Rockwell Collins 6229210 TRANSPONDER User Manual P1

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Document Description	User Manual P1
Short Term Confidential	No
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Document Type	User Manual
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Filesize	387.66kB (4845692 bits)
Date Submitted	2012-12-11 00:00:00
Date Available	2013-01-25 00:00:00
Creation Date	2012-09-25 09:00:51
Producing Software	Acrobat Distiller 9.5.1 (Windows)
Document Lastmod	2012-09-25 09:00:51
Document Title	TDR-94/94D (-004 Status and Higher) ATC/Mode S Transponder (ICA)
Document Creator	PScript5.dll Version 5.2.2
Document Author:	Rockwell Collins, Inc.

component
maintenance
manual
TDR-94/94D (-004 Status
and Higher) ATC/Mode S
Transponder (ICA)
34-50-96
(with illustrated parts list)
Export Control Classification Notice (ECCN) for this document is 6E991.
© Copyright 2010 Rockwell Collins, Inc. All rights reserved.
May 20, 2010
TO: HOLDERS OF THE ROCKWELL COLLINS® TDR-94/94D (-004 STATUS AND HIGHER) ATC/MODE
S TRANSPONDER (ICA) COMPONENT MAINTENANCE MANUAL WITH IPL (CPN 523-0778502)
DESCRIPTION OF REVISION NO 13, MAY 20, 2010
This page shows all pages of the manual that are added, changed, or removed. Replace the specified pages of
the manual with the new pages supplied. Record the applicable data on the Record of Revisions page.
All changed pages keep data necessary to do maintenance on all equipment models. Black bars on the side
of the page identify changes.
PAGE
NUMBER
DESCRIPTION OF REVISION AND
REASON FOR CHANGE
SERVICE
BULLETIN
EFFECTIVITY
LEP-1 thru
LEP-14
Updated to reflect current revision.
None
All models
LOI-3 thru
LOI-5/LOI-6
Updated to reflect current revision.
None
All models
LOT-1, LOT-2
Updated to reflect current revision.
None
All models
INTRO-3
Revised Note explaining the use of XXX.
None
All models
Revised Equipment Covered Table 1 to add
new CPNs.
None
622-9352-310,
622-9352-410,
622-9210-310,
622-9210-410
23 thru 26, 28
Revised Assembly Identification Tables, Table 6
to include new CPNs.
622-9352-310,
622-9352-410,
622-9210-310,
622-9210-410
2007, 2009/
2010
Revised Assembly Revision Level and Diagram
Reference Table 2002 to add new cards.
All models
2008
Relocation of data.
None
All models
2048.1/2048.2
Added Power Amplifier Circuit Card A2
(CPN 687-0722-006), Maintenance Aid and
Schematic Changes Table 2006.1.
None
All models
PAGE
NUMBER
DESCRIPTION OF REVISION AND
REASON FOR CHANGE
SERVICE
BULLETIN
EFFECTIVITY
2048.3/2048.4
thru 2048.7/
2048.8
Added Power Amplifier Circuit Card A2 (CPN
687-0722-006), Maintenance Aid Diagram
Figure 2008.1.
None
All models
2048.9/2048.10
thru 2048.13/
2048.14
Added Power Amplifier Circuit Card A2 (CPN
687-0722-006), Schematic Diagram Figure
2008.2.
None
All models
2146.1/2146.2
Added CPU-I/O Programmed Assembly A5
(CPN 653-3674-025, -026) and CPU-I/O Circuit
Card A5A1 (CPN 828-2700-004), Maintenance
Aid and Schematic Changes Table 2012.1.
None
All models
2146.3/2146.4
thru 2146.9/
2146.10
Added CPU-I/O Programmed Assembly A5
(CPN 653-3674-025, -026) and CPU-I/O Circuit
Card A5A1 (CPN 828-2700-004), Maintenance
Aid Diagram Figure 2021.1.
None
All models
2146.11/
2146.12 thru
2146.27/
2146.28
Added CPU-I/O Programmed Assembly A5
(CPN 653-3674-025, -026) and CPU-I/O Circuit
Card A5A1 (CPN 828-2700-004), Schematic
Diagram Figure 2021.2 .
None
All models
2195/2196
Revised Video Processor Circuit Card A6 (CPN
687-0726-006) and Video Processor Circuit
Card Assembly A6 (CPN 983-8019-001),
Maintenance Aid and Schematic Changes
Table 2015.
None
All models
2220.1/2220.2
Added Video Processor Circuit Card A6
(CPN 687-0726-007), Maintenance Aid and
Schematic Changes Table 2015.1.
None
All models
2220.3/2220.4
thru 2220.9/
2220.10
Added Video Processor Circuit Card A6 (CPN
687-0726-007), Maintenance Aid Diagram
Figure 2028.1.
None
All models
2220.11/
2220.12 thru
2220.25/
2220.26
Added Video Processor Circuit Card A6 (CPN
687-0726-007), Schematic Diagram Figure
2028.2.
None
All models
PAGE
NUMBER
DESCRIPTION OF REVISION AND
REASON FOR CHANGE
SERVICE
BULLETIN
EFFECTIVITY
2239/2240
Revised IF Receiver, DPSK Detector, and
LVPS Circuit Card A7 (CPN 687-0727-005),
Maintenance Aid and Schematic Changes
Table 2017.
None
All models
2259/2260,
2261/2262
Revised IF Receiver, DPSK Detector, and
LVPS Circuit Card A7 (CPN 687-0727-005),
Schematic Diagram (Sheets 6 and 7).
None
All models
9005
Revised Special Test Equipment Required.
(Preferred List) Table 9002.
None
All models
10004 thru
10005/10006
Updated Equipment Designator Prefixes
table to reflect current revision and addition
of top levels CPN 622-9210-310, -410, CPN
622-9352-310, -410; addition of Chassis
Assembly, Main CPN 653-2254-039, -040,
-041, -042 and addition of new figures 20 thru
24 CPN 687-0726-007, CPN 828-2700-004,
CPN 687-0722-006, CPN 653-0030-002 and
CPN 653-0030-003.
None
All models
10007 thru
10011/10012
Updated Manufacturer's Code, Name and
Address Index to reflect current revision.
None
All models
10008.1/
10008.2
New pages added to Manufacturer's Code,
Name and Address Index due to new/revised
data added on previous pages (data pushed
from previous page).
None
All models
10014 thru
10016, 10023
thru 10040,
10050
Updated Equipment Designator Index to reflect
current revision.
None
All models
PAGE
NUMBER
DESCRIPTION OF REVISION AND
REASON FOR CHANGE
SERVICE
BULLETIN
EFFECTIVITY
10014.1/
10014.2,
10024.1/
10024.2,
10026.1/
10026.2,
10028.1/
10028.2,
10032.1/
10032.2,
10034.1/
10034.2,
10036.1/
10036.2,
10038.2/
10038.2
New pages added to Equipment Designator
Index due to new/revised data added on
previous pages (data pushed from previous
page). These pages also updated to reflect
current revision.
None
All models
10016.1/
10016.2,
10040.1/
10040.2
New pages added to Equipment Designator
Index due to new/revised data added on
previous pages (data pushed from previous
page).
None
All models
10051 thru
10083/10084
Updated Numerical Index to reflect current
revision.
None
All models
PAGE
NUMBER
DESCRIPTION OF REVISION AND
REASON FOR CHANGE
SERVICE
BULLETIN
EFFECTIVITY
10052.1/
10052.2,
10054.1/
10054.2,
10056.1/
10056.2,
10058.1/
10058.2,
10060.1/
10060.2,
10062.1/
10062.2,
10064.1/
10064.2,
10068.1/
10068.2,
10074.1/
10074.2,
10076.1/
10076.2,
10078.1/
10078.2,
10080.1/
10080.2,
10082.1/
10082.2
New pages added to Numerical Index due to
new/revised data added on previous pages
(data pushed from previous page). These
pages also updated to reflect current revision.
None
All models
10085 thru
10090, 10091
thru 10101/
10102
Updated Optional Vendor Index to reflect
current revision.
None
All models
10103/10104
Updated Figure 1 illustration and illustration
title to reflect current revision and addition
of top levels CPN 622-9210-310, -410, CPN
622-9352-310, -410.
None
All models
10105 thru
10107/10108
Updated Figure 1 to reflect current revision,
addition of top levels (items 1Y thru 2A) and
correction of item 1X nomenclature.
None
All models
PAGE
NUMBER
DESCRIPTION OF REVISION AND
REASON FOR CHANGE
SERVICE
BULLETIN
EFFECTIVITY
10111/10112,
10113 thru
10114.1/
10114.2
Updated Figure 2 to reflect current revision for
top level CPN 653-2255-006.
None
All models
10121/10122
Updated Figure 4 illustration and illustration title
to reflect current revision and addition of top
levels CPN 653-2254-039, -040, -041, -042.
None
All models
10123 thru
10127/10128
Updated Figure 4 to reflect current revision and
addition of top level items 1U thru 1X.
None
All models
10124.1/
10124.2,
10126.3/
10126.4
New pages added to Figure 4 due to
new/revised data added on previous pages
(data pushed from previous page). These
pages updated to reflect current revision.
None
All models
10157, 10158
Updated Figure 7 to reflect current next higher
assembly reference for item 1.
None
All models
10158.1/
10158.2
New pages added to Figure 7 due to
new/revised data added on previous pages
(data pushed from previous page).
None
All models
10349 thru
10366
Added new Figure 20, CPN 687-0726-007.
None
All models
10367 thru
10382
Added new Figure 21, CPN 828-2700-004.
None
All models
10383 thru
10396
Added new Figure 22, CPN 687-0722-006.
None
All models
10397/10398
Added new Figure 23, CPN 653-0030-002 (no
illustration required).
None
All models
10399/10400
Added new Figure 24, CPN 653-0030-003 (no
illustration required).
None
All models
TDR-94/94D (-004 Status
and Higher) ATC/Mode S
Transponder (ICA)
component maintenance manual
(with illustrated parts list)
This manual includes data for the equipment that follows:
Unit
ATC/Mode S Transponder
Model
TDR-94
ATC/Mode S Transponder
TDR-94D
Collins Part No
622-9352-004, -005, -006, -007, -008, -108,
-207, -308, -309, -310, -408, -409, -410
622-9210-004, -005, -006, -007, -008, -108,
-207, -308, -309, -310, -408, -409, -410
Printed in the United States of America
© Copyright 2010 Rockwell Collins, Inc. All rights reserved.
7'5B&00B0$300 000 lb)
open
High performance
gnd
Rotor craft
Type_X Select Straps (Type Set B)
Aircraft Type Set B
Type_2 Type_1
P1-22
P1-21
open
open
open
open
open
gnd
open
gnd
gnd
open
gnd
open
gnd
gnd
gnd
gnd
(Type_3 (P1-23) = gnd)
Type_0
P1-20
Code
Meaning
open
No aircraft type information
gnd
Glider/sail plane
open
Lighter-than-air
gnd
Parachutist/skydiver
open
Surface vehicle
gnd
Fixed ground or tethered obstruction
open
Unmanned aerial vehicle
gnd
Unassigned
Equipment Specifications
Table 4/Table 34-50-96-99A-036-A01
34-50-96
Page 17
May 18/06
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
CONDITIONS
DO-160C PARA
NO
SPECIFICATION
Temp and Altitude
Low Operating Temp
High Operating Temp
Low Storage Temp
High Storage Temp
Altitude
4.0
4.5.1
4.5.3
4.5.1
4.5.2
4.6.1
Categories 'A2' and 'E1'.
-55 °C (-67 °F)
+70 °C (+158 °F)
-65 °C (-85 °F)
+85 °C (+185 °F)
Category 'A2'. Certified for installation in a controlled
temperature location in an aircraft where pressures are no
lower than an altitude equivalent of 4600 m (15 000 ft) msl.
Category 'E1'. Certified for installation in a nonpressurized
but noncontrolled temperature location in an aircraft 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 aircraft.
Humidity
6.0
Category 'B'. Certified for a Severe Humidity Environment.
Shock
Operational
Crash Safety:
Impulse
Sustained
7.0
7.2
7.3
7.3.1
7.3.2
Vibration
8.0
Categories C, L, M, and Y
Category C: Certified for fuselage mounting in a fixed wing
turbojet or turbofan aircraft.
Category L: Certified for fuselage mounting in a fixed wing
aircraft having multiple reciprocating or turbopropeller
engines and a weight over 5700 kg (12 500 lb).
Category M: Certified for fuselage mounting in a fixed
wing aircraft having multiple, or a single reciprocating or
turbopropeller engines and a weight less than 5700 kg
(12 500 lb).
Category Y: Certified for fuselage mounting in piston or
turbojet rotary wing aircraft.
Explosion Proofness
9.0
Category E1: Certified for installation in an environment in
which uncovered flammable fluids or vapors exist, either
continuously or intermittently.
Waterproofness
10.0
Category X (no test required): Certified for installation
in locations not subject to falling water (including
condensation), rainwater, or sprayed water.
Tested at 6 g peak (11 ±2 ms duration, 6 positions)
Tested at 15 g, 6 positions
Tested at 12 g, 6 positions
Environmental Qualifications Form Cont.
Table 5/Table 34-50-96-99A-037-A01
34-50-96
Page 18
May 18/06
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
CONDITIONS
DO-160C PARA
NO
SPECIFICATION
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 F: Fungus test not performed. However, the
unit is composed entirely of non-nutrient materials and is
therefore classified as Category F.
Salt Spray
14.0
Category X: Certified for installation in locations not
subject to a salt atmosphere.
Magnetic Effect
15.0
Category Z: Unit causes a 1° deflection of an
uncompensated compass at a distance less than 0.3 m
(1.0 ft).
Power Input
16.0
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.
Voltage Spike
17.0
Category A: Certified for installation in systems where a
high degree of voltage spike protection is required.
Audio Frequency
Conducted Susceptibility power inputs
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 (radiated
and conducted)
20.0
Category R: Certified for operation in systems where
bench testing is allowed to meet the high intensity radiated
field (HIRF) associated with the normal environment
intended for the unit installation.
Emission of RF Energy
21.0
Category Z: Certified for operation in systems where
interference-free operation is required.
Lightning Induced
Transient Susceptibility
22.0
Category Z3Z3: Certified for installation in a moderate
environment, such as the more electromagnetically open
areas of an aircraft composed principally of metal (e.g.,
cockpit).
Environmental Qualifications Form Cont.
Table 5/Table 34-50-96-99A-037-A01
34-50-96
Page 19
May 18/06
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
CONDITIONS
DO-160C PARA
NO
SPECIFICATION
Lightning Direct Effects
23.0
Category X (no test required): Certified for operation in
which lightning effects are insignificant or not applicable.
Icing
24.0
Category X (no test performed): Certified for installation in
a location not subject to ice formation.
Environmental Qualifications Form
Table 5/Table 34-50-96-99A-037-A01
TASK 34-50-96-870-804-A01
4. Equipment Description
A. Mechanical Description
(1) The TDR-94/94D is a half-ATR short low rack mounted unit. Electrical connections
are made through two ThinLine II, 60-pin connectors. Refer to Table 4/Table
34-50-96-99A-036-A01, Equipment Specifications, for additional mount and mating
connector information.
(2) Refer to the Collins Pro Line II Comm/Nav/Pulse System Installation Manual,
523-0772719, for mounting and dimensional information.
(3) Figure 2/GRAPHIC 34-50-96-99B-002-A01 lists the three major subassemblies in
the TDR-94/94D. The main chassis occupies the center of the unit and includes the
high-voltage power supply card A1 at the front, the CPU-I/O card A5, and video
processor card A6 assemblies in the center-rear. One of the two main rear connectors
is mounted on each of these circuit cards. As viewed from the front, A5 is on the left
side, and A6 is on the right.
(4) The two outer subassemblies are the RFPA chassis assembly on the left and the IF
receiver chassis assembly on the right. Each of these also contains various circuit card
assemblies. These are all illustrated in Figure 2/GRAPHIC 34-50-96-99B-002-A01.
Table 6/Table 34-50-96-99A-004-A01 also gives listings showing the top level
configuration as well as the configurations of each of these major subassemblies.
34-50-96
Page 20
May 18/06
34-50-96
Assembly Identification Diagram
Figure 2/GRAPHIC 34-50-96-99B-002-A01
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
Page 21/22
May 18/06
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
TDR-94 Top Level, Configuration Matrix
TDR-94
622-9352-
REV
MAIN CHASSIS
CPN 653-2254-
RFPA CHASSIS
CPN 653-2255-
IF/RCVR/DPSK/
LVPS CHASSIS
CPN 653-2256-
004
V (SB 13)
012
004
005
004
W (SB 14)
016
004
005
004
AC
016
005
005
004
AT
016
005
006
005
AE (SB17)
018
005
005
005
AT
018
005
006
006
AG
020
005
005
006
AH
022
005
005
006
AT
022
005
006
007
AL
024
005
005
007
AT
024
005
006
008
AR
026
005
006
108
AR
028
005
006
207
BF
030
005
006
308
BJ
032
005
006
408
BJ
034
005
006
309
BM
036
005
006
409
BM
038
005
006
310
BW
040
005
006
410
BW
042
005
006
Assembly Identification Tables Cont.
Table 6/Table 34-50-96-99A-004-A01
34-50-96
Page 23
May 20/10
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
TDR-94D Top Level, Configuration Matrix
REV
MAIN CHASSIS
CPN 653-2254-
RFPA CHASSIS
CPN 653-2255-
IF/RCVR/DPSK/
LVPS CHASSIS
CPN 653-2256-
004
U (SB13)
011
001
005
004
V (SB 14)
015
001
005
004
AB
015
003
005
004
AK
015
006
005
004
AV
015
006
006
005
AD (SB17)
017
003
005
005
AK
017
006
005
005
AV
017
006
006
006
AG
019
003
005
006
AJ
021
003
005
006
AK
021
006
005
006
AV
021
006
006
007
AN
023
006
005
007
AV
023
006
006
008
AU
025
006
006
108
AU
027
006
006
207
BF
029
006
006
308
BJ
031
006
006
408
BJ
033
006
006
309
BM
035
006
006
409
BM
037
006
006
310
BW
039
006
006
410
BW
041
006
006
TDR-94D
622-9210-
Assembly Identification Tables Cont.
Table 6/Table 34-50-96-99A-004-A01
34-50-96
Page 24
May 20/10
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
Main Chassis Assembly (With SB 13 and SB 14 Installed), Configuration Matrix.
CPU-I/O PROG
ASSY A5
MAIN
CHASSIS CPN
653-2254-
REV
HVPS CCA A1
CPN 687-0721-
011 (-94D)
AA
002
005
001
015 (-94D)
002
004
003
015 (-94D)
002
005
003
015 (-94D)
003
005
003
015 (-94D)
003
006
003
017 (-94D)
002
005
005
017 (-94D)
003
005
005
017 (-94D)
003
006
005
019 (-94D)
003
005
007
019 (-94D)
003
006
007
021 (-94D)
003
005
009
021 (-94D)
003
005
011
021 (-94D)
003
006
011
023 (-94D)
003
005
013
023 (-94D)
003
006
013
025 (-94D)
003
006
015
025 (-94D)
003
027 (-94D)
003
006
015
027 (-94D)
003
006
017
029 (-94D)
003
006
019
029 (-94D)
003
006
019
031 (-94D)
003
033 (-94D)
003
035 (-94D)
003
037 (-94D)
003
039 (-94D)
003
041 (-94D)
003
VIDEO PROC CCA A6
CPN
687-0726-
CPN
983-8019-
001
001
006
CPN
653-3674-
015
021
021
001
006
023
023
001
007
025
025
Assembly Identification Tables Cont.
Table 6/Table 34-50-96-99A-004-A01
34-50-96
Page 25
May 20/10
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
Main Chassis Assembly (With SB 13 and SB 14 Installed), Configuration Matrix. (Cont.)
CPU-I/O PROG
ASSY A5
MAIN
CHASSIS CPN
653-2254-
REV
HVPS CCA A1
CPN 687-0721-
012 (-94)
002
005
002
016 (-94)
002
004
004
016 (-94)
002
005
004
016 (-94)
003
005
004
016 (-94)
003
006
004
018 (-94)
002
005
006
018 (-94)
003
005
006
018 (-94)
003
006
006
020 (-94)
003
005
008
020 (-94)
003
006
008
022 (-94)
003
005
010
022 (-94)
003
005
012
022 (-94)
003
006
012
024 (-94)
003
005
014
024 (-94)
003
006
014
026 (-94)
003
028 (-94)
003
006
016
028 (-94)
003
006
018
030 (-94)
003
006
020
030 (-94)
003
006
020
032 (-94)
003
034 (-94)
003
036 (-94)
003
038 (-94)
003
040 (-94)
003
042 (-94)
003
VIDEO PROC CCA A6
CPN
687-0726-
CPN
983-8019-
001
001
006
CPN
653-3674
016
022
022
001
006
024
024
001
007
026
026
Assembly Identification Tables Cont.
Table 6/Table 34-50-96-99A-004-A01
34-50-96
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COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
Programmed Assembly, Configuration Matrix
CPU-I/O PROGRAMMED
ASSEMBLY A5
PROGRAMMED
ASSEMBLY
CPU-I/O CCA
A5A1
CPN 831-6270-
CPN 828-2700-
CPN 653-3674-
REV
001
002
002
002
003
002
004
002
005
002
006
002
007
007
002
008
007
002
009
008
002
010
008
002
011
009
002
012
009
002
013
010
002
014
010
002
015
015
016
016
017
017
018
018
109
003
019
011
002
019
011
002
020
011
002
020
011
002
021
110
003
022
110
003
003
108
003
003
108
003
003
109
003
003
Assembly Identification Tables Cont.
Table 6/Table 34-50-96-99A-004-A01
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TDR-94, PART NO 622-9352
Programmed Assembly, Configuration Matrix (Cont.)
CPU-I/O PROGRAMMED
ASSEMBLY A5
PROGRAMMED
ASSEMBLY
CPU-I/O CCA
A5A1
CPN 653-3674-
REV
CPN 831-6270-
CPN 828-2700-
023
111
003
024
111
003
025
112
004
026
112
004
RFPA Chassis Assembly, Configuration Matrix
RFPA
CHASSIS
ASSEMBLY
SYNTHESIZER
CCA A4
MODULATOR CCA A3
POWER
AMPLIFIER
CCA A2
CPN 653-2255-
REV
CPN 687-0724-
CPN 687-0723-
CPN 687-0722-
001
002
004
003
001
AD
002
005
003
001
AE
003
005
003
003
002
004
004
003
AE
003
004
004
004
002
004
003
004
AE
003
004
003
005
002
004
004
005
AD
002
005
004
005
AE
003
005
004
006
AC
002
005
004
006
AE
003
005
004
005
AK
003
005
004 or 006
006
AK
003
005
004 or 006
Assembly Identification Tables Cont.
Table 6/Table 34-50-96-99A-004-A01
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TDR-94, PART NO 622-9352
IF Receiver Chassis Assembly, Configuration Matrix
IF RCVR/LVPS
CCA A7
IF RECEIVER
CHASSIS
653-2256-
REV
CPN 687-0727-
005
004
006
005
Assembly Identification Tables
Table 6/Table 34-50-96-99A-004-A01
B. Electrical Description
(1) Refer to Table 4/Table 34-50-96-99A-036-A01, Equipment Specifications, for detailed
listing and descriptions of all input/output signals used in the TDR-94/94D Transponder.
C. Controls and Indicators
(1) Refer to the system pilot's guide or operation section of the system installation manual
for complete descriptions of indicators and displays.
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TASK 34-50-96-870-805-A01
5. Installation Data
A. Refer to the TDR-94/94D Installation Section in the Pro Line II Comm/Nav/Pulse System
Installation Manual for installation information relative to the TDR-94/94D Mode S
Transponder.
TASK 34-50-96-870-806-A01
6. System Theory of Operation
SUBTASK 34-50-96-870-001-A01
A. Introduction
(1) The air traffic control radar beacon system (ATCRBS) is a surveillance system in
wide use to locate and identify airplanes within an airspace. However, because of
increasing air traffic, this system is expanding 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.
(2) If this is your first contact 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 system.
SUBTASK 34-50-96-870-002-A01
B. Radar Systems
(1) Refer to Figure 3/GRAPHIC 34-50-96-99B-070-A01. The ATCRBS consists of a
primary surveillance radar (PSR) and a secondary surveillance radar (SSR). The
large rotating radar antenna that can be seen at or near most air terminals is that of
the PSR. This system uses conventional radar to locate all airplanes within its range
in terms of range and azimuth. It transmits a burst of energy and then measures the
time to an echo. The time thus measured is converted into range (refer to the note
below for additional information). The direction the antenna is pointing at the time of
echo detection establishes the azimuth to the reflecting target. This target information is
displayed Figure 3/GRAPHIC 34-50-96-99B-070-A01 on the air traffic controller's PPI
(Plan Position Indicator).
NOTE: The time is easily converted into range. The mathematical formula
for distance is: D = velocity x time. The propagation velocity of radio
energy is usually expressed as 12.359 μs / radar mile.
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ATCRBS, PSR and SSR System
Figure 3/GRAPHIC 34-50-96-99B-070-A01
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SUBTASK 34-50-96-870-003-A01
C. ATCRBS Operation
(1) ATCRBS Interrogation Modes
(a) The SSR system interrogates the airplane transponder for airplane identity and
altitude. The interrogations are in the form of two modes: mode A for airplane
identity and mode C which is used to request altitude information (refer to the note
below for additional information).
NOTE: In the original definition of ATC modes, two other modes were defined;
mode B and mode D. These also differ only in pulse spacing with mode B
pulses spaced 17 μs, and mode D pulses spaced 25 μs. Mode D was
widely used in Great Britain but recently the aviation industry
has settled on mode A for ATCRBS operation and mode C for
altitude reporting. Modes B and D have been largely abandoned.
The US Military uses a system similar to ATCRBS. It is known as IFF
(Identification - Friend or Foe). As this name implies, it is concerned
primarily with mission security. Three modes are defined; modes 1, 2, and
3. Mode 3 is common to the civil mode A with a pulse spacing of 8 μs. This
allows air traffic control visibility of all airplanes, both civil and military.
(b) All pulses are 0.8 μs wide. The interrogations from the ground station are at
a frequency of 1030 MHz. The transponder replies at a frequency of 1090
MHz. The received signal from the airborne transponder is decoded by the
ground system and displayed on the ATC radar screen (see Figure 4/GRAPHIC
34-50-96-99B-071-A01). The replies produce either a single or double slash target
display on the controller screen. The controller can also elect to display the airplane
identification number (as selected by the aircrew) and altitude.
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Air Traffic Presentation on the ATC Radarscope
Figure 4/GRAPHIC 34-50-96-99B-071-A01
(2) SSR System Interrogation Description
(a) Refer to Figure 5/GRAPHIC 34-50-96-99B-072-A01 and Figure 6/GRAPHIC
34-50-96-99B-073-A01. 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 μs while in mode C
the pulses are spaced 21 μs. The SSR also uses an omnidirectional antenna to
transmit a third pulse designated P2. This pulse is transmitted 2 μs 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 side lobe of the directional antenna.
Typically, this is about 18 dB below the peak of the directional (main) beam.
(b) Refer to Figure 5/GRAPHIC 34-50-96-99B-072-A01. Notice the two airplanes on
the drawing. Airplane A is shown within the main lobe of the directional antenna.
The amplitude of the P1 and P3 pulses will be substantially greater here than the
P2 pulse radiated from the omnidirectional antenna. Therefore, the transponder in
this airplane will interpret this interrogation as valid.
(c) Airplane B, however, is outside the main lobe and within one of the side lobes.
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
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TDR-94, PART NO 622-9352
equal in amplitude to that of the peak side lobe. Therefore, the P2 pulse detected
by airplane B will be at least as great in amplitude as the P1/P3 pulses. The
transponder in airplane 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 late-arriving echoes to
this invalid interrogation, the transponder suppresses replies to all interrogations
for an additional 25 to 45 μs. In addition, the receiver is desensitized for reception
of P1/P3 pulses. The rationale here is that if the side lobes are detectable, then
the main lobe must be much greater.
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ATCRBS, SSR Antenna Radiation Pattern
Figure 5/GRAPHIC 34-50-96-99B-072-A01
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ATCRBS Interrogator Pulse
Figure 6/GRAPHIC 34-50-96-99B-073-A01
(3) ATC Transponder Replies
(a) As mentioned earlier, the most common transponder modes are mode A and mode
C. Mode A provides ident (identification) information, while mode C provides altitude
data. The reply formats are very similar, differing only in pulse spacing (delay).
(b) The ATCRBS mode A transponder reply signal is shown in Figure 7/GRAPHIC
34-50-96-99B-074-A01. Notice that the signal can consist of from 2 to 16 pulses.
The two framing pulses F1 and F2 are always present and spaced 20.3 μs. An
identification pulse may be transmitted 4.35 μs after the last framing pulse F2. The
intervening pulses, A1 through D4, make up the coded reply. The X pulse is not
used. The coded reply consists of twelve pulses; four groupings of three pulses
each. These groupings give four digits of octal data. The digits are formed by
the sum of the pulse (bit) values; 1, 2, or 4, which can produce a digit value 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 1324. The first digit, 1, is formed by 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 =
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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 4096 (212) different codes possible which
explains the label 4096 code.
(c) The ATCRBS mode C transponder reply consists of the same framing pulses F1
and F2 but spaced 21 μs. The intervening pulses, A1 through D4 (except for D1),
make up the coded reply. The coding scheme is defined by ARINC 572, commonly
referred to as the Gillham code, and provides encoded altitude data in the range of
-1000 to 127 000 feet, to the nearest 100 feet. Recall that in mode A the individual
bits assume a binary value which combines into four, three-bit groups, each group
forming an octal digit. In mode C the individual pulses are combined into three
groups. The A, B, and D (except for bit D1) pulses are grouped into two four-bit
groups to encode the altitude to the nearest 500 feet. The C pulses provide the
100-feet deviation (above or below) from the 500-feet level. The mode C encoding
scheme is described in Figure 8/GRAPHIC 34-50-96-99B-075-A01. Notice that the
bit pattern does not follow a conventional binary progression. This scheme was
designed to provide a sequence in which only one bit changes at a time as the
altitude increases or decreases.
(d) The upper part of the table consists of a matrix of numbers arranged into rows
and columns. These numbers can be referred to as segment numbers. To find
the altitude to the nearest 500 feet, represented by a given bit pattern, you must
first find the segment that corresponds to that bit sequence. Multiply the segment
number by 500 and subtract 1000 (or subtract 2 from the segment number and
then multiply by 500).
(e) The 100-feet altitude is not as easy. To determine the 100-feet level, it is first
necessary to decide whether the 500-feet segment is odd or even. Knowing that,
you add or subtract 0, 100, or 200 feet to or from the 500-feet level depending on
the C bit sequence as shown in the lower portion of the table.
Transponder 4096 Reply Code, Signal Format
Figure 7/GRAPHIC 34-50-96-99B-074-A01
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Gillham Altitude, ARINC 572, Encoding Scheme
Figure 8/GRAPHIC 34-50-96-99B-075-A01
SUBTASK 34-50-96-870-004-A01
D. ATCRBS with Mode S
(1) Introduction
(a) Refer to Figure 9/GRAPHIC 34-50-96-99B-076-A01. Mode S substantially
enhances the capability of the ATCRBS by adding data link and select 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 multisite
(ground station-to-ground station) 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).
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Mode S, PSR and SSR System
Figure 9/GRAPHIC 34-50-96-99B-076-A01
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(2) Mode S Interrogation Modes
(a) Eight different formats of interrogation are used in mode S. These eight can be
summarized as three basic types. These are shown in Figure 10/GRAPHIC
34-50-96-99B-077-A01 and Figure 11/GRAPHIC 34-50-96-99B-078-A01. Table
7/Table 34-50-96-99A-038-A01 is a summary of all eight. The three basic types
are as follows:
Universal ATCRBS All Call
This interrogation is in the form of P1, P3, and an 0.8 μs P4 pulse. This
interrogation is recognized by all non mode S transponders in the airspace.
ATCRBS transponders reply as usual with the 4096 identification code
for mode A interrogations and altitude data for mode C. Mode S
transponders do not react to this interrogation.
Mode S Only All Call
The second type is the same as the previous universal ATCRBS All Call
interrogation except that the P4 pulse is 1.6 μs long. This interrogation is
recognized only by mode S transponders. However, mode S transponders may
suppress replies if in the lockout condition. Mode S transponders in lockout
reply only to the select address interrogation.
Mode S (Select) Interrogation
The third interrogation type is directed to a specific Mode-S equipped airplane.
This interrogation is in the form of P1, P2, and P6. The presence of the P2
pulse at the normal ATCRBS SLS location effectively suppresses
the non mode S transponder reply.
(b) This variety of interrogation capability gives the ground controller the flexibility of
addressing airplanes of immediate interest, as opposed to processing replies from
every airplane in the area.
(c) All of the Mode-S uplink or interrogation message formats are summarized in
Table 7/Table 34-50-96-99A-038-A01. The fields are described in the following
paragraphs. These descriptions mirror Document RTCA/DO 181 with minor
changes to clarify the text.
Address/Parity (AP)
The 24 bit AP field contains the parity overlaid on the address. The field
appears at the end of all transmissions for uplink interrogations and downlink
replies, except for Downlink Format (DF) number 11.
Acquisition Special (AQ)
The 1 bit AQ field designates uplink format (UF) numbers 0 and
16 as acquisition transmissions and repeats as received by the
transponder in DF numbers 0 and 16.
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Comm B Data Selector (BDS)
This 8 bit BDS field in UF number 1 contains the identity of the
ground-initiated Comm B register whose contents appear in the
MV field of the corresponding reply.
Designator Identification (DI)
The 3 bit DI field identifies the coding within the special designator (SD) field in
UF numbers 4, 5, 20, and 21. The codes are defined as follows:
DI
3-6
DEFINITION
SD contains Interrogator Identification (IIS) information. IIS data is
basically the same as the II field except that it appears as a subfield in
multisite data protocol.
SD contains multisite information
SD contains extended squitter control information
(not assigned)
SD contains extended data readout requests
Interrogator Identification (II)
The 4 bit II field identifies the interrogator and appears in UF number 11 (Mode
S only all call).
Message, Comm A (MA)
The 56 bit MA field contains messages directed to the airplane during Comm A
interrogations (UF numbers 20 and 21).
Message, Comm C (MC)
The 80 bit MC field contains one of a sequence of segments transmitted to the
transponder in the extended length message (ELM) (112 bits) using
UF number 24.
Message, Comm U (MU)
The 56 bit MU field contains information used in air to air message exchanges
and is part of the long special surveillance interrogation using UF number 16.
This message field does not use the Comm A protocol.
Number of C Segment (NC)
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 using UF number 24.
10 Protocol (PC)
The 3 bit PC field contains operating commands to the transponder
and is part of surveillance and Comm-A interrogations using UF
numbers 4, 5, 20, and 21. The codes used in this field are as follows:
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PC
2-3
DESCRIPTION
No changes in transponder state
Nonselective all call lockout
(not assigned)
Close out B
Close out C
Close out D
(not assigned)
11 Probability of Reply (PR)
The 4 bit PR field contains commands to the transponder to specify
the reply probability to the mode S only all call interrogation, UF
number 11. A command to disregard any lockout state
can also be given. The assigned codes are as follows:
PR
5 -7
10
11
12
13 -15
DESCRIPTION
Reply with probability = 1
Reply with probability = 1/2
Reply with probability = 1/4
Reply with probability = 1/8
Reply with probability = 1/16
Do not reply
Disregard lockout, reply with probability = 1
Disregard lockout, reply with probability = 1/2
Disregard lockout, reply with probability = 1/4
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 than 0 or 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
airplanes whose replies would otherwise synchronously garble each other.
12 Reply Control (RC)
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 action by
the transponder. RC is part of the Comm C interrogation, UF number 24.
13 Reply Length (RL)
The 1 bit RL field commands a reply in DF number 0 if the bit is logic 0, and a
reply in DF number 16 if the bit is logic 1.
14 Reply Request (RR)
The 5 bit RR field contains the length and content of the reply
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requested by the interrogators. The RR field is part of the surveillance
and Comm A interrogations using UF numbers 4, 5, 20, and 21.
The codes used in the RR field are described as follows:
RR
0 - 15
16
17
18
19
20 - 31
REPLY LENGTH
short
long
long
long
long
long
MB CONTENT
------------Air-initiated Comm B
Extended capability
Flight ID
TCAS resolution advisory report
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.
15 Special Designator (SD)
The 16 bit SD field contains control codes affecting the transponder protocol
and is part of surveillance and Comm A interrogations using UF numbers 4, 5,
20, and 21. The content is specified by the DI field. A 4-bit IIS subfield is within
all SD fields of UF numbers 4, 5, 20, and 21 if the DI code is 0, 1, or 7. The IIS
is used to specify the interrogator identifier.
16 Uplink Format (UF)
UF is a general term referring to the first field in all uplink formats and is the
transmission descriptor in all interrogations. UF refers to all messages
described in Table 7/Table 34-50-96-99A-038-A01.
FORMAT
NUMBER
UPLINK BIT FORMAT
HEX/
DEC
UF
0/0
0 0000
1/1
0 0001
2/2
0 0010
AP: 24
3/3
0 0011
AP: 24
4/4
0 0100
SHORT MESSAGE STRUCTURE
෥3෥
RL: 1
෥4෥
AQ: 1
BDS:
෥10෥
Length, content, and structure undefined
PC: 3
RR: 5
DI: 3
SD: 16
MESSAGE TYPE
AP: 24
AP: 24
AP: 24
SHORT
SPECIAL (Air-Air)
SURVEILLANCE
NOT PRESENTLY
DEFINED
OR NOT USED
SURVEILLANCE,
ALTITUDE
REQUEST
Mode S, Interrogation Code Summary Cont.
Table 7/Table 34-50-96-99A-038-A01
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FORMAT
NUMBER
UPLINK BIT FORMAT
5/5
0 0101
PC: 3
RR: 5
DI: 3
SD: 16
AP: 24
6/6
0 0110
7/7
0 0111
AP: 24
8/8
0 1000
AP: 24
9/9
0 1001
AP: 24
A / 10
0 1010
AP: 24
B / 11
0 1011
C / 12
0 1100
D / 13
0 1101
AP: 24
E / 14
0 1110
AP: 24
F / 15
0 1111
AP: 24
Length, content, and structure undefined
PR: 4
෥19 (ALL ONES)෥
II: 4
AP: 24
AP: 24
Length, content, and structure undefined
AP: 24
SURVEILLANCE,
IDENTITY
REQUEST
NOT PRESENTLY
DEFINED
OR NOT USED
MODE S ONLY,
ALL-CALL
NOT PRESENTLY
DEFINED
OR NOT USED
LEGEND: XX: M designates a field containing M bits, ෥N෥ denotes free space with N available bits.
FIELD DESIGNATORS:
AP = Address/Parity
AQ = Acquisition Special
BDS = Comm-B Data Selector
DI = Designator Identification
RR = Reply Request
SD = Special Designator
UF = Uplink Format
II = Interrogator Identification
PC = Protocol
PR = Probability of Reply
RL = Reply Length
HEX/
DEC
UF
01/ 16
1 0000
11/ 17
1 0001
12/ 18
1 0010
AP: 24
13/ 19
1 0011
AP: 24
14/ 20
1 0100
PC: 3
RR: 5
DI: 3
SD: 16
MA: 56
AP: 24
COMM-A,
ALTITUDE
REQUEST
15/ 21
1 0101
PC: 3
RR: 5
DI: 3
SD: 16
MA: 56
AP: 24
COMM-A,
IDENTITY
REQUEST
LONG MESSAGE STRUCTURE
෥3෥
RL: 1
෥4෥
AQ: 1
-18-
MU-56
Length, content, and structure undefined
MESSAGE TYPE
AP: 24
AP: 24
LONG SPECIAL
SURVEILLANCE
NOT DEFINED
OR NOT USED
Mode S, Interrogation Code Summary Cont.
Table 7/Table 34-50-96-99A-038-A01
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FORMAT
NUMBER
UPLINK BIT FORMAT
16/ 22
1 0110
17/ 23
1 0111
18/ 24
(see
note)
11
Length, content, and structure undefined
RC: 2
NC: 4
MC: 80
P: 24
P: 24
NOT PRESENTLY
DEFINED
OR NOT USED
AP: 24
COMM-C,
EXTENDED
LENGTH
MESSAGE
LEGEND:
XX: M designates a field containing M bits, ෥N෥ denotes free space with N available bits.
NOTE:
Format number 18 / 24 is defined as the beginning with "11" in the first two bit positions while the following
three bits vary with the interrogation content; i.e., two bits are the C field and the remaining bit is in the
NC field.
FIELD DESIGNATORS:
AP = Address/Parity
AQ = Acquisition Special
DI = Designator Identification
MA = Message, Comm-A
MC = Message, Comm-C
MU = Message, Comm-U
NC = Number of C-Segment
PC = Protocol
RC = Reply Control
RL = Reply Length
RR = Reply Request
SD = Special Designator
UF = Uplink Format
Mode S, Interrogation Code Summary
Table 7/Table 34-50-96-99A-038-A01
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Mode S, All-Call, and Discrete Addressing, Interrogation Format
Figure 10/GRAPHIC 34-50-96-99B-077-A01
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Mode S Discrete Addressing, Pulse P6 Definition
Figure 11/GRAPHIC 34-50-96-99B-078-A01
(3) Mode S SSR Radiation Pattern and SLS
(a) Refer to Figure 12/GRAPHIC 34-50-96-99B-079-A01. 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 μs before the first spr. Thus, if the
amplitude of P5 is sufficient to blank the first spr of P6, the interrogation is most
likely from a side lobe and not from the main lobe. In this case the spr is hidden
from the transponder and the reply is suppressed.
(b) The transmission of mode S interrogation uses a technique known as binary
differential phase shift keying (DPSK). This technique is illustrated in Figure
11/GRAPHIC 34-50-96-99B-078-A01. For greater detail, refer to the information
below.
(c) The SSR mode S interrogation pulse spacing and identification is different from
earlier ATCRBS. Notice that the rotating beam transmits two different pulse
combinations. 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
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μs. The pulse width of P4 determines the all-call objective. A 0.8 μs pulse is only for
non-mode S transponders, while the 1.6 μs pulse is only for mode S transponders.
(d) The mode S discrete addressing interrogation takes yet another form. For this
interrogation the rotating beam antenna transmits pulses P1, P2, and P6. P1 and
P2 are 0.8 μs pulses spaced 2 μs between leading edges. P6 is a single pulse that
is either 16.00 or 30.00 μs long. A data technique known as DPSK decodes the
information transmitted in the P6 pulse. This technique involves the detection of the
phase relationship of the signal at certain intervals. These intervals are referred to
as chips. Therefore, timing is the critical factor in this decoding process. Each chip is
defined as an unmodulated interval of 0.25 μs and may be in phase or out of phase
with the preceding chip. If it is out of phase, it is recognized as representing a bit
value of 1. A chip that is in phase with the preceding chip represents a bit value of 0.
(e) As shown in Figure 10/GRAPHIC 34-50-96-99B-077-A01, P6 begins 1.5 μs after
the start of pulse P2. At 1.25 μs after the start of P6, the first phase reversal (pr)
occurs. This first pr is identified as the sync phase reversal (spr). 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.
(f) The ground mode S interrogator system uses a monopulse processing scheme to
determine the azimuth bearing to the airplane. 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 airplane. 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 airplane
from the antenna beam centerline. The address (derived from the reply) and
location (azimuth and range) of the mode S airplane is entered into a roll-call file.
This file can be visualized as a list of the mode S-equipped airplanes within their
assigned airspace. On a later scan, the mode S airplane 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.
(g) When a mode S-equipped airplane moves from one assigned airspace into another,
the first ground interrogator can communicate with the next interrogator and pass
airplane 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 airplane and the second interrogator will schedule discrete roll-call
interrogations for that airplane as needed. This technique makes it possible to
increase the airplane handling capacity of the ground interrogator.
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(h) 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 airplane on the roll-call list. This enables a second
ground interrogator to acquire an airplane into its assigned airspace using the
all-call technique as previously described.
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Mode S, SSR Antenna Radiation Pattern
Figure 12/GRAPHIC 34-50-96-99B-079-A01
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(4) Mode S Transponder Replies
(a) Typically, the ground-based interrogator tracks an airplane throughout its assigned
airspace. The mode S transponder equipped airplane 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 illustrated in Figure 13/GRAPHIC 34-50-96-99B-080-A01. 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. In addition to the message data contained within
each reply transmission, the mode S interrogation also contains a 24-bit discrete
address. This uniquely identifies the reply and provides for a large number of
airplanes, each with its own distinct address. The mode S reply format is described
in the following paragraphs.
Mode S, Transponder Reply Code Pulse Format
Figure 13/GRAPHIC 34-50-96-99B-080-A01
(5) Mode S Reply Description
(a) The reply pulse pattern is shown in Figure 13/GRAPHIC 34-50-96-99B-080-A01.
The reply data block is formed by PPM encoding of the reply data. The first pulse
occurs 128 μs after the start of the P4 interrogation pulse. The mode S transponder
reply to an ATCRBS interrogation is identical to the reply transmitted by a non mode
S transponder (see Figure 7/GRAPHIC 34-50-96-99B-074-A01). However, the reply
to a mode S interrogation can assume several different formats as summarized
in Figure 14/GRAPHIC 34-50-96-99B-081-A01. The fields are described in the
following paragraphs.
Announced Address (AA)
The 24-bit AA field contains the airplane address in the clear (no special
coding) and is used in DF number 11.
Altitude Code (AC) Field
The 13 bit AC field contains the altitude code and is used in downlink format
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(DF) numbers 0, 4, 16, and 20. The field is similar to that shown in Figure
7/GRAPHIC 34-50-96-99B-074-A01 except that the X bit is defined as the M
bit. 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.
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 interrogations and
downlink replies (except for DF number 11).
Capability, Transponder (CA) Field
The 3 bit CA field reports transponder capability and is used in DF number 11,
i.e. the Mode S All Call reply. The CA codes are defined as follows:
CA
1-3
DESCRIPTION
No communications capability (surveillance only)
Not used
Comm A and Comm B capability, ability to set code 7 on the ground
Comm A and Comm B capability, ability to set code 7 airbourne
Comm A, Comm B, ability to set code 7 on the ground or airbourne
Indicates DR is not = 0; or FS = 2, 3, 4, or 5, either airborne or on ground
CA codes 1 - 3 were used by earlier mode S transponders that did not have the
ability to set code 7.
Crosslink Capability (CC) Field
This 1-bit CC field indicates the ability of the transponder to support the
crosslink capability, i.e. decode the contents of the BDS field in UF number 0
interrogation and respond with the contents of the specified ground-initiated
Comm B register in the MV field of the corresponding DF number 16 reply.
Codes are: logic 0 if aircraft supports crosslink capability; logic 1 if aircraft
cannot support crosslink capability.
Downlink Format (DF)
Field DF is a general term referring to the first field in all downlink format and is
the transmission descriptor in all replies. DF refers to all messages described
in Figure 14/GRAPHIC 34-50-96-99B-081-A01.
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Downlink Request (DR) Field
The 5 bit DR field is used to request extraction of downlink messages from the
transponder by the interrogator. The codes are defined as follows:
DR
8 - 15
16 - 31
Flight Status (FS) Field
The 3 bit FS field reports the flight status of the
airplane. The codes are defined as follows:
FS
6-7
DESCRIPTION
No downlink request
Request to send Comm B message
TCAS information available
TCAS information available and request to send Comm B message
Comm B broadcast #1 available
Comm B broadcast #2 available
TCAS information and Comm B broadcast #1 available
TCAS information and Comm B broadcast #2 available
(Not assigned)
Comm D, not implemented in TDR-94/94D Class 3A
Mode S Transponders
ALERT
SPI
no
no
no
no
yes
no
yes
no
yes
yes
no
yes
(Not assigned)
AIRBORNE/ON THE GROUND
airborne
on the ground
airborne
on the ground
either
either
Identification (ID) Field
The 13 bit ID field contains the 4096 identification code as selected
by the operator.
10 ELM Control (KE) Field
The 1 bit KE field defines the content of the ND and MD fields in Comm D
replies, i.e. DF number 24. This function is not implemented in the
TDR-94/94D Class 3A Mode S Transponders.
11 Message Comm B (MB) Field
The 56 bit MB field contains messages transmitted to the interrogator. In those
formats that use the ground initiated Comm B protocol, the MB field contains
an 8 bit subfield (BDS) defining the contents of the Comm B message. BDS is
expressed in two 4-bit groups identified as BDS1 and BDS2.
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12 Extended Squitter Message (ME) Field
The 56 bit ME field is used to transmit extended squitter Automatic Dependent
Surveillance (ADS) and Aircraft Identification (AI) in DF number 17 messages.
13 Message Comm V (MV) Field
The 56 bit MV field contains information used in the air to air exchanges
between mode S transponders and is part of the long special surveillance reply
using DF number 16. Note that this message field does not follow the
Comm B protocol.
14 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. It is not implemented in the
TDR-94/94D Class 3A Mode S Transponders.
15 Parity/Interrogator Identity (PI) Field
The 24 bit PI field contains the parity overlaid on the interrogator identity code.
16 Reply Information (RI) Field
The 4 bit RI field (used in special surveillance replies DF
numbers 0 and 16) reports the airspeed capability and type of
reply to an interrogating airplane. Codes are defined as follows:
DESCRIPTION
No on-board TCAS
(Not assigned)
On-board TCAS with resolution capability inhibited
On-board TCAS with vertical-only resolution capability (TCAS II)
On-board TCAS with vertical and horizontal resolution capability
(TCAS III)
5 - 7 (Not assigned)
8 - 15 Indicates that downlink is an acquisition reply,
further defined as follows:
No maximum airspeed data available
Airspeed up to 75 knots
10
Airspeed is greater than 75, up to and including 150 knots
11
Airspeed is greater than 150, up to and including 300 knots
12
Airspeed is greater than 300, up to and including 600 knots
13
Airspeed is greater than 600, up to and including 1200 knots
14
Airspeed is greater than 1200 knots
15
(Not assigned)
RI
Bit 14 of this field is the AQ bit of the interrogation.
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17 Sensitivity Level (SL) Field
This 3-bit UM field reports the sensitivity level at which the TCAS unit
is currently operating. This field appears in special surveillance
reply formats DF numbers 0 and 16 (for TCAS compatible
transponders only). The codes are defined as follows:
No TCAS sensitivity level reported
TCAS is operating at sensitivity level
TCAS is operating at sensitivity level
TCAS is operating at sensitivity level
TCAS is operating at sensitivity level
TCAS is operating at sensitivity level
TCAS is operating at sensitivity level
TCAS is operating at sensitivity level
Note the SL field has no meaning for aircraft that set RI = 0, 1, or 2 (no on
board capability to generate resolution advisories).
18 Utility Message (UM) Field
The 6 bit UM field contains transponder status readouts and are
used in DF numbers 4, 5, 20, and 21.
19 Vertical Status (VS) Field
The 1 bit VS field indicates the airplane is airborne (VS = 0), or the airplane is
on the ground (VS = 1). This field is used in DF numbers 0 and 16.
20 Free and Unassigned Coding Space Fields
Free coding space contains all zeros as transmitted by the interrogators
and transponders. Unassigned coding space existing within fields
is reserved for possible future use.
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Mode S, Reply Code Summary
Figure 14 (Sheet 1 of 2)/GRAPHIC 34-50-96-99B-081-A01
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Mode S, Reply Code Summary
Figure 14 (Sheet 2 of 2)/GRAPHIC 34-50-96-99B-081-A01
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TDR-94, PART NO 622-9352
SUBTASK 34-50-96-870-005-A01
E. Typical TDR 94/94D ATC/Mode S Transponder Installations
(1) Introduction
(a) This paragraph gives you an overview of the TDR 94/94D operating environment.
For installation detail, refer to the TDR 94/94D ATC/Mode S Transponder,
Installation Manual which is contained in the Collins Pro Line II Comm/Nav/Pulse
System Installation Manual, CPN 523-0772719.
(b) The TDR 94/94D ATC/Mode S Transponder offers a wide range of installation
options. First you should recognize the difference between the TDR 94 and the
TDR 94D; the TDR 94 is for single antenna installations, while the TDR 94D can
operate with single or dual antenna installations. You are likely to find the TDR 94D
in most TCAS installations because dual antennas are required in TCAS.
(c) Both transponders can accept control data in CSDB or ARINC 429 format; this is
set at installation by means of special external straps and is determined by the type
of control being used.
(d) The following paragraphs and accompanying diagrams describe various installation
configurations. The first diagram, Figure 15/GRAPHIC 34-50-96-99B-082-A01,
shows the various strapping options that must be considered for all installations.
These strapping options are applicable to all installations even though they are
not shown on the other block diagrams.
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TDR-94, PART NO 622-9352
TDR-94/94D ATC Mode S Transponder Strapping Options
Figure 15/GRAPHIC 34-50-96-99B-082-A01
(2) TDR-94 with CSDB Code Selection
(a) Figure 16/GRAPHIC 34-50-96-99B-083-A01 shows a TDR 94 installation with a
CTL 92/92A CSDB transponder control unit and an altitude encoder. This type
of encoder typically supplies altitude data in Gillham code (ARINC 572) format.
The encoder data can be supplied to the CTL 92/92A or directly to the TDR 94.
However, because the encoder is likely to be located in the radio rack, with or near
the transponder, most installations will have the encoder connected directly to the
transponder to keep the wire run short.
(b) Figure 17/GRAPHIC 34-50-96-99B-084-A01 shows an installation using a Central
Air Data Computer (CADC) for altitude data which is similar to Figure 16/GRAPHIC
34-50-96-99B-083-A01. In each of these cases, external strapping is required
according to the type of altitude data being used.
(c) 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 of Figure 15/GRAPHIC
34-50-96-99B-082-A01.
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(d) In TCAS installations using Gillham code encoders, two independent encoders
are required for monitoring redundancy and integrity. In this case, one encoder is
connected to the transponder, while the other supplies data to the CTL-92/92A. In
the control the altitude data is converted to CSDB data which is supplied to the
CTL-92T. The CSDB data is converted here to ARINC 429 and supplied to the
transponder. In the transponder the altitude from the directly-connected encoder is
compared to the ARINC 429 data from the other encoder. If the two altitude sources
do no agree within 500 feet, a diagnostic code is generated.
TDR-94 ATC/Mode S Transponder, with CTL-92/92A Transponder Control
Unit, Typical Installation Diagram
Figure 16/GRAPHIC 34-50-96-99B-083-A01
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TDR-94, PART NO 622-9352
TDR-94 ATC/Mode S Transponder, With CTL-92/92A Transponder Control and CADC
Altitude Source, Typical Installation Diagram
Figure 17/GRAPHIC 34-50-96-99B-084-A01
(3) TDR-94D with CSDB Code Selection and Dual Antenna Operation
(a) Figure 18/GRAPHIC 34-50-96-99B-085-A01 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 16/GRAPHIC
34-50-96-99B-083-A01. Either way, appropriate strapping is required. The
CTL-92T, a requirement for TCAS control, is connected between the TDR-94D and
the CTL-92/92A. In this installation, transponder control data is entered on the
CTL-92/92A, and the TCAS control data is added to the data word in the CTL-92T.
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TDR-94, PART NO 622-9352
TDR-94D ATC/Mode S Transponder, Datalink and TCAS Installation, With CSDB Control
and CADC Altitude Data Source, Typical Installation Diagram
Figure 18/GRAPHIC 34-50-96-99B-085-A01
(4) TDR-94D/TCAS with ARINC 429 Code Selection and Dual Antenna
(a) Figure 19/GRAPHIC 34-50-96-99B-086-A01 shows a TDR 94D in a relatively
complex installation. This can be seen as a typical TCAS and data link installation
using an ARINC 429 source for code selection.
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TDR-94, PART NO 622-9352
TDR-94D ATC/Mode S Transponder, with ARINC 429 Tuning Source, Typical Installation Diagram
Figure 19/GRAPHIC 34-50-96-99B-086-A01
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TDR-94, PART NO 622-9352
TASK 34-50-96-870-807-A01
7. Integrated Circuit Descriptions
A. The TDR-94/94D uses numerous types of integrated circuits. Always refer to the Illustrated
Parts List (IPL) when replacement parts are necessary. Table 8/Table 34-50-96-99A-039-A01
shows the different types of integrated circuits that the TDR-94/94D uses. Refer to the
manufacturer's data manuals (or WEB sites) if special data is necessary.
IC TYPE
DESCRIPTION
Refer to Figure
20/GRAPHIC 3450-96-99B-087-A01
Basic Logic Gate Descriptions
Refer to Figure
21/GRAPHIC 3450-96-99B-088-A01
Basic Operational Amplifier Descriptions
02
+5V Precision Voltage Reference/Temperature Transducer
117
Adjustable 3-Terminal Positive Voltage Regulator (1.2 to 37V)
1596
Balance Modulator ෥ Demodulator Microcircuit
1825
High Speed Pulse Width Modulator Regulator
10135
2X J-K Master/Slave Flip Flop
12093
Low Power Prescaler
2222A
4X 2222A Transistor Package
22V10C
Programmed PAL
26LS32
4X Differential Line Receiver
28HC256
32k x 8-Bit EEPROM
29F010
128k x 8-Bit Flash Memory
3127
High Frequency Low Current Transmitter Array
317L
Adjustable Positive Voltage Regulator
31015
ARINC 429 Receiver/Transmitter ASIC
580
Voltage Reference
7C109
128k x 8-Bit Static RAM
7C291L
Programmed 2k x 8-Bit UV EPROM
7C291L
Programmed 2k x 8-Bit UV EPROM
7130
1k x 8-Bit Dual Port Static RAM
Integrated Circuit Descriptions Cont.
Table 8/Table 34-50-96-99A-039-A01
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IC TYPE
DESCRIPTION
74AHC1G04
Inverting Buffer
74HC259
8-Bit Addressable Latch/1 of 8 Decoder
74HC373
Octal 3-State Inverting D-Type Transparent Latch
74HC74
Dual D-Type Flip Flop with Set and Reset
74HCT244
Octal 3- State Buffer
74AC245
Octal Bus Transceiver, 3-State Non-Inverting
74AC374
Octal D-Type Flip Flop with 3-State Outputs
74HCT74
Dual D-Type Flip Flop
7800-10B
Pulse Decoder Gate Array
80C196KC
16-Bit Microcontroller
831-7172-001
Programmed FPGA
835-1681-030
Memory Decode and Mux Logic Microcircuit
9638
Dual Differential Line Driver
9665-052
Message Processor Gate Array
AD580TH
Low Drift Voltage Reference
AS214-92
0.1-3 GHz SPDT Switch
ATtiny 13
Programmed 8-Bit Microcontroller
ERA-2SM
RF/MMIC Surface Mount Amplifier
ERA-5SM
RF/MMIC Surface Mount Amplifier
JMS-5LH
Double Balance RF Mixer (Surface Mount Package)
LM235
Temperature Sensor
LM317M
Adjustable Positive Voltage Regulator
LMX2326TM
Frequency Synthesis Phase-Lock Loop Microcircuit
M27C256B-70C6
Programmed 32k x 8-Bit UV EPROM
MAX2606EUT-T
Voltage-Controlled Oscillator Microcircuit
MAX693A
Microprocessor Supervisory Circuit
MB1501
Serial Input Phase-Lock Loop Frequency Synthesizer
MC149680
Modulator/Demodulator Microcircuit
MC74HC4316AD
Quad Switch Microcircuit
MMPQ2907
Quad General Purpose PNP Transistor Package
Integrated Circuit Descriptions Cont.
Table 8/Table 34-50-96-99A-039-A01
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IC TYPE
DESCRIPTION
MSA-0686
RF/MMIC Amplifier Microcircuit
MSA-386
RF/MMIC Amplifier Microcircuit
RF MIXER
Double Balance RF Mixer (Surface Mount Package)
RMS-5
Double Balance RF Mixer (Surface Mount Package)
SGA-4586
Cascadeable 50-Ohm Amplifier
SL1451
Wide-Band Phase Lock Loop FM Detector
SN74BNT2244ADB
Octal Buffer and Line/MOS Drivers with 3-State Outputs
UPC1663GV
Ultra Wide-Band Amplifier
UPC2712TB
MMIC Wide-Band Amplifier
Integrated Circuit Descriptions
Table 8/Table 34-50-96-99A-039-A01
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Basis Logic Gate Descriptions
Figure 20/GRAPHIC 34-50-96-99B-087-A01
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Basis Operational Amplifier Descriptions
Figure 21/GRAPHIC 34-50-96-99B-088-A01
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TDR-94, PART NO 622-9352
TESTING AND FAULT ISOLATION
TASK 34-50-96-700-801-A01
1. Introduction
A. Performance (customer acceptance) test procedures, calibration procedures, and
schematics for the -004, -005, -006, -007, -008, -108, -308, -309, -408, and -409 statuses of
the TDR-94/94D Mode S Transponder are provided in this section.
TASK 34-50-96-700-802-A01
2. Test Equipment
A. Refer to the Special Tools, Fixtures, and Equipment section for information on the test
equipment required.
TASK 34-50-96-700-803-A01
3. Test Procedures
SUBTASK 34-50-96-700-001-A01
A. Use of Test Procedures
NOTE: Testing is restricted to only authorized Rockwell Collins service centers.
(1) Use Table 1001/Table 34-50-96-99A-009-A01, Final Performance (Customer
Acceptance) Test to determine if the TDR-94/94D is operating properly. Use the
alignment procedures in Table 1002/Table 34-50-96-99A-010-A01 to calibrate the
TDR-94/94D.
SUBTASK 34-50-96-700-002-A01
B. Final Performance (Customer Acceptance) Test
(1) The Final Performance (Customer Acceptance) Test, Table 1001/Table
34-50-96-99A-009-A01, is performed with the cover on the unit and provides a relatively
high degree of assurance that the TDR-94/94D is properly operating. The final
performance test is essentially a return-to-service test. The final performance test
can also be used as a customer acceptance or receiving inspection test. After any
repairs, all final performance test steps must be successfully completed with the cover
installed before returning a unit to service. The final performance test can also be used
to isolate a fault to a functional area, thus determining which alignment procedures
may be applicable. Some of the performance criteria have been adjusted to allow for
the tolerances of typical test equipment.
SUBTASK 34-50-96-700-003-A01
C. Detailed Performance Test
(1) The detailed performance test is combined with the final performance test in Table
1001/Table 34-50-96-99A-009-A01.
34-50-96
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ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
SUBTASK 34-50-96-700-004-A01
D. Alignment Procedures
(1) Refer to Table 1002/Table 34-50-96-99A-010-A01 for the alignment procedures for
the TDR-94/94D. If the final performance (customer acceptance) test successfully
completes, no alignment procedures are required.
TASK 34-50-96-810-801-A01
4. Fault Isolation
SUBTASK 34-50-96-810-001-A01
A. Fault Isolation Philosophy
CAUTION: REFER TO ADVISORIES PARAGRAPH IN THE INTRODUCTION FOR
ESDS HANDLING CAUTION AND COMPONENT WARNING.
(1) This section provides the primary information that repair personnel should use to isolate
faults in the TDR 94/94D. All sections of this manual have important data to aid in the
total repair and understanding of the unit. These sections are referenced, as necessary,
to facilitate completion of the repair tasks.
(2) Defective avionics equipment will usually fall into one of two categories: failure with a
specific complaint and failures with an unspecified complaints. The function of this
section is to guide fault isolation, first to a specific malfunction, then to the applicable
circuit area. Voltages and waveforms, in addition to the theory of operation help the
technician to isolate the faulty parts.
(3) Fault isolation and troubleshooting are performed using the test equipment listed in the
Special Tools, Fixtures, Equipment and Consumables section of this manual.
SUBTASK 34-50-96-810-002-A01
B. Troubleshooting Approach
(1) Unspecified Complaint
(a) Troubleshooting a unit with an unspecified complaint requires the technician to test
the unit according to the performance test to determine if a fault actually exists. In
cases where the unit passes all portions of the test and no fault is discovered, the
unit can be returned to the aircraft as good and reinstalled. However, an actual fault
may still persist and all associated equipment and aircraft wiring should be checked.
(b) When a unit does fail the performance test, the next objective is to isolate the actual
fault or faults, and begin in-depth troubleshooting procedures. Begin by performing
the specific fault isolation procedure(s) in this section.
34-50-96
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ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
(2) Specified Complaint
(a) Maintenance tags that indicate specific complaints help expedite the troubleshooting
process. The technician may, in many cases, choose to omit the performance test
and proceed directly to the any applicable fault isolation procedure.
SUBTASK 34-50-96-810-003-A01
C. Troubleshooting Aids
(1) Maintenance Aid Diagrams - Maintenance aid diagrams are provided in the Schematics
and Wiring Diagrams section of this manual, facing the schematic diagrams, to aid in
component location and identification/location of test points. Waveforms (if applicable)
are shown at troubleshooting test points.
(2) Maintenance Aid and Schematic Change Pages - Maintenance Aid and Schematic
Change Pages are included in the Schematic and Wiring Diagrams section of this
manual to provide information on schematic changes necessitated by production
changes of service bulletin modifications.
(3) Schematic Diagrams - Schematic diagrams are provided in the Schematic and Wiring
Diagrams section of this manual as an aid to signal tracing and fault isolation.
(4) Fault Isolation and Diagnostic Procedures - Digital circuit card troubleshooting will be
accomplished using standard digital troubleshooting techniques with standard test
equipment.
34-50-96
Page 1003/1004
May 18/06
34-50-96
TDR-94/94D Test Setup Diagram (Preferred Method)
Figure 1001/GRAPHIC 34-50-96-99B-020-A01
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
Page 1005/1006
May 18/06
34-50-96
TDR-94/94D Test Setup Diagram (Alternate Method)
Figure 1002/GRAPHIC 34-50-96-99B-036-A01
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
Page 1007/1008
May 18/06
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
TASK 34-50-96-810-802-A01
5. Procedures
SUBTASK 34-50-96-810-004-A01
A. TDR-94/94D Final Performance (Customer Acceptance) Test Procedure
STEP
PROCEDURE
DESIRED RESULTS
0.0
SETUP INSTRUCTIONS
0.1
Preferred Setup: Connect TDR-94/94D as shown in Figure
1001/GRAPHIC 34-50-96-99B-020-A01. Test equipment
item numbers (XX) that appear in the illustration identify
test equipment in Table 9002/Table 34-50-96-99A-032-A01
of the Special Tools, Fixtures, and Equipment section.
Alternate Setup: Connect TDR-94/94D as shown in Figure
1002/GRAPHIC 34-50-96-99B-036-A01. Test equipment
item numbers (XX) that appear in the illustration identify test
equipment in the Special Tools, Fixtures, and Equipment
section Table 9003/Table 34-50-96-99A-042-A01.
NOTE: Interrogation power levels and transmitter output
power are referenced to the rear connector(s)
of the unit under test (UUT). The insertion loss
of coaxial cables between the UUT and the test
equipment must be accounted for.
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
Page 1009
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ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
0.2
PROCEDURE
DESIRED RESULTS
AUTOMATIC TEST EQUIPMENT (FINAL) TESTS
Preferred Setup: The TDR-94 and TDR-94D are
“semi-automatically” tested on a station configured per Figure
1001/GRAPHIC 34-50-96-99B-020-A01 and Table 9002/Table
34-50-96-99A-032-A01. Test software is listed in Table
9002/Table 34-50-96-99A-032-A01. Insert Disk 1 and run
SETUP procedure.
Alternate Setup: The TDR-94 and TDR-94D are
"semi-automatically" tested on a station configured per Figure
1002/GRAPHIC 34-50-96-99B-036-A01and Table 9003/Table
34-50-96-99A-042-A01. Test software is listed in Table
9003/Table 34-50-96-99A-042-A01. Insert Disk 1 and run
SETUP procedure.
NOTE: Software is written/used by the factory, and may
contain specifications which are actually tighter than
required per the performance test requirements
(ptr). Therefore, refer to this test document for test
specifications for those automatic tests which fail.
0.3
IFR S-1403DL SETUP INFORMATION
The IFR S-1403DL test set must have C-Menu setup information
stored into memory for proper operation. Ensure that all
S-Menus (including S-Menu 00) are turned off. Set the following
C-Menu configuration and save it to store locations 1 and 2.
C-10
C-50
C-71
C-72
C-73
C-74
C-75
C-76
0.4
"f01 ATC" ANT B "off"
Counts "10s"
Trig Source "Selfinterr"
All On, Cal
All On
All On
ANT A mod source: "Int", ANT A Enable: "On"
S menu Radix: Octal
TEST CONDITIONS
Final data is to be taken after a 30 minute warm-up with
primary power applied. Perform the setup instructions in Table
1002/Table 34-50-96-99A-010-A01 for standard switch settings
prior to running an automatic test.
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
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ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
0.5
PROCEDURE
DESIRED RESULTS
BUS NAMING CONVENTIONS
When reading this test procedure, the terms CSDB and PLII
are used interchangeably to denote the Commercial Standard
Digital Bus, commonly known as the Pro-Line II bus at Rockwell
Collins, Inc.
The ARINC 429 data bus is commonly called the ARINC bus or
the 429 bus and either term may appear in documentation.
Selection of busses from the test software will refer to port "A"
as port 0, port "B" as port 1, and port "C" as port 2.
1.0
RECEIVER TESTS
Perform the following tests on both the top and bottom antenna
ports for the TDR-94D. For the TDR-94, perform only those
tests specified for the bottom channel.
1.1
MTL Test
Test MTL is defined as the minimum interrogation power level
which produces a reply rate of at least 90%.
Determine the minimum interrogation level (MTL) required to
obtain at least a 90% reply rate for the following interrogations.
Verify that these levels are between -75 and -79 dBm.
TOP
_____
_____
_____
Interrogations
A. MODE-S only All-Call
B. ATCRBS MODE-A/MODE-S All-Call
C. ATCRBS MODE-C
NOTE: If the MTL cannot be established within the specification
limits, A7R127 and/or A7R137 (CPN 833-6008-020)
may be added as required to adjust temperature
compensation. Refer to the A7 maintenance aid
diagram for component location. This information is
provided for reference only, after initial values are
determined in production, no further temperature
compensation adjustments should be necessary.
1.2
Sensitivity Variation with Frequency Test
Using ATCRBS MODE-C interrogations, ensure that MTL does
not vary by more than ±1 dB for interrogation frequencies
between 1029.8 and 1030.2 MHz.
BOTTOM
_____
_____
_____
NOTE: Refer to step 22.0 in
Table 1002/Table 3450-96-99A-010-A01,
Alignment Procedure.
TOP BOT
1029.8 MHz ____ ____
1030.2 MHz ____ ____
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
Page 1011
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ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
1.3
1.4
PROCEDURE
DESIRED RESULTS
Receiver Bandwidth Test
Vary the interrogation RF frequency to 1007, 1053, 1060, and
1150 MHz. Verify the MODE-A interrogation level, required to
produce 90% reply efficiency is greater than -17 dBm.
Dynamic Range Test
Verify a minimum reply rate of at least 90% for the following
interrogations at input signal levels of -73 dBm and -19 dBm.
Interrogations
A. MODE-S only All-Call
B. ATCRBS MODE-A/MODE-S All-Call
C. ATCRBS MODE-C
1.5
Signal level (dBm)
-73 dBm
-19 dBm
TOP BOT TOP BOT
___ ___ ___ ___
___ ___ ___ ___
___ ___ ___ ___
TOP
_____
_____
_____
BOTTOM
_____
_____
_____
Undesired Replies
For this test, squitter must be disabled by setting Self-Test Inhibit
discrete input, P2-38 (-004 thru -007) or P1-19 (-008, -108,
-308, -309, -408, -409) to ground. Turn off all interrogations.
Verify that the ATCRBS random replies are less than 5 per
second and the MODE-S replies are less than 1 per 10
seconds, averaged over a period of at least 30 seconds.
After this test, turn interrogations back on and remove the
ground from P2-38 or P1-19.
2.0
BOT
____
____
____
____
Sensitivity Limit Test
For the following interrogations at a -81 dBm input signal level,
verify that the reply rate does not exceed 10%.
Interrogations
A. MODE-S only All-Call
B. ATCRBS MODE-A/MODE-S All-Call
C. ATCRBS MODE-C
1.6
1007 MHz
1053 MHz
1060 MHz
1150 MHz
TOP
____
____
____
____
TOP BOT
ATCRBS ____ ____
MODE-S ____ ____
TRANSMITTER REQUIREMENTS
Unless otherwise specified, perform the following tests on both
the top and bottom antenna ports using a MODE-S test set. For
the TDR-94, you must do only the tests for the bottom antenna
port.
2.1
Transmitter Frequency Test
Ensure that the output transmitter frequency is 1090 ±0.5 MHz.
_____ MHz
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
Page 1012
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ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
2.2
PROCEDURE
DESIRED RESULTS
Transmitter Power Test
a. Interrogate ATCRBS interrogations at a rate of 450 per
second, or MODE-S interrogations at a rate of 50 per
second. Verify that the output transmitter power is between
315 and 500 watts measured at the strongest reply pulse.
Verify that the weakest pulse is within 1 dB of the strongest
for ATCRBS replies and within 2 dB for MODE-S replies.
Verify the weakest pulse exceeds 250 watts.
Strongest ATCRBS pulse Spec: 315 to 500 watts
Weakest ATCRBS pulse Spec: = strongest ±1 dB
Weakest MODE-S pulse Spec: = strongest ±2 dB
TOP
_____
_____
_____
BOTTOM
_____
_____
_____
TOP
_____
BOTTOM
_____
NOTE: Record the peak level of the strongest pulse in dBm to
use as a reference for measurements made in step 2.3.
CAUTION:
BEFORE PERFORMING STEP B, SEPARATE
THE TRANSMITTER MODULE FROM THE MAIN
CHASSIS AND DISCONNECT HIGH VOLTAGE
FROM THE TRANSMITTER. FAILURE TO DO
THIS WILL RESULT IN SEVERE DAMAGE TO
THE SPECTRUM ANALYZER. ALL COVERS
MUST REMAIN INTACT FOR DATA TO BE VALID.
b. Connect the transmitter output directly to the spectrum
analyzer. Ensure that the 1090 MHz L.O. leakage from the
antenna port is less than -70 dBm when not transmitting.
Reconnect high voltage to the transmitter and reassemble
the transmitter module to the main chassis after completing
the test.
1090 MHz L.O. leakage Spec: less than -70 dBm
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
Page 1013
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ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
2.2
(Cont)
PROCEDURE
DESIRED RESULTS
(This test applies to TDR-94D only.)
c. Set the self-test inhibit discrete to active to prevent
squittering. Ensure that the transmitter power output of the
nonselected antenna is attenuated at least 20 dB relative
to the selected antenna during the time the transmitter is
transmitting on the other antenna port. Set the self-test
inhibit discrete to disable after completing the test.
Nonselected antenna power Spec: MIN. 20 dB attenuation
2.3
2.4
_____
Transmitter Spectrum and Reply Pulse Shape
Set up to transmit only MODE-S replies at 50/second. Observe
the output spectrum with a spectrum analyzer. Use a 100-kHz
resolution bandwidth or less. Use the peak level reference
recorded in step 2.2. for the measurements below. Verify the
spectrum does not exceed the following limits:
Frequency Difference
(MHz from Carrier)
Spec:
>=
>=
>=
>=
20
40
60
1.3 and <7
7 and <23
23 and <78
78
Max Relative Response
(dB down from peak ref)
TOP
BOTTOM
_____
_____
_____
_____
_____
_____
_____
_____
Reply Pulse Shape
For both ATCRBS and MODE-S replies, verify that the pulse
rise time is less than 100 ns and that the pulse decay time is
less than 200 ns.
ATCRBS
MODE-S
TOP
BOTTOM
RISE FALL RISE FALL
____ ____ ____ ____
____ ____ ____ ____
If these results are not met,
select A3C216 test select
value from page 10150 (figure
6) to get results into specs.
2.5
Burst Tests
For these tests, verify correct replies and output power for all
interrogations.
2.5.1
ATCRBS Burst Tests
Verify that at least 120 ATCRBS 15-pulse replies can be
generated in 100 ms. Repeat the test at a once per second rate.
TOP
_____
BOTTOM
_____ (x)
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
Page 1014
Mar 14/08
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
2.5.2
PROCEDURE
DESIRED RESULTS
MODE-S Burst Tests
Verify the following MODE-S reply capabilities:
50 MODE-S replies in a 1-second interval including
at least 16 long replies.
TOP
_____
BOTTOM
_____ (x)
18 MODE-S replies in a 100-ms interval including
at least 6 long replies.
_____
_____ (x)
8 MODE-S replies in a 25-ms interval including at
least 4 long replies.
_____
_____ (x)
_____
_____ (x)
4 MODE-S replies in a 1.6-ms interval including at
least 2 long replies.
2.6
MODE-A Reply Format, Ident Interval, and Reply Delay
Inject a normal MODE-A interrogation on the bottom channel
only. Select 7777 ident code on the test bench control head
simulator (computer). Verify IFR displays a 7777 code. Ensure
the downlink first framing pulse occurs 3.00 ±0.45 ˩s after the
P3 leading edge of the interrogation input. Momentarily activate
the Ident switch and verify that the SPI pulse is present for 18
±2 seconds. Verify that the ATCRBS Downlink modulation has
pulse widths of 0.45 ±0.05 ˩s. Verify the following spacings
from the first framing pulse. All spacing and width tolerances
are ±50 ns. Repeat the reply delay test on the top channel
(TDR-94D only).
Downlink first framing pulse.
Spec: 3.00 ±0.45 ˩s after P3 input
TOP
_____ ws
BOTTOM
_____ ws
SPI pulse time
Spec: 18 ±2 seconds
BOTTOM
_____ s
ATCRBS Downlink pulse width
Spec: 0.45 ±0.05 ˩s
BOTTOM
_____ ws
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
Page 1015
May 18/06
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
PROCEDURE
2.6
(Cont)
Reply Pulse
C1
A1
C2
A2
C4
A4
B1
D1
B2
D2
B4
D4
2ND framing pulse
SPI
2.7
MODE-C Reply Format and Reply Delay
DESIRED RESULTS
BOTTOM
_______ (x)
_______ (x)
_______ (x)
_______ (x)
_______ (x)
_______ (x)
_______ (x)
_______ (x)
_______ (x)
_______ (x)
_______ (x)
_______ (x)
_______ (x)
_______ (x)
Position (˩s)
1.45 ±50 ns
2.90 ±50 ns
4.35 ±50 ns
5.80 ±50 ns
7.25 ±50 ns
8.70 ±50 ns
11.60 ±50 ns
13.05 ±50 ns
14.50 ±50 ns
15.95 ±50 ns
17.40 ±50 ns
18.85 ±50 ns
20.30 ±50 ns
24.65 ±50 ns
Interrogate with a normal MODE-C signal on the bottom
channel only. Select the Gillham discretes as the altitude
source by disconnecting rear connector P2 pins 41 and 42
from ground. Verify that F1 of the ATCRBS reply occurs 3.00
±0.45 ˩s after the interrogation P3 leading edge. Observe the
transmitted MODE-C reply. Verify that each of the Gillham ALT
bits will go low individually with a 39-k pull-down resistor. Use
the following table listed to locate the Gillham ALT bits. Repeat
the reply delay test on the top channel (TDR-94D only).
ATCRBS F1 spacing from P3
Spec: 3.00 ±0.45 ˩s
TOP
_____ ws
BOTTOM
_____ ws
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
Page 1016
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ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
PROCEDURE
DESIRED RESULTS
2.7
(Cont)
LOCATION
P1-1
P1-2
P1-3
P1-4
P1-5
P1-6
P1-7
P1-8
P1-9
P1-10
P1-11
Bit
Reply Pulse
Toggles
Spacing
(BOTTOM) from F1 (—s)
_____
17.40
_____
14.50
_____
11.60
_____
8.70
_____
5.80
_____
2.90
_____
18.85
_____
15.95
_____
7.25
_____
4.35
_____
1.45
_____
20.30
SIGNAL NAME
Gillham ALT B4
Gillham ALT B2
Gillham ALT B1
Gillham ALT A4
Gillham ALT A2
Gillham ALT A1
Gillham ALT D4
Gillham ALT D2
Gillham ALT C4
Gillham ALT C2
Gillham ALT C1
F2 (2nd Framing Pulse)
3.0
DECODER TESTS
Unless otherwise specified, perform the following tests at -74
dBm and -20 dBm interrogation levels at each antenna port.
3.1
MODE-A P3 Deviation Negative, Max
Interrogate MODE-A with a P3 deviation of -0.9 — s on the
appropriate channel. Verify that the reply rate is NOT GREATER
than 10%.
Signal level (dBm)
-74
-20
BOT _____
_____
TOP _____
_____
3.2
MODE-A P3 Deviation Positive, Max
Interrogate MODE-A with a P3 deviation of +0.9 — s on the
appropriate channel. Verify that the reply rate is NOT GREATER
than 10%.
Signal level (dBm)
-74
-20
BOT _____
_____
TOP _____
_____
3.3
MODE-A Pulse Width, Narrow
Interrogate MODE-A with 0.30 — s pulse width at a level of -45
dBm on the appropriate channel. Verify that the reply rate is
NOT GREATER than 10%.
Signal level (dBm)
-45
BOT _____
TOP _____
3.4
MODE-A Pulse Width, Normal
Interrogate MODE-A with 0.60 — s pulse width on the
appropriate channel. Verify AT LEAST 90% MODE-A replies
are transmitted.
Signal level (dBm)
-74
-20
BOT _____
_____
TOP _____
_____
3.5
MODE-A P3 Deviation Negative, Min
Interrogate MODE-A with a P3 deviation of -0.30 — s on the
appropriate channel. Verify AT LEAST 90% MODE-A replies
are transmitted.
Signal level (dBm)
-74
-20
BOT _____
_____
TOP _____
_____
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
Page 1017
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ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
PROCEDURE
DESIRED RESULTS
3.6
MODE-A P3 Deviation Positive, Min
Interrogate MODE-A with a P3 deviation of +0.30 — s on the
appropriate channel. Verify AT LEAST 90% MODE-A replies
are transmitted.
Signal level (dBm)
-74
-20
BOT _____
_____
TOP _____
_____
3.7
MODE-C P3 Deviation Negative, Max
Interrogate MODE-C with a P3 deviation of -0.90 — s on the
appropriate channel. Verify that the reply rate is NOT GREATER
than 10%.
Signal level (dBm)
-74
-20
BOT _____
_____
TOP _____
_____
3.8
MODE-C P3 Deviation Positive, Max
Interrogate MODE-C with a P3 deviation of +0.90 — s on the
appropriate channel. Verify that the reply rate is NOT GREATER
than 10%.
Signal level (dBm)
-74
-20
BOT _____
_____
TOP _____
_____
3.9
MODE-C P3 Deviation Negative, Min
Interrogate MODE-C with a P3 deviation of -0.30 — s on the
appropriate channel. Verify that the reply rate is AT LEAST 90%.
Signal level (dBm)
-74
-20
BOT _____
_____
TOP _____
_____
3.10
MODE-C P3 Deviation Positive, Min
Interrogate MODE-C with a P3 deviation of +0.30 — s on the
appropriate channel. Verify that the reply rate is AT LEAST 90%.
Signal level (dBm)
-74
-20
BOT _____
_____
TOP _____
_____
4.0
ATCRBS SLS TEST
Perform the following tests at MTL +3 dB or -74 dBm. Test also
at -60 dBm, -40 dBm, and -22 dBm input signal levels. Conduct
the following tests on the bottom antenna port for both TDR-94
and TDR-94D. Repeat the tests on the top antenna port of the
TDR-94D only.
4.1
MODE-C P2 at -1 dB
Interrogate with a MODE-C P1, P2, P3 triad with P2 at -1 dB.
Deviate the P2 position +0.2 and -0.2 — s. Verify that the reply
rate is NOT GREATER than 10%.
Signal level (dBm)
-74 -60 -40 -22
BOT __ __ __ __
TOP __ __ __ __
4.2
MODE-C P2 at -9 dB
Interrogate with a MODE-C P1, P2, P3 triad with P2 at -9 dB.
Verify that the reply rate is AT LEAST 90%.
Signal level (dBm)
-74 -60 -40 -22
BOT __ __ __ __
TOP __ __ __ __
4.3
MODE-C P2 at 0 dB
Interrogate with a MODE-C P1, P2, P3 triad with P2 at 0 dB.
Set P2 pulse width to 0.60 — s and verify that the reply rate is
NOT GREATER than 1%.
Signal level (dBm)
-74 -60 -40 -22
BOT __ __ __ __
TOP __ __ __ __
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
Page 1018
May 18/06
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
PROCEDURE
DESIRED RESULTS
4.4
MODE-A P2 at 0 dB
Interrogate with a MODE-A P1, P2, P3 triad with P2 at 0 dB.
Deviate the P2 position +0.65 — s and -0.65 — s and verify that
the reply rate is AT LEAST 90%.
4.5
SLS Suppression Interval
Interrogate with a P1, P2, ATCRBS suppression pair with P2
at 0 dB relative to P1. Follow with a normal MODE-A P1, P3
interrogation. Delay the second interrogation 26 — s from P2
of the first interrogation and verify that the reply rate is NOT
GREATER than 10%. Delay the second interrogation 44 — s
from P2 of the first interrogation and verify that replies are
generated in response to the second interrogation at a rate of
AT LEAST 90%.
5.0
Signal level (dBm)
-74 -60 -40 -22
BOT __ __ __ __
TOP __ __ __ __
Second interrogation delayed 26 — s. NOT GREATER than 10%
ATCRBS reply
________
Second interrogation delayed 44 — s. AT LEAST 90% replies
to second interrogation
________
MODE-S SLS TEST
Perform the following tests at MTL +3 dB or -73 dBm and also at
-22 dBm interrogation input signal levels applied to the bottom
antenna port. Repeat the test for the top antenna port of the
TDR-94D only.
5.1
P5 Greater than P6
Ensure that a P5 pulse overlaying the SPR (Sync Phase
Reversal) of a MODE-S interrogation results in a reply rate of
NOT GREATER than 10% if its amplitude is greater than P6
by 3 dB.
Signal level (dBm)
-73
-22
BOT _____
_____
TOP _____
_____
5.2
P5 Less Than P6
Ensure that a P5 pulse overlaying the SPR of a MODE-S
interrogation results in greater than 99% replies if its amplitude
is less than P6 by 12 dB
Signal level (dBm)
-73
-22
BOT _____
_____
TOP _____
_____
6.0
ALL-CALL DECODER TEST
Perform the following tests at MTL +1 dB or -75 dBm and also
at -22 dBm interrogation input signal levels. Unless otherwise
specified, test the bottom antenna port for the TDR-94, and
both antenna ports for the TDR-94D.
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
Page 1019
May 18/06
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
6.1
6.2
PROCEDURE
DESIRED RESULTS
P4 Pulse Width Variation, ATCRSB/MODE-S All-Call
a. Interrogate with a P1, P3, P4 ATCRBS/MODE-S ALL-CALL.
Vary the P4 pulse width from 1.45 to 1.75 — s. Ensure that
the downlink MODE-S reply rate exceeds 90%.
Signal level (dBm)
-75
-22
BOT _____
_____
TOP _____
_____
b. Ensure the downlink first preamble pulse occurs 128.00
±0.50 — s after the P4 pulse leading edge.
Signal level (dBm)
-75
-22
BOT _____
_____
TOP _____
_____
c. Ensure that the downlink modulation has proper spacing and
widths for the preamble and information pulses. All spacing
and width tolerances are ±30 ns.
Signal level (dBm)
-75
-22
BOT _____
_____
TOP _____
_____
MODE-S Address
Ensure that the MODE-S address bits will go low individually
with a 1.82-k pull-down resistor and remain high individually
with a 18.2-k pull-down resistor. Use the following table to
locate and address the MODE-S address bits.
NOTE: TDR-94/94D transponders -004 status and later, read
and accept the MODE-S Address during power-on
initialization only. If the MODE-S Address is changed
after power-on initialization, the address will not
be accepted for use in replies to interrogations.
Consequently, if the MODE-S Address provided to
the UUT is changed, power to the UUT may have to
be cycled before proceeding with this test.
NOTE: If the resistor pull-down tests are performed at an
assembly level test, the top-level test may substitute
a short-to-ground, or open circuit, for 1.82 k and
18.2 k , respectively. Conduct this test for the bottom
antenna port only and at a convenient input signal level.
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
Page 1020
May 18/06
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
6.2
(Cont)
PROCEDURE
SIGNAL NAME
MODE-S ADDR B1
MODE-S ADDR B2
MODE-S ADDR B3
MODE-S ADDR B4
MODE-S ADDR B5
MODE-S ADDR B6
MODE-S ADDR B7
MODE-S ADDR B8
MODE-S ADDR B9
MODE-S ADDR B10
MODE-S ADDR B11
MODE-S ADDR B12
MODE-S ADDR B13
MODE-S ADDR B14
MODE-S ADDR B15
MODE-S ADDR B16
MODE-S ADDR B17
MODE-S ADDR B18
MODE-S ADDR B19
MODE-S ADDR B20
MODE-S ADDR B21
MODE-S ADDR B22
MODE-S ADDR B23
MODE-S ADDR B24
LOCATION
P1-33
P1-34
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
DESIRED RESULTS
_____
_____
_____
_____
_____
_____
_____
_____
_____
_____
_____
_____
_____
_____
_____
_____
_____
_____
_____
_____
_____
_____
_____
_____
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
Page 1021
May 18/06
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
PROCEDURE
DESIRED RESULTS
6.3
P4 Pulse Width Variation, ATCRBS-ONLY ALL
Interrogate with a P1, P3, P4 ATCRBS-Only All-Call. Vary the
P4 pulse width from 0.60 to 1.00 — s. Verify that the reply rate
is NOT GREATER than 10%.
Signal level (dBm)
-75
-22
BOT _____
_____
TOP _____
_____
6.4
P4 Pulse Width Variation, ATCRBS/MODE-S ALL CALL
Interrogate with a P1, P3, P4 ATCRBS/MODE-S All-Call. Set
the P4 pulse width to 1.1 and 2.4 — s. Verify that the reply rate
is NOT GREATER than 10%.
Signal level (dBm)
-75
-22
BOT _____
_____
TOP _____
_____
6.5
P4 Minimum Pulse Width, ATCRBS-ONLY ALL CALL
Interrogate with a P1, P3, P4 ATCRBS-Only All-Call. Set P4
pulse width to 0.30 — s. Verify that an ATCRBS reply occurs
within 3.00 ±0.50 — s from P3, at a rate of AT LEAST 90%, and
the MODE-S reply rate is NOT GREATER than 10%.
Signal level (dBm)
-75
-22
BOT _____
_____
TOP _____
_____
10% or < MODE-S reply
90% or > ATCRBS reply
BOT
TOP
6.6
P4 Position Variation, ATCRBS/MODE-S ALL CALL
Interrogate with normal P1, P3, P4 ATCRBS/MODE-S All-Call
interrogations. Deviate the P4 position ±50 ns. Verify that the
All-Call replies are transmitted at a rate of AT LEAST 90%.
6.7
P4 Amplitude 6 dB Below P3
Interrogate with ATCRBS/MODE-S All-Call interrogations.
Adjust the P4 amplitude 6 dB below the amplitude of P3. Verify
that the MODE-S reply rate is NOT GREATER than 10% and
the ATCRBS rate is AT LEAST 90%.
10% or < MODE-S reply
90% or > ATCRBS reply
_____
_____
_____
_____
Signal level (dBm)
-75
-22
BOT _____
_____
TOP _____
_____
Signal level (dBm)
-75
-22
BOT _____
_____
TOP _____
_____
BOT
TOP
_____
_____
_____
_____
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
Page 1022
May 18/06
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
6.8
PROCEDURE
DESIRED RESULTS
P4 Deviation, ATCRBS/MODE-S ALL CALL
Interrogate with ATCRBS/MODE-S All-Call interrogations.
Deviate P4 ±0.30 — s and verify that the ATCRBS reply rate is
AT LEAST 90% and the MODE-S reply rate is NOT GREATER
than 10%.
Signal level (dBm)
-75
-22
BOT _____
_____
TOP _____
_____
10% or < MODE-S reply
90% or > ATCRBS reply
BOT
TOP
_____
_____
_____
_____
6.9
P4 Amplitude 1 dB Below P3
Interrogate with ATCRBS-Only All-Call interrogation having a
signal level of -73 dBm. Adjust the P4 amplitude 1 dB below
amplitude of P3. Verify that the reply rate is NOT GREATER
than 10%.
Signal level (dBm)
-73
BOT _____
TOP _____
7.0
MODE-S DECODER TEST
Perform the following tests at MTL +1 dB or -75 dBm and also
-22 dBm interrogation levels. Test the bottom antenna port of
the TDR-94, and both antenna ports of the TDR-94D. Set the
ADLP select to active. If air/ground discrete is set to airborne,
cycle power before beginning tests.
Signal level (dBm)
-75
-22
BOT _____
_____
TOP _____
_____
7.1
MODE-S Reply Delay
Interrogate with Uplink Format UF=11 interrogations. Verify that
the first downlink preamble pulse occurs 128.00 ±0.25 — s after
the SPR (Sync Phase Reversal) of the interrogation inputs.
Verify that the Downlink Response is DF=11.
7.2
SPR Deviation -Low
Interrogate with Uplink Format UF=11 interrogations. Deviate
the SPR position over +50 and -50 ns. Verify that the DF=11
downlink response rate is AT LEAST 90%.
+50 ns
-50 ns
Signal level (dBm)
-75
-22
BOT _____
_____
TOP _____
_____
BOT
TOP
_____
_____
_____
_____
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
Page 1023
May 18/06
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
7.3
PROCEDURE
DESIRED RESULTS
SPR Deviation -High
Interrogate with Uplink Format UF=11 interrogations. Deviate
the SPR position to +200 ns and -200 ns. Verify that the DF=11
downlink response rate is NOT GREATER than 10%.
Signal level (dBm)
-75
-22
BOT _____
_____
TOP _____
_____
+200 ns
BOT
TOP
-200 ns
7.4
UF = 5/DF = 5
Interrogate with Uplink Format UF=5 interrogations. Verify that
the downlink response is DF=5. Conduct this test for bottom
antenna port only and at a convenient input signal level.
_____
_____
_____
_____
BOTTOM _____
7.5
UF = 5 Different Address
Interrogate with Uplink Format UF=5 interrogations that have
an address different than that of the unit under test. Verify no
reply occurs other than normal DF=11 squitter transmissions.
Conduct this test for the bottom antenna port only and at a
convenient input signal level.
BOTTOM _____
7.6
UF = 21/DF = 21
Interrogate with Uplink Format UF=21 interrogations. Verify that
the downlink response is DF=21. Conduct this test for bottom
antenna port only and at a convenient input signal level.
BOTTOM _____
7.7
UF = 0, Max Airspeed
Interrogate with Uplink Format UF=0 interrogations. Verify
that the MAX AIR SPEED bits independently toggle in the
downlink response of DF=0 when discrete pins P2-43, 44, 45
are switched. Conduct this test for bottom antenna port only
and at a convenient input signal level.
BOTTOM _____
7.8
UF = 11, Low-Level
Interrogate with Uplink Format UF=11 interrogations that have
an input signal level at MTL or -76 dBm. Trigger the scope
from the generator output of the IFR. Connect the transmitter
jack of the IFR to the vertical scope channel. Use the delayed
sweep function of the scope to view the first reply pulse with a
horizontal rate of 50 ns/div. Verify the jitter of the pulse does not
exceed 160 ns total (±80 ns.).
Signal level (dBm)
-76
-22
BOT _____
_____
TOP _____
_____
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
Page 1024
May 18/06
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
8.0
PROCEDURE
DESIRED RESULTS
INTERFERENCE TEST
Perform the following tests for UF=11 MODE-S interrogations
at signal levels of -68 and -22 dBm. Inject an interference
pulse of 0.80 — s duration, at a carrier frequency of 1030 MHz,
but incoherent with the interrogation signal. Test the bottom
antenna port for the TDR-94, and both antenna ports for the
TDR-94D.
NOTE: For steps 8.1 and 8.2, the interference pulse
can be coincident with a group of 3 or more
phase transitions spaced 0.25 — s.
8.1
Interference Level 3 dB Less Than Signal Level
Verify that when the interference pulse overlays the MODE-S
interrogation anywhere after the Sync Phase Reversal, the reply
rate exceeds 50% if the interference amplitude is 3 dB less than
the interrogation signal level.
Signal level (dBm)
-68
-22
BOT _____
_____
TOP _____
_____
8.2
Interference Level 9 dB Less Than Signal Level
Verify that when the interference pulse overlays the MODE-S
interrogation anywhere after the MODE-S P1 pulse leading
edge, the reply rate is AT LEAST 90% if the interference
amplitude is 9 dB less than the interrogation signal level.
Signal level (dBm)
-68
-22
BOT _____
_____
TOP _____
_____
9.0
SQUITTER TEST
For this test, turn off the input interrogations.
9.1
Dual Antenna Squitter Rate
Ensure that squitter is generating a DF=11 (Acquisition Squitter)
reply at an average rate of 1.0 Hz, alternating between the top
and bottom antenna ports for the TDR-94D, and fixed on the
bottom antenna port for the TDR-94.
____ (check if okay)
9.2
Single Antenna Squitter Rate
Ensure that grounding the single antenna strap (by selecting
single antenna active on the test computer) prevents squitter
transmissions on the top antenna port, and that the bottom
antenna port alone continues to squitter at a 1.0-Hz rate.
____ (check if okay)
NOTE: Unit input power must be cycled to recognize the
Single Antenna Strap discrete change.
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
Page 1025
May 18/06
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
9.3
PROCEDURE
DESIRED RESULTS
Airborne Position Extended Squitter (-004 through -007 and
-207 status TDR-94/94D)
a. Ensure that neither Air/Ground Discrete #1 or #2 (P2-53
or P1-27) are connected to ground (i.e., establishes the
airborne state).
b. Via the GPS/GNSS Input Data Bus, provide the transponder
with the appropriate labels and data indicated in Figure
1003/GRAPHIC 34-50-96-99B-021-A01. Each data
parameter shall be updated at least once per second.
c. Verify that the transponder properly transmits an
“Even_Second" DF=17 Extended Squitter transmission that
has the exact structure for the 'ME" field as shown in Figure
1003/GRAPHIC 34-50-96-99B-021-A01.
d. Verify that the transponder properly transmits the Airborne
Position Message at random intervals that are uniformly
distributed over the range from 0.4 to 0.6 second.
e. Verify that the transponder properly transmits the Airborne
Position alternately from the top and bottom antenna ports
for the TDR-94D and from the bottom antenna port only for
the TDR-94.
f. Verify the transponder continues to transmit DF=11
Acquisition Squitters while continuing to transmit the
Airborne Position Squitter Messages as specified in previous
steps c, d, and e.
g. Maintain the data inputs as provided in step b with
the exception that the UTC Time input should be
changed to read as indicated in Figure 1003/GRAPHIC
34-50-96-99B-021-A01.
h. Verify that the transponder properly transmits an
"Odd_Second" DF=17 Extended Squitter transmission that
has the exact structure for the "ME" field shown in Figure
1003/GRAPHIC 34-50-96-99B-021-A01.
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
Page 1026
Nov 10/06
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
9.3A
PROCEDURE
DESIRED RESULTS
GPS Bus/Airborne Position Extended Squitter/Time Tag
Verification (-108 status TDR-94/94D only)
a. Ensure that neither Air/Ground Discrete #1 or #2 (P2-53
or P1-27) are connected to ground (i.e., establishes the
airborne state).
b. Ensure that neither Configuration Select discrete 0 or 1
(P1-28 or P1-17) are connected to ground.
c. Ensure that ARINC 429 label 203 is not present on the
selected Altitude Input Bus.
d. Provide the transponder with a GPS Time Tag signal via the
GPS Time Tag input (P2-37 high, P2-38 low). The GPS
Time Tag signal is a differential (0-5 Vdc) 1 ms pulse that
repeats once per second.
e. Via the GPS/GNSS Input Data Bus, provide the transponder
with the appropriate labels and data indicated in Figure
1004/GRAPHIC 34-50-96-99B-022-A01. Each data
parameter must be updated at least one time each second.
f. Verify that the transponder properly transmits an
Even-Second DF=17 Extended Squitter transmission that
has the exact structure for the "ME" field indicated in Figure
1004/GRAPHIC 34-50-96-99B-022-A01.
g. Verify that the transponder properly transmits the Airborne
Position Message at random intervals that are uniformly
distributed over the range from 0.4 to 0.6 seconds.
h. Verify that the transponder properly transmits the Airborne
Position alternately from the top and bottom antenna ports
of the TDR-94D and from the bottom antenna port only of
the TDR-94.
i. Verify that the transponder continues to transmit DF=11
Acquisition Squitters while continuing to transmit the
Airborne Position Squitter messages indicated in steps f,
g, and h. above.
j. Verify that the transponder properly transmits an Odd-Second
DF=17 Extended Squitter transmission that has the
exact structure for the "ME" field indicated in Figure
1004/GRAPHIC 34-50-96-99B-022-A01.
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
Page 1027
May 18/06
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
9.3B
PROCEDURE
DESIRED RESULTS
GPS Bus/Airborne Position Extended Squitter/Time Tag
Verification (-008 status TDR-94/94D only)
a. Ensure that neither Air/Ground Discrete #1 or #2 (P2-53
or P1-27) are connected to ground (i.e., establishes the
airborne state).
b. Ensure that neither Configuration Select discrete 0 or 1
(P1-28 or P1-17) are connected to ground.
c. Ensure that ARINC 429 label 203 is not present on the
selected Altitude Input Bus.
d. Provide the transponder with a GPS Time Tag signal via the
GPS Time Tag input (P2-37 high, P2-38 low). The GPS
Time Tag signal is a differential (0-5 Vdc) 1 ms pulse that
repeats once per second.
e. Via the GPS/GNSS Input Data Bus, provide the transponder
with the appropriate labels and data indicated in Figure
1004/GRAPHIC 34-50-96-99B-022-A01 (for step e of test
9.3A). Each data parameter must be updated at least one
time each second.
f. Interrogate the transponder with the MODE-S interrogations
indicated in Figure 1005/GRAPHIC 34-50-96-99B-023-A01
to request BDS register 0.5.
g. Verify that the transponder responds properly with two DF=20
replies that have the exact structures for the "MB" field
indicated in Figure 1005/GRAPHIC 34-50-96-99B-023-A01.
h. Repeat step f. as necessary.
i. Verify that the transponder responds properly with two DF=20
replies that have the exact structures for the "MB" field
indicated in Figure 1005/GRAPHIC 34-50-96-99B-023-A01.
NOTE:
9.3C
Steps h. and i. may have to be repeated to get an
odd encoding since the transponder alternates the
encoding of latitude and longitude data on odd and
even intervals at rates of either 100 or 200 ms.
GPS Bus / Airborne Position Extended Squitter / Time Tag
Verification (-408/-409 )
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
Page 1028
Dec 16/09
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
PROCEDURE
DESIRED RESULTS
a. Ensure that both Air/Ground Discrete #1 (P2-53) and
Air/Ground Discrete #2 (P1-27) are NOT connected to ground
(i.e., establish the airborne state).
b. Ensure that both Configuration Select “0” (P1-28) and
Configuration Select “1” (P1-17) are NOT connected to ground.
c. Ensure that there is no Arinc 429 Label 203 present on the
selected Altitude Input Bus.
d. Provide the transponder unit with a GPS Time Tag signal via
the GPS Time Tag inputs (P2-37 High, P2-38 Low). The GPS
time tag signal shall be a differential (0 –5 vdc) 1 millisecond
pulse, at a repetition rate of 1 per second.
e. Via the GPS/GNSS Input Data Bus, provide the transponder
with the appropriate labels and data indicated in Figure
1018/GRAPHIC 34-50-96-99B-089-A01. Each data parameter
shall be updated at least once per second.
f. Verify that the transponder properly transmits an
”Even-Second” DF=17 Extended Squitter transmission having
the exact structure for the ”ME” field indicated in Figure
1018/GRAPHIC 34-50-96-99B-089-A01.
NOTE: The single Antenna Bit (RF bit 40) will be set to a "0"
for the TDR-94D and a "1" for the TDR-94.
g. Verify that the transponder properly transmits the Airborne
Position Message at random intervals that are uniformly
distributed over the range from 0.4 to 0.6 seconds (i.e., 0.5
+/-0.1 seconds).
h. Verify that the transponder properly transmits the Airborne
Position alternately from the top and bottom antenna ports for
the TDR-94D and from the bottom antenna only for the TDR-94.
i. Verify that the transponder continues to transmit DF=11
Acquisition Squitters while continuing to transmit the Airborne
Position Squitter Messages as specified steps f, g, and h.
j. Verify that the transponder properly transmits an
”Odd-Second” DF=17 Extended Squitter transmission having
the exact structure for the ”ME” field indicated in Figure
1018/GRAPHIC 34-50-96-99B-089-A01.
9.3D
GPS Bus / Airborne Position Extended Squitter / Time Tag
Verification (-308, -309 ONLY)
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
Page 1028.1
Jun 20/08
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
PROCEDURE
DESIRED RESULTS
a. Ensure that both Air/Ground Discrete #1 (P2-53) and
Air/Ground Discrete #2 (P1-27) are NOT connected to ground
(i.e., establish the airborne state).
b. Ensure that both Configuration Select “0” (P1-28) and
Configuration Select “1” (P1-17) are NOT connected to ground.
c. Ensure that there is no Arinc 429 Label 203 present on the
selected Altitude Input Bus.
d. Provide the transponder unit with a GPS Time Tag signal via
the GPS Time Tag inputs (P2-37 High, P2-38 Low). The GPS
time tag signal shall be a differential (0 –5 vdc) 1 millisecond
pulse, at a repetition rate of 1 per second.
e. Via the GPS/GNSS Input Data Bus, provide the transponder
with the appropriate labels and data indicated in Figure
1019/GRAPHIC 34-50-96-99B-090-A01. Each data parameter
shall be updated at least once per second.
f. Interrogate the transponder with the Mode-S interrogation
indicated in Figure 1019/GRAPHIC 34-50-96-99B-090-A01 to
request BDS Register 0,5.
g. Verify that the transponder responds properly with two
DF=20 replies containing the exact structures for the ”MB” field
indicated in Figure 1019/GRAPHIC 34-50-96-99B-090-A01.
NOTE: The single Antenna Bit (RF bit 40) will be set to a "0"
for the TDR94D and a "1" for the TDR-94.
NOTE: Steps f and g may need to be repeated in order
to get an even encoding since the transponder
is alternating encoding of latitude and longitude
data on odd and even intervals at rates of either
100 or 200 milliseconds.
h. Repeat step f as needed.
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
Page 1028.2
May 07/07
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
PROCEDURE
DESIRED RESULTS
i. Verify that the transponder responds properly with two
DF=20 replies containing the exact structures for the ”MB” field
indicated in Figure 1019/GRAPHIC 34-50-96-99B--A01.
NOTE: The single Antenna Bit (RF bit 40) will be set to a "0"
for the TDR94D and a "1" for the TDR-94.
NOTE: Steps h and i may need to be repeated in order to get
an even encoding since the transponder is alternating
encoding of latitude and longitude data on odd and
even intervals at rates of either 100 or 200 milliseconds.
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
Page 1028.3/1028.4
May 07/07
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
9.4
PROCEDURE
DESIRED RESULTS
Acquisition Squitter Inhibit (-004 through -007 and -207 status
TDR-94/94D)
a. Connect the Acquisition Squitter Inhibit (F) Discrete (P1-26)
to ground. Verify that the transponder ceases to transmit
DF=11 Acquisition Squitter messages but continues to
transmit either airborne or Surface Position Squitter DF=
17 messages.
b. Set the Aquisition Squitter Inhibit (F) discrete (P1-26) to open
before continuing to the next step.
9.5
Surface Position Extended Squitter (-004 through -007 and
-207 status TDR-94/94D)
a. Connect either Air/Ground Discrete #1 (P2-53) or Air/Ground
Discrete #2 (P1-27) to ground (i.e., establish the surface
state).
b. Via the GPS/GNSS Input Data Bus, provide the transponder
with the appropriate labels and data indicated in Figure
1006/GRAPHIC 34-50-96-99B-024-A01 . Each data
parameter is updated at least once per second.
c. Verify that the transponder properly transmits an
"Even_Second" DF=17 Extended Squitter transmission that
has the exact structure for the “ME" fieldas shown in Figure
1006/GRAPHIC 34-50-96-99B-024-A01.
d. Verify that the transponder properly transmits the Surface
Position Message at random intervals that are uniformly
distributed over the range from 0.4 to 0.6 second.
e. Verify that the transponder properly transmits the Surface
Position alternately from the top antenna port for the
TDR-94D and from the bottom antenna port only for the
TDR-94.
f. Verify the transponder continues to transmit DF=11
Acquisition Squitters while continuing to transmit the Surface
Position Squitter Messages indicated in steps c, d, and e.
g. Maintain the data inputs as provided in step b with the
exception that the UTC Time input should be changed to read
as shown in Figure 1006/GRAPHIC 34-50-96-99B-024-A01.
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
Page 1029
Nov 10/06
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
PROCEDURE
DESIRED RESULTS
h. Verify that the transponder properly transmits an
"Odd_Second" DF=17 Extended Squitter transmission that
has the exact structure for the "ME" field as shown in Figure
1006/GRAPHIC 34-50-96-99B-024-A01.
9.5A
GPS Bus/Surface Position Extended Squitter/Time Tag
Verification (-108 status TDR-94/94D only)
a. Connect either air/ground discrete #1 or #2 (P2-53 or P1-27)
to ground (i.e., establishes the surface state).
b. Ensure that neither configuration select discrete 0 or 1
(P1-28 or P1-17) are connected to ground.
c. Provide the transponder with a GPS Time Tag signal via the
GPS Time Tag inputs (P2-37 high, P2-38 low). The GPS
Time Tag signal is a differential (0-5 Vdc) 1 ms pulse, that
repeats once per second.
d. Via the GPS/GNSS Input Data Bus, provide the transponder
with the appropriate labels and data indicated in Figure
1007/GRAPHIC 34-50-96-99B-025-A01. Each data
parameter must be updated at least one time each second.
e. Verify that the transponder properly transmits an
Even-Second DF=17 Extended Squitter Transmission that
has the exact structure for the "ME" field indicated in Figure
1007/GRAPHIC 34-50-96-99B-025-A01.
f. Verify that the transponder properly transmits the Surface
Position Message at random intervals that are uniformly
distributed over the range from 0.4 to 0.6 seconds.
g. Verify that the transponder properly transmits the Surface
Position from the top antenna port only of the TDR-94D and
from the bottom antenna port only of the TDR-94.
h. Verify that the transponder does not transmit DF=11
Acquisition Squitters while transmitting the Surface Position
Squitter Messages indicated in steps e, f, and g.
i. Do not provide the transponder with a GPS Time Tag signal
via the GPS Time Tag inputs (P2-37 high, P2-38 low).
j. Verify that the transponder properly transmits an Odd-Second
DF=17 Extended Squitter transmission that has the
exact structure for the "ME" field indicated in Figure
1007/GRAPHIC 34-50-96-99B-025-A01.
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
Page 1030
May 18/06
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
9.5B
PROCEDURE
DESIRED RESULTS
GPS Bus/Airborne Surface Extended Squitter/Time Tag
Verification (-008 status TDR-94/94D only)
a. Connect either air/ground discrete #1 or #2 (P2-53 or P1-27)
to ground (i.e., establishes the surface state).
b. Ensure that neither configuration select discrete 0 or 1
(P1-28 or P1-17) are connected to ground.
c. Provide the transponder with a GPS Time Tag signal via the
GPS Time Tag inputs (P2-37 high, P2-38 low). The GPS
Time Tag signal is a differential (0-5 Vdc) 1 ms pulse, that
repeats once per second.
d. Via the GPS/GNSS Input Data Bus, provide the transponder
with the appropriate labels and data indicated in Figure
1007/GRAPHIC 34-50-96-99B-025-A01 (for step d of test
9.5A). Each data parameter must be updated at least one
time each second.
e. Interrogate the transponder with the MODE-S interrogations
indicated in Figure 1008/GRAPHIC 34-50-96-99B-026-A01
to request BDS register 0,6.
f. Verify that the transponder responds properly with two DF=20
replies that have the exact structures for the "MB" field
indicated in Figure 1008/GRAPHIC 34-50-96-99B-026-A01.
g. Do not provide the transponder with a GPS Time Tag signal
via the GPS Time Tag inputs (P2-37 high, P2-38).
h. Repeat step e. as necessary.
i. Verify that the transponder responds properly with two DF=20
replies that have the exact structure for the "MB" field in
Figure 1008/GRAPHIC 34-50-96-99B-026-A01.
NOTE: Steps h and i may have to be repeated to get an
odd encoding since the transponder alternates the
encoding of latitude and longitude data on odd and
even intervals at rates of either 100 or 200 ms.
9.5C
GPS Bus / Surface Position Extended Squitter / Time Tag
Verification/ (-408/-409)
a. Connect either Air/Ground Discrete #1 (P2-53) or Air/Ground
Discrete #2 (P1-27) to ground (i.e., establish the surface state).
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
Page 1031
Dec 16/09
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
PROCEDURE
DESIRED RESULTS
b. Ensure that both Configuration Select “0” (P1-28) and
Configuration Select “1” (P1-17) are NOT connected to ground.
c. Provide the transponder unit with a GPS Time Tag signal via
the GPS Time Tag inputs (P2-37 High, P2-38 Low). The GPS
time tag signal shall be a differential (0 –5 vdc) 1 millisecond
pulse, at a repetition rate of 1 per second.
d. Via the GPS/GNSS Input Data Bus, provide the transponder
with the appropriate labels and data indicated in Figure
1020/GRAPHIC 34-50-96-99B-091-A01. Each data parameter
shall be updated at least once per second.
e. Verify that the transponder properly transmits an
”Even-Second” DF=17 Extended Squitter transmission having
the exact structure for the ”ME” field indicated in Figure
1020/GRAPHIC 34-50-96-99B-091-A01.
f. Verify that the transponder properly transmits the Surface
Position Message at random intervals that are uniformly
distributed over the range from 0.4 to 0.6 seconds (i.e., 0.5
+/-0.1 seconds).
g. Verify that the transponder properly transmits the Surface
Position from the top antenna port only for the TDR-94D and
from the bottom antenna only for the TDR-94.
h. Verify that the transponder does not transmit DF=11
Acquisition Squitters while transmitting the Surface Position
Squitter Messages as specified steps e, f, and g.
i. Do NOT provide the transponder unit with a GPS Time Tag
signal via the GPS Time Tag inputs (P2-37 High, P2-38 Low).
j. Verify that the transponder properly transmits an
”Odd-Second” DF=17 Extended Squitter transmission having
the exact structure for the ”ME” field Figure 1020/GRAPHIC
34-50-96-99B-091-A01.
9.5D
GPS Bus / Surface Position Extended Squitter / Time Tag
Verification (-308, -309 ONLY)
a. Connect either Air/Ground Discrete #1 (P2-53) or Air/Ground
Discrete #2 (P1-27) to ground (i.e., establish the surface state).
b. Ensure that both Configuration Select “0” (P1-28) and
Configuration Select “1” (P1-17) are NOT connected to ground.
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
Page 1032
Jun 20/08
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
PROCEDURE
DESIRED RESULTS
c. Provide the transponder unit with a GPS Time Tag signal via
the GPS Time Tag inputs (P2-37 High, P2-38 Low). The GPS
time tag signal shall be a differential (0 –5 vdc) 1 millisecond
pulse, at a repetition rate of 1 per second.
d. Via the GPS/GNSS Input Data Bus, provide the transponder
with the appropriate labels and data indicated in Figure
1021/GRAPHIC 34-50-96-99B-092-A01. Each data parameter
shall be updated at least once per second.
e. Interrogate the transponder with the Mode-S interrogation
indicated in Figure 1021/GRAPHIC 34-50-96-99B-092-A01 to
request BDS Register 0,6.
f. Verify that the transponder responds properly with two DF
20 replies containing the exact structures for the “MB” field
indicated in Figure 1021/GRAPHIC 34-50-96-99B-092-A01.
NOTE: Steps e and f may need to be repeated in order
to get an even encoding since the transponder
is alternating encoding of latitude and longitude
data on odd and even intervals at rates of either
100 or 200 milliseconds.
g. Do NOT provide the transponder unit with a GPS Time Tag
signal via the GPS Time Tag inputs (P2-37 High, P2-38 Low).
h. Repeat step e as needed.
i. Verify that the transponder responds properly with two DF
20 replies containing the exact structures for the “MB” field
indicated in Figure 1021/GRAPHIC 34-50-96-99B-092-A01.
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
Page 1032.1
May 07/07
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
9.6
PROCEDURE
DESIRED RESULTS
FMS/INS Primary Data(-004 through -007 and -207 status
TDR-94/94D)
a. Ensure that neither Air/Ground Discrete #1 or #2 (P2-53
or P1-27) are connected to ground (i.e., establishes the
airborne state).
b. Via the FMS/IRS Input Data Bus, provide the transponder
with the appropriate labels and data indicated in Figure
1009/GRAPHIC 34-50-96-99B-027-A01. Each data
parameter is updated at least once per second.
c.Via the selected ARINC-429 Altitude Input Data Bus, provide
the transponder with the appropriate labels and data
indicated in Figure 1009/GRAPHIC 34-50-96-99B-027-A01.
Each data parameter is updated at least once per second.
d. Connect the IRS ENABLE (F) Discrete (P1-17) to ground to
select the FMS/IRS input as the primary navigation data
source.
e. Verify that the transponder properly transmits a DF=17
Extended Squitter transmission that has the exact structure
for the “ME" field shown in Figure 1009/GRAPHIC
34-50-96-99B-027-A01.
9.6A
FMS/INS Primary Data (-008 and -108 status TDR-94/94D only)
a. Ensure that neither Air/Ground Discrete #1 or #2 (P2-53
or P1-27) are connected to ground (i.e., establishes the
airborne state).
b. Ensure that all GPS labels are removed from the GPS Input
Data Bus.
c. Via the FMS/IRS Input Data Bus, provide the transponder
with the appropriate labels and data indicated in Figure
1010/GRAPHIC 34-50-96-99B-028-A01. Each data
parameter must be updated at least once per second.
d. Via the selected ARINC-429 Altitude Input Data Bus, provide
the transponder with the appropriate label and data indicated
in Figure 1010/GRAPHIC 34-50-96-99B-028-A01. Each
data parameter must be updated at least once per second.
e. Interrogate the transponder with the MODE-S interrogation
indicated in Figure 1010/GRAPHIC 34-50-96-99B-028-A01
to request BDS register 0,5.
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
Page 1032.2
May 07/07
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
9.6A
(Cont)
PROCEDURE
DESIRED RESULTS
f. Verify that the transponder responds properly with two DF=20
replies that have the exact structure for the "MB" field in
Figure 1010/GRAPHIC 34-50-96-99B-028-A01.
NOTE: It may be necessary to repeat steps e. and f. to get an
even encoding since the transponder alternates the
encoding of latitude and longitude data on odd and
even intervals at rates of either 100 and 200 ms.
g. Repeat step e. as necessary.
h. Verify that the transponder responds properly with two
DF=20 replies that have the exact structures for the "MB"
field in Figure 1010/GRAPHIC 34-50-96-99B-028-A01.
NOTE: It may be necessary to repeat steps g and h to get an
even encoding since the transponder alternates the
encoding of latitude and longitude data on odd and
even intervals at rates of either 100 and 200 ms.
i. Remove ARINC-429 labels 310, 311, and 313 from the
FMS/IRS Input Data Bus.
9.7
Aircraft Identification Squitter (-004 through -007 and -207
status TDR-94/94D)
a. Ensure that Ground Speed Data provided to the transponder
via either the GPS/GNSS or FMS/IRS Input Data Buses is
set to 0.
b. Connect either Air/Ground Discrete #1 or #2 (P2-53 or
P1-27) to ground (i.e., establishes the surface state).
c. Verify that TYPE_3 (F) (P1-23) discrete input is in the
open-circuit state in order to select Aircraft Type Set A.
d. Connect TYPE_2 (F) and TYPE_0 (F) discrete inputs (P1-22
and P1-20) to ground to select Aircraft Type 5, (Heavy,
>300,000 lbs).
e. Via the selected Control Input Data Bus, provide the
transponder with the appropriate labels and data indicated in
Figure 1011/GRAPHIC 34-50-96-99B-029-A01. Each data
parameter must be updated at least once per second.
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
Page 1033
Nov 10/06
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
9.7
(Cont)
PROCEDURE
DESIRED RESULTS
f. Verify that the transponder properly transmits a DF=17
Extended Squitter transmission that has the exact structure
for the "ME" field indicated in Figure 1011/GRAPHIC
34-50-96-99B-029-A01.
g. Verify that the transponder properly transmits the Aircraft
Identification Message that has same "ME" field given in
step f at random intervals that are uniformly distributed over
the range from 9.6 to 10.4 seconds.
h. Ensure that neither Air/Ground Discrete #1 or #2 (P2-53
or P1-27) are connected to ground (i.e., establishes the
airborne state).
i. Verify that the transponder properly transmits the Aircraft
Identification Message that has same "ME" field given in
step f at random intervals that are uniformly distributed over
the range from 4.8 to 5.2 seconds.
9.7A
Aircraft Identification Squitter (-108 status TDR-94/94D only)
a. Ensure that Ground Speed Data provided to the transponder
via the GPS/GNSS or FMS/IRS Input Data Buses is set to 0
or not available.
b. Connect either Air/Ground Discrete #1 or #2 (P2-53 or
P1-27) to ground (i.e., establishes the surface state).
c. Verify that the TYPE_3 (F) discrete input (P1-23) is in the
open-circuit state to select Aircraft Type Set A.
d. Connect TYPE_2 (F) and TYPE_0 (F) discrete inputs (P1-22
and P1-20) to ground to select Aircraft Type 5 (greater than
300,000 pounds).
e. Via the selected Control Input Data Bus, provide the
transponder with the appropriate labels and data indicated in
Figure 1012/GRAPHIC 34-50-96-99B-030-A01. Each data
parameter must be updated at least once per second.
f. Verify that the transponder properly transmits a DF=17
Extended Squitter transmission that has the exact
structure for the "ME" field in Figure 1012/GRAPHIC
34-50-96-99B-030-A01.
g. Connect TYPE_3 (F) discrete input (P-23) to ground to select
Aircraft Type Set B.
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
Page 1034
May 18/06
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
9.7A
(Cont)
PROCEDURE
DESIRED RESULTS
h. Connect TYPE _1 (F) discrete input (P1-21) to ground and
verify that TYPE_2 (F) and TYPE_0 (F) discrete inputs
(P1-22 and P1-20) are in the open-circuit state to select
Aircraft Type 2 (lighter-than-air).
i. Verify that the transponder properly transmits a DF=17
Extended Squitter transmission that has the exact
structure for the "ME" field in Figure 1012/GRAPHIC
34-50-96-99B-030-A01.
j. Verify that the transponder properly transmits the Aircraft
Identification Message that has the "ME" field from step i
at random intervals that are uniformly distributed over the
range from 9.6 to 10.4 seconds.
k. Ensure that neither Air/Ground Discrete #1 or #2 (P2-53
or P1-27) are connected to ground (i.e., establishes the
airborne state.
l. Verify that the transponder properly transmits the Aircraft
Identification Message that has the "ME" field from step i
at random intervals that are uniformly distributed over the
range from 4.8 to 5.2 seconds.
9.7B
Aircraft Identification Message (-008 status TDR-94/94D only)
a. Ensure that Ground Speed Data provided to the transponder
via the GPS/GNSS or FMS/IRS Input Data Buses is set to 0
or not available.
b. Connect either Air/Ground Discrete #1 or #2 (P2-53 or
P1-27) to ground (i.e., establishes the surface state).
c. Verify that the TYPE_3 (F) discrete input (P1-23) is in the
open-circuit state to select Aircraft Type Set A.
d. Connect TYPE_2 (F) and TYPE_0 (F) discrete inputs (P1-22
and P1-20) to ground to select Aircraft Type 5 (greater than
300,000 pounds).
e. Via the selected Control Input Data Bus, provide the
transponder with the appropriate labels and data indicated
in Figure 1012/GRAPHIC 34-50-96-99B-030-A01 (for step
e of test 9.7A). Each data parameter must be updated at
least once per second.
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
Page 1035
May 18/06
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
9.7B
(Cont)
PROCEDURE
DESIRED RESULTS
f. Interrogate the transponder with the MODE-S interrogations
indicated Figure 1013/GRAPHIC 34-50-96-99B-031-A01
to request BDS register 0, 8.
g. Verify that the transponder responds properly with a DF=20
reply that has the exact structure for the "MB" field in Figure
1013/GRAPHIC 34-50-96-99B-031-A01.
h. Connect the TYPE_3 discrete input (P1-23) to ground to
select Aircraft Type Set B.
i. Connect the TYPE_1 (F) discrete input (P1-21) to ground and
verify that the TYPE_2 (F) and TYPE_0 (F) discrete inputs
(P1-22 and P1-20) are both in the open-circuit state to select
Aircraft Type 2 (lighter-than-air).
j. Repeat step f.
k. Verify that the transponder responds properly with a DF=20
reply that has the exact structure for the "MB" field in Figure
1013/GRAPHIC 34-50-96-99B-031-A01.
9.7C
Aircraft Identification Squitter (-408/-409)
a. Ensure that Ground Speed Data provided to the transponder
via either the GPS/GNSS or FMS/IRS Input Data buses is set
to ZERO or is NOT Available.
b. Connect either Air/Ground Discrete #1 (P2-53) or Air/Ground
Discrete #2 (P1-27) to ground (i.e., establish the surface state).
c. Verify that TYPE_3 (F) (P1-23) discrete input is in the
open-circuit state in order to select Aircraft Type Set A.
d. Connect TYPE_2 (F) (P1-22) and TYPE_0 (F) (P1-20)
discrete inputs to ground in order to select Aircraft Type 5, i.e.,
Heavy (>300,000 lbs.).
e. Via the selected Control Input Data Bus, provide the
transponder with the appropriate labels and data indicated in
Figure 1022/GRAPHIC 34-50-96-99B-093-A01. Each data
parameter shall be updated at least once per second.
NOTE:
All characters are set equal to the ICAO
ANNEX 10 Character "U".
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
Page 1036
Dec 16/09
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
PROCEDURE
DESIRED RESULTS
f. Verify that the transponder properly transmits a DF=17
Extended Squitter transmission having the exact structure
for the ”ME” field indicated in Figure 1022/GRAPHIC
34-50-96-99B-093-A01.
g. Connect TYPE_3 (F) (P1-23) discrete input to ground in
order to Select Aircraft Type Set B.
h. Connect TYPE_1 (F) (P1-21) discrete input to ground and
verify that TYPE_2 (F) (P1-22) and TYPE_0 (F) (P1-20) are in
the open-circuit state in order to Select
i. Verify that the transponder properly transmits a DF=17
Extended Squitter transmission having the exact structure
for the ”ME” field indicated in Figure 1022/GRAPHIC
34-50-96-99B-093-A01.
j. Verify that the transponder properly transmits the Aircraft
Identification Message having the "ME" field given in step f. at
random intervals that are uniformly distributed over the range
from 9.6 to 10.4 seconds (i.e., 10.0+/- 0.4 seconds).
k. Ensure that both Air/Ground Discrete #1 (P2-53) and
Air/Ground Discrete #2 (P1-27) are NOT connected to ground
(i.e., establish the airborne state).
l. Verify that the transponder properly transmits the Aircraft
Identification Message having the ”ME” field given in step f. at
random intervals that are uniformly distributed over the range
from 4.8 to 5.2 seconds (i.e., 5.0 +/- 0.2 seconds).
9.7D
Aircraft Identification Message -308, -309 ONLY
a. Ensure that Ground Speed Data provided to the transponder
via either the GPS/GNSS or FMS/IRS Input Data buses is set
to ZERO or is NOT Available.
b. Connect either Air/Ground Discrete #1 (P2-53) or Air/Ground
Discrete #2 (P1-27) to ground (i.e., establish the surface state).
c. Verify that TYPE_3 (F) (P1-23) discrete input is in the
open-circuit state in order to select Aircraft Type Set A.
d. Connect TYPE_2 (F) (P1-22) and TYPE_0 (F) (P1-20)
discrete inputs to ground in order to select Aircraft Type 5, i.e.,
Heavy (>300,000 lbs.).
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
Page 1036.1
Jun 20/08
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
PROCEDURE
DESIRED RESULTS
e. Via the selected Control Input Data Bus, provide the
transponder with the appropriate labels and data indicated in
Figure 1023/GRAPHIC 34-50-96-99B-094-A01. Each data
parameter shall be updated at least once per second.
f. Interrogate the transponder with the Mode-S interrogation
indicated in Figure 1023/GRAPHIC 34-50-96-99B-094-A01 to
request BDS Register 0,8.
g. Verify that the transponder responds properly with a DF20
reply containing the exact structure for the ”MB” field indicated
in Figure 1023/GRAPHIC 34-50-96-99B-094-A01.
h. Connect TYPE_3 (F) (P1-23) discrete input to ground in
order to Select Aircraft Type Set B.
i. Connect TYPE_1 (F) (P1-21) discrete input to ground and
verify that TYPE_2 (F) (P1-22) and TYPE_0 (F) (P1-20) are
in the open-circuit state in order to Select Aircraft Type 2, i.e.,
Lighter-than-Air.
j. Repeat Step f
k. Verify that the transponder responds properly with a DF20
reply containing the exact structure for the ”MB” field indicated
in Figure 1023/GRAPHIC 34-50-96-99B-094-A01.
9.8
AIS/ADSS Primary Data (-008 and -108 status TDR-94/94D)
a. Ensure that neither Air/Ground discrete inputs #1 or #2
(P2-53 or P1-27) are connected to ground (i.e., establishes
the airborne state).
b. Ensure that all GPS labels are removed from the GPS Input
Data Bus.
c. Ensure that all GPS labels are removed from the FMS/IRS
Input Data Bus.
d. Ensure that Configuration Select S0 discrete input (P1-28)
is in the open-circuit state.
e. Connect Configuration Select S1 discrete input (P1-17) to
ground to select configuration 2.
f. Via the AIS/ADS Input Data Bus, provide the transponder
with the appropriate labels and data indicated in Figure
1014/GRAPHIC 34-50-96-99B-032-A01. Each data
parameter must be updated at least once per second.
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
Page 1036.2
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ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
PROCEDURE
DESIRED RESULTS
g. Interrogate the transponder with the MODE-S interrogations
indicated in Figure 1014/GRAPHIC 34-50-96-99B-032-A01
to request BDS register 0,5.
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
Page 1036.3/1036.4
May 18/06
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
PROCEDURE
DESIRED RESULTS
9.8
(Cont)
h. Verify that the transponder responds properly with DF=20
replies that have the exact structures for the "MB" field in
Figure 1014/GRAPHIC 34-50-96-99B-032-A01.
9.8B
AIS/ADSS Primary Data (-308, -309, -408, -409)
a. Ensure that both Air/Ground Discrete #1 (P2-53) and
Air/Ground Discrete #2 (P1-27) are NOT connected to ground
(i.e., establish the airborne state).
b. Ensure that all GPS labels are removed from the GPS Input
Data Bus.
c. Ensure that all GPS labels are removed from the FMS IRS
Input Bus.
d. Ensure that Configuration Select ‘S0’ (P1-28) discrete input
is in the open-circuit state.
e. Connect Configuration Select ‘S1’ (P1-17) discrete to ground
in order to select Configuration 2.
f. Via the AIS/ADS Input Data Bus, provide the transponder
with the appropriate labels and data indicated in Figure
1024/GRAPHIC 34-50-96-99B-095-A01. Each data parameter
shall be updated at least once per second.
g. Interrogate the transponder with the Mode-S interrogation
indicated in Figure 1024/GRAPHIC 34-50-96-99B-095-A01 to
request BDS Register 0,5.
h. Verify that the transponder responds properly with DF=20
replies containing the exact structures for the ”MB” field
indicated in Figure 1024/GRAPHIC 34-50-96-99B-095-A01.
9.9
Illegal Configuration Select Check (-008 , -108, -308, -309,
-408, and -409 status TDR-94/94D only).
a. Do not change the existing settings from Test 9.8.
b. Connect Configuration Select S0 discrete input (P1-28) to
ground to select configuration 3.
c. Verify bit 14 in label 353 on the TDR Output Bus is set to 1.
d. Ensure that the Configuration Select S0 and S1 discrete
inputs (P1-28 and P1-17) are both set to the open-circuit
state to select configuration 0 before you continue to the
next test.
10.0
ATCRBS LIMITING
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
Page 1037
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ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
PROCEDURE
DESIRED RESULTS
Test the bottom antenna port for the TDR-94, and both antenna
ports for the TDR-94D.
10.1
500 Hz Rate
Interrogate with MODE-C at a 500-Hz rate with an input level of
-75 dBm. Verify that the reply rate is AT LEAST 90%.
TOP
_____ (x)
BOTTOM
_____ (x)
10.2
750 Hz Rate
Interrogate with MODE-C at a 750-Hz rate and adjust the input
level to -45 dBm. Verify that the average reply rate is LESS
THAN 90%.
TOP
_____ (x)
BOTTOM
_____ (x)
11.0
STANDBY/ON CROSS-FEED
For these tests, the Burst Enable strap, P2-59, must be
grounded (set to active). The input (P1-15) "ground" state must
be verified at 2.0 V dc; additional tests may be conducted at 0
to 2.0 V dc. The input "open" state must be verified at 15 V
dc; additional testing may be conducted using an open circuit
input. The output (P1-30) "high impedance" state must be
verified to sink less than 100 — A from a > +20 volt source, and
its "low-impedance" state must be verified to sink 1.0 ma at an
output level less than 1.0 V dc.
11.1
High Impedance State Test
Set STBY/ON XF IN to the active state (ground P1-15) and
verify that STBY/ON XF OUT (P1-30) is in a high-impedance
state. Also verify the unit is in Standby Mode and does not
respond to interrogations.
STBY/ON XF OUT HIGH IMPEDANCE
Unit is in standby.
11.2
Low Impedance State Test
Set STBY/ON XF IN to the inactive state (P1-15 open
circuit) and verify that STBY/ON XF OUT (P1-30) is in a
low-impedance state. Also verify the unit is active and responds
to interrogations in normal fashion.
STBY/ON XF OUT HIGH IMPEDANCE
Unit is in active.
12.0
_____ (x)
_____ (x)
_____ (x)
_____ (x)
FAIL-WARNING REQUIREMENTS
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
Page 1038
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ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
PROCEDURE
DESIRED RESULTS
12.1
Bad MODE-S Discrete Address Input
Remove power from the UUT and ground all MODE-S Discrete
Address inputs. Restore power to the UUT. After initialization
has been completed, ensure that Fail-Warning output, P1-31, is
active low (less than 1.5 V dc).
12.2
Restored MODE-S Discrete Address Input
Remove power from the UUT and set MODE-S Discrete
Address Inputs for a valid address, i.e. one where all such
inputs are not the same (ground or open). Restore power to the
UUT and after initialization has been completed, ensure that
Fail-Warning output, P1-31, is set high (greater than 23 V dc
when loaded with 140 ohms).
Method: Interrogate the unit with MODE-S interrogations set for
address 52525252. Set the computer strapping for a MODE-S
UUT address of 52525252. Cycle the power and verify that
the fail-warn light comes on. Set the computer strapping for
a MODE-S UUT address of 00000000. Cycle the power and
verify that the Fail warning light goes out. Reset the computer
strapping for a MODE-S UUT address of 52525252 and cycle
the power.
Fail warning lamp on
Switches off with a bad address
_____ (x)
_____ (x)
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
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ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
13.0
PROCEDURE
DESIRED RESULTS
MUTUAL SUPPRESSION REQUIREMENTS
Ensure that a mutual suppression output pulse occurs that
brackets any transmissions at an amplitude of 20 volts or more.
Verify that a suppression pulse of 15 volts or more prevents
ATCRBS decoding during that pulse's time interval. Verify
decoder suppression for both top and bottom antenna ports
on the TDR-94D, and only for the bottom antenna port on the
TDR-94.
Output pulse 20 or > volts
ATCRBS suppression
14.0
___ (x)
TOP ___ (x) BOT ___ (x)
SELF TEST REQUIREMENTS (-004 through -008 status
TDR-94/94D only)
Ensure that the UUT initiates Self-Test by grounding the
Self-Test Discrete, P2-54. Only one Self-Test cycle should be
executed each time the P2-54 discrete input is grounded. Verify
that the label 350 output word SSM code changes from 11 to
10 to 01 and back to 11 (normal operation). Transitions from 11
to 10 to 11 are also acceptable.
Method: Switch the Air/ground discrete to ground. Use
"Select card type" (31) from the computer menu to select
CONTROL-ALT CARD TYPE. Use menu option (9), "Control
Select Lines", to set the control to ARINC bus 0. Use menu
option (36) "TDR Bus A", to change to ARINC label 350. Note
the 350 word displayed on the computer screen. Set the
Self-Test discrete to active and update the 350 word display
by rapidly selecting option 11 three times and pushing the
enter key. Verify that the third two-digit number in the 350 word
changes from 60 to 40 to 20 then back to 60, or from 60 to 40
back to 60. Reset the Self-Test discrete to inactive.
NOTE: The 350 word may blank at the first update,
if so repeat procedure.
Unit executes a self test cycle
____ (x)
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
Page 1039
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ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
14A.0
PROCEDURE
DESIRED RESULTS
SIL Designator Requirements (-108, -308, -309, -408, -409
status TDR-94/94D only)
a. Verify that the SIL Designator discrete input, P2-54 is in the
open-circuit state.
b. Interrogate to transponder with MODE-S interrogation as
indicated in Figure 1015/GRAPHIC 34-50-96-99B-033-A01
to request BDS register 6,5 (Aircraft Operational Status).
c. Verify that the transponder responds properly with a
DF=20 reply that has the "MB" field indicated in Figure
1015/GRAPHIC 34-50-96-99B-033-A01.
d. Connect the SIL Designator discrete input, P2-54, to ground
to initiate a higher Surveillance Integrity Level.
e. Interrogate the transponder with the MODE-S interrogations
indicated in Figure 1015/GRAPHIC 34-50-96-99B-033-A01
to request BDS register 6,5.
f. Verify that the transponder responds properly with a
DF=20 reply that has the "MB" field indicated in Figure
1015/GRAPHIC 34-50-96-99B-033-A01.
g. Remove the ground from SIL Designator discrete input,
P2-54.
15.0
TDR-94D DIVERSITY TEST
15.1
Bottom Signal Greater Than Top Signal
Interrogate into the top antenna port with a UF=11 MODE-S
interrogation that has a signal level of -53 dBm. Interrogate into
the bottom antenna port with a UF=11 signal at -50 dBm that
is delayed not less than 100 ns from the top signal. Verify that
the reply transmits on the bottom antenna port at a rate of AT
LEAST 90%, and replies from the top antenna port are at a
rate NOT GREATER than 10%.
90% or > replies on the bottom antenna port,
10% or < on top antenna port
____ (x)
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
Page 1040
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ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
15.2
PROCEDURE
DESIRED RESULTS
Top Signal Greater Than Bottom Signal
Interrogate into the bottom antenna port with an UF=11
MODE-S signal at -53 dBm. Interrogate into the top antenna
port with a UF=11 signal at -50 dBm that is delayed not less than
100 ns from the bottom signal. Verify that the reply transmits on
the top antenna port at a rate of AT LEAST 90%, and replies
from the bottom antenna port are NOT GREATER than 10%.
90% or > replies on the bottom antenna port,
10% or < on top antenna port
15.3
Top Signal Leads Bottom Signal
Interrogate into the top antenna port with a UF=11 MODE-S
signal at -73 dBm. Interrogate into the bottom antenna port with
a UF=11 signal at -50 dBm that is delayed not more than 350
ns from the top signal. Verify that the reply transmits on the top
antenna port at a rate of AT LEAST 90%, and replies from the
bottom antenna port are NOT GREATER than 10%.
90% or > replies on the bottom antenna port,
10% or < on top antenna port
15.4
____ (x)
Bottom Signal Leads Top Signal
Interrogate into the bottom antenna port with a UF=11 MODE-S
signal at -73 dBm. Interrogate into the top antenna port with a
UF=11 signal at -50 dBm that is delayed not more 350 ns from
the bottom signal. Verify that the reply transmits on the bottom
antenna port at a rate of AT LEAST 90%, and replies from the
top antenna port are NOT GREATER than 10%.
90% or > replies on the bottom antenna port,
10% or < on top antenna port
16.0
____ (x)
____ (x)
I/O REQUIREMENTS
Ensure that the following tests meet the appropriate ARINC 429
or CSDB specification.
16.1
Comm-A/B I/O
Set ADLP Present Discrete, P2-60, to its active state (ground).
Verify that data can be received on the Comm A/B serial input
port, P2-1 and P2-2. Also verify that data is transmitted on the
Comm A/B serial output port, P2-3 and P2-4. Data may be
transmitted at a low repetition rate.
Comm-A/B I/O operation O.K.
____ (x)
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
Page 1041
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ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
16.2
PROCEDURE
DESIRED RESULTS
ADLP Present Discrete (P2-60)
Verify that when this discrete is ground, the Comm-A/B
serial/output bus, P2-3 and P2-4, transmits appropriate ARINC
429 words at a 100 kBps rate.
Present Discrete operation O.K.
16.3
____ (x)
TX/XT I/O Ports (Applies to TDR-94D only)
Ensure that data can be received on the TX port, P2-9 and
P2-10, and transmitted on the XT port, P2-11 and P2-12.
Ensure that grounding the TCAS Select [F] Discrete input,
P1-13, results in periodic transmissions on the XT bus. When
the TCAS Select [F] discrete input is open, there should be no
transmissions on the XT bus. Verify that the word transmissions
have a bit rate of 100 kbps.
Data can be received on the TX port.
Data can be transmitted on the XT port.
TCAS Select operation O.K.
16.4
____ (x)
____ (x)
____ (x)
Altitude Inputs
a. Set the S-1403 function to 1 (ATCRBS).
Set IFR display select to XPDR CODE.
Set XPDR CODE switch on IFR to AC2 FEET.
Set ARINC altitude on the test computer to output standard
ARINC 429 on PORT 0.
Set the altitude select on the computer menu for ARINC 429
altitude, PORT 0
Verify that the altitude data displayed on the IFR matches
data being sent by the test computer.
ARINC Altitude operation O.K.
____ (x)
b. Set ARINC altitude on the test computer to output standard
ARINC 429 on PORT 1. Verify the IFR does not display
valid altitude. Set the altitude select on the computer menu
for ARINC 429 altitude, PORT 1. Verify that the altitude
data displayed on the IFR matches data being sent by the
test computer.
ARINC Altitude operation O.K.
____ (x)
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
Page 1042
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ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
16.4
(Cont)
PROCEDURE
DESIRED RESULTS
c. Set the test computer to output PLII altitude on PLII altitude
PORT 0. Change the ARINC bus used for altitude data in the
previous steps to ADLP. Verify the IFR does not display valid
altitude. Set the altitude select on the computer menu for
PLII altitude, PORT 0. Verify that the altitude data displayed
on the IFR matches data being sent by the test computer.
PLII Altitude operation O.K.
____ (x)
d. Set the test computer to output PLII altitude on PLII altitude
PORT 1. Verify the IFR does not display valid altitude. Set
the altitude select on the computer menu for PLII altitude,
PORT 1. Verify that the altitude data displayed on the IFR
matches data being sent by the test computer.
PLII Altitude operation O.K.
____ (x)
e. Set the altitude select lines to GILLHAM. Verify the altitude
displayed on the IFR matches what the test computer shows
is being sent.
GILLHAM Altitude operation O.K.
16.5
____ (x)
ARINC 429 Control Selection
a. Select ARlNC control. Use the PLII/A429 Control Select
to set the control discretes for ARINC 0 input (ARINC 429
PORT 0). Set the ARINC control bus to PORT 0 on the test
computer. Monitor label 350 on the TDR bus and verify that
valid data is returned.
ARINC 0 operation O.K.
____ (x)
b. Set the control discretes for ARINC 1 input (ARINC 429
PORT 1). Verify that valid data is not returned. Set the
ARINC control bus to PORT 1 on the test computer. Monitor
label 350 on the TDR bus and verify that valid data is
returned.
ARINC 1 operation O.K.
____ (x)
c. Set the control discretes for ARINC 2 input (ARINC 429
PORT 2). Verify that valid data is not returned. Set the
ARINC control bus to PORT 2 on the test computer. Verify
that valid data is returned.
ARINC 2 operation O.K.
____ (x)
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
Page 1043
May 18/06
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
16.5
(Cont)
PROCEDURE
DESIRED RESULTS
d. Set the Burst Enable to active and verify that burst data can
be extracted from all three ports. Reset the burst enable
discrete to inactive.
Burst Enable discrete operation O.K.
16.6
____ (x)
CSDB/PLII Control Selection
Set the CSDB (PLII)/A429 Control Select discrete to PLII
(ground P2-56). Set the PLII output on the test computer to
output data on the control bus (P2-31, 32). Verify that PLII
echo is transmitted on PLII output bus (P2-23, 24 ), Option 40
on the computer.
CSDB/A429 Control Select/CSDB operation O.K.
16.7
____ (x)
Source Ident Straps (P2-46 and P2-47)
a. Connect P2-46 to P2-50 (common). Open circuit P2-47.
Verify that the TDR output data reflects side two in the SDI
bits if ARINC 429 configured, or SI bits if CSDB configured.
Method A: Set SDI discretes to 1. Set PLII data to SDI 1 using
option 39 on the computer. Verify unit responds with valid data
on the PLII bus.
Source Ident Straps operation O.K.
____ (x)
b. Connect P2-47 to P2-50 (common). Open circuit P2-46.
Verify that the TDR output data reflects side two in the
SDI bits if ARINC 429 is configured, or SI bits if CSDB is
configured.
Method B: Set SDI discretes to 2. Verify no valid data is echoed
on the PLII bus.
Source Ident Straps operation O.K.
16.8
____ (x)
Self-Test Inhibit Discrete (P2-38 for -004, -005, -006, -007,
-207 status TDR-94/94D or P1-19 for -008/-108, -308/-309/
-408/-409 status TDR-94/94D)
Verify that when this discrete input (P2-38 or P1-19) is
grounded, the unit suspends monitoring and test functions
associated with squitter generation.
Reduce signal level to a low level that will not cause replies.
Ensure that the IFR test set indicates squitter output. Switch
the Self-Test inhibit discrete to active (ground). Verify squitter
generation is suspended. Reset the Self-Test inhibit to inactive.
Self-Test Inhibit Discrete operation O.K.
____ (x)
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
Page 1044
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ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
PROCEDURE
16.9
Air/Ground Discretes
16.9.1
Air/Ground Discrete #1 (P2-53)
DESIRED RESULTS
Ensure that grounding the Air/Ground Discrete #1, P2-53, sets
bit 6 (vertical status) in DF=1 downlink replies to 1.
Verify that transponder continues to reply to ATCRBS and
MODE-S interrogations when the Air/Ground Discrete #1,
P2-53, is connected to ground.
Verify that bit 6 (Vertical Status) in DF= 0 downlink replies is
set to 0 when the Air/Ground Discrete #1 is disconnected from
ground.
Air/Ground Discrete #1 operation O.K.
16.9.2
____ (x)
Air/Ground Discrete #2 (P1-27)
Ensure that grounding the Air/Ground Discrete #2, P1-27, sets
bit 6 (vertical status) in DF=0 downlink replies to 1.
Verify that the transponder continues to reply properly to
ATCRBS interrogations while the Air/Ground Discrete #2,
P1-27, is connected to ground.
Verify that transponder DOES NOT reply to ATCRBS
interrogations while the Air/Ground Discrete #2, P1-27, is
connected to ground.
Verify that bit 6 (Vertical Status) in DF=0 downlink replies is
set to 0 when the Air/Ground Discrete #2 is disconnected from
ground.
Air/Ground Discrete #2 operation O.K.
____ (x)
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
Page 1045
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ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
16.10
PROCEDURE
DESIRED RESULTS
Auto Altitude Selection Test (-004 through -006 status
TDR-94/94D)
NOTE:
The Auto Altitude Selection test applies to -004
through -006 status TDR-94 and TDR-94D units only.
a. Establish ARINC-429 Control for the UUT and ensure that
the UUT is configured for altitude selections as follows:
PIN NAME
CNTRL/ALT
AS0
AS1
AUTO ALT SEL
ALT PORT SEL
PIN NUMBER
P1-14
P2-41
P2-42
P1-28
P2-48
CONDITION
OPEN
GROUND
GROUND
OPEN
OPEN
Ensure that the Alternate Source Select Bit (bit 14) is "0" in the
"031" control word provided to the UUT.
Alternate Source Select bit is "0".
____ (x)
b. Connect a valid ARINC-429 Altitude source to Altitude Port
B of the UUT (P2-29, 30). Select XPONDER MODE, AC2,
on the IFR test set and interrogate the UUT with standard
MODE-C ATCRBS interrogations. Verify that the altitude
displayed by the IFR test set is "EEEE".
Displayed altitude is "EEEE".
____ (x)
c. Connect Auto Alt Sel (P1-28) to ground and continue to
interrogate the UUT with standard MODE-C ATCRBS
interrogations. Verify that the altitude displayed by the IFR
test set is the same as that provided by the altitude source
connected to altitude Port B.
Displayed altitude matches Port B source altitude.
16.10A
____ (x)
Configuration Select Discretes (-008, -108, -308, -309, -408,
-409 TDR-94/94D only)
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
Page 1046
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ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
16.10A.1
PROCEDURE
DESIRED RESULTS
Configuration Select S0 (P1-28)
a. Verify that Configuration Select S0 and S1 discrete inputs
P1-28 and P1-17 are in the open-circuit state to select
configuration 0.
b. Via FMS/IRS Input Data Bus, provide the transponder
with the appropriate label and data indicated in Figure
1016/GRAPHIC 34-50-96-99B-034-A01. Each data
parameter must be updated at least once per second.
c. Interrogate the transponder with the MODE-S interrogations
indicated in Figure 1016/GRAPHIC 34-50-96-99B-034-A01
to request BDS register 5,0.
d. Verify that the transponder responds properly with a DF=20
reply that has the "MB" field in Figure 1016/GRAPHIC
34-50-96-99B-034-A01.
e. Connect Configuration Select S0 discrete input P1-28 to
ground to select configuration 1.
f. Interrogate the transponder with the MODE-S interrogation
indicated in Figure 1016/GRAPHIC 34-50-96-99B-034-A01
to request BDS register 5,0.
g. Verify that the transponder responds properly with a
DF=20 reply that has the "MB" field indicated in Figure
1016/GRAPHIC 34-50-96-99B-034-A01.
h. Remove the ground from Configuration Select S0 discrete
input P1-28.
i. Remove ARINC label 335 from the FMS/IRS Data Input Bus.
16.10A.2
Configuration Select S1 (P1-17)
a. Connect Configuration Select S1 discrete input P1-17 to
ground to select configuration 2.
b. Verify that Altitude Select AS0 and AS1 discrete inputs P2-41
and P2-42 are in the open-circuit state.
c. Ensure that no GPS data is being applied to the transponder
via the GPS Input Data Bus.
d. Via the FMS/IRS Input Data Bus, provide the transponder
with the labels and data indicated in Figure 1017/GRAPHIC
34-50-96-99B-035-A01. Each data parameter must be
updated at least once per second.
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
Page 1047
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ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
PROCEDURE
DESIRED RESULTS
16.10A.2
(Cont)
e. Interrogate the transponder with the MODE-S interrogations
in Figure 1017/GRAPHIC 34-50-96-99B-035-A01 to request
BDS register 0,5.
f. Verify that the transponder responds properly with a
DF=20 reply that has the Type Code indicated in Figure
1017/GRAPHIC 34-50-96-99B-035-A01 for the "MB" field.
g. Remove the ground from Configuration Select S1 discrete
input P1-17.
h. Interrogate the transponder with the MODE-S interrogation
indicated in Figure 1017/GRAPHIC 34-50-96-99B-035-A01
to request BDS register 0,5.
i. Verify that the transponder responds properly with a DF=20
reply that has the Type Code for the "MB" field indicated in
Figure 1017/GRAPHIC 34-50-96-99B-035-A01.
16.11
Remote Ident Test
a. Ensure that the SPI IDENT (F) discrete input, P1-16, is in
the open-circuit state.
SPI IDENT (F) is in open-circuit state.
____ (x)
b. Interrogate the UUT with standard ATCRBS MODE-A
interrogations. Verify that the reply displayed on the IFR test
set DOES NOT indicate "ID".
IFR reply does not indicate "ID".
____ (x)
c. Momentarily connect the SPI IDENT (F) discrete input,
P1-16, to ground. Verify that the reply displayed on the IFR
test set indicates "ID" for approximately 18 seconds.
IFR reply indicates "ID" for approximately 18 sec.
16.12
____ (x)
FMS/IRS Lo/Hi Select Discrete (P1-24) (-008, -108, -308, -309,
-408, -409 TDR-94/94D only)
a. Connect the FMS/IRS Lo/Hi Select input P1-24 to ground.
Cycle UUT power off and then back on so that the
transponder accepts the configuration change.
b. Repeat FMS/INS Primary Data test 9.6A and verify
high-speed operation of the FMS/INS Input Data Bus (P2-27,
P2-28).
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
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ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
16.12
(Cont)
PROCEDURE
DESIRED RESULTS
c. Remove the ground from FMS/INS Lo/Hi Select Discrete,
P1-24. Cycle UUT power off and then back on so that the
transponder accepts the configuration change.
d. Repeat FMS/INS Primary Data test 9.6A and verify
low-speed operation of the FMS/INS Input Data Bus (P2-27,
P2-28)
16.13
AIS/ADS Lo/Hi Select Discrete (P1-57) (-008, -108, -308, -309,
-408, -409 TDR-94/94D only)
a. Connect the AIS/ADS Lo/Hi Select Discrete, P1-57 to
ground. Cycle UUT power off and then back on so that the
transponder accepts the configuration change.
b. Repeat AIS/ADSS Primary Data test 9.8 and verify
high-speed operation of AIS/ADS Input Data Bus (P2-39,
P2-40).
c. Remove the ground from the AIS/ADS Lo/Hi Select Discrete,
P1-24. Cycle UUT power off and then back on so that the
transponder accepts the configuration change.
d. Repeat AIS/AADSS Primary Data test 9.8 and verify
low-speed operation of AIS/ADS Input Data Bus (P2-39,
P2-40).
16.14
GPS Lo/Hi Select Discrete (P1-18) (-008 , -108, -308, -309,
-408, -409 TDR-94/94D only)
a. Connect the GPS Lo/Hi Select Discrete, P1-18, to ground.
Cycle UUT power off and then back on so that the
transponder accepts the configuration change.
b. Repeat GPS Bus/Airborne Position Extended Squitter test
9.3A (for -108 status TDR-94/94D), test 9.3B (for -008 status
TDR-94/94D), test 9.3C (for -408, -409 status) or test 9.3D
(for -308, -309 status) and verify high-speed operation of
GPS Input Data Bus (P2-49, P2-50).
c. Remove the ground from GPS Lo/Hi Select Discrete,
P1-18 . Cycle UUT power off and then back on so that the
transponder accepts the configuration change.
d. Repeat GPS Bus/Airborne Position Extended Squitter test
9.3A (for -108 status TDR-94/94D) or test 9.3B (for -008
status TDR-94/94D) and verify low-speed operation of GPS
Input Data Bus P2-49, P2-50.
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
Page 1049
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ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
16.15
PROCEDURE
DESIRED RESULTS
Altitude Port A/B Lo/Hi Select Discrete (P1-26) (-008, -108,
-308, -309, -408, -409 TDR-94/94D only)
a. Connect Altitude Port A/B Lo Hi Select Discrete, P1-26, to
ground. Cycle UUT power off and then back on so that the
transponder accepts the configuration change.
b. Verify high-speed operation of the Altitude Port A Input Data
Bus (P2-25, P2-26).
c. Remove the ground from Altitude Port A/B Lo/Hi Select
Discrete, P1-26. Cycle UUT power off and then back on so
that the transponder accepts the configuration change.
d. Verify low-speed operation of the Altitude Port A Input Data
Bus (P2-25, P2-26).
16.16
Maximum Airspeed Select Discretes (P2-43, P2-44, P2-45)
(-008, -108, -308, -309, -408, -409 TDR-94/94D only)
a. Connect either of Air/Ground discrete inputs #1 or #2 (P2-53
or P1-27) to ground (i.e., establishes a surface state).
b. Verify on the TDR Output Bus (P2-15, P2-16) that bits 22
through 25 of ARINC label 276 are set correctly for the
input states of the Maximum Airspeed Select Discretes as
indicated below. UUT power must be cycled off and then
back on each time the maximum airspeed configuration is
changed.
P2-45
MAX A/S
BIT 17
OPEN
OPEN
OPEN
GROUND
P2-44
MAX A/S
BIT 16
OPEN
OPEN
GROUND
OPEN
P2-43
MAX A/S
BIT 15
OPEN
GROUND
OPEN
OPEN
LABEL 276
MSB
LSB
22
24
000
001
010
100
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
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ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
17.0
PROCEDURE
DESIRED RESULTS
TRANSPONDER TESTS AND INSPECTIONS
COMPLIANCE WITH CODE OF FEDERAL
REGULATIONS (CFR), TITLE 14, CHAPTER 1,
FEDERAL AVIATION ADMINISTRATION, DEPARTMENT
OF TRANSPORTATION, PART 43, APPENDIX
F-ATC TRANSPONDER TESTS AND INSPECTIONS.
THE FOLLOWING TESTS OR NOTATIONS HAVE BEEN
ADDED TO MORE EASILY DEMONSTRATE COMPLIANCE
WITH CFR, TITLE 14, CHAPTER 1, PART 43, APPENDIX F,
FOR RETURNING THE TDR-94/94D TRANSPONDER TO
SERVICE.
17.1
Radio Reply Frequency (Appendix F, Paragraph (a)(4))
The requirement to demonstrate proper compliance with this
paragraph has been stated in step 2.1. of this procedure, and
will not be repeated here.
17.2
Suppression (Appendix F, Paragraph (b)(1))
The requirement to demonstrate proper compliance with this
paragraph has been stated in step 4.3. of this procedure and
will not be repeated here.
NOTE: RTCA DO-181 paragraph 2.2.5.1.a. and c. set the
limits at 10% versus the 1% limit set by CFR, TITLE 14,
CHAPTER 1, PART 43, APPENDIX F, Paragraph (b)(1).
17.3
Suppression (Appendix F, Paragraph (b)(2))
The requirement to demonstrate proper compliance with this
paragraph has been stated in step 4.2. of this procedure, and
will not be repeated here.
17.4
Receiver Sensitivity ( Appendix F, Paragraph (c)(1))
The requirement to demonstrate proper compliance with this
paragraph has been stated in step 1.1. of this procedure and
will not be repeated here.
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
Page 1051
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ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
17.5
PROCEDURE
DESIRED RESULTS
Receiver Sensitivity (Appendix F, Paragraph (c)(2))
MTL is defined as the minimum interrogation power level which
produces a reply rate of at least 90%.
Interrogate the transponder with standard MODE-A
interrogations, and verify that the MTL is between -75 and -79
dBm.
Interrogate the transponder with standard MODE-C
interrogations, and verify that the MTL is between -75 and -79
dBm. Verify that the difference between the MODE-A MTL and
the MODE-C MTL does not exceed 1 dB.
Difference between MODE-A MTL and MODE-C MTL is 1dB
or less.
17.6
____ (x)
Radio Frequency (RF) Peak Output Power (Appendix F,
Paragraphs (d)(iii) and (d)(v))
The requirement to demonstrate proper compliance with these
paragraphs has been stated in step 2.2.A. of this procedure
and will not be repeated here.
17.7
MODE-S Diversity Transmission Channel
Isolation Appendix F, Paragraph (e)
The requirement to demonstrate proper compliance with this
paragraph has been stated in step 2.2.C. of this procedure and
will not be repeated here.
17.8
MODE-S Address (Appendix F, Paragraph (f))
Ensure that some of the MODE-S Discrete Address inputs to
the UUT are set to open circuit and some are shorted to ground.
A MODE-S Address of all 0s, or all 1s, is NOT acceptable
and will result in a Fail/Warn condition. Likewise, a MODE-S
Address of all 0s or all 1s will result in the UUT remaining in
the "STANDBY" mode.
NOTE: The MODE-S Address is binary, however, when
using the IFR S-1403 and manual test software the
MODE-S Address must be is entered in octal.
If the Address is changed at this time, UUT power must be
removed and then reapplied to make the TDR Transponder
recognize and use the new address.
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
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ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
17.8
(Cont)
PROCEDURE
DESIRED RESULTS
Interrogate the transponder with UF=4 interrogations using the
same address as that provided to the UUT, and at a nominal
rate of 50 per second. Verify that the transponder properly
replies with DF=4 and with AT LEAST a 90% reply ratio.
Interrogate the transponder with at least two UF=4 interrogations
using addresses that are different than the discrete address
provided to the UUT, at a nominal rate of 50 per second. Verify
that the transponder does not reply to the interrogations.
17.9
MODE-S Formats (Appendix F, Paragraph (g))
PART A: ALTITUDE/MODE-C/UF=4/UF=20
Ensure that Gillham Altitude is selected via the Altitude Selects
and set the discrete Gillham Altitude inputs as follows:
Gillham Altitude Bits
BIT POSITION
D2 D4 A1 A2 A4 B1 B2 B4 C1 C2 C4
---------------------------------------------------------------------------------------------------------Data:
1 0
0 1
1 0 1
(49,950 to 50,050 feet)
"1" indicates connection to ground (selected)
"0" indicates open-circuited (not selected)
Reference (Gillham code 2524).
Interrogate the transponder with standard MODE-C
interrogations. Verify that the transponder replies with the
altitude value provided via the Gillham inputs.
Interrogate the transponder with MODE-S UF=4 interrogations
with the PC, RR, DI and SD fields set to 0, and the MODE-S
address set the same as that provided to the transponder. Verify
that the transponder replies with the altitude value provided
via the Gillham inputs.
Interrogate the transponder with MODE-S UF=20 interrogations
and that have the MODE-S address set the same as that
provided to the transponder. Verify that the transponder replies
with the altitude value provided via the Gillham inputs.
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
Page 1053
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ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
17.9
(Cont)
PROCEDURE
DESIRED RESULTS
Gillham Altitude Bits
BIT POSITION
D2 D4 A1 A2 A4 B1 B2 B4 C1 C2 C4
---------------------------------------------------------------------------------------------------------Data:
0 1
1 0
0 1 0
(24, 250 to 24,350 feet)
"1" indicates connection to ground (selected)
"0" indicates open-circuited (not selected)
Reference (Gillham code 5210).
PART B: IDENT/MODE-A/UF=5/UF=21
Via the selected control bus, supply the transponder with a valid
4096 identification code.
Interrogate the transponder with standard MODE-A
interrogations. Verify that the transponder replies with the Ident
Code provided via the control bus.
Interrogate the transponder with MODE-S UF=5 interrogations
with the PC, RR, DI and SD fields set to 0, and the MODE-S
address set the same as that provided to the transponder.
Verify that the transponder replies with the Ident Code provided
via the control bus.
Interrogate the transponder with MODE-S UF=21 interrogations
and that have the MODE-S address set the same as that
provided to the transponder. Verify that the transponder replies
with the Ident Code provided via the control bus.
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
Page 1054
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ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
17.10
PROCEDURE
DESIRED RESULTS
MODE-S All-Call Interrogations (Appendix F, Paragraph (h))
Interrogate the transponder with MODE-S ONLY ALL-CALL
(UF=11) interrogations. Verify that the transponder replies with
DF=11 replies that have the same MODE-S Address as the one
provided to the transponder via the discrete MODE-S Address
inputs.
Verify that the Transponder replies with DF=11 replies that have
the "CA" field set to one of the following "0, 4, 5, or 7".
NOTE: RTCA Document No. DO-181, paragraph 2.2.14.4.5,
Change 3, pages 4-5, totally redefined the "CA" filed.
Prior to Change 3, the "CA" field was defined for codes "0"
through "3" only, and the code remained fixed for the UUT after
the installation was completed.
Change 3, now defines codes "0, 4, 5, 6, and 7" with codes "1,
2, and 3" being "Not Defined". In addition, the "CA" field is no
longer fixed, but will be dynamic depending on the UUT status
at the time of reply.
17.11
ATCRBS-ONLY All-Call Interrogations (Appendix F, Paragraph
(i))
Interrogate the transponder with ATCRBS MODE-A ONLY
ALL-CALL interrogations that have the nominal pulse spacing
and signal level of -50 dBm. Verify that the transponder does
not reply to the interrogations. Essentially, a reply ratio NOT
GREATER THAN 1% constitutes the NO REPLY condition.
Interrogate the transponder with ATCRBS MODE-C ONLY
ALL-CALL interrogations having the nominal pulse spacing
and signal level of -50 dBm. Verify that the transponder does
not reply to the interrogations. Essentially, a reply ratio NOT
GREATER THAN 1% constitutes the NO REPLY condition.
17.12
Squitter Appendix F, Paragraph (j)
The requirement to demonstrate proper compliance with
this paragraph has been stated in steps 9.1 and 9.2 of this
procedure and will not be repeated here.
18.0
MAINTENANCE FAULT COUNTER RESET
The steps of this test may be accomplished using option 17 of
the automatic test program if so desired.
Final Performance (Customer Acceptance) Test. Cont.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
Page 1055
May 18/06
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
18.1
PROCEDURE
DESIRED RESULTS
Reset Function
After completion of all tests, reset the maintenance fault counter
by entering the current date as the Last Maintenance Date via
the ARINC control bus word having Label = 277, bits 31, 30 =
10, and data for the current date as follows:
BITS
DATA
29
Month (BCD Tens)
25 - 28
Month (BCD Units)
21 - 24
Day (BCD Tens)
17 - 20
Day (BCD Units)
13 - 16
Year (BCD Tens)
9 - 12
Year (BCD Units)
Fault counter has been reset.
18.2
____ (x)
Reset Function Close Out
Enter ARINC control word having Label = 277, bits 31, 30 =
11, and data as follows:
BITS
17 - 29
12 - 16
9 - 11
DATA
PAD
Verify that the UUT responds on the TDR Output Bus with
a ARINC word having Label = 351, bits 31, 30 = 11, and
maintenance date data in the same format as that given in
step 18.1.
19.0
Service Bulletin Tests
19.1
Verify SW Version Date
Send an ARINC label 277 with bits 31,30 set to 0 to request an
ARINC label 351 from the UUT.
Verify that the UUT responds by transmitting an ARINC label
351 data word on the TDR Output Bus that has bits 31, 30 set
to 0 and the Last Software Version date data given in the same
format as shown in the table of test 18.1.
Final Performance (Customer Acceptance) Test.
Table 1001/Table 34-50-96-99A-009-A01
34-50-96
Page 1056
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ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
Airborne Position Extended Squitter Test 9.3, Input Data and Results
Figure 1003/GRAPHIC 34-50-96-99B-021-A01
34-50-96
Page 1057
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ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
GPS Bus/Airborne Position Extended Squitter/Time Tag Verification Test 9.3A, Input Data and Results
Figure 1004/GRAPHIC 34-50-96-99B-022-A01
34-50-96
Page 1058
May 18/06
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
GPS Bus/Airborne Position Extended Squitter/Time Tag Verification Test 9.3B, Input Data and Results
Figure 1005/GRAPHIC 34-50-96-99B-023-A01
34-50-96
Page 1059
May 18/06
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
Surface Position Extended Squitter Test 9.5, Input Data and Results
Figure 1006/GRAPHIC 34-50-96-99B-024-A01
34-50-96
Page 1060
May 18/06
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
GPS Bus/Airborne Surface Position Extended Squitter/Time Tag Verification
Test 9.5A, Input Data and Results
Figure 1007/GRAPHIC 34-50-96-99B-025-A01
34-50-96
Page 1061
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ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
GPS Bus/Airborne Surface Position Extended Squitter/Time Tag Verification
Test 9.5B, Input Data and Results
Figure 1008/GRAPHIC 34-50-96-99B-026-A01
34-50-96
Page 1062
May 18/06
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
FMS/INS Primary Data Test 9.6, Input Data and Results
Figure 1009/GRAPHIC 34-50-96-99B-027-A01
34-50-96
Page 1063
May 18/06
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
FMS/INS Primary Data Test 9.6A, Input Data and Results
Figure 1010/GRAPHIC 34-50-96-99B-028-A01
34-50-96
Page 1064
May 18/06
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
Aircraft Identification Squitter Test 9.7, Input Data and Results
Figure 1011/GRAPHIC 34-50-96-99B-029-A01
34-50-96
Page 1065
May 18/06
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
Aircraft Identification Squitter Test 9.7A, Input Data and Results
Figure 1012/GRAPHIC 34-50-96-99B-030-A01
34-50-96
Page 1066
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ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
Aircraft Identification Message Test 9.7B, Input Data and Results
Figure 1013/GRAPHIC 34-50-96-99B-031-A01
34-50-96
Page 1067
May 18/06
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
AIS/ADSS Primary Data Test 9.8, Input Data and Results
Figure 1014/GRAPHIC 34-50-96-99B-032-A01
34-50-96
Page 1068
May 18/06
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
SIL Designator Requirements Test 14A.0, Input Data and Results
Figure 1015/GRAPHIC 34-50-96-99B-033-A01
34-50-96
Page 1069
May 18/06
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
Configuration Select S0 Discrete Test 16.10A.1, Input Data and Results
Figure 1016/GRAPHIC 34-50-96-99B-034-A01
34-50-96
Page 1070
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ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
Configuration Select S1 Discrete Test 16.10A.2, Input Data and Results
Figure 1017/GRAPHIC 34-50-96-99B-035-A01
34-50-96
Page 1071
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ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
Airborne Position Extended Squitter Test 9.3C, Input Data and Results
Figure 1018/GRAPHIC 34-50-96-99B-089-A01
34-50-96
Page 1072
May 07/07
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
GPS Bus / Airborne Position Extended Squitter / Time Tag Test 9.3D, Input Data and Results
Figure 1019/GRAPHIC 34-50-96-99B-090-A01
34-50-96
Page 1072.1
May 07/07
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
GPS Bus / Surface Position Extended Squitter / Time Tag Verification Test 9.5C, Input Data and Results
Figure 1020/GRAPHIC 34-50-96-99B-091-A01
34-50-96
Page 1072.2
May 07/07
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
GPS Bus / Surface Position Extended Squitter / Time Tag Verification Test 9.5D
Figure 1021/GRAPHIC 34-50-96-99B-092-A01
34-50-96
Page 1072.3
May 07/07
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
Aircraft Identification Massage (-408 ONLY) Test 9.7C
Figure 1022/GRAPHIC 34-50-96-99B-093-A01
34-50-96
Page 1072.4
May 07/07
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
Aircraft Identification Massage (-308, -309 ONLY) Test 9.7D
Figure 1023/GRAPHIC 34-50-96-99B-094-A01
34-50-96
Page 1072.5
Jun 20/08
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
AIS/ADSS Primary Data (-308, -309, -408, -409) Test 9.8B
Figure 1024/GRAPHIC 34-50-96-99B-095-A01
34-50-96
Page 1072.6
Jun 20/08
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
SUBTASK 34-50-96-810-005-A01
B. TDR-94/94D Alignment Procedures
STEP
PROCEDURE
DESIRED RESULTS
0.0
SETUP INSTRUCTIONS
0.1
Remove UUT dust cover. Connect TDR-94/94D as shown
in Figure 1002/GRAPHIC 34-50-96-99B-036-A01 or Figure
1001/GRAPHIC 34-50-96-99B-020-A01. Test equipment item
numbers (XX) that appear in the test setup diagrams are identified
in Table 9003/Table 34-50-96-99A-042-A01 or Table 9002/Table
34-50-96-99A-032-A01 of the Special Tools, Fixtures, and
Equipment section.
0.2
Set up IFR 1400C front panel as follows:
SWITCH
DISPLAY SELECT
DME REPLY EFFICENXPDR MODE
TACAN
DBL INTERR
/INTRF PULSE
PRF
SQTR
IDENT
F2/P2-F1/P1
XPDR P2/P3 DEV
P2, P3
FREQ
FUNCTION SELECT
DELTA F
DME P2 DEV, P2
XPDR PULSE WIDTH
SLS/ECHO
RANGE/VEL/ACCEL
IN/OUT, -1 NMI/NORM
RF LEVEL -DBM
CW/NORM/OFF
SUPPRESSOR
SYNC T0/TAC/TD
SUPPRESSOR VAR
CAL MARKS
AUTO MAN/MAN STEP
FREQ STEP RATE
POSITION
FREQ MHZ
OFF
000.0
OFF
50
ON
OFF
F2/P2
0.00
CAL, CAL
1030
XPDR
0.00 OFF
0.0, CAL
0.80 CAL
-0, OFF
00000
OUT, NORM
90
NORM
OFF
T0
ADJ to 15V P-P
1.45 US
MAN
OFF
Alignment Procedure Cont.
Table 1002/Table 34-50-96-99A-010-A01
34-50-96
Page 1072.7/1072.8
May 07/07
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
0.3
PROCEDURE
Set up rear of ATC-1400C/S1403C test set as follows:
SWITCH
DECODER
EQUALIZER
SELF-INTERR
INST DIM
ADDRESS
0.4
POSITION
NARROW
OFF
OFF
LOW
10101100
Set up front panel of 5359A time synthesizer as follows:
SWITCH
SLOPE
LEVEL
SYNC DELAY
OUTPUT POLARITY
AMPLITUDE
OFFSET
0.5
DESIRED RESULTS
POSITION
+2V
PRESET
NORM, POS
ADJ to 2.5V
OFF, 0
Set up rear of 5359A time synthesizer as follows:
SWITCH
POSITION
EXT TIMING
DISABLE
EVENTS,SLOPE
FREQ-STD
INT
ADDRESS
0001000
NOTE: Interrogation power levels and transmitter output power
levels specified in this document are referenced to the
rear connector(s) of the Unit Under Test (UUT). The
insertion loss of coaxial cables between the UUT and
the test equipment must be accounted for.
NOTE: Perform alignment steps 1.X for Receiver IF/LVPS
Assembly, CPN 687-0727-004. Perform alignment steps
2.X for Receiver IF/LVPS Assembly, CPN 687-0727-005.
1.0
Receiver IF/LVPS Assembly, Alignment for CPN 687-0727-004 or prior.
1.1
Monitor the +5 V dc output at J7-26 with a DVM. Adjust A7R507 if
necessary
1.2
Monitor J7-33 on Video Processor A6 with an oscilloscope.
Verify a reading between 4.99
to 5.01 V dc.
Alignment Procedure Cont.
Table 1002/Table 34-50-96-99A-010-A01
34-50-96
Page 1073
Apr 17/07
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
PROCEDURE
DESIRED RESULTS
1.3
Set the MODE-S test set to generate ATCRBS MODE-C
interrogations and apply to the bottom antenna connector. Set the
interrogation rate to 450 per second
1.4
a. Set the MODE-S test set signal strength to -79 dBm. Monitor
the Bottom Video signal at A6P22-Pin 33. Adjust A7R131 fully
clockwise.
Adjust A7R140 for an
observed video level of 0.7
volts peak.
NOTE: The oscilloscope must be set to the averaging
mode to properly measure the video pulse at the
low signal levels required.
b. Set the MODE-S test set signal strength to -77 dBm.
Adjust A7R131 for an
observed video level of 0.7
volts peak.
c. Verify that the reply rate is between 90% and 100%. If not,
readjust A7R140 for desired result.
Reply rate is between 90%
and 100%.
1.5
Set the signal strength to -31 dBm. Adjust A7R133 for desired
results.
Amplitude of the P1 pulse at
J7-33 is 5.00 ±0.05 volts.
1.6
Repeat steps 1.4 and 1.5 as required.
1.7
Monitor the positive end of A6C67 on top side of the card.
1.8
Interrogate with a normal MODE-S signal at -27 dBm. Adjust
A6R118 until the ditch-slope waveform resulting from P1 has the
desired results.
1.9
Do steps 1.10 thru 1.16 for the TDR-94D only. Apply MODE-C
interrogations to the UUT top antenna connector.
1.10
a. Set the MODE-S test set signal strength to -79 dBm. Monitor
the Top Video signal at A6P22-Pin 31. Adjust A7R124 fully
clockwise.
16.2 ±0.2 microseconds wide
at its base.
Adjust A7R111 for an
observed video level of 0.7
volts peak.
NOTE: The oscilloscope must be set to the averaging
mode to properly measure the video pulse at the
low signal levels required.
b. Set the MODE-S test set signal strength to -77 dBm.
Adjust A7R124 for an
observed video level of 0.7
volts peak.
Alignment Procedure Cont.
Table 1002/Table 34-50-96-99A-010-A01
34-50-96
Page 1074
May 18/06
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
1.11
PROCEDURE
DESIRED RESULTS
Verify that the reply rate is between 90% and 100%. If not,
readjust A7R111 for a reply rate between 90% and 100%.
NOTE: If the Minimum Trigger Level (MTL) cannot be established
within the specified limits, or if the MTL does not
stay within the specified limits over the operational
temperature range, the A7R127 (for the Top channel)
and/or A7R137 (for the Bottom channel) (CPN
705-3543-020) may be added as needed.
1.12
Set the MODE-S test set signal strength for -31 dBm. Adjust
A7R123 for desired results.
Amplitude of the P1 pulse at
J7-31 is 5.00 ±0.05 volts.
1.13
Repeat steps 1.11 and 1.12 as required.
1.14
a. Set the MODE-S test set signal strength to -50 dBm. Measure
and note the amplitude of the P1 pulse at J7-31.
____ V
b. Apply the same input signal level to the bottom channel.
Measure and note the amplitude of the P1 pulse at J7-33.
_____V
c. Verify that the two amplitudes are within 0.1 volts of each
other. If this is not the case, reduce the stronger of the two
measurements by adjusting the appropriate Slope Adjust,
A7R123 or A7R133, until the difference is less than 0.1 volts.
Voltage difference should be
less than 0.1 volt
NOTE: If this readjustment is performed, then the MTL
must be readjusted in accordance with either step
1.4 or 1.11, whichever is appropriate for the Top or
Bottom channel requiring adjustment.
1.15
Monitor the positive end of A6C59 on the Video Processor board.
1.16
Set the MODE-S test set signal strength to -27 dBm. Adjust
A6R117 on the Video Processor board such that the ditch-slope
waveform resulting from P1 has the desired results.
16.2 ±0.2 ȝs wide at its base
NOTE: Extra care must be taken in the adjustments made in
the following steps 1.17 through 1.19. DPSK trimmer
capacitor A7C301 adjustments should be made in very
small increments or steps. These adjustments are critical
to the performance of the UUT. Capacitor A7C301 should
only be adjusted at the board or card level (if possible).
Alignment Procedure Cont.
Table 1002/Table 34-50-96-99A-010-A01
34-50-96
Page 1075
Apr 17/07
ROCKWELL COLLINS
COMPONENT MAINTENANCE MANUAL with IPL
TDR-94, PART NO 622-9352
STEP
1.17
PROCEDURE
DESIRED RESULTS
To align the DPSK Demodulator VCO, interrogate
the bottom channel with MODE-S ONLY ALL-CALL
interrogations having a signal strength of -60 dBm.
_____
_____
Vary the interrogation center frequency above 1030 MHz until the
reply rate reduces to 90% and note the frequency as the upper
frequency limit.
Vary the interrogation center frequency below 1030 MHz and note
the frequency as the lower frequency limit.
Adjust A7C306 such that the two limit frequencies are equidistant
from 1030.00 MHz. Verify that both frequencies are removed from
1030 MHz by at least 0.6 MHz. If exact centering of the center
frequency is difficult to achieve, the adjustment should be made
to slightly favor the higher frequency limit.
1.18
The IF bandwidth may be adjusted with A7R305. Adjustment
of A7R305 is critical to the performance of the unit and should
not be performed at the top-level assembly unless necessary. If
adjustment of A7R205 is necessary, then the frequency centering
adjustments performed in step 1.17 must be rechecked.
1.19
To align the DPSK demodulator VCO, interrogate the top channel
with a Mode-S Only All-Call interrogations having a signal level of
-60 dBm and a center frequency of 1030.0 MHz. Monitor A7TP303
with the oscilloscope and slowly adjustA7C352 for the cleanest
and most square observed signal pulses.
NOTE: DPSK adjustments are interactive. Steps 1.17
through 1.19 should be rechecked prior to continuing
with the following procedures.
1.20
Monitor J7-33. Interrogate the bottom channel with MODE-A
or MODE-C interrogations having a signal level of -67 dBm
and measure the video amplitude of P1 observed. Turn off all
interrogations to the UUT.
NOTE: Enable the Self-Test function and adjust A7R122 such
that the observed self-test signal P1 is equal to the video
amplitude previously observed within ±0.2 volts.
Alignment Procedure Cont.
Table 1002/Table 34-50-96-99A-010-A01
34-50-96
Page 1076
May 18/06

---

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Title                           : TDR-94/94D (-004 Status and Higher) ATC/Mode S Transponder (ICA)
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