIRED RESULTS OR SETUP SCREEN
On test select: • Set EXT STBY switch to STBY • Set POWER switch OFF On ATC-601: • Select POWER TEST • Press RUN to indicate TEST RUNNING -------->
** POWER TEST - Top Antenna ANTENNA UNITS ERP MTL *****
TEST RUNNING
** STATUS NO REPLY
*****
Note: If necessary, press SELECT (or SLEW) to select Top Antenna. Be sure that the ATC-601 rf cable is connected to the top antenna port and the rf termination is connected to the bottom port. On DATATRAC 200: set screen ------>
LBL SI 29-HEX RCV-11 SM P MSEC >> NO DATA RECEIVED LBL SI 29-HEX XMT-11 031 01 55980 203 01 20000
On test : • Set POWER switch ON • Set EXT STBY switch to OPR
SM P MSEC 00 1 100 11 1 100
** POWER TEST - Top Antenna ANTENNA UNITS ERP MTL Top dBm 55.7 -76.0
** STATUS ED
***** TEST RUNNING *****
After a few seconds, the ATC-601 shows ----> On ATC-601: Press RUN/STOP to stop the test. If the UUT is a TDR-94, skip this step. On test : • Set EXT STBY switch to STBY • Set POWER switch OFF • On TDR-94D mount: Swap the rf cable connection and termination on the UUT antenna ports. (Rf cable to bottom port and termination to top antenna port.) On test : • Set POWER switch to ON • Set EXT STBY switch to OPR On ATC-601: • Press RUN to indicate TEST RUNNING Wait a few seconds then press RUN/STOP to stop the test.
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If a failure is detected, a small arrow will be shown to the left of the offending parameter(s). Make a note of the test results, if a record is needed, and label it as applicable to the UUT bottom antenna port. The data displayed here will be overwritten on the next test. You should see a similar display on the ATC-601 except this data is applicable to the top antenna port. The data can be slightly different. See below for test tolerances and an explanation of a possible failure indication due to high sensitivity. Note: You may also select bottom antenna screen on the ATC-601. Note: You may see a marginal test failure if the UUT is relatively cold. In this case allow the unit to warm up a few minutes and then repeat the test.
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP
TITLE
3.0 (cont’d)
Power output and Rcvr Sensi-tivity Test (cont’d)
PROCEDURE
DESIRED RESULTS OR SETUP SCREEN
The test tolerances are: ERP: > 48.5 dBm and < 57.0 dBm MTL: -73.0 (±4.0) dBm The ATC-601 will indicate that the UUT has FAILED if the MTL is more than -77.0 dBm or less than 71 dBm. Collins prefers, however, that a FAILURE should be reported only if the MTL is less than 71 dBm. Therefore, if you have a unit displaying an MTL of -77.1 or more, you should see that value as acceptable. Obviously, an MTL indication approaching -80 dBm or more may be cause for suspecting a problem with test set calibration. You may also see a failure because the ERP, Effective Radiated Power or Peak Pulse Power , is more than 57 dBm. Power measurements taken with a ramp tester can be confusing. The various test equipment manufacturers use different dimensions for displaying the test results, the test specifications are not always clear on how the test is to be performed to produce the specified result, and the test method; direct or radiation, yields different results. As in the case of MTL, an ERP slightly greater than 57 dBm ( e.g., 59 dBm max), using the direction connection method, should not be seen as cause for unit rejection. DO-181 specifies the transponder power output at the antenna. Testing a unit on the bench by direct connection to the antenna port yields a power reading at the transmitter output. The difference is, of course, antenna cable and connector losses. DO-181 specifies transponder power output in watts and dBW. The IFR ATC-601 displays power in dBm (ERP). The TIC-48/-49 displays power in watts. The following chart may be useful for proper test evaluation:
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Watts
dBW
dBm
50 70 100 125 150 200 250 300 350 400 450 500
16.99 18.45 20.00 20.97 21.76 23.01 23.98 24.77 25.44 26.02 26.53 26.99
46.99 48.45 50.00 50.97 51.76 53.01 53.98 54.77 55.44 56.02 56.53 56.99
TDR-94/94D Spec
(Min for airplanes limited to 15 000 ft and 175 kts.) Minimum at antenna (ramp testing)
Minimum direct (on bench)
Maximum at antenna
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP 4.0
TITLE Gillham Altitude Test
PROCEDURE
DESIRED RESULTS OR SETUP SCREEN
On ATC-601: select
** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant)
ATCRBS REPLY TEST ----------->
CODE=
ALT=
[
]
Press RUN to start
On test select: • Set POWER switch to OFF • ALT TYPE SELECT: ARINC 572 • ARINC 572 ALT IN: TO TDR On DATATRAC 200: • Set XMT label 203 word to OFF • Set RCV and XMT screen ------>
Lbl SI 29-Hex RCV-11 SM P MSEC >> NO DATA RECEIVED
On test : • Set all ARINC 572 switches to OFF: Then set A4, C2, C4, and B4 to SEL. • Set POWER to ON • Set EXT STBY switch to OPR
The XFEED OUT lamp turns on. The ATC-601 REPLY lamp indicates that UUT is responding to interrogations.
DATATRAC 200 RCV screen shows: -------------------->
Lbl SI 29-HEX RCV-11 031 01 55980 203 01 05C30
Lbl SI 29-HEX XMT-11 031 01 55980
SM P MSEC 00 1 100
SM P MSEC 11 1 100 11 1 100
(ignore any other displayed labels) On ATC-601: • Press RUN. Screen shows: -------------------->
** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE=5263 *****
ALT=5,900 FT TEST RUNNING
[4460] *****
(The CODE 5263 depends on your selection in the 031 XMT word. See note 1 under step 1.2 above) At this step you are asked to toggle each of the ARINC 572 switches and the altitude display. You should also watch the RCV data word on the DATATRAC 200 display. By cycling each switch between OFF and SEL you should see the ATC601 display and the DATATRAC 200 and 203 data words change. If the displays do not change for a particular switch, this would indicate either an open or a shorted code line. If the wrong altitude is shown that code line may be effecting another line; i.e., causing two or more inputs to change simultaneously. In either case the UUT, the test , or the interconnecting cable needs repair. Set each switch as shown in the listing below to the (position) shown, and back, and the altitude display at both positions. The altitude display should always revert to the initial display when the switch is returned to its original position. There is no serious need to the correctness of the RCV word as long as the ATC-601 display is correct. SWITCH Initial A1 (SEL) A2 (SEL) A4 (OFF) C1 (SEL) C2 (OFF)
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DISPLAYED ALTITUDE 5,900 FT [4460] 23,600 FT [5460] 7,600 FT [6460] -400 FT (0460] none (blank; this is invalid) 5,800 FT [4440]
SWITCH C4 (OFF) B1 (SEL) B2 (SEL) B4 (OFF) D2 (SEL) D4 (SEL)
DISPLAYED ALTITUDE 6,000 FT [4420] 3,600 FT [4560] 5,600 FT [4660] 6,600 FT [4060] 119,600 FT [4462] 55,600 FT [4464]
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP
TITLE
PROCEDURE
DESIRED RESULTS OR SETUP SCREEN
Gillham Code, Altitude Listing: ATC-601 ALT DISPLAY -1000 FT 0 FT 500 FT 1000 FT 1300 FT
D2 0 0 0 0 0
D4 0 0 0 0 0
A1 0 0 0 0 0
GILLHAM A2 0 0 0 0 0
CODE SWITCHES A4 B1 B2 B4 0 0 0 0 0 0 1 1 0 0 1 0 0 1 1 0 0 1 1 1
C1 0 0 0 0 1
C2 1 1 1 1 0
C4 0 0 0 0 0
1500 1800 2000 2600 2700
FT FT FT FT FT
0 0 0 0 0
0 0 0 0 0
0 0 0 0 0
0 0 0 0 0
0 0 0 0 0
1 1 1 1 1
1 0 0 0 0
1 1 1 0 0
0 0 0 0 0
1 0 1 1 0
0 1 0 1 1
3000 4000 6000 6800 8000
FT FT FT FT FT
0 0 0 0 0
0 0 0 0 0
0 0 0 0 0
0 0 0 1 1
1 1 1 1 1
1 1 0 0 0
0 1 0 0 1
0 1 1 0 1
0 0 0 0 0
1 1 1 0 1
0 0 0 1 0
10000 12000 14000 14800 16000
FT FT FT FT FT
0 0 0 0 0
0 0 0 0 0
0 0 0 1 1
1 1 1 1 1
1 0 0 0 0
1 1 0 0 0
0 1 0 0 1
1 1 1 0 1
0 0 0 0 0
1 1 1 0 1
0 0 0 1 0
16100 16200 18000 20000 22000
FT FT FT FT FT
0 0 0 0 0
0 0 0 0 0
1 1 1 1 1
1 1 1 1 1
0 0 0 1 1
0 0 1 1 0
1 1 0 1 0
1 1 1 1 1
1 1 0 0 0
1 0 1 1 1
0 0 0 0 0
25000 30000 30800 35000 40000
FT FT FT FT FT
0 0 0 0 0
0 0 1 1 1
1 1 1 1 1
0 0 0 0 1
1 0 0 1 1
1 0 0 1 0
1 0 0 0 1
0 1 0 0 1
0 0 0 0 0
1 1 0 1 1
0 0 1 0 0
45000 50000 66000 67500
FT FT FT FT
0 0 1 1
1 1 1 1
1 0 0 0
1 1 0 0
0 0 0 1
0 1 1 1
1 0 0 0
0 1 1 1
0 0 0 0
1 1 1 1
0 0 0 0
----------------------------------------------------------------------------------In all cases, set the applicable switch to SEL for those pulses identified by a logic 1. For addtional information on Gillham code structure, refer to paragraph 5.7 in this section.
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP 5.0
TITLE CSDB tuning and altitude test
PROCEDURE
DESIRED RESULTS
On ATC-601: • Press RUN/STOP to stop the interrogations On test : • Set POWER OFF On DATATRAC 200: • Turn POWER to OFF • Wait a few seconds, then turn POWER to ON • At the initial screen, select CSDB (enter C and press ENT) • At the DATA RECEIVER SETUP screen, press 2 (for HEX DATA) and press ENT (this brings up the RCV DATA screen) • Press XMT to show the TRANSMITTER SETUP screen (default values should be correct) • Press ENT (this brings up the combined screen) Note screen ---------->
LBL 7-STAT-0 HEX RCV DATA >> NO DATA RECEIVED
MSEC
LBL 7-STAT-0 HEX XMT DATA
MSEC
(Note cursor is under the B in the XMT LBL field) On the back of the DATATRAC 200: • Move the cables (HI and LO) connected to the 429 TX to CSDB TX • Move the cables (HI and LO) connected to the 429 RX to CSDB RX On DATATRAC 200: • Enter 1E (this is the CSDB tuning word label) • DATATRAC responds with a default field of 0’s and 100 below MSEC
• Change XMT data field as shown -------------> (Be sure to press INC)
LBL 7-STAT-0 HEX XMT DATA MSEC 1E 10011001 63 52 44 13 100 |||||||| || || ||<||<-Gillham altitude * |||||||| ||<||<-ATC code * |||||| |<- SI; 01 = side 1, 10 = side 2 ||||||<-Test; 1 = on |||||<-ATC ident; 1 = on ||||<-Altitude reporting; 1 = on |||<-Mode; 1 = standby ||<-Pad (not used) |<-Validity; 1 = valid
* Refer to paragraph 5.6.3.2 for code description. On ATC-601: select ATCRBS REPLY TEST and press RUN to indicate TEST RUNNING
----------->
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** ATCRBS REPLY TEST
NO REPLY **
(lines 2-4 are irrelevant) CODE= *****
ALT= TEST RUNNING
[
]
*****
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP 5.0 (cont’d)
TITLE CSDB tuning and altitude test (cont’d)
PROCEDURE
DESIRED RESULTS
On test : • Set CONTROL DATA SELECT to CSDB • Set ALTITUDE DATA, ALTITUDE TYPE SELECT to CSDB (CTL) • Set OUTPUT PORT SELECT to CSDB PORT 1 • Set ARINC 572 ALT IN to TO CTL • Set SOURCE SELECT to CTL • On the test CONTROL CONNECTOR J1, connect two jumpers: From Pin To Pin 26 41 25 8 Note: These jumpers are not required if MOD 1 has been installed in the test . • Set POWER switch ON DATATRAC 200 screen -->
On test : • Set the OUTPUT PORT SELECT switch to CSDB PORT 2.
LBL 1F A0 F3
7-STAT-0 11011001 10000001 00000001
HEX RCV DATA 63 52 44 13 20 20 00 00 00 00 00 00
MSEC 0100 0100 0100
LBL 7-STAT-0 1E 10011001
HEX XMT DATA 63 52 44 13
MSEC 100
Notice that the same data is displayed. (The data may flicker somwhat while you are switching; ignore that.)
Important points: • The 1F RCV word is a reflection of the 1E XMT word • The A0 RCV word is irrelavent here, the hex data shown above can be different • The F3 word is the diagnostic word and should indicate no faults; HEX DATA is all 0’s. Bits 1 and 0 of the status byte are the SI bits and indicate that the UUT is set for side 1 (01) which must be true of all word labels. The ATC-601 screen shows:
** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE=5263 *****
ALT= 32,800 FT [1344] TEST RUNNING *****
Important points: • Notice that the CODE agrees with the HEX XMT DATA 1E word except that the hex digital pair groupings are reversed in order. That is, the XMT and RCV words show 63 52 while the ATC601 shows 5263. In the altitude field, the XMT and RCV words show 44 13 while the ATC-601 shows 1344. 6.0
ARINC 429 Altitude Test
On ATC-601: select ATCRBS REPLY TEST and press RUN to indicate TEST RUNNING --------->
** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE= *****
ALT= [ ] TEST RUNNING *****
On test : • Set EXT STBY switch to STBY • Set the POWER switch to OFF • Set ALT TYPE SELECT to ARINC 429 • Set OUTPUT PORT SELECT switch to ARINC 429 PORT A • Set CONTROL DATA SELECT switch to PA On DATATRAC 200: • Move the TX and RX leads to the ARINC ports. • Reinitialize the unit for ARINC 429 operation.
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP
TITLE
6.0 (cont’d)
ARINC 429 Altitude Test (cont’d)
PROCEDURE
DESIRED RESULTS OR SETUP SCREEN
On DATATRAC 200: • Set XMT to ON • Setup screen ------>
Lbl SI 29-Hex RCV-11 SM P MSEC >> NO DATA RECEIVED
On test : • Set POWER to ON • EXT STBY to OPR • Be sure REP ALT switch is at PA
POWER indicator comes on immediately and after a few seconds the XFEED OUT lamp turns on. The ATC601 REPLY lamp indicates that UUT is responding to interrogations.
Lbl SI 29-HEX XMT-11 031 01 55980 203 01 20000
The ATC-601 screen shows: --->
SM P MSEC 00 1 100 11 1 100
** ATCRBS REPLY TEST **
(lines 2-4 are irrelavent) CODE=5263 *****
ALT=32 800 FT [1344] TEST RUNNING *****
(The CODE 5263 depends on your selection in the 031 XMT word. See note 1 under step 1.2 above.) DATATRAC 200 RCV screen shows: ------->
Lbl 031 203 350
SI 29-HEX RCV-11 01 559A0 01 20000 01 00000
SM 11 11 11
P 1 1 1
MSRC 0200 0200 0200
(ignore any other displayed labels, and the order is not important) 6.1
ARINC Altitude Control Disc-retes Tests
On the test : • Be sure the SOURCE SELECT switch is set to SEL. On the test : • Set the REP ALT SEL switch to PB
** ATCRBS REPLY TEST **
(lines 2-4 are irrelavent) CODE=5263 *****
ALT=32 800 FT [1344] TEST RUNNING *****
Notice that the ATC-601 altitude display blanks. Note: At this point the UUT is configured to report altitude data from port B. There is none so the display blanks.
On the test : • Move the parallel connection from the PRIMARY DIGITAL ALTITUDE SOURCE jack to the ALTERNATE DIGITAL ALTITUDE SOURCE jack.
Notice that the ATC-601 altitude display returns.
On the test : • Set the REP ALT SEL switch to PA
Notice that the ATC-601 altitude display blanks.
Note: This verifies that UUT is configured to report altitude data being supplied on port B.
Note: UUT is returned to port A. This series of steps has verified that the Reporting Altitude discrete is switchable. On the test : • Set the SOURCE SELECT switch to CTL
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Notice that the ATC-601 altitude display returns. Note: This switches the UUT to the altitude data supplied on the control port.
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP
TITLE
PROCEDURE
DESIRED RESULTS OR SETUP SCREEN
6.1 (cont’d)
ARINC Alltitude Control Disc-retes Tests (cont’d)
On the test : • Disconnect the parallel connection from the ALTERNATE DIGITAL ALTITUDE SOURCE jack. (Wait about 5 seconds)
Notice that the ATC-601 altitude display remains.
On test : • Set the SOURCE SELECT switch to SEL.
Notice that the ATC-601 altitude display blanks.
On test : • Reconnect the parallel connection to the ALTERNATE DIGITAL ALTITUDE SOURCE jack.
Notice that the ATC-601 altitude display remains blanked.
On test : • Set the AUTO ALT switch to SEL (-003 UUT units only)
Notice that the ATC-601 altitude display returns.
On test : • Set AUTO ALT switch to OFF. (-003 UUT units only)
Notice that ATC-601 altitude display blanks.
On the DATATRAC: • Set the XMT label 031 word to -------->
Lbl SI 29-HEX XMT-11 031 01 55988
Note: This verifies the previous step; that altitude is being drawn from the control port; all other sources are now disconnected.
Note: This verifies that the Source Select Discrete is switchable.
Note: This enables the automatic altitude port select feature and verifies that the UUT switches to alternate port B even though port A is selected (REP ALT at PA).
Note: This verifies that the AUTO ALT discrete is switchable. SM P MSRC 00 1 100
Notice that the ATC-601 altitude display returns. Note: This digitally switches the UUT to port B. If this test is correct while the earlier test of port B altitude failed, suspect a problem with the Reporting Altitude Select discrete. If both tests failed, suspect a problem with the altitude data receivers.
On test : • Set EXT STBY switch to STBY. • Set the POWER switch OFF.
Lbl SI 29-HEX XMT-11 031 01 55980
SM P MSRC 00 1 100
On DATATRAC 200: • Set the XMT label 031 word to --------->
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP
TITLE
PROCEDURE
DESIRED RESULTS OR SETUP SCREEN
The remainder of the step is optional. Testing for various digital altitude inputs is primarily software verification and therefore unnecessary. If the UUT responds to one altitude word input it will likely respond to all. If you wish, you can set the XMT label 203 data field bits 12 through 28 to any combination of 1 and 0. The RCV label 203 word data field will follow the XMT word exactly while the ATC-601, set to the ATCRBS REPLY TEST mode, will show the altitude to the nearest 100 feet. When set to the MODE UF0 TEST, the ATC-601 displays altitude to the nearest 25 feet. The label 203 bit values are shown in note 2 following step 1.2. To 1. 2. 3. 4. 5. 6.
simulate any altitude up to about 131,000 feet: Select the desired altitude. Find the data bit with the maximum bit value less than the selected altitude. Make a note of that bit number. Subtract that bit value from your selected value. Find the next bit with the maximum bit value less than the remainder. Make a note of that bit number. Subtract that bit value from your remainder. Repeat steps 4 and 5 until the remainder is 0.
In the XMT label 203 data word, set all noted bits to 1. You should see your selected altitude, to the nearest 100 feet, displayed on the ATC-601. 7.0
ARING 575 Altitude Test
On test : • SOURCE SELECT: SEL • ALT TYPE SELECT: ARINC 429 On DATATRAC 200: • Set screen ------>
LBL SI 29-HEX RCV-11 >> NO DATA RECEIVED
SM P MSEC
LBL SI 031 01 203 01
SM P MSEC 00 1 100 00 1 100
29-HEX XMT-11 55980 10000
On test : • Connect parallel control cable to PRIMARY DIGITAL ALTITUDE SOURCE jack. • Set POWER switch to ON. • Set EXT STBY switch to OPR. On ATC-601: • Select ATCRBS REPLY TEST and press RUN to indicate TEST RUNNING. ATC-601 screen --------> On test : • Set ALT TYPE SELECT switch to ARINC 575 On DATATRAC: • Set XMT label 203 word --------> (just change the SM to 00) ATC-601 screen -------->
** ATCRBS REPLY TEST **
(lines 2-4 are irrelavent) CODE=5263 ***** LBL SI 031 01 203 01
29-HEX RCV-11 55980 10000
SM P MSEC 00 1 0100 00 1 0200
** ATCRBS REPLY TEST **
(lines 2-4 are irrelavent) CODE=5263 *****
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ALT=32,800 FT [1344] TEST RUNNING *****
ALT=16,400 FT [3230] TEST RUNNING *****
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP 7.0 (cont’d)
TITLE ARINC 575 Altitude Test (cont’d)
PROCEDURE DATATRAC screen --------->
DESIRED RESULTS OR SETUP SCREEN LBL SI 203 01
29-HEX RCV-11 10000
SM P MSEC 11 1 100
(ignore any other displayed words) LBL SI 031 01 203 01
29-HEX XMT-11 55980 20000
SM P MSEC 00 1 100 00 1 100
In addition to testing the altitude type select discrete, this test illustrates the differences between ARINC 429 and ARINC 575 data. Notice that the msb in the RCV label 203 word (above) are offset by one bit from the XMT label 203 word and the SSM code is 11 as opposed to the 00 in the XMT word. In ARINC 575, the LSB is bit 13; in ARINC 429 the LSB is bit 12. In ARINC 575, bits 30 and 31 determine the sign; 00 being positive. Notice also, that the altitude displayed on the ATC-601 corresponds to the code in the RCV word; not the XMT word. This is also due to the UUT being configured for ARINC 575 and thus the bit values are offset by 1 bit position which has the effect of changing the altitude by a factor of 1/2. On test : • Set ALT TYPE SELECT switch to ARINC 429 On DATATRAC: • Set XMT label 203 word ---->
LBL SI 031 01 203 01
(Set SM to 11)
ATC-601 screen:
29-HEX XMT-11 55980 20000
SM P MSEC 00 1 100 11 1 100
** ATCRBS REPLY TEST **
(lines 2-4 are irrelavent) CODE=5263 *****
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ALT=32,800 FT [1344] TEST RUNNING *****
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP 8.0
TITLE Mode S Address Disc-retes Test
PROCEDURE
DESIRED RESULTS OR SETUP SCREEN
On the test : • Set POWER switch OFF • Set all test mode s address switches to SEL except switch P1-56; set it to OFF. • Set POWER switch ON On ATC-601: • Set for MODE S ALL CALL TEST ------->
** MODE S ALL CALL TEST - NO REPLY ALL CALL ADDRESS = [ NUMBER = Press RUN to start
On ATC 601: • Press RUN • Note screen ----->
** MODE S ALL CALL TEST ALL CALL ADDRESS = FFFFFE TAIL NUMBER =
** ]
TAIL
ED ** [77777776]
****** TEST RUNNING *****
The remainder of this step will require a few minutes because of the delay involved in cycling power between each switch setting.
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On test : • Set POWER switch OFF. • Set each triad of address switches for an octal digit 6. • Set POWER switch ON.
After a few seconds, UUT begins to reply and shortly thereafter the ATC-601 screen shows the following address:
On test : • Set POWER switch OFF. • Set each triad of address switches for an octal digit 4. • Set POWER switch ON.
After a few seconds, UUT begins to reply and shortly thereafter the ATC-601 screen shows the following address:
On test : • Set POWER switch OFF. • Set each triad of address switches for an octal digit 0, except the eighth triad which is set to 1. • Set POWER switch ON.
After a few seconds, UUT begins to reply and shortly thereafter the ATC-601 screen shows the following address:
ALL CALL ADDRESS = DB6DB6
ALL CALL ADDRESS = 924924
ALL CALL ADDRESS = 000001
[66666666]
[44444444]
[00000001]
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP 9.0
TITLE TCAS / NO TCAS Discrete Select and TCAS Bus Test
PROCEDURE
DESIRED RESULTS
On test : • Set POWER switch OFF On DATATRAC 200: • Set XMT words as shown ----->:
LBL SI 031 01 203 01
29-HEX XMT-11 55980 20000
SM P MSEC 00 1 100 11 1 100
ATC-601 is not needed for this test but can be left on. On test : • Set POWER switch ON
After a few seconds the RCV portion of the DATATRAC 200 screen shows:
After data appears on the RCV display, press RCV and then INC to scroll the words so that you can see the 350 word.
LBL SI 350 01
On test : • Set POWER switch to OFF • Set TCAS/NO TCAS switch to TCAS On DATATRAC 200: • Press RCV and then ENT On test : • Set POWER switch to ON
After a few seconds the RCV portion of the DATATRAC 200 screen shows: (use INC key to scroll words) LBL SI 350 01
29-HEX RCV-11 00000
29-HEX RCV-11 45980
SM P MSEC 11 1 0200
SM P MSEC 11 1 0200
Refer to paragraph 5.7.2 for a more detailed discussion. The 45980 display translates into a diagnostic B3 which is interpreted: TCAS Bus Inactive. This verifies that the discrete properly configures the unit for operation with a TCAS. However, no TCAS data is being supplied in this step, therefore, the unit declares a B3 diagnostic. TCAS Bus Test, XPDR to TCAS
Connect the DATATRAC RCV to the TCAS OUT jack. that the data word labels are detectable as shown ------->. Note: Except for the diagnostic code in the label 350 data word, the data content is not important. It is quite likely that the data will be different. The presence of the data word labels shown verifies that the TCAS data bus output is active and appears to be normal.
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LBL 275 276 350
SI 00 10 01
29-HEX RCV-11 00000 07C00 45980
SM P MSEC 00 1 0150 00 1 0150 11 1 0150
Notice the higher speed. Other labels may also be present.
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP 9.0 (cont’d)
TITLE TCAS to XPDR Bus Test
PROCEDURE
DESIRED RESULTS
Note: In this step you need the capability of transmitting data to two separate input ports simultaneously and at different speeds; the 031 control word must be low speed (12.5-kbps) while the TCAS label 274 data word must be high speed (100-kbps). All DATATRAC instruments, as well as the JC Air 429E, can transmit at either of these speeds but only the DATATRAC 400 can do so on two separate ports simultaneously. Otherwise, you will need two simulators. If you do not have this capability, you may not be able to the integrity of the TCAS bus input port. If you are using a DATATRAC 400, or have access to a second bus simulator, connect your second transmitter port or data bus simulator to the TCAS IN and setup as shown -------->:
LBL SI 274 00
On bus reader RCV (1) display:
After a few seconds, the 350 word shows:
Note: The objective is to that the UUT recognizes a valid TCAS label 274 word and declares this by removing the diagnostic B3.
LBL SI 350 01
On the bus reader: Set the XMT (2) word to OFF
After a few seconds, notice that the B3 diagnostic returns.
29-HEX RCV-11 C0000
SM P MSEC 00 1 0100
Note: Be sure to set the higher speed.
29-HEX RCV-11 00000
SM P MSEC 11 1 0150
Note: This verifies that the unit is able to receognize a valid TCAS label 274 word and declare that by removing the B3 diagnostic code.
Note: Disconnect XMT (2) from the TCAS IN jack and CONNECT IT TO THE PRIMARY DIGITAL CONTROL. Reconnect RCV to the DATA BUS OUTPUT port. Final step in this test, all setups
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On test : • Set POWER switch to OFF • Set TCAS/NO TCAS switch to NO TCAS On DATATRAC 200: • Press RCV and then ENT On test : • Set POWER switch to ON
After a few seconds, the original 350 word returns: -----------------RCV--(ALL)---12.5 KHz Lbl SDI 32-Hex Data-1 SSM Par msec 350 01 00 00 01 17 11 1 0200
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP 10.0
TITLE Side 1/ Side 2 Discrete Test
PROCEDURE
DESIRED RESULTS
On test : • Set POWER switch OFF • Be sure SIDE 1/SIDE 2 switch is set to SIDE 1. On DATATRAC 200: • Same setup as in step 1.1. On ATC-601: • Set for ATCRBS REPLY TEST screen ------>
CODE= *****
On test : • Set POWER switch ON
After a few seconds, X FEED OUT and ATC-601 REPLY lamps light and the ATC-601 shows:
** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) ALT= TEST RUNNING
[ *****
]
** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE=5263 ALT=32,800 FT [1344] ***** TEST RUNNING *****
On test : • Set POWER switch to OFF • Set SIDE 1/SIDE 2 switch to SIDE 2 (wait a few seconds, then) • Set POWER switch to ON
Notice that UUT does not reply (X FEED OUT lamp and REPLY lamps are off and no altitude is displayed on ATC-601). Wait about 10 seconds.
On DATATRAC 200: • On XMT, label 031 word, set the SI to 10 and press INC
Notice that unit begins to reply almost immediately (XFEED OUT lamp turns on and ATC-601 REPLY lamp lights).
Note: UUT does not respond because the SI and side strapping do not agree. Note: If you do not allow sufficient time for the U to power down, it may not recognize the power interruption and fail to re-initialize properly. The SIDE 1/2 strap is one of several that is not monitored except at initialization. Therefore, if this test fails, cycle power again but allow more time between power-off and power-on.
Note: UUT responds because SI and side strapping agrees.
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On DATATRAC 200: • On XMT, label 031 word, set SI to 01 and press INC.
Notice that unit stops replying (X FEED OUT lamp and ATC-601 REPLY lamps turn off).
On test : • Set POWER switch to OFF • Set SIDE 1/SIDE 2 switch to SIDE 1 (wait a few seconds) • Set POWER switch to ON
After a few seconds, X FEED OUT and ATC-601 REPLY lamps light and the ATC-601 shows that the UUT is replying.
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP 11.0
TITLE AIR/ GND Discrete Test
PROCEDURE
DESIRED RESULTS
On test : • Same as initial setup • Set EXT STBY switch to STBY On DATATRAC 200: • Same setup as for step 1.1. On ATC-601: • Set for MODE S UF4 TEST screen -------->
** MODE S UF4 TEST - NO REPLY ** DF FS= ADDRESS= *****
On test : • Set EXT STBY switch OPR • Set AIR/GND switch AIR ATC-601 screen shows ----->:
DR=
UM=
TEST RUNNING
AC= *****
After a few seconds, X FEED OUT and ATC-601 REPLY lamps light and the ATC-601 shows: ** MODE S UF4 TEST - ED ** DF 4 FS=0 DR=00 UM=00 ADDRESS=000001 *****
TEST RUNNING
AC=32,775 FT *****
Note: Initially the screen may show FS=2 for about 2 seconds and then change to FS=0. On test : • Set AIR/GND switch to GND
After a few seconds, the ATC-601 shows: ** MODE S UF4 TEST - ED ** DF 4 FS=1 DR=00 ADDRESS=000001 *****
UM=00 AC=32,775 FT
TEST RUNNING
*****
Of particular significance here is the FS (flight status) indication. For a detailed description of each of these message fields, refer to the Theory of Operation section. On test : • Set AIR/GND switch to AIR
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After a few seconds, notice that the ATC-601 FS field again shows 0.
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP 12.0
TITLE DL ANT/ SGL ANT Discrete Test (TDR-94D only)
PROCEDURE
DESIRED RESULTS
On test : • Set POWER switch OFF On DATATRAC 200: • Same setup as for step 1.1. On ATC-601, set for SQUITTER TEST screen -----> Be sure the ATC-601 is connected to the top antenna port. On test : • Set DL ANT/SGL ANT switch to DL ANT • Set POWER switch ON You can watch the PERIOD display for a time. After ED appears, press RUN/STOP to stop the test.
** SQUITTER TEST - NO REPLY ** PERIOD = SECONDS TAIL NUMBER = SQUITTER ADDRESS= [ *****
TEST RUNNING
]
*****
After a few seconds, the ATC-601 screen shows: See note below. ** SQUITTER TEST - ED PERIOD = 2.00 SECONDS TAIL NUMBER = SQUITTER ADDRESS= [ *****
TEST RUNNING
** ]
*****
See the note at the end of this step for test tolerances. On test : • Set POWER switch OFF • Set DL ANT/SGL ANT switch to SGL ANT • Set POWER switch ON After FAILED (or ED) appears, press RUN/STOP to stop the test.
After a few seconds, the ATC-601 screen shows: ** SQUITTER TEST - FAILED PERIOD = SECONDS TAIL NUMBER = SQUITTER ADDRESS= [ *****
TEST RUNNING
** ]
*****
Note: This test is intended to fail. When the UUT is set for single antenna operation, there is no transmission from the top antenna port. Therefore, if this test indicates ED, recheck all switch settings, or suspect a problem with the SGL/DL ANT select strap. It should not .
On test : • Set POWER switch OFF On ATC-601: • Press RUN to stop the test. • Remove rf terminator from bottom antenna connector • Connect ATC-601 cable to bottom antenna connector • Connect rf terminator to top antenna connector
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP 12.0
TITLE DL ANT /SGL ANT Discrete Test (cont’d) (TDR-94D only)
PROCEDURE On test : • Set POWER switch to ON. On ATC-601: • Press RUN to start the test.
DESIRED RESULTS After 15 to 20 seconds, the ATC-601 screen shows: See note below. ** SQUITTER TEST - ED PERIOD = 1.00 SECONDS TAIL NUMBER = SQUITTER ADDRESS= [
• After ED appears, press RUN/STOP to stop the test. On test : • Set POWER switch OFF • Set DL ANT/SGL ANT switch to DL ANT • Set POWER switch ON
*****
TEST RUNNING
** ]
*****
After 15 to 20 seconds, the ATC-601 screen shows: See note below. ** SQUITTER TEST - ED PERIOD = 2.00 SECONDS TAIL NUMBER = SQUITTER ADDRESS= [
• After ED appears, press RUN/STOP to stop the test.
*****
TEST RUNNING
** ]
*****
Note: The PERIOD value tends to vary somewhat in all cases. When the UUT is set for dual antenna operation and the ATC-601 is monitoring the top or the bottom antenna port, the value can vary from 1.6 to 2.4. When the UUT is set for single antenna operation there should be no transmission from the top antenna port and the transmission PERIOD from the bottom antenna port can vary from 0.6 to 1.4. 13.0
Burst Tune and CrossFeed In Discrete Test
On test : • Set POWER switch OFF • CONTROL DATA PORT SEL: PB On DATATRAC 200: • Same setup as for step 1.1. On ATC-601, set for ATCRBS REPLY TEST screen -----> If necessary, reconnect ATC-601 to top antenna connector, with terminator on bottom antenna connector.
** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE= *****
ALT= [ ] TEST RUNNING *****
On test : • Set POWER switch ON
After a few seconds, the test X FEED OUT and the ATC-601 REPLY lamps light indicating that the unit is replying. The ATC-601 screen data indicates ED.
On test : • Set X FEED IN/OUT switch to IN
Notice that both X FEED lamps are lighted.
On DATATRAC 200: • Set XMT to OFF
Notice that the X FEED OUT and ATC-601 REPLY lamps turns off (X FEED IN stays on).
Note: The easiest method of interrupting the data input is simply to disconnect it from the test .
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP 13.0 (cont’d)
TITLE Burst Tune and CrossFeed In Discrete Test (cont’d)
PROCEDURE
DESIRED RESULTS
On DATATRAC 200: • Set XMT to ON (reconnect the control input)
Notice that the X FEED IN and OUT and REPLY lamps are lit.
On test : • Set XFEED switch to OUT. • Set BURST switch to BURST
Notice that XFEED IN lamp turns off and that UUT replies (X FEED OUT and REPLY lamps turn on).
On test : • Disconnect the DATATRAC XMT input from the test .
Notice that UUT continues to reply (X FEED OUT and REPLY lamps stay on).
On DATATRAC 200: • Set BURST switch to OFF
Notice that UUT stops replying (X FEED OUT and REPLY lamps turn off).
On test : • Set BURST switch to BURST
Notice that UUT does not reply (X FEED OUT and REPLY lamps remain off).
On test : • Reconnect the DATATRAC XMT to the test
Notice that UUT replies (X FEED OUT and REPLY lamps turn on).
On test : • Set BURST switch to OFF 14.0
Output Port Discrete Test
On test : • Set POWER switch OFF • OUTPUT PORT SELECT: ARINC 429 PORT A On DATATRAC 200: • Set for the same screen as for test 1.1 On ATC-601, set for ATCRBS REPLY TEST screen ----->
** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE= *****
ALT= [ ] TEST RUNNING *****
On test : • Set POWER switch ON
After a few seconds, the test X FEED OUTand the ATC-601 REPLY lamps light indicating that the unit is replying. The ATC-601 screen data indicates ED.
On test : • Set OUTPUT PORT SELECT switch to ARINC 429 PORT B
Notice that there is no change in the test result; X FEED OUT and REPLY lights are on and ATC-601 display does not change.
On test : • Set OUTPUT PORT SELECT switch to ARINC 429 PORT A
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP 15.0
TITLE Control Data Input Port Select Discrete Test
PROCEDURE
DESIRED RESULTS
On test : • Set POWER switch OFF • Set SOURCE SELECT switch to SEL • ALT TYPE SELECT: ARINC 429 • CONTROL DATA SELECT: ARINC PORT PA On DATATRAC 200: • Same setup as for step 1.1. On ATC-601, set for ATCRBS REPLY TEST screen ----->
** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE= *****
16.0
Manual STBY Discrete Test
ALT= [ ] TEST RUNNING *****
On test : • Set POWER switch ON
After a few seconds, the test X FEED OUT and the ATC-601 REPLY lamps light indicating that the unit is replying. The ATC-601 screen data indicates ED.
On test : • Set CONTROL DATA SELECT switch to ARINC PORT PB
Notice that there is no change in the test result; X FEED OUTand REPLY lights are on and ATC-601 display does not change.
On test : • Set CONTROL DATA SELECT switch to ARINC PORT PC
Notice that there is no change in the test result; X FEED OUT and REPLY lights are on and ATC-601 display does not change.
On test : • Set EXT STBY switch to STBY • Set POWER switch OFF • Set CONTROL DATA SELECT switch to ARINC PORT PA On DATATRAC 200: • Same setup as for step 1.1. On ATC-601: • Set for ATCRBS REPLY TEST screen ---------->
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** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE= *****
ALT= [ ] TEST RUNNING *****
On test : • Set POWER switch ON • Set EXT STBY switch to OPR
After a few seconds, the test X FEED OUTand the ATC-601 REPLY lamps light indicating that the unit is replying. The ATC-601 screen data indicates ED.
On test : • Set EXT STBY switch to STBY
Note that X FEED OUT lamp and ATC-601 REPLY lamps turn off and ATC-601 indicates NO REPLY. See note below.
On test : • Set EXT STBY switch to OPR
Note that X FEED OUT lamp and ATC-601 REPLY lamps light almost immediately and ATC-601 indicates ED.
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP 17.0
TITLE Max Airspeed Test
PROCEDURE
DESIRED RESULTS
On test : • Set POWER switch OFF • ALT TYPE SELECT: ARINC 429 • Be sure that all three MAX AIRSPEED switches are set to OFF (opposite of SEL). On DATATRAC 200: • Same setup as for step 1.1. (The DATATRAC is used here only for tuning data.) On ATC-601: • Set for MODE S UF0 TEST screen ------>
** MODE S UF0 TEST - NO REPLY ** DF
VS= ADDRESS= *****
On test : • Set POWER switch ON
RI=
AC=
TEST RUNNING
*****
After a few seconds, the test X FEED OUT lamp and the ATC-601 REPLY lamps light indicating that the unit is replying.
Note the ATC-601 screen ----------->
** MODE S UF0 TEST - ED ** DF 0 VS=0 RI=8 ADDRESS=000001 *****
AC= 32,775 FT
TEST RUNNING
*****
Exercise the MAX AIRSPEED switches on the test and the correct RI indication as shown in the following list. Cycle power between each switch change. Allow about 2 or 3 seconds OFF time and about 5 seconds for processor initialization and ATC-601 response time between each switch setting. MAX AIRSPEED SWITCH BIT 15 BIT 16 BIT 17 OFF OFF OFF SEL OFF OFF OFF SEL OFF SEL SEL OFF OFF OFF SEL SEL OFF SEL OFF SEL SEL SEL SEL SEL
RI VALUE 8 9 A B C D E F (not an assigned configuration)
It is worth noting that in this test mode the ATC-601 displays the altitude to the nearest 25 feet.
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP 18.0
TITLE Ext Suppression Test
PROCEDURE
DESIRED RESULTS
On test : • ALT TYPE SELECT: ARINC 429 On DATATRAC 200: • Same setup as for test 1.1. On ATC-601: • Set for ATCRBS REPLY TEST screen -----> • Connect scope channel A to the test SUPPR test points. • Connect scope channel B to the REPLY VIDEO BNC connector on the ATC-601. • Set the scope to display both channels
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** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE= *****
ALT= [ ] TEST RUNNING *****
Note a (approx) 30µs pulse on channel A. Note a reply waveform on channel B. If your scope is able, you will see the individual reply code pulses on channel B. You may also see the occasional squitter transmission which appears as a much longer series of pulses at about 1 transmission every 2 sec. Of particular importance, however, is that the channel A (suppression) pulse is about 30 µs long during ATCRBS reply, and brackets the 21 µs ATCRBS reply. During squitter transmission, the suppression pulse extends to bracket the squitter transmission. The squitter transmission is a DF11 reply about 72 µs long.
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP 19.0
TITLE ADLP Select, Discrete Strap Test
PROCEDURE
DESIRED RESULTS
On test : • Be sure DATALINK switch is set to NO ADLP. On DATATRAC 200: • Same setup as for test 1.1. DATATRAC RCV screen ------>
LBL SI 350 00
29-HEX RCV-11 60000
SM P MSEC 11 1 0200
LBL SI 350 00
29-HEX RCV-11 25100
SM P MSEC 11 1 0200
Note: The ATC-601 is not needed for this test but it can remain connected and operating. On test : • Set POWER switch to OFF • Set DATALINK switch to ADLP. • Be sure DATALINK SELECT switch is set to A/B. • Set POWER switch to ON.
Note: The diagnostic A2 identifies an inactive ADLP bus. This test verifies that the ADLP enable discrete is functional.
DATATRAC RCV screen ------> On test : • Set POWER switch to OFF. • Set DATALINK switch to NO ADLP. • Set POWER switch to ON.
LBL SI 350 01
29-HEX RCV-11 60000
SM P MSEC 11 1 0200
DATATRAC RCV screen ------> Note: The Airborne Datalink system is not fully implemented at this time. If and when an ADLP (Airborne DataLink Processor) becomes available and operational, suitable procedures will be provided to the integrity of the ADLP input/output ports. At this point, therefore, verification of the ADLP SELECT strap is seen as sufficient to prevent nuisance diagnostics that can occur if the select input should be defective. You will notice that the DATALINK SELECT A/B, C/D function is also not tested.
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP 20.0
TITLE Remote IDENT Discrete Test
PROCEDURE
DESIRED RESULTS
On test : • Same as initial setup On DATATRAC 200: • Same setup as for test 1.1. On ATC-601: • Setup for ATCRBS REPLY test
** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE= *****
On test : • Press and release the REMOTE IDENT switch. On DATATRAC 200: • Note RCV screen ----->:
On ATC-601: • Notice the ID display. ID should display for about 18 seconds.
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LBL SI 031 00
ALT= [ ] TEST RUNNING *****
29-HEX RCV-11 SM P MSEC 55984 11 1 0200 |<----Ident bit
Note: The 4 should appear in the data field only while the switch is being pressed. This verifies that the discrete input is functional. ** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE=ID5263 ALT= 32,800 FT [1344] |<----ID display ***** TEST RUNNING *****
On Datatrac 200: • Set the label 031 XMT word:
LBL SI 031 00
On DATATRAC RCV and on ATC-601:
You should see the same displays as immediately above. If the test failed using the REMOTE IDENT switch, but succeeds here, then suspect a failure in the discrete input or the test .
On Datatrac 200: • Set the label 031 XMT word:
LBL SI 031 00
29-HEX XMT-11 55984
29-HEX XMT-11 55980
SM P MSEC 00 1 100
SM P MSEC 00 1 100
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP 21.0
TITLE Self Test
PROCEDURE
DESIRED RESULTS
On test : • Set POWER switch OFF • ALT TYPE SELECT: ARINC 429 • AIR/GND: AIR • SELF TEST: ENABLE: OFF On DATATRAC 200: • Same setup as for test 1.1. On ATC-601: • Set for ATCRBS REPLY TEST ---------->
** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE= *****
ALT= [ ] TEST RUNNING *****
On test : • Set POWER switch ON
After a few seconds, the test X FEED OUT lamp and the ATC-601 REPLY lamps light indicating that the unit is replying. The ATC-601 screen indicates ED.
On DATATRAC 200: screen shows: --------->
LBL 031 203 350
SI 01 01 01
29-HEX RCV-11 559A0 00000 00000
SM 11 11 11
P 1 1 1
MSEC 0200 0200 0200
(You may need to press INC to display all three labels.) In the next few steps, watch the DATATRAC RCV screen carefully. On the test : • Press and hold the SELF TEST pushbutton for about 1 sec.
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After a few seconds, notice that the DATATRAC and ATC-601 screens do not change. (The test TEST lamp lights while you hold the switch but otherwise there is no change.)
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP 21.0
TITLE Self Test (cont’d)
PROCEDURE
DESIRED RESULTS
On test : • Set the AIR/GND switch to GND • Set the SELF TEST/ENABLE switch to ON • Press and hold the SELF-TEST button for about 1 s
Self-test Displays: After a few seconds, notice that the X FEED OUT lamp turns off briefly while the ATC-601 screen shows +’s or -’s in most of the data fields, followed by blank fields.
Note: The test TEST lamp lights while you hold the switch. This has no bearing on UUT operation, however. If the lamp does not light, check the test . On the DATATRAC 200, press RCV (either once or twice) to return to the setup screen, followed by ENT, to clear the screen of any extraneous labels.
After a few seconds, notice that the X FEED OUT lamps turns on again and the ATC-601 screen returns to the normal display. On the DATATRAC, notice that the SM’s change to 10 and then back to 11. This instrument has a tendency to retain superceded data words, therefore, you may need to clear the screen repeatedly to be sure that you are viewing current data. You should try to be especially watchful of the 350 data word and try to catch any diagnostic codes that may be displayed during the selftest sequence.
On the test : • Set the SELF TEST/ENABLE switch to OFF. • Press and hold the SELF TEST button for about 1 s.
Notice that the self-test displays as described above do not appear..
On the test : • Set the SELF TEST/ENABLE switch to ON. • Set the AIR/GND switch to AIR. • Wait about 5 seconds *. • Press and hold the SELF TEST button for about 1 s.
Notice that the self-test displays as described above do not appear..
Note: This verifies that self test is properly inhibited by the self-test inhibit discrete.
Note: This verifies that self test is properly inhibited by the AIR/GND discrete.
*Note: The U must be allowed sufficient time to complete at least one software cycle in order to recognize the change in the AIR/GND discrete. If you press the SELF TEST switch in less than about 3 seconds of setting the AIR/GND switch to AIR, the unit may execute self-test as though it were not inhibited. This should be seen as normal. On the test : • Set the SELF TEST/ENABLE switch to ON. • Set the AIR/GND switch to GND. • Press and hold the SELF TEST button for about 1 s.
Notice the self-test displays as described above reappear. Note: This verifies that the self-test inhibit and AIR/GND discretes are switchable.
This completes this test sequence. Successful completion of this series provides reasonable assurance that the unit is operational. However, this test does not satisfy the requirements of a Detailed Performance Test which must be performed after any repair operation. Turn off all power, disconnect the equipment, and return it to its normal storage location. Return the UUT to its original shipping container, or equivalent, if it is to remain in storage. Otherwise, prepare it for installation.
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Procedures using the JcAIR 429E Transmitter/Receiver Table 5-13. Acceptance Test Procedures, Using the JcAIR 429E Transmitter/Receiver
STEP
TITLE
PROCEDURE
DESIRED RESULTS
1.0
Setup
Note: If you are using a Test built according to instruction provided in a previous edition of this manual, it may be necessary to upgrade the . Refer to paragraph 5-8. • If not already done, connect equipment as shown in figure 5-2 using cables shown in figure 5-9. • TX to test DIGITAL CONTROL port, • Parallel connect TX to test PRIMARY DIGITAL ALTITUDE PORT, • RX to test DATA BUS READER port. • Connect the ATC-601 to the UUT bottom antenna connector. • Connect an rf termination to the TOP antenna port (TDR-94D only). • Connect power to test power jacks - observe proper polarity. • Preset the switches as shown in paragraph 5.4.5.6 above. Be sure POWER switch is OFF and EXT STBY switch is at STBY. On test , set the MODE S ADDRESS switches to any combination except all OFF or all to SEL. If all switches are set OFF or all set SEL, a diagnostic code FF will result.
1.1
Setup
Turn the JcAIR 429E on and set the TX 1 and TX 2 screens ----->
031 01 1566C1 00 203 01 640001 11
Turn on TDR-94/94D
On test : • Set POWER switch to ON Monitor current. If OK: • Set EXT STBY switch to OPR Monitor current.
If the unit has been in service and there is a possibility of an over-current condition, monitor the power supply current output. The setup should draw no more than 1.5 A. Typically it draws about 0.9 to 1.1 A when the UUT is transmitting.
Setup (power-up)
Turn the ATC-601 on and press SELECT for the screen -------------->
** ATCRBS REPLY TEST - NOT RUN **
(lines 2-4 are irrelevant) CODE=
See Note in next cell below. 1.2
ARINC 429 tuning test
On the ATC-601, press RUN ATC-601 screen --------->
ALT= Press RUN to start
[
]
UUT responds to interrogations as indicated by a lighted XFEED OUT lamp on the test and a lighted REPLY lamp on the ATC-601.
Note: When power is applied and proper control data is supplied, the TDR-94/94D should turn on the XFEED OUT lamp almost immediately. The FAULT MON lamp may be off for a few seconds and then turn on. A lighted FAULT MON lamp should generally be seen as a no-fault indication. See table 109.
CODE=5263 *****
The JcAIR 429E RX displays show --------->
203 01 E40000 11 031 01 F56681 11 350 01 600001 11
** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) ALT=32,800 FT [1344] TEST RUNNING *****
To change the CODE, see note 1 below. To change the ALTITUDE, see note 2 below.
Note: Any other labels displayed are irrelevant to this test. See Note 3 below.
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maintenance 523-0775657 Table 5-13. Acceptance Test Procedures, Using the JcAIR 429E Transmitter/Receiver (Cont).
STEP
TITLE
PROCEDURE
DESIRED RESULTS
Note 1. You can change the (octal) CODE=XXXX display by changing data bits 18 through 29 in the label 031 data word (TX field of the JcAIR 429E) as follows: ATC-601 digit: Bit: Data: Hex value: JcAIR 429E (Hex): Binary: Octal value: Produces CODE:
32 Par 8
| 0
Bits 11 through 17, of the JcAIR 429E (Hex) bits: Bit: 16 Bit values: 8 Assignment:
| Pad
31 30 SSM 4 2 1 0 0
First Second 29 28 27 26 25 |<-----Data -------> 1 8 4 2 1 | | 5 | 1 0 1 0 1 4 2 1 4 2 5 2
Third 23
24 8 | 0 1
4
21
2
1 | 0 1
6 1 4
Fourth 20 19 18 ----->| 8 4 2 | 6 0 1 1 4 2 1 3
22
1 2 6
17 Pad 1 |
label 031 control word, are assigned the following functions: 5th 6th 15 14 13 12 11 10 9 4 2 1 8 4 2 1 | | | Pad | |<- |<--SDI Pad | | |<--Altitude reporting, 1 = OFF | |<--Ident, 1 = ON |<--Altitude port select, 1 = B
Note 2: You can set the TX label 203 data field bits 12 through 28 to any combination of 1 and 0. The RCV 1 label 203 word data field will reflect the TX word while the ATC-601 will show the altitude to the nearest 100 feet. The label 203 word data bit values are as follows: JcAIR 429E digit *: lst | 2nd | | Hex value: 8 4 2 1 8 Bit: 29 28 27 26 25 24 Alt value:(sign bit; 0 = +) 65536 32768 16384 8192 4096 (in feet) JcAIR 429E digit *: | 4th | | 5th Hex value: 8 4 2 1 8 4 2 Bit: 20 19 18 17 16 15 14 Alt value 256 128 64 32 16 8 4 (in feet) Determine the altitude by totaling the bit values of all bits set to 1.
| 1 13 2
3rd 4 23 2048
2 22 1024
| 8 12 1
4 11 **
| 1 21 512 6th 2 10 **
| 1 09 **
* The left-most Hex Data bit (bit 1) is determined by the parity bit 32, the SSM bits 31 and 30, and sign bit 29. Since bit 29 must always be a 0, this Hex bit must always be an odd number. **= Not used Note 3: You may see a label 371 data word. This is the ARINC 429 Specific Equipment Identification word which is structured the same as other ARINC 429 words but conveys the following information: Bits 11 through 18 identify the equipment type. The code for ATC transponders is 18 therefore bits 14 and 15 are 1; the others are 0. Bits 19 through 24 convey a binary code identifying the equipment manufacturer. Collins’ is 6. Therefore bits 20 and 21 are 1; all others are 0. Bits 24 through 29 are reserved for purposes to be defined. When ARINC 572 altitude data is active, you will see a label 200 data word. This word reflects the ARINC 572 (Gillham code) altitude data. This word is structured the same as other ARINC 429 words, except bits 9 and 10 are part of the data field; i.e., there is no SDI. Bits 9,10, and 11 reflect the D1, D2, and D4 code bits respectively. Bits 13, 14, and 15 reflect the C-bits, bits 17, 18, and 19 reflect the B-bits, and 21, 22, and 23 reflect the A-bits.
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maintenance 523-0775657 Table 5-13. Acceptance Test Procedures, Using the JcAIR 429E Transmitter/Receiver (Cont).
STEP
TITLE
2.0
Test set, Auto Test
PROCEDURE On ATC-601: • Press RUN/STOP to stop • Press AUTO TEST • Press RUN to start Note: This test requires a few seconds to run. It will stop automatically.
DESIRED RESULTS Ensure that all tests . See note below.
On test : • Set EXT STBY switch to STBY • Set POWER switch OFF On UUT: • Move the test set rf cable to the UUT top antenna connector and the rf termination to the bottom. On test : • Set POWER switch ON • Set EXT STBY switch to OPR On ATC-601: • Repeat the AUTO TEST
Ensure that all tests . See note below.
Note. The AUTO TEST sequence will indicate FAILED even when certain tests result in a NO REPLY condition. The NO REPLY conditions are the result of no ADLP (Airborne Data Link Processor) data in this setup. This same condition is likely to occur when using the ATC-601 as a ramp tester when testing an installation not equipped with an ADLP. To that the test can be seen as successful, proceed as follows: • When the test sequence is completed and the ATC-601 stops, as indicated by INTERR and REPLY lamps off, you will likely see a screen as follows: ** AUTO TEST - FAILED ** MODES TESTED - A,C,S FREQ: MODES ED - A,C,S ERP: MODES FAILED -> MTL: DIVERSITY ISOLATION: >40 dB Press RUN to start
1089.92 Mhz 55 Dbm -77 Dbm
(The FREQ, ERP, and MTL values can vary from UUT to UUT and to a lesser degree on UUT temperature.) the test results as follows: On the ATC-601, use the SELECT up arrow or down arrow key to scroll through the following list of tests performed; the numbers are for reference purposes only and do not appear on the test set screen. If you use the down arrow, you will see the list in the order shown; from test 1 through test 19. If you use the up arrow key, you will see the list in reverse order, starting at test 19. You will likely notice that all tests ed except tests 13, 14, and 15 which had a NO REPLY. NO.
TEST NAME AND RESULT
1.0
**
REPLY DELAY TEST - ED
2.0
**
REPLY JITTER TEST - ED
**
MODE S: =< 0.05 µs ITM: =< 0.06 µs (All others): =< 0.1 µs
3.0
**
ATCRBS REPLY TEST - ED
**
F1 TO F2 SPACING: 20.3 (±0.1) µs All PULSE WIDTH: 0.45 (±0.1) µs
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TEST SPECIFICATION / DESCRIPTION **
MODE S: 128.00 (±0.25) µs ITM A: 128.00 (±0.25) µs (All others): 3.00 (±0.50) µs
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maintenance 523-0775657 Table 5-13. Acceptance Test Procedures, Using the JcAIR 429E Transmitter/Receiver (Cont).
STEP
TITLE
NO.
TEST NAME AND RESULT
4.0
**
5.0
** ATC ONLY ALL-CALL TEST - ED **
The TDR-94/94D should not reply to this mode a and mode c only interrogation. ED indicates a correct (NO) response.
6.0
** MODE S ALL-CALL TEST - ED **
The TDR-94/94D should reply to this interrogation. ED indicates a correct response. UUT address previously determined in mode s interrogation, is sent to UUT in UF4 (Uplink Format 4) and verified in DF4 (Downlink Format 4) reply.
7.0
** INVALID ADDRESS TEST - ED **
UUT is interrogated with two addresses, both of which are different from the correct address. ED indicates UUT did not reply to interrogation.
8.0
** SPR ON/OFF TEST - ED **
UUT is interrogated first with SPR ON and verifies a proper reply, then with SPR OFF and verifies no reply. ED indicates UUT responded correctly.
9.0
**
MODE S UF0 TEST - ED
**
UUT is interrogated with mode S UF0, ing correct altitude as compared to previous mode c reply, correct address as compared to DF11 address, and correct format. ED indicates correct UUT response.
10.0
**
MODE S UF4 TEST - ED
**
UUT is interrogated with UF4, ing correct altitude as compared to previous mode c reply, correct address as compared to DF11 reply, and correct format. ED indicates correct UUT response.
11.0
**
MODE S UF5 TEST - ED
**
UUT is interrogated with UF5, ing the correct ID code as compared to previous mode a reply, correct address as compared to DF11 reply, and correct format. ED indicates correct UUT response.
12.0
**
MODE S UF11 TEST - ED
13.0
**
MODE S UF16 TEST - NO REPLY
**
(See test 15.)
14.0
**
MODE S UF20 TEST - NO REPLY
**
(See test 15.)
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PROCEDURE
DESIRED RESULTS
SLS LEVEL TEST - ED
TEST SPECIFICATION / DESCRIPTION UUT is interrogated with F2 (SLS) pulse at 9 dB below F1. UUT should reply to this interrogation. Then UUT is interrogated with F2 equal to F1. UUT should not reply. ED indicates correct response to both tests.
**
UUT is interrogated with UF11, ing correct address as compared to previous response, and correct format. ED indicates correct UUT response.
**
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maintenance 523-0775657 Table 5-13. Acceptance Test Procedures, Using the JcAIR 429E Transmitter/Receiver (Cont).
STEP
TITLE
PROCEDURE
DESIRED RESULTS OR SETUP SCREEN
NO.
TEST NAME AND RESULT
15.0
**
MODE S UF21 TEST - NO REPLY
16.0
**
SQUITTER TEST - ED
17.0
**
FREQUENCY TEST - ED
**
Freq: 1090 (±3) MHz
18.0
**
DIVERSITY TEST - ED
**
ATC-601 monitors squitter pulses on active antenna port (as in test 16) and then monitors for intervening squitter pulses that are not greater than 20 dB below the active squitter. This test will always fail when the UUT is a TDR-94 (non diversity) because squitter is transmitter every second on the same antenna port. If you are testing a TDR-94D and the DL ANT/SGL ANT switch is set to SGL ANT, the test will also fail because this causes the unit to operate like a TDR-94. ED indicates a correct response from a TDR-94D.
19.0
**
MTL DIFFERENCE TEST - ED
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TEST SPECIFICATION / DESCRIIPTION **
UUT is interrogated with UF16, UF20, and UF21. These formats are all related to the airborne data link function. This function has not been implemented. The TDR-94/94D will not reply to these interrogation formats. NO REPLY should not be seen as a failure. When set for daul antenna operation, the TDR-94D transmits a squitter pulse once each second, alternating between top and bottom antenna ports. The ATC-601 verifies that one squitter pulse is received every 1.6 to 2.4 seconds. The test ANT SGL/DL switch must be in the DL position. When set for single antenna operation, or when testing a TDR-94, only the bottom antenna port is used. In this case the ATC-601 verifies that one squitter pulse is received every 0.6 to 1.4 seconds. When you change the ANT SGL/DL switch, you must cycle power to the UUT in order for it to take effect. ED indicates a correct UUT response.
**
**
ATC-601 verifies that the MTL difference between mode a and mode c responses is < 1.0 dB. At this point, another press of the arrow key will display the first item; either 1.0 or 18.0, depending on which arrow was used.
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maintenance 523-0775657 Table 5-13. Acceptance Test Procedures, Using the JcAIR 429E Transmitter/Receiver (Cont).
STEP 3.0
TITLE Power output and Rcvr Sensitivity Test
PROCEDURE
DESIRED RESULTS OR SETUP SCREEN
On test select: • Set EXT STBY switch to STBY • Set POWER switch OFF On ATC-601: • Select POWER TEST • Press RUN to indicate TEST RUNNING -------->
** POWER TEST - Top Antenna ANTENNA UNITS ERP MTL *****
TEST RUNNING
** STATUS NO REPLY
*****
Note: If necessary, press SELECT (or SLEW) to select Top Antenna. Be sure that the ATC-601 rf cable is connected to the top antenna port and the rf termination is connected to the bottom port. On JcAIR 429E: set TX --->
screen ---
On test : • Set POWER switch ON • Set EXT STBY switch to OPR
031 01 1566C1 00 203 01 640001 11 ** POWER TEST - Top Antenna ANTENNA UNITS ERP MTL Top dBm 55.7 -76.0
** STATUS ED
***** TEST RUNNING *****
After a few seconds, the ATC-601 shows ----> On ATC-601: Press RUN/STOP to stop the test. If the UUT is a TDR-94, skip this step. On test : • Set EXT STBY switch to STBY • Set POWER switch OFF • On TDR-94D mount: Swap the rf cable connection and termination on the UUT antenna ports. (Rf cable to bottom port and termination to top antenna port.) On test : • Set POWER switch to ON • Set EXT STBY switch to OPR On ATC-601: • Press RUN to indicate TEST RUNNING Wait a few seconds then press RUN/STOP to stop the test.
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If a failure is detected, a small arrow will be shown to the left of the offending parameter(s). Make a note of the test results, if a record is needed, and label it as applicable to the UUT bottom antenna port. The data displayed here will be overwritten on the next test. You should see a similar display on the ATC-601 except this data is applicable to the top antenna port. The data can be slightly different. See below for test tolerances and an explanation of a possible failure indication due to high sensitivity. Note: You may also select bottom antenna screen on the ATC-601. Note: You may see a marginal test failure if the UUT is relatively cold. In this case allow the unit to warm up a few minutes and then repeat the test.
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STEP 3.0 (cont’d)
TITLE Power output and Rcvr Sensitivity Test (cont’d)
PROCEDURE
DESIRED RESULTS OR SETUP SCREEN
The test tolerances are: ERP: > 48.5 dBm and < 57.0 dBm MTL: -73.0 (±4.0) dBm The ATC-601 will indicate that the UUT has failed if the MTL is more than -77.0 dBm or less than -71 dBm. Collins prefers, however, that a failure should be reported only if the MTL is less than -71 dBm. Therefore, if you have a unit displaying an MTL of -77.1 or more, you should see that value as acceptable. Obviously, an MTL indication approaching -80 dBm or more may be cause for suspecting a problem with test set calibration. You may also see a failure because the ERP, Effective Radiated Power or Peak Pulse Power , is more than 57 dBm. Power measurements taken with a ramp tester can be confusing. The various test equipment manufacturers use different dimensions for displaying the test results, the test specifications are not always clear on how the test is to be performed to produce the specified result, and the test method; direct or radiation, yields different results. As in the case of MTL, an ERP slightly greater than 57 dBm ( e.g., 59 dBm max), using the direction connection method, should not be seen as cause for unit rejection. DO-181 specifies the transponder power output at the antenna. Testing a unit on the bench by direct connection to the antenna port yields a power reading at the transmitter output. The difference is, of course, antenna cable and connector losses. DO-181 specifies transponder power output in watts and dBW. The IFR ATC-601 displays power in dBm (ERP). The TIC-48/-49 displays power in watts. The following chart may be useful for proper test evaluation: Watts
dBW
dBm
50 70 100 125 150 200 250 300 350 400 450 500
16.99 18.45 20.00 20.97 21.76 23.01 23.98 24.77 25.44 26.02 26.53 26.99
46.99 48.45 50.00 50.97 51.76 53.01 53.98 54.77 55.44 56.02 56.53 56.99
TDR-94/94D Spec
(Min for airplanes limited to 15 000 ft and 175 kts.) Minimum at antenna (ramp testing)
Minimum direct (on bench)
Maximum at antenna
To convert milliwatts to dBm, or watts to dBW: a. For calculators with log(10) (usually written log or LOG): P(dBW) = 10 x LOG(P). b. For calculators with log(e) (usually written ln or LN): P(dBW) = 10 x [LN(P) / LN(10)] In both cases, P must be in watts. For dBm, P must be in milliwatts; for example: 450 watts = 450 000 milliwatts. To convert from dBm to milliwatts or dBW to watts: a. For calculators equipped with LOG : P = INVLOG (P(dBW) / 10) b. For calculators equipped with LN : P = INVLN [(P(dBW) / 10) x 2.30259] The result P will be in milliwatts if you use P(dBm) , or watts if you use P(dBW). Most scientific calculators have both the LN (natural logarithm - base e) and the LOG (logarithm base 10) capabiliity. Likewise, most have an INV (inverse) function. Thus you must press INV and then LN or LOG for the INVLN or INVLOG function.
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maintenance 523-0775657 Table 5-13. Acceptance Test Procedures, Using the JcAIR 429E Transmitter/Receiver (Cont).
STEP 4.0
TITLE Gillham Altitude Test
PROCEDURE
DESIRED RESULTS OR SETUP SCREEN
On ATC-601: select
** ATCRBS REPLY TEST ** (lines 2-4 are irrelevant) CODE= ALT=
ATCRBS REPLY TEST ----------->
[
]
Press RUN to start On test select: • ALT TYPE SELECT: ARINC 572 • ARINC 572 ALT IN: TO TDR • Set SOURCE SEL switch to SEL On JcAIR 429E: • Set TX screen ------>
031 01 1566C1 00
On test : • Set POWER to OFF • Set all ARINC 572 switches to OFF: Then set A4, C2, C4, and B4 to SEL. • Set POWER to ON • Set EXT STBY switch to OPR On ATC-601: • Press RUN.
The XFEED OUT lamp turns on. The ATC-601 REPLY lamp indicates that UUT is responding to interrogations.
JcAIR 429E RCV 1 screen shows: ------------------->
203 01 031 01
ATC-601 Screen shows: -------------------->
E0B861 11 F56681 11
(ignore any other labels) ** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE=5263 *****
ALT=5900 FT TEST RUNNING
[4460] *****
(The CODE 5263 depends on your selection in the 031 TX word. See note 1 under step 1.2 above) At this step you are asked to toggle each of the ARINC 572 switches and the altitude display. You should also watch the RX data word on the JcAIR 429E display. By cycling each switch between OFF and SEL you should see the ATC-601 display and the JcAIR 429E 203 data word change. If the displays do not change for a particular switch, this would indicate either an open or a shorted code line. If the wrong altitude is shown, this would suggest that the code line is affecting another line; i.e., causing two or more inputs to change simultaneously. In either case the UUT, the test , or the interconnecting cable needs repair. Set each switch as shown in the listing below to the (position) shown, and back, and the altitude display at both positions. The altitude display should always revert to the initial display when the switch is returned to its original position. There is no serious need to the correctness of the RCV word provided the ATC-601 display is correct. SWITCH Initial A1 (SEL) A2 (SEL) A4 (OFF) C1 (SEL) C2 (OFF)
DISPLAYED ALTITUDE 5,900 FT [4460] 23,600 FT [5460] 7,600 FT [6460] -400 FT (0460] none (blank; this is invalid) 5,800 FT [4440]
SWITCH C4 (OFF) B1 (SEL) B2 (SEL) B4 (OFF) D2 (SEL) D4 (SEL)
DISPLAYED ALTITUDE 6,000 FT [4420] 3,600 FT [4560] 5,600 FT [4660] 6,600 FT [4060] 119,600 FT [4462] 55,600 FT [4464]
For additional information on Gillham code structure, refer to paragraph 5.7 below.
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maintenance 523-0775657 Table 5-13. Acceptance Test Procedures, Using the JcAIR 429E Transmitter/Receiver (Cont).
STEP 5.0
TITLE CSDB tuning test
PROCEDURE
This test cannot be performed using a JcAIR 429E because these instruments are not capable of transmitting or receiver CSDB data. However, as an acceptable alternative, you can use a CTL92/92A, connected to the test using the cable shown in figure 907. • Turn power off and connect CTL-92/92A to test . Be sure CTL-92/92A mode knob is set to OFF. • Disconnect the JCAIR 429E from the test . • Turn power on and set the CTL-92/92A mode knob to ALT. On the CTL: • Set the CTL-92/92A to 5263 or any desired ident code.
5.1
CSDB altitude test
DESIRED RESULTS OR SETUP SCREEN
** ATCRBS REPLY TEST **
(lines 2-4 are irrelavent) CODE=5263 *****
ALT=32 800 FT [1344] TEST RUNNING *****
On test : • Set CONTROL DATA SELECT to CSDB • Set OUTPUT PORT SELECT to CSDB PORT 1 • Set ALT TYPE SELECT to CSDB • Set ARINC 572 ALT IN to TO CTL • Set SOURCE SELECT to CTL
The CODE 5263 depends on your selection on the CTL92/92A code select knobs. See note 1 under step 1.2 above. The ALT display depends on the altitude selection on the test ARINC 572 ALT IN switches.
On the test : • Set OUTPUT PORT SELECT to CSDB PORT 2
Be sure that the ACT display, on the CTL-92/92A, does not flash. A flashing ACT at either port selection indicates that output port has failed. If both ports flash, there may be a problem with the test wiring or the CTL input.
Be sure that the ACT display, on the CTL-92/92A does not flash. A flashing ACT indicates that the control label 1F data, from the TDR, does not agree with the CLT-92/92A output label 1E data to the TDR. Only one of the two data CTL input ports is being used; pins U/V.
In this altitude test configuration, Gillham altitude data is being supplied to the CTL (ARINC 572 ALT IN to CTL). The CTL converts this data to CSDB and supplies it to the TDR via the CSDB data output port (only 1 port is used; pins S/R). The CSDB altitude data is being read on the control bus input (SOURCE SELECT to CTL). You can this by setting the CTL mode switch to ON. If you suspect a problem with the altitude data, check the following:
On the test : • Set ARINC 572 ALT IN to TO TDR • Set ALT TYPE SELECT to ARINC 572 • Set SOURCE SELECT to SEL
The ATC-601 ALT display should be the same as above since the ultimate source of altitude information is the same in both tests. If it is different here, suspect a problem with one or more of the altitude discrete inputs to the CTL. If you encounter such a problem, you can identify the defective discrete by returning these three switches to the settings above and then performing the ARINC 572 switching sequence shown following step 4.0 above.
On test : • Set power to OFF • Disconnect the CTL-92/92A from the test • Set CONTROL DATA SELECT - ARINC PORT to PA • Set OUTPUT PORT SELECT to ARINC 429 PORT A • Reconnect the JcAIR 429E from the test .
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maintenance 523-0775657 Table 5-13. Acceptance Test Procedures, Using the JcAIR 429E Transmitter/Receiver (Cont).
STEP
6.0
TITLE
ARINC 429 Altitude Test
PROCEDURE On test : • Set EXT STBY switch to STBY • Set POWER switch to OFF • ALT TYPE SELECT: ARINC 429 • OUTPUT PORT SELECT: ARINC 429 PORT A On JcAIR 429E: • Set TX screen ------> On ATC-601: select ATCRBS REPLY TEST and press RUN to indicate TEST RUNNING --------->
On test : • Set POWER to ON • Set EXT STBY to OPR The ATC-601 screen shows: --->
DESIRED RESULTS OR SETUP SCREEN 031 01 1566C1 00 203 01 640001 11
** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE= *****
ALT= [ ] TEST RUNNING *****
The XFEED OUT lamp turns on. The ATC-601 REPLY lamp indicates that UUT is responding to interrogations.
** ATCRBS REPLY TEST **
(lines 2-4 are irrelavent) CODE=5263 *****
ALT=32 800 FT [1344] TEST RUNNING *****
(The CODE 5263 depends on your selection in the 031 TX word. See note 1 under step 1.2 above.) JcAIR 429E RX screen shows: -------> 6.1
ARINC Altitude Control Disc-retes Tests
On the test : • Be sure the SOURCE SELECT switch is set to SEL. On the test : • Set the REP ALT SEL switch to PB
203 01 640001 11
(ignore any other displayed labels) ** ATCRBS REPLY TEST **
(lines 2-4 are irrelavent) CODE=5263 *****
ALT=32 800 FT [1344] TEST RUNNING *****
Notice that the ATC-601 altitude display blanks. Note: At this point the UUT is configured to report altitude data from port B. There is none so the display blanks.
On the test : • Move the parallel connection from the PRIMARY DIGITAL ALTITUDE SOURCE jack to the ALTERNATE DIGITAL ALTITUDE SOURCE jack.
Notice that the ATC-601 altitude display returns.
On the test : • Set the REP ALT SEL switch to PA
Notice that the ATC-601 altitude display blanks.
Note: This verifies that UUT is configured to report altitude data being supplied on port B.
Note: UUT is returned to port A. This series of steps has verified that the Reporting Altitude discrete is switchable. On the test : • Set the SOURCE SELECT switch to CTL
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Notice that the ATC-601 altitude display returns. Note: This switches the UUT to the altitude data supplied on the control port.
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STEP
TITLE
PROCEDURE
DESIRED RESULTS OR SETUP SCREEN
6.1 (cont’d)
ARINC Control Disc-retes Tests (cont’d)
On the test : • Disconnect the parallel connection from the ALTERNATE DIGITAL ALTITUDE SOURCE jack. (Wait about 5 seconds)
Notice that the ATC-601 altitude display remains.
On JcAIR 429E: • Set the SOURCE SELECT switch to SEL.
Notice that the ATC-601 altitude display blanks.
On test : • Reconnect the parallel connection to the ALTERNATE DIGITAL ALTITUDE SOURCE jack.
Notice that the ATC-601 altitude display remains blanked.
On test : • Set the AUTO ALT switch to SEL (-003 UUT units only)
Notice that the ATC-601 altitude display returns.
On test : • Set the AUTO ALT switch to OFF (-003 UUT units only)
Notice that the ATC-601 altitude display blanks.
On the JcAIR 429E: • Set the TX label 031 word to -------->
031 01 9566E1 00
Note: This verifies the previous step; that altitude is being drawn from the control port; all other sources are disconnected.
Note: This verifies that the Source Select Discrete is switchable.
Note: This enables the automatic altitude port select feature and verifies that the UUT does switch to alternate port B even though port A is the selected port.
Note: This verifies that the AUTO ALT discrete is switchable.
Notice that the ATC-601 altitude display returns. Note: This digitally switches the UUT to port B. If this test is correct while the earlier test of port B altitude failed, suspect a problem with the Reporting Altitude Select discrete. If both tests failed, suspect a problem with the altitude data receivers.
On test : • Set EXT STBY switch to STBY. • Set the POWER switch OFF. On JcAIR 429E: • Set the TX label 031 word to: --------->
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031 01 1566C1 00
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maintenance 523-0775657 Table 5-13. Acceptance Test Procedures, Using the JcAIR 429E Transmitter/Receiver (Cont).
STEP
TITLE
PROCEDURE
DESIRED RESULTS OR SETUP SCREEN
The remainder of the step is optional. Testing for various digital altitude inputs is primarily software verification and therefore unnecessary. If the UUT responds to one altitude word input it will likely respond to all. If you wish, you can set the TX label 203 data field bits 12 through 28 to any combination of 1 and 0. The RCV 1 label 203 word data field will follow the TX word exactly while the ATC-601, set to the ATCRBS REPLY TEST mode, will show the altitude to the nearest 100 feet. When set to the MODE UF0 TEST, the ATC-601 displays altitude to the nearest 25 feet. The label 203 bit values are shown in note 2 following step 1.2. To 1. 2. 3. 4. 5. 6.
simulate any altitude up to about 131,000 feet: Select the desired altitude. Find the data bit with the maximum bit value less than the selected altitude. Make a note of that bit number. Subtract that bit value from your selected value. Find the next bit with the maximum bit value less than the remainder. Make a note of that bit number. Subtract that bit value from your remainder. Repeat steps 4 and 5 until the remainder is 0.
In the TX label 203 data word, set all noted bits to 1. You should see your selected altitude, to the nearest 100 feet, displayed on the ATC-601. 7.0
ARINC 575 Altitude Test
On test : • SOURCE SELECT: SEL • ALT TYPE SELECT: ARINC 429 On JcAIR 429E: • Set screen ------>
031 01 1566C1 00 203 01 640001 11
On test : • Connect parallel control cable to PRIMARY DIGITAL ALTITUDE SOURCE jack. • Set POWER switch to ON. • Set EXT STBY switch to OPR. On ATC-601: • Select ATCRBS REPLY TEST and press RUN to indicate TEST RUNNING. ATC-601 screen --------> On test : • Set ALT TYPE SELECT switch to ARINC 575 On JcAIR 429E: • Set TX label 203 word --------> (just change the SSM to 00) ATC-601 screen -------->
** ATCRBS REPLY TEST **
(lines 2-4 are irrelavent) CODE=5263 *****
203 01 040001 00
** ATCRBS REPLY TEST **
(lines 2-4 are irrelavent) CODE=5263 *****
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ALT=32,800 FT [1344] TEST RUNNING *****
ALT=16,400 FT [3230] TEST RUNNING *****
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STEP 7.0 (cont’d)
TITLE ARINC 575 Altitude Test (cont’d)
PROCEDURE JcAIR 429E RX screen --------->
DESIRED RESULTS OR SETUP SCREEN 203 01 620001 11
In addition to testing the altitude type select discrete, this test illustrates the differences between ARINC 429 and ARINC 575 data. Notice that the second data bit in the RX label 203 word (above) one-half the bit value of the corresponding bit in the TX label 203 word and the SSM code is 11 as opposed to the 00 in the TX word. In ARINC 575, the LSB is bit 13; in ARINC 429 the LSB is bit 12. In ARINC 575, bits 30 and 31 determine the sign; 00 being positive. Notice also, that the altitude displayed on the ATC-601 corresponds to the code in the RX word; not the TX word. This is also due to the UUT being configured for ARINC 575 and thus the bit values are offset by 1 bit position which has the effect of changing the altitude by a factor of 1/2. On test : • Set ALT TYPE SELECT switch to ARINC 429 On JcAIR 429E: • Set TX label 203 word ---->
031 01 1566C1 00 203 01 640001 11
ATC-601 screen: ** ATCRBS REPLY TEST **
(lines 2-4 are irrelavent) CODE=5263 *****
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ALT=32,800 FT [1344] TEST RUNNING *****
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maintenance 523-0775657 Table 5-13. Acceptance Test Procedures, Using the JcAIR 429E Transmitter/Receiver (Cont).
STEP 8.0
TITLE Mode S Address Discretes Test
PROCEDURE
DESIRED RESULTS OR SETUP SCREEN
On the test : • Set POWER switch OFF • Set all test mode s address switches to SEL except switch P1-56; set it to OFF. • Set POWER switch ON On ATC-601: • Set for MODE S ALL CALL TEST ------->
** MODE S ALL CALL TEST - NO REPLY ALL CALL ADDRESS = [ NUMBER = Press RUN to start
On ATC 601: • Press RUN • Note screen ----->
** MODE S ALL CALL TEST ALL CALL ADDRESS = FFFFFE TAIL NUMBER =
** ]
TAIL
ED ** [77777776]
****** TEST RUNNING *****
The remainder of this step should be seen as optional unless you have reason to suspect a failure in one or more of the address discrete lines. The procedure will require a few minutes because of the delay involved in cycling power between each switch setting.
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On test : • Set POWER switch OFF. • Set each triad of address switches for an octal digit 6. • Set POWER switch ON.
After a few seconds, UUT begins to reply and shortly thereafter the ATC-601 screen shows the following address:
On test : • Set POWER switch OFF. • Set each triad of address switches for an octal digit 4. • Set POWER switch ON.
After a few seconds, UUT begins to reply and shortly thereafter the ATC-601 screen shows the following address:
On test : • Set POWER switch OFF. • Set each triad of address switches for an octal digit 0, except the eighth triad which is set to 1. • Set POWER switch ON.
After a few seconds, UUT begins to reply and shortly thereafter the ATC-601 screen shows the following address:
ALL CALL ADDRESS = DB6DB6
ALL CALL ADDRESS = 924924
ALL CALL ADDRESS = 000001
[66666666]
[44444444]
[00000001]
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maintenance 523-0775657 Table 5-13. Acceptance Test Procedures, Using the JcAIR 429E Transmitter/Receiver (Cont).
STEP 9.0
TITLE TCAS / NO TCAS Discrete Select and TCAS Bus Test
PROCEDURE
DESIRED RESULTS
On test : • Set POWER switch OFF On JcAIR 429E: • Same setup as STEP 1.1. ATC-601 is not needed for this test but can be left on. On test : • Set POWER switch ON
The JcAIR 429E RX screen shows: 350 01 600001 11
After unit begins operating, display the 350 word. On test : • Set POWER switch to OFF • Set TCAS/NO TCAS switch to TCAS On test : • Set POWER switch to ON
The JcAIR 429E RX screen shows: 350 01 68B301 11 |<---diagnostic code B3
The diagnostic code B3 indicates a TCAS bus failure. Bit 28 in the data word is also set which produces the 8 in the display. See paragraph 5.B. below.
Refer to paragraph 5.B. for a more detailed discussion. This display shows a diagnostic B3 which is interpreted: TCAS Bus Inactive. This verifies that the discrete properly configures the unit for operation with a TCAS. However, no TCAS data is being supplied in this step, therefore, the unit declares a B3 diagnostic. TCAS Bus Test, XPDR to TCAS
Connect the JcAIR 429E RX to the TCAS OUT jack. that the data word labels are detectable as shown ------->. Note: Except for the diagnostic code in the label 350 data word, the data content is not important. It is quite likely that the data will be different. The presence of the data word labels shown verifies that the TCAS data bus output is active and appears to be normal.
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275 00 800000 00 276 10 80F802 00 350 01 68B301 11 |<---diagnostic code B3
Set the JcAIR 429E for high speed. Other labels may also be present.
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maintenance 523-0775657 Table 5-13. Acceptance Test Procedures, Using the JcAIR 429E Transmitter/Receiver (Cont).
STEP 9.0 (cont’d)
TITLE TCAS to XPDR Bus Test
PROCEDURE
DESIRED RESULTS
Note: In this step you need the capability of transmitting data to two separate input ports simultaneously and at different speeds; the 031 control word must be low speed (12.5-kbps) while the TCAS label 274 data words must be high speed (100-kbps). All JcAIR 429E instruments can transmit at either of these speeds but not on two separate ports simultaneously. If you do not have this capability, you may not be able to the integrity of the TCAS bus input port. If you have access to a second JcAIR 429E, connect your second transmitter port or data bus simulator to the TCAS IN and setup as shown -------->:
274 00 180000 00
On bus reader RCV display:
After a few seconds, the 350 word shows:
Note: The objective is to that the UUT recognizes a valid TCAS label 274 word and declares this by removing the diagnostic B3.
350 01 680001 11 |<---diagnostic code 00
On the bus reader: Set the XMT 2 word to OFF
After a few seconds, notice that the B3 diagnostic returns.
Note: Be sure to set for high speed.
Note: Disconnect XMT 2 from the TCAS IN jack and reconnect RCV 1 to the DATA BUS OUTPUT port. Final step in this test, all setups
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On test : • Set POWER switch to OFF • Set TCAS/NO TCAS switch to NO TCAS On test : • Set POWER switch to ON
After a few seconds, the original 350 word returns: 350 01 000001 11
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STEP 10.0
TITLE Side 1/ Side 2 Discrete Test
PROCEDURE
DESIRED RESULTS
On test : • Set POWER switch OFF • Be sure SIDE 1/SIDE 2 switch is set to SIDE 1. On JcAIR 429E: • Same setup as STEP 1.1. On ATC-601: • Set for ATCRBS REPLY TEST screen ----->
CODE= *****
On test : • Set POWER switch ON
After a few seconds, X FEED OUT and ATC-601 REPLY lamps light and the ATC-601 shows:
** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) ALT= TEST RUNNING
[ *****
]
** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE=5263 ALT=32,800 FT [1344] ***** TEST RUNNING *****
On test : • Set POWER switch to OFF • Set SIDE 1/SIDE 2 switch to SIDE 2 • Set POWER switch to ON
Note that unit does not reply (X FEED OUT lamp and REPLY lamps are off and no altitude is displayed on ATC-601). Wait about 10 seconds. Note: UUT does not respond because the SDI and side strapping do not agree. Note: Be sure to allow adequate time for the U to reinitialize properly between power off and power on. The SIDE 1/2 strap is one of several that are monitored only at processor initialization. Therefore, if this tests fails, cycle power again but allow more time between power off and power on.
On JcAIR 429E: • On TX, label 031 word, set the SDI to 10
Notice that unit begins to reply almost immediately (XFEED OUT lamp turns on and ATC-601 REPLY lamp lights). Note: UUT responds because the SDI and side strapping agree.
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On JcAIR 429E: • On TX, label 031 word, set SDI to 01.
Notice that unit stops replying (X FEED OUT lamp and ATC-601 REPLY lamps turn off).
On test : • Set POWER switch OFF • Set SIDE 1/SIDE 2 switch to SIDE 1 • Set POWER switch ON
After a few seconds, X FEED OUT and ATC-601 REPLY lamps light and the ATC-601 shows that the UUT is replying.
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STEP 11.0
TITLE AIR/ GND Discrete Test
PROCEDURE
DESIRED RESULTS
On test : • Set POWER switch OFF • TDR ALT SOURCE: EXT DIRECT • ALT TYPE SELECT: ARINC 429 On JcAIR 429E: • Same setup as STEP 1.1. On ATC-601: • Set for MODE S UF4 TEST screen ----->
** MODE S UF4 TEST - NO REPLY ** DF FS= ADDRESS= *****
On test : • Set POWER switch ON ATC-601 screen shows ----->:
DR=
UM=
TEST RUNNING
AC= *****
After a few seconds, X FEED OUT and ATC-601 REPLY lamps light and the ATC-601 shows: ** MODE S UF4 TEST - ED ** DF 4 FS=0 DR=00 UM=00 ADDRESS=000001 *****
TEST RUNNING
AC=32,775 FT *****
Note: Initially the screen will show FS=2 for about 2 seconds and then change to FS=0. On test : • Set AIR/GND switch to GND
After a few seconds, the ATC-601 shows: ** MODE S UF4 TEST - ED ** DF 4 FS=1 DR=00 ADDRESS=000001 *****
UM=00 AC=32,775 FT
TEST RUNNING
*****
Of particular significance here is the FS (flight status) indication. For a detailed description of each of these message fields, refer to the Theory of Operation section. On test : • Set AIR/GND switch to AIR
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After a few seconds, notice that the ATC-601 FS field again shows 0.
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maintenance 523-0775657 Table 5-13. Acceptance Test Procedures, Using the JcAIR 429E Transmitter/Receiver (Cont). STEP 12.0
TITLE DL ANT/ SGL ANT Discrete Test (TDR-94D only)
PROCEDURE
DESIRED RESULTS
On test : • Set POWER switch OFF On JcAIR 429E: • Same setup as STEP 1.1. On ATC-601, set for SQUITTER TEST screen -----> Be sure the ATC-601 is connected to the top antenna port. On test : • Set DL ANT/SGL ANT switch to DL ANT • Set POWER switch ON Watch the PERIOD display for a time. You will notice it changing somewhat but it should remain at or near 2 seconds.
** SQUITTER TEST - NO REPLY ** PERIOD = SECONDS TAIL NUMBER = SQUITTER ADDRESS= [ *****
TEST RUNNING
]
*****
After a few seconds, the ATC-601 screen shows: See note below. ** SQUITTER TEST - ED PERIOD = 2.00 SECONDS TAIL NUMBER = SQUITTER ADDRESS= [ *****
TEST RUNNING
** ]
*****
See the note at the end of this step for test tolerances. On test : • Set POWER switch OFF • Set DL ANT/SGL ANT switch to SGL ANT • Set POWER switch ON
After a few seconds, the ATC-601 screen shows: ** SQUITTER TEST - FAILED PERIOD = SECONDS TAIL NUMBER = SQUITTER ADDRESS= [ *****
TEST RUNNING
** ]
*****
Note: This test is intended to fail. When the UUT is set for single antenna operation, there is no transmission from the top antenna port. Therefore, if this test indicates ED, recheck all switch settings or suspect a problem with the SGL/DL ANT select strap. It should not . On test : • Set POWER switch OFF On ATC-601: • Press RUN to stop the test. • Remove rf terminator from bottom antenna connector • Connect ATC-601 cable to bottom antenna connector • Connect rf terminator to top antenna connector
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maintenance 523-0775657 Table 5-13. Acceptance Test Procedures, Using the JcAIR 429E Transmitter/Receiver (Cont).
STEP 12.0 (cont’d)
TITLE DL ANT /SGL ANT Discrete Test (cont’d) (TDR-94D only)
PROCEDURE On test : • Set POWER switch ON On ATC-601: • Press RUN to start the test.
DESIRED RESULTS After a few seconds, the ATC-601 screen shows: See note below. ** SQUITTER TEST - ED PERIOD = 1.00 SECONDS TAIL NUMBER = SQUITTER ADDRESS= [ *****
On test : • Set POWER switch OFF • Set DL ANT/SGL ANT switch to DL ANT • Set POWER switch ON
TEST RUNNING
** ]
*****
After a few seconds, the ATC-601 screen shows: See note below. ** SQUITTER TEST - ED PERIOD = 2.00 SECONDS TAIL NUMBER = SQUITTER ADDRESS= [ *****
TEST RUNNING
** ]
*****
Note: The PERIOD value tends to vary somewhat in all cases. When the UUT is set for dual antenna operation and the ATC-601 is monitoring the top or the bottom antenna port, the value can vary from 1.6 to 2.4. When the TDR-94D is set for single antenna operation, or the UUT is a TDR-94, there is no transmission from the top antenna port and and the transmission PERIOD from the bottom antenna port can vary from 0.6 to 1.4. 13.0
Burst Tune and CrossFeed In DiscreteT est
On ATC-601, set for SQUITTER TEST screen -----> If necessary, reconnect ATC-601 to bottom antenna connector, with terminator on top (TDR-94D only) connector.
** SQUITTER TEST - NO REPLY ** PERIOD = SECONDS TAIL NUMBER = SQUITTER ADDRESS= [ ] *****
TEST RUNNING
*****
On JcAIR 429E: • Same setup as STEP 1.1. On test : • CONTROL DATA SELECT: PA • ALT TYPE SELECT: ARINC 429 • SOURCE SELECT: SEL • Be sure that X FEED IN/OUT switch is set to OUT • Be sure that BURST TUNE switch is set to OFF. On test : • Set POWER switch ON
After a few seconds, the test X FEED OUT and the ATC-601 REPLY lamps light indicating that the unit is replying. The ATC-601 screen data indicates ED.
On test : • Set X FEED IN/OUT switch to IN
Notice that both X FEED lamps are lighted.
On JcAIR 429E: • Set TX to OFF
Notice that the X FEED OUT and ATC-601 REPLY lamps turns off (X FEED IN stays on).
(The easiest way to turn TX off is to disconnect it from the test )
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maintenance 523-0775657 Table 5-13. Acceptance Test Procedures, Using the JcAIR 429E Transmitter/Receiver (Cont). STEP 13.0 (cont’d)
14.0
TITLE Burst Tune and CrossFeed In Discrete Test (cont’d)
Output Port Discrete Test
PROCEDURE
DESIRED RESULTS
On JcAIR 429E: • Set TX to ON
Notice that the X FEED IN and OUT and REPLY lamps are lighted.
On test : • Set X FEED IN/OUT switch to OUT • Set BURST TUNE to ON On JcAIR 429E: • Set TX to OFF
Notice that UUT continues to reply. Watch the unit for a few seconds. (The X FEED IN lamp extinguishes because the switch turns it off.)
On test : • Set BURST TUNE switch to OFF
Notice that UUT stops replying (X FEED OUT and REPLY lamps turn off).
On test : • Set BURST TUNE to ON
Notice that UUT does not reply (X FEED OUT and REPLY lamps do not light).
On JcAIR 429E: • Set TX to ON
Notice that UUT replys (X FEED OUT and REPLY lamps are on).
On test : • Set BURST TUNE to OFF On JcAIR 429E: • Set TX to OFF
Notice that UUT stops replying (X FEED OUT and REPLY lamps are off).
On JcAIR 429E: • Set TX to ON
X FEED OUT lamp and the REPLY lamp turns on again.
On test : • Set X FEED IN/OUT switch to IN • Set BURST TUNE switch to ON. • Set TX to ON
X FEED OUT lamp flashes .
On test : • Set BURST TUNE to OFF • Set POWER switch to OFF • Set X FEED IN/OUT to OUT • ALT TYPE SELECT: ARINC 429 • CONTROL DATA SEL: PA • OUTPUT PORT SELECT: ARINC 429 PORT A On JcAIR 429E: • The same as STEP 1.1 On test : • Set POWER switch to ON
Both X FEED OUT and REPLY lamps are on.
JcAIR 429E RCV screen ----->
031 01 F56681 11
Note: Be sure that the JcAIR screen flashes somewhat. This indicates that the screen is being updated. A nonflashing screen usually indicates that obsolete data is being displayed.
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On ATC-601, set for SQUITTER TEST
After a few seconds, the ATC-601 screen data indicates ED.
On test : • Set OUTPUT PORT SELECT switch to ARINC 429 PORT B
Notice that there is no change in the test result; X FEED OUT and REPLY lights are on and JCAIR screen does not change.
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STEP 15.0
TITLE Control Data Input Port Select Discrete Test
PROCEDURE
DESIRED RESULTS
On test : • Set POWER switch OFF • Set SOURCE SELECT switch to SEL • ALT TYPE SELECT: ARINC 429 • CONTROL DATA SELECT: ARINC PORT PA On JcAIR 429E: • Same setup as for STEP 1.1. On ATC-601, set for SQUITTER TEST screen ----->
** SQUITTER TEST - NO REPLY ** PERIOD = SECONDS TAIL NUMBER = SQUITTER ADDRESS= [ ] *****
16.0
Manual STBY Discrete Test
TEST RUNNING
*****
On test : • Set POWER switch ON
After a few seconds, the test X FEED OUT and the ATC-601 REPLY lamps light indicating that the unit is replying. The ATC-601 screen data indicates ED.
On test : • Set CONTROL DATA SELECT switch to ARINC PORT PB
Notice that there is no change in the test result; X FEED OUTand REPLY lights are on and ATC-601 display does not change.
On test : • Set CONTROL DATA SELECT switch to ARINC PORT PC
Notice that there is no change in the test result; X FEED OUT and REPLY lights are on and ATC-601 display does not change.
On test : • Set EXT STBY switch to STBY • Set POWER switch OFF • Set CONTROL DATA SELECT switch to ARINC PORT PA On JcAIR 429E: • Same setup as for STEP 1.1. On ATC-601: • Set for ATCRBS REPLY TEST screen ---------->
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** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE= *****
ALT= [ ] TEST RUNNING *****
On test : • Set POWER switch ON • Set EXT STBY switch to OPR
After a few seconds, the test X FEED OUTand the ATC-601 REPLY lamps light indicating that the unit is replying. The ATC-601 screen data indicates ED.
On test : • Set EXT STBY switch to STBY
Note that X FEED OUT lamp and ATC-601 REPLY lamps turn off and ATC-601 indicates NO REPLY. See note below.
On test : • Set EXT STBY switch to OPR
Note that X FEED OUT lamp and ATC-601 REPLY lamps light almost immediately and ATC-601 indicates ED.
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maintenance 523-0775657 Table 5-13. Acceptance Test Procedures, Using the JcAIR 429E Transmitter/Receiver (Cont).
STEP 17.0
TITLE Max Airspeed Test
PROCEDURE
DESIRED RESULTS
On test : • Set POWER switch OFF • ALT TYPE SELECT: ARINC 429 • Be sure that all three MAX AIRSPEED switches are set to OFF. On JcAIR 429E: • Same setup as for STEP 1.1. (The JcAIR 429E is used here only for tuning data.) On ATC-601: • Set for MODE S UF0 TEST screen --->
** MODE S UF0 TEST - NO REPLY ** DF
VS= ADDRESS= *****
On test : • Set POWER switch ON
RI=
AC=
TEST RUNNING
*****
After a few seconds, the test X FEED OUT lamp and the ATC-601 REPLY lamps light indicating that the unit is replying.
Note the ATC-601 screen ----------->
** MODE S UF0 TEST - ED ** DF 0 VS=0 RI=8 ADDRESS=000001 *****
AC= 32,775 FT
TEST RUNNING
*****
Exercise the MAX AIRSPEED switches on the test and the correct RI indication as shown in the following list. Cycle power and allow about 2 or 3 seconds of OFF time and about 5 seconds for processor initialization and ATC-601 response time between each switch setting. MAX AIRSPEED SWITCH BIT 15 BIT 16 BIT 17 OFF OFF OFF SEL OFF OFF OFF SEL OFF SEL SEL OFF OFF OFF SEL SEL OFF SEL OFF SEL SEL SEL SEL SEL
RI VALUE 8 9 A B C D E F (not an assigned configuration)
It is worth noting that in this test mode the ATC-601 displays the altitude to the nearest 25 feet.
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maintenance 523-0775657 Table 5-13. Acceptance Test Procedures, Using the JcAIR 429E Transmitter/Receiver (Cont).
STEP 18.0
TITLE Ext Suppression Test
PROCEDURE
DESIRED RESULTS
On test : • ALT TYPE SELECT: ARINC 429 On JcAIR 429E: • Same setup as for STEP 1.1. On ATC-601: • Set for ATCRBS REPLY TEST screen -->
** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE= *****
• Connect scope channel A to the test SUPPR test points. • Connect scope channel B to the REPLY VIDEO BNC connector on the ATC-601. • Set the scope to display both channels
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ALT= [ ] TEST RUNNING *****
Note a (approx) 30µs pulse on channel A. Note a reply waveform on channel B. If your scope is able, you will see the individual reply code pulses on channel B. You may also see the occasional squitter transmission which appears as a much longer series of pulses at about 1 transmission every 2 sec. Of particular importance, however, is that the channel A (suppression) pulse is about 30 µs long during ATCRBS reply, and brackets the 21 µs ATCRBS reply. During squitter transmission, the suppression pulse extends to bracket the squitter transmission. The squitter transmission is a DF11 reply about 72 µs long.
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maintenance 523-0775657 Table 5-13. Acceptance Test Procedures, Using the JcAIR 429E Transmitter/Receiver (Cont).
STEP 19.0
TITLE ADLP Select, Discrete Strap Test
PROCEDURE
DESIRED RESULTS
On test : • Be sure DATALINK switch is set to NO ADLP. On JcAIR 429E: • Same setup as for STEP 1.1. JcAIR 429E RX screen ------>
350 01 600001 11
Note: The ATC-601 is not needed for this test but it can remain connected and operating. On test : • Set POWER switch to OFF • Set DATALINK switch to ADLP. • Be sure DATALINK SELECT switch is set to A/B. • Set POWER switch to ON.
350 01 64A201 11 |<---diagnostic code A2
Note: The diagnostic A2 identifies an inactive ADLP bus. This test verifies that the ADLP enable discrete is functional. The 4 reflects bit 27 in the data word which is also set indicating an ADLP bus failure.
JcAIR 429E RX screen ------> On test : • Set POWER switch to OFF. • Set DATALINK switch to NO ADLP. • Set POWER switch to ON.
350 01 600001 11 |<---diagnostic code 00
JcAIR 429E RX screen ------> Note: The Airborne Datalink system is not fully implemented at this time. If and when an ADLP (Airborne DataLink Processor) becomes available and operational, suitable procedures will be provided to the integrity of the ADLP input/output ports. At this point, therefore, verification of the ADLP SELECT strap is seen as sufficient to prevent nuisance diagnostics that can occur if the select input should be defective. You will notice that the DATALINK SELECT A/B, C/D function is also not tested.
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maintenance 523-0775657 Table 5-13. Acceptance Test Procedures, Using the JcAIR 429E Transmitter/Receiver (Cont).
STEP 20.0
TITLE Remote IDENT Discrete Test
PROCEDURE
DESIRED RESULTS
On test : • Same as initial setup On JcAIR 429E: • Same setup as for STEP 1.1. On ATC-601: • Setup for ATCRBS REPLY test
** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE= *****
On test : • Set the POWER switch to ON • Set the EXT STBY switch to OPR • Press and release the REMOTE IDENT switch. On JcAIR 429E: • Notice RX screen ----->: On ATC-601: • Notice the ID display. ID should display for about 18 seconds.
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ALT= [ ] TEST RUNNING *****
031 01 756691 11 |<----Ident bit
Note: The 9 should appear in the data field only while the switch is being pressed. This, together with the ID display on the ATC-601, verifies that the REMOTE IDENTdiscrete input is functional. ** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE=ID5263 ALT= 32,800 FT [1344] |<----ID display ***** TEST RUNNING *****
On JcAIR 429E: • Set the label 031 TX word:
031 01 156691 00
On JcAIR 429E RX and on ATC-601 screens:
You should see the same displays as immediately above. If the test failed using the REMOTE IDENT switch, but succeeds here, then suspect a failure in the discrete input or the test .
On JcAIR 429E: • Set the label 031 TX word:
031 01 956681 00
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maintenance 523-0775657 Table 5-13. Acceptance Test Procedures, Using the JcAIR 429E Transmitter/Receiver (Cont).
STEP 21.0
TITLE Self Test
PROCEDURE
DESIRED RESULTS
On test : • Set POWER switch OFF • ALT TYPE SELECT: ARINC 429 • AIR/GND: AIR • SELF TEST: ENABLE: OFF On JcAIR 429E: • Same setup as for STEP 1.1. On ATC-601: • Set for ATCRBS REPLY TEST ---------->
** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE= *****
ALT= [ ] TEST RUNNING *****
On test : • Set POWER switch ON
After a few seconds, the test X FEED OUT lamp and the ATC-601 REPLY lamps light indicating that the unit is replying. The ATC-601 screen indicates ED.
On JcAIR 429E: RX screen shows: --------->
031 01 F56681 11 203 01 640001 11 350 01 600001 11
In the next few steps, watch the JcAIR 429E RX screen carefully. On the test : • Press and hold the SELF TEST pushbutton for about 1 sec.
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After a few seconds, notice that the ATC-601 screen does not change The JcAIR 429E RX display may go blank.
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STEP 21.0
TITLE Self Test (cont’d)
PROCEDURE
DESIRED RESULTS
On test : • Set the AIR/GND switch to GND • Set the SELF TEST/ENABLE switch to ON • Press and hold the SELF-TEST button for about 1 s
Self-test Displays: After a few seconds, notice that the X FEED OUT lamp turns off briefly while the ATC-601 screen shows +’s or -’s in most of the data fields, followed by blank fields.
Note: The test TEST lamp lights while you hold the switch. This has no bearing on UUT operation, however. If the lamp does not light, check the test .
After a few seconds, notice that the X FEED OUT lamps turns on again and the ATC-601 screen returns to the normal display. On the JcAIR 429E notice that the SM changes to 10 and then back to 11.You should try to be especially watchful of the 350 data word and try to catch any diagnostic codes that may be displayed during the selftest sequence.
On the test : • Set the SELF TEST/ENABLE switch to OFF. • Press and hold the SELF TEST button for about 1 s.
Notice that the self-test displays as described above do not appear..
On the test : • Set the SELF TEST/ENABLE switch to ON. • Set the AIR/GND switch to AIR. • Wait about 5 seconds *. • Press and hold the SELF TEST button for about 1 s.
Notice that the self-test displays as described above do not appear..
Note: This verifies that self test is properly inhibited by the self-test inhibit discrete.
Note: This verifies that self test is properly inhibited by the AIR/GND discrete.
*Note: The U must be allowed sufficient time to complete at least one software cycle in order to recognize the change in the AIR/GND discrete. If you press the SELF TEST switch in less than about 3 seconds of setting the AIR/GND switch to AIR, the unit may execute self-test as though it were not inhibited. This should be seen as normal. On the test : • Set the SELF TEST/ENABLE switch to ON. • Set the AIR/GND switch to GND. • Press and hold the SELF TEST button for about 1 s.
Notice the self-test displays as described above reappear. Note: This verifies that the self-test inhibit and AIR/GND discretes are switchable.
This completes this test sequence. Successful completion of this series provides reasonable assurance that the unit is operational. However, this test does not satisfy the requirements of a Final Performance Test which must be performed after any repair operation. Turn off all power, disconnect the equipment, and return it to its normal storage location. Return the UUT to its original shipping container, or equivalent, if it is to remain in storage. Otherwise, prepare it for installation.
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maintenance 523-0775657 5.4.5.11.1 JcAIR 429E Transmitter/Receiver, Operating Instructions This paragraph provides instructions that may be helpful in operating the JcAIR 429E Transmitter / Receiver. It is intended for those who may be unfamiliar with its operation and may need some help.
If you are familiar with the JcAIR 429E: Set the TX 1 output to: 031 01 156681 00; this produces an ATC code: 5236. Set the TX 2 output to: 203 01 640000 11; this produces an altitude: 32,800 ft. These are the TX hex values used most often in the procedures of Table 5-13.
Setup and Operating Instructions if you are unfamiliar with the operation of the JcAir 429E: During the course of this procedure, do not turn power off to the JcAIR 429E. All entered data is lost. Preliminary setup Set: TX Parity to ODD TX Speed to LO RX Speed to LO Display to Hex TX label and word setup for this procedure 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. 13. 14. 15. 16. 17. 18. 19. 20. 21. 22. 23. 24. 25. 26. 27. 28. 29. 30.
When screen shows: 0 RX LABELS, press TX/RX Screen shows: 0 TX LABELS Press ’up arrow’ key Screen shows: TX 1 INACTIVE Press EDIT/DEL Screen shows a blinking cursor on an otherwise blank screen Enter 031 Press ENT Screen shows: 031 BCN ATC CODE Press LAB/DAT Screen shows: 031 00 000000 00 Press EDIT/DEL Screen shows a blinking cursor on an otherwise blank screen Enter 6-digit Hex code as desired or 156681 Press ENT Screen shows: 031 01 956681 00 (The parity bit causes the change from 1 to 9 in the first digit) Press TX/RX until screen shows 1 TX LABELS Press ’up arrow’ until screen shows TX 2 INACTIVE Press EDIT/DEL Screen shows a blinking cursor on an otherwise blank screen Enter 203 Press ENT Screen shows: 203 ALTITUDE Press LAB/DAT Screen shows: 203 00 000000 00 Press EDIT/DEL Screen shows a blinking cursor on an otherwise blank screen Enter E40000 Press ENT Screen shows: 203 01 E40000 11
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maintenance 523-0775657
RX labels setup for this procedure: Note: The procedures below may not be needed depending on the software version of the JcAIR 429E being used. The objective of the test is to capture (trap) ARINC 429 labels 031, 203, and 350 words. Consult the JcAIR 429E Operator’s Manual for detailed instructions if needed. 1. 2. 3. 4. 5. 6. 7. 8. 9. 10.
If the JcAIR 429E is not already on, turn POWER switch to ON If necessary, press TX/RX until screen shows: 0 RX LABELS Press TRAP Screen shows a blinking cursor on an otherwise blank screen Enter 031 Press ENT Screen shows: 031 SDI? _ (blinking cursor) Enter 01 Press ENT Screen shows: 0 RX LABELS
Note: This screen tends to blink slightly indicating that the display is being updated. If data is being received, the left digit will increment (quite rapidly) to a maximum of 255 indicating the number of words that have been captured. 11. Press TRAP until screen again shows a blinking cursor 12. Repeat steps 3 through 11 but enter 203 at step 5. (At step 10, the display will show: 1 RX LABELS) 13. Repeat steps 3 through 11 but enter 350 at step 5. (At step 10, the display will show: 2 RX LABELS) 14. Press ENT twice. To change altitude: 1. 2. 3. 4. 5. 6. 7. 8.
Press TX/RX until the screen shows: 2 TX LABELS (The 2 is an integer indicating the number of TX labels that are entered) Press the ’up arrow’ key until the screen shows: 203 ALTITUDE Press LAB/DAT until the screen shows: 203 01 E40000 11 (The six-digit hex code will be the most recently entered code) Press EDIT/DEL Screen shows a blinking cursor on an otherwise blank screen Enter the necessary hex value for the desired altitude or E41BB1 (33,654 ft) (see note 2 under step 1.4 below) Press ENT Screen shows: 203 01 641BB1 11
This entry will cause the ATC-601 to show 33,700 FT..
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To change ATC code: 1. 2. 3. 4.
Press TX/RX until the screen shows: 2 TX LABELS (The 2 is an integer indicating the number of TX labels that are entered) Press the ’up arrow’ key until the screen shows: 031 BCN ATC CODE Press LAB/DAT Screen shows: 031 BCN ATC CODE
4.
Press EDIT/DEL
5. 6. 7. 8. 9.
Screen shows a blinking cursor on an otherwise blank screen Enter the necessary hex value for the desired ATC code or 5263 Press ENT TX screen shows: 031 01 0E5C01 00 RX screen shows: 031 01 0E5C01 00
This entry will cause the ATC-601 to show CODE=6352 Note: You can set the JcAIR DISPLAY switch to Eng to show the 4-digit code. The ATC-601 CODE and JcAIR 429E Eng code displays should always agree. 10.
Reset the TX 031 and 203 words to the Initial Setup
To view captured data: 1. 2.
3. 4.
Press TX/RX until the screen shows: 3 RX LABELS Press ’up arrow’ to select the desired word label/title: 031 BCN ATC CODE 203 ALTITUDE 350 MAINT DATA 1 Press LAB/DAT
Screen shows the selected word/data (only one at a time): 031 01 156681 00 203 01 640000 11 350 01 000001 11
To select a different word: 5. 6. 7. 8.
Press LAB/DAT Press ’up arrow’ or ’down arrow’ to select one word label/title as shown in 2. above: Press LAB/DAT to view the data Screen shows the selected word data as in 4 above.
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maintenance 523-0775657 5.5 MAINTENANCE DIAGNOSTIC DATA RETRIEVAL AND ANALYSIS 5.5.1
Introduction
This paragraph provides detailed information related to the diagnostic data stored in the TDR-94/94D transponder. It is intended to the procedures found in table 5-6. The stored data consists of fault and maintenance data which is stored in nonvolatile memory. Memory space, for this purpose, is allocated according to table 5-14. Notice that there are two categories of data: general maintenance and diagnostic data. Table 5-14 shows structure of the diagnostic data.
Memory space consists of 256 bytes of NVRAM. The general maintenance data buffers use 14 bytes and the remainder is used for diagnostic data storage. Each diagnostic occurrence uses 10 bytes. Thus, there is space for 24 diagnostic occurrences. If more than 24 occurrences are detected, the most recent is retained as follows: In -002 units, the most recent occurrence is overwritten. That is, occurrences 1 through 23 are retained while the 24th occurrence is overwritten when a new occurrence is detected. In -003 units, the oldest occurrence is overwritten.
Table 5-14. Maintenance and Diagnostic Data Memory Structure
GENERAL MAINTENANCE DATA BUFFERS DATA DESCRIPTION
BYTES USED
Pointer to next diagnostic code location
2
Power-on cycle counter
2
Total diagnostic counter
1
Total power-on timer (minutes)
1
Power-on timer (hours)
2
Last POC diagnostic counter
1
Current POC timer
1
Last maintenance date
4 DIAGNOSTIC DATA BUFFERS
Time from last power on
1
Diagnostic code
1
(not used)
1
Transmitter temperature (degrees Celsius)
1
Current power-on cycle count buffer
2
Air/ground state at time of diagnostic
1
Time at end of power-on cycle
1
Altitude at time of diagnostic
1
Altitude at time of diagnostic
1
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maintenance 523-0775657 5.5.2
General Diagnostic Formats
Maintenance diagnostic data is provided on the ARINC 429 output buses only. The maintenance data is provided on a label 351 data word when requested by an ARINC 429 label 277 data word at any of the ARINC 429 input ports. Unless a total is requested, the output is based on a oneresponse for one-request basis. In all cases, no data is provided unless the Air/ground discrete is at a logic 0; that is, the airplane is on the ground. No stored diagnostic data is provided on any of the CSDB buses. This procedure uses the Atlantic Instruments, DataTrac 400 DataTrac 400H, DataTrac 200 Databus Readers, or the JcAIR 429E Transmitter/Receiver for data request and receive. For the sake of brevity, in these procedures the term "bus reader" should be understood to apply to either of these instruments. If you have or prefer an equivalent instrument, feel free to use it. Some procedural adaptation may be required. Control ports A, B, or C can be used. The general format of the maintenance request and response data is as follows: BIT NO. BIT DESIGNATION 1 - 8 MSB - LSB LABEL (see note 1) 9 Hex fault code B0 10 Hex fault code B1 11 Hex fault code B2 12 Hex fault code B3 13 Hex fault code B4 14 Hex fault code B5 15 Hex fault code B6 16 Hex fault code B7 17 Hex fault code B8 18 Hex fault code B9 19 Hex fault code B10 20 Hex fault code B11 21 Hex fault code B12 22 Hex fault code B13 23 Hex fault code B14 24 Hex fault code B15 25 Hex fault code B16 26 Hex fault code B17 27 Hex fault code B18 28 Hex fault code B19 29 PAD 30 Test type (see note 2) 31 Test type (see note 2) 32 Parity 5/5/1993
Note 1: Label structure: Bit: 8 7 6 5 4 Value: 1 2 4 1 2 Label 277: 1 1 1 1 1 Label 351: 1 0 0 1 0 See also paragraph
3 2 1 4 1 2 1 0 1 1 1 1 5.7.4.8
Note 2: Test type definition: BIT 31 0
BIT 30 DEFINITION 0 Software rev status, request or response 0 1 RAM memory output, re quest or response; requires 4-digit address code for specific data 1 0 Last maintenance date, load command * 1 1 Detailed diagnostic data, request or response. Requires 2-digit hex code(**) for specific data * s are CAUTIONED not to use this code. This code will destroy some of the stored diagnostic data. It is intended for use only after bench repair. See paragraph 5.5.11. ** Hex code listing: Hex Requested data 01 Contents of total power-on cycle counter buffer 02 Contents of total fault counter buffer 03 Contents of total power-on timer (hours) buffer 04 Contents of total power-on timer (minutes) buffer 05 Contents of last power-on cycle fault counter buffer 06 Not defined 07 Contents of last maintenance date buffer 08-0F Not defined 10 of the diagnostic codes detected during the most recent power-on cycle (if any- see below) 11-1X of the diagnostic codes detected during preceding power-on cycles, where 11 is the next to the most recent and 1X is the request code that produces a 00EOF (End Of File) response.
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maintenance 523-0775657 5.5.3 Software Revision Status (SRS) Reporting The software revision status is of questionable value for field use. It is presented here so that if a need or purpose develops it can be accessed.
5.5.3.1 SRS Word Definition Upon receipt of a label 277 request for diagnostic data, with bits 31 and 30 set to 00, the TDR-94D responds with a label 351 word with the following structure:
1: 32 31 30 29 28 27 26 25 24 23 22 21 20 2: 8 4 2 1 8 4 2 1 8 | | | | \ | | / \ | | / \ | | | | | | | \ / \__BCD month \ BCD day | \__SSM bits, 11 implies a request \__Parity
19 18 17 16 15 14 13 12 11 10 4 2 1 8 4 2 1 8 4 2 | | / | | | | | | | | \ | | / \ | | / \ BCD yr / for diagnostic data
Description: Bit 32: Parity bit: This bit is set to a 1 when the total of the other 31 bits set to 1 is 0 or an even number. Bits 31 and 30: SSM bits: 11 implies a request for diagnostic data. Bits 29 - 25: BCD month: Bit 29 gives the tens value; 0 or 1. Bits 28 -25 give the units value; 0 - 9. Bits 24 - 17: BCD day: Bits 24 - 21 give the tens value; 0 - 3. Bits 17 - 20 give the units value; 0 - 9. Bits 16 - 9: BCD year: Bits 16 - 13 give the tens value; 8,9,0. Bits 12 - 9 give the units value; 0 - 9.
Set the bus reader XMT for a label 277 data word as follows:
5.5.3.2 SRS Data Request Note: The AIR/GND switch, in the test , must be in the GND position and TEST INHIBIT must be off. That is, pin P238 must be open.
9 1 | /
DataTrac: ON--------------XMT 1----------12.5 KHz LBL SDI 11----- Data--- SSM Par msec 277 00 60 00 00 FD 11 1 0100
JcAIR 429E: 277 00 600000 11
It is important that the SM (SSM) is set to 11. The SDI is set automatically when data is entered into the 5th and 6th digits of the data field. These are the only XMT digits that will be manually changed in this procedure. Response example: DataTrac: ----------------RCV 1--(ALL)---12.5 KHz LBL SDI 32-Hex Data-1 SSM Par Tmin 351 10 09 12 90 97 11 1 0200
JcAIR 429E: 351 10 091290 11
This indicates that the SRS of this unit is: 9 December 1990. It is important to set the bus reader to the proper display format for easy data interpretation.
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maintenance 523-0775657 5.5.4 Memory Examination Request and Response (MERR) This paragraph is provided for information purposes only. Memory allocation, within the memory blocks, is controlled dynamically by the operating software and therefore is difficult predict. Data necessary for maintenance can be obtained more easily by the procedures in the rest of this paragraph.
5.5.4.1 MERR, General Word Definition The memory examination request word label 277 is defined as follows:
32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 9 1 8 4 2 1 8 4 2 1 8 4 2 1 8 4 2 1 8 4 2 1 | \ / | | | | | | | | | | | | | | | | | | | | | | | Pad | || || || || | | | \<-------------- 00000H to 0FFFFH --------------> / | | (memory locations) | \__SSM, 11 implies a request for diagnostic data \__Parity The response word label 351 is defined as follows: 32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 9 - - - - - - - - 8 4 2 1 8 4 2 1 8 4 2 1 8 4 2 1 | \__/ | \__|__|__/ \__|__|__/ \__|__|__/ \__|__|__/ \__|__|__/ | | | | | | | | | | \<-Pad->/ \<--Data in requested location------>/ | \__SSM, 11 implies memory examination request \__Parity
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maintenance 523-0775657 5.5.5
Total Power-on Cycle Count (TPOCC) Buffer
Each time the TDR-94/94D is turned on, the TPOCC buffer is incremented. Therefore, this buffer contains the number of times the unit has experienced a power application.
5.5.5.1 TPOCC General Word Definition The total power-on cycle counter data request word label 277 is defined as follows:
32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 9 - - - - - - - - - - - - - - - - 8 4 2 1 8 4 2 1 | \__/ | \__|__|__/ \__|__|__/ \__|__|__/ \__|__|__/ \__|__|__/ | | | | | | | | | | \<------------Pad-------------> / \<----01H--->/ | \__SSM, 11 implies a diagnostic data request \__Parity The response word label 351 is defined as follows: 32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 - - - - - - - - - - - - - - - - 8 4 2 1 8 4 2 | \__/ | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | Pad \10,000’S/ \1,000’S / \ 100’S / \ 10’S / \units | \__SSM, 11 implies response to a diagnostic data request \__Parity
9 1 | | /
5.5.5.2 TPOCC Buffer Examination Setup bus reader XMT screens as follows: DataTrac: ON------------XMT 1----------12.5 KHz LBL SDI 32-Hex Data-1 SSM Par msec 277 01 00 00 00 FD 11 1 0100
JcAIR 429E:
The reader should respond with a label 351 word similar to this: DataTrac: ON------------RCV 1--(ALL)---12.5 KHz LBL SDI 32-Hex Data-1 SSM Par msec 351 10 00 30 56 97 11 1 0200
277 01 800001 11
JcAIR 429E: 351 10 003056 11
This indicates that the UUT has undergone 3,056 power-on cycles.
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maintenance 523-0775657 5.5.6
Total Fault Counter (TFC) Buffer
Each time a diagnostic condition is recognized, the TFC buffer is incremented. Therefore, this buffer contains the number diagnostic conditions the unit has experienced.
5.5.6.1 TFC General Word Definition The TFC buffer data request word label 277 is defined as follows:
32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 9 - - - - - - - - - - - - - - - - 8 4 2 1 8 4 2 1 | \__/ | \__|__|__/ \__|__|__/ \__|__|__/ \__|__|__/ \__|__|__/ | | | | | | | | | | \<------------Pad--- -------->/ \<---02H--->/ | \__SSM, 11 implies a request for diagnostic data \__Parity The response word label 351 is defined as follows: 32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 - - - - - - - - - - - - - - - - 8 4 2 1 8 4 2 | \__/ | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | Pad \10,000’S/ \1,000’S / \ 100’S / \ 10’S / \units | \__SSM, 11 implies response to a request for diagnostic data \__Parity
9 1 | | /
5.5.6.2 TFC Buffer Examination Setup bus reader XMT screens as follows:
The reader should respond with a label 351 word similar to this:
DataTrac: ON------------XMT 1----------12.5 KHz LBL SDI 32-Hex Data-1 SSM Par msec 277 10 80 00 02 FD 11 1 0100
JcAIR 429E: 277 10 800002 11
DataTrac: ON------------RCV 1--(ALL)---12.5 KHz LBL SDI 32-Hex Data-1 SSM Par msec 351 10 60 01 02 97 11 1 0200
JcAIR 429E: 351 10 600102 11
This indicates that the UUT has experienced 102 diagnostic conditions.
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maintenance 523-0775657 5.5.7 Total Power-on Timer (Hours) (TPOTH) Buffer Two data buffers are used to record the total time the unit is in operation; an hours buffer and a minutes buffer. As the unit is operating, the minutes counter is continuously incremented. The hours buffer is incremented each time the minutes counter overflows.
5.5.7.1 TPOTH General Word Definition The total TPOTH buffer data request word label 277 is defined as follows:
32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 9 - - - - - - - - - - - - - - - - 8 4 2 1 8 4 2 1 | \__/ | \__|__|__/ \__|__|__/ \__|__|__/ \__|__|__/ \__|__|__/ | | | | | | | | | | \<--------Pad------------> / \<----03H--->/ | \__SSM, 11 implies a request for diagnostic data \__Parity The response word label 351 is defined as follows: 32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 - - - - - - - - - - - - - - - - 8 4 2 1 8 4 2 | \__/ | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | Pad \10,000’S/ \1,000’S / \ 100’S / \ 10’S / \units | \__SSM, 11 implies response to a request for diagnostic data \__Parity
9 1 | | /
5.5.7.2 TPOTH Buffer Examination Setup bus reader XMT screens as follows:
The reader should respond with a label 351 word similar to this:
DataTrac: ON------------XMT 1----------12.5 KHz LBL SDI 32-Hex Data-1 SSM Par msec 277 11 60 00 03 FD 11 1 0100
JcAIR 429E: 277 11 600003 11
DataTrac: ON------------RCV 1--(ALL)---12.5 KHz LBL SDI 32-Hex Data-1 SSM Par msec 351 11 E0 03 57 97 11 1 0200
JcAIR 429E: 351 11 E00357 11
This example shows that the TPTOH buffer contains the value 357.
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maintenance 523-0775657 5.5.8 Total Power-on Timer (Minutes) (TPOTM) Buffer The TPOTM buffer is incremented each minute that the unit has power applied. Overflow of this buffer causes the TPOTH buffer to be incremented.
5.5.8.1 TPOTM General Word Definition The total TPOTM buffer data request word label 277 is defined as follows:
32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 - - - - - - - - - - - - - - - | \__/ | \__|__|__/ \__|__|__/ \__|__|__/ | | | | | | | | \<--------Pad------------> / | \__SSM, 11 implies a request for diagnostic \__Parity
16 15 14 13 12 11 10 9 8 4 2 1 8 4 2 1 \__|__|__/ \__|__|__/ | | \<---04H--->/ data
The response word label 351 is defined as follows: 32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 - - - - - - - - - - - - - - - - 8 4 2 1 8 4 2 | \__/ | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | Pad \not used/ \not used/ \not used/ \ 10’S / \units | \__SSM, 11 implies response to a request for diagnostic data \__Parity
9 1 | | /
5.5.8.2 TPOTM Buffer Examination Setup bus reader XMT screens as follows:
The reader should respond with a label 351 word similar to this:
DataTrac: ON------------XMT 1----------12.5 KHz LBL SDI 32-Hex Data-1 SSM Par msec 277 00 E0 00 04 FD 11 1 0100
JcAIR 429E: 277 00 E00004 11
DataTrac: ON------------RCV 1--(ALL)---12.5 KHz LBL SDI 32-Hex Data-1 SSM Par msec 351 11 60 00 27 97 11 1 0200
JcAIR 429E: 351 11 600027 11
This indicates that the unit TPTOM buffer contains the number 27.
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maintenance 523-0775657 5.5.9 Last Power-on Cycle (LPOC) Fault Counter Buffer This buffer contains the number of diagnostic conditions detected during the most recent power-on cycle.
5.5.9.1 LPOC General Word Definition The last LPOC fault counter buffer data request word label 277 is defined as follows:
32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 9 - - - - - - - - - - - - - - - - 8 4 2 1 8 4 2 1 | \__/ | \__|__|__/ \__|__|__/ \__|__|__/ \__|__|__/ \__|__|__/ | | | | | | | | | | \<--------Pad------------> / \<---05H--->/ | \__SSM, 11 implies a request for diagnostic data \__Parity The response word label 351 is defined as follows: 32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 - - - - - - - - - - - - - - - - 8 4 2 1 8 4 2 | \__/ | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | Pad \not used/ \not used/ \ 100’s / \ 10’s / \units | \__SSM, 11 implies response to request for diagnostic data \__Parity
9 1 | | /
5.5.9.2 LPOC Buffer Examination Setup bus reader XMT screens as follows:
The reader should respond with a label 351 word similar to this:
DataTrac: ON------------XMT 1----------12.5 KHz LBL SDI 32-Hex Data-1 SSM Par msec 277 01 60 00 05 FD 11 1 0100
JcAIR 429E: 277 01 600005 11
DataTrac: ON------------RCV 1--(ALL)---12.5 KHz LBL SDI 32-Hex Data-1 SSM Par msec 351 11 E0 00 07 97 11 0200
JcAIR 429E: 351 11 E00007 11
This indicates that during the most recent poweron cycle 7 diagnostic conditions were detected.
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maintenance 523-0775657 5.5.10 Last Maintenance Date (LMD) Buffer (Examination)
upon whether the date was properly entered. 5.5.10.1
This buffer should contains the most recent maintenance date. Whether or not this date accurately reflects the date on which the unit was most recently repaired or tested depends
LMD General Word Definition
The LMD buffer data request word label 277 is defined as follows:
32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 9 - - - - - - - - - - - - - - - - 8 4 2 1 8 4 2 1 | \__/ | \__|__|__/ \__|__|__/ \__|__|__/ \__|__|__/ \__|__|__/ | | | | | | | | | | \<--------Pad------------> / \<---07H--->/ | \__SSM, 11 implies a request for diagnostic data \__Parity The response word label 351 is defined as follows: 1: 32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 2: 8 4 2 1 8 4 2 1 8 4 2 1 8 4 2 1 8 | | | | \ | | / \ | | / \ | | / | | | | | | | | \ | \ / \__BCD month \ BCD day / | \__SSM bits, 11 implies response to a request \__Parity 5.5.10.2
LMD Buffer Examination
Setup bus reader XMT screens as follows: DataTrac: ON------------XMT 1----------12.5 KHz LBL SDI 32-Hex Data-1 SSM Par msec 277 11 E0 00 07 FD 11 1 0100
JcAIR 429E: 277 11 E00007 11
The reader should respond with a label 351 word similar to this: DataTrac: ON------------RCV 1--(ALL)---12.5 KHz LBL SDI 32-Hex Data-1 SSM Par msec 351 01 70 06 91 97 11 1 0200
15 4 | |
14 2 | |
13 12 11 10 9 1 8 4 2 1 | | | | | / \ | | / \ BCD yr / for diagnostic data
This indicates that the last maintenance date for this unit was October 6, 1991. You need to recognize that the 7, here, includes the SSM bits which for a value of 6 (4 + 2). Thus 7 - 6 = 1 which means that bit 29 is a 1. This sets the month at 10; October. 5.5.11 Last Maintenance Date (LMD) Buffer (Update) A method for updating the LMD buffer is not included in this manual. The LMD buffer should be changed only after a repair action, unit modification, or detailed test procedure has been performed.
JcAIR 429E: 351 01 700691 11
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maintenance 523-0775657 5.5.12 Last Power-on Cycle Faults (LPOCF) Data This process allows for retrieval of all the diagnostics detected during the most recent power-on cycle. This can be seen as an extension to step 5.5.5. In that step we learned the number of faults detected during the most recent power-on cycle. In this sequence we will learn what those diagnostic codes are. In this sequence you must watch the label 351 word carefully. The UUT may transmit several words, each with a different diagnostic code, at 5-second intervals.
The first transmission is the contents of the current Total Power-on Cycle count buffer (as in 5.5.5 above). This is followed, in 5-second intervals, with a transmission of each of the diagnostic codes encountered during the most recent power-on cycle (self-test). The sequence is automatic therefore you should be prepared to write down the data as it appears. The final label 351 word is likely to be a word similar to 07FFE which does not translate into a meaningful diagnostic code. 5.5.12.1
LPOCF General Word Definition
The LPOCF data request word label 277 is defined as follows:
32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 9 - - - - - - - - - - - - - - - - 8 4 2 1 8 4 2 1 | \__/ | \__|__|__/ \__|__|__/ \__|__|__/ \__|__|__/ \__|__|__/ | | | | | | | | | | \<--------Pad------------> / \<---10H--->/ | \__SSM, 11 implies a request for diagnostic data \__Parity The first response label 351 word is defined in paragraph 5.5.5.
The second and subsequent response label 351 word(s) are defined as follows:
32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 9 - - - - - - - - - - - - - - - - 8 4 2 1 8 4 2 1 | \__/ | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | Pad \not used/ \not used/ \not used/ \ Hex fault code / | \__11 implies response to detailed diagnostic data request \__Parity 5.5.12.2
LPOCF Data
Setup bus reader XMT screens as follows:
The reader should respond with a label 351 word similar to this:
DataTrac: ON------------XMT 1----------12.5 KHz LBL SDI 32-Hex Data-1 SSM Par msec 277 00 E0 00 10 FD 11 1 0100
JcAIR 429E: 277 00 E00010 11
DataTrac: ON------------RCV 1--(ALL)---12.5 KHz LBL SDI 32-Hex Data-1 SSM Par msec 351 11 E0 00 B3 97 11 1 0200
JcAIR 429E: 351 11 E000B3 11
This example indicates that this unit experienced a diagnostic code B3 at the last power on cycle. One of the 351 label words may indicate an FF label which. This code is not defined and so you can ignore it.
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You may likely encounter a diagnostic code B3 on the bench. This diagnostic is interpreted as "TCAS bus inactive".
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maintenance 523-0775657 5.5.13 Continue Flight Fault (CFF) Data This paragraph can be seen as an extension of the previous paragraph 5.5.12. In that paragraph only those diagnostics detected during the most recent power-on cycle are revealed. In this paragraph, 5.5.12, all of the diagnostics stored in NVRAM and detected during preceding power-on cycles are examined. 5.5.13.1
CFF General Word Definition
The data format is the same as in paragraph 5.5.12 except that the hex data in the label 277 interrogation word is incremented from 10H to 1XH. Of course, if you have already examined the 10H, in paragraph 5.5.12, you Buffer 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16
277 Word 10H 11H 12H 13H 14H 15H 16H 17H 18H 19H 1AH 1BH 1CH 1DH 1EH 1FH
can begin here with 11H. The UUT responds by sending each stored code for a 5-second period. Continue incrementing the hex data until the UUT sends an ’end of file’ data field = 00EOFH. This is displayed on the DataTrac and JcAIR 429E as 000EOF. , you only need to change digits 5 and 6 in the data fields of both the DataTrac and JcAIR readers. The SDI and parity bits will change automatically. 5.5.13.2
CFF General Procedures
The diagnostic conditions detected during the preceding 16 (maximum) power-on cycles can be reviewed by interrogating the UUT with a label 277 data word, with SSM set to 10 and the data in the bit field, bits 9 through 16 set to 1X as follows (assuming no. 1 being the most recent):
DataTrac 200/400/400H, 277 Word Setup Lbl SDI 32-Hex Data-1 SM Par msec 277 00 E0 00 10 FD 11 1 0100 277 01 60 00 11 FD 11 1 0100 277 10 60 00 12 FD 11 1 0100 277 11 E0 00 13 FD 11 1 0100 277 00 60 00 14 FD 11 1 0100 277 01 E0 00 15 FD 11 1 0100 277 10 E0 00 16 FD 11 1 0100 277 11 60 00 17 FD 11 1 0100 277 00 60 00 18 FD 11 1 0100 277 01 E0 00 19 FD 11 1 0100 277 10 E0 00 1A FD 11 1 0100 277 11 60 00 1B FD 11 1 0100 277 00 E0 00 1C FD 11 1 0100 277 01 60 00 1D FD 11 1 0100 277 10 60 00 1E FD 11 1 0100 277 11 E0 00 1F FD 11 1 0100
JcAIR 429E, 277 word 277 277 277 277 277 277 277 277 277 277 277 277 277 277 277 277
00 01 10 11 00 01 10 11 00 01 10 11 00 01 10 11
E00010 600011 600012 E00013 600014 E00015 E00016 600017 600018 E00019 E0001A 60001B E0001C 60001D 60001E E0001F
11 11 11 11 11 11 11 11 11 11 11 11 11 11 11 11
Any of the above can produce a response:
DataTrac: ON------------RCV 1--(ALL)---12.5 KHz LBL SDI 32-Hex Data-1 SSM Par msec 351 11 E0 30 57 97 11 1 0200 351 11 E0 0E 0F 97 11 1 0200
JcAIR 429E: 351 11 E03057 00 351 11 E00E0F 00
The UUT should respond with at least two label 351 data words. The first is the contents of the Total Power-on Counter buffer
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which may be a relatively large number depending on the length of time the unit has been in service.
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maintenance 523-0775657 Special note for -002 units: In -002 units, only the internal diagnostic conditions resulting in a failure-warn condition and improper mode S address diagnostic conditions are stored. The mode S address diagnostic can easily occur when the unit is turned on with all address lines open or shorted to ground. Consequently you may frequently notice a 0000FF hex code as the second 351 word. It is also possible that in some units you may encounter a Total Power-on Timer (Hours) buffer with an unrealistically large number. Early units were not properly cleared at production. In these cases, of course, the data is of no value.
intended for use with a data storage device which is capable of capturing and storing data transmitted in rapid sequence. The DataTrac 400/400H is capable of this function. After ing the data, it can then be further ed, using procedures and software supplied with the DataTrac 400/400H, onto a PC for detailed analysis and permanent storage. The DataTrac 200 is capable of capturing the data but lacks the means of transferring it for external storage and interpretation. A manual analysis is seen as inefficiently laborious and time consuming and therefore is not recommended. However, if this is not seen as prohibitive, refer to paragraph 5.5.14 for the Slow Fault Data . 5.5.14.1
FF General Word Definition
5.5.14 Fast Fault (FF) Data The feature used in this paragraph is
The FF data request word label 277 is defined as follows:
32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 9 - - - - - - - - - - - - - - - - 8 4 2 1 8 4 2 1 | \__/ | \__|__|__/ \__|__|__/ \__|__|__/ \__|__|__/ \__|__|__/ | | | | | | | | | | \<--------Pad------------> / \<---50H--->/ | \__SSM, 11 implies a request for diagnostic data \__Parity 5.5.14.2 FF Data Description When the 277 label word as described in paragraph 5.5.14.1 is sent to the UUT, it responds as follows: a. Power-on cycle counter buffer as described in paragraph 5.5.5 above. b. Total fault counter buffer as described in paragraph 5.5.6 above. c. Total power-on timer (hours) buffer as described in paragraph 5.5.7 above. d. Total power-on timer (minutes) buffer as described in paragraph 5.5.8 above. e. Last power-on cycle fault counter buffer as described in paragraph 5.5.9 above. f. Last maintenance date buffer as described in paragraph 5.5.10 above.
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The UUT then transmits a ’break’ indicator using the same format as described in paragraph 5.5.7 (power-on timer (hours)), except the data is set to 00FFFF. Following this the UUT transmits the nine (9) fault data bytes for the last recorded diagnostic in the following sequence and formats: g. Current Power-on Cycle count buffer as described in 5.5.5 above. h. Diagnostic code as described in paragraph 5.5.9 above. i. Time from last power-on using the following format:
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maintenance 523-0775657 32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 - - - - - - - - - - - - 8 4 2 1 8 4 2 1 8 4 2 | \__/ | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | Pad \not used/ \not used/ \ 1 Hr / \10 min / \ 1 min | \__SSM, 11 implies response to request for diagnostic data \__Parity
9 1 | | /
j. Transmitter temperature at time of diagnostic using the following format: 32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 - - - - - - - - - - - - 8 4 2 1 8 4 2 1 8 4 2 | \__/ | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | Pad \not used/ \not used/ \ 100’s / \ 10’s / \ units | \__SSM, 11 implies response to request for diagnostic data \__Parity
9 1 | | /
k. Air/ground state at time the diagnostic was detected, using the following format: 32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 - - - - - - - - - - - - - - - - 8 4 2 1 8 4 2 | \__/ | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | FAH = in air | | Pad \not used/ \not used/ \not used/ \ FDH = on ground | \__SSM, 11 implies response to request for diagnostic data \__Parity
9 1 | / /
l. Time at end of power-on cycle as described in transmission i. above. m. Altitude at time of diagnostic using the following format: 32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 - - - - - - - - - - - - - - - - 8 4 2 1 8 4 2 | \__/ | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | Pad \10,000s / \1000s / \ 100s / \ 10s / \ units | \__SSM, 11 implies response to request for diagnostic data \__Parity
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9 1 | | /
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maintenance 523-0775657 5.5.14.3
FF Data Equipment
This feature is intended for those with access to an automated means of requesting, capturing, and analyzing the data. Such facilities are at least partially available from sources other than Collins and you are encouraged to acquire and use them. For example: • Atlantic Instruments supplies hardware and software, operating with the DataTrac 400/400H, for automatically capturing and ing the data onto a PC. • Avionica Inc., 3830, SW 130th Ave., Miami FL 33175, supplies a laptop computer equipped with appropriate hardware and software to , store, and display diagnostic data from a number of Collins units including the TDR-94/94D Mode S Transponder as well as the TTR-920 TCAS Transmitter/Receiver.
5.5.15.1
SF General Word Definition
Same as 5.5.13.1 except hex data is set to 51H. 5.5.15.2
SF Data Procedure
Use the following chart, reproduced in a quantity required, to record the data as it appears on your databus reader. Set the bus reader for the proper display format for direct interpretation of the data as described in the preceding paragraphs.
5.5.15 Slow Fault (SF) Data This data feature is basically the same as that described in paragraph 5.5.13 except that the hex field in the data request word is set to 51H (instead of 50H). This will cause the UUT to transmit the same data as described in paragraph 5.5.13 except that it is transmitted one data file at a time at 5 seconds intervals.
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maintenance 523-0775657 *******
Duplicate this sheet as required
*******
Date: _______________ UUT Type: _____( ) TDR-94: Part No: 622-9352UUT Type: _____( ) TDR-94D: Part No: 622-9210UUT Serno: _____________ Customer: _________________________________________ Data taken by: ____________________________________ (Your name)
TDR-94/94D Diagnostic
Diagnostic Code
Power-on Cycle Counter: _________ Total Fault Counter: _________ Total Power-on Timer (Hrs): _________ Total Power-on Timer (Min): _________ Last Power-on Fault Counter: _________ Existing Last Maintenance Date: _________ New Last Maintenance Date: * _________ Break: ___ 0FFFFF Current Power-on Cycle Count: _________ Diagnostic Code: _________ Time From Last Power-on: _________ Xmitter Temp at Diag: _________ Air/Gnd State at Diag: _________ Time at end of Power-on Cycle: _________ Altitude at Diag: _________
Data Record Interpretation _______________________ _______________________ _______________________ _______________________ _______________________ _______________________ _______________________ _______________________ _______________________ _______________________ _______________________ _______________________ _______________________ _______________________
* To be changed only after repair, modification, or detailed (bench) test. Power-on cycle diagnostics (1 = most recent): 1:___________, 2:___________, 3:_____________, 4:____________, 5:____________, 6:___________, 7:____________, 8:____________, 9:___________, 10:___________, 11:__________, 12:___________, 13:___________, 14:____________, 15:___________, 16:____________, 17:___________, 19:___________, 20:___________, 21:____________, 22:___________, 23:____________, 24:____________ Comments: ______________________________________________________________________________ _____________________________________________________________________________ _____________________________________________________________________________ _____________________________________________________________________________
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maintenance 523-0775657 5.6 NUMBER SYSTEM CONVERSION AND DATA WORD DESCRIPTIONS
If you have one of these, use it. Otherwise, this paragraph describes a relatively simple method of converting between the Hexadecimal and Octal numbering systems. This is useful for Mode S transponder testing because the data systems used in the mode s transponder use all three systems. For example, the mode s address is typically assigned as an eight-digit octal number. This octal number is translated into a binary number for address strapping at installation. During testing, quite often this address is displayed as a six-digit hexadecimal number.
This paragraph provides detailed descriptions of the various data formats used in the TDR94/94D. These formats use a variety of numbering systems including binary, octal, and hexadecimal. Paragraph 5.6.1 provides a procedure for conversion between these numbering systems. If you are familiar with a conversion process, you should feel free to use that process. 5.6.1 Octal-to-Binary-to-Hexadecimal, and Back
Use the following listing to convert your hexadecimal or octal number to its binary equivalent.
There are many relatively inexpensive handheld calculators with number conversion capability available. Hex-to-Binary Conversion Hex 0 1 2 3 4 5 6 7
Binary 0000 0001 0010 0011 0100 0101 0110 0111
Hex 8 9 A B C D E F
Octal-to-Binary Conversion
Binary 1000 1001 1010 1011 1100 1101 1110 1111
Octal 0 1 2 3 4 5 6 7
Convert from the six-digit hexadecimal number to an eight-digit octal number as follows: Enter the hex number on the top (Hex) line of the following chart. Then enter the equivalent binary values for each hex Hex: Bit Val:
Binary 000 001 010 011 100 101 110 111
digit from the listing above in the center (Bin) line. Then use the lower bit values to convert those binary bits, three bits at a time, into the equivalent octal number and enter those numbers on the lower (Oct) line.
8
4
2
1
8
4
2
1
8
4
2
1
8
4
2
1
8
4
2
1
8
4
2
1
4
2
1
4
2
1
4
2
1
4
2
1
4
2
1
4
2
1
4
2
1
4
2
1
Bin: Bit Val: Oct:
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maintenance 523-0775657 Example: Suppose the test set shows a hex code 3AC421. Enter this code on the top line. Then write the equivalent four digit binary values (from the
hexadecimal listing above) in spaces below each hex digit. Then translate each threedigit grouping of binary numbers into the equivalent octal number.
Hex: Bit Val:
8
4
2
1
8
4
2
1
8
4
2
1
8
4
2
1
8
4
2
1
8
4
2
1
Binary:
0
0
1
1
1
0
1
0
1
1
0
0
0
1
0
0
0
0
1
0
0
0
0
1
Bit Val: Oct:
4
2 1
1
4
2 6
1
4
2 5
1
4
2 4
1
4
2 2
1
4
2 0
1
4
2 4
1
4
2 1
1
3
A
C
To convert from octal to hex, reverse the above process by entering the octal number into the spaces on the lower line. Convert each octal digit into its equivalent binary value. Then convert each four-digit grouping into its equivalent hex value as shown in the Hex-to-Binary conversion listing above-left. Write these numbers into the spaces on the top line. The binary digits, read from left to right, correspond to the mode s addressing switches on the test . That is, the far left digit corresponds to switch and rear connector pin P1-33, the next P1-34, etc, to the far right which is P1-56. The switch set to the OFF position corresponds to a 0; the switch set to SEL corresponds to a 1. The suggested layout shown in figure 5-3 shows the mode s switches labeled according to the octal digits that each controls. This makes the octal code easy to read from the switch positions by adding the binary value of those switches in each 3-switch group set to SEL. You must avoid, however, the combination with all switches up or all switches down. These two combinations are not allowed in the mode s addressing scheme and will produce a transponder diagnostic code FF in TDR-94/94D units with N ending in -002. 5.6.2 Diagnostic Word, ARINC 429 label 350, Definition and Decoding Procedure 5.6.2.1 On DataTrac 400/400H The diagnostic codes listed in table 5-2 are available for viewing on the ARINC 429 label 350 diagnostic word. The DataTrac 400 is capable of displaying this word in a variety of binary and hexadecimal forms. The form that is selected is largely a matter of 5/5/1993
4
2
1
personal preference but the form chosen here is labeled BIN19L. This paragraph shows you how to decode the diagnostic information from this displayed word. Refer to the screen representation below. This shows the label 350 word from bits 29 through 11 as it appears on the DataTrac 400/400H display set for a BIN19L display. (The actual screen will show other words and their labels but this discussion focuses only on the label 350 word.) -----------------RCV 1--(ALL)---12.5 KHz Lbl SDI 29--Binary Data--11 SSM Par msec 350 01 1000010110011000000 11 1 0200
Of course, you can also select the hex display mode for a direct display of the diagnostic code and avoid the conversion process. -----------------RCV 1----------12.5 KHz Lbl SDI 32-Hex Data-1 SSM Par msec 350 01 70 B3 01 17 11 1 0200 ||<---diagnostic code
This display can be reproduced as follows: a. With the ATC-601 set for ATCRBS REPLY, set the test POWER switch to OFF. b. On the test , set the TCAS/NO TCAS switch to TCAS. c. On the DataTrac 400/400H, press RCV and then press ENT. (This clears the display and prepares the analyzer to receive new data.) d. On the test , set the POWER switch to ON. e. After a few seconds, the XFEED OUT lamp lights, the ATC-601 REPLY lamp lights, and the data is displayed on the DataTrac 400/400H RCV 1 screen.
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maintenance 523-0775657 Note: If the 350 word does not appear on the DataTrac 400/400H screen initially, press RCV (until the cursor is at the left of HOLD), then press the down arrow (or up arrow) key to scroll the data words until the 350 word appears. Bits 17 through 24 are the eight data bits that define the 2-digit hexadecimal diagnostic code as follows: Diagnostic digit: MSB Bit: 24 23 Bin value: 8 4 Example: 1 0 Diag: |< B
Bit DEFINITION Bit DEFINITION 11 Xpdr failure
16 Serial control port c failure
12 RAM failure
25 Serial altitude port a failure
13 ROM failure
26 Serial altitude port b failure
LSB 22 2 1
21 1 1 >|
20 8 0 |<
19 18 4 2 0 1 3
14 Port b failure 27 Serial ADLP bus failure
17 1 1 >|
15 Port a failure 28 Serial TCAS bus failure *
Interpretation:TCAS bus inactive (see table 5-2)
The defined failure condition exists when a logic 1 appears in the corresponding bit location.
The conversion process involves translating each of these four-bit groupings into the equivalent hexadecimal value using the binary to hex conversion list in paragraph 5.6.1 above.
* Notice in the screen example above, bit 28 is also set to 1. Incidentally, in the label 350 diagnostic word, bit 29 is defined as a PAD.
Bits 11 through 16, and 25 through 28 identify specific failure conditions. These are defined below.
5.6.2.2 On DataTrac 200 The DataTrac 200 displays the diagnostic code in the HEX RCV field in the form of 5 hex digits as follows:
Hex:
MSB
Data bit: Bit Val:
4
3
2
LSB
30
29
28
27
26
25
24
23
22
21
20
19
18
17
16
15
14
13
12
11
10
8
4
2
1
8
4
2
1
8
4
2
1
8
4
2
1
8
4
2
1
*
* bit 10 is not included in the display
In the test procedures, a TCAS Bus failure diagnostic is induced producing a diagnostic code B3. This
5/5/1993
appears on the DataTrac 200 as a Hex code 45980. This is produced as follows:
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MSB
Data bit: Bit Val: Hex value: Binary: Bit Val:
30 8
29 4
0
1
28 2
4
3
27 1
26 8
25 4
24 2
0
0
1 8
0 4
4 0
23 1
2
22 8
21 4
20 2
1 1
0 8
0 4
5
Data bit: Bit Val: Hex value: Binary: Bit Val:
30 8
29 4
0
1
28 2
Hex value:
15 1
1 1
0
0
0
26 8
25 4
24 2
0
0
1 8
1 4
23 1
12 2
11 1
0
0
0
10 *
0 0
-----------------RCV 1--(ALL)---12.5 KHz Lbl SDI 32-Hex Data-1 SSM Par msec 350 01 68 B3 01 17 11 1 0200 ||<---diagnostic code
In this format you can read the diagnostic code directly from the second pair of hex digits (from the left). Suppose the DataTrac 200 shows a HEX DATA field 47A80. You would interpret this code as follows:
2
22 8
21 4
20 2
1 1
0 8
1 4
7
19 1
LSB
18 8
17 4
16 2
15 1
1 1
0
0
0
A 1 2
13 4
8
3
27 1
14 8
There is an easier way to interpret the diagnostic code and that is to select the 32-Hex Data--1 display format. This will give you a display:
4
4 0
16 2
3
Thus, to properly interpret a diagnostic code as displayed on the DataTrac 200, you must first translate that code into its binary form, extending from bit 11 through 29. Then translate the two four-bit groupings, 18 through 21 for the LSB, and 22 through 25 for the MSB, into the hex diagnostic code. Then refer to table 5-2 for the defined diagnostic. It is important to that bits 11 through 16, and 25 through 28, define specific failure conditions as described in the previous paragraph for the DataTrac 400.
MSB
17 4
1 2
B
Hex bit:
18 8
9 1 2
Hex value:
19 1
LSB
F
14 8
13 4
12 2
11 1
0
0
0
8
0 2
10 *
0 0
5
Thus a DataTrac 200, HEX DATA field display of 47A80 is a diagnostic code F5, which is shown on table 5-2 as Port Selects Changed.
first byte (first 8 bits which forms byte 0) of the data word. The label is described in paragraph 5.6.5 below.
5.6.3 tions
The data word with label 031 is the only control word used by the TDR-94/94D. Label 031 is the standard ATCRBS control word. Word label 016 has been redefined for addressing the TCAS displays. Word labels 013 and 015 are TCAS related words. Labels 016 and 015 are described here only for informational purposes. The TDR-94/94D will accept word labels 013, 015, and 016
Transponder Control Word Defini-
This paragraph describes the various control words used by the TDR-94/94D mode s transponder. 5.6.3.1 ARINC 429, Label 031, 015, and 016, Control Words In ARINC 429, the label is formed by the 5/5/1993
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Label 015: Bit No. 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32
Label 031: Bit No. 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32
Definition SDI Code (see note 1) SDI Code (see note 1) Alt Reporting, On/Off (1=on) Pad Ident, On/Off (1=on) Alt Port Selected, (1=B) Pad Pad Pad Mode a, code D1 Mode a, code D2 Mode a, code D4 Mode a, code C1 Mode a, code C2 Mode a, code C4 Mode a, code B1 Mode a, code B2 Mode a, code B4 Mode a, code A1 Mode a, code A2 Mode a, code A4 SSM (see note 4) SSM (see note 4) Parity
Label 016: Bit No. 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32
5/5/1993
Definition SDI Code (see note 1) SDI Code (see note 1) Altitude limit A 100 Altitude limit A 200 Altitude limit A 400 Altitude limit A 800 Altitude limit A 1600 Altitude limit A 3200 Altitude limit A 6400 Altitude limit B 100 Altitude limit B 200 Altitude limit B 400 Altitude limit B 800 Altitude limit B 1600 Altitude limit B 3200 Altitude limit B 6400 spare spare spare spare spare SSM (see note 4) SSM (see note 4) Parity
Note 1: See paragraph 5.6.4.1 below Note 2: The display control bits control the TCAS display as follows. This information is supplied by a TCAS control and is ed through the transponder unchanged.
Definition SDI Code (see note 1) SDI Code (see note 1) Alt Reporting, On/Off (1=on) SPI (0=ident off) Display control (see note 2) Display control (see note 2) Sens level 0 (see note 3) Sens level 1 (see note 3) Sens level 2 (see note 3) 4096, code D1 4096, code D2 4096, code D4 4096, code C1 4096, code C2 4096, code C4 4096, code B1 4096, code B2 4096, code B4 4096, code A1 4096, code A2 4096, code A4 SSM (see note 4) SSM (see note 4) Parity
BIT 14 13
Definition
0 0 1 1
Primary and traffic display Primary display only TCAS traffic display only No control function possible
0 1 0 1
Note 3: Sensitivity level is TCAS control information that is provided via an uplink message from a groundbased controller. Bit combination definitions are as follows: BIT 17 16 15 0 0 0 0 0 1 0 1 0 0 1 1 1 0 0 1 0 1 1 1 0 1 1 1
Definition SL 0 (Automatic) SL 1 (STBY) SL 2 (TA only) SL 3 SL 4 SL 5 SL 6 SL 7
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maintenance 523-0775657 Note 4: SSM code definitions are as follows: BIT 31 30
Definitions Label 031
Label 016/015/013
0 0 1 1
Normal operation No computed data Functional test Not used
Normal operation No computed data Functional test Failure warning
0 1 0 1
Label 013: Bit No. 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32
The first eight bits form the first byte and contain the word label: Byte 0 is the label byte: Bit: Logic: Hex:
7 0 |
6 0
5 0 1
4 1 |
3 1 |
2 1
1 1 E
0 0 |
Byte 1 is the status byte: Definition SDI Code (see note 1) SDI Code (see note 1) Flight level (0=relative, 1= absolute) Altitude select (see note 2) Altitude select (see note 2) spare spare spare spare defined defined defined defined 0.5, TCAS range 1.0, TCAS range 2.0, TCAS range 4.0, TCAS range 8.0, TCAS range 16.0, TCAS range 32.0, TCAS range 64.0, TCAS range SSM (see note 4 above) S2SM (see note 4 above) Parity
Bit: Def:
7 6 5 4 3 2 1 0 | | | | | | |< --|<--SI(*) | | | | | |<--Test (1= on) | | | | |<--ATC Ident (1=on) | | | |<--Alt reporting (1=on) | | |<--Mode (1 = standby) | |<--Pad |<--Code valid (1 = valid)
* For Source identifier definition, refer to paragraph 5.6.4.2 below. Bytes 2 and 3 convey the ATC code: Byte 2: Bit: Value: Def:
7 6 4 Pd | < ATC
5 4 2 1 | | C codes >
3 2 4 Pd | < ATC
7 6 4 Pd | < ATC
5 4 2 1 | | A codes >
3 2 4 Pd | < ATC
1 0 2 1 | | D codes >
Byte 3:
Note 1: See paragraph 5.6.4.1 below Note 2: TCAS Altitude selects:
Bit: Value: Def:
1 0 2 1 | | B codes >
BIT 13 12
Definition
0 0 1 1
Normal (-A to +A) Above (-A to +B) Below (-B to +A) Unrestricted
Bytes 4 and 5 convey the Gillham code altitude information:
CSDB, Label 1E, Control Word
Bit: Value: Def:
0 1 0 1
5.6.3.2
The TDR-94/94D uses CSDB word label 1E for CSDB control. All CSDB words consist of 6 bytes, with each bytes consisting of 8 bits. These bytes are typically identified as bytes 0 through 5. Byte 0 is the label byte, byte 1 is known as the status byte, and bytes 2 through 5 transmit the object data. The bytes are described as follows:
6/15/1995
Byte 4:
7 6 5 4 4 2 1 Pd | | | < ALT C codes >
3 2 4 Pd | < Alt D
1 0 2 1 | | codes >
7 6 5 4 4 2 1 Pd | | | < ALT A codes >
3 2 4 Pd | < Alt B
1 0 2 1 | | codes >
Byte 5: Bit: Value: Def:
Refer to paragraph 5.7 for additional Gillham altitude code information.
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Bytes 4 and 5 convey barometric altitude:
The TDR-94/94D uses CSDB word label A0 for CSDB altitude data; both pressure and barometric. As in all other CSDB words, word label A0 consists of six 8-bit bytes, identified as bytes 0 through 5. Byte 0 is the label byte; byte 1 is the status byte; bytes 2 and 3 transmit the pressure altitude information; bytes 4 and 5 transmit the barometric altitude information. The detailed structure is as follows:
Byte 4: part 1 of barometric alt data:
7 1 |
6 0
5 1 A
4 0 |
3 0 |
2 0
1 0 0
0 0 |
Byte 1 is the status byte: Bit: Def:
7 6 5 4 3 2 1 0 | | | | | | |<- |<--SI(*) | | | | | |<--Test (1 = on) | | | | |<-- 1 = xside baro | | | |<--Strut sw (1 = on gnd) | | |<-- Rsvd for preselect (**) | |<--Baro alt valid (1 = valid) |<--Pres alt valid (1 = valid)
* For Source identifier definition, refer to paragraph 5.6.4.2 below. ** Bit 5 of byte 1 is bit 1 of a two-bit matrix for a altitude preselect function. Bit 2 is in the same location of data word A1. Bytes 2 and 3 convey pressure altitude: Byte 2: part 1 of pressure alt data: Bit: Bin wt: Alt wt:
7 6 5 4 8 4 2 1 | | | |<16 | | |<32 | |<64 |<128
3 2 1 0 8 4 2 1 | | | |<1 | | |<2 | |<4 |<8
Byte 3: part 2 of pressure alt data: Bit: Bin wt: Alt wt:
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7 8 | | | |<
6 5 4 4 2 1 | | |<4096 | |<8192 |<16384 -32768
3 2 1 0 8 4 2 1 | | | |<-256 | | |<512 | |<1024 |<2048
7 6 5 4 8 4 2 1 | | | |<16 | | |<32 | |<64 |<128
3 2 1 0 8 4 2 1 | | | |<1 | | |<2 | |<4 |<8
Byte 5: part 2 of barometric alt data: Bit: Bin wt: Alt wt:
Byte 0 is the label byte: Bit: Logic: Hex:
Bit: Bin wt: Alt wt:
7 8 | | | |<
6 5 4 4 2 1 | | |<4096 | |<8192 |<16384 -32768
3 2 1 0 8 4 2 1 | | | |<-256 | | |<512 | |<1024 |<2048
The bit pattern for any altitude within the range -8191 to +57343 feet, pressure or barometric, is encoded using two’s complement arithmetic with a 24576 foot offset. Use the following conversion methods as you wish: 1. Select the altitude to be encoded. 2. Subtract 24576 from that quantity. 3. If the result is negative, add 32768. * 4. Convert the result to binary using the altitude bit weights shown above. * If you use a calculator to do the decimal to binary conversion, you may not need to add this quantity. If it uses 2’s complement arithmetic for the conversion, you can ignore the addition. To decode a 16-bit binary number into a decimal quantity: 1. Select the binary quantity. 2. Convert the binary number into decimal using the altitude bit weights shown above. 3. If the MSB (bit 7 of bytes 3/5) is = 1, subtract 8192. If it is = 0, add 24576. ** 4. The result is the equivalent decimal quantity. ** If you use a calculator to do the binary-todecimal conversion, you may not need to subtract the 8192 in step 3. But you must add the 24576. (The 8192 is the difference between the 32768 2’s complement sign factor and the 24576 offset.)
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maintenance 523-0775657 5.6.4
SDI/SI Code Definitions
There are three important points here:
5.6.4.1 ARINC 429, SDI Definition In ARINC 429, bits 8 and 9, of all word labels, form the SDI code. The code definitions depend on the label as follows:
2. Notice also that the most significant bit (MSB) is defined by only two bits. This means that the MSB can have a value no greater than 3 (2 + 1). This also means that the numerically largest octal code possible is 377 which is displayed, bits 0 through 7, as 11111111.
BITS 9 8 0 0 0 1 1 0 1 1
DEFINITION FOR LABELS: 203/204 031/350/371 All-call Not used Side 1 Side 1 Side 2 Side 2 Not used Not used
BITS 9 8 0 0 0 1 1 0 1 1
DEFINITION FOR LABEL: 013 both left and right, RA/TA, bus #1 and #2 left, RA/TA, bus #1 right, RA/TA, bus #2 not defined
3. Notice also that the bit values are reversed from the values in the data fields. In the data fields, the values increase as you move from right to left. Here they values decrease in value, moving from right to left.
5.6.4.2 CSDB, SI Definition In CSDB, bits 0 and 1 of byte 1 form the source identifier and are defined as follows: BITS 1 0 0 0 0 1 1 0 1 1
DEFINITION FOR LABELS: 1E/1F/A0/F3 Not used Side 1 Side 2 Not used
5.6.5
Octal Label Definitions
1. Notice that the MSB is on the right, defined by the lower ordered bits. This is reversed from that of the data field where the MSB is defined by the higher ordered bits.
5.6.5.2 CSDB Hexadecimal Label Definition In CSDB the label of the word is a two digit hexadecimal number and is defined in the first 8-bits, byte 0, of the CSDB transmission. The bits are defined as follows: Label digit:
In ARINC 429, the label is expressed as an octal number. The equivalent in CSDB is expressed as a hexadecimal number.
MSB
Bit: 7 Bit value: 8 Example: Interp:
6 4
LSB 5 2
4 1
0 0 0 1 |------1-------|
3 8
2 4
1 2
0 1
1 1 1 0 |------E-------|
5.6.5.1 ARINC 429, Octal Label Definition Bits 0 through 7 form the octal label and are defined as follows: Label digit:
LSB
Bit: Bit value:
7 1
Example: Interp:
1 0 1 |<--5-->|
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6 2
2 5 4
4 1
3 2
MSB 2 4
1 0 0 |<--1-->|
1 1
0 2
0 0 |-0-|
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6/15/1995
5-154.2
maintenance 523-0775657 5.7 GILLHAM CODE DESCRIPTION with ENCODING AND DECODING INSTRUCTIONS This paragraph contains a description of the Gillham (ARINC 572) altitude encoding scheme. The paragraph also includes instructions for encoding and decoding. This can be helpful if you encounter an altitude discrepancy during a test or fault isolation procedure that is caused by a faulty digitizer or broken wire in the altitude bus.
Table 5-15 shows the encoding matrix for both the 500-foot increments as well as the 100-foot increments. Following the table are the encoding and decoding instructions.
Table 5-15. Gillham Altitude, ARINC 572, Encoding Scheme
|<--- ----D2,D4, A1,A2 0000 0001 0011 0010 0110 0111 0101 0100 1100 1101 1111 1110 1010 1011 1001 1000
-----
-----
-----
-----
-----
A4, B1, B2, B4
----
-----
-----
-----
-----
-----
----
----
--->|
0000
0001
0011
0010
0110
0111
0101
0100
1100
1101
1111
1110
1010
1011
1001
1000
0 31 32 63 64 95 96 127 128 159 160 191 192 223 224 255
1 30 33 62 65 94 97 126 129 158 161 190 193 222 225 254
2 29 34 61 66 93 98 125 130 157 162 189 194 221 226 253
3 28 35 60 67 92 99 124 131 156 163 188 195 220 227 252
4 27 36 59 68 91 100 123 132 155 164 187 196 219 228 251
5 26 37 58 69 90 101 122 133 154 165 186 197 218 229 250
6 25 38 57 70 89 102 121 134 153 166 185 198 217 230 249
7 24 39 56 71 88 103 120 135 152 167 184 199 216 231 248
8 23 40 55 72 87 104 119 136 151 168 183 200 215 232 247
9 22 41 54 73 86 105 118 137 150 169 182 201 214 233 246
10 21 42 53 74 85 106 117 138 149 170 181 202 213 234 245
11 20 43 52 75 84 107 116 139 148 171 180 203 212 235 244
12 19 44 51 76 83 108 115 140 147 171 179 204 211 236 243
13 18 45 50 77 82 109 114 141 146 173 178 205 210 237 242
14 17 46 49 78 81 110 113 142 145 174 177 206 209 238 241
15 16 47 48 79 80 111 112 143 144 175 176 207 208 239 240
256 segments, at 500 -ft intervals, from -1000 ft to 127,000 ft. 100-ft bits C1 __ 0 0 0 1 1
C2 __ 0 1 1 1 0
100-ft value if 500-ft segment is: C4 __ 1 1 0 0 0
odd _______ 7 (+ 200) 6 (+ 100) 5 (00) 4 (- 100) 3 (- 200)
even _______ 8 (- 200) 9 (- 100) 0 (00) 1 (+ 100) 2 (+ 200)
It is important to note that this scheme has no provision for C1, C2, and C4 bit patterns 000, 111, or 101.
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Gillham Code Decoding Instructions
This paragraph provides a method of translating a Gillham code pattern into altitude.
into the following measured bits row. If any of the bits are missing or not connected (and this is likely for bits D2, and D4.) just enter a 1 for that bit. (A measured 1 means it is not active.)
1. Determine the encoded bits and write them Bit names:
A
___ 1
A ___2
A ___4
B ___1
B ___2
B ___4
C ___1
C ___2
C ___4
D * D * D ___1 ___2 ___4
Measured bits:
___ ___ ___ ___ ___ ___ ___ ___ ___ _1_ ___ ___
Inverted logic:
___ ___ ___ ___ ___ ___ ___ ___ ___ _0_ ___ ___
2. Invert each of the bits and write that pattern into the inverted logic row.
8. Multiply that segment number by 500 and then subtract 1000. The result is the altitude to the nearest 500 feet.
3. From the inverted logic row, determine the encoded bit pattern for bits A4, B1, B2, B4.
9. From the inverted logic row, determine the encoded bit pattern for bits C1, C2 and C4 .
4. Compare that pattern to the listing of patterns on Table 5-15 for A4, B1, B2, B4 and note the column where you found the match.
10. If C1 and C4 are both 0 then you are finished. The result of step 8. is the final result. If C1 and C4 are not both 0 then proceed.
5. From the inverted logic row, determine the encoded bit pattern for bits D2, D4, A1, A2.
11. Find the sequence for C1, C2 and C4 in the lower part of Table 5-15. Note that row.
6. Compare that pattern to the listing of patterns in the left column of Table 5-15 and note the row where you found the match.
12. Depending on whether the segment number from step 7. above was odd or even, add or subtract either 100 or 200 to or from the 500-ft altitude. The result is the altitude to the nearest 100 feet.
7. Read the segment number from the point at which your marked column and row intersect.
Example: Suppose you measure the following logic levels on the test (1 = high or open, and 0 = low) Test Points: Measured: Invert logic:
___ 1
A
A ___2
A ___4
B ___1
B ___2
B ___4
C ___1
C ___2
C ___4
D * ___1
D * ___2
D ___4
1 0
0 1
0 1
0 1
1 0
1 0
1 0
1 0
0 1
1 0
1 0
0 1
Column data: 1100 Row data: 0101 Referring to the matrix in Table 5-15 above, this identifies segment 104. Multiply segment by 500 and subtract 1000: 104 x 500 - 1000 = 51 000. The C1, C2, and C4 bits determine the 100-ft altitude offset from the rounded 500-ft value. Because the identified segment is an even number, use the data under the even column. Comparing the inverted logic bit pattern for 6/15/1995
C1, C2, and C4 (001) to the listing, we find that it corresponds to the first entry. This declares that the hundred foot value is the nearest 800 (or 200 feet less than the rounded 500-ft level). Thus the measured bit pattern yields an altitude of 50 800 feet. * D1 and D2 are not connected on the test . For purposes of this illustration, assume an open to be a logic 1. You will notice in Table 5-15 that D1 is not used, and D2 is not active at altitudes below 60 000 feet.
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maintenance 523-0775657 5.7.2 Gillham Code, Encoding Instructions
b. Read the logic pattern for D2, D4, A1, A2 from the left column of the segment row and enter it in the spaces below.
This paragraph will describe a process to determine the code needed for a particular altitude:
6. If the absolute value of the saved difference from 3. above is less than 50, use the third pattern for C1, C2, and C4 (010). If the value of the saved difference from 3. above is 50 or more, round it to the nearest 100. This must be either 100 or 200 and either more or less than the 500-ft value.
1. Select the desired altitude. 2. Add 1000 to that number. 3. Round that number to the nearest multiple of 500. (Save the difference thus dropped; it will be needed to determine the 100-foot bit pattern in step 6. below.)
7. If the 500-ft segment number is an even number use the even column to determine the 100-ft bit pattern. (This means that the altitude rounded to the nearest 500-ft must be in the form of XX000.)
4. Divide the rounded number by 500. This becomes the 500-ft segment number for the matrix in Table 5-15 above.
8. If the 500-ft segment number is an odd number use the odd column to determine the 100-ft bit pattern. (This means that the altitude rounded to the nearest 500-ft must be in the form of XX500.
5. Locate the segment number in the table and: a. Read the logic pattern for A4, B1, B2, B4 from the top of the column and enter it in the spaces below. Bit pattern entry: Altitude:
A1
A2
A4
B1
B2
B4
C1
C2
C4
D2
D4
_______
___
___
___
___
___
___
___
___
___
___
___
Example: Determine the bit pattern for an altitude of 11 800 feet.
b. Read the D2, D4, A1, A2 bit pattern from the left column of the same row. 0001. Then enter each bit into the appropriate space below. 5. The saved value from step 3. is -200. 6. The segment number 26 is an even number, therefore the C1, C2, C4 bit pattern is read from the top entry: 001. You can, of course, also read this on the basis of the hundreth’s digit value which in this case is an 8.
1. Add 1000: 12 800. 2. Round to nearest multiple of 500: 13 000, and save difference: -200 ( less). 3. Divide 13 000 by 500: 26. 4. Locate segment number 26 on the matrix above and: a. Read the A4, B1, B2, B4 bit pattern from the top of the column: 0111. Then enter each bit into the appropriate space below. Bit pattern entry:
6/15/1995
Altitude:
A1
A2
A4
B1
B2
B4
C1
C2
C4
D2
D4
_11 800__
_0_
_1_
_0_
_1_
_1_
_1_
_0_
_0_
_1_
_0_
_0_
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5.8 ACCEPTANCE TEST, TEST ASSEMBLY INSTRUCTIONS
version. Figure 5-4 is a schematic diagram of the abbreviated test .
5.8.1
Figure 5-5 is a schematic diagram for the enhanced version of test . Table 5-16 is a list of the material required for the enhanced version. Table 5-17 is a similar listing for the abbreviated version. Table 5-18 is a listing of the manufacturers and suppliers for the various items needed to assemble the s. Equivalent parts may be obtained from other sources. Paragraph 5.8.2 and figures 5-5 through 5-8 describe the control interconnect cables. You may select one or more of these cables, depending on the type of control you plan to use. These cables are required for both test versions. However, you will notice that the cable for the CTL-92/92A can be different, depending on the test version you intend to use. The abbreviated version has no provision for Gillham code switching and a number of other functions. Thus, these connections are not required in the cable if you are using that version test .
GENERAL
This paragraph provides the instructions and material listing necessary for assembly of the ATP test s listed in table 5-1. Several test equipment suppliers offer a product item(s) equivalent to these specifications. If you wish, you should feel free to purchase such an item. Otherwise, it can be locally fabricated using the data supplied in this paragraph. If you fabricated your fixture according to instructions supplied an earlier edition of this manual, you will find modification instructions in paragraph 5.8.3 below. This edition, and all subsequent editions that introduce changes to the Acceptance Test Test will give modification instructions in paragraph 5.8.3. Figure 5-2 is the test setup diagram showing how the various items are interconnected. Figure 5-3 is a suggested layout for the enhanced
Table 5-16. Enhanced Version of Test , Parts List
ITEM
REF DES
QTY
MANUFACTURER NAME
Toggle switch, SP, on/off
S1, S5, S7, S8, S10, S11, S17S57, S59
48
Toggle switch, SPDT, on/on
S9
1
Toggle switch, DPDT, on/on
S2, S3
Momentary switch, SP, pushon
S4, S6
5/5/1993
C & K Components, Inc
COLLINS PART NUMBER PN
7107SYZWQE
266-5321-150
2
7201SYZQE
266-5321-200
2
8121SHZGE
266-5404-010
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Table 5-16. Enhanced Version of Test , Parts List (cont’d)
ITEM
REF DES
QTY
MANUFACTURER NAME
PN
Wafer, switch, 2pole, 4-psn
S13
1
Wafer switch, 5pole, 2 -psn
S58
1
44A3004202NF
Wafer switch, 4pole, 4 -psn
S12
1
44A3002204NF
Wafer switch, 6pole, 4 -psn
S16
1
44A3006204NF
Lamp holder
6
Grayhill Inc.
COLLINS PART NUMBER
Chicago Miniature Lamp, Inc.
44A3001204NF
Not available from Collins
LH73/1
included in 2622828-0X0
Lamp len, red
LDS 2-3
2
LC12YN2
262-2828-010
Lamp lens, yellow
LDS 1,4-6
4
LC12RN2
262-2828-030
Lamp, 28 V
DS1-6
6
GE Co.
385
262-2171-010
Fuse holder
XF1
1
Bussman Div.
HKP-H, or FHN-20G
Not available from Collins
Fuse, 5A SB
F1
1
Banana jack, blk
TP1,3,5
2
Banana jack, yel
TP2,4,6
3
Phono plug, 1/4"
J2,3,4,5,6,7,8,9
8
Phono jack
To mate with: J2,3,4,5,6,7,8,9 See figure 5-9
AR
BNC to TNC adapter
Needed to adapt ATC601 rf cable to antenna connectors
2
RF load (also shown on table 5-1
Needed to terminate unused rf antenna connection.
1
50-pin D-submin, conn (socket) 50-pin D-submin, conn (plug)
5/5/1993
1
See figures 56, 5-7, 5-8
AR
F02G250V5AS E.F.Johnson Co.
360-0241-000 360-0245-000
Switchcraft Inc.
M/A-COM Omni Spectra, Inc.
M641/12-1
358-0014-000
PJ-055B
Not available from Collins
3182-2320-00
Not available from Collins
3101-6100-00
ITT Cannon
DDMF-50S-A176
371-0182-000
DDM50P-C37-A176
371-0118-000
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Table 5-16. Enhanced Version of Test , Parts List (cont’d)
ITEM
REF DES
QTY
MANUFACTURER NAME
COLLINS PART NUMBER PN
TDR-94D installation kit
1
Collins General Aviation Division
628-8660-001
MMT-150 Mounting Tray
1
622-9672-003
CTL-92/92A mating connector
See figure 5-6
1
359-0305-590, or 371-6110-000
RTU-870A/T mating connector
See figure 5-7
1
359-0601-010
TTC-920G mating connectors
See figure 5-8
1 of each
Res, film, 100kΩ, ±1%, 1/4W
R1-11
11
Res, film, 825Ω, ±1%, 1/2W
R12-22
11
Grommet, 1-in, id
MS
J1: MD24266R76B24S7 J2: MS24266R16B24SB
J1: 359-4068-030 J2: 359-4118-240
RN65D1003F
705-7192-000
RN65D8250F
705-7092-000
1
Atlantic India Rubber Co.
2277
201-0012-000
021-0347-050
Chassis, 8 x 12-in , box
Or use a 19 rack mounting
1
Bud Industries, Inc.
AC 424
Switch knobs
For wafer switches
5
any with 1/4-inch shaft dia and setscrew locking
N/A
Data bus reader cables
See figure 5-9
Chassis, bottom
Optional
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AR
1
BPA 1519
Not available from Collins
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Table 5-17. Abbreviated Version of Test , Parts List
ITEM
REF DES
QTY
MANUFACTURER NAME
BNC to TNC adapter
Needed to adapt ATC601 rf cable to antenna connectors
2
RF load (also shown on table 5-1
Needed to terminate unused rf antenna connection.
1
50-pin D-submin, conn (socket) 50-pin D-submin, conn (plug)
1
See figures 56, 5-7, 5-8
M/A-COM Omni Spectra, Inc.
COLLINS PART NUMBER PN
3182-2320-00
Not available from Collins
3101-6100-00
ITT Cannon
AR
DDMF-50S-A176
371-0182-000
DDM50P-C37-A176
371-0118-000
TDR-94D installation kit
1
Collins General Aviation Division
628-8660-001
MMT-150 Mounting Tray
1
622-9672-003
CTL-92/92A mating connector
See figure 5-6
1
359-0305-590, or 371-6110-000
RTU-870A/T mating connector
See figure 5-7
1
359-0601-010
TTC-920G mating connectors
See figure 5-8
1 of each
Chassis
Note: The size of chassis for the abbreviated version of the test is optional. The primary limitation is that it must be large enough to accomodate the connectors and other parts. Use of a 50pin D-type connector can also be seen as optional. If you plan to use only one type of control, such as the CTL-92/92A, you may want to connect the cable directly to the test as a pendant cable.
Cable grommet, 1/2-in. id
For pendant cable exit if used.
5/5/1993
1
J1: MD24266R76B24S7 J2: MS24266R16B24SB
Atlantic India
2283
J1: 359-4068-030 J2: 359-4118-240
201-0002-006
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Table 5-14. Equipment and Component Manufacturers and Suppliers
SUPPLIER
ADDRESS
PRODUCT
Collins General Aviation Division
400 Collins Road Cedar Rapids IA 52498
TDR-94D Installation kit, MMT-150 Mounting Tray, CTL-92/92A mating connector, RTU-870A/T mating connector, TTC-920G mating connector
IFR Systems, Inc.
10200, West York Street Wichita, KS 67215
ATC-601 Ramp Test Set
Atlantic Instruments, Inc.
P.O. Box 021466 Melbourne, FL 32902
DataTrac 200/400/400H Databus Analyzers
JcAIR
400 Industrial Parkway, Industrial Airport, KS 66031
Test and 429E ARINC 429 TX/RX Databus Analyzer
Avionics Specialist, Inc.
3833 Premier Ave. Memphis, TN 38118
Test
M/A-COM Omni Spctra, Inc.
21 Continental Blvd Merrimac, NH 03054-9979
Rf load and BNC-to-TNC adapter
C & K Components, Inc.
15-T Riverdale Ave. Newton, lMA 02158 (617) 964-6400
Toggle switches
Grayhill Inc.
561 Hillgrove, P.O.Box 10373 LaGrange IL 60525 (708) 354-1040
Wafer switches
Chicago Miniature Lamp, Inc.
1080-T Johnson Dr. Buffalo Grove, IL 60089 (908) 459-3400
Indicator lamp holders and lens
Bussman Div., Cooper Industries
P.O. Box 14460 St. Louis, MO 63178 (314) 394-2877
Fuses and fuse holder
GE Co., Miniature Lamp Dept.
Nela Park Cleveland OH 44112 (216) 266-2121
Light bulb
E.F. Johnson Co.
Minneapolis, MN 55459-0089
Banana jacks
ITT Cannon, Corp.
1851-T E. Deer Ave. Santa Ana, CA 92705 (714) 557-4700
Connectors
Bud Industries, Inc.
P.O. Box 431, 4605 E. 355th St. Willoughby, OH 44094 (216) 946-3200
Chassis
Atlantic India Rubber Co.
317 W. Doublas St. Goshen, IN 46256
Rubber grommet
Switchcraft Inc.
5555-T N. Elston Ave. Chicago, IL 60630 (312) 792-2700
Phono plug and jack
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Acceptance Test, Test Layout Diagram Figure 5-3
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Acceptance Test, Abbreviated Test Schematic Diagram Figure 5-4
6/15/1995
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Acceptance Test, Enhanced Test Schematic Diagram Figure 5-5 (Sheet 1 of 3)
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Acceptance Test, Enhanced Test Schematic Diagram Figure 5-5 (Sheet 2)
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Acceptance Test, Enhanced Test Schematic Diagram Figure 5-5 (Sheet 3)
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Test Mating Connector, D-submin, 50-pin, plug DDM50P-C37-A176, N: 371-0118-000
CTL-92/92A Control, Mating Connector P1 MS3126 E20-41SY, N 359-0305-590, or MS 3116E20,41SY, N: 371-6110-000
Signal Name/Description
To Pin No.
From Pin No.
Wire Size or Type
28 V dc, primary power no. 1 (+)
1
G
22 AWG
28 V dc, primary power no. 2 (+)
18
t
22 AWG
Primary power, ground (-)
17
s
22 AWG
Primary power, ground (-)
50
P
22 AWG
CTL data out, 1B
8
S
26 AWG, STP
CTL data out, 1A
41
R
26 AWG, STP
CTL data in, 1B
31
U
26 AWG, STP
CTL data in, 1A
10
V
26 AWG, STP
Ident input
4
b
26 AWG
Self-test (discrete input/output)
6
E
26 AWG (this wire was not included in the original version of this cable)
The remaining connections are not required when using the Abbreviated Version of Test No. 1 transponder in stby
20
W
26 AWG (this wire was not included in the original version of this cable)
No. 2 transponder in stby
10
X
26 AWG
No. 1 transponder on/off
11
B
26 AWG
No. 2 transponder on/off
27
C
26 AWG
No. 1 sw 28 V dc out
28
k
26 AWG
No. 2 sw 28 V dc out
43
j
26 AWG
Acceptance Test, Test CTL-92/92A Control Interconnect Cable Assembly Diagram and Wire List Figure 5-6 (Sheet 1 of 2)
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maintenance 523-0775657 Test Mating Connector, D-submin, 50-pin, plug DDM50P-C37-A176, N: 371-0118-000
CTL-92/92A Control, Mating Connector P1 MS3126 E20-41SY, N 359-0305-590, or MS 3116E20,41SY, N: 371-6110-000
Signal Name/Description
To Pin No.
From Pin No.
Wire Size or Type
Alt code, A1 (input)
12
c
26 AWG
Alt code, A2 (input)
13
e
26 AWG
Alt code, A4 (input)
14
d
26 AWG
Alt code, B1 (input)
28
i
26 AWG
Alt code, B2 (input)
29
h
26 AWG
Alt code, B4 (input)
30
f
26 AWG
Alt code, C1 (input)
45
J
26 AWG
Alt code, C2 (input)
46
H
26 AWG
Alt code, C4 (input)
47
F
26 AWG
Alt code, D4 (input)
48
p
26 AWG
Alt code, common
5
g
26 AWG
Acceptance Test, Test CTL-92/92A Control Interconnect Cable Assembly Diagram and Wire List Figure 5-6 (Sheet 2)
Acceptance Test, Test RTU-870A Control Interconnect Cable Assembly Diagram and Wire List Figure 5-7 (Sheet 1 of 2)
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Test Mating Connector, D-submin, 50-pin, plug DDM50P-C37-A176, N: 371-0118-000
RTU-870A/T Radio Tuning Unit, Mating Connector P1 MS27473T20F-2S, N 359-0601-010, Strain relief: MS27506F20-2, N: 359-0637-070
Signal Name/Description
To Pin No.
From Pin No.
Wire Size or Type
28 V dc, primary power no. 1 (+)
1
1
22 AWG
28 V dc, primary power no. 2 (+)
18
7
22 AWG
Primary power, ground (-)
17
3
22 AWG
Primary power, ground (-)
50
3
22 AWG
RTU data out, 1B (ARINC 429 data from RTU to XPDR)
26
45
26 AWG, STP
RTU data out, 1A (ARINC 429 data from RTU to XPDR)
25
44
26 AWG, STP
RTU data in, 1B (ARINC 429 data input to RTU from XPDR)
31
29
26 AWG, STP
RTU data in, 1A (ARINC 429 data input to RTU from XPDR)
10
28
26 AWG, STP
Ident input
4
11
26 AWG
Acceptance Test, Test RTU-870A Control Interconnect Cable Assembly Diagram and Wire List Figure 5-7 (Sheet 2)
Acceptance Test, Test TTC-920G Control Interconnect Cable Assembly Diagram and Wire List Figure 5-8 (Sheet 1 of 2)
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Test Mating Connector, D-submin, 50-pin, plug DDM50P-C37-A176, N: 371-0118-000
TTC-920G Transponder/TCAS Control, Mating Connector1 P1: MD24266R76B24S7, N: 359-4068-030 P2: MS24266R16B24S8, N: 359-4095-700
Signal Name/Description
From Pin No.
To Pin No.
115 V ac, 400 Hz, primary power1 (high) (external source)
Source High
J1-3 J2-3*
22 AWG
115 V ac, 400 Hz, primary power (low) (external source)
Source Low
J1-4 J2-4*
22 AWG
Primary power, ground (-)
17
J1-6 J2-6*
22 AWG
Air ground (input) (strap for normal operation)
17
J1-11* J2-11*
26 AWG
Primary power, ground (-)
50
J1-8 J2-8*
22 AWG
ARINC 429, data out, 1B (TTC-920G output to XPDR)
25
J1-22
26 AWG, STP
ARINC 429, data out, 1A (TTC-920G output to XPDR)
26
J1-23
26 AWG, STP
Air ground (input)
17*
J1-11* J2-11*
26 AWG
Monitor lamp power (+28 V dc)
1*
J1-18*
26 AWG
Monitor lamp power (+28 V dc)
1*
J1-18*
26 AWG
Lighting power (+28 V dc)
18*
J2-1*
26 AWG
Standby/on
20*
J1-7
26 AWG
Fault Monitor (XPDR output)
12*
J1-20* J2-20*
26 AWG
Wire Size or Type
* These wires were not shown in the original cable wiring list.
Acceptance Test, Test TTC-920G Control Interconnect Cable Assembly Diagram and Wire List Figure 5-8 (Sheet 2)
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maintenance 523-0775657 5.8.2Miscellaneous Cables Figure 5-9 shows the addtional cables needed for the Acceptance Test. The tip jack cables shown in the upper section of sheet 1 are needed for dc power input to the DataTrac 200 or 400. If you operate from ac power or battery power only you do not need these. The DataTrac 400H and JcAIR 429E, as well as some DataTrac 200, have their own ac-todc power converter/battery recharge facility.
In the lower section of sheet 1, the BNC-tosingle phono jack cables are needed for the RX function of the DataTrac 400, and 400H. For DataTrac 400 operation you can substitute two of the lower cable for the upper and then use a separate TX port. For the DataTrac 400H you must use the upper cable because it has only one TX port and therefore you must use that port for both the control and altitude functions. Sheet 2 of this figure shows the cables needed for the DataTrac 200 and the JcAIR 429E, respectively.
Acceptance Test, Bus Reader to Test Interconnecting Cables Figure 5-9 (sheet 1 of 2)
In assembling the BNC-to-phono plug cables, be sure to connect the bus A wires between the BNC center and the proper phono plug . In assembling the phono plug-tophono plug cables, be sure to connect similar s; i.e., do not reverse the A and B
5/5/1993
lines. In assembling the phono plug-to-tip jack cables, be sure the A wire is connected to the jack identified as HI. In all cases, do not use the the phono plug common as a signal carrying .
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Acceptance Test, Bus Reader to Test Interconnect Cables Figure 5-9 (sheet 2)
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maintenance 523-0775657 5.8.1Acceptance Test Modification Record. 5.8.1.1Modification 1. At modification 1 the following changes are introduced. 1. An additional SPDT switch, S56, is added with connection to UUT pin P1-28. This function is labeled AUTO ALT. When this function is enabled (EN, ground applied to P1-28), the unit automatically switches to the non-selected altitude port for valid reporting altitude data if the altitude data at the selected source is interrupted or invalid. 2. Existing switch, S17, with connection to UUT pin P2-14 is redefined. This switch previously functioned as the ALT INPUT PORT SEL and switched the altitude input to either port A or port B. In -003 units, altitude data is required at both ports simultaneously therefore this switching function is changed (see 3. below). The new function, SOURCE SELECT, CTL/SEL, functions with the existing altitude source select pins P2-41 and P2-42 as follows: SS* AS0 AS1 1 1 1 1
0 0 1 1
Altitude Type Selected
0 1 0 1
ARINC 429 on ARINC ports A and B CSDB on CSDB ports A and B ARINC 575 on ARINC ports A and B ARINC 572 (Gillham) on the Gillham parallel port 0 0 0 Port A altitude on the selected control bus (either ARINC 429 or CSDB) and port B altitude type ARINC 429 on ARINC port B. 0 0 1 Port A altitude on the selected control bus (either ARINC 429 or CSBB) and port B altitude type CSDB on CSDB port B. 0 1 0 Port A altitude on the selected control bus (either ARINC 429 or CSDB) and port B altitude type ARINC 575 on ARINC port B. 0 1 1 Port A altitude on the selected control bus (either ARINC 429 or CSDB) and port B altitude type Gillham on the Gillham parallel port. * CTL = active low (ground on P2-48) and SEL = open.
S16 also controls the select discretes P2-41 (AS0) and P2-42 (AS1) (see 2. above). Data supplied on the ALTERNATE DIGITAL ALTITUDE SOURCE is switched to port B; either ARINC or CSDB. 4. Existing altitude input jack J4 is relabeled as PRIMARY DIGITAL ALTITUDE SOURCE. Switch S16 controls the connection of this input to the appropriate UUT port A (either ARINC or CSDB). 5. Switch S57, REPORTING ALT SEL, PA/PB, is added. This switch controls the discrete P2-48 which selects the altitude port used for altitude reporting (Modes C and S). When P2-48 is grounded, port B data is used for altitude reporting. When open port A data is used. 6. TCAS IN and TCAS OUT input jacks, J6 and J7, are added to allow monitoring of the TCAS data. 7. DATALINK IN and DATALINK OUT jacks, J8 and J9, are added to allow airborne datalink bus monitoring. s should see this addition as optional at this time because the airborne datalink function has not been industry defined and therefore is not fully implemented. It is presented here primarily so that builders of this test can allow for the eventual addition of this function if and when it is required. Part of this change also includes the addition of switch S58. This switch supplies a ground to P2-60 to enable/select the airborne datalink function. 8. That portion of S12 which supplies the ground to pins P2-56, -57, and -58 has been changed slightly. The common was connected to ground. It should instead be connected to P2-52 which is available at switch S16. 9. The common for the Gillham code switches should be connected to P1-12. 10. The XFEED IN and OUT lamps, DS3 and DS4, and switch S3 position labeling was reversed on the 6 January 1992 issue of the test schematic diagram. No wiring changes are needed. 11. Check the layout, figure 5-3 carefully. You will find a few minor label changes.
3. ALTERNATE DIGITAL ALTITUDE SOURCE input jack J5 is added and existing switch S16 is expanded to allow two altitude sources to be connected simultaneously. S16 allows selection of the appropriate input port depending on the type of data being supplied. 5/5/1993
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maintenance 523-0775657 5.9 FLIGHTLINE TEST, TEST ASSEMBLY INSTRUCTIONS 5.9.1
Introduction
This paragraph provides the instructions and material listing necessary to assemble the Flightline Test shown in figure 5-10. A number of test equipment suppliers may offer a product item equivalent these specifications. If so, you should feel free to purchase such an item. Otherwise, it can be locally fabricated using the data in this paragraph. 5.9.2 Flightline Test Assembly and Use This test allows access to all input and output signals to and from the applicable control; CTL-92 ATC Control, CTL-92A ATC Control, CTL-92T ATC and TCAS Control, TTC-920G Transponder-TCAS Control, RTU870A Radio Tuning Unit, and RTU-870T Radio Tuning Unit (TCAS). Using this test on the flightline, with a dvm and a bus reader, can help to isolate a problem to either the control or the transponder unit and thus increase the probability of correctly removing the faulty unit in a multi-unit system. It is intended that a ramp tester be used for ATC ground station simulation. The test consists of a with several test points for individual signal testing and phono jacks and switching for data bus monitoring and data word injection. When using the , you will select the proper interconnecting cables and test overlay, depending on the control present in the installation. The respective overlay reflects the test point and other i/o signal identification peculiar to that control. The numbers or letters under each test point are the connector pin numbers of the ATC control involved. Figure 5-10 is the test setup diagram showing the test connected between the
5/5/1993
airplane harness control head mating connector and the control head. In the case of the CTL-92T, you should be aware that the ATC control data originates in the CTL92/92A as CSDB data. This is supplied to the CTL-92T where it is converted to ARINC 429 data, TCAS data is added, and the composite data is then supplied to the transponder and subsequently to the TCAS. Therefore, the communication between the CTL-92T and the CTL-92/92A is in CSDB, while the communication between the CTL92T and the transponder/TCAS is in ARINC 429. Figure 5-11 is the suggested layout of the components; banana jacks, switches, indicator lamps, etc. If you decide to fabricate your own and wish to retain the overall versatility, be aware that the overlays are intended to be selectable. The design allows the overlay to rest on top of the and therefore must fit the component placement rather closely. Figure 13 through 19 is a series of diagrams showing the various overlays; each applicable to a given control type. With suitable size adjustment, figure 5-11 can be used as a template. The overlays must (then) also be size adjusted. Four D-type connectors are located on the edge of the ; two on each side. These connectors mate with the cable connectors. The 25-pin connectors carry only the digital data lines using shielded wiring while the 50pin connectors carry all other input/output functions. You may choose to use only a single connector to carry all i/o. Figure 5-12 is the schematic diagram of the test . Use this diagram as the guide for wiring the . Table 5-19 is a list of the parts needed to assemble the test . See paragraph 5.8 for a listing of suppliers. Figures 5-20 through 5-25 show the cables and wiring. Select the cables needed depending on which of the various controls; CTL-92, CTL-92A, CTL-92T Controls, RTU870A, or RTU-870T Radio Tuning Units, TTC-920G Transponder/TCAS Control, or Gables 429 control.
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Flightline Test Setup Diagram Figure 5-10
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Flightline Test , Layout Diagram Figure 5-11
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Flightline Test , Schematic Diagram Figure 5-12 (Sheet 1 of 5)
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Flightline Test , Schematic Diagram Figure 5-12 (Sheet 2)
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Flightline Test , Schematic Diagram Figure 5-12 (Sheet 3)
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Flightline Test , Schematic Diagram Figure 5-12 (Sheet 4)
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Flightline Test , Schematic Diagram Figure 5-12 (Sheet 5)
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maintenance 523-0775657 Table 5-19. Flightline Test Parts List
ITEM
REF DES
QTY
MANUFACTURER NAME
COLLINS PART NUMBER PN
Lamp Holder
DS1,2,5,6,
2
Chicago Miniature Lamp, Inc.
LH73/1
included in 262-28280X0 N
Lamp lens, red
LDS5,6
2
GE Co.
LC12RN2
262-2828-030
Lamp lens, yellow
LDS1,2
2
LC12YN2
Lamp, 28 V
DS1-2
2
385
Lamp, assy, 115 V
DS3-4
2
LeeCraft, SnapLite
Toggle switch DPDT, on/on
S3-S10
8
C&K Components, Inc.
Momentary switch, SP, Pushon
S1,S2
2
Stereo Phono jack, 1/4-inch
J3-J10
8
Banana jack, 1/4"
TP1-45
50-pin D-submin, conn (socket) 25-pin D-submin, conn (socket)
262-2852-050
7101SYZQE
266-5321-150
8121SHZGE
266-5404-010
Switchcraft Inc.
PJ-055B
Not available from Collins
45
E.F. Johnson Co.
blk: 108-0903-001 yel: 108-0907-001 (other colors are optional)
blk: 360-0241-000 yel: 358-0245-000
J1A, J2A
2
ITT Cannon
DDMF-50S-A176
371-0182-000
J1B, J2B
2
DDMF-25S-A176
371-0166-000
AC 424
021-0347-050
BPA-1519
Not available from Collins
3182-2320-00
Not available from Collins
Chassis
1
Chassis, bottom
1
BNC to TNC adapter
262-2171-010
Needed to adapt ATC601 rf cable to antenna cable connector for directionconnection method only.
1
Bud Industries, Inc.
M/A-COM Omni Spectra, Inc.
Control head cables
Locally fabricated
See figures 5-19 through 5-24
Bus reader cables
Locally fabricated
See figure 5-9
Tip jack test leads
5/5/1993
As required for use with dvm
Not available from Collins
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Flightline Test , Overlay for CTL-92/92A Figure 5-13
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Flightline Test , Overlay for CTL-92T Figure 5-14
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Flightline Test , Overlay for RTU-870A/T Testing Figure 5-15
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Flightline Test , Overlay for TTC-920G Testing Figure 5-16
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Cable B: Connector information: J1: KPT2E20-41PYDV, N: 371-8625-440 P1A: DD 50P C37, N 371-0118-000; Hood: N 371-0187-000 P1B: M243083-3, N 371-0170-000 Hood: N 371-0815-000
Signal name / description
From J1
Cable A: Connector information: P1: MS3126E20-41SY, N 359-0305-590, or MS3116E20,41SY, N 371-6110-000 P2A: DD 50P C37, N 371-0118-000; Hood: N 371-0187-000 P2B: M243083-3, N 371-0170-000 Hood: N 371-0815-000 To P1-A
To P1-B
From P2-A
From P2-B
To P1
Wire size/type (both cables)
Data bus 1A (from XPDR)
V
1
1
V
Shielded, twisted pair
Data bus 1B (from XPDR)
U
14
14
U
Shielded, twisted pair
Shield for U/V
T
25
25
T
Shield
Data bus 2A (from XPDR)
a
2
2
a
Shielded, twisted pair
Data bus 2B (from XPDR)
Z
15
15
Z
Shielded, twisted pair
Shield for a/Z
Y
12
12
Y
Shield
Data bus 1A (to XPDR)
S
3
3
S
Shielded, twisted pair
Data bus 1B (to XPDR)
R
16
16
R
Shielded, twisted pair
Shield for S/R
P
24
24
P
Shield
Data bus 2A (to XPDR)
N
4
4
N
Shielded, twisted pair
Data bus 2B (to XPDR)
M
17
17
M
Shielded, twisted pair
Shield for N/M
L
11
11
L
Shield
28 V dc pwr no. 1 (+)
t
1
1
t
22 AWG
28 V dc pwr no. 2 (+)
G
3
3
G
22 AWG
Dc pwr gnd
s
50
50
s
22 AWG
Dc pwr gnd
s
17
17
s
22 AWG
Chassis gnd
D
33
33
D
22 AWG
5 V lighting, hi
A
7
7
A
26 AWG
28 V lighting, hi
r
40
40
r
26 AWG
Lighting common
q
39
39
q
26 AWG
CTL-92/92A Control, Flightline Test Cables, Assembly Diagram and Wire List Figure 5-19 (sheet 1 of 2)
5/5/1993
5-188
maintenance 523-0775657
CTL-92/92A Cable B (cont’d)
CTL-92/92A Cable A (cont’d)
Signal name / description
From J1
To P1-A
Dimming bus
n
6
Self-test discrete, input/output
E
Ident discrete input
To P1-B
From P2-A
From P2-B
To P1
Wire size/type
6
n
26 AWG
38
38
E
26 AWG
b
5
5
b
26 AWG
Remote tuning select, discrete input
K
21
21
K
26 AWG
No. 1 XPDR in stby, discrete output
W
42
42
W
26 AWG
No. 2 XPDR in stby, discrete output
X
10
10
X
26 AWG
28 V dc, sw output, no. 1
k
28
28
k
26 AWG
28 V dc, sw output, no. 2
j
43
43
j
26 AWG
Dual select (CTL -002 only)
m
8
8
m
26 AWG
No. 1 XPDR off, discrete output
B
11
11
B
26 AWG
No. 2 XPDR off, discrete output
C
27
27
C
26 AWG
Alt code A1
c
29
29
c
26 AWG
Alt code A2
e
30
30
e
26 AWG
Alt code A4
d
45
45
d
26 AWG
Alt code B1
i
46
46
i
26 AWG
Alt code B2
h
14
14
h
26 AWG
Alt code B4
f
15
15
f
26 AWG
Alt code C1
J
31
31
H
26 AWG
Alt code C2
H
32
32
H
26 AWG
Alt code C4
F
47
47
F
26 AWG
Alt code D4
p
4
4
p
26 AWG
Alt code common
g
37
37
g
26 AWG
CTL-92/92A Control, Flightline Test Cables, Assembly Diagram and Wire List Figure 5-19 (sheet 2)
5/5/1993
5-189
maintenance 523-0775657
Cable B: Connector information: J1: 27508E20B2PA, N 859-0004-010 P1A: DD 50P C37, N 371-0118-000; Hood: N 371-0187-000 P1B: M243083-3, N 371-0170-000 Hood: N 371-0815-000
Signal name / description
Cable A: Connector information: P1: KJ6F20BSA, N: 350-0601-020 Strain relief: MS27506F20-2, N 359-0637-070 P2A: DD 50P C37, N 371-0118-000; Hood: N 371-0187-000 P2B: M243083-3, N 371-0170-000 Hood: N 371-0815-000
From J1
To P1-A
To P1-B
From P2-A
From P2-B
To P1
Wire size/type (both cables)
CSDB data in, 1A (from CTL)
23
1
1
23
Shielded twisted pair
CSDB data in, 1B (from CTL)
22
14
14
22
Shielded twisted pair
25
25
Shield for 23/22
Shield for 23/22
ARINC 429 in, 1A (from ARINC CTL)
15
2
2
15
Shielded twisted pair
ARINC 429 in, 1B (from ARINC CTL)
14
15
15
14
Shielded twisted pair
12
12
Shield for 15/14
Shield for 15/14
CSDB data out, 1A (to CTL)
16
3
3
16
Shielded twisted pair
CSDB data out, 1B (to CTL)
17
16
16
17
Shielded twisted pair
24
24
Shield for 16/17
Shield for 16/17
ARINC 429 out, 1A (to ARINC CTL)
8
4
4
8
Shielded twisted pair
ARINC 429 out, 1B (to ARINC CTL)
9
17
17
9
Shielded twisted pair
11
11
Shield for 8/9
Shield for 8/9
ARINC 429 in, 1A (from XPDR)
11
5
5
11
Shielded twisted pair
ARINC 429 in, 1B (from XPDR)
10
18
18
10
Shielded twisted pair
23
23
Shield for 11/10
Shield for 11/10
ARINC 429 in, 2A (from XPDR)
13
6
6
13
Shielded twisted pair
ARINC 429 in, 2B (from XPDR)
12
19
19
12
Shielded twisted pair
10
10
Shield for 13/12
Shield for 13/12
CTL-92T Control, Flightline Test Cables, Assembly Diagram and Wire List Figure 5-20 (sheet 1 of 3)
5/5/1993
5-190
maintenance 523-0775657
CTL-92T Cable B (cont’d) Signal name / description
From J1
CTL-92T Cable A (cont’d) To P1-A
To P1-B
From P2-A
From P2-B
To P1
Wire size/type
ARINC 429 out, 1A (to XPDR)
5
7
7
5
Shielded twisted pair
ARINC 429 out, 1B (to XPDR)
4
20
20
4
Shielded twisted pair
22
22
Shield for 5/4
Shield for 5/4
ARINC 429 out, 2A (to XPDR)
6
8
8
13
Shielded twisted pair
ARINC 429 out, 2B (to XPDR)
7
21
21
12
Shielded twisted pair
9
9
Shield for 6/7
Shield for 6/7
28 V dc pwr input no. 1 (+)
1
1
1
1
22 AWG
28 V dc pwr input no. 1 (+)
2
2
2
2
22 AWG
28 V dc pwr input no. 2 (+)
3
19
19
3
22 AWG
28 V dc pwr input no. 2 (+)
28
3
3
28
22 AWG
Pwr gnd
59
50
50
59
22 AWG
Pwr gnd
60
20
20
60
22 AWG
Pwr gnd
32
17
17
32
22 AWG
Self-test input
46
38
38
46
26 AWG
Ident input
21
5
5
21
26 AWG
28 V lighting input, hi
48
40
40
48
26 AWG
5 V lighting input, hi
50
7
7
50
26 AWG
Lighting common
62
39
39
62
26 AWG
Strap no. 1
53
8
8
53
26 AWG
Strap no. 2
49
21
21
49
26 AWG
Strap no. 3
52
9
9
52
26 AWG
Strap no. 4
51
22
22
51
26 AWG
Strap no. 5
47
23
23
47
26 AWG
Strap no. 6
24
24
24
24
26 AWG
Strap common
27
41
41
27
26 AWG
ATC no. 1 select, input
19
42
42
19
26 AWG
ATC no. 2 select, input
18
10
10
18
26 AWG
28 V switched output
25
11
11
25
26 AWG
CTL-92T Control, Flightline Test Cables, Assembly Diagram and Wire List Figure 5-20 (sheet 2)
5/5/1993
5-191
maintenance 523-0775657
CTL-92T Cable B (cont’d) Signal name / description
CTL-92T Cable A (cont’d)
From J1
To P1-A
Reply lamp output (+)
33
28
Reply lamp output (-)
41
Altitude reporting input
To P1-B
From P2-A
From P2-B
To P1
Wire size/type
28
33
26 AWG
43
43
41
26 AWG
20
44
44
20
26 AWG
ATC code A1
44
29
29
44
26 AWG
ATC code A2
26
30
30
26
26 AWG
ATC code A4
45
45
45
45
26 AWG
ATC code B1
56
46
46
56
26 AWG
ATC code B2
55
14
14
55
26 AWG
ATC code B4
57
15
15
57
26 AWG
ATC code C1
39
31
31
39
26 AWG
ATC code C2
42
32
32
42
26 AWG
ATC code C4
54
47
47
54
26 AWG
ATC code D1
61
48
48
61
26 AWG
ATC code D2
37
49
49
37
26 AWG
ATC code D4
63
4
4
63
26 AWG
ATC code common
64
37
37
64
26 AWG
CTL-92T Control, Flightline Test Cables, Assembly Diagram and Wire List Figure 5-20 (sheet 3)
5/5/1993
5-192
maintenance 523-0775657
Cable B: Connector information: J1: MS27508E20F-2P, N: 359-0667-280 P1A: DD 50P C37, N 371-0118-000; Hood: N 371-0187-000 P1B: M243083-3, N 371-0170-000 Hood: N 371-0815-000
Signal name / description
From J1
Cable A: Connector information: P1: MS27493T20f-2S, N 359-0601-020 Strain relief: MS27506F20-2, N 359-0637-070 P2A: DD 50P C37, N 371-0118-000; Hood: N 371-0187-000 P2B: M243083-3, N 371-0170-000 Hood: N 371-0815-000 To P1-A
To P1-B
From P2-A
From P2-B
To P1
Wire size/type (both cables)
ARINC 429, Data Input, A, A
28
1
1
28
Shielded twisted pair
ARINC 429, Data Input, A, B
29
14
14
29
Shielded twisted pair
Shield
30
25
25
30
Shield
ARINC 429, Data Input, B, A
31
2
2
31
Shielded twisted pair
ARINC 429, Data Input, B, B
32
15
15
32
Shielded twisted pair
Shield
33
12
12
33
Shield
ARINC 429, Data Input, C, A
34
5
5
34
Shielded twisted pair
ARINC 429, Data Input, C, B
35
18
18
5
Shielded twisted pair
Shield
36
23
23
36
Shield
ARINC 429, Data Output, A, A
44
4
4
44
Shielded twisted pair
ARINC 429, Data Output, A, B
45
17
17
45
Shielded twisted pair
Shield
46
11
11
46
Shield
ARINC 429, Data Output, B, A
47
7
7
47
Shielded twisted pair
ARINC 429, Data Output, B, B
48
20
20
48
Shielded twisted pair
Shield
49
22
22
49
Shield
ARINC 429, Data Output, C, A
50
8
8
50
Shielded twisted pair
ARINC 429, Data Output, C, B
51
21
21
51
Shielded twisted pair
Shield
52
9
9
52
Shield
28 V dc pwr input, No. 1 (+)
1
1
1
1
22 AWG
28 V dc pwr input, No. 2 (+)
7
3
3
7
22 AWG
RTU-870A/T Radio Tuning Unit, Flightline Test Cables, Assembly Diagram and Wire List Figure 5-21 (sheet 1 of 3)
5/5/1993
5-193
maintenance 523-0775657
RTU-870A/T Cable B (cont’d) Signal name / description
RTU-870A/T Cable A (cont’d)
From J1
To P1-A
3
50
50
17
17
23
23
(common - connect to P1-A 23)
13
13
22 AWG (connect to J1-A 23)
(common - connect to P1-A 23)
37
37
22 AWG (connect to J1-A 23)
Power ground Ground (connect to P1-A 50) Strap common
53
To P1-B
From P2-A
From P2-B
To P1 3
Wire size/type
22 AWG 22 AWG
53
22 AWG
115 V ac lighting, hi
5
36
36
5
26 AWG
Lighting common
4
16
16
4
26 AWG
Dimming input (+28 V dc)
8
6
6
8
26 AWG
Dim common
10
39
39
10
26 AWG
Remote ident input
11
5
5
11
26 AWG
Cross-side RTU disable
63
8
8
63
26 AWG
Reversionary data display enable
39
21
21
39
26 AWG
MB sense enable
61
9
9
61
26 AWG
ATC 1 select
13
22
22
13
26 AWG
RTU side 2 select
64
23
23
64
26 AWG
Remote tune enable
12
24
24
12
26 AWG
RTU on/off
9
25
25
9
26 AWG
L Eng data no. 1, A
37
42
42
37
Shielded twisted pair
L Eng data no. 1, B
38
10
10
38
Shielded twisted pair
Shield for 37/38
40
2
2
40
Shield for 37/38
R Eng data no. 2, A
41
11
11
41
Shielded twisted pair
R Eng data no. 2, B
42
27
27
42
Shielded twisted pair
Shield for 41/42
43
19
19
43
Shield for 41/42
RTU test mode enable
60
28
28
60
26 AWG
RTU-870A/T Radio Tuning Unit, Flightline Test Cables, Assembly Diagram and Wire List Figure 5-21 (sheet 2)
5/5/1993
5-194
maintenance 523-0775657
RTU-870A/T Cable B (cont’d) Signal name / description
RTU-870A/T Cable A (cont’d)
From J1
To P1-A
Nav radio test inhibit
58
43
MLS no. 1 select
16
MLS no. 2 select
To P1-B
From P2-A
From P2-B
To P1
Wire size/type
43
58
26 AWG
44
44
16
26 AWG
62
12
12
62
26 AWG
DME no. 2 deselect
59
29
29
59
26 AWG
ADF no. 2 deselect
57
30
30
57
26 AWG
UHF no. 1 select
17
45
45
17
26 AWG
UHF no. 2 select
18
46
46
18
26 AWG
TACAN no. 1 select
19
14
14
37
26 AWG
TACAN no. 2 select
20
15
15
20
26 AWG
TCAS on board select
21
31
31
21
26 AWG
ADF TC-X select
23
32
32
23
26 AWG
Inv TACAN inhibit select
24
47
47
24
26 AWG
Comm extended freq select
54
48
48
54
26 AWG
Nav extended freq select
55
49
49
55
26 AWG
ADF extended freq select
56
4
4
56
26 AWG
RTU-870A/T Radio Tuning Unit, Flightline Test Cables, Assembly Diagram and Wire List Figure 5-21 (sheet 3)
5/5/1993
5-195
maintenance 523-0775657
Cable B: Connector information: J1: MIL-C-26500, N 359-4118-240 J2: MIL-C-26500, N 359-4118-250 P1A: DD 50P C37, N 371-0118-000; Hood: N 371-0187-000 P1B: M243083-3, N 371-0170-000 Hood: N 371-0815-000
Cable A: Connector information: P1: MD24266R76B24S7, N 359-4068-030 P2: MS24266R16B24S8, N 359-4095-700 Strain relief: MS27506F20-2, N 359-0637-070 P2A: DD 50P C37, N 371-0118-000; Hood: N 371-0187-000 P2B: M243083-3, N 371-0170-000 Hood: N 371-0815-000
Signal name / description
From J1/J2
ARINC 429 to XPDR no. 1, 2A
J1-22
ARINC 429 to XPDR no. 1, 2B
J1-23
To P1-A
Shield for J1-22/23
To P1-B
From P2-A
From P2-B
To P1/P2
Wire size/type (both cables)
7
7
P1-22
Shielded twisted pair
20
20
P1-23
Shielded twisted pair
22
22
Shield for P1-22/23
ARINC 429 to XPDR no. 2, 2A
J2-22
8
8
P2-22
Shielded twisted pair
ARINC 429 to XPDR no. 2, 2B
J2-23
21
21
P2-22
Shielded twisted pair
9
9
Shield for J2-22/23
Shield for P2-22/23
115 V ac pwr no. 1, Hi
J1-3
34
34
P1-3
22 AWG
115 V ac pwr no. 1, Lo
J1-4
18
18
P1-4
22 AWG
115 V ac pwr no. 2, Hi
J2-3
36
36
P2-3
22 AWG
115 V ac pwr no. 2, Lo
J2-4
16
16
P2-4
22 AWG
Self-test input
J1-9
38
38
P1-9
26 AWG
Monitor lamp test input
J1-21
5
5
P1-21
26 AWG
28 V lighting, Hi
J2-1
40
40
P2-1
26 AWG
28 V lighting, Lo
J2-2
39
39
P2-2
26 AWG
5 V lighting, Hi
J1-1
7
7
P2-1
26 AWG
5 V lighting, Lo
J1-2
6
6
P1-2
26 AWG
Antenna select, no. 1
J1-5
8
8
P1-5
26 AWG
Antenna transfer common
J2-10
21
21
P2-10
26 AWG
Antenna select, no. 2
J2-5
9
9
P2-5
26 AWG
TTC-920G TCAS/Transponder Control, Flightline Test Cables, Assembly Diagram and Wire List Figure 5-22 (sheet 1 of 2)
5/5/1993
5-196
maintenance 523-0775657
TTC-920G Cable B (cont’d)
TTC-920G Cable A (cont’d)
Signal name / description
From J1/J2
To P1-A
Air/gnd no. 1, input
J1-24
22
Air/gnd no. 1, output
J1-15
Air/gnd no. 2, input
To P1-B
From P2-A
From P2-B
To P1/P2
Wire size/type
22
P1-24
26 AWG
23
23
P1-15
26 AWG
J2-24
24
24
P2-24
26 AWG
Air/gnd no. 2, output
J2-15
25
25
P2-15
26 AWG
Monitor lamp pwr, input 12/28 V
J1-18
26
26
P1-18
26 AWG
Signal common, no. 1
J1-6
41
41
P1-6
26 AWG
Signal common, no. 2
J2-6
13
13
P2-6
26 AWG
XPDR fail warn, no. 1
J1-12
42
42
P1-12
26 AWG
XPDR fail warn, no. 2
J2-12
11
11
P2-12
26 AWG
XPDR fail warn output
J1-10
10
10
P2-10
26 AWG
XPDR in stby, no. 1
J1-7
27
27
P1-7
26 AWG
XPDR in stby, no. 2
J2-7
28
28
P2-7
26 AWG
Alternate AD select, no. 1
J1-16
43
43
P1-16
26 AWG
Alternate AD select, no. 2
J2-16
44
44
P2-16
26 AWG
Chassis gnd, no. 1
J1-8
4
4
P1-8
26 AWG
Chassis gnd, no. 2
J2-8
37
37
P2-8
26 AWG
Air/gnd no. 1, output
J1-11
29
29
P1-11
26 AWG
Air/gnd no. 2, output
J2-11
30
30
P2-11
26 AWG
XPDR fail, discrete no. 1
J1-20
45
45
P1-20
26 AWG
XPDR fail, discrete no. 2
J2-20
46
46
P2-20
26 AWG
TTC-920G TCAS/Transponder Control, Flightline Test Cables, Assembly Diagram and Wire List Figure 5-22 (sheet 2)
5/5/1993
5-197
Collins General Aviation Division
June 15, 1995
TO:
HOLDERS OF THE TDR-94/94D ATC/MODE S TRANSPONDER SYSTEM INSTRUCTION BOOK (523-0775652)
7TH EDITION HIGHLIGHTS The attached pages complete replace the existing instruction book. bars in the margin of the page.
All changes are identified by black
This new material incorporates changes and new material previously published via Addendums and various material found necessary during the review effort. Principle among these changes are the Acceptance Test Procedures in tables 5-11, 5-12, and 5-13.
PUBLICATIONS DEPARTMENT
1/2
523-0775652-00711A 7th Edition, 15 June 1995
Collins TDR-94/94D ATC/Mode S Transponder System
instruction book This publication includes: General Information Operation Theory of Operation Maintenance
Collins General Aviation Division Rockwell International Corporation Cedar Rapids, Iowa 52498 Printed in the United States of America ©Rockwell International 1995
523-0775653 523-0775655 523-0775656 523-0775657
WARNING INFORMATION SUBJECT TO EXPORT CONTROL LAWS This document may contain information subject to the International Traffic in Arms Regulation (ITAR) or the Export istration Regulation (EAR) of 1979 which may not be exported, released, or disclosed to foreign nationals inside or outside of the United States without first obtaining an export license. A violation of the ITAR or EAR may be subject to a penalty of up to 10 years imprisonment and a fine of up to $1,000,000 under 22 U.S.C.2778 of the Arms Export Control Act of 1976 or section 2410 of the Export istration Act of 1979. Include this notice with any reproduced portion of this document.
Caution The material in this publication is subject to change. Before attempting any maintenance operation on the equipment covered in this publication, that you have complete and up-to-date publications by referring to the applicable Publications and Service Bulletin Indexes.
SOFTWARE COPYRIGHT NOTICE Copyright, 1989, 1990, 1991, 1992, 1993, 1994, 1995 Rockwell International Corporation All software resident in this equipment is protected by copyright.
We welcome your comments concerning this publication. Although every effort has been made to keep it free of errors, some may occur. When reporting a specific problem, please describe it briefly and include the publication part number, the paragraph or figure number, and the page number. Send your comments to:
Publications Department MS 106-124 Collins General Aviation Division Rockwell International Corporation Cedar Rapids, Iowa 52498 or by Internet E-Mail to: [email protected]
SPECIFIC ADVISORIES FOR THE <EQ TYPE> Warning Rockwell International does not take the responsibility for certification of the TDR-94/94D when used with equipment other than those covered by the Rockwell International Collins Avionics safety analysis. Warning Electronic control systems, such as autopilots, engine controls, fuel controls, temperature sensors, etc, used for aircraft control can be susceptible to transmissions from communications transceivers, DME’s, transponders, etc, that can interfere with aircraft operations. If such a situation occurs, discontinue transmission or select a different frequency. If necessary, turn off the radio. Warning Service personnel are to obey standard safety precautions, such as wearing safety glasses, to prevent personal injury while installing or doing maintenance on this unit. Warning Use care when using sealants, solvents, and other chemical compounds. Do not expose to excessive heat or open flame. Use adequate ventilation. Avoid prolonged breathing of vapors and avoid prolonged with skin. Observe all cautions and warnings given by the manufacturer. Warning Remove all power to the unit before disassembling it. Disassembling the unit with power connected is dangerous to life and may cause voltage transients that can damage the unit. Warning This unit may have components that contain materials (such as beryllium oxide, acids, lithium, radioactive material, mercury, etc) that can be hazardous to your health. If the component enclosure is broken, handle the component in accordance with OSHA requirements 29CFR 1910.1000 or superseding documents to prevent personal with or inhalation of hazardous materials. Since it is virtually impossible to determine which components do or do not contain such hazardous materials, do not open or disassemble components for any reason. Warning This unit exhibits a high degree of functional reliability. Nevertheless, s must know that it is not practical to monitor for all conceivable system failures and, however unlikely, it is possible that erroneous operation could occur without a fault indication. The pilot has the responsibility to find such an occurrence by means of cross-checks with redundant or correlated data available in the cockpit. Caution Turn off power before disconnecting any unit from wiring. Disconnecting the unit without turning power off may cause voltage transients that can damage the unit.
i
Caution This unit contains electrostatic discharge sensitive (ESDS) components and ESDS assemblies that can be damaged by static voltages. Although most ESDS components contain internal protection circuits, good procedures dictate careful handling of all ESDS components and ESDS assemblies. Obey the precautions given below when moving, touching, or repairing all ESDS components and units containing ESDS components. a. Deenergize or remove all power, signal sources, and loads used with the unit. b. Place the unit on a work surface that can conduct electricity (is grounded). c. Ground the repair operator through a conductive wrist strap or other device using a 470-kΩ or 1-MΩ series resistor to prevent operator injury. d. Ground any tools (and soldering equipment) that will the unit. with the operator’s hand is a sufficient ground for hand tools that are electrically isolated. e. All ESDS replacement components are shipped in conductive foam or tubes and must be stored in their shipping containers until installed. f. ESDS devices and assemblies, that are removed from a unit, must immediately be put on the conductive work surface or in conductive containers. g. Place repaired or disconnected circuit cards in aluminum foil or in plastic bags that have a layer of, or are made with, conductive material. h. Do not touch ESDS devices/assemblies or remove them from their containers until they are needed. Failure to handle ESDS devices as described above can permanently damage them. This damage can cause immediate or premature device failure.
ii
ROCKWELL COLLINS INSTRUCTION BOOK TDR-94/94D, PART NO 622-9352/622-9210 RECORD OF TEMPORARY REVISIONS Note: Insert this page following Specific Advisories page ii. TEMPORARY REV NO
PAGE NUMBER
DATE ISSUED
1
1-11
Aug 15/00 Rockwell Collins
2
1-2
Nov 22/02 Rockwell Collins
BY
DATE REMOVED
BY
NOTICE INFORMATION SUBJECT TO EXPORT CONTROL LAWS This document contains technical data that may be restricted for export under the International Traffic in Arms Regulations (ITAR) or the Export istration Regulations (EAR). Violations of these export laws may be subject to fines and penalties under the Arms Export Control Act (22 U.S. C. 2778).
Temporary Revision 2 523-0775652-02711A
RTR-1/RTR-2 Nov 25/02
523-0775653-006118 6th Edition, 15 June 1995
TDR-94/94D ATC/Mode S Transponder System General Information
table of contents
Paragraph
Page
1.1 INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1-1
1.2 PURPOSE OF EQUIPMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1-1
1.3 EQUIPMENT REQUIRED BUT NOT SUPPLIED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1-1
1.4 RELATED PUBLICATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1-2
1.5 STORAGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1-12
1.6 RELATED SERVICE BULLETINS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1-12
NOTICE: This section replaces fifth edition dated 5 May 1993.
List of Effective Pages Page
*The asterisk indicates pages changed, added, or deleted by the current change.
Issue
*Title . . . . . . . . . . . . . . *List of Effective pages 1-1 thru 1-5 . . . . . . . . . 1-6 thru 1-9 . . . . . . . . . 1-10 thru 1-13 . . . . . . . 1-14 Blank . . . . . . . . . .
. . . . . .
. . . . . .
. . . . . .
. . . . . .
. . . . . .
15 Jun 15 Jun . 5 May 15 Jun . 5 May . 5 May
95 95 93 95 93 93
Record of Revisions INSERTION DATE/BY
RETAIN THIS RECORD IN THE FRONT OF THE MANUAL. ON RECEIPT OF REVISIONS, INSERT REVISED PAGES IN THE MANUAL, AND ENTER DATE INSERTED AND INITIALS.
REV / ED NO
REVISION DATE
SB NUMBER INCLUDED
0/1
4 Apr 89
None
0/2
4 Apr 90
None
0/3
29 Apr 91
None
0/4
6 Jan 92
None
0/5
5 May 93
See Table 1-6
0/6
15 Jun 95
See Table 1-6
REV / ED NO
REVISION DATE
INSERTION DATE/BY
SB NUMBER INCLUDED
I
section general information 1.1 INTRODUCTION This publication provides all the specifications, principles of operation, and information necessary to test and troubleshoot the TDR-94 and TDR-94D Mode S Transponder System in the airplane. The information includes a bench testing procedure to the performance capability before installation of a new or newly repaired transponder. Refer to table 1-1 for a list of equipment covered in this manual and table 1-2 for the TDR-94/94D
Comm/Nav/Pulse System Installation Manual for a listing of the various CTL-92/92A, RTU-870A/T and other controls available for use with the TDR94/94D. The TDR-94D Transponder is a Diversity version; i.e., it is capable of transmitting and receiving on either of two antennas. The TDR-94 is a non-diversity model. The TDR-94D is fully compatible with TCAS II system installations requiring antenna diversity. Either of two antenna types can be used with the TDR-94/94D as shown in table 1-1. 1.2 PURPOSE OF EQUIPMENT
TDR-94/94D Mode S Transponder Figure 1-1
specifications. Table 1-3 is a listing of environmental requirements for DO-160B. Table 1-4 is a listing of publications related to the TDR-94/94D. Table 1-6 is a listing of Service Bulletins and Service Information Letters that have been released up to the date of this manual edition. Figure 1-1 is an overall view of the TDR-94/94D.
The TDR-94/94D is an integral part of the Air Traffic Control Radar Beacon System (ATCRBS). The TDR-94/94D operates in mode A by responding to normal beacon radar interrogations. This mode provides identification of transponderequipped airplanes on the ground controller’s plan position indication (PPI). If the installation is equipped with a compatible altitude encoder, it can operate in mode C and provide altitude data long with the normal reply. In the mode S scheme, each airplane is assigned a unique identification code which allows automatic and unique interrogation and display of a specific airplane. The airplane identification is assigned at installation and is based on the identification (tail) number. The unique identifier is required in TCAS operation. In addition, the TDR-94/94D can receive and send data link messages that are required for ATC automation. The added data link capability allows the transponder to perform additional air traffic control and airplane separation assurance (ASA) functions.
1.1.1 General Description The TDR-94/94D Transponder is a solid-state, airborne, air traffic control (ATC) transponder. The TDR-94 or TDR-94D Transponder is normally mounted in a MMT-150 Modular Mounting Tray and controlled by an ATC control like the the CTL-92/92A Control. Refer to the Pro Line II
5/5/1993
1.3 EQUIPMENT REQUIRED BUT NOT SUPPLIED Table 1-4 lists the equipment required for proper operation of the TDR-94/94D but is not supplied with the unit. Equivalent equipment may be substituted.
1-1
general information 523-0775653 1.4 RELATED PUBLICATIONS Table 1-5 lists publications related to TDR-94/94D operation. Table 1-1. Equipment Covered. COLLINS EQUIPMENT
DESCRIPTION
PART NUMBER
TDR-94
Mode A, C, and S ATC Transponder
622-9352-003
ANT-42
L-band antenna for transponder or DME. Uses ac signal coupling to radiating. element.
622-6591-001
MMT-150
Mounting Tray for TDR-94/94D
622-9672-003
FOR INSTALLATIONS USING CSDB TUNING CTL-92
Pro Line II, ATC Control (uses CSDB data format). Refer to Pro Line II Comm/NAV/Pulse Installation Manual for available options.
622-6523-XXX
CTL-92T
Transponder and TCAS Control, used in conjunction with CTL-92/92A to add TCAS control functions. Refer to TCAS-94 Traffic Alert and Collision Avoidance System Installation Manual for available options.
622-9614-XXX
FOR INSTALLATIONS USING ARINC 429 TUNING RTU-870A
Remote Tuning Unit, gives centralized control and display of the frequency/ATC code and modes of the Collins -4XX series of General Aviation equipment. Refer to Pro Line II Comm/NAV/Pulse Installation Manual for available options.
622-9346-XXX
RTU-870T
Remote Tuning Unit, same as RTU-870A except includes TCAS control capability. Refer to Pro Line II Comm/NAV/Pulse Installation Manual for available options.
622-9856-XXX
ALTERNATE MODELS AVAILABLE TDR-94D
Same as TDR-94 except with diversity capability
622-9210-003
TDR-94
Same as TDR-94 -003 except without TCAS compatibility features. Can be used in installations without TCAS and where diversity is not required.
622-9352-002
TDR-94D
Same as TDR-94D -003 except without TCAS compatibility features. Can be used in installations without TCAS and where diversity is needed.
622-9210-002
TDR-94/94D
This model is no longer ed. All existing -001 units should be upgraded to at least -002.
622-9352-001 622-9210-001
CTL-92A
Same as CTL-92 except with enhanced display capability Refer to Pro Line II Comm/NAV/Pulse Installation Manual for available options.
622-8740-XXX
237Z-1
Similar to ANT-42 except uses dc coupling to radiating element.
522-2632-001
TTC-920G
Transponder/TCAS Control. Dedicated control for TCAS and Mode S Transponder. Refer to TCAS-94 Traffic Alert and Collision Avoidance System Installation Manual for available options.
822-0078-XXX
5/5/1993
1-2
ROCKWELL COLLINS INSTRUCTION BOOK TDR-94/94D, PART NO 622-9352/622-9210 TDR-94/94D ATC/Mode S Transponder System INSTRUCTION BOOK (523-0775652, 7TH EDITION, DATED JUN 15/95)
TEMPORARY REVISION NO. 02 Insert facing page 1-2. Subject: Elementary Surveillance (Flight ID) Installation Guidelines Flight ID capability is one of the functions required by Elementary (Basic) Surveillance. Elementary Surveillance is a subset of Enhanced Surveillance. The -007 version of the TDR-95/94D s both Elementary and Enhanced Surveillance requirements. Details of the requirements for Enhanced Surveillance will be covered in a future Service Information Letter. Existing versions of the TDR-94/94D can be updated to Elementary/Enhanced Surveillance functionality as shown below. UNIT
PRIOR PART NUMBER
SERVIE BULLETINS REQUIRED
NEW PART NUMBER*
TDR-94
622-9352-003
13, 501
622-9352-007
TDR-94D
622-9210-003
13, 501
622-9352-007
*The new TDR-94/94D part numbers (-007 status) are covered in associated TDR-94/94D component maintenance manual (523-0778502). Refer to the Pro Line II Installation Manual (523-0772719) for TDR94/94D installation requirements, and to TDR-94/94D SIL 1-02 for additional system operation and
aircraft installation information. If converting a TDR-94/94D -003 status, additional wiring changes will be required. Refer to SIL 1-96 on the TDR-94/94D for additional information on the applicable changes.
Temporary Revision 2 523-0775652-02711A
Page 1 of 1 Nov 25/02
general information 523-0775653
Table 1-2. Equipment Specifications. CHARACTERISTIC
SPECIFICATION
Certification TSO FAA
TSO-C112, class 2A
RTCA
D0-181, D0-144
Software
DO-178A, level 2
EUROCAE
ED-12A
Deutsche Bundespost FTZ
A44652010
ICAO
Annex 10
Environmental FAA
DO-160B, refer to table 1-3 for additional information
EUROCAE
ED-12A
Height
84.6 mm (3.33 in)
Width
124.5 mm (4.90 in)
Length
317.5 mm (12.50 in)
Weight
3.6 kg (8.5 lb)
Physical Size
Mounting
MMT-150; 1/2 ATR, short, dwarf ( Refer to Pro Line II Comm/NAV/Pulse Installation Manual for additional information.)
Mating Connector
Thinline II, qty 2, 60-pin (Kits: N: 628-8661-001/002 or 628-8660-001/002) ( Refer to Pro Line II Comm/NAV/Pulse Installation Manual for additional information.)
Time between overhaul
On condition of failure or as required by Federal Regulations (see below)
Regulatory requirement for flightline test
FAR 91.413 ATC TRANSPONDER TESTS AND INSPECTIONS. "(a) No person may use an ATC transponder that is specified in Part 125 §91.24 (a), §121.345, §127.123 (b), or §135.143 (c) of this chapter unless, within the preceding 24 calendar months, that ATC transponder has been tested and inspected and found to comply with Appendix F of Part 43 of this chapter; and following any installation or maintenance on an ATC transponder where data correspondence error could be introduced, the integrated system has been tested, inspected, and found to comply with paragraph Appendix E of Part 43 of this chapter."
Power requirements
27.5 ±2.5 V dc at 28 watts nominal, 30 watts maximum
Transmitter Frequency
1090 MHz, ±1 MHz
Power output
250 watts min, 625 watts maximum
Load impedance
50Ω nominal
VSWR
1.5:1 service max., 3:1 survival
5/5/1993
1-3
general information 523-0775653
Table 1-2. Equipment Specifications. (cont’d) CHARACTERISTIC
SPECIFICATION
Receiver Frequency
1030 MHz nominal
IF
60 MHz
Sensitivity
-77 dBm ±3 dBm
Reply modes
ATCRBS mode A ATCRBS mode C ATCRBS mode A/Mode S All Call ATCRBS mode C/Mode S All Call ATCRBS mode A only All Call ATCRBS mode C only All Call Mode S, short (56-bit) Mode S, long (112-bit)
Reply rate ATCRBS
500 15-pulse replies/sec 1200 15-pulse replies in 100 ms
Mode S
34 short and 16 long replies in 1 sec 12 short and 6 long replies in 100 ms 4 short and 4 long replies in 25 ms 2 short and 2 long in 1.6 ms
ATCRBS side lobe suppression Max of 10%l replies and sls initiated
P1 pulse is MTL + 3 dB to -21 dBm and P2 equal to or greater than P1
Max of 10% replies and sls may be initiated
P1 pulse is MTL to MTL + 3 dB and P2 equal to or greater than P1
Minimum of 90% replies and no sls
P1 pulse is MTL +3 dB to -21 dBm, and P1 pulse is min 9 dB greater than P2 No P2 pulse occurs at 2.0 ±0.7 µs after leading edge of P1, or P2 pulse duration is less than 0.3 µs
Mode S side lobe suppression
Max of 10%
Electrical Primary power (P1-58)
27.5, ±2.5, V dc (+), 28 watts nominal, 100 watts peak
Primary power common (P1-60)
27.5 V dc (-)
5/5/1993
1-4
general information 523-0775653
Table 1-2. Equipment Specifications. (cont’d) CHARACTERISTIC
SPECIFICATION
Data bus: CSDB Structure
8-bits/byte, 6-bytes/block
Rate
12.5 Baud, 10-block/sec nominal, 18 max
Data blocks
(all labels are in hexadecimal form) A5: sync; input A0: altitude data; input 1E: ATC code/altitude; input or output 1F: ATC data; output F3: diagnostic data; output
ARINC 429 Structure
8-bits/byte, 4-bytes/word
Rate
5-words/sec min
Data labels
(all labels are in octal form) *013: TDR and TCAS control; input/output *015: Altitude select limits, input/output *016: Mode S control; input/output *031: ATC Transponder Control, input/output *200: Gillham altitude encoder data; input/output *203: TDR altitude data to TCAS; input/output 204: TDR corrected barometric altitude to TCAS; output 272: TCAS coordination data, part 1; output 273: TCAS data for downlink message formats 16, 20, 21; input 274: TCAS coordination data, part 2; output 274: TCAS data for downlink message formats 0 and 16; input 275: TCAS control, part 1; output 275: TCAS acknowledge; input 276: TCAS control, part 2; output 277: TCAS acknowledge; input 277: Diagnostic data request; input 350: Maintenance data; output 371: Equipment ident; output * These labels are normally echoed, and/or ed through to the TCAS, as received except for the SSM which may be different depending on the state of the transponder.
Tuning inputs
Monitored only if Burst Mode (P2-59) is not selected; i.e., P2-59 is open
P2-31 P2-32
CSDB, A CSDB, B
P2-17 P2-18
ARINC 429, A (tune input port A) ARINC 429, B (tune input port A)
P2-13 P2-14
ARINC 429, A (tune input port B) ARINC 429, B (tune input port B)
P2-21 P2-22
ARINC 429, A (tune input port C) ARINC 429, B (tune input port C)
Altitude inputs P2-33 P2-34
CSDB, A (altitude input port A) CSDB, B (altitude input port A)
P2-35 P3-36
CSDB, A (altitude input port B) CSDB, B (altitude input port B)
5/5/1993
1-5
general information 523-0775653
Table 1-2. Equipment Specifications. (cont’d) CHARACTERISTIC
SPECIFICATION
Input/Output Altitude inputs (cont’d) P2-25 P2-26
ARINC 429/575, A (altitude input port A) ARINC 429/575, B (altitude input port A)
P2-29 P2-30
ARINC 429/575, A (altitude input port B) ARINC 429/575, B (altitude input port B)
Data outputs P2-23 P2-24
CSDB, A (Bus 1) CSDB, B (Bus 1)
P2-27 P2-28
CSDB, A (Bus 2) CSDB, B (Bus 2)
P2-15 P2-16
ARINC 429, A (Port A) ARINC 429, B (Port A)
P2-19 P2-20
ARINC 429, A (Port B) ARINC 429, B (Port B)
Peripheral data P2-1 P2-2
ARINC 429, A (Comm A/B input) ARINC 429, B (Comm A/B input)
P2-3 P2-4
ARINC 429, A (Comm A/B output) ARINC 429, B (Comm A/B output)
P2-5 P2-6
ARINC 429, A (Comm C/D input) ARINC 429, B (Comm C/D input)
P2-7 P2-8
ARINC 429, A (Comm C/D output) ARINC 429, B (Comm C/D output)
P2-9 P2-10
ARINC 429, A (TCAS coord data input) ARINC 429, B (TCAS coord data input)
P2-11 P2-12
ARINC 429, A (TCAS coord data output) ARINC 429, B (TCAS coord data output)
Discrete inputs P1-1 P1-2 P1-3 P1-4 P1-5 P1-6 P1-7 P1-8 P1-9 P1-10 P1-11 P1-12
B4, ARINC 572 altitude input B2, ARINC 572 altitude input B1, ARINC 572 altitude input A4, ARINC 572 altitude input A2, ARINC 572 altitude input A1, ARINC 572 altitude input D4, ARINC 572 altitude input D2, ARINC 572 altitude input C4, ARINC 572 altitude input C2, ARINC 572 altitude input C1, ARINC 572 altitude input Common, ARINC 572 altitude input
Mode S address discretes P1-32 P1-33 P1-34
6/15/1995
Common B1 B2
1-6
general information 523-0775653
Table 1-2. Equipment Specifications. (cont’d) CHARACTERISTIC
SPECIFICATION
Input/Output (continued) Mode S address discretes (cont’d) P1-35 P1-36 P1-37 P1-38 P1-39 P1-40 P1-41 P1-42 P1-43 P1-44 P1-45 P1-46 P1-47 P1-48 P1-49 P1-50 P1-51 P1-52 P1-53 P1-54 P1-55 P1-56
B3 B4 B5 B6 B7 B8 B9 B10 B11 B12 B13 B14 B15 B16 B17 B18 B19 B20 B21 B22 B23 B24
Single discrete straps P2-51
Antenna, dual/single select (gnd = single)
P2-56
CSDB/ARINC 429 control select (gnd = CSDB)
P2-60
ADLP installed (gnd = ADLP included in installation)
P1-13
TCAS installed (gnd = TCAS included in installation) Note: There is no provision for TCAS control in CSDB. Therefore, the TDR-94D will not report TCAS capability in its replies to interrogations when CSDB is enabled (P2-56 grounded) even if TCAS is selected (P1-13 grounded) and dual antenna enabled (P2-51 open).
Discrete I/O P2-55
Standby discrete (gnd = in standby)
P1-28 (-003)
Automatic altitude select (gnd = auto alt select enabled)
P1-14
Control Altitude Select (See Combination Discretes below) (gnd = port A altitude data supplied on control port, port B same as open), (open = ports A and B altitude selectable via altitude type select discretes, P2-41/42)
P2-53
Air/ground discrete (gnd = WOW)
P2-48
Reporting altitude port select (gnd = port B)
P2-59
Burst tune enable (gnd = burst) Note: In Burst Tune mode the control port strapping (P2-57/58) is ignored. Burst tune data is accepted on ports A, B, and C as 30 ARINC-429 words spaced over an interval of 1.5 seconds with 500 msec dwell time on each port and the dwell time suspended when data is present. Continuous data is always accepted if available.
6/15/1995
1-7
general information 523-0775653
Table 1-2. Equipment Specifications. (cont’d) CHARACTERISTIC
SPECIFICATION
Discrete I/O (continued) P1-15 P1-30
Cross-side input (connected to opposite TDR P1-30, gnd input = command to standby) Cross-side output (connected to opposite TDR P1-15, gnd output = active mode) (These connections are used in dual burst-tune TDR installations to ensure that only one transponder is operating at a time)
P1-31
Fault monitor output (28 V dc = valid, 200 mA max)
P1-29
Suppression input/output (connected to all other L-band equipment)
P1-16 (-003)
SPI (remote ident) input
Maintenance specific: P2-38
Self-test inhibit (gnd = inhibited) (for maintenance purposes only)
P2-54
Self-test discrete (gnd = self-test on) (for bench test/maintenance purposes only)
Combination discrete straps P2-41, P2-42, and P1-14
P1-14
P2-41
P2-42
Altitude Type Selected
open open open open gnd
gnd open gnd open gnd
gnd gnd open open gnd
gnd
open
gnd
gnd
gnd
open
gnd
open
open
ARINC 429 on ARINC ports A and B CSDB on CSDB ports A and B ARINC 575 on ARINC ports A and B ARINC 572 (Gillham) on the Gillham parallel port Port A altitude on the selected control bus (either ARINC 429 or CSDB) and port B altitude type ARINC 429 on ARINC port B. Port A altitude on the selected control bus (either ARINC 429 or CSBB) and port B altitude type CSDB on CSDB port B. Port A altitude on the selected control bus (either ARINC 429 or CSDB) and port B altitude type ARINC 575 on ARINC port B. Port A altitude on the selected control bus (either ARINC 429 or CSDB) and port B altitude type Gillham on the Gillham parallel port.
P2-43, P2-44, P2-45
Max airspeed programming (gnd to P2-49) P2-43 P2-44 P2-45 Definition open open open none selected gnd open open 0 to 75 knots open gnd open 75 to 150 knots gnd gnd open 150 to 300 knots open open gnd 300 to 600 knots gnd open gnd 600 to 1200 knots open gnd gnd more than 1200 knots gnd gnd gnd (not defined)
P2-46, P2-47
SDI input (gnd to P2-50) P2-46 P2-47 Definition open open (not used) open gnd side 1 gnd open side 2 gnd gnd (not used)
6/15/1995
1-8
general information 523-0775653
Table 1-2. Equipment Specifications. (cont’d) CHARACTERISTIC
SPECIFICATION
Discrete I/O (continued) Combination discrete straps (continued) P2-57, P2-58
Control port select (gnd to P2-52) P2-57 P2-58 Definition gnd open Port A selected open open Port B selected open gnd Port C selected gnd gnd (not defined) Table 1-3. DO-160B Environmental Qualifications.
CHARACTERISTIC
DO-160B PARA NO
QUALIFICATION LEVEL
Temperature and Altitude
4.0
Category F2:
Low Operating Temp High Operating Temp Low Storage Temp High Storage Temp
4.5.1 4.5.3 4.5.1 4.5.2
-55 °C (-67 °F) +70 °C (+158 °F) -55 °C (-67 °F) +85 °C (+185 °F)
Altitude
4.6.1
Category A2: Certified for installation in a controlled temperature locations where pressures are no lower than an altitudes equivalent to 4600 m (15 000 ft) msl. Category E1: Certified for installation in a nonpressurized and noncontrolled temperature locations in an airplane that is operated at altitudes up to 21 300 m (70 000 ft) msl.
Temperature Variation
5.0
Category B:
Certified for installation in a controlled or noncontrolled temperature location in the airplane.
Humidity
6.0
Category B:
Certified for a Severe Humidity Environment - Level I.
Shock Operational Crash Safety
7.0 7.2 7.3
Tested at 6 g peak Tested at 15 g (11 ms duration)
Vibration
8.0
Category J: Category Y:
Certified for fuselage mounting in a fixed wing turbojet or turbofan airplane. Certified for fuselage mounting in a piston or turbojet rotary wing airplane.
Explosion Proofness
9.0
Category E1: Certified for installation in a location where an explosive atmosphere may occur as a result of leakage or spillage.
Waterproofness
10.0
Category X:
No test required. Certified for installation in locations not subject to falling water (including condensation), rain water, or sprayed water.
Fluids Susceptibility
11.0
Category X:
No test required. Certified for installation in locations not exposed to fluid contamination from fuel, hydraulic fluids, oil, solvents, etc.
Sand and Dust
12.0
Category X:
No test required. Certified for installation in locations not subject to blowing sand and dust.
Fungus Resistance
13.0
Category X:
Fungus resistance test not performed.
Salt Spray
14.0
Category X:
Salt spray test not performed.
6/15/1995
1-9
general information 523-0775653
Table 1-3. DO-160B Environmental Qualifications.
CHARACTERISTIC
DO-160B PARA NO
QUALIFICATION LEVEL
Magnetic Effect
15.0
Category Z:
Unit causes a 1° deflection of an uncompensated com at a distance less than 0.3 m (1.0 ft).
Power Input
16.0
Category Z:
Certified for use on airplane electrical systems not applicable to any other category. For example, a dc system from a variable range generator where a small capacity or no battery is floating on the dc bus.
Voltage Spike
17.0
Category A:
Certified for installation in systems where a high degree of voltage spike protection is required.
Audio Frequency Susceptibility
18.0
Category Z:
Certified for use on aircraft electrical systems not applicable to any other category. For example, a dc system from a variable range generator where a small capacity or no battery is floating on the dc bus.
Induced Signal Susceptibility
19.0
Category Z:
Certified for operation in systems where interference-free operation is required.
RF Susceptibility
20.0
Category Z:
Certified for operation in systems where interference-free operation is required.
Emission of RF Energy
21.0
Category Z:
Certified for operation in systems where interference-free operation is required.
Lightning
22.0
Category L:
Long and short wave (750 volts) Damped sinusoidal wave (600 volts)
5/5/1993
1-10
BUSINESS AND REGIONAL SYSTEMS INSTRUCTION BOOK TDR-94/94D, PART NO 622-9352/622-9210 TDR-94/94D ATC/Mode S Transponder System INSTRUCTION BOOK (523-0775652, 7TH EDITION, DATED JUN 15/95)
TEMPORARY REVISION NO. 01 Insert facing page 1-11 Subject:Add BA609 Connector Kit and Mount A new version of the MMT-150 Modular Mounting Tray and TDR-94/94D Connector Kit has been created for BA609 aircraft installations. MMT-150 622-9672-004 and Connector Kit 628-8660-003 are added to Table 1-4. P/O Table 1-4. Equipment Required But Not Supplied. EQUIPMENT
TYPE OR DESCRIPTION
QTY
**
MMT-150 Mount
½ ATR, short, dwarf mount (N: 622-9672-004) for BA609 installations
1
**
60-pin, Thinline II connector, qty 2 each, (Kit N 628-8661-001/002 or 628-8660-001/002 or 628-8660-003 for BA609 installations) (Refer to Pro Line II Installation Manual, for additional details.)
1-kit
Connector Kit
**
Refer to TDR-94/94D installation section in Pro Line II Comm/Nav/Pulse System Installation Manual for additional mount and mating connector information.
Temporary Revision 1 523-0775652-01711A
Page 1 of 1 Aug 15/00
general information 523-0775653
Table 1-4. Equipment Required But Not Supplied. EQUIPMENT
TYPE OR DESCRIPTION
QTY
**MMT-150 Mount
1/2 ATR, short, dwarf mount (N: 622-9672-003)
1
**Connector Kit
60-pin, Thinline II connector, qty 2 each, (Kit N: 628-8661-001/002, or 6288660-001/002) (Refer to Pro Line II Installation Manual, for additional details)
1-kit
**Crimp s
For wires with: up to 0.050 in. insulation dia (372-2514-110), or 0.050 to 0.080 in. insul dia (372-2514-180)
* 105 used, 15 spares
L-band antenna
Collins ANT-42, N: 622-6591-001, or Collins 237Z-1, N: 522-2632-001; qty 1 for TDR-94, qty 2 for TDR-94D
AR
ATC Control
CSDB data format: Collins CTL-92/92A ATC Control, with Collins CTL-92T if TCAS is used, ARINC 429 data format: Collins RTU-870A Radio Tuning Unit, or Collins RTU-870T TCAS/ATC Radio Tuning Unit, or Collins TTC-920G TCAS/ATC Control, or Gables model 816
Altitude data source
Collins ADS-85 Air Data System (Refer to ADS-85 Air Data System Installation Manual)
Air Data Link Message Processor
TBA (not available at time of this publication)
Traffic Alert and Collision Avoidance System
Collins TCAS-94 System (Refer to TCAS-94 Installation Manual)
*Quantity required for typical installation **Refer to installation section for additional mount and mating connector information Table 1-5. Related Publications. PUBLICATION
ATA NUMBER
COLLINS PART NUMBER
Collins Avionics Standard Shop Practices, Instruction Manual
none
523-0768039
TDR-94/94D ATC/Mode S Transponder, Component Maintenance Manual
34-50-91
523-0775997
Collins Pro Line II Comm/Nav/Pulse System, Installation Manual
none
523-0772719
TCAS-94 Traffic Alert and Collision Avoidance System, Installation Manual
none
523-0775833
CTL-92T TCAS Control
34-40-84
523-0776595
RTU-870A/870T Radio Tuning Unit, Component Maintenance Manual
23-80-80
523-0774068
CTL-X2/X2A Controls, Instruction Book (Repair Manual)
23-80-10
523-0772495
Collins TDR-94 Mode S Transponder, Pilot’s Guide
none
523-0776370
5/5/1993
1-11
general information 523-0775653
1.5 STORAGE The TDR-94/94D should be stored in its original packing materials and shipping container. If the unit is to be stored for a long period of time, put the unit in an airtight plastic bag with sufficient desiccant to absorb moisture. At no time should the ambient temperature of the storage area fall below -55 °C (-67 °F) or rise above +85 °C (+185 °F). The relative humidity should never exceed 95 percent. If the unit is stored for an extended period of time, retest the unit prior to returning it to service to ensure that possible component degradation has not affected performance.
5/5/1993
1.6 RELATED RELATED SERVICE SERVICE BULLETINS AND SERVICE SERVICE INFORMATION INFORMATION LETTERS Table 1-6 is a listing of the Service Bulletins and Service Informtion Letters issued and applicable to the TDR-94/94D Mode S Transponder as of the date of this manual. You will notice that many of these have direct application to unit performance in the airplane. It may be helpful to review this listing whenever there is a failure report to determine whether a particular modification may have application to the reported symptom. This implies, of course, that you must determine the modification status of the unit in question.
1-12
general information 523-0775653
Table 1-6. Related Service Bulletins. SERVICE BULLETIN NUMBER, TITLE AND DESCRIPTION
PUBLICATION DATE
SB 1: Convert TDR-94’s and TDR-94D’s to -002 status (Converts -001 to -002 status). The modifications in this service bulletin upgrade the TCAS interface performance. This service bulletin adds altitude input via the control bus and improves the burst control interface.
Rev 1: May 23, 1991
SB 2: Improve Burst Tuning Interface, Self-Test Performance, and EMI Compatibility. Installation of this service bulletin protects transmitter power output transistor during self-test, corrects burst tuning cross-side standby operation, and improves EMI compatibility.
Jan 18, 1991
SB 3: Prevent Corruption of Mode A/C Replies. ATC may report loss of reply or incorrect reply code. Several minutes to several hours may elapse before this malfunction occurs. Once precipitated, the condition will persist until primary power is cycled.
Jan 18, 1991
SB 4: Prevent Occasional Loss of Transponder Function. Reception of certain combinations of transponder interrogations can cause the TDR-94 and TDR-94D not to reply to subsequent interrogations. Once this occurs power must be cycled to restart transponder operation.
Mar 5, 1991
SB 5: A7U301 or A7U304 Replacement. In some units, when A7U301 or A7U304 are replaced, one or both channels may fail the DPSK related test. This service bulletin should be installed when replacing IC A7U301 or A7U304.
Rev 1: Jun 10, 1993
SB 6: Convert TDR-94’s and TDR-94D’s to -003 Status (Converts -002 status to -003 status). Installation of this service bulletin updates the TDR-94/94D to include changes to the Mode S transponder requirements by RTCA. Installation configuration options are expanded and enhancements to its diagnostic and maintenance performance is implemented.
Rev 2: Sep 22, 1992
SB 7: A6U105 or A6U120 PROM Replacement. If A6U105, on the -002/102 Video Processor Card or A6U120 on the -003/103 Video Processor Card, requires replacement, the new PROM may exhibit different parameters which affect the performance of the transponder. If this service is not installed when changing A6U105 or A6U120, the transponder may not reply to interrogations. This service bulletin compensates for the parameter changes.
Rev 1: Sep 17, 1992
SB 8: Replacement of A7U500 or A7U502. The current IC U500 (circuit card assembly A7, N 687-0727-002/102) or U502 (circuit card assembly A7, N 687-0727-001/101) has exhibited some cold start problems. The new U500 or U502 performs better over temperature but requires some changes to accommodate the new IC. This service bulletin should be installed only if U500 or U502 requires replacement.
Rev 1: Sep 22, 1992
SB 9: Prevent Possible Intermittent Operation. A rare combination of events can cause the TDR94/94D to be intermittent. If a specific memory location is corrupted and the unit tries to report a diagnostic, intermittent operation can occur.
Rev 3: Apr 22, 1993
SB 10: Improve Operation of Remote Ident Input. In aircraft which utilize the remote ident input (P1-16), the active transponder may squawk ident if power is removed from the inactive transponder.
Oct 2, 1992
SB 11: Improve Power-On Initialization. To ensure that the TDR-94/94D powers up in less than two seconds and initializes the air/ground Mode S status to the correct reporting position.
Feb 5, 1993
SB 12: Add Diode Isolation to Strap Inputs. In aircraft which parallel the CSDB and ARINC 429 Control select and Burst Enable inputs to other systems, removal of transponder power may cause unrequested activation of the function in another system.
Aug 2, 1993
SB A: Same as SB 3.
Dec 11, 1990
SB B: Improve Start-Up Compatibility With The Gulfstream G-IV Gables 6969 TCAS Control Adapter. Installations utilizing the Gables 6969 TCAS control adapter may power up in the standby mode regardless of the mode the system was powered down in.
Sep 29, 1992
SIL A-90: Connector Plate Inspection (N 629-8657-001/002. Some connector plates used with the TDR-94/94D mounting rack may exhibit one or more discrepancies. This connector plate is available individually and is included as part of connector kits, N 628-8660-001/002 and N 628-8661001/002. All connector plates "REV A" through "REV C" that do not have "A-90" marked on them should be inspected and adjusted if found discrepant. Connector plates "REV D" or later are inspected during manufacture.
Oct 22, 1990
5/5/1993
1-13
523-0775655-103118 3rd Edition, 29 April 1991 1st Revision, 15 June 1995
TDR-94/94D ATC/Mode S Transponder System Operation
Table of Contents
Paragraph
Page
3.1 3.1.1 3.1.2
TDR-94/94D TRANSPONDER OPERATING INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-1 Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-1 CTL-92/92A Control, Controls and Indicators . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-1
3.2 3.2.1 3.2.2 3.2.3 3.2.4 3.2.5 3.2.6 3.2.6.1
OPERATING INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . Operating Instructions for Installations Using a CTL-92/92A Control Equipment Turn On . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Code Selection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Code Storage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Normal Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Self-Test . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CTL-92/92A ATC Control, Diagnostic Codes . . . . . . . . . . . . . . . . . . .
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NOTICE: This section replaces third edition dated 29 April 1991. Only the Title Page has changed in this revision.
. . . . . . . .
. . . . . . . .
. . . . . . . .
. . . . . . . .
. . . . . . . .
3-1 3-1 3-1 3-1 3-2 3-2 3-3 3-5
List of Effective Pages Page
*The asterisk indicates pages changed, added, or deleted by the current change.
Issue
*Title . . . . . . . . . . . . . . *List of Effective pages 3-1 thru 3-4 . . . . . . . . . 3-5 . . . . . . . . . . . . . . . 3-6 Blank . . . . . . . . . .
. . . . .
. . . . .
. . . . .
. . . . .
. . . . .
15 Jun 15 Jun . 4 Apr 29 Apr . 4 Apr
95 95 90 91 89
Record of Revisions INSERTION DATE / BY
RETAIN THIS RECORD IN THE FRONT OF THE MANUAL. ON RECEIPT OF REVISIONS, INSERT REVISED PAGES IN THE MANUAL, AND ENTER DATE INSERTED AND INITIALS.
REV / ED NO
REVISION DATE
SB NUMBER INCLUDED
0/1
4 Apr 89
None
0/2
4 Apr 90
None
0/3
29 Apr 91
None
1/3
15 Jun 95
See Table 1-6
REV / ED NO
REVISION DATE
INSERTION DATE/BY
SB NUMBER INCLUDED
,,
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523-0775656-102118 2nd Edition, 4 April 1990 1st Revision, 15 June 1995
TDR-94/94D ATC/Mode S Transponder System Theory of Operation
Table of Contents
Paragraph
Page
4.1 TDR-94/94D Transponder System theory of Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-1 4.1.1 General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-1 4.1.2 Physical Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-1 4.2
Purpose of Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-2
4.3 4.3.1 4.3.2 4.3.3 4.3.4 4.3.5
Background . . . . . . . . . . . . . . . Introduction . . . . . . . . . . . . . . . . Radar Systems . . . . . . . . . . . . . . ATCRBS Interrogation Modes . . SSR Radiation Patterns and SLS ATC Transponder 4096 Replies .
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4.4 4.4.1 4.4.2 4.4.3 4.4.4
ATCRBS and Mode S . . . . . . . . . . . . . Introduction . . . . . . . . . . . . . . . . . . . . . . Mode S Interrogation Modes . . . . . . . . . Mode S SSR Radiation Pattern and SLS Mode S Transponder Replies . . . . . . . . .
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4.5 4.5.1 4.5.2 4.5.3 4.5.4
TDR-94/94D Theory of Operation . . . . . . . . . Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . Installation Strapping Options . . . . . . . . . . . . . . Typical Configurations . . . . . . . . . . . . . . . . . . . . TDR-94/94D Block Diagram Theory of Operation
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NOTICE: This section replaces second edition dated 4 April 1990. Only the Title Page has changed in this revision.
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*Title . . . . . . . . . . . . . List of Effective pages 4-1 . . . . . . . . . . . . . . . 4-2 thru 4-4 . . . . . . . . 4-5 . . . . . . . . . . . . . . 4-6 thru 4-7 . . . . . . . . 4-9 . . . . . . . . . . . . . . . 4-10 thur 4-18 . . . . . . 4-19 thru 4-24 . . . . . .
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15 Jun 4 Apr 4 Apr 4 Apr 4 Apr 4 Apr 4 Apr 4 Apr 4 Apr
95 90 90 90 89 90 89 90 90
Record of Revisions INSERTION DATE/BY
RETAIN THIS RECORD IN THE FRONT OF THE MANUAL. ON RECEIPT OF REVISIONS, INSERT REVISED PAGES IN THE MANUAL, AND ENTER DATE INSERTED AND INITIALS.
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4 Apr 89
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See Table 1-6
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section
IV
theory of operation 4.1 TDR-94/94D TRANSPONDER SYSTEM THEORY OF OPERATION 4.1.1 General The TDR-94/94D Mode S Transponder is a solid-state, airborne, air traffic control (ATC) transponder that responds to ATCRBS (air traffic control radar beacon system) mode A and mode C interrogations and mode select (mode S) interrogations. The mode S transponder differs from earlier ATCRBS transponders in operation in that it is capable of discrete addressing. That is, in mode S each transponder acquires a unique identity and responds when interrogated according to that identity. In addition, mode S includes the capability of sending and receiving
data link messages. Diversity-equipped mode S transponders are also capable of receiving and transmitting on two antennas. These are usually mounted one on top and the other on the bottom of the fuselage. This provides for more reliable air-to-air surveillance and communications. 4.1.2 Physical Description Figure 4-1 is a view of the TDR-94/94D Mode S Transponder. The unit dimensions are 5 inches wide, by 3 ¾ inches high, by 14 inches long. It weighs about 7.5 pounds. All electrical connectors are at the rear of the unit. These include two 60-pin Thinline connectors and either one (for TDR-94) or two (for TDR-94D) antenna connectors. The unit is normally mounted in a MMT-150 Modular Mounting Tray.
CTL-92/92A Control, Controls and Indicators Figure 3-1
Revised 4 April 1990
4-1
operation 523-0775656 4.2 PURPOSE OF EQUIPMENT The TDR-94/94D transponder is the airborne transponder for the ATCRBS. The TDR-94/94D provides mode A, mode C, and special identification replies to ATCRBS interrogators for tracking, identification, and altitude reporting. In addition, the TDR94/94D is capable of receiving and sending mode S messages that will be required by TCAS II and TCAS III (Traffic Alert and Collision Avoidance System), It also includes the data link capability necessary for aircraft separation assurance (ASA) function.
consisting mainly of a large rotating radar antenna that can be seen at or near most air terminals. This system uses conventional radar to locate all aircraft within its range in of range and azimuth. It transmits a burst of energy and then measures the time to an echo.* The direction in which the antenna is pointing at the time the echo is detected establishes the azimuth to the reflecting target. This target information is displayed on the air traffic controller’s PPI (plan position indicator) (see figure 4-3).
4.3 BACKGROUND 4.3.1 Introduction The air traffic control radar beacon system (ZTCRBS) is a surveillance system in wide use that locates and identifies aircraft within an airspace. However, because of increasing air traffic, this system is being expanded to include additional facilities for airborne collision avoidance. To gain a good understanding of mode S transponder operation, it is necessary to understand the operation of the existing air traffic control (ATC) system. If this is your first with the ATCRBS and related equipment, this paragraph will give you an overall description of the present ATCRBS and then expand that understanding into the new mode S operation. 4.3.2 Radar Systems Refer to figure 4-2. The ATCRBS consists of a primary surveillance radar (PSR) and a secondary surveillance radar (SSR). The PSR can be visualized as
4.3.3 ATCRBS Interrogation Modes
The SSR system interrogates the aircraft transponder for aircraft identity and altitude. The interrogations are in the form of either of two modes: mode A for aircraft identity and mode C, which is used to request altitude information.**
All pulses are 0.8 us wide. The interrogations from the ground station are at a frequency of 1030 MHz. The transponder replies at a frequency of 1090 MHz. The signal received from the airborne transponder is decoded by the round system so that it can be displayed on the ATC radar screen (see figure 4-3). The replies produce either a single or double slash target display on the controller screen. The controller can also elect to display the aircraft identification number (as selected by the aircrew) and the aircraft altitude.
*The time is easily converted into range. The propagation velocity of radio energy is known. The mathematical formula for distance is: D = velocity x (multiplied by) time. However, radio propagation velocity is usually expressed as 12.359 us per radar mile. Notice that this is the inverse of what is necessary for the distance formula, which must have velocity expressed as a measure of distance per unit of time (eg, miles per hour). Therefore, the distance formula must be modified slightly: D = time / (divided by) propagation velocity. **In the original definition of ATC modes, two other modes were defined: mode B and mode D. These also differ only in of pulse spacing, with mode B pulses spaced 17 us and mode D pulses spaced 25 us. For a time, mode D was widely used in Great Britain, but in recent years most of the aviation industry has settled on mode A for ATCRBS operation and mode C for altitude reporting, and modes B and D have been largely abandoned. In US military applications, a system similar to ATCRBS is used; it is known as IFF (identification friend or foe). As this name implies, it has to do with mission security. Three modes are defined: modes 1, 2, and 3. Mode 3 is common to the civil mod A, with a pulse spacing of 8 us. This allows air traffic control visibility of all aircraft, both civil and military. 4 April 1989
4-2
operation 523-0775656
ATC, PSR and SSR System Figure 4-2
4 April 1989
4-3
operation 523-0775656
Air Traffic Presentation on the ATC Radarscope Figure 4-3
4 April 1989
4-4
operation 523-0775656 4.3.4 SSR Radiation Patterns and SLS Refer to figures 4-4 and 4-5. The SSR uses a rotating directional antenna to transmit two pulses, which are identified as P1 and P3. The spacing of these pulses determines the mode. In mode a the pulses are spaced 8 us, while in mode C the pulses are spaced 21 us. The SSR also uses an omnidirectional antenna to transmit a third pulse, designated P2. This pulse is transmitted 2 us after the P1 pulse and provides a reference for side-lobe suppression (sls). The amplitude of the P2 pulse is about the same as the peak sidelobe of the directional antenna. Typically, this is about 18 dB below the peak of the directional (main) beam. Refer to figure 4-4. Notice the two aircraft on the drawing. Aircraft A is shown as being within the main lobe of the directional antenna. The amplitude of the P1 and P3 pulses will be substantially greater here than that of the P2 pulse radiated from the omnidirectional antenna. Therefore, this aircraft transponder will interpret this interrogation as valid. Aircraft B, however, is outside the main lobe and within one of the sidelobes. The P1 and P3 pulses detected here will be the result of side-lobe radiation. Recall that the P2 pulse is transmitted by an omnidirectional antenna and is about equal in amplitude to that of the peak sidelobe. Therefore, the P2 pulse detected by aircraft B will be at least as great in amplitude as the P1, P3 pulses. The transponder in aircraft B will detect this relationship in pulses and discard the interrogation as invalid, because the P2 pulse is not substantially less than the P1, P3 pulses. As a further safeguard against replies to possible late-arriving echoes to this invalid interrogation, the
Revised 4 April 1990
transponder suppresses replies to all interrogations for an additional 25 to 45 ms. In addition, the receiver is desensitized for reception of P1, P3 pulses. The rationale here is that if the sidelobes are detectable, then the main lobe must be much greater, increasing the likelihood of echo reception. 4.3.5 ATC Transponder 4096 Replies The ATCRBS transponder 4096 reply signal is shown in figure 4-6. Notice that the signal can consist of from 2 to 15 pulses (the X pulse is not used). The two framing pulses, F1 and F2, are always present and spaced 20.3 us. An identification pulse may be transmitted 4.35 us after the last framing pulse, F2. The intervening pulses, C1 through D4 on the figure, make up the coded reply. The coded reply consists of four digits ranging from 0 through 7. The digits are formed by the sum of the suffix numbers ranging from 0 through 7. The A group (A1, A2, and A4) makes up the first digit, the B group makes up the second digit, etc. (On the figure, a pulse outlined with a solid line indicates that the pulse is present. A pulse outlined with dashed lines indicates the position for that pulse when it is present.) The pulse configuration on the figure indicates a reply code of 1324. The first digit, 1, is formed y the presence of only the A1 pulse. The second digit, 3, is formed by the presence of B1 and B2 (1 + 2 = 3). A digit 7 is formed when all three pulses of the group are present (1 + 2 + 4 = 7). Therefore, a reply sequence with all pulses present constitutes a code 7777. The X pulse is not defined in ATCRBS replies. This combination of four digits, each ranging from 0 through 7, makes possible 4096 different codes, which explains the reason for calling it the 4096 code.
4-5
operation 523-0775656
ATCRBS, SSR Antenna Radiation Pattern Figure 4-3
4 April 1989
4-6
operation 523-0775656
ATCRBS, Interrogator Pulse Spacing Figure 4-5
ATCRBS and Mode S, Transponder 4096 Reply Code, Signal Format Figure 4-6
4 April 1989
4-7
operation 523-0775656 4.4 ATCRBS AND MODE S (Refer to figure 4-7) 4.4.1 Introduction Mode S substantially enhances the capability of the ATCRBS by adding data link and discrete interrogation features. The data link capability includes air-to-air information exchange, ground-to-air (data uplink or comm A), air-to-ground (data downlink or comm B), and multiple ground stations message protocol. The mode S transponder can also function as part of an airborne separation assurance (ASA) system when interfaced with a Traffic Alert and Collision Avoidance System (TCAS). 4.4.2 Mode S Interrogation Modes (Refer to figures 4-8, 4-9, and 4-10) There are eight different formats of interrogation used in mode S. These eight formats can be summarized in of three basic types. These are shown in figures 4-8 and 4-9. Figure 4-10 is a summary of all eight. This variety of interrogation capability gives the ground controller the flexibility of addressing only those aircraft of immediate interest, as opposed to processing replies from all aircraft. All eight of the interrogation modes are summarized in figure 4-10. The various fields are described in the following paragraphs. These descriptions are largely as provided in Document RTCA/DO-181, with minor changes to clarify the text. a. Address/Parity (AP) Field: The 24-bit* AP field contains the parity overlaid on the address and appears at the end of all transmissions for uplink interrogations and downlink replies, except for downlink format (DF) number 11. b. Acquisition Special (AQ) Field: The 1-bit AQ field designates uplink format (UF) numbers 0 and 16 as acquisition transmissions and is repeated as received by the transponder in DF numbers 0 and 16. *In the RTCA document, some graphic material refers to these as chips. For this description, the are regarded as synonymous.
Revised 4 April 1990
c.
Designator Identification (DI) Field: The 3-bit DI field identifies the coding contained in the special designator (SD) field in IF numbers 4, 5, 20, and 21. The codes are defined as follows: DI 0 1 2-6 7
DEFINITION Not used SD contains multisite information Not assigned SD contains extended data readout request
d. Interrogator Identification (II) Field: The 4-bit II field identifies the interrogator and appears in UF number 11 (mode S only all-call). e. Message, Comm A (MA) Field: The 56-bit MA field contains messages directed to the aircraft (UF numbers 20 and 21). This field also contains the 8-bit comm A definition subfield (ADS). ADS defines the content of the MA message field, of which it is a part. f. Message, Comm C (MC) Field: The 80-bit MC field contains one segment of a sequence of segments transmitted to the transponder in the extended length message (ELM) (112 bits) mode. The field contains an 8-bit comm C definition subfield (CDS) that defines the message to be sent to the transponder and is included in segment zero of the ELM uplink sequence. g. Message, Comm U (MU) Field: The 80-bit MU field contains information used in air-to-air message exchanges. h. Number of C-Segment (NC) Field: The 4-bit NC field provides the number of a segment transmitted in an uplink ELM message and is part of the comm C interrogation, UF number 24. i. Protocol (PC) Field: The 3-bit PC field contains the operating commands to the transponder. The code description is as follow: DI 0 1 2-3 4 5 6 7
DEFINITION No changes in transponder state Nonselective all-call lockout Not assigned Cancel B Cancel C Cancel D Not assigned
4-8
operation 523-0775656
Mode S, PSR and SSR System Figure 4-7
Revised 4 April 1990
4-9
operation 523-0775656
Mode S, All-Call and Discrete Addressing, Interrogation Format Figure 4-8
Mode S, Discrete Addressing, Pulse P6 Definition Figure 4-9
Revised 4 April 1990
4-10
operation 523-0775656
ATCRBS, SSR Antenna Radiation Pattern Figure 4-10
Revised 4 April 1990
4-11
operation 523-0775656 j.
Probability of Reply (PR) Field: The 4-bit PR field contains commands to the transponder to specify the reply probability to the mode S only all-call interrogation, IF number 11. The code description is as follows: PR 0 1 2 3 4 5-7 8 9 10 11 12 13-15
DEFINITION Reply with probability = 1 Reply with probability = 1/2 Reply with probability = ¼ Reply with probability = 1/8 Reply with probability = 1/16 No reply Disregard lockout, reply with probability = 1 Disregard lockout, reply with probability = ½ Disregard lockout, reply with probability = ¼ Disregard lockout, reply with probability = 1/8 Disregard lockout, reply with probability = 1/16 Do not reply
After receiving a mode S only all-call containing a PR code other that 0 through 8, the transponder will execute a random process and make a reply decision for this interrogation in accordance with the command probability. Random occurrence of replies enables the interrogator to acquire closely spaced aircraft that might otherwise synchronously garble the transponder replies.
Revised 4 April 1990
k. Reply Control (RC) Field: The 2-bit RC field designates the transmitted segment as initial (0), intermediate (1), or final (3). An RC field (3) is used to request a comm d downlink by the transponder. RC is part of the comm C interrogation, UF number 24. l.
Reply Length (RL) Field: The 1-bit RL field commands a reply (DFO) if the bit is 0 and a reply in DF number 16 if the bit is 1.
m. Reply Request (RR) Field: The 5-bit RR field describes the length and content of the information requested (MB - see reply field descriptions below ) by the interrogator. The code description is as follow.: RR
REPLY LENGTH
0-15 16 17 18 19-31
Short Long Long Long Long
MB CONTENT Air initiated comm B Extended capability Flight identification Not assigned
If the first bit of the RR code is logic 1, then the decimal equivalent of the last four bits designates the requested source. n. Special Designator (SD) Field: The 16-bit SD field contains control codes affecting the transponder protocol. The content is specified by the DI field. A subfield, IIS, is contained within the SD field and specifies the interrogator identifier.
4-12
operation 523-0775656 4.4.3 Mode S SSR Radiation Pattern and SLS (Refer to figure 4-11) The mode S interrogation is transmitted through a technique known as binary differential phase-shift keying (DPSK). This technique is described graphically in figure 4-9. A chip is an unmodulated interval of 0.25 us that may be preceded by a phase reversal (pr). If a chip is preceded by a pr, it represents a logic 1. If it is not preceded by a pr, it represents a logic 0. In mode S, the omnidirectional antenna transmits pulse P5 as the sls reference pulse. The P5 pulse occurs within the P6 pulse and is timed 0.4 us before the spr (sync phase reversal). Thus, if the amplitude of P5 is sufficient to blank the spr of P6, the interrogation is most likely from a sidelobe and not from the main love. In this case, the spr is hidden from the transponder, so the reply is suppressed. The SSR mode S interrogation pulse spacing and identification is different from that of the earlier ATCRBS. Figures 4-8, 4-9, and 4-10 show these configurations. Notice that the rotating beam transmits two different pulse combination. For all-call interrogations, the transmitted pulses are P1, P3 , and P4. In these interrogations the sls reference pulse, P2, is transmitted by the omnidirectional antenna as in conventional ATCRBS. The P1-to-P3 pulse spacing is either 8 µs (for mode A) or 21 µs (for mode C), also as in ATCRBS. The P4 pulse follows the P3 pulse by 2 µs and can be either 0.8 µs (the same as P1 and P3) or 1.6 µs. The pulse width of P4 determines the all-call objective as follow (all times are in microseconds): P1-P2
PULSE SPACING P1-P3 P3-P4
P4
2±0.15 2±0.15 2±0.15
8±0.2 21±0.2 8±0.2
2 ±0.05
None None Long
2±0.15
21±0.2
2 ±0.05
Long
2±0.15
8±0.2
2 ±0.05
Short
2±0.15
21±0.2
2 ±0.05
Short
INTERROGATION TYPE
ATCRBS Mode A ATCRBS Mode C ATCRBS Mode A/Mode S all-call ATCRBS Mode C/Mode S all-call ATCRBS Mode A-only all-call ATCRBS Mode C-only all-call
Where P4 long pulse width is 1.6 ±0.1 µs and P4 short pulse width is 0.8 ±0.1 µs.
A 0.8-µs pulse is only for non-mode S transponders, while the 1.6-µs pulse is for both ATCRBS and mode S transponders.
Revised 4 April 1990
The mode S discrete addressing interrogation takes yet another form. For this interrogation, the rotating beam antenna transmits pulses P1, P2, and P6. P6 is in reality a series of either 56 or 112 bits identified as chips that define the data. At 1.25 µs after the start of P6, the spr occurs. This spr must be detected in order to enable a reply response. The final chip is followed by a 0.5-µs guard interval. This prevents the trailing edge of P6 from interfering with the demodulation process. The P2 pulse follows the P1 pulse by 2 µs. P6 begins about 1.5 µs after P2. The ground mode S interrogator system uses a monopulse processing scheme to determine the azimuth bearing to the aircraft., This scheme requires only a single reply from an airborne transponder, as opposed to the two replies necessary in the earlier ATCRBS system, to establish the azimuth to the aircraft.* The address (derived from the reply) and location (azimuth and range) of the mode S aircraft is entered into a roll-call file. This file can be visualized as a list of the mode S transponder equipped aircraft within its assigned airspace. On a later scan, the mode S aircraft is discretely addressed. This discrete address contains a command field that is used to desensitize the mode S transponder to further mode S all-call interrogations. This desensitization is called mode S lockout. The ATCRBS-only transponders are not affected by this lockout technique and mode S transponders continue to reply to ATCRBS interrogations. When a mode S transponder equipped aircraft moves from one assigned airspace into another, the first ground interrogator can communicate with the next interrogator and aircraft information to that second interrogator. This communication link can be via ground lines or radio link. If this method is used, the mode S lockout is not disabled on the affected aircraft and the second interrogator will schedule discrete roll-call interrogations for that aircraft as needed. This technique makes it possible to increase the aircraft handling capacity of the ground interrogator. *In this scheme, the monopulse system generates two separate patterns: a single (sum) pattern and a dual lobe (difference) pattern. The ratio of the energy received by the sum pattern to the energy received by the difference pattern determines the bearing of the aircraft from the antenna beam center line.
4-13
operation 523-0775656 In regions where mode S interrogators are not connected via ground or radio link, the protocol for the transponder allows it to be in mode S lockout only for those interrogators that have the aircraft on the rollcall list. This enables a second ground interrogator to acquire an aircraft into its assigned airspace using the all-call technique as previously described. 4.4.4 Mode S Transponder Replies Typically, the ground-based interrogator tracks an aircraft throughout its assigned airspace. The mode S transponder equipped aircraft responds to mode S interrogations with the ATCRBS 4096 code and the mode S reply format. During each scan, the SSR interrogations are in both mode A and mode C. The mode S transponder reply uses a technique known as pulse-position modulation (PPM). This is described graphically in figure 4-12. A pulse transmitted in the first half of the interval represents a logic 1, while a pulse transmitted in the second half represents a logic 0. The mode S reply format is described in the following paragraphs. 4.4.5 Mode S Reply Description The reply waveform is shown in figure 4-12. The reply data block is formed by PPM encoding of the reply data, as previously described. The first preamble pulse occurs 128 µs after the start of the P4 interrogation pulse or the spr. The ATCRBS reply to an ATCRBS interrogation is identical to the reply transmitted by an non-mode S transponder (see figure 4-6). All reply formats are summarized in figure 4-13. The fields are described in the following paragraphs. Address, Announced (AA) Field: The 24-bit AA field contains the aircraft address (uncoded) and is used in the all-call reply. b. Altitude Code (AC) Field: The 13-bit AC field contains the altitude code. The encoded altitude is coded as shown in figure 4-6. The M bit has been redefined for mode S; it was the X bit shown in figure 4-6. In mode S the M bit may be used in the future for encoding the altitude in metric units. Zero is transmitted in each of the 13 bits if altitude information is not available. c. Address/Parity (AP) Field: The 24-bit AP field contains the parity overlaid on the address and appears at the end of all transmissions on both uplink and downlink, except for DF number 11. d. Capability, Transponder (CA) Field: The 3-bit CA field reports transponder capability. The code description is as follows:
CA 0
No communications capability (surveillance only) Comm A and comm B capability Comm A, comm B, and downlink ELM capability Comm A, comm B, uplink ELM, and downlink ELM capability Not assigned
1 2 3 4-7
If the transponder CA code is 1, 2, or 3, the data link capability report is used to indicate the specific data link capabilities of the overall airborne installation. e.
Downlink Request (DR) Field: The 5-bit DR field is used to request extraction of downlink messages from the transponder by the interrogator. The code description is as follow: DESCRIPTION
DR 0 1 2-15 16-31
a.
Revised 4 April 1990
DESCRIPTION
No downlink request Request to send comm B message Not assigned Request permission to send extended length message (ELM’s) of n-segments. The code inserted into the DR field corresponds to 15 + n. Downlink ELM’s are transmitted only after authorization by the interrogator. The segments are transmitted on comm D replies. On receipt of the authorization, the transponder sends a segment every 136 Ts. After receipt of all segments, the interrogator replies with a closeout transmission to indicate that all segments have been received and allow the DR field to be reset. The closeout transmission is contained in a surveillance or comm A interrogation.
f. Flight Status (FS) Field: The 3-bit FS field reports the flight status of the aircraft. The code description is as follows: FS
ALERT
SPI
AIRBORNE/ON THE GROUND
0 1 2 3 4 5
No No Yes Yes Yes No
No No No No Yes Yes
Airborne On the ground Airborne On the ground Either Either 4-14
operation 523-0775656 g. Identification (ID) Field: The 13-bit ID field contains the 4096 identification code as selected by the pilot. h. ELM Control (KE) Field: The 1-bit KE field defines the content of the ND and MD fields in comm D replies. The transponder acknowledges receipt of a final segment with a comm D transmission with KE = 1. The MD field contains a transmission acknowledgement subfield (TAS). The information contained in the TAS subfield is continuously updated as segments are received and is cleared when a closeout occurs or a new initializing segment is received. i. Message Comm B (MF) Field: The 56-bit MD field contains the message transmitted to the interrogator. The field contains an 8-bit subfield (BDS) that defines the contents of the comm B message. j. Message Comm D (MD) Field: The 80-bit MD field contains one segment of a sequence of segments transmitted by the transponder in the ELM mode. It also may contain a summary of the received MC segments of an uplink ELM. An 8-bit subfield (DDS) defines the message to be transmitted and is included in segment 0 of the ELM downlink. k. Message Comm V (MV) Field: The 56-bit MV field contains information used in the air-toair exchanges between mode S transponders. l. Number of D-Segment (ND) Field: The 4-bit ND field provides the number of the segment transmitted in a downlink ELM and is part of the comm D reply. m. Parity/Interrogator Identity (PI) Field: The 24bit PI field contains the parity overlaid on the interrogator identity code.
Revised 4 April 1990
n. Reply Information (RI) Field: The 4-bit RI field reports the airspeed capability and type of reply to the interrogating aircraft. The code description is as follows: RI
DESCRIPTION
0-7
Indicates that downlink is the reply to an air-to-air acquisition interrogation Indicates that downlink is an acquisition reply as follows: No maximum airspeed data is available Airspeed is up to 75 knots Airspeed is between 75 and 150 knots Airspeed is between 150 and 300 knots Airspeed is between 300 and 600 knots Airspeed is between 600 and 1200 knots Airspeed is more than 1200 knots Not assigned
8-15 8 9 10 11 12 13 14 15 o.
Utility Message (UM) Field: The 6-bit UM field contains transponder status readouts. p. Vertical Status (VS) Field: The 1-bit VS field indicates that the aircraft is airborne (VS = 0) or on the ground (VS = 1). q. Free and Unassigned Coding Space Fields: Free coding space contains all logic level 0, as transmitted by the interrogator or transponder. Unassigned coding space that exists within fields is reserved for possible future use.
4-15
operation 523-0775656
Mode S, SSR Antenna Radiation Pattern Figure 4-11
Revised 4 April 1990
4-16
operation 523-0775656
Mode S, Transponder Reply Code Pulse Spacing Figure 4-12
Mode S, Transponder Reply Code Summary Figure 4-13
Revised 4 April 1990
4-17
operation 523-0775656 4.5 TDR-94/94D THEORY OF OPERATION 4.5.1 Introduction This paragraph gives you an overview of the TDR94/94D operating environment. If you are familiar with the various installation configurations and options, you can skip over this paragraph. 4.5.2 Installation Strapping Options The TDR-94 and TDR-94D ATC/Mode S Transponders offer a wide range of installation options. First you should recognize the difference between the TDR-94 and the TDR-94D; the TDR94 is for single
antenna installations, while the TDR-94D is for antenna diversity (dual antenna) installations. You are likely to find the TDR-94D in most TCAS installations because dual antennas are required in TCAS. Both transponders can accept control data in CSDB or ARINC 429 format; this is set at installation by means of special external straps. The following paragraphs and accompanying diagrams describe the various installation configurations. Figure 4-14 shows the various strapping options that must be considered for all installations. You should understand that these strapping options can apply to all installations.
TDR-94/94D ATC/Mode S Transponder Strapping Options Figure 4-14
Revised 4 April 1990
4-18
operation 523-0775656 4.5.3 Typical Configurations Figure 4-15 shows a TDR-94 installation with a CTL-92/92A CSDB transponder control unit and an encoding altimeter. This type of encoder typically supplies altitude data in Gillham code (ARINC 572)
format. The encoded data can be supplied to the CTL-92/92A or directly to the TDR-4. Installers should choose the connection that involves the shortest wire run.
TDR-94 ATC/Mode S Transponder With CTL-92/92A Transponder Control Unit and Altitude Encoder, Typical Figure 4-14
Revised 4 April 1990
4-19
operation 523-0775656 Figure 4-16 shows a similar installation except it uses a central air data computer (CADC) for altitude data. In each of these cases, external strapping is required according to the type of altitude data that is being used. An alternate Installation configuration is
possible using ARINC 429 code selection. In this case, an ARINC 429 source, such as an FMS, would be shown in place of the CTL-92/92A, with appropriate strapping as shown in figure 4-14.
TDR-94 ATC/Mode S Transponder With CTL-92/92A Transponder Control Unit and CADC Altitude Source, Typical Installation Diagram Figure 4-16
Revised 4 April 1990
4-20
operation 523-0775656 Figure 4-17 shows a TDR-94D in a TCAS installation with a CSDB control and dual antennas. If the transponder is operated with only a single antenna, a special strap is required. The diagram also shows a CADC for altitude data. This can be an encoder as shown in figure 4-15. Either way, appropriate
strapping is required. The CTL-92T is required for TCAS control and is connected between the TDR94D and CTL-92/92A. In this installation, transponder control data is entered on the CTL92/92A and the TCAS control data is added to the data word in the CTL-92T.
TDR-94D ATC/Mode S Transponder, Data Link, and TCAS Installation With CSDB Control and CADC Altitude Data Source, Typical Installation Diagram Figure 4-17
Revised 4 April 1990
4-21
operation 523-0775656 Figure 4-18 shows an installation similar to that of figure 4-17. This can be seen as a typical TCAS and
data link installation using an ARINC 429 control for code selection and transponder/TCAS control.
TDR-94D ATC/Mode S Transponder, Data Link, and TCAS Installation With ARINC 429 Transponder Control and CADC Altitude Data Source, Typical Installation Diagram Figure 4-18
Revised 4 April 1990
4-22
operation 523-0775656 4.5.4 TDR-94/94D Block Diagram Theory of Operation 4.5.4.1 Introduction The TDR-94/94D ATC/Mode S Transponder is the airborne portion of the SSR system. It is capable of operating with ATCRBS and mode S interrogators. The TDR-94D can operate with two antennas for improved air-to-air surveillance. This capability is required in TCAS installations. The TDR94/94D also provides data link message capability. 4.5.4.2 Overall Functional Block Diagram Theory of Operation (Refer to figure 4-19) The TDR-94/94D consists of seven major subassemblies numbered A1 through A7. These are described in the following paragraphs. The transponder interrogations and uplink messages are received by either one or both of the antennas. This received signal is routed through the receive signal detector in module A2 to the IF amplifier in module A7. If the transponder is a diversity (dual antenna) unit, the IF amplifier operates on both the top and bottom signals independently. The IF amplifier ensures that the interrogation is a valid signal and processses that signal into the level required by the video processor in module 6. Module A7 also contains the DPSK detector, which detects the presence of a differential phase reversal in a mode S interrogation. The video processor evaluates the video data from the IF amplifier to determine whether the interrogation is an ATCRBS or mode S interrogation. The
Revised 4 April 1990
processor also determines whether a response is appropriate. Depending on certain criteria, the processor also determines which antenna should be used for reply, top or bottom. This data is supplied to modulator A3, where the proper diode drive signals are generated. These diode drive signals control the diversity switch in module A2. The video processor also supplied the proper reply data to the modulator. The modulator controls the bracket drive signals which drive the power amplifer. The response pulse train is formed in the power amplifier. This pulse train is switched through the diversity switch and low- filter and is radiated by the appropriately selected antenna. The U and I/O module contains most of the circuits involved in the digital input and output signals. The discrete inputs include a number of strapping options, like TCAS select and control format select (CSDB or ARINC 429). The digital inputs include altitude and communications data. The digital outputs include communication, TCAS, and altitude data. A few of the discrete inputs, like TCAS select, the altitude digitizer inputs, and the mode S identification strapping inputs, enter the unit on the A6 module. The synthesizer generates the 1090-MHz CW signal that is used to drive the power amplifier. The modulator effectively switches the power amplifier on and off to create the output pulse train that becomes the reply or downlink transmission. The diversity switch directs the power amplifier output to the top or bottom antenna. The modulator controls the diversity switch in response to control signals from the video processor.
4-23
operation 523-0775656
TDR-94/94D Mode S Transponder Overall Block Diagram Figure 4-19
Revised 4 April 1990
4-24
523-0775657-005118 5th Edition, 15 June 1995
TDR-94/94D ATC/Mode S Transponder System Maintenance
Table of Contents
Paragraph
Page
5.1 GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-1 5.2 MAINTENANCE SCHEDULE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-1 5.3 TEST EQUIPMENT AND POWER REQUIREMENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-1 5.4 TESTING AND TROUBLESHOOTING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-1 5.5 MAINTENANCE DIANOSTIC DATA TREIEVAL AND ANALYSIS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-132 5.6 NUMBER SYSTEM CONVERSION AND DATA WORD DESCRIPTIONS . . . . . . . . . . . . . . . . . . . . . . . 5-148 5.7 GILLHAM CODE DESCRIPTION WITH ENCODING AND DECODING INSTRUCTIONS . . . . . . . . . 5-155 5.8 ACCEPTANCE TEST, TEST ASSEMBLY INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-158 5.9 FLIGHTLINE TEST, TEST ASSEMBLY INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-175
NOTICE: This section replaces fourth edition dated 5 May 1993.
List of Effective Pages Page
*The asterisk indicates pages changed, added, or deleted by the current change.
Issue
*Title . . . . . . . . . . . . . . . . . . . 15 Jun 95 *List of Effective pages . . . . . 15 Jun 95 5-1 thru 5-8 . . . . . . . . . . . . . . . 5 May 93 *5-9 . . . . . . . . . . . . . . . . . . . 15 Jun 95 5-10 thru 5-36 . . . . . . . . . . . . 5 May 93 *5-37 . . . . . . . . . . . . . . . . . . 15 Jun 95 5-38 thru 5-42 . . . . . . . . . . . . . 5 May 93 *5-43 thru 5-132 . . . . . . . . . . 15 Jun 95 5-133 thru 5-152 . . . . . . . . . . . 5 May 93 *5-153 thru 5-154.1 . . . . . . . 15 Jun 95 *5-154.2 . . . . . . . . . . . . . . . . . . . Blank *5-155 thru 5-158 . . . . . . . . . 15 Jun 95 5-159 thru 5-162 . . . . . . . . . . . 5 May 93 *5-163 thru 5-169 . . . . . . . . . 15 Jun 95 5-170 thru 5-187 . . . . . . . . . . . 5 May 93 *5-188 thru 5-189 (deleted) . . . 5 May 93 *5-200 thru 5-201 (deleted) . . . 5 May 93 *5-188 thru 5-197 (page numbers15only) Jun 95
Record of Revisions INSERTION DATE/BY
RETAIN THIS RECORD IN THE FRONT OF THE MANUAL. ON RECEIPT OF REVISIONS, INSERT REVISED PAGES IN THE MANUAL, AND ENTER DATE INSERTED AND INITIALS.
REV / ED NO
REVISION DATE
SB NUMBER INCLUDED
1st Ed
4 Apr 90
None
2nd Ed
29 Apr 91
None
3rd Ed
6 Jan 92
None
4th Ed
5 May 93
See Table 1-6
5th Ed
15 Jun 95
See Table 1-6
REV / ED NO
REVISION DATE
INSERTION DATE/BY
SB NUMBER INCLUDED
V
section maintenance 5.1 GENERAL
5.2 MAINTENANCE SCHEDULE
This section provides on board maintenance procedures and limited bench checkout procedures for the TDR-94/94D ATC/Mode S Transponder. The test procedures are for use in:
Collins has no requirement for periodic maintenance of the TDR-94/94D Mode S Transponder.
a. Checking a transponder system on the bench before installation to ensure that it is functioning properly, or b. Exercising the transponder system on board the airplane through a systematic routine for fault isolation to a defective LRU. The bench procedures use a special test described in paragraph 5.9. The Flightline Fault Isolation procedures use a similar, but less complex, test which is described in paragraph 5.9. In both cases, data is provided to allow local fabrication, or purchase from a supplier such as Avionics Specialists Inc, or JcAIR.
5.3 TEST EQUIPMENT AND POWER REQUIREMENTS 5.3.1 Test Equipment Table 5-1 lists the test equipment required to perform the test procedures found in this section. Equivalent test equipment can be substituted in place of the listed items. 5.3.2 Power Requirements All power required to perform the flightline system tests and LRU fault isolation procedures is provided by the airplane in which the system is installed.
Fault isolation procedures should include a check of the airplane installation and wiring with special attention to conditions that can contribute to a failure of the transponder system.
A bench 28-V dc supply, with at least 5-A peak current output, is needed for the bench procedure.
On board airplane fault isolation most often assumes that a self-test can be performed. A system that is totally non-responsive is usually best evaluated on the bench.
Note
The TDR-94/94D performs a full self-test automatically upon unit power-up. It then performs extensive background testing to bus status and the condition of critical functions for diagnostic purposes. Use the TEST button on the control head to initiate a self-test.
5/5/1993
5.4 TESTING AND TROUBLESHOOTING
The following test procedures assume that the airplane interconnect wiring has been verified and is correct. Test procedures in table 5-2 provide an operational test of the TDR-94/94D Mode S Transponder. If any of these tests fail, or if there is reason to suspect a failure, then the Fault Isolation Procedures in Table 5-5 and can be used to help isolate a defective unit.
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Table 5-1. Test Equipment Required.
EQUIPMENT
MANUFACTURER
CHARACTERISTIC
FUNCTION
Fluke 8010A, Dvm
John Fluke Mfg. Co., Inc. Suite 113 1380 Corporate Center Curve Eagan, MN 55121-1200 (612) 452-4264
Portable, 3-1/2 digit accuracy
Measure ac and dc voltages; for use on ramp for wiring checkout and with Flightline Test or on bench for Acceptance Testing
Tektronix 455, 2235, 2236, Oscilloscope
Tektronix 5350 Keystone Court Rolling Meadows, IL 60008 (708) 259-7580
Portable, dc to 10 MHz
Measure serial logic levels; for use with Flightline Test or on bench for Acceptance Testing
ATC-601 Ramp Test Set
IFR. Inc., 4053 Navajo Lane Wichita, KS 67210 (316) 522-4981
Portable ATCRBS transponder Ramp Test Set. Capable of broadcast and direct-connection testing of normal transponder operation in modes A, C, and Mode S, as well as all defined and applicable uplink / downlink formats.
For ATCRBS and Mode S ground station simulation in flightline or bench testing procedures.
RF load
M/A-COM Omni Spectra, Inc. 21 Continental Blvd Merrimac, NH 03054-9979
50-Ω at 1090 MHz TNC or BNC with adapter
RF termination of unused antenna output (TDR-94D only). Needed on flightline only when using direction connection method.
Diversity Boot
Locally fabricated (included with ATC-601)
Rf opaque for diversity testing. Ideally, it should have an adhesive base.
To isolate antenna ports for broadcast diversity testing on the flightline.
DataTrac 400H * DataTrac 400 * DataTrac 200 **
Atlantic Instruments, Inc. P.O. Box 021466 Melbourne, FL 32902 (407) 951-2542
Portable, battery operable, *ARINC 429 bus simulation and analysis, ** ARINC 429 and CSDB bus simulation and analysis
Control head simulation and data bus analysis; for use on ramp with Flightline Test or on bench for Acceptance Testing
JcAIR 429E
JcAIR 400 Industrial Parkway Industrial Airport, KS 66031 (913) 764-2452
ARINC 429 bus simulation and analysis
Control head simulation and data bus analysis; for use on ramp with Flightline Test or on bench for Acceptance Testing
Acceptance Test, Test
Locally fabricated according to data in paragraph 5.8 at the end of this section. This paragraph also lists the various cables needed.
Bench test
To provide input/output control and unit/test equipment interface for bench testing.
Flightline Test
Locally fabricated according to data in paragraph 5.9 at the end of this section. This paragraph also lists the various cables needed.
Portable test device
To provide access to signals between control and transponder unit
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5-2
maintenance 523-0775657 5.4.1 Diagnostic Information The procedures in table 5-6 provide for the retrieval of diagnostic data that is stored in non-volatile memory in the TRD-94/94D transponder. This data can be helpful in diagnosing certain type of failures especially those of a more transient nature. Refer to table 5-3 for a description of the diagnostic codes and the recommended troubleshooting procedure. Table 5-4 provides additional information for proper interpretation of the diagnostic codes.
Most transponder ramp testers can be used in direct-connect or broadcast operating modes. At times both methods are useful in isolating a transponder malfunction between the antenna / antenna cables and the transponder unit. For example, if in the broadcast method the test shows a low power output or low sensitivity. Switching to the direct-connection method can effectively isolate the problem to the transmitter/receiver or the antenna system.
5.4.2 Test Equipment Installation and Power Application For Flightline Testing Using A Ramp Tester
If you use the direct connection method and you are using a test set other than the IFR ATC-601, be sure it has the proper attenuation in the RF link to prevent damage to the transponder receiver. The IFR ATC-601 has the proper attenuation built into its rf port. If another type of tester is being used, check the manual to be sure it provides adequate protection. Be sure that the injected signal level is not greater than -20 dBm.
5.4.2.1 Preliminary Instructions Refer to table 5-2 for the transponder system flightline testing and fault isolation procedures. These procedures use the test setup shown in figure 5-1 and provide for a quick initial check to determine whether or not the transponder system is functional. If this check shows that a fault exists, refer to the procedures in table 5-5 for more detailed fault isolation. A test and data bus reader are needed for these procedures. 5.4.2.2 Bus Reader Selection Any one of the four bus readers listed in table 5-1 can be used. However, of those listed only the Atlantic Instruments DataTrac 200 is capable of receiving and transmitting either the CSDB or the ARINC 429 bus format. The others are ARINC 429 only. Therefore, if the installation includes a CTL-92/92A control, only the DataTrac 200 can be used to simulate that control. 5.4.2.3 Ramp Tester Selection and Use The IFR ATC-601 was used in the development of the procedures in this manual. It is possible that other instruments, i.e., instruments provided by other manuafacturers, have comparably and acceptable features. You should feel free to use your choice of instruments. However, be sure that it is capable of testing the transponder operating items listed at the end of this paragraph.
5/5/1993
Most transponder ramp test sets allow operation inside a hanger. Be aware, however, that the glossy (and often painted) floor surfaces found in most hangers can result in substantial signal reflection. This can have an effect on power output and receiver sensitivity tests. Moving the sense antenna above or below the transponder antenna usually produces different results and demonstrates the effect of signal reflection. It is for this reason that you should try a few different sense antenna heights, distances, and airplane parking locations to gain a basis for test result interpretation and evaluation. Be guided by the antenna placement requirements of the test set manufacturer. Locate the ramp tester sense antenna at the proper distance from the airplane transponder antenna. The best distance and height may be specified by the manufacturer. Mode s diversity transponder installations may require shielding of one antenna for diversity testing. An RF opaque boot of nearly any design is acceptable for this purpose. It should fit completely over the antenna and provide good base grounding. An adhesive base may be best for easy installation and removal.
5-3
maintenance 523-0775657 The IFR ATC-601 features a special automatic test sequence that significantly reduces the time required for the test. Using the automatic sequence or an equivalent manual sequence is largely a matter of personal choice. However, if a particular test fails in the automatic sequence, it might be advisable to repeat that test manually to help in isolating the fault. Follow the test set operating procedures as provided. At least the following transponder operating items should be tested. The order is not critical.: 1. Mode A response. 2. Mode C response with altitude if available. 3. Mode S all-call response, 4. Mode S lockout. 5. Transmitter frequency. 6. Transponder power output. 7. Receiver frequency discrimination. 8. Receiver sensitivity. 9. Receiver interrogation pulse spacing discrimination (all modes). This involves altering the pulse spacing from normal and testing the transponder’s reply or lack of reply. 10. Individual pulse-width discrimination (all modes). This is the same type of test as 9. except that the pulse width is changed instead of the pulse spacing. 11. SLS (side lobe suppression). This involves changing the P2 pulse amplitude with respect to the P1/P3 pulses and testing the transponder’s response. 12. Transponder response to invalid address interrogations. 13. SPR on/off. 14. Mode S, UF0 (uplink format 0). 15. Mode S, UF4. 16. Mode S, UF5. 17. Mode S, UF11. 18. Mode S, UF16. 19. Mode S, UF20. 20. Mode S, UF21. 21. Diversity isolation (TDR-94D, operating with dual antennas only). 22. Transponder squitter. 23. Airplane identification code.
5/5/1993
5.4.2.4 Transponder System Inspection If the nature of the transponder failure report is such that it may be caused by antenna cables or antennas, inspect these for possible physical damage or deteriorated installation integrity. The condition of the transponder antenna, antenna cable(s), and cable connectors can have a significant effect on transponder operation. Therefore, an occasional visual inspection of these components is advisable. However, do not disassemble the airplane to inspect antenna cables unless you have good reason to suspect a cable or connector problem. 5.4.2.5 Transponder System Ground Test Enable Some transponder installations use a weight-onwheels transponder inhibit mechanism to prevent response to interrogations while the airplane is on the ground. It is necessary to disable this inhibit feature for testing. This is unique to each airplane therefore you must consult the airplane manual for the necessary instructions. It may also be necessary to condition the altitude data system for test purposes. 5.4.3 Flightline Test Procedures Transponder system testing procedures, for use on the flightline, are shown in table 5-2. These procedures will that the system is functional. If a failure is detected or suspected because of pilot complaint or other evidence, the fault isolation procedures in table 5-5 provide more detailed testing and LRU performance analysis.
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Table 5-2. Transponder System, Flightline Test Procedures.
TEST
1.
PROCEDURE
Setup:
DESIRED RESULT
TROUBLESHOOTING INSTRUCTIONS
Prepare the airplane and transponder system for testing as required. As a minimum this will require: • Be sure that the air/ground test inhibit, if used, is functional. P2-53 must be grounded to allow a manual self-test. • Set altimeter system(s) for a test altitude (consult airplane manual for necessary procedures) especially as may be required for TCAS if used. • Setup IFR ATC-601 Ramp Tester and perform the necessary preliminary tests for it. • If the broadcast method of testing will be used with the ATC-601 (or equivalent) ramp tester and the installation consists of a TDR-94D diversity transponder install an rf boot over the top antenna. If the direct connection is being used, disconnect both antenna cables from the transponder mount, connect the ATC-601 to the lower antenna connector and install an rf load on the upper connector. Note: If the transponder installation makes the direct connection method quite difficult, the broadcast method should be seen as preferred unless initial tests suggest an advantage in favor of direct connection.
2.0
Inspection:
Before applying power to the transponder system, make a visual inspection of the transponder antenna(s), ATC control, and the r/t. Be sure the r/t is firmly seated in its mount and there are no obvious signs of a dysfunctional installation. If it is possible, check the antenna cable connections on the back of the transponder for tightness and the wire harness for obvious signs of broken wires or dislodged connector pins.
3.0
Power application: Apply power to the transponder system. Enter an appropriate code into the control and set for normal operation.
Normal operation: In the case of the IFR ATC-601, the INTERR and REPLY indicators should both be lit.
5/5/1993
If the installation is equipped with a CTL-92/92A -2XX control, "diAG" may be displayed in the lower window if a diagnostic is detected. It is necessary, then, to press TEST to display the diagnostic code.
If the broadcast method of testing is being used with the ATC-601, avoid use of an emergency ident code (consult the airplane manual if you are unsure). If the INTERR lamp does not light, the ramp tester is not functioning properly. If the REPLY lamp does not light, the transponder is not responding. Check for possible ground operation inhibits.
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Table 5-2. Transponder System, Flightline Test Procedures.
TEST
4.0
PROCEDURE
Self Test: Press the ATC TEST button on the ATC control. Note: The installation may feature a remote ATC TEST button in which case use it instead.
DESIRED RESULT
TROUBLESHOOTING INSTRUCTIONS
If the installation uses an ATC control head other than the CTL-92/92A or RTU-870A/T, you may need to consult the airplane manual to determine where the ATC self test results are displayed and in what format any diagnostics are disclosed. Test results should not show any diagnostic other than 00 (no faults detected). In the case of the CTL-92/92A , the diagnostics are displayed on the control.
See table 5-3 for an interpretation of the diagnostic code.
A normal indication on the CTL-92/92A is: • The active code display intensity modulates from minimum to maximum. • On all CTL-92/92A controls: • "AL" is displayed in the upper window and the altitude in thousands of feet in 100-foot increments is displayed in the lower window. • If a diagnostic condition is detected, the upper window shows "dIAG" and the two-digit diagnostic code is displayed in the lower window. Refer to table 5-3 for a listing of the codes, and table 5-4 for an interpretation and explanation of each. 5.0
Auto Test: Select AUTO TEST on the IFR ATC-601 and press RUN.
All AUTO TEST items should indicate ED. This test takes about 30 seconds to complete. Note: It is possible that tests 13, 14, and 15 indicate FAILED. These items are a function of datalink capabilities and may not be implemented in which case you can ignore this failure indication.
Successful completion of tests ing these items, and no other indication of failure (like pilot or ATC complaints), indicates a functional transponder.
If there is a substantial difference in receiver sensitivity and/or power output, it may be caused by a faulty antenna, antenna cable, or connector installation. In this case, inspection and repair of the antennas, cables, or cable connectors is needed.
Otherwise, a failure of any one or more of the items, may indicate a performance problem. In this case, consider removing the transponder for additional analysis and repair on the bench.
6.0
Opposite antenna test: If the direct connection method is being used, switch the test set cable to the other antenna port. If the broadcast method is being used, move the rf boot to the top (or opposite) antenna connector and repeat the test.
The test results should be approximately equivalent between the two antenna test.
7.0
Equipment removal and restoration:
Restore all equipment to its normal ground operating configuration. Return the test set to its normal storage location. Careful handling and storage of all ramp test equipment prolongs the service life and reduces maintenance costs.
5/5/1993
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maintenance 523-0775657
Table 5-3. TDR-94/94D Diagnostic Codes
PRIMARY CODE
SECONDARY CODE
DESCRIPTION
DIAGNOSTIC DISPLAY
TI
F/W
00
No fault found
10
Power supply diagnostics
(1)
(1)
11
+5 V dc
Yes
Yes
12
+70 V dc
No
No
13
+35 V dc
No
No
14
LVPS
No
No
Transmitter/modulator diagnostics
(2)
(2)
21
Final stage, overcurrent
Yes
Yes
22
Top antenna, low power output
No
No
23
Bottom antenna low power output
No
No
24
Transmitter overtemperature
No
No
Synthesize diagnostics
No
No
31
Synthesizer lock detect
No
No
32
Synthesizer low power detect
No
No
Receiver/IF diagnostics
No
No
41
Top receiver channel
No
No
42
Bottom receiver channel
No
No
43
Top DPSK demodulator
No
No
44
Bottom DPSK demodulator
No
No
Program memory (ROM) diagnostics
Yes
Yes
51
High-byte ROM
Yes
Yes
52
Low-byte ROM
Yes
Yes
53
Both ROM chips
Yes
Yes
Volatile memory (RAM) diagnostics
Yes
Yes
High-byte RAM
Yes
Yes
20
30
40
50
60 61
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PRIMARY CODE
60 (cont’d)
SECONDARY CODE
DESCRIPTION
DIAGNOSTIC DISPLAY
TI
F/W
62
Low-byte RAM
Yes
Yes
63
Both RAM chips
Yes
Yes
64
Cache RAM
Yes
Yes
65
Cache RAM and high-byte RAM
Yes
Yes
66
Cache RAM and low-byte RAM
Yes
Yes
67
Cache RAM and both RAM chips
Yes
Yes
68
Dual port RAM
Yes
Yes
70
Nonvolatile memory (NVRAM)diagnostics
No
No
80
Serial input control bus diagnostics
(4)
No
81
ARINC 429 control UART
(4)
No
82
ARINC 429 control port A inactive
(4)
No
83
ARINC 429 control port B inactive
(4)
No
84
ARINC 429 control port C inactive
(4)
No
85
CSDB control input port A inactive
(4)
No
Serial altitude input diagnostics
No
No
91
ARINC 429/575 altitude UART
No
No
92
ARINC 429/575 input port A inactive
No
No
93
ARINC 429/575 input port B inactive
No
No
94
CSDB altitude input port A inactive
No
No
95
CSDB altitude input port B inactive
No
No
ADLP communication diagnostics
No
No
A1
ADLP comm A/B UART
No
No
A2
ADLP comm A/B bus inactive
No
No
A3
ADLP comm C/D UART
No
No
A4
ADLP comm C/D bus inactive
No
No
TCAS communication diagnostics
No
No
B1
TCAS UART
No
No
B2
TCAS unit
-
-
B3
TCAS bus inactive
No
No
B4
TCAS protocol error
No
No
Squitter diagnostics
No
Yes
C1 (TDR-94D only)
Top channel squitter
No
Yes
C2 (TDR-94D only)
Bottom channel squitter
No
Yes
90
A0
B0
C0
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PRIMARY CODE D0
SECONDARY CODE
DESCRIPTION
DIAGNOSTIC DISPLAY TI
F/W
Diversity diagnostic
No
Yes
Message processor diagnostics
No
No
E1 (TDR-94D only)
Top channel message processor, soft failure
No
No
E2
Bottom channel message processor, soft failure
No
No
E3
Top channel message processor, hard failure
Yes
Yes
E4
Bottom channel message processor, hard failure
Yes
Yes
Configuration diagnostics
No
No
F1
Mode S discrete address changed
No
No
F2
TCAS selection changed
No
No
F3
Altitude units selection changed
No
No
F4
Max airspeed program selects changed
No
No
F5
Port selects changed
No
No
F6
SDI selects changed
No
No
F7
Single antenna selection changed
No
No
F8
ADLP selection changed
No
No
F9-FE
(not assigned)
FF
Unacceptable mode s address selected (address lines are all 0 or all 1)
Yes
Yes
(TDR-94D only)
E0
F0
Notes: (1) (2) (3) (4) (5)
1
Except for 00, 70, and D0, primary diagnostics are not displayed. Transmitter is inhibited (TI) and failure warn (F/W1) output (P1-31) is set only if a diagnostic code 11 is detected. Transmitter is inhibited and F/W1 discrete is set only if a diagnostic code 21 is detected. Transmitter is inhibited and TDR-94/94D is set to standby only if all selected control inputs are nonfunctional. Transmitter is inhibited and TDR-94/94D is set to standby only if the control bus failure is detected on the selected control bus. Transmitter is inhibited and TDR-94/94D is set to standby only if serial control is selected and all serial inputs are nonfunctional.
"F/W set" here refers to: a. TDR-94/94D fault monitor discrete output, P1-31, set to high level, b. TDR-94/94D CSDB data word label 1F, byte-1, bit-7, set to logic 0, and c. TDR-94/94D ARINC 429 SSM and other data bits related to diagnostics set to the appropriate fault level.
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Table 5-4. TDR-94/94D Diagnostic Code Description and LRU Disposition
Diagnostic Code
Title
Description and LRU Disposition
For purposes of this diagnostic code interpretation and for the sake of brevity, the following fault levels are defined: Level 1: A level 1 fault is defined as one in which the TDR-94/94D should be removed for further testing or fault isolation on the bench. Level 2: A level 2 fault is defined as one in which the TDR-94/94D is demonstrating a failure which may not prevent it from performing continued but temporary service. That is, a diagnostic which indicates a failure in a peripheral function. For example, a diagnostic code A? indicating an ADLP fault. If an ADLP is not being used in the installation the transponder may operate normally in its other functions. Level 3: A level 3 fault is defined as one in which the TDR-94/94D has experienced a change in the installation, i.e., external to the TDR-94/94D. In this case, further analysis is needed to correct or restore the installation as needed. For example, a diagnostic code F4 indicating a change in the max airspeed strapping. This strongly suggests an airplane wiring problem. Reference to a failure warning indication should be understood to be the flag. 00
No fault found
This code indicates that no failure was detected during the most recent self test routine.
11
+5 V dc
Level 1. This diagnostic code is typically accompanied by a failure warning indication. It is caused by a out-of-tolerance condition in the +5 V dc power supply.
12
+70 V dc
Level 1. Same as 11 except that it applies to the +70 V dc supply on hvps module A1.
13
+35 V dc
Level 1. Same as 11 except that it applies to the +35 V dc supply on hvps module A1.
14
LVPS
Level 1. Same as 11 except that it applies to the low voltage power supply on module A7.
21
Transmitter/modulator, final stage, overcurrent
Level 1. This diagnostic code is typically accompanied by a failure warning indication. It is caused by a sensed high current condition in the final transmitter stage. This may be accompanied by a diagnostic code 24.
22
Top antenna low power output
Level 1 if verifiable, otherwise level 2. This diagnostic code is typically not accompanied by a failure warning indication. It is caused by a sensed low power output condition at the top antenna output final stage. This may be verifiable in the ATC-601 test. This diagnostic will not occur on a TDR-94 (non-diversity) unit.
23
Bottom antenna low power output
Same as 22 except that it applies to the bottom antenna output port.
24
Transmitter over temperature
Level 1. The same as 21 except that it is caused by a high temperature condition.
31
Synthesizer lock detect
Level 1. This diagnostic code is typically not accompanied by a failure warning condition and occurs when the synthesizer output frequency does not agree with the processor command. This condition may be verifiable in the ATC-601 test as a transmitter off frequency failure.
32
Synthesizer low power detect
Level 1. Much the same as 31 except that it applies to the synthesizer output level. A sufficiently low output may prevent the modulator, and hence the transmitter or receiver, from operating.
Top receiver channel
Level 2. This diagnostic code is typically not accompanied by a failure warning condition and occurs when the top receiver channel does not respond properly to a simulated test signal generated by the bottom channel receiver. It is possible that the bottom channel may still be functional. Neither diagnostic 41, 42 or 43 occur on a TDR-94. * See the note 1 at the end of this table
41 *
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Table 5-4. TDR-94/94D Diagnostic Code Description and LRU Disposition
Diagnostic Code 42 *
Title
Description and LRU Disposition
Bottom receiver channel
Level 2. Same as 41 except that the channel roles are reversed. See note 1 at the end of this table.
43
Top DPSK demodulator
Level 1. This diagnostic code is typically not accompanied by a failure warning condition and occurs when the top DPSK demodulator does not respond properly to a simulated mode s test signal. It is possible that the unit may still respond properly to ATCRBS (mode A and C) interrogations. * See the note at te end of this table.
44
Bottom DPSK demodulator
Level 1. Same as 43 except that it applies to the bottom channel.
51
High-byte ROM
Level 1. This diagnostic code is typically accompanied by a failure warning condition. During self-test the microprocessor executes a memory modulo 64K summation of all memory locations and compares that result against a stored check-sum value. This diagnostic indicates that the high-byte ROM failed that comparison test.
52
Low-byte ROM
Level 1. Same as 51 except that the low-byte ROM failed the test.
53
Both ROM chips
Level 1. Same as 51 except that both ROMs failed the test.
61
High-byte RAM
Level 1. This diagnostic code is typically accompanied by a failure warning condition. During self-test the microprocessor executes a read/write test on all available volatile RAM locations using AAAAH and 5555H data. This diagnostic indicates that one or more high-byte RAM device failed this test.
62
Low-byte RAM
Level 1. Same as 61 except that the low-byte RAM device failed the test.
63
Both RAM
Level 1. Same as 61 except that both RAM device failed the test.
64
Cache RAM
Level 1. Same as 61 except that the cache RAM failed the test.
65
Cache and highbyte RAM
Level 1. Same as 61 except that both the high-byte RAM (61) and cache RAM (64) failed the test.
66
Cache and low-byte RAM
Level 1. Same as 61 except that both the low-byte RAM (62) and cache RAM (64) failed the test.
67
Cache and both RAM
Level 1. Same as 61 except that both RAM (63) and cache RAM (64) failed the test.
68
Dual port RAM
Level 1. Same as 61 except that the dual port RAM failed the test.
70
NVRAM
Level 1. This diagnostic code is typically not accompanied by a failure warning condition. During power-up the microprocessor executes a read/write test on the last 16 bytes of the NVRAM to proper operation. This diagnostic indicates that the NVRAM failed that test.
81
ARINC 429 UART
Level 1. This diagnostic code is typically not accompanied by a failure warning condition. During self-test, the microprocessor forces the output from all serial control UARTs to to the input. The microprocessor verifies that the UART processes this ARINC word properly. This diagnostic indicates that the ARINC 429 UART failed this test.
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Table 5-4. TDR-94/94D Diagnostic Code Description and LRU Disposition
Diagnostic Code
Title
Description and LRU Disposition
82
ARINC 429 control port A inactive
Level 2. This diagnostic code is typically not accompanied by a failure warning condition. During normal non-burst mode operation, the microprocessor periodically monitors the selected serial ports for bus activity. During burst mode, this test is not performed because there is no way of predicting the arrival of control data. This diagnostic code indicates that ARINC 429 control port A has no bus activity for at least 1-second.
83
ARINC 429 control port B inactive
Level 2. Same as 82 except that it applies to ARINC 429 control port B.
84
ARINC 429 control port C inactive
Level 2. Same as 82 except that it applies to ARINC 429 control port C.
85
CSDB control port A inactive
Level 2. Same as 82 except that it applies to CSDB control port A. Monitor time is extended to 2-seconds.
86
CSDB control port B inactive
Level 2. Same as 85 except that it applies to CSDB control port B.
91
ARINC 429/575 altitude UART
Level 2. Same as 81 except that it applies to the ARINC 429/575 altitude UART.
92
ARINC 429/575 altitude input port A
Level 2. This diagnostic code is typically not accompanied by a failure warning condition. During normal operation, the microprocessor periodically monitors the selected altitude input ports for bus activity. This diagnostic code indicates that ARINC 429/575 altitude input port A has no bus activity for at least 2-seconds.
93
ARINC 429/575 altitude input port B
Level 2. Same as 92 except that it applies to ARINC 429/575 altitude input port B.
94
CSDB altitude input port A
Level 2. Same as 92 except that it applies to CSDB altitude input port A.
95
CSDB altitude input port B
Level 2. Same as 92 except that it applies to CSDB altitude input port B.
A1
ADLP comm A/B UART
Level 2. This diagnostic code is typically not accompanied by a failure warning condition. During power-on self-test and whenever a comm A/B bus failure is suspected, the microprocessor forces the UART output to to the input and verifies that the UART processes the data properly. This diagnostic code indicates that ADLP comm A/B UART failed the test.
A2
ADLP comm A/B input port
Level 2. This diagnostic code is typically not accompanied by a failure warning condition. The determination of a failure in this function involves a highly complicated exchange between data link transmitters and receivers involving data word check-sums and parity checks. This diagnostic code results after repeated attempts to establish a reliable communications link fail. The failure should be verifiable in the ATC-601 tests 9 through 15.
A3
ADLP comm C/D UART
Level 2. Same as A1 except that it applies to ADLP comm C/D UART.
A4
ADLP comm C/D input port
Level 2. Same as A2 except that it applies to ADLP comm C/D input port.
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Table 5-4. TDR-94/94D Diagnostic Code Description and LRU Disposition
Diagnostic Code
Title
Description and LRU Disposition
B1
TCAS UART
Level 2. This diagnostic code is typically not accompanied by a failure warning condition. Whenever a TCAS is selected and a bus failure is suspected, the microprocessor forces the UART output to to the input and verifies that the UART processes the data properly. This diagnostic code indicates that TCAS UART failed the test.
B2
TCAS unit failure
Level 3. This diagnostic code is typically not accompanied by a TDR-94D failure warning condition. This diagnostic code indicates that TCAS operation is selected and a TCAS unit failure warning has been received. The TCAS unit should be indicating a failure warning.
B3
TCAS bus inactive
Level 2. This diagnostic code is typically not accompanied by a failure warning condition. When TCAS is selected, the microprocessor periodically monitors the TCAS input port for bus activity. This diagnostic code indicates that the TCAS input port is inactive, or fails to meet certain parity, rate, and status conditions, for a time exceeding the normal update rate which varies according to the type of data to be exchanged.
TCAS protocol error
Level 2. This diagnostic code is typically not accompanied by a failure warning condition. This diagnostic code indicates that the TCAS data being received does not comply with the required protocol. * See the note 2 at the end of this table.
C1
Top channel squitter (TDR-94D only)
Level 1. This diagnostic code is typically accompanied by a failure warning condition and indicates that the top channel squitter function is not functioning properly.
C2
Bottom channel squitter
Level 1: Same as C1 except that it applies to the bottom channel.
D0
Diversity (TDR94D only)
Level 1. This diagnostic code is typically accompanied by a failure warning condition and indicates an inability to exchange data between the top and bottom channel as described for diagnostic 41 and 42 and others below.
E1
Top channel message processor
This diagnostic code without an accompanying E3 diagnostic code is typically not accompanied by a failure warning condition. During self test the bottom channel PAM is preloaded to generate an ATCRBS or mode s interrogation which is injected into the top channel for processing. If the message is not properly processed an E1 diagnostic code is recorded and the process is repeated. If the failure occurs on three consecutive attempts, an E3 diagnostic code is recorded. An E3 diagnostic code is typically accompanied by a failure warning condition. Therefore, an E1 diagnostic code without an accompanying E3 diagnostic code can be ignored unless a pattern is detected which may indicate a marginal condition.
E2
Bottom channel message processor
Same as E1 except that it applies to the bottom channel message processor.
E3
Top channel hard message processor
Level 1. See E1 above.
E4
Bottom channel hard message processor
Level 1. Same as E3 except that it applies to the bottom channel message processor.
B4 *
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Table 5-4. TDR-94/94D Diagnostic Code Description and LRU Disposition
Diagnostic Code
Title
Description and LRU Disposition
F1
Mode s discrete address changed
Level 3. This diagnostic code is typically not accompanied by a failure warning condition and indicates that one or more of the mode s address straps has changed since the previous power-up. These straps are monitored only during power-up. If the straps change during a flight leg, the condition will not be detected until the next power-up.
F2
TCAS selection changed
Level 3. Same as F1 except that it applies to the TCAS selection strap.
F3
Altitude units selection changed
Level 3. Same as F1 except that it applies to the altitude units (metric or decimal ) selection strap. (At the time of this publication, this function has not been implemented.)
F4
Max airspeed programs selects changed
Level 3. Same as F1 except that it applies to the max airspeed straps.
F5
Control port selects changed
Level 3. Same as F1 except that it applies to the control port select straps.
F6
SDI selects changed
Level 3. Same as F1 except that it applies to the SDI select straps.
F7
Single antenna select strap changed
Level 3. Same as F1 except that it applies to the single antenna select strap.
F8
ADLP selection changed
Level 3. Same as F1 except that it applies to the ADLP select strap.
FF
Unacceptable address
Level 3. This diagnostic code occurs when an unacceptable mode s address strapping is detected; e.g., all straps open or all straps shorted to ground. This can occur if the strapping plug is removed or the common line has opened.
Note 1: Several of these diagnostic codes may be seen in a diagnostic data . In most cases they can be ignored. If, however, one remains for an extended period (more than 1 or 2 seconds) during manual self-test, the unit should undergo more detailed testing. Explanation: During self-test (automatic and manual) a simulated interrogation signal is generated in one receiver (call this the sending receiver) and is injected into the opposite receiver (call this the target receiver). If the target receiver does not return a proper response, the appropriate diagnostic is recorded. Scenario: If a valid interrogation arrives in the target receiver at the same time as or slightly ahead of the test signal, it will respond to the valid interrogation and therefore fail the test evaluation. Because the test signal is automatically generated at least once per second, the probability of this scenario occurring is rather high and increases as a function of the interrogation rate. If the valid interrogation arrives at the sending or target receiver during the time this test sequence is in process, the unit will simply not respond to the interrogation. This will most likely be unnoticed. Note 2: The B4 diagnostic may be seen repeatedly in a diagnostic data . From the point of view of the transponder and if it is not accompanyed by a TCAS FAIL on the TCAS display, it can be ignored. Explanation: The B4 diagnostic can occur because of an incompatibility between the TCAS and transponder protocols as defined in the respective MOPS (Minimum Operating Performance Standards).
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maintenance 523-0775657 5.4.4 Flightline Fault Isolation Procedures This paragraph provides procedures for isolating a transponder equipment malfunction to a particular LRU. The procedures in table 5-5 require the use of a test , ramp tester, dvm, and a data bus reader/simulator.
Table 5-1 lists the various units which can be used. Other similar units may become available which also can be used provided the capabilities are similar to those listed. Refer to figure 5-1 for the test setup diagram.
Flightline Fault Isolation, Test Setup Diagram Figure 5-1
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Table 5-5. Transponder System, Flightline Fault Isolation Procedures.
TEST
1.0
PROCEDURE
Setup: If this is a continuation of table 5-2, skip to step 7.
DESIRED RESULT
TROUBLESHOOTING INSTRUCTIONS
Prepare the airplane and transponder system for testing as required. As a minimum this will require: • Be sure that the air/ground test inhibit, if used,is functional. P2-53 must be grounded to allow a manual self-test. • Set altimeter system(s) for a test altitude (consult airplane manual for necessary procedures) especially as may be required for TCAS, if used. • Setup IFR ATC-601 Ramp Test Set (or equivalent) and perform the necessary preliminary tests for it. • If the broadcast method of testing will be used with the ATC-601 Ramp Test Set, and the installation consists of a TDR-94D diversity transponder, install an rf boot over the top antenna. If the direct connection is being used, disconnect both antenna cables from the transponder mount, connect the ATC-601 to the lower antenna connector and install a load on the upper connector. Note: If the transponder installation restricts use of the direct connection method, the broadcast method should be used unless or until tests indicate the need for direct connection.
2.0
Inspection:
Before applying power to the transponder system, make a visual inspection of the transponder antenna(s), ATC control, and the r/t. Be sure the r/t is firmly seated in its mount and there are no obvious signs of loose or damaged system components. If it is possible, check the antenna cable connections on the back of the transponder for tightness and the wire harness for obvious signs of broken wires or dislodged connector pins.
3.0
Power application: Apply power to the transponder system. Enter an appropriate code into the control and set for normal operation.
At power-up, you may see diAG along with a diagnostic code number. These random indications should be ignored. You should be concerned primarily with those diagnostics that persist.
4.0
Self Test:
If the installation uses an ATC control head other than the CTL-92/92A, you may need to consult the airplane manual to determine where the ATC self test results are displayed and in what format any diagnostics are disclosed. Test results should not show any diagnostic other than 00 (no faults detected). In the case of the CTL-92/92A units, the diagnostics are displayed on the control.
4.1.a.
Self-test display on CTL92/92A: Press the ATC TEST button on the ATC control. Note: The installation may feature a remote ATC TEST button in which case use it instead. If the CTL-92/92A has a 1/2 switch (dual transponder control), set the 1/2 switch to 2 and repeat the test.
A normal indication on the CTL-92/92A is: • The active code display intensity modulates from minimum to maximum. • On any CTL-92/92A controls with N ending in other than -2XX: • If an altitude encoder is connected to the control and operating, "AL" is displayed in the upper window and the altitude in thousands of feet in 100-foot increments is displayed in the lower window. • If altitude data is not being supplied to the control, "AL" is displayed in the upper window and the lower window remains "-------". • If a diagnostic condition is detected, the upper window shows "dIAG" and the two-digit diagnostic code is displayed in the lower window. Refer to table 5-3 for a listing of the codes, and table 5-4 for an interpretation and explanation of each.
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See table 5-3 for an interpretation of the diagnostic codes and table 5-4 for disposition of LRU.
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Table 5-5. Transponder System, Flightline Fault Isolation Procedures.
TEST
PROCEDURE
DESIRED RESULT
TROUBLESHOOTING INSTRUCTIONS
4.1.b.
Self-test display on RTU870A/T: Select the ATC page and press the ATC test key.
A normal indication on the RTU-870/870A is (top to bottom): • Upper window: ON ALT • Second window: XXXXX FT • Third window: (not used) • Fourth window: TST • Lower window: (ATC code)* RTN
4.1.c.
ATC self-test display for systems using the TTC-920G, CTL-92T, or other type of ARINC 429 transponder / TCAS control. Press the TEST button on the control.
Consult the airplane manual for the location and format of transponder and TCAS self-test display, especially the display of any possible ATC diagnostics.
5.0
Setup the ATC-601 for AUTO TEST and select RUN.
All AUTO TEST items should indicate ED. This test takes about 30 seconds to complete. Note: It is possible that tests 13, 14, and 15 indicate FAILED. These items are a function of datalink capabilities and may not be implemented in which case you can ignore this failure indication.
Otherwise, a failure of any one or more of the items, may indicate a performance problem. In this case, consider removing the transponder for additional analysis and repair on the bench.
6.0
Opposite antenna test: If the direct connection method is being used, switch the test set cable to the other antenna port. If the broadcast method is being used, move the rf boot to the top (or opposite) antenna connector and repeat the test.
The test results should be approximately equivalent between the two antenna test.
If there is a substantial difference in receiver sensitivity and/or power output, it may be caused by a faulty antenna, antenna cable, or connector installation. In this case, inspection and repair of the antennas, cables, or cable connectors is needed.
Successful completion of all tests to this point verifies a functional transponder system unless there are other indications of failure (like pilot or ATC complaints). If any test(s) failed or if you need added assurance, continue with the fault isolation procedures below. These procedures will help you isolate a failure between the control(s) and the transponder unit. The steps that follow require the use of a flightline test and bus reader. This allows access to the data busses for detailed fault isolation and data analysis. The test is described in paragraph 5.9. Refer to figure 5-1 for a diagram of the setup needed for this procedure. If you choose to continue in this series, you should feel free to pick any or all of the tests as seems necessary depending on the suspected failure. The sequence of tests given is not important. For example, if the self-test test failed to produce any results, you should perform the Self-test switch test 9.2.1. to be sure that self-test is being commanded properly.
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Table 5-5. Transponder System, Flightline Fault Isolation Procedures.
TEST
PROCEDURE
7.0
LRU fault isolation:
7.1 Setup
IF POWER IS ON, TURN POWER OFF TO THE TRANSPONDER (AND TCAS SYSTEM IF USED) Remove the control from its location and install the flightline test and appropriate cable. Connect the control to the test mating connector. Set all test data bus switches to MON. Connect the compatible data bus reader RX terminals to the test OUT terminals. If your bus reader has a second RX port, connect it to the test IN terminals. Set the ATC-601 for ATCRBS REPLY TEST
8.0 Code verification
Normal operation test: Turn power on to the system, and set the control for 2150 or any ATCRBS code (avoid the emergency codes). Set for normal operation. Read the appropriate label as shown ---->.
DESIRED RESULT
TROUBLESHOOTING INSTRUCTIONS
Flightline Test installation: • If you are connecting the test between a CTL-92/92A and the airplane wiring (with no CTL-92T; i.e., a non-TCAS installation) you will need a CSDB reader/simulator like the DataTrac 200. • If you are connecting the test between the CTL-92/92A and the airplane wiring which uses a CTL-92T (i.e., a TCAS installation), you will need a CSDB reader/simulator like the DataTrac 200 to monitor/simulate the CSDB data between the CTL-92/92A and the CTL-92T, and the CSDB data from the TDR-94D. • If you are connecting the test between the Gables 816 Control, the CTL-92T Transponder/TCAS Control, TTC-920G Transponder/TCAS Control, or an RTU-870A/T Radio Tuning Unit and the airplane wiring, you will need an ARINC 429 reader/simulator. Note: Do not connect the bus reader TX port to the test OUT terminals while the control is also connected and operating, unless you set the corresponding test switch to EXT INPUT. The test IN and OUT bus terminal labeling is with reference to the control. That is, OUT is data being transmitted OUT from the control, while IN is data being received by/into the control. Placing the corresponding switch to the EXT INPUT position disconnects the source so that external data can be injected without interference. You can always connect the bus reader RX to either the IN or OUT terminals to monitor the source of that particular data (test switch in the MON position). Note that the bus reader shows the correct data. Control
Word Format/Label
CTL-92/92A CSDB/1E CTL-92T ARINC 429/031 RTU-870A/T ARINC 429/031 TTC-920G ARINC 429/031 X = any octal character
Bus Reader ATC-601 RX 1 (Note 1) CODE= 2150 (Note 1) CODE= 2150 (Note 1) CODE= 2150 (Note 1) CODE= 2150
Bus Reader RX 2 (Note 2) (Note 2) (Note 2) (Note 2)
Note 1: This is the data being transmitted by the control. ( , the CTL-92/92A input/output is CSDB data. In all other controls the data is ARINC 429.) CSDB (CTL-92/92A): DataTrac 200: ARINC 429: DataTrac (all): JcAIR 429E:
LBL 7-STAT-0 1E 00011111
HEX-XMT-DATA 21 50 24 10
MSEC 0100
LBL SI 29-HEX-XMT-11 SM P MSEC 031 01 21 50 XX XX 00 1 0100 031 01 142211 00
Note 2: This is data being returned by the transponder. CSDB : DataTrac 200:
LBL 7-STAT-0 1F 00011111
HEX-RCV-DATA 21 50 24 11
ARINC 429: DataTrac (all): LBL SI 29-HEX-RCV-11 031 01 21 50 XX X JcAIR 429E:
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MSEC 0100
SM P MSEC 11 1 0100
031 01 142211 11
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Table 5-5. Transponder System, Flightline Fault Isolation Procedures.
TEST
8.1 Ident
PROCEDURE
ATC code test: Press IDENT on the control head or on the test .
DESIRED RESULT
TROUBLESHOOTING INSTRUCTIONS
A normally operating transponder should transmit the IDENT code for about 18 seconds (18 ± 1 s) and then stop. During that time the ATC-601 shows CODE=ID2150; the CODE preceded by "ID". If the CODE being displayed on the ATC-601 is not the same as the code you entered on the control head recheck your setup to be certain of the code that you are supplying. The code being supplied and displayed is entirely a software function and therefore is highly unlikely of failure.
Note: When the TDR-94/94D first begins transmitting the IDENT code, the ATC-601 displays: CODE=ID2150. After about 18 seconds (18 ± 1) the ID portion disappears but the code number remains. If IDENT was last commanded by way of a digital word it is necessary to transmit a new digital word with the IDENT bit reset (bit 13 = 0) before IDENT can be commanded again either by way of the digital word or by a discrete command. If you use the IDENT button on the control head, the unit will be automatically reset. 9.0
Altitude Test: Altitude information can be supplied to the transponder in a number of formats: a. ARINC 429, b. ARINC 575, c. CSDB, or d. ARINC 572 (Gillham code); paragraph 5.7 provides encoding and decoding information for Gillham code. In a TCAS installation and if the altitude source is a system using the Gillham code, two sources of altitude data are required. One source is connected directly to the transponder while the other is connected to the CTL-92/92A control. In the control the Gillham data is converted to CSDB and supplied to the CTL-92T where it is converted to ARINC 429 and supplied to the transponder. In the transponder the two sources are compared. If they do not agree within 500-ft, the transponder will set the altitude word SSM output to NCD (No Computed Data). If the altitude system is one of the first three listed, the data is supplied directly to the transponder. One or two altitude sources may be used. In either case they are connected directly to the transponder. In non-TCAS installations using a CTL-92/92A control, i.e., no CTL-92T, typically the altitude data is supplied directly to the transponder. It is possible, however, that the Gillham code can also be supplied to the CTL-92/92A. In this case it is supplied to the transponder as CSDB altitude data.
10.0
Power Test: Connect the dvm to the appropriate power terminals on the test .
11.0
Self-test switch verification: Self-test can be initiated in the transponder with either of two inputs; discrete or digital. In most installations the discrete input to the transponder is not used. In step 4.0 above, self-test was initiated digitally. Therefore, if step 4.0 was successful, there is very little to be gained by performing this step. If it failed, however, step 11.1 below provides instructions for verification of the self-test switch by monitoring the control internal switching function. If the control does not have a discrete self-test input/output, or if it does not have a self-test switch, step 11.1 cannot be performed.
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The TTC-920G uses 115 V ac , 400 Hz, power, all others use +28 V dc. Allow ± 10% for 115 Vac or ± 15% for 28 V dc.
If the power is not correct, repair airplane wiring or power source as needed.
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Table 5-5. Transponder System, Flightline Fault Isolation Procedures.
TEST
11.0 (cont ’d)
PROCEDURE
DESIRED RESULT
TROUBLESHOOTING INSTRUCTIONS
Step 11.2 is using the bus simulator to monitor the digital output from the control and then to generate a digital self-test command. If step 4.0 above failed, you can perform step 11.2. If the control output is not correct (i.e., the test bits do not change) the probable cause of failure is in the control. If the transponder still does not respond correctly when a simulated self-test word is injected, the failure appears to be in the transponder. Step 11.2 also provides instructions to monitor the from the transponder to the control. In the case of CSDB data, the word label is 1F. In ARINC 429 the word label is the same as the control word label; 031. When the transponder is replying to interrogations, the SSM is set to 11. Otherwise it is the same as the control word.
11.1
Self-test switch test. Connect the dvm to the TEST terminal on the test [ref to COMM or 28V (-)]. Press TEST on the control (or remote switch if used - not the switch on the test .)
Dvm shows +5 Vdc (± 1) when no TEST switch (either on the control, test , or elsewhere), is pressed. Dvm shows less than +3 V dc when any TEST switch is pressed.
11.2
Control output test: With the bus reader RCV connected to the test OUT terminals and the corresponding switch set to MON, you should see the test bits change when you press the TEST switch. Self-test using bus simulator: If there is no response, connect the bus reader XMT to the OUT terminals on the test . Set the corresponding test switch to EXT INPUT and set the bus reader as shown --->.
CSDB (CTL-92/92A): DataTrac 200: ARINC 429: DataTrac (all) *
JcAIR 429E: (TX)
If +5 V dc voltage is not correct, or is correct but does not change when the switch is pressed, the fault appears to be in the control and it should be removed for further testing on the bench.
LBL 7-STAT-0 HEX-XMT-DATA 1E 10000101 21 50 24 10 |<---test bit LBL SI 29-HEX-XMT-11 031 01 21 50 XX X1
MSEC 0100
SM P MSEC 01 1 0100 ||<--test command
031 01 142211 01 ||<--test command
* Recognize that the column headers are slightly different between the DataTrac 200 and the DataTrac 400/400H.
In the first part of this test, the control output should be as shown above. In the second part of this test, the transponder should respond to the simulated self-test command. Be sure to set the data back to normal (non-test) after the self-test sequence. As a further verfication of inter-unit communication, you can connect the bus reader RCV to the test IN terminals and set the corresponding switch to MON. This will allow you to monitor the data from the transponder to the control. You should see the test bits change when you press the test switch when the self-test command is transmitted. If so, this verifies that the transponder is receiving the command properly. It is highly unlikely, however, that the transponder can provide a proper without properly executing a self-test command.
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Table 5-5. Transponder System, Flightline Fault Isolation Procedures.
TEST
PROCEDURE
DESIRED RESULT
TROUBLESHOOTING INSTRUCTIONS
Note: The remainder of this procedure consists of explanatory information that may be useful for troubleshooting. The test test points labeling reflects the signal or voltage that is found at that point. In most cases, that signal or voltage depends on certain installation options. Therefore, you will need to consult the airplane manual to determine which of those options are active or inactive in your installation. Then use the following procedures to the correctness of the installation. The procedures are separated according to the control present in the installation. CTL92 /92A discretes and etc
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Use a multimeter at the following test test points, connect the reference lead to COMM (P1-s): • DUAL select (P1-m) (-2XX controls only):
Selected = ground Not selected = near +5-V dc (pull-up resistor to +5 V dc internal).
When this pin is grounded the no. 2 CSDB input port is defined as the no. 2 TDR port.
• REMOTE select (P1-K)
Selected = ground Not selected = near +5-V dc (pull-up resistor to +5-V dc internal).
This pin is typically connected to a remote switch labeled REMOTE (or similar). When grounded the CTL-92/92A: • controls are inoperative, • display shows RMT, and • code is determined by the remote tuning device.
• XPDR STBY No. 1 and No. 2 (P1-W and P1-X) (applies only to CTL-92/92A units with 1/2 switch)
P1-W is at ground when 1/2 switch on CTL is in the No. 2 position. Near + 5-V dc when 1/2 switch is in the No.1 position. P1-X is always opposite of P1W.
These pins may be used to operate a relay which controls power to either or both transponders. In this case, the high voltage may be near +28-V.
• XPDR ON/OFF, No. 1 and No.2 (P1-B and P1-C).
These two pins are identical and at ground when the CTL function switch is at OFF and open otherwise.
These pins are typically connected to the XPDR ON/OFF; no. 1 to the no. 1 transponder, and no. 2 to no.2, in dual installations.
• SW 28 V DC OUT, No. 1 and No. 2 (P1-k and P1-j).
These two pins provide switch +28 V dc output through the control. The outputs are identical and high in all CTL control switch positions other than OFF.
These outputs may be used to switch power to the transponders through an external relay.
• DATA BUS SHIELDS (P1D, P1-L, P1-P, P1-T, and P1V)
Pin P1-D is typically connected to chassis ground. The other are connected to an associated data bus shield. All of these pins are internally connected (within the CTL) to 28-V dc common.
It is important that these pins are properly isolated from either of the two associated data bus lines.
• TEST (P1-E) and IDENT (P1-b)
Both of these pins should reflect a TTL high (near + 5-V dc) when none of the associated switches are depressed and a short to ground when the switch is depressed.
In both cases, the function is activated at the low level. A constant ground (even when the switch is not pressed) should be seen as a failure and will disallow the function.
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Table 5-5. Transponder System, Flightline Fault Isolation Procedures.
TEST
CTL92T discretes and etc
PROCEDURE
DESIRED RESULT
TROUBLESHOOTING INSTRUCTIONS
Use a multimeter at the following test test points, connect the reference lead to COMM (P1/2-32). Strapping Options 1 through 6.
• No. 1 (P1-53):
The airplane manual should reveal those strapping options selected. In all cases, the selected strap should show a short-to-ground while those not selected (open strap) should show a TTL high (near +5-V dc). open = All traffic display, grounded = RA/TA only display selected.
• No. 2: (P1-49) Range select strap:
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• On units with pushbuttons and N ending in 0XX:
• Open = 5/10/20 nmi ranges enabled • Ground = 6/12 nmi ranges enabled
• On units with pushbuttons and N ending in 1XX:
• Open = 40/20/10/5/3 ranges enabled • Ground = 6/12 nmi ranges enabled
• On units without pushbuttons and N ending in 0XX:
• Open = 20 nmi range selected • Ground = 12 nmi range selected
• On units without pushbuttons and N ending in 1XX:
• Open = 5 nmi range selected • Ground = 12 nmi range selected
• No. 3: (P1-52) Relative / Absolute intruder altitude display select:
• Open = intruder altitude displayed as relative to own • Ground = intruder altitude displayed as absolute
• No. 4: (P1-51)
Not used
• No. 5 (P1-47) Serial / Parallel Transponder Control Select
• Open = Serial control selected (CTL-92/92A or ARINC 429) • Ground = Parallel control selected (CTL-90)
• No. 6: P1-24)
Not used
Control Functions:
The airplane manual should reveal the control functions which are active in your installation. Most control functions are intended for use with a parallel ATC control head like the CTL-90.
• ATC SEL IN, No. 1 (P1-19) and No. 2 (P1-18)
P1-18 open open gnd gnd
P1-19 open gnd gnd open
ATC Active or Standby No. 1 & No. 2 in standby No. 1 is active No. 1 is active No. 2 is active
• SW 28 V DC OUT No. 1 (P1-25)
Operable only on units with OFF control switch position. Provides switched +28 V dc output when switch is other than OFF; 1.5 A max, open in OFF position.
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Table 5-5. Transponder System, Flightline Fault Isolation Procedures.
TEST
CTL92T discretes and etc (cont ’d)
PROCEDURE
DESIRED RESULT
TROUBLESHOOTING INSTRUCTIONS
Control Functions (cont’d): • Reply Lamp Hi (P1-33) and Lo (P1-41)
Provides a constant +5 V dc high and switched low output to drive the CTL-90 reply lamp. The lamp lights while the transponder is replying to interrogations.
• ALT REP (Altitude Reporting) (P1-20)
Provides a switched low output to drive the CTL-90 altitude reporting indicator.
• GRAY CODE TUNING (From CTL-90)
These 12 lines are the Gray code tuning lines from the CTL-90. These parallel inputs are translated into ARINC 429 and become the label 031 tuning control output to the transponder (ARINC TO XPDR), P1-5/4 and P1-6/7.
SERIAL DATA INPUT/OUTPUT: • When used with the CTL-92/92A ATC Control
In this application, the inter-unit communication formats are: To CTL-92/92A CSDB
• When used with the CTL-90 ATC Control
From CTL-92/92A To XPDR(s) CSDB ARINC 429
From XPDR(s) ARINC 429
In this application, the inter-unit communication formats are: To CTL-90 *
From CTL-90 **
To XPDR(s) ARINC 429
From XPDR(s) ARINC 429
* Data to the CTL-90 is in the form of discretes: • Reply lamp switching • Altitude reporting lamp switching ** Data from the CTL-90 is in the form of discretes: • Test • Ident • ATC Select, No. 1 and No. 2 • Gray code • When used with an ARINC 429 Control
In this application, the inter-unit communication formats are: To ATC Control ARINC 429
From ATC Control ARINC 429
To XPDR(s) ARINC 429
From XPDR(s) ARINC 429
If all tests ed successfully, restore all equipment to its normal ground operating configuration. Return the test set to its normal storage location. Careful handling and storage of all ramp test equipment prolongs the service life and reduces maintenance costs.
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Table 5-5. Transponder System, Flightline Fault Isolation Procedures.
TEST
RTU870A/T, power and lighting
RTU870A/T, discretes
5/5/1993
PROCEDURE
DESIRED RESULT
TROUBLESHOOTING INSTRUCTIONS
Use a multimeter at the following test test points. Connect the reference lead to the appropriate "L" test point for power measurements, or COMM (P1-53) for signal checks. Discrete ON/OFF: Connect meter + to ON/OFF, meter - to 28 V DC POWER IN L (No. 1 or No. 2)
This input must be low (ground) to enable the RTU. A cross-side switch may be used to select to enable the unit.
28 V dc power input: Connect meter + to: a. 28 V DC POWER IN, NO. 1, H b. 28 V DC POWER IN, NO 2, H
+28 V dc ±5
The No. 1 and No. 2 power inputs are combined (or’d) internally. Therefore, the unit will operate on either.
115 v ac lighting bus: Connect meter + to 115 V AC LIGHTING BUS H and - to L.
115 V ac ± 15
Check 115 V ac lighting supply
28 V dc dimming input: Connect meter + to DIM, - to COMM
28 V dc ± 15, max, depending on dim control setting. If dimming is manually controllable, adjust the DIM control and note that brightness range appears correct.
Check 28 V dimming supply
Discretes:
Note: With the exception of ON/OFF, those test points labeled DISCRETES are all strapping or switching options. You will need to check the airplane manual to determine which options have been selected. In most cases, a high reading is the result of an internal pullup to + 12 V dc and indicates the option is not selected or enabled.
• X-SIDE
This is an output to a cross-side RTU A low output indicates the on-side RTU is on. A high (near + 12 V dc) indicates the cross-side RTU is enabled.
Check RTU
• EDAT (Engine Data Select, RTU-870A only)
This is a reversionary input from an external switch. This should be low (ground) when Engine Data is selected and high (near +12 V dc) otherwise. Engine data information can be monitored at the ARINC 429 ENGINE DATA No. 1 and No. 2, A/B test points.
Check external switch or RTU
• MB (Marker Beacon Sensitivity Select)
This input is normally connected to an external MKR BCN switch. In the HI (high) position this input should be high. In the LO position this input should be low (ground).
Check external switch or RTU.
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Table 5-5. Transponder System, Flightline Fault Isolation Procedures.
TEST
RTU870A/T, discretes (cont ’d)
RTU870A/T, Strappin options
5/5/1993
PROCEDURE
Discretes (cont’d): • ATC 1 (transponder no. 1)
DESIRED RESULT
This input is normally connected to an external ATC (select) switch. A low (near ground) input indicates that transponder no. 1 is selected. A high (+12 V dc pull-up) indicates, no. 2 is selected.
TROUBLESHOOTING INSTRUCTIONS Check external switch or RTU.
• RTU 2
A ground at this point designates this RTU as the no. 2 (co-pilot’s) RTU. An open (near +12 V dc) is no. 1 (pilot’s side).
• REM (remote)
If remote tuning is available, this pin is used to enable the remote tune function. The external REMOTE TUNE switch supplies 28 V dc to this pin when remote tune is enabled. A ground indicates disable.
Check external switch or RTU.
Strapping options: • TST EN (Self test enable)
A switched ground at this input causes the RTU to turn on all display segments and indicators (DME HOLD and REPLY). It also transmits the following data word on the ARINC 429 data bus: 1. Diagnostic label 350, 2. Dim bus word label 351, and 3. Self test word label 352 (RTU-870T only). You will need an ARINC 429 bus reader, connected to any one of the ARINC 429 OUT test jacks if you want to this.
Check airplane wiring or RTU
• N TST (Nav test)
A ground at this point disables the NAV test function. "TEST" is removed from the VOR or MLS subpages.
Check airplane wiring or RTU
• MLS 1 and MLS 2
A ground at these points configures the RTU to display MLS 1/2 on the top line of the main menu. This is used only on installations equipment with a microwave landing system (or systems). If the installed MLS is on same side as the RTU, the MLS control words are added to its ARINC output bus and to the top line of the VOR subpage.
Check airplane wiring or RTU
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Table 5-5. Transponder System, Flightline Fault Isolation Procedures.
TEST
RTU870A/T Strappin options (cont ’d)
5/5/1993
PROCEDURE
DESIRED RESULT
TROUBLESHOOTING INSTRUCTIONS
• DME (No DME2)
A ground at this point causes the pilot’s RTU to transmit only the channel 1 ARINC 429 tuning word to the DME. A ground at this point on the copilot’s RTU causes that RTU to transmit only the channel 2 ARINC 429 tuning word to the DME. The copilot’s RTU transmits channel 3 data only when the copilot’s RTU receives channel 3 data from the remote tuning source. With this pin at ground, only SDI 01 is transmitted.
Check airplane wiring or RTU
• ADF (No ADF 2)
A ground at this point indicates there is no ADF on the copilot’s side. This causes the RTU to transmit tune data only for the pilot’s ADF.
Check airplane wiring or RTU
• UHF 1 (RTU-870T only)
An open at this point selects vhf 1 COMM 1 as the left-side COMM. A ground selects UHF 1 as the left side COMM.
Check airplane wiring or RTU
• UHF 2 (RTU-870T only)
Same as UHF 1 except as it applies to the copilot’s side and no. 2 systems.
Check airplane wiring or RTU
• TCN 1 (TACAN No. 1) (RTU-870T only)
A ground at this point selects the TACAN transceiver for the left-side DME transceiver. TCN is shown on the display. An open selects the left-side DME transceiver .
Check airplane wiring or RTU
• TCN 2 (TACAN No. 2) (RTU-870T only)
Same as TCN 1 except as it applies to the copilot’s side.
Check airplane wiring or RTU
• TCAS (RTU-870T only)
There should be a ground at this point if a TCAS is installed on this airplane. Open if no TCAS is installed.
Check airplane wiring or RTU
• ADF X (ADF extended frequency range) (RTU870T only)
A ground at this point configures the RTU to use the 2091 kHz ADF extended tuning frequency range with or in place of the 2081 kHz extended range.
Check airplane wiring or RTU
• INV TC (Inverse TACAN) (RTU-870T only)
A ground at this point disables the inverse TACAN function. An open enables.
Check airplane wiring or RTU
• C EXT (COMM frequency extension)
A ground at this point selects the extended frequency range (above 135.95 MHz).
Check airplane wiring or RTU
• N EXT (NAV frequency extension)
A ground at this point enables the NAV frequencies up to 135.00 MHz.
Check airplane wiring or RTU
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Table 5-5. Transponder System, Flightline Fault Isolation Procedures.
TEST
RTU870A/T Strappin options (cont ’d) RTU870A/T Data Buses
PROCEDURE
• A EXT (ADF frequency extension)
DESIRED RESULT
TROUBLESHOOTING INSTRUCTIONS
A ground at this point enables the ADF emergency frequency, 2182 kHz.
Check airplane wiring or RTU
Data Buses
The RTU-870A/T can receive and transmit ARINC 429 data on three data buses, labeled A, B, and C. This is in addition to the engine data input buses described below. A data bus reader can be used to read the data. Typical labels seen here are (update rate): • 016*: ATC mode S (5/s), • 030: VHF COMM frequency (10/s), • 031: ATC control code (5/s), • 032: ADF tune frequency (5/s), • 034: VHF NAV tune frequency (5/s), • 035: DME tune frequency (30/s), • 036: MLS channel echo (5/s), • 051*: UHF frequency and control (5/s), • 053*: TACAN tune frequency and control (5/s), • 154: MLS max select GP angle (5/s), • 157: Basic data word 2 (5/s), • 166*: DPU mode W and 1 (5/s), • 203: ATC altitude code (5/s), • 254: FCC mode word 3 (10/s), • 270: FMC mode (5/s), • 301: VHF COMM frequency (burst), • 302: VHF NAV frequency (burst), • 303: DME frequency X3 (burst), • 304: ADF frequency (burst), • 305: ATC code (burst), • 320*: Heading word, • 376*: UHF frequency (burst), and • 377*: TACAN channel (burst). * = RTU-870T only
If the installation is nontypical, consult airplane manual to determine the buses active and the information that each can be expected to reveal.
Engine Data Buses:
Typically the labels seen here are (update rate): • 340: Torque (percent of max) (10/s), • 344: Propeller RPM (10/s), • 345: Inner turbine temperature (10/s), and • 346: Turbine speed (percent of max in RPM) (10/s).
If all tests ed successfully, restore all equipment to its normal ground operating configuration. Return the test set to its normal storage location. Careful handling and storage of all ramp test equipment prolongs the service life and reduces maintenance costs.
5/5/1993
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Table 5-5. Transponder System, Flightline Fault Isolation Procedures.
TEST
TTC920G, power and lighting
TTC920G, manual controls, tests
PROCEDURE
DESIRED RESULT
TROUBLESHOOTING INSTRUCTIONS
Note: You can skip any tests that have been performed earlier as part of this test sequence. Check the airplane manual to determine the strapping and switching functions used in your installation. These procedures assume all functions are active which may not be true in all cases. For example, you will never find an installation that uses both 28 V and 5 V lighting. Power Test: Connect multimeter to 115 VAC POWER IN, NO. 1 and NO. 2 test points.
Measure aircraft power at both sets of test points. Allow 10% tolerance.
Check aircraft power source(s).
Lighting and Dimming Control Test: Connect multimeter to LIGHTING power test points; either 28V or 5 V, as applicable. If a manual dimming control is used, adjust it.
Measure lighting power. Note that dimming control works and intensity appears correct. Note that all switch and control legends are properly illuminated. It may be necessary to block the cockpit light, especially if this is being done outdoors.
Check lighting and dimming source. If any legends are not properly lit, remove TTC for bench repair.
Monitor Lamp Power test: Connect multimeter (+) to MON LMP PWR point and (-) to COMM (J1-6)
Measure the monitor lamp power input. This may be 28 V or 12 V. Allow 10% tolerance.
Check power source.
Note an open when the switch is not pressed and a short when the switch is pressed.
Check TTC.
Note an open when the switch is not pressed and a short when the switch is pressed.
Check TTC.
Connect multimeter, set for resistance measurement: (+) to No. 1, (-) to COMM (J1-6)
Note an open when the XPDR switch is at position 2 and a short when the switch is at position 1.
Check TTC.
Connect multimeter, set for resistance measurement: (+) to No. 2, (-) to COMM (J2-6)
Note an open when the XPDR switch is at position 1 and a short when the switch is at position 2.
Check TTC.
Self Test Switch tests: Connect multimeter, set for resistance measurement: (+) to SELF TEST, (-) to COMM (J1-6). Fault Monitor Lamp Test Switch tests: Connect multimeter, set for resistance measurement: (+) to MON, (-) to COMM (J1-6). ANTENNA SELECT Switch tests:
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Table 5-5. Transponder System, Flightline Fault Isolation Procedures.
TEST
PROCEDURE
TTC920G, manual controls, tests (cont’d)
XPDR IN STBY Switch tests:
DESIRED RESULT
TROUBLESHOOTING INSTRUCTIONS
Connect multimeter, set for resistance measurement: (+) to No. 1, (-) to COMM (J1-6)
Note an open when the XPDR switch is at position 2 and a short when the switch is at position 1.
Check TTC.
Connect multimeter, set for resistance measurement: (+) to No. 2, (-) to COMM (J2-6)
Note an open when the XPDR switch is at position 1 and a short when the switch is at position 2.
Check TTC.
Connect multimeter, set for resistance measurement: (+) to NO. 1, (-) to COMM (J1-6)
Note an open when the switch is at position 2 and a short when the switch is at position 1.
Check TTC.
Connect multimeter, set for resistance measurement: (+) to NO. 2, (-) to COMM (J2-6)
Note an open when the switch is at position 1 and a short when the switch is at position 2.
Check TTC.
Connect multimeter, set for resistance measurement: (+) to NO. 1 IN, (-) to COMM (J1-6) (NO. 1 OUT is identical)
Note: This input is normally connected to an airplane strut switch. With weight on wheels this point should show a short to chassis ground (CHAS GND, J1-8 or J2-8). If this function has been defeated for test purposes, it should show an open.
Check airplane wiring
Connect multimeter, set for resistance measurement: (+) to NO. 2 IN, (-) to COMM (J1-6) (NO. 2 OUT is identical)
Note: This input is normally connected to an airplane strut switch. With weight on wheels this point should show a short to chassis ground. If this function has been defeated for test purposes, it should show an open.
Check airplane wiring
28 V dc at either of these points indicates that no detected failure exists in the applicable transponder. If this voltage is low, you may need to use an ARINC 429 data bus reader to determine the diagnostic condition - see Diagnostic Code Retrieval Procedures below.
Note: Not all diagnostic conditions produce a failure warn (flag) output. Refer to tables 5-3 and 5-4.
This is an inverted failure warn output. If either of the two transponder fail inputs are low, this point should be high. If both inputs are high, this point should be low.
Check TTC.
REP ALT SEL (Reporting Altitude Select) Switch tests:
TTC920G, discretes tests, (cont’d)
AIR/GRD Tests:
Transponder Fail I/O Tests: TTC920G, Xpdr fail warn tests
Connect multimeter, set for dc voltage measurement: (+) to TRANSPONDER FAIL, 1-IN, (-) to COMM (J1-6) Connect multimeter, set for dc voltage measurement: (+) to TRANSPONDER FAIL, 2-IN, (-) to COMM (J2-6) Connect multimeter, set for dc voltage measurement: (+) to TRANSPONDER FAIL, OUT, (-) to COMM (J1-6)
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Table 5-5. Transponder System, Flightline Fault Isolation Procedures.
TEST
TTC920G, data bus output tests
PROCEDURE
DESIRED RESULT
Connect an ARINC 429 bus reader to the ARINC 429 OUT NO. 1 jack. Select transponder no. 1.
TROUBLESHOOTING INSTRUCTIONS
Set the bus reader to read ARINC 429 word labels 13, 15, or 16. The words are defined as follows:
Label 013: Bit(s) 0-7 8, 9 10 11, 12 13 14 - 20 21 - 28 29, 30 31
Definition Label (in octal): bits 0,1 = MSB, 2-4 = second digit, 5-7 = LSB, SDI (source destination (or data) identifier), Intruder altitude (ABS/REL), ABS = 1 Altitude select, bits 12/11: 00 = normal, 10 = above, 01 = below, 11 = unrestricted Display: all traffic/threat traffic, all = 0 (not used) TCAS range (see below) SSM (see below) Parity bit
Label 015: Bit(s) 0-7 8, 9 10 - 16 17 - 23 24 - 28 29, 30 31
Definition Label (in octal): bits 0,1 = MSB, 2-4 = second digit, 5-7 = LSB, SDI (source destination (or data) identifier), Altitude A limits (see airplane manual) Altitude B limits (see airplane manual) (not used) SSM (see below) Parity bit
Label 016: Bit(s) 0-7 8, 9 10 11 12, 13 14 - 16 17 - 19 20 - 22 23 - 25 26 - 28 29, 30 31
Definition Label (in octal): bits 0,1 = MSB, 2-4 = second digit, 5-7 = LSB, SDI (source destination (or data) identifier), Altitude reporting, on/off, 1 = off, Ident mode Display control Sensitivity control Digit 4 code Digit 3 code Digit 2 code Digit 1 code SSM (see below) Parity bit
TCAS range bit definition: bit 21 = 0.5 nmi bit 22 = 1.0 nmi bit 23 = 2.0 nmi bit 24 = 4.0 nmi bit 25 = 8.0 nmi bit 26 = 16.0 nmi bit 27 = 32.0 nmi bit 28 = 64.0 nmi
5/5/1993
SSM definition (bits 30/29): 00 = normal operation 01 = NCD (no computed data) 10 = Functional test 11 = Failure warn
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Table 5-5. Transponder System, Flightline Fault Isolation Procedures.
TEST
TTC920G (cont’d)
PROCEDURE
DESIRED RESULT
TROUBLESHOOTING INSTRUCTIONS
If all tests ed successfully, restore all equipment to its normal ground operating configuration. Return the test set to its normal storage location. Careful handling and storage of all ramp test equipment prolongs the service life and reduces maintenance costs.
Table 5-6. Transponder System, Diagnostic Data Retrieval Procedures.
TEST NO and DATA TITLE
BUS READER, TX SETUP
RESULTS and COMMENTS
1.0 Introduction
Note: These procedures apply only to installations using the CTL-92T or the RTU-870A/T. Diagnostic information is available only on the ARINC 429 data bus. Installations using a TTC920G or a CTL-90, do not return this bus to the control. Installations using a CTL-92/92A only use the CSDB bus which does not carry diagnostic data beyond the current diagnostic code which is displayed on the CTL-92/92A during self test. Refer to paragraph 5.5 for added information on Diagnostic Data Retrieval and Interpretation.
2.0 Setup
These procedures use the same setup as used for the procedures in table 5-5, shown on figure 5-1. In all cases, the XMT word label is 277 and the response word label is 351. Note: Throughout these procedures be sure the SSM is always set to 11. If you are using the DataTrac 400/400H you need change only digits 5 and 6 of the data fields; digit 1 (e.g., the 6 in step 3.0) is always set automatically. This bit is set by data word bits 29 through 32. On the DataTrac 200 you set the SI field. For the sake of simplicity, the column headers are not shown on the DataTrac display examples below.
3.0 Soft-ware Rev Status
Data request: DataTrac 400/400H XMT: 277 00 00 00 00 FD 00 1 0100 DataTrac 200 XMT: 277 00 00000 00 1 0100 JcAIR 429E TX, label 277: E00000
Response form (data may differ): DataTrac 400/400H RCV: 351 10 90 26 92 97 00 1 0100 DataTrac 200 RCV: 351 10 81348 00 1 0100 JcAIR 429E RX, label 351: 902692 This shows a SRS = 10-26-92
4.0 Total PwrOn Cycle Counter
Data request: DataTrac 400/400H XMT: 277 01 E0 00 01 FD 11 1 0100 DataTrac 200 XMT: 277 01 00000 11 1 0100 JcAIR 429E TX, label 277: E00001
Six-digit data field displays count in decimal form. DataTrac 400/400H RCV: 351 00 60 02 00 97 11 1 0100 DataTrac 200 RCV: 351 00 00100 11 1 0100 JcAIR 429E RX, label 351: 600200 This shows a POCC = 200.
5.0 Total Fault Counter
Data request: DataTrac 400/400H XMT: 277 10 E0 00 02 FD 11 1 0100 DataTrac 200 XMT: 277 10 00000 11 1 0100 JcAIR 429E TX, label 277: 600002
Six-digit data field displays count in decimal form. DataTrac 400/400H RCV: 351 00 60 02 08 97 11 1 0100 DataTrac 200 RCV: 351 00 00104 11 1 0100 JcAIR 429E RX, label 351: 600208 This shows a TFC = 208.
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Table 5-6. Transponder System, Diagnostic Data Retrieval Procedures.
TEST NO and DATA TITLE
BUS READER, TX SETUP
RESULTS and COMMENTS
6.0 Total Pwr-on Timer (Hrs)
Data request: DataTrac 400/400H XMT: 277 11 60 00 03 FD 11 1 0100 DataTrac 200 XMT: 277 11 00000 11 1 0100 JcAIR 429E TX label 277: 600003
7.0 Total Pwr-on Timer (Min)
Note: If you watch this data item for a minute or less you will see the data increment. Data request: DataTrac 400/400H XMT: 277 00 E0 00 04 FD 11 1 0100 DataTrac 200 XMT: 277 00 00002 11 1 0100 JcAIR 429E TX label 277: 600004
Six-digit data field displays count in decimal form. DataTrac 400/400H RCV: 351 11 60 00 11 97 11 1 0100 DataTrac 200 RCV: 351 11 00008 11 1 0100 JcAIR 429E RX, label 351: 600011 This shows a TPOTM = 11.
8.0 Last Pwron Cycle Fault Cntr
Data request: DataTrac 400/400H XMT: 277 01 60 00 05 FD 11 1 0100 DataTrac 200 XMT: 277 01 00002 11 1 0100 JcAIR 429E TX label 277: 600005
Six-digit data field displays count in decimal form. DataTrac 400/400H RCV: 351 10 E0 00 02 97 11 1 0100 DataTrac 200 RCV: 351 10 00000 11 1 0100 JcAIR 429E RX, label 351: 600002 This shows a LPOCFC = 2.
9.0 Last Maintenance Date
Data request: DataTrac 400/400H XMT: 277 11 60 00 07 FD 11 1 0100 DataTrac 200 XMT: 277 11 00002 11 1 0100 JcAIR 429E TX label 277: 600007
Six-digit data field displays in the form MMDDYY. Six-digit data field displays count in decimal form. DataTrac 400/400H RCV: 351 11 E6 29 93 97 11 1 0100 DataTrac 200 RCV: 351 11 314C8 11 1 0100 JcAIR 429E RX, label 351: E62993 This shows a LMD = 6-29-93 (June 29, 1993)
10.0 Last Pwr-on Cycle Fault Data
Note: In this sequence you must watch the label 351 word carefully. The UUT may transmit several words, each with a different diagnostic code, at 5-second intervals. The first transmission is the contents of the current Total Power-on Cycle count buffer (see step 4.0; above). This is followed, in 5-seconds intervals, with a transmission of each of the secondary diagnostic codes encountered during the most recent power-on cycle (auto self-test). This sequence is automatic and noninterruptable. If you are using the JcAIR 429E, be prepared to write down the data as it appears. The DataTrac units will retain the data. The final label 351 word is likely to be a word similar to XXXEOF which translates into "End of File".
5/5/1993
Six-digit data field displays count in decimal form. DataTrac 400/400H RCV: 351 11 60 00 77 97 11 1 0100 DataTrac 200 RCV: 351 11 0003A 11 1 0100 JcAIR 429E RX, label 351: 600077 This shows a TPOTH = 77.
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Table 5-6. Transponder System, Diagnostic Data Retrieval Procedures.
TEST NO and DATA TITLE
BUS READER, TX SETUP
RESULTS and COMMENTS
10.0 Last Pwr-on Cycle Fault Data (cont’d)
Data request: DataTrac 400/400H XMT: 277 00 60 00 10 FD 11 1 0100 DataTrac 200 XMT: 277 00 00008 11 1 0100 JcAIR 429E TX, label 277: 600010
11.0 Continue (prior) Pwr-on Cycles Fault Data
Note: This step can be seen as an extension of the previous step by retrieving diagnostic data stored during earlier power-on cycles. Data delivery and interpretation is the same as step 10.0. The most recent 16 power-on cycle sequences are stored and are read by incrementing data field bit 6 (bit 5 on the DataTrac 200) 1 through F (Hex). Data request: DataTrac 400/400H XMT: 277 00 60 00 11 FD 11 1 0100 DataTrac 200 XMT: 277 01 00008 11 1 0100 JcAIR 429E TX, label 277: 600011
12.0 Fast Data
Same as step 10.0 except one set of data for each interrogation. A convenient Record Chart is provided, following paragraph 5.5.14.2, for manually entering the data.
Note: This step is for those with access to an automated means of requesting, capturing, and analyzing the data. Such facilities are available from sources other than Collins. For example, Atlantic Instruments supplies hardware and software, operating with the DataTrac 400/400H, for automated ing of the captured data on a PC for detailed analysis and storage. For manual (slower) data , use step 13.0 below. Data request: DataTrac 400/400H XMT: 277 00 60 00 50 FD 11 1 0100 DataTrac 200 XMT: 277 00 00028 11 1 0100 JcAIR 429E TX, label 277: 600050
13.0 Slow Data
Six-digit data field displays count in decimal form. DataTrac 400/400H RCV: 351 00 E0 02 00 97 11 1 6800 351 10 60 00 82 97 11 1 6800 351 11 E0 0E 0F 97 11 1 6800 DataTrac 200 RCV: 351 00 00100 11 1 4999 351 10 00040 11 1 4999 351 11 00706 11 1 4999 JcAIR 429E RX, label 351: E00200 600082 E00E0F
Refer to paragraph 5.5.13.2 for a detailed description of the data that is transmitted here. If you are retrieving data manually, e.g., with the JcAIR 429E, use step 13.0 instead. In this step, step 12.0, the data is transmitted to quickly to be read manually. See note below.
Note: This step is essentially the same as the previous step, step 12.0. Here, however, the data output rate is slower; each sequence is transmitted for a 5-second period, separated by a break transmission 0FFFFH. Data request: DataTrac 400/400H XMT: 277 00 60 00 51 FD 11 1 0100 DataTrac 200 XMT: 277 01 00028 11 1 0100 JcAIR 429E TX, label 277: 600051
Same as step 12.0 except the data is transmitted at 5--second interval.
Note: The DataTrac 400/400H units have a Break Data Review feature which can be effectively used here to capture the data. Consult the applicable manual for the necessary operating procedures. Return the test set to its normal storage location. Careful handling and storage of all ramp test equipment prolongs the service life and reduces maintenance costs.
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maintenance 523-0775657 5.4.5 ACCEPTANCE TEST PROCEDURES 5.4.5.1
Introduction
The Acceptance Test Procedures (ATP) should be used to that the equipment is operational; that no shipping damage has occurred. ing equipment operation before installation helps to isolate most problems discovered after installation. The procedures in this paragraph can also be seen as a Return to Service Test (RTS). In this scenario a the pilot complaint and the flightline test is not conclusive. Thus the unit is removed from an airplane and tested on the bench to isolate a malfunction between the unit or the airplane installation. If the unit performs properly on the bench using the RTS, it can be returned to service. The procedures in this paragraph must not be seen as the equivalent of a Final Performance Test (FPT). An FPT must be performed after any repair operation and is considerably more detailed than this ATP. The FPT is provided in the TDR-94/94D Component Maintenance Manual.
item. A refers to the abbreviated shown schematically in figure 5-4. E is the enhanced version shown in figures 5-3 and 5-5. TE items keyed A and E can be used with either . TE items keyed A only can be used only with the abbreviated version; items keyed E are for use only on the enhanced version. 5.4.5.3 Test Options Table 5-7 shows two test s. Option 1A is the enhanced version and will allow use of a databus reader and various controls and control simulators in addition to a number of altitude sources. The details of this are included in paragraph 5.8 Option 1B is the abbreviated version mentioned in paragraph 5.4.5.2. It is expected that the abbreviated test is assembled locally. The enhanced version can also be locally assembled or purchased from a number of suppliers. Those known suppliers are included in the vendor listing in table 5-8.
The procedures are provided in four different procedures. The procedure chosen depends on equipment available and on the extent to which testing is to be performed. The first procedure uses the CTL-92/92A CSDB control and an abbreviated version of the test . This procedure satisfies a minimum level of acceptance testing by ing that the UUT is able to respond to CSDB tuning data and report any internal diagnostics that may exist.
The abbreviated test , when used with the automatic test capability of the ATC601, satisfies the requirements of ADVISORY CIRCULAR NO 43.13-6A, dated 11/11/77; Subject: Automatic Pressure Altitude Encoding Systems and Transponder Maintenance and Inspection Practices. The IFR ATC-601 Test Set, or equivalent, can be used with either of the two versions.
The remaining procedures utilize the enhanced version of test and provide a greater level of I/O testing capability. These procedures differ only in the particular data bus analyzer being used.
If you are using a test built according to instructions in an earlier version of this manual, it may need to be updated. Refer to paragraph 5.8.1 for update information.
5.4.5.2
ATP Setup Description
Table 5-7 is a list of the equipment required for this ATP. The equipment includes an IFR ATC-601 Mode S Test Set. If an other test set is used, you should be sure that it is capable of performing the tests as defined in these procedures and as listed in paragraph 5.4.2. The right hand column in table 5-7 identifies the test required for the use of that TE 5/5/1993
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maintenance 523-0775657 Table 5-7. Equipment Required for ATP
Item
Manufacturer
Mfg Part Number
Purpose
A/E
Test Option 1A
Locally fabricated
See figure 5-3 and 5-5
To interconnect equipment for ATP
E
Test Option 1B
Locally fabricated
See figure 5-4
To interconnect equipment for ATP
A
ATC/Mode S Test Set
IFR Systems, Inc. Wichita, KS
ATC-601
For rf testing
A,E
ARINC Bus Reader Option 2A
Atlantic Instr. Melbourne, FL
DataTrac 200, Data Trac 400, or DataTrac 400H
For bus monitor and simulation
E
ARINC Bus Reader Option 2B
JcAIR Industrial Airport, KS
429E ARINC 429 Transmitter / Receiver
For bus monitor and simulation
E
Transponder Control Option 3A
Collins
CTL-92 or CTL-92A Transponder Control
Transponder control
A,E
Interconnect cable for option 3A
Same as test
See figure 5-6
For CTL-92/92A interface to test
A,E
Transponder Control Option 3B
Collins
RTU-870A or RTU-870T Radio Tuning Unit
Transponder or transponder/TCAS control
E
Interconnect cable for option 3B
Same as test
See figure 5-7
For RTU-870/870A interface to test
E
Transponder Control Option 3C
Collins
TTC-920G TCAS / Transponder Control
Transponder control
E
Interconnect cable for option 3C
Same as test
See figure 5-8
For TTC-920G interface to test
E
RF load
Omni-Spectra
3101-6100-00
RF termination of unused antenna port
A,E
Interconnect cables for Bus Readers and control simulators
Locally fabricated or the same as test
See figure 5-9
To connect bus reader and control / altitude simulator to test
E
28 V dc power supply
any
5 A minimum capability
For test setup power
A,E
Scope
any
any
For suppression test
A,E
Table 5-8. Equipment Suppliers
Supplier
Address
Product
IFR Systems, Inc.
10200, West York Street Wichita, KS 67215
ATC-601 Ramp Test Set
Atlantic Instruments, Inc.
P.O. Box 021466 Melbourne,FL 32902
DataTrac 400 DataTrac 400H and DataTrac 200 Databus Analyzers
JcAIR
400 Industrial Parkway, Industrial Airport, KS 66031
AcceptanceTest , Flightline Test , and 429E ARINC 429 Transmitter/Receiver
Avionics Specialist, Inc
3833 Premier Ave. Memphis, TN 38118
Acceptance Test and Flightline Test
5/5/1993
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maintenance 523-0775657 The enhanced version of test , also satisfies these requirements, and offers additional capabilities for more complete I/O testing as follows: Gillham altitude simulation, Gillham altitude switching for direct or through CTL testing, Mode S address code selection, Control type selection, Control input port selection, Digital altitude type selection; ARINC 429, ARINC 575, or CSDB, TCAS i/o bus verification, Digital altitude and control port selection, Manual ident, Crossfeed switching, Side 1/Side 2 switching, Output port selection, and Use of a data bus analyzer. The control interface cables, shown in figures 5-6, 5-7, and 5-8 can be used with either . 5.4.5.4 Control Options Some type of transponder control is required with either test . The abbreviated version uses the CTL-92/92A Control. The enhanced version can use any of the currently available controls or a simulator. If you have a databus receiver/transmitter, like the DataTrac 400, DataTrac 400H, or DataTrac 200, by Atlantic Instruments, it can be used to simulate an ARINC 429 control. The DataTrac 200 can also simulate a CSDB control. If you plan to used the TTC-920G TCAS control, be aware that it requires 115 Vac, 400 Hz, power which is not provided in the test . The interconnect cable, figure 5-8, has a patch provision for 115 Vac power input. Table 5-8 is a listing of suppliers for the various test equipment items as well as the test .
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5.4.5.5
Gillham Code Simulator
The TDR-94/94D Mode S Transponder Acceptance Test used here includes a built-in Gillham code (ARINC 572) simulator. The Gillham Code Altitude Tests in this section include a listing of a number of altitudes and corresponding Gillham code switch settings. Set the corresponding switch down (SEL) for an active code selection, and set the switch up (OFF) for an inactive selection. 5.4.5.6
ATC Setup Description
If you are using this setup for the first time, check that 28 volts appears only on the correct pins. Use the schematic diagram shown in figure 5-4 or 5-5 as applicable to the you are using. WARNING: Do not use a standard multimeter probe when making continuity tests to the ProLine II UUT mating connector. These types of probes have been known to cause the forks to break resulting in unreliable operation. It is far better to fabricate one or two test probes using a short length of flexible 22 or 26 AWG wire, terminated at one end with a mating blade like those used in the UUT connector. Terminate the other end with a small alligator clip or tip jack to connect to the multimeter lead.
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maintenance 523-0775657 Interconnect the equipment as shown in figure 5-2. The data bus readers are not used with the abbreviated test . Be sure that the rf connections to the antenna connectors are fully inserted and that the i/o mating connectors are firmly seated before applying power. Terminate the unused antenna port with a TNC 50Ω rf termination as identified in table 5-1 and table 5-7. Turn on the ATC-601 Test Set, or equivalent, and exercise the self test routine. If the test set is operational continue with the test. Otherwise, repair the test set. If you are using the test shown on figure 5-5, set the switches as follows: The abbreviated has only the UUT POWER and EXT STBY switches. If you are using a test built according to instructions in an earlier version of this manual, it may require modification. Refer to paragraph 5.8.1.
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SWITCH
POSITION
UUT POWER: OFF EXT STBY: STBY XFEED: OUT SELF TEST: EN TCAS/NO TCAS: NO TCAS SDI: SIDE 1 AIR: AIR ANT: DL AUTO ALT: OFF REP ALT SEL: PA DATA LINK SEL: A/B BURST TUNE: OFF DATALINK: NO ADLP CONTROL DATA SELECT: ARINC PORT: PA OUTPUT PORT SELECT: ARINC 429 PORT A ARINC 572 ALT IN: TO TDR ALT TYPE SELECT: ARINC 429 SOURCE SELECT: SEL ARINC 572 ALT IN: TO TDR Gillham Code switches: All OFF except C2 and B1 to SEL (2, 500 ft) MAX AIRSPEED: All OFF MODE S ADDRESS SELECT: All OFF except: P1-35, 36, 37, 39, 41, 42, 46, 51, 56. (Hex code: 3AC421, Octal: 16542041)
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maintenance 523-0775657
Acceptance Test, Test Setup Diagram Figure 5-2
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maintenance 523-0775657 5.4.5.7 Minimum Acceptance Test, Using a CSDB Control and the Abbreviated Test The procedures in table 5-9 use a CSDB control like the CTL-92/92A to provide transponder control and the abbreviated version of test
for equipment interconnection. Successful completion of these procedures verifies the performance of the UUT by providing reasonable assurance of the functional integrity of the transmitter, receiver, the CSDB control input, and internal data handling.
Table 5-9. Minimum Acceptance Test Procedures, Using a CSDB Control and the Abbreviated Test
STEP
TITLE
PROCEDURE
DESIRED RESULTS
1.0
Setup
If not already done, connect equipment as shown in figure 5-2. • Connect the CTL-92/92A using the cable shown in figure 5-6. • Connect the ATC-601 (or equivalent) to the UUT bottom antenna connector. • Connect and rf termination to the top antenna connector. • Connect power to the power jacks - observe proper polarity. • Be sure POWER switch is OFF and EXT STBY switch is at STBY. • The bus reader is not needed in this setup.
2.0
Initial Test
Power application Set test POWER switch to ON Set CTL to any valid ATC code; e.g. 1234
3.0
UUT Self Test
Set CTL switch to STBY
ATC-601 REPLY lamp is off; no replies.
Set CTL switch to OPR
No change.
Set EXT STBY switch to OPR
ATC-601 REPLY lamp lights; UUT is replying to the interrogations.
Press the TEST button; either on the test or on the CTL. Notice any diagnostic code that may be displayed on the CTL. If diAG and a diagnostic code is displayed, refer to table 5-3 and 5-4 for an interpretation. If a code from 10 to 70 (inclusive), C(), or D0 is displayed, the UUT should be rejected. Any other code may not be indicative of an equipment failure but rather the result of an inactive data bus. As a general rule in testing a UUT with N ending in -002, those diagnostic conditions accompanied by an extinguished FLT MON (fault monitor) lamp on test , should be seen as cause for unit rejection. Others may be the result of the an incomplete equipment complement and may not be indicative of an equipment failure.
4.0
Test Set, Auto Test
Follow the instructions in the Test Set operation manual for the Auto Test mode and execute the test.
Ensure that all tests . See note below.
Set the test POWER switch to Off Switch the RF connector on the UUT from top to bottom (or bottom to top) Repeat the Auto Test sequence.
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Ensure that all tests . See note below.
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maintenance 523-0775657 Table 5-9. Minimum Acceptance Test Procedures, Using a CSDB Control and the Abbreviated Test (Cont).
STEP
TITLE
PROCEDURE
DESIRED RESULTS
This completes the minimum test requirement. -------------------------------------------------------------------------------Note. The AUTO TEST sequence will indicate FAILED even when certain tests result in a NO REPLY condition. The NO REPLY conditions are the result of no ADLP (Airborne Data Link Processor) data being supplied in this setup. This same condition is likely to occur when using the ATC-601 as a ramp tester when testing an installation not equipped with an ADLP. It is also possible that the AUTO TEST fails because the UUT sensitivity is more than -77.0 dBm. If you find this to be the case, recognize that Collins prefers that a sensitivity (MTL) greater than 77.0 be seen as acceptable. Obviously, an MTL approaching -80 dBm tends to indicate a problem with test equipment calibration. To that the test can be seen as successful, proceed as follows: • When the test sequence is completed and the ATC-601 stops (as indicated by no INTERR lamp off, you will see a screen as follows: ** AUTO TEST - FAILED ** MODES TESTED - A,C,S FREQ: 1089.92 MHz MODES ED - A,C.S ERP: 55 dBm MODES FAILED -> MTL: -77 dBm DIVERSITY ISOLATION: >40 dB Press RUN to start
the test results as follows: Use the SELECT up arrow or down arrow key to scroll through the following list of tests performed. If you use the up arrow, you will see the sequence as listed from top to bottom. If you use the down arrow, you will see the sequence is reverse order. 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. 13. 14. 15. 16. 17. 18. 19.
** ** ** ** ** ** ** ** ** ** ** ** ** ** ** ** ** ** **
MTL DIFFERENCE TEST - ED ** DIVERSITY TEST - ED ** FREQUENCY TEST - ED ** SQUITTER TEST - ED ** MODE S UF21 TEST - NO REPLY ** MODE S UF20 TEST - NO REPLY ** MODE S UF16 TEST - NO REPLY ** MODE S UF11 TEST - ED ** MODE S UF5 TEST - ED ** MODE S UF4 TEST - ED ** MODE S UF0 TEST - ED ** SPR ON/OFF TEST - ED ** INVALID ADDRESS TEST - ED ** MODE S ALL-CALL TEST - ED ** ATC ONLY ALL-CALL TEST - ED ** SLS LEVEL TEST - ED ** ATCRBS REPLY TEST - ED ** REPLY JITTER TEST - ED ** REPLY DELAY TEST - ED **
At this point, another press of the arrow key will redisplay the first item; either 1. or 19., depending which arrow was used. In each case, the screen also shows the particular test parameter and the test result. If the test has failed, this value can be compared to the required value to gain more definitive insight into the reason for the failure.
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maintenance 523-0775657 5.4.5.8 Minimum Acceptance Test, Using a ARINC 429 Control and the Abbreviated Test The procedures in table 5-10 use an ARINC 429 control like the RTU-870A/T to provide transponder control and the abbreviated version of test for equipment interconnection. Successful
completion of these procedures verifies the performance of the UUT by providing reasonable assurance of the functional integrity of the transmitter, receiver, the ARINC 429 control input, and internal data handling.
Table 5-10. Minimum Acceptance Test Procedures, Using an ARINC 429 Control and the Abbreviated Test
STEP
TITLE
PROCEDURE
DESIRED RESULTS
1.0
Setup
If not already done, connect equipment as shown in figure 5-2. • Connect the ARINC 429 control using the cable shown in figure 5-7 or 5-8. • Connect the ATC-601 (or equivalent) to the UUT bottom antenna connector. • Connect and rf termination to the top antenna connector. • Connect power to the power jacks - observe proper polarity. • Be sure POWER switch is OFF and EXT STBY switch is at STBY. • The bus reader is not needed in this setup.
2.0
Initial Test
Power application Set test POWER switch to ON Set CTL to any valid ATC code; e.g. 7777
3.0
UUT Self Test
Set CTL switch to STBY
ATC-601 REPLY lamp is off; no replies.
Set CTL switch to OPR
No change.
Set EXT STBY switch to OPR
ATC-601 REPLY lamp lights; UUT is replying to the interrogations.
Press the TEST button; either on the test or on the control. Notice any diagnostic code that may be displayed. If a diagnostic code is displayed, refer to table 5-3 and 5-4 for an interpretation. If a code from 10 to 70 (inclusive), C(), or D0 is displayed, the UUT should be rejected. Any other code may not be indicative of an equipment failure but rather the result of an inactive data bus. As a general rule in testing a UUT with N ending in -002, those diagnostic conditions accompanied by an extinguished FLT MON (fault monitor) lamp on test , should be seen as cause for unit rejection. Others may be the result of the an incomplete equipment complement and may not be indicative of an equipment failure.
4.0
Test Set, Auto Test
Follow the instructions in the Test Set operation manual for the Auto Test mode and execute the test.
Ensure that all tests . See note below.
Set the test POWER switch to Off Switch the RF connector on the UUT from top to bottom (or bottom to top) Repeat the Auto Test sequence.
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Ensure that all tests . See note below.
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maintenance 523-0775657 Table 5-10. Minimum Acceptance Test Procedures, Using an ARINC 429 Control and the Abbreviated Test (Cont).
STEP
TITLE
PROCEDURE
DESIRED RESULTS
This completes the minimum test requirement. -------------------------------------------------------------------------------Note. The AUTO TEST sequence will indicate FAILED even when certain tests result in a NO REPLY condition. The NO REPLY conditions are the result of no ADLP (Airborne Data Link Processor) data being supplied in this setup. This same condition is likely to occur when using the ATC-601 as a ramp tester when testing an installation not equipped with an ADLP. It is also possible that the AUTO TEST fails because the UUT sensitivity is more than -77.0 dBm. If you find this to be the case, recognize that Collins prefers that a sensitivity (MTL) greater than 77.0 be seen as acceptable. Obviously, an MTL approaching -80 dBm tends to indicate a problem with test equipment calibration. To that the test can be seen as successful, proceed as follows: • When the test sequence is completed and the ATC-601 stops (as indicated by no INTERR lamp off, you will see a screen as follows: ** AUTO TEST - FAILED ** MODES TESTED - A,C,S FREQ: 1089.92 MHz MODES ED - A,C.S ERP: 55 dBm MODES FAILED -> MTL: -77 dBm DIVERSITY ISOLATION: >40 dB Press RUN to start
the test results as follows: Use the SELECT up arrow or down arrow key to scroll through the following list of tests performed. If you use the up arrow, you will see the sequence as listed from top to bottom. If you use the down arrow, you will see the sequence is reverse order. 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. 13. 14. 15. 16. 17. 18. 19.
** ** ** ** ** ** ** ** ** ** ** ** ** ** ** ** ** ** **
MTL DIFFERENCE TEST - ED ** DIVERSITY TEST - ED ** FREQUENCY TEST - ED ** SQUITTER TEST - ED ** MODE S UF21 TEST - NO REPLY ** MODE S UF20 TEST - NO REPLY ** MODE S UF16 TEST - NO REPLY ** MODE S UF11 TEST - ED ** MODE S UF5 TEST - ED ** MODE S UF4 TEST - ED ** MODE S UF0 TEST - ED ** SPR ON/OFF TEST - ED ** INVALID ADDRESS TEST - ED ** MODE S ALL-CALL TEST - ED ** ATC ONLY ALL-CALL TEST - ED ** SLS LEVEL TEST - ED ** ATCRBS REPLY TEST - ED ** REPLY JITTER TEST - ED ** REPLY DELAY TEST - ED **
At this point, another press of the arrow key will redisplay the first item; either 1. or 19., depending which arrow was used. In each case, the screen also shows the particular test parameter and the test result. If the test has failed, this value can be compared to the required value to gain more definitive insight into the reason for the failure.
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5.4.5.9 Procedures using the DataTrac 400 or DataTrac 400H Databus Analyzer Table 5-11 Acceptance Test Procedures, Using the DATATRAC 400 or DATATRAC 400H Databus Analyzer STEP
TITLE
PROCEDURE
DESIRED RESULTS
1.0
Setup
Note: If you are using a Test built according to instruction provided in a previous edition of this manual, it may be necessary to upgrade the . Refer to paragraph the Special Tools and Fixture Section. If not already done, connect equipment as shown in figure 5-2. • Connect DATATRAC as follows using cables shown in figure 5-9. • XMT 1 to test DIGITAL CONTROL port, • Parallel connect XMT 1 to test PRIMARY DIGITAL ALTITUDE PORT, • RCV 1 to test DATA BUS READER port. • Connect the ATC-601 to the UUT bottom antenna connector. • Connect an rf termination to the TOP antenna port. • Connect power to test power jacks - observe proper polarity. • Preset the switches as shown in paragraph 5.4.4 above. Be sure POWER switch is OFF and EXT STBY switch is at STBY. On test , set the MODE S ADDRESS switches to any combination except all OFF or all to SEL. If all switches are set OFF or all set SEL, a diagnostic code FF will result.
1.1
Setup
Turn the DATATRAC ( ) on and set the RCV 1, and XMT 1 screen ----->
-----------------RCV 1--(ALL)---12.5 KHz Lbl SDI 32-Hex Data-1 SSM Par msec ... no data present ...
(See notes 1 and 2 that follow test step 1.2)
-ON-------------XMT 1 ----------12.5 KHz Lbl SDI 32-Hex Data-1 SSM Par msec 031 01 15 66 C1 98 00 1 0100 203 01 64 00 01 C1 11 1 0100
Turn on TDR-94/94D
On test : • Set POWER switch to ON Monitor current. If OK: • Set EXT STBY switch to OPR Monitor current.
If the unit has been in service and there is a possibility of an over-current condition, monitor the power supply current output. The setup should draw no more than 1.5 A. Typically it draws about 0.9 to 1.1 A when the UUT is transmitting.
Setup (power-up)
Turn the ATC-601 on and press SELECT for the screen -------------->
** ATCRBS REPLY TEST - NOT RUN **
(lines 2-4 are irrelevant) CODE=
See Note in next cell below. 1.2
ARINC 429 tuning test
On the ATC-601, press RUN ATC-601 screen ---------> Note: When power is applied and proper control data is supplied, the TDR-94/94D should turn on the XFEED OUT lamp almost immediately. The FAULT MON lamp may be off for a few seconds and then turn on. A lighted FAULT MON lamp should generally be seen as a no-fault indication. See table 5-3. The DATATRAC ( ) RCV 1 display becomes --------->
ALT= Press RUN to start
[
]
UUT responds to interrogations as indicated by a lighted XFEED OUT lamp on the test and a lighted REPLY lamp on the ATC-601. ** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE=5263 *****
ALT=32,800 FT [1344] TEST RUNNING *****
To change the CODE, see note 1 below. To change the ALT, see note 2 below. -----------------RCV 1--(ALL)---12.5 KHz Lbl SDI 32-Hex Data-1 SSM Par msec 203 01 64 00 01 C1 11 1 0200 031 01 F5 66 81 98 00 1 0200 350 01 60 00 01 17 11 1 0200 ... no data present ...
Note: Any other labels displayed are irrelevant to this test. Use the down arrow key to scroll the display. See Note 3 below.
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maintenance 523-0775657 Table 5-11 Acceptance Test Procedures, Using the DATATRAC 400 or DATATRAC 400H Databus Analyzer (Cont).
STEP
TITLE
PROCEDURE
DESIRED RESULTS
Note 1. You can change the (octal) CODE=XXXX display by changing data bits 18 through 29 in the label 031 data word (XMT 1 field of the DATATRAC ( )) as follows: ATC-601 digit: First Second Third Bit: 32 31 30 29 28 27 26 25 Data: Par SSM |<-----Data -------> Hex value: 8 4 2 1 8 4 2 1 DATATRAC (Hex): | 1 | | 5 Binary: 0 0 0 1 0 1 0 1 Octal value: 4 2 1 4 2 Produces CODE: 5 2 Bits 11 through 17, of the label 031 control DATATRAC Hex bits: 5th Bit: 16 15 14 13 Bit values: 8 4 2 1 Assignment:
| Pad
| Pad
Fourth 22 21
24
23
8 | 0 1
4 | 1 4
2
20
1
8 | 0 4
6 1 2 6
19 18 17 ----->| Pad 4 2 1 | 6 1 1 2 1 3
0 1
|
word, are assigned the following functions: 6th 12 8 Pad
11 10 9 4 2 1 | |<- |<--SDI |<--Altitude reporting, 1 = OFF
| | | | | |<--Ident, 1 = ON |<--Altitude port select, 1 = B
Note 2: You can set the XMT 1 label 203 data field bits 12 through 28 to any combination of 1 and 0. The RCV 1 label 203 word data field will reflect the XMT 1 word while the ATC-601 will show the altitude to the nearest 100 feet. The label 203 word data bit values are as follows: DATATRAC Hex *: | 2nd Hex value: 8 4 2 Bit: 29 28 27 26 Alt value:(sign bit; 0 = +) 65536 32768 16384 (in feet) DATATRAC Hex *: | 4th | | Hex value: 8 4 2 1 8 Bit: 20 19 18 17 16 Alt value 256 128 64 32 16 (in feet) Determine the altitude by totaling the bit value of all bits set to
| 1 25 8192
| 8 24 4096
5th 4 15 8
2 14 4
3rd 4 23 2048 | 1 13 2
| 8 12 1
| 1 21 512
2 22 1024 6th 4 11 **
2 10 **
| 1 09 **
1.
* The left-most Hex Data bit (bit 1) is determined by the parity bit 32, the SSM bits 31 and 30, and sign bit 29. Since bit 29 must always be a 0, this Hex bit must always be an odd number. The right-most bits (bits 7 and 8) are determined by the label. **= Not used Note 3: You will see a label 371 data word. This is the ARINC 429 Specific Equipment Identification word which is structured the same as other ARINC 429 words but conveys the following information: Bits 11 through 18 identify the equipment type. The code for ATC transponders is 18 therefore bits 14 and 15 are 1; the others are 0. Bits 19 through 24 convey a binary code identifying the equipment manufacturer. Collins’ is 6. Therefore bits 20 and 21 are 1; all others are 0. Bits 24 through 29 are reserved for purposes to be defined. When ARINC 572 altitude data is active, you will see a label 200 data word. This word reflects the ARINC 572 (Gillham code) altitude data. This word is structured the same as other ARINC 429 words, except bits 9 and 10 are part of the data field; i.e., there is no SDI. Bits 9,10, and 11 reflect the D1, D2, and D4 code bits respectively. Bits 13, 14, and 15 reflect the C-bits, bits 17, 18, and 19 reflect the B-bits, and 21, 22, and 23 reflect the A-bits.
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maintenance 523-0775657 Table 5-11 Acceptance Test Procedures, Using the DATATRAC 400 or DATATRAC 400H Databus Analyzer (Cont).
STEP
TITLE
2.0
Test set, Auto Test
PROCEDURE On ATC-601: • Press RUN/STOP to stop • Press AUTO TEST • Press RUN to start Note: This test requires a few seconds to run. It will stop automatically.
DESIRED RESULTS Ensure that all tests . See note below.
On test : • Set EXT STBY switch to STBY • Set POWER switch OFF On UUT: • Move the test set rf cable to the UUT top antenna connector and the rf termination to the bottom. On test : • Set POWER switch ON • Set EXT STBY switch to OPR On ATC-601: • Repeat the AUTO TEST
Ensure that all tests . See note below.
Note. The AUTO TEST sequence will indicate FAILED even when certain tests result in a NO REPLY condition. The NO REPLY conditions are the result of no ADLP (Airborne Data Link Processor) data in this setup. This same condition is likely to occur when using the ATC-601 as a ramp tester when testing an installation not equipped with an ADLP. To that the test can be seen as successful, proceed as follows: • When the test sequence is completed and the ATC-601 stops, as indicated by INTERR and REPLY lamps off, you will likely see a screen as follows: ** AUTO TEST - FAILED ** MODES TESTED - A,C,S FREQ: MODES ED - A,C,S ERP: MODES FAILED -> MTL: DIVERSITY ISOLATION: >40 dB Press RUN to start
1089.92 Mhz 55 Dbm -77 Dbm
(The FREQ, ERP, and MTL values can vary from UUT to UUT and to a lesser degree on UUT temperature.) the test results as follows: On the ATC-601, use the SELECT 6th up arrow or down arrow key to scroll through the following list of tests performed; the numbers are for reference purposes only and do not appear on the test set screen. If you use the down arrow, you will see the list in the order shown; from test 1 through test 19. If you use the up arrow key, you will see the list in reverse order, starting at test 19. You will likely notice that all tests ed except tests 13, 14, and 15 which had a NO REPLY. NO.
TEST NAME AND RESULT
1.0
**
REPLY DELAY TEST - ED
2.0
**
REPLY JITTER TEST - ED
TEST SPECIFICATION / DESCRIPTION **
**
MODE S: 128.00 (±0.25) µs ITM A: 128.00 (±0.25) µs (All others): 3.00 (±0.50) µs MODE S: =< 0.05 µs ITM: =< 0.06 µs
(All others): =< 0.1 µs 3.0
**
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ATCRBS REPLY TEST - ED
**
F1 TO F2 SPACING: 20.3 (±0.1) µs All PULSE WIDTH: 0.45 (±0.1) µs
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maintenance 523-0775657 Table 5-11 Acceptance Test Procedures, Using the DATATRAC 400 or DATATRAC 400H Databus Analyzer (Cont).
STEP
TITLE
NO.
TEST NAME AND RESULT
4.0
**
5.0
** ATC ONLY ALL-CALL TEST - ED **
The TDR-94/94D should not reply to this mode a and mode c only interrogation. ED indicates a correct (NO) response.
6.0
** MODE S ALL-CALL TEST - ED **
The TDR-94/94D should reply to this interrogation. ED indicates a correct response. UUT address previously determined in mode s interrogation, is sent to UUT in UF4 (Uplink Format 4) and verified in DF4 (Downlink Format 4) reply.
7.0
** INVALID ADDRESS TEST - ED **
UUT is interrogated with two addresses, both of which are different from the correct address. ED indicates UUT did not reply to interrogation.
8.0
** SPR ON/OFF TEST - ED **
UUT is interrogated first with SPR ON and verifies a proper reply, then with SPR OFF and verifies no reply. ED indicates UUT responded correctly.
9.0
**
MODE S UF0 TEST - ED
**
UUT is interrogated with mode S UF0, ing correct altitude as compared to previous mode c reply, correct address as compared to DF11 address, and correct format. ED indicates correct UUT response.
10.0
**
MODE S UF4 TEST - ED
**
UUT is interrogated with UF4, ing correct altitude as compared to previous mode c reply, correct address as compared to DF11 reply, and correct format. ED indicates correct UUT response.
11.0
**
MODE S UF5 TEST - ED
**
UUT is interrogated with UF5, ing the correct ID code as compared to previous mode a reply, correct address as compared to DF11 reply, and correct format. ED indicates correct UUT response.
12.0
**
MODE S UF11 TEST - ED
13.0
**
MODE S UF16 TEST - NO REPLY
**
(See test 15.)
14.0
**
MODE S UF20 TEST - NO REPLY
**
(See test 15.)
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PROCEDURE
DESIRED RESULTS
SLS LEVEL TEST - ED
TEST SPECIFICATION / DESCRIPTION UUT is interrogated with F2 (SLS) pulse at 9 dB below F1. UUT should reply to this interrogation. Then UUT is interrogated with F2 equal to F1. UUT should not reply. ED indicates correct response to both tests.
**
UUT is interrogated with UF11, ing correct address as compared to previous response, and correct format. ED indicates correct UUT response.
**
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maintenance 523-0775657 Table 5-11 Acceptance Test Procedures, Using the DATATRAC 400 or DATATRAC 400H Databus Analyzer (Cont).
STEP
TITLE
PROCEDURE
DESIRED RESULTS OR SETUP SCREEN
NO.
TEST NAME AND RESULT
15.0
**
MODE S UF21 TEST - NO REPLY
16.0
**
SQUITTER TEST - ED
17.0
**
FREQUENCY TEST - ED
**
Freq: 1090 (±1) MHz
18.0
**
DIVERSITY TEST - ED
**
ATC-601 monitors squitter pulses on active antenna port (as in test 16) and then monitors for intervening squitter pulses that are not greater than 20 dB below the active squitter. This test will always fail when the UUT is a TDR-94 (non diversity) because squitter is transmitter every second on the same antenna port. If you are testing a TDR-94D and the DL ANT/SGL ANT switch is set to SGL ANT, the test will also fail because this causes the unit to operate like a TDR-94. ED indicates a correct response from a TDR-94D.
19.0
**
MTL DIFFERENCE TEST - ED
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TEST SPECIFICATION / DESCRIPTION **
UUT is interrogated with UF16, UF20, and UF21. These formats are all related to the airborne data link function. This function has not been implemented. The TDR-94/94D will not reply to these interrogation formats. NOT REPLY should not be seen as a failure. When set for dual antenna operation, the TDR-94D transmits a squitter pulse once each second, alternating between top and bottom antenna ports. The ATC-601 verifies that one squitter pulse is received every 1.6 to 2.4 seconds. The test ANT SGL/DL switch must be in the DL position. When set for single antenna operation, or when testing a TDR-94, only the bottom antenna port is used. In this case the ATC-601 verifies that one squitter pulse is received every 0.6 to 1.4 seconds. When you change the ANT SGL/DL switch, you must cycle power to the UUT in order for it to take effect. ED indicates a correct UUT response.
**
**
ATC-601 verifies that the MTL difference between mode a and mode c responses is < 1.0 dB. At this point, another press of the arrow key will display the first item; either 1.0 or 18.0, depending on which arrow was used.
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maintenance 523-0775657 Table 5-11 Acceptance Test Procedures, Using the DATATRAC 400 or DATATRAC 400H Databus Analyzer (Cont).
STEP 3.0
TITLE Power output and Rcvr Sensi-tivity Test
PROCEDURE
DESIRED RESULTS OR SETUP SCREEN
On test select: • Set EXT STBY switch to STBY • Set POWER switch OFF On ATC-601: • Select POWER TEST • Press RUN to indicate TEST RUNNING ------>
** POWER TEST - Top Antenna ANTENNA UNITS ERP MTL *****
TEST RUNNING
** STATUS NO REPLY
*****
Note: If necessary, press SELECT (or SLEW) to select Top Antenna. Be sure that the ATC-601 rf cable is connected to the top antenna port and the rf termination is connected to the bottom port. On DATATRAC ( ): set screen ------>
-----------------RCV 1--(ALL)---12.5 KHz Lbl SDI 32-Hex Data-1 SSM Par msec ... no data present ... -ON-------------XMT 1 ----------12.5 KHz Lbl SDI 32-Hex Data-1 SSM Par msec 031 01 15 66 C1 98 00 1 0100 203 01 64 00 01 C1 11 1 0100
On test : • Set POWER switch ON • Set EXT STBY switch to OPR
** POWER TEST - Top Antenna ANTENNA UNITS ERP MTL Top dBm 55.7 -76.0
** STATUS ED
***** TEST RUNNING *****
After a few seconds, the ATC-601 shows ----> On ATC-601: Press RUN/STOP to stop the test. If the UUT is a TDR-94, skip this step. On test : • Set EXT STBY switch to STBY • Set POWER switch OFF • On TDR-94D mount: Swap the rf cable connection and termination on the UUT antenna ports. (Rf cable to bottom port and termination to top antenna port.) On test : • Set POWER switch to ON • Set EXT STBY switch to OPR On ATC-601: • Press RUN to indicate TEST RUNNING Wait a few seconds then press RUN/STOP to stop the test.
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If a failure is detected, a small arrow will be shown to the left of the offending parameter(s). Make a note of the test results, if a record is needed, and label it as applicable to the UUT bottom antenna port. The data displayed here will be overwritten on the next test. You should see a similar display on the ATC-601 except this data is applicable to the top antenna port. The data can be slightly different. See below for test tolerances and an explanation of a possible failure indication due to high sensitivity. Note: You may also select bottom antenna screen on the ATC-601. Note: You may see a marginal test failure if the UUT is relatively cold. In this case allow the unit to warm up a few minutes and then repeat the test.
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maintenance 523-0775657 Table 5-11 Acceptance Test Procedures, Using the DATATRAC 400 or DATATRAC 400H Databus Analyzer (Cont).
STEP 3.0 (cont’d)
TITLE Power output and Rcvr Sensi-tivity Test (cont’d)
PROCEDURE
DESIRED RESULTS OR SETUP SCREEN
The test tolerances are: ERP: > 48.5 dBm and < 57.0 dBm MTL: -73.0 (±4.0) dBm The ATC-601 will indicate that the UUT has FAILED if the MTL is more than -77.0 dBm or less than 71 dBm. Collins prefers, however, that a FAILURE should be reported only if the MTL is less than 71 dBm. Therefore, if you have a unit displaying an MTL of -77.1 or more, you should see that value as acceptable. Obviously, an MTL indication approaching -80 dBm or more may be cause for suspecting a problem with test set calibration. You may also see a failure because the ERP, Effective Radiated Power or Peak Pulse Power , is more than 57 dBm. Power measurements taken with a ramp tester can be confusing. The various test equipment manufacturers use different dimensions for displaying the test results, the test specifications are not always clear on how the test is to be performed to produce the specified result, and the test method; direct or radiation, yields different results. As in the case of MTL, an ERP slightly greater than 57 dBm ( e.g., 59 dBm max), using the direction connection method, should not be seen as cause for unit rejection. DO-181 specifies the transponder power output at the antenna. Testing a unit on the bench by direct connection to the antenna port yields a power reading at the transmitter output. The difference is, of course, antenna cable and connector losses. DO-181 specifies transponder power output in watts and dBW. The IFR ATC-601 displays power in dBm (ERP). The TIC-48/-49 displays power in watts. The following chart may be useful for proper test evaluation:
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Watts
dBW
dBm
50 70 100 125 150 200 250 300 350 400 450 500
16.99 18.45 20.00 20.97 21.76 23.01 23.98 24.77 25.44 26.02 26.53 26.99
46.99 48.45 50.00 50.97 51.76 53.01 53.98 54.77 55.44 56.02 56.53 56.99
TDR-94/94D Spec
(Min for airplanes limited to 15 000 ft and 175 kts.) Minimum at antenna (ramp testing)
Minimum direct (on bench)
Maximum at antenna
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maintenance 523-0775657 Table 5-11 Acceptance Test Procedures, Using the DATATRAC 400 or DATATRAC 400H Databus Analyzer (Cont).
STEP 4.0
TITLE Gillham Altitude Test
PROCEDURE On ATC-601: select
DESIRED RESULTS OR SETUP SCREEN ** ATCRBS REPLY TEST **
ATCRBS REPLY TEST ----------->
(lines 2-4 are irrelevant) CODE=
ALT=
[
]
Press RUN to start
On test select: • ALT TYPE SELECT: ARINC 572 • ARINC 572 ALT IN: TO TDR On DATATRAC ( ): • Set XMT 1 label 203 word to OFF • Set RCV 1 and XMT 1 screen ------>
-----------------RCV 1--(ALL)---12.5 KHz Lbl SDI 32-Hex Data-1 SSM Par msec ... no data present ...
On test : • Set all ARINC 572 switches to OFF: Then set A4, C2, C4, and B4 to SEL. • Set POWER to ON • Set EXT STBY switch to OPR
The XFEED OUT lamp turns on. The ATC-601 REPLY lamp indicates that UUT is responding to interrogations.
DATATRAC ( ) RCV 1 screen shows: ------------------->
----------------RCV 1--(ALL)---12.5 Lbl SDI 32-Hex Data-1 SSM Par 203 01 E0 B8 61 C1 11 1 031 01 F5 66 81 98 11 1
-ON-------------XMT 1 ----------12.5 KHz Lbl SDI 32-Hex Data-1 SSM Par msec 031 01 15 66 C1 98 00 1 0100
KHz msec 0200 0200
(ignore any other displayed labels) On ATC-601: • Press RUN. Screen shows: -------------------->
** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE=5263 *****
ALT=5900 FT TEST RUNNING
[4460] *****
(The CODE 5263 depends on your selection in the 031 XMT 1 word. See note 1 under step 1.2 above) At this step you are asked to toggle each of the ARINC 572 switches and the altitude display. You should also watch the RCV 1 data word on the DATATRAC ( ) display. By cycling each switch between OFF and SEL you should see the ATC601 display and the DATATRAC ( ) 203 data word change. If the displays do not change for a particular switch, this would indicate either an open or a shorted code line. If the wrong altitude is shown, this would suggest that the code line is affecting another line; i.e., causing two or more inputs to change simultaneously. In either case the UUT, the test , or the interconnecting cable needs repair. Set each switch as shown in the listing below to the (position) shown, and back, and the altitude display at both positions. The altitude display should always revert to the initial display when the switch is returned to its original position. There is no serious need to the correctness of the RCV word as long as the ATC-601 display is correct. SWITCH Initial A1 (SEL) A2 (SEL) A4 (OFF) C1 (SEL) C2 (OFF)
DISPLAYED ALTITUDE 5,900 FT [4460] 23,600 FT [5460] 7,600 FT [6460] -400 FT (0460] none (blank; this is invalid) 5,800 FT [4440]
SWITCH C4 (OFF) B1 (SEL) B2 (SEL) B4 (OFF) D2 (SEL) D4 (SEL)
DISPLAYED ALTITUDE 6,000 FT [4420] 3,600 FT [4560] 5,600 FT [4660] 6,600 FT [4060] 119,600 FT [4462] 55,600 FT [4464]
For addtional information on Gillham code structure, refer to paragraph 5.7 in this section.
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maintenance 523-0775657 Table 5-11 Acceptance Test Procedures, Using the DATATRAC 400 or DATATRAC 400H Databus Analyzer (Cont).
STEP 5.0
TITLE CSDB tuning test
PROCEDURE
This test cannot be performed using a DATATRAC 400/400H because these instruments are not capable of transmitting or receiver CSDB data. However, as an acceptable alternative, you can use a CTL-92/92A, connected to the test using the cable shown in figure 907. • Turn power off and connect CTL-92/92A to test . Be sure CTL-92/92A mode knob is set to OFF. • Turn power on and set the CTL-92/92A mode knob to ALT. On the CTL: • Set the CTL-92/92A to 5263 or any desired ident code.
5.1
CSDB altitude test
DESIRED RESULTS OR SETUP SCREEN
** ATCRBS REPLY TEST **
(lines 2-4 are irrelavent) CODE=5263 *****
ALT=32 800 FT [1344] TEST RUNNING *****
On test : • Set CONTROL DATA SELECT to CSDB • Set OUTPUT PORT SELECT to CSDB PORT 1 • Set ALT TYPE SELECT to CSDB • Set ARINC 572 ALT IN to TO CTL • Set SOURCE SELECT to CTL
The CODE 5263 depends on your selection on the CTL92/92A code select knobs. See note 1 under step 1.2 above. The ALT display depends on the altitude selection on the test ARINC 572 ALT IN switches.
On the test : • Set OUTPUT PORT SELECT to CSDB PORT 2
Be sure that the ACT display, on the CTL-92/92A, does not flash. A flashing ACT at either port selection indicates that output port has failed. If both ports flash, there may be a problem with the test wiring or the CTL input.
Be sure that the ACT display, on the CTL-92/92A does not flash. A flashing ACT indicates that the control label 1F data, from the TDR, does not agree with the CLT-92/92A output label 1E data to the TDR. Only one of the two data CTL input ports is being used; pins U/V.
In this altitude test configuration, Gillham altitude data is being supplied to the CTL (ARINC 572 ALT IN to CTL). The CTL converts this data to CSDB and supplies it to the TDR via the CSDB data output port (only 1 port is used; pins S/R). The CSDB altitude data is being read on the control bus input (SOURCE SELECT to CTL). You can this by setting the CTL mode switch to ON. If you suspect a problem with the altitude data, check the following:
On the test : • Set ARINC 572 ALT IN to TO TDR • Set ALT TYPE SELECT to ARINC 572 • Set SOURCE SELECT to SEL
The ATC-601 ALT display should be the same as above since the ultimate source of altitude information is the same in both tests. If it is different here, suspect a problem with one or more of the altitude discrete inputs to the CTL. If you encounter such a problem, you can identify the defective discrete by returning these three switches to the settings above and then performing the ARINC 572 switching sequence shown following step 4.0 above.
On test : • Set power to OFF • Disconnect the CTL-92/92A from the test • Set CONTROL DATA SELECT ARINC PORT to PA • Set OUTPUT PORT SELECT to ARINC 429 PORT A
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maintenance 523-0775657 Table 103. Acceptance Test Procedures, Using the DATATRAC 400 or DATATRAC 400H Databus Analyzer (Cont).
STEP 6.0
TITLE ARINC 429 Altitude Test
PROCEDURE On ATC-601: select ATCRBS REPLY TEST and press RUN to indicate TEST RUNNING --------->
DESIRED RESULTS OR SETUP SCREEN ** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE= *****
ALT= [ ] TEST RUNNING *****
On test : • Set EXT STBY switch to STBY • Set POWER switch to OFF • ALT TYPE SELECT: ARINC 429 • OUTPUT PORT SELECT: ARINC 429 PORT A On DATATRAC ( ): • Set XMT 1 to ON • Setup screen ------>
-----------------RCV 1--(ALL)---12.5 KHzLbl SDI 32-Hex Data-1 SSM Par msec ... no data present ...
On test : • Set POWER to ON • EXT STBY to OPR
The XFEED OUT lamp turns on. The ATC-601 REPLY lamp indicates that UUT is responding to interrogations.
The ATC-601 screen shows: --->
-ON-------------XMT 1 ----------12.5 KHz Lbl SDI 32-Hex Data-1 SSM Par msec 031 01 15 66 C1 98 00 1 0100 203 01 64 00 01 C1 11 1 0100
** ATCRBS REPLY TEST **
(lines 2-4 are irrelavent) CODE=5263 *****
ALT=32 800 FT [1344] TEST RUNNING *****
(The CODE 5263 depends on your selection in the 031 XMT 1 word. See note 1 under step 1.2 above.) DATATRAC ( ) RCV 1 screen shows: ------>
-----------------RCV 1--(ALL)---12.5 KHz Lbl SDI 32-Hex Data-1 SSM Par msec 203 01 64 00 01 C1 11 1 0200
(ignore any other displayed labels)
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maintenance 523-0775657 Table 103. Acceptance Test Procedures, Using the DATATRAC 400 or DATATRAC 400H Databus Analyzer (Cont).
STEP 6.1
TITLE ARINC Control Discretes Tests (cont’d)
PROCEDURE On the test : • Be sure the SOURCE SELECT switch is set to SEL. On the test : • Set the REP ALT SEL switch to PB
DESIRED RESULTS OR SETUP SCREEN ** ATCRBS REPLY TEST **
(lines 2-4 are irrelavent) CODE=5263 *****
ALT=32 800 FT [1344] TEST RUNNING *****
Notice that the ATC-601 altitude display blanks. Note: At this point the UUT is configured to report altitude data from port B. There is none so the display blanks.
On the test : • Move the parallel connection from the PRIMARY DIGITAL ALTITUDE SOURCE jack to the ALTERNATE DIGITAL ALTITUDE SOURCE jack.
Notice that the ATC-601 altitude display returns.
On the test : • Set the REP ALT SEL switch to PA
Notice that the ATC-601 altitude display blanks.
Note: This verifies that UUT is configured to report altitude data being supplied on port B.
Note: UUT is returned to port A. This series of steps has verified that the Reporting Altitude discrete is switchable.
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On the test : • Set the SOURCE SELECT switch to CTL
Notice that the ATC-601 altitude display returns.
On the test : • Disconnect the parallel connection from the ALTERNATE DIGITAL ALTITUDE SOURCE jack. (Wait about 5 seconds)
Notice that the ATC-601 altitude display remains.
On DATATRAC ( ): • Set the SOURCE SELECT switch to SEL.
Notice that the ATC-601 altitude display blanks.
On test : • Reconnect the parallel connection to the ALTERNATE DIGITAL ALTITUDE SOURCE jack.
Notice that the ATC-601 altitude display remains blanked.
Note: This switches the UUT to the altitude data supplied on the control port.
Note: This verifies the previous step; that altitude is being drawn from the control port; all other sources are disconnected.
Note: This verifies that the Source Select Discrete is switchable.
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maintenance 523-0775657 Table 103. Acceptance Test Procedures, Using the DATATRAC 400 or DATATRAC 400H Databus Analyzer (Cont).
STEP
TITLE
6.1 (cont’d)
ARINC Control Discretes Tests (cont’d)
PROCEDURE
DESIRED RESULTS OR SETUP SCREEN
On test : • Set the AUTO ALT switch to SEL (-003 UUT units only)
Notice that the ATC-601 altitude display returns.
On test : • Set the AUTO ALT switch to OFF (-003 UUT units only)
Notice that the ATC-601 altitude display blanks.
On the DATATRAC: • Set the XMT 1 label 031 word to -------->
-ON-------------XMT 1 ----------12.5 KHz Lbl SDI 32-Hex Data-1 SSM Par msec 031 01 95 66 E1 98 00 1 0100
Note: This enables the automatic altitude port select feature and verifies that the UUT does switch to alternate port B even though port A is the selected port.
Note: This enables the AUTO ALT discrete is switchable.
Notice that the ATC-601 altitude display returns. Note: This digitally switches the UUT to port B. If this test is correct while the earlier test of port B altitude failed, suspect a problem with the Reporting Altitude Select discrete. If both tests failed, suspect a problem with the altitude data receivers. On test : • Set EXT STBY switch to STBY. • Set the POWER switch OFF. • Set the AUTO ALT switch to OFF. On DATATRAC ( ): • Set the XMT 1 label 031 word to ------>
-ON-------------XMT 1 ----------12.5 KHz Lbl SDI 32-Hex Data-1 SSM Par msec 031 01 15 66 C1 98 00 1 0100
If you wish, you can set the XMT 1 label 203 data field bits 12 through 28 to any combination of 1 and 0. The RCV 1 label 203 word data field will follow the XMT 1 word exactly while the ATC-601, set to the ATCRBS REPLY TEST mode, will show the altitude to the nearest 100 feet. When set to the MODE UF0 TEST, the ATC-601 displays altitude to the nearest 25
feet. The label 203 bit values are shown in note 2 following step 1.2. To 1. 2. 3. 4. 5. 6.
simulate any altitude up to about 131,000 feet: Select the desired altitude. Find the data bit with the maximum bit value less than the selected altitude. Make a note of that bit number. Subtract that bit value from your selected value. Find the next bit with the maximum bit value less than the remainder. Make a note of that bit number. Subtract that bit value from your remainder. Repeat steps 4 and 5 until the remainder is 0.
In the XMT 1 label 203 data word, set all noted bits to 1. You should see your selected altitude, to the nearest 100 feet, displayed on the ATC-601. 7.0
ARINC 575 Altitude Test
On test : • SOURCE SELECT: SEL • ALT TYPE SELECT: ARINC 429 On DATATRAC ( ): • Set screen ------> Note: The binary data format is retained here to emphasize the similarity between ARINC 429 and ARINC 575. If you are more comfortable with the Hex data format, feel free to use it instead.
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-----------------RCV 1--(ALL)---12.5 KHz Lbl SDI 29--Binary Data--11 SSM Par msec ... no data present ... -ON--------------XMT 1----------12.5 KHz Lbl SDI 29--Binary Data--11 SSM Par msec 031 01 0000000111011111011 00 1 0100 203 01 0010001010101010100 00 1 0100
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maintenance 523-0775657 Table 103. Acceptance Test Procedures, Using the DATATRAC 400 or DATATRAC 400H Databus Analyzer (Cont).
STEP 7.0 (cont’d)
TITLE ARINC 575 Altitude Test (cont’d)
PROCEDURE
DESIRED RESULTS OR SETUP SCREEN
On test : • Connect parallel control cable to PRIMARY DIGITAL ALTITUDE SOURCE jack. • Set POWER switch to ON. • Set EXT STBY switch to OPR. On ATC-601: • Select ATCRBS REPLY TEST and press RUN to indicate TEST RUNNING. ATC-601 screen --------> On test : • Set ALT TYPE SELECT switch to ARINC 575 On DATATRAC: • Set XMT 1 label 203 word --------> (just change the SSM to 00) ATC-601 screen -------->
** ATCRBS REPLY TEST **
(lines 2-4 are irrelavent) CODE=5263 *****
-ON--------------XMT 1----------12.5 KHz Lbl SDI 29--Binary Data--11 SSM Par msec 203 01 0010001010101010100 00 1 0100
** ATCRBS REPLY TEST **
(lines 2-4 are irrelavent) CODE=5263 *****
DATATRAC screen --------->
ALT=35,500 FT [5524] TEST RUNNING *****
ALT=17,700 FT [3740] TEST RUNNING *****
-----------------RCV 1--(ALL)---12.5 KHz Lbl SDI 29--Binary Data--11 SSM Par msec 203 01 0001000101010101010 11 1 0100 | | | | | | | / / / / / / / | | | | | | | -ON--------------XMT 1----------12.5 KHz Lbl SDI 29--Binary Data--11 SSM Par msec 203 01 0010001010101010100 00 1 0100
In addition to testing the altitude type select discrete, this test illustrates the differences between ARINC 429 and ARINC 575 data. Notice that the bits in the RCV 1 label 203 word (above) are offset to the right by one bit from the XMT 1 label 203 word and the SSM code is 11 as opposed to the 00 in the XMT 1 word. In ARINC 575, the LSB is bit 13; in ARINC 429 the LSB is bit 12. In ARINC 575, bits 30 and 31 determine the sign; 00 being positive. Notice also, that the altitude displayed on the ATC-601 corresponds to the code in the RCV 1 word; not the XMT 1 word. This is also due to the UUT being configured for ARINC 575 and thus the bit values are offset by 1 bit position which has the effect of changing the altitude by a factor of 1/2. On test : • Set ALT TYPE SELECT switch to ARINC 429 On DATATRAC: • Set XMT 1 label 203 word ----> ATC-601 screen:
-ON--------------XMT 1----------12.5 KHz Lbl SDI 29--Binary Data--11 SSM Par msec 203 01 0010001010101010100 11 1 0100
** ATCRBS REPLY TEST **
(lines 2-4 are irrelavent) CODE=5263 *****
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ALT=35,500 FT [5524] TEST RUNNING *****
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maintenance 523-0775657 Table 5-11 Acceptance Test Procedures, Using the DATATRAC 400 or DATATRAC 400H Databus Analyzer (Cont).
STEP 8.0
TITLE Mode S Address Discretes Test
PROCEDURE
DESIRED RESULTS OR SETUP SCREEN
On the test : • Set POWER switch OFF • Set all test mode s address switches to SEL except switch P1-56; set it to OFF. • Set POWER switch ON On ATC-601: • Set for MODE S ALL CALL TEST ------->
** MODE S ALL CALL TEST - NO REPLY ALL CALL ADDRESS = [ NUMBER = Press RUN to start
On ATC 601: • Press RUN • Note screen ----->
** MODE S ALL CALL TEST ALL CALL ADDRESS = FFFFFE TAIL NUMBER =
** ]
TAIL
ED ** [77777776]
****** TEST RUNNING *****
The remainder of this step should be seen as optional unless you have reason to suspect a failure in one or more of the address discrete lines. The procedure will require a few minutes because of the delay involved in cycling power between each switch setting.
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On test : • Set POWER switch OFF. • Set each triad of address switches for an octal digit 6. • Set POWER switch ON.
After a few seconds, UUT begins to reply and shortly thereafter the ATC-601 screen shows the following address:
On test : • Set POWER switch OFF. • Set each triad of address switches for an octal digit 4. • Set POWER switch ON.
After a few seconds, UUT begins to reply and shortly thereafter the ATC-601 screen shows the following address:
On test : • Set POWER switch OFF. • Set each triad of address switches for an octal digit 0, except the eighth triad which is set to 1. • Set POWER switch ON.
After a few seconds, UUT begins to reply and shortly thereafter the ATC-601 screen shows the following address:
ALL CALL ADDRESS = DB6DB6
ALL CALL ADDRESS = 924924
ALL CALL ADDRESS = 000001
[66666666]
[44444444]
[00000001]
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maintenance 523-0775657 Table 5-11 Acceptance Test Procedures, Using the DATATRAC 400 or DATATRAC 400H Databus Analyzer (Cont).
STEP 9.0
TITLE TCAS / NO TCAS Discrete Select and TCAS Bus Test
PROCEDURE
DESIRED RESULTS
On test : • Set POWER switch OFF On DATATRAC ( ): • Same setup as STEP 1.1. ATC-601 is not needed for this test but can be left on. On test : • Set POWER switch ON
After a few seconds the RCV 1 portion of the DATATRAC ( ) screen shows:
After data appears on the RCV 1 display, press RCV and then ENT and use the down arrow key to scroll the words so that you can see the 350 word.
-----------------RCV 1--(ALL)---12.5 KHz Lbl SDI 32-Hex Data-1 SSM Par msec 350 01 00 00 01 17 11 1 0200
On test : • Set POWER switch to OFF • Set TCAS/NO TCAS switch to TCAS On DATATRAC ( ): • Press RCV and then ENT On test : • Set POWER switch to ON
After a few seconds the RCV 1 portion of the DATATRAC ( ) screen shows: (use down arrow key to scroll words) -----------------RCV 1--(ALL)---12.5 KHz Lbl SDI 32-Hex Data-1 SSM Par msec 350 01 68 B3 01 17 11 1 0200 |<---diagnostic code B3
This display shows a diagnostic B3 which is interpreted: TCAS Bus Inactive. This verifies that the discrete properly configures the unit for operation with a TCAS. However, no TCAS data is being supplied in this step, therefore, the unit declares a B3 diagnostic.
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maintenance 523-0775657 Table 5-11 Acceptance Test Procedures, Using the DATATRAC 400 or DATATRAC 400H Databus Analyzer (Cont).
STEP 9.0 (cont’d)
TITLE TCAS Bus Test, XPDR to TCAS
TCAS to XPDR Bus Test
PROCEDURE
DESIRED RESULTS
Connect the DATATRAC RCV 1 to the TCAS OUT jack. that the data word labels are detectable as shown -->.
-----------------RCV 1--(ALL)----100 KHz Lbl SDI 32-Hex Data-1 SSM Par msec 275 00 80 00 00 BD 00 1 0150 276 10 80 F8 02 7D 00 1 0150 350 01 68 B3 01 17 11 1 0150
Note: Except for the diagnostic code in the label 350 data word, the data content is not important. It is quite likely that the data will be different. The presence of the data word labels shown verifies that the TCAS data bus output is active and appears to be normal.
Notice the higher speed. Other labels may also be present.
Note: In this step you need the capability of transmitting data to two separate input ports simultaneously and at different speeds; the 031 control word must be low speed (12.5-kbps) while the TCAS label 274 data words must be high speed (100-kbps). All DATATRAC instruments, as well as the JC Air 429E, can transmit at either of these speeds but only the DATATRAC 400 can do so on two separate ports simultaneously. Otherwise, you will need two simulators. If you do not have this capability, you may not be able to the integrity of the TCAS bus input port. If you are using a DATATRAC 400, or have access to a second bus simulator, connect your second transmitter port or data bus simulator to the TCAS IN and setup as shown -------->:
-ON-------------XMT 2 -----------100 KHz Lbl SDI 32-Hex Data-1 SSM Par msec 274 00 18 00 00 3D 00 1 0100
On bus reader RCV display:
After a few seconds, the 350 word shows:
Note: The objective is to that the UUT recognizes a valid TCAS label 274 word and declares this by removing the diagnostic B3.
-----------------RCV 1--(ALL)---12.5 KHz Lbl SDI 32-Hex Data-1 SSM Par msec 350 01 68 00 01 17 11 1 0150 |<---diagnostic code 00
On the bus reader: Set the XMT 2 word to OFF
After a few seconds, notice that the B3 diagnostic returns.
Note: Be sure to set the higher speed.
Note: Disconnect XMT 2 from the TCAS IN jack and reconnect RCV 1 to the DATA BUS OUTPUT port. Final step in this test, all setups
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On test : • Set POWER switch to OFF • Set TCAS/NO TCAS switch to NO TCAS On DATATRAC ( ): • Press RCV and then ENT On test : • Set POWER switch to ON
After a few seconds, the original 350 word returns: -----------------RCV 1--(ALL)---12.5 KHz Lbl SDI 32-Hex Data-1 SSM Par msec 350 01 00 00 01 17 11 1 0200
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STEP 10.0
TITLE Side 1/ Side 2 Discrete Test
PROCEDURE
DESIRED RESULTS
On test : • Set POWER switch OFF • Be sure SIDE 1/SIDE 2 switch is set to SIDE 1. On DATATRAC ( ): • Same setup as STEP 9.0. On ATC-601: • Set for ATCRBS REPLY TEST screen -->
On test : • Set POWER switch ON
** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE= *****
ALT= TEST RUNNING
[ *****
]
After a few seconds, X FEED OUT and ATC-601 REPLY lamps light and the ATC-601 shows: ** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE=5263 ALT=32,800 FT [1344] ***** TEST RUNNING *****
On test : • Set POWER switch to OFF • Set SIDE 1/SIDE 2 switch to SIDE 2 • Set POWER switch to ON
Note that unit does not reply (X FEED OUT lamp and REPLY lamps are off and no altitude is displayed on ATC-601). Wait about 10 seconds. Note: UUT does not respond because the SDI and side strapping do not agree. Note: Be sure to allow adequate time for the U to reinitialize properly between power off and power on. The SIDE 1/2 strap is one of several that are monitored only at processor initialization. Therefore, if this tests fails, cycle power again but allow more time between power off and power on.
On DATATRAC ( ): • On XMT 1, label 031 word, set the SDI to 10 and press ENTER
Notice that unit begins to reply almost immediately (XFEED OUT lamp turns on and ATC-601 REPLY lamp lights). Note: UUT responds because the SDI and side strapping agree.
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On DATATRAC ( ): • On XMT 1, label 031 word, set SDI to 01 and press ENTER.
Notice that unit stops replying (X FEED OUT lamp and ATC-601 REPLY lamps turn off).
On test : • Set POWER switch OFF • Set SIDE 1/SIDE 2 switch to SIDE 1 • Set POWER switch ON
After a few seconds, X FEED OUT and ATC-601 REPLY lamps light and the ATC-601 shows that the UUT is replying.
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maintenance 523-0775657 Table 5-11 Acceptance Test Procedures, Using the DATATRAC 400 or DATATRAC 400H Databus Analyzer (Cont).
STEP 11.0
TITLE AIR/ GND Discrete Test
PROCEDURE
DESIRED RESULTS
On test : • Set POWER switch OFF • TDR ALT SOURCE: EXT DIRECT • ALT TYPE SELECT: ARINC 429 On DATATRAC ( ): • Same setup as STEP 9.0. On ATC-601: • Set for MODE S UF4 TEST screen ----->
** MODE S UF4 TEST - NO REPLY ** DF FS= ADDRESS= *****
On test : • Set POWER switch ON ATC-601 screen shows ----->:
DR=
UM=
TEST RUNNING
AC= *****
After a few seconds, X FEED OUT and ATC-601 REPLY lamps light and the ATC-601 shows: ** MODE S UF4 TEST - ED ** DF 4 FS=0 DR=00 UM=00 ADDRESS=000001 *****
TEST RUNNING
AC=32,775 FT *****
Note: Initially the screen will show FS=2 for about 2 seconds and then change to FS=0. On test : • Set AIR/GND switch to GND
After a few seconds, the ATC-601 shows: ** MODE S UF4 TEST - ED ** DF 4 FS=1 DR=00 ADDRESS=000001 *****
UM=00 AC=32,775 FT
TEST RUNNING
*****
Of particular significance here is the FS (flight status) indication. For a detailed description of each of these message fields, refer to the Theory of Operation section. On test : • Set AIR/GND switch to AIR
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After a few seconds, notice that the ATC-601 FS field again shows 0.
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maintenance 523-0775657 Table 5-11 Acceptance Test Procedures, Using the DATATRAC 400 or DATATRAC 400H Databus Analyzer (Cont).
STEP 12.0
TITLE DL ANT/ SGL ANT Discrete Test (TDR-94D only)
PROCEDURE
DESIRED RESULTS
On test : • Set POWER switch OFF On DATATRAC ( ): • Same setup as STEP 9.0. On ATC-601, set for SQUITTER TEST screen -----> Be sure the ATC-601 is connected to the top antenna port. On test : • Set DL ANT/SGL ANT switch to DL ANT • Set POWER switch ON You can watch the PERIOD display for a time.
** SQUITTER TEST - NO REPLY ** PERIOD = SECONDS TAIL NUMBER = SQUITTER ADDRESS= [ *****
TEST RUNNING
]
*****
After a few seconds, the ATC-601 screen shows: See note below. ** SQUITTER TEST - ED PERIOD = 2.00 SECONDS TAIL NUMBER = SQUITTER ADDRESS= [ *****
TEST RUNNING
** ]
*****
See the note at the end of this step for test tolerances. On test : • Set POWER switch OFF • Set DL ANT/SGL ANT switch to SGL ANT • Set POWER switch ON
After a few seconds, the ATC-601 screen shows: ** SQUITTER TEST - FAILED PERIOD = SECONDS TAIL NUMBER = SQUITTER ADDRESS= [ *****
TEST RUNNING
** ]
*****
Note: This test is intended to fail. When the UUT is set for single antenna operation, there is no transmission from the top antenna port. Therefore, if this test indicates ED, recheck all switch settings or suspect a problem with the SGL/DL ANT select strap. It should not . On test : • Set POWER switch OFF On ATC-601: • Press RUN to stop the test. • Remove rf terminator from bottom antenna connector • Connect ATC-601 cable to bottom antenna connector • Connect rf terminator to top antenna connector
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STEP 12.0
TITLE DL ANT /SGL ANT Discrete Test (cont’d) (TDR-94D only)
PROCEDURE On test : • Set POWER switch ON On ATC-601: • Press RUN to start the test.
DESIRED RESULTS After a few seconds, the ATC-601 screen shows: See note below. ** SQUITTER TEST - ED PERIOD = 1.00 SECONDS TAIL NUMBER = SQUITTER ADDRESS= [ *****
On test : • Set POWER switch OFF • Set DL ANT/SGL ANT switch to DL ANT • Set POWER switch ON
TEST RUNNING
** ]
*****
After a few seconds, the ATC-601 screen shows: See note below. ** SQUITTER TEST - ED PERIOD = 2.00 SECONDS TAIL NUMBER = SQUITTER ADDRESS= [ *****
TEST RUNNING
** ]
*****
Note: The PERIOD value tends to vary somewhat in all cases. When the UUT is set for dual antenna operation and the ATC-601 is monitoring the top or the bottom antenna port, the value can vary from 1.6 to 2.4. When the TDR-94D is set for single antenna operation, or the UUT is a TDR-94, there is no transmission from the top antenna port and and the transmission PERIOD from the bottom antenna port can vary from 0.6 to 1.4. 13.0
Burst Tune and CrossFeed In Discrete Test
On test : • Set POWER switch OFF • Set CONTROL DATA SELECT to PA • Set ALT TYPE SELECT to ARINC 429 • Set SOURCE SELECT to SEL On DATATRAC ( ): • Same setup as STEP 1.1. On ATC-601, set for SQUITTER TEST screen -----> If necessary, reconnect ATC-601 to top antenna connector, with terminator on bottom connector.
** SQUITTER TEST - NO REPLY ** PERIOD = SECONDS TAIL NUMBER = SQUITTER ADDRESS= [ ] *****
TEST RUNNING
*****
On test : • Set POWER switch ON
After a few seconds, the test X FEED OUT and the ATC-601 REPLY lamps light indicating that the unit is replying. The ATC-601 screen data indicates ED.
On test : • Set X FEED IN/OUT switch to IN
Notice that both X FEED lamps are lighted.
On DATATRAC ( ): • Set XMT 1 to OFF
Notice that the X FEED OUT and ATC-601 REPLY lamps turns off (X FEED IN stays on).
(With the cursor on the 1, press ENT)
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STEP 13.0 (cont’d)
14.0
TITLE Burst Tune and CrossFeed In Discrete Test (cont’d)
Output Port Discrete Test
PROCEDURE
DESIRED RESULTS
On DATATRAC ( ): • Set XMT 1 to ON
Notice that the X FEED IN and OUT and REPLY lamps are lighted.
On test : • Set X FEED IN/OUT switch to OUT • Set BURST TUNE switch to ON On DATATRAC ( ): • Set XMT 1 to OFF
Notice that UUT continues to reply. Watch the unit for a few seconds.
On test : • Set BURST TUNE switch to OFF
Notice that UUT stops replying (X FEED OUT and REPLY lamps turn off).
On test : • Set BURST TUNE switch to ON
Notice that UUT does not reply (X FEED OUT and REPLY lamps do not light).
On DATATRAC ( ): • Set XMT 1 to ON
Notice that UUT replys (X FEED OUT and REPLY lamps are on).
On test : • Set BURST TUNE switch to OFF On DATATRAC ( ): • Set XMT 1 to OFF
Notice that UUT stops replying (X FEED OUT and REPLY lamps are off).
On test : • Set BURST TUNE switch to ON On DATATRAC ( ): • Set XMT 1 to ON
X FEED OUT lamp flashes while XMT 1 is on .
On test : • Set XMT 1 to OFF
X FEED OUT lamp remains off when XMT is OFF.
On test : • Set BURST TUNE switch to OFF • Set SOURCE SELECT switch to SEL • ALT TYPE SELECT: ARINC 429 • CONTROL DATA PORT SEL: PA • OUTPUT PORT SELECT: ARINC 429 PORT A On DATATRAC ( ): • The same as STEP 1.1 • Set XMT 1 to ON On ATC-601, set for SQUITTER TEST screen ----->
** SQUITTER TEST - NO REPLY ** PERIOD = SECONDS TAIL NUMBER = SQUITTER ADDRESS= [ *****
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TEST RUNNING
]
*****
On test : • Set POWER switch ON
After a few seconds, the test X FEED OUTand the ATC-601 REPLY lamps light indicating that the unit is replying. The ATC-601 screen data indicates ED.
On test : • Set OUTPUT PORT SELECT switch to ARINC 429 PORT B
Notice that there is no change in the test result; X FEED OUT and REPLY lights are on and ATC-601 display does not change.
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STEP 15.0
TITLE Control Data Input Port Select Discrete Test
PROCEDURE
DESIRED RESULTS
On test : • Set POWER switch OFF • Set SOURCE SELECT switch to SEL • ALT TYPE SELECT: ARINC 429 • CONTROL DATA SELECT: ARINC PORT PA On DATATRAC ( ): • Same setup as for STEP 9.0. On ATC-601, set for SQUITTER TEST screen ----->
** SQUITTER TEST - NO REPLY ** PERIOD = SECONDS TAIL NUMBER = SQUITTER ADDRESS= [ ] *****
16.0
Manual STBY Discrete Test
TEST RUNNING
*****
On test : • Set POWER switch ON
After a few seconds, the test X FEED OUTand the ATC-601 REPLY lamps light indicating that the unit is replying. The ATC-601 screen data indicates ED.
On test : • Set CONTROL DATA SELECT switch to ARINC PORT PB
Notice that there is no change in the test result; X FEED OUTand REPLY lights are on and ATC-601 display does not change.
On test : • Set CONTROL DATA SELECT switch to ARINC PORT PC
Notice that there is no change in the test result; X FEED OUT and REPLY lights are on and ATC-601 display does not change.
On test : • Set EXT STBY switch to STBY • Set POWER switch OFF • Set CONTROL DATA SELECT switch to ARINC PORT PA On DATATRAC ( ): • Same setup as for STEP 9.0. On ATC-601: • Set for ATCRBS REPLY TEST screen ---------->
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** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE= *****
ALT= [ ] TEST RUNNING *****
On test : • Set POWER switch ON • Set EXT STBY switch to OPR
After a few seconds, the test X FEED OUTand the ATC-601 REPLY lamps light indicating that the unit is replying. The ATC-601 screen data indicates ED.
On test : • Set EXT STBY switch to STBY
Note that X FEED OUT lamp and ATC-601 REPLY lamps turn off and ATC-601 indicates NO REPLY. See note below.
On test : • Set EXT STBY switch to OPR
Note that X FEED OUT lamp and ATC-601 REPLY lamps light almost immediately and ATC-601 indicates ED.
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STEP 17.0
TITLE Max Airspeed Test
PROCEDURE
DESIRED RESULTS
On test : • Set POWER switch OFF • ALT TYPE SELECT: ARINC 429 • Be sure that all three MAX AIRSPEED switches are set to OFF. On DATATRAC ( ): • Same setup as for STEP 9.0. (The DATATRAC is used here only for tuning data.) On ATC-601: • Set for MODE S UF0 TEST screen >
** MODE S UF0 TEST - NO REPLY ** DF
VS= ADDRESS= *****
On test : • Set POWER switch ON
RI=
AC=
TEST RUNNING
*****
After a few seconds, the test X FEED OUT lamp and the ATC-601 REPLY lamps light indicating that the unit is replying.
Note the ATC-601 screen ----------->
** MODE S UF0 TEST - ED ** DF 0 VS=0 RI=8 ADDRESS=000001 *****
AC= 32,775 FT
TEST RUNNING
*****
Exercise the MAX AIRSPEED switches on the test and the correct RI indication as shown in the following list. Cycle power and allow about 2 or 3 seconds of OFF time and about 5 seconds for processor initialization and ATC-601 response time between each switch setting. MAX AIRSPEED SWITCH BIT 15 BIT 16 BIT 17 OFF OFF OFF SEL OFF OFF OFF SEL OFF SEL SEL OFF OFF OFF SEL SEL OFF SEL OFF SEL SEL SEL SEL SEL
RI VALUE 8 9 A B C D E F (not an assigned configuration)
It is worth noting that in this test mode the ATC-601 displays the altitude to the nearest 25 feet.
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maintenance 523-0775657 Table 5-11 Acceptance Test Procedures, Using the DATATRAC 400 or DATATRAC 400H Databus Analyzer (Cont).
STEP 18.0
TITLE Ext Suppression Test
PROCEDURE
DESIRED RESULTS
On test : • ALT TYPE SELECT: ARINC 429 On DATATRAC ( ): • Same setup as for STEP 9.0. On ATC-601: • Set for ATCRBS REPLY TEST screen -----> • Connect scope channel A to the test SUPPR test points. • Connect scope channel B to the REPLY VIDEO BNC connector on the ATC-601. • Set the scope to display both channels
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** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE= *****
ALT= [ ] TEST RUNNING *****
Note a (approx) 30µs pulse on channel A. Note a reply waveform on channel B. If your scope is able, you will see the individual reply code pulses on channel B. You may also see the occasional squitter transmission which appears as a much longer series of pulses at about 1 transmission every 2 sec. Of particular importance, however, is that the channel A (suppression) pulse is about 30 µs long during ATCRBS reply, and brackets the 21 µs ATCRBS reply. During squitter transmission, the suppression pulse extends to bracket the squitter transmission. The squitter transmission is a DF11 reply about 72 µs long.
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maintenance 523-0775657 Table 5-11 Acceptance Test Procedures, Using the DATATRAC 400 or DATATRAC 400H Databus Analyzer (Cont).
STEP 19.0
TITLE ADLP Select, Discrete Strap Test
PROCEDURE
DESIRED RESULTS
On test : • Be sure DATALINK switch is set to NO ADLP. On DATATRAC ( ): • Same setup as for STEP 9.0. DATATRAC RCV 1 screen ------> Note: The ATC-601 is not needed for this test but it can remain connected and operating. On test : • Set POWER switch to OFF • Set DATALINK switch to ADLP. • Be sure DATALINK SELECT switch is set to A/B. • Set POWER switch to ON.
-----------------RCV 1--(ALL)---12.5 KHz Lbl SDI 32-Hex Data-1 SSM Par msec 350 01 60 00 01 17 11 1 0100
-----------------RCV 1--(ALL)---12.5 KHz Lbl SDI 32-Hex Data-1 SSM Par msec 350 01 64 A2 01 17 11 1 0100 |<---diagnostic code A2
Note: The diagnostic A2 identifies an inactive ADLP bus. This test verifies that the ADLP enable discrete is functional.
DATATRAC RCV 1 screen ------> On test : • Set POWER switch to OFF. • Set DATALINK switch to NO ADLP. • Set POWER switch to ON.
-----------------RCV 1--(ALL)---12.5 KHz Lbl SDI 32-Hex Data-1 SSM Par msec 350 01 60 00 01 17 11 1 0100 |<---diagnostic code 00
DATATRAC RCV 1 screen ------> Note: The Airborne Datalink system is not fully implemented at this time. If and when an ADLP (Airborne DataLink Processor) becomes available and operational, suitable procedures will be provided to the integrity of the ADLP input/output ports. At this point, therefore, verification of the ADLP SELECT strap is seen as sufficient to prevent nuisance diagnostics that can occur if the select input should be defective. You will notice that the DATALINK SELECT A/B, C/D function is also not tested.
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STEP 20.0
TITLE Remote IDENT Discrete Test
PROCEDURE
DESIRED RESULTS
On test : • Same as initial setup On DATATRAC ( ): • Same setup as for STEP 9.0. On ATC-601: • Setup for ATCRBS REPLY test
** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE= *****
On test : • Press and release the REMOTE IDENT switch. On DATATRAC ( ): • Note RCV screen ----->:
On ATC-601: • Notice the ID display. ID should display for about 18 seconds.
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ALT= [ ] TEST RUNNING *****
-----------------RCV 1--(ALL)---12.5 KHz Lbl SDI 32-Hex Data-1 SSM Par msec 031 01 75 66 91 98 11 1 0200 |<----Ident bit
Note: The 9 should appear in the data field only while the switch is being pressed. This, together with the ID display on the ATC-601, verifies that the REMOTE IDENTdiscrete input is functional. ** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE=ID5263 ALT= 32,800 FT [1344] |<----ID display ***** TEST RUNNING *****
On Datatrac ( ): • Set the label 031 XMT 1 word:
-ON--------------XMT 1--(ALL)---12.5 KHz Lbl SDI 32-Hex Data-1 SSM Par msec 031 01 15 66 91 98 00 1 0100
On DATATRAC RCV 1 and on ATC-601 screens:
You should see the same displays as immediately above. If the test failed using the REMOTE IDENT switch, but succeeds here, then suspect a failure in the discrete input or the test .
On Datatrac ( ): • Set the label 031 XMT word:
-ON--------------XMT 1--(ALL)---12.5 KHz Lbl SDI 32-Hex Data-1 SSM Par msec 031 01 95 66 81 98 00 1 0100
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STEP 21.0
TITLE Self Test
PROCEDURE
DESIRED RESULTS
On test : • Set POWER switch OFF • ALT TYPE SELECT: ARINC 429 • AIR/GND: AIR • SELF TEST: ENABLE: OFF On DATATRAC ( ): • Same setup as for STEP 9.0. On ATC-601: • Set for ATCRBS REPLY TEST ---------->
** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE= *****
ALT= [ ] TEST RUNNING *****
On test : • Set POWER switch ON
After a few seconds, the test X FEED OUT lamp and the ATC-601 REPLY lamps light indicating that the unit is replying. The ATC-601 screen indicates ED.
On DATATRAC ( ): screen shows: --------->
-----------------RCV 1--(ALL)---12.5 KHz Lbl SDI 32-Hex Data-1 SSM Par msec 031 01 F5 66 81 98 11 1 0200 203 01 64 00 01 C1 11 1 0200 350 01 60 00 01 17 11 1 0200 (You may need to press INC to display all three labels.)
In the next few steps, watch the DATATRAC RCV screen carefully. On the test : • Press and hold the SELF TEST pushbutton for about 1 sec.
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After a few seconds, notice that the DATATRAC ( ) and ATC-601 screens do not change except that the DATATRAC briefly shows *’s to the left of the 0200 time displays in the RH column. (The test TEST lamp lights while you hold the switch but otherwise there is no change.)
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maintenance 523-0775657 Table 5-11 Acceptance Test Procedures, Using the DATATRAC 400 or DATATRAC 400H Databus Analyzer (Cont).
STEP 21.0
TITLE Self Test (cont’d)
PROCEDURE
DESIRED RESULTS
On test : • Set the AIR/GND switch to GND • Set the SELF TEST/ENABLE switch to ON • Press and hold the SELF-TEST button for about 1 s
Self-test Displays: After a few seconds, notice that the X FEED OUT lamp turns off briefly while the ATC-601 screen shows +’s or -’s in most of the data fields, followed by blank fields.
Note: The test TEST lamp lights while you hold the switch. This has no bearing on UUT operation, however. If the lamp does not light, check the test . On the DATATRAC ( ), press RCV (either once or twice) to return to the setup screen, followed by ENT, to clear the screen of any extraneous labels.
After a few seconds, notice that the X FEED OUT lamps turns on again and the ATC-601 screen returns to the normal display. On the DATATRAC ( ), notice that the SSM’s change to 10 and then back to 11.You should try to be especially watchful of the 350 data word and try to catch any diagnostic codes that may be displayed during the selftest sequence.
On the test : • Set the SELF TEST/ENABLE switch to OFF. • Press and hold the SELF TEST button for about 1 s.
Notice that the self-test displays as described above do not appear..
On the test : • Set the SELF TEST/ENABLE switch to ON. • Set the AIR/GND switch to AIR. • Wait about 5 seconds *. • Press and hold the SELF TEST button for about 1 s.
Notice that the self-test displays as described above do not appear..
Note: This verifies that self test is properly inhibited by the self-test inhibit discrete.
Note: This verifies that self test is properly inhibited by the AIR/GND discrete.
*Note: The U must be allowed sufficient time to complete at least one software cycle in order to recognize the change in the AIR/GND discrete. If you press the SELF TEST switch in less than about 3 seconds of setting the AIR/GND switch to AIR, the unit may execute self-test as though it were not inhibited. This should be seen as normal. On the test : • Set the SELF TEST/ENABLE switch to ON. • Set the AIR/GND switch to GND. • Press and hold the SELF TEST button for about 1 s.
Notice the self-test displays as described above reappear. Note: This verifies that the self-test inhibit and AIR/GND discretes are switchable.
This completes this test sequence. Successful completion of this series provides reasonable assurance that the unit is operational. However, this test does not satisfy the requirements of a Final Performance Test which must be performed after any repair operation. Turn off all power, disconnect the equipment, and return it to its normal storage location. Return the UUT to its original shipping container, or equivalent, if it is to remain in storage. Otherwise, prepare it for installation.
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TITLE
PROCEDURE
DESIRED RESULTS
1.0
Setup
Note: If you are using a Test built according to instruction provided in a previous edition of this manual, it may be necessary to upgrade the . Refer to the Special Tools and Fixtures Section. If not already done, connect equipment as shown in figure 5-2. • Connect DATATRAC 200 as follows and using cables shown in the Special Tools and Fixtures paragraph. • ARINC 429 XMT to test DIGITAL CONTROL port, • Parallel connect XMT to test PRIMARY DIGITAL ALTITUDE PORT, • ARINC 429 RCV to test DATA BUS READER port. • Connect the ATC-601 to the UUT bottom antenna connector. • Connect an rf termination to the top antenna port. • Connect power to test power jacks - observe proper polarity. • Preset the switches as shown in paragraph 5.4.5.6. above. Be sure POWER switch is OFF and EXT STBY switch is at STBY.
1.1
Setup
Turn the DATATRAC 200 on, intialize for ARINC 429, and set the RCV, and XMT screen ----->
Lbl SI 29-Hex RCV-11 SM P MSEC >> NO DATA RECEIVED Lbl SI 29-HEX XMT-11 031 01 55980 203 01 20000
SM P MSRC 00 1 100 11 1 100
(See notes 1 and 2 that follow test step 1.2) On test , set switches as shown in paragraph 5.4.4. above.
1.2
Turn on TDR-94/94D
On test : • Set POWER switch to ON Monitor current. If OK: • Set EXT STBY switch to OPR Monitor current.
Setup (power-up)
Turn the ATC-601 on and press SELECT for the screen -------------->
UUT power on and ARINC 429 tuning test
ATC-601 screen --------->
If the unit has been in service and there is a possibility of an over-current condition, monitor the power supply current output. The setup should draw no more than 1.5 A. Typically it draws about 0.9 to 1.1 A when the UUT is transmitting. ** ATCRBS REPLY TEST - NOT RUN **
(lines 2-4 are irrelevant) CODE=
ALT= Press RUN to start
[
]
** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE=5263 *****
ALT=32,800 FT [1344] TEST RUNNING *****
To change the CODE, see note 1 below. To change the ALT, see note 2 below. The DATATRAC 200 RCV display becomes --------->
Lbl 031 203 350
SI 01 01 01
29-Hex RCV-11 559A0 20000 00000
SM 11 11 11
P 1 1 1
MSEC 0200 0200 0200
Note: Any other labels displayed are irrelevant to this test. Use the INC key to scroll the display. See Note 3 below. On the ATC-601, press RUN
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UUT responds to interrogations as indicated by a lighted XFEED OUT lamp on the test and a lighted REPLY lamp on the ATC-601.
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STEP
TITLE
PROCEDURE
DESIRED RESULTS
Note 1. You can change the (octal) CODE=XXXX display by changing data bits 18 through 29 in the label 031 data word (XMT field of the DATATRAC 200) as follows: ATC-601 octal digit: Bit: 32 31 30 Data: Par SSM DATATRAC Hex Bits: 8 DATATRAC Hex value: DATATRAC (Hex): Binary: 0 0 0 Octal value: Produces an ATC-601 CODE:
First Second 29 28 27 26 25 24 |<-----Data ------->
First 4
2 0 2 5
21
Second 1
8
4
2
5 1 4
Third 22
23
Fourth 19 18 ----->|
20
Third
1
8
4
2
5 1 1
0 4
1 2 2
0 1
17 Pad
16 Pad
Fourth 1
8
4
2
9 1 4
1 2 6
0 1
0 4
15 Pad 1
8 1 2 3
1 1
0
0
0
Bits 11 through 17, of the label 031 control word, are assigned the following functions: DATATRAC Hex bits: Fifth Bit: 14 13 12 11 10 9 Bit values: 8 4 2 1 8 4 2 1 DATATRAC (Hex): 0 Assignment:
| | Pad | |<- |<--SDI | | |<--Altitude reporting, 1 = OFF | |<--Ident, 1 = ON |<--Altitude port select, 1 = B
Note 2: You can set the XMT label 203 data field bits 12 through 28 to any combination of 1 and 0. The RCV label 203 word data field will reflect the XMT word while the ATC-601 will show the altitude to the nearest 100 feet. The label 203 word data bit values are as follows: lst | DATATRAC (Hex) *: | Hex value: 8 4 2 1 Bit: 29 28 27 26 Alt value:(sign bit; 0 = +) 65536 32768 16384 (in feet) DATATRAC (Hex) *: | 3rd | | Hex value: 8 4 2 1 8 4 Bit: 21 20 19 18 17 16 Alt value 512 256 128 64 32 16 (in feet) Determine the altitude by totaling the bit value of all bits set to
| 8 25 8192
2nd 4 24 4096
4th 2 15 8
| 1 14 4
| 1 22 1024
2 23 2048 | 8 13 2
5th 4 12 1
2 11 **
| 1 10 **
09 **
1.
* The first (lst) Hex Data bit sets data bits 26 through 29. Since bit 29 must always be a 0, this Hex bit must not be set to a hex number greater than 7. The fifth (5th) bit includes part of the SI, bit 10, therefore you will see it change whenever the SI is set to any value other than 01. ** Bits 9, 10, and 11 are not used in the altitude definitions. Note 3: You will see a label 371 data word. This is the ARINC 429 Specific Equipment Identification word which is structured the same as other ARINC 429 words but conveys the following information: Bits 11 through 18 identify the equipment type. The code for ATC transponders is 18 therefore bits 14 and 15 are 1; the others are 0. Bits 19 through 24 convey a binary code identifying the equipment manufacturer. Collins’ is 6. Therefore bits 20 and 21 are 1; all others are 0. Bits 24 through 29 are reserved for purposes to be defined. When ARINC 572 altitude data is active, you will see a label 200 data word. This word reflects the ARINC 572 (Gillham code) altitude data. This word is structured the same as other ARINC 429 words, except bits 9 and 10 are part of the data field; i.e., there is no SDI. Bits 9,10, and 11 reflect the D1, D2, and D4 code bits respectively. Bits 13, 14, and 15 reflect the C-bits, bits 17, 18, and 19 reflect the B-bits, and 21, 22, and 23 reflect the A-bits.
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP
TITLE
2.0
Test set, Auto Test
PROCEDURE
DESIRED RESULTS
On ATC-601: • Press RUN/STOP to stop • Press AUTO TEST • Press RUN to start Note: This test requires a few seconds to run. It will stop automatically.
Ensure that all tests . See note below.
On test : • Set EXT STBY switch to STBY • Set POWER switch OFF On UUT: • Move the test set rf cable to the UUT top antenna connector and the rf termination to the bottom. On test : • Set POWER switch ON • Set EXT STBY switch to OPR On ATC-601: • Repeat the AUTO TEST
Ensure that all tests . See note below.
Note. The AUTO TEST sequence will indicate FAILED even when certain tests result in a NO REPLY condition. The NO REPLY conditions are the result of no ADLP (Airborne Data Link Processor) data in this setup. This same condition is likely to occur when using the ATC-601 as a ramp tester when testing an installation not equipped with an ADLP. To that the test can be seen as successful, proceed as follows: • When the test sequence is completed and the ATC-601 stops, as indicated by INTERR and REPLY lamps off, you will likely see a screen as follows: ** AUTO TEST - FAILED ** MODES TESTED - A,C,S FREQ: MODES ED - A,C,S ERP: MODES FAILED -> MTL: DIVERSITY ISOLATION: >40 dB Press RUN to start
1089.92 Mhz 55 Dbm -77 Dbm
(The FREQ, ERP, and MTL values can vary from UUT to UUT and to a lesser degree on UUT temperature.) the test results as follows: On the ATC-601, use the SELECT up arrow or down arrow key to scroll through the following list of tests performed; the numbers are for reference purposes only and do not appear on the test set screen. If you use the down arrow, you will see the list in the order shown; from test 1 through test 19. If you use the up arrow key, you will see the list in reverse order, starting at test 19. You will likely notice that all tests ed except tests 13, 14, and 15 which had a NO REPLY. NO.
TEST NAME AND RESULT
1.0
**
REPLY DELAY TEST - ED
2.0
**
REPLY JITTER TEST - ED
TEST SPECIFICATION / DESCRIPTION **
**
MODE S: 128.00 (±0.25) µs ITM A: 128.00 (±0.25) µs (All others): 3.00 (±0.50) µs MODE S: =< 0.05 µs ITM: =< 0.06 µs
(All others): =< 0.1 µs 3.0
**
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ATCRBS REPLY TEST - ED
**
F1 TO F2 SPACING: 20.3 (±0.1) µs All PULSE WIDTH: 0.45 (±0.1) µs
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP
TITLE
NO.
TEST NAME AND RESULT
4.0
**
5.0
** ATC ONLY ALL-CALL TEST - ED **
The TDR-94/94D should not reply to this mode a and mode c only interrogation. ED indicates a correct (NO) response.
6.0
** MODE S ALL-CALL TEST - ED **
The TDR-94/94D should reply to this interrogation. ED indicates a correct response. UUT address previously determined in mode s interrogation, is sent to UUT in UF4 (Uplink Format 4) and verified in DF4 (Downlink Format 4) reply.
7.0
** INVALID ADDRESS TEST - ED **
UUT is interrogated with two addresses, both of which are different from the correct address. ED indicates UUT did not reply to interrogation.
8.0
** SPR ON/OFF TEST - ED **
UUT is interrogated first with SPR ON and verifies a proper reply, then with SPR OFF and verifies no reply. ED indicates UUT responded correctly.
9.0
**
MODE S UF0 TEST - ED
**
UUT is interrogated with mode S UF0, ing correct altitude as compared to previous mode c reply, correct address as compared to DF11 address, and correct format. ED indicates correct UUT response.
10.0
**
MODE S UF4 TEST - ED
**
UUT is interrogated with UF4, ing correct altitude as compared to previous mode c reply, correct address as compared to DF11 reply, and correct format. ED indicates correct UUT response.
11.0
**
MODE S UF5 TEST - ED
**
UUT is interrogated with UF5, ing the correct ID code as compared to previous mode a reply, correct address as compared to DF11 reply, and correct format. ED indicates correct UUT response.
12.0
**
MODE S UF11 TEST - ED
13.0
**
MODE S UF16 TEST - NO REPLY
**
(See test 15.)
14.0
**
MODE S UF20 TEST - NO REPLY
**
(See test 15.)
6/15/1995
PROCEDURE
DESIRED RESULTS
SLS LEVEL TEST - ED
TEST SPECIFICATION / DESCRIPTION UUT is interrogated with F2 (SLS) pulse at 9 dB below F1. UUT should reply to this interrogation. Then UUT is interrogated with F2 equal to F1. UUT should not reply. ED indicates correct response to both tests.
**
UUT is interrogated with UF11, ing correct address as compared to previous response, and correct format. ED indicates correct UUT response.
**
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP
TITLE
STEP
TEST NAME AND RESULT
15.0
**
MODE S UF21 TEST - NO REPLY
16.0
**
SQUITTER TEST - ED
17.0
**
FREQUENCY TEST - ED
**
Freq: 1090 (±1) MHz
18.0
**
DIVERSITY TEST - ED
**
ATC-601 monitors squitter pulses on active antenna port (as in test 16) and then monitors for intervening squitter pulses that are not greater than 20 dB below the active squitter. This test will always fail when the UUT is a TDR-94 (non diversity) because squitter is transmitter every second on the same antenna port. If you are testing a TDR-94D and the DL ANT/SGL ANT switch is set to SGL ANT, the test will also fail because this causes the unit to operate like a TDR-94. ED indicates a correct response from a TDR-94D.
19.0
**
MTL DIFFERENCE TEST - ED
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PROCEDURE
DESIRED RESULTS TEST SPECIFICATION / DESCRIPTION
**
UUT is interrogated with UF16, UF20, and UF21. These formats are all related to the airborne data link function. This function has not been implemented. The TDR-94/94D will not reply to these interrogation formats. NOT REPLY should not be seen as a failure. When set for daul antenna operation, the TDR-94D transmits a squitter pulse once each second, alternating between top and bottom antenna ports. The ATC-601 verifies that one squitter pulse is received every 1.6 to 2.4 seconds. The test ANT SGL/DL switch must be in the DL position. When set for single antenna operation, or when testing a TDR-94, only the bottom antenna port is used. In this case the ATC-601 verifies that one squitter pulse is received every 0.6 to 1.4 seconds. When you change the ANT SGL/DL switch, you must cycle power to the UUT in order for it to take effect. ED indicates a correct UUT response.
**
**
ATC-601 verifies that the MTL difference between mode a and mode c responses is < 1.0 dB. At this point, another press of the arrow key will display the first item; either 1.0 or 18.0, depending on which arrow was used.
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP 3.0
TITLE Power output and Rcvr Sensitivity Test
PROCEDURE
DESIRED RESULTS OR SETUP SCREEN
On test select: • Set EXT STBY switch to STBY • Set POWER switch OFF On ATC-601: • Select POWER TEST • Press RUN to indicate TEST RUNNING -------->
** POWER TEST - Top Antenna ANTENNA UNITS ERP MTL *****
TEST RUNNING
** STATUS NO REPLY
*****
Note: If necessary, press SELECT (or SLEW) to select Top Antenna. Be sure that the ATC-601 rf cable is connected to the top antenna port and the rf termination is connected to the bottom port. On DATATRAC 200: set screen ------>
LBL SI 29-HEX RCV-11 SM P MSEC >> NO DATA RECEIVED LBL SI 29-HEX XMT-11 031 01 55980 203 01 20000
On test : • Set POWER switch ON • Set EXT STBY switch to OPR
SM P MSEC 00 1 100 11 1 100
** POWER TEST - Top Antenna ANTENNA UNITS ERP MTL Top dBm 55.7 -76.0
** STATUS ED
***** TEST RUNNING *****
After a few seconds, the ATC-601 shows ----> On ATC-601: Press RUN/STOP to stop the test. If the UUT is a TDR-94, skip this step. On test : • Set EXT STBY switch to STBY • Set POWER switch OFF • On TDR-94D mount: Swap the rf cable connection and termination on the UUT antenna ports. (Rf cable to bottom port and termination to top antenna port.) On test : • Set POWER switch to ON • Set EXT STBY switch to OPR On ATC-601: • Press RUN to indicate TEST RUNNING Wait a few seconds then press RUN/STOP to stop the test.
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If a failure is detected, a small arrow will be shown to the left of the offending parameter(s). Make a note of the test results, if a record is needed, and label it as applicable to the UUT bottom antenna port. The data displayed here will be overwritten on the next test. You should see a similar display on the ATC-601 except this data is applicable to the top antenna port. The data can be slightly different. See below for test tolerances and an explanation of a possible failure indication due to high sensitivity. Note: You may also select bottom antenna screen on the ATC-601. Note: You may see a marginal test failure if the UUT is relatively cold. In this case allow the unit to warm up a few minutes and then repeat the test.
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP
TITLE
3.0 (cont’d)
Power output and Rcvr Sensi-tivity Test (cont’d)
PROCEDURE
DESIRED RESULTS OR SETUP SCREEN
The test tolerances are: ERP: > 48.5 dBm and < 57.0 dBm MTL: -73.0 (±4.0) dBm The ATC-601 will indicate that the UUT has FAILED if the MTL is more than -77.0 dBm or less than 71 dBm. Collins prefers, however, that a FAILURE should be reported only if the MTL is less than 71 dBm. Therefore, if you have a unit displaying an MTL of -77.1 or more, you should see that value as acceptable. Obviously, an MTL indication approaching -80 dBm or more may be cause for suspecting a problem with test set calibration. You may also see a failure because the ERP, Effective Radiated Power or Peak Pulse Power , is more than 57 dBm. Power measurements taken with a ramp tester can be confusing. The various test equipment manufacturers use different dimensions for displaying the test results, the test specifications are not always clear on how the test is to be performed to produce the specified result, and the test method; direct or radiation, yields different results. As in the case of MTL, an ERP slightly greater than 57 dBm ( e.g., 59 dBm max), using the direction connection method, should not be seen as cause for unit rejection. DO-181 specifies the transponder power output at the antenna. Testing a unit on the bench by direct connection to the antenna port yields a power reading at the transmitter output. The difference is, of course, antenna cable and connector losses. DO-181 specifies transponder power output in watts and dBW. The IFR ATC-601 displays power in dBm (ERP). The TIC-48/-49 displays power in watts. The following chart may be useful for proper test evaluation:
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Watts
dBW
dBm
50 70 100 125 150 200 250 300 350 400 450 500
16.99 18.45 20.00 20.97 21.76 23.01 23.98 24.77 25.44 26.02 26.53 26.99
46.99 48.45 50.00 50.97 51.76 53.01 53.98 54.77 55.44 56.02 56.53 56.99
TDR-94/94D Spec
(Min for airplanes limited to 15 000 ft and 175 kts.) Minimum at antenna (ramp testing)
Minimum direct (on bench)
Maximum at antenna
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP 4.0
TITLE Gillham Altitude Test
PROCEDURE
DESIRED RESULTS OR SETUP SCREEN
On ATC-601: select
** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant)
ATCRBS REPLY TEST ----------->
CODE=
ALT=
[
]
Press RUN to start
On test select: • Set POWER switch to OFF • ALT TYPE SELECT: ARINC 572 • ARINC 572 ALT IN: TO TDR On DATATRAC 200: • Set XMT label 203 word to OFF • Set RCV and XMT screen ------>
Lbl SI 29-Hex RCV-11 SM P MSEC >> NO DATA RECEIVED
On test : • Set all ARINC 572 switches to OFF: Then set A4, C2, C4, and B4 to SEL. • Set POWER to ON • Set EXT STBY switch to OPR
The XFEED OUT lamp turns on. The ATC-601 REPLY lamp indicates that UUT is responding to interrogations.
DATATRAC 200 RCV screen shows: -------------------->
Lbl SI 29-HEX RCV-11 031 01 55980 203 01 05C30
Lbl SI 29-HEX XMT-11 031 01 55980
SM P MSEC 00 1 100
SM P MSEC 11 1 100 11 1 100
(ignore any other displayed labels) On ATC-601: • Press RUN. Screen shows: -------------------->
** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE=5263 *****
ALT=5,900 FT TEST RUNNING
[4460] *****
(The CODE 5263 depends on your selection in the 031 XMT word. See note 1 under step 1.2 above) At this step you are asked to toggle each of the ARINC 572 switches and the altitude display. You should also watch the RCV data word on the DATATRAC 200 display. By cycling each switch between OFF and SEL you should see the ATC601 display and the DATATRAC 200 and 203 data words change. If the displays do not change for a particular switch, this would indicate either an open or a shorted code line. If the wrong altitude is shown that code line may be effecting another line; i.e., causing two or more inputs to change simultaneously. In either case the UUT, the test , or the interconnecting cable needs repair. Set each switch as shown in the listing below to the (position) shown, and back, and the altitude display at both positions. The altitude display should always revert to the initial display when the switch is returned to its original position. There is no serious need to the correctness of the RCV word as long as the ATC-601 display is correct. SWITCH Initial A1 (SEL) A2 (SEL) A4 (OFF) C1 (SEL) C2 (OFF)
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DISPLAYED ALTITUDE 5,900 FT [4460] 23,600 FT [5460] 7,600 FT [6460] -400 FT (0460] none (blank; this is invalid) 5,800 FT [4440]
SWITCH C4 (OFF) B1 (SEL) B2 (SEL) B4 (OFF) D2 (SEL) D4 (SEL)
DISPLAYED ALTITUDE 6,000 FT [4420] 3,600 FT [4560] 5,600 FT [4660] 6,600 FT [4060] 119,600 FT [4462] 55,600 FT [4464]
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP
TITLE
PROCEDURE
DESIRED RESULTS OR SETUP SCREEN
Gillham Code, Altitude Listing: ATC-601 ALT DISPLAY -1000 FT 0 FT 500 FT 1000 FT 1300 FT
D2 0 0 0 0 0
D4 0 0 0 0 0
A1 0 0 0 0 0
GILLHAM A2 0 0 0 0 0
CODE SWITCHES A4 B1 B2 B4 0 0 0 0 0 0 1 1 0 0 1 0 0 1 1 0 0 1 1 1
C1 0 0 0 0 1
C2 1 1 1 1 0
C4 0 0 0 0 0
1500 1800 2000 2600 2700
FT FT FT FT FT
0 0 0 0 0
0 0 0 0 0
0 0 0 0 0
0 0 0 0 0
0 0 0 0 0
1 1 1 1 1
1 0 0 0 0
1 1 1 0 0
0 0 0 0 0
1 0 1 1 0
0 1 0 1 1
3000 4000 6000 6800 8000
FT FT FT FT FT
0 0 0 0 0
0 0 0 0 0
0 0 0 0 0
0 0 0 1 1
1 1 1 1 1
1 1 0 0 0
0 1 0 0 1
0 1 1 0 1
0 0 0 0 0
1 1 1 0 1
0 0 0 1 0
10000 12000 14000 14800 16000
FT FT FT FT FT
0 0 0 0 0
0 0 0 0 0
0 0 0 1 1
1 1 1 1 1
1 0 0 0 0
1 1 0 0 0
0 1 0 0 1
1 1 1 0 1
0 0 0 0 0
1 1 1 0 1
0 0 0 1 0
16100 16200 18000 20000 22000
FT FT FT FT FT
0 0 0 0 0
0 0 0 0 0
1 1 1 1 1
1 1 1 1 1
0 0 0 1 1
0 0 1 1 0
1 1 0 1 0
1 1 1 1 1
1 1 0 0 0
1 0 1 1 1
0 0 0 0 0
25000 30000 30800 35000 40000
FT FT FT FT FT
0 0 0 0 0
0 0 1 1 1
1 1 1 1 1
0 0 0 0 1
1 0 0 1 1
1 0 0 1 0
1 0 0 0 1
0 1 0 0 1
0 0 0 0 0
1 1 0 1 1
0 0 1 0 0
45000 50000 66000 67500
FT FT FT FT
0 0 1 1
1 1 1 1
1 0 0 0
1 1 0 0
0 0 0 1
0 1 1 1
1 0 0 0
0 1 1 1
0 0 0 0
1 1 1 1
0 0 0 0
----------------------------------------------------------------------------------In all cases, set the applicable switch to SEL for those pulses identified by a logic 1. For addtional information on Gillham code structure, refer to paragraph 5.7 in this section.
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP 5.0
TITLE CSDB tuning and altitude test
PROCEDURE
DESIRED RESULTS
On ATC-601: • Press RUN/STOP to stop the interrogations On test : • Set POWER OFF On DATATRAC 200: • Turn POWER to OFF • Wait a few seconds, then turn POWER to ON • At the initial screen, select CSDB (enter C and press ENT) • At the DATA RECEIVER SETUP screen, press 2 (for HEX DATA) and press ENT (this brings up the RCV DATA screen) • Press XMT to show the TRANSMITTER SETUP screen (default values should be correct) • Press ENT (this brings up the combined screen) Note screen ---------->
LBL 7-STAT-0 HEX RCV DATA >> NO DATA RECEIVED
MSEC
LBL 7-STAT-0 HEX XMT DATA
MSEC
(Note cursor is under the B in the XMT LBL field) On the back of the DATATRAC 200: • Move the cables (HI and LO) connected to the 429 TX to CSDB TX • Move the cables (HI and LO) connected to the 429 RX to CSDB RX On DATATRAC 200: • Enter 1E (this is the CSDB tuning word label) • DATATRAC responds with a default field of 0’s and 100 below MSEC
• Change XMT data field as shown -------------> (Be sure to press INC)
LBL 7-STAT-0 HEX XMT DATA MSEC 1E 10011001 63 52 44 13 100 |||||||| || || ||<||<-Gillham altitude * |||||||| ||<||<-ATC code * |||||| |<- SI; 01 = side 1, 10 = side 2 ||||||<-Test; 1 = on |||||<-ATC ident; 1 = on ||||<-Altitude reporting; 1 = on |||<-Mode; 1 = standby ||<-Pad (not used) |<-Validity; 1 = valid
* Refer to paragraph 5.6.3.2 for code description. On ATC-601: select ATCRBS REPLY TEST and press RUN to indicate TEST RUNNING
----------->
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** ATCRBS REPLY TEST
NO REPLY **
(lines 2-4 are irrelevant) CODE= *****
ALT= TEST RUNNING
[
]
*****
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP 5.0 (cont’d)
TITLE CSDB tuning and altitude test (cont’d)
PROCEDURE
DESIRED RESULTS
On test : • Set CONTROL DATA SELECT to CSDB • Set ALTITUDE DATA, ALTITUDE TYPE SELECT to CSDB (CTL) • Set OUTPUT PORT SELECT to CSDB PORT 1 • Set ARINC 572 ALT IN to TO CTL • Set SOURCE SELECT to CTL • On the test CONTROL CONNECTOR J1, connect two jumpers: From Pin To Pin 26 41 25 8 Note: These jumpers are not required if MOD 1 has been installed in the test . • Set POWER switch ON DATATRAC 200 screen -->
On test : • Set the OUTPUT PORT SELECT switch to CSDB PORT 2.
LBL 1F A0 F3
7-STAT-0 11011001 10000001 00000001
HEX RCV DATA 63 52 44 13 20 20 00 00 00 00 00 00
MSEC 0100 0100 0100
LBL 7-STAT-0 1E 10011001
HEX XMT DATA 63 52 44 13
MSEC 100
Notice that the same data is displayed. (The data may flicker somwhat while you are switching; ignore that.)
Important points: • The 1F RCV word is a reflection of the 1E XMT word • The A0 RCV word is irrelavent here, the hex data shown above can be different • The F3 word is the diagnostic word and should indicate no faults; HEX DATA is all 0’s. Bits 1 and 0 of the status byte are the SI bits and indicate that the UUT is set for side 1 (01) which must be true of all word labels. The ATC-601 screen shows:
** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE=5263 *****
ALT= 32,800 FT [1344] TEST RUNNING *****
Important points: • Notice that the CODE agrees with the HEX XMT DATA 1E word except that the hex digital pair groupings are reversed in order. That is, the XMT and RCV words show 63 52 while the ATC601 shows 5263. In the altitude field, the XMT and RCV words show 44 13 while the ATC-601 shows 1344. 6.0
ARINC 429 Altitude Test
On ATC-601: select ATCRBS REPLY TEST and press RUN to indicate TEST RUNNING --------->
** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE= *****
ALT= [ ] TEST RUNNING *****
On test : • Set EXT STBY switch to STBY • Set the POWER switch to OFF • Set ALT TYPE SELECT to ARINC 429 • Set OUTPUT PORT SELECT switch to ARINC 429 PORT A • Set CONTROL DATA SELECT switch to PA On DATATRAC 200: • Move the TX and RX leads to the ARINC ports. • Reinitialize the unit for ARINC 429 operation.
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP
TITLE
6.0 (cont’d)
ARINC 429 Altitude Test (cont’d)
PROCEDURE
DESIRED RESULTS OR SETUP SCREEN
On DATATRAC 200: • Set XMT to ON • Setup screen ------>
Lbl SI 29-Hex RCV-11 SM P MSEC >> NO DATA RECEIVED
On test : • Set POWER to ON • EXT STBY to OPR • Be sure REP ALT switch is at PA
POWER indicator comes on immediately and after a few seconds the XFEED OUT lamp turns on. The ATC601 REPLY lamp indicates that UUT is responding to interrogations.
Lbl SI 29-HEX XMT-11 031 01 55980 203 01 20000
The ATC-601 screen shows: --->
SM P MSEC 00 1 100 11 1 100
** ATCRBS REPLY TEST **
(lines 2-4 are irrelavent) CODE=5263 *****
ALT=32 800 FT [1344] TEST RUNNING *****
(The CODE 5263 depends on your selection in the 031 XMT word. See note 1 under step 1.2 above.) DATATRAC 200 RCV screen shows: ------->
Lbl 031 203 350
SI 29-HEX RCV-11 01 559A0 01 20000 01 00000
SM 11 11 11
P 1 1 1
MSRC 0200 0200 0200
(ignore any other displayed labels, and the order is not important) 6.1
ARINC Altitude Control Disc-retes Tests
On the test : • Be sure the SOURCE SELECT switch is set to SEL. On the test : • Set the REP ALT SEL switch to PB
** ATCRBS REPLY TEST **
(lines 2-4 are irrelavent) CODE=5263 *****
ALT=32 800 FT [1344] TEST RUNNING *****
Notice that the ATC-601 altitude display blanks. Note: At this point the UUT is configured to report altitude data from port B. There is none so the display blanks.
On the test : • Move the parallel connection from the PRIMARY DIGITAL ALTITUDE SOURCE jack to the ALTERNATE DIGITAL ALTITUDE SOURCE jack.
Notice that the ATC-601 altitude display returns.
On the test : • Set the REP ALT SEL switch to PA
Notice that the ATC-601 altitude display blanks.
Note: This verifies that UUT is configured to report altitude data being supplied on port B.
Note: UUT is returned to port A. This series of steps has verified that the Reporting Altitude discrete is switchable. On the test : • Set the SOURCE SELECT switch to CTL
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Notice that the ATC-601 altitude display returns. Note: This switches the UUT to the altitude data supplied on the control port.
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP
TITLE
PROCEDURE
DESIRED RESULTS OR SETUP SCREEN
6.1 (cont’d)
ARINC Alltitude Control Disc-retes Tests (cont’d)
On the test : • Disconnect the parallel connection from the ALTERNATE DIGITAL ALTITUDE SOURCE jack. (Wait about 5 seconds)
Notice that the ATC-601 altitude display remains.
On test : • Set the SOURCE SELECT switch to SEL.
Notice that the ATC-601 altitude display blanks.
On test : • Reconnect the parallel connection to the ALTERNATE DIGITAL ALTITUDE SOURCE jack.
Notice that the ATC-601 altitude display remains blanked.
On test : • Set the AUTO ALT switch to SEL (-003 UUT units only)
Notice that the ATC-601 altitude display returns.
On test : • Set AUTO ALT switch to OFF. (-003 UUT units only)
Notice that ATC-601 altitude display blanks.
On the DATATRAC: • Set the XMT label 031 word to -------->
Lbl SI 29-HEX XMT-11 031 01 55988
Note: This verifies the previous step; that altitude is being drawn from the control port; all other sources are now disconnected.
Note: This verifies that the Source Select Discrete is switchable.
Note: This enables the automatic altitude port select feature and verifies that the UUT switches to alternate port B even though port A is selected (REP ALT at PA).
Note: This verifies that the AUTO ALT discrete is switchable. SM P MSRC 00 1 100
Notice that the ATC-601 altitude display returns. Note: This digitally switches the UUT to port B. If this test is correct while the earlier test of port B altitude failed, suspect a problem with the Reporting Altitude Select discrete. If both tests failed, suspect a problem with the altitude data receivers.
On test : • Set EXT STBY switch to STBY. • Set the POWER switch OFF.
Lbl SI 29-HEX XMT-11 031 01 55980
SM P MSRC 00 1 100
On DATATRAC 200: • Set the XMT label 031 word to --------->
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP
TITLE
PROCEDURE
DESIRED RESULTS OR SETUP SCREEN
The remainder of the step is optional. Testing for various digital altitude inputs is primarily software verification and therefore unnecessary. If the UUT responds to one altitude word input it will likely respond to all. If you wish, you can set the XMT label 203 data field bits 12 through 28 to any combination of 1 and 0. The RCV label 203 word data field will follow the XMT word exactly while the ATC-601, set to the ATCRBS REPLY TEST mode, will show the altitude to the nearest 100 feet. When set to the MODE UF0 TEST, the ATC-601 displays altitude to the nearest 25 feet. The label 203 bit values are shown in note 2 following step 1.2. To 1. 2. 3. 4. 5. 6.
simulate any altitude up to about 131,000 feet: Select the desired altitude. Find the data bit with the maximum bit value less than the selected altitude. Make a note of that bit number. Subtract that bit value from your selected value. Find the next bit with the maximum bit value less than the remainder. Make a note of that bit number. Subtract that bit value from your remainder. Repeat steps 4 and 5 until the remainder is 0.
In the XMT label 203 data word, set all noted bits to 1. You should see your selected altitude, to the nearest 100 feet, displayed on the ATC-601. 7.0
ARING 575 Altitude Test
On test : • SOURCE SELECT: SEL • ALT TYPE SELECT: ARINC 429 On DATATRAC 200: • Set screen ------>
LBL SI 29-HEX RCV-11 >> NO DATA RECEIVED
SM P MSEC
LBL SI 031 01 203 01
SM P MSEC 00 1 100 00 1 100
29-HEX XMT-11 55980 10000
On test : • Connect parallel control cable to PRIMARY DIGITAL ALTITUDE SOURCE jack. • Set POWER switch to ON. • Set EXT STBY switch to OPR. On ATC-601: • Select ATCRBS REPLY TEST and press RUN to indicate TEST RUNNING. ATC-601 screen --------> On test : • Set ALT TYPE SELECT switch to ARINC 575 On DATATRAC: • Set XMT label 203 word --------> (just change the SM to 00) ATC-601 screen -------->
** ATCRBS REPLY TEST **
(lines 2-4 are irrelavent) CODE=5263 ***** LBL SI 031 01 203 01
29-HEX RCV-11 55980 10000
SM P MSEC 00 1 0100 00 1 0200
** ATCRBS REPLY TEST **
(lines 2-4 are irrelavent) CODE=5263 *****
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ALT=32,800 FT [1344] TEST RUNNING *****
ALT=16,400 FT [3230] TEST RUNNING *****
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP 7.0 (cont’d)
TITLE ARINC 575 Altitude Test (cont’d)
PROCEDURE DATATRAC screen --------->
DESIRED RESULTS OR SETUP SCREEN LBL SI 203 01
29-HEX RCV-11 10000
SM P MSEC 11 1 100
(ignore any other displayed words) LBL SI 031 01 203 01
29-HEX XMT-11 55980 20000
SM P MSEC 00 1 100 00 1 100
In addition to testing the altitude type select discrete, this test illustrates the differences between ARINC 429 and ARINC 575 data. Notice that the msb in the RCV label 203 word (above) are offset by one bit from the XMT label 203 word and the SSM code is 11 as opposed to the 00 in the XMT word. In ARINC 575, the LSB is bit 13; in ARINC 429 the LSB is bit 12. In ARINC 575, bits 30 and 31 determine the sign; 00 being positive. Notice also, that the altitude displayed on the ATC-601 corresponds to the code in the RCV word; not the XMT word. This is also due to the UUT being configured for ARINC 575 and thus the bit values are offset by 1 bit position which has the effect of changing the altitude by a factor of 1/2. On test : • Set ALT TYPE SELECT switch to ARINC 429 On DATATRAC: • Set XMT label 203 word ---->
LBL SI 031 01 203 01
(Set SM to 11)
ATC-601 screen:
29-HEX XMT-11 55980 20000
SM P MSEC 00 1 100 11 1 100
** ATCRBS REPLY TEST **
(lines 2-4 are irrelavent) CODE=5263 *****
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ALT=32,800 FT [1344] TEST RUNNING *****
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP 8.0
TITLE Mode S Address Disc-retes Test
PROCEDURE
DESIRED RESULTS OR SETUP SCREEN
On the test : • Set POWER switch OFF • Set all test mode s address switches to SEL except switch P1-56; set it to OFF. • Set POWER switch ON On ATC-601: • Set for MODE S ALL CALL TEST ------->
** MODE S ALL CALL TEST - NO REPLY ALL CALL ADDRESS = [ NUMBER = Press RUN to start
On ATC 601: • Press RUN • Note screen ----->
** MODE S ALL CALL TEST ALL CALL ADDRESS = FFFFFE TAIL NUMBER =
** ]
TAIL
ED ** [77777776]
****** TEST RUNNING *****
The remainder of this step will require a few minutes because of the delay involved in cycling power between each switch setting.
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On test : • Set POWER switch OFF. • Set each triad of address switches for an octal digit 6. • Set POWER switch ON.
After a few seconds, UUT begins to reply and shortly thereafter the ATC-601 screen shows the following address:
On test : • Set POWER switch OFF. • Set each triad of address switches for an octal digit 4. • Set POWER switch ON.
After a few seconds, UUT begins to reply and shortly thereafter the ATC-601 screen shows the following address:
On test : • Set POWER switch OFF. • Set each triad of address switches for an octal digit 0, except the eighth triad which is set to 1. • Set POWER switch ON.
After a few seconds, UUT begins to reply and shortly thereafter the ATC-601 screen shows the following address:
ALL CALL ADDRESS = DB6DB6
ALL CALL ADDRESS = 924924
ALL CALL ADDRESS = 000001
[66666666]
[44444444]
[00000001]
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP 9.0
TITLE TCAS / NO TCAS Discrete Select and TCAS Bus Test
PROCEDURE
DESIRED RESULTS
On test : • Set POWER switch OFF On DATATRAC 200: • Set XMT words as shown ----->:
LBL SI 031 01 203 01
29-HEX XMT-11 55980 20000
SM P MSEC 00 1 100 11 1 100
ATC-601 is not needed for this test but can be left on. On test : • Set POWER switch ON
After a few seconds the RCV portion of the DATATRAC 200 screen shows:
After data appears on the RCV display, press RCV and then INC to scroll the words so that you can see the 350 word.
LBL SI 350 01
On test : • Set POWER switch to OFF • Set TCAS/NO TCAS switch to TCAS On DATATRAC 200: • Press RCV and then ENT On test : • Set POWER switch to ON
After a few seconds the RCV portion of the DATATRAC 200 screen shows: (use INC key to scroll words) LBL SI 350 01
29-HEX RCV-11 00000
29-HEX RCV-11 45980
SM P MSEC 11 1 0200
SM P MSEC 11 1 0200
Refer to paragraph 5.7.2 for a more detailed discussion. The 45980 display translates into a diagnostic B3 which is interpreted: TCAS Bus Inactive. This verifies that the discrete properly configures the unit for operation with a TCAS. However, no TCAS data is being supplied in this step, therefore, the unit declares a B3 diagnostic. TCAS Bus Test, XPDR to TCAS
Connect the DATATRAC RCV to the TCAS OUT jack. that the data word labels are detectable as shown ------->. Note: Except for the diagnostic code in the label 350 data word, the data content is not important. It is quite likely that the data will be different. The presence of the data word labels shown verifies that the TCAS data bus output is active and appears to be normal.
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LBL 275 276 350
SI 00 10 01
29-HEX RCV-11 00000 07C00 45980
SM P MSEC 00 1 0150 00 1 0150 11 1 0150
Notice the higher speed. Other labels may also be present.
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP 9.0 (cont’d)
TITLE TCAS to XPDR Bus Test
PROCEDURE
DESIRED RESULTS
Note: In this step you need the capability of transmitting data to two separate input ports simultaneously and at different speeds; the 031 control word must be low speed (12.5-kbps) while the TCAS label 274 data word must be high speed (100-kbps). All DATATRAC instruments, as well as the JC Air 429E, can transmit at either of these speeds but only the DATATRAC 400 can do so on two separate ports simultaneously. Otherwise, you will need two simulators. If you do not have this capability, you may not be able to the integrity of the TCAS bus input port. If you are using a DATATRAC 400, or have access to a second bus simulator, connect your second transmitter port or data bus simulator to the TCAS IN and setup as shown -------->:
LBL SI 274 00
On bus reader RCV (1) display:
After a few seconds, the 350 word shows:
Note: The objective is to that the UUT recognizes a valid TCAS label 274 word and declares this by removing the diagnostic B3.
LBL SI 350 01
On the bus reader: Set the XMT (2) word to OFF
After a few seconds, notice that the B3 diagnostic returns.
29-HEX RCV-11 C0000
SM P MSEC 00 1 0100
Note: Be sure to set the higher speed.
29-HEX RCV-11 00000
SM P MSEC 11 1 0150
Note: This verifies that the unit is able to receognize a valid TCAS label 274 word and declare that by removing the B3 diagnostic code.
Note: Disconnect XMT (2) from the TCAS IN jack and CONNECT IT TO THE PRIMARY DIGITAL CONTROL. Reconnect RCV to the DATA BUS OUTPUT port. Final step in this test, all setups
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On test : • Set POWER switch to OFF • Set TCAS/NO TCAS switch to NO TCAS On DATATRAC 200: • Press RCV and then ENT On test : • Set POWER switch to ON
After a few seconds, the original 350 word returns: -----------------RCV--(ALL)---12.5 KHz Lbl SDI 32-Hex Data-1 SSM Par msec 350 01 00 00 01 17 11 1 0200
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP 10.0
TITLE Side 1/ Side 2 Discrete Test
PROCEDURE
DESIRED RESULTS
On test : • Set POWER switch OFF • Be sure SIDE 1/SIDE 2 switch is set to SIDE 1. On DATATRAC 200: • Same setup as in step 1.1. On ATC-601: • Set for ATCRBS REPLY TEST screen ------>
CODE= *****
On test : • Set POWER switch ON
After a few seconds, X FEED OUT and ATC-601 REPLY lamps light and the ATC-601 shows:
** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) ALT= TEST RUNNING
[ *****
]
** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE=5263 ALT=32,800 FT [1344] ***** TEST RUNNING *****
On test : • Set POWER switch to OFF • Set SIDE 1/SIDE 2 switch to SIDE 2 (wait a few seconds, then) • Set POWER switch to ON
Notice that UUT does not reply (X FEED OUT lamp and REPLY lamps are off and no altitude is displayed on ATC-601). Wait about 10 seconds.
On DATATRAC 200: • On XMT, label 031 word, set the SI to 10 and press INC
Notice that unit begins to reply almost immediately (XFEED OUT lamp turns on and ATC-601 REPLY lamp lights).
Note: UUT does not respond because the SI and side strapping do not agree. Note: If you do not allow sufficient time for the U to power down, it may not recognize the power interruption and fail to re-initialize properly. The SIDE 1/2 strap is one of several that is not monitored except at initialization. Therefore, if this test fails, cycle power again but allow more time between power-off and power-on.
Note: UUT responds because SI and side strapping agrees.
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On DATATRAC 200: • On XMT, label 031 word, set SI to 01 and press INC.
Notice that unit stops replying (X FEED OUT lamp and ATC-601 REPLY lamps turn off).
On test : • Set POWER switch to OFF • Set SIDE 1/SIDE 2 switch to SIDE 1 (wait a few seconds) • Set POWER switch to ON
After a few seconds, X FEED OUT and ATC-601 REPLY lamps light and the ATC-601 shows that the UUT is replying.
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP 11.0
TITLE AIR/ GND Discrete Test
PROCEDURE
DESIRED RESULTS
On test : • Same as initial setup • Set EXT STBY switch to STBY On DATATRAC 200: • Same setup as for step 1.1. On ATC-601: • Set for MODE S UF4 TEST screen -------->
** MODE S UF4 TEST - NO REPLY ** DF FS= ADDRESS= *****
On test : • Set EXT STBY switch OPR • Set AIR/GND switch AIR ATC-601 screen shows ----->:
DR=
UM=
TEST RUNNING
AC= *****
After a few seconds, X FEED OUT and ATC-601 REPLY lamps light and the ATC-601 shows: ** MODE S UF4 TEST - ED ** DF 4 FS=0 DR=00 UM=00 ADDRESS=000001 *****
TEST RUNNING
AC=32,775 FT *****
Note: Initially the screen may show FS=2 for about 2 seconds and then change to FS=0. On test : • Set AIR/GND switch to GND
After a few seconds, the ATC-601 shows: ** MODE S UF4 TEST - ED ** DF 4 FS=1 DR=00 ADDRESS=000001 *****
UM=00 AC=32,775 FT
TEST RUNNING
*****
Of particular significance here is the FS (flight status) indication. For a detailed description of each of these message fields, refer to the Theory of Operation section. On test : • Set AIR/GND switch to AIR
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After a few seconds, notice that the ATC-601 FS field again shows 0.
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP 12.0
TITLE DL ANT/ SGL ANT Discrete Test (TDR-94D only)
PROCEDURE
DESIRED RESULTS
On test : • Set POWER switch OFF On DATATRAC 200: • Same setup as for step 1.1. On ATC-601, set for SQUITTER TEST screen -----> Be sure the ATC-601 is connected to the top antenna port. On test : • Set DL ANT/SGL ANT switch to DL ANT • Set POWER switch ON You can watch the PERIOD display for a time. After ED appears, press RUN/STOP to stop the test.
** SQUITTER TEST - NO REPLY ** PERIOD = SECONDS TAIL NUMBER = SQUITTER ADDRESS= [ *****
TEST RUNNING
]
*****
After a few seconds, the ATC-601 screen shows: See note below. ** SQUITTER TEST - ED PERIOD = 2.00 SECONDS TAIL NUMBER = SQUITTER ADDRESS= [ *****
TEST RUNNING
** ]
*****
See the note at the end of this step for test tolerances. On test : • Set POWER switch OFF • Set DL ANT/SGL ANT switch to SGL ANT • Set POWER switch ON After FAILED (or ED) appears, press RUN/STOP to stop the test.
After a few seconds, the ATC-601 screen shows: ** SQUITTER TEST - FAILED PERIOD = SECONDS TAIL NUMBER = SQUITTER ADDRESS= [ *****
TEST RUNNING
** ]
*****
Note: This test is intended to fail. When the UUT is set for single antenna operation, there is no transmission from the top antenna port. Therefore, if this test indicates ED, recheck all switch settings, or suspect a problem with the SGL/DL ANT select strap. It should not .
On test : • Set POWER switch OFF On ATC-601: • Press RUN to stop the test. • Remove rf terminator from bottom antenna connector • Connect ATC-601 cable to bottom antenna connector • Connect rf terminator to top antenna connector
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP 12.0
TITLE DL ANT /SGL ANT Discrete Test (cont’d) (TDR-94D only)
PROCEDURE On test : • Set POWER switch to ON. On ATC-601: • Press RUN to start the test.
DESIRED RESULTS After 15 to 20 seconds, the ATC-601 screen shows: See note below. ** SQUITTER TEST - ED PERIOD = 1.00 SECONDS TAIL NUMBER = SQUITTER ADDRESS= [
• After ED appears, press RUN/STOP to stop the test. On test : • Set POWER switch OFF • Set DL ANT/SGL ANT switch to DL ANT • Set POWER switch ON
*****
TEST RUNNING
** ]
*****
After 15 to 20 seconds, the ATC-601 screen shows: See note below. ** SQUITTER TEST - ED PERIOD = 2.00 SECONDS TAIL NUMBER = SQUITTER ADDRESS= [
• After ED appears, press RUN/STOP to stop the test.
*****
TEST RUNNING
** ]
*****
Note: The PERIOD value tends to vary somewhat in all cases. When the UUT is set for dual antenna operation and the ATC-601 is monitoring the top or the bottom antenna port, the value can vary from 1.6 to 2.4. When the UUT is set for single antenna operation there should be no transmission from the top antenna port and the transmission PERIOD from the bottom antenna port can vary from 0.6 to 1.4. 13.0
Burst Tune and CrossFeed In Discrete Test
On test : • Set POWER switch OFF • CONTROL DATA PORT SEL: PB On DATATRAC 200: • Same setup as for step 1.1. On ATC-601, set for ATCRBS REPLY TEST screen -----> If necessary, reconnect ATC-601 to top antenna connector, with terminator on bottom antenna connector.
** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE= *****
ALT= [ ] TEST RUNNING *****
On test : • Set POWER switch ON
After a few seconds, the test X FEED OUT and the ATC-601 REPLY lamps light indicating that the unit is replying. The ATC-601 screen data indicates ED.
On test : • Set X FEED IN/OUT switch to IN
Notice that both X FEED lamps are lighted.
On DATATRAC 200: • Set XMT to OFF
Notice that the X FEED OUT and ATC-601 REPLY lamps turns off (X FEED IN stays on).
Note: The easiest method of interrupting the data input is simply to disconnect it from the test .
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP 13.0 (cont’d)
TITLE Burst Tune and CrossFeed In Discrete Test (cont’d)
PROCEDURE
DESIRED RESULTS
On DATATRAC 200: • Set XMT to ON (reconnect the control input)
Notice that the X FEED IN and OUT and REPLY lamps are lit.
On test : • Set XFEED switch to OUT. • Set BURST switch to BURST
Notice that XFEED IN lamp turns off and that UUT replies (X FEED OUT and REPLY lamps turn on).
On test : • Disconnect the DATATRAC XMT input from the test .
Notice that UUT continues to reply (X FEED OUT and REPLY lamps stay on).
On DATATRAC 200: • Set BURST switch to OFF
Notice that UUT stops replying (X FEED OUT and REPLY lamps turn off).
On test : • Set BURST switch to BURST
Notice that UUT does not reply (X FEED OUT and REPLY lamps remain off).
On test : • Reconnect the DATATRAC XMT to the test
Notice that UUT replies (X FEED OUT and REPLY lamps turn on).
On test : • Set BURST switch to OFF 14.0
Output Port Discrete Test
On test : • Set POWER switch OFF • OUTPUT PORT SELECT: ARINC 429 PORT A On DATATRAC 200: • Set for the same screen as for test 1.1 On ATC-601, set for ATCRBS REPLY TEST screen ----->
** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE= *****
ALT= [ ] TEST RUNNING *****
On test : • Set POWER switch ON
After a few seconds, the test X FEED OUTand the ATC-601 REPLY lamps light indicating that the unit is replying. The ATC-601 screen data indicates ED.
On test : • Set OUTPUT PORT SELECT switch to ARINC 429 PORT B
Notice that there is no change in the test result; X FEED OUT and REPLY lights are on and ATC-601 display does not change.
On test : • Set OUTPUT PORT SELECT switch to ARINC 429 PORT A
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP 15.0
TITLE Control Data Input Port Select Discrete Test
PROCEDURE
DESIRED RESULTS
On test : • Set POWER switch OFF • Set SOURCE SELECT switch to SEL • ALT TYPE SELECT: ARINC 429 • CONTROL DATA SELECT: ARINC PORT PA On DATATRAC 200: • Same setup as for step 1.1. On ATC-601, set for ATCRBS REPLY TEST screen ----->
** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE= *****
16.0
Manual STBY Discrete Test
ALT= [ ] TEST RUNNING *****
On test : • Set POWER switch ON
After a few seconds, the test X FEED OUT and the ATC-601 REPLY lamps light indicating that the unit is replying. The ATC-601 screen data indicates ED.
On test : • Set CONTROL DATA SELECT switch to ARINC PORT PB
Notice that there is no change in the test result; X FEED OUTand REPLY lights are on and ATC-601 display does not change.
On test : • Set CONTROL DATA SELECT switch to ARINC PORT PC
Notice that there is no change in the test result; X FEED OUT and REPLY lights are on and ATC-601 display does not change.
On test : • Set EXT STBY switch to STBY • Set POWER switch OFF • Set CONTROL DATA SELECT switch to ARINC PORT PA On DATATRAC 200: • Same setup as for step 1.1. On ATC-601: • Set for ATCRBS REPLY TEST screen ---------->
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** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE= *****
ALT= [ ] TEST RUNNING *****
On test : • Set POWER switch ON • Set EXT STBY switch to OPR
After a few seconds, the test X FEED OUTand the ATC-601 REPLY lamps light indicating that the unit is replying. The ATC-601 screen data indicates ED.
On test : • Set EXT STBY switch to STBY
Note that X FEED OUT lamp and ATC-601 REPLY lamps turn off and ATC-601 indicates NO REPLY. See note below.
On test : • Set EXT STBY switch to OPR
Note that X FEED OUT lamp and ATC-601 REPLY lamps light almost immediately and ATC-601 indicates ED.
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP 17.0
TITLE Max Airspeed Test
PROCEDURE
DESIRED RESULTS
On test : • Set POWER switch OFF • ALT TYPE SELECT: ARINC 429 • Be sure that all three MAX AIRSPEED switches are set to OFF (opposite of SEL). On DATATRAC 200: • Same setup as for step 1.1. (The DATATRAC is used here only for tuning data.) On ATC-601: • Set for MODE S UF0 TEST screen ------>
** MODE S UF0 TEST - NO REPLY ** DF
VS= ADDRESS= *****
On test : • Set POWER switch ON
RI=
AC=
TEST RUNNING
*****
After a few seconds, the test X FEED OUT lamp and the ATC-601 REPLY lamps light indicating that the unit is replying.
Note the ATC-601 screen ----------->
** MODE S UF0 TEST - ED ** DF 0 VS=0 RI=8 ADDRESS=000001 *****
AC= 32,775 FT
TEST RUNNING
*****
Exercise the MAX AIRSPEED switches on the test and the correct RI indication as shown in the following list. Cycle power between each switch change. Allow about 2 or 3 seconds OFF time and about 5 seconds for processor initialization and ATC-601 response time between each switch setting. MAX AIRSPEED SWITCH BIT 15 BIT 16 BIT 17 OFF OFF OFF SEL OFF OFF OFF SEL OFF SEL SEL OFF OFF OFF SEL SEL OFF SEL OFF SEL SEL SEL SEL SEL
RI VALUE 8 9 A B C D E F (not an assigned configuration)
It is worth noting that in this test mode the ATC-601 displays the altitude to the nearest 25 feet.
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP 18.0
TITLE Ext Suppression Test
PROCEDURE
DESIRED RESULTS
On test : • ALT TYPE SELECT: ARINC 429 On DATATRAC 200: • Same setup as for test 1.1. On ATC-601: • Set for ATCRBS REPLY TEST screen -----> • Connect scope channel A to the test SUPPR test points. • Connect scope channel B to the REPLY VIDEO BNC connector on the ATC-601. • Set the scope to display both channels
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** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE= *****
ALT= [ ] TEST RUNNING *****
Note a (approx) 30µs pulse on channel A. Note a reply waveform on channel B. If your scope is able, you will see the individual reply code pulses on channel B. You may also see the occasional squitter transmission which appears as a much longer series of pulses at about 1 transmission every 2 sec. Of particular importance, however, is that the channel A (suppression) pulse is about 30 µs long during ATCRBS reply, and brackets the 21 µs ATCRBS reply. During squitter transmission, the suppression pulse extends to bracket the squitter transmission. The squitter transmission is a DF11 reply about 72 µs long.
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP 19.0
TITLE ADLP Select, Discrete Strap Test
PROCEDURE
DESIRED RESULTS
On test : • Be sure DATALINK switch is set to NO ADLP. On DATATRAC 200: • Same setup as for test 1.1. DATATRAC RCV screen ------>
LBL SI 350 00
29-HEX RCV-11 60000
SM P MSEC 11 1 0200
LBL SI 350 00
29-HEX RCV-11 25100
SM P MSEC 11 1 0200
Note: The ATC-601 is not needed for this test but it can remain connected and operating. On test : • Set POWER switch to OFF • Set DATALINK switch to ADLP. • Be sure DATALINK SELECT switch is set to A/B. • Set POWER switch to ON.
Note: The diagnostic A2 identifies an inactive ADLP bus. This test verifies that the ADLP enable discrete is functional.
DATATRAC RCV screen ------> On test : • Set POWER switch to OFF. • Set DATALINK switch to NO ADLP. • Set POWER switch to ON.
LBL SI 350 01
29-HEX RCV-11 60000
SM P MSEC 11 1 0200
DATATRAC RCV screen ------> Note: The Airborne Datalink system is not fully implemented at this time. If and when an ADLP (Airborne DataLink Processor) becomes available and operational, suitable procedures will be provided to the integrity of the ADLP input/output ports. At this point, therefore, verification of the ADLP SELECT strap is seen as sufficient to prevent nuisance diagnostics that can occur if the select input should be defective. You will notice that the DATALINK SELECT A/B, C/D function is also not tested.
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP 20.0
TITLE Remote IDENT Discrete Test
PROCEDURE
DESIRED RESULTS
On test : • Same as initial setup On DATATRAC 200: • Same setup as for test 1.1. On ATC-601: • Setup for ATCRBS REPLY test
** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE= *****
On test : • Press and release the REMOTE IDENT switch. On DATATRAC 200: • Note RCV screen ----->:
On ATC-601: • Notice the ID display. ID should display for about 18 seconds.
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LBL SI 031 00
ALT= [ ] TEST RUNNING *****
29-HEX RCV-11 SM P MSEC 55984 11 1 0200 |<----Ident bit
Note: The 4 should appear in the data field only while the switch is being pressed. This verifies that the discrete input is functional. ** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE=ID5263 ALT= 32,800 FT [1344] |<----ID display ***** TEST RUNNING *****
On Datatrac 200: • Set the label 031 XMT word:
LBL SI 031 00
On DATATRAC RCV and on ATC-601:
You should see the same displays as immediately above. If the test failed using the REMOTE IDENT switch, but succeeds here, then suspect a failure in the discrete input or the test .
On Datatrac 200: • Set the label 031 XMT word:
LBL SI 031 00
29-HEX XMT-11 55984
29-HEX XMT-11 55980
SM P MSEC 00 1 100
SM P MSEC 00 1 100
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP 21.0
TITLE Self Test
PROCEDURE
DESIRED RESULTS
On test : • Set POWER switch OFF • ALT TYPE SELECT: ARINC 429 • AIR/GND: AIR • SELF TEST: ENABLE: OFF On DATATRAC 200: • Same setup as for test 1.1. On ATC-601: • Set for ATCRBS REPLY TEST ---------->
** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE= *****
ALT= [ ] TEST RUNNING *****
On test : • Set POWER switch ON
After a few seconds, the test X FEED OUT lamp and the ATC-601 REPLY lamps light indicating that the unit is replying. The ATC-601 screen indicates ED.
On DATATRAC 200: screen shows: --------->
LBL 031 203 350
SI 01 01 01
29-HEX RCV-11 559A0 00000 00000
SM 11 11 11
P 1 1 1
MSEC 0200 0200 0200
(You may need to press INC to display all three labels.) In the next few steps, watch the DATATRAC RCV screen carefully. On the test : • Press and hold the SELF TEST pushbutton for about 1 sec.
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After a few seconds, notice that the DATATRAC and ATC-601 screens do not change. (The test TEST lamp lights while you hold the switch but otherwise there is no change.)
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maintenance 523-0775657 Table 5-12 Acceptance Test Procedures, Using the DATATRAC 200 Databus Analyzer (Cont).
STEP 21.0
TITLE Self Test (cont’d)
PROCEDURE
DESIRED RESULTS
On test : • Set the AIR/GND switch to GND • Set the SELF TEST/ENABLE switch to ON • Press and hold the SELF-TEST button for about 1 s
Self-test Displays: After a few seconds, notice that the X FEED OUT lamp turns off briefly while the ATC-601 screen shows +’s or -’s in most of the data fields, followed by blank fields.
Note: The test TEST lamp lights while you hold the switch. This has no bearing on UUT operation, however. If the lamp does not light, check the test . On the DATATRAC 200, press RCV (either once or twice) to return to the setup screen, followed by ENT, to clear the screen of any extraneous labels.
After a few seconds, notice that the X FEED OUT lamps turns on again and the ATC-601 screen returns to the normal display. On the DATATRAC, notice that the SM’s change to 10 and then back to 11. This instrument has a tendency to retain superceded data words, therefore, you may need to clear the screen repeatedly to be sure that you are viewing current data. You should try to be especially watchful of the 350 data word and try to catch any diagnostic codes that may be displayed during the selftest sequence.
On the test : • Set the SELF TEST/ENABLE switch to OFF. • Press and hold the SELF TEST button for about 1 s.
Notice that the self-test displays as described above do not appear..
On the test : • Set the SELF TEST/ENABLE switch to ON. • Set the AIR/GND switch to AIR. • Wait about 5 seconds *. • Press and hold the SELF TEST button for about 1 s.
Notice that the self-test displays as described above do not appear..
Note: This verifies that self test is properly inhibited by the self-test inhibit discrete.
Note: This verifies that self test is properly inhibited by the AIR/GND discrete.
*Note: The U must be allowed sufficient time to complete at least one software cycle in order to recognize the change in the AIR/GND discrete. If you press the SELF TEST switch in less than about 3 seconds of setting the AIR/GND switch to AIR, the unit may execute self-test as though it were not inhibited. This should be seen as normal. On the test : • Set the SELF TEST/ENABLE switch to ON. • Set the AIR/GND switch to GND. • Press and hold the SELF TEST button for about 1 s.
Notice the self-test displays as described above reappear. Note: This verifies that the self-test inhibit and AIR/GND discretes are switchable.
This completes this test sequence. Successful completion of this series provides reasonable assurance that the unit is operational. However, this test does not satisfy the requirements of a Detailed Performance Test which must be performed after any repair operation. Turn off all power, disconnect the equipment, and return it to its normal storage location. Return the UUT to its original shipping container, or equivalent, if it is to remain in storage. Otherwise, prepare it for installation.
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Procedures using the JcAIR 429E Transmitter/Receiver Table 5-13. Acceptance Test Procedures, Using the JcAIR 429E Transmitter/Receiver
STEP
TITLE
PROCEDURE
DESIRED RESULTS
1.0
Setup
Note: If you are using a Test built according to instruction provided in a previous edition of this manual, it may be necessary to upgrade the . Refer to paragraph 5-8. • If not already done, connect equipment as shown in figure 5-2 using cables shown in figure 5-9. • TX to test DIGITAL CONTROL port, • Parallel connect TX to test PRIMARY DIGITAL ALTITUDE PORT, • RX to test DATA BUS READER port. • Connect the ATC-601 to the UUT bottom antenna connector. • Connect an rf termination to the TOP antenna port (TDR-94D only). • Connect power to test power jacks - observe proper polarity. • Preset the switches as shown in paragraph 5.4.5.6 above. Be sure POWER switch is OFF and EXT STBY switch is at STBY. On test , set the MODE S ADDRESS switches to any combination except all OFF or all to SEL. If all switches are set OFF or all set SEL, a diagnostic code FF will result.
1.1
Setup
Turn the JcAIR 429E on and set the TX 1 and TX 2 screens ----->
031 01 1566C1 00 203 01 640001 11
Turn on TDR-94/94D
On test : • Set POWER switch to ON Monitor current. If OK: • Set EXT STBY switch to OPR Monitor current.
If the unit has been in service and there is a possibility of an over-current condition, monitor the power supply current output. The setup should draw no more than 1.5 A. Typically it draws about 0.9 to 1.1 A when the UUT is transmitting.
Setup (power-up)
Turn the ATC-601 on and press SELECT for the screen -------------->
** ATCRBS REPLY TEST - NOT RUN **
(lines 2-4 are irrelevant) CODE=
See Note in next cell below. 1.2
ARINC 429 tuning test
On the ATC-601, press RUN ATC-601 screen --------->
ALT= Press RUN to start
[
]
UUT responds to interrogations as indicated by a lighted XFEED OUT lamp on the test and a lighted REPLY lamp on the ATC-601.
Note: When power is applied and proper control data is supplied, the TDR-94/94D should turn on the XFEED OUT lamp almost immediately. The FAULT MON lamp may be off for a few seconds and then turn on. A lighted FAULT MON lamp should generally be seen as a no-fault indication. See table 109.
CODE=5263 *****
The JcAIR 429E RX displays show --------->
203 01 E40000 11 031 01 F56681 11 350 01 600001 11
** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) ALT=32,800 FT [1344] TEST RUNNING *****
To change the CODE, see note 1 below. To change the ALTITUDE, see note 2 below.
Note: Any other labels displayed are irrelevant to this test. See Note 3 below.
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maintenance 523-0775657 Table 5-13. Acceptance Test Procedures, Using the JcAIR 429E Transmitter/Receiver (Cont).
STEP
TITLE
PROCEDURE
DESIRED RESULTS
Note 1. You can change the (octal) CODE=XXXX display by changing data bits 18 through 29 in the label 031 data word (TX field of the JcAIR 429E) as follows: ATC-601 digit: Bit: Data: Hex value: JcAIR 429E (Hex): Binary: Octal value: Produces CODE:
32 Par 8
| 0
Bits 11 through 17, of the JcAIR 429E (Hex) bits: Bit: 16 Bit values: 8 Assignment:
| Pad
31 30 SSM 4 2 1 0 0
First Second 29 28 27 26 25 |<-----Data -------> 1 8 4 2 1 | | 5 | 1 0 1 0 1 4 2 1 4 2 5 2
Third 23
24 8 | 0 1
4
21
2
1 | 0 1
6 1 4
Fourth 20 19 18 ----->| 8 4 2 | 6 0 1 1 4 2 1 3
22
1 2 6
17 Pad 1 |
label 031 control word, are assigned the following functions: 5th 6th 15 14 13 12 11 10 9 4 2 1 8 4 2 1 | | | Pad | |<- |<--SDI Pad | | |<--Altitude reporting, 1 = OFF | |<--Ident, 1 = ON |<--Altitude port select, 1 = B
Note 2: You can set the TX label 203 data field bits 12 through 28 to any combination of 1 and 0. The RCV 1 label 203 word data field will reflect the TX word while the ATC-601 will show the altitude to the nearest 100 feet. The label 203 word data bit values are as follows: JcAIR 429E digit *: lst | 2nd | | Hex value: 8 4 2 1 8 Bit: 29 28 27 26 25 24 Alt value:(sign bit; 0 = +) 65536 32768 16384 8192 4096 (in feet) JcAIR 429E digit *: | 4th | | 5th Hex value: 8 4 2 1 8 4 2 Bit: 20 19 18 17 16 15 14 Alt value 256 128 64 32 16 8 4 (in feet) Determine the altitude by totaling the bit values of all bits set to 1.
| 1 13 2
3rd 4 23 2048
2 22 1024
| 8 12 1
4 11 **
| 1 21 512 6th 2 10 **
| 1 09 **
* The left-most Hex Data bit (bit 1) is determined by the parity bit 32, the SSM bits 31 and 30, and sign bit 29. Since bit 29 must always be a 0, this Hex bit must always be an odd number. **= Not used Note 3: You may see a label 371 data word. This is the ARINC 429 Specific Equipment Identification word which is structured the same as other ARINC 429 words but conveys the following information: Bits 11 through 18 identify the equipment type. The code for ATC transponders is 18 therefore bits 14 and 15 are 1; the others are 0. Bits 19 through 24 convey a binary code identifying the equipment manufacturer. Collins’ is 6. Therefore bits 20 and 21 are 1; all others are 0. Bits 24 through 29 are reserved for purposes to be defined. When ARINC 572 altitude data is active, you will see a label 200 data word. This word reflects the ARINC 572 (Gillham code) altitude data. This word is structured the same as other ARINC 429 words, except bits 9 and 10 are part of the data field; i.e., there is no SDI. Bits 9,10, and 11 reflect the D1, D2, and D4 code bits respectively. Bits 13, 14, and 15 reflect the C-bits, bits 17, 18, and 19 reflect the B-bits, and 21, 22, and 23 reflect the A-bits.
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maintenance 523-0775657 Table 5-13. Acceptance Test Procedures, Using the JcAIR 429E Transmitter/Receiver (Cont).
STEP
TITLE
2.0
Test set, Auto Test
PROCEDURE On ATC-601: • Press RUN/STOP to stop • Press AUTO TEST • Press RUN to start Note: This test requires a few seconds to run. It will stop automatically.
DESIRED RESULTS Ensure that all tests . See note below.
On test : • Set EXT STBY switch to STBY • Set POWER switch OFF On UUT: • Move the test set rf cable to the UUT top antenna connector and the rf termination to the bottom. On test : • Set POWER switch ON • Set EXT STBY switch to OPR On ATC-601: • Repeat the AUTO TEST
Ensure that all tests . See note below.
Note. The AUTO TEST sequence will indicate FAILED even when certain tests result in a NO REPLY condition. The NO REPLY conditions are the result of no ADLP (Airborne Data Link Processor) data in this setup. This same condition is likely to occur when using the ATC-601 as a ramp tester when testing an installation not equipped with an ADLP. To that the test can be seen as successful, proceed as follows: • When the test sequence is completed and the ATC-601 stops, as indicated by INTERR and REPLY lamps off, you will likely see a screen as follows: ** AUTO TEST - FAILED ** MODES TESTED - A,C,S FREQ: MODES ED - A,C,S ERP: MODES FAILED -> MTL: DIVERSITY ISOLATION: >40 dB Press RUN to start
1089.92 Mhz 55 Dbm -77 Dbm
(The FREQ, ERP, and MTL values can vary from UUT to UUT and to a lesser degree on UUT temperature.) the test results as follows: On the ATC-601, use the SELECT up arrow or down arrow key to scroll through the following list of tests performed; the numbers are for reference purposes only and do not appear on the test set screen. If you use the down arrow, you will see the list in the order shown; from test 1 through test 19. If you use the up arrow key, you will see the list in reverse order, starting at test 19. You will likely notice that all tests ed except tests 13, 14, and 15 which had a NO REPLY. NO.
TEST NAME AND RESULT
1.0
**
REPLY DELAY TEST - ED
2.0
**
REPLY JITTER TEST - ED
**
MODE S: =< 0.05 µs ITM: =< 0.06 µs (All others): =< 0.1 µs
3.0
**
ATCRBS REPLY TEST - ED
**
F1 TO F2 SPACING: 20.3 (±0.1) µs All PULSE WIDTH: 0.45 (±0.1) µs
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TEST SPECIFICATION / DESCRIPTION **
MODE S: 128.00 (±0.25) µs ITM A: 128.00 (±0.25) µs (All others): 3.00 (±0.50) µs
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maintenance 523-0775657 Table 5-13. Acceptance Test Procedures, Using the JcAIR 429E Transmitter/Receiver (Cont).
STEP
TITLE
NO.
TEST NAME AND RESULT
4.0
**
5.0
** ATC ONLY ALL-CALL TEST - ED **
The TDR-94/94D should not reply to this mode a and mode c only interrogation. ED indicates a correct (NO) response.
6.0
** MODE S ALL-CALL TEST - ED **
The TDR-94/94D should reply to this interrogation. ED indicates a correct response. UUT address previously determined in mode s interrogation, is sent to UUT in UF4 (Uplink Format 4) and verified in DF4 (Downlink Format 4) reply.
7.0
** INVALID ADDRESS TEST - ED **
UUT is interrogated with two addresses, both of which are different from the correct address. ED indicates UUT did not reply to interrogation.
8.0
** SPR ON/OFF TEST - ED **
UUT is interrogated first with SPR ON and verifies a proper reply, then with SPR OFF and verifies no reply. ED indicates UUT responded correctly.
9.0
**
MODE S UF0 TEST - ED
**
UUT is interrogated with mode S UF0, ing correct altitude as compared to previous mode c reply, correct address as compared to DF11 address, and correct format. ED indicates correct UUT response.
10.0
**
MODE S UF4 TEST - ED
**
UUT is interrogated with UF4, ing correct altitude as compared to previous mode c reply, correct address as compared to DF11 reply, and correct format. ED indicates correct UUT response.
11.0
**
MODE S UF5 TEST - ED
**
UUT is interrogated with UF5, ing the correct ID code as compared to previous mode a reply, correct address as compared to DF11 reply, and correct format. ED indicates correct UUT response.
12.0
**
MODE S UF11 TEST - ED
13.0
**
MODE S UF16 TEST - NO REPLY
**
(See test 15.)
14.0
**
MODE S UF20 TEST - NO REPLY
**
(See test 15.)
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PROCEDURE
DESIRED RESULTS
SLS LEVEL TEST - ED
TEST SPECIFICATION / DESCRIPTION UUT is interrogated with F2 (SLS) pulse at 9 dB below F1. UUT should reply to this interrogation. Then UUT is interrogated with F2 equal to F1. UUT should not reply. ED indicates correct response to both tests.
**
UUT is interrogated with UF11, ing correct address as compared to previous response, and correct format. ED indicates correct UUT response.
**
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maintenance 523-0775657 Table 5-13. Acceptance Test Procedures, Using the JcAIR 429E Transmitter/Receiver (Cont).
STEP
TITLE
PROCEDURE
DESIRED RESULTS OR SETUP SCREEN
NO.
TEST NAME AND RESULT
15.0
**
MODE S UF21 TEST - NO REPLY
16.0
**
SQUITTER TEST - ED
17.0
**
FREQUENCY TEST - ED
**
Freq: 1090 (±3) MHz
18.0
**
DIVERSITY TEST - ED
**
ATC-601 monitors squitter pulses on active antenna port (as in test 16) and then monitors for intervening squitter pulses that are not greater than 20 dB below the active squitter. This test will always fail when the UUT is a TDR-94 (non diversity) because squitter is transmitter every second on the same antenna port. If you are testing a TDR-94D and the DL ANT/SGL ANT switch is set to SGL ANT, the test will also fail because this causes the unit to operate like a TDR-94. ED indicates a correct response from a TDR-94D.
19.0
**
MTL DIFFERENCE TEST - ED
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TEST SPECIFICATION / DESCRIIPTION **
UUT is interrogated with UF16, UF20, and UF21. These formats are all related to the airborne data link function. This function has not been implemented. The TDR-94/94D will not reply to these interrogation formats. NO REPLY should not be seen as a failure. When set for daul antenna operation, the TDR-94D transmits a squitter pulse once each second, alternating between top and bottom antenna ports. The ATC-601 verifies that one squitter pulse is received every 1.6 to 2.4 seconds. The test ANT SGL/DL switch must be in the DL position. When set for single antenna operation, or when testing a TDR-94, only the bottom antenna port is used. In this case the ATC-601 verifies that one squitter pulse is received every 0.6 to 1.4 seconds. When you change the ANT SGL/DL switch, you must cycle power to the UUT in order for it to take effect. ED indicates a correct UUT response.
**
**
ATC-601 verifies that the MTL difference between mode a and mode c responses is < 1.0 dB. At this point, another press of the arrow key will display the first item; either 1.0 or 18.0, depending on which arrow was used.
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maintenance 523-0775657 Table 5-13. Acceptance Test Procedures, Using the JcAIR 429E Transmitter/Receiver (Cont).
STEP 3.0
TITLE Power output and Rcvr Sensitivity Test
PROCEDURE
DESIRED RESULTS OR SETUP SCREEN
On test select: • Set EXT STBY switch to STBY • Set POWER switch OFF On ATC-601: • Select POWER TEST • Press RUN to indicate TEST RUNNING -------->
** POWER TEST - Top Antenna ANTENNA UNITS ERP MTL *****
TEST RUNNING
** STATUS NO REPLY
*****
Note: If necessary, press SELECT (or SLEW) to select Top Antenna. Be sure that the ATC-601 rf cable is connected to the top antenna port and the rf termination is connected to the bottom port. On JcAIR 429E: set TX --->
screen ---
On test : • Set POWER switch ON • Set EXT STBY switch to OPR
031 01 1566C1 00 203 01 640001 11 ** POWER TEST - Top Antenna ANTENNA UNITS ERP MTL Top dBm 55.7 -76.0
** STATUS ED
***** TEST RUNNING *****
After a few seconds, the ATC-601 shows ----> On ATC-601: Press RUN/STOP to stop the test. If the UUT is a TDR-94, skip this step. On test : • Set EXT STBY switch to STBY • Set POWER switch OFF • On TDR-94D mount: Swap the rf cable connection and termination on the UUT antenna ports. (Rf cable to bottom port and termination to top antenna port.) On test : • Set POWER switch to ON • Set EXT STBY switch to OPR On ATC-601: • Press RUN to indicate TEST RUNNING Wait a few seconds then press RUN/STOP to stop the test.
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If a failure is detected, a small arrow will be shown to the left of the offending parameter(s). Make a note of the test results, if a record is needed, and label it as applicable to the UUT bottom antenna port. The data displayed here will be overwritten on the next test. You should see a similar display on the ATC-601 except this data is applicable to the top antenna port. The data can be slightly different. See below for test tolerances and an explanation of a possible failure indication due to high sensitivity. Note: You may also select bottom antenna screen on the ATC-601. Note: You may see a marginal test failure if the UUT is relatively cold. In this case allow the unit to warm up a few minutes and then repeat the test.
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STEP 3.0 (cont’d)
TITLE Power output and Rcvr Sensitivity Test (cont’d)
PROCEDURE
DESIRED RESULTS OR SETUP SCREEN
The test tolerances are: ERP: > 48.5 dBm and < 57.0 dBm MTL: -73.0 (±4.0) dBm The ATC-601 will indicate that the UUT has failed if the MTL is more than -77.0 dBm or less than -71 dBm. Collins prefers, however, that a failure should be reported only if the MTL is less than -71 dBm. Therefore, if you have a unit displaying an MTL of -77.1 or more, you should see that value as acceptable. Obviously, an MTL indication approaching -80 dBm or more may be cause for suspecting a problem with test set calibration. You may also see a failure because the ERP, Effective Radiated Power or Peak Pulse Power , is more than 57 dBm. Power measurements taken with a ramp tester can be confusing. The various test equipment manufacturers use different dimensions for displaying the test results, the test specifications are not always clear on how the test is to be performed to produce the specified result, and the test method; direct or radiation, yields different results. As in the case of MTL, an ERP slightly greater than 57 dBm ( e.g., 59 dBm max), using the direction connection method, should not be seen as cause for unit rejection. DO-181 specifies the transponder power output at the antenna. Testing a unit on the bench by direct connection to the antenna port yields a power reading at the transmitter output. The difference is, of course, antenna cable and connector losses. DO-181 specifies transponder power output in watts and dBW. The IFR ATC-601 displays power in dBm (ERP). The TIC-48/-49 displays power in watts. The following chart may be useful for proper test evaluation: Watts
dBW
dBm
50 70 100 125 150 200 250 300 350 400 450 500
16.99 18.45 20.00 20.97 21.76 23.01 23.98 24.77 25.44 26.02 26.53 26.99
46.99 48.45 50.00 50.97 51.76 53.01 53.98 54.77 55.44 56.02 56.53 56.99
TDR-94/94D Spec
(Min for airplanes limited to 15 000 ft and 175 kts.) Minimum at antenna (ramp testing)
Minimum direct (on bench)
Maximum at antenna
To convert milliwatts to dBm, or watts to dBW: a. For calculators with log(10) (usually written log or LOG): P(dBW) = 10 x LOG(P). b. For calculators with log(e) (usually written ln or LN): P(dBW) = 10 x [LN(P) / LN(10)] In both cases, P must be in watts. For dBm, P must be in milliwatts; for example: 450 watts = 450 000 milliwatts. To convert from dBm to milliwatts or dBW to watts: a. For calculators equipped with LOG : P = INVLOG (P(dBW) / 10) b. For calculators equipped with LN : P = INVLN [(P(dBW) / 10) x 2.30259] The result P will be in milliwatts if you use P(dBm) , or watts if you use P(dBW). Most scientific calculators have both the LN (natural logarithm - base e) and the LOG (logarithm base 10) capabiliity. Likewise, most have an INV (inverse) function. Thus you must press INV and then LN or LOG for the INVLN or INVLOG function.
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maintenance 523-0775657 Table 5-13. Acceptance Test Procedures, Using the JcAIR 429E Transmitter/Receiver (Cont).
STEP 4.0
TITLE Gillham Altitude Test
PROCEDURE
DESIRED RESULTS OR SETUP SCREEN
On ATC-601: select
** ATCRBS REPLY TEST ** (lines 2-4 are irrelevant) CODE= ALT=
ATCRBS REPLY TEST ----------->
[
]
Press RUN to start On test select: • ALT TYPE SELECT: ARINC 572 • ARINC 572 ALT IN: TO TDR • Set SOURCE SEL switch to SEL On JcAIR 429E: • Set TX screen ------>
031 01 1566C1 00
On test : • Set POWER to OFF • Set all ARINC 572 switches to OFF: Then set A4, C2, C4, and B4 to SEL. • Set POWER to ON • Set EXT STBY switch to OPR On ATC-601: • Press RUN.
The XFEED OUT lamp turns on. The ATC-601 REPLY lamp indicates that UUT is responding to interrogations.
JcAIR 429E RCV 1 screen shows: ------------------->
203 01 031 01
ATC-601 Screen shows: -------------------->
E0B861 11 F56681 11
(ignore any other labels) ** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE=5263 *****
ALT=5900 FT TEST RUNNING
[4460] *****
(The CODE 5263 depends on your selection in the 031 TX word. See note 1 under step 1.2 above) At this step you are asked to toggle each of the ARINC 572 switches and the altitude display. You should also watch the RX data word on the JcAIR 429E display. By cycling each switch between OFF and SEL you should see the ATC-601 display and the JcAIR 429E 203 data word change. If the displays do not change for a particular switch, this would indicate either an open or a shorted code line. If the wrong altitude is shown, this would suggest that the code line is affecting another line; i.e., causing two or more inputs to change simultaneously. In either case the UUT, the test , or the interconnecting cable needs repair. Set each switch as shown in the listing below to the (position) shown, and back, and the altitude display at both positions. The altitude display should always revert to the initial display when the switch is returned to its original position. There is no serious need to the correctness of the RCV word provided the ATC-601 display is correct. SWITCH Initial A1 (SEL) A2 (SEL) A4 (OFF) C1 (SEL) C2 (OFF)
DISPLAYED ALTITUDE 5,900 FT [4460] 23,600 FT [5460] 7,600 FT [6460] -400 FT (0460] none (blank; this is invalid) 5,800 FT [4440]
SWITCH C4 (OFF) B1 (SEL) B2 (SEL) B4 (OFF) D2 (SEL) D4 (SEL)
DISPLAYED ALTITUDE 6,000 FT [4420] 3,600 FT [4560] 5,600 FT [4660] 6,600 FT [4060] 119,600 FT [4462] 55,600 FT [4464]
For additional information on Gillham code structure, refer to paragraph 5.7 below.
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maintenance 523-0775657 Table 5-13. Acceptance Test Procedures, Using the JcAIR 429E Transmitter/Receiver (Cont).
STEP 5.0
TITLE CSDB tuning test
PROCEDURE
This test cannot be performed using a JcAIR 429E because these instruments are not capable of transmitting or receiver CSDB data. However, as an acceptable alternative, you can use a CTL92/92A, connected to the test using the cable shown in figure 907. • Turn power off and connect CTL-92/92A to test . Be sure CTL-92/92A mode knob is set to OFF. • Disconnect the JCAIR 429E from the test . • Turn power on and set the CTL-92/92A mode knob to ALT. On the CTL: • Set the CTL-92/92A to 5263 or any desired ident code.
5.1
CSDB altitude test
DESIRED RESULTS OR SETUP SCREEN
** ATCRBS REPLY TEST **
(lines 2-4 are irrelavent) CODE=5263 *****
ALT=32 800 FT [1344] TEST RUNNING *****
On test : • Set CONTROL DATA SELECT to CSDB • Set OUTPUT PORT SELECT to CSDB PORT 1 • Set ALT TYPE SELECT to CSDB • Set ARINC 572 ALT IN to TO CTL • Set SOURCE SELECT to CTL
The CODE 5263 depends on your selection on the CTL92/92A code select knobs. See note 1 under step 1.2 above. The ALT display depends on the altitude selection on the test ARINC 572 ALT IN switches.
On the test : • Set OUTPUT PORT SELECT to CSDB PORT 2
Be sure that the ACT display, on the CTL-92/92A, does not flash. A flashing ACT at either port selection indicates that output port has failed. If both ports flash, there may be a problem with the test wiring or the CTL input.
Be sure that the ACT display, on the CTL-92/92A does not flash. A flashing ACT indicates that the control label 1F data, from the TDR, does not agree with the CLT-92/92A output label 1E data to the TDR. Only one of the two data CTL input ports is being used; pins U/V.
In this altitude test configuration, Gillham altitude data is being supplied to the CTL (ARINC 572 ALT IN to CTL). The CTL converts this data to CSDB and supplies it to the TDR via the CSDB data output port (only 1 port is used; pins S/R). The CSDB altitude data is being read on the control bus input (SOURCE SELECT to CTL). You can this by setting the CTL mode switch to ON. If you suspect a problem with the altitude data, check the following:
On the test : • Set ARINC 572 ALT IN to TO TDR • Set ALT TYPE SELECT to ARINC 572 • Set SOURCE SELECT to SEL
The ATC-601 ALT display should be the same as above since the ultimate source of altitude information is the same in both tests. If it is different here, suspect a problem with one or more of the altitude discrete inputs to the CTL. If you encounter such a problem, you can identify the defective discrete by returning these three switches to the settings above and then performing the ARINC 572 switching sequence shown following step 4.0 above.
On test : • Set power to OFF • Disconnect the CTL-92/92A from the test • Set CONTROL DATA SELECT - ARINC PORT to PA • Set OUTPUT PORT SELECT to ARINC 429 PORT A • Reconnect the JcAIR 429E from the test .
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STEP
6.0
TITLE
ARINC 429 Altitude Test
PROCEDURE On test : • Set EXT STBY switch to STBY • Set POWER switch to OFF • ALT TYPE SELECT: ARINC 429 • OUTPUT PORT SELECT: ARINC 429 PORT A On JcAIR 429E: • Set TX screen ------> On ATC-601: select ATCRBS REPLY TEST and press RUN to indicate TEST RUNNING --------->
On test : • Set POWER to ON • Set EXT STBY to OPR The ATC-601 screen shows: --->
DESIRED RESULTS OR SETUP SCREEN 031 01 1566C1 00 203 01 640001 11
** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE= *****
ALT= [ ] TEST RUNNING *****
The XFEED OUT lamp turns on. The ATC-601 REPLY lamp indicates that UUT is responding to interrogations.
** ATCRBS REPLY TEST **
(lines 2-4 are irrelavent) CODE=5263 *****
ALT=32 800 FT [1344] TEST RUNNING *****
(The CODE 5263 depends on your selection in the 031 TX word. See note 1 under step 1.2 above.) JcAIR 429E RX screen shows: -------> 6.1
ARINC Altitude Control Disc-retes Tests
On the test : • Be sure the SOURCE SELECT switch is set to SEL. On the test : • Set the REP ALT SEL switch to PB
203 01 640001 11
(ignore any other displayed labels) ** ATCRBS REPLY TEST **
(lines 2-4 are irrelavent) CODE=5263 *****
ALT=32 800 FT [1344] TEST RUNNING *****
Notice that the ATC-601 altitude display blanks. Note: At this point the UUT is configured to report altitude data from port B. There is none so the display blanks.
On the test : • Move the parallel connection from the PRIMARY DIGITAL ALTITUDE SOURCE jack to the ALTERNATE DIGITAL ALTITUDE SOURCE jack.
Notice that the ATC-601 altitude display returns.
On the test : • Set the REP ALT SEL switch to PA
Notice that the ATC-601 altitude display blanks.
Note: This verifies that UUT is configured to report altitude data being supplied on port B.
Note: UUT is returned to port A. This series of steps has verified that the Reporting Altitude discrete is switchable. On the test : • Set the SOURCE SELECT switch to CTL
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Notice that the ATC-601 altitude display returns. Note: This switches the UUT to the altitude data supplied on the control port.
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maintenance 523-0775657 Table 5-13. Acceptance Test Procedures, Using the JcAIR 429E Transmitter/Receiver (Cont).
STEP
TITLE
PROCEDURE
DESIRED RESULTS OR SETUP SCREEN
6.1 (cont’d)
ARINC Control Disc-retes Tests (cont’d)
On the test : • Disconnect the parallel connection from the ALTERNATE DIGITAL ALTITUDE SOURCE jack. (Wait about 5 seconds)
Notice that the ATC-601 altitude display remains.
On JcAIR 429E: • Set the SOURCE SELECT switch to SEL.
Notice that the ATC-601 altitude display blanks.
On test : • Reconnect the parallel connection to the ALTERNATE DIGITAL ALTITUDE SOURCE jack.
Notice that the ATC-601 altitude display remains blanked.
On test : • Set the AUTO ALT switch to SEL (-003 UUT units only)
Notice that the ATC-601 altitude display returns.
On test : • Set the AUTO ALT switch to OFF (-003 UUT units only)
Notice that the ATC-601 altitude display blanks.
On the JcAIR 429E: • Set the TX label 031 word to -------->
031 01 9566E1 00
Note: This verifies the previous step; that altitude is being drawn from the control port; all other sources are disconnected.
Note: This verifies that the Source Select Discrete is switchable.
Note: This enables the automatic altitude port select feature and verifies that the UUT does switch to alternate port B even though port A is the selected port.
Note: This verifies that the AUTO ALT discrete is switchable.
Notice that the ATC-601 altitude display returns. Note: This digitally switches the UUT to port B. If this test is correct while the earlier test of port B altitude failed, suspect a problem with the Reporting Altitude Select discrete. If both tests failed, suspect a problem with the altitude data receivers.
On test : • Set EXT STBY switch to STBY. • Set the POWER switch OFF. On JcAIR 429E: • Set the TX label 031 word to: --------->
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031 01 1566C1 00
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maintenance 523-0775657 Table 5-13. Acceptance Test Procedures, Using the JcAIR 429E Transmitter/Receiver (Cont).
STEP
TITLE
PROCEDURE
DESIRED RESULTS OR SETUP SCREEN
The remainder of the step is optional. Testing for various digital altitude inputs is primarily software verification and therefore unnecessary. If the UUT responds to one altitude word input it will likely respond to all. If you wish, you can set the TX label 203 data field bits 12 through 28 to any combination of 1 and 0. The RCV 1 label 203 word data field will follow the TX word exactly while the ATC-601, set to the ATCRBS REPLY TEST mode, will show the altitude to the nearest 100 feet. When set to the MODE UF0 TEST, the ATC-601 displays altitude to the nearest 25 feet. The label 203 bit values are shown in note 2 following step 1.2. To 1. 2. 3. 4. 5. 6.
simulate any altitude up to about 131,000 feet: Select the desired altitude. Find the data bit with the maximum bit value less than the selected altitude. Make a note of that bit number. Subtract that bit value from your selected value. Find the next bit with the maximum bit value less than the remainder. Make a note of that bit number. Subtract that bit value from your remainder. Repeat steps 4 and 5 until the remainder is 0.
In the TX label 203 data word, set all noted bits to 1. You should see your selected altitude, to the nearest 100 feet, displayed on the ATC-601. 7.0
ARINC 575 Altitude Test
On test : • SOURCE SELECT: SEL • ALT TYPE SELECT: ARINC 429 On JcAIR 429E: • Set screen ------>
031 01 1566C1 00 203 01 640001 11
On test : • Connect parallel control cable to PRIMARY DIGITAL ALTITUDE SOURCE jack. • Set POWER switch to ON. • Set EXT STBY switch to OPR. On ATC-601: • Select ATCRBS REPLY TEST and press RUN to indicate TEST RUNNING. ATC-601 screen --------> On test : • Set ALT TYPE SELECT switch to ARINC 575 On JcAIR 429E: • Set TX label 203 word --------> (just change the SSM to 00) ATC-601 screen -------->
** ATCRBS REPLY TEST **
(lines 2-4 are irrelavent) CODE=5263 *****
203 01 040001 00
** ATCRBS REPLY TEST **
(lines 2-4 are irrelavent) CODE=5263 *****
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ALT=32,800 FT [1344] TEST RUNNING *****
ALT=16,400 FT [3230] TEST RUNNING *****
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STEP 7.0 (cont’d)
TITLE ARINC 575 Altitude Test (cont’d)
PROCEDURE JcAIR 429E RX screen --------->
DESIRED RESULTS OR SETUP SCREEN 203 01 620001 11
In addition to testing the altitude type select discrete, this test illustrates the differences between ARINC 429 and ARINC 575 data. Notice that the second data bit in the RX label 203 word (above) one-half the bit value of the corresponding bit in the TX label 203 word and the SSM code is 11 as opposed to the 00 in the TX word. In ARINC 575, the LSB is bit 13; in ARINC 429 the LSB is bit 12. In ARINC 575, bits 30 and 31 determine the sign; 00 being positive. Notice also, that the altitude displayed on the ATC-601 corresponds to the code in the RX word; not the TX word. This is also due to the UUT being configured for ARINC 575 and thus the bit values are offset by 1 bit position which has the effect of changing the altitude by a factor of 1/2. On test : • Set ALT TYPE SELECT switch to ARINC 429 On JcAIR 429E: • Set TX label 203 word ---->
031 01 1566C1 00 203 01 640001 11
ATC-601 screen: ** ATCRBS REPLY TEST **
(lines 2-4 are irrelavent) CODE=5263 *****
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ALT=32,800 FT [1344] TEST RUNNING *****
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maintenance 523-0775657 Table 5-13. Acceptance Test Procedures, Using the JcAIR 429E Transmitter/Receiver (Cont).
STEP 8.0
TITLE Mode S Address Discretes Test
PROCEDURE
DESIRED RESULTS OR SETUP SCREEN
On the test : • Set POWER switch OFF • Set all test mode s address switches to SEL except switch P1-56; set it to OFF. • Set POWER switch ON On ATC-601: • Set for MODE S ALL CALL TEST ------->
** MODE S ALL CALL TEST - NO REPLY ALL CALL ADDRESS = [ NUMBER = Press RUN to start
On ATC 601: • Press RUN • Note screen ----->
** MODE S ALL CALL TEST ALL CALL ADDRESS = FFFFFE TAIL NUMBER =
** ]
TAIL
ED ** [77777776]
****** TEST RUNNING *****
The remainder of this step should be seen as optional unless you have reason to suspect a failure in one or more of the address discrete lines. The procedure will require a few minutes because of the delay involved in cycling power between each switch setting.
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On test : • Set POWER switch OFF. • Set each triad of address switches for an octal digit 6. • Set POWER switch ON.
After a few seconds, UUT begins to reply and shortly thereafter the ATC-601 screen shows the following address:
On test : • Set POWER switch OFF. • Set each triad of address switches for an octal digit 4. • Set POWER switch ON.
After a few seconds, UUT begins to reply and shortly thereafter the ATC-601 screen shows the following address:
On test : • Set POWER switch OFF. • Set each triad of address switches for an octal digit 0, except the eighth triad which is set to 1. • Set POWER switch ON.
After a few seconds, UUT begins to reply and shortly thereafter the ATC-601 screen shows the following address:
ALL CALL ADDRESS = DB6DB6
ALL CALL ADDRESS = 924924
ALL CALL ADDRESS = 000001
[66666666]
[44444444]
[00000001]
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STEP 9.0
TITLE TCAS / NO TCAS Discrete Select and TCAS Bus Test
PROCEDURE
DESIRED RESULTS
On test : • Set POWER switch OFF On JcAIR 429E: • Same setup as STEP 1.1. ATC-601 is not needed for this test but can be left on. On test : • Set POWER switch ON
The JcAIR 429E RX screen shows: 350 01 600001 11
After unit begins operating, display the 350 word. On test : • Set POWER switch to OFF • Set TCAS/NO TCAS switch to TCAS On test : • Set POWER switch to ON
The JcAIR 429E RX screen shows: 350 01 68B301 11 |<---diagnostic code B3
The diagnostic code B3 indicates a TCAS bus failure. Bit 28 in the data word is also set which produces the 8 in the display. See paragraph 5.B. below.
Refer to paragraph 5.B. for a more detailed discussion. This display shows a diagnostic B3 which is interpreted: TCAS Bus Inactive. This verifies that the discrete properly configures the unit for operation with a TCAS. However, no TCAS data is being supplied in this step, therefore, the unit declares a B3 diagnostic. TCAS Bus Test, XPDR to TCAS
Connect the JcAIR 429E RX to the TCAS OUT jack. that the data word labels are detectable as shown ------->. Note: Except for the diagnostic code in the label 350 data word, the data content is not important. It is quite likely that the data will be different. The presence of the data word labels shown verifies that the TCAS data bus output is active and appears to be normal.
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275 00 800000 00 276 10 80F802 00 350 01 68B301 11 |<---diagnostic code B3
Set the JcAIR 429E for high speed. Other labels may also be present.
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maintenance 523-0775657 Table 5-13. Acceptance Test Procedures, Using the JcAIR 429E Transmitter/Receiver (Cont).
STEP 9.0 (cont’d)
TITLE TCAS to XPDR Bus Test
PROCEDURE
DESIRED RESULTS
Note: In this step you need the capability of transmitting data to two separate input ports simultaneously and at different speeds; the 031 control word must be low speed (12.5-kbps) while the TCAS label 274 data words must be high speed (100-kbps). All JcAIR 429E instruments can transmit at either of these speeds but not on two separate ports simultaneously. If you do not have this capability, you may not be able to the integrity of the TCAS bus input port. If you have access to a second JcAIR 429E, connect your second transmitter port or data bus simulator to the TCAS IN and setup as shown -------->:
274 00 180000 00
On bus reader RCV display:
After a few seconds, the 350 word shows:
Note: The objective is to that the UUT recognizes a valid TCAS label 274 word and declares this by removing the diagnostic B3.
350 01 680001 11 |<---diagnostic code 00
On the bus reader: Set the XMT 2 word to OFF
After a few seconds, notice that the B3 diagnostic returns.
Note: Be sure to set for high speed.
Note: Disconnect XMT 2 from the TCAS IN jack and reconnect RCV 1 to the DATA BUS OUTPUT port. Final step in this test, all setups
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On test : • Set POWER switch to OFF • Set TCAS/NO TCAS switch to NO TCAS On test : • Set POWER switch to ON
After a few seconds, the original 350 word returns: 350 01 000001 11
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STEP 10.0
TITLE Side 1/ Side 2 Discrete Test
PROCEDURE
DESIRED RESULTS
On test : • Set POWER switch OFF • Be sure SIDE 1/SIDE 2 switch is set to SIDE 1. On JcAIR 429E: • Same setup as STEP 1.1. On ATC-601: • Set for ATCRBS REPLY TEST screen ----->
CODE= *****
On test : • Set POWER switch ON
After a few seconds, X FEED OUT and ATC-601 REPLY lamps light and the ATC-601 shows:
** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) ALT= TEST RUNNING
[ *****
]
** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE=5263 ALT=32,800 FT [1344] ***** TEST RUNNING *****
On test : • Set POWER switch to OFF • Set SIDE 1/SIDE 2 switch to SIDE 2 • Set POWER switch to ON
Note that unit does not reply (X FEED OUT lamp and REPLY lamps are off and no altitude is displayed on ATC-601). Wait about 10 seconds. Note: UUT does not respond because the SDI and side strapping do not agree. Note: Be sure to allow adequate time for the U to reinitialize properly between power off and power on. The SIDE 1/2 strap is one of several that are monitored only at processor initialization. Therefore, if this tests fails, cycle power again but allow more time between power off and power on.
On JcAIR 429E: • On TX, label 031 word, set the SDI to 10
Notice that unit begins to reply almost immediately (XFEED OUT lamp turns on and ATC-601 REPLY lamp lights). Note: UUT responds because the SDI and side strapping agree.
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On JcAIR 429E: • On TX, label 031 word, set SDI to 01.
Notice that unit stops replying (X FEED OUT lamp and ATC-601 REPLY lamps turn off).
On test : • Set POWER switch OFF • Set SIDE 1/SIDE 2 switch to SIDE 1 • Set POWER switch ON
After a few seconds, X FEED OUT and ATC-601 REPLY lamps light and the ATC-601 shows that the UUT is replying.
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STEP 11.0
TITLE AIR/ GND Discrete Test
PROCEDURE
DESIRED RESULTS
On test : • Set POWER switch OFF • TDR ALT SOURCE: EXT DIRECT • ALT TYPE SELECT: ARINC 429 On JcAIR 429E: • Same setup as STEP 1.1. On ATC-601: • Set for MODE S UF4 TEST screen ----->
** MODE S UF4 TEST - NO REPLY ** DF FS= ADDRESS= *****
On test : • Set POWER switch ON ATC-601 screen shows ----->:
DR=
UM=
TEST RUNNING
AC= *****
After a few seconds, X FEED OUT and ATC-601 REPLY lamps light and the ATC-601 shows: ** MODE S UF4 TEST - ED ** DF 4 FS=0 DR=00 UM=00 ADDRESS=000001 *****
TEST RUNNING
AC=32,775 FT *****
Note: Initially the screen will show FS=2 for about 2 seconds and then change to FS=0. On test : • Set AIR/GND switch to GND
After a few seconds, the ATC-601 shows: ** MODE S UF4 TEST - ED ** DF 4 FS=1 DR=00 ADDRESS=000001 *****
UM=00 AC=32,775 FT
TEST RUNNING
*****
Of particular significance here is the FS (flight status) indication. For a detailed description of each of these message fields, refer to the Theory of Operation section. On test : • Set AIR/GND switch to AIR
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After a few seconds, notice that the ATC-601 FS field again shows 0.
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maintenance 523-0775657 Table 5-13. Acceptance Test Procedures, Using the JcAIR 429E Transmitter/Receiver (Cont). STEP 12.0
TITLE DL ANT/ SGL ANT Discrete Test (TDR-94D only)
PROCEDURE
DESIRED RESULTS
On test : • Set POWER switch OFF On JcAIR 429E: • Same setup as STEP 1.1. On ATC-601, set for SQUITTER TEST screen -----> Be sure the ATC-601 is connected to the top antenna port. On test : • Set DL ANT/SGL ANT switch to DL ANT • Set POWER switch ON Watch the PERIOD display for a time. You will notice it changing somewhat but it should remain at or near 2 seconds.
** SQUITTER TEST - NO REPLY ** PERIOD = SECONDS TAIL NUMBER = SQUITTER ADDRESS= [ *****
TEST RUNNING
]
*****
After a few seconds, the ATC-601 screen shows: See note below. ** SQUITTER TEST - ED PERIOD = 2.00 SECONDS TAIL NUMBER = SQUITTER ADDRESS= [ *****
TEST RUNNING
** ]
*****
See the note at the end of this step for test tolerances. On test : • Set POWER switch OFF • Set DL ANT/SGL ANT switch to SGL ANT • Set POWER switch ON
After a few seconds, the ATC-601 screen shows: ** SQUITTER TEST - FAILED PERIOD = SECONDS TAIL NUMBER = SQUITTER ADDRESS= [ *****
TEST RUNNING
** ]
*****
Note: This test is intended to fail. When the UUT is set for single antenna operation, there is no transmission from the top antenna port. Therefore, if this test indicates ED, recheck all switch settings or suspect a problem with the SGL/DL ANT select strap. It should not . On test : • Set POWER switch OFF On ATC-601: • Press RUN to stop the test. • Remove rf terminator from bottom antenna connector • Connect ATC-601 cable to bottom antenna connector • Connect rf terminator to top antenna connector
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STEP 12.0 (cont’d)
TITLE DL ANT /SGL ANT Discrete Test (cont’d) (TDR-94D only)
PROCEDURE On test : • Set POWER switch ON On ATC-601: • Press RUN to start the test.
DESIRED RESULTS After a few seconds, the ATC-601 screen shows: See note below. ** SQUITTER TEST - ED PERIOD = 1.00 SECONDS TAIL NUMBER = SQUITTER ADDRESS= [ *****
On test : • Set POWER switch OFF • Set DL ANT/SGL ANT switch to DL ANT • Set POWER switch ON
TEST RUNNING
** ]
*****
After a few seconds, the ATC-601 screen shows: See note below. ** SQUITTER TEST - ED PERIOD = 2.00 SECONDS TAIL NUMBER = SQUITTER ADDRESS= [ *****
TEST RUNNING
** ]
*****
Note: The PERIOD value tends to vary somewhat in all cases. When the UUT is set for dual antenna operation and the ATC-601 is monitoring the top or the bottom antenna port, the value can vary from 1.6 to 2.4. When the TDR-94D is set for single antenna operation, or the UUT is a TDR-94, there is no transmission from the top antenna port and and the transmission PERIOD from the bottom antenna port can vary from 0.6 to 1.4. 13.0
Burst Tune and CrossFeed In DiscreteT est
On ATC-601, set for SQUITTER TEST screen -----> If necessary, reconnect ATC-601 to bottom antenna connector, with terminator on top (TDR-94D only) connector.
** SQUITTER TEST - NO REPLY ** PERIOD = SECONDS TAIL NUMBER = SQUITTER ADDRESS= [ ] *****
TEST RUNNING
*****
On JcAIR 429E: • Same setup as STEP 1.1. On test : • CONTROL DATA SELECT: PA • ALT TYPE SELECT: ARINC 429 • SOURCE SELECT: SEL • Be sure that X FEED IN/OUT switch is set to OUT • Be sure that BURST TUNE switch is set to OFF. On test : • Set POWER switch ON
After a few seconds, the test X FEED OUT and the ATC-601 REPLY lamps light indicating that the unit is replying. The ATC-601 screen data indicates ED.
On test : • Set X FEED IN/OUT switch to IN
Notice that both X FEED lamps are lighted.
On JcAIR 429E: • Set TX to OFF
Notice that the X FEED OUT and ATC-601 REPLY lamps turns off (X FEED IN stays on).
(The easiest way to turn TX off is to disconnect it from the test )
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maintenance 523-0775657 Table 5-13. Acceptance Test Procedures, Using the JcAIR 429E Transmitter/Receiver (Cont). STEP 13.0 (cont’d)
14.0
TITLE Burst Tune and CrossFeed In Discrete Test (cont’d)
Output Port Discrete Test
PROCEDURE
DESIRED RESULTS
On JcAIR 429E: • Set TX to ON
Notice that the X FEED IN and OUT and REPLY lamps are lighted.
On test : • Set X FEED IN/OUT switch to OUT • Set BURST TUNE to ON On JcAIR 429E: • Set TX to OFF
Notice that UUT continues to reply. Watch the unit for a few seconds. (The X FEED IN lamp extinguishes because the switch turns it off.)
On test : • Set BURST TUNE switch to OFF
Notice that UUT stops replying (X FEED OUT and REPLY lamps turn off).
On test : • Set BURST TUNE to ON
Notice that UUT does not reply (X FEED OUT and REPLY lamps do not light).
On JcAIR 429E: • Set TX to ON
Notice that UUT replys (X FEED OUT and REPLY lamps are on).
On test : • Set BURST TUNE to OFF On JcAIR 429E: • Set TX to OFF
Notice that UUT stops replying (X FEED OUT and REPLY lamps are off).
On JcAIR 429E: • Set TX to ON
X FEED OUT lamp and the REPLY lamp turns on again.
On test : • Set X FEED IN/OUT switch to IN • Set BURST TUNE switch to ON. • Set TX to ON
X FEED OUT lamp flashes .
On test : • Set BURST TUNE to OFF • Set POWER switch to OFF • Set X FEED IN/OUT to OUT • ALT TYPE SELECT: ARINC 429 • CONTROL DATA SEL: PA • OUTPUT PORT SELECT: ARINC 429 PORT A On JcAIR 429E: • The same as STEP 1.1 On test : • Set POWER switch to ON
Both X FEED OUT and REPLY lamps are on.
JcAIR 429E RCV screen ----->
031 01 F56681 11
Note: Be sure that the JcAIR screen flashes somewhat. This indicates that the screen is being updated. A nonflashing screen usually indicates that obsolete data is being displayed.
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On ATC-601, set for SQUITTER TEST
After a few seconds, the ATC-601 screen data indicates ED.
On test : • Set OUTPUT PORT SELECT switch to ARINC 429 PORT B
Notice that there is no change in the test result; X FEED OUT and REPLY lights are on and JCAIR screen does not change.
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STEP 15.0
TITLE Control Data Input Port Select Discrete Test
PROCEDURE
DESIRED RESULTS
On test : • Set POWER switch OFF • Set SOURCE SELECT switch to SEL • ALT TYPE SELECT: ARINC 429 • CONTROL DATA SELECT: ARINC PORT PA On JcAIR 429E: • Same setup as for STEP 1.1. On ATC-601, set for SQUITTER TEST screen ----->
** SQUITTER TEST - NO REPLY ** PERIOD = SECONDS TAIL NUMBER = SQUITTER ADDRESS= [ ] *****
16.0
Manual STBY Discrete Test
TEST RUNNING
*****
On test : • Set POWER switch ON
After a few seconds, the test X FEED OUT and the ATC-601 REPLY lamps light indicating that the unit is replying. The ATC-601 screen data indicates ED.
On test : • Set CONTROL DATA SELECT switch to ARINC PORT PB
Notice that there is no change in the test result; X FEED OUTand REPLY lights are on and ATC-601 display does not change.
On test : • Set CONTROL DATA SELECT switch to ARINC PORT PC
Notice that there is no change in the test result; X FEED OUT and REPLY lights are on and ATC-601 display does not change.
On test : • Set EXT STBY switch to STBY • Set POWER switch OFF • Set CONTROL DATA SELECT switch to ARINC PORT PA On JcAIR 429E: • Same setup as for STEP 1.1. On ATC-601: • Set for ATCRBS REPLY TEST screen ---------->
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** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE= *****
ALT= [ ] TEST RUNNING *****
On test : • Set POWER switch ON • Set EXT STBY switch to OPR
After a few seconds, the test X FEED OUTand the ATC-601 REPLY lamps light indicating that the unit is replying. The ATC-601 screen data indicates ED.
On test : • Set EXT STBY switch to STBY
Note that X FEED OUT lamp and ATC-601 REPLY lamps turn off and ATC-601 indicates NO REPLY. See note below.
On test : • Set EXT STBY switch to OPR
Note that X FEED OUT lamp and ATC-601 REPLY lamps light almost immediately and ATC-601 indicates ED.
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STEP 17.0
TITLE Max Airspeed Test
PROCEDURE
DESIRED RESULTS
On test : • Set POWER switch OFF • ALT TYPE SELECT: ARINC 429 • Be sure that all three MAX AIRSPEED switches are set to OFF. On JcAIR 429E: • Same setup as for STEP 1.1. (The JcAIR 429E is used here only for tuning data.) On ATC-601: • Set for MODE S UF0 TEST screen --->
** MODE S UF0 TEST - NO REPLY ** DF
VS= ADDRESS= *****
On test : • Set POWER switch ON
RI=
AC=
TEST RUNNING
*****
After a few seconds, the test X FEED OUT lamp and the ATC-601 REPLY lamps light indicating that the unit is replying.
Note the ATC-601 screen ----------->
** MODE S UF0 TEST - ED ** DF 0 VS=0 RI=8 ADDRESS=000001 *****
AC= 32,775 FT
TEST RUNNING
*****
Exercise the MAX AIRSPEED switches on the test and the correct RI indication as shown in the following list. Cycle power and allow about 2 or 3 seconds of OFF time and about 5 seconds for processor initialization and ATC-601 response time between each switch setting. MAX AIRSPEED SWITCH BIT 15 BIT 16 BIT 17 OFF OFF OFF SEL OFF OFF OFF SEL OFF SEL SEL OFF OFF OFF SEL SEL OFF SEL OFF SEL SEL SEL SEL SEL
RI VALUE 8 9 A B C D E F (not an assigned configuration)
It is worth noting that in this test mode the ATC-601 displays the altitude to the nearest 25 feet.
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maintenance 523-0775657 Table 5-13. Acceptance Test Procedures, Using the JcAIR 429E Transmitter/Receiver (Cont).
STEP 18.0
TITLE Ext Suppression Test
PROCEDURE
DESIRED RESULTS
On test : • ALT TYPE SELECT: ARINC 429 On JcAIR 429E: • Same setup as for STEP 1.1. On ATC-601: • Set for ATCRBS REPLY TEST screen -->
** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE= *****
• Connect scope channel A to the test SUPPR test points. • Connect scope channel B to the REPLY VIDEO BNC connector on the ATC-601. • Set the scope to display both channels
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ALT= [ ] TEST RUNNING *****
Note a (approx) 30µs pulse on channel A. Note a reply waveform on channel B. If your scope is able, you will see the individual reply code pulses on channel B. You may also see the occasional squitter transmission which appears as a much longer series of pulses at about 1 transmission every 2 sec. Of particular importance, however, is that the channel A (suppression) pulse is about 30 µs long during ATCRBS reply, and brackets the 21 µs ATCRBS reply. During squitter transmission, the suppression pulse extends to bracket the squitter transmission. The squitter transmission is a DF11 reply about 72 µs long.
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maintenance 523-0775657 Table 5-13. Acceptance Test Procedures, Using the JcAIR 429E Transmitter/Receiver (Cont).
STEP 19.0
TITLE ADLP Select, Discrete Strap Test
PROCEDURE
DESIRED RESULTS
On test : • Be sure DATALINK switch is set to NO ADLP. On JcAIR 429E: • Same setup as for STEP 1.1. JcAIR 429E RX screen ------>
350 01 600001 11
Note: The ATC-601 is not needed for this test but it can remain connected and operating. On test : • Set POWER switch to OFF • Set DATALINK switch to ADLP. • Be sure DATALINK SELECT switch is set to A/B. • Set POWER switch to ON.
350 01 64A201 11 |<---diagnostic code A2
Note: The diagnostic A2 identifies an inactive ADLP bus. This test verifies that the ADLP enable discrete is functional. The 4 reflects bit 27 in the data word which is also set indicating an ADLP bus failure.
JcAIR 429E RX screen ------> On test : • Set POWER switch to OFF. • Set DATALINK switch to NO ADLP. • Set POWER switch to ON.
350 01 600001 11 |<---diagnostic code 00
JcAIR 429E RX screen ------> Note: The Airborne Datalink system is not fully implemented at this time. If and when an ADLP (Airborne DataLink Processor) becomes available and operational, suitable procedures will be provided to the integrity of the ADLP input/output ports. At this point, therefore, verification of the ADLP SELECT strap is seen as sufficient to prevent nuisance diagnostics that can occur if the select input should be defective. You will notice that the DATALINK SELECT A/B, C/D function is also not tested.
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maintenance 523-0775657 Table 5-13. Acceptance Test Procedures, Using the JcAIR 429E Transmitter/Receiver (Cont).
STEP 20.0
TITLE Remote IDENT Discrete Test
PROCEDURE
DESIRED RESULTS
On test : • Same as initial setup On JcAIR 429E: • Same setup as for STEP 1.1. On ATC-601: • Setup for ATCRBS REPLY test
** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE= *****
On test : • Set the POWER switch to ON • Set the EXT STBY switch to OPR • Press and release the REMOTE IDENT switch. On JcAIR 429E: • Notice RX screen ----->: On ATC-601: • Notice the ID display. ID should display for about 18 seconds.
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ALT= [ ] TEST RUNNING *****
031 01 756691 11 |<----Ident bit
Note: The 9 should appear in the data field only while the switch is being pressed. This, together with the ID display on the ATC-601, verifies that the REMOTE IDENTdiscrete input is functional. ** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE=ID5263 ALT= 32,800 FT [1344] |<----ID display ***** TEST RUNNING *****
On JcAIR 429E: • Set the label 031 TX word:
031 01 156691 00
On JcAIR 429E RX and on ATC-601 screens:
You should see the same displays as immediately above. If the test failed using the REMOTE IDENT switch, but succeeds here, then suspect a failure in the discrete input or the test .
On JcAIR 429E: • Set the label 031 TX word:
031 01 956681 00
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STEP 21.0
TITLE Self Test
PROCEDURE
DESIRED RESULTS
On test : • Set POWER switch OFF • ALT TYPE SELECT: ARINC 429 • AIR/GND: AIR • SELF TEST: ENABLE: OFF On JcAIR 429E: • Same setup as for STEP 1.1. On ATC-601: • Set for ATCRBS REPLY TEST ---------->
** ATCRBS REPLY TEST **
(lines 2-4 are irrelevant) CODE= *****
ALT= [ ] TEST RUNNING *****
On test : • Set POWER switch ON
After a few seconds, the test X FEED OUT lamp and the ATC-601 REPLY lamps light indicating that the unit is replying. The ATC-601 screen indicates ED.
On JcAIR 429E: RX screen shows: --------->
031 01 F56681 11 203 01 640001 11 350 01 600001 11
In the next few steps, watch the JcAIR 429E RX screen carefully. On the test : • Press and hold the SELF TEST pushbutton for about 1 sec.
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After a few seconds, notice that the ATC-601 screen does not change The JcAIR 429E RX display may go blank.
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maintenance 523-0775657 Table 5-13. Acceptance Test Procedures, Using the JcAIR 429E Transmitter/Receiver (Cont).
STEP 21.0
TITLE Self Test (cont’d)
PROCEDURE
DESIRED RESULTS
On test : • Set the AIR/GND switch to GND • Set the SELF TEST/ENABLE switch to ON • Press and hold the SELF-TEST button for about 1 s
Self-test Displays: After a few seconds, notice that the X FEED OUT lamp turns off briefly while the ATC-601 screen shows +’s or -’s in most of the data fields, followed by blank fields.
Note: The test TEST lamp lights while you hold the switch. This has no bearing on UUT operation, however. If the lamp does not light, check the test .
After a few seconds, notice that the X FEED OUT lamps turns on again and the ATC-601 screen returns to the normal display. On the JcAIR 429E notice that the SM changes to 10 and then back to 11.You should try to be especially watchful of the 350 data word and try to catch any diagnostic codes that may be displayed during the selftest sequence.
On the test : • Set the SELF TEST/ENABLE switch to OFF. • Press and hold the SELF TEST button for about 1 s.
Notice that the self-test displays as described above do not appear..
On the test : • Set the SELF TEST/ENABLE switch to ON. • Set the AIR/GND switch to AIR. • Wait about 5 seconds *. • Press and hold the SELF TEST button for about 1 s.
Notice that the self-test displays as described above do not appear..
Note: This verifies that self test is properly inhibited by the self-test inhibit discrete.
Note: This verifies that self test is properly inhibited by the AIR/GND discrete.
*Note: The U must be allowed sufficient time to complete at least one software cycle in order to recognize the change in the AIR/GND discrete. If you press the SELF TEST switch in less than about 3 seconds of setting the AIR/GND switch to AIR, the unit may execute self-test as though it were not inhibited. This should be seen as normal. On the test : • Set the SELF TEST/ENABLE switch to ON. • Set the AIR/GND switch to GND. • Press and hold the SELF TEST button for about 1 s.
Notice the self-test displays as described above reappear. Note: This verifies that the self-test inhibit and AIR/GND discretes are switchable.
This completes this test sequence. Successful completion of this series provides reasonable assurance that the unit is operational. However, this test does not satisfy the requirements of a Final Performance Test which must be performed after any repair operation. Turn off all power, disconnect the equipment, and return it to its normal storage location. Return the UUT to its original shipping container, or equivalent, if it is to remain in storage. Otherwise, prepare it for installation.
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maintenance 523-0775657 5.4.5.11.1 JcAIR 429E Transmitter/Receiver, Operating Instructions This paragraph provides instructions that may be helpful in operating the JcAIR 429E Transmitter / Receiver. It is intended for those who may be unfamiliar with its operation and may need some help.
If you are familiar with the JcAIR 429E: Set the TX 1 output to: 031 01 156681 00; this produces an ATC code: 5236. Set the TX 2 output to: 203 01 640000 11; this produces an altitude: 32,800 ft. These are the TX hex values used most often in the procedures of Table 5-13.
Setup and Operating Instructions if you are unfamiliar with the operation of the JcAir 429E: During the course of this procedure, do not turn power off to the JcAIR 429E. All entered data is lost. Preliminary setup Set: TX Parity to ODD TX Speed to LO RX Speed to LO Display to Hex TX label and word setup for this procedure 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. 13. 14. 15. 16. 17. 18. 19. 20. 21. 22. 23. 24. 25. 26. 27. 28. 29. 30.
When screen shows: 0 RX LABELS, press TX/RX Screen shows: 0 TX LABELS Press ’up arrow’ key Screen shows: TX 1 INACTIVE Press EDIT/DEL Screen shows a blinking cursor on an otherwise blank screen Enter 031 Press ENT Screen shows: 031 BCN ATC CODE Press LAB/DAT Screen shows: 031 00 000000 00 Press EDIT/DEL Screen shows a blinking cursor on an otherwise blank screen Enter 6-digit Hex code as desired or 156681 Press ENT Screen shows: 031 01 956681 00 (The parity bit causes the change from 1 to 9 in the first digit) Press TX/RX until screen shows 1 TX LABELS Press ’up arrow’ until screen shows TX 2 INACTIVE Press EDIT/DEL Screen shows a blinking cursor on an otherwise blank screen Enter 203 Press ENT Screen shows: 203 ALTITUDE Press LAB/DAT Screen shows: 203 00 000000 00 Press EDIT/DEL Screen shows a blinking cursor on an otherwise blank screen Enter E40000 Press ENT Screen shows: 203 01 E40000 11
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maintenance 523-0775657
RX labels setup for this procedure: Note: The procedures below may not be needed depending on the software version of the JcAIR 429E being used. The objective of the test is to capture (trap) ARINC 429 labels 031, 203, and 350 words. Consult the JcAIR 429E Operator’s Manual for detailed instructions if needed. 1. 2. 3. 4. 5. 6. 7. 8. 9. 10.
If the JcAIR 429E is not already on, turn POWER switch to ON If necessary, press TX/RX until screen shows: 0 RX LABELS Press TRAP Screen shows a blinking cursor on an otherwise blank screen Enter 031 Press ENT Screen shows: 031 SDI? _ (blinking cursor) Enter 01 Press ENT Screen shows: 0 RX LABELS
Note: This screen tends to blink slightly indicating that the display is being updated. If data is being received, the left digit will increment (quite rapidly) to a maximum of 255 indicating the number of words that have been captured. 11. Press TRAP until screen again shows a blinking cursor 12. Repeat steps 3 through 11 but enter 203 at step 5. (At step 10, the display will show: 1 RX LABELS) 13. Repeat steps 3 through 11 but enter 350 at step 5. (At step 10, the display will show: 2 RX LABELS) 14. Press ENT twice. To change altitude: 1. 2. 3. 4. 5. 6. 7. 8.
Press TX/RX until the screen shows: 2 TX LABELS (The 2 is an integer indicating the number of TX labels that are entered) Press the ’up arrow’ key until the screen shows: 203 ALTITUDE Press LAB/DAT until the screen shows: 203 01 E40000 11 (The six-digit hex code will be the most recently entered code) Press EDIT/DEL Screen shows a blinking cursor on an otherwise blank screen Enter the necessary hex value for the desired altitude or E41BB1 (33,654 ft) (see note 2 under step 1.4 below) Press ENT Screen shows: 203 01 641BB1 11
This entry will cause the ATC-601 to show 33,700 FT..
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To change ATC code: 1. 2. 3. 4.
Press TX/RX until the screen shows: 2 TX LABELS (The 2 is an integer indicating the number of TX labels that are entered) Press the ’up arrow’ key until the screen shows: 031 BCN ATC CODE Press LAB/DAT Screen shows: 031 BCN ATC CODE
4.
Press EDIT/DEL
5. 6. 7. 8. 9.
Screen shows a blinking cursor on an otherwise blank screen Enter the necessary hex value for the desired ATC code or 5263 Press ENT TX screen shows: 031 01 0E5C01 00 RX screen shows: 031 01 0E5C01 00
This entry will cause the ATC-601 to show CODE=6352 Note: You can set the JcAIR DISPLAY switch to Eng to show the 4-digit code. The ATC-601 CODE and JcAIR 429E Eng code displays should always agree. 10.
Reset the TX 031 and 203 words to the Initial Setup
To view captured data: 1. 2.
3. 4.
Press TX/RX until the screen shows: 3 RX LABELS Press ’up arrow’ to select the desired word label/title: 031 BCN ATC CODE 203 ALTITUDE 350 MAINT DATA 1 Press LAB/DAT
Screen shows the selected word/data (only one at a time): 031 01 156681 00 203 01 640000 11 350 01 000001 11
To select a different word: 5. 6. 7. 8.
Press LAB/DAT Press ’up arrow’ or ’down arrow’ to select one word label/title as shown in 2. above: Press LAB/DAT to view the data Screen shows the selected word data as in 4 above.
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maintenance 523-0775657 5.5 MAINTENANCE DIAGNOSTIC DATA RETRIEVAL AND ANALYSIS 5.5.1
Introduction
This paragraph provides detailed information related to the diagnostic data stored in the TDR-94/94D transponder. It is intended to the procedures found in table 5-6. The stored data consists of fault and maintenance data which is stored in nonvolatile memory. Memory space, for this purpose, is allocated according to table 5-14. Notice that there are two categories of data: general maintenance and diagnostic data. Table 5-14 shows structure of the diagnostic data.
Memory space consists of 256 bytes of NVRAM. The general maintenance data buffers use 14 bytes and the remainder is used for diagnostic data storage. Each diagnostic occurrence uses 10 bytes. Thus, there is space for 24 diagnostic occurrences. If more than 24 occurrences are detected, the most recent is retained as follows: In -002 units, the most recent occurrence is overwritten. That is, occurrences 1 through 23 are retained while the 24th occurrence is overwritten when a new occurrence is detected. In -003 units, the oldest occurrence is overwritten.
Table 5-14. Maintenance and Diagnostic Data Memory Structure
GENERAL MAINTENANCE DATA BUFFERS DATA DESCRIPTION
BYTES USED
Pointer to next diagnostic code location
2
Power-on cycle counter
2
Total diagnostic counter
1
Total power-on timer (minutes)
1
Power-on timer (hours)
2
Last POC diagnostic counter
1
Current POC timer
1
Last maintenance date
4 DIAGNOSTIC DATA BUFFERS
Time from last power on
1
Diagnostic code
1
(not used)
1
Transmitter temperature (degrees Celsius)
1
Current power-on cycle count buffer
2
Air/ground state at time of diagnostic
1
Time at end of power-on cycle
1
Altitude at time of diagnostic
1
Altitude at time of diagnostic
1
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maintenance 523-0775657 5.5.2
General Diagnostic Formats
Maintenance diagnostic data is provided on the ARINC 429 output buses only. The maintenance data is provided on a label 351 data word when requested by an ARINC 429 label 277 data word at any of the ARINC 429 input ports. Unless a total is requested, the output is based on a oneresponse for one-request basis. In all cases, no data is provided unless the Air/ground discrete is at a logic 0; that is, the airplane is on the ground. No stored diagnostic data is provided on any of the CSDB buses. This procedure uses the Atlantic Instruments, DataTrac 400 DataTrac 400H, DataTrac 200 Databus Readers, or the JcAIR 429E Transmitter/Receiver for data request and receive. For the sake of brevity, in these procedures the term "bus reader" should be understood to apply to either of these instruments. If you have or prefer an equivalent instrument, feel free to use it. Some procedural adaptation may be required. Control ports A, B, or C can be used. The general format of the maintenance request and response data is as follows: BIT NO. BIT DESIGNATION 1 - 8 MSB - LSB LABEL (see note 1) 9 Hex fault code B0 10 Hex fault code B1 11 Hex fault code B2 12 Hex fault code B3 13 Hex fault code B4 14 Hex fault code B5 15 Hex fault code B6 16 Hex fault code B7 17 Hex fault code B8 18 Hex fault code B9 19 Hex fault code B10 20 Hex fault code B11 21 Hex fault code B12 22 Hex fault code B13 23 Hex fault code B14 24 Hex fault code B15 25 Hex fault code B16 26 Hex fault code B17 27 Hex fault code B18 28 Hex fault code B19 29 PAD 30 Test type (see note 2) 31 Test type (see note 2) 32 Parity 5/5/1993
Note 1: Label structure: Bit: 8 7 6 5 4 Value: 1 2 4 1 2 Label 277: 1 1 1 1 1 Label 351: 1 0 0 1 0 See also paragraph
3 2 1 4 1 2 1 0 1 1 1 1 5.7.4.8
Note 2: Test type definition: BIT 31 0
BIT 30 DEFINITION 0 Software rev status, request or response 0 1 RAM memory output, re quest or response; requires 4-digit address code for specific data 1 0 Last maintenance date, load command * 1 1 Detailed diagnostic data, request or response. Requires 2-digit hex code(**) for specific data * s are CAUTIONED not to use this code. This code will destroy some of the stored diagnostic data. It is intended for use only after bench repair. See paragraph 5.5.11. ** Hex code listing: Hex Requested data 01 Contents of total power-on cycle counter buffer 02 Contents of total fault counter buffer 03 Contents of total power-on timer (hours) buffer 04 Contents of total power-on timer (minutes) buffer 05 Contents of last power-on cycle fault counter buffer 06 Not defined 07 Contents of last maintenance date buffer 08-0F Not defined 10 of the diagnostic codes detected during the most recent power-on cycle (if any- see below) 11-1X of the diagnostic codes detected during preceding power-on cycles, where 11 is the next to the most recent and 1X is the request code that produces a 00EOF (End Of File) response.
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maintenance 523-0775657 5.5.3 Software Revision Status (SRS) Reporting The software revision status is of questionable value for field use. It is presented here so that if a need or purpose develops it can be accessed.
5.5.3.1 SRS Word Definition Upon receipt of a label 277 request for diagnostic data, with bits 31 and 30 set to 00, the TDR-94D responds with a label 351 word with the following structure:
1: 32 31 30 29 28 27 26 25 24 23 22 21 20 2: 8 4 2 1 8 4 2 1 8 | | | | \ | | / \ | | / \ | | | | | | | \ / \__BCD month \ BCD day | \__SSM bits, 11 implies a request \__Parity
19 18 17 16 15 14 13 12 11 10 4 2 1 8 4 2 1 8 4 2 | | / | | | | | | | | \ | | / \ | | / \ BCD yr / for diagnostic data
Description: Bit 32: Parity bit: This bit is set to a 1 when the total of the other 31 bits set to 1 is 0 or an even number. Bits 31 and 30: SSM bits: 11 implies a request for diagnostic data. Bits 29 - 25: BCD month: Bit 29 gives the tens value; 0 or 1. Bits 28 -25 give the units value; 0 - 9. Bits 24 - 17: BCD day: Bits 24 - 21 give the tens value; 0 - 3. Bits 17 - 20 give the units value; 0 - 9. Bits 16 - 9: BCD year: Bits 16 - 13 give the tens value; 8,9,0. Bits 12 - 9 give the units value; 0 - 9.
Set the bus reader XMT for a label 277 data word as follows:
5.5.3.2 SRS Data Request Note: The AIR/GND switch, in the test , must be in the GND position and TEST INHIBIT must be off. That is, pin P238 must be open.
9 1 | /
DataTrac: ON--------------XMT 1----------12.5 KHz LBL SDI 11----- Data--- SSM Par msec 277 00 60 00 00 FD 11 1 0100
JcAIR 429E: 277 00 600000 11
It is important that the SM (SSM) is set to 11. The SDI is set automatically when data is entered into the 5th and 6th digits of the data field. These are the only XMT digits that will be manually changed in this procedure. Response example: DataTrac: ----------------RCV 1--(ALL)---12.5 KHz LBL SDI 32-Hex Data-1 SSM Par Tmin 351 10 09 12 90 97 11 1 0200
JcAIR 429E: 351 10 091290 11
This indicates that the SRS of this unit is: 9 December 1990. It is important to set the bus reader to the proper display format for easy data interpretation.
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maintenance 523-0775657 5.5.4 Memory Examination Request and Response (MERR) This paragraph is provided for information purposes only. Memory allocation, within the memory blocks, is controlled dynamically by the operating software and therefore is difficult predict. Data necessary for maintenance can be obtained more easily by the procedures in the rest of this paragraph.
5.5.4.1 MERR, General Word Definition The memory examination request word label 277 is defined as follows:
32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 9 1 8 4 2 1 8 4 2 1 8 4 2 1 8 4 2 1 8 4 2 1 | \ / | | | | | | | | | | | | | | | | | | | | | | | Pad | || || || || | | | \<-------------- 00000H to 0FFFFH --------------> / | | (memory locations) | \__SSM, 11 implies a request for diagnostic data \__Parity The response word label 351 is defined as follows: 32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 9 - - - - - - - - 8 4 2 1 8 4 2 1 8 4 2 1 8 4 2 1 | \__/ | \__|__|__/ \__|__|__/ \__|__|__/ \__|__|__/ \__|__|__/ | | | | | | | | | | \<-Pad->/ \<--Data in requested location------>/ | \__SSM, 11 implies memory examination request \__Parity
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maintenance 523-0775657 5.5.5
Total Power-on Cycle Count (TPOCC) Buffer
Each time the TDR-94/94D is turned on, the TPOCC buffer is incremented. Therefore, this buffer contains the number of times the unit has experienced a power application.
5.5.5.1 TPOCC General Word Definition The total power-on cycle counter data request word label 277 is defined as follows:
32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 9 - - - - - - - - - - - - - - - - 8 4 2 1 8 4 2 1 | \__/ | \__|__|__/ \__|__|__/ \__|__|__/ \__|__|__/ \__|__|__/ | | | | | | | | | | \<------------Pad-------------> / \<----01H--->/ | \__SSM, 11 implies a diagnostic data request \__Parity The response word label 351 is defined as follows: 32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 - - - - - - - - - - - - - - - - 8 4 2 1 8 4 2 | \__/ | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | Pad \10,000’S/ \1,000’S / \ 100’S / \ 10’S / \units | \__SSM, 11 implies response to a diagnostic data request \__Parity
9 1 | | /
5.5.5.2 TPOCC Buffer Examination Setup bus reader XMT screens as follows: DataTrac: ON------------XMT 1----------12.5 KHz LBL SDI 32-Hex Data-1 SSM Par msec 277 01 00 00 00 FD 11 1 0100
JcAIR 429E:
The reader should respond with a label 351 word similar to this: DataTrac: ON------------RCV 1--(ALL)---12.5 KHz LBL SDI 32-Hex Data-1 SSM Par msec 351 10 00 30 56 97 11 1 0200
277 01 800001 11
JcAIR 429E: 351 10 003056 11
This indicates that the UUT has undergone 3,056 power-on cycles.
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maintenance 523-0775657 5.5.6
Total Fault Counter (TFC) Buffer
Each time a diagnostic condition is recognized, the TFC buffer is incremented. Therefore, this buffer contains the number diagnostic conditions the unit has experienced.
5.5.6.1 TFC General Word Definition The TFC buffer data request word label 277 is defined as follows:
32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 9 - - - - - - - - - - - - - - - - 8 4 2 1 8 4 2 1 | \__/ | \__|__|__/ \__|__|__/ \__|__|__/ \__|__|__/ \__|__|__/ | | | | | | | | | | \<------------Pad--- -------->/ \<---02H--->/ | \__SSM, 11 implies a request for diagnostic data \__Parity The response word label 351 is defined as follows: 32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 - - - - - - - - - - - - - - - - 8 4 2 1 8 4 2 | \__/ | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | Pad \10,000’S/ \1,000’S / \ 100’S / \ 10’S / \units | \__SSM, 11 implies response to a request for diagnostic data \__Parity
9 1 | | /
5.5.6.2 TFC Buffer Examination Setup bus reader XMT screens as follows:
The reader should respond with a label 351 word similar to this:
DataTrac: ON------------XMT 1----------12.5 KHz LBL SDI 32-Hex Data-1 SSM Par msec 277 10 80 00 02 FD 11 1 0100
JcAIR 429E: 277 10 800002 11
DataTrac: ON------------RCV 1--(ALL)---12.5 KHz LBL SDI 32-Hex Data-1 SSM Par msec 351 10 60 01 02 97 11 1 0200
JcAIR 429E: 351 10 600102 11
This indicates that the UUT has experienced 102 diagnostic conditions.
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maintenance 523-0775657 5.5.7 Total Power-on Timer (Hours) (TPOTH) Buffer Two data buffers are used to record the total time the unit is in operation; an hours buffer and a minutes buffer. As the unit is operating, the minutes counter is continuously incremented. The hours buffer is incremented each time the minutes counter overflows.
5.5.7.1 TPOTH General Word Definition The total TPOTH buffer data request word label 277 is defined as follows:
32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 9 - - - - - - - - - - - - - - - - 8 4 2 1 8 4 2 1 | \__/ | \__|__|__/ \__|__|__/ \__|__|__/ \__|__|__/ \__|__|__/ | | | | | | | | | | \<--------Pad------------> / \<----03H--->/ | \__SSM, 11 implies a request for diagnostic data \__Parity The response word label 351 is defined as follows: 32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 - - - - - - - - - - - - - - - - 8 4 2 1 8 4 2 | \__/ | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | Pad \10,000’S/ \1,000’S / \ 100’S / \ 10’S / \units | \__SSM, 11 implies response to a request for diagnostic data \__Parity
9 1 | | /
5.5.7.2 TPOTH Buffer Examination Setup bus reader XMT screens as follows:
The reader should respond with a label 351 word similar to this:
DataTrac: ON------------XMT 1----------12.5 KHz LBL SDI 32-Hex Data-1 SSM Par msec 277 11 60 00 03 FD 11 1 0100
JcAIR 429E: 277 11 600003 11
DataTrac: ON------------RCV 1--(ALL)---12.5 KHz LBL SDI 32-Hex Data-1 SSM Par msec 351 11 E0 03 57 97 11 1 0200
JcAIR 429E: 351 11 E00357 11
This example shows that the TPTOH buffer contains the value 357.
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maintenance 523-0775657 5.5.8 Total Power-on Timer (Minutes) (TPOTM) Buffer The TPOTM buffer is incremented each minute that the unit has power applied. Overflow of this buffer causes the TPOTH buffer to be incremented.
5.5.8.1 TPOTM General Word Definition The total TPOTM buffer data request word label 277 is defined as follows:
32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 - - - - - - - - - - - - - - - | \__/ | \__|__|__/ \__|__|__/ \__|__|__/ | | | | | | | | \<--------Pad------------> / | \__SSM, 11 implies a request for diagnostic \__Parity
16 15 14 13 12 11 10 9 8 4 2 1 8 4 2 1 \__|__|__/ \__|__|__/ | | \<---04H--->/ data
The response word label 351 is defined as follows: 32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 - - - - - - - - - - - - - - - - 8 4 2 1 8 4 2 | \__/ | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | Pad \not used/ \not used/ \not used/ \ 10’S / \units | \__SSM, 11 implies response to a request for diagnostic data \__Parity
9 1 | | /
5.5.8.2 TPOTM Buffer Examination Setup bus reader XMT screens as follows:
The reader should respond with a label 351 word similar to this:
DataTrac: ON------------XMT 1----------12.5 KHz LBL SDI 32-Hex Data-1 SSM Par msec 277 00 E0 00 04 FD 11 1 0100
JcAIR 429E: 277 00 E00004 11
DataTrac: ON------------RCV 1--(ALL)---12.5 KHz LBL SDI 32-Hex Data-1 SSM Par msec 351 11 60 00 27 97 11 1 0200
JcAIR 429E: 351 11 600027 11
This indicates that the unit TPTOM buffer contains the number 27.
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maintenance 523-0775657 5.5.9 Last Power-on Cycle (LPOC) Fault Counter Buffer This buffer contains the number of diagnostic conditions detected during the most recent power-on cycle.
5.5.9.1 LPOC General Word Definition The last LPOC fault counter buffer data request word label 277 is defined as follows:
32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 9 - - - - - - - - - - - - - - - - 8 4 2 1 8 4 2 1 | \__/ | \__|__|__/ \__|__|__/ \__|__|__/ \__|__|__/ \__|__|__/ | | | | | | | | | | \<--------Pad------------> / \<---05H--->/ | \__SSM, 11 implies a request for diagnostic data \__Parity The response word label 351 is defined as follows: 32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 - - - - - - - - - - - - - - - - 8 4 2 1 8 4 2 | \__/ | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | Pad \not used/ \not used/ \ 100’s / \ 10’s / \units | \__SSM, 11 implies response to request for diagnostic data \__Parity
9 1 | | /
5.5.9.2 LPOC Buffer Examination Setup bus reader XMT screens as follows:
The reader should respond with a label 351 word similar to this:
DataTrac: ON------------XMT 1----------12.5 KHz LBL SDI 32-Hex Data-1 SSM Par msec 277 01 60 00 05 FD 11 1 0100
JcAIR 429E: 277 01 600005 11
DataTrac: ON------------RCV 1--(ALL)---12.5 KHz LBL SDI 32-Hex Data-1 SSM Par msec 351 11 E0 00 07 97 11 0200
JcAIR 429E: 351 11 E00007 11
This indicates that during the most recent poweron cycle 7 diagnostic conditions were detected.
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maintenance 523-0775657 5.5.10 Last Maintenance Date (LMD) Buffer (Examination)
upon whether the date was properly entered. 5.5.10.1
This buffer should contains the most recent maintenance date. Whether or not this date accurately reflects the date on which the unit was most recently repaired or tested depends
LMD General Word Definition
The LMD buffer data request word label 277 is defined as follows:
32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 9 - - - - - - - - - - - - - - - - 8 4 2 1 8 4 2 1 | \__/ | \__|__|__/ \__|__|__/ \__|__|__/ \__|__|__/ \__|__|__/ | | | | | | | | | | \<--------Pad------------> / \<---07H--->/ | \__SSM, 11 implies a request for diagnostic data \__Parity The response word label 351 is defined as follows: 1: 32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 2: 8 4 2 1 8 4 2 1 8 4 2 1 8 4 2 1 8 | | | | \ | | / \ | | / \ | | / | | | | | | | | \ | \ / \__BCD month \ BCD day / | \__SSM bits, 11 implies response to a request \__Parity 5.5.10.2
LMD Buffer Examination
Setup bus reader XMT screens as follows: DataTrac: ON------------XMT 1----------12.5 KHz LBL SDI 32-Hex Data-1 SSM Par msec 277 11 E0 00 07 FD 11 1 0100
JcAIR 429E: 277 11 E00007 11
The reader should respond with a label 351 word similar to this: DataTrac: ON------------RCV 1--(ALL)---12.5 KHz LBL SDI 32-Hex Data-1 SSM Par msec 351 01 70 06 91 97 11 1 0200
15 4 | |
14 2 | |
13 12 11 10 9 1 8 4 2 1 | | | | | / \ | | / \ BCD yr / for diagnostic data
This indicates that the last maintenance date for this unit was October 6, 1991. You need to recognize that the 7, here, includes the SSM bits which for a value of 6 (4 + 2). Thus 7 - 6 = 1 which means that bit 29 is a 1. This sets the month at 10; October. 5.5.11 Last Maintenance Date (LMD) Buffer (Update) A method for updating the LMD buffer is not included in this manual. The LMD buffer should be changed only after a repair action, unit modification, or detailed test procedure has been performed.
JcAIR 429E: 351 01 700691 11
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maintenance 523-0775657 5.5.12 Last Power-on Cycle Faults (LPOCF) Data This process allows for retrieval of all the diagnostics detected during the most recent power-on cycle. This can be seen as an extension to step 5.5.5. In that step we learned the number of faults detected during the most recent power-on cycle. In this sequence we will learn what those diagnostic codes are. In this sequence you must watch the label 351 word carefully. The UUT may transmit several words, each with a different diagnostic code, at 5-second intervals.
The first transmission is the contents of the current Total Power-on Cycle count buffer (as in 5.5.5 above). This is followed, in 5-second intervals, with a transmission of each of the diagnostic codes encountered during the most recent power-on cycle (self-test). The sequence is automatic therefore you should be prepared to write down the data as it appears. The final label 351 word is likely to be a word similar to 07FFE which does not translate into a meaningful diagnostic code. 5.5.12.1
LPOCF General Word Definition
The LPOCF data request word label 277 is defined as follows:
32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 9 - - - - - - - - - - - - - - - - 8 4 2 1 8 4 2 1 | \__/ | \__|__|__/ \__|__|__/ \__|__|__/ \__|__|__/ \__|__|__/ | | | | | | | | | | \<--------Pad------------> / \<---10H--->/ | \__SSM, 11 implies a request for diagnostic data \__Parity The first response label 351 word is defined in paragraph 5.5.5.
The second and subsequent response label 351 word(s) are defined as follows:
32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 9 - - - - - - - - - - - - - - - - 8 4 2 1 8 4 2 1 | \__/ | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | Pad \not used/ \not used/ \not used/ \ Hex fault code / | \__11 implies response to detailed diagnostic data request \__Parity 5.5.12.2
LPOCF Data
Setup bus reader XMT screens as follows:
The reader should respond with a label 351 word similar to this:
DataTrac: ON------------XMT 1----------12.5 KHz LBL SDI 32-Hex Data-1 SSM Par msec 277 00 E0 00 10 FD 11 1 0100
JcAIR 429E: 277 00 E00010 11
DataTrac: ON------------RCV 1--(ALL)---12.5 KHz LBL SDI 32-Hex Data-1 SSM Par msec 351 11 E0 00 B3 97 11 1 0200
JcAIR 429E: 351 11 E000B3 11
This example indicates that this unit experienced a diagnostic code B3 at the last power on cycle. One of the 351 label words may indicate an FF label which. This code is not defined and so you can ignore it.
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You may likely encounter a diagnostic code B3 on the bench. This diagnostic is interpreted as "TCAS bus inactive".
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maintenance 523-0775657 5.5.13 Continue Flight Fault (CFF) Data This paragraph can be seen as an extension of the previous paragraph 5.5.12. In that paragraph only those diagnostics detected during the most recent power-on cycle are revealed. In this paragraph, 5.5.12, all of the diagnostics stored in NVRAM and detected during preceding power-on cycles are examined. 5.5.13.1
CFF General Word Definition
The data format is the same as in paragraph 5.5.12 except that the hex data in the label 277 interrogation word is incremented from 10H to 1XH. Of course, if you have already examined the 10H, in paragraph 5.5.12, you Buffer 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16
277 Word 10H 11H 12H 13H 14H 15H 16H 17H 18H 19H 1AH 1BH 1CH 1DH 1EH 1FH
can begin here with 11H. The UUT responds by sending each stored code for a 5-second period. Continue incrementing the hex data until the UUT sends an ’end of file’ data field = 00EOFH. This is displayed on the DataTrac and JcAIR 429E as 000EOF. , you only need to change digits 5 and 6 in the data fields of both the DataTrac and JcAIR readers. The SDI and parity bits will change automatically. 5.5.13.2
CFF General Procedures
The diagnostic conditions detected during the preceding 16 (maximum) power-on cycles can be reviewed by interrogating the UUT with a label 277 data word, with SSM set to 10 and the data in the bit field, bits 9 through 16 set to 1X as follows (assuming no. 1 being the most recent):
DataTrac 200/400/400H, 277 Word Setup Lbl SDI 32-Hex Data-1 SM Par msec 277 00 E0 00 10 FD 11 1 0100 277 01 60 00 11 FD 11 1 0100 277 10 60 00 12 FD 11 1 0100 277 11 E0 00 13 FD 11 1 0100 277 00 60 00 14 FD 11 1 0100 277 01 E0 00 15 FD 11 1 0100 277 10 E0 00 16 FD 11 1 0100 277 11 60 00 17 FD 11 1 0100 277 00 60 00 18 FD 11 1 0100 277 01 E0 00 19 FD 11 1 0100 277 10 E0 00 1A FD 11 1 0100 277 11 60 00 1B FD 11 1 0100 277 00 E0 00 1C FD 11 1 0100 277 01 60 00 1D FD 11 1 0100 277 10 60 00 1E FD 11 1 0100 277 11 E0 00 1F FD 11 1 0100
JcAIR 429E, 277 word 277 277 277 277 277 277 277 277 277 277 277 277 277 277 277 277
00 01 10 11 00 01 10 11 00 01 10 11 00 01 10 11
E00010 600011 600012 E00013 600014 E00015 E00016 600017 600018 E00019 E0001A 60001B E0001C 60001D 60001E E0001F
11 11 11 11 11 11 11 11 11 11 11 11 11 11 11 11
Any of the above can produce a response:
DataTrac: ON------------RCV 1--(ALL)---12.5 KHz LBL SDI 32-Hex Data-1 SSM Par msec 351 11 E0 30 57 97 11 1 0200 351 11 E0 0E 0F 97 11 1 0200
JcAIR 429E: 351 11 E03057 00 351 11 E00E0F 00
The UUT should respond with at least two label 351 data words. The first is the contents of the Total Power-on Counter buffer
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which may be a relatively large number depending on the length of time the unit has been in service.
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maintenance 523-0775657 Special note for -002 units: In -002 units, only the internal diagnostic conditions resulting in a failure-warn condition and improper mode S address diagnostic conditions are stored. The mode S address diagnostic can easily occur when the unit is turned on with all address lines open or shorted to ground. Consequently you may frequently notice a 0000FF hex code as the second 351 word. It is also possible that in some units you may encounter a Total Power-on Timer (Hours) buffer with an unrealistically large number. Early units were not properly cleared at production. In these cases, of course, the data is of no value.
intended for use with a data storage device which is capable of capturing and storing data transmitted in rapid sequence. The DataTrac 400/400H is capable of this function. After ing the data, it can then be further ed, using procedures and software supplied with the DataTrac 400/400H, onto a PC for detailed analysis and permanent storage. The DataTrac 200 is capable of capturing the data but lacks the means of transferring it for external storage and interpretation. A manual analysis is seen as inefficiently laborious and time consuming and therefore is not recommended. However, if this is not seen as prohibitive, refer to paragraph 5.5.14 for the Slow Fault Data . 5.5.14.1
FF General Word Definition
5.5.14 Fast Fault (FF) Data The feature used in this paragraph is
The FF data request word label 277 is defined as follows:
32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 9 - - - - - - - - - - - - - - - - 8 4 2 1 8 4 2 1 | \__/ | \__|__|__/ \__|__|__/ \__|__|__/ \__|__|__/ \__|__|__/ | | | | | | | | | | \<--------Pad------------> / \<---50H--->/ | \__SSM, 11 implies a request for diagnostic data \__Parity 5.5.14.2 FF Data Description When the 277 label word as described in paragraph 5.5.14.1 is sent to the UUT, it responds as follows: a. Power-on cycle counter buffer as described in paragraph 5.5.5 above. b. Total fault counter buffer as described in paragraph 5.5.6 above. c. Total power-on timer (hours) buffer as described in paragraph 5.5.7 above. d. Total power-on timer (minutes) buffer as described in paragraph 5.5.8 above. e. Last power-on cycle fault counter buffer as described in paragraph 5.5.9 above. f. Last maintenance date buffer as described in paragraph 5.5.10 above.
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The UUT then transmits a ’break’ indicator using the same format as described in paragraph 5.5.7 (power-on timer (hours)), except the data is set to 00FFFF. Following this the UUT transmits the nine (9) fault data bytes for the last recorded diagnostic in the following sequence and formats: g. Current Power-on Cycle count buffer as described in 5.5.5 above. h. Diagnostic code as described in paragraph 5.5.9 above. i. Time from last power-on using the following format:
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maintenance 523-0775657 32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 - - - - - - - - - - - - 8 4 2 1 8 4 2 1 8 4 2 | \__/ | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | Pad \not used/ \not used/ \ 1 Hr / \10 min / \ 1 min | \__SSM, 11 implies response to request for diagnostic data \__Parity
9 1 | | /
j. Transmitter temperature at time of diagnostic using the following format: 32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 - - - - - - - - - - - - 8 4 2 1 8 4 2 1 8 4 2 | \__/ | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | Pad \not used/ \not used/ \ 100’s / \ 10’s / \ units | \__SSM, 11 implies response to request for diagnostic data \__Parity
9 1 | | /
k. Air/ground state at time the diagnostic was detected, using the following format: 32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 - - - - - - - - - - - - - - - - 8 4 2 1 8 4 2 | \__/ | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | FAH = in air | | Pad \not used/ \not used/ \not used/ \ FDH = on ground | \__SSM, 11 implies response to request for diagnostic data \__Parity
9 1 | / /
l. Time at end of power-on cycle as described in transmission i. above. m. Altitude at time of diagnostic using the following format: 32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 - - - - - - - - - - - - - - - - 8 4 2 1 8 4 2 | \__/ | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | Pad \10,000s / \1000s / \ 100s / \ 10s / \ units | \__SSM, 11 implies response to request for diagnostic data \__Parity
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9 1 | | /
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maintenance 523-0775657 5.5.14.3
FF Data Equipment
This feature is intended for those with access to an automated means of requesting, capturing, and analyzing the data. Such facilities are at least partially available from sources other than Collins and you are encouraged to acquire and use them. For example: • Atlantic Instruments supplies hardware and software, operating with the DataTrac 400/400H, for automatically capturing and ing the data onto a PC. • Avionica Inc., 3830, SW 130th Ave., Miami FL 33175, supplies a laptop computer equipped with appropriate hardware and software to , store, and display diagnostic data from a number of Collins units including the TDR-94/94D Mode S Transponder as well as the TTR-920 TCAS Transmitter/Receiver.
5.5.15.1
SF General Word Definition
Same as 5.5.13.1 except hex data is set to 51H. 5.5.15.2
SF Data Procedure
Use the following chart, reproduced in a quantity required, to record the data as it appears on your databus reader. Set the bus reader for the proper display format for direct interpretation of the data as described in the preceding paragraphs.
5.5.15 Slow Fault (SF) Data This data feature is basically the same as that described in paragraph 5.5.13 except that the hex field in the data request word is set to 51H (instead of 50H). This will cause the UUT to transmit the same data as described in paragraph 5.5.13 except that it is transmitted one data file at a time at 5 seconds intervals.
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maintenance 523-0775657 *******
Duplicate this sheet as required
*******
Date: _______________ UUT Type: _____( ) TDR-94: Part No: 622-9352UUT Type: _____( ) TDR-94D: Part No: 622-9210UUT Serno: _____________ Customer: _________________________________________ Data taken by: ____________________________________ (Your name)
TDR-94/94D Diagnostic
Diagnostic Code
Power-on Cycle Counter: _________ Total Fault Counter: _________ Total Power-on Timer (Hrs): _________ Total Power-on Timer (Min): _________ Last Power-on Fault Counter: _________ Existing Last Maintenance Date: _________ New Last Maintenance Date: * _________ Break: ___ 0FFFFF Current Power-on Cycle Count: _________ Diagnostic Code: _________ Time From Last Power-on: _________ Xmitter Temp at Diag: _________ Air/Gnd State at Diag: _________ Time at end of Power-on Cycle: _________ Altitude at Diag: _________
Data Record Interpretation _______________________ _______________________ _______________________ _______________________ _______________________ _______________________ _______________________ _______________________ _______________________ _______________________ _______________________ _______________________ _______________________ _______________________
* To be changed only after repair, modification, or detailed (bench) test. Power-on cycle diagnostics (1 = most recent): 1:___________, 2:___________, 3:_____________, 4:____________, 5:____________, 6:___________, 7:____________, 8:____________, 9:___________, 10:___________, 11:__________, 12:___________, 13:___________, 14:____________, 15:___________, 16:____________, 17:___________, 19:___________, 20:___________, 21:____________, 22:___________, 23:____________, 24:____________ Comments: ______________________________________________________________________________ _____________________________________________________________________________ _____________________________________________________________________________ _____________________________________________________________________________
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maintenance 523-0775657 5.6 NUMBER SYSTEM CONVERSION AND DATA WORD DESCRIPTIONS
If you have one of these, use it. Otherwise, this paragraph describes a relatively simple method of converting between the Hexadecimal and Octal numbering systems. This is useful for Mode S transponder testing because the data systems used in the mode s transponder use all three systems. For example, the mode s address is typically assigned as an eight-digit octal number. This octal number is translated into a binary number for address strapping at installation. During testing, quite often this address is displayed as a six-digit hexadecimal number.
This paragraph provides detailed descriptions of the various data formats used in the TDR94/94D. These formats use a variety of numbering systems including binary, octal, and hexadecimal. Paragraph 5.6.1 provides a procedure for conversion between these numbering systems. If you are familiar with a conversion process, you should feel free to use that process. 5.6.1 Octal-to-Binary-to-Hexadecimal, and Back
Use the following listing to convert your hexadecimal or octal number to its binary equivalent.
There are many relatively inexpensive handheld calculators with number conversion capability available. Hex-to-Binary Conversion Hex 0 1 2 3 4 5 6 7
Binary 0000 0001 0010 0011 0100 0101 0110 0111
Hex 8 9 A B C D E F
Octal-to-Binary Conversion
Binary 1000 1001 1010 1011 1100 1101 1110 1111
Octal 0 1 2 3 4 5 6 7
Convert from the six-digit hexadecimal number to an eight-digit octal number as follows: Enter the hex number on the top (Hex) line of the following chart. Then enter the equivalent binary values for each hex Hex: Bit Val:
Binary 000 001 010 011 100 101 110 111
digit from the listing above in the center (Bin) line. Then use the lower bit values to convert those binary bits, three bits at a time, into the equivalent octal number and enter those numbers on the lower (Oct) line.
8
4
2
1
8
4
2
1
8
4
2
1
8
4
2
1
8
4
2
1
8
4
2
1
4
2
1
4
2
1
4
2
1
4
2
1
4
2
1
4
2
1
4
2
1
4
2
1
Bin: Bit Val: Oct:
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maintenance 523-0775657 Example: Suppose the test set shows a hex code 3AC421. Enter this code on the top line. Then write the equivalent four digit binary values (from the
hexadecimal listing above) in spaces below each hex digit. Then translate each threedigit grouping of binary numbers into the equivalent octal number.
Hex: Bit Val:
8
4
2
1
8
4
2
1
8
4
2
1
8
4
2
1
8
4
2
1
8
4
2
1
Binary:
0
0
1
1
1
0
1
0
1
1
0
0
0
1
0
0
0
0
1
0
0
0
0
1
Bit Val: Oct:
4
2 1
1
4
2 6
1
4
2 5
1
4
2 4
1
4
2 2
1
4
2 0
1
4
2 4
1
4
2 1
1
3
A
C
To convert from octal to hex, reverse the above process by entering the octal number into the spaces on the lower line. Convert each octal digit into its equivalent binary value. Then convert each four-digit grouping into its equivalent hex value as shown in the Hex-to-Binary conversion listing above-left. Write these numbers into the spaces on the top line. The binary digits, read from left to right, correspond to the mode s addressing switches on the test . That is, the far left digit corresponds to switch and rear connector pin P1-33, the next P1-34, etc, to the far right which is P1-56. The switch set to the OFF position corresponds to a 0; the switch set to SEL corresponds to a 1. The suggested layout shown in figure 5-3 shows the mode s switches labeled according to the octal digits that each controls. This makes the octal code easy to read from the switch positions by adding the binary value of those switches in each 3-switch group set to SEL. You must avoid, however, the combination with all switches up or all switches down. These two combinations are not allowed in the mode s addressing scheme and will produce a transponder diagnostic code FF in TDR-94/94D units with N ending in -002. 5.6.2 Diagnostic Word, ARINC 429 label 350, Definition and Decoding Procedure 5.6.2.1 On DataTrac 400/400H The diagnostic codes listed in table 5-2 are available for viewing on the ARINC 429 label 350 diagnostic word. The DataTrac 400 is capable of displaying this word in a variety of binary and hexadecimal forms. The form that is selected is largely a matter of 5/5/1993
4
2
1
personal preference but the form chosen here is labeled BIN19L. This paragraph shows you how to decode the diagnostic information from this displayed word. Refer to the screen representation below. This shows the label 350 word from bits 29 through 11 as it appears on the DataTrac 400/400H display set for a BIN19L display. (The actual screen will show other words and their labels but this discussion focuses only on the label 350 word.) -----------------RCV 1--(ALL)---12.5 KHz Lbl SDI 29--Binary Data--11 SSM Par msec 350 01 1000010110011000000 11 1 0200
Of course, you can also select the hex display mode for a direct display of the diagnostic code and avoid the conversion process. -----------------RCV 1----------12.5 KHz Lbl SDI 32-Hex Data-1 SSM Par msec 350 01 70 B3 01 17 11 1 0200 ||<---diagnostic code
This display can be reproduced as follows: a. With the ATC-601 set for ATCRBS REPLY, set the test POWER switch to OFF. b. On the test , set the TCAS/NO TCAS switch to TCAS. c. On the DataTrac 400/400H, press RCV and then press ENT. (This clears the display and prepares the analyzer to receive new data.) d. On the test , set the POWER switch to ON. e. After a few seconds, the XFEED OUT lamp lights, the ATC-601 REPLY lamp lights, and the data is displayed on the DataTrac 400/400H RCV 1 screen.
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maintenance 523-0775657 Note: If the 350 word does not appear on the DataTrac 400/400H screen initially, press RCV (until the cursor is at the left of HOLD), then press the down arrow (or up arrow) key to scroll the data words until the 350 word appears. Bits 17 through 24 are the eight data bits that define the 2-digit hexadecimal diagnostic code as follows: Diagnostic digit: MSB Bit: 24 23 Bin value: 8 4 Example: 1 0 Diag: |< B
Bit DEFINITION Bit DEFINITION 11 Xpdr failure
16 Serial control port c failure
12 RAM failure
25 Serial altitude port a failure
13 ROM failure
26 Serial altitude port b failure
LSB 22 2 1
21 1 1 >|
20 8 0 |<
19 18 4 2 0 1 3
14 Port b failure 27 Serial ADLP bus failure
17 1 1 >|
15 Port a failure 28 Serial TCAS bus failure *
Interpretation:TCAS bus inactive (see table 5-2)
The defined failure condition exists when a logic 1 appears in the corresponding bit location.
The conversion process involves translating each of these four-bit groupings into the equivalent hexadecimal value using the binary to hex conversion list in paragraph 5.6.1 above.
* Notice in the screen example above, bit 28 is also set to 1. Incidentally, in the label 350 diagnostic word, bit 29 is defined as a PAD.
Bits 11 through 16, and 25 through 28 identify specific failure conditions. These are defined below.
5.6.2.2 On DataTrac 200 The DataTrac 200 displays the diagnostic code in the HEX RCV field in the form of 5 hex digits as follows:
Hex:
MSB
Data bit: Bit Val:
4
3
2
LSB
30
29
28
27
26
25
24
23
22
21
20
19
18
17
16
15
14
13
12
11
10
8
4
2
1
8
4
2
1
8
4
2
1
8
4
2
1
8
4
2
1
*
* bit 10 is not included in the display
In the test procedures, a TCAS Bus failure diagnostic is induced producing a diagnostic code B3. This
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appears on the DataTrac 200 as a Hex code 45980. This is produced as follows:
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maintenance 523-0775657 Hex bit:
MSB
Data bit: Bit Val: Hex value: Binary: Bit Val:
30 8
29 4
0
1
28 2
4
3
27 1
26 8
25 4
24 2
0
0
1 8
0 4
4 0
23 1
2
22 8
21 4
20 2
1 1
0 8
0 4
5
Data bit: Bit Val: Hex value: Binary: Bit Val:
30 8
29 4
0
1
28 2
Hex value:
15 1
1 1
0
0
0
26 8
25 4
24 2
0
0
1 8
1 4
23 1
12 2
11 1
0
0
0
10 *
0 0
-----------------RCV 1--(ALL)---12.5 KHz Lbl SDI 32-Hex Data-1 SSM Par msec 350 01 68 B3 01 17 11 1 0200 ||<---diagnostic code
In this format you can read the diagnostic code directly from the second pair of hex digits (from the left). Suppose the DataTrac 200 shows a HEX DATA field 47A80. You would interpret this code as follows:
2
22 8
21 4
20 2
1 1
0 8
1 4
7
19 1
LSB
18 8
17 4
16 2
15 1
1 1
0
0
0
A 1 2
13 4
8
3
27 1
14 8
There is an easier way to interpret the diagnostic code and that is to select the 32-Hex Data--1 display format. This will give you a display:
4
4 0
16 2
3
Thus, to properly interpret a diagnostic code as displayed on the DataTrac 200, you must first translate that code into its binary form, extending from bit 11 through 29. Then translate the two four-bit groupings, 18 through 21 for the LSB, and 22 through 25 for the MSB, into the hex diagnostic code. Then refer to table 5-2 for the defined diagnostic. It is important to that bits 11 through 16, and 25 through 28, define specific failure conditions as described in the previous paragraph for the DataTrac 400.
MSB
17 4
1 2
B
Hex bit:
18 8
9 1 2
Hex value:
19 1
LSB
F
14 8
13 4
12 2
11 1
0
0
0
8
0 2
10 *
0 0
5
Thus a DataTrac 200, HEX DATA field display of 47A80 is a diagnostic code F5, which is shown on table 5-2 as Port Selects Changed.
first byte (first 8 bits which forms byte 0) of the data word. The label is described in paragraph 5.6.5 below.
5.6.3 tions
The data word with label 031 is the only control word used by the TDR-94/94D. Label 031 is the standard ATCRBS control word. Word label 016 has been redefined for addressing the TCAS displays. Word labels 013 and 015 are TCAS related words. Labels 016 and 015 are described here only for informational purposes. The TDR-94/94D will accept word labels 013, 015, and 016
Transponder Control Word Defini-
This paragraph describes the various control words used by the TDR-94/94D mode s transponder. 5.6.3.1 ARINC 429, Label 031, 015, and 016, Control Words In ARINC 429, the label is formed by the 5/5/1993
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maintenance 523-0775657 and them through unchanged to the TCAS computer. The data field, bits 9 through 32, are described as follows:
Label 015: Bit No. 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32
Label 031: Bit No. 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32
Definition SDI Code (see note 1) SDI Code (see note 1) Alt Reporting, On/Off (1=on) Pad Ident, On/Off (1=on) Alt Port Selected, (1=B) Pad Pad Pad Mode a, code D1 Mode a, code D2 Mode a, code D4 Mode a, code C1 Mode a, code C2 Mode a, code C4 Mode a, code B1 Mode a, code B2 Mode a, code B4 Mode a, code A1 Mode a, code A2 Mode a, code A4 SSM (see note 4) SSM (see note 4) Parity
Label 016: Bit No. 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32
5/5/1993
Definition SDI Code (see note 1) SDI Code (see note 1) Altitude limit A 100 Altitude limit A 200 Altitude limit A 400 Altitude limit A 800 Altitude limit A 1600 Altitude limit A 3200 Altitude limit A 6400 Altitude limit B 100 Altitude limit B 200 Altitude limit B 400 Altitude limit B 800 Altitude limit B 1600 Altitude limit B 3200 Altitude limit B 6400 spare spare spare spare spare SSM (see note 4) SSM (see note 4) Parity
Note 1: See paragraph 5.6.4.1 below Note 2: The display control bits control the TCAS display as follows. This information is supplied by a TCAS control and is ed through the transponder unchanged.
Definition SDI Code (see note 1) SDI Code (see note 1) Alt Reporting, On/Off (1=on) SPI (0=ident off) Display control (see note 2) Display control (see note 2) Sens level 0 (see note 3) Sens level 1 (see note 3) Sens level 2 (see note 3) 4096, code D1 4096, code D2 4096, code D4 4096, code C1 4096, code C2 4096, code C4 4096, code B1 4096, code B2 4096, code B4 4096, code A1 4096, code A2 4096, code A4 SSM (see note 4) SSM (see note 4) Parity
BIT 14 13
Definition
0 0 1 1
Primary and traffic display Primary display only TCAS traffic display only No control function possible
0 1 0 1
Note 3: Sensitivity level is TCAS control information that is provided via an uplink message from a groundbased controller. Bit combination definitions are as follows: BIT 17 16 15 0 0 0 0 0 1 0 1 0 0 1 1 1 0 0 1 0 1 1 1 0 1 1 1
Definition SL 0 (Automatic) SL 1 (STBY) SL 2 (TA only) SL 3 SL 4 SL 5 SL 6 SL 7
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maintenance 523-0775657 Note 4: SSM code definitions are as follows: BIT 31 30
Definitions Label 031
Label 016/015/013
0 0 1 1
Normal operation No computed data Functional test Not used
Normal operation No computed data Functional test Failure warning
0 1 0 1
Label 013: Bit No. 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32
The first eight bits form the first byte and contain the word label: Byte 0 is the label byte: Bit: Logic: Hex:
7 0 |
6 0
5 0 1
4 1 |
3 1 |
2 1
1 1 E
0 0 |
Byte 1 is the status byte: Definition SDI Code (see note 1) SDI Code (see note 1) Flight level (0=relative, 1= absolute) Altitude select (see note 2) Altitude select (see note 2) spare spare spare spare defined defined defined defined 0.5, TCAS range 1.0, TCAS range 2.0, TCAS range 4.0, TCAS range 8.0, TCAS range 16.0, TCAS range 32.0, TCAS range 64.0, TCAS range SSM (see note 4 above) S2SM (see note 4 above) Parity
Bit: Def:
7 6 5 4 3 2 1 0 | | | | | | |< --|<--SI(*) | | | | | |<--Test (1= on) | | | | |<--ATC Ident (1=on) | | | |<--Alt reporting (1=on) | | |<--Mode (1 = standby) | |<--Pad |<--Code valid (1 = valid)
* For Source identifier definition, refer to paragraph 5.6.4.2 below. Bytes 2 and 3 convey the ATC code: Byte 2: Bit: Value: Def:
7 6 4 Pd | < ATC
5 4 2 1 | | C codes >
3 2 4 Pd | < ATC
7 6 4 Pd | < ATC
5 4 2 1 | | A codes >
3 2 4 Pd | < ATC
1 0 2 1 | | D codes >
Byte 3:
Note 1: See paragraph 5.6.4.1 below Note 2: TCAS Altitude selects:
Bit: Value: Def:
1 0 2 1 | | B codes >
BIT 13 12
Definition
0 0 1 1
Normal (-A to +A) Above (-A to +B) Below (-B to +A) Unrestricted
Bytes 4 and 5 convey the Gillham code altitude information:
CSDB, Label 1E, Control Word
Bit: Value: Def:
0 1 0 1
5.6.3.2
The TDR-94/94D uses CSDB word label 1E for CSDB control. All CSDB words consist of 6 bytes, with each bytes consisting of 8 bits. These bytes are typically identified as bytes 0 through 5. Byte 0 is the label byte, byte 1 is known as the status byte, and bytes 2 through 5 transmit the object data. The bytes are described as follows:
6/15/1995
Byte 4:
7 6 5 4 4 2 1 Pd | | | < ALT C codes >
3 2 4 Pd | < Alt D
1 0 2 1 | | codes >
7 6 5 4 4 2 1 Pd | | | < ALT A codes >
3 2 4 Pd | < Alt B
1 0 2 1 | | codes >
Byte 5: Bit: Value: Def:
Refer to paragraph 5.7 for additional Gillham altitude code information.
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Bytes 4 and 5 convey barometric altitude:
The TDR-94/94D uses CSDB word label A0 for CSDB altitude data; both pressure and barometric. As in all other CSDB words, word label A0 consists of six 8-bit bytes, identified as bytes 0 through 5. Byte 0 is the label byte; byte 1 is the status byte; bytes 2 and 3 transmit the pressure altitude information; bytes 4 and 5 transmit the barometric altitude information. The detailed structure is as follows:
Byte 4: part 1 of barometric alt data:
7 1 |
6 0
5 1 A
4 0 |
3 0 |
2 0
1 0 0
0 0 |
Byte 1 is the status byte: Bit: Def:
7 6 5 4 3 2 1 0 | | | | | | |<- |<--SI(*) | | | | | |<--Test (1 = on) | | | | |<-- 1 = xside baro | | | |<--Strut sw (1 = on gnd) | | |<-- Rsvd for preselect (**) | |<--Baro alt valid (1 = valid) |<--Pres alt valid (1 = valid)
* For Source identifier definition, refer to paragraph 5.6.4.2 below. ** Bit 5 of byte 1 is bit 1 of a two-bit matrix for a altitude preselect function. Bit 2 is in the same location of data word A1. Bytes 2 and 3 convey pressure altitude: Byte 2: part 1 of pressure alt data: Bit: Bin wt: Alt wt:
7 6 5 4 8 4 2 1 | | | |<16 | | |<32 | |<64 |<128
3 2 1 0 8 4 2 1 | | | |<1 | | |<2 | |<4 |<8
Byte 3: part 2 of pressure alt data: Bit: Bin wt: Alt wt:
6/15/1995
7 8 | | | |<
6 5 4 4 2 1 | | |<4096 | |<8192 |<16384 -32768
3 2 1 0 8 4 2 1 | | | |<-256 | | |<512 | |<1024 |<2048
7 6 5 4 8 4 2 1 | | | |<16 | | |<32 | |<64 |<128
3 2 1 0 8 4 2 1 | | | |<1 | | |<2 | |<4 |<8
Byte 5: part 2 of barometric alt data: Bit: Bin wt: Alt wt:
Byte 0 is the label byte: Bit: Logic: Hex:
Bit: Bin wt: Alt wt:
7 8 | | | |<
6 5 4 4 2 1 | | |<4096 | |<8192 |<16384 -32768
3 2 1 0 8 4 2 1 | | | |<-256 | | |<512 | |<1024 |<2048
The bit pattern for any altitude within the range -8191 to +57343 feet, pressure or barometric, is encoded using two’s complement arithmetic with a 24576 foot offset. Use the following conversion methods as you wish: 1. Select the altitude to be encoded. 2. Subtract 24576 from that quantity. 3. If the result is negative, add 32768. * 4. Convert the result to binary using the altitude bit weights shown above. * If you use a calculator to do the decimal to binary conversion, you may not need to add this quantity. If it uses 2’s complement arithmetic for the conversion, you can ignore the addition. To decode a 16-bit binary number into a decimal quantity: 1. Select the binary quantity. 2. Convert the binary number into decimal using the altitude bit weights shown above. 3. If the MSB (bit 7 of bytes 3/5) is = 1, subtract 8192. If it is = 0, add 24576. ** 4. The result is the equivalent decimal quantity. ** If you use a calculator to do the binary-todecimal conversion, you may not need to subtract the 8192 in step 3. But you must add the 24576. (The 8192 is the difference between the 32768 2’s complement sign factor and the 24576 offset.)
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maintenance 523-0775657 5.6.4
SDI/SI Code Definitions
There are three important points here:
5.6.4.1 ARINC 429, SDI Definition In ARINC 429, bits 8 and 9, of all word labels, form the SDI code. The code definitions depend on the label as follows:
2. Notice also that the most significant bit (MSB) is defined by only two bits. This means that the MSB can have a value no greater than 3 (2 + 1). This also means that the numerically largest octal code possible is 377 which is displayed, bits 0 through 7, as 11111111.
BITS 9 8 0 0 0 1 1 0 1 1
DEFINITION FOR LABELS: 203/204 031/350/371 All-call Not used Side 1 Side 1 Side 2 Side 2 Not used Not used
BITS 9 8 0 0 0 1 1 0 1 1
DEFINITION FOR LABEL: 013 both left and right, RA/TA, bus #1 and #2 left, RA/TA, bus #1 right, RA/TA, bus #2 not defined
3. Notice also that the bit values are reversed from the values in the data fields. In the data fields, the values increase as you move from right to left. Here they values decrease in value, moving from right to left.
5.6.4.2 CSDB, SI Definition In CSDB, bits 0 and 1 of byte 1 form the source identifier and are defined as follows: BITS 1 0 0 0 0 1 1 0 1 1
DEFINITION FOR LABELS: 1E/1F/A0/F3 Not used Side 1 Side 2 Not used
5.6.5
Octal Label Definitions
1. Notice that the MSB is on the right, defined by the lower ordered bits. This is reversed from that of the data field where the MSB is defined by the higher ordered bits.
5.6.5.2 CSDB Hexadecimal Label Definition In CSDB the label of the word is a two digit hexadecimal number and is defined in the first 8-bits, byte 0, of the CSDB transmission. The bits are defined as follows: Label digit:
In ARINC 429, the label is expressed as an octal number. The equivalent in CSDB is expressed as a hexadecimal number.
MSB
Bit: 7 Bit value: 8 Example: Interp:
6 4
LSB 5 2
4 1
0 0 0 1 |------1-------|
3 8
2 4
1 2
0 1
1 1 1 0 |------E-------|
5.6.5.1 ARINC 429, Octal Label Definition Bits 0 through 7 form the octal label and are defined as follows: Label digit:
LSB
Bit: Bit value:
7 1
Example: Interp:
1 0 1 |<--5-->|
6/15/1995
6 2
2 5 4
4 1
3 2
MSB 2 4
1 0 0 |<--1-->|
1 1
0 2
0 0 |-0-|
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This page is intentionally left blank.
6/15/1995
5-154.2
maintenance 523-0775657 5.7 GILLHAM CODE DESCRIPTION with ENCODING AND DECODING INSTRUCTIONS This paragraph contains a description of the Gillham (ARINC 572) altitude encoding scheme. The paragraph also includes instructions for encoding and decoding. This can be helpful if you encounter an altitude discrepancy during a test or fault isolation procedure that is caused by a faulty digitizer or broken wire in the altitude bus.
Table 5-15 shows the encoding matrix for both the 500-foot increments as well as the 100-foot increments. Following the table are the encoding and decoding instructions.
Table 5-15. Gillham Altitude, ARINC 572, Encoding Scheme
|<--- ----D2,D4, A1,A2 0000 0001 0011 0010 0110 0111 0101 0100 1100 1101 1111 1110 1010 1011 1001 1000
-----
-----
-----
-----
-----
A4, B1, B2, B4
----
-----
-----
-----
-----
-----
----
----
--->|
0000
0001
0011
0010
0110
0111
0101
0100
1100
1101
1111
1110
1010
1011
1001
1000
0 31 32 63 64 95 96 127 128 159 160 191 192 223 224 255
1 30 33 62 65 94 97 126 129 158 161 190 193 222 225 254
2 29 34 61 66 93 98 125 130 157 162 189 194 221 226 253
3 28 35 60 67 92 99 124 131 156 163 188 195 220 227 252
4 27 36 59 68 91 100 123 132 155 164 187 196 219 228 251
5 26 37 58 69 90 101 122 133 154 165 186 197 218 229 250
6 25 38 57 70 89 102 121 134 153 166 185 198 217 230 249
7 24 39 56 71 88 103 120 135 152 167 184 199 216 231 248
8 23 40 55 72 87 104 119 136 151 168 183 200 215 232 247
9 22 41 54 73 86 105 118 137 150 169 182 201 214 233 246
10 21 42 53 74 85 106 117 138 149 170 181 202 213 234 245
11 20 43 52 75 84 107 116 139 148 171 180 203 212 235 244
12 19 44 51 76 83 108 115 140 147 171 179 204 211 236 243
13 18 45 50 77 82 109 114 141 146 173 178 205 210 237 242
14 17 46 49 78 81 110 113 142 145 174 177 206 209 238 241
15 16 47 48 79 80 111 112 143 144 175 176 207 208 239 240
256 segments, at 500 -ft intervals, from -1000 ft to 127,000 ft. 100-ft bits C1 __ 0 0 0 1 1
C2 __ 0 1 1 1 0
100-ft value if 500-ft segment is: C4 __ 1 1 0 0 0
odd _______ 7 (+ 200) 6 (+ 100) 5 (00) 4 (- 100) 3 (- 200)
even _______ 8 (- 200) 9 (- 100) 0 (00) 1 (+ 100) 2 (+ 200)
It is important to note that this scheme has no provision for C1, C2, and C4 bit patterns 000, 111, or 101.
5/5/1993
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Gillham Code Decoding Instructions
This paragraph provides a method of translating a Gillham code pattern into altitude.
into the following measured bits row. If any of the bits are missing or not connected (and this is likely for bits D2, and D4.) just enter a 1 for that bit. (A measured 1 means it is not active.)
1. Determine the encoded bits and write them Bit names:
A
___ 1
A ___2
A ___4
B ___1
B ___2
B ___4
C ___1
C ___2
C ___4
D * D * D ___1 ___2 ___4
Measured bits:
___ ___ ___ ___ ___ ___ ___ ___ ___ _1_ ___ ___
Inverted logic:
___ ___ ___ ___ ___ ___ ___ ___ ___ _0_ ___ ___
2. Invert each of the bits and write that pattern into the inverted logic row.
8. Multiply that segment number by 500 and then subtract 1000. The result is the altitude to the nearest 500 feet.
3. From the inverted logic row, determine the encoded bit pattern for bits A4, B1, B2, B4.
9. From the inverted logic row, determine the encoded bit pattern for bits C1, C2 and C4 .
4. Compare that pattern to the listing of patterns on Table 5-15 for A4, B1, B2, B4 and note the column where you found the match.
10. If C1 and C4 are both 0 then you are finished. The result of step 8. is the final result. If C1 and C4 are not both 0 then proceed.
5. From the inverted logic row, determine the encoded bit pattern for bits D2, D4, A1, A2.
11. Find the sequence for C1, C2 and C4 in the lower part of Table 5-15. Note that row.
6. Compare that pattern to the listing of patterns in the left column of Table 5-15 and note the row where you found the match.
12. Depending on whether the segment number from step 7. above was odd or even, add or subtract either 100 or 200 to or from the 500-ft altitude. The result is the altitude to the nearest 100 feet.
7. Read the segment number from the point at which your marked column and row intersect.
Example: Suppose you measure the following logic levels on the test (1 = high or open, and 0 = low) Test Points: Measured: Invert logic:
___ 1
A
A ___2
A ___4
B ___1
B ___2
B ___4
C ___1
C ___2
C ___4
D * ___1
D * ___2
D ___4
1 0
0 1
0 1
0 1
1 0
1 0
1 0
1 0
0 1
1 0
1 0
0 1
Column data: 1100 Row data: 0101 Referring to the matrix in Table 5-15 above, this identifies segment 104. Multiply segment by 500 and subtract 1000: 104 x 500 - 1000 = 51 000. The C1, C2, and C4 bits determine the 100-ft altitude offset from the rounded 500-ft value. Because the identified segment is an even number, use the data under the even column. Comparing the inverted logic bit pattern for 6/15/1995
C1, C2, and C4 (001) to the listing, we find that it corresponds to the first entry. This declares that the hundred foot value is the nearest 800 (or 200 feet less than the rounded 500-ft level). Thus the measured bit pattern yields an altitude of 50 800 feet. * D1 and D2 are not connected on the test . For purposes of this illustration, assume an open to be a logic 1. You will notice in Table 5-15 that D1 is not used, and D2 is not active at altitudes below 60 000 feet.
5-156
maintenance 523-0775657 5.7.2 Gillham Code, Encoding Instructions
b. Read the logic pattern for D2, D4, A1, A2 from the left column of the segment row and enter it in the spaces below.
This paragraph will describe a process to determine the code needed for a particular altitude:
6. If the absolute value of the saved difference from 3. above is less than 50, use the third pattern for C1, C2, and C4 (010). If the value of the saved difference from 3. above is 50 or more, round it to the nearest 100. This must be either 100 or 200 and either more or less than the 500-ft value.
1. Select the desired altitude. 2. Add 1000 to that number. 3. Round that number to the nearest multiple of 500. (Save the difference thus dropped; it will be needed to determine the 100-foot bit pattern in step 6. below.)
7. If the 500-ft segment number is an even number use the even column to determine the 100-ft bit pattern. (This means that the altitude rounded to the nearest 500-ft must be in the form of XX000.)
4. Divide the rounded number by 500. This becomes the 500-ft segment number for the matrix in Table 5-15 above.
8. If the 500-ft segment number is an odd number use the odd column to determine the 100-ft bit pattern. (This means that the altitude rounded to the nearest 500-ft must be in the form of XX500.
5. Locate the segment number in the table and: a. Read the logic pattern for A4, B1, B2, B4 from the top of the column and enter it in the spaces below. Bit pattern entry: Altitude:
A1
A2
A4
B1
B2
B4
C1
C2
C4
D2
D4
_______
___
___
___
___
___
___
___
___
___
___
___
Example: Determine the bit pattern for an altitude of 11 800 feet.
b. Read the D2, D4, A1, A2 bit pattern from the left column of the same row. 0001. Then enter each bit into the appropriate space below. 5. The saved value from step 3. is -200. 6. The segment number 26 is an even number, therefore the C1, C2, C4 bit pattern is read from the top entry: 001. You can, of course, also read this on the basis of the hundreth’s digit value which in this case is an 8.
1. Add 1000: 12 800. 2. Round to nearest multiple of 500: 13 000, and save difference: -200 ( less). 3. Divide 13 000 by 500: 26. 4. Locate segment number 26 on the matrix above and: a. Read the A4, B1, B2, B4 bit pattern from the top of the column: 0111. Then enter each bit into the appropriate space below. Bit pattern entry:
6/15/1995
Altitude:
A1
A2
A4
B1
B2
B4
C1
C2
C4
D2
D4
_11 800__
_0_
_1_
_0_
_1_
_1_
_1_
_0_
_0_
_1_
_0_
_0_
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5.8 ACCEPTANCE TEST, TEST ASSEMBLY INSTRUCTIONS
version. Figure 5-4 is a schematic diagram of the abbreviated test .
5.8.1
Figure 5-5 is a schematic diagram for the enhanced version of test . Table 5-16 is a list of the material required for the enhanced version. Table 5-17 is a similar listing for the abbreviated version. Table 5-18 is a listing of the manufacturers and suppliers for the various items needed to assemble the s. Equivalent parts may be obtained from other sources. Paragraph 5.8.2 and figures 5-5 through 5-8 describe the control interconnect cables. You may select one or more of these cables, depending on the type of control you plan to use. These cables are required for both test versions. However, you will notice that the cable for the CTL-92/92A can be different, depending on the test version you intend to use. The abbreviated version has no provision for Gillham code switching and a number of other functions. Thus, these connections are not required in the cable if you are using that version test .
GENERAL
This paragraph provides the instructions and material listing necessary for assembly of the ATP test s listed in table 5-1. Several test equipment suppliers offer a product item(s) equivalent to these specifications. If you wish, you should feel free to purchase such an item. Otherwise, it can be locally fabricated using the data supplied in this paragraph. If you fabricated your fixture according to instructions supplied an earlier edition of this manual, you will find modification instructions in paragraph 5.8.3 below. This edition, and all subsequent editions that introduce changes to the Acceptance Test Test will give modification instructions in paragraph 5.8.3. Figure 5-2 is the test setup diagram showing how the various items are interconnected. Figure 5-3 is a suggested layout for the enhanced
Table 5-16. Enhanced Version of Test , Parts List
ITEM
REF DES
QTY
MANUFACTURER NAME
Toggle switch, SP, on/off
S1, S5, S7, S8, S10, S11, S17S57, S59
48
Toggle switch, SPDT, on/on
S9
1
Toggle switch, DPDT, on/on
S2, S3
Momentary switch, SP, pushon
S4, S6
5/5/1993
C & K Components, Inc
COLLINS PART NUMBER PN
7107SYZWQE
266-5321-150
2
7201SYZQE
266-5321-200
2
8121SHZGE
266-5404-010
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Table 5-16. Enhanced Version of Test , Parts List (cont’d)
ITEM
REF DES
QTY
MANUFACTURER NAME
PN
Wafer, switch, 2pole, 4-psn
S13
1
Wafer switch, 5pole, 2 -psn
S58
1
44A3004202NF
Wafer switch, 4pole, 4 -psn
S12
1
44A3002204NF
Wafer switch, 6pole, 4 -psn
S16
1
44A3006204NF
Lamp holder
6
Grayhill Inc.
COLLINS PART NUMBER
Chicago Miniature Lamp, Inc.
44A3001204NF
Not available from Collins
LH73/1
included in 2622828-0X0
Lamp len, red
LDS 2-3
2
LC12YN2
262-2828-010
Lamp lens, yellow
LDS 1,4-6
4
LC12RN2
262-2828-030
Lamp, 28 V
DS1-6
6
GE Co.
385
262-2171-010
Fuse holder
XF1
1
Bussman Div.
HKP-H, or FHN-20G
Not available from Collins
Fuse, 5A SB
F1
1
Banana jack, blk
TP1,3,5
2
Banana jack, yel
TP2,4,6
3
Phono plug, 1/4"
J2,3,4,5,6,7,8,9
8
Phono jack
To mate with: J2,3,4,5,6,7,8,9 See figure 5-9
AR
BNC to TNC adapter
Needed to adapt ATC601 rf cable to antenna connectors
2
RF load (also shown on table 5-1
Needed to terminate unused rf antenna connection.
1
50-pin D-submin, conn (socket) 50-pin D-submin, conn (plug)
5/5/1993
1
See figures 56, 5-7, 5-8
AR
F02G250V5AS E.F.Johnson Co.
360-0241-000 360-0245-000
Switchcraft Inc.
M/A-COM Omni Spectra, Inc.
M641/12-1
358-0014-000
PJ-055B
Not available from Collins
3182-2320-00
Not available from Collins
3101-6100-00
ITT Cannon
DDMF-50S-A176
371-0182-000
DDM50P-C37-A176
371-0118-000
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Table 5-16. Enhanced Version of Test , Parts List (cont’d)
ITEM
REF DES
QTY
MANUFACTURER NAME
COLLINS PART NUMBER PN
TDR-94D installation kit
1
Collins General Aviation Division
628-8660-001
MMT-150 Mounting Tray
1
622-9672-003
CTL-92/92A mating connector
See figure 5-6
1
359-0305-590, or 371-6110-000
RTU-870A/T mating connector
See figure 5-7
1
359-0601-010
TTC-920G mating connectors
See figure 5-8
1 of each
Res, film, 100kΩ, ±1%, 1/4W
R1-11
11
Res, film, 825Ω, ±1%, 1/2W
R12-22
11
Grommet, 1-in, id
MS
J1: MD24266R76B24S7 J2: MS24266R16B24SB
J1: 359-4068-030 J2: 359-4118-240
RN65D1003F
705-7192-000
RN65D8250F
705-7092-000
1
Atlantic India Rubber Co.
2277
201-0012-000
021-0347-050
Chassis, 8 x 12-in , box
Or use a 19 rack mounting
1
Bud Industries, Inc.
AC 424
Switch knobs
For wafer switches
5
any with 1/4-inch shaft dia and setscrew locking
N/A
Data bus reader cables
See figure 5-9
Chassis, bottom
Optional
5/5/1993
AR
1
BPA 1519
Not available from Collins
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Table 5-17. Abbreviated Version of Test , Parts List
ITEM
REF DES
QTY
MANUFACTURER NAME
BNC to TNC adapter
Needed to adapt ATC601 rf cable to antenna connectors
2
RF load (also shown on table 5-1
Needed to terminate unused rf antenna connection.
1
50-pin D-submin, conn (socket) 50-pin D-submin, conn (plug)
1
See figures 56, 5-7, 5-8
M/A-COM Omni Spectra, Inc.
COLLINS PART NUMBER PN
3182-2320-00
Not available from Collins
3101-6100-00
ITT Cannon
AR
DDMF-50S-A176
371-0182-000
DDM50P-C37-A176
371-0118-000
TDR-94D installation kit
1
Collins General Aviation Division
628-8660-001
MMT-150 Mounting Tray
1
622-9672-003
CTL-92/92A mating connector
See figure 5-6
1
359-0305-590, or 371-6110-000
RTU-870A/T mating connector
See figure 5-7
1
359-0601-010
TTC-920G mating connectors
See figure 5-8
1 of each
Chassis
Note: The size of chassis for the abbreviated version of the test is optional. The primary limitation is that it must be large enough to accomodate the connectors and other parts. Use of a 50pin D-type connector can also be seen as optional. If you plan to use only one type of control, such as the CTL-92/92A, you may want to connect the cable directly to the test as a pendant cable.
Cable grommet, 1/2-in. id
For pendant cable exit if used.
5/5/1993
1
J1: MD24266R76B24S7 J2: MS24266R16B24SB
Atlantic India
2283
J1: 359-4068-030 J2: 359-4118-240
201-0002-006
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Table 5-14. Equipment and Component Manufacturers and Suppliers
SUPPLIER
ADDRESS
PRODUCT
Collins General Aviation Division
400 Collins Road Cedar Rapids IA 52498
TDR-94D Installation kit, MMT-150 Mounting Tray, CTL-92/92A mating connector, RTU-870A/T mating connector, TTC-920G mating connector
IFR Systems, Inc.
10200, West York Street Wichita, KS 67215
ATC-601 Ramp Test Set
Atlantic Instruments, Inc.
P.O. Box 021466 Melbourne, FL 32902
DataTrac 200/400/400H Databus Analyzers
JcAIR
400 Industrial Parkway, Industrial Airport, KS 66031
Test and 429E ARINC 429 TX/RX Databus Analyzer
Avionics Specialist, Inc.
3833 Premier Ave. Memphis, TN 38118
Test
M/A-COM Omni Spctra, Inc.
21 Continental Blvd Merrimac, NH 03054-9979
Rf load and BNC-to-TNC adapter
C & K Components, Inc.
15-T Riverdale Ave. Newton, lMA 02158 (617) 964-6400
Toggle switches
Grayhill Inc.
561 Hillgrove, P.O.Box 10373 LaGrange IL 60525 (708) 354-1040
Wafer switches
Chicago Miniature Lamp, Inc.
1080-T Johnson Dr. Buffalo Grove, IL 60089 (908) 459-3400
Indicator lamp holders and lens
Bussman Div., Cooper Industries
P.O. Box 14460 St. Louis, MO 63178 (314) 394-2877
Fuses and fuse holder
GE Co., Miniature Lamp Dept.
Nela Park Cleveland OH 44112 (216) 266-2121
Light bulb
E.F. Johnson Co.
Minneapolis, MN 55459-0089
Banana jacks
ITT Cannon, Corp.
1851-T E. Deer Ave. Santa Ana, CA 92705 (714) 557-4700
Connectors
Bud Industries, Inc.
P.O. Box 431, 4605 E. 355th St. Willoughby, OH 44094 (216) 946-3200
Chassis
Atlantic India Rubber Co.
317 W. Doublas St. Goshen, IN 46256
Rubber grommet
Switchcraft Inc.
5555-T N. Elston Ave. Chicago, IL 60630 (312) 792-2700
Phono plug and jack
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Acceptance Test, Test Layout Diagram Figure 5-3
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Acceptance Test, Abbreviated Test Schematic Diagram Figure 5-4
6/15/1995
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Acceptance Test, Enhanced Test Schematic Diagram Figure 5-5 (Sheet 1 of 3)
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Acceptance Test, Enhanced Test Schematic Diagram Figure 5-5 (Sheet 2)
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Acceptance Test, Enhanced Test Schematic Diagram Figure 5-5 (Sheet 3)
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Test Mating Connector, D-submin, 50-pin, plug DDM50P-C37-A176, N: 371-0118-000
CTL-92/92A Control, Mating Connector P1 MS3126 E20-41SY, N 359-0305-590, or MS 3116E20,41SY, N: 371-6110-000
Signal Name/Description
To Pin No.
From Pin No.
Wire Size or Type
28 V dc, primary power no. 1 (+)
1
G
22 AWG
28 V dc, primary power no. 2 (+)
18
t
22 AWG
Primary power, ground (-)
17
s
22 AWG
Primary power, ground (-)
50
P
22 AWG
CTL data out, 1B
8
S
26 AWG, STP
CTL data out, 1A
41
R
26 AWG, STP
CTL data in, 1B
31
U
26 AWG, STP
CTL data in, 1A
10
V
26 AWG, STP
Ident input
4
b
26 AWG
Self-test (discrete input/output)
6
E
26 AWG (this wire was not included in the original version of this cable)
The remaining connections are not required when using the Abbreviated Version of Test No. 1 transponder in stby
20
W
26 AWG (this wire was not included in the original version of this cable)
No. 2 transponder in stby
10
X
26 AWG
No. 1 transponder on/off
11
B
26 AWG
No. 2 transponder on/off
27
C
26 AWG
No. 1 sw 28 V dc out
28
k
26 AWG
No. 2 sw 28 V dc out
43
j
26 AWG
Acceptance Test, Test CTL-92/92A Control Interconnect Cable Assembly Diagram and Wire List Figure 5-6 (Sheet 1 of 2)
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maintenance 523-0775657 Test Mating Connector, D-submin, 50-pin, plug DDM50P-C37-A176, N: 371-0118-000
CTL-92/92A Control, Mating Connector P1 MS3126 E20-41SY, N 359-0305-590, or MS 3116E20,41SY, N: 371-6110-000
Signal Name/Description
To Pin No.
From Pin No.
Wire Size or Type
Alt code, A1 (input)
12
c
26 AWG
Alt code, A2 (input)
13
e
26 AWG
Alt code, A4 (input)
14
d
26 AWG
Alt code, B1 (input)
28
i
26 AWG
Alt code, B2 (input)
29
h
26 AWG
Alt code, B4 (input)
30
f
26 AWG
Alt code, C1 (input)
45
J
26 AWG
Alt code, C2 (input)
46
H
26 AWG
Alt code, C4 (input)
47
F
26 AWG
Alt code, D4 (input)
48
p
26 AWG
Alt code, common
5
g
26 AWG
Acceptance Test, Test CTL-92/92A Control Interconnect Cable Assembly Diagram and Wire List Figure 5-6 (Sheet 2)
Acceptance Test, Test RTU-870A Control Interconnect Cable Assembly Diagram and Wire List Figure 5-7 (Sheet 1 of 2)
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Test Mating Connector, D-submin, 50-pin, plug DDM50P-C37-A176, N: 371-0118-000
RTU-870A/T Radio Tuning Unit, Mating Connector P1 MS27473T20F-2S, N 359-0601-010, Strain relief: MS27506F20-2, N: 359-0637-070
Signal Name/Description
To Pin No.
From Pin No.
Wire Size or Type
28 V dc, primary power no. 1 (+)
1
1
22 AWG
28 V dc, primary power no. 2 (+)
18
7
22 AWG
Primary power, ground (-)
17
3
22 AWG
Primary power, ground (-)
50
3
22 AWG
RTU data out, 1B (ARINC 429 data from RTU to XPDR)
26
45
26 AWG, STP
RTU data out, 1A (ARINC 429 data from RTU to XPDR)
25
44
26 AWG, STP
RTU data in, 1B (ARINC 429 data input to RTU from XPDR)
31
29
26 AWG, STP
RTU data in, 1A (ARINC 429 data input to RTU from XPDR)
10
28
26 AWG, STP
Ident input
4
11
26 AWG
Acceptance Test, Test RTU-870A Control Interconnect Cable Assembly Diagram and Wire List Figure 5-7 (Sheet 2)
Acceptance Test, Test TTC-920G Control Interconnect Cable Assembly Diagram and Wire List Figure 5-8 (Sheet 1 of 2)
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Test Mating Connector, D-submin, 50-pin, plug DDM50P-C37-A176, N: 371-0118-000
TTC-920G Transponder/TCAS Control, Mating Connector1 P1: MD24266R76B24S7, N: 359-4068-030 P2: MS24266R16B24S8, N: 359-4095-700
Signal Name/Description
From Pin No.
To Pin No.
115 V ac, 400 Hz, primary power1 (high) (external source)
Source High
J1-3 J2-3*
22 AWG
115 V ac, 400 Hz, primary power (low) (external source)
Source Low
J1-4 J2-4*
22 AWG
Primary power, ground (-)
17
J1-6 J2-6*
22 AWG
Air ground (input) (strap for normal operation)
17
J1-11* J2-11*
26 AWG
Primary power, ground (-)
50
J1-8 J2-8*
22 AWG
ARINC 429, data out, 1B (TTC-920G output to XPDR)
25
J1-22
26 AWG, STP
ARINC 429, data out, 1A (TTC-920G output to XPDR)
26
J1-23
26 AWG, STP
Air ground (input)
17*
J1-11* J2-11*
26 AWG
Monitor lamp power (+28 V dc)
1*
J1-18*
26 AWG
Monitor lamp power (+28 V dc)
1*
J1-18*
26 AWG
Lighting power (+28 V dc)
18*
J2-1*
26 AWG
Standby/on
20*
J1-7
26 AWG
Fault Monitor (XPDR output)
12*
J1-20* J2-20*
26 AWG
Wire Size or Type
* These wires were not shown in the original cable wiring list.
Acceptance Test, Test TTC-920G Control Interconnect Cable Assembly Diagram and Wire List Figure 5-8 (Sheet 2)
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maintenance 523-0775657 5.8.2Miscellaneous Cables Figure 5-9 shows the addtional cables needed for the Acceptance Test. The tip jack cables shown in the upper section of sheet 1 are needed for dc power input to the DataTrac 200 or 400. If you operate from ac power or battery power only you do not need these. The DataTrac 400H and JcAIR 429E, as well as some DataTrac 200, have their own ac-todc power converter/battery recharge facility.
In the lower section of sheet 1, the BNC-tosingle phono jack cables are needed for the RX function of the DataTrac 400, and 400H. For DataTrac 400 operation you can substitute two of the lower cable for the upper and then use a separate TX port. For the DataTrac 400H you must use the upper cable because it has only one TX port and therefore you must use that port for both the control and altitude functions. Sheet 2 of this figure shows the cables needed for the DataTrac 200 and the JcAIR 429E, respectively.
Acceptance Test, Bus Reader to Test Interconnecting Cables Figure 5-9 (sheet 1 of 2)
In assembling the BNC-to-phono plug cables, be sure to connect the bus A wires between the BNC center and the proper phono plug . In assembling the phono plug-tophono plug cables, be sure to connect similar s; i.e., do not reverse the A and B
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lines. In assembling the phono plug-to-tip jack cables, be sure the A wire is connected to the jack identified as HI. In all cases, do not use the the phono plug common as a signal carrying .
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Acceptance Test, Bus Reader to Test Interconnect Cables Figure 5-9 (sheet 2)
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maintenance 523-0775657 5.8.1Acceptance Test Modification Record. 5.8.1.1Modification 1. At modification 1 the following changes are introduced. 1. An additional SPDT switch, S56, is added with connection to UUT pin P1-28. This function is labeled AUTO ALT. When this function is enabled (EN, ground applied to P1-28), the unit automatically switches to the non-selected altitude port for valid reporting altitude data if the altitude data at the selected source is interrupted or invalid. 2. Existing switch, S17, with connection to UUT pin P2-14 is redefined. This switch previously functioned as the ALT INPUT PORT SEL and switched the altitude input to either port A or port B. In -003 units, altitude data is required at both ports simultaneously therefore this switching function is changed (see 3. below). The new function, SOURCE SELECT, CTL/SEL, functions with the existing altitude source select pins P2-41 and P2-42 as follows: SS* AS0 AS1 1 1 1 1
0 0 1 1
Altitude Type Selected
0 1 0 1
ARINC 429 on ARINC ports A and B CSDB on CSDB ports A and B ARINC 575 on ARINC ports A and B ARINC 572 (Gillham) on the Gillham parallel port 0 0 0 Port A altitude on the selected control bus (either ARINC 429 or CSDB) and port B altitude type ARINC 429 on ARINC port B. 0 0 1 Port A altitude on the selected control bus (either ARINC 429 or CSBB) and port B altitude type CSDB on CSDB port B. 0 1 0 Port A altitude on the selected control bus (either ARINC 429 or CSDB) and port B altitude type ARINC 575 on ARINC port B. 0 1 1 Port A altitude on the selected control bus (either ARINC 429 or CSDB) and port B altitude type Gillham on the Gillham parallel port. * CTL = active low (ground on P2-48) and SEL = open.
S16 also controls the select discretes P2-41 (AS0) and P2-42 (AS1) (see 2. above). Data supplied on the ALTERNATE DIGITAL ALTITUDE SOURCE is switched to port B; either ARINC or CSDB. 4. Existing altitude input jack J4 is relabeled as PRIMARY DIGITAL ALTITUDE SOURCE. Switch S16 controls the connection of this input to the appropriate UUT port A (either ARINC or CSDB). 5. Switch S57, REPORTING ALT SEL, PA/PB, is added. This switch controls the discrete P2-48 which selects the altitude port used for altitude reporting (Modes C and S). When P2-48 is grounded, port B data is used for altitude reporting. When open port A data is used. 6. TCAS IN and TCAS OUT input jacks, J6 and J7, are added to allow monitoring of the TCAS data. 7. DATALINK IN and DATALINK OUT jacks, J8 and J9, are added to allow airborne datalink bus monitoring. s should see this addition as optional at this time because the airborne datalink function has not been industry defined and therefore is not fully implemented. It is presented here primarily so that builders of this test can allow for the eventual addition of this function if and when it is required. Part of this change also includes the addition of switch S58. This switch supplies a ground to P2-60 to enable/select the airborne datalink function. 8. That portion of S12 which supplies the ground to pins P2-56, -57, and -58 has been changed slightly. The common was connected to ground. It should instead be connected to P2-52 which is available at switch S16. 9. The common for the Gillham code switches should be connected to P1-12. 10. The XFEED IN and OUT lamps, DS3 and DS4, and switch S3 position labeling was reversed on the 6 January 1992 issue of the test schematic diagram. No wiring changes are needed. 11. Check the layout, figure 5-3 carefully. You will find a few minor label changes.
3. ALTERNATE DIGITAL ALTITUDE SOURCE input jack J5 is added and existing switch S16 is expanded to allow two altitude sources to be connected simultaneously. S16 allows selection of the appropriate input port depending on the type of data being supplied. 5/5/1993
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maintenance 523-0775657 5.9 FLIGHTLINE TEST, TEST ASSEMBLY INSTRUCTIONS 5.9.1
Introduction
This paragraph provides the instructions and material listing necessary to assemble the Flightline Test shown in figure 5-10. A number of test equipment suppliers may offer a product item equivalent these specifications. If so, you should feel free to purchase such an item. Otherwise, it can be locally fabricated using the data in this paragraph. 5.9.2 Flightline Test Assembly and Use This test allows access to all input and output signals to and from the applicable control; CTL-92 ATC Control, CTL-92A ATC Control, CTL-92T ATC and TCAS Control, TTC-920G Transponder-TCAS Control, RTU870A Radio Tuning Unit, and RTU-870T Radio Tuning Unit (TCAS). Using this test on the flightline, with a dvm and a bus reader, can help to isolate a problem to either the control or the transponder unit and thus increase the probability of correctly removing the faulty unit in a multi-unit system. It is intended that a ramp tester be used for ATC ground station simulation. The test consists of a with several test points for individual signal testing and phono jacks and switching for data bus monitoring and data word injection. When using the , you will select the proper interconnecting cables and test overlay, depending on the control present in the installation. The respective overlay reflects the test point and other i/o signal identification peculiar to that control. The numbers or letters under each test point are the connector pin numbers of the ATC control involved. Figure 5-10 is the test setup diagram showing the test connected between the
5/5/1993
airplane harness control head mating connector and the control head. In the case of the CTL-92T, you should be aware that the ATC control data originates in the CTL92/92A as CSDB data. This is supplied to the CTL-92T where it is converted to ARINC 429 data, TCAS data is added, and the composite data is then supplied to the transponder and subsequently to the TCAS. Therefore, the communication between the CTL-92T and the CTL-92/92A is in CSDB, while the communication between the CTL92T and the transponder/TCAS is in ARINC 429. Figure 5-11 is the suggested layout of the components; banana jacks, switches, indicator lamps, etc. If you decide to fabricate your own and wish to retain the overall versatility, be aware that the overlays are intended to be selectable. The design allows the overlay to rest on top of the and therefore must fit the component placement rather closely. Figure 13 through 19 is a series of diagrams showing the various overlays; each applicable to a given control type. With suitable size adjustment, figure 5-11 can be used as a template. The overlays must (then) also be size adjusted. Four D-type connectors are located on the edge of the ; two on each side. These connectors mate with the cable connectors. The 25-pin connectors carry only the digital data lines using shielded wiring while the 50pin connectors carry all other input/output functions. You may choose to use only a single connector to carry all i/o. Figure 5-12 is the schematic diagram of the test . Use this diagram as the guide for wiring the . Table 5-19 is a list of the parts needed to assemble the test . See paragraph 5.8 for a listing of suppliers. Figures 5-20 through 5-25 show the cables and wiring. Select the cables needed depending on which of the various controls; CTL-92, CTL-92A, CTL-92T Controls, RTU870A, or RTU-870T Radio Tuning Units, TTC-920G Transponder/TCAS Control, or Gables 429 control.
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Flightline Test Setup Diagram Figure 5-10
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Flightline Test , Layout Diagram Figure 5-11
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Flightline Test , Schematic Diagram Figure 5-12 (Sheet 1 of 5)
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Flightline Test , Schematic Diagram Figure 5-12 (Sheet 2)
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Flightline Test , Schematic Diagram Figure 5-12 (Sheet 3)
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Flightline Test , Schematic Diagram Figure 5-12 (Sheet 4)
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Flightline Test , Schematic Diagram Figure 5-12 (Sheet 5)
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maintenance 523-0775657 Table 5-19. Flightline Test Parts List
ITEM
REF DES
QTY
MANUFACTURER NAME
COLLINS PART NUMBER PN
Lamp Holder
DS1,2,5,6,
2
Chicago Miniature Lamp, Inc.
LH73/1
included in 262-28280X0 N
Lamp lens, red
LDS5,6
2
GE Co.
LC12RN2
262-2828-030
Lamp lens, yellow
LDS1,2
2
LC12YN2
Lamp, 28 V
DS1-2
2
385
Lamp, assy, 115 V
DS3-4
2
LeeCraft, SnapLite
Toggle switch DPDT, on/on
S3-S10
8
C&K Components, Inc.
Momentary switch, SP, Pushon
S1,S2
2
Stereo Phono jack, 1/4-inch
J3-J10
8
Banana jack, 1/4"
TP1-45
50-pin D-submin, conn (socket) 25-pin D-submin, conn (socket)
262-2852-050
7101SYZQE
266-5321-150
8121SHZGE
266-5404-010
Switchcraft Inc.
PJ-055B
Not available from Collins
45
E.F. Johnson Co.
blk: 108-0903-001 yel: 108-0907-001 (other colors are optional)
blk: 360-0241-000 yel: 358-0245-000
J1A, J2A
2
ITT Cannon
DDMF-50S-A176
371-0182-000
J1B, J2B
2
DDMF-25S-A176
371-0166-000
AC 424
021-0347-050
BPA-1519
Not available from Collins
3182-2320-00
Not available from Collins
Chassis
1
Chassis, bottom
1
BNC to TNC adapter
262-2171-010
Needed to adapt ATC601 rf cable to antenna cable connector for directionconnection method only.
1
Bud Industries, Inc.
M/A-COM Omni Spectra, Inc.
Control head cables
Locally fabricated
See figures 5-19 through 5-24
Bus reader cables
Locally fabricated
See figure 5-9
Tip jack test leads
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As required for use with dvm
Not available from Collins
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Flightline Test , Overlay for CTL-92/92A Figure 5-13
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Flightline Test , Overlay for CTL-92T Figure 5-14
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Flightline Test , Overlay for RTU-870A/T Testing Figure 5-15
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Flightline Test , Overlay for TTC-920G Testing Figure 5-16
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Cable B: Connector information: J1: KPT2E20-41PYDV, N: 371-8625-440 P1A: DD 50P C37, N 371-0118-000; Hood: N 371-0187-000 P1B: M243083-3, N 371-0170-000 Hood: N 371-0815-000
Signal name / description
From J1
Cable A: Connector information: P1: MS3126E20-41SY, N 359-0305-590, or MS3116E20,41SY, N 371-6110-000 P2A: DD 50P C37, N 371-0118-000; Hood: N 371-0187-000 P2B: M243083-3, N 371-0170-000 Hood: N 371-0815-000 To P1-A
To P1-B
From P2-A
From P2-B
To P1
Wire size/type (both cables)
Data bus 1A (from XPDR)
V
1
1
V
Shielded, twisted pair
Data bus 1B (from XPDR)
U
14
14
U
Shielded, twisted pair
Shield for U/V
T
25
25
T
Shield
Data bus 2A (from XPDR)
a
2
2
a
Shielded, twisted pair
Data bus 2B (from XPDR)
Z
15
15
Z
Shielded, twisted pair
Shield for a/Z
Y
12
12
Y
Shield
Data bus 1A (to XPDR)
S
3
3
S
Shielded, twisted pair
Data bus 1B (to XPDR)
R
16
16
R
Shielded, twisted pair
Shield for S/R
P
24
24
P
Shield
Data bus 2A (to XPDR)
N
4
4
N
Shielded, twisted pair
Data bus 2B (to XPDR)
M
17
17
M
Shielded, twisted pair
Shield for N/M
L
11
11
L
Shield
28 V dc pwr no. 1 (+)
t
1
1
t
22 AWG
28 V dc pwr no. 2 (+)
G
3
3
G
22 AWG
Dc pwr gnd
s
50
50
s
22 AWG
Dc pwr gnd
s
17
17
s
22 AWG
Chassis gnd
D
33
33
D
22 AWG
5 V lighting, hi
A
7
7
A
26 AWG
28 V lighting, hi
r
40
40
r
26 AWG
Lighting common
q
39
39
q
26 AWG
CTL-92/92A Control, Flightline Test Cables, Assembly Diagram and Wire List Figure 5-19 (sheet 1 of 2)
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CTL-92/92A Cable B (cont’d)
CTL-92/92A Cable A (cont’d)
Signal name / description
From J1
To P1-A
Dimming bus
n
6
Self-test discrete, input/output
E
Ident discrete input
To P1-B
From P2-A
From P2-B
To P1
Wire size/type
6
n
26 AWG
38
38
E
26 AWG
b
5
5
b
26 AWG
Remote tuning select, discrete input
K
21
21
K
26 AWG
No. 1 XPDR in stby, discrete output
W
42
42
W
26 AWG
No. 2 XPDR in stby, discrete output
X
10
10
X
26 AWG
28 V dc, sw output, no. 1
k
28
28
k
26 AWG
28 V dc, sw output, no. 2
j
43
43
j
26 AWG
Dual select (CTL -002 only)
m
8
8
m
26 AWG
No. 1 XPDR off, discrete output
B
11
11
B
26 AWG
No. 2 XPDR off, discrete output
C
27
27
C
26 AWG
Alt code A1
c
29
29
c
26 AWG
Alt code A2
e
30
30
e
26 AWG
Alt code A4
d
45
45
d
26 AWG
Alt code B1
i
46
46
i
26 AWG
Alt code B2
h
14
14
h
26 AWG
Alt code B4
f
15
15
f
26 AWG
Alt code C1
J
31
31
H
26 AWG
Alt code C2
H
32
32
H
26 AWG
Alt code C4
F
47
47
F
26 AWG
Alt code D4
p
4
4
p
26 AWG
Alt code common
g
37
37
g
26 AWG
CTL-92/92A Control, Flightline Test Cables, Assembly Diagram and Wire List Figure 5-19 (sheet 2)
5/5/1993
5-189
maintenance 523-0775657
Cable B: Connector information: J1: 27508E20B2PA, N 859-0004-010 P1A: DD 50P C37, N 371-0118-000; Hood: N 371-0187-000 P1B: M243083-3, N 371-0170-000 Hood: N 371-0815-000
Signal name / description
Cable A: Connector information: P1: KJ6F20BSA, N: 350-0601-020 Strain relief: MS27506F20-2, N 359-0637-070 P2A: DD 50P C37, N 371-0118-000; Hood: N 371-0187-000 P2B: M243083-3, N 371-0170-000 Hood: N 371-0815-000
From J1
To P1-A
To P1-B
From P2-A
From P2-B
To P1
Wire size/type (both cables)
CSDB data in, 1A (from CTL)
23
1
1
23
Shielded twisted pair
CSDB data in, 1B (from CTL)
22
14
14
22
Shielded twisted pair
25
25
Shield for 23/22
Shield for 23/22
ARINC 429 in, 1A (from ARINC CTL)
15
2
2
15
Shielded twisted pair
ARINC 429 in, 1B (from ARINC CTL)
14
15
15
14
Shielded twisted pair
12
12
Shield for 15/14
Shield for 15/14
CSDB data out, 1A (to CTL)
16
3
3
16
Shielded twisted pair
CSDB data out, 1B (to CTL)
17
16
16
17
Shielded twisted pair
24
24
Shield for 16/17
Shield for 16/17
ARINC 429 out, 1A (to ARINC CTL)
8
4
4
8
Shielded twisted pair
ARINC 429 out, 1B (to ARINC CTL)
9
17
17
9
Shielded twisted pair
11
11
Shield for 8/9
Shield for 8/9
ARINC 429 in, 1A (from XPDR)
11
5
5
11
Shielded twisted pair
ARINC 429 in, 1B (from XPDR)
10
18
18
10
Shielded twisted pair
23
23
Shield for 11/10
Shield for 11/10
ARINC 429 in, 2A (from XPDR)
13
6
6
13
Shielded twisted pair
ARINC 429 in, 2B (from XPDR)
12
19
19
12
Shielded twisted pair
10
10
Shield for 13/12
Shield for 13/12
CTL-92T Control, Flightline Test Cables, Assembly Diagram and Wire List Figure 5-20 (sheet 1 of 3)
5/5/1993
5-190
maintenance 523-0775657
CTL-92T Cable B (cont’d) Signal name / description
From J1
CTL-92T Cable A (cont’d) To P1-A
To P1-B
From P2-A
From P2-B
To P1
Wire size/type
ARINC 429 out, 1A (to XPDR)
5
7
7
5
Shielded twisted pair
ARINC 429 out, 1B (to XPDR)
4
20
20
4
Shielded twisted pair
22
22
Shield for 5/4
Shield for 5/4
ARINC 429 out, 2A (to XPDR)
6
8
8
13
Shielded twisted pair
ARINC 429 out, 2B (to XPDR)
7
21
21
12
Shielded twisted pair
9
9
Shield for 6/7
Shield for 6/7
28 V dc pwr input no. 1 (+)
1
1
1
1
22 AWG
28 V dc pwr input no. 1 (+)
2
2
2
2
22 AWG
28 V dc pwr input no. 2 (+)
3
19
19
3
22 AWG
28 V dc pwr input no. 2 (+)
28
3
3
28
22 AWG
Pwr gnd
59
50
50
59
22 AWG
Pwr gnd
60
20
20
60
22 AWG
Pwr gnd
32
17
17
32
22 AWG
Self-test input
46
38
38
46
26 AWG
Ident input
21
5
5
21
26 AWG
28 V lighting input, hi
48
40
40
48
26 AWG
5 V lighting input, hi
50
7
7
50
26 AWG
Lighting common
62
39
39
62
26 AWG
Strap no. 1
53
8
8
53
26 AWG
Strap no. 2
49
21
21
49
26 AWG
Strap no. 3
52
9
9
52
26 AWG
Strap no. 4
51
22
22
51
26 AWG
Strap no. 5
47
23
23
47
26 AWG
Strap no. 6
24
24
24
24
26 AWG
Strap common
27
41
41
27
26 AWG
ATC no. 1 select, input
19
42
42
19
26 AWG
ATC no. 2 select, input
18
10
10
18
26 AWG
28 V switched output
25
11
11
25
26 AWG
CTL-92T Control, Flightline Test Cables, Assembly Diagram and Wire List Figure 5-20 (sheet 2)
5/5/1993
5-191
maintenance 523-0775657
CTL-92T Cable B (cont’d) Signal name / description
CTL-92T Cable A (cont’d)
From J1
To P1-A
Reply lamp output (+)
33
28
Reply lamp output (-)
41
Altitude reporting input
To P1-B
From P2-A
From P2-B
To P1
Wire size/type
28
33
26 AWG
43
43
41
26 AWG
20
44
44
20
26 AWG
ATC code A1
44
29
29
44
26 AWG
ATC code A2
26
30
30
26
26 AWG
ATC code A4
45
45
45
45
26 AWG
ATC code B1
56
46
46
56
26 AWG
ATC code B2
55
14
14
55
26 AWG
ATC code B4
57
15
15
57
26 AWG
ATC code C1
39
31
31
39
26 AWG
ATC code C2
42
32
32
42
26 AWG
ATC code C4
54
47
47
54
26 AWG
ATC code D1
61
48
48
61
26 AWG
ATC code D2
37
49
49
37
26 AWG
ATC code D4
63
4
4
63
26 AWG
ATC code common
64
37
37
64
26 AWG
CTL-92T Control, Flightline Test Cables, Assembly Diagram and Wire List Figure 5-20 (sheet 3)
5/5/1993
5-192
maintenance 523-0775657
Cable B: Connector information: J1: MS27508E20F-2P, N: 359-0667-280 P1A: DD 50P C37, N 371-0118-000; Hood: N 371-0187-000 P1B: M243083-3, N 371-0170-000 Hood: N 371-0815-000
Signal name / description
From J1
Cable A: Connector information: P1: MS27493T20f-2S, N 359-0601-020 Strain relief: MS27506F20-2, N 359-0637-070 P2A: DD 50P C37, N 371-0118-000; Hood: N 371-0187-000 P2B: M243083-3, N 371-0170-000 Hood: N 371-0815-000 To P1-A
To P1-B
From P2-A
From P2-B
To P1
Wire size/type (both cables)
ARINC 429, Data Input, A, A
28
1
1
28
Shielded twisted pair
ARINC 429, Data Input, A, B
29
14
14
29
Shielded twisted pair
Shield
30
25
25
30
Shield
ARINC 429, Data Input, B, A
31
2
2
31
Shielded twisted pair
ARINC 429, Data Input, B, B
32
15
15
32
Shielded twisted pair
Shield
33
12
12
33
Shield
ARINC 429, Data Input, C, A
34
5
5
34
Shielded twisted pair
ARINC 429, Data Input, C, B
35
18
18
5
Shielded twisted pair
Shield
36
23
23
36
Shield
ARINC 429, Data Output, A, A
44
4
4
44
Shielded twisted pair
ARINC 429, Data Output, A, B
45
17
17
45
Shielded twisted pair
Shield
46
11
11
46
Shield
ARINC 429, Data Output, B, A
47
7
7
47
Shielded twisted pair
ARINC 429, Data Output, B, B
48
20
20
48
Shielded twisted pair
Shield
49
22
22
49
Shield
ARINC 429, Data Output, C, A
50
8
8
50
Shielded twisted pair
ARINC 429, Data Output, C, B
51
21
21
51
Shielded twisted pair
Shield
52
9
9
52
Shield
28 V dc pwr input, No. 1 (+)
1
1
1
1
22 AWG
28 V dc pwr input, No. 2 (+)
7
3
3
7
22 AWG
RTU-870A/T Radio Tuning Unit, Flightline Test Cables, Assembly Diagram and Wire List Figure 5-21 (sheet 1 of 3)
5/5/1993
5-193
maintenance 523-0775657
RTU-870A/T Cable B (cont’d) Signal name / description
RTU-870A/T Cable A (cont’d)
From J1
To P1-A
3
50
50
17
17
23
23
(common - connect to P1-A 23)
13
13
22 AWG (connect to J1-A 23)
(common - connect to P1-A 23)
37
37
22 AWG (connect to J1-A 23)
Power ground Ground (connect to P1-A 50) Strap common
53
To P1-B
From P2-A
From P2-B
To P1 3
Wire size/type
22 AWG 22 AWG
53
22 AWG
115 V ac lighting, hi
5
36
36
5
26 AWG
Lighting common
4
16
16
4
26 AWG
Dimming input (+28 V dc)
8
6
6
8
26 AWG
Dim common
10
39
39
10
26 AWG
Remote ident input
11
5
5
11
26 AWG
Cross-side RTU disable
63
8
8
63
26 AWG
Reversionary data display enable
39
21
21
39
26 AWG
MB sense enable
61
9
9
61
26 AWG
ATC 1 select
13
22
22
13
26 AWG
RTU side 2 select
64
23
23
64
26 AWG
Remote tune enable
12
24
24
12
26 AWG
RTU on/off
9
25
25
9
26 AWG
L Eng data no. 1, A
37
42
42
37
Shielded twisted pair
L Eng data no. 1, B
38
10
10
38
Shielded twisted pair
Shield for 37/38
40
2
2
40
Shield for 37/38
R Eng data no. 2, A
41
11
11
41
Shielded twisted pair
R Eng data no. 2, B
42
27
27
42
Shielded twisted pair
Shield for 41/42
43
19
19
43
Shield for 41/42
RTU test mode enable
60
28
28
60
26 AWG
RTU-870A/T Radio Tuning Unit, Flightline Test Cables, Assembly Diagram and Wire List Figure 5-21 (sheet 2)
5/5/1993
5-194
maintenance 523-0775657
RTU-870A/T Cable B (cont’d) Signal name / description
RTU-870A/T Cable A (cont’d)
From J1
To P1-A
Nav radio test inhibit
58
43
MLS no. 1 select
16
MLS no. 2 select
To P1-B
From P2-A
From P2-B
To P1
Wire size/type
43
58
26 AWG
44
44
16
26 AWG
62
12
12
62
26 AWG
DME no. 2 deselect
59
29
29
59
26 AWG
ADF no. 2 deselect
57
30
30
57
26 AWG
UHF no. 1 select
17
45
45
17
26 AWG
UHF no. 2 select
18
46
46
18
26 AWG
TACAN no. 1 select
19
14
14
37
26 AWG
TACAN no. 2 select
20
15
15
20
26 AWG
TCAS on board select
21
31
31
21
26 AWG
ADF TC-X select
23
32
32
23
26 AWG
Inv TACAN inhibit select
24
47
47
24
26 AWG
Comm extended freq select
54
48
48
54
26 AWG
Nav extended freq select
55
49
49
55
26 AWG
ADF extended freq select
56
4
4
56
26 AWG
RTU-870A/T Radio Tuning Unit, Flightline Test Cables, Assembly Diagram and Wire List Figure 5-21 (sheet 3)
5/5/1993
5-195
maintenance 523-0775657
Cable B: Connector information: J1: MIL-C-26500, N 359-4118-240 J2: MIL-C-26500, N 359-4118-250 P1A: DD 50P C37, N 371-0118-000; Hood: N 371-0187-000 P1B: M243083-3, N 371-0170-000 Hood: N 371-0815-000
Cable A: Connector information: P1: MD24266R76B24S7, N 359-4068-030 P2: MS24266R16B24S8, N 359-4095-700 Strain relief: MS27506F20-2, N 359-0637-070 P2A: DD 50P C37, N 371-0118-000; Hood: N 371-0187-000 P2B: M243083-3, N 371-0170-000 Hood: N 371-0815-000
Signal name / description
From J1/J2
ARINC 429 to XPDR no. 1, 2A
J1-22
ARINC 429 to XPDR no. 1, 2B
J1-23
To P1-A
Shield for J1-22/23
To P1-B
From P2-A
From P2-B
To P1/P2
Wire size/type (both cables)
7
7
P1-22
Shielded twisted pair
20
20
P1-23
Shielded twisted pair
22
22
Shield for P1-22/23
ARINC 429 to XPDR no. 2, 2A
J2-22
8
8
P2-22
Shielded twisted pair
ARINC 429 to XPDR no. 2, 2B
J2-23
21
21
P2-22
Shielded twisted pair
9
9
Shield for J2-22/23
Shield for P2-22/23
115 V ac pwr no. 1, Hi
J1-3
34
34
P1-3
22 AWG
115 V ac pwr no. 1, Lo
J1-4
18
18
P1-4
22 AWG
115 V ac pwr no. 2, Hi
J2-3
36
36
P2-3
22 AWG
115 V ac pwr no. 2, Lo
J2-4
16
16
P2-4
22 AWG
Self-test input
J1-9
38
38
P1-9
26 AWG
Monitor lamp test input
J1-21
5
5
P1-21
26 AWG
28 V lighting, Hi
J2-1
40
40
P2-1
26 AWG
28 V lighting, Lo
J2-2
39
39
P2-2
26 AWG
5 V lighting, Hi
J1-1
7
7
P2-1
26 AWG
5 V lighting, Lo
J1-2
6
6
P1-2
26 AWG
Antenna select, no. 1
J1-5
8
8
P1-5
26 AWG
Antenna transfer common
J2-10
21
21
P2-10
26 AWG
Antenna select, no. 2
J2-5
9
9
P2-5
26 AWG
TTC-920G TCAS/Transponder Control, Flightline Test Cables, Assembly Diagram and Wire List Figure 5-22 (sheet 1 of 2)
5/5/1993
5-196
maintenance 523-0775657
TTC-920G Cable B (cont’d)
TTC-920G Cable A (cont’d)
Signal name / description
From J1/J2
To P1-A
Air/gnd no. 1, input
J1-24
22
Air/gnd no. 1, output
J1-15
Air/gnd no. 2, input
To P1-B
From P2-A
From P2-B
To P1/P2
Wire size/type
22
P1-24
26 AWG
23
23
P1-15
26 AWG
J2-24
24
24
P2-24
26 AWG
Air/gnd no. 2, output
J2-15
25
25
P2-15
26 AWG
Monitor lamp pwr, input 12/28 V
J1-18
26
26
P1-18
26 AWG
Signal common, no. 1
J1-6
41
41
P1-6
26 AWG
Signal common, no. 2
J2-6
13
13
P2-6
26 AWG
XPDR fail warn, no. 1
J1-12
42
42
P1-12
26 AWG
XPDR fail warn, no. 2
J2-12
11
11
P2-12
26 AWG
XPDR fail warn output
J1-10
10
10
P2-10
26 AWG
XPDR in stby, no. 1
J1-7
27
27
P1-7
26 AWG
XPDR in stby, no. 2
J2-7
28
28
P2-7
26 AWG
Alternate AD select, no. 1
J1-16
43
43
P1-16
26 AWG
Alternate AD select, no. 2
J2-16
44
44
P2-16
26 AWG
Chassis gnd, no. 1
J1-8
4
4
P1-8
26 AWG
Chassis gnd, no. 2
J2-8
37
37
P2-8
26 AWG
Air/gnd no. 1, output
J1-11
29
29
P1-11
26 AWG
Air/gnd no. 2, output
J2-11
30
30
P2-11
26 AWG
XPDR fail, discrete no. 1
J1-20
45
45
P1-20
26 AWG
XPDR fail, discrete no. 2
J2-20
46
46
P2-20
26 AWG
TTC-920G TCAS/Transponder Control, Flightline Test Cables, Assembly Diagram and Wire List Figure 5-22 (sheet 2)
5/5/1993
5-197
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