TDR 94 5230775652

7/22/2019 TDR 94 5230775652

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instruction

book

TDR-94/94D ATC/Mode S

Transponder System

© Copyright 2007 Rockwell Collins, Inc. All rights reserved.

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1/2

March 07, 2007

TO: HOLDERS OF ROCKWELL COLLINS® TDR-94/94D ATC/Mode STRANSPONDER SYSTEM (CPN 523-0775652)

DESCRIPTION OF REVISION NO 1

This page shows all pages of the manual that are added, changed, or removed. Replace thespecified pages of the manual with the new pages supplied. Record the applicable data on theRecord of Revisions page.

All changed pages keep data necessary to do maintenance on all equipment models. Black barson the side of the page identify changes.

This revision does not include copies of service bulletins (SB) and service information letters(SIL) applicable to this equipment. This manual includes all data from applicable SBs and SILs.The front area of this manual contains a list of all released SBs and SILs. For this revision, movethe SBs and SILs from your manual to this manual. Discard all replaced pages.

PAGE NUMBERDESCRIPTION OF REVISION

AND REASON FOR CHANGE

SERVICE

BULLETINEFFECTIVITY

RTR-1/RTR-2 Revised to reflect current revision. None

General InformationTOC, LEP, RR

Revised LEP entries. None

General Informationpages 1-2

Incorporated TR2 adding 622-9352-007and 622-9210-007.

None

General Informationpages 1-11

Incorporated TR1 adding MMT-150Mount for BA609 installations.

None

Theory of OperationTOC, LEP, RR


Maintenance TOC,

LEP, RR


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instruction book

Rockwell Collins, Inc.

Cedar Rapids, Iowa 52498

T-1

Printed in the United States of America

© Copyright 2007 Rockwell Collins, Inc. All rights reserved.

523-0775652-12711A7th Edition, June 15/1995

7th Edition, 1st Revision, March 7/2007

TDR-94/94D ATC/MODE STransponder System

This publication includes:

General Information 523-0775653

Operation 523-0775655 Theory of Operation 523-0775656 Maintenance 523-0775657

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ROCKWELL COLLINS

INSTRUCTION BOOK

TDR-94/94D, PART NO 622-9352/622-9210

T-2Mar 7/07

PROPRIETARY NOTICE

NOTICE: FREEDOM OF INFORMATION ACT (5 USC 552) AND DISCLOSURE OFCONFIDENTIAL INFORMATION GENERALLY (18 USC 1905)This document and the information disclosed herein are proprietary data of Rockwell Collins, Inc.Neither this document nor the information contained herein shall be used, reproduced, or disclosedto others without the written authorization of Rockwell Collins, Inc., except to the extent required forinstallation or maintenance of recipient’s equipment. This document is being furnished inconfidence by Rockwell Collins, Inc. The information disclosed herein falls within exemption (b) (4)of 5 USC 552 and the prohibitions of 18 USC 1905.

SOFTWARE COPYRIGHT NOTICE

© COPYRIGHT 1989 - 1995 ROCKWELL COLLINS, INC. ALL RIGHTS RESERVED. All software resident in this equipment is protected by copyright.

We try to supply manuals that are free of errors, but some can occur. If a problem is found with thismanual, you can send the necessary data to Rockwell Collins. When you report a specifiedproblem, give short instructions. Include the manual part number, the paragraph or figure number,and the page number.

To send data to Rockwell Collins about this manual:

Address: Rockwell Collins, Inc.350 Collins Road NE, M/S 153-250Cedar Rapids, IA 52498-0001

Email: [email protected]

To get more manuals:

Address: Rockwell Collins, Inc.Customer Response Center400 Collins Road NE, M/S 133-100

Cedar Rapids, IA 52498-0001

TELEPHONE: 1.888.265.5467INTERNATIONAL: 1.319.265.5467FAX: 319.295.4941

Email: [email protected]

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SPECI FIC ADVISORIE S FOR THE <EQ TYPE >

W a r n i n g

Rockwell In terna tional does not t ake the responsibility for cert ifi cation of t he TDR-94/94D wh en used wit h

equipment other than those covered by the Rockwell International Collins Avionics safety analysis.

W a r n i n g

Electronic control sy stems, such a s aut opilots, engine contr ols, fuel controls, t empera ture sensors, etc, usedfor aircra ft control can be susceptible to tra nsmissions from communicat ions t ra nsceivers, DME ’s, tr an spond-

ers, etc, that can interfere with a ircraft opera tions. I f such a situa tion occurs, discontinue transm ission or

select a different frequency. I f necessar y, turn off the ra dio.

W a r n i n g

Service personnel are to obey sta nda rd sa fety precaut ions, such as wea ring sa fety glasses, to prevent persona

injury while installing or doing maintenance on this unit .

W a r n i n g

U se care w hen using seala nts, solvents, a nd other chemical compounds. Do not expose to excessive heat or

open fla me. U se adequa te ventilat ion. Avoid prolonged breat hing of vapors an d avoid prolonged contact w ithsk in . Ob serve a l l ca u t io n s a n d w a rn in g s g iven b y t h e m a n u f a ct u re r.

W a r n i n g

Re m ove a l l p o we r t o t h e u n it b ef ore d isa sse m b lin g i t . D isa sse m b lin g t h e u n it w it h p o we r con n e ct e d is

d a n g e rou s t o l if e a n d m a y ca u se volt a g e t ra n sien t s t h a t ca n d a m a g e t h e u n it .

W a r n i n g

This unit may have components that contain materials (such as beryllium oxide, acids, l ithium, radioactive

ma terial, mercury, etc) tha t can be ha zar dous to your hea lth. I f the component enclosure is broken, handle

th e component in a ccorda nce with OS HA requir ements 29CFR 1910.1000 or superseding document s to prevent

personal conta ct with or inha lat ion of hazar dous materia ls. Since it is virtua lly impossible to determine wh ichcomponents do or do not contain such hazardous materials, do not open or disassemble components for any

reason.

W a r n i n g

Th is u n it e xh ib it s a h ig h d e g ree o f f u n ct ion a l re lia b i li t y. N e ve rt h eless, u se rs m u st k n ow t h a t i t is n ot

practical to monitor for all conceivable system failures and, however unlikely, it is possible that erroneous

operat ion could occur wit hout a fault indicat ion. The pilot ha s th e responsibility to fi nd such a n occurrence

by means of cross-checks with redundant or correlated data available in the cockpit .

C a u t i o n

Turn off pow er before disconnecting a ny unit from w iring. Disconnecting the unit wit hout tur ning power of

m a y ca u se vo lt a g e t ra n sie n t s t h a t ca n d a m a g e t h e u n it .

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C a u t i o n

Th is u n it con t a in s e lect rost a t ic d isch a rg e se n si t ive (E S D S ) com p on e n t s a n d E S D S a sse m b lies t h a t ca n b e

d a m a g ed b y st a t ic vol t a g e s. Alt h ou g h m ost E S D S com p on e n t s con t a in in t e rn a l p rot e ct ion circuit s , g o od

procedures dictate careful handling of all ESDS components and ESDS assemblies.

Ob ey t h e p reca u t io n s g iven b elow wh e n m o vin g , t o u ch in g , o r re p a irin g a l l E S D S com p on e n t s a n d u n it s

containing ESDS components.

a . D e en e rg iz e or re m o ve a l l p owe r, s ig n a l so u rce s, a n d loa d s u sed w it h t h e u n it .b. P lace the unit on a work surface that can conduct electricity (is grounded).

c. G round the repair operat or through a conductive wr ist stra p or other device using a 470-kΩ or 1-MΩ series

resistor t o prevent operat or injury.

d . G rou n d a n y t o ols (a n d so ld erin g equ ip m en t ) t h a t w il l con t a ct t h e u n it . Co n t a ct wit h t h e op era t or ’s h a n d

is a sufficient ground for hand tools that are electrically isolated.

e. All ESD S replacement components a re shipped in conductive foam or tubes an d must be stored in their

shipping containers until installed.

f . E S D S d e vice s a n d a sse m blie s, t h a t a re re m oved f rom a u n it , m u st im m e dia t e ly b e pu t o n t h e con d u ct ive

w ork surface or in conductive conta iners.

g. P lace repaired or disconnected circuit cards in a luminum foil or in plast ic bags th at ha ve a layer of, or ar e

m a d e wit h , con d u ct ive m a t e ria l .

h. Do not touch E SD S devices/assemblies or remove them from their conta iners until they a re needed.

F a i lu re t o h a n d le E S D S d e vice s a s d e scrib ed a b ove ca n p erm a n e n t ly d a m a g e t h e m . Th is d a m a g e ca n ca u se

immediate or prema ture d evice failure.

i i

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RTR-1/RTR-2

Mar 7/07

ROCKWELL COLLINS

INSTRUCTION BOOK

TDR-94/94D, PART NO 622-9352/622-9210

RECORD OF TEMPORARY REVISIONS

TEMPORARYREV NO

PAGE NUMBERDATE

ISSUEDBY

DATEREMOVED

BY

1 1-11 Aug 15/00 Rockwell Collins Mar 7/07 Rockwell Collins

2 1-2 Nov 22/02 Rockwell Collins Mar 7/07 Rockwell Collins

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523-0775653-0061186th Edition, 15 June 1995

TDR-94/94D

ATC/Mode STransponder System

General Information

table of contents

P a r a g r a p h P a g e

1.1 INTR ODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 -1

1.2 PURPOSE OF EQUIPMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-1

1.3 EQUIPMENT REQUIRED BUT NOT SUPPLIE D . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-1

1.4 REL ATED PUBLICATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-2

1.5 STORAGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-12

1.6 REL ATED SERVICE BULLE TINS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-12

NOTICE: This section replaces fifth edition dated 5 May 1993.

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Page No Issue

* Title............................................7 Mar 07

* List of Effective Pages ...............7 Mar 07

1-1.............................................. 5 May 93

* 1-2...............................................7 Mar 07

1-3 thru 1-5 ............................... 5 May 93

1-6 thru 1-9 .............................. 15 Jun 95

1-10............................................ 5 May 93

* 1-11.............................................7 Mar 071-12 thru 1-13............................ 5 May 93

1-14 Blank................................. 5 May 93

Record of RevisionsRETAIN THIS RECORD IN THE FRONT OF THE MANUAL. ON RECEIPT OF

REVISIONS, INSERT REVISED PAGES IN THE MANUAL, AND ENTER DATE

INSERTED AND INITIALS.

REV/

ED NO

REVISION

DATE

INSERTION

DATE/BY

SB NUMBER IN-

CLUDED

REV

NO

REVISION

DATE

INSERTION

DATE/BY

SB NUMBER IN-

CLUDED

0 / 1 4 Apr 89 None

0 / 2 4 Apr 90 None

0 / 3 29 Apr 91 None

0 / 4 6 Jan 92 None

0 / 5 5 May 93 See Table 1-6

0 / 6 15 Jun 95 See Table 1-6

1 / 6 7 Mar 07 See Table 1-6

List of Effective Pages *The asterisk indicates pages changed, added, or deleted by the current change.

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section Igeneral information

1.1 INTRODUCTION

This publication provides all the specifications,

principles of opera tion, a nd informa tion necessar y

to test and troubleshoot the TDR-94 and TDR-94D

Mode S Tra nsponder S ystem in t he a irplane. The

informa tion includes a bench testing procedure t o

verify the performa nce capa bility before installa -

t ion of a new or newly repaired transponder.

Refer to table 1-1 for a list of equipment covered

TD R- 94/ 94D M ode S T r ansponder

Figur e 1-1

in t his ma nua l a nd ta ble 1-2 for t he TDR -94/94D

specifi cat ions. Ta ble 1-3 is a listing of environ-

menta l requirements for DO-160B. Table 1-4 is a

listing of publications rela ted to the TDR -94/94D.

Table 1-6 is a list ing of Service Bulletins a nd Ser-

vice Information Letters that have been released

u p t o t h e d a t e o f t h is m a n u a l e d it ion . F ig u re 1-1

is a n overa ll view of th e TD R-94/94D.

1.1.1 General Description

The TDR -94/94D Tra nspond er is a solid-st a te,

airborne, air traffic control (ATC) transponder.

The TDR -94 or TD R-94D Tra nspond er is norm a lly

mounted in a MMT-150 Modular Mounting Tra y

an d controlled by an ATC contr ol like the the

CTL-92/92A Control. Refer t o the P ro Line I I

Comm/Nav/P ulse Sy stem Inst alla t ion Ma nua l for

a lis ti ng of t he v a ri ous C TL-92/92A, R TU -870A/T

and other controls available for use with the TDR-

94/94D. The TDR -94D Tra nspond er is a D ivers ity

version; i .e . , i t is capable of transmitt ing and re-

ceiving on either of tw o ant ennas. The TDR-94 is

a non-diversity model. The TDR -94D is fully

compatible with TCAS II system installat ions re-

qu irin g a n t e n n a d iversi t y. E i t h e r of t wo a n t e n n a

ty pes can be u sed w ith the TDR -94/94D a s sh own

in table 1-1.

1.2 PURPOSE OF E QUIPMENT

The TDR -94/94D is a n integr a l pa rt of th e Air

Tra ffic Control Rada r B eacon Syst em (ATCRB S).

The TDR-94/94D opera tes in mode A by respond -

in g t o n o rm a l b e a con ra d a r in t e rrog a t io n s. Th is

mode provides identifi cation of tr an sponder-

equipped a irplanes on the ground controller ’s plan

posit ion indicat ion (P P I). I f the installa t ion is

equipped w ith a compat ible alt itude encoder, it

ca n o pe ra t e in m o d e C a n d p rovid e a l t i t u d e d a t a

lon g w it h t h e n o rm a l re ply. I n t h e m o d e S

scheme, each airplane is assigned a unique identi-fi ca t ion cod e wh ich a l lows a u t o m a t ic a n d u n iqu e

interrogation and display of a specific airplane.

The airplane identification is assigned at installa-

t ion and is based on the identification (tail) num-

ber. The unique identifi er is required in TCAS

opera tion. In a ddition, th e TDR -94/94D ca n re-

ceive a n d se n d d a t a l in k m essa g e s t h a t a re re -

quired for ATC a utomat ion. The added da ta link

capability allows the transponder to perform addi-

t ion a l a ir t ra f f ic con t ro l a n d a irp la n e se pa ra t ion

assurance (ASA) functions.

1.3 EQUIPMENT R EQUIRE D BUT NOT SUP-PLIED

Ta ble 1-4 lists th e equipment requir ed for proper

opera tion of the TDR-94/94D but is n ot su pplied

wit h t h e u n it . E qu iva le n t equ ipm e n t m a y b e su b-

st i t u t e d .

5/ 5/ 1993 1-1

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general information 523-0775653

7 March 2007 1-2

1.4 RELATED PUBLICATIONS

Table 1-5 lists publications related to TDR-94/94D

operation.

Table 1-1. Equipment Covered.

COLLINS

EQUIPMENT DESCRIPTION PART NUMBER

TDR-94

ANT-42

MMT-150

Mode A, C, and S ATC Transponder

L-band antenna for transponder or DME. Uses ac signal coupling to radiating

element.

Mounting Tray for TDR-94/94D

622-9352-003

622-6591-001

622-9672-003

FOR INSTALLATIONS USING CSDB TUNING

CTL-92

CTL-92T

Pro Line II, ATC Control (uses CSDB data format). Refer to Pro Line II

Comm/Nav/Pulse System Installation Manual for available options.

Transponder and TCAS Control, used in conjunction with CTL-92/92A to add TCAS

control functions. Refer to TCAS-94 Traffic Alert and Collision Avoidance System

Installation Manual for available options.

622-6523-XXX

622-9614-XXX

FOR INSTALLATIONS USING ARING 429 TUNING

RTU-870A

RTU-870T

Remote Tuning Unit, gives centralized control and display of the frequency/ATC

code and modes of the Collins -4XX series of General Aviation equipment. Refer to

Pro Line II Comm/Nav/Pulse System Installation Manual for available options.

RTU-870T Remote Tuning Unit, same as RTU-870A except includes TCAS control

capability. Refer to Pro Line II Comm/NAV/Pulse Installation Manual for available

options.

622-9346-XXX

622-9856-XXX

ALTERNATE MODELS AVAILABLE

TDR-94DTDR-94

TDR-94D

TDR-94

TDR-94D

TDR-94/94D

CTL-92A

237Z-1

TTC-920G

TDR-94D Same as TDR-94 except with diversity capabilityThe -007 version of the TDR-94 supports both Elementary and Enhanced Surveil-

lance requirements. Existing versions of the TDR-94 can be updated to Elementary

Enhanced Surveillance functionality by incorporating SB 13 and SB 501.

The -007 version of the TDR-94D supports both Elementary and Enhanced Sur-

veillance requirements. Existing versions of the TDR-94D can be updated to Ele-

mentary Enhanced Surveillance functionality by incorporating SB 13 and SB 501.

Same as TDR-94 -003 except without TCAS compatibility features. Can be used in

installations without TCAS and where diversity is not required.

Same as TDR-94D -003 except without TCAS compatibility features. Can be used in

installations without TCAS and where diversity is needed.

These models are no longer supported. All existing -001 units should be upgraded to

at least -002.

Same as CTL-92 except with enhanced display capability Refer to Pro Line II

Comm/Nav/Pulse System Installation Manual for available options.

Similar to ANT-42 except uses dc coupling to radiating element.

Transponder/TCAS Control. Dedicated control for TCAS and Mode S Transponder.

Refer to TCAS-94 Traffic Alert and Collision Avoidance System Installation

Manual for available options.

622-9210-003622-9352-007

622-9210-007

622-9352-002

622-9210-002

622-9352-001

622-9210-001

622-8740-XXX

522-2632-001

822-0078-XXX

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Table 1-2. Equ ipm ent Specificati ons.

C H ARAC TE RI S TI C S P E C I F I C ATI ON

Certification

TSO

FAA TS O-C 112, cla ss 2A

RTC A D 0-181, D 0-144

S oft w a r e D O-178A, level 2

E U ROC AE E D -12A

Deutsche Bundespost

F TZ

A44652010

I C AO Annex 10

Environmental

FAA D O-160B , r efer t o t a ble 1-3 for a dd it ion al in for ma t ion

E U ROC AE E D -12A

Physical

Size

H eight 84.6 m m (3.33 in)

Widt h 124.5 mm (4.90 in)

Lengt h 317.5 mm (12.50 in)

Weight 3.6 kg (8.5 lb)

M ou n t in g M MT-150; 1/2 ATR , s h or t , d w a r f ( R ef er t o P r o L in e I I C om m /N AV/P u l se I n st a l la t i on

Manua l for a ddit ional informat ion.)

Mating Connector Thinline II , qty 2, 60-pin (Kits: CP N: 628-8661-001/002 or 628-8660-001/002) ( Refer to Pro

Line II Comm/NAV/P ulse Inst alla tion Ma nua l for a dditional informa tion.)

Ti m e b et w e e n ov er h a u l O n c on d it i on of f a i lu r e o r a s r e q u ir e d b y F e d er a l R e gu l a t i on s (s e e b el ow )

Regulatory requirement for

flightl ine test

FAR 91.413 ATC TRANSPONDER TESTS AND INSPECTIONS.

"(a) No person may use an ATC t ransponder t hat is specified in P art 125 §91.24 (a),

§121.345, §127.123 (b), or §135.143 (c) of this chapter unless, within the preceding 24

calendar months, tha t ATC tra nsponder has been t ested and inspected and found t o comply

with Appendix F of P art 43 of this chapter ; a nd fol lowing any instal lat ion or maintenance on

an ATC transponder where data correspondence error could be introduced, the integrated

system ha s been tested, inspected, and found to comply with para graph Appendix E of Pa rt

43 of this chapter."

P ow er r eq uir em en ts 27.5 ± 2.5 V d c a t 28 w a t ts n om in a l, 30 w a t ts m a xim um

Tra nsmitt er

F req uency 1090 MH z, ± 1 MH z

P ow er out put 250 w at ts min, 625 w at ts ma xim um

Loa d im peda nce 50Ω nominal

VS WR 1.5:1 service ma x., 3:1 surviva l

5/ 5/ 1993 1-3

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Table 1-2. Equ ipm ent S pecifications. (cont’d)


D a t a b u s :

C S D B

S tr uct ur e 8-bit s/by te, 6-by tes /block

Ra te 12.5 B a ud, 10-block/sec nomina l, 18 ma x

D a ta blocks (a ll la bels a re in h exa decim al for m)

A5: sy nc; input

A0: al t i tude dat a; input

1E: ATC code/a ltit ude; in put or outpu t

1F: ATC data; output

F3: diagnostic data ; output

ARINC 429

S tr uct ur e 8-bit s/by te, 4-by tes /w or d

Ra t e 5-w ords/sec min

D at a la bels (a ll la bels a re in oct al form )

*013: TDR a nd TCAS control; inpu t/outpu t

*015: Altit ude select limits , input /outpu t

*016: Mode S control; inpu t/output

*031: ATC Tra nsponder Cont rol, inpu t/output

*200: Gillha m a ltitude encoder dat a; input/output

*203: TDR a ltitude da ta to TCAS; input/output

204: TDR corrected barometric altitude to TCAS; output

272: TCAS coordination data, part 1; output

273: TCAS data for downlink message formats 16, 20, 21; input

274: TCAS coordination data, part 2; output

274: TCAS data for downlink message formats 0 and 16; input

275: TCAS control, pa rt 1; output

275: TCAS acknowledge; input

276: TCAS control, pa rt 2; output

277: TCAS acknowledge; input

277: Diagnostic data request ; input350: Maintenance dat a; output

371: Equipment ident; output

* These labels a re norma lly echoed, a nd/or passed through to th e TCAS, a s received

except for the S SM which may be different depending on t he sta te of the tra nsponder.

Tu n in g i np ut s M on it or ed on ly i f B u r s t M od e (P 2 -59) i s n ot s el ect e d; i .e ., P 2 -59 i s op en

P 2-31

P 2-32

C S D B , A

C S D B , B

P 2-17

P 2-18

ARINC 429, A (tune input port A)

ARINC 429, B (tune input port A)

P 2-13

P 2-14

ARINC 429, A (tune input port B)

ARINC 429, B (tune input port B)

P 2-21P 2-22

ARINC 429, A (tune input port C)ARINC 429, B (tune input port C)

Altitude inputs

P 2-33

P 2-34

CSD B, A (al t i tude input port A)

CSDB, B (al t i tude input port A)

P 2-35

P 3-36

CSDB, A (al t i tude input port B)

CSDB, B (al t i tude input port B)

5/ 5/ 1993 1-5

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Table 1-2. Equ ipm ent Sp ecifications. (cont’d)


Inpu t/Out put

Altitude inputs (cont’d)

P 2-25P 2-26

ARINC 429/575, A (alt itud e input port A)ARINC 429/575, B (altit ude in put port A)

P 2-29

P 2-30

ARINC 429/575, A (a ltit ude in put port B )

ARINC 429/575, B (altit ude inpu t port B )

D a t a o u t p u t s

P 2-23

P 2-24

CSDB, A (Bus 1)

C S D B , B (B u s 1 )

P 2-27

P 2-28

CSDB, A (Bus 2)

C S D B , B (B u s 2 )

P 2-15

P 2-16

ARINC 429, A (Port A)

ARINC 429, B (Port A)

P 2-19P 2-20

ARINC 429, A (Port B)ARINC 429, B (Port B)

Peripheral data

P 2-1

P 2-2

ARINC 429, A (Comm A/B input )

ARINC 429, B (Comm A/B input )

P 2-3

P 2-4

ARINC 429, A (Comm A/B output )

ARINC 429, B (Comm A/B output )

P 2-5

P 2-6

ARINC 429, A (Comm C /D input )

ARINC 429, B (Comm C /D inpu t)

P 2-7

P 2-8

ARINC 429, A (Comm C /D out put)

ARINC 429, B (Comm C /D out put)

P 2-9P 2-10

ARINC 429, A (TCAS coord da ta input)ARINC 429, B (TCAS coord data input)

P 2-11

P 2-12

ARINC 429, A (TCAS coord da ta output)

ARINC 429, B (TCAS coord data output)

Discrete inputs

P 1-1

P 1-2

P 1-3

P 1-4

P 1-5

P 1-6

P 1-7

P 1-8

P 1-9P 1-10

P 1-11

P 1-12

B4, ARINC 572 altitude input



A4, ARINC 572 altitude input



D4, ARINC 572 altitude input

D2, ARINC 572 altitude input

C4, ARINC 572 altitude inputC2, ARINC 572 altitude input

C1, ARINC 572 altitude input

Common, ARINC 572 altitude input

Mode S address discretes

P 1-32

P 1-33

P 1-34

Common

B 1

B 2

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Inpu t/Out put (continued )

Mode S address discretes

(cont’d)

P 1-35

P 1-36

P 1-37

P 1-38

P 1-39

P 1-40

P 1-41

P 1-42

P 1-43

P 1-44

P 1-45

P 1-46

P 1-47

P 1-48

P 1-49P 1-50

P 1-51

P 1-52

P 1-53

P 1-54

P 1-55

P 1-56

B 3

B 4

B 5

B 6

B 7

B 8

B 9

B 10

B 11

B 12

B 13

B 14

B 15

B 16

B 17B 18

B 19

B 20

B 21

B 22

B 23

B 24

Single discrete stra ps

P 2-51 Ant enna , dua l/single select (gnd = single)

P 2-56 C SD B/ARI NC 429 cont rol select (gnd = C SD B)

P 2-60 AD LP in st a lled (gn d = AD LP in clu ded in in st a lla t ion )

P 1-13 TC AS in st a lled (g nd = TC AS in clu ded in in st a lla t ion )Note: There is no provision for TCAS control in CSD B . Therefore, the TDR-94D will

not report TCAS capability in its replies to interrogations when CSDB is enabled (P2-56

grounded) even if TCAS is selected (P1-13 grounded) and dual antenna enabled (P2-51

open).

Discret e I/O

P 2-55 S t a ndby discr et e (gnd = in st a ndby )

P 1 -28 (-003) Au t om a t i c a l t it u d e s el ect (g n d = a u t o a l t s el ect e na b le d)

P 1 -14 C on t rol Al tit u de S ele ct (S ee C om bin a t ion D is cr et es b el ow ) (g nd = p or t A a l ti tu de d a t a

supplied on control port, port B same as open), (open = ports A and B altitude selectable via

a ltit ude t ype select dis cretes, P 2-41/42)

P 2-53 Air/ground discret e (gnd = WOW)

P 2-48 Report ing a lt it ude port select (gnd = port B )

P 2-59 B urst t une ena ble (gnd = bur st )

Note: In B urst Tune mode the control port st ra pping (P 2-57/58) is ignored. B urst tune

data is accepted on ports A, B, and C as 30 ARINC-429 words spaced over a n interval

of 1.5 seconds with 500 msec dwell time on each port and the dwell time suspended

when data is present. Continuous data is always a ccepted i f avai lable.

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Table 1-2. Equ ipm ent Sp ecifications. (cont’d)


Discret e I/O (cont inued)

P 1-15

P 1-30

Cross-side input (connected to opposite TDR P1-30, gnd input = command to standby)

Cross-side output (connected to opposite TDR P 1-15, gnd output = active m ode)

(These connections are used in dual burst-tune TDR installations to ensure that only one

transponder is operating at a t ime)

P 1-31 F ault monit or out put (28 V dc = va lid, 200 m A ma x)

P 1 -29 S u ppr es sion i np ut /ou t pu t (con ne ct ed t o a l l ot h er L -b a nd eq u ip me nt )

P 1-16 (-003) S P I (r em ot e id en t) in pu t

Maintenance specific:

P 2 -38 S el f-t es t i nh ib it (g nd = in h ib it ed ) (f or m a in t en a n ce p ur pos es on ly )

P 2 -54 S e lf -t e st d is cr et e (g n d = s el f-t e st on ) (f or b en ch t e st /m a i nt e na n ce p ur pos es on ly )

Combination discrete

s t r a p s

P2-41, P2-42, and

P 1-14

P 1 -14 P 2 -41 P 2 -42 Al t it u d e Ty p e S e le ct e d

open g nd gn d AR INC 429 on AR INC por ts A a nd B

open open gnd C SD B on C SD B port s A a nd B

open g nd open AR IN C 575 on AR IN C por ts A a n d B

op en op en op en AR I NC 572 (G i ll ha m ) on t h e G i ll ha m p a r a ll el p or t

g nd g nd g nd P o rt A a l t it u de on t h e s el ect ed con t rol b us (ei th er AR I NC 429 or

CSDB ) and port B al t i tude type ARINC 429 on ARINC port B .

g n d op en g n d P o r t A a l t it u d e on t h e s el ec t ed c on t r ol b us (e it h er AR I NC 429 or

C S B B ) a n d p or t B a l t i t u d e t y p e C S D B o n C S D B p or t B .

g n d g n d op en P o r t A a l t it u d e on t h e s el ec t ed c on t r ol b us (e it h er AR I NC 429 or

CSDB ) and port B al t i tude type ARINC 575 on ARINC port B .

g n d op en op en P o r t A a l t it u d e on t h e s el ec t ed c on t r ol b us ( ei t he r AR I NC 429

or CSDB) and port B al t i tude type Gil lham on the Gil lham

parallel port.

P 2 -4 3, P 2 -4 4, P 2 -45 M a x a i r s pe ed p r og r a m m i n g (g n d t o P 2 -4 9)

P 2-43 P 2-44 P 2-45 D efi n it ion

open open open n on e s elect ed

gnd open open 0 t o 75 knot s

open gnd open 75 t o 150 kn ot s

gnd gnd open 150 t o 300 knot s

open open gnd 300 t o 600 knot s

gnd open gnd 600 t o 1200 knot s

open gnd gnd more t ha n 1200 knot s

gnd gnd gnd (n ot defi ned)

P 2-46, P 2-47 S DI in pu t (gn d t o P 2-50)

P 2 -46 P 2 -47 D efi n it ion

open open (n ot u sed )

open gnd side 1

gnd open side 2

gnd gnd (not used)

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Discret e I/O (continued )

Combination discrete

straps (continued)

P 2-57, P 2-58 C on tr ol por t select (gn d t o P 2-52)

P 2-57 P 2-58 D efi nit ion

gnd open P ort A select ed

open open P ort B select ed

open gnd P ort C select ed

gnd gnd (not defi ned)

Table 1- 3. DO- 160B Envi r onment al Qual ificat ions.

CHARACTERISTIC

DO-160B

P ARA NO QU ALI F I C ATI ON LE VE L

Temperat ure a nd Altitude

Low Opera ting Temp

High Operat ing Temp

Low S torag e Temp

High S tora ge Temp

Altitude

4.0

4.5.1

4.5.3

4.5.1

4.5.2

4.6.1

Category F2:

-55 °C (-67 °F )

+ 70 ° C (+ 158 ° F)

-55 °C (-67 °F )

+ 85 ° C (+ 185 ° F)

Cat egory A2: Certified for instal lat ion in a controlled temperature locations where

pressures are no lower tha n a n a l t i tudes equivalent t o 4600 m

(15 000 ft) msl.

Cat egory E 1: Certified for instal lat ion in a nonpressurized and noncontrolled tem-

perature locations in an airplane that is operated at al t i tudes up to 21

300 m (70 000 ft) msl.

Te mp er a t u r e Va r i a t ion 5. 0 C a t e gor y B : C e rt i fi ed f or i ns t a ll a t ion i n a con t r ol le d or n on con t r ol le d t e mp er a t u r e

location in the airplane.

H umidit y 6.0 C a tegory B : C ert ifi ed for a S evere H um idit y E nvir onm ent - Level I .

Shock

Operational

C r a s h S a f e t y

7.0

7.2

7.3

Tested a t 6 g pea k

Tested a t 15 g (11 ms d ura tion)

Vibra tion 8.0 C at egory J : C ert ifi ed for fusela ge m ount ing in a fi xed w ing t urbojet or t urbofa n

airplane.

Cat egory Y: Certified for fuselage mounting in a piston or turbojet rota ry wing

airplane.

E x pl os ion P r oof ne ss 9. 0 C a t eg or y E 1: C er t ifi e d f or i ns t a ll a ti on i n a l oca t i on w h er e a n e xpl os iv e a t m os ph er e

may occur as a result of leakage or spil lage.

Wa t er pr oofn es s 10. 0 C a t eg or y X: N o t es t r eq uir ed . C er tifi e d f or in st a lla t ion in loca t ion s n ot s ub ject t o

fal l ing wa ter (including condensation), ra in w ater , or spray ed wa ter .

F lu id s S u sce pt ib il it y 11. 0 C a t eg or y X: N o t es t r eq u ir ed . C er t ifi e d f or in st a ll a ti on in loca t ion s n ot ex pos ed t o

fluid contamination from fuel, hydraulic fluids, oil, solvents, etc.

S a nd a n d D us t 12. 0 C a t eg or y X: N o t es t r eq uir ed . C er tifi e d f or in st a lla t ion in loca t ion s n ot s ub ject t o

blowing sand and dust .

F un gu s R es ist a nce 13.0 C a tegor y X: F un gu s r esist a nce t est n ot per for med .

S a lt S pra y 14.0 C a tegory X: S a lt spra y t est not perfor med.

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Table 1-3. DO-160B E nvironmenta l Qualifi cations.

CHARACTERISTIC

DO-160B

P ARA NO QU AL I F I C ATI ON LE VE L

M a gn et ic E ff ect 15.0 C a t eg or y Z: U n it ca u ses a 1° d efl ect ion of a n u ncom pen sa t ed com pa s s a t a d is -

tance less than 0.3 m (1.0 ft).

P ow er I npu t 16.0 C a teg or y Z: C er tifi ed for u se on a ir pla ne elect rica l sy st em s n ot a pplica ble t o a ny

other cat egory. For example, a dc system from a variable range

generator where a small capacity or no battery is floating on the dc

bus.

Volt a ge S pike 17.0 C a t eg or y A: C er t ifi e d f or in st a lla t ion in s ys tem s w her e a h ig h d eg ree of v olt a ge

spike protection is required.

Audio Frequency

Susceptibility

18. 0 C a t e g or y Z: C e rt i fi ed f or u s e on a i r cr a f t e le ct r ica l s y st e ms n ot a p pl ica b l e t o a n y

other cat egory. 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 C a t e g or y Z: C e rt i fi ed f or op er a t i on i n s y st e ms w h er e i nt e rf er en ce -f r ee op er a t i on i s

required.

R F S u sce pt ib il it y 20. 0 C a t eg or y Z: C er t ifi e d f or op er a t ion in s ys t em s w h er e i nt er fe ren ce -f re e op er a t ion is

required.

E m i ss ion of R F E n er g y 21. 0 C a t e g or y Z: C e rt i fi ed f or op er a t i on i n s y st e ms w h er e i nt e rf er en ce -f r ee op er a t i on i s

required.

Light ning 22.0 C a tegor y L: L ong a nd short w a ve (750 volt s)

Damped sinusoidal wave (600 volts)

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7 March 2007 1-11

Table 1-4. Equipment Required But Not Supplied.

EQUIPMENT TYPE OR DESCRIPTION QTY

**MMT-150 Mount 1/2 ATR, short, dwarf mount (CPN: 622-9672-003)

1/2 ATR, short, dwarf mount (CPN: 622-9672-004) for BA609 installations

1

**Connector Kit 60-pin, Thinline II connector, qty 2 each, (Kit CPN: 628-8661-001/002, or

628-8660-001/002 or 628-8660-003 for BA609 installations) (Refer to Pro Line IIInstallation Manual, for additional details)

1-kit

**Crimp contacts **Crimp contacts For wires with:

up to 0.050 in. insulation dia (372-2514-110), or

0.050 to 0.080 in. insul dia (372-2514-180)

*105 used,

15 spares

L-band antenna Collins ANT-42, CPN: 622-6591-001, or

Collins 237Z-1, CPN: 522-2632-001; qty 1 for TDR-94, qty 2 for TDR-94D

AR

ATC Control CSDB data format:

Collins CTL-92/92A ATC Control, with Collins CTL-92T if TCAS is used,

ARINC 429 data format:

Collins RTU-870A Radio Tuning Unit, or

Collins RTU-870T TCAS/ATC Radio Tuning Unit, or

Collins TTC-920G TCAS/ATC Control, or

Gables model 816

Altitude data source Collins ADS-85 Air Data System (Refer to ADS-85 Air Data System Installation

Manual)

Air Data Link Message Processor TBA (not available at time of this publication)

Traffic Alert and Collision Avoid-

ance System

Collins TCAS-94 System (Refer to TCAS-94 Installation Manual)

*Quantity required for typical installation

**Refer to TDR-94/94D installation section in the Pro Line II Comm/Nav/Pulse System Installation Manual for additional mount and

mating connector information

Table 1-5. Related Publications

PUBLICATION ATA NUMBERCOLLINS PART

NUMBER

Collins Avionics Standard Shop Practices, Instruction Manual none 523-0768039

TDR-94/94D ATC/Mode S Transponder, Component Maintenance

Manual

34-50-91 523-0775997

Collins Pro Line II Comm/Nav/Pulse System, Installation Manual none 523-0772719

TCAS-94 Traffic Alert and Collision Avoidance System, Installation

Manual

none 523-0775833

CTL-92T TCAS Control 34-40-84 523-0776595

RTU-870A/870T Radio Tuning Unit, Component Maintenance

Manual

23-80-80 523-0774068

CTL-X2/X2A Controls, Instruction Book (Repair Manual) 23-80-10 523-0772495

Collins TDR-94 Mode S Transponder, Pilot’s Guide none 523-0776370

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Table 1-6. Relat ed Ser vice Bul let ins.

SE RVI CE BUL L ET IN NUMBE R, T IT LE AND DE SC RI PT ION PUBL IC AT ION DAT E

SB 1: Convert TDR -94’s and TDR -94D’s to -002 status (Converts -001 to -002 status). The

modifica tions in this service bulletin upgra de the TCAS interfa ce performance. This service bulletin

adds al t i tude input via t he control bus a nd improves the burst control interface.

Rev 1: Ma y 23, 1991

SB 2: Improve Burst Tuning Interface, Self-Test Performance, and EMI C ompatibility.

Installation of this service bulletin protects transmitter power output transistor during self-test, corrects

burst tuning cross-side standby operation, and improves EMI compatibility.

J an 18, 1991

SB 3: Prevent Corruption of Mode A/C Replies. ATC ma y report loss of reply or incorrect reply

code. Several minutes to several hours ma y elapse before this malfunction occurs. Once precipitated,

the condition will persist until primary power is cycled.

J an 18, 1991

SB 4: Prevent Occasional L oss of Transponder Function. Reception of certain combinat ions of

transponder interrogations can cause the TDR-94 and TDR-94D not to reply to subsequent interroga-

tions. Once this occurs power m ust be cycled to restart transponder operation.

Mar 5, 1991

SB 5: A7U301 or A7U304 Replacement. In some units, w hen A7U301 or A7U304 are replaced, one

or both channels may fai l the DP SK related test . This service bulletin should be instal led when

replacing IC A7U301 or A7U304.

Rev 1: J un 10, 1993

SB 6: Convert TDR -94’s and TDR -94D’s to -003 Status (Converts -002 status to -003 status).Inst alla tion of this service bulletin upda tes t he TDR-94/94D t o include chan ges to th e Mode S tra n-

sponder requirements by RTCA. Insta l lat ion configurat ion options a re expanded and enhancements t o

i ts diagnostic and maintenance performance is implemented.

Rev 2: Sep 22, 1992

SB 7: A6U105 or A6U120 PROM Replacement. If A6U105, on th e -002/102 Video Processor C a rd or

A6U120 on the -003/103 Video P rocessor C ar d, req uires replacement, the new P ROM m ay exhibit

different para meters which affect the performance of the tra nsponder. I f this service is not insta l led

when cha nging A6U105 or A6U120, the tra nsponder may not reply to interrogat ions. This service

bulletin compensates for the para meter changes.

Rev 1: Sep 17, 1992

SB 8: Replacement of A7U500 or A7U502. The current IC U500 (circuit card assembly A7, CPN

687-0727-002/102) or U 502 (circu it ca rd a ssem bly A7, CP N 687-0727-001/101) ha s exh ibit ed s ome cold

star t problems. The new U500 or U 502 performs better over t emperat ure but requires some changes to

accommodate t he new IC . This service bulletin should be installed only if U500 or U502 requires

replacement.

Rev 1: Sep 22, 1992

SB 9: Prevent Possible Intermittent Operation. A rare combination of events can cause the TDR-

94/94D t o be intermit tent. If a specifi c memory location is corrupted a nd th e unit t ries to report a

diagnostic, intermittent operation can occur.

Rev 3: Apr 22, 1993

SB 10: Improve Operation of Remote Ident Input. In a ircraft which uti l ize the remote ident input

(P1-16), the active transponder may squawk ident if power is removed from the inactive transponder.

Oct 2, 1992

SB 11: Improve Power-On Initialization. To ensure t ha t t he TDR-94/94D powers u p in less t ha n

tw o seconds and initializes the a ir/ground Mode S sta tus t o the correct reporting position.

Feb 5, 1993

SB 12: Add Diode Isolation to Strap Inputs. In aircraft which paral lel the CSDB and ARINC 429

Control select a nd B urst E nable inputs to other systems, removal of tra nsponder power may cause

unrequested activation of the function in another system.

Aug 2, 1993

SB A : S a me a s S B 3. D ec 11, 1990

SB B: Improve Start-Up C ompatibility With T he Gulfstream G-IV Gables 6969 TCAS ControlAdapter. Insta l lat ions uti l izing the G ables 6969 TCAS control adapter m ay power up in the st andby

mode regardless of the mode the system w as powered down in.

Sep 29, 1992

SIL A-90: Connector Plate Inspection (CPN 629-8657-001/002. Some connector plates used with

the TDR-94/94D m ounting ra ck may exhibit one or more discrepan cies. This connector plat e is a vaila ble

individu a lly a nd is included a s pa rt of connector kits, C P N 628-8660-001/002 a nd C P N 628-8661-

001/002. All connector plates " REV A" through " REV C" tha t do not have " A-90" ma rked on them

should be inspected a nd a djusted i f found discrepant. Connector plates " REV D" or later a re inspected

during manufacture.

Oct 22, 1990

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523-0775655-1031183rd Edition, 29 April 1991

1st Revision, 15 June 1995

TDR-94/94D

ATC/Mode STransponder System

Operation

Table of Contents

P a r a g r a p h P a g e

3.1 TDR-94/94D TRANSPONDER OPERATING INSTRUCTI ONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-1

3 .1 .1 Introducti on . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 -1

3.1.2 CTL-92/92A Control, Contr ols a nd In dicat ors . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-1

3.2 OPERATING INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 -1

3.2.1 Opera ting I nstr uctions for Inst allat ions U sing a CTL-92/92A Control . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-1

3 .2 .2 Eq ui pment Turn On . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 -1

3 .2 .3 Code Sel ect i on . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 -1

3 .2 .4 Code Storage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 -23 .2 .5 Normal Operat i on . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 -2

3 .2 .6 Sel f-Test . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-3

3.2.6.1 C TL-92/92A ATC Control, Dia gnostic Codes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-5

NOTICE: This section replaces third edition dated 29 April 1991. Only the Title Page has changed in this revision.

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P a ge I ssue

*Title . . . . . . . . . . . . . . . . . . . 15 J un 95

*List of Effective pages . . . . . 15 J un 95

3-1 thru 3-4 . . . . . . . . . . . . . . . 4 Apr 90

3 -5 . . . . . . . . . . . . . . . . . . . . 2 9 Ap r 91

3 -6 B l a n k . . . . . . . . . . . . . . . . 4 Ap r 89

Record of RevisionsRETAIN THIS RECORD IN THE FRONT OF THE MANUAL. ON RECE IP T OFREVISIONS, INSERT REVISED PAGES IN THE MANUAL, AND ENTER DATE


REV /

E D N O

REVISION

D ATE

INSERTION

DATE /BY

S B N U M B E R

I N C L U D E D

REV /

E D N O

REVISION

D ATE

INSERTION

D ATE /B Y

S B N U M B E R

I N C L U D E D

0/1 4 Apr 89 None

0/2 4 Apr 90 None

0/3 29 Apr 91 None

1/3 15 J un 95 S ee Ta ble 1-6

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7/22/2019 TDR 94 5230775652


523-0775656-202118

2nd Edition, 4 April 1990

2nd Revision, 7 March 2007

TDR-94/94D ATC/Mode STransponder System

Theory of Operation

Table of Contents

Paragraph Page

4.1 TDR-94/94D Transponder System theory of Operation...........................................................................................4-1

4.1.1 General............................................................................................................................................................................4-1

4.1.2 Physical Description .......................................................................................................................................................4-1

4.2 Purpose of Equipment ...................................................................................................................................................4-2

4.3 Background .....................................................................................................................................................................4-2

4.3.1 Introduction ....................................................................................................................................................................4-2

4.3.2 Radar Systems................................................................................................................................................................4-2

4.3.3 ATCRBS Interrogation Modes .......................................................................................................................................4-5

4.3.4 SSR Radiation Patterns and SLS..................................................................................................................................4-5

4.3.5 ATC Transponder 4096 Replies .....................................................................................................................................4-5

4.4 ATCRBS and Mode S .....................................................................................................................................................4-8

4.4.1 Introduction ....................................................................................................................................................................4-8

4.4.2 Mode S Interrogation Modes ........................................................................................................................................4-13

4.4.3 Mode S SSR Radiation Pattern and SLS....................................................................................................................4-14

4.4.4 Mode S Transponder Replies .......................................................................................................................................4-14

4.5 TDR-94/94D Theory of Operation ..............................................................................................................................4-18

4.5.1 Introduction..................................................................................................................................................................4-18

4.5.2 Installation Strapping Options....................................................................................................................................4-184.5.3 Typical Configurations .................................................................................................................................................4-19

4.5.4 TDR-94/94D Block Diagram Theory of Operation .....................................................................................................4-23

NOTICE: This title page replaces 1st revision, 2nd edition title page dated 15 June 1995.

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Page No Issue

* Title............................................7 Mar 07


4-1............................................... 4 Apr 90

4-2 thru 4-4 ................................ 4 Apr 89

4-5............................................... 4 Apr 90

4-6 thru 4-7 ................................ 4 Apr 89

4-8 thru 4-24 .............................. 4 Apr 90




REV/

ED NO

REVISION

DATE

INSERTION

DATE/BY

SB NUMBER IN-

CLUDED

REV

NO

REVISION

DATE

INSERTION

DATE/BY

SB NUMBER IN-

CLUDED

0 / 1 4 Apr 89 None

0 / 2 4 Apr 90 None

1 / 2 15 Jun 95 None

2 / 2 3 Mar 07 None


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Revised 4 April 1990 4-1

section IVtheory of operation

4.1 TDR-94/94D TRANSPONDER SYSTEM

THEORY OF OPERATION

4.1.1 General

The TDR-94/94D Mode S Transponder is a solid-state,

airborne, air traffic control (ATC) transponder that re-

sponds to ATCRBS (air traffic control radar beacon sys-

tem) mode A and mode C interrogations and mode se-

lect (mode S) interrogations. The mode S transponder

differs from earlier ATCRBS transponders in operationin that it is capable of discrete addressing. That is, in

mode S each transponder acquires a unique identity

and responds when interrogated according to that iden-

tity. In addition, mode S includes the capability of

sending and receiving

data link messages. Diversity-equipped mode S

transponders are also capable of receiving and trans

mitting on two antennas. These are usually mounted

one on top and the other on the bottom of the fuselage

This provides for more reliable air-to-air surveillance

and communications.

4.1.2 Physical Description

Figure 4-1 is a view of the TDR-94/94D Mode S

Transponder. The unit dimensions are 5 inches wide, by

3 ¾ inches high, by 14 inches long. It weighs about 7.5

pounds. All electrical connectors are at the rear of the

unit. These include two 60-pin Thinline connectors and

either one (for TDR-94) or two (for TDR-94D) antenna

connectors. The unit is normally mounted in a MMT-150

Modular Mounting Tray.

CTL-92/92A Control, Controls and IndicatorsFigure 3-1

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operation 523-0775656

4 April 1989 4-2

4.2 PURPOSE OF EQUIPMENT

The TDR-94/94D transponder is the airborne

transponder for the ATCRBS. The TDR-94/94D pro-

vides mode A, mode C, and special identification re-

plies to ATCRBS interrogators for tracking, identifica-

tion, and altitude reporting. In addition, the TDR-94/94D is capable of receiving and sending mode S

messages that will be required by TCAS II and TCAS

III (Traffic Alert and Collision Avoidance System), It

also includes the data link capability necessary for air-

craft separation assurance (ASA) function.

4.3 BACKGROUND

4.3.1 Introduction

The air traffic control radar beacon system (ZTCRBS)

is a surveillance system in wide use that locates and

identifies aircraft within an airspace. However, be-cause of increasing air traffic, this system is being ex-

panded to include additional facilities for airborne col-

lision avoidance. To gain a good understanding of

mode S transponder operation, it is necessary to un-

derstand the operation of the existing air traffic con-

trol (ATC) system.

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 operation.

4.3.2 Radar Systems

Refer to figure 4-2. The ATCRBS consists of a primary

surveillance radar (PSR) and a secondary surveillance

radar (SSR). The PSR can be visualized as

consisting mainly of a large rotating radar an-

tenna that can be seen at or near most air termi-

nals. This system uses conventional radar to lo-

cate all aircraft within its range in terms of range

and azimuth. It transmits a burst of energy and

then measures the time to an echo.* The direction

in which the antenna is pointing at the time theecho is detected establishes the azimuth to the re-

flecting target. This target information is dis-

played on the air traffic controller’s PPI (plan po-

sition indicator) (see figure 4-3).

4.3.3 ATCRBS Interrogation Modes

The SSR system interrogates the aircraft

transponder for aircraft identity and altitude. Theinterrogations are in the form of either of two

modes: mode A for aircraft identity and mode C,

which is used to request altitude information.**

All pulses are 0.8 us wide. The interrogations

from the ground station are at a frequency of 1030

MHz. The transponder replies at a frequency of

1090 MHz. The signal received from the airborne

transponder is decoded by the round system so

that it can be displayed on the ATC radar screen

(see figure 4-3). The replies produce either a sin-

gle or double slash target display on the controller

screen. The controller can also elect to display the

aircraft identification number (as selected by the

aircrew) and the aircraft altitude.

*The time is easily converted into range. The propagation velocity of radio energy is known. The mathe-

matical formula for distance is: D = velocity x (multiplied by) time. However, radio propagation velocity is

usually expressed as 12.359 us per radar mile. Notice that this is the inverse of what is necessary for the dis-

tance formula, which must have velocity expressed as a measure of distance per unit of time (eg, miles per

hour). Therefore, the distance formula must be modified slightly: D = time / (divided by) propagation velocity.

**In the original definition of ATC modes, two other modes were defined: mode B and mode D. These alsodiffer only in terms of pulse spacing, with mode B pulses spaced 17 us and mode D pulses spaced 25 us. For a

time, mode D was widely used in Great Britain, but in recent years most of the aviation industry has settled

on mode A for ATCRBS operation and mode C for altitude reporting, and modes B and D have been largely

abandoned.

In US military applications, a system similar to ATCRBS is used; it is known as IFF (identification friend or

foe). As this name implies, it has to do with mission security. Three modes are defined: modes 1, 2, and 3.

Mode 3 is common to the civil mod A, with a pulse spacing of 8 us. This allows air traffic control visibility of

all aircraft, both civil and military.

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4 April 1989 4-3

ATC, PSR and SSR System

Figure 4-2

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4 April 1989 4-4

Air Traffic Presentation on the ATC RadarscopeFigure 4-3

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4.3.4 SSR Radiation Patterns and SLS

Refer to figures 4-4 and 4-5. The SSR uses a ro-

tating directional antenna to transmit two pulses,

which are identified as P1 and P3. The spacing of

these pulses determines the mode. In mode a the

pulses are spaced 8 us, while in mode C the pulsesare spaced 21 us. The SSR also uses an omnidirec-

tional antenna to transmit a third pulse, desig-

nated P2. This pulse is transmitted 2 us after the

P1 pulse and provides a reference for side-lobe

suppression (sls). The amplitude of the P2 pulse is

about the same as the peak sidelobe of the direc-

tional antenna. Typically, this is about 18 dB be-

low the peak of the directional (main) beam.

Refer to figure 4-4. Notice the two aircraft on the

drawing. Aircraft A is shown as being within the

main lobe of the directional antenna. The ampli-

tude of the P1 and P3 pulses will be substantiallygreater here than that of the P2 pulse radiated

from the omnidirectional antenna. Therefore, this

aircraft transponder will interpret this interroga-

tion as valid.

Aircraft B, however, is outside the main lobe and

within one of the sidelobes. The P1 and P3 pulses

detected here will be the result of side-lobe radia-

tion. Recall that the P2 pulse is transmitted by an

omnidirectional antenna and is about equal in

amplitude to that of the peak sidelobe. Therefore,

the P2 pulse detected by aircraft B will be at least

as great in amplitude as the P1, P3 pulses. The

transponder in aircraft B will detect this relation-

ship in pulses and discard the interrogation as in-

valid, because the P2 pulse is not substantially

less than the P1, P3 pulses. As a further safeguard

against replies to possible late-arriving echoes to

this invalid interrogation, the

transponder suppresses replies to all interroga-

tions for an additional 25 to 45 ms. In addition

the receiver is desensitized for reception of P1, P3

pulses. The rationale here is that if the sidelobes

are detectable, then the main lobe must be much

greater, increasing the likelihood of echo recep

tion.

4.3.5 ATC Transponder 4096 Replies

The ATCRBS transponder 4096 reply signal is shown

in figure 4-6. Notice that the signal can consist of

from 2 to 15 pulses (the X pulse is not used). The two

framing pulses, F1 and F2, are always present and

spaced 20.3 us. An identification pulse may be trans-

mitted 4.35 us after the last framing pulse, F2. The in

tervening pulses, C1 through D4 on the figure, make

up the coded reply.

The coded reply consists of four digits rangingfrom 0 through 7. The digits are formed by the

sum of the suffix numbers ranging from 0 through

7. The A group (A1, A2, and A4) makes up the

first digit, the B group makes up the second digit

etc. (On the figure, a pulse outlined with a solid

line indicates that the pulse is present. A pulse

outlined with dashed lines indicates the position

for that pulse when it is present.) The pulse con-

figuration on the figure indicates a reply code of

1324. The first digit, 1, is formed y the presence o

only the A1 pulse. The second digit, 3, is formed

by the presence of B1 and B2 (1 + 2 = 3). A digit 7

is formed when all three pulses of the group are

present (1 + 2 + 4 = 7). Therefore, a reply sequence

with all pulses present constitutes a code 7777

The X pulse is not defined in ATCRBS replies

This combination of four digits, each ranging from

0 through 7, makes possible 4096 different codes

which explains the reason for calling it the 4096

code.

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4 April 1989 4-6

ATCRBS, SSR Antenna Radiation Pattern

Figure 4-3

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4.4 ATCRBS AND MODE S (Refer to figure

4-7)

4.4.1 Introduction

Mode S substantially enhances the capability of the

ATCRBS by adding data link and discrete interro-gation features. The data link capability includes

air-to-air information exchange, ground-to-air (data

uplink or comm A), air-to-ground (data downlink or

comm B), and multiple ground stations message pro-

tocol. The mode S transponder can also function as

part of an airborne separation assurance (ASA) sys-

tem when interfaced with a Traffic Alert and Colli-

sion Avoidance System (TCAS).

4.4.2 Mode S Interrogation Modes (Refer to

figures 4-8, 4-9, and 4-10)

There are eight different formats of interrogationused in mode S. These eight formats can be summa-

rized in terms of three basic types. These are shown

in figures 4-8 and 4-9. Figure 4-10 is a summary of

all eight.

This variety of interrogation capability gives the

ground controller the flexibility of addressing only

those aircraft of immediate interest, as opposed to

processing replies from all aircraft.

All eight of the interrogation modes are summa-

rized in figure 4-10. The various fields are de-

scribed in the following paragraphs. These de-

scriptions are largely as provided in Document

RTCA/DO-181, with minor changes to clarify the

text.

a. Address/Parity (AP) Field: The 24-bit* AP

field contains the parity overlaid on the ad-

dress and appears at the end of all transmis-

sions for uplink interrogations and downlink

replies, except for downlink format (DF) num-

ber 11.

b. Acquisition Special (AQ) Field: The 1-bit AQfield designates uplink format (UF) numbers 0

and 16 as acquisition transmissions and is re-

peated as received by the transponder in DF

numbers 0 and 16.

*In the RTCA document, some graphic material

refers to these as chips. For this description, the

terms are regarded as synonymous.

c. Designator Identification (DI) Field: The 3-bit

DI field identifies the coding contained in the

special designator (SD) field in IF numbers 4,

5, 20, and 21. The codes are defined as follows:

DI DEFINITION

0

1

2-6

7

Not used

SD contains multisite information

Not assigned

SD contains extended data readout

request

d. Interrogator Identification (II) Field: The 4-bit

II field identifies the interrogator and appears

in UF number 11 (mode S only all-call).

e. Message, Comm A (MA) Field: The 56-bit MA

field contains messages directed to the aircraft

(UF numbers 20 and 21). This field also con-tains the 8-bit comm A definition subfield

(ADS). ADS defines the content of the MA

message field, of which it is a part.

f. Message, Comm C (MC) Field: The 80-bit MC

field contains one segment of a sequence of

segments transmitted to the transponder in

the extended length message (ELM) (112 bits)

mode. The field contains an 8-bit comm C

definition subfield (CDS) that defines the

message to be sent to the transponder and is

included in segment zero of the ELM uplink

sequence.

g. Message, Comm U (MU) Field: The 80-bit MUfield contains information used in air-to-air

message exchanges.

h. Number of C-Segment (NC) Field: The 4-bit

NC field provides the number of a segment

transmitted in an uplink ELM message and is

part of the comm C interrogation, UF number

24.

i. Protocol (PC) Field: The 3-bit PC field contains

the operating commands to the transponder.

The code description is as follow:

DI DEFINITION

0

1

2-3

4

5

6

7

No changes in transponder state

Nonselective all-call lockout

Not assigned

Cancel B

Cancel C

Cancel D

Not assigned

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Mode S, PSR and SSR System

Figure 4-7

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Mode S, All-Call and Discrete Addressing, Interrogation Format

Figure 4-8

Mode S, Discrete Addressing, Pulse P6 Definition

Figure 4-9

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ATCRBS, SSR Antenna Radiation Pattern

Figure 4-10

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j. Probability of Reply (PR) Field: The 4-bit PR

field contains commands to the transponder to

specify the reply probability to the mode S

only all-call interrogation, IF number 11. The

code description is as follows:

PR DEFINITION

0

1

2

3

4

5-7

8

9

10

11

12

13-15

Reply with probability = 1

Reply with probability = 1/2

Reply with probability = ¼



No reply

Disregard lockout, reply with prob-

ability = 1


ability = ½


ability = ¼Disregard lockout, reply with prob-

ability = 1/8


ability = 1/16

Do not reply

After receiving a mode S only all-call containing a

PR code other that 0 through 8, the transponder

will execute a random process and make a reply

decision for this interrogation in accordance with

the command probability. Random occurrence of

replies enables the interrogator to acquire closely

spaced aircraft that might otherwise synchro-

nously garble the transponder replies.

k. Reply Control (RC) Field: The 2-bit RC field

designates the transmitted segment as initial

(0), intermediate (1), or final (3). An RC field

(3) is used to request a comm d downlink by

the transponder. RC is part of the comm C in-

terrogation, UF number 24.

l. Reply Length (RL) Field: The 1-bit RL field

commands a reply (DFO) if the bit is 0 and a

reply in DF number 16 if the bit is 1.

m. Reply Request (RR) Field: The 5-bit RR field

describes the length and content of the infor-

mation requested (MB - see reply field de-

scriptions below ) by the interrogator. The

code description is as follow.:

RR REPLY

LENGTH MB CONTENT

0-15

16

17

18

19-31

Short

Long

Long

Long

Long

Air initiated comm B

Extended capability

Flight identification

Not assigned

If the first bit of the RR code is logic 1, then the

decimal equivalent of the last four bits designates

the requested source.

n. Special Designator (SD) Field: The 16-bit SD

field contains control codes affecting the

transponder protocol. The content is specified by

the DI field. A subfield, IIS, is contained within

the SD field and specifies the interrogator identi-

fier.

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4.4.3 Mode S SSR Radiation Pattern and

SLS (Refer to figure 4-11)

The mode S interrogation is transmitted through a

technique known as binary differential phase-shift

keying (DPSK). This technique is described graphi-

cally in figure 4-9. A chip is an unmodulated intervalof 0.25 us that may be preceded by a phase reversal

(pr). If a chip is preceded by a pr, it represents a logic

1. If it is not preceded by a pr, it represents a logic 0.

In mode S, the omnidirectional antenna transmits

pulse P5 as the sls reference pulse. The P5 pulse oc-

curs within the P6 pulse and is timed 0.4 us before

the spr (sync phase reversal). Thus, if the amplitude

of P5 is sufficient to blank the spr of P6, the interro-

gation is most likely from a sidelobe and not from

the main love. In this case, the spr is hidden from

the transponder, so the reply is suppressed.

The SSR mode S interrogation pulse spacing and

identification is different from that of the earlier

ATCRBS. Figures 4-8, 4-9, and 4-10 show these con-

figurations. Notice that the rotating beam transmits

two different pulse combination. For all-call interro-

gations, the transmitted pulses are P1, P3 , and P4.

In these interrogations the sls reference pulse, P2, is

transmitted by the omnidirectional antenna as in

conventional ATCRBS. The P1-to-P3 pulse spacing is

either 8 µs (for mode A) or 21 µs (for mode C), also as

in ATCRBS. The P4 pulse follows the P3 pulse by 2 µs

and can be either 0.8 µs (the same as P1 and P3) or 1.6

µs. The pulse width of P4 determines the all-call ob-

jective as follow (all times are in microseconds):

INTERROGATION TYPE PULSE SPACING

P1-P2 P1-P3 P3-P4 P4

ATCRBS Mode A

ATCRBS Mode C

ATCRBS Mode A/Mode S

all-call

ATCRBS Mode C/Mode S

all-call

ATCRBS Mode A-only

all-call

ATCRBS Mode C-only

all-call

2±0.15

2±0.15

2±0.15

2±0.15

2±0.15

2±0.15

8±0.2

21±0.2

8±0.2

21±0.2

8±0.2

21±0.2

2 ±0.05

2 ±0.05

2 ±0.05

2 ±0.05

None

None

Long

Long

Short

Short

Where P4 long pulse width is 1.6 ±0.1 µs and P4 short pulse width is 0.8

±0.1 µs.

A 0.8-µs pulse is only for non-mode S transpon-

ders, while the 1.6-µs pulse is for both ATCRBS

and mode S transponders.

The mode S discrete addressing interrogation takes

yet another form. For this interrogation, the rotat-

ing beam antenna transmits pulses P1, P2, and P6

P6 is in reality a series of either 56 or 112 bits identi

fied as chips that define the data. At 1.25 µs after thestart of P6, the spr occurs. This spr must be detected

in order to enable a reply response. The final chip is

followed by a 0.5-µs guard interval. This prevents the

trailing edge of P6 from interfering with the de-

modulation process. The P2 pulse follows the P1

pulse by 2 µs. P6 begins about 1.5 µs after P2.

The ground mode S interrogator system uses a mo

nopulse processing scheme to determine the azi

muth bearing to the aircraft., This scheme requires

only a single reply from an airborne transponder

as opposed to the two replies necessary in the ear-

lier ATCRBS system, to establish the azimuth tothe aircraft.* The address (derived from the reply)

and location (azimuth and range) of the mode S air

craft is entered into a roll-call file. This file can be

visualized as a list of the mode S transponder

equipped aircraft within its assigned airspace. On a

later scan, the mode S aircraft is discretely ad

dressed. This discrete address contains a command

field that is used to desensitize the mode S

transponder to further mode S all-call interroga-

tions. This desensitization is called mode S lockout

The ATCRBS-only transponders are not affected by

this lockout technique and mode S transponders

continue to reply to ATCRBS interrogations.

When a mode S transponder equipped aircraft

moves from one assigned airspace into another

the first ground interrogator can communicate

with the next interrogator and pass aircraft in

formation to that second interrogator. This com-

munication link can be via ground lines or radio

link. If this method is used, the mode S lockout is

not disabled on the affected aircraft and the sec

ond interrogator will schedule discrete roll-call in

terrogations for that aircraft as needed. This

technique makes it possible to increase the air-craft handling capacity of the ground interrogator.

*In this scheme, the monopulse system generates

two separate patterns: a single (sum) pattern and a

dual lobe (difference) pattern. The ratio of the energy

received by the sum pattern to the energy received

by the difference pattern determines the bearing o

the aircraft from the antenna beam center line

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In regions where mode S interrogators are not con-

nected via ground or radio link, the protocol for the

transponder allows it to be in mode S lockout only for

those interrogators that have the aircraft on the roll-

call list. This enables a second ground interrogator to

acquire an aircraft into its assigned airspace using the

all-call technique as previously described.

4.4.4 Mode S Transponder Replies

Typically, the ground-based interrogator tracks an

aircraft throughout its assigned airspace. The mode

S transponder equipped aircraft responds to mode S

interrogations with the ATCRBS 4096 code and the

mode S reply format. During each scan, the SSR in-

terrogations are in both mode A and mode C. The

mode S transponder reply uses a technique known as

pulse-position modulation (PPM). This is described

graphically in figure 4-12. A pulse transmitted in the

first half of the interval represents a logic 1, while apulse transmitted in the second half represents a

logic 0. The mode S reply format is described in the

following paragraphs.

4.4.5 Mode S Reply Description

The reply waveform is shown in figure 4-12. The re-

ply data block is formed by PPM encoding of the re-

ply data, as previously described. The first preamble

pulse occurs 128 µs after the start of the P4 inter-

rogation pulse or the spr. The ATCRBS reply to an

ATCRBS interrogation is identical to the reply trans-

mitted by an non-mode S transponder (see figure 4-6).

All reply formats are summarized in figure 4-13. The

fields are described in the following paragraphs.

a. Address, Announced (AA) Field: The 24-bit AA

field contains the aircraft address (uncoded) and is

used in the all-call reply.

b. Altitude Code (AC) Field: The 13-bit AC field con-

tains the altitude code. The encoded altitude is

coded as shown in figure 4-6. The M bit has been

redefined for mode S; it was the X bit shown in

figure 4-6. In mode S the M bit may be used in the

future for encoding the altitude in metric units.

Zero is transmitted in each of the 13 bits if alti-

tude information is not available.

c. Address/Parity (AP) Field: The 24-bit AP field con-

tains the parity overlaid on the address and ap-

pears at the end of all transmissions on both

uplink and downlink, except for DF number 11.

d. Capability, Transponder (CA) Field: The 3-bit CA

field reports transponder capability. The code de-

scription is as follows:

CA DESCRIPTION

0

1

2

3

4-7

No communications capability

(surveillance only)

Comm A and comm B capability

Comm A, comm B, and downlink ELM ca-

pabilityComm A, comm B, uplink ELM, and

downlink ELM capability

Not assigned

If the transponder CA code is 1, 2, or 3, the data

link capability report is used to indicate the spe-

cific data link capabilities of the overall airborne

installation.

e. Downlink Request (DR) Field: The 5-bit DR

field is used to request extraction of downlink

messages from the transponder by the inter-

rogator. The code description is as follow:

DR DESCRIPTION

0

1

2-15

16-31

No downlink request

Request to send comm B message

Not assigned

Request permission to send extended

length message (ELM’s) of n-segments.

The code inserted into the DR field corre-

sponds to 15 + n. Downlink ELM’s are

transmitted only after authorization by

the interrogator. The segments are

transmitted on comm D replies. On receiptof the authorization, the transponder

sends a segment every 136 Ts. After re-

ceipt of all segments, the interrogator re-

plies with a closeout transmission to indi-

cate that all segments have been received

and allow the DR field to be reset. The

closeout transmission is contained in a

surveillance or comm A interrogation.

f. Flight Status (FS) Field: The 3-bit FS field

reports the flight status of the aircraft. The

code description is as follows:

FS ALERT SPI

AIRBORNE/ON

THE GROUND

0

1

2

3

4

5

No

No

Yes

Yes

Yes

No

No

No

No

No

Yes

Yes

Airborne

On the ground

Airborne

On the ground

Either

Either

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g. Identification (ID) Field: The 13-bit ID field

contains the 4096 identification code as se-

lected by the pilot.

h. ELM Control (KE) Field: The 1-bit KE field

defines the content of the ND and MD fields in

comm D replies. The transponder acknowl-

edges receipt of a final segment with a commD transmission with KE = 1. The MD field

contains a transmission acknowledgement

subfield (TAS). The information contained in

the TAS subfield is continuously updated as

segments are received and is cleared when a

closeout occurs or a new initializing segment

is received.

i. Message Comm B (MF) Field: The 56-bit MD

field contains the message transmitted to the

interrogator. The field contains an 8-bit sub-

field (BDS) that defines the contents of the

comm B message.

j. Message Comm D (MD) Field: The 80-bit MDfield contains one segment of a sequence of

segments transmitted by the transponder in

the ELM mode. It also may contain a sum-

mary of the received MC segments of an

uplink ELM. An 8-bit subfield (DDS) defines

the message to be transmitted and is included

in segment 0 of the ELM downlink.

k. Message Comm V (MV) Field: The 56-bit MV

field contains information used in the air-to-

air exchanges between mode S transponders.

l. Number of D-Segment (ND) Field: The 4-bit

ND field provides the number of the segment

transmitted in a downlink ELM and is part of

the comm D reply.

m. Parity/Interrogator Identity (PI) Field: The 24-

bit PI field contains the parity overlaid on the

interrogator identity code.

n. Reply Information (RI) Field: The 4-bit RI

field reports the airspeed capability and type

of reply to the interrogating aircraft. The code

description is as follows:

RI DESCRIPTION

0-7

8-15

8

9

10

11

12

13

14

15

Indicates that downlink is the reply to an

air-to-air acquisition interrogation

Indicates that downlink is an acquisition

reply as follows:

No maximum airspeed data is available

Airspeed is up to 75 knots

Airspeed is between 75 and 150 knots




Airspeed is more than 1200 knots

Not assigned

o. Utility Message (UM) Field: The 6-bit UM

field contains transponder status readouts.

p. Vertical Status (VS) Field: The 1-bit VS field

indicates that the aircraft is airborne (VS = 0)

or on the ground (VS = 1).

q. Free and Unassigned Coding Space Fields

Free coding space contains all logic level 0, as

transmitted by the interrogator or transpon-

der. Unassigned coding space that exists

within fields is reserved for possible future

use.

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Mode S, SSR Antenna Radiation PatternFigure 4-11

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Mode S, Transponder Reply Code Pulse Spacing

Figure 4-12

Mode S, Transponder Reply Code Summary

Figure 4-13

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4.5 TDR-94/94D THEORY OF OPERATION

4.5.1 Introduction

This paragraph gives you an overview of the TDR-

94/94D operating environment. If you are familiar

with the various installation configurations andoptions, you can skip over this paragraph.

4.5.2 Installation Strapping Options

The TDR-94 and TDR-94D ATC/Mode S

Transponders offer a wide range of installation

options. First you should recognize the difference

between the TDR-94 and the TDR-94D; the TDR-

94 is for single

antenna installations, while the TDR-94D is for

antenna diversity (dual antenna) installations.

You are likely to find the TDR-94D in most TCAS

installations because dual antennas are required

in TCAS. Both transponders can accept control

data in CSDB or ARINC 429 format; this is set at

installation by means of special external straps.

The following paragraphs and accompanying dia-

grams describe the various installation configura-

tions. Figure 4-14 shows the various strapping op-

tions that must be considered for all installations.

You should understand that these strapping op-

tions can apply to all installations.

TDR-94/94D ATC/Mode S Transponder

Strapping Options

Figure 4-14

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4.5.3 Typical Configurations

Figure 4-15 shows a TDR-94 installation with a

CTL-92/92A CSDB transponder control unit and

an encoding altimeter. This type of encoder typi-

cally supplies altitude data in Gillham code

(ARINC 572)

format. The encoded data can be supplied to the

CTL-92/92A or directly to the TDR-4. Installers

should choose the connection that involves the

shortest wire run.

TDR-94 ATC/Mode S Transponder WithCTL-92/92A Transponder Control

Unit and Altitude Encoder,

Typical

Figure 4-14

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Figure 4-16 shows a similar installation except it

uses a central air data computer (CADC) for alti-

tude data. In each of these cases, external strap-

ping is required according to the type of altitude

data that is being used. An alternate Installation

configuration is

possible using ARINC 429 code selection. In this

case, an ARINC 429 source, such as an FMS,

would be shown in place of the CTL-92/92A, with

appropriate strapping as shown in figure 4-14.

TDR-94 ATC/Mode S Transponder With

CTL-92/92A Transponder Control Unit

and CADC Altitude Source,Typical Installation Diagram

Figure 4-16

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Figure 4-17 shows a TDR-94D in a TCAS installa-

tion with a CSDB control and dual antennas. If

the transponder is operated with only a single an-

tenna, a special strap is required. The diagram

also shows a CADC for altitude data. This can be

an encoder as shown in figure 4-15. Either way,

appropriate

strapping is required. The CTL-92T is required for

TCAS control and is connected between the TDR-

94D and 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.

TDR-94D ATC/Mode S Transponder, Data Link, and TCAS Installation

With CSDB Control and CADC Altitude Data Source,

Typical Installation Diagram

Figure 4-17

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Figure 4-18 shows an installation similar to that

of figure 4-17. This can be seen as a typical TCAS

and

data link installation using an ARINC 429 control

for code selection and transponder/TCAS control.

TDR-94D ATC/Mode S Transponder, Data Link, and TCAS Installation

With ARINC 429 Transponder Control and

CADC Altitude Data Source,Typical Installation Diagram

Figure 4-18

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TDR-94/94D Mode S Transponder

Overall Block Diagram

Figure 4-19

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523-0775657-105118

5th Edition, 15 June 1995

1st Revision, 7 March 2007

TDR-94/94D ATC/Mode STransponder System

Maintenance

Table of Contents

Paragraph Page

5.1 GENERAL ........................................................................................................................................................................5-1

5.2 MAINTENANCE SCHEDULE ......................................................................................................................................5-1

5.3 TEST EQUIPMENT AND POWER REQUIREMENTS.............................................................................................5-1

5.4 TESTING AND TROUBLESHOOTING ......................................................................................................................5-1

5.5 MAINTENANCE DIANOSTIC DATA TREIEVAL AND ANALYSIS ..................................................................5-132

5.6 NUMBER SYSTEM CONVERSION AND DATA WORD DESCRIPTIONS.......................................................5-148

5.7 GILLHAM CODE DESCRIPTION WITH ENCODING AND DECODING INSTRUCTIONS ........................5-155

5.8 ACCEPTANCE TEST, TEST PANEL ASSEMBLY INSTRUCTIONS................................................................5-158

5.9 FLIGHTLINE TEST, TEST PANEL ASSEMBLY INSTRUCTIONS ..................................................................5-175

NOTICE: This section replaces 5th edition dated 15 June 1995.

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Page No Issue

* Title............................................7 Mar 07


5-1 thru 5-6 ............................... 5 May 93

5-7 thru 5-9 .............................. 15 Jun 95

5-10 thru 5-36............................ 5 May 93

5-37 thru 5-38........................... 15 Jun 95

5-39 thru 5-42............................ 5 May 93

5-43 thru 5-131........................... 5 Jun 955-132 thru 5-152........................ 5 May 93

5-153 thry 5-154....................... 15 Jun 95

5-154.1 Added........................... 15 Jun 95

5-154.2 Added Blank................ 15 Jun 95

5-155.......................................... 5 May 93

5-156 thru 157......................... 15 Jun 95

5-158 thru 5-163........................ 5 May 93

5-164 thru 5-168....................... 15 Jun 95

5-170 thru 5-197........................ 5 May 93

5-198 Blank............................... 5 May 93

5-199 thru 5-201 Deleted.......... 5 May 93




REV/

ED NO

REVISION

DATE

INSERTION

DATE/BY

SB NUMBER IN-

CLUDED

REV

NO

REVISION

DATE

INSERTION

DATE/BY

SB NUMBER IN-

CLUDED

0 / 1 4 Apr 90 None

0 / 2 29 Apr 91 None

0 / 3 6 Jan 92 None

0 / 4 5 May 93 See Table 1-6

0 / 5 15 Jun 95 See Table 1-6

1 / 5 7 Mar 07 See Table 1-6


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section Vmaintenance

5.1 GENE RAL

This section provides on board maintenance proce-

dures and limited bench checkout procedures for

t he TDR -94/94D ATC /Mode S Tra ns pond er. The

test procedures a re for use in:

a . Ch e ck in g a t ra n sp on d e r syst em on t h e b en ch

before installat ion to ensure that it is function-

ing properly, or

b . E xe rcisin g t h e t ra n sp on d e r syst e m on b oa rd

t h e a irpla n e t h rou g h a syst e m a t ic ro u t in e f orfault isolat ion to a defective LRU.

The bench procedures use a special test pa nel

described in para gra ph 5.9. The Flightline Fa ult

Isolat ion procedures use a similar, but less com-

plex, test panel which is described in paragraph

5.9. In both cases, data is provided to allow local

fabrication, or purchase from a supplier such as

Avionics Specialist s Inc, or J cAIR.

Fault isolation procedures should include a check

of t h e a irpla n e in st a l la t io n a n d wirin g w it h sp e cia l

at tention to condit ions that can contribute to afailure of the transponder system.

On board airplane fault isolat ion most often as-

sumes tha t a self-test can be performed. A system

that is totally non-responsive is usually best eval-

uated on the bench.

The TDR -94/94D perform s a full self-test a ut oma t-

ically upon unit power-up. I t then performs exten-

sive b a ck g rou n d t e st in g t o veri f y b u s st a t u s a n d

the condit ion of crit ical functions for diagnostic

purposes. U se the TES T button on the control

head to init iate a self-test .

5.2 MAINTE NANCE SCHE DULE

Collins h as no requirement for periodic maint e-

na nce of t he TD R-94/94D Mode S Tra nspond er.

5.3 TEST EQUIPMENT AND POWERREQUIREMENTS

5 .3 .1 T est E q u i p m e n t

Table 5-1 lists the test equipment required t o per-

form the t est procedures found in t his section.Equivalent test equipment can be substituted in

place of t he listed items.

5 .3 .2 P o w e r R eq u i r em en t s

All power required to perform the fl ightline sys-

tem tests and LRU fault isolat ion procedures is

provided by the airplane in which the system is

installed.

A bench 28-V dc supply, with at least 5-A peak

current output, is needed for the bench procedure.

5.4 TESTING AND T ROUBLESHOOTING

N ot e

The follow ing t est procedures a ssume t ha t

the airplane interconnect wiring has been

verified and is correct .

Test procedures in ta ble 5-2 provide a n opera tion-

a l t est of t he TDR -94/94D Mode S Tra nsponder. If

a n y of t h e se t e st s f a i l, o r i f t h e re is re a son t o su s-

pect a failure, then the Fault Isolat ion Proceduresin Table 5-5 a nd can be used to h elp isolat e a de-

fective unit.

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maintenance 523-0775657

Table 5-1. Test Equipm ent Requir ed.

E QU I P ME NT MANU FAC TU RE R C H ARAC TE RI S TI C F U NC TI ON

F lu ke 8010A, D v m J oh n F lu ke M fg . C o. , I n c.

Suit e 1131380 Corporate Center Curve

Eagan, MN 55121-1200

(612) 452-4264

P orta ble, 3-1/2 digit a ccu-

racy

Measure ac a nd dc voltages; for

use on ramp for wiring checkoutand with Flightl ine Test P anel or

on bench for Accepta nce Testin g

Tekt roni x 455, 2235,

2236, Oscilloscope

Tekt ronix

5350 Keystone Court

Rolling Meadows, IL 60008

(708) 259-7580

P o r t a b l e, d c t o 1 0 M H z M ea s u r e s e ri a l l og i c l ev el s ; f or

use with Flightline Test P an el or

on bench for Accepta nce Testin g

ATC -6 01 R a m p Te s t S e t I F R . I n c. ,

4053 Navajo Lane

Wichita, KS 67210

(316) 522-4981

Portable ATCRBS tran-

sponder Ram p Test S et.

Capable of broadcast and

direct-connection testing

of normal t ransponder

opera tion in modes A, C,

a n d M o d e S , a s w e l l a s a l ldefined a nd a pplicable

uplink /downlink for-

m a t s .

For ATCRBS and Mode S ground

stat ion simulation in fl ightl ine or

bench testing procedures.

RF loa d M/A-C OM Omni S pect ra , I nc.

21 Continental Blvd

Merrimac, NH 03054-9979

50-Ω at 1090 MHz TNC

or B N C w i t h a d a p t er

RF termination of unused anten-

na output (TDR-94D only). Need-

ed on flightl ine only when using

direction connection met hod.

D iv er sit y B oot L oca lly f a br ica t ed (in clu ded

with ATC-601)

Rf opaque for diversity

testing. Ideally, it should

have an adhesive base.

To isolat e an tenna ports for broa-

dcast diversi ty testing on the

flightline.

Da ta Tra c 400H *

Da ta Tra c 400 *

Da ta Tra c 200 **

Atlantic Inst ruments, Inc.

P.O. Box 021466

Melbourne, FL 32902(407) 951-2542

Portable, battery opera-

ble,

*ARINC 429 bus simula-tion and analysis,

** ARINC 429 and CSDB

bus simulation and analy-

si s

Control head simulation and data

bus analysis; for use on ramp

with Flightline Test P an el or onbench for Accepta nce Testin g

J cAI R 429E J cAI R

400 Industrial Parkway

Industrial Airport, KS 66031

(913) 764-2452

ARINC 429 bus simula-

tion and analysis

Control head simulation and data

bus analysis; for use on ramp

with Flightline Test P an el or on

bench for Accepta nce Testin g

Accepta nce Test , Test

P a n e l

Locally fabricated according to

d a t a i n p a r a g r a p h 5. 8 a t t h e

end of this section. This para-

graph a lso lists the va rious

cables needed.

B e nch t es t p a ne l To pr ov id e i npu t /ou t pu t con t rol

and unit/test equ ipment interfa ce

for bench testing.

F l ig h t li ne Te st P a n e l L oca l ly f a b ri ca t e d a c cor d in g t o

d a t a i n p a r a g r a p h 5. 9 a t t h e

end of this section. This para-

graph a lso lists the va rious

cables needed.

P o r ta b l e t e st d ev ice To p rov id e a c ce ss t o s ig n a ls b e-

tween control a nd t ransponder

unit

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5 .4 .1 D i a g n o st i c I n f o r m a t i o n

The procedures in table 5-6 provide for the retriev-

al of diagnostic data that is stored in non-volatile

memory in t he TRD -94/94D tr a nsponder. This

data can be helpful in diagnosing certain type of

failures especially those of a more transient na-ture. R efer to ta ble 5-3 for a description of the

diagnostic codes a nd the recommended t rouble-

shooting procedure. Ta ble 5-4 provides a dditiona l

informa tion for proper interpretat ion of th e diag-

nostic codes.

5 .4 .2 T est E q u i p m e n t I n s t a l l a t i o n a n d P o w er

A p p l i c a t i o n F o r F l i g h t l i n e Test i n g U s i n g A

R a m p T e s t e r

5 .4 .2 .1 P r el i m i n a r y I n s t r u c t i o n s

Refer to table 5-2 for the transponder system flig-htline t est ing a nd fault isolat ion procedures. These

procedures use t he test setup shown in fi gure 5-1

an d provide for a quick init ial check to determine

whether or not the transponder system is function-

a l . I f t h is ch eck sh ows t h a t a f a u lt e xist s , re fe r t o

the procedures in ta ble 5-5 for more deta iled fault

isola t ion . A t e st p a n e l a n d d a t a b u s rea d e r a re

needed for these procedures.

5 .4 .2 .2 B u s R e a d e r S e l e ct i o n

Any one of th e four bus readers listed in ta ble 5-1

can be used. However, of those listed only the

Atla ntic Inst ruments Da ta Tra c 200 is capable of

re ce ivin g a n d t r a n sm it t in g e i t h er t h e CS D B or t h e

ARINC 429 bus forma t. The others a re ARINC

429 only. Therefore, if the installation includes a

CTL-92/92A contr ol, only t he D a ta Tra c 200 ca n be

used to simulate that control.

5 .4 .2 .3 R a m p T est e r S el ec t i o n a n d U se

The IFR ATC-601 was used in the development of

t h e p roced u re s in t h is m a n u a l . I t is p ossible t h a t

other instruments, i .e . , instruments provided byot h e r m a n u a f a ct u re rs, h a ve com p a ra b ly a n d a c-

ceptable featur es. You should feel free to use your

choice of instruments. However, be sure tha t it is

capable of test ing the transponder operating items

list e d a t t h e e n d of t h is p a ra g ra p h .

Most transponder ramp testers can be used in

direct-connect or broadca st opera ting modes. At

t im e s b ot h m e t h od s a re u se fu l in isola t in g a t ra n -

sponder malfunction between the antenna /anten-

n a ca b le s a n d t h e t ra n sp on d e r u n it . F o r exa m p le,i f in t h e b ro a d ca st m e t h o d t h e t e st sh ows a low

pow er output or low sensit ivity. Sw itching to the

direct-connection method can effectively isolate the

problem t o the tra nsmitt er/receiver or the a nten-

n a syst e m .

If y ou use the direct connection method a nd y ou

are using a test set other than the IFR ATC-601,

b e su re it h a s t h e p ro pe r a t t e n u a t ion in t h e RF

link to prevent damage to the transponder receiv-

er. The IF R ATC-601 ha s t he proper a t tenua tion

b u ilt in t o i t s r f p o rt . I f a n ot h e r t yp e of t e st e r is

being used, check the manual to be sure it pro-vid es a d e qu a t e p rot e ct ion . B e su re t h a t t h e in je ct -

ed signal level is not greater than -20 dBm.

Most transponder ramp test sets allow operation

in sid e a h a n g e r. B e a wa re , h owe ve r, t h a t t h e

glossy (an d often pa inted) floor surfaces found in

m o st h a n g e rs ca n re sult in su b st a n t ia l s ig n a l re -

fl ection. This can ha ve an effect on power output

an d receiver sensit ivity tests. Moving the sense

a n t e n n a a b o ve o r b e low t h e t r a n sp on d e r a n t e n n a

usually produces different results and demonstrat-

es the effect of signal reflection. I t is for this rea-

son t h a t yo u sh ou ld t ry a f ew d iff ere n t se n se a n -

t e n n a h e ig h t s , d ist a n ces, a n d a irpla n e p a rk in g

locations to gain a basis for test result interpreta-

t ion a n d e va lu a t io n . B e g u id ed b y t h e a n t e n n a

placement requirements of the test set manufac-

turer.

L oca t e t h e ra m p t e st e r sen se a n t e n n a a t t h e p rop -

e r d ist a n ce f rom t h e a irpla n e t ra n sp on d e r a n t e n -

n a . Th e b est d ist a n ce a n d h e ig h t m a y b e sp ecifi e d

b y t h e m a n u f a ct u re r.

Mode s diversity transponder installat ions mayrequire shielding of one antenna for diversity test-

ing. An RF opaque boot of near ly any design is

acceptable for t his purpose. I t should fi t complete-

ly over the antenna and provide good base ground-

in g . An a d h e sive ba se m a y b e b est f o r ea sy in st a l-

la t ion a n d re m ova l .

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The IFR ATC-601 features a special automatic test

se qu en ce t h a t s ig n ifi ca n t ly re d u ce s t h e t im e re-

qu ire d for t h e t e st . Usin g t h e a u t o m a t ic sequ e n ce

or a n e qu iva le n t m a n u a l se qu e n ce is la rg e ly a

ma tt er of personal choice. However, if a par t ic-

u la r t e st f a i ls in t h e a u t om a t ic sequ e n ce , i t m ig h t

b e a d visa b le t o re pe a t t h a t t e st m a n u a lly t o h e lpin isola t in g t h e f a u lt . F o llow t h e t e st se t o pe ra t -

ing procedures as provided.

At least the following transponder operating items

should be tested. The order is not crit ical. :

1. Mode A response.

2 . M od e C re sp on se wit h a l t i t u d e if a va i la b le.

3. Mode S all-call response,

4. Mode S lockout.

5. Tra nsmitt er frequency.

6. Tra nsponder power output.

7. Receiver frequency discrimina tion.

8. Receiver sensit ivity.9. Receiver interrogation pulse spacing discrimi-

na tion (all modes). This involves altering the

pulse spacing from normal and test ing the

transponder’s reply or lack of reply.

10. Individual pulse-widt h d iscriminat ion (all

modes). This is the sam e type of test a s 9.

except that the pulse width is changed instead

of the pulse spacing.

11. SL S (side lobe suppression). This involves

changing the P2 pulse amplitude with respect

to the P 1/P 3 pulses an d t est ing the t ra nspond-

er’s r esponse.

12. Tra nsponder response t o invalid add ress int er-

rogations.

13. S P R on/off.

14. Mode S, U F0 (uplink format 0).

15. Mode S, UF4.

16. Mode S, UF5.

17. Mode S, U F11.

18. Mode S, U F16.

19. Mode S, U F20.

20. Mode S, U F21.

21. Diversity isolation (TDR-94D, operating with

d u a l a n t e n n a s on ly).

22. Tra nsponder sq uitt er.23. Airplane identification code.

5 .4 .2 .4 T r a n s p o n d e r S y st e m I n s p e ct i o n

I f t h e n a t u re o f t h e t ra n sp on d e r f a i lu re re port is

su ch t h a t i t m a y b e ca u se d b y a n t e n n a ca b les o r

antennas, inspect these for possible physical dam-

age or deteriorated installat ion integrity.

The condit ion of the transponder antenna, anten-

na cable(s), a nd ca ble connectors can h ave a signif-

ican t effect on tra nsponder opera tion. Therefore,

an occasional visual inspection of these compo-

nents is advisa ble. However, do not disassemble

the airplane to inspect antenna cables unless you

have good reason to suspect a cable or connector

problem.

5 .4 .2 .5 T r a n s p o n d e r S y st e m G r o u n d T es t E n -

a b l e

Some transponder installat ions use a weight-on-wheels transponder inhibit mechanism to prevent

response to interrogations while the airplane is on

t h e g rou n d . I t is n e ce ssa ry t o d isa b le t h is in h ibi t

f ea t u re f or t e st in g . Th is is u n iqu e t o e a ch a ir-

plane therefore you must consult the airplane

manual for the necessary instructions.

I t m a y a lso b e n e ce ssa ry t o con d it ion t h e a l t i t u d e

data system for test purposes.

5 .4 .3 F l i g h t l i n e T est P r o c ed u r es

Tra nsponder sy stem test ing procedures, for us e on

the fl ightline, are shown in ta ble 5-2. These pro-

cedures will verify that the system is functional.

If a failure is detected or suspected because of

pilot complaint or other evidence, the fault isola-

tion procedures in table 5-5 provide more detailed

t e st in g a n d L RU p erf orm a n ce a n a lysis .

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Table 5-2. Tran spond er System, Fl igh tl i ne Test Procedu res.

TE S T P ROC E D U RE D E S I RE D RE S U LT TROU B LE S H OOTI NG

INSTRUCTIONS

1. S et up: P repa re t he a irpla ne a nd t ra nsponder sy st em for t est ing a s req uired. As a m ini-

mum t his wil l require:• Be sure that t he air/ground test inhibit , i f used, is functional . P2-53 must be

grounded to al low a ma nual self-test .

• Set al t imeter system(s) for a test al t i tude (consult airplane manual for neces-

sary procedures) especially as may be required for TCAS if used.

• Setup IFR ATC-601 Ramp Tester and perform the necessary preliminary tests

for it.

• I f the broadcast method of testing will be used with the ATC-601 (or equiva-

lent) ramp tester a nd t he instal lat ion consists of a TDR-94D diversi ty t ran-

sponder instal l a n r f boot over the top antenna . I f the direct connection is

being used, disconnect both ant enna cables from t he tra nsponder mount,

connect the ATC-601 to the lower antenna connector and install an rf load on

the upper connector.

Note: I f the t ransponder instal lat ion ma kes the direct connection method quite

difficult , th e broadcast method should be seen as preferred unless ini t ial t ests

suggest an adva nta ge in fa vor of direct connection.

2. 0 I ns pect ion : B efor e a pply in g pow er t o t he t r an spon der s ys tem , m a ke a v is ua l in spect ion of t he

tra nsponder antenn a(s), ATC control, and t he r/t. B e sure the r/t is fir mly seat ed

in i ts mount and there are no obvious signs of a dysfunctional insta l lat ion. I f i t is

possible, check the antenna cable connections on the back of the transponder for

tightness and the wire harness for obvious signs of broken wires or dislodged

connector pins.

3.0 P ow er a pplica t ion :

Apply power to t he tra n-

s p on d er s y s t e m . E n t e r a n

appropriate code into the

control and set for normal

operation.

Normal operation:

In the case of the IFR ATC-601, the

INTERR and REP LY indicators should

both be lit.

I f the instal lat ion is equipped with a

CTL-92/92A -2XX contr ol, " diAG " ma ybe displayed in the lower window i f a

diagnostic is detected. I t is necessary,

then, to press TEST to display t he

diagn ostic code.

If the broadcast method of testing is

being used with the ATC-601, a void use

of an emergency ident code (consult the

airplane manual i f you are unsure).

I f the INTERR la mp does not l ight , t he

ramp tester is not functioning properly.

I f the REPLY lamp does not l ight , thetran sponder is not responding. Check

for possible ground operation inhibits.

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Table 5-2. Tran spond er System, Fl ight l i ne Test Procedu res.

TE S T P ROC E D U RE D E S I RE D RE S U LT TROU B L E S H OOTI NG

INSTRUCTIONS

4.0 S elf Test :

Press the ATC TEST buttonon the ATC control.

Note: The instal lat ion may

feature a remote ATC TEST

button in which case use i t

instead.

If the insta l lat ion uses an ATC control

hea d ot her th a n t he C TL-92/92A orRTU-870A/T, you ma y n eed t o consult

the airplane manual to determine

where the ATC self test results are

d i sp la y e d a n d i n w h a t f or m a t a n y d i a g -

nostics are disclosed.

Test results should not show a ny dia g-

nostic other tha n 00 (no faults detect-

ed). In th e case of t he C TL-92/92A , th e

diagnostics are displayed on the control.

See ta ble 5-3 for an interpretat ion of the

diagn ostic code.

A norma l ind icat ion on t he C TL-92/92A is:

• The active code display intensity modulates from minimum to maximum.

• On all CTL-92/92A controls:

• "AL" is displayed in the upper window a nd the al t i tude in thousands of feet

in 100-foot increments is displayed in the lower window.

• I f a diagnostic condition is detected, the upper window shows "dIAG" and the

tw o-digit dia gnostic code is displayed in t he lower window. Refer to ta ble 5-3

for a l ist ing of the codes, and table 5-4 for an interpreta tion and explanat ion

of each.

5.0 Aut o Test :

Select AUTO TES T on the

IFR ATC-601 and press

R U N .

All AUTO TES T items should indicate

PASSED. This test ta kes about 30 sec-

onds t o complete.

Note: I t is possible that t ests 13, 14,

and 15 indicat e FAILED . These i tems

are a function of da tal ink capabil i t ies

and may not be implemented in w hich

case you can ignore this fai lure indica-

tion.

Successful completion of tests verifying

these i tems, a nd no other indicat ion of

failure (like pilot or ATC complaints),

indicates a functional transponder.

Otherwise, a fa i lure of a ny one or more

of the i tems, may indicat e a performance

problem. In this case, consider removing

the transponder for addit ional analysis

and repair on the bench.

6.0 Oppos it e a n ten na t es t:

If the direct connection met-

hod is being used, switch the

test set cable to the other

a n t e n n a p or t . I f t h e b roa d -

cast m ethod is being used,

move the r f boot to the top

(or opposite) an tenna con-

nector and repeat the test .

The test results should be approximate-

ly equivalent between the two antenna

test .

I f there is a substantia l di fference in

receiver sensitivity an d/or power out put,

i t m a y b e ca u s e d b y a f a u l t y a n t e n n a ,

antenna cable, or connector installation.

In t his case, inspection a nd repair of the

antennas, cables, or cable connectors is

needed.

7.0 E q uipm en t r em ov a l a n d r es -

toration:

Restore al l equipment t o i ts normal ground operating configura tion. Return the test

set to i ts normal storage location. Careful handling and storage of al l ramp t est

equipment prolongs the service life and reduces maintenance costs.

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Tab le 5-3. TDR -94/94D D ia gnost ic Codes

PRIMARY

CODE

SECONDARY

CODE

DESCRIPTION DIAGNOSTIC DISPLAY

TI F/W

00 No fault found

10 Power supply diagnostics (1) (1)

11 +5 V dc Yes Yes

12 +70 V dc No No

13 +35 V dc No No

14 LVPS No No

20 Transmitter/modulator diagnostics (2) (2)

21 Final stage, overcurrent Yes Yes

22 Top antenna, low power output No No

23 Bottom antenna low power output No No

24 Transmitter overtemperature No No

30 Synthesize diagnostics No No

31 Synthesizer lock detect No No

32 Synthesizer low power detect No No

40 Receiver/IF diagnostics No No

41 Top receiver channel No No

42 Bottom receiver channel No No

43 Top DPSK demodulator No No

44 Bottom DPSK demodulator No No

50 Program memory (ROM) diagnostics Yes Yes

51 High-byte ROM Yes Yes

52 Low-byte ROM Yes Yes

53 Both ROM chips Yes Yes

60 Volatile memory (RAM) diagnostics Yes Yes

61 High-byte RAM Yes Yes

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PRIMARY

C O D E

SECONDARY

C O D E

D E S C RI P TI ON D I AG NOS TI C D I S P LAY

TI F /W

60 (cont ’d) 62 Low -by t e RAM Yes Yes

63 B ot h RAM chips Yes Yes

64 C a che RAM Yes Yes

65 C a che RAM a nd high-by t e RAM Yes Yes

66 C a che RAM a nd low -by t e RAM Yes Yes

67 C a che RAM a nd bot h RAM chips Yes Yes

68 D ua l port RAM Yes Yes

70 Nonvola t ile memory (NVRAM)dia gnos-

tics

No No

80 S er ia l input cont r ol bus dia gn ost ics (4) No

81 ARI NC 429 cont r ol U ART (4) No

82 ARI NC 429 cont r ol por t A ina ct ive (4) No

83 ARI NC 429 cont r ol por t B ina ct ive (4) No

84 ARI NC 429 cont r ol por t C ina ct ive (4) No

85 C S D B cont rol input port A ina ct ive (4) No

90 S er ia l a lt it ude input dia gnost ics No No

91 ARI NC 429/575 a lt it ude U ART No No

92 ARI NC 429/575 input port A ina ct ive No No

93 ARI NC 429/575 input port B ina ct ive No No

94 C S D B a lt it ude input port A ina ct ive No No

95 C S D B a lt it ude input port B ina ct ive No No

A0 AD L P comm unica t ion dia gnost ics No No

A1 AD L P comm A/B U ART No No

A2 AD L P comm A/B bus ina ct ive No No

A3 AD L P comm C /D U ART No No

A4 AD L P comm C /D bus ina ct ive No No

B 0 TC AS communica t ion dia gnost ics No No

B 1 TC AS U ART No No

B 2 TC AS unit - -

B 3 TC AS bus ina ct ive No No

B 4 TC AS prot ocol error No No

C 0 S q uit t er dia gnost ics No Yes

C 1 (TD R-94D only ) Top cha nnel sq uit t er No Yes

C 2 (TD R-94D only) B ot t om cha nnel sq uit t er No Yes

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PRIMARY

CODE

SECONDARY

CODE

DESCRIPTION DIAGNOSTIC DISPLAY

TI F/W

D0 (TDR-94D only) Diversity diagnostic No Yes

E0 Message processor diagnostics No No

E1 (TDR-94D only) Top channel message processor, soft

failure

No No

E2 Bottom channel message processor, soft

failure

No No

E3 Top channel message processor, hard

failure

Yes Yes

E4 Bottom channel message processor, hard

failure

Yes Yes

F0 Configuration diagnostics No No

F1 Mode S discrete address changed No No

F2 TCAS selection changed No No

F3 Altitude units selection changed No No

F4 Max airspeed program selects changed No No

F5 Port selects changed No No

F6 SDI selects changed No No

F7 Single antenna selection changed No No

F8 ADLP selection changed No No

F9-FE (not assigned)

FF Unacceptable mode s address selected

(address lines are all 0 or all 1)

Yes Yes

Notes:

Except for 00, 70, and D0, primary diagnostics are not displayed.

(1) Transmitter is inhibited (TI) and failure warn (F/W1) output (P1-31) is set only if a diagnostic code 11 is detected.

(2) Transmitter is inhibited and F/W1 discrete is set only if a diagnostic code 21 is detected.

(3) Transmitter is inhibited and TDR-94/94D is set to standby only if all selected control inputs are nonfunctional.

(4) Transmitter is inhibited and TDR-94/94D is set to standby only if the control bus failure is detected on the selected control

bus.

(5) Transmitter is inhibited and TDR-94/94D is set to standby only if serial control is selected and all serial inputs are

nonfunctional.

1 "F/W set" here refers to:

a. TDR-94/94D fault monitor discrete output, P1-31, set to high level,

b. TDR-94/94D CSDB data word label 1F, byte-1, bit-7, set to logic 0, and

c. TDR-94/94D ARINC 429 SSM and other data bits related to diagnostics set to the appropriate fault level.

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Table 5- 4. TD R- 94/ 94D Di agnost ic Code Descr ipt ion an d L RU Di sposi t ion

Diagnostic

Code

Tit le D escr ipt ion a nd L RU D isposit ion

For purposes of this diagnostic code interpretation and for the sake of brevity, the following fault levels are defined:

Level 1: A level 1 fault is d efin ed as one in which th e TDR-94/94D sh ould be removed for furt her test ing or fau lt isolation onthe bench.

Level 2: A level 2 fault is defin ed as one in wh ich the TDR-94/94D is demonstr at ing a failure w hich may not prevent it from

performing continued but t emporary service. That is , a diagnostic which indicat es a fai lure in a peripheral function. For

example, a diagnostic code A? indicating an ADLP fault . I f a n ADLP is not being used in the insta l lat ion the t ransponder ma y

operate normally in its other functions.

Level 3: A level 3 fault is d efin ed as one in which th e TDR-94/94D h as experienced a cha nge in t he insta llation, i .e., external t o

the TDR-94/94D. In th is case, further a na lysis is needed to correct or restore the insta llation as needed. For example, a

diagnostic code F4 indicat ing a change in the ma x airspeed strapping. This strongly suggests a n a irplane w iring problem.

Reference to a fai lure wa rning indication should be understood to be the fla g.

00 N o f a u lt f ou n d Th is c od e i nd ica t e s t h a t n o f a il ur e w a s d et e ct e d d u ri ng t h e m os t r ece nt s el f t e st

routine.

11 + 5 V d c L ev el 1. Th is d ia g nos t ic cod e is t y pi ca l ly a ccom pa n ie d b y a f a il ur e w a r n in g in di ca t ion .

It is caus ed by a out-of-tolerance condition in t he + 5 V dc power supply.

12 + 70 V d c L evel 1. S a m e a s 11 except t ha t it a pplies t o t he + 70 V d c s upply on h vps m od ule A1.

13 + 35 V d c L evel 1. S a m e a s 11 except t ha t it a pplies t o t he + 35 V d c s upply on h vps m od ule A1.

14 LVP S L evel 1. S a me a s 11 except t ha t it a pplies t o t he low volt a ge pow er s upply on m od ule

A7.

21 Tr a nsmit -

ter/modulat or, fi na l

stage, overcurrent

Level 1. This diagnostic code is typically a ccompanied by a fa ilure war ning indication.

I t is caused by a sensed high current condition in the fi nal tra nsmitter stage. This

may be accompanied by a diagnostic code 24.

22 Top a nt enna low

power output

Level 1 if verifia ble, otherw ise level 2. This diag nostic code is ty pically not a ccompa-

nied by a fai lure wa rning indication. I t is caused by a sensed low power output

condition a t the top ant enna output fi nal st age. This may be verifia ble in the ATC-601

test. This dia gnostic will not occur on a TDR-94 (non-diversity) unit.

23 B ot t om a nt enna

low power output

Sa me as 22 except that i t applies to the bottom antenna output port .

24 Tr ansmit ter over

temperature

Level 1. The same as 21 except tha t i t is caused by a high temperature condition.

31 S ynt hesizer lock

detect

Level 1. This diagnostic code is typically not accompanied by a fa ilure wa rning condi-

tion and occurs when t he synthesizer output frequency does not a gree with the proces-

sor command . This condition may be verifia ble in the ATC-601 test a s a t ra nsmitt er

off frequency failure.

32 S ynt hesizer low

power detect

Level 1. Much the same a s 31 except tha t i t applies to the synt hesizer output level. A

sufficiently low output ma y prevent the modulat or, a nd hence the t ransmitter or

receiver, from operat ing.

41 * Top r eceiv er ch a n-

ne l


tion and occurs when the top receiver channel does not respond properly to a simulated

test signal generat ed by the bottom channel receiver. I t is possible tha t t he bottom

channel ma y st ill be functional. Neither dia gnostic 41, 42 or 43 occur on a TDR-94.

* See the note 1 at the end of this ta ble

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Table 5- 4. TD R- 94/ 94D D iagnost ic Code Descr ipt ion an d L RU Di sposi t ion

Diagnostic

Code

Tit le D escript ion a nd LRU D isposit ion

42 * B ot tom r eceiver

channel

Level 2. Sa me as 41 except that the channel roles are reversed. See note 1 at t he end

of this ta ble.

43 Top D PS K demodu-

lator

Level 1. This diagnostic code is typically not accompanied by a failure warning condi-

tion and occurs when t he top DP SK demodulator does not respond properly to a

simulated mode s test signal . I t is possible that the unit ma y st i l l respond properly to

ATCRB S (mode A and C) interrogations. * See the note at te end of this table.

44 B ot t om D P SK de-

modulator

Level 1. Sa me as 43 except tha t i t applies to the bottom channel .

51 H i gh -b y t e R O M L ev el 1. Th is d ia g n os t ic cod e i s t y pi ca l ly a c com pa n i ed b y a f a il ur e w a r n i ng con d it i on .

During self-test the microprocessor executes a memory modulo 64K summation of all

memory locat ions a nd compares t hat result aga inst a stored check-sum va lue. This

diagnostic indicat es tha t the high-byte ROM fa i led t hat comparison t est .

52 L ow -b yt e R OM L ev el 1. S a m e a s 51 ex ce pt t h a t t h e l ow -b yt e R OM f a il ed t h e t es t .

53 B ot h R OM ch ips L ev el 1. S a m e a s 51 ex ce pt t h a t b ot h R OM s f a ile d t h e t es t .

61 H i gh -b y t e R AM L ev el 1. Th is d ia g n os t ic cod e i s t y pi ca l ly a c com pa n i ed b y a f a il ur e w a r n in g c on d it i on .

During self-test the microprocessor executes a read /writ e test on all a vaila ble volat ile

RAM locat ions using AAAAH a nd 5555H da ta . This diagn ostic indicat es tha t one or

more high-byte RAM device failed this test.

62 L ow -b yt e R AM L ev el 1. S a m e a s 61 ex ce pt t h a t t h e l ow -b yt e R AM d ev ice f a ile d t h e t es t .

63 B ot h R AM L evel 1. Sa me a s 61 except t ha t bot h RAM d evice fa iled t he t es t.

64 C a ch e R AM L ev el 1. Sa m e a s 61 except t ha t t he ca ch e R AM f a iled t he t es t.

65 C a che a nd high-

byte RAM

Level 1. Sa me a s 61 except tha t both the high-byte RAM (61) and ca che RAM (64)

fai led the test .

66 C a che a nd low -byt eRAM

Level 1. Sa me a s 61 except tha t both the low-byte RAM (62) and ca che RAM (64)fai led the test .

67 C a che a nd bot h

RAM

Level 1. Sa me as 61 except tha t both RAM (63) and cache RAM (64) failed the test.

68 D u a l por t R AM L ev el 1. S a m e a s 61 ex ce pt t h a t t h e d ua l por t R AM f a ile d t h e t es t .

70 N VR AM L ev el 1. Th is d ia g n os t ic cod e i s t y pica l ly n ot a ccom pa n ied b y a f a ilu re w a r n in g con di -

tion. During power-up the microprocessor executes a read/wr ite test on t he last 16

bytes of the NVRAM to verify proper operat ion. This diagn ostic indicates th at the

NVRAM fai led tha t t est .

81 AR I NC 429 U AR T L ev el 1. Th is d ia g n os t ic cod e i s t y p ica l ly n ot a c com pa n i ed b y a fa i lu r e w a r n i ng

condition. Dur ing self-test, t he microprocessor forces the output from all serial control

UARTs to feedback to t he input. The microprocessor verifi es tha t t he U ART processes

this ARINC w ord properly. This diagn ostic indicat es tha t t he ARINC 429 UART failedthis test .

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Table 5- 4. TD R- 94/ 94D Di agnost ic Code Descr ipt ion an d L RU Di sposi t ion

Diagnostic

Code

Tit le D escr ipt ion a nd L RU D isposit ion

82 ARI NC 429 cont rol

port A inactive


tion. During normal non-burst mode operat ion, the microprocessor periodicallymonitors the selected serial ports for bus activi ty. During burst mode, this t est is not

performed because there is no wa y of predicting the a rrival of control data . This

diagnostic code indicates t hat ARINC 429 control port A has no bus a ctivity for at least

1-second.


port B inactive

Level 2. Sa me as 82 except tha t i t a pplies to ARINC 429 control port B.


port C inactive

Level 2. Sa me as 82 except t hat it a pplies to ARINC 429 control port C.

85 C S DB cont rol port

A inactive

Level 2. Sa me as 82 except that i t a pplies to CSDB control port A. Monitor t ime is

extended to 2-seconds.

86 C S DB cont rol port

B inactive

Level 2. Sa me as 85 except that i t applies to CSDB control port B .

91 AR INC 429/575

alti tude U ART

Level 2. Sa me a s 81 except t hat it a pplies to the ARINC 429/575 altit ude U ART.

92 AR INC 429/575

alti tude input port

A


tion. During normal operat ion, the microprocessor periodically monitors t he selected

alt i tude input ports for bus activi ty. This diagnostic code indicates tha t ARINC

429/575 alt itude input port A has no bus a ctivity for a t lea st 2-seconds.

93 AR INC 429/575

alti tude input port

B

Level 2. Sa me as 92 except tha t it applies to ARINC 429/575 altitu de input port B .

94 C S D B a lt it ude

input port A

Level 2. Sa me as 92 except that i t applies to CSDB al t i tude input port A.

95 C S D B a lt it ude

input port B

Level 2. Sa me as 92 except that i t applies to CSDB al t i tude input port B .

A1 AD LP comm A/B

UART


tion. During power-on self-test a nd w henever a comm A/B bus fa ilure is suspected, th e

microprocessor forces the UART output to feedback to the input and verifies that the

UART processes the dat a properly. This diagnostic code indicates tha t ADLP comm

A/B UART failed t he t est.

A2 AD LP comm A/B

input port


tion. The determina tion of a fa ilure in this function involves a highly complicat ed

exchange between dat a l ink transmitters and receivers involving dat a word check-sums

and pa ri ty checks. This diagnostic code results after repeated a ttempts to establish a

reliable communica tions link fail. The fa ilure should be verifia ble in the ATC-601 tests

9 through 15.

A3 AD LP comm C /D

UART

Level 2. Sa me as A1 except tha t it applies to ADLP comm C /D U ART.

A4 AD LP comm C /D

input port

Level 2. Sa me as A2 except tha t it a pplies to ADLP comm C/D input port.

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Table 5- 4. TD R- 94/ 94D D iagnost ic Code Descr ipt ion an d L RU Di sposi t ion

Diagnostic

Code

Tit le D escript ion a nd LRU D isposit ion

B 1 TC AS U AR T L ev el 2. Th is d ia g n os t ic cod e i s t y p ica l ly n ot a c com pa n i ed b y a f a il ur e w a r n i ng con d i-

tion. Whenever a TCAS is selected an d a bus fa ilure is suspected, the microprocessorforces t he U ART output to feedback to the input a nd verifies that the U ART processes

the da ta properly. This diagnostic code indicates tha t TCAS UART failed the test .

B 2 TC AS u n i t f a i lu r e L e ve l 3 . Th i s d i a g n os t i c c od e i s t y p ic a l ly n ot a c com p a n i ed b y a TD R -9 4D f a i lu r e

wa rning condition. This diagn ostic code indicates tha t TCAS opera tion is selected and

a TCAS unit fa ilure wa rning ha s been received. The TCAS unit should be indicat ing a

fai lure warning.

B 3 TC AS b u s i n a ct i v e L e ve l 2 . Th i s d i a g n os t i c c od e i s t y p ic a l ly n ot a c com p a n i ed b y a f a i lu r e w a r n i n g c on d i -

tion. When TCAS is selected, the microprocessor periodically monitors t he TCAS input

port for bus activity. This diagnostic code indicates tha t th e TCAS input port is

inactive, or fai ls to meet certain par i ty, ra te, and stat us conditions, for a t ime exceed-

ing the normal update ra te which varies according to the type of data to be exchanged.

B 4 * TC AS prot ocol

error

Level 2. This diagn ostic code is typically not a ccompan ied by a fa ilure wa rning condi-

tion. This diagn ostic code indicat es tha t t he TCAS da ta being received does not complywith t he required protocol. * See the note 2 at t he end of this table.

C 1 Top cha nnel

squitter (TDR-94D

only)

Level 1. This diagn ostic code is typically a ccompan ied by a fa ilure wa rning condition

and indicat es tha t the t op channel squitter function is not functioning properly.

C 2 B ot t om cha nnel

squitter

Level 1: Sa me as C1 except that i t applies to the bottom channel .

D 0 D iver sit y (TD R-

94D only)

Level 1. This diagn ostic code is typically a ccompan ied by a fa ilure wa rning condition

and indicates an inabil i ty to exchange data between the top and bottom channel as

described for diagnostic 41 and 42 and others below.

E 1 Top cha nnel m es-

sag e processor

This diagn ostic code without a n accompanying E 3 diagnostic code is typically not

accompanied by a fai lure wa rning condition. During self test the bottom channel PAM

is preloaded to generate an ATCRBS or mode s interrogation which is injected into thetop channel for processing. I f t he message is n ot properly processed an E1 diagnostic

code is recorded a nd th e process is repeated. If th e failure occurs on thr ee consecutive

at tempts, an E3 diagnostic code is recorded. An E 3 diagnostic code is typical ly

accompanied by a fa ilure war ning condition. Therefore, an E 1 diag nostic code wit hout

an accompanying E 3 diagnostic code can be ignored unless a pattern is detected w hich

may indicate a marginal condition.

E 2 B ot t om cha nnel

messag e processor

Sa me a s E 1 except tha t i t a pplies to the bottom channel message processor.

E 3 Top cha nnel ha rd

messag e processor

Level 1. See E1 above.

E 4 B ot t om cha nnel

hard message pro-

cessor

Level 1. Sa me as E3 except tha t i t a pplies to the bottom channel message processor.

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5.4.4 5.4.4 F l i g h t l i n e F a u l t I sol a t i o n

Pr o ce d u r es

This paragraph provides procedures for

isolat ing a transponder equipment

m a lf u n ct ion t o a p a rt icu la r L RU . Th e

procedures in ta ble 5-5 require the use of at e st p a n e l , ra m p t e st e r , d vm , a n d a d a t a b u s

rea der/simula tor.

Table 5-1 lists t he va rious units w hich can be

used. Other similar units may become

available which also can be used provided the

capabilit ies ar e similar t o those listed. Referto figure 5-1 for the t est setup dia gra m.

Fl ight l ine Faul t I solat ion, Test Set up Diagr am

Figur e 5-1

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Table 5- 5. Tr ansponder Syst em, Fl ight l i ne Faul t I solat i on Pr ocedur es.


INSTRUCTIONS

4 .1 .b . S e lf -t e s t d i sp la y o n R TU -

870A/T:Select the ATC page and

press the ATC test key.

A norma l in dicat ion on th e R TU -870/870A

is (top t o bottom):• U p pe r w i n dow : O N AL T

• S e con d w i n dow : X XX XX F T

• Th i r d w i n d ow : (n ot u s ed )

• F ou r th w i nd ow : TS T

• Lower window: (ATC code)* RTN

4 .1 .c . ATC s e lf -t e s t d i sp la y f or

systems using the TTC-920G,

CTL-92T, or other type of

ARINC 429 transponder /

TCAS control.

Press the TEST button on the

control.

Consult the airplane manual for the

location and format of transponder a nd

TCAS self-test display, especially the

display of any possible ATC diagnostics.

5. 0 S e t up t h e ATC -601 f or AU TO

TEST and select RUN.

All AUTO TES T items sh ould indicat e

PASSE D. This test takes about 30 sec-onds t o complete.

Note: I t is possible that t ests 13, 14, and

15 indicat e FAILED. These items a re a

function of data l ink capabil i t ies a nd ma y

not be implemented in which case you can

ignore this failure indication.

Otherwise, a fai lure of any

one or more of the items,may indicat e a performance

problem. In this case, con-

sider removing t he tra n-

sponder for additional

analysis and repair on the

bench.

6.0 Oppos it e a n ten na t es t:

If the direct connection

method is being used, switch

the test set cable to the other

a n t e n n a p or t . I f t h e br oa d -

cast method is being used,

move the rf boot to the top (or

opposite) antenn a connectorand repeat the test .

The test results should be approximately

equivalent between the two antenna test .

I f t h e r e i s a s u b s t a n t i a l

difference in receiver

sensit ivity a nd/or power

output, i t may be caused by

a f a u l t y a n t e n na , a n t e n n a

cable, or connector installa-

tion. In this case,

inspection and repair of theantenna s, cables, or cable

connectors is needed.

Successful completion of all tests to this point verifies a functional transponder system unless there are other

indications of failure (like pilot or ATC complaints). If a ny t est(s) failed or if you need added a ssura nce, continue wit h

the fa ult isolation procedures below. These procedures will help you isolat e a fa ilure between th e control(s) an d the

tra nsponder unit .

The steps tha t fol low require the use of a f l ightl ine test panel a nd bus rea der. This al lows access to the da ta busses for

detai led fault isolat ion a nd da ta ana lysis. The test panel is described in para graph 5.9. Refer to figure 5-1 for a

diagram of the setup needed for this procedure.

If you choose to continue in this series, you should feel free to pick any or all of the tests as seems necessary depending

on the suspected fai lure. The sequence of tests given is not importa nt . For example, i f the self-test test fai led to

produce an y results, you should perform th e Self-test sw itch test 9.2.1. to be sure tha t self-test is being comma nded

properly.

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TE S T P ROC E D U RE D E S I RE D RE S U LT TROU B LE S H OOTI NG

INSTRUCTIONS

7. 0 L RU fa u lt is ola t ion :

7.1

Setup

IF POWER IS ON, TURN

P OWER OFF TO THE TRAN-

SPONDER (AND TCAS

S Y S TE M I F U S E D )

Remove the control from its

location and instal l the

fl ightl ine test panel a nd

appropriate cable. Connect

the control to the t est panel

mating connector.

S e t a l l t e s t p a n e l d a t a b u s

switches to MON. Connect

the compatible data bus read-

er RX terminals to the test

p a n e l O U T t e r m in a l s . I f

your bus reader has a second

RX port, connect it to the test

panel IN terminals.

Set the ATC-601 for ATCRBS

REPLY TEST

Flightl ine Test P anel insta l lat ion:

• If you ar e connecting the test panel betw een a CTL-92/92A an d the

airpla ne w iring (with no CTL-92T; i.e., a non-TCAS inst alla tion) you will

need a CS DB reader/simulat or like the Da ta Tra c 200.

• If you ar e connecting the test panel betw een the CTL-92/92A an d the

airplane wiring which uses a CTL-92T (i.e., a TCAS installation), you will

need a CS DB reader/simulat or like the Da ta Tra c 200 to monitor/simulat e

the C SD B da ta between t he CTL-92/92A and t he CTL-92T, a nd t he CS DB

data feedback from the TDR-94D.

• I f you are connecting the test panel between the Ga bles 816 Control ,

th e C TL-92T Tra nsp onder /TCAS Con tr ol, TTC-920G Tra ns ponder /TCAS

Control, or a n RTU-870A/T Radio Tuning Un it a nd the airpla ne w iring,

you w ill need a n ARINC 429 reader/simulat or.

Note: Do not connect the bus reader TX port to the test panel OUT

terminals while the control is also connected and operating, unless you set

the corresponding test pa nel switch to EXT INPU T. The test pa nel IN

and OUT bus terminal labeling is w ith reference to the control . That is ,

OUT is dat a being t r ansmit t ed OUT from the control, while I N i s d a t a

being received by/into the control. P lacing the corresponding sw itch to the

EXT INPU T posit ion disconnects t he source so that external da ta can be

injected w ithout interference. You can alwa ys connect the bus reader RX

to ei ther the IN or OU T terminals to monitor t he source of that particular

data (test panel switch in the MON position).

8.0

Code

verifi-

cation

Normal operat ion test :

Turn power on to the system,

and set the control for 2150

or any ATCRB S code (avoid

the emergency codes). Set for

normal operation. Read theappropriate la bel as shown

---->.

Note that the bus reader shows the correct data.

C on t r ol Wor d F or m a t /L a b el B u s R ea d e r ATC -601 B u s R ea d e r

RX 1 RX 2

C TL -92/92A C S DB /1E (N ot e 1) CODE= 2150 (Note 2)

C TL -92 T AR I N C 4 29 /0 31 (N ot e 1) CODE= 2150 (Note 2)RTU -870A/T ARINC 429/031 (Note 1) CODE= 2150 (Note 2)

TTC-920G ARINC 429/031 (Note 1) CODE= 2150 (Note 2)

X = any octal character

Note 1: This is the da ta being tra nsmitt ed by th e contr ol. ( Remember, the CTL-92/92A input/output is CS DB da ta . In

all other controls the data is ARINC 429.)

CS D B (CTL-92/92A):

DataTrac 200: LBL 7-STAT-0 HEX-XMT-DATA MSEC

1E 00011111 21 50 24 10 0100

ARINC 429:

DataTrac (all): LBL SI 29-HEX-XMT-11 SM P MSEC

031 01 21 50 XX XX 00 1 0 100

J cAIR 429E: 031 01 142211 00

Note 2: This is data being returned by the t ransponder.

C S D B :

DataTrac 200: LBL 7-STAT-0 HEX-RCV-DATA MSEC

1F 00011111 21 50 24 11 0100

ARINC 429:DataTrac (all): LBL SI 29-HEX-RCV-11 SM P MSEC

031 01 21 50 XX X 11 1 0100

J cAIR 429E: 031 01 142211 11

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TE S T P ROC E D U RE D E S I RE D RE S U L T TROU B LE S H OOTI NG

INSTRUCTIONS

8.1

Ident

ATC code test:

Press IDENT on the controlhead or on the test panel .

A normally operating transponder should tra nsmit t he ID ENT code for

about 18 seconds (18 ± 1 s) an d then st op. During t ha t t ime the ATC-601shows CODE=ID2150; t h e C OD E p r ec ed e d b y "ID" . I f t h e C O D E be in g

displayed on the ATC-601 is not the same as the code you entered on the

control head recheck your setup t o be certa in of the code that you are

supplying. The code being supplied a nd displayed is entirely a softwa re

function and therefore is highly unlikely of failure.

Note: When the TDR-94/94D first begins t ra nsmitt ing the IDE NT code, the ATC-601 displays: CODE=ID2150. Af t e r

about 18 seconds (18 ± 1) the ID portion disappears but the code number remains. I f ID ENT was la st commanded by

wa y of a digi ta l word i t is necessary to transmit a new digi tal w ord with the I DENT bit reset (bit 13 = 0) before IDENT

can be commanded a gain ei ther by wa y of the digita l word or by a discrete command. I f you use the IDENT button on

the control head, the unit wil l be automat ical ly reset .

9 .0 Al t it u d e Te s t : Al t it u d e i n for m a t i on ca n b e s u pp li ed t o t h e t r a n s p on d e r i n a n u m b er of f or m a t s :

a. ARINC 429,

b. ARINC 575,

c . C S D B , o rd. ARINC 572 (Gillham code); paragraph 5.7 provides encoding and decoding information for Gillham

code.

In a TCAS instal lat ion and i f the a l t i tude source is a syst em using the G il lham code, two sources of al t i tude

data are required. One source is connected directly to t he tra nsponder while the other is connected to t he

CTL-92/92A control. In t he control the Gillha m da ta is converted t o CSD B an d supplied to the C TL-92T

where i t is converted to ARINC 429 and supplied to the tra nsponder. In the t ransponder the two sources

are compared. I f they do not a gree within 500-ft , the tra nsponder wil l set the al t i tude w ord SSM output to

NCD (No Computed Da ta).

I f the a l t i tude system is one of the first three l isted, the data is supplied directly to the t ransponder. One or

two a l t i tude sources ma y be used. In ei ther case they a re connected directly to the t ransponder.

In non-TCAS inst alla tions using a CTL-92/92A control, i .e., no CTL-92T, typically the alt itude d at a is

supplied directly t o the t ransponder. I t is possible, however, tha t the G il lham code can also be supplied to

the CTL-92/92A. In t his case i t is supplied to the t ransponder a s CS DB al t i tude da ta .

10.0 P ow er Test :

Connect the dvm to the

appropriate power terminals

on the test pa nel .

The TTC-920G uses 115 V ac , 400 Hz,

power, all others u se + 28 V dc. Allow ±

10%for 115 Vac or ± 15%for 28 V dc.

If the power is not correct,

repair airplane w iring or

power source as needed.

1 1. 0 S e lf -t e s t s w i t ch v e ri fi ca t i on :

Self-test can be init iat ed in the t ransponder w ith ei ther of two inputs; discrete or digi tal . In most

instal lat ions the discrete input t o the tra nsponder is not used. In st ep 4.0 above, self-test w as ini t iated

digita l ly. Therefore, i f step 4.0 was successful, there is very l i t t le to be gained by performing this step. I f i t

failed, however, step 11.1 below provides instructions for verification of the self-test switch by monitoring the

control interna l switching function. If th e control does not have a discrete self-test input /output, or if it does

not have a self-test switch, step 11.1 cannot be performed.

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INSTRUCTIONS

11.0

(cont’d)

Step 11.2 is using the bus simulator t o monitor the digi tal output from the control and then to generate a

digita l self-test comma nd. If step 4.0 above failed, you can perform step 11.2. If the control output is notcorrect (i .e. , the t est bi ts do not change) the probable cause of fai lure is in the control . I f t he tra nsponder

still does not respond correctly when a simulated self-test word is injected, the failure appears to be in the

transponder.

Step 11.2 also provides instructions t o monitor the feedback from the t ransponder t o the control . In t he case

of CSDB dat a, t he feedback word label is 1F. In ARINC 429 the feedback word label is the same a s the

control word label; 031. When the tr an sponder is replying to interrogat ions, the feedback SS M is set to 11.

Otherwise i t is the same as the control word.

11. 1 S elf -t es t s w it ch t es t .

Connect t he dvm t o the TEST

terminal on t he test panel [ref

to COMM or 28V (-)]. P ress

TEST on the control (or

remote sw itch i f used - not the

switch on the test panel .)

Dvm shows + 5 Vdc (± 1) when no TES T

switch (either on the control, test panel,

or elsewhere), is pressed.

Dvm shows less than + 3 V dc when any

TEST switch is pressed.

If + 5 V dc voltage is not

correct, or is correct but does

not change when the switch

is pressed, the fault appears

to be in t he control and i t

should be r emoved for

further testing on t he bench.

11. 2 C on t rol ou t pu t t es t :

With the bus reader RCV

connected t o the test panel

OUT terminals and the

corresponding switch set to

MON, you should see the test

bits change when you press

the TEST switch.

Self-test using bus simulator:

If there is no response,

connect the bus reader XMT

to the OU T terminals on the

t e s t pa n e l . S e t t h e

corresponding test panelswitch to EXT INPUT and set

the bus reader as shown --->.

CS D B (CTL-92/92A):

DataTrac 200: LBL 7-STAT-0 HEX-XMT-DATA MSEC

1E 10000101 21 50 24 10 0100

|<---test bit

ARINC 429:

Da ta Trac (al l) * LBL SI 29-HEX-XMT-11 SM P MSEC

031 01 21 50 XX X1 01 1 0100

||<--test command

J cAIR 429E: (TX) 031 01 142211 01

||<--test command

* Recognize tha t the column hea ders are sl ightly di fferent between the

Da ta Tra c 200 and t he D at aTrac 400/400H.

In t he first part of this test , the control output should be a s shown a bove.

In t he second part of this test , the t ransponder should respond to the simulated self-test command. Be sure

to set the da ta back to normal (non-test) after the self-test sequence.

As a further verfication of inter-unit communication, you can connect the bus reader RCV to the test panel

IN terminals a nd set t he corresponding switch to MON. This wil l al low you to monitor the feedback dat a

from the tra nsponder to the control . You should see the test bi ts change w hen you press the test sw itch

when the self-test command is transmitt ed. I f so, this verifies tha t t he transponder is receiving the

command properly. I t is highly unlikely, however, that the t ransponder can provide a proper feedback

without properly executing a self-test command.

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INSTRUCTIONS

Note: The remaind er of this procedure consists of explana tory informat ion that ma y be useful for troubleshooting.

The test panel test points labeling reflects the signal or volta ge that is found at that point . In most cases, that signalor voltage depends on certain instal lat ion options. Therefore, you w il l need t o consult the airplane ma nual to

determine w hich of those options a re active or inactive in your insta llation. Then use the following procedures to verify

the correctness of the instal lat ion. The procedures are separa ted a ccording to t he control present in the instal lat ion.

CTL-

92

/92A

dis-

cretes

a nd

et c

U s e a m u l t im e t er a t t h e

following test panel test

points, connect the reference

lead to C OMM (P1-s):

• DU AL select (P1-m) (-2XX

controls only):

Selected = ground

Not selected = near + 5-V dc (pull-up

resistor to + 5 V dc internal).

When this pin is grounded

the no. 2 CSDB input port is

defined as the no. 2 TDR

feedback port.

• RE M OTE s el ect (P 1 -K ) S ele ct ed = g rou nd

Not selected = near + 5-V dc (pull-upresistor t o + 5-V dc int ernal).

This pin is typically

connected to a remote switchlabeled REMOTE (or

similar). When grounded

t he C TL-92/92A:

• controls are inoperative,

• d i sp la y s h ow s R M T, a n d

• code is determined by the

remote tuning device.

• XPDR STBY No. 1 and No.

2 (P 1-W and P 1-X) (applies

only to CTL-92/92A units wit h

1/2 sw it ch)

P 1-W is at ground w hen 1/2 sw itch on

CTL is in the No. 2 position. Near + 5-V

dc wh en 1/2 swit ch is in the No.1

position. P 1-X is alwa ys opposite of P1-

W.

These pins may be used to

operate a relay which

controls power to either or

b ot h t r a n s p on d e rs . I n t h is

case, the high voltage may

be near + 28-V.

• XPDR ON/OFF, No. 1 andNo.2 (P 1-B an d P 1-C).

These two pins are identical and atground when the CTL function switch is

at OFF and open otherwise.

These pins are typicallyconnected t o the XPDR

ON/OFF; no. 1 to the no. 1

transponder, and no. 2 to

no.2, in dua l insta l lat ions.

• SW 28 V DC OUT, No. 1

and No. 2 (P1-k a nd P 1-j).

These t wo pins provide switch + 28 V dc

output through the control . The outputs

are identical a nd high in a l l CTL control

switch posit ions other t han OFF.

These outputs ma y be used

to switch power to the

transponders through an

external relay.

• D ATA B U S S H I E L D S ( P 1-

D, P1-L, P1-P, P1-T, and P1-

V)

Pin P1-D is typically connected to chassis

ground. The other are connected to an

associated da ta bus shield. All of these

pins are internally connected (within the

CTL) to 28-V dc common.

It is important that these

pins are properly isolated

from either of the tw o

associated da ta bus l ines.

• TEST (P1-E) and IDE NT

(P1-b)

Both of these pins should reflect a TTL

high (near + 5-V dc) when none of the

associated sw itches a re depressed and a

short to ground when the switch is

depressed.

In both cases, the function is

activated at t he low level. A

constant ground (even when

the sw itch is not pressed)

should be seen as a fai lure

and wil l disal low the

function.

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INSTRUCTIONS

CTL-

92Tdis-

cretes

a nd

et c

Us e a multimeter at the following test panel t est points, connect t he reference lead to COMM (P1/2-32).

Stra pping Options 1 through

6.

The a irplane manua l should reveal t hose strapping options selected. In

all cases, the selected strap should show a short-to-ground while those not

selected (open strap) should show a TTL high (near + 5-V dc).

• No. 1 (P 1-53): open = All t ra ffic displa y,

groun ded = RA/TA only d ispla y selected .

• No. 2: (P 1-49) Ran ge select

s t r a p :

• O n u n it s w i t h p us h -

buttons and CPN ending in

0XX:

• Open = 5/10/20 nmi ra nges enabled

• Ground = 6/12 nmi ranges enabled

• O n u n it s w it h pu s h -


1XX:

• Open = 40/20/10/5/3 ra ng es ena bled

• Ground = 6/12 nmi ranges enabled

• O n un i t s w i t h ou t pu s h -


0XX:

• Open = 20 nmi range selected

• G r o u n d = 1 2 n m i r a n g e s e le ct e d

• O n un i t s w i t h ou t pu s h -


1XX:

• O p en = 5 nm i r a n g e s e le ct e d

• G r o u n d = 1 2 n m i r a n g e s e le ct e d

• No. 3: (P1-52) Relative /

Absolute intruder altitude

display select:

• O p en = i n t r u de r a l t i t u de d is p la y e d a s r e l a t i ve t o ow n

• G r o u n d = i n t r u d er a l t i t u d e di s pl a y e d a s a b s ol u t e

• No. 4: (P 1-51) Not used

• No. 5 (P1-47) Serial /Parallel Transponder Control

Select

• Open = Seria l control selected (CTL-92/92A or ARINC 429)• Ground = P ara l lel control selected (CTL-90)

• No. 6: P 1-24) Not used

C on t r ol F u n ct i on s : Th e a i r pl a n e m a n u a l s h ou ld r ev ea l t h e con t r ol f u nct i on s w h ich a r e a c t iv e

in your instal lat ion. Most control functions a re intended for use w ith a

parallel ATC control head like the CTL-90.

• ATC SE L IN, No. 1

(P1-19) and No. 2 (P1-18)

P 1-18 P 1-19 ATC Act iv e or S t a nd by

open open No. 1 & No. 2 in st andby

open gnd No. 1 is a ct ive

gnd gnd No. 1 is a ct ive

gnd open No. 2 is a ct ive

• SW 28 V DC OUT No. 1

(P 1-25)

Operable only on units w ith OFF control switch posit ion. P rovides

switched + 28 V dc output when sw itch is other tha n OFF ; 1.5 A max, open

in OFF position.

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INSTRUCTIONS

CTL-

92Tdis-

cretes

a nd

et c

(cont

’d)

Control Functions (cont’d):

• Reply La mp Hi (P1-33) and

Lo (P 1-41)

Pr ovides a constant + 5 V dc high and switched low output to drive the

CTL-90 reply lamp. The lamp lights w hile the tra nsponder is replying to

interrogations.

• ALT REP (Alti tude

Reportin g) (P 1-20)

Provides a switched low output to drive the CTL-90 altitude reporting

indicator.

• GRAY CODE TUNING

(From CTL-90)

These 12 lines are t he G ra y code tuning lines from t he CTL-90. These

para l lel inputs a re tra nslated into ARINC 429 and become the label 031

tuning control output to th e tr ans ponder (ARINC TO XP DR), P 1-5/4 an d

P 1-6/7.

SERIAL DATA

INP U T/OU TP U T:

• When used with the

C TL-92/92A ATC C ont rol

In this a pplication, the inter-unit communicat ion format s a re:

To CTL-92/92A From CTL-92/92A To XPD R(s) From XP DR(s)

C S D B C S D B ARI NC 429 ARI NC 429

• When used with the

CTL-90 ATC Control


To C TL -90 F r om C TL -90 To XP D R (s ) F r om XP D R (s )

* ** ARI NC 429 ARI NC 429

* Da ta to the C TL-90 is in t he form of discretes:

• Reply lamp switching

• Alti tude reporting lamp switching

** Da ta from the CTL-90 is in the form of discretes:

• Test

• I d en t

• ATC S elect, No. 1 and No. 2

• G r a y cod e

• Wh e n u se d w i t h a n

ARINC 429 Control


To ATC C o nt r o l F r om ATC C o nt r o l To X P D R (s ) F r om X P D R (s )

ARI NC 429 ARI NC 429 ARI NC 429 ARI NC 429

If a l l tests pa ssed successfully, restore al l equipment to i ts normal ground operating configurat ion. Return

the test set to i ts normal storage location. Ca reful handling and storage of al l ramp test equipment prolongs

the service life and reduces maintenance costs.

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INSTRUCTIONS

RTU-

870-A/T,

power

a nd

light-

in g

Use a multimeter at t he fol lowing test panel test points. Connect t he

reference lead t o the a ppropriate " L" test point for power mea surements, orCOMM (P1-53) for sign al checks.

Discret e ON/OFF :

Connect meter + to

ON/OFF , met er - to 28 V

DC POWER IN L (No. 1

or No. 2)

This input must be low (ground) to

enable the RTU. A cross-side switch

may be used to select to enable the unit .

28 V dc power input:

Connect meter + to:

a . 28 V D C P O WE R

IN, NO. 1, H

b . 28 V D C P O WE R

IN, NO 2, H

+ 28 V dc ± 5 The No. 1 a nd No. 2 pow er

inputs ar e combined (or’d)

interna lly. Therefore, the

unit will operate on either.

115 v ac lighting bus:Connect meter + to 115 V

AC L I G H TI N G B U S H

a n d - t o L .

115 V a c ± 15 C heck 115 V a c light ingsupply

28 V dc dimming input:

Connect meter + to DIM,

- to COMM

28 V dc ± 15, ma x, depending on dim

control sett ing. I f dimming is manua lly

controllable, a djust the DIM control and

note that brightness range appears

correct.

Check 28 V dimming supply

RTU-

870-

A/T,

disc-

retes

D iscret es: Not e: Wit h t he except ion of ON/OF F,

those test points labeled DIS CRETES

are al l stra pping or switching options.

You will need to check the airplane

manua l to determine which options have

been selected. In most cases, a highreading is the result of a n internal pull-

up to + 12 V dc and indicat es the option

is not selected or enabled.

• X -S ID E This is a n out put t o a cross-side RTU A

low output indicates the on-side RTU is

on. A high (near + 12 V dc) indicat es the

cross-side RTU is ena bled.

Check RTU

• E D A T (E n g i n e D a t a

Select, RTU -870A only)

This is a reversionary input from an

external sw itch. This should be low

(ground) when Engine Da ta is selected

and high (near + 12 V dc) otherwise.

Engine data information can be

monitored at the ARINC 429 ENG INE

DATA No. 1 a nd No. 2, A/B test points.

Check external switch or

RTU

• MB (Marker Beacon

Sensitivity Select)

This input is normally connected to an

e xt e r n a l MK R B C N s w i t c h . I n t h e H I

(high) position this input should be high.

In the LO position this input should be

low (ground).


RTU.

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INSTRUCTIONS

RTU-

870-A/T,

disc-

retes

(cont

’d)

Discretes (cont’d):

• ATC 1 (tra nsponder no.1)

This input is normally connected to an

externa l ATC (select) swit ch. A low (near ground) input indicat es tha t

tra nsponder no. 1 is selected. A high

(+ 12 V dc pull-up) indicates, no. 2 is

selected.


RTU.

• RTU 2 A ground a t t his point designa tes t his

RTU a s th e no. 2 (co-pilot’s) RTU . An

open (near + 12 V dc) is no. 1 (pilot’s

side).

• R EM (r em ot e) I f r em ot e t un in g is a va ila ble, t his pin is

used to ena ble the remote tune function.

The external REMOTE TUNE switch

supplies 28 V dc to this pin when remote

tune is enabled. A ground indicat es

disable.


RTU.

RTU-

870-

A/T,

S t r a p -

pin

op-

tions

Strapping options:

• TST EN (Self test

enable)

A switched ground a t t his input causes

the RTU to turn on al l display segments

and indicators (DME HOLD and

REP LY). I t a lso tra nsmits the fol lowing

data word on the ARINC 429 data bus:

1. Dia gnostic label 350,

2. Dim bus word label 351, and

3. Self test word la bel 352 (RTU-870T

only). You will need a n ARINC 429 bus

reader, connected t o any one of the

ARINC 429 OUT test jacks if you want

to verify this.

Check airplane wiring or

RTU

• N TS T (N a v t es t ) A g rou nd a t t h is p oi nt d is a ble s t h e N AV

test function. "TEST" is removed from

the VOR or MLS subpages.


RTU

• M LS 1 a n d M LS 2 A g rou nd a t t h es e poin t s con fi gu res t h e

RTU to display MLS 1/2 on the top line

of the main menu. This is used only on

instal lat ions equipment with a

microwave landing system (or systems).

I f the instal led MLS is on same side as

the RTU, the MLS control words are

added to i ts ARINC output bus and to

the top l ine of the VOR subpage.


RTU

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7/22/2019 TDR 94 5230775652





INSTRUCTIONS

RTU-

870-A/T

S t r a p -

pin

op-

tions

(cont

’d)

• A EXT (ADF frequency

extension)

A ground a t this point ena bles the ADF

emergency frequ ency, 2182 kHz.


RTU

RTU-

870-

A/T

D a t a

Buses

D a ta B uses The RTU -870A/T ca n r eceive a nd

transmit ARINC 429 data on three data

buses, labeled A, B , and C. This is in

addition to the engine data input buses

described below. A dat a bus rea der can

be used to read the data . Typical labels

seen here a re (update rat e):

• 016*: ATC m ode S (5/s),

• 030: VHF C OMM freq uency (10/s),

• 031: ATC con tr ol code (5/s),

• 032: ADF t une freq uency (5/s),

• 034: VHF NAV tune fr equen cy (5/s),

• 035: DME tu ne freq uency (30/s),

• 036: MLS cha nnel echo (5/s),

• 051*: U HF frequency a nd control (5/s),

• 053*: TACAN tune freq uency an d

cont rol (5/s),

• 154: MLS ma x select G P an gle (5/s),

• 157: Ba sic dat a word 2 (5/s),

• 166*: D P U mode W and 1 (5/s),

• 203: ATC a ltit ude code (5/s),

• 254: FC C m ode word 3 (10/s),

• 270: FMC mode (5/s),• 301: VHF COMM frequency (burst),

• 302: VHF NAV frequency (burst),

• 303: DME frequency X3 (burst),

• 304: ADF freq uency (burst),

• 305: ATC code (burst ),

• 320*: Heading word,

• 376*: UH F frequency (burst), and

• 377*: TACAN cha nnel (burst ).

* = RTU-870T only

If the instal lat ion is non-

typical , consult airplane

manual to determine the

buses active and the

information that each can be

expected to reveal.

E ng in e D a ta B u ses : Ty pica lly t he la bels s een h er e a re

(update rat e):

• 340: Torq ue (percent of ma x) (10/s),

• 344: P ropeller RP M (10/s),

• 345: Inner t urbine t emperat ure (10/s),

a nd

• 346: Turbine speed (percent of max in

RP M) (10/s).

I f a l l tests passed successfully, restore al l equipment to i ts normal ground operating configuration. Return the test set

to i ts normal storage locat ion. Ca reful handling and storage of al l ram p test equipment prolongs the service l ife and

reduces maintenance costs.

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INSTRUCTIONS

TTC -

920G,power

a nd

light-

in g

Note: You can skip any tests tha t ha ve been performed earl ier as part of this test sequence.

Check the airplane ma nual t o determine the stra pping a nd sw itching functions used in your insta l lat ion.These procedures assume a l l functions are a ctive which ma y not be t rue in a l l cases. For example, you wil l

never find a n insta l lat ion tha t uses both 28 V and 5 V l ighting.

Power Test:

Connect multimeter to 115

VAC P OWER IN, NO. 1 and

NO. 2 test points.

Measure aircraft power at both sets of

test points. Allow 10%tolerance.

Check aircraft power

source(s).

Lighting and Dimming

Control Test:

Connect multimeter to

LIGH TING power t est points;

either 28V or 5 V, as

a p p li ca b l e. I f a m a n u a l

dimming control is used,

adjust i t .

Measure lighting power. Note that

dimming control works a nd intensity

appears correct . Note that al l switch

and control legends are properly

i l luminated. I t may be necessary to

block the cockpit light, especially if this

is being done outdoors.

Check l ighting a nd dimming

source. I f any legends are

not properly lit, remove TTC

for bench repair.

Monitor Lamp Power test :

Connect multimeter (+ ) to

MON LMP PWR point and (-)

to COMM (J 1-6)

Measure the monitor lamp power input.

This ma y be 28 V or 12 V. Allow 10%

tolerance.

Check power source.

TTC -

920G,

m a n -

ua l

con-

trols,

tests

Self Test Switch tests:

Connect multimeter, set for

resista nce measurement:

(+ ) to S ELF TES T,

(-) to COMM (J 1-6).

Note a n open w hen the sw itch is not

pressed and a short when the switch is

pressed.

Check TTC.

Fault Monitor Lamp Test

Switch tests:



(+ ) to MON,

(-) to COMM (J 1-6).

Note a n open w hen the sw itch is not

pressed and a short when the switch is

pressed.

Check TTC.

ANTENNA SELECT Switch

tests:



(+ ) to No. 1,

(-) to COMM (J 1-6)

Note an open when the XPDR switch is

at posit ion 2 and a short when the

switch is at position 1.

Check TTC.



(+ ) to No. 2,(-) to COMM (J 2-6)




Check TTC.

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INSTRUCTIONS

TTC-

920G,m a n -

ua l

con-

trols,

tests

(con-

t’d)

XPDR IN STBY Switch tests:


resistance measurement:

(+ ) to No. 1,

(-) to COMM (J 1-6)




Check TTC.



(+ ) to No. 2,

(-) to COMM (J 2-6)




Check TTC.

REP ALT SEL (Reporting

Altitude Select) Switch tests:



(+ ) to NO. 1,

(-) to COMM (J 1-6)

Note an open when the switch is at

posit ion 2 and a short when the sw itch is

at position 1.

Check TTC.



(+ ) to NO. 2,

(-) to COMM (J 2-6)

Note an open when the switch is at

posit ion 1 and a short when the sw itch is

at position 2.

Check TTC.

TTC-

920G,

disc-

retes

tests,

(con-

t’d)

AIR/G RD Test s:



(+ ) to NO. 1 I N,

(-) to COMM (J 1-6)

(NO. 1 OUT is identical)

Note: This input is normally connected

to an airplane strut switch. With weight

on wheels this point should show a short

to chassis ground (CHAS GND, J 1-8 or

J 2-8). I f this function ha s been defeated

for test purposes, it should show an

open.

Check airplane wiring



(+ ) to NO. 2 I N,

(-) to COMM (J 1-6)

(NO. 2 OUT is identical)

Note: This input is normally connected

to an airplane strut switch. With weight

on wheels this point should show a short

to chassis ground. I f this function has

been defeated for test purposes, it should

show an open.

Check airplane wiring

Tra nsponder Fa il I/O Tests:

TTC-

920G,

Xpdr

fai l

w a r n

tests

Connect multimeter, set for dc

voltage measurement:

(+ ) to TRANSPOND ER FAIL,

1-IN, (-) to COMM (J 1-6)

28 V dc at either of these points

indicat es tha t no detected fa i lure exists

in the applicable tra nsponder. I f this

voltage is low, you ma y need to use a n

ARINC 429 data bus reader t o determine

the diagnostic condition - see DiagnosticCode Retrieval Procedures below.

Note: Not al l diagnostic

conditions produce a failure

wa rn (flag) output. Refer to

tables 5-3 and 5-4.




2-IN, (-) to COMM (J 2-6)




OUT, (-) to COMM (J 1-6)

This is an inverted fai lure wa rn output.

I f ei ther of the tw o transponder fai l

inputs are low, this point should be high.

If both inputs are high, this point should

be low.

Check TTC.

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INSTRUCTIONS

TTC -

920G,d a t a

bu s

output

tests

Connect an ARINC 429 bus

reader t o the ARINC 429OUT NO. 1 jack. Select

transponder no. 1.

Set the bus reader to read ARINC 429

word la bels 13, 15, or 16. The words a redefined as follows:

La bel 013:

B it (s) D efinit ion

0 - 7 L abel (in oct a l): bit s 0,1 = MS B , 2-4 = secon d d igit , 5-7 = L SB ,

8, 9 S DI (source dest ina tion (or da ta ) ident ifier),

10 I nt ruder a lt it ude (AB S/RE L), AB S = 1

11, 12 Alt it u de s el ect , b it s 12/11: 00 = n or m a l, 10 = a b ov e, 01 = b elow , 11 = u nr es t rict ed

13 D ispla y: a ll t ra ffic/t hrea t t ra ffic, a ll = 0

14 - 20 (not used)

21 - 28 TC AS ra nge (see below )

29, 30 S S M (see below )

31 P a rit y bit

La bel 015:




10 - 16 Alt it ude A limit s (see a irpla ne m anua l)

17 - 23 Alt it ude B limit s (see a irpla ne m anua l)

24 - 28 (not used)


31 P a rit y bit

La bel 016:




10 Alt it ude r epor t ing, on/off, 1 = off,

11 I dent mode

12, 13 D ispla y cont rol

14 - 16 S ensit ivit y cont rol

17 - 19 D igit 4 code





31 P a rit y bit

TCAS range bit definition:

bit 21 = 0.5 nmi

bit 22 = 1.0 nmi

bit 23 = 2.0 nmi

bit 24 = 4.0 nmibit 25 = 8.0 nmi

bit 26 = 16.0 nmi

bit 27 = 32.0 nmi

bit 28 = 64.0 nmi

SS M definit ion (bits 30/29):

00 = normal operation

01 = NCD (no computed dat a)

10 = Functional t est

1 1 = F a i l u re w a r n

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Table 5- 6. Tr ansponder Syst em, D iagnost ic D at a Ret r i eval Pr ocedur es.

TEST NO and

DATA TITLE

B US RE AD E R, TX S E TU P RE S U LTS a nd C OMME NTS

6.0 Tota l

Pwr-onTimer (Hrs)

D a t a r e q u es t :

Da ta Tra c 400/400H XMT:2 77 1 1 6 0 00 03 F D 11 1 01 00

Da ta Tra c 200 XMT:

277 11 00000 11 1 0100

J cAIR 429E TX la bel 277:

600003

Six-digit data field displays count in decimal

form.Da ta Tra c 400/400H RC V:

351 11 60 00 77 97 11 1 0100

Da ta Trac 200 RCV:

351 11 0003A 11 1 0100

J cAIR 429E RX, label 351:

600077

This shows a TPOTH = 77.

7.0 Tota l

Pwr-on

Timer (Min)

Note: I f you wat ch this data i tem for a minute or less you wil l see the dat a increment.


Da ta Tra c 400/400H XMT:

277 00 E 0 00 04 F D 11 1 0100


277 00 00002 11 1 0100

J cAIR 429E TX la bel 277:600004


form.

Da ta Tra c 400/400H RC V:

351 11 60 00 11 97 11 1 0100

Da ta Trac 200 RCV:

351 11 00008 11 1 0100J cAIR 429E RX, label 351:

600011

This shows a TPOTM = 11.

8. 0 L a s t P w r -

on Cycle

F a u l t C n t r



2 77 0 1 6 0 00 05 F D 11 1 01 00


277 01 00002 11 1 0100


600005


form.


3 51 1 0 E 0 00 02 97 11 1 0 10 0

Da ta Trac 200 RCV:

351 10 00000 11 1 0100


600002

This shows a LPOCFC = 2.

9. 0 L a s t

Maintenance

D a t e



2 77 1 1 6 0 00 07 F D 11 1 01 00


277 11 00002 11 1 0100


600007

Six-digit data field displays in the form

MMDDYY.


form.


3 51 1 1 E 6 29 93 97 11 1 0 10 0

Da ta Trac 200 RCV:

351 11 314C8 11 1 0100


E62993

This s hows a LMD = 6-29-93 (J une 29, 1993)

10.0 L ast

Pwr-on

Cycle Fault

D a t a

Note: In this sequence you must wa tch the label 351 word carefully. The UU T may transmit

several words, each wit h a different dia gnostic code, at 5-second interva ls. The first tra nsmission is

the contents of the current Total P ower-on Cycle count buffer (see step 4.0; a bove). This is followed,

in 5-seconds intervals, with a transmission of each of the secondary diagnostic codes encountered

during t he most recent power-on cycle (au to self-test). This sequence is aut omatic a nd non-interruptable. I f you are using the J cAIR 429E, be prepared to wri te down t he dat a as i t appears.

The Dat aTrac units w il l reta in the dat a. The final label 351 word is l ikely to be a w ord similar t o

XXXEOF which translates into "End of Fi le" .

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Table 5- 6. Tr ansponder Syst em, D iagnost ic D at a Ret r i eval Pr ocedur es.

TEST NO a nd

DATA TITLE

B US RE AD E R, TX S E TU P RE S U LTS a nd C OMME NTS

10.0 Last

Pwr-onCycle Fault

Data (cont’d)


Da ta Tra c 400/400H XMT:2 77 0 0 6 0 0 0 1 0 F D 1 1 1 0 100


277 00 00008 11 1 0100

J cAIR 429E TX, la bel 277:

600010


form.Da ta Tra c 400/400H RCV:

3 51 0 0 E 0 0 2 0 0 9 7 1 1 1 6 800

351 10 60 00 82 97 11 1 6800

3 51 1 1 E 0 0 E 0 F 9 7 1 1 1 6 80 0

Dat aTrac 200 RCV:

351 00 00100 11 1 4999

351 10 00040 11 1 4999

351 11 00706 11 1 4999


E00200

600082

E00E0F

11.0 Continue

(prior)

Pwr-onCycles Fa ult

D a t a

Note: This step can be seen as an extension of the previous step by retr ieving diagnostic data stored

during earl ier power-on cycles. Da ta delivery and interpretat ion is t he same as step 10.0. The most

recent 16 power-on cycle sequences are stored and are read by incrementing data field bit 6 (bit 5 onthe DataTrac 200) 1 through F (Hex).



2 77 0 0 6 0 0 0 1 1 F D 1 1 1 0 100


277 01 00008 11 1 0100


600011

Sa me a s step 10.0 except one set of dat a for

each interrogation.

A convenient Record Chart is provided,

following paragraph 5.5.14.2, for manually

e n t er i ng t h e d a t a .

12.0 F ast

D a t a

Download

Note: This step is for those with a ccess to an a utomated means of requesting, capturing, and

ana lyzing the data. Such faci li t ies are a vai lable from sources other than Collins. For example,

Atlant ic Instruments supplies hardw are and softwa re, operat ing w ith the D at aTrac 400/400H, for

automated downloading of the captured data on a PC for detai led analysis and storage. For manual

(slower) data download, use step 13.0 below.



2 77 0 0 6 0 0 0 5 0 F D 1 1 1 0 100


277 00 00028 11 1 0100


600050

Refer to paragraph 5.5.13.2 for a detailed

description of the data that is transmitted

here. I f you are retr ieving dat a ma nually,

e.g., with the J cAIR 429E, use step 13.0

instead. In this step, step 12.0, the data is

transmitted to quickly to be read manually.

See note below.

13.0 Slow

D a t a

Download

Note: This step is essential ly the same a s the previous step, step 12.0. Here, however, the data

output rat e is slower; each sequence is tra nsmitted for a 5-second period, separat ed by a break

transmission 0FFFFH.



2 77 0 0 6 0 0 0 5 1 F D 1 1 1 0 100Da ta Tra c 200 XMT:

277 01 00028 11 1 0100


600051

Same as step 12.0 except the data is

transmitted at 5--second interval.

Note: The Da ta Trac 400/400H units have a Brea k Da ta Review feat ure which can be effectively used here to capture

the dat a. Consult t he applicable manual for the necessary operating procedures.

Return the test set to i ts normal storage locat ion. Ca reful handling and storage of al l ramp test equipment prolongs

the service life and reduces maintenance costs.

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5 .4 .5 A C C E P T A N C E T E S T P R O C E D U R E S

5 .4 .5 .1 I n t r o d u c t i o n

The Acceptance Test Procedures (ATP) should

be used to verify that the equipment is

op era t ion a l ; t h a t n o sh ipp in g d a m a g e h a soccurred. Verifyin g equipment operat ion before

insta llat ion helps to isolat e most problems

discovered after inst alla t ion. The procedures in

t h is p a ra g ra p h ca n a lso b e se e n a s a Re t u rn t o

Service Test (RTS). In this scenario a the

pilot complaint and the flightline test is not

conclusive. Thus t he unit is removed from a n

airplane and tested on the bench to isolate a

malfunction between the unit or the airplane

insta llat ion. I f the unit performs properly on

the bench using the RTS, it can be returned to

service. The procedures in this par agr aph

m u st n o t b e se en a s t h e e qu iva len t o f a F in a lP erforma nce Test (FP T). An FP T must be

performed after any repair operation and is

considerably more detailed tha n th is ATP . The

FP T is pr ovided in th e TDR -94/94D C omponent

M a in t e n a n ce M a n u a l .

The procedures are provided in four different

procedures. The procedure chosen depends on

e qu ipm e n t a va i la b le a n d on t h e e xt en t t o wh ich

testing is t o be performed. The first procedure

uses t he C TL-92/92A CS DB contr ol an d a n

abbreviat ed version of the test panel. This

procedure sa t isfies a minimum level of

a cce pt a n ce t e st in g b y ve rif yin g t h a t t h e U UT is

a b le t o re sp o n d t o CS D B t u n in g d a t a a n d

re port a n y in t ern a l d ia g n ost ics t h a t m a y e xist .

The r emaining procedures ut ilize t he enha nced

version of test panel and provide a greater level

of I/O test ing ca pability . These procedures

d iff er o n ly in t h e p a rt icu la r d a t a b u s a n a lyz er

being used.

5 .4 .5 .2 A T P S et u p D esc r i p t i o n

Table 5-7 is a list of the equipment required for

this ATP . The equipment includes a n IF R

ATC-601 Mode S Test S et. If a n other t est set

is used, you should be sure that it is capable of

performing the tests as defined in these

procedures and as listed in paragraph 5.4.2.

The right hand column in table 5-7 identifies

the test panel required for the use of that TE

it e m . P a n e l A re fe rs t o t h e a b b re via t e d

panel shown schema tically in f igure 5-4.

P a n e l E is t h e e n h a n ced ve rsion sh o wn in

figures 5-3 and 5-5. TE it ems keyed A and

E ca n b e u sed w it h e i t h er p a n e l . TE i t e m s

keyed A only can be used only with the

abbreviated version; items keyed E are foruse only on th e enha nced version.

5 .4 .5 .3 T e st P a n e l O p t i o n s

Table 5-7 shows tw o test panels. Option

1A is the enhanced version and will a llow

u se of a d a t a b u s re a d e r a n d va riou s

contr ols a nd control simulators in addit ion

to a number of alt itude sources. The

details of this panel are included in

p a ra g ra p h 5.8 Op t ion 1 B is t h e

abbreviat ed version mentioned in

p a ra g ra p h 5.4.5.2. I t is e xpe ct e d t h a t t h eabbreviated test panel is assembled locally.

The enhanced version can also be locally

assembled or purchased from a number of

suppliers. Those known suppliers a re

included in the vendor list ing in ta ble 5-8.

The abbreviated test panel, when used with

the automatic test capability of the ATC-

601, sat isfies t he requirements of

ADVISORY CIRCULAR NO 43.13-6A,

da ted 11/11/77; S ubject: Automa tic

Pressure Altitude Encoding Systems and

Tra nsponder Ma intenan ce and InspectionP ra ctices. The IF R ATC-601 Test S et, or

equivalent , can be used with either of the

two panel versions.

If you are using a test panel built according

to instructions in an earlier version of this

m a n u a l , it m a y n e ed t o b e u p d a t e d . Re fe r

to paragraph 5.8.1 for update information.

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T a b l e 5 -7 . E q u i p me n t R e qu i r e d f o r A T P

I t em Ma nufa ct urer Mfg P a rt Num ber P urpose P a nel

A/E

Test P anel

Option 1A

L oca lly f ab rica t ed S ee fig ur e 5-3 a n d 5-5 To in ter con nect

equipment for ATP

E

Test P anel

Option 1B

Loca lly fa brica ted S ee figure 5-4 To int erconnect

equipment for ATP

A

ATC/Mod e S Test

S et

IFR Systems, Inc.

Wichita, KS

ATC -601 F or r f t est ing A,E

ARINC Bus Reader

Option 2A

Atlantic Inst r .

Melbourne, FL

DataTrac 200, Data Trac

400, or Da ta Tra c 400H

For bus monitor a nd

simulation

E

ARINC Bus Reader

Option 2B

J cAIR

Industrial Airport , KS

429E ARINC 429

Tra nsmitt er /Receiver

For bus monitor a nd

simulation

E

Transponder

Control

Option 3A

C ollins C TL-92 or C TL-92A

Transponder Control

Tr a ns pon der con tr ol A,E

Interconnect cablefor option 3A

S a me a s t est pa nel S ee figure 5-6 F or C TL-92/92Ainterface to test panel

A,E

Transponder

Control

Option 3B

C ollins RTU -870A or RTU -870T

Radio Tuning Unit

Tra nsponder or

tr a ns ponder /TCAS

control

E

Interconnect cable

for option 3B

S ame a s t est pa nel S ee figure 5-7 F or RTU -870/870A

interface to test panel

E

Transponder

Control Option 3C

C ollins TTC -920G TC AS /

Transponder Control

Tr an spon der con tr ol E

Interconnect cable

for option 3C

S ame a s t est pa nel S ee figure 5-8 F or TTC -920G int erfa ce

to test panel

E

RF loa d Omni-S pect ra 3101-6100-00 RF t erm ina t ion of

unused antenna port

A,E

Interconnect cables

for Bus Readers

and control

simulators

Locally fa bricat ed or the

s a m e a s t e s t p a n el

S ee figure 5-9 To connect bus rea der

and control /al t i tude

simulator to test panel

E

28 V dc power

supply

a ny 5 A m inimum ca pa bilit y F or t est set up pow er A,E

S cope a ny a ny F or suppression t est A,E

T a b l e 5 - 8 . E q u i p me n t S u p p l i er s

S upplier Address P r oduct

I FR S yst ems, I nc. 10200, West York S treet

Wichita, KS 67215

ATC-601 Ramp Test Set

At la n t ic I n st r um en t s, I n c. P . O. B ox 021466

Melbourne,FL 32902

Da taTrac 400 Da ta Trac 400H and

Da taTrac 200 Dat abus Analyzers

J cAI R 400 I ndu st ria l P a r kw a y ,


AcceptanceTest Panel, Flightline Test Panel,

a nd 429E ARINC 429 Tra nsm itt er/Receiver

Av ion ics S peci a li st , I n c 3833 P r em ie r Av e.

Memphis, TN 38118

Acceptance Test Panel and Flightline Test

P a n e l

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The enha nced version of test panel, a lso

satisfies these requirements, and offers

a ddit ional ca pabilities for more complete I /O

testing as follows:

G illh a m a l t i t u d e sim u la t ion ,

Gillham alt itude switching for direct orthrough CTL testing,

Mode S address code selection,

Control type selection,

Control input port selection,

Digita l a lt itude t ype selection; ARINC 429,

ARINC 575, or CSDB,

TCAS i/o bus verifica tion,

Digital a lt itude and control port selection,

M a n u a l id e n t ,

Crossfeed sw itching,

Side 1/Side 2 sw itching,

Output port selection, a nd

U s e o f a d a t a b u s a n a l y z er .

The control interface cables, shown in figures

5-6, 5-7, and 5-8 can be used with either panel.

5 .4 .5 .4 C o n t r o l P a n e l O p t i o n s

Some type of transponder control is required

w ith either test panel. The abbreviated version

uses t he C TL-92/92A Cont rol. The enh a nced

ve rsion ca n u se a n y of t h e cu rre n t ly a va i la b le

con t ro ls or a s im u la t o r . I f you h a ve a d a t a b u s

receiver/tr a nsmit ter, like the D a ta Tra c 400,

DataTrac 400H, or DataTrac 200, by Atlantic

I n st ru m e n t s, i t ca n b e u sed t o s im u la t e a n

ARINC 429 contr ol. The Da ta Tra c 200 can

a lso sim u la t e a CS D B con t ro l. I f you p la n t o

used the TTC-920G TCAS control, be aware

that it requires 115 Vac, 400 Hz, power which

is not provided in the t est panel. The

interconnect cable, f igure 5-8, ha s a patch

provision for 115 Va c pow er input . Ta ble 5-8 is

a list ing of suppliers for the various test

e qu ipm e n t i t e m s a s we ll a s t h e t e st p a n e l .

5.4 .5.5 G i l l h a m C od e S i m u l a t o r

The TD R-94/94D Mode S Tra ns ponder

Acceptance Test Panel used here includes a

built-in Gillham code (ARINC 572)

simulat or. The Gillham Code Altitude

Tests in this section include a list ing of anumber of a lt itudes a nd corresponding

G il lh a m cod e swit ch se t t in gs. S e t t h e

corresponding sw itch down (SE L) for a n

active code selection, a nd set the sw itch up

(OFF) for an inactive selection.

5 .4 .5 .6 A T C S et u p D esc r i p t i o n

I f yo u a re u sin g t h is se t u p f or t h e f irst

t ime, check th at 28 volts a ppear s only on

t h e corre ct p in s. Use t h e sch e m a t ic

diagra m shown in figure 5-4 or 5-5 as

applicable to the panel you are using.

WARNING: D o n ot u s e a s t a n d a r d

multimeter probe when making continuity

t e st s t o t h e Pro L in e I I UU T m a t in g

connector. These types of probes ha ve been

known to cause the contact forks to break

result ing in unreliable operat ion. I t is far

better to fabricate one or two test probes

using a short length of flexible 22 or 26

AWG wire , t e rm in a t e d a t on e e n d wit h a

mating blade contact like those used in the

U U T connector. Terminat e the other end

wit h a sm a ll a l l ig a t o r cl ip o r t ip ja ck t o

connect to th e multimeter lead.

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Interconnect the equipment as shown in figure

5 -2 . Th e d a t a b u s re a d e rs a re n o t u se d wit h

t h e a b b revia t e d t est p a n e l. B e su re t h a t t h e r f

connections to th e a ntenna connectors ar e fully

inserted an d t ha t t he i/o mat ing connectors a re

firmly sea ted before a pplying power.

Te rm in a t e t h e u n u se d a n t e n n a p ort wit h aTNC 50Ω r f t e rm in a t ion a s id en t i f ie d in t a b le

5-1 a nd ta ble 5-7.

Turn on t he ATC-601 Test Set , or equiva lent,

a n d e xe rcise t h e sel f t e st ro u t in e. I f t h e t e st

set is operational continue with the test .

Ot h e rwise, re p a ir t h e t e st se t .

I f yo u a r e u sin g t h e t e st p a n e l sh o wn o n f ig u re

5-5, set the sw itches a s follow s: The

a b b re via t e d p a n e l h a s on ly t h e U UT POWE R

a n d E X T S TB Y swit ch es. I f yo u a re u sin g a

test panel built according to instructions in an

e a rl ier ve rsion o f t h is m a n u a l , i t m a y re qu iremodificat ion. Refer to para gra ph 5.8.1.

S WI TC H P OS I TI ON

U U T P OWE R: OF F

E XT S TB Y: S TB Y

XF E E D : OU T

S E L F TE S T: E NTC AS /N O TC AS : N O TC AS

S D I : S I D E 1

AI R : AI R

ANT: D L

AU TO AL T: OF F

RE P AL T S E L : P A

D ATA L IN K S E L: A/B

B U R S T TU NE : OF F

D ATAL I NK : NO AD L P

CON TROL DATA SE LE CT:

ARINC PORT: PA

OUTP UT P ORT S E L E C T:

ARINC 429 PORTA

AR I N C 572 AL T I N : TO TD R

AL T TY P E S E L E C T: AR I N C 429

S OU RC E S EL E CT: S EL

AR I N C 572 AL T I N : TO TD R

Gillham Code switches:

All OFF except C2 and B1 to SEL (2,

500 ft )

MAX AI RS P E E D: All OF F

M O D E S A D D R E S S S E L E C T: Al l O F F

except: P 1-35, 36, 37, 39, 41, 42, 46, 51, 56.

(Hex code: 3AC421, Octal: 16542041)

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Acceptance Test, Test Setup Diagram

Figur e 5- 2

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5 .4 .5 .7 M i n i m u m A c c ep t a n c e T est , U s i n g a

C S D B C o n t r o l a n d t h e A b b r ev i a t e d T est

P a n e l

The procedures in t able 5-9 use a CS DB contr ol

like t he CTL-92/92A to provide tr a ns ponder

control and the abbreviated version of test

panel for equipment interconnection.

Su ccessful completion of these procedures

verifies th e performa nce of t he U U T by

providing reasonable assurance of the

f u n ct ion a l in t e gri t y of t h e t ra n sm it t e r ,

receiver, the CSDB control input, and

in t e rn a l d a t a h a n d lin g .

T a b l e 5 - 9 . Mi n i mu m A c ce p t a n c e Te s t Pr o ce d u r e s , Us i n g a CS DB Co n t r o l

a n d t h e A b b r e v i a t e d T e s t P a n e l

S TE P TI TLE P ROC E D U RE D E S I RE D RE S U LTS

1. 0 S e t up I f n ot a l r ea d y d on e, con n ect e q ui pm en t a s s h ow n i n f ig u re 5-2.

• Connect t he C TL-92/92A using t he ca ble shown in figur e 5-6.

• Connect the ATC-601 (or equivalent) to the U UT bott om ant enna connector.

• Connect and rf t ermination to the top antenna connector.

• Connect power to the power jacks - observe proper polarit y.

• Be sure POWER switch is OFF a nd EXT STBY switch is at S TBY.

• The bus reader is not needed in this setup.

2.0 I nit ia l

Test

Power application

Set test panel POWER switch to ON

Set CTL to any valid ATC code; e.g. 1234

S et C TL sw it ch t o S TB Y ATC -601 REPLY lamp is off; no replies.

S et C TL sw it ch t o OP R No cha nge.

S et E XT S TB Y sw it ch t o OP R ATC -601 REPLY la mp l ights; UU T is replying

to t he interrogations.

3.0 U U T S elf

Test

Press the TEST button; ei ther on the test

panel or on the CTL.

Notice any diagnostic code that ma y be displayed on the C TL. I f diAG and a diagnostic code is

displayed, refer t o table 5-3 and 5-4 for a n interpret at ion. If a code from 10 to 70 (inclusive),

C(), or D0 is displayed, the U U T should be rejected. Any other code may not be indicative of

an equipment fai lure but ra ther the result of an inactive data bus. As a general rule in testing

a UUT with CPN ending in -002, those diagnostic conditions accompanied by an extinguished

FLT MON (fault monitor) lamp on test panel, should be seen as cause for unit rejection.

Others may be the result of the a n incomplete equipment complement a nd ma y not be

indicat ive of a n equipment fa i lure.

4.0 Tes t S et ,

Auto Test

Follow the instructions in the Test Set

operation manual for the Auto Test mode and

execute the test .

Ensure that al l tests pass. See note below.

Set the test panel POWER switch to Off

Switch t he RF connector on the UU T from topto bottom (or bottom to top)

R epea t t he Au to Tes t s eq uen ce. E n su re t ha t a ll t es ts pa s s. See n ot e b elow .

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T a b l e 5 - 9 . Mi n i m u m A c ce p t a n c e Te s t Pr o ce d u r e s , Us i n g a CS DB Co n t r o l

a n d t h e A b b r e v i a t ed T es t P a n e l ( Con t ) .

S TE P TI TLE P ROC E D U RE D E S I RE D RE S U L TS

This completes the minimum test requirement.

--------------------------------------------------------------------------------

Note. The AUTO TES T sequence will indicat e FAILED even w hen certa in tests result in a NO REPLY condition. The NO

REPLY conditions a re the result of no ADLP (Airborne Da ta Link Processor) data being supplied in this setup. This

same condition is likely to occur when using the ATC-601 as a ramp tester when testing an installation not equipped

w i t h a n A D L P . I t i s a l s o po ss i bl e t h a t t h e AUTO TEST fai ls because t he UU T sensit ivi ty is more than -77.0 dBm. I f you

find this to be the case, recognize that Coll ins prefers tha t a sensit ivi ty (MTL) greater tha n 77.0 be seen as acceptable.

Obviously, an MTL a pproaching -80 dBm t ends to indicat e a problem w ith t est equipment cal ibration. To verify tha t

the test can be seen as successful, proceed as follows:

• When the test sequence is completed a nd the ATC-601 stops (as indica ted by no INTERR lamp off, you will see a

screen as follows:

** AUTO TEST - FAILED ** MODES TESTED - A,C,S FREQ: 1089.92 MHz MODES PASSED - A,C.S ERP: 55 dBm MODES FAILED - -> MTL: -77 dBm DIVERSITY ISOLATION: >40 dB

Press RUN to start

Verify the test results as follows:

U s e t h e SELECT up arrow or down arrow key to scroll through the following l ist of tests performed. I f you use the up

arrow, you w il l see the sequence as l isted from top to bottom. I f you use the down ar row, you wil l see the sequence is

reverse order.

1. ** MTL DIFFERENCE TEST - PASSED **

2. ** DIVERSITY TEST - PASSED **

3. ** FREQUENCY TEST - PASSED **

4. ** SQUITTER TEST - PASSED **

5. * * M OD E S UF 21 TE ST - N O R EP LY * *



8. * * M OD E S UF 11 TE ST - PA SS ED **

9. * * M OD E S UF 5 T ES T - PA SSE D * *10. * * M OD E S UF 4 T ES T - PA SSE D * *

11. * * M OD E S UF 0 T ES T - PA SSE D * *

12. ** SPR ON/OFF TEST - PASSED **

13. ** INVALID ADDRESS TEST - PASSED **

14. ** MODE S ALL-CALL TEST - PASSED **

15. ** ATC ONLY ALL-CALL TEST - PASSED **

16. ** SLS LEVEL TEST - PASSED **

17. ** ATCRBS REPLY TEST - PASSED **

18. ** REPLY JITTER TEST - PASSED **

19. ** REPLY DELAY TEST - PASSED **

At this point , a nother press of the arrow key wil l redisplay the first i tem; ei ther 1. or 19., depending w hich a rrow w as

used.

In each case, the screen also shows the particular t est parameter a nd the test result . I f the test has fa i led, this value

can be compared to the required value to ga in more definit ive insight into the reason for the fai lure.

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5 .4 .5 .8 M i n i m u m A cc ep t a n c e T e st , U s i n g

a A R I N C 4 2 9 C o n t r o l a n d t h e A b b r ev i a t e d

T e s t P a n e l

The procedures in table 5-10 use an ARINC

429 contr ol li ke th e RTU -870A/T to provide

transponder control and the abbreviatedversion of test pa nel for equipment

interconnection. Su ccessful

completion of these procedures verifies the

performance of the U U T by providing

reasonable assurance of the functional

integrity of the transmitter, receiver, the

ARINC 429 control input, and internal data

h a n d lin g .

T a b l e 5 - 1 0 . Mi n i mu m A c c ep t a n c e T es t P r oc ed u r e s , Us i n g a n A RI NC 4 2 9 Co n t r o l

a n d t h e A b b r e v i a t e d T e s t P a n e l


1. 0 S e t up I f n ot a l r ea d y d on e, con n ect e q ui pm en t a s s h ow n i n f ig u re 5-2.

• Connect the ARINC 429 contr ol using the cable shown in figure 5-7 or 5-8.

• Connect the ATC-601 (or equivalent) to the U UT bott om ant enna connector.

• Connect and rf t ermination to the top antenna connector.

• Connect power to the power jacks - observe proper polarit y.

• Be sure POWER switch is OFF a nd EXT STBY switch is at S TBY.• The bus reader is not needed in this setup.

2.0 I nit ia l

Test

Power application

Set test panel POWER switch to ON

Set CTL to any valid ATC code; e.g. 7777

S et C TL sw it ch t o S TB Y ATC -601 REPLY lamp is off; no replies.

S et C TL sw it ch t o OP R No cha nge.

S et E XT S TB Y sw it ch t o OP R ATC -601 REPLY la mp l ights; UU T is replying

to t he interrogations.

3.0 U U T S elf

Test

Press the TEST button; ei ther on the test

panel or on the control.

Notice any dia gnostic code tha t ma y be displayed. I f a diagnostic code is displayed, refer to

ta ble 5-3 and 5-4 for an interpreta tion. If a code from 10 to 70 (inclusive), C(), or D 0 is

displayed, the UU T should be r ejected. Any other code may not be indicative of a n equipment

fai lure but ra ther the result of an inactive data bus. As a general rule in testing a U UT with

CPN ending in -002, those diagnostic conditions accompanied by an extinguished FLT MON

(fault monitor) lamp on test panel , should be seen as cause for unit rejection. Others may be

the result of the an incomplete equipment complement and may not be indicat ive of a n

equipment failure.

4.0 Tes t S et ,

Auto Test

Follow the instructions in the Test Set

operation manual for the Auto Test mode and

execute the test .


Set the test panel POWER switch to Off

Switch t he RF connector on the UU T from top

to bottom (or bottom to top)

R epea t t he Au to Tes t s eq uen ce. E n su re t ha t a ll t es ts pa s s. See n ot e b elow .

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T a b l e 5 - 1 0 . Mi n i mu m A c c e p t a n c e T es t P r oc ed u r e s , Us i n g a n A RI NC 4 2 9 Co n t r o l

a n d t h e A b b r e v i a t ed T es t P a n e l ( Con t ) .


This completes the minimum test requirement.

--------------------------------------------------------------------------------

Note. The AUTO TES T sequence will indicat e FAILED even w hen certa in tests result in a NO REPLY condition. The NO

REPLY conditions a re the result of no ADLP (Airborne Da ta Link Processor) data being supplied in this setup. This

same condition is likely to occur when using the ATC-601 as a ramp tester when testing an installation not equipped

w i t h a n A D L P . I t i s a l s o po ss i bl e t h a t t h e AUTO TEST fai ls because t he UU T sensit ivi ty is more than -77.0 dBm. I f you

find this to be the case, recognize that Coll ins prefers tha t a sensit ivi ty (MTL) greater tha n 77.0 be seen as acceptable.

Obviously, an MTL a pproaching -80 dBm t ends to indicat e a problem w ith t est equipment cal ibration. To verify tha t

the test can be seen as successful, proceed as follows:

• When the test sequence is completed a nd the ATC-601 stops (as indica ted by no INTERR lamp off, you will see a

screen as follows:

** AUTO TEST - FAILED ** MODES TESTED - A,C,S FREQ: 1089.92 MHz MODES PASSED - A,C.S ERP: 55 dBm MODES FAILED - -> MTL: -77 dBm DIVERSITY ISOLATION: >40 dB

Press RUN to start


U s e t h e SELECT up arrow or down arrow key to scroll through the following l ist of tests performed. I f you use the up

arrow, you w il l see the sequence as l isted from top to bottom. I f you use the down ar row, you wil l see the sequence is

reverse order.

1. ** MTL DIFFERENCE TEST - PASSED **

2. ** DIVERSITY TEST - PASSED **

3. ** FREQUENCY TEST - PASSED **

4. ** SQUITTER TEST - PASSED **




8. * * M OD E S UF 11 TE ST - PA SS ED **

9. * * M OD E S UF 5 T ES T - PA SSE D * *10. * * M OD E S UF 4 T ES T - PA SSE D * *

11. * * M OD E S UF 0 T ES T - PA SSE D * *

12. ** SPR ON/OFF TEST - PASSED **

13. ** INVALID ADDRESS TEST - PASSED **

14. ** MODE S ALL-CALL TEST - PASSED **

15. ** ATC ONLY ALL-CALL TEST - PASSED **

16. ** SLS LEVEL TEST - PASSED **

17. ** ATCRBS REPLY TEST - PASSED **

18. ** REPLY JITTER TEST - PASSED **

19. ** REPLY DELAY TEST - PASSED **

At this point , a nother press of the arrow key wil l redisplay the first i tem; ei ther 1. or 19., depending w hich a rrow w as

used.

In each case, the screen also shows the particular t est parameter a nd the test result . I f the test has fa i led, this value

can be compared to the required value to ga in more definit ive insight into the reason for the fai lure.

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5 .4 .5 .9 P r o ced u r es u s i n g t h e D a t a T r a c 4 00 o r D a t a T r a c 4 00 H D a t a b u s A n a l y zer

Table 5-11 Acceptance Test Procedures,

Using the DATATRAC 400 or DATATRAC 400H Databus Analyzer

STEP TITLE PROCEDURE DESIRED RESULTS

1.0 Setup Note: If you are using a Test Panel built according to instruction provided in a previous edition of this

manual, it may be necessary to upgrade the panel. Refer to paragraph the Special Tools and Fixture

Section.

If not already done, connect equipment as shown in figure 5-2.

• Connect DATATRAC as follows using cables shown in figure 5-9.

• XMT 1 to test panel DIGITAL CONTROL port,

• Parallel connect XMT 1 to test panel PRIMARY DIGITAL ALTITUDE PORT,

• RCV 1 to test panel DATA BUS READER port.

• Connect the ATC-601 to the UUT bottom antenna connector.

• Connect an rf termination to the TOP antenna port.

• Connect power to test panel power jacks - observe proper polarity.

• Preset the switches as shown in paragraph 5.4.4 above. Be sure POWER switch is OFF and EXT

STBY switch is at STBY.

On test panel, set the MODE S ADDRESS switches to any combination except all OFF or all to SEL.

If all switches are set OFF or all set SEL, a diagnostic code FF will result.

1.1 Setup Turn the DATATRAC ( ) on and set the

RCV 1, and XMT 1 screen ----->

(See notes 1 and 2 that follow test step

1.2)

-----------------RCV 1--(ALL)---12.5 KHzLbl SDI 32-Hex Data-1 SSM Par msec

... no data present ...

-ON-------------XMT 1 ----------12.5 KHzLbl SDI 32-Hex Data-1 SSM Par msec031 01 15 66 C1 98 00 1 0 100203 01 64 00 01 C1 11 1 0 100

Turn on

TDR-94/94D

On test panel:

• Set POWER switch to ON

Monitor current. If OK:

• Set EXT STBY switch to OPR

Monitor current.

If the unit has been in service and there is a possibility of

an over-current condition, monitor the power supply

current output. The setup should draw no more than 1.5

A. Typically it draws about 0.9 to 1.1 A when the UUT is

transmitting.

Setup

(power-up)

Turn the ATC-601 on and press SELECT

for the screen -------------->

See Note in next cell below.

** ATCRBS REPLY TEST - NOT RUN **

(lines 2-4 are irrelevant)

CODE= ALT= [ ]Press RUN to start

1.2 ARINC 429

tuning test

On the ATC-601, press RUN

ATC-601 screen --------->

Note: When power is applied and proper

control data is supplied, the TDR-94/94D

should turn on the XFEED OUT lamp

almost immediately. The FAULT MON

lamp may be off for a few seconds and

then turn on. A lighted FAULT MON lamp

should generally be seen as a no-fault

indication. See table 5-3.

UUT responds to interrogations as indicated by a lighted

XFEED OUT lamp on the test panel and a lighted REPLY

lamp on the ATC-601.

** ATCRBS REPLY TEST **

(lines 2-4 are irrelevant)C OD E= 52 63 A LT= 32 ,8 00 F T [ 134 4]

***** TEST RUNNING *****

To change the CODE, see note 1 below.

To change the ALT, see note 2 below.

The DATATRAC ( ) RCV 1 display

becomes --------->

-----------------RCV 1--(ALL)---12.5 KHzLbl SDI 32-Hex Data-1 SSM Par msec203 01 64 00 01 C1 11 1 0 200031 01 F5 66 81 98 00 1 0 200350 01 60 00 01 17 11 1 0 200


Note: Any other labels displayed are irrelevant to this

test. Use the down arrow key to scroll the display. See

Note 3 below.

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Using the DATATRAC 400 or DATATRAC 400H Databus Analyzer (Cont) .


2.0 Test set, Auto

Test

On ATC-601:

• Press RUN/STOP to stop

• Press AUTO TEST

• Press RUN to start

Note: This test requires a few

seconds to run. It will stop

automatically.

Ensure that all tests pass. See note below.

On test panel:

• Set EXT STBY switch to STBY

• Set POWER switch OFF

On UUT:

• Move the test set rf cable to the UUT top antenna connector and the rf termination to the

bottom.

On test panel:

• Set POWER switch ON


On ATC-601:

• Repeat the AUTO TEST


Note. The AUTO TEST sequence will indicate FAILED even when certain tests result in a NO REPLY condition. The NO REPLY

conditions are the result of no ADLP (Airborne Data Link Processor) data in this setup. This same condition is likely to occur

when using the ATC-601 as a ramp tester when testing an installation not equipped with an ADLP. To verify that the test can

be seen as successful, proceed as follows:

• When the test sequence is completed and the ATC-601 stops, as indicated by INTERR and REPLY lamps off, you will likely

see a screen as follows:

** AUTO TEST - FAILED ** MODES TESTED - A,C,S FREQ: 1089.92 Mhz MODES PASSED - A,C,S ERP: 55 Dbm MODES FAILED - -> MTL: -77 Dbm DIVERSITY ISOLATION: >40 dB

Press RUN to start

(The FREQ, ERP, a n d MTL values can vary from U UT to UUT and to a lesser degree on UU T temperature.)


On the ATC-601, use the SELECT 6th up arrow or down arrow key to scroll through the following list of tests performed; the

numbers are for reference purposes only and do not appear on the test set screen. If you use the down arrow, you will see

the list in the order shown; from test 1 through test 19. If you use the up arrow key, you will see the list in reverse order,

starting at test 19. You will likely notice that all tests passed except tests 13, 14, and 15 which had a NO REPLY.

NO. TEST NAME AND RESULT TEST SPECIFICATION / DESCRIPTION

1.0 ** REPLY DELAY TEST - PASSED ** MODE S: 128.00 (±0.25) µsITM A: 128.00 (±0.25) µs

(All others): 3.00 (±0.50) µs

2.0 ** REPLY JITTER TEST - PASSED ** MODE S: =< 0.05 µsITM: =< 0.06 µs

(All others): =< 0.1 µs

3.0 ** ATCRBS REPLY TEST - PASSED ** F1 TO F2 SPACING: 20.3 (±0.1) µs

All PULSE WIDTH: 0.45 (±0.1) µs

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Using the DATATRAC 400 or DATATRAC 400H Databus Analyzer (Cont).



4.0 ** SLS LEVEL TEST - PASSED ** UUT is interrogated with F2 (SLS) pulse at 9 dB below F1.UUT should reply to this interrogation. Then UUT is

interrogated with F2 equal to F1. UUT should not reply.

PASSED indicates correct response to both tests.

5.0 ** ATC ONLY ALL-CALL TEST - PASSED ** The TDR-94/94D should not reply to this mode a and mode

c only interrogation. PASSED indicates a correct (NO)

response.

6.0 ** MODE S ALL-CALL TEST - PASSED ** The TDR-94/94D should reply to this interrogation. PASSED

indicates a correct response. UUT address previously

determined in mode s interrogation, is sent to UUT in UF4

(Uplink Format 4) and verified in DF4 (Downlink Format 4)

reply.

7.0 ** INVALID ADDRESS TEST - PASSED ** UUT is interrogated with two addresses, both of which are

different from the correct address. PASSED indicates UUTdid not reply to interrogation.

8.0 ** SPR ON/OFF TEST - PASSED ** UUT is interrogated first with SPR ON and verifies a proper

reply, then with SPR OFF and verifies no reply. PASSED

indicates UUT responded correctly.

9.0 * * M OD E S U F0 T ES T - P AS SE D * * UUT is interrogated with mode S UF0, verifying correct

altitude as compared to previous mode c reply, correct

address as compared to DF11 address, and correct format.

PASSED indicates correct UUT response.

10.0 * * M OD E S UF 4 T ES T - PA SSE D * * UUT is interrogated with UF4, verifying correct altitude as

compared to previous mode c reply, correct address as

compared to DF11 reply, and correct format. PASSED

indicates correct UUT response.

11.0 * * M OD E S UF 5 T ES T - PA SSE D * * UUT is interrogated with UF5, verifying the correct ID code

as compared to previous mode a reply, correct address as



12.0 * * M OD E S UF 11 TE ST - P ASS ED ** UUT is interrogated with UF11, verifying correct address as

compared to previous response, and correct format.


13.0 * * M OD E S UF 16 TE ST - N O R EP LY * * (See test 15.)

14.0 * * M OD E S UF 20 TE ST - N O R EP LY * * (See test 15.)

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STEP TITLE PROCEDURE DESIRED RESULTS OR SETUP SCREEN


15.0 * * M OD E S UF 21 TE ST - N O R EP LY ** UUT is interrogated with UF16, UF20, and UF21.These formats are all related to the airborne data link

function. This function has not been implemented.

The TDR-94/94D will not reply to these interrogation

formats. NOT REPLY should not be seen as a failure.

16.0 ** SQUITTER TEST - PASSED ** When set for dual antenna operation, the TDR-94D

transmits a squitter pulse once each second, alternating

between top and bottom antenna ports. The ATC-601

verifies that one squitter pulse is received every 1.6 to

2.4 seconds. The test panel ANT SGL/DL switch must

be in the DL position. When set for single antenna

operation, or when testing a TDR-94, only the bottom

antenna port is used. In this case the ATC-601 verifies

that one squitter pulse is received every 0.6 to 1.4

seconds. When you change the ANT SGL/DL switch,you must cycle power to the UUT in order for it to take

effect. PASSED indicates a correct UUT response.

17.0 ** FREQUENCY TEST - PASSED ** Freq: 1090 (±1) MHz

18.0 ** DIVERSITY TEST - PASSED ** ATC-601 monitors squitter pulses on active antenna

port (as in test 16) and then monitors for intervening

squitter pulses that are not greater than 20 dB below

the active squitter. This test will always fail when the

UUT is a TDR-94 (non diversity) because squitter is

transmitter every second on the same antenna port. If

you are testing a TDR-94D and the DL ANT/SGL ANT

switch is set to SGL ANT, the test will also fail because

this causes the unit to operate like a TDR-94. PASSED

indicates a correct response from a TDR-94D.

19.0 ** MTL DIFFERENCE TEST - PASSED ** ATC-601 verifies that the MTL difference between mode

a and mode c responses is < 1.0 dB. At this point,

another press of the arrow key will display the first item;

either 1.0 or 18.0, depending on which arrow was used.

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3.0 Power

output and

RcvrSensi-tivity

Test

On test panel select:



On ATC-601:

• Select POWER TEST

• Press RUN to indicate TEST RUNNING ----

--->

** POWER TEST - Top Antenna ** ANTENNA UNITS ERP MTL STATUS

NO REPLY***** TEST RUNNING *****

Note: If necessary, press SELECT (or SLEW ) to select Top Antenna. Be sure that the ATC-601 rf

cable is connected to the top antenna port and the rf termination is connected to the bottom port.

On DATATRAC ( ): set screen ------> -----------------RCV 1--(ALL)---12.5 KHzLbl SDI 32-Hex Data-1 SSM Par msec


-ON-------------XMT 1 ----------12.5 KHzLbl SDI 32-Hex Data-1 SSM Par msec031 01 15 66 C1 98 00 1 0100203 01 64 00 01 C1 11 1 0100

On test panel:



After a few seconds, the ATC-601

shows ---->

On ATC-601:

Press RUN/STOP to stop the test.


Top dBm 55.7 -76.0 PASSED


If a failure is detected, a small arrow will be shown to

the left of the offending parameter(s). Make a note of

the test results, if a record is needed, and label it as

applicable to the UUT bottom antenna port. The data

displayed here will be overwritten on the next test.

If the UUT is a TDR-94, skip this step.

On test panel:



• On TDR-94D mount:Swap the rf cable connection and

termination on the UUT antenna ports.

(Rf cable to bottom port and termination

to top antenna port.)

On test panel:



On ATC-601:

• Press RUN to indicate TEST RUNNING

Wait a few seconds then press RUN/STOP

to stop the test.

You should see a similar display on the ATC-601

except this data is applicable to the top antenna port.

The data can be slightly different. See below for test

tolerances and an explanation of a possible failure

indication due to high sensitivity.

Note: You may also select bottom antenna screen on

the ATC-601.

Note: You may see a marginal test failure if the UUT is

relatively cold. In this case allow the unit to warm up a

few minutes and then repeat the test.

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3.0

(con-

t’d)

Power

output and

RcvrSensi-tivity

Test

(cont’d)

The test tolerances are:

ERP: > 48.5 dBm and < 57.0 dBm

MTL: -73.0 (±4.0) dBm

The ATC-601 will indicate that the UUT has FAILED if the MTL is more than -77.0 dBm or less than -

71 dBm. Collins prefers, however, that a FAILURE should be reported only if the MTL is less than -

71 dBm. Therefore, if you have a unit displaying an MTL of -77.1 or more, you should see that value

as acceptable. Obviously, an MTL indication approaching -80 dBm or more may be cause for

suspecting a problem with test set calibration.

You may also see a failure because the ERP, Effective Radiated Power or Peak Pulse Power , is

more than 57 dBm. Power measurements taken with a ramp tester can be confusing. The various

test equipment manufacturers use different dimensions for displaying the test results, the test

specifications are not always clear on how the test is to be performed to produce the specified result,

and the test method; direct or radiation, yields different results. As in the case of MTL, an ERP

slightly greater than 57 dBm ( e.g., 59 dBm max), using the direction connection method, should not

be seen as cause for unit rejection.

DO-181 specifies the transponder power output at the antenna. Testing a unit on the bench by direct

connection to the antenna port yields a power reading at the transmitter output. The difference is,

of course, antenna cable and connector losses.

DO-181 specifies transponder power output in watts and dBW. The IFR ATC-601 displays power in

dBm (ERP). The TIC-48/-49 displays power in watts. The following chart may be useful for proper

test evaluation:

Watts dBW dBm TDR-94/94D Spec

50 16.99 46.99

70 18.45 48.45 (Min for airplanes limited to 15 000 ft and 175 kts.)

100 20.00 50.00

125 20.97 50.97 Minimum at antenna (ramp testing)

150 21.76 51.76

200 23.01 53.01

250 23.98 53.98 Minimum direct (on bench)

300 24.77 54.77

350 25.44 55.44

400 26.02 56.02

450 26.53 56.53

500 26.99 56.99 Maximum at antenna

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4.0 Gillham

Altitude

Test

On ATC-601: select

ATCRBS REPLY TEST ----------->



CODE= ALT= [ ]

Press RUN to start


• ALT TYPE SELECT: ARINC 572

• ARINC 572 ALT IN: TO TDR

On DATATRAC ( ):

• Set XMT 1 label 203 word to OFF

• Set RCV 1 and XMT 1 screen

------>

-----------------RCV 1--(ALL)---12.5 KHzLbl SDI 32-Hex Data-1 SSM Par msec


-ON-------------XMT 1 ----------12.5 KHzLbl SDI 32-Hex Data-1 SSM Par msec031 01 15 66 C1 98 00 1 0100

On test panel:

• Set all ARINC 572 switches to OFF:

Then set A4, C2, C4, and B4 to SEL.• Set POWER to ON


The XFEED OUT lamp turns on. The ATC-601 REPLY

lamp indicates that UUT is responding to interrogations.

DATATRAC ( ) RCV 1 screen shows: -----

--------------->

----------------RCV 1--(ALL)---12.5 KHzLbl SDI 32-Hex Data-1 SSM Par msec203 01 E0 B8 61 C1 11 1 0200031 01 F5 66 81 98 11 1 0200

(ignore any other displayed labels)

On ATC-601:

• P r e s s R U N . S c r ee n s h ow s :

-------------------->


(lines 2-4 are irrelevant)CODE=5263 ALT=5900 FT [4460]


(The CODE 5263 depends on your selection in the 031

XMT 1 word. See note 1 under step 1.2 above)

At this step you are asked to toggle each of the ARINC 572 switches and verify the altitude display. You should also watchthe RCV 1 data word on the DATATRAC ( ) display. By cycling each switch between OFF and SEL you should see the ATC-

601 display and the DATATRAC ( ) 203 data word change. If the displays do not change for a particular switch, this would

indicate either an open or a shorted code line. If the wrong altitude is shown, this would suggest that the code line is affecting

another line; i.e., causing two or more inputs to change simultaneously. In either case the UUT, the test panel, or the

interconnecting cable needs repair.

Set each switch as shown in the listing below to the (position) shown, and back, and verify the altitude display at both

positions. The altitude display should always revert to the initial display when the switch is returned to its original position.

There is no serious need to verify the correctness of the RCV word as long as the ATC-601 display is correct.

SWITCH DISPLAYED ALTITUDE SWITCH DISPLAYED ALTITUDE

Initial 5,900 FT [4460] C4 (OFF) 6,000 FT [4420]

A1 (SEL) 23,600 F T [5460] B1 (SEL) 3,600 FT [4560]

A2 (SEL) 7,600 FT [6460] B2 (SEL) 5,600 FT [4660]

A4 (OFF ) -400 FT (0460] B4 (OFF) 6,600 FT [4060]

C1 (SEL) none (blank; this is invalid) D2 (SEL) 119,600 FT [4462]

C2 (OFF) 5,800 FT [4440] D4 (SEL) 55,600 FT [4464]

For addtional information on Gillham code structure, refer to paragraph 5.7 in this section.

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5.0 CSDB

tuning

test

This test cannot be performed using a DATATRAC 400/400H because these instruments are not

capable of transmitting or receiver CSDB data. However, as an acceptable alternative, you can use

a CTL-92/92A, connected to the test panel using the cable shown in figure 907.• Turn power off and connect CTL-92/92A to test panel. Be sure CTL-92/92A mode knob is set to

OFF.

• Turn power on and set the CTL-92/92A mode knob to ALT.

On the CTL:

• Set the CTL-92/92A to 5263 or any

desired ident code.

On test panel:

• Set CONTROL DATA SELECT to

CSDB

• Set OUTPUT PORT SELECT to CSDB

PORT 1

• Set ALT TYPE SELECT to CSDB

• Set ARINC 572 ALT IN to TO CTL• Set SOURCE SELECT to CTL


(lines 2-4 are irrelavent)CODE=5263 ALT=32 800 FT [1344]


The CODE 5263 depends on your selection on the CTL-

92/92A code select knobs. See note 1 under step 1.2

above. The ALT display depends on the altitude

selection on the test panel ARINC 572 ALT IN switches.

Be sure that the ACT display, on the CTL-92/92A does

not flash. A flashing ACT indicates that the controlfeedback label 1F data, from the TDR, does not agree

with the CLT-92/92A output label 1E data to the TDR.

Only one of the two data CTL input ports is being used;

pins U/V.

On the test panel:


PORT 2

Be sure that the ACT display, on the CTL-92/92A, does

not flash. A flashing ACT at either port selection

indicates that output port has failed. If both ports flash,

there may be a problem with the test panel wiring or the

CTL input.

5.1 CSDB

altitude

test

In this altitude test configuration, Gillham altitude data is being supplied to the CTL (ARINC 572 ALT

IN to CTL). The CTL converts this data to CSDB and supplies it to the TDR via the CSDB data

output port (only 1 port is used; pins S/R). The CSDB altitude data is being read on the control bus

input (SOURCE SELECT to CTL). You can verify this by setting the CTL mode switch to ON. If you

suspect a problem with the altitude data, check the following:

On the test panel:

• Set ARINC 572 ALT IN to TO TDR

• Set ALT TYPE SELECT to ARINC 572

• Set SOURCE SELECT to SEL

The ATC-601 ALT display should be the same as

above since the ultimate source of altitude information

is the same in both tests. If it is different here, suspect

a problem with one or more of the altitude discrete

inputs to the CTL. If you encounter such a problem,

you can identify the defective discrete by returning

these three switches to the settings above and then

performing the ARINC 572 switching sequence shown

following step 4.0 above.

On test panel:

• Set power to OFF

• Disconnect the CTL-92/92A from the

test panel

• Set CONTROL DATA SELECT -

ARINC PORT to PA

• Set OUTPUT PORT SELECT to ARINC

429 PORT A

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Table 103. Acceptance Test Procedures,



6.0 ARINC

429

AltitudeTest

On ATC-601: select

ATCRBS REPLY TEST and press RUN to

indicate TEST RUNNING --------->



CODE= ALT= [ ]***** TEST RUNNING *****

On test panel:


• Set POWER switch to OFF


• OUTPUT PORT SELECT: ARINC 429

PORT A

On DATATRAC ( ):

• Set XMT 1 to ON

• Setup screen ------>

-----------------RCV 1--(ALL)---12.5 KHzLblSDI 32-Hex Data-1 SSM Par msec


-ON-------------XMT 1 ----------12.5 KHzLbl SDI 32-Hex Data-1 SSM Par msec031 01 15 66 C1 98 00 1 0100203 01 64 00 01 C1 11 1 0100

On test panel:

• Set POWER to ON

• EXT STBY to OPR



The ATC-601 screen shows: ---> ** ATCRBS REPLY TEST **




XMT 1 word. See note 1 under step 1.2 above.)

DATATRAC ( ) RCV 1 screen shows: ----

--->

-----------------RCV 1--(ALL)---12.5 KHzLbl SDI 32-Hex Data-1 SSM Par msec203 01 64 00 01 C1 11 1 0200


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6.1 ARINC

Control

DiscretesTests

(cont’d)

On the test panel:

• Be sure the SOURCE SELECT switch

is set to SEL.


(lines 2-4 are irrelavent)

CODE=5263 ALT=32 800 FT [1344]***** TEST RUNNING *****

On the test panel:

• Set the REP ALT SEL switch to PB

Notice that the ATC-601 altitude display blanks.

Note: At this point the UUT is configured to report

altitude data from port B. There is none so the display

blanks.

On the test panel:

• Move the parallel connection from the

PRIMARY DIGITAL ALTITUDE SOURCE

jack to the ALTERNATE DIGITAL

ALTITUDE SOURCE jack.

Notice that the ATC-601 altitude display returns.

Note: This verifies that UUT is configured to report

altitude data being supplied on port B.

On the test panel:

• Set the REP ALT SEL switch to PA


Note: UUT is returned to port A. This series of steps

has verified that the Reporting Altitude discrete is

switchable.

On the test panel:

• Set the SOURCE SELECT switch to

CTL


Note: This switches the UUT to the altitude data

supplied on the control port.

On the test panel:

• Disconnect the parallel connection from

the ALTERNATE DIGITAL ALTITUDE

SOURCE jack. (Wait about 5 seconds)

Notice that the ATC-601 altitude display remains.

Note: This verifies the previous step; that altitude is

being drawn from the control port; all other sources are

disconnected.

On DATATRAC ( ):• Set the SOURCE SELECT switch to

SEL.


Note: This verifies that the Source Select Discrete is

switchable.

On test panel:

• Reconnect the parallel connection to


SOURCE jack.

Notice that the ATC-601 altitude display remains

blanked.

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6.1

(cont’d)

ARINC

Control

DiscretesTests

(cont’d)

On test panel:

• Set the AUTO ALT switch to SEL

(-003 UUT units only)


Note: This enables the automatic altitude port selectfeature and verifies that the UUT does switch to

alternate port B even though port A is the selected port.

On test panel:

• Set the AUTO ALT switch to OFF



Note: This enables the AUTO ALT discrete is

switchable.

On the DATATRAC:

• Set the XMT 1 label 031 word to

-------->

-ON-------------XMT 1 ----------12.5 KHzLbl SDI 32-Hex Data-1 SSM Par msec031 01 95 66 E1 98 00 1 0100


Note: This digitally switches the UUT to port B. If this

test is correct while the earlier test of port B altitude

failed, suspect a problem with the Reporting Altitude

Select discrete. If both tests failed, suspect a problem

with the altitude data receivers.

On test panel:

• Set EXT STBY switch to STBY.

• Set the POWER switch OFF.

• Set the AUTO ALT switch to OFF.

On DATATRAC ( ):

• Set the XMT 1 label 031 word to ------>

-ON-------------XMT 1 ----------12.5 KHzLbl SDI 32-Hex Data-1 SSM Par msec031 01 15 66 C1 98 00 1 0100

If you wish, you can set the XMT 1 label 203 data field bits 12 through 28 to any combination of 1 and 0. The RCV 1

label 203 word data field will follow the XMT 1 word exactly while the ATC-601, set to the ATCRBS REPLY TEST mode, will

show the altitude to the nearest 100 feet. When set to the MODE UF0 TEST, the ATC-601 displays altitude to the nearest 25

feet. The label 203 bit values are shown in note 2 following step 1.2.

To simulate any altitude up to about 131,000 feet:

1. Select the desired altitude.

2. Find the data bit with the maximum bit value less than the selected altitude. Make a note of that bit number.

3. Subtract that bit value from your selected value.

4. Find the next bit with the maximum bit value less than the remainder. Make a note of that bit number.

5. Subtract that bit value from your remainder.

6. Repeat steps 4 and 5 until the remainder is 0.

In the XMT 1 label 203 data word, set all noted bits to 1. You should see your selected altitude, to the nearest 100 feet,

displayed on the ATC-601.

7.0 ARINC

575

Altitude

Test

On test panel:

• SOURCE SELECT: SEL


On DATATRAC ( ):• Set screen ------>

Note: The binary data format is retained

here to emphasize the similarity between

ARINC 429 and ARINC 575. If you are

more comfortable with the Hex data

format, feel free to use it instead.

-----------------RCV 1--(ALL)---12.5 KHzLbl SDI 29--Binary Data--11 SSM Par msec


-ON--------------XMT 1----------12.5 KHzLbl SDI 29--Binary Data--11 SSM Par msec031 01 0000000111011111011 00 1 0100203 01 0010001010101010100 00 1 0100

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7.0

(con-

t’d)

ARINC

575

AltitudeTest

(cont’d)

On test panel:

• Connect parallel control cable to

PRIMARY DIGITAL ALTITUDE SOURCE jack.

• Set POWER switch to ON.

• Set EXT STBY switch to OPR.

On ATC-601:

• Select ATCRBS REPLY TEST and

press RUN to indicate TEST RUNNING.

ATC-601 screen -------->


(lines 2-4 are irrelavent)CODE=5263 ALT=35,500 FT [5524]


On test panel:

• Set ALT TYPE SELECT switch to

ARINC 575

On DATATRAC:

• Set XMT 1 label 203 word

-------->

(just change the SSM to 00)

-ON--------------XMT 1----------12.5 KHzLbl SDI 29--Binary Data--11 SSM Par msec203 01 0010001010101010100 00 1 0100

ATC-601 screen --------> ** ATCRBS REPLY TEST **



DATATRAC screen ---------> -----------------RCV 1--(ALL)---12.5 KHzLbl SDI 29--Binary Data--11 SSM Par msec203 01 0001000101010101010 11 1 0100

| | | | | | |/ / / / / / /

| | | | | | |-ON--------------XMT 1----------12.5 KHzLbl SDI 29--Binary Data--11 SSM Par msec203 01 0010001010101010100 00 1 0100

In addition to testing the altitude type select discrete, this test illustrates the differences between

ARINC 429 and ARINC 575 data. Notice that the bits in the RCV 1 label 203 word (above) are offset

to the right by one bit from the XMT 1 label 203 word and the SSM code is 11 as opposed to the 00 in

the XMT 1 word. In ARINC 575, the LSB is bit 13; in ARINC 429 the LSB is bit 12. In ARINC 575,

bits 30 and 31 determine the sign; 00 being positive.

Notice also, that the altitude displayed on the ATC-601 corresponds to the code in the RCV 1 word;

not the XMT 1 word. This is also due to the UUT being configured for ARINC 575 and thus the bit

values are offset by 1 bit position which has the effect of changing the altitude by a factor of 1/2.

On test panel:


ARINC 429

On DATATRAC:

• Set XMT 1 label 203 word ---->

-ON--------------XMT 1----------12.5 KHzLbl SDI 29--Binary Data--11 SSM Par msec203 01 0010001010101010100 11 1 0100

ATC-601 screen: ** ATCRBS REPLY TEST **



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8.0 Mode S

Address

DiscretesTest

On the test panel:


• Set all test panel mode s address switches to SEL except switch P1-56; set it to OFF.• Set POWER switch ON

On ATC-601:

• Set for MODE S ALL CALL TEST ------->

* * M OD E S A LL C AL L TE ST - N O RE PL Y * * ALL CALL ADDRESS = [ ] TAIL NUMBER =

Press RUN to start

On ATC 601:

• Press RUN

• Note screen ----->

* * MO DE S AL L CA LL T ES T - P AS SE D * * ALL CALL ADDRESS = FFFFFE [77777776]

T AI L NU MB ER =

****** TEST RUNNING *****

The remainder of this step should be seen as optional unless you have reason to suspect a failure in

one or more of the address discrete lines. The procedure will require a few minutes because of the

delay involved in cycling power between each switch setting.

On test panel:

• Set POWER switch OFF.

• Set each triad of address switches for

an octal digit 6.

• Set POWER switch ON.

After a few seconds, UUT begins to reply and shortly

thereafter the ATC-601 screen shows the following

address:

ALL CALL ADDRESS = DB6DB6 [66666666]

On test panel:



an octal digit 4.




address:

ALL CALL ADDRESS = 924924 [44444444]

On test panel:



an octal digit 0, except the eighth triadwhich is set to 1.




address:

ALL CALL ADDRESS = 000001 [00000001]

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9.0 TCAS /

NO TCAS

DiscreteSelect

and

TCAS

Bus Test

On test panel:


On DATATRAC ( ):

• Same setup as STEP 1.1.

ATC-601 is not needed for this test but can be left on.

On test panel:


After data appears on the RCV 1 display,

press RCV and then ENT and use the

down arrow key to scroll the words so

that you can see the 350 word.

After a few seconds the RCV 1 portion of the

DATATRAC ( ) screen shows:

-----------------RCV 1--(ALL)---12.5 KHzLbl SDI 32-Hex Data-1 SSM Par msec350 01 00 00 01 17 11 1 0200

On test panel:


• Set TCAS/NO TCAS switch to TCASOn DATATRAC ( ):

• Press RCV and then ENT

On test panel:


After a few seconds the RCV 1 portion of the

DATATRAC ( ) screen shows: (use down arrow key to

scroll words)

-----------------RCV 1--(ALL)---12.5 KHzLbl SDI 32-Hex Data-1 SSM Par msec350 01 68 B3 01 17 11 1 0200

|<---diagnostic code B3

This display shows a diagnostic B3 which is interpreted: TCAS Bus Inactive. This verifies that the

discrete properly configures the unit for operation with a TCAS. However, no TCAS data is being

supplied in this step, therefore, the unit declares a B3 diagnostic.

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9.0

(cont’d)

TCAS

Bus Test,

XPDR toTCAS

Connect the DATATRAC RCV 1 to the

TCAS OUT jack. Verify that the data

word labels are detectable as shown -->.

Note: Except for the diagnostic code in

the label 350 data word, the data content

is not important. It is quite likely that the

data will be different. The presence of

the data word labels shown verifies that

the TCAS data bus output is active and

appears to be normal.

-----------------RCV 1--(ALL)----100 KHzLbl SDI 32-Hex Data-1 SSM Par msec275 00 80 00 00 BD 00 1 0150276 10 80 F8 02 7D 00 1 0150350 01 68 B3 01 17 11 1 0150

Notice the higher speed. Other labels may also be

present.

TCAS to

XPDR

Bus Test

Note: In this step you need the capability of transmitting data to two separate input ports

simultaneously and at different speeds; the 031 control word must be low speed (12.5-kbps) while

the TCAS label 274 data words must be high speed (100-kbps). All DATATRAC instruments, as

well as the JC Air 429E, can transmit at either of these speeds but only the DATATRAC 400 can do

so on two separate ports simultaneously. Otherwise, you will need two simulators. If you do not

have this capability, you may not be able to verify the integrity of the TCAS bus input port.

If you are using a DATATRAC 400, or

have access to a second bus simulator,

connect your second transmitter port or

data bus simulator to the TCAS IN and

setup as shown -------->:

-ON-------------XMT 2 -----------100 KHzLbl SDI 32-Hex Data-1 SSM Par msec274 00 18 00 00 3D 00 1 0100

Note: Be sure to set the higher speed.

On bus reader RCV display:

Note: The objective is to verify that the

UUT recognizes a valid TCAS label 274

word and declares this by removing the

diagnostic B3.

After a few seconds, the 350 word shows:


|<---diagnostic code 00

On the bus reader:

Set the XMT 2 word to OFF

After a few seconds, notice that the B3 diagnostic

returns.

Note: Disconnect XMT 2 from the TCAS

IN jack and reconnect RCV 1 to the

DATA BUS OUTPUT port.

Final step

in this

test, all

setups

On test panel:


• Set TCAS/NO TCAS switch to NO

TCAS

On DATATRAC ( ):


On test panel:


After a few seconds, the original 350 word returns:-----------------RCV 1--(ALL)---12.5 KHzLbl SDI 32-Hex Data-1 SSM Par msec350 01 00 00 01 17 11 1 0200

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10.0 Side 1/

Side 2

DiscreteTest

On test panel:


• Be sure SIDE 1/SIDE 2 switch is set toSIDE 1.

On DATATRAC ( ):


On ATC-601:

• Set for ATCRBS REPLY TEST screen -->


(lines 2-4 are irrelevant)CODE= ALT= [ ]


On test panel:


After a few seconds, X FEED OUT and ATC-601 REPLY

lamps light and the ATC-601 shows:


(lines 2-4 are irrelevant)CODE=5263 ALT=32,800 FT [1344]


On test panel:


• Set SIDE 1/SIDE 2 switch to SIDE 2


Note that unit does not reply (X FEED OUT lamp and

REPLY lamps are off and no altitude is displayed on

ATC-601). Wait about 10 seconds.

Note: UUT does not respond because the SDI and side

strapping do not agree.

Note: Be sure to allow adequate time for the CPU to

reinitialize properly between power off and power on.

The SIDE 1/2 strap is one of several that are monitored

only at processor initialization. Therefore, if this tests

fails, cycle power again but allow more time between

power off and power on.

On DATATRAC ( ):

• On XMT 1, label 031 word, set the SDIto 10 and press ENTER

Notice that unit begins to reply almost immediately

(XFEED OUT lamp turns on and ATC-601 REPLY lamplights).

Note: UUT responds because the SDI and side

strapping agree.

On DATATRAC ( ):

• On XMT 1, label 031 word, set SDI to

01 and press ENTER .

Notice that unit stops replying (X FEED OUT lamp and

ATC-601 REPLY lamps turn off).

On test panel:





lamps l ight a nd t he ATC-601 shows tha t the U UT is

replying.

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11.0 AIR/

GND

DiscreteTest

On test panel:


• TDR ALT SOURCE: EXT DIRECT• ALT TYPE SELECT: ARINC 429

On DATATRAC ( ):


On ATC-601:

• Set for MODE S UF4 TEST screen ----->

** MODE S UF4 TEST - NO REPLY **

DF FS= DR= UM= AC= ADDRESS=


On test panel:


ATC-601 screen shows ----->:



** MODE S UF4 TEST - PASSED **

DF 4 FS=0 DR=00 UM=00 AC=32,775 FT ADDRESS=000001


Note: Initially the screen will show FS=2 for about 2

seconds and then change to FS=0.

On test panel:

• Set AIR/GND switch to GND

After a few seconds, the ATC-601 shows:




Of particular significance here is the FS (flight status) indication.

For a detailed description of each of these message fields, refer to the Theory of Operation section.

On test panel:

• Set AIR/GND switch to AIR

After a few seconds, notice that the ATC-601 FS field

again shows 0.

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12.0 DL ANT/

SGL ANT

DiscreteTest

(TDR-94D

only)

On test panel:


On DATATRAC ( ):


On ATC-601, set for SQUITTER TEST

screen ----->

Be sure the ATC-601 is connected to the

top antenna port.

** SQUITTER TEST - NO REPLY **PERIOD = SECONDSTAIL NUMBER =SQUITTER ADDRESS= [ ]


On test panel:

• Set DL ANT/SGL ANT switch to DL

ANT


You can watch the PERIOD display for a

time.

After a few seconds, the ATC-601 screen shows: See

note below.

* * S QU ITT ER T ES T - PA SS ED * *PERIOD = 2.00 SECONDSTAIL NUMBER =SQUITTER ADDRESS= [ ]


See the note at the end of this step for test tolerances.

On test panel:


• Set DL ANT/SGL ANT switch to SGL

ANT


After a few seconds, the ATC-601 screen shows:

* * S QU IT TE R T EST - F AI LE D * *PERIOD = SECONDSTAIL NUMBER =SQUITTER ADDRESS= [ ]


Note: This test is intended to fail. When the UUT is set

for single antenna operation, there is no transmission

from the top antenna port. Therefore, if this test

indicates PASSED, recheck all switch settings or

suspect a problem with the SGL/DL ANT select strap.

It should not pass.

On test panel:


On ATC-601:

• Press RUN to stop the test.

• Remove rf terminator from bottom

antenna connector

• Connect ATC-601 cable to bottom

antenna connector

• Connect rf terminator to top antenna

connector

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12.0 DL ANT

/SGL

ANTDiscrete

Test

(cont’d)

(TDR-94D

only)

On test panel:


On ATC-601:

• Press RUN to start the test.


note below.

* * S QUI TT ER TE ST - P AS SE D * *PERIOD = 1.00 SECONDSTAIL NUMBER =SQUITTER ADDRESS= [ ]


On test panel:



ANT



note below.

* * S QUI TT ER TE ST - P AS SE D * *PERIOD = 2.00 SECONDSTAIL NUMBER =SQUITTER ADDRESS= [ ]


Note: The PERIOD value tends to vary somewhat in all cases. When the UUT is set for dual antenna

operation and the ATC-601 is monitoring the top or the bottom antenna port, the value can vary from1.6 to 2.4. When the TDR-94D is set for single antenna operation, or the UUT is a TDR-94, there is

no transmission from the top antenna port and and the transmission PERIOD from the bottom

antenna port can vary from 0.6 to 1.4.

13.0 Burst

Tune and

Cross-

Feed In

Discrete

Test

On test panel:


• Set CONTROL DATA SELECT to PA



On DATATRAC ( ):



screen ----->

If necessary, reconnect ATC-601 to top

antenna connector, with terminator on

bottom connector.

** SQUITTER TEST - NO REPLY **PERIOD = SECONDS

TAIL NUMBER =SQUITTER ADDRESS= [ ]


On test panel:


After a few seconds, the test panel X FEED OUT and

the ATC-601 REPLY lamps light indicating that the unit is

replying. The ATC-601 screen data indicates PASSED.

On test panel:

• Set X FEED IN/OUT switch to IN

Notice that both X FEED lamps are lighted.

On DATATRAC ( ):

• Set XMT 1 to OFF

(With the cursor on the 1, press ENT)

Notice that the X FEED OUT and ATC-601 REPLY

lamps turns off (X FEED IN stays on).

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13.0

(cont’d)

Burst

Tune and

Cross-Feed In

Discrete

Test

(cont’d)

On DATATRAC ( ):

• Set XMT 1 to ON

Notice that the X FEED IN and OUT and REPLY lamps

are lighted.

On test panel:

• Set X FEED IN/OUT switch to OUT

• Set BURST TUNE switch to ON

On DATATRAC ( ):


Notice that UUT continues to reply. Watch the unit for

a few seconds.

On test panel:

• Set BURST TUNE switch to OFF

Notice that UUT stops replying (X FEED OUT and

REPLY lamps turn off).

On test panel:


Notice that UUT does not reply (X

FEED OUT and REPLY lamps do not light).

On DATATRAC ( ):

• Set XMT 1 to ON

Notice that UUT replys (X FEED OUT and REPLY lamps

are on).

On test panel:• Set BURST TUNE switch to OFF

On DATATRAC ( ):


Notice that UUT stops replying (X FEED OUT andREPLY lamps are off).

On test panel:


On DATATRAC ( ):

• Set XMT 1 to ON

X FEED OUT lamp flashes while XMT 1 is on .

On test panel:


X FEED OUT lamp remains off when XMT is OFF.

14.0 Output

Port

Discrete

Test

On test panel:


• Set SOURCE SELECT switch to SEL

• ALT TYPE SELECT: ARINC 429• CONTROL DATA PORT SEL: PA

• OUTPUT PORT SELECT: ARINC 429 PORT A

On DATATRAC ( ):

• The same as STEP 1.1

• Set XMT 1 to ON


screen ----->



On test panel:


After a few seconds, the test panel X FEED OUTand


replying. The ATC-601 screen data indicates PASSED

.

On test panel:

• Set OUTPUT PORT SELECT switch to

ARINC 429 PORT B

Notice that there is no change in the test result; X

FEED OUT and REPLY lights are on and ATC-601

display does not change.

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15.0 Control

Data

Input PortSelect

Discrete

Test

On test panel:


• Set SOURCE SELECT switch to SEL• ALT TYPE SELECT: ARINC 429

• CONTROL DATA SELECT: ARINC

PORT PA

On DATATRAC ( ):

• Same setup as for STEP 9.0.


screen ----->



On test panel:





On test panel:

• Set CONTROL DATA SELECT switch

to ARINC PORT PB


FEED OUTand REPLY lights are on and ATC-601


On test panel:


to ARINC PORT PC




16.0 Manual

STBY

Discrete

Test

On test panel:



• Set CONTROL DATA SELECT switch to ARINC PORT PA

On DATATRAC ( ):• Same setup as for STEP 9.0.

On ATC-601:

• Set for ATCRBS REPLY TEST screen

---------->




On test panel:






On test panel:


Note that X FEED OUT lamp and ATC-601 REPLY

lamps turn off and ATC-601 indicates NO REPLY. See

note below.

On test panel:



lamps light almost immediately and ATC-601 indicates

PASSED.

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17.0 Max Air-

speed

Test

On test panel:


• ALT TYPE SELECT: ARINC 429• Be sure that all three MAX AIRSPEED switches are set to OFF.

On DATATRAC ( ):


(The DATATRAC is used here only for

tuning data.)

On ATC-601:

• Set for MODE S UF0 TEST screen >


DF VS= RI= AC= ADDRESS=


On test panel:


After a few seconds, the test panel X FEED OUT lamp

and the ATC-601 REPLY lamps light indicating that the

unit is replying.

Note the ATC-601 screen -----------> ** MODE S UF0 TEST - PASSED **

DF 0 VS=0 RI=8 AC= 32,775 FT ADDRESS=000001


Exercise the MAX AIRSPEED switches on the test panel and verify the correct RI indication as

shown in the following list. Cycle power and allow about 2 or 3 seconds of OFF time and about 5

seconds for processor initialization and ATC-601 response time between each switch setting.

MAX AIRSPEED SWITCH RI VALUEBIT 15 BIT 16 BIT 17

OFF OFF OFF 8SEL OFF OFF 9OFF SEL OFF A SEL SEL OFF BOFF OFF SEL CSEL OFF SEL DOFF SEL SEL E

SEL SEL SEL F (not an assigned configuration)

It is worth noting that in this test mode the ATC-601 displays the altitude to the nearest 25 feet.

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18.0 Ext Sup-

pression

Test

On test panel:


On DATATRAC ( ):


On ATC-601:

• Set for ATCRBS REPLY TEST screen -----

->




• Connect scope channel A to the test

panel SUPPR test points.

• Connect scope channel B to the REPLY

VIDEO BNC connector on the ATC-601.

• Set the scope to display both channels

Note a (approx) 30µs pulse on channel A.

Note a reply waveform on channel B. If your scope is

able, you will see the individual reply code pulses on

channel B. You may also see the occasional squitter

transmission which appears as a much longer series of

pulses at about 1 transmission every 2 sec. Of

particular importance, however, is that the channel A

(suppression) pulse is about 30 µs long during ATCRBS

reply, and brackets the 21 µs ATCRBS reply. During

squitter transmission, the suppression pulse extends to

bracket the squitter transmission. The squitter

transmission is a DF11 reply about 72 µs long.

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19.0 ADLP

Select,

DiscreteStrap

Test

On test panel:

• Be sure DATALINK switch is set to NO

ADLP.

On DATATRAC ( ):


DATATRAC RCV 1 screen ------>

Note: The ATC-601 is not needed for

this test but it can remain connected and

operating.


On test panel:


• Set DATALINK switch to ADLP.

• Be sure DATALINK SELECT switch is

set to A/B.



-----------------RCV 1--(ALL)---12.5 KHzLbl SDI 32-Hex Data-1 SSM Par msec350 01 64 A2 01 17 11 1 0100

|<---diagnostic code A2

Note: The diagnostic A2 identifies an inactive ADLP

bus. This test verifies that the ADLP enable discrete is

functional.

On test panel:

• Set POWER switch to OFF.

• Set DATALINK switch to NO ADLP.





Note: The Airborne Datalink system is not fully implemented at this time. If and when an ADLP

(Airborne DataLink Processor) becomes available and operational, suitable procedures will be

provided to verify the integrity of the ADLP input/output ports. At this point, therefore, verification of

the ADLP SELECT strap is seen as sufficient to prevent nuisance diagnostics that can occur if the

select input should be defective. You will notice that the DATALINK SELECT A/B, C/D function isalso not tested.

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20.0 Remote

IDENT

DiscreteTest

On test panel:

• Same as initial setup

On DATATRAC ( ):


On ATC-601:

• Setup for ATCRBS REPLY test




On test panel:

• Press and release the REMOTE IDENT

switch.

On DATATRAC ( ):

• Note RCV screen ----->:


|<----Ident bit

Note: The 9 should appear in the data field only while

the switch is being pressed. This, together with the ID

display on the ATC-601, verifies that the REMOTE

IDENTdiscrete input is functional.

On ATC-601:

• Notice the ID display. ID should

display for about 18 seconds.


(lines 2-4 are irrelevant)CODE=ID5263 ALT= 32,800 FT [1344]

|<----ID display***** TEST RUNNING *****

On Datatrac ( ):

• Set the label 031 XMT 1 word:

-ON--------------XMT 1--(ALL)---12.5 KHzLbl SDI 32-Hex Data-1 SSM Par msec031 01 15 66 91 98 00 1 0100

On DATATRAC RCV 1 and on ATC-601

screens:

You should see the same displays as immediately

above. If the test failed using the REMOTE IDENT

switch, but succeeds here, then suspect a failure in the

discrete input or the test panel.

On Datatrac ( ):• Set the label 031 XMT word:

-ON--------------XMT 1--(ALL)---12.5 KHzLbl SDI 32-Hex Data-1 SSM Par msec031 01 95 66 81 98 00 1 0100

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21.0 Self Test On test panel:


• ALT TYPE SELECT: ARINC 429• AIR/GND: AIR

• SELF TEST: ENABLE: OFF

On DATATRAC ( ):


On ATC-601:

• Set for ATCRBS REPLY TEST

---------->




On test panel:




unit is replying. The ATC-601 screen indicates PASSED.

On DATATRAC ( ):

screen shows: --------->

-----------------RCV 1--(ALL)---12.5 KHz

Lbl SDI 32-Hex Data-1 SSM Par msec031 01 F5 66 81 98 11 1 0200203 01 64 00 01 C1 11 1 0200350 01 60 00 01 17 11 1 0200

(You may need to press INC to display all three labels.)

In the next few steps, watch the

DATATRAC RCV screen carefully.

On the test panel:

• Press and hold the SELF TEST

pushbutton for about 1 sec.

After a few seconds, notice that the DATATRAC ( ) and

ATC-601 screens do not change except that the

DATATRAC briefly shows *’s to the left of the 0200 time

displays in the RH column. (The test panel TEST lamp

lights while you hold the switch but otherwise there is

no change.)

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21.0 Self Test

(cont’d)

On test panel:

• Set the AIR/GND switch to GND

• Set the SELF TEST/ENABLE switch toON

• Press and hold the SELF-TEST button

for about 1 s

Note: The test panel TEST lamp lights

while you hold the switch. This has no

bearing on UUT operation, however. If

the lamp does not light, check the test

panel.

On the DATATRAC ( ), press RCV (either

once or twice) to return to the setup

screen, followed by ENT, to clear the

screen of any extraneous labels.

Self-test Displays:

After a few seconds, notice that the X FEED OUT lamp

turns off briefly while the ATC-601 screen shows +’s or-’s in most of the data fields, followed by blank fields.

After a few seconds, notice that the X FEED OUT

lamps turns on again and the ATC-601 screen returns

to the normal display.

On the DATATRAC ( ), notice that the SSM’s change to

10 and then back to 11.You should try to be especially

watchful of the 350 data word and try to catch any

diagnostic codes that may be displayed during the self-

test sequence.

On the test panel:

• Set the SELF TEST/ENABLE switch to

OFF.

• Press and hold the SELF TEST button

for about 1 s.

Notice that the self-test displays as described above do

not appear..

Note: This verifies that self test is properly inhibited by

the self-test inhibit discrete.

On the test panel:


ON.

• Set the AIR/GND switch to AIR.

• Wait about 5 seconds *.


for about 1 s.


not appear..


the AIR/GND discrete.

*Note: The CPU must be allowed sufficient time to complete at least one software cycle in order to

recognize the change in the AIR/GND discrete. If you press the SELF TEST switch in less thanabout 3 seconds of setting the AIR/GND switch to AIR, the unit may execute self-test as though it

were not inhibited. This should be seen as normal.

On the test panel:


ON.

• Set the AIR/GND switch to GND.


for about 1 s.

Notice the self-test displays as described above

reappear.

Note: This verifies that the self-test inhibit and AIR/GND

discretes are switchable.

This completes this test sequence. Successful completion of this series provides reasonable

assurance that the unit is operational. However, this test does not satisfy the requirements of a Final

Performance Test which must be performed after any repair operation.

Turn off all power, disconnect the equipment, and return it to its normal storage location. Return theUUT to its original shipping container, or equivalent, if it is to remain in storage. Otherwise, prepare

it for installation.

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5 .4 .5 .1 0 P r o ced u r es U s i n g T h e A t l a n t i c I n s t r u m en t s

D a t a T r a c 2 0 0 D a t a b u s A n a l y z er


Using the DATATRAC 200 Databus Analyzer


1.0 Setup Note: If you are using a Test Panel built according to instruction provided in a previous edition of this

manual, it may be necessary to upgrade the panel. Refer to the Special Tools and Fixtures Section.

If not already done, connect equipment as shown in figure 5-2.

• Connect DATATRAC 200 as follows and using cables shown in the Special Tools and Fixtures

paragraph.

• ARINC 429 XMT to test panel DIGITAL CONTROL port,

• Parallel connect XMT to test panel PRIMARY DIGITAL ALTITUDE PORT,

• ARINC 429 RCV to test panel DATA BUS READER port.


• Connect an rf termination to the top antenna port.


• Preset the switches as shown in paragraph 5.4.5.6. above. Be sure POWER switch is OFF and EXT


1.1 Setup Turn the DATATRAC 200 on, intialize for

ARINC 429, and set the RCV , and XMT

screen ----->

(See notes 1 and 2 that follow test step

1.2)

L bl SI 29 -H ex RC V-1 1 S M P MS EC

>> NO DATA RECEIVED

L bl SI 29 -H EX XM T-1 1 S M P MS RC031 01 55980 00 1 100203 01 20000 11 1 100

On test panel, set switches as shown in paragraph 5.4.4. above.

Turn on

TDR-94/94D

On test panel:




Monitor current.





transmitting.

Setup

(power-up)





CODE= ALT= [ ]Press RUN to start

1.2 UUT power

on and

ARINC 429

tuning test

ATC-601 screen ---------> ** ATCRBS REPLY TEST **

(lines 2-4 are irrelevant)C OD E= 52 63 A LT =32 ,8 00 F T [ 13 44]



To change the ALT, see note 2 below.

The DATATRAC 200 RCV display becomes

--------->

Lbl SI 29-Hex RCV-11 SM P MSEC031 01 559A0 11 1 0200203 01 20000 11 1 0200350 01 00000 11 1 0200


test. Use the INC key to scroll the display. See Note 3

below.

On the ATC-601, press RUN UUT responds to interrogations as indicated by a lighted



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Using the DATATRAC 200 Databus Analyzer (Cont).


Note 1. You can change the (octal) CODE=XXXX display by changing data bits 18 through 29 in the label 031 data word ( XMT

field of the DATATRAC 200) as follows:

ATC-601 octal digit: First Second Third Fourth

Bit: 32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15

Data: Par SSM |<-----Data -------> ----->| Pad Pad Pad

DATATRAC Hex Bits: First Second Third Fourth

DATATRAC Hex value: 8 4 2 1 8 4 2 1 8 4 2 1 8 4 2 1

DATATRAC (Hex): 5 5 9 8

Binary: 0 0 0 1 0 1 0 1 0 1 1 0 0 1 1 0 0 0

Octal value: 4 2 1 4 2 1 4 2 1 4 2 1

Produces an ATC-601 CODE: 5 2 6 3

Bits 11 through 17, of the label 031 control word, are assigned the following functions:

DATATRAC Hex bits: Fifth

Bit: 14 13 12 11 10 9

Bit values: 8 4 2 1 8 4 2 1

DATATRAC (Hex): 0| | Pad | |<- |<--SDI

Assignment: | | |<--Altitude reporting, 1 = OFF

| |<--Ident, 1 = ON

|<--Altitude port select, 1 = B

Note 2: You can set the XMT label 203 data field bits 12 through 28 to any combination of 1 and 0. The RCV label 203 word

data field will reflect the XMT word while the ATC-601 will show the altitude to the nearest 100 feet. The label 203 word data

bit values are as follows:

DATATRAC (Hex) *: | lst | | 2nd |

Hex value: 8 4 2 1 8 4 2 1

Bit: 29 28 27 26 25 24 23 22

Alt value:(sign bit; 0 = +) 65536 32768 16384 8192 4096 2048 1024

(in feet)

DATATRAC (Hex) *: | 3rd | | 4th | | 5th |

Hex value: 8 4 2 1 8 4 2 1 8 4 2 1

Bit: 21 20 19 18 17 16 15 14 13 12 11 10 09

Alt value 512 256 128 64 32 16 8 4 2 1 ** ** **

(in feet)

Determine the altitude by totaling the bit value of all bits set to 1.

* The first (lst) Hex Data bit sets data bits 26 through 29. Since bit 29 must always be a 0, this Hex bit must not be set to a

hex number greater than 7. The fifth (5th) bit includes part of the SI, bit 10, therefore you will see it change whenever the SI

is set to any value other than 01. ** Bits 9, 10, and 11 are not used in the altitude definitions.

Note 3: You will see a label 371 data word. This is the ARINC 429 Specific Equipment Identification word which is

structured the same as other ARINC 429 words but conveys the following information:

Bits 11 through 18 identify the equipment type. The code for ATC transponders is 18 therefore bits 14 and 15 are 1; the

others are 0. Bits 19 through 24 convey a binary code identifying the equipment manufacturer. Collins’ is 6. Therefore bits

20 and 21 are 1; all others are 0. Bits 24 through 29 are reserved for purposes to be defined.

When ARINC 572 altitude data is active, you will see a label 200 data word. This word reflects the ARINC 572 (Gillham code)

altitude data. This word is structured the same as other ARINC 429 words, except bits 9 and 10 are part of the data field; i.e.,

there is no SDI. Bits 9,10, and 11 reflect the D1, D2, and D4 code bits respectively. Bits 13, 14, and 15 reflect the C-bits,

bits 17, 18, and 19 reflect the B-bits, and 21, 22, and 23 reflect the A-bits.

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2.0 Test set, Auto

Test

On ATC-601:


• Press AUTO TEST

• Press RUN to start

Note: This test requires a few sec-

onds to run. It will stop automati-

cally.


On test panel:



On UUT:

• Move the test set rf cable to the UUT top antenna connector and the rf termination to the

bottom.

On test panel:



On ATC-601:

• Repeat the AUTO TEST


Note. The AUTO TEST sequence will indicate FAILED even when certain tests result in a NO REPLY condition. The NO REPLY

conditions are the result of no ADLP (Airborne Data Link Processor) data in this setup. This same condition is likely to occur

when using the ATC-601 as a ramp tester when testing an installation not equipped with an ADLP. To verify that the test can

be seen as successful, proceed as follows:




Press RUN to start

(The FREQ, ERP, and MTL values can vary from UUT to UUT and to a lesser degree on UUT temperature.)


On the ATC-601, use the SELECT up arrow or down arrow key to scroll through the following list of tests performed; the





1.0 ** REPLY DELAY TEST - PASSED ** MODE S: 128.00 (±0.25) µsITM A: 128.00 (±0.25) µs

(All others): 3.00 (±0.50) µs

2.0 ** REPLY JITTER TEST - PASSED ** MODE S: =< 0.05 µsITM: =< 0.06 µs

(All others): =< 0.1 µs



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4.0 ** SLS LEVEL TEST - PASSED ** UUT is interrogated with F2 (SLS) pulse at 9 dB below F1.UUT should reply to this interrogation. Then UUT is interro-

gated with F2 equal to F1. UUT should not reply. PASSED

indicates correct response to both tests.



response.





reply.






9.0 * * M OD E S U F0 TE ST - P AS SE D * * UUT is interrogated with mode S UF0, verifying correct




10.0 * * M OD E S UF 4 TE ST - P AS SE D * * UUT is interrogated with UF4, verifying correct altitude as




11.0 * * M OD E S UF 5 TE ST - P AS SE D * * UUT is interrogated with UF5, verifying the correct ID code




12.0 * * M OD E S UF 11 TE ST - P AS SED * * UUT is interrogated with UF11, verifying correct address as



13.0 * * M OD E S UF 16 TE ST - N O R EP LY ** (See test 15.)


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STEP TEST NAME AND RESULT TEST SPECIFICATION / DESCRIPTION

15.0 * * MO DE S UF 21 TES T - NO RE PLY * * UUT is interrogated with UF16, UF20, and UF21. Theseformats are all related to the airborne data link function. This

function has not been implemented. The TDR-94/94D will

not reply to these interrogation formats. NOT REPLY should

not be seen as a failure.

16.0 ** SQUITTER TEST - PASSED ** When set for daul antenna operation, the TDR-94D transmits

a squitter pulse once each second, alternating between top

and bottom antenna ports. The ATC-601 verifies that one

squitter pulse is received every 1.6 to 2.4 seconds. The test

panel ANT SGL/DL switch must be in the DL position.

When set for single antenna operation, or when testing a

TDR-94, only the bottom antenna port is used. In this case

the ATC-601 verifies that one squitter pulse is received every

0.6 to 1.4 seconds. When you change the ANT SGL/DL

switch, you must cycle power to the UUT in order for it to

take effect. PASSED indicates a correct UUT response.


18.0 ** DIVERSITY TEST - PASSED ** ATC-601 monitors squitter pulses on active antenna port (as

in test 16) and then monitors for intervening squitter pulses

that are not greater than 20 dB below the active squitter.

This test will always fail when the UUT is a TDR-94 (non

diversity) because squitter is transmitter every second on the

same antenna port. If you are testing a TDR-94D and the DL

ANT/SGL ANT switch is set to SGL ANT, the test will also

fail because this causes the unit to operate like a TDR-94.

PASSED indicates a correct response from a TDR-94D.

19.0 ** MTL DIFFERENCE TEST - PASSED ** ATC-601 verifies that the MTL difference between mode a

and mode c responses is < 1.0 dB. At this point, anotherpress of the arrow key will display the first item; either 1.0 or

18.0, depending on which arrow was used.

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S TE P TI TL E P ROC E D U RE D E S I RE D RE S U L TS OR S E TU P S C RE E N

3.0 P ow er

output

and RcvrSensi-

tivity Test


• Set E XT STBY sw itch to STBY

• S e t P O WE R s w i t ch O F F

On ATC-601:


• Press RUN to indicate TEST RUNNING ----

----->



Note: If necessary, press SELECT (or SLEW ) to select Top Antenna. Be sure that the ATC-601 rf


On DATATRAC 200: set screen ------> L BL S I 2 9- HE X R CV -11 S M P M SE C>> NO DATA RECEIVED

L BL SI 29 -H EX XM T- 11 S M P MS EC031 01 55980 00 1 100203 01 20000 11 1 100

On test panel:




shows ---->

On ATC-601:


** POWER TEST - Top Antenna **

ANTENNA UNITS ERP MTL STATUSTop dBm 55.7 -76.0 PASSED








On test panel:



• On TDR-94D mount:

Swap the rf cable connection and ter-mination on the UUT antenna ports. (Rf

cable to bottom port and termination to

top antenna port.)

On test panel:



On ATC-601:


Wait a few seconds then press RUN/STOP

to stop the test.

You should see a similar display on the ATC-601 ex-

cept this data is applicable to the top antenna port. The

data can be slightly different. See below for test




the ATC-601.




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3.0

(cont-

’d)

Power

output and

RcvrSensi-tivity

Test

(cont’d)



MTL: -73.0 (±4.0) dBm

The ATC-601 will indicate that the UUT has FAILED if the MTL is more than -77.0 dBm or less than -

71 dBm. Collins prefers, however, that a FAILURE should be reported only if the MTL is less than -

71 dBm. Therefore, if you have a unit displaying an MTL of -77.1 or more, you should see that value

as acceptable. Obviously, an MTL indication approaching -80 dBm or more may be cause for














test evaluation:


50 16.99 46.99


100 20.00 50.00


150 21.76 51.76

200 23.01 53.01

250 23.98 53.98 Minimum di rect (on bench)

300 24.77 54.77

350 25.44 55.44

400 26.02 56.02

450 26.53 56.53


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4.0 Gillham

Altitude

Test

On ATC-601: select




CODE= ALT= [ ]

Press RUN to start





On DATATRAC 200:

• Set XMT label 203 word to OFF

• Set RCV and XMT screen

------>

L bl SI 2 9- He x R CV -11 S M P MS EC>> NO DATA RECEIVED

L bl SI 29 -H EX XM T- 11 S M P MS EC031 01 55980 00 1 100

On test panel:


Then set A4, C2, C4, and B4 to SEL.

• Set POWER to ON• Set EXT STBY switch to OPR



DATATRAC 200 RCV screen shows:

-------------------->

L bl SI 29 -H EX RC V- 11 S M P MS EC031 01 55980 11 1 100203 01 05C30 11 1 100


On ATC-601:

• Press RUN. Screen shows:

-------------------->





XMT word. See note 1 under step 1.2 above)

At this step you are asked to toggle each of the ARINC 572 switches and verify the altitude display. You should also watch

the RCV data word on the DATATRAC 200 display. By cycling each switch between OFF and SEL you should see the ATC-601 display and the DATATRAC 200 and 203 data words change. If the displays do not change for a particular switch, this

would indicate either an open or a shorted code line. If the wrong altitude is shown that code line may be effecting another

line; i.e., causing two or more inputs to change simultaneously. In either case the UUT, the test panel, or the interconnecting

cable needs repair.



There is no serious need to verify the correctness of the RCV word as long as the ATC-601 display is correct.

SWITCH DISPLAYED ALTITUDE SWITCH DISPLAYED ALTITUDE


A1 (SEL) 23,600 FT [5460] B1 (SEL) 3,600 FT [4560]

A2 (SEL) 7,600 FT [6460] B2 (SEL) 5,600 FT [4660]

A4 (OFF) -400 FT (0460] B4 (OFF) 6,600 FT [4060]


C2 (OFF) 5,800 FT [4440] D4 (SEL) 55,600 FT [4464]

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Gillham Code, Altitude Listing:GILLHAM CODE SWITCHES

ATC-601 ALT DISPLAY D2 D4 A1 A2 A4 B1 B2 B4 C1 C2 C4-1000 FT 0 0 0 0 0 0 0 0 0 1 0

0 FT 0 0 0 0 0 0 1 1 0 1 0500 FT 0 0 0 0 0 0 1 0 0 1 0

1000 FT 0 0 0 0 0 1 1 0 0 1 01300 FT 0 0 0 0 0 1 1 1 1 0 0

1500 FT 0 0 0 0 0 1 1 1 0 1 01800 FT 0 0 0 0 0 1 0 1 0 0 12000 FT 0 0 0 0 0 1 0 1 0 1 02600 FT 0 0 0 0 0 1 0 0 0 1 12700 FT 0 0 0 0 0 1 0 0 0 0 1

3000 FT 0 0 0 0 1 1 0 0 0 1 04000 FT 0 0 0 0 1 1 1 1 0 1 06000 FT 0 0 0 0 1 0 0 1 0 1 06800 FT 0 0 0 1 1 0 0 0 0 0 18000 FT 0 0 0 1 1 0 1 1 0 1 0

10000 FT 0 0 0 1 1 1 0 1 0 1 012000 FT 0 0 0 1 0 1 1 1 0 1 0

14000 FT 0 0 0 1 0 0 0 1 0 1 014800 FT 0 0 1 1 0 0 0 0 0 0 116000 FT 0 0 1 1 0 0 1 1 0 1 0

16100 FT 0 0 1 1 0 0 1 1 1 1 016200 FT 0 0 1 1 0 0 1 1 1 0 018000 FT 0 0 1 1 0 1 0 1 0 1 020000 FT 0 0 1 1 1 1 1 1 0 1 022000 FT 0 0 1 1 1 0 0 1 0 1 0

25000 FT 0 0 1 0 1 1 1 0 0 1 030000 FT 0 0 1 0 0 0 0 1 0 1 030800 FT 0 1 1 0 0 0 0 0 0 0 135000 FT 0 1 1 0 1 1 0 0 0 1 040000 FT 0 1 1 1 1 0 1 1 0 1 0

45000 FT 0 1 1 1 0 0 1 0 0 1 050000 FT 0 1 0 1 0 1 0 1 0 1 066000 FT 1 1 0 0 0 1 0 1 0 1 067500 FT 1 1 0 0 1 1 0 1 0 1 0

-----------------------------------------------------------------------------------

In all cases, set the applicable switch to SEL for those pulses identified by a logic 1.For addtional information on Gillham code structure, refer to paragraph 5.7 in this section.

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5.0 CSDB tun-

ing and

altitude test

On ATC-601:

• Press RUN/STOP to stop the interrogations

On test panel:• Set POWER OFF

On DATATRAC 200:

• Turn POWER to OFF

• Wait a few seconds, then turn POWER to ON

• At the initial screen, select CSDB (enter C and press ENT)

• At the DATA RECEIVER SETUP screen, press 2 (for HEX DATA ) and press ENT (this brings up the

RCV DATA screen)

• Press XMT to show the TRANSMITTER SETUP screen (default values should be correct)

• Press ENT (this brings up the combined screen)

Note screen ----------> LBL 7-STAT-0 HEX RCV DATA MSEC>> NO DATA RECEIVED

LBL 7-STAT-0 HEX XMT DATA MSEC

(Note cursor is under the B in the XMT LBL field)

On the back of the DATATRAC 200:

• Move the cables (HI and LO) connected to the 429 TX to CSDB TX

• Move the cables (HI and LO) connected to the 429 RX to CSDB RX

On DATATRAC 200:

• Enter 1E (this is the CSDB

tuning word label)

• DATATRAC responds with a

default field of 0 ’s and 100 below MSEC

• Change XMT data field as shown

------------->

(Be sure to press INC)

LBL 7-STAT-0 HEX XMT DATA MSEC1E 10011001 63 52 44 13 100

|||||||| || || ||<||<-Gillham altitude *

|||||||| ||<||<-ATC code *

|||||| |<- SI; 01 = side 1, 10 = side 2

||||||<-Test; 1 = on

|||||<-ATC ident; 1 = on

||||<-Altitude reporting; 1 = on

|||<-Mode; 1 = standby

||<-Pad (not used)

|<-Validity; 1 = valid

* Refer to paragraph 5.6.3.2 for code description.

On ATC-601: select ATCRBS REPLY TEST

and press RUN to indicate TEST

RUNNING

----------->

** ATCRBS REPLY TEST NO REPLY **



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5.0

(cont’d)

CSDB tuning

and altitude

test (cont’d)

On test panel:

• Set CONTROL DATA SELECT to CSDB

• Set ALTITUDE DATA, ALTITUDE TYPE SELECT to CSDB (CTL)• Set OUTPUT PORT SELECT to CSDB PORT 1

• Set ARINC 572 ALT IN to TO CTL

• Set SOURCE SELECT to CTL

• On the test panel CONTROL CONNECTOR J1, connect two jumpers:

From Pin To Pin

26 41

25 8 Note: These jumpers are not required if MOD 1 has been installed in the

test panel.


DATATRAC 200 screen --> L BL 7 -S TA T- 0 H EX R CV D AT A MS EC1F 11011001 63 52 44 13 0100

A0 10000001 20 20 00 00 0100F3 00000001 00 00 00 00 0100

L BL 7 -S TA T- 0 H EX X MT D AT A MS EC

1E 10011001 63 52 44 13 100

On test panel:

• Set the OUTPUT PORT SELECT

switch to CSDB PORT 2.

Notice that the same data is displayed. (The data may

flicker somwhat while you are switching; ignore that.)

Important points:

• The 1F RCV word is a reflection of the 1E XMT word

• The A0 RCV word is irrelavent here, the hex data shown above can be different

• The F3 word is the diagnostic word and should indicate no faults; HEX DATA is all 0’s. Bits 1

and 0 of the status byte are the SI bits and indicate that the UUT is set for side 1 (01) which

must be true of all word labels.

The ATC-601 screen shows: ** ATCRBS REPLY TEST **

(lines 2-4 are irrelevant)CODE=5263 ALT= 32,800 FT [1344]


Important points:

• Notice that the CODE agrees with the HEX XMT DATA 1E word except that the hex digital pair

groupings are reversed in order. That is, the XMT and RCV words show 63 52 while the ATC-

601 shows 5263. In the altitude field, the XMT and RCV words show 44 13 while the ATC-601

shows 1344.

6.0 ARINC 429

Altitude Test

On ATC-601: select

ATCRBS REPLY TEST and press RUN

to indicate TEST RUNNING --------->




On test panel:


• Set the POWER switch to OFF


• Set OUTPUT PORT SELECT switch to ARINC 429 PORT A

• Set CONTROL DATA SELECT switch to PA

On DATATRAC 200:

• Move the TX and RX leads to the ARINC ports.

• Reinitialize the unit for ARINC 429 operation.

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6.0

(cont’d)

ARINC

429 Alti-

tude Test(cont’d)

On DATATRAC 200:

• Set XMT to ON

• Setup screen ------>

L bl SI 2 9- He x R CV -11 S M P MS EC>> NO DATA RECEIVED

L bl SI 29 -H EX XM T- 11 S M P MS EC031 01 55980 00 1 100203 01 20000 11 1 100

On test panel:

• Set POWER to ON

• EXT STBY to OPR

• Be sure REP ALT switch is at PA

POWER indicator comes on immediately and after a

few seconds the XFEED OUT lamp turns on. The ATC-

601 REPLY lamp indicates that UUT is responding to

interrogations.





XMT word. See note 1 under step 1.2 above.)

DATATRAC 200 RCV screen shows:------->

L bl SI 29 -H EX RC V- 11 S M P MS RC031 01 559A0 11 1 0200203 01 20000 11 1 0200350 01 00000 11 1 0200

(ignore any other displayed labels, and the order is not

important)

6.1 ARINC

Altitude

Control

Disc-retes

Tests

On the test panel:


is set to SEL.




On the test panel:



Note: At this point the UUT is configured to report

altitude data from port B. There is none so the display

blanks.

On the test panel:



jack to the ALTERNATE DIGITAL ALTI-

TUDE SOURCE jack.




On the test panel:





switchable.

On the test panel:


CTL


Note: This switches the UUT to the altitude data sup-plied on the control port.

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6.1

(cont’d)

ARINC

Alltitude

ControlDisc-retes

Tests

(cont’d)

On the test panel:


the ALTERNATE DIGITAL ALTITUDESOURCE jack. (Wait about 5 seconds)


Note: This verifies the previous step; that altitude isbeing drawn from the control port; all other sources are

now disconnected.

On test panel:


SEL.



switchable.

On test panel:



SOURCE jack.


blanked.

On test panel:




Note: This enables the automatic altitude port select

feature and verifies that the UUT switches to alternate

port B even though port A is selected (REP ALT at PA).

On test panel:

• Set AUTO ALT switch to OFF.


Notice that ATC-601 altitude display blanks.

Note: This verifies that the AUTO ALT discrete is

switchable.

On the DATATRAC:

• Set the XMT label 031 word to

-------->

L bl SI 29 -H EX XMT -1 1 S M P MS RC031 01 55988 00 1 100




failed, suspect a problem with the Reporting AltitudeSelect discrete. If both tests failed, suspect a problem

with the altitude data receivers.

On test panel:



On DATATRAC 200:

• Set the XMT label 031 word to

--------->

L bl SI 29 -H EX XMT -1 1 S M P MS RC031 01 55980 00 1 100

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The remainder of the step is optional. Testing for various digital altitude inputs is primarily software verification and therefore

unnecessary. If the UUT responds to one altitude word input it will likely respond to all.

If you wish, you can set the XMT label 203 data field bits 12 through 28 to any combination of 1 and 0. The RCV label 203word data field will follow the XMT word exactly while the ATC-601, set to the ATCRBS REPLY TEST mode, will show the altitude

to the nearest 100 feet. When set to the MODE UF0 TEST, the ATC-601 displays altitude to the nearest 25 feet. The label

203 bit values are shown in note 2 following step 1.2.








In the XMT label 203 data word, set all noted bits to 1. You should see your selected altitude, to the nearest 100 feet,

displayed on the ATC-601.

7.0 ARING

575 Alti-

tude Test

On test panel:



On DATATRAC 200:

• Set screen ------>

LBL SI 29-HEX RCV-11 SM P MSEC>> NO DATA RECEIVED

LBL SI 29-HEX XMT-11 SM P MSEC031 01 55980 00 1 100203 01 10000 00 1 100

On test panel:

• Connect parallel control cable to PRI-

MARY DIGITAL ALTITUDE SOURCE

jack.



On ATC-601:

• Select ATCRBS REPLY TEST and


ATC-601 screen -------->




On test panel:


ARINC 575

On DATATRAC:

• Set XMT label 203 word

-------->

(just change the SM to 00)

LBL SI 29-HEX RCV-11 SM P MSEC031 01 55980 00 1 0100203 01 10000 00 1 0200


(lines 2-4 are irrelavent)

CODE=5263 ALT=16,400 FT [3230]***** TEST RUNNING *****

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7.0

(con-

t’d)

ARINC

575 Alti-

tude Test(cont’d)

DATATRAC screen ---------> LBL SI 29-HEX RCV-11 SM P MSEC203 01 10000 11 1 100

(ignore any other displayed words)LBL SI 29-HEX XMT-11 SM P MSEC031 01 55980 00 1 100203 01 20000 00 1 100

In addition to testing the altitude type select discrete, this test illustrates the differences between

ARINC 429 and ARINC 575 data. Notice that the msb in the RCV label 203 word (above) are offset

by one bit from the XMT label 203 word and the SSM code is 11 as opposed to the 00 in the XMT word.

In ARINC 575, the LSB is bit 13; in ARINC 429 the LSB is bit 12. In ARINC 575, bits 30 and 31

determine the sign; 00 being positive.

Notice also, that the altitude displayed on the ATC-601 corresponds to the code in the RCV word; not

the XMT word. This is also due to the UUT being configured for ARINC 575 and thus the bit values

are offset by 1 bit position which has the effect of changing the altitude by a factor of 1/2.

On test panel:


ARINC 429On DATATRAC:

• Set XMT label 203 word ---->


(Set SM to 11) ATC-601 screen:** ATCRBS REPLY TEST **



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8.0 Mode S

Address

Disc-retesTest

On the test panel:



On ATC-601:



Press RUN to start

On ATC 601:

• Press RUN


** M ODE S A LL C AL L T ES T - P AS SE D * * ALL CALL ADDRESS = FFFFFE [77777776]

T AI L N UMB ER =


The remainder of this step will require a few minutes because of the delay involved in cycling power

between each switch setting.

On test panel:



an octal digit 6.




address:


On test panel:



an octal digit 4.




address:

ALL CALL ADDRESS = 924924 [44444444]

On test panel:



an octal digit 0, except the eighth triad

which is set to 1.• Set POWER switch ON.



address:

ALL CALL ADDRESS = 000001 [00000001]

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9.0 TCAS /

NO TCAS

DiscreteSelect

and

TCAS

Bus Test

On test panel:


On DATATRAC 200:

• Set XMT words as shown ----->:


ATC-601 is not needed for this test but can be left on.

On test panel:


After data appears on the RCV display,

press RCV and then INC to scroll the

words so that you can see the 350 word.

After a few seconds the RCV portion of the DATATRAC

200 screen shows:

LBL SI 29-HEX RCV-11 SM P MSEC350 01 00000 11 1 0200

On test panel:


• Set TCAS/NO TCAS switch to TCAS

On DATATRAC 200:


On test panel:


After a few seconds the RCV portion of the DATATRAC

200 screen shows: (use INC key to scroll words)


Refer to paragraph 5.7.2 for a more detailed discussion. The 45980 display translates into a

diagnostic B3 which is interpreted: TCAS Bus Inactive. This verifies that the discrete properly

configures the unit for operation with a TCAS. However, no TCAS data is being supplied in this step,

therefore, the unit declares a B3 diagnostic.

TCAS

Bus Test,

XPDR to

TCAS

Connect the DATATRAC RCV to the

TCAS OUT jack. Verify that the data

word labels are detectable as shown -----

--->.

Note: Except for the diagnostic code inthe label 350 data word, the data content

is not important. It is quite likely that the

data will be different. The presence of

the data word labels shown verifies that

the TCAS data bus output is active and

appears to be normal.

LBL SI 29-HEX RCV-11 SM P MSEC275 00 00000 00 1 0150276 10 07C00 00 1 0150350 01 45980 11 1 0150

Notice the higher speed. Other labels may also be

present.

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9.0

(cont’d)

TCAS to

XPDR

Bus Test

Note: In this step you need the capability of transmitting data to two separate input ports simulta-

neously and at different speeds; the 031 control word must be low speed (12.5-kbps) while the

TCAS label 274 data word must be high speed (100-kbps). All DATATRAC instruments, as well asthe JC Air 429E, can transmit at either of these speeds but only the DATATRAC 400 can do so on

two separate ports simultaneously. Otherwise, you will need two simulators. If you do not have this

capability, you may not be able to verify the integrity of the TCAS bus input port.

If you are using a DATATRAC 400, or

have access to a second bus simulator,

connect your second transmitter port or

data bus simulator to the TCAS IN and

setup as shown -------->:

LBL SI 29-HEX RCV-11 SM P MSEC274 00 C0000 00 1 0100

Note: Be sure to set the higher speed.

On bus reader RCV (1) display:




diagnostic B3.



Note: This verifies that the unit is able to receognize avalid TCAS label 274 word and declare that by remov-

ing the B3 diagnostic code.

On the bus reader:

Set the XMT (2) word to OFF


returns.

Note: Disconnect XMT (2) from the

TCAS IN jack and CONNECT IT TO THE

PRIMARY DIGITAL CONTROL.

Reconnect RCV to the DATA BUS

OUTPUT port.

Final step

in this

test, all

setups

On test panel:



TCASOn DATATRAC 200:


On test panel:


After a few seconds, the original 350 word returns:-----------------RCV--(ALL)---12.5 KHzLbl SDI 32-Hex Data-1 SSM Par msec350 01 00 00 01 17 11 1 0200

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Using the DATATRAC 200 Databus Analyzer (Cont) .


10.0 Side 1/

Side 2

DiscreteTest

On test panel:



On DATATRAC 200:

• Same setup as in step 1.1.

On ATC-601:


------>




On test panel:







On test panel:



(wait a few seconds, then)


Notice that UUT does not reply (X FEED OUT lamp and



Note: UUT does not respond because the SI and side


Note: If you do not allow sufficient time for the CPU to

power down, it may not recognize the power interruption

and fail to re-initialize properly. The SIDE 1/2 strap is

one of several that is not monitored except at initial-

ization. Therefore, if this test fails, cycle power again

but allow more time between power-off and power-on.

On DATATRAC 200:

• On XMT, label 031 word, set the SI to10 and press INC



Note: UUT responds because SI and side strapping

agrees.

On DATATRAC 200:

• On XMT, label 031 word, set SI to 01

and press INC.



On test panel:



(wait a few seconds)



lamps light and the ATC-601 shows that the UUT is

replying.

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11.0 AIR/

GND

DiscreteTest

On test panel:



On DATATRAC 200:

• Same setup as for step 1.1.

On ATC-601:

• Set for MODE S UF4 TEST screen

-------->




On test panel:

• Set EXT STBY switch OPR

• Set AIR/GND switch AIR





DF 4 FS=0 DR=00 UM=00 AC=32,775 FT

ADDRESS=000001


Note: Initially the screen may show FS=2 for about 2


On test panel:








On test panel:



again shows 0.

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12.0 DL ANT/

SGL ANT

DiscreteTest

(TDR-94D

only)

On test panel:


On DATATRAC 200:



screen ----->


top antenna port.



On test panel:


ANT


You can watch the PERIOD display for a

time. After PASSED appears, press

RUN/STOP to stop the test.


note below.

* * SQ UI TT ER T ES T - P ASS ED * *PERIOD = 2.00 SECONDSTAIL NUMBER =SQUITTER ADDRESS= [ ]



On test panel:



ANT


After FAILED (or PASSED) appears, press



** S QU IT TE R T ES T - F AI LE D **PERIOD = SECONDSTAIL NUMBER =SQUITTER ADDRESS= [ ]





indicates PASSED, recheck all switch settings, or suspect

a problem with the SGL/DL ANT select strap. It should

not pass.

On test panel:


On ATC-601:



antenna connector


antenna connector


connector

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12.0 DL ANT

/SGL

ANT Dis-crete Test

(cont’d)

(TDR-94D

only)

On test panel:


On ATC-601:


• After PASSED appears, press RUN/STOP

to stop the test.

After 15 to 20 seconds, the ATC-601 screen shows:

See note below.

* * S QU ITT ER T ES T - P AS SE D * *PERIOD = 1.00 SECONDSTAIL NUMBER =SQUITTER ADDRESS= [ ]


On test panel:



ANT


• After PASSED appears, press RUN/STOP

to stop the test.

After 15 to 20 seconds, the ATC-601 screen shows:

See note below.




operation and the ATC-601 is monitoring the top or the bottom antenna port, the value can vary from

1.6 to 2.4. When the UUT is set for single antenna operation there should be no transmission from

the top antenna port and the transmission PERIOD from the bottom antenna port can vary from 0.6 to

1.4.

13.0 Burst

Tune and

Cross-

Feed In

Discrete

Test

On test panel:


• CONTROL DATA PORT SEL:

PB

On DATATRAC 200:


On ATC-601, set for ATCRBS REPLY

TEST screen ----->

If necessary, reconnect ATC-601 to top

antenna connector, with terminator on

bottom antenna connector.


(lines 2-4 are irrelevant)CODE= ALT= [ ]***** TEST RUNNING *****

On test panel:





On test panel:



On DATATRAC 200:

• Set XMT to OFF

Note: The easiest method of interruptingthe data input is simply to disconnect it

from the test panel.

Notice that the X FEED OUT and ATC-601 REPLY

lamps turns off (X FEED IN stays on).

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13.0

(con-

t’d)

Burst

Tune and

Cross-Feed In

Discrete

Test

(cont’d)

On DATATRAC 200:

• Set XMT to ON (reconnect the control

input)


are lit.

On test panel:

• Set XFEED switch to OUT.

• Set BURST switch to BURST

Notice that XFEED IN lamp turns off and that UUT

replies (X FEED OUT and REPLY lamps turn on).

On test panel:

• Disconnect the DATATRAC XMT input

from the test panel.

Notice that UUT continues to reply (X

FEED OUT and REPLY lamps stay on).

On DATATRAC 200:

• Set BURST switch to OFF



On test panel:

• Set BURST switch to BURST

Notice that UUT does not reply (X FEED OUT and

REPLY lamps remain off).

On test panel:• Reconnect the DATATRAC XMT to the

test panel

Notice that UUT replies (X FEED OUT and REPLYlamps turn on).

On test panel:

• Set BURST switch to OFF

14.0 Output

Port Dis-

crete Test

On test panel:



On DATATRAC 200:

• Set for the same screen as for test 1.1

On ATC-601, set for ATCRBS REPLY

TEST screen ----->




On test panel:



the ATC-601 REPLY lamps light indicating that the unit

is replying. The ATC-601 screen data indicates

PASSED.

On test panel:


ARINC 429 PORT B




On test panel:


ARINC 429 PORT A

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15.0 Control

Data

Input PortSelect

Discrete

Test

On test panel:




PORT PA

On DATATRAC 200:


On ATC-601, set for ATCRBS REPLY TEST

screen ----->




On test panel:





On test panel:


to ARINC PORT PB


FEED OUTand REPLY lights are on and ATC-601 dis-

play does not change.

On test panel:


to ARINC PORT PC




16.0 Manual

STBY

Discrete

Test

On test panel:




On DATATRAC 200:


On ATC-601:


screen ---------->




On test panel:






On test panel:




note below.

On test panel:



lamps light almost immediately and ATC-601 indicates

PASSED.

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17.0 Max Air-

speed

Test

On test panel:


• ALT TYPE SELECT: ARINC 429• Be sure that all three MAX AIRSPEED switches are set to OFF (opposite of SEL).

On DATATRAC 200:


(The DATATRAC is used here only for

tuning data.)

On ATC-601:

• Set for MODE S UF0 TEST screen ------>




On test panel:




unit is replying.





shown in the following list. Cycle power between each switch change. Allow about 2 or 3 seconds

OFF time and about 5 seconds for processor initialization and ATC-601 response time between each

switch setting.

MAX AIRSPEED SWITCH RI VALUE

BIT 15 BIT 16 BIT 17

OFF OFF OFF 8

SEL OFF OFF 9

OFF SEL OFF A

SEL SEL OFF B

OFF OFF SEL C

SEL OFF SEL D

OFF SEL SEL E



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18.0 Ext Sup-

pression

Test

On test panel:


On DATATRAC 200:

• Same setup as for test 1.1.

On ATC-601:


->














pulses at about 1 transmission every 2 sec. Of particu-

lar importance, however, is that the channel A (sup-

pression) pulse is about 30 µs long during ATCRBS



bracket the squitter transmission. The squitter trans-

mission is a DF11 reply about 72 µs long.

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19.0 ADLP

Select,

DiscreteStrap

Test

On test panel:


ADLP.

On DATATRAC 200:


DATATRAC RCV screen ------>



operating.


On test panel:




set to A/B.






functional.

On test panel:











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20.0 Remote

IDENT

DiscreteTest

On test panel:


On DATATRAC 200:


On ATC-601:





On test panel:


switch.

On DATATRAC 200:

• Note RCV screen ----->:


|<----Ident bit


the switch is being pressed. This verifies that the dis-

crete input is functional.

On ATC-601:• Notice the ID display. ID should dis-

play for about 18 seconds.

** ATCRBS REPLY TEST **(lines 2-4 are irrelevant)CODE=ID5263 ALT= 32,800 FT [1344]


On Datatrac 200:

• Set the label 031 XMT word:

LBL SI 29-HEX XMT-11 SM P MSEC031 00 55984 00 1 100

On DATATRAC RCV and on ATC-601: You should see the same displays as immediately




On Datatrac 200:

• Set the label 031 XMT word:

LBL SI 29-HEX XMT-11 SM P MSEC031 00 55980 00 1 100

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On DATATRAC 200:


On ATC-601:


---------->




On test panel:





On DATATRAC 200:

screen shows: --------->

LBL SI 29-HEX RCV-11 SM P MSEC

031 01 559A0 11 1 0200203 01 00000 11 1 0200350 01 00000 11 1 0200

(You may need to press INC to display all three labels.)

In the next few steps, watch the

DATATRAC RCV screen carefully.

On the test panel:



After a few seconds, notice that the DATATRAC and

ATC-601 screens do not change. (The test panel TEST

lamp lights while you hold the switch but otherwise

there is no change.)

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21.0 Self Test

(cont’d)

On test panel:




for about 1 s





panel.

On the DATATRAC 200, press RCV

(either once or twice) to return to the

setup screen, followed by ENT, to clear

the screen of any extraneous labels.

Self-test Displays:






On the DATATRAC, notice that the SM’s change to 10

and then back to 11. This instrument has a tendency to

retain superceded data words, therefore, you may need

to clear the screen repeatedly to be sure that you are

viewing current data. You should try to be especially



test sequence.

On the test panel:


OFF.


for about 1 s.


not appear..



On the test panel:


ON.




for about 1 s.


not appear..




recognize the change in the AIR/GND discrete. If you press the SELF TEST switch in less thanabout 3 seconds of setting the AIR/GND switch to AIR, the unit may execute self-test as though it


On the test panel:


ON.



for about 1 s.

Notice the self-test displays as described above reap-

pear.




assurance that the unit is operational. However, this test does not satisfy the requirements of a

Detailed Performance Test which must be performed after any repair operation.

Turn off all power, disconnect the equipment, and return it to its normal storage location. Return theUUT to its original shipping container, or equivalent, if it is to remain in storage. Otherwise, prepare


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5 .4 .5 .1 1 P r o c ed u r es u s i n g t h e J c A I R 4 2 9 E T r a n s m i t t er / R ec ei v e r

Table 5-13. Acceptance Test Procedures,

Using the JcAIR 429E Transmitter/Receiver


1.0 Setup Note: If you are using a Test Panel built according to instruction provided in a previous edition of thismanual, it may be necessary to upgrade the panel. Refer to paragraph 5-8.

• If not already done, connect equipment as shown in figure 5-2 using cables shown in figure 5-9.

• TX to test panel DIGITAL CONTROL port,

• Parallel connect TX to test panel PRIMARY DIGITAL ALTITUDE PORT,

• RX to test panel DATA BUS READER port.


• Connect an rf termination to the TOP antenna port (TDR-94D only).


• Preset the switches as shown in paragraph 5.4.5.6 above. Be sure POWER switch is OFF and EXT


On test panel, set the MODE S ADDRESS switches to any combination except all OFF or all to SEL.

If all switches are set OFF or all set SEL, a diagnostic code FF will result.

1.1 Setup Turn the JcAIR 429E on and set the TX 1

and TX 2 screens ----->

031 01 1566C1 00203 01 640001 11

Turn on

TDR-94/94D

On test panel:




Monitor current.





transmitting.

Setup

(power-up)



See Note in next cell below.



Press RUN to start

1.2 ARINC 429

tuning test

On the ATC-601, press RUN

ATC-601 screen --------->

Note: When power is applied and proper

control data is supplied, the TDR-94/94D

should turn on the XFEED OUT lamp

almost immediately. The FAULT MON

lamp may be off for a few seconds and

then turn on. A lighted FAULT MON lamp

should generally be seen as a no-fault

indication. See table 109.

UUT responds to interrogations as indicated by a lighted




(lines 2-4 are irrelevant)C OD E= 52 63 A LT =32 ,8 00 F T [ 13 44]



To change the ALTITUDE, see note 2 below.

The JcAIR 429E RX displays show

--------->

203 01 E40000 11031 01 F56681 11350 01 600001 11


test. See Note 3 below.

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Using the JcAIR 429E Transmitter/Receiver (Cont).


Note 1. You can change t he (octa l) CODE=XXXX display by changing data bits 18 through 29 in the label 031 data word ( TX

field of the JcAIR 429E) as follows:

ATC-601 digit: First Second Third Fourth

Bit: 32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17

Data: Par SSM |<-----Data -------> ----->| Pad

Hex value: 8 4 2 1 8 4 2 1 8 4 2 1 8 4 2 1

JcAIR 429E (Hex): | 1 | | 5 | | 6 | | 6 |

Binary: 0 0 0 1 0 1 0 1 0 1 1 0 0 1 1

Octal value: 4 2 1 4 2 1 4 2 1 4 2 1

Produces CODE: 5 2 6 3

Bits 11 through 17, of the label 031 control word, are assigned the following functions:

J cAIR 429E (Hex) bits: 5th 6th

Bit: 16 15 14 13 12 11 10 9

Bit values: 8 4 2 1 8 4 2 1

| | | | Pad | |<- |<--SDI

Assignment: Pad Pad | | |<--Altitude reporting, 1 = OFF| |<--Ident, 1 = ON

|<--Altitude port select, 1 = B

Note 2: You can set the TX label 203 data field bits 12 through 28 to any combination of 1 and 0. The RCV 1 label 203 word

data field will reflect the TX word while the ATC-601 will show the altitude to the nearest 100 feet. The label 203 word data bit

values are as follows:

JcAIR 429E digit *: lst | 2nd | | 3rd |

Hex value: 8 4 2 1 8 4 2 1

Bit: 29 28 27 26 25 24 23 22 21

Alt value:(sign bit; 0 = +) 65536 32768 16384 8192 4096 2048 1024 512

(in feet)

JcAIR 429E digit *: | 4th | | 5th | | 6th |

Hex value: 8 4 2 1 8 4 2 1 8 4 2 1

Bit: 20 19 18 17 16 15 14 13 12 11 10 09

Alt value 256 128 64 32 16 8 4 2 1 ** ** **

(in feet)

Determine the altitude by totaling the bit values of all bits set to 1.

* The left-most Hex Data bit (bit 1) is determined by the parity bit 32, the SSM bits 31 and 30, and sign bit 29. Since bit 29

must always be a 0, this Hex bit must always be an odd number. **= Not used

Note 3: You may see a label 371 data word. This is the ARINC 429 Specific Equipment Identification word which is

structured the same as other ARINC 429 words but conveys the following information:

Bits 11 through 18 identify the equipment type. The code for ATC transponders is 18 therefore bits 14 and 15 are 1; the

others are 0. Bits 19 through 24 convey a binary code identifying the equipment manufacturer. Collins’ is 6. Therefore bits

20 and 21 are 1; all others are 0. Bits 24 through 29 are reserved for purposes to be defined.

When ARINC 572 altitude data is active, you will see a label 200 data word. This word reflects the ARINC 572 (Gillham code)

altitude data. This word is structured the same as other ARINC 429 words, except bits 9 and 10 are part of the data field; i.e.,

there is no SDI. Bits 9,10, and 11 reflect the D1, D2, and D4 code bits respectively. Bits 13, 14, and 15 reflect the C-bits,bits 17, 18, and 19 reflect the B-bits, and 21, 22, and 23 reflect the A-bits.

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2.0 Test set, Auto

Test

On ATC-601:


• P r es s AUTO TEST

• P r es s RUN t o s t a r t

Note: This test requires a few

seconds to run. I t w il l stop

automatical ly.


On test panel :

• Set E XT STBY sw itch to STBY

• S e t P O WE R s w i t ch O F F

On UUT:

• Move the test set r f cable to the UUT top ant enna connector and t he r f termination to the

bottom.

On test panel :

• S e t P O WE R s w i t ch O N


On ATC-601:

• R e pe a t t h e AUTO TEST


Note. The AUTO TEST sequence will indicate FAILED even when certain tests result in a NO REPLY condition. The NO

REPLY conditions are the result of no ADLP (Airborne Data Link Processor) data in this setup. This same condition is likely

to occur when using the ATC-601 as a ramp tester when testing an installation not equipped with an ADLP. To verify that the

test can be seen as successful, proceed as follows:




Press RUN to start

(The FREQ, ERP, and MTL values can vary from UUT to UUT and to a lesser degree on UUT temperature.)


On the ATC-601, use the SELECT up arrow or down arrow key to scroll through the following list of tests performed; the





1.0 ** REPLY DELAY TEST - PASSED ** MODE S: 128.00 (±0.25) µs

ITM A: 128.00 (±0.25) µs

(All others): 3.00 (±0.50) µs

2.0 ** REPLY JITTER TEST - PASSED ** MODE S: =< 0.05 µs

ITM: = < 0.06 µs

(All others ): =< 0.1 µs



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4.0 ** SLS LEVEL TEST - PASSED ** UUT is interrogated with F2 (SLS) pulse at 9 dB below F1.UUT should reply to this interrogation. Then UUT is

interrogated with F2 equal to F1. UUT should not reply.

PASSED indicates correct response to both tests.



response.





reply.






9.0 * * M OD E S U F0 TE ST - P AS SE D * * UUT is interrogated with mode S UF0, verifying correct




10.0 * * M OD E S UF 4 TE ST - P AS SE D * * UUT is interrogated with UF4, verifying correct altitude as




11.0 * * M OD E S UF 5 TE ST - P AS SE D * * UUT is interrogated with UF5, verifying the correct ID code




12.0 * * M OD E S UF 11 TE ST - P AS SED * * UUT is interrogated with UF11, verifying correct address as





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NO. TEST NAME AND RESULT TEST SPECIFICATION / DESCRIIPTION

15.0 * * MO DE S UF 21 TES T - NO RE PLY * * UUT is interrogated with UF16, UF20, and UF21.These formats are all related to the airborne data link

function. This function has not been implemented.

The TDR-94/94D will not reply to these interrogation

formats. NO REPLY should not be seen as a failure.

16.0 ** SQUITTER TEST - PASSED ** When set for daul antenna operation, the TDR-94D

transmits a squitter pulse once each second, alternating

between top and bottom antenna ports. The ATC-601

verifies that one squitter pulse is received every 1.6 to

2.4 seconds. The test panel ANT SGL/DL switch must

be in the DL position. When set for single antenna

operation, or when testing a TDR-94, only the bottom

antenna port is used. In this case the ATC-601 verifies

that one squitter pulse is received every 0.6 to 1.4

seconds. When you change the ANT SGL/DL switch,you must cycle power to the UUT in order for it to take

effect. PASSED indicates a correct UUT response.


18.0 ** DIVERSITY TEST - PASSED ** ATC-601 monitors squitter pulses on active antenna

port (as in test 16) and then monitors for intervening

squitter pulses that are not greater than 20 dB below

the active squitter. This test will always fail when the

UUT is a TDR-94 (non diversity) because squitter is

transmitter every second on the same antenna port. If

you are testing a TDR-94D and the DL ANT/SGL ANT

switch is set to SGL ANT, the test will also fail because

this causes the unit to operate like a TDR-94. PASSED

indicates a correct response from a TDR-94D.

19.0 ** MTL DIFFERENCE TEST - PASSED ** ATC-601 verifies that the MTL difference between mode

a and mode c responses is < 1.0 dB. At this point,

another press of the arrow key will display the first item;

either 1.0 or 18.0, depending on which arrow was used.

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3.0 Power

output and

RcvrSensitivity

Test




On ATC-601:


• P r es s RUN to indicate TEST RUNNING ---

------>



Note: If necessary, press SELECT (or SLEW) to select Top Antenna. Be sure that the ATC-601 rf


On JcAIR 429E: set TX screen ---

--->

031 01 1566C1 00203 01 640001 11

On test panel:




shows ---->

On ATC-601:



Top dBm 55.7 -76.0 PASSED








On test panel:



• On TDR-94D mount:

Swap the rf cable connection and

termination on the UUT antenna ports.

(Rf cable to bottom port and termination

to top antenna port.)On test panel:



On ATC-601:


Wait a few seconds then press


You should see a similar display on the ATC-601

except this data is applicable to the top antenna port.

The data can be slightly different. See below for test




the ATC-601.




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3.0

(con-

t’d)

Power

output and

RcvrSensitivity

Test

(cont’d)



MTL: -73.0 (±4.0) dBm

The ATC-601 will indicate that the UUT has failed if the MTL is more than -77.0 dBm or less than -71

dBm. Collins prefers, however, that a failure should be reported only if the MTL is less than -71

dBm. Therefore, if you have a unit displaying an MTL of -77.1 or more, you should see that value as

acceptable. Obviously, an MTL indication approaching -80 dBm or more may be cause for














test evaluation:


50 16.99 46.99


100 20.00 50.00


150 21.76 51.76

200 23.01 53.01

250 23.98 53.98 Minimum di rect (on bench)

300 24.77 54.77

350 25.44 55.44

400 26.02 56.02

450 26.53 56.53


To convert milliwatts to dBm, or watts to dBW:

a. For calculators with log(10) (usually written log or LOG): P(dBW) = 10 x LOG(P).

b. For calculators with log(e) (usually written ln or LN): P(dBW) = 10 x [LN(P) / LN(10)]

In both cases, P must be in watts. For dBm, P must be in milliwatts; for example:

450 watts = 450 000 milliwatts.

To convert from dBm to milliwatts or dBW to watts:

a. For calculators equipped with LOG : P = INVLOG (P(dBW) / 10)

b. For calculators equipped with LN : P = INVLN [(P(dBW) / 10) x 2.30259]

The result P will be in milliwatts if you use P (dBm) , or watts if you use P(dBW).

Most scientific calculators have both the LN (natural logarithm - base e) and the LOG (logarithm base

10) capabiliity. Likewise, most have an INV (inverse) function. Thus you must press INV and then

LN or LOG for the INVLN or INVLOG function.

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4.0 Gillham

Altitude

Test

On ATC-601: select




CODE= ALT= [ ]

Press RUN to start




• Set SOURCE SEL switch to SEL

On JcAIR 429E:

• Set TX screen ------>

031 01 1566C1 00

On test panel:

• Set POWER to OFF


Then set A4, C2, C4, and B4 to SEL.

• Set POWER to ON• Set EXT STBY switch to OPR

On ATC-601:

• Press RUN.



JcAIR 429E RCV 1 screen shows: ---------

----------->

203 01 E0B861 11031 01 F56681 11

(ignore any other labels)

ATC-601 Screen shows:

-------------------->


(lines 2-4 are irrelevant)CODE=5263 ALT=5900 FT [4460]



TX word. See note 1 under step 1.2 above)

At this step you are asked to toggle each of the ARINC 572 switches and verify the altitude display. You should also watchthe RX data word on the JcAIR 429E display. By cycling each switch between OFF and SEL you should see the ATC-601

display and the JcAIR 429E 203 data word change. If the displays do not change for a particular switch, this would indicate

either an open or a shorted code line. If the wrong altitude is shown, this would suggest that the code line is affecting another

line; i.e., causing two or more inputs to change simultaneously. In either case the UUT, the test panel, or the interconnecting

cable needs repair.



There is no serious need to verify the correctness of the RCV word provided the ATC-601 display is correct.

SWITCH DISPLAYED ALTITUDE SWITCH DISPLAYED ALT ITUDE


A1 (SEL) 23,600 FT [5460] B1 (SEL) 3,600 FT [4560]

A2 (SEL) 7,600 FT [6460] B2 (SEL) 5,600 FT [4660]

A4 (OFF) -400 FT (0460] B4 (OFF) 6,600 FT [4060]


C2 (OFF) 5,800 FT [4440] D4 (SEL) 55,600 FT [4464]

For additional information on Gillham code structure, refer to paragraph 5.7 below.

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5.0 CSDB

tuningtest

This test cannot be performed using a JcAIR 429E because these instruments are not capable of

transmitting or receiver CSDB data. However, as an acceptable alternative, you can use a CTL-92/92A, connected to the test panel using the cable shown in figure 907.

• Turn power off and connect CTL-92/92A to test panel. Be sure CTL-92/92A mode knob is set to

OFF.

• Disconnect the JCAIR 429E from the test panel.

• Turn power on and set the CTL-92/92A mode knob to ALT.

On the CTL:

• Set the CTL-92/92A to 5263 or any

desired ident code.

On test panel:

• Set CONTROL DATA SELECT to

CSDB


PORT 1• Set ALT TYPE SELECT to CSDB

• Set ARINC 572 ALT IN to TO CTL

• Set SOURCE SELECT to CTL




The CODE 5263 depends on your selection on the CTL-

92/92A code select knobs. See note 1 under step 1.2

above. The ALT display depends on the altitude

selection on the test panel ARINC 572 ALT IN switches.

Be sure that the ACT display, on the CTL-92/92A does

not flash. A flashing ACT indicates that the control

feedback label 1F data, from the TDR, does not agree

with the CLT-92/92A output label 1E data to the TDR.

Only one of the two data CTL input ports is being used;

pins U/V.

On the test panel:


PORT 2

Be sure that the ACT display, on the CTL-92/92A, does

not flash. A flashing ACT at either port selection

indicates that output port has failed. If both ports flash,

there may be a problem with the test panel wiring or the

CTL input.

5.1 CSDB

altitude

test

In this altitude test configuration, Gillham altitude data is being supplied to the CTL (ARINC 572 ALT

IN to CTL). The CTL converts this data to CSDB and supplies it to the TDR via the CSDB data

output port (only 1 port is used; pins S/R). The CSDB altitude data is being read on the control businput (SOURCE SELECT to CTL). You can verify this by setting the CTL mode switch to ON. If you

suspect a problem with the altitude data, check the following:

On the test panel:

• Set ARINC 572 ALT IN to TO TDR



The ATC-601 ALT display should be the same as

above since the ultimate source of altitude information

is the same in both tests. If it is different here, suspect

a problem with one or more of the altitude discrete

inputs to the CTL. If you encounter such a problem,

you can identify the defective discrete by returning

these three switches to the settings above and then

performing the ARINC 572 switching sequence shown

following step 4.0 above.

On test panel:

• Set power to OFF

• Disconnect the CTL-92/92A from the test panel

• Set CONTROL DATA SELECT - ARINC PORT to PA

• Set OUTPUT PORT SELECT to ARINC 429 PORT A

• Reconnect the JcAIR 429E from the test panel.

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6.0 ARINC

429Altitude

Test

On test panel:


• Set POWER switch to OFF• ALT TYPE SELECT: ARINC 429

• OUTPUT PORT SELECT: ARINC 429

PORT A

On JcAIR 429E:

• Set TX screen ------>

031 01 1566C1 00203 01 640001 11

On ATC-601: select

ATCRBS REPLY TEST and press RUN to

indicate TEST RUNNING --------->




On test panel:

• Set POWER to ON

• Set EXT STBY to OPR







TX word. See note 1 under step 1.2 above.)

JcAIR 429E RX screen shows:

------->

203 01 640001 11


6.1 ARINC

Altitude

Control

Disc-retes

Tests

On the test panel:


is set to SEL.




On the test panel:



Note: At this point the UUT is configured to reportaltitude data from port B. There is none so the display

blanks.

On the test panel:



jack to the ALTERNATE DIGITAL

ALTITUDE SOURCE jack.




On the test panel:





switchable.

On the test panel:• Set the SOURCE SELECT switch to

CTL


Note: This switches the UUT to the altitude data

supplied on the control port.

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6.1

(cont’d)

ARINC

Control

Disc-retesTests

(cont’d)

On the test panel:


the ALTERNATE DIGITAL ALTITUDESOURCE jack. (Wait about 5 seconds)


Note: This verifies the previous step; that altitude isbeing drawn from the control port; all other sources are

disconnected.

On JcAIR 429E:


SEL.



switchable.

On test panel:



SOURCE jack.


blanked.

On test panel:




Note: This enables the automatic altitude port select

feature and verifies that the UUT does switch to

alternate port B even though port A is the selected port.

On test panel:

• Set the AUTO ALT switch to OFF



Note: This verifies that the AUTO ALT discrete is

switchable.

On the JcAIR 429E:

• Set the TX label 031 word to

-------->

031 01 9566E1 00




failed, suspect a problem with the Reporting Altitude

Select discrete. If both tests failed, suspect a problemwith the altitude data receivers.

On test panel:



On JcAIR 429E:

• Set the TX label 031 word to:

--------->

031 01 1566C1 00

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The remainder of the step is optional. Testing for various digital altitude inputs is primarily software verification and therefore

unnecessary. If the UUT responds to one altitude word input it will likely respond to all.

If you wish, you can set the TX label 203 data field bits 12 through 28 to any combination of 1 and 0. The RCV 1 label 203word data field will follow the TX word exactly while the ATC-601, set to the ATCRBS REPLY TEST mode, will show the altitude

to the nearest 100 feet. When set to the MODE UF0 TEST, the ATC-601 displays altitude to the nearest 25 feet. The label

203 bit values are shown in note 2 following step 1.2.








In the TX label 203 data word, set all noted bits to 1. You should see your selected altitude, to the nearest 100 feet, displayed

on the ATC-601.

7.0 ARINC

575

Altitude

Test

On test panel:



On JcAIR 429E:

• Set screen ------>

031 01 1566C1 00203 01 640001 11

On test panel:

• Connect parallel control cable to


jack.



On ATC-601:• Select ATCRBS REPLY TEST and


ATC-601 screen -------->

** ATCRBS REPLY TEST **(lines 2-4 are irrelavent)CODE=5263 ALT=32,800 FT [1344]


On test panel:


ARINC 575

On JcAIR 429E:

• Set TX label 203 word -------->

(just change the SSM to 00)

203 01 040001 00




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7.0

(con-

t’d)

ARINC

575

AltitudeTest

(cont’d)

JcAIR 429E RX screen ---------> 203 01 620001 11

In addition to testing the altitude type select discrete, this test illustrates the differences betweenARINC 429 and ARINC 575 data. Notice that the second data bit in the RX label 203 word (above)

one-half the bit value of the corresponding bit in the TX label 203 word and the SSM code is 11 as

opposed to the 00 in the TX word. In ARINC 575, the LSB is bit 13; in ARINC 429 the LSB is bit 12.

In ARINC 575, bits 30 and 31 determine the sign; 00 being positive.

Notice also, that the altitude displayed on the ATC-601 corresponds to the code in the RX word; not

the TX word. This is also due to the UUT being configured for ARINC 575 and thus the bit values

are offset by 1 bit position which has the effect of changing the altitude by a factor of 1/2.

On test panel:


ARINC 429

On JcAIR 429E:

• Set TX label 203 word ---->

031 01 1566C1 00203 01 640001 11

ATC-601 screen:** ATCRBS REPLY TEST **



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8.0 Mode S

Address

DiscretesTest

On the test panel:



On ATC-601:



Press RUN to start

On ATC 601:

• Press RUN


** M ODE S A LL C AL L T ES T - P AS SE D * * ALL CALL ADDRESS = FFFFFE [77777776]

T AI L N UMB ER =


The remainder of this step should be seen as optional unless you have reason to suspect a failure in

one or more of the address discrete lines. The procedure will require a few minutes because of the

delay involved in cycling power between each switch setting.

On test panel:



an octal digit 6.




address:


On test panel:



an octal digit 4.




address:

ALL CALL ADDRESS = 924924 [44444444]

On test panel:



an octal digit 0, except the eighth triadwhich is set to 1.




address:

ALL CALL ADDRESS = 000001 [00000001]

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9.0

(cont’d)

TCAS to

XPDR

Bus Test

Note: In this step you need the capability of transmitting data to two separate input ports

simultaneously and at different speeds; the 031 control word must be low speed (12.5-kbps) while

the TCAS label 274 data words must be high speed (100-kbps). All JcAIR 429E instruments cantransmit at either of these speeds but not on two separate ports simultaneously. If you do not have

this capability, you may not be able to verify the integrity of the TCAS bus input port.

If you have access to a second JcAIR

429E, connect your second transmitter

port or data bus simulator to the TCAS

IN and setup as shown -------->:

274 00 180000 00

Note: Be sure to set for high speed.

On bus reader RCV display:




diagnostic B3.


350 01 680001 11


On the bus reader:

Set the XMT 2 word to OFF


returns.

Note: Disconnect XMT 2 from the TCAS

IN jack and reconnect RCV 1 to the

DATA BUS OUTPUT port.

Final step

in this

test, all

setups

On test panel:



TCAS

On test panel:


After a few seconds, the original 350 word returns:350 01 000001 11

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10.0 Side 1/

Side 2

DiscreteTest

On test panel:



On JcAIR 429E:


On ATC-601:


->




On test panel:







On test panel:




Note that unit does not reply (X FEED OUT lamp and



Note: UUT does not respond because the SDI and side


Note: Be sure to allow adequate time for the CPU to

reinitialize properly between power off and power on.

The SIDE 1/2 strap is one of several that are monitored

only at processor initialization. Therefore, if this tests

fails, cycle power again but allow more time between

power off and power on.

On JcAIR 429E:

• On TX, label 031 word, set the SDI to10



Note: UUT responds because the SDI and side

strapping agree.

On JcAIR 429E:

• On TX, label 031 word, set SDI to 01.



On test panel:





lamps light and the ATC-601 shows that the UUT is

replying.

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11.0 AIR/

GND

DiscreteTest

On test panel:


• TDR ALT SOURCE: EXT DIRECT• ALT TYPE SELECT: ARINC 429

On JcAIR 429E:


On ATC-601:

• Set for MODE S UF4 TEST screen ----->




On test panel:








Note: Initially the screen will show FS=2 for about 2


On test panel:








On test panel:



again shows 0.

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12.0 DL ANT/

SGL ANT

DiscreteTest

(TDR-94D

only)

On test panel:


On JcAIR 429E:



screen ----->


top antenna port.



On test panel:


ANT


Watch the PERIOD display for a time.

You will notice it changing somewhat butit should remain at or near 2 seconds.


note below.

* * SQ UI TT ER T ES T - P ASS ED * *PERIOD = 2.00 SECONDSTAIL NUMBER =SQUITTER ADDRESS= [ ]



On test panel:



ANT



** S QU IT TE R T ES T - F AI LE D **PERIOD = SECONDSTAIL NUMBER =SQUITTER ADDRESS= [ ]





indicates PASSED, recheck all switch settings or

suspect a problem with the SGL/DL ANT select strap.It should not pass.

On test panel:


On ATC-601:



antenna connector


antenna connector


connector

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12.0

(cont’d)

DL ANT

/SGL

ANTDiscrete

Test

(cont’d)

(TDR-94D

only)

On test panel:


On ATC-601:



note below.



On test panel:



ANT



note below.




operation and the ATC-601 is monitoring the top or the bottom antenna port, the value can vary from1.6 to 2.4. When the TDR-94D is set for single antenna operation, or the UUT is a TDR-94, there is

no transmission from the top antenna port and and the transmission PERIOD from the bottom

antenna port can vary from 0.6 to 1.4.

13.0 Burst

Tune and

Cross-

Feed In

DiscreteT

est


screen ----->

If necessary, reconnect ATC-601 to

bottom antenna connector, with

terminator on top (TDR-94D only)

connector.



On JcAIR 429E:


On test panel:• CONTROL DATA SELECT: PA



• Be sure that X FEED IN/OUT switch is

set to OUT

• Be sure that BURST TUNE switch is

set to OFF.

On test panel:





On test panel:



On JcAIR 429E:• Set TX to OFF

(The easiest way to turn TX off is to

disconnect it from the test panel)

Notice that the X FEED OUT and ATC-601 REPLYlamps turns off (X FEED IN stays on).

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13.0

(cont’d)

Burst

Tune and

Cross-Feed In

Discrete

Test

(cont’d)

On JcAIR 429E:

• Set TX to ON


are lighted.

On test panel:

• Set X FEED IN/OUT switch to OUT

• Set BURST TUNE to ON

On JcAIR 429E:

• Set TX to OFF

Notice that UUT continues to reply. Watch the unit for

a few seconds. (The X FEED IN lamp extinguishes

because the switch turns it off.)

On test panel:




On test panel:

• Set BURST TUNE to ON

Notice that UUT does not reply (X

FEED OUT and REPLY lamps do not light).

On J cAIR 429E:

• S e t TX to ON

Notice that UUT replys (X FEED OUT and REPLY lamps

are on).

On test panel:

• Set BURST TUNE to OFFOn JcAIR 429E: • Set TX to OFF


REPLY lamps are off).

On JcAIR 429E: • Set TX to ON X FEED OUT lamp and the REPLY lamp turns on again.

On test panel:


• Set BURST TUNE switch to ON.

• Set TX to ON

X FEED OUT lamp flashes .

14.0 Output

Port

Discrete

Test

On test panel:

• Set BURST TUNE to OFF


• Set X FEED IN/OUT to OUT


• CONTROL DATA SEL: PA


On JcAIR 429E:

• The same as STEP 1.1

On test panel:


Both X FEED OUT and REPLY lamps are on.

JcAIR 429E RCV screen -----> 031 01 F56681 11

Note: Be sure that the JcAIR screen flashes somewhat.

This indicates that the screen is being updated. A non-

flashing screen usually indicates that obsolete data is

being displayed.

On ATC-601, set for SQUITTER TEST After a few seconds, the ATC-601 screen data indicates

PASSED.

On test panel:• Set OUTPUT PORT SELECT switch to

ARINC 429 PORT B

Notice that there is no change in the test result; XFEED OUT and REPLY lights are on and JCAIR screen

does not change.

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15.0 Control

Data

Input PortSelect

Discrete

Test

On test panel:




PORT PA

On JcAIR 429E:



screen ----->



On test panel:





On test panel:


to ARINC PORT PB


FEED OUTand REPLY lights are on and ATC-601


On test panel:


to ARINC PORT PC




16.0 Manual

STBY

Discrete

Test

On test panel:




On JcAIR 429E:• Same setup as for STEP 1.1.

On ATC-601:


---------->




On test panel:






On test panel:




note below.

On test panel:• Set EXT STBY switch to OPR

Note that X FEED OUT lamp and ATC-601 REPLYlamps light almost immediately and ATC-601 indicates

PASSED.

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17.0 Max Air-

speed

Test

On test panel:


• ALT TYPE SELECT: ARINC 429• Be sure that all three MAX AIRSPEED switches are set to OFF.

On JcAIR 429E:


(The JcAIR 429E is used here only for

tuning data.)

On ATC-601:

• Set for MODE S UF0 TEST screen --->




On test panel:




unit is replying.





shown in the following list. Cycle power and allow about 2 or 3 seconds of OFF time and about 5

seconds for processor initialization and ATC-601 response time between each switch setting.

MAX AIRSPEED SWITCH RI VALUEBIT 15 BIT 16 BIT 17

OFF OFF OFF 8SEL OFF OFF 9OFF SEL OFF A SEL SEL OFF BOFF OFF SEL CSEL OFF SEL DOFF SEL SEL E



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18.0 Ext Sup-

pression

Test

On test panel:


On JcAIR 429E:


On ATC-601:

• Set for ATCRBS REPLY TEST screen -->














pulses at about 1 transmission every 2 sec. Of

particular importance, however, is that the channel A

(suppression) pulse is about 30 µs long during ATCRBS



bracket the squitter transmission. The squitter

transmission is a DF11 reply about 72 µs long.

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19.0 ADLP

Select,

DiscreteStrap

Test

On test panel:


ADLP.

On JcAIR 429E:


JcAIR 429E RX screen ------>



operating.

350 01 600001 11

On test panel:




set to A/B.



350 01 64A201 11

|<---diagnostic code A2



functional. The 4 reflects bit 27 in the data word whichis also set indicating an ADLP bus failure.

On test panel:





350 01 600001 11







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20.0 Remote

IDENT

DiscreteTest

On test panel:


On JcAIR 429E:


On ATC-601:





On test panel:

• Set the POWER switch to ON

• Set the EXT STBY switch to OPR


switch.

On JcAIR 429E:

• Notice RX screen ----->:

031 01 756691 11

|<----Ident bit


the switch is being pressed. This, together with the ID

display on the ATC-601, verifies that the REMOTE

IDENTdiscrete input is functional.

On ATC-601:

• Notice the ID display. ID should

display for about 18 seconds.


(lines 2-4 are irrelevant)CODE=ID5263 ALT= 32,800 FT [1344]


On JcAIR 429E:

• Set the label 031 TX word:

031 01 156691 00

On JcAIR 429E RX and on ATC-601

screens:

You should see the same displays as immediately




On JcAIR 429E:

• Set the label 031 TX word:

031 01 956681 00

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On JcAIR 429E:


On ATC-601:


---------->




On test panel:





On JcAIR 429E:

RX screen shows: --------->

031 01 F56681 11

203 01 640001 11350 01 600001 11

In the next few steps, watch the JcAIR

429E RX screen carefully.

On the test panel:



After a few seconds, notice that the ATC-601 screen

does not change The JcAIR 429E RX display may go

blank.

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21.0 Self Test

(cont’d)

On test panel:




for about 1 s





panel.

Self-test Displays:






On the JcAIR 429E notice that the SM changes to 10

and then back to 11.You should try to be especially



test sequence.

On the test panel:


OFF.• Press and hold the SELF TEST button

for about 1 s.


not appear..



On the test panel:


ON.




for about 1 s.


not appear..




recognize the change in the AIR/GND discrete. If you press the SELF TEST switch in less than

about 3 seconds of setting the AIR/GND switch to AIR, the unit may execute self-test as though it


On the test panel:


ON.



for about 1 s.

Notice the self-test displays as described above

reappear.




assurance that the unit is operational. However, this test does not satisfy the requirements of a Final

Performance Test which must be performed after any repair operation.

Turn off all power, disconnect the equipment, and return it to its normal storage location. Return the

UUT to its original shipping container, or equivalent, if it is to remain in storage. Otherwise, prepare


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5 .4 .5 .1 1. 1 J c A I R 4 29 E T r a n sm i t t er / R ec ei v er , O p er a t i n g I n s t r u c t i o n s

This para graph provides instructions tha t may be helpful

in operating the J cAIR 429E Transmitter /Receiver. It is

intended for those who may be unfamiliar with i ts

operation and may need some help.

If you a re familiar with the J cAIR 429E:

Set the TX 1 output to: 031 01 156681 00; this

produces an ATC code: 5236.

Set the TX 2 output to: 203 01 640000 11; this

produces an altitude: 32,800 ft.

These are the TX hex values used most often in theprocedures of Table 5-13.

Setup a nd Operating Instructions i f you a re unfamiliar with the operation of the J cAir 429E:

During the course of this procedure, do not t urn power off to the J cAIR 429E. All entered da ta is lost.

Prel iminary setup

Set: TX Parity to ODD

TX Speed to LO

RX Speed to LO

Display to Hex

TX label and word setup for this procedure

1. When screen shows: 0 RX LABELS, press TX/RX

2. Screen shows: 0 TX LABELS

3. Press ’up arrow’ key

4. Screen shows: TX 1 INACTIVE

5. Press EDIT/DEL

6. Screen shows a blinking cursor on an otherwise blank screen

7. Enter 031

8. Press ENT

9. Screen shows: 031 BCN ATC CODE

10. Press LAB/DAT

11. Screen shows: 031 00 000000 00

12. Press EDIT/DEL


14. Enter 6-digit Hex code as desired or 156681

15. Press ENT

16. Screen shows: 031 01 956681 00 (The parity bit causes the change from 1 to 9 in the first digit)

17. Press TX/RX until screen shows 1 TX LABELS18. Press ’up arrow’ until screen shows TX 2 INACTIVE

19. Press EDIT/DEL


21. Enter 203

22. Press ENT

23. Screen shows: 203 ALTITUDE

24. Press LAB/DAT

25. Screen shows: 203 00 000000 00

26. Press EDIT/DEL


28. Enter E40000

29. Press ENT

30. Screen shows: 203 01 E40000 11

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RX labels setup for this procedure:

Note: The procedures below may not be needed depending on the software version of the JcAIR 429E being used. The objective

of the test is to capture (trap) ARINC 429 labels 031, 203, and 350 words. Consult the JcAIR 429E Operator’s Manual for detailed

instructions if needed.

1. If the JcAIR 429E is not already on, turn POWER switch to ON

2. If necessary, press TX/RX until screen shows: 0 RX LABELS

3. Press TRAP


5. Enter 031

6. Press ENT

7. Screen shows: 031 SDI? _ (blinking cursor)

8. Enter 01

9. Press ENT

10. Screen shows: 0 RX LABELS

Note: This screen tends to blink slightly indicating that the display is being updated. If data is being received, the left digit will

increment (quite rapidly) to a maximum of 255 indicating the number of words that have been captured.

11. Press TRAP until screen again shows a blinking cursor

12. Repeat steps 3 through 11 but enter 203 at step 5. (At step 10, the display will show:

1 RX LABELS)13. Repeat steps 3 through 11 but enter 350 at step 5. (At step 10, the display will show:

2 RX LABELS)

14. Press ENT twice.

To change altitude:

1. Press TX/RX until the screen shows: 2 TX LABELS (The 2 is an integer indicating the number of TX labels that are entered)

2. Press the ’up arrow’ key until the screen shows: 203 ALTITUDE

3. Press LAB/DAT until the screen shows: 203 01 E40000 11 (The six-digit hex code will be the most recently entered code)

4. Press EDIT/DEL


6. Enter the necessary hex value for the desired altitude or E41BB1 (33,654 ft) (see note 2 under step 1.4 below)

7. Press ENT

8. Screen shows: 203 01 641BB1 11

This entry will cause the ATC-601 to show 33,700 FT..

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To change ATC code:

1. Press TX/RX until the screen shows: 2 TX LABELS (The 2 is an integer indicating the number of TX labels that are entered)

2. Press the ’up arrow’ key until the screen shows: 031 BCN ATC CODE

3. Press LAB/DAT

4. Screen shows: 031 BCN ATC CODE

4 . P re ss EDIT/DEL

5. Screen shows a blinking cursor on an otherwise blank screen6. Enter the necessary hex value for the desired ATC code or 5263

7. Press ENT

8. TX screen shows: 031 01 0E5C01 00

9. RX screen shows: 031 01 0E5C01 00

This entry will cause the ATC-601 to show CODE=6352

Note: You can set the JcAIR DISPLAY switch to Eng to show the 4-digit code. The ATC-601 CODE and JcAIR 429E Eng code

displays should always agree.

10. Reset the TX 031 and 203 words to the Initial Setup

To view captured data:

1. Press TX/RX until the screen shows: 3 RX LABELS

2. Press ’up arrow’ to select the desired word label/title:031 BCN ATC CODE203 ALTITUDE350 MAINT DATA 1

3. Press LAB/DAT

4. Screen shows the selected word/data (only one at a time):031 01 156681 00

203 01 640000 11

350 01 000001 11

To select a different word:

5. Press LAB/DAT

6. Press ’up arrow’ or ’down arrow’ to select one word label/title as shown in 2. above:

7. Press LAB/DAT to view the data

8. Screen shows the selected word data as in 4 above.

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5 .5 M A I N T E N A N C E D I A G N O ST I C

D A T A R E T R I E V A L A N D A N A L Y SI S

5 .5.1 I n t r od u c t i o n

This par agr aph provides detailed informa tion

re la t e d t o t h e d ia g n o st ic d a t a s t o red in t h eTDR -94/94D t ra nsponder. It is int ended to

support the procedures found in table 5-6.

The stored data consists of fault and

m a in t e n a n ce d a t a wh ich is s t o red in

nonvolat ile memory. Memory spa ce, for th is

purpose, is allocated according to table 5-14.

N ot ice t h a t t h e re a re t w o ca t e gories o f d a t a :

g e n era l m a in t e n a n ce a n d d ia g n ost ic d a t a .

Table 5-14 shows structure of the diagnostic

d a t a .

Memory space consists of 256 bytes of

NVRAM. The general ma intenan ce dat a

buffers use 14 bytes and the remainder is

u sed for d ia g n o st ic d a t a s t o ra g e . E a ch

diagnostic occurrence uses 10 bytes. Thus,there is space for 24 diagnostic occurrences.

If more than 24 occurrences a re detected, the

most recent is retained as follows:

In -002 units, the most recent occurrence is

overwr it ten. Tha t is, occurrences 1 through

23 are r etained wh ile the 24th occurrence is

overwrit ten when a new occurrence is

detected.

In -003 units, the oldest occurrence is

overwrit ten.

Table 5-14. M aint enance and D iagnost ic Dat a M emor y St r uct ur e

GENERAL MAINTENANCE DATA BUFFERS

D ATA D E S C RI P TI ON B YTE S U S E D

P oint er t o next dia gnost ic code loca t ion 2

P ow er-on cycle count er 2

Tot a l dia gnost ic count er 1

Tot a l pow er-on t im er (m inut es) 1

P ow er-on t im er (hours) 2

La st P OC dia gnost ic count er 1

C urr ent P OC t im er 1

La st ma int ena nce da t e 4

DIAGNOSTIC DATA B UFF ERS

Time from la st pow er on 1

D ia gnost ic code 1

(not used) 1

Tra nsm it t er t emper a t ur e (degrees C elsius) 1

C urr ent pow er-on cy cle count buffer 2

Air/ground st a t e a t t ime of dia gnost ic 1

Time a t end of pow er-on cy cle 1

Alt it ude a t t ime of dia gnost ic 1

Alt it ude a t t ime of dia gnost ic 1

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5 .5 .2 G en e r a l D i a g n o st i c F or m a t s

Maintenance diagnostic data is provided on

the ARINC 429 output buses only. The

maintenance data is provided on a label 351

d a t a wo rd w h e n re qu est e d b y a n ARI N C 4 2 9

la b e l 27 7 d a t a wo rd a t a n y o f t h e ARI N C 4 29in pu t p ort s . Un le ss a t o t a l d o wn loa d is

requested, the output is based on a one-

response for one-request ba sis. In a ll cas es,

no da ta is provided unless t he Air/ground

d iscre t e is a t a log ic 0; t h a t is , t h e a irp la n e is

on t h e g ro u n d . N o st ore d d ia g n ost ic d a t a is

provided on an y of the CS DB buses. This

procedure uses the Atlantic Instruments,

D a t a Tra c 4 00 D a t a Tra c 4 00 H, D a t a Tra c 2 00

Da ta bus Rea ders, or the J cAIR 429E Tra ns-

mitt er/Receiver for da ta requ est a nd r eceive.

For t he sa ke of brevity, in t hese procedures

the term "bus reader" should be understoodt o a p p ly t o ei t h e r of t h e se in st ru m e n t s. I f

you have or prefer an equivalent instrument,

feel free to use it . Some procedura l

a d a p t a t io n m a y b e re qu ired . Co n t rol p ort s A ,

B , or C ca n b e u se d.

The general format of the maintenance re-

qu e st a n d re sp on se d a t a is a s f o llows:

B I T N O . B I T D E S I G N ATI O N

1 - 8 M S B - L S B L AB E L (s ee n ot e 1)

9 H ex fa ult cod e B 0

10 H ex fa u lt cod e B 1













23 H ex fa u lt cod e B 1424 H ex fa u lt cod e B 15





29 P AD

30 Tes t t y pe (s ee n ot e 2)

31 Tes t t y pe (s ee n ot e 2)

32 P a r it y

N ot e 1: L a b e l s t ru ct u re :

B it : 8 7 6 5 4 3 2 1

Va lue: 1 2 4 1 2 4 1 2

L a bel 277: 1 1 1 1 1 1 0 1

L a bel 351: 1 0 0 1 0 1 1 1

S e e a lso p a ra g ra p h 5 .7 .4 .8

Note 2: Test ty pe definit ion:

B I T 31 B I T 30 D E F I N I TI O N

0 0 S oft wa re r ev st at us, req uest

or response

0 1 RAM m em or y out put , r e

quest or response;

requires 4-digit address code

for specific data

1 0 L a st m a in t en a nce da te, loa d

command *

1 1 D et ailed dia gn ost ic d a ta ,request or response.

Requires 2-digit hex code(**)

for specific data

* U s e r s a r e CAUTIONED not to use this

code. This code w ill destroy some of th e

st ore d d ia g n ost ic d a t a . I t is in t en d e d for u se

on ly a f t e r b e n ch re p a ir . S e e pa ra g ra p h

5.5.11.

** Hex code list ing:

H ex R eq u es t ed d a t a

01 C on t e nt s of t ot a l p ow e r -on cy cl e cou n -

ter buffer

02 C on t e nt s of t ot a l f a u lt cou n t er b u ff er

03 C on t e nt s of t ot a l p ow e r -on t i m er

(hours) buffer

04 C on t e nt s of t ot a l p ow e r -on t i m er

(minut es) buffer

05 C on t e nt s of l a s t p ow e r -on cy cl e f a u lt

counter buffer

06 Not d efin ed

07 C on t en t s of l a s t m a i nt en a n ce d a t e

buffer

08-0F Not defined

10 D ow n l oa d of t h e d ia g n os t ic cod esdetected dur ing th e most r ecent

pow er-on cycle (if a ny- see below)

11-1X Download of the dia gnostic codes de-

tected during preceding power-on cy-

cles, wh ere 11 is th e next t o the most

recent and 1X is the request code that

produces a 00EOF (En d Of File) re-

sponse.

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5 .5 .3 S of t w a r e R ev i si o n S t a t u s ( SR S )

R ep o r t i n g

The software revision status is of

questionable value for f ield use. I t is

presented here so that if a need or purpose

develops it can be accessed.

5 .5 .3 .1 S R S W o r d D ef i n i t i o n

Upon receipt of a label 277 request for

d ia g n ost ic d a t a , w it h b i t s 3 1 a n d 3 0 se t t o 0 0,

the TDR-94D responds wit h a label 351 w ord

with the following structure:

1: 32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 92: 8 4 2 1 8 4 2 1 8 4 2 1 8 4 2 1 8 4 2 1

| | | | \ | | / \ | | / \ | | / | | | | | | | || | | | | | | \ | | / \ | | /| \ / \__BCD month \ BCD day / \ BCD yr /| \__SSM bits, 11 implies a request for diagnostic data\__Parity

Description:

B it 3 2: P a ri t y b i t : Th is b it is se t t o a 1 wh e n

the total of the other 31 bits set to 1 is 0 or

an even number.B it s 31 a n d 30 : S S M b it s : 1 1 im plie s a

re qu est f or d ia g n ost ic d a t a .

B i t s 2 9 - 2 5: B CD m on t h : B i t 2 9 gives t h e

tens va lue; 0 or 1. B its 28 -25 give the units

value; 0 - 9.

B it s 2 4 - 1 7: B CD d a y: B i t s 2 4 - 2 1 g ive t h e

t e n s va lu e ; 0 - 3 . B i t s 1 7 - 2 0 g ive t h e u n it s

value; 0 - 9.

B i t s 1 6 - 9: B C D y e a r : B i t s 1 6 - 13 g iv e t h e

tens va lue; 8,9,0. B its 12 - 9 give the units

value; 0 - 9.

5 .5 .3 .2 S R S D a t a R eq u es t

Note: The AIR/G ND swit ch, in the t est

p a n e l, m u st b e in t h e G N D p osit ion a n d

TES T INH IB IT must be off. Tha t is, pin P 2-

38 must be open.

Set the bus reader XMT for a label 277 data

word as follows:

D a t a T ra c:ON--------------XMT 1----------12.5 KHzLBL SDI 11-----User Data--- SSM Par msec277 00 60 00 00 FD 11 1 0100

J cAIR 429E :277 00 600000 11

I t is im port a n t t h a t t h e S M (S S M ) is set t o 11 .

Th e S D I is set a u t o m a t ica l ly w h e n d a t a is

e n t ere d in t o t h e 5 t h a n d 6 t h d ig i t s o f t h e d a t a

field. These are the only XMT digits tha t w ill be

manually changed in this procedure.

Response example:

D a t a T ra c:----------------RCV 1--(ALL)---12.5 KHz

LBL SDI 32-Hex Data-1 SSM Par Tmin351 10 09 12 90 97 11 1 0200

J cAIR 429E :351 10 091290 11

Th is in d ica t e s t h a t t h e S RS of t h is u n it is :

9 December 1990.

I t is im port a n t t o set t h e b u s re a d e r t o t h e

proper display format for easy data

interpretat ion.

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5 .5 .4 M e m o r y E x a m i n a t i o n R eq u est

a n d R esp o n s e ( M E R R )

This pa ra gra ph is provided for informa tion

purposes only. Memory a llocation, within the

memory blocks, is controlled dyna mically by

the operating software and therefore isdifficult predict . Da ta necessary for

maintenance can be obtained more easily by

the procedures in the rest of this paragraph.

5 .5 .4 .1 M E R R , G e n er a l W o r d D e f i n i t i o n

The memory examina tion request word label 277

is defined as follow s:

32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 91 8 4 2 1 8 4 2 1 8 4 2 1 8 4 2 1 8 4 2 1

| \ / | | | | | | | | | | | | | | | | | | | | || | Pad | || || || || || | \<-------------- 00000H to 0FFFFH --------------> /| | (memory locations)| \__SSM, 11 implies a request for diagnostic data

\__Parity

The response word label 351 is defined as follows:

32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 9- - - - - - - - 8 4 2 1 8 4 2 1 8 4 2 1 8 4 2 1

| \__/ | \__|__|__/ \__|__|__/ \__|__|__/ \__|__|__/ \__|__|__/| | | | | | | || | \<-Pad->/ \<--Data in requested location------>/| \__SSM, 11 implies memory examination request\__Parity

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5 .5.5 T o t a l P ow er -on C ycl e C ou n t

( T P O C C ) B u f f er

E a ch tim e th e TDR -94/94D is t urn ed on, th e

TP OCC buffer is incremented. Therefore,

this buffer contains the number of t imes the

unit ha s experienced a power applicat ion.

5 .5 .5 .1 T P O C C G en e r a l W o r d D e f i n i t i o n

The total power-on cycle counter data request

word label 277 is defined a s follows:

32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 9- - - - - - - - - - - - - - - - 8 4 2 1 8 4 2 1

| \__/ | \__|__|__/ \__|__|__/ \__|__|__/ \__|__|__/ \__|__|__/| | | | | | | || | \<------------Pad-------------> / \<----01H--->/| \__SSM, 11 implies a diagnostic data request\__Parity


32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 9- - - - - - - - - - - - - - - - 8 4 2 1 8 4 2 1

| \__/ | | | | | | | | | | | | | | | | | | | | || | | | | | | | | | | | || | Pad \10,000’S/ \1,000’S / \ 100’S / \ 10’S / \units /| \__SSM, 11 implies response to a diagnostic data request\__Parity

5 .5 .5 .2 T P O C C B u f f er E x a m i n a t i o n

Setup bus reader XMT screens a s follows:

D a t a T ra c:ON------------XMT 1----------12.5 KHz

L BL SDI 32 -He x D ata -1 S SM Pa r m sec277 01 00 00 00 FD 11 1 0100

J cAIR 429E:277 01 800001 11

The reader should respond w ith a label 351 word

sim ila r t o t h is :

D a t a T ra c:ON------------RCV 1--(ALL)---12.5 KHz

LB L S DI 32 -H ex Da ta- 1 S SM Pa r m sec

351 10 00 30 56 97 11 1 0200

J cAIR 429E :351 10 003056 11

This indicates that the UUT has undergone 3,056

power-on cycles.

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5.5.6 T o t a l F a u l t C ou n t er ( T F C ) B u f f er

Each t ime a diagnostic condit ion is

recognized, the TFC buffer is incremented.

Therefore, t his buffer conta ins the number

diagnostic condit ions the unit has

experienced.

5 .5 .6 .1 T F C G e n e r a l W o r d D e f i n i t i o n

The TFC buffer d at a request w ord label 277 is

defined a s follows :

32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 9- - - - - - - - - - - - - - - - 8 4 2 1 8 4 2 1

| \__/ | \__|__|__/ \__|__|__/ \__|__|__/ \__|__|__/ \__|__|__/| | | | | | | || | \<------------Pad--- -------->/ \<---02H--->/| \__SSM, 11 implies a request for diagnostic data\__Parity


32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 9- - - - - - - - - - - - - - - - 8 4 2 1 8 4 2 1

| \__/ | | | | | | | | | | | | | | | | | | | | |

| | | | | | | | | | | | || | Pad \10,000’S/ \1,000’S / \ 100’S / \ 10’S / \units /| \__SSM, 11 implies response to a request for diagnostic data\__Parity

5 .5 .6 .2 T F C B u f f er E x a m i n a t i o n

Setup bus reader XMT screens as follows:


L BL SD I 3 2- He x D at a-1 S SM Par ms ec277 10 80 00 02 FD 11 1 0100

J cAIR 429E :

277 10 800002 11

The reader should r espond wit h a label 351 word



L BL SD I 3 2- He x D at a-1 SS M P ar ms ec351 10 60 01 02 97 11 1 0200

J cAIR 429E :351 10 600102 11

This indicates t ha t the U U T ha s experienced 102

diagnostic conditions.

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5 .5 .7 T o t a l P o w er -o n T i m e r ( H o u r s)

( T P O T H ) B u f f er

Two data buffers are used to record the total

t ime the unit is in operation; an hours buffer

a n d a m in u t e s b u f fe r . As t h e u n it is

operat ing, the m inutes counter iscont inuously incremented. The hours buffer

is incremented ea ch t ime t he minutes counter

overflows.

5 .5 .7 .1 T P O T H G en e r a l W o r d D e f i n i t i o n

The total TPOTH buffer data request word label

277 is defined as follows:

32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 9- - - - - - - - - - - - - - - - 8 4 2 1 8 4 2 1

| \__/ | \__|__|__/ \__|__|__/ \__|__|__/ \__|__|__/ \__|__|__/| | | | | | | || | \<--------Pad------------> / \<----03H--->/| \__SSM, 11 implies a request for diagnostic data\__Parity

The response word label 351 is defined as

follows:

32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 9- - - - - - - - - - - - - - - - 8 4 2 1 8 4 2 1

| \__/ | | | | | | | | | | | | | | | | | | | | || | | | | | | | | | | | || | Pad \10,000’S/ \1,000’S / \ 100’S / \ 10’S / \units /| \__SSM, 11 implies response to a request for diagnostic data\__Parity

5 . 5 . 7 . 2 T P O T H B u f f e r E x a m i n a t i o n


D a t a T ra c:ON------------XMT 1----------12.5 KHzL BL SDI 32 -He x D ata -1 S SM Pa r m sec277 11 60 00 03 FD 11 1 0100

J cAIR 429E:277 11 600003 11




LB L S DI 32 -H ex Da ta- 1 S SM Pa r m sec351 11 E0 03 57 97 11 1 0200

J cAIR 429E :351 11 E00357 11

This exam ple shows tha t the TP TOH buffer

conta ins t he va lue 357.

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5 .5 .8 T o t a l P o w er -o n T i m er ( M i n u t es)

( T P O T M ) B u f f er

The TPOTM buffer is incremented each

m in u t e t h a t t h e u n it h a s p owe r a p plied .

Overflow of this buffer causes the TPOTH

buffer to be incremented.

5 .5 .8 .1 T P O T M G en e r a l W o r d D e f i n i t i o n

The total TPOTM buffer data request word label

277 is defined as follows:

32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 9- - - - - - - - - - - - - - - - 8 4 2 1 8 4 2 1

| \__/ | \__|__|__/ \__|__|__/ \__|__|__/ \__|__|__/ \__|__|__/| | | | | | | || | \<--------Pad------------> / \<---04H--->/| \__SSM, 11 implies a request for diagnostic data\__Parity


follows:

32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 9- - - - - - - - - - - - - - - - 8 4 2 1 8 4 2 1

| \__/ | | | | | | | | | | | | | | | | | | | | || | | | | | | | | | | | || | Pad \not used/ \not used/ \not used/ \ 10’S / \units /| \__SSM, 11 implies response to a request for diagnostic data\__Parity

5 . 5 . 8 . 2 T P O T M B u f f e r E x a m i n a t i o n



L BL SD I 3 2- He x D at a-1 S SM Par ms ec277 00 E0 00 04 FD 11 1 0100

J cAIR 429E :277 00 E00004 11

The reader should r espond wit h a label 351 word



L BL SD I 3 2- He x D at a-1 SS M P ar ms ec

351 11 60 00 27 97 11 1 0200

J cAIR 429E :351 11 600027 11

This indicates tha t the un it TP TOM buffer

conta ins t he number 27.

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5 .5 .9 L a s t P o w e r -o n C y c l e ( L P O C ) F a u l t

C ou n t er B u f f er

This buffer conta ins t he number of dia gnostic

condit ions detected during the most r ecent

power-on cycle.

5 .5 .9 .1 L P O C G e n er a l W o r d D ef i n i t i o n

The last LPOC fault counter buffer data request

word label 277 is defined a s follows:

32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 9- - - - - - - - - - - - - - - - 8 4 2 1 8 4 2 1



follows:

32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 9- - - - - - - - - - - - - - - - 8 4 2 1 8 4 2 1

| \__/ | | | | | | | | | | | | | | | | | | | | || | | | | | | | | | | | || | Pad \not used/ \not used/ \ 100’s / \ 10’s / \units /| \__SSM, 11 implies response to request for diagnostic data\__Parity

5 .5 .9 .2 L P O C B u f f er E x a m i n a t i o n



L BL SDI 32 -He x D ata -1 S SM Pa r m sec277 01 60 00 05 FD 11 1 0100

J cAIR 429E:277 01 600005 11




LB L S DI 32 -H ex Da ta- 1 S SM Pa r m sec351 11 E0 00 07 97 11 0200

J cAIR 429E :351 11 E00007 11

This indicates that during the most recent power-

on cycle 7 diagnostic conditions were detected.

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5 .5 .1 0 L a s t M a i n t en a n c e D a t e ( L M D )

B u f f e r ( E x a m i n a t i o n )

This buffer should contains the most recent

m a in t e n a n ce d a t e . Wh e t h er o r n ot t h is d a t e

accurately reflects the date on which the unit

was most recently repaired or tested depends

upon whether the date was properly entered.

5 .5 .1 0.1 L M D G en e r a l W o r d D e f i n i t i o n

The LMD buffer da ta request w ord label 277 is


32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 9- - - - - - - - - - - - - - - - 8 4 2 1 8 4 2 1



follows:

1: 32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 92: 8 4 2 1 8 4 2 1 8 4 2 1 8 4 2 1 8 4 2 1 8 4 2 1

| | | | \ | | / \ | | / \ | | / | | | | | | | || | | | | | | \ | | / \ | | /| \ / \__BCD month \ BCD day / \ BCD yr /| \__SSM bits, 11 implies response to a request for diagnostic data\__Parity

5.5.10.2 L M D B u f f er E x a m i n a t i o n



L BL SD I 3 2- He x D at a-1 S SM Par ms ec277 11 E0 00 07 FD 11 1 0100

J cAIR 429E :277 11 E00007 11

The reader should r espond wit h a label 351

wo rd sim ila r t o t h is :


L BL SD I 3 2- He x D at a-1 S SM Par ms ec351 01 70 06 91 97 11 1 0200

J cAIR 429E :351 01 700691 11

Th is in d ica t e s t h a t t h e la st m a in t e n a n ce d a t e f or

this unit w as October 6, 1991.

You n eed to recognize tha t the 7, here, includes

the SSM bits which account for a value of 6 (4 +

2 ). Th u s 7 - 6 = 1 wh ich m e a n s t h a t b i t 2 9 is a

1. This sets the month a t 10; October.

5 .5 .1 1 L a s t M a i n t en a n c e D a t e ( L M D ) B u f f e r ( U p d a t e )

A method for updating the LMD buffer is not

included in this manu al. The LMD buffer should

be changed only after a repair act ion, unit

modificat ion, or detailed t est procedure h as been

performed.

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5 .5 .1 2 L a s t P o w e r -o n C y c l e F a u l t s

( L P O C F ) D a t a D o w n l o a d

This process a llow s for r etrieval of a ll the

diagnostics detected dur ing th e most recent

power-on cycle. This can be seen a s a n

e xt e n sion t o st e p 5.5.5. I n t h a t s t e p welearned the number of faults detected during

the most recent pow er-on cycle. In t his

se qu en ce we w ill le a rn wh a t t h o se d ia g n o st ic

cod e s a re . I n t h is se qu e n ce you m u st w a t ch

the label 351 word carefully. The UU T ma y

t ra n sm it se vera l wo rd s, e a ch w it h a d i ff ere n t

diagnostic code, at 5-second intervals.

The first transmission is the contents of the

current Total Power-on Cycle count buffer (as in

5.5.5 a bove). This is followed, in 5-second

in t erva ls , w it h a t ra n sm ission o f e a ch

of t he dia gnostic codes encountered during the

most recent power -on cycle (self-test ). The

sequence is a utomat ic therefore you should bep re p a re d t o wri t e d o wn t h e d a t a a s i t a p p e a rs.

The final label 351 word is likely t o be a word

sim ila r t o 0 7F F E wh ich d oe s n ot t ra n sla t e in t o a

meaningful diagnostic code.

5 .5 .1 2.1 L P O C F G en e r a l W o r d D e f i n i t i o n

The LPOCF data request word label 277 is

defined a s follows:

32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 9

- - - - - - - - - - - - - - - - 8 4 2 1 8 4 2 1| \__/ | \__|__|__/ \__|__|__/ \__|__|__/ \__|__|__/ \__|__|__/| | | | | | | || | \<--------Pad------------> / \<---10H--->/| \__SSM, 11 implies a request for diagnostic data\__Parity

The first response label 351 word is defined

in paragraph 5.5.5.

The second and subsequent response label 351

word(s) are defined a s follow s:

32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 9- - - - - - - - - - - - - - - - 8 4 2 1 8 4 2 1

| \__/ | | | | | | | | | | | | | | | | | | | | || | | | | | | | | | | | || | Pad \not used/ \not used/ \not used/ \ Hex fault code /

| \__11 implies response to detailed diagnostic data request\__Parity

5 .5.1 2.2 L P O C F D a t a D o w n l o a d



L BL SDI 32 -He x D ata -1 S SM Pa r m sec277 00 E0 00 10 FD 11 1 0100

J cAIR 429E:277 00 E00010 11




LB L S DI 32 -H ex Da ta- 1 S SM Pa r m sec

351 11 E0 00 B3 97 11 1 0200

J cAIR 429E :351 11 E000B3 11

This example indicates that this unit

experienced a diagnostic code B3 at the last

power on cycle. One of the 351 label words

m a y in d ica t e a n F F la b e l wh ich . Th is cod e is

not defined and so you can ignore it .

You m ay likely encounter a diagnostic code B 3 on

the bench. This diagnostic is interpreted as

"TCAS bus inactive".

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5.5.13 C on t i n u e F l i g h t F a u l t ( C F F ) D a t a

D o w n l o a d

This paragraph can be seen as an extension

of the previous para gra ph 5.5.12. In tha t

paragraph only those diagnostics detected

during t he most recent power-on cycle ar ere vea le d . I n t h is p a ra g ra p h , 5.5.12 , a l l of t h e

diagnostics stored in NVRAM a nd detected

during preceding power-on cycles are

examined.

5 .5 .1 3.1 C F F G en e r a l W o r d D e f i n i t i o n

T h e d a t a f o rm a t is t h e sa m e a s in p a ra g ra p h

5.5.12 except that the hex data in the label

277 interrogat ion word is incremented from

10H t o 1XH. Of course, if you ha ve already

examined the 10H, in par agr aph 5.5.12, you

can begin here w ith 11H. The U U T responds by

sending each stored code for a 5-second period.

Co n t in ue in cre m en t in g t h e h e x d a t a u n t i l t h e

UUT sends an ’end of f ile’ data f ield = 00EOFH.

This is display ed on the D at aTra c an d J cAIR

429E a s 000EOF. Remember, you only need to

ch a n g e d ig i t s 5 a n d 6 in t h e d a t a f ield s of b ot ht h e D a t a Tra c a n d J cAI R re a d e rs. Th e S D I a n d

p a ri t y b i t s wil l ch a n g e a u t o m a t ica l ly .

5 .5 .1 3. 2 C F F G e n e r a l P r o c ed u r es

The diagnostic condit ions detected dur ing the

preceding 16 (maximum) power-on cycles can be

re vie we d b y in t e rrog a t in g t h e U UT wit h a la b e l

2 7 7 d a t a wo rd , wit h S S M se t t o 1 0 a n d t h e d a t a

in the bit f ield, bits 9 through 16 set to 1X as

follows (assuming no. 1 being the most recent):

Buffer 277 Word DataTrac 200/400/400H, 277 Word Setup JcAIR 429E, 277 word

Lbl SDI 32-Hex Data-1 SM Par msec1 10H 277 00 E0 00 10 FD 11 1 0100 277 00 E00010 112 11H 277 01 60 00 11 FD 11 1 0100 277 01 600011 113 12H 277 10 60 00 12 FD 11 1 0100 277 10 600012 114 13H 277 11 E0 00 13 FD 11 1 0100 277 11 E00013 115 14H 277 00 60 00 14 FD 11 1 0100 277 00 600014 116 15H 277 01 E0 00 15 FD 11 1 0100 277 01 E00015 117 16H 277 10 E0 00 16 FD 11 1 0100 277 10 E00016 118 17H 277 11 60 00 17 FD 11 1 0100 277 11 600017 119 18H 277 00 60 00 18 FD 11 1 0100 277 00 600018 1110 19H 277 01 E0 00 19 FD 11 1 0100 277 01 E00019 1111 1AH 277 10 E0 00 1A FD 11 1 0100 277 10 E0001A 1112 1BH 277 11 60 00 1B FD 11 1 0100 277 11 60001B 1113 1CH 277 00 E0 00 1C FD 11 1 0100 277 00 E0001C 1114 1DH 277 01 60 00 1D FD 11 1 0100 277 01 60001D 1115 1EH 277 10 60 00 1E FD 11 1 0100 277 10 60001E 1116 1FH 277 11 E0 00 1F FD 11 1 0100 277 11 E0001F 11

Any of the a bove can produce a response:


L BL SD I 3 2- He x D at a-1 S SM Par ms ec351 11 E0 30 57 97 11 1 0200351 11 E0 0E 0F 97 11 1 0200

J cAIR 429E :351 11 E03057 00351 11 E00E0F 00

Th e U UT sh ou ld re spon d w it h a t lea st t w o

la b e l 35 1 d a t a wo rd s. Th e f irst is t h e

contents of the Total Power-on Counter buffer

wh ich m a y b e a re la t ive ly la rg e n u m b er

depending on the length of t ime the unit has

been in service.

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Special note for -002 units:

In -002 units, only t he interna l diagn ostic

condit ions result ing in a failure-warn

condit ion an d improper m ode S a ddress

diagnostic condit ions a re st ored.

The mode S a ddress diagnostic can easilyoccu r w h e n t h e u n it is t u rn e d o n wit h a l l

ad dress lines open or shorted t o ground.

Consequently you may frequently notice a

0000FF hex code as the second 351 word. I t

is also possible that in some units you may

encounter a Total Power-on Timer (Hours)

b u f fe r w it h a n u n re a l ist ica l ly la rg e n u m b e r.

Early units were not properly cleared at

production. In t hese cases, of course, the

d a t a is of n o va lu e.

5 .5.1 4 F a st F a u l t ( F F ) D a t a D o w n l o a d

The feature used in this paragraph is

in t e n de d f or u se w it h a d a t a s t o ra g e d evice

which is capable of capturing and storing

d a t a t ra n sm it t e d in ra p id sequ e n ce . Th e

Da ta Tra c 400/400H is ca pable of t his function.

Af t e r d own lo a d in g t h e d a t a , i t ca n t h e n b e

further download ed, using procedures an d

softw a re supplied wit h th e Da ta Tra c 400/400H,on t o a P C f o r d e t a i led a n a lysis a n d p erm a n e n t

storage. The Da ta Tra c 200 is capable of

ca p t u rin g t h e d a t a b u t la ck s t h e m ea n s of

t ra n sf errin g i t f or e xt e rn a l s t o ra g e a n d

in t erp ret a t ion . A m a n u a l a n a lysis is see n a s

inefficiently la borious an d t ime consuming an d

therefore is not recommended. However, if this

is not seen as prohibit ive, refer to paragraph

5.5.14 for the Slow Fault Data Download.

5 .5 .1 4.1 F F G en e r a l W o r d D ef i n i t i o n

The FF data request word label 277 is defined asfollows:

32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 9- - - - - - - - - - - - - - - - 8 4 2 1 8 4 2 1


5 .5.1 4.2 F F D a t a D o w n l o a d

D es cr i p t i o n

When t he 277 label w ord a s described in

paragraph 5.5.14.1 is sent to the UUT, it

responds as follows:

a . P ow er-on cycle counter buffer as described

in paragraph 5.5.5 above.

b. Tota l fault counter buffer as described in

paragraph 5.5.6 above.

c. Tota l pow er-on timer (hours) buffer as

described in pa ra gra ph 5.5.7 above.

d. Total power-on t imer (minutes) buffer as

described in pa ra gra ph 5.5.8 above.

e. La st power-on cycle fault counter buffer asdescribed in pa ra gra ph 5.5.9 above.

f . L a st m a in t e n a n ce d a t e b u ff er a s d e scrib ed

in pa ra gra ph 5.5.10 above.

The UUT then transmits a ’break’ indicator using

t h e sa m e f orm a t a s d e scrib ed in p a ra g ra p h 5 .5 .7

(power-on timer (hours)), except the data is set to00FFFF.

F ollowin g t h is t h e U UT t ra n sm it s t h e n in e ( 9)

fault data bytes for the last recorded diagnostic

in the following sequence and formats:

g. Curr ent P ower-on Cycle count buffer as

described in 5.5.5 above.

h . D ia g n o st ic cod e a s d e scrib ed in p a ra g ra p h

5.5.9 above.

i. Time from last pow er-on using th e follow ing

f o rm a t :

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32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 9- - - - - - - - - - - - 8 4 2 1 8 4 2 1 8 4 2 1

| \__/ | | | | | | | | | | | | | | | | | | | | || | | | | | | | | | | | || | Pad \not used/ \not used/ \ 1 Hr / \10 min / \ 1 min /| \__SSM, 11 implies response to request for diagnostic data\__Parity

j. Tra n sm it t e r t e m p era t u re a t t im e of

diagnostic using the following format:

32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 9- - - - - - - - - - - - 8 4 2 1 8 4 2 1 8 4 2 1

| \__/ | | | | | | | | | | | | | | | | | | | | || | | | | | | | | | | | || | Pad \not used/ \not used/ \ 100’s / \ 10’s / \ units /| \__SSM, 11 implies response to request for diagnostic data\__Parity

k. Air/ground stat e at t ime the diagnostic

was detected, using the following format:

32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 9- - - - - - - - - - - - - - - - 8 4 2 1 8 4 2 1

| \__/ | | | | | | | | | | | | | | | | | | | | || | | | | | | | | | FAH = in air /| | Pad \not used/ \not used/ \not used/ \ FDH = on ground /| \__SSM, 11 implies response to request for diagnostic data\__Parity

l. Time at end of power-on cycle as described

in transmission i . above.

m . Alt i t u d e a t t im e o f d ia g n o st ic u sin g t h e

follow ing forma t:

32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 9- - - - - - - - - - - - - - - - 8 4 2 1 8 4 2 1

| \__/ | | | | | | | | | | | | | | | | | | | | || | | | | | | | | | | | || | Pad \10,000s / \1000s / \ 100s / \ 10s / \ units /| \__SSM, 11 implies response to request for diagnostic data\__Parity

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5 .5.1 4.3 F F D a t a D o w n l o a d E q u i p m en t

This feat ure is int ended for t hose with access

t o a n a u t o m a t e d m e a n s o f re qu est in g ,

ca p t u r in g , a n d a n a l y zi n g t h e da t a . S u ch

f a cil it ie s a re a t lea st p a rt ia l ly a va i la b le fro m

sources other than Collins and you aree n cou ra g e d t o a cqu ire a n d u se t h e m . F o r

example:

• At la n t ic I n st ru m en t s su p plie s h a rd wa re

a n d so f t wa re , o p e ra t in g wit h t h e D a t a T ra c

400/400H, for au toma tica lly captu ring a nd

d o wn lo a d in g t h e d a t a o n t o a PC.

• Avionica Inc., 3830, SW 130th Ave., Miam i

FL 33175, supplies a laptop computer

e qu ipp ed w it h a p prop ria t e h a rd w a re a n d

sof t wa re t o d own lo a d , s t o re, a n d d ispla y

diagnostic data from a number of Collins

uni ts includ ing th e TDR -94/94D Mode S

Tra nsponder a s w ell a s th e TTR-920 TCASTra nsm itt er/Receiver.

5 .5 .1 5 S l o w F a u l t ( SF ) D a t a D o w n l o a d

Th is d a t a d own lo a d f e a t u re is b a sica l ly t h e

sa m e a s t h a t d e scrib ed in p a ra g ra p h 5 .5 .1 3

except that the hex field in the data request

w ord is set to 51H (instead of 50H). This w ill

ca u s e t h e U U T t o t r a n s m i t t h e s a m e d a t a a s

described in pa ra gra ph 5.5.13 except tha t it

is t ra n sm it t e d o n e d a t a f i le a t a t im e a t 5

seconds interva ls.

5 .5 .1 5.1 S F G en e r a l W o r d D ef i n i t i o n

Same as 5.5.13.1 except hex data is set to 51H.

5 .5 .1 5.2 S F D a t a D o w n l o a d P r o ced u r e

Use the following chart , reproduced in a quantityre qu ire d , t o re cord t h e d a t a a s i t a p pe a rs o n yo u r

d a t a b u s rea d e r. S e t t h e b us re a d er f or t h e

proper display forma t for d irect interpretat ion of

the data as described in the preceding

p a ra g ra p h s.

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* * * * * * * D u plica t e t h is s heet a s r eq u ir ed * * * * * * *

D a t e: _______________ U U T Type: _____( ) TD R-94: P a rt No: 622-9352-

U U T Type: _____( ) TDR -94D: P a rt No: 622-9210-

U U T S er n o: _____________

C ust om er : _________________________________________

D a t a t a ken by : ____________________________________ (Your n a m e)

TDR-94/94D Diagnostic Data Record

D ia gn ost ic C ode I n t er pr et a t ion

P ow er-on C ycle C oun t er: _________ _______________________Tota l Fa ult Count er: _________ _______________________Tota l P ow er-on Timer (Hr s): _________ _______________________

Tota l P ow er-on Tim er (Min ): _________ _______________________La st P ow er-on F a ult C oun t er: _________ _______________________E xist in g La st Ma in t ena nce D a t e: _________ _______________________New La st Ma in t en a n ce D a t e: * _________ _______________________B r ea k: ___ 0F F F F FC ur ren t P ow er-on C ycle C oun t : _________ _______________________D ia g no st ic Co de: _________ _______________________Tim e F rom L a st P ow er-on: _________ _______________________Xmit ter Temp a t D ia g: _________ _______________________Air/G nd S t a te a t D ia g: _________ _______________________Tim e a t end of P ow er -on Cy cle: _________ _______________________

Alt i t ude a t D ia g : _________ _______________________

* To be chan ged only a fter repair, modifica tion, or d eta iled (bench) test .

Power-on cycle diagnostics (1 = most recent):

1: ___________, 2: ___________, 3: _____________, 4: ____________, 5: ____________,6: ___________, 7: ____________, 8: ____________, 9:___________, 10: ___________,11:__________, 12:___________, 13:___________, 14:____________, 15:___________,16:____________, 17: ___________, 19:___________, 20: ___________, 21:____________,22:___________, 23:____________, 24:____________

Comments:_____________________________________________________________________________________________________________________________________________________________________________________________________________________________________________________________________________________________________________________

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5 .6 N U M B E R S Y S T E M C O N V E R S I O N

A N D D A T A W O R D D E S C R I P T I O N S

This para gra ph provides detailed descriptions

of t h e va riou s d a t a f orm a t s u se d in t h e TD R-

94/94D. These form a ts us e a va riety of

numbering systems including binary, octal,a n d h e xa d e cim a l . P a ra g ra p h 5 .6 .1 provid es a

procedure for conversion between these

n u m b erin g syst em s. I f you a re f a m il ia r w it h

a conversion process, you should feel free to

use that process.

5 .6 .1 O c t a l -t o -B i n a r y -t o -H ex a d ec i m a l ,

a n d B a c k

There are many relat ively inexpensive hand-

held calculat ors w ith number conversion

capability available.

If you have one of these, use it . Otherw ise,

this paragraph describes a relat ively simple

method of converting between t he

He xa d e cim a l a n d Oct a l n u m b e rin g syst e m s.

This is useful for Mode S t ra nsponder t est ing

b eca u se t h e d a t a syst e m s u sed in t h e m o d e s

t ra n sp on d e r u se a l l t h re e syst e m s. F o rexample, the mode s address is typically as-

signed as a n eight-digit octal number. This

oct a l n u m b e r is t ra n sla t e d in t o a b in a ry

n u m b er f o r a d d re ss st r a p p in g a t in st a l la t ion .

D u rin g t e st in g , qu it e o ft e n t h is a d d re ss is

displayed as a six-digit hexadecimal number.

U se the follow ing list ing to convert your

hexadecimal or octal number to its binary

equivalent .

H ex-t o-B in a ry C on ver sion Oct a l-t o-B in a ry C on ver sion

H ex B in a r y H ex B in a r y Oct a l B in a r y

0 0000 8 1000 0 000

1 0001 9 1001 1 001

2 0010 A 1010 2 010

3 0011 B 1011 3 011

4 0100 C 1100 4 100

5 0101 D 1101 5 101

6 0110 E 1110 6 110

7 0111 F 1111 7 111

Convert from t he six-digit hexadecimal num -

ber to a n eight-digit octa l number a s follows:

Enter the hex number on the top (Hex) line

of the following char t . Then enter the

equivalent binary values for each hex

digit from the list ing above in the center

(B in) line. Then use the lower bit va lues to

con ve rt t h o se b in a ry b i t s , t h re e b it s a t a

t im e , in t o t h e e qu iva len t oct a l n u m b e r a n d

enter t hose numbers on the lower (Oct) line.

Hex:

B it V a l : 8 4 2 1 8 4 2 1 8 4 2 1 8 4 2 1 8 4 2 1 8 4 2 1

B i n :

B it V a l : 4 2 1 4 2 1 4 2 1 4 2 1 4 2 1 4 2 1 4 2 1 4 2 1

Oct:

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Example: Suppose the test set shows a hex

code 3AC421. Enter this code on the top line.

Then write the equivalent four digit binary

values (from th e

hexadecimal list ing a bove) in spaces below

each hex digit . Then translate each three-

digit grouping of binary numbers into the

equivalent octal number.

Hex: 3 A C 4 2 1

B it V a l : 8 4 2 1 8 4 2 1 8 4 2 1 8 4 2 1 8 4 2 1 8 4 2 1

B i n a r y : 0 0 1 1 1 0 1 0 1 1 0 0 0 1 0 0 0 0 1 0 0 0 0 1

B it V a l : 4 2 1 4 2 1 4 2 1 4 2 1 4 2 1 4 2 1 4 2 1 4 2 1

Oct: 1 6 5 4 2 0 4 1

To convert from octal to hex, reverse the

above process by entering t he octa l number

into the spaces on the low er line. Convert

each octal digit into its equivalent binary

va lue. Then convert ea ch four-digit grouping

in t o it s e qu iva le n t h e x va lu e a s sh own in t h e

Hex-to-Binary conversion listing above-left.Write t hese numbers into t he spaces on the

top line.

The binary digits, read from left to right ,

correspond t o the mode s a ddressing sw itches

on t h e t e st p a n e l . Th a t is , t h e fa r lef t d ig it

corresponds to sw itch a nd rear connector pin

P 1-33, t he next P 1-34, etc, to t he fa r right

wh ich is P 1-56. The switch set to the OFF

position corresponds to a 0; t h e swit ch se t t o

SE L corresponds to a 1. The suggested panel

layout shown in figure 5-3 shows t he mode s

swit ches la beled a ccording to the octal d igitstha t ea ch controls. This ma kes the octal code

easy to read from the switch posit ions by

a d d in g t h e b in a ry va lu e o f t h ose swit ch es in

each 3-swit ch group set to SE L. You must

avoid, however, the combination with all

swit ch es u p o r a l l sw it ch e s d own . Th e se t w o

combinations are not allowed in the mode s

a d d re ssin g sch em e a n d wil l p rod u ce a t ra n -

sponder diagnostic code FF in TD R-94/94D

units with CPN ending in -002.

5 .6 .2 D i a g n o st i c W or d , A R I N C 42 9 l a b el

3 50 , D ef i n i t i o n a n d D e c od i n g P r o ced u r e

5 .6 .2 .1 O n D a t a T r a c 4 0 0/ 40 0 H

The diagnostic codes listed in table 5-2 are

available for viewing on the ARINC 429 label

350 diagnostic word. The Da ta Tra c 400 is

capable of displaying this word in a variety of

binary a nd hexadecimal forms. The form

t h a t is se le ct e d is la rg e ly a m a t t e r o f

personal preference but the form chosen here

is labeled BIN19L . Th is pa ra g ra p h sh ows

you how to decode th e diagnostic informa tion

from this displayed word.

Refer to th e screen r epresentat ion below.

This shows the label 350

word from bits 29t h ro u gh 1 1 a s i t a p p ea rs on t h e D a t a Tra c

400/400H displa y set for a BIN19L display.

(The actual screen will show other words and

their labels but this discussion focuses only

on the label 350 word.)

-----------------RCV 1--(ALL)---12.5 KHzLbl SDI 29--Binary Data--11 SSM Par msec350 01 1000010110011000000 11 1 0200

Of course, you can also select the h ex display

mode for a direct display of the diagnostic

code and avoid the conversion process.

-----------------RCV 1----------12.5 KHzLbl SDI 32-Hex Data-1 SSM Par msec350 01 70 B3 01 17 11 1 0200

||<---diagnostic code

This display can be reproduced as follows:

a . With th e ATC-601 set for ATCRBS RE-

PL Y , set t h e t e st p a n e l POWE R swit ch t o

OF F .

b. On the test pan el, set the TCAS/NO

TCAS switch to TCAS.

c. On the Da ta Tra c 400/400H, press RCV

a n d t h e n p ress ENT . (This clears the

d ispla y a n d p re pa re s t h e a n a lyz e r t o

receive new data.)

d . On t h e t e st pa n e l , set t h e POWE R sw it ch

t o ON .

e . Af t e r a f e w secon d s, t h e XF E E D OUT

lamp lights, the ATC-601 REPLY l a m p

ligh t s , a n d t h e d a t a is d isp la ye d o n t h e

D a ta Tra c 400/400H RCV 1 screen.

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N ot e : I f t h e 350 word does not appear on the

Da ta Tra c 400/400H screen init ia lly, press

RCV (until the cursor is at the left of HOLD),

then press the down arrow (or up arrow) key

t o scrol l t h e d a t a wo rd s u n t i l t h e 350 wo rd

a p p ea rs. B i t s 1 7 t h ro u gh 2 4 a re t h e e ig h t

data bits that define the 2-digit hexadecimaldiagnostic code a s follows:

Diagnostic digit :

MS B L S B

B i t : 24 23 22 21 20 19 18 17

B in va lu e: 8 4 2 1 8 4 2 1

Example: 1 0 1 1 0 0 1 1

D i a g : | < B >| | < 3 >|

Int erpretat ion:TCAS bus inactive (see ta ble

5-2)

The conversion process involves translatingeach of t hese four-bit gr oupings int o the

equivalent hexadecimal value using the

binary to hex conversion list in paragraph

5.6.1 a bove.

Bits 11 through 16, and 25 through 28

identify specific failure condit ions. These ar e

defined below.

B i t D E F I N I TI O N B i t D E F I N I TI O N

11 X pd r f a i lu r e 16 S e r ia l con t r ol p or t c

failure

12 R AM f a i lu r e 25 S e r ia l a l t i t ud e p or t a

failure

13 R O M f a i lu r e 26 S e r ia l a l t i t ud e p or t b

failure

14 P o r t b f a i lu r e 27 S e r ia l AD L P b u s f a i l-

ure

15 P o r t a f a i lu r e 28 S e r ia l TC AS b u s f a i l-

u re *

The defined failure condition exists when a

logic 1 a ppears in t he corresponding bit loca-

tion.

* Notice in the screen example a bove, bit 28

is also set to 1.

Incidentally, in the label 350 diagnostic word,

bit 29 is defined as a PAD.

5 .6 .2 .2 O n D a t a T r a c 2 0 0

The DataTrac 200 displays the diagnostic

code in the HEX RCV field in the form of 5

hex digits a s follows:

H ex: MS B 4 3 2 L S B

D a t a b i t : 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10

B it V a l : 8 4 2 1 8 4 2 1 8 4 2 1 8 4 2 1 8 4 2 1 *

* bit 10 is not included in the display

In the test procedures, a TCAS Bus failure

diagnostic is induced producing a diagnostic

code B3. This

a p p ea rs on t h e D a t a Tra c 2 00 a s a He x cod e

45980. This is produced as follows:

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H ex bit : MS B 4 3 2 L S B

D a t a b i t : 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10

B it V a l : 8 4 2 1 8 4 2 1 8 4 2 1 8 4 2 1 8 4 2 1 *

H ex va lue: 4 5 9 8 0

B i n a r y : 0 1 0 0 0 1 0 1 1 0 0 1 1 0 0 0 0 0 0 0B it V a l : 8 4 2 1 8 4 2 1

H ex va lue: B 3

Thus, t o properly interpret a diagnostic code

as displayed on the DataTrac 200, you must

f irst t ra n sla t e t h a t cod e in t o it s b in a ry f orm ,

extending from bit 11 thr ough 29. Then

translate the two four-bit groupings, 18

t h ro u gh 2 1 f or t h e L S B , a n d 2 2 t h rou g h 2 5

for the MS B , into t he hex diagnostic code.

Then refer to table 5-2 for the defined diag-

nostic.I t is im port a n t t o re m em b er t h a t b i t s 1 1

through 16, a nd 25 through 28, define

specific failure condit ions as described in the

previous paragraph for the DataTrac 400.

Th e re is a n e a sie r w a y t o in t e rpre t t h e

diagnostic code and that is to select the 32--

Hex Data--1 d ispla y f o rm a t . Th is wil l g ive

you a display:

-----------------RCV 1--(ALL)---12.5 KHzLbl SDI 32-Hex Data-1 SSM Par msec350 01 68 B3 01 17 11 1 0200

||<---diagnostic code

I n t h is f orm a t yo u ca n re a d t h e d ia g n o st iccode directly from the second pair of hex

digits (from the left).

S u p pose t h e D a t a Tra c 2 0 0 sh ows a HE X D A -

TA f ield 47A80. You would interpret this

code as follows:

H ex bit : MS B 4 3 2 L S B

D a t a b i t : 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10

B it V a l : 8 4 2 1 8 4 2 1 8 4 2 1 8 4 2 1 8 4 2 1 *

H ex va lue: 4 7 A 8 0

B i n a r y : 0 1 0 0 0 1 1 1 1 0 1 0 1 0 0 0 0 0 0 0

B it V a l : 8 4 2 1 8 4 2 1

H ex va lue: F 5

Thus a Da ta Tra c 200, HEX DATA field display

of 47A80 is a diagnostic code F5, which is

shown on table 5-2 as Port Selects Changed.

5 .6 .3 T r a n sp o n d er C on t r o l W o r d D ef i n i -

t i o n s

This pa ra gra ph describes t he va rious control

w ords us ed by th e TDR -94/94D mode s t ra n-

sponder.

5 .6 . 3. 1 A R I N C 4 2 9 , L a b e l 0 3 1 , 01 5 , a n d

0 1 6 , C o n t r o l W o r d s

In ARINC 429, the label is formed by the

first byt e (first 8 bits wh ich forms by te 0) of

the dat a w ord. The label is described in

para gra ph 5.6.5 below.

The data word with label 031 is the only con-

tr ol word used by th e TDR -94/94D. La bel031 is the standard ATCRBS control word.

Word label 016 has been redefined for ad-

dressing the TCAS displays. Word labels

013 and 015 ar e TCAS related w ords. La bels

016 and 015 are described here only for

inform a tiona l purposes. The TDR -94/94D

will accept word labels 013, 015, and 016

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a n d p a ss t h e m t h r ou g h u n ch a n g ed t o t h e

TCAS computer. The data f ield, bits 9

thr ough 32, a re described a s follows:

La bel 031:

B it No. D efin it ion

9 S DI C ode (see not e 1)10 S DI C ode (see not e 1)

11 Al t R ep or t in g, O n/O ff (1= on )

12 P a d

13 I den t, O n/O ff (1= on )

14 Alt P or t S elect ed, (1= B )

15 P a d

16 P a d

17 P a d

18 Mode a , code D 1



21 Mode a , code C 1



24 Mode a , code B 125 Mode a , code B 2

26 Mode a , code B 4

27 Mode a , code A1

28 Mode a , code A2

29 Mode a , code A4

30 S SM (see not e 4)


32 P a r it y

La bel 016:


9 S DI C ode (see not e 1)

10 S DI C ode (see not e 1)11 Al t R ep or t in g, O n/O ff (1= on )

12 S P I (0= ident off)

13 D is pla y con tr ol (s ee n ot e 2)

14 D is pla y con tr ol (s ee n ot e 2)

15 S en s level 0 (see n ot e 3)



18 4096, code D 1

19 4096, code D 2

20 4096, code D 4

21 4096, code C 1

22 4096, code C 2

23 4096, code C 4

24 4096, code B 1

25 4096, code B 2

26 4096, code B 427 4096, code A1

28 4096, code A2

29 4096, code A4



32 P a r it y

Label 015:

B it N o. D efin it ion



11 Alt it ude limit A 100




15 Alt it ud e lim it A 1600



18 Alt it ude limit B 100




22 Alt it ud e lim it B 1600



25 spa r e

26 spa r e

27 spa r e

28 spa r e29 spa r e



32 P a rit y

Note 1: See para gra ph 5.6.4.1 below

Note 2: The display control bits control t he TCAS

display a s follows. This information is supplied by a

TCAS control and is passed through the transponder

unchanged.

B I T

14 13 D efinit ion

0 0 P rima ry a nd t ra ffic displa y

0 1 P rima ry displa y only

1 0 TC AS t ra ffic d is pla y on ly

1 1 N o con tr ol fu nct ion pos sib le

Note 3: Sensitivity level is TCAS contr ol informat ion

that is provided via an uplink message from a ground-

based controller . Bi t combination definit ions a re as

follows:

B I T

17 16 15 D efinit ion

0 0 0 S L 0 (Aut oma t ic)

0 0 1 S L 1 (S TB Y)

0 1 0 S L 2 (TA only )

0 1 1 S L 3

1 0 0 S L 4

1 0 1 S L 5

1 1 0 S L 6

1 1 1 S L 7

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Note 4: SSM code definitions are as follows:

B I T D efinit ions

31 30 L abel 031 L abel 016/015/013

0 0 N or ma l oper a tion N or ma l oper a tion

0 1 No com pu ted da t a No com pu ted d at a

1 0 F unct iona l t est F unct iona l t est

1 1 Not used F a ilure w a rning

Label 013:




11 F lig ht l ev el (0= r el a ti ve, 1= a b sol ut e)

12 Alt it ud e s elect (s ee n ot e 2)

13 Alt it ud e s elect (s ee n ot e 2)

14 spa re

15 spa re

16 spa re

17 spa re

18 U ser defined

19 U ser defined20 U ser defined

21 U ser defined

22 0.5, TC AS ra nge








30 S SM (see not e 4 a bove)

31 S 2S M (s ee n ot e 4 a bove)

32 P a rit y

Note 1: See para gra ph 5.6.4.1 below

Note 2: TCAS Altitu de selects:

B I T

13 12 D efinit ion

0 0 Norm a l (-A t o + A)

0 1 Above (-A t o + B )

1 0 B elow (-B t o + A)

1 1 U nrest rict ed

5 .6 .3 .2 C S D B , L a b e l 1 E , C o n t r o l Wo r d

The TDR -94/94D us es C S DB w ord la bel 1E

for CS DB contr ol. All CS DB words consist of6 bytes, with each bytes consist ing of 8 bits.

These bytes are typically identified as bytes 0

t h ro u gh 5 . B yt e 0 is t h e la b el b yt e , byt e 1 is

k n o wn a s t h e st a t u s b yt e , a n d b yt e s 2

t h ro u gh 5 t ra n sm it t h e o bje ct d a t a . Th e

bytes a re described a s follows:

The first eight bits form the first byte and

contain the word label:

B y t e 0 is t h e la b el b yt e :

B it : 7 6 5 4 3 2 1 0

Logic: 0 0 0 1 1 1 1 0H ex: | 1 | | E |

B yt e 1 is t h e st a t u s b yt e :

B it : 7 6 5 4 3 2 1 0

D ef: | | | | | | | < --| <--S I (*)

| | | | | | <--Test (1= on)

| | | | | <--ATC I den t (1= on)

| | | | <--Alt r epor tin g (1= on )

| | | <--M od e (1 = s ta n d by )

| | <--P a d

| <--Code valid (1 = valid)

* For Source identifier definit ion, refer topara gra ph 5.6.4.2 below.

B ytes 2 a nd 3 convey t he ATC code:

B yt e 2 :

B it : 7 6 5 4 3 2 1 0

Va lue: - 4 2 1 - 4 2 1

D ef: P d | | | P d | | |

< ATC C codes > < ATC D codes >

B yt e 3 :

B it : 7 6 5 4 3 2 1 0

Va lue: - 4 2 1 - 4 2 1

D ef: P d | | | P d | | |

< ATC A codes > < ATC B codes >

By t e 4:

By t es 4 and 5 convey the G i ll ham c ode al t i tude

information:

B it : 7 6 5 4 3 2 1 0

Va lue: - 4 2 1 - 4 2 1

D ef: P d | | | P d | | |

< AL T C cod es > < Al t D cod es >

By t e 5:

B it : 7 6 5 4 3 2 1 0

Va lue: - 4 2 1 - 4 2 1

D ef: P d | | | P d | | |

< ALT A c odes > < Al t B codes >

Re fe r t o p a ra g ra p h 5 .7 f or a d d it ion a l G il lh a m

alt itude code informat ion.

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5 .6 .3 .3 C S D B , L a b e l A 0 , A l t i t u d e W o r d

The TD R-94/94D us es C SD B w ord la bel A0

f o r CS D B a l t i t u d e d a t a ; b o t h p re ssu re a n d

b a ro m et ric . As in a l l ot h e r CS D B wo rd s,

word label A0 consists of six 8-bit bytes,

id en t i f ie d a s b yt e s 0 t h ro u gh 5 . B yt e 0 is t h ela b e l b yt e; b yt e 1 is t h e st a t u s b yt e ; b yt e s 2

a n d 3 t ra n sm it t h e pre ssure a l t i t u d e

in f orm a t ion ; b yt e s 4 a n d 5 t ra n sm it t h e

bar ometric alt itude informat ion. The

detailed structure is as follows:

B yt e 0 is t h e la b e l b yt e:

B it : 7 6 5 4 3 2 1 0

L ogic: 1 0 1 0 0 0 0 0

H ex: | A | | 0 |

B y t e 1 i s t h e s t a t u s b y t e :

B it : 7 6 5 4 3 2 1 0

D ef: | | | | | | | <- | <--S I (*)

| | | | | | <--Test (1 = on )

| | | | | <-- 1 = xside ba ro

| | | | <--S tr ut sw (1 = on gn d)

| | | <-- R s vd f or p res el ect (** )

| | <--B a r o a l t v a l id (1 = v a l i d)

| <--Pres alt valid (1 = valid)

* For Source identifier definit ion, r efer to

para gra ph 5.6.4.2 below.

** Bit 5 of byte 1 is bit 1 of a two-bit matrixfor a alt itude preselect function. B it 2 is in

the same location of data word A1.

Bytes 2 and 3 convey pressure alt itude:

B yt e 2 : pa rt 1 of p ressu re a l t d a t a :

B it : 7 6 5 4 3 2 1 0

B in w t : 8 4 2 1 8 4 2 1

Alt w t : | | | | <16 | | | | <1

| | | <32 | | | <2

| | <64 | | <4

| <128 | <8

B yt e 3 : pa rt 2 of p ressu re a l t d a t a :

B it : 7 6 5 4 3 2 1 0

B in w t : 8 4 2 1 8 4 2 1

Alt w t : | | | | <4096 | | | | <-256

| | | <8192 | | | <512

| | <16384 | | <1024

| < -32768 | <2048

B yt e s 4 a n d 5 con vey b a ro m et ric a l t i t u d e :

B yt e 4: p a rt 1 o f b a rom e t ric a l t d a t a :

B it : 7 6 5 4 3 2 1 0

B in w t : 8 4 2 1 8 4 2 1

Alt w t : | | | | <16 | | | | <1| | | <32 | | | <2

| | <64 | | <4

| <128 | <8

B yt e 5: p a rt 2 o f b a rom e t ric a l t d a t a :

B it : 7 6 5 4 3 2 1 0

B in w t : 8 4 2 1 8 4 2 1

Alt w t : | | | | <4096 | | | | <-256

| | | <8192 | | | <512

| | <16384 | | <1024

| < -32768 | <2048

Th e b it p a t t e rn f o r a n y a l t i t u d e wit h in t h era nge -8191 to + 57343 feet, pressure or

barometric, is encoded using two’s

complement arithmetic with a 24576 foot

offset . U se the following conversion methods

a s yo u wish :

1. Select t he alt itude t o be encoded.

2. S u b t ra ct 24 57 6 f rom t h a t qu a n t i t y .

3. I f the result is negat ive, add 32768. *

4. Co n vert t h e resu lt t o bin a ry u sin g t h e

a l t i t u d e b i t w e ig h t s sh o wn a b o ve.

* I f yo u u se a ca lcu la t o r t o d o t h e d e cim a l t obinary conversion, you may not need to add

this qua ntity . I f i t uses 2’s complement

ar ithmetic for the conversion, y ou can ignore

the addit ion.

To decode a 16-bit binary number into a

d e cim a l q u a n t i t y :

1. S e lect t h e bin a ry qu a n t i t y .

2. Co n vert t h e b in a ry n u m b er in t o d ecim a l

u sin g t h e a l t i t u d e b it we ig h t s sh o wn a b ove .

3. I f t he MSB (bit 7 of bytes 3/5) is = 1,

subtra ct 8192. If i t is = 0, ad d 24576. **

4. The result is the equiva lent decima l

q u a n t i t y .

** If you use a calculator to do the binary-to-

decimal conversion, you ma y n ot need to

subtract the 8192 in step 3. But you must

ad d t he 24576. (The 8192 is th e difference

between the 32768 2’s complement sign factor

and the 24576 offset.)

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5 .6 .4 S D I / SI C od e D e f i n i t i o n s

5 .6 .4 .1 A R I N C 4 2 9, S D I D e f i n i t i o n

In ARINC 429, bits 8 and 9, of all word la-

bels, form t he SD I code. The code definitions

depend on the label a s follows:

B I TS D E F I NI TI ON F OR L AB E L S :

9 8 203/204 031/350/371

0 0 All-ca ll Not used

0 1 S ide 1 S ide 1

1 0 S ide 2 S ide 2

1 1 Not used Not used

B I TS D E F I NI TI ON F OR L AB E L :

9 8 013

0 0 b ot h le ft a n d r i gh t , R A/TA, b u s # 1 a n d #2

0 1 l ef t , R A/TA, b u s # 1

1 0 r ig h t , R A/TA, b u s # 2

1 1 not defined

5 .6 .4 .2 C S D B , S I D e f i n i t i o n

I n C S D B , b i t s 0 a n d 1 of b yt e 1 form t h e

source identifier a nd a re defined a s follows:

B I TS D E F I N I TI O N F O R L AB E L S :

1 0 1E/1F/A0/F3

0 0 Not used

0 1 S ide 1

1 0 S ide 2

1 1 Not used

5 .6 .5 O c t a l L a b el D ef i n i t i o n s

In ARINC 429, the label is expressed as an

oct a l n u m b er. Th e e qu iva le n t in CS D B is

expressed as a hexadecimal number.

5 .6 .5 .1 A R I N C 4 2 9, O c t a l L a b e l D ef i n i t i o n

B it s 0 t h ro ug h 7 f orm t h e oct a l la b e l a n d a re


L a bel digit : L S B 2 MS B

B it : 7 6 5 4 3 2 1 0

B it va lue: 1 2 4 1 2 4 1 2

E xa m ple: 1 0 1 1 0 0 0 0

I n ter p: | <--5-->| | <--1-->| | -0-|

There ar e thr ee importan t points here:

1 . N ot ice t h a t t h e M S B is on t h e r ig h t , d e-

fined by t he lower ordered bits. This is re-

verse d f rom t h a t of t h e d a t a f ie ld w h e re t h e

MSB is defined by the higher ordered bits.

2. Notice also tha t th e most significan t bit

(MSB ) is defined by only tw o bits. This

m ea n s t h a t t h e M S B ca n h a v e a v a l u e n o

g re a t e r t h a n 3 (2 + 1 ). Th is a lso m e a n s t h a t

the numerically la rgest octa l code possible is

377 which is displayed, bits 0 through 7, as

11111111.

3 . N ot ice a lso t h a t t h e b it va lu es a r e re-

verse d fro m t h e va lu es in t h e d a t a f ield s. I n

t h e d a t a f ield s, t h e va lu e s in cre a se a s yo u

m ove f rom rig h t t o lef t . He re t h e y va lu e s

decrease in value, moving from right to left .

5 .6 .5 .2 C S D B H ex a d ec i m a l L a b e l

D e f i n i t i o n

I n CS D B t h e la b e l o f t h e wo rd is a t wo d ig i t

hexadecimal number and is defined in the

f irst 8 -b it s , b yt e 0, o f t h e CS D B

tra nsmission. The bits a re defined as follows:

L a bel digit : MS B L S B

B it : 7 6 5 4 3 2 1 0

B it va lue: 8 4 2 1 8 4 2 1

E xa m ple: 0 0 0 1 1 1 1 0

In ter p: | ------1-------| | ------E -------|

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5.7 G I L L H A M C O D E D E SC R I P T I O N

w i t h E N C O D I N G A N D D E C O D I N G

I N ST R U C T I O N S

Th is p a ra g ra p h con t a in s a d e scrip t ion of t h e

G i ll ha m (AR I NC 572) a l t it u de en cod in g

s ch em e. Th e pa r a gr a ph a l so in clu desinstructions for encoding a nd decoding. This

ca n b e h e lp fu l i f y o u e ncou n t er a n a l t i t u de

d is cr e pa n c y d u r in g a t e st or f a u lt i s ol a t i on

procedure that is caused by a faulty digitizer or

b rok en wire in t h e a l t i t u d e b us.

Table 5-15 shows the encoding matrix for both

the 500-foot increments a s w ell a s t he 100-foot

in cr em en t s. F ollow i ng t h e t a b le a r e t h eencoding an d decoding instructions.

T a b l e 5 -1 5 . G i l l h a m A l t i t u d e, A R I N C 5 7 2 , E n c od i n g S ch em e

| <--- ----- ----- ----- ----- ----- ----- A4, B 1, B 2, B 4 ---- ----- ----- ----- ----- ----- ---- ---- --->|

D 2,D 4, A1,A2 0000 0001 0011 0010 0110 0111 0101 0100 1100 1101 1111 1110 1010 1011 1001 1000

0000

0001

0011

0010

0110

0111

0101

0100

1100

1101

1111

1110

1010

1011

1001

1000

0 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15

31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16

32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47

63 62 61 60 59 58 57 56 55 54 53 52 51 50 49 48

64 65 66 67 68 69 70 71 72 73 74 75 76 77 78 79

95 94 93 92 91 90 89 88 87 86 85 84 83 82 81 80

96 97 98 99 100 101 102 103 104 105 106 107 108 109 110 111

127 126 125 124 123 122 121 120 119 118 117 116 115 114 113 112

128 129 130 131 132 133 134 135 136 137 138 139 140 141 142 143

159 158 157 156 155 154 153 152 151 150 149 148 147 146 145 144

160 161 162 163 164 165 166 167 168 169 170 171 171 173 174 175

191 190 189 188 187 186 185 184 183 182 181 180 179 178 177 176

192 193 194 195 196 197 198 199 200 201 202 203 204 205 206 207

223 222 221 220 219 218 217 216 215 214 213 212 211 210 209 208

224 225 226 227 228 229 230 231 232 233 234 235 236 237 238 239

255 254 253 252 251 250 249 248 247 246 245 244 243 242 241 240

256 segments, at 500 -ft interva ls, from -1000 ft t o 127,000 ft.

1 00 -f t b i t s 10 0-f t v a l u e i f 50 0-f t s eg m e nt i s :

C 1 C 2 C 4 o dd even

__ __ __ _______ _______

0 0 1 7 (+ 200) 8 (- 200)

0 1 1 6 (+ 100) 9 (- 100)

0 1 0 5 (00) 0 (00)

1 1 0 4 (- 100) 1 (+ 100)

1 0 0 3 (- 200) 2 (+ 200)

It is importa nt to note that this scheme has no provision for C 1, C 2, a n d C 4 bit pa tt erns 000, 111, or 101.

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5 .7.1 G i l l h a m Cod e D ec od i n g I n st r u c t i o n s

This paragraph provides a method of

t ra n sla t in g a G il lh a m co d e p a t t e rn in t o

a l t i t u d e .

1 . D e t e rm in e t h e e n cod e d b it s a n d w ri t e t h e m

in t o t h e fol lowin g m e a su re d b i t s row. I f a n y of t h e

bits a re missing or n ot connected (and this is likely for

b it s D 2, a n d D 4.) ju st e n t e r a 1 f or t h a t b i t . (A

measured 1 means it is not act ive.)

B it n a m es: A1 A2 A4 B 1 B 2 B 4 C 1 C 2 C 4 D 1* D 2* D 4___ ___ ___ ___ ___ ___ ___ ___ ___ ___ ___ ___

Meas ured bits: ___ ___ ___ ___ ___ ___ ___ ___ ___ _1_ ___ ___

Inv erted logic: ___ ___ ___ ___ ___ ___ ___ ___ ___ _0_ ___ ___

2 . I n ve rt ea ch of t h e bi t s a n d wr i t e t h a t

pattern into the inverted logic row.

3. From the inverted logic row, determine the

encoded bit pat tern for bits A4, B 1, B 2, B 4.

4. C om p a r e t ha t p a t t er n t o t h e l is t i ng of

patt erns on Table 5-15 for A4, B 1, B 2, B 4 a n d

note the column where you found the match.

5. From the inverted logic row, determine the

encoded bit pattern for bits D 2, D 4, A1, A2.

6 . Co m pa re t h a t p a t t e rn t o t h e l is t in g of

patterns in the left column of Table 5-15 and

n ot e t h e r ow wh e re yo u f ou n d t h e m a t ch .

7. Read th e segment number from the point

a t wh ich you r m a rk e d colu m n a n d row intersect .

8 . M u lt ip ly t h a t se g m e n t n u m b er b y 5 0 0 a n d t h e n

subtra ct 1000. The result is the a lt itude to the

nearest 500 feet.

9. From th e inverted logic row , determine the encoded

b it p a t t e rn f o r b i t s C 1, C 2 a n d C 4 .

10. I f C 1 a n d C 4 a re b ot h 0 t h e n you a re f in ish ed .

The result of step 8. is the final result . I f C 1 a n d C 4

ar e not both 0 t hen proceed.

11. Find the sequence for C 1, C 2 a n d C 4 in the lower

part of Table 5-15. Note that row.

12. Depending on whether the segment number from

step 7. above was odd or even, add or subtract either

100 or 200 to or fr om the 500-ft a ltit ude. The result is

the alt itude to the nearest 100 feet .

Exa mple: Suppose you measure t he following logic levels on the t est pan el (1 = high or open, and

0 = lo w)

Tes t P oin ts : A1 A2 A4 B 1 B 2 B 4 C 1 C 2 C 4 D 1* D 2* D 4___ ___ ___ ___ ___ ___ ___ ___ ___ ___ ___ ___

Mea sur ed: 1 0 0 0 1 1 1 1 0 1 1 0

I n ver t logic: 0 1 1 1 0 0 0 0 1 0 0 1

C ol u mn da t a : 1100

R ow da ta : 0101

Referring to t he ma trix in Table 5-15 above,this identifies segment 104.

Multiply segment by 500 an d subtra ct 1000:

104 x 500 - 1000 = 51 000.

The C 1, C 2, a n d C 4 bits determine the 100-ft

alt itude offset from th e rounded 500-ft value.

Because the identified segment is an even

number, use the data under the even column.

Comparing the inverted logic bit pattern for

C 1, C 2, a n d C 4 (001) to the list ing, we find tha t it

corresponds to the first entry. This declares tha t th e

hundred foot va lue is t he nea rest 800 (or 200 feet lessthan the rounded 500-ft level). Thus the measured bit

pattern yields an alt itude of 50 800 feet .

* D 1 a n d D 2 are not connected on the test panel. For

purposes of this illustrat ion, assume an open to be a

logic 1. You will notice in Ta ble 5-15 tha t D 1 is not

u sed , a n d D 2 is not act ive at a lt itudes below 60 000

feet.

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5.7.2 G i l l h a m C od e, E n c od i n g

I n st r u c t i o n s

This paragraph will describe a process to

determine the code needed for a part icular

a l t i t u d e :

1. Select the desired alt itude.

2. Add 1000 to tha t number.

3 . Rou n d t h a t n u m b e r t o t h e n ea re st m u lt ip le

of 500. (Sa ve the difference thus dropped; it

will be needed to determine the 100-foot bit

pattern in step 6. below.)

4. Divide the rounded number by 500. This

becomes the 500-ft segment number for the

matrix in Table 5-15 above.

5 . L oca t e t h e seg m e n t n u m b er in t h e t a b le

a n d :

a . Re a d t h e log ic p a t t e rn f or A4, B 1, B 2, B 4

from the top of the column and enter it in

the spaces below .

b . Re a d t h e log ic p a t t e rn f or D 2, D 4, A1, A2 from

the left column of the segment row and enter i

the spaces below.

6. I f t he a bsolute va lue of th e sa ved difference from

a b o ve is le ss t h a n 5 0, u se t h e t h ird p a t t e rn f o r C 1, a n d C 4 (010). I f t he va lue of th e saved difference f

3. above is 50 or more, round it t o the nea rest 100.

This must be either 100 or 200 and either more or

tha n t he 500-ft va lue.

7. I f the 500-ft segment number is a n even numbe

use th e even column to determine th e 100-ft bit pa

t e rn . (Th is m e a n s t h a t t h e a l t i t u d e rou n d ed t o t h e

nearest 500-ft must be in the form of XX000.)

8 . I f t h e 5 00 -f t se g m en t n u m b e r is a n od d n u m b e

use th e odd column to determine th e 100-ft bit pa t

t e rn . (Th is m e a n s t h a t t h e a l t i t u d e rou n d ed t o t h enearest 500-ft must be in the form of XX500.

B it p a t t e rn e n t ry:

Alt it ude: A1 A2 A4 B 1 B 2 B 4 C 1 C 2 C 4 D 2 D 4

_______ ___ ___ ___ ___ ___ ___ ___ ___ ___ ___ ___

Example:

D e t e rm in e t h e b i t p a t t e rn f o r a n a l t i t u d e o f 11

800 feet.

1. Add 1000: 12 800.

2. Round to near est mult iple of 500: 13 000,

a nd sa ve difference: -200 ( less).

3. Divide 13 000 by 500: 26.

4 . L oca t e se gm e n t n u m b e r 2 6 on t h e m a t rix

a b o ve a n d :

a . R ea d t h e A4, B 1, B 2, B 4 b it p a t t e rn f ro m t h e

top of the column: 0111. Then ent er each bitinto the appropriate space below.

b . R ea d t h e D 2, D 4, A1, A2 bit pattern from the left

column of the sam e row. 0001. Then enter each b

into the appropriate space below.

5. The sa ved va lue from step 3. is -200.

6. The segment nu mber 26 is an even number,

t h e ref ore t h e C1, C 2, C 4 b it p a t t e rn is re a d f rom t h

top entry: 001. You can, of course, also read this o

the basis of the hundreth’s digit value which in thi

ca se is a n 8 .

B it p a t t e rn e n t ry:

Alt it ud e: A1 A2 A4 B 1 B 2 B 4 C 1 C 2 C 4 D 2 D 4

_11 800__ _0_ _1_ _0_ _1_ _1_ _1_ _0_ _0_ _1_ _0_ _0_

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5.8 A C CE P T A N C E T E ST , T E ST P A N E L

A S S E M B L Y I N S T R U C T I O N S

5 .8 .1 G E N E R A L

This paragraph provides the instructions and

ma terial l ist ing necessar y for a ssembly of the ATP

test panels listed in ta ble 5-1. Several test

equipment suppliers offer a product item(s)

equivalent to these specificat ions. I f you wish, you

should feel free to purcha se such a n it em.

Otherwise, it can be locally fabricated using the

d a t a su p plied in t h is p a ra g ra p h .

If you fabricated your fixture according to

instructions supplied an earlier edit ion of this

manual, you will f ind modificat ion instructions inpara gra ph 5.8.3 below. This edit ion, an d all

subsequent edit ions that introduce changes to the

Acceptance Test Test Panel will give modification

instructions in paragraph 5.8.3.

Figure 5-2 is the test setup diagram showing how

t h e va riou s i t em s a re in t ercon n e ct e d . F ig u re 5 -3

is a suggested panel layout for the enhanced

version. Figure 5-4 is a schemat ic diagra m of the

abbreviated test panel.

Figure 5-5 is a schematic diagram for the enhanced

version of test pa nel. Table 5-16 is a list of the

ma terial required for th e enha nced version. Table

5-17 is a similar list ing for the a bbreviat ed version.

Table 5-18 is a list ing of the ma nufacturers an d

suppliers for t he va rious items needed t o assemble

t h e p a n e ls . E qu iva le n t p a rt s m a y b e ob t a in e d f rom

other sources. P ar agr aph 5.8.2 an d figures 5-5

through 5-8 describe the control interconnect

cables. You ma y select one or more of these cables,

depending on th e ty pe of control you plan to use.

These cables a re required for both t est pan el

versions. However, you will notice tha t the cable

for t he C TL-92/92A can be differ ent , depend ing onthe test pa nel version you intend to use. The

abbreviated version has no provision for Gillham

code switching and a number of other functions.

Thus, t hese connections a re not required in the

cable if you are using that version test panel.

Ta b le 5 - 1 6 . En h a n c ed Ve r s io n o f Te s t Pa n e l, Pa r t s L is t

I TE M RE F D E S QTY MANU F AC TU RE R C OLLI NS P ART

N U M B E RNAME P N

Toggle switch,

SP , on/off

S1, S5, S7, S8,

S10, S11, S17-

S57, S59

48 C & K C om pon en ts , I nc 7107S YZWQE 266-5321-150

Toggle switch,

SP DT, on/on

S 9 1

Toggle switch,

DP DT, on /on

S 2, S 3 2 7201S YZQE 266-5321-200

Momentary

switch, SP, push-

on

S 4, S 6 2 8121S H ZG E 266-5404-010

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Ta b le 5 - 1 6 . En h a n c ed Ve r s io n o f Te s t Pa n e l, Pa r t s L is t ( co n t ’d )

I TE M RE F D E S QTY MANU F AC TU RE R C OLL I NS P ART

N U M B E R

NAME P N

Wafer, switch, 2-

pole, 4-psn

S 13 1 G r a y hill I nc. 44A3001204NF Not a va ila ble from

Collins

Wafer switch, 5-

pole, 2 -psn

S 58 1 44A3004202NF

Wafer switch, 4-

pole, 4 -psn

S 12 1 44A3002204NF

Wafer switch, 6-

pole, 4 -psn

S 16 1 44A3006204NF

L a m p holder 6 C hica go Minia t ure

Lamp, Inc.

L H 73/1 included in 262-

2828-0X0

L a m p len, red L D S 2-3 2 L C 12YN2 262-2828-010

L a m p lens, y ellow L D S 1,4-6 4 L C 12RN2 262-2828-030

L a m p, 28 V D S 1-6 6 G E C o. 385 262-2171-010

F use holder XF 1 1 B ussma n D iv. H KP -H , or F H N-20G Not a va ila ble from

CollinsF use, 5A S B F 1 1 F 02G 250V5AS

B a na na ja ck, blk TP 1,3,5 2 E .F .J ohnson C o. 360-0241-000

B a na na ja ck, y el TP 2,4,6 3 360-0245-000

P hono plug, 1/4" J 2,3,4,5,6,7,8,9 8 S wit chcr a ft I nc. M641/12-1 358-0014-000

P hono ja ck To ma te w it h:J 2,3,4,5,6,7,8,9

See figure 5-9

AR P J -055B Not a va ila ble fromCollins

BNC to TNC

a d a p t e r

Needed to

adapt ATC-

601 rf cable to

a n t e n n a

connectors

2 M/A-C OM Om ni

Spectra , Inc.

3182-2320-00 N ot a va ila b le f rom

Collins

RF load (also

shown on table 5-1

Needed to

t e r m i n a t e

unused rf

a n t e n n a

connection.

1 3101-6100-00

50-pin D-submin,conn (socket)

1 I TT C a nnon D D MF -50S -A176 371-0182-000

50-pin D-submin,

conn (plug)

See figures 5-

6, 5-7, 5-8

AR D D M50P -C 37-A176 371-0118-000

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Ta b le 5 - 1 6 . En h a n c ed V e r s ion o f Te s t Pa n e l, Pa r t s L is t (c on t ’d )

I TE M RE F D E S QTY MANU F AC TU RE R C OLLI NS P ART

N U M B E R

NAME P N

TDR-94D

instal lat ion kit

1 C ollins G enera l

Aviat ion D ivision

628-8660-001

MMT-150

Mounting Tray

1 622-9672-003

C TL-92/92A

mating connector

S ee figure 5-6 1 359-0305-590, or

371-6110-000

RTU-870A/T

mating connector

S ee figure 5-7 1 359-0601-010

TTC-920G mating

connectors

S ee fig ur e 5-8 1 of

each

J 1:

MD24266R76B24S7

J 2:MS24266R16B24SB

J 1: 359-4068-030

J 2: 359-4118-240

Res, film, 100kΩ,

± 1%, 1/4W

R1-11 11 MS RN65D 1003F 705-7192-000

Res, film, 825Ω,

± 1%, 1/2W

R12-22 11 RN65D 8250F 705-7092-000

G rommet , 1-in, id 1 At la nt ic I ndia Rubber

C o.

2277 201-0012-000

Chassis,

8 x 12-in , box

Or use a 19

rack mounting

panel

1 B ud I ndust ries, I nc. AC 424 021-0347-050

S wit ch knobs F or w aferswitches

5 a n y w i th 1/4-in ch s ha f tdia and setscrew

locking

N/A

D a t a b u s r ea d e r

cables

S ee fig ur e 5-9 AR

Chassis, bottom

panel

Opt iona l 1 B P A 1519 Not a va ila ble from

Collins

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Ta b le 5 - 1 7 . Ab b r e v ia t e d Ve r s io n o f Tes t Pa n e l, Pa r t s L is t

I TE M RE F D E S QTY MANU F AC TU RE R C OLL I NS P ART

N U M B E R

NAME P N

BNC to TNC

a d a p t e r

Needed to

adapt ATC-

601 rf cable to

a n t e n n a

connectors

2 M/A-C OM Om ni

Spectra , Inc.

3182-2320-00 N ot a va ila b le f rom

Collins

RF load (also

shown on table 5-1

Needed to

t e r m i n a t e

unused rf

a n t e n n a

connection.

1 3101-6100-00

50-pin D-submin,

conn (socket)

1 I TT C a nnon D D MF -50S -A176 371-0182-000

50-pin D-submin,

conn (plug)

See figures 5-

6, 5-7, 5-8

AR D D M50P -C 37-A176 371-0118-000

TDR-94D

instal lat ion kit

1 C ollins G enera l

Aviat ion D ivision

628-8660-001

MMT-150

Mounting Tray

1 622-9672-003

C TL-92/92A

mating connector

S ee figure 5-6 1 359-0305-590, or

371-6110-000

RTU-870A/T

mating connector

S ee figure 5-7 1 359-0601-010

TTC-920G ma tin gconnectors

S ee fig ur e 5-8 1 ofeach

J 1:MD24266R76B24S7

J 2:

MS24266R16B24SB

J 1: 359-4068-030J 2: 359-4118-240

C h a s si s N ot e : Th e s iz e of ch a s si s f or t h e a b b re vi a t ed v er s ion of t h e t e st p a n el i s op t ion a l . Th e p ri ma r y

limitat ion is tha t i t must be large enough to accomodate the connectors and other parts. Use of a 50-

pin D-type connector can a lso be seen as optional. If you plan to use only one type of control, such as

the C TL-92/92A, you ma y w an t t o connect th e cable directly to the t est pa nel as a pendant cable.

Ca ble grommet,

1/2-in. id

For pendant

cable exit i f

used.

1 At la nt ic I n dia 2283 201-0002-006

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Ta b le 5 - 1 4 . Eq u ip me n t a n d Co mp o n e n t Ma n u f a c t u r e r s a n d Su p p l ie r s

S U P P LI E R AD D RE S S P ROD U C T

C ol li ns G e n er a l Av ia t i on D i vi si on 400 C ol li ns R oa d

Cedar Rapids IA 52498

TDR-94D Installation kit, MMT-150

Mount ing Tra y, CTL-92/92A mat ing

connect or, RTU-870A/T ma tin g

connector, TTC-920G mating connector

I F R S yst ems, I nc. 10200, West York S t reet

Wichita, KS 67215

ATC-601 Ramp Test Set

At la nt ic I nst rument s, I nc. P .O. B ox 021466

Melbourne, FL 32902

Da ta Tra c 200/400/400H Da ta bus

Analyzers

J cAI R 400 I ndust ria l P a rkw a y ,


Test pan el a nd 429E ARINC 429 TX/RX

Databus Analyzer

Avionics S pecia list , I nc. 3833 P remier Ave.

Memphis, TN 38118

Test panel

M/A-C OM Om ni S pct ra , I nc. 21 C on tin en ta l B lvd

Merrimac, NH 03054-9979

Rf load and BNC-to-TNC adapter

C & K C omponent s, I nc. 15-T River da le Ave.

Newton, lMA 02158

(617) 964-6400

Toggle switches

G ra y hill I nc. 561 H illgr ove, P .O.B ox 10373

LaG range I L 60525

(708) 354-1040

Wafer switches

C hica g o Min ia t ur e L a mp, I nc. 1080-T J oh ns on D r.

Buffalo Grove, IL 60089

(908) 459-3400

Indicator lamp holders and lens

B u s sm a n D iv ., C oop er I n du st r ies P . O. B ox 14460St. Louis, MO 63178

(314) 394-2877

Fuses a nd fuse holder

G E C o., Minia ture La mp D ept . Nela P a rk

Cleveland OH 44112

(216) 266-2121

Light bulb

E .F . J ohn son C o. Minnea polis, MN 55459-0089 B a na na ja cks

I TT C a nnon, C orp. 1851-T E . D eer Ave.

Santa Ana, CA 92705

(714) 557-4700

Connectors

B ud I ndust ries, I nc. P .O. B ox 431, 4605 E . 355t h S t.

Willoughby, OH 44094

(216) 946-3200

Chassis

At la nt ic I ndia Rubber C o. 317 W. D oubla s S t.

Goshen, IN 46256

Rubber grommet

S w it chcra ft I nc. 5555-T N. E lst on Ave.

Chicago, I L 60630

(312) 792-2700

Ph ono plug and jack

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Acceptance Test, Abbreviated Test Panel

Schematic Diagram

Figure 5-4

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Ac c ep ta n c e Te s t, En h a n c e d Te s t Pa n e l

Sc h ema tic D ia g r a m

Fig u r e 5 - 5 ( Sh ee t 1 o f 3 )

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Fig u r e 5 - 5 ( Sh e e t 2 )

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Fig u r e 5 - 5 ( Sh e e t 3 )

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Test Panel Mating Connector, D-submin, 50-pin, plug

DD M50P -C37-A176, C P N: 371-0118-000

CTL-92/92A Cont rol, Ma ting Connect or P 1

MS 3126 E20-41SY, CP N 359-0305-590, or

MS 3116E 20,41SY, C P N: 371-6110-000

S igna l Na me/D escript ion F rom

Pin No.

To

Pin No.

Wire Size or Type

28 V dc, pr im a r y pow er no. 1 (+ ) 1 G 22 AWG

28 V dc, pr im a r y pow er no. 2 (+ ) 18 t 22 AWG

P rima ry pow er, ground (-) 17 s 22 AWG

P rima ry pow er, ground (-) 50 P 22 AWG

C TL da t a out , 1B 8 S 26 AWG , S TP

C TL da t a out , 1A 41 R 26 AWG , S TP

C TL da t a in , 1B 31 U 26 AWG , S TP

C TL da t a in , 1A 10 V 26 AWG , S TP

I dent input 4 b 26 AWG

S elf-t est (discret e input /out put ) 6 E 26 AWG (t his w ire w as not included in t he

original version of this cable)

The remaining connections ar e not required when using the Abbreviat ed Version of Test P an el

No. 1 t ra nsponder in st by 20 W 26 AWG (t his w ire w a s not included in t he

original version of this cable)

No. 2 t ra nsponder in st by 10 X 26 AWG

No. 1 t ra nsponder on/off 11 B 26 AWG

No. 2 t ra nsponder on/off 27 C 26 AWG

No. 1 sw 28 V dc out 28 k 26 AWG

No. 2 sw 28 V dc out 43 j 26 AWG

Acceptance Test, Test Panel

CTL - 9 2 / 9 2 A Co n t r o l I n t e r c o n n e c t Ca b le As s e mb ly Dia g r a m a n d Wir e L is t

Figure 5-6 (Sheet 1 of 2)

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DD M50P -C37-A176, C P N: 371-0118-000

CTL-92/92A Cont rol, Ma ting Connect or P 1

MS 3126 E20-41SY, CP N 359-0305-590, or

MS 3116E 20,41SY, C P N: 371-6110-000


Pin No.

To

Pin No.

Wire Size or Type

Alt code, A1 (input ) 12 c 26 AWG

Alt code, A2 (input ) 13 e 26 AWG

Alt code, A4 (input ) 14 d 26 AWG

Alt code, B 1 (input ) 28 i 26 AWG

Alt code, B 2 (input ) 29 h 26 AWG

Alt code, B 4 (input ) 30 f 26 AWG

Alt code, C 1 (input ) 45 J 26 AWG

Alt code, C 2 (input ) 46 H 26 AWG

Alt code, C 4 (input ) 47 F 26 AWG

Alt code, D 4 (input ) 48 p 26 AWG

Alt code, comm on 5 g 26 AWG


CTL - 9 2 / 9 2 A Co n t r o l I n t e r c o n n e c t Ca b le As s e mb ly Dia g r a m a n d Wir e L is t

Figure 5-6 (Sheet 2)


RTU- 8 7 0 A Co n t r o l I n t e r c o n n e c t Ca b le As s e mb ly Dia g r a m a n d Wir e L is t

Fig u r e 5 - 7 ( Sh ee t 1 o f 2 )

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DD M50P -C37-A176, C P N: 371-0118-000

RTU -870A/T Ra dio Tunin g U nit , Ma tin g Conn ector P 1

MS 27473T20F-2S, CP N 359-0601-010,

Strain relief: MS27506F20-2, CPN: 359-0637-070

S igna l Na me/D escript ion F romPin No.

ToPin No.

Wire Size or Type

28 V dc, pr im a r y pow er no. 1 (+ ) 1 1 22 AWG

28 V dc, pr im a r y pow er no. 2 (+ ) 18 7 22 AWG

P rima ry pow er, ground (-) 17 3 22 AWG

P rima ry pow er, ground (-) 50 3 22 AWG

RTU data out, 1B (ARINC 429 data from

RTU to XPDR)

26 45 26 AWG , S TP

RTU data out, 1A (ARINC 429 data from

RTU to XPDR)

25 44 26 AWG , S TP

RTU dat a in , 1B (ARINC 429 data input to

RTU from XPDR)

31 29 26 AWG , S TP

RTU data in, 1A (ARINC 429 data input to

RTU from XPDR)

10 28 26 AWG , S TP

I dent input 4 11 26 AWG


RTU- 8 7 0 A Co n t r o l I n t e r c o n n e c t Ca b le As s e mb ly Dia g r a m a n d Wir e L is t



TTC- 9 2 0 G Co n t r o l I n t e r c o n n e c t Ca b le As s e mb ly Dia g r a m a n d Wir e L is t


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DD M50P -C37-A176, C P N: 371-0118-000

TTC-920G Tra nsponder /TCAS C ontr ol, Ma ting Connect or1

P 1: M D24266R76B24S7, CP N: 359-4068-030

P 2: M S24266R16B24S8, CP N: 359-4095-700


Pin No.

To

Pin No.

Wire Size or Type

115 V ac, 400 Hz, primar y power1 (high)(externa l source)

SourceHigh

J 1-3J 2-3*

22 AWG

115 V ac, 400 Hz, prima ry power (low)

(externa l source)

Source

Lo w

J 1-4

J 2-4*

22 AWG

P r im a ry pow er, ground (-) 17 J 1-6

J 2-6*

22 AWG

Air ground (input) (strap for normal

operation)

17 J 1-11*

J 2-11*

26 AWG

P r im a ry pow er, ground (-) 50 J 1-8

J 2-8*

22 AWG

ARINC 429, da ta out, 1B (TTC-920G

output to XPDR)

25 J 1-22 26 AWG , S TP

ARINC 429, da ta out, 1A (TTC-920G

output to XPDR)

26 J 1-23 26 AWG , S TP

Air gr ound (input ) 17* J 1-11*

J 2-11*

26 AWG

Monit or la m p pow er (+ 28 V dc) 1* J 1-18* 26 AWG

Monit or la m p pow er (+ 28 V dc) 1* J 1-18* 26 AWG

Light ing pow er (+ 28 V dc) 18* J 2-1* 26 AWG

S t a ndby/on 20* J 1-7 26 AWG

F a ult Monit or (XP DR out pu t ) 12* J 1-20*

J 2-20*

26 AWG

* These wires were not shown in the original cable wiring list.


TTC-9 2 0 G Co n t r o l I n t e r co n n e ct Ca b le As s e mb ly Dia g r a m a n d Wir e L is t


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5 . 8 . 2 M i s c e l l a n e o u s C a b l e s

Figure 5-9 shows the a ddtional cables n eeded

for the Accepta nce Test. The tip jack cables

shown in the upper section of sheet 1 are

needed for dc power input to the DataTrac

200 or 400. If you opera te from a c power or

battery power only you do not need these.The D at aTra c 400H an d J cAIR 429E, a s w ell

a s som e D a t a Tra c 2 00 , h a ve t h e ir o wn a c-t o -

dc pow er convert er/ba tt ery recha rge fa cility.

In t he lower section of sheet 1, the B NC-to-

single phono jack cables a re needed for th e

RX function of the Da ta Tra c 400, and 400H.

For Da ta Tra c 400 operat ion y ou can

substitute two of the lower cable for the

u p pe r a n d t h e n u se a se pa ra t e TX p ort . F o r

the DataTrac 400H you must use the uppercable because it ha s only one TX port an d

therefore you must use that port for both the

control and alt itude functions.

Sheet 2 of this f igure shows the cables

needed for th e Da ta Tra c 200 a nd the J cAIR

429E, respectively.

In assembling the B NC-to-phono plug cables,

be sure to connect the bus A wires between

the BNC center and the proper phono plug

conta ct . In a ssembling th e phono plug-to-

phono plug cables, be sure t o connect similar

conta cts; i .e. , do not reverse the A a nd B

lines. In assembling t he phono plug-to-tip

jack cables, be sure the A w ire is connected to

t h e ja ck id en t i f ie d a s H I . I n a l l ca se s, d o n ot

use the the phono plug common as a signal

carrying contact .

Acceptan ce Test, B us Reader t o Test Panel I nterconnecting Cables

Figure 5-9 (sheet 1 of 2)

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Acceptance Test, Bus Reader to Test Panel Interconnect Cables

Figure 5-9 (sheet 2)

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5 .8 .1 A c cep t a n c e T e st P a n el M o d i f i c a t i o n

R e c o r d .

5 . 8 . 1 . 1 M o d i f i c a t i o n 1 .

At modificat ion 1 the following changes a re

introduced.

1 . An a d d it ion a l S P D T swit ch , S 56 , is a d d ed

w ith connection to U U T pin P 1-28. This

function is la beled AUTO ALT. When th is

function is ena bled (EN, gr ound applied to

P1-28), the unit automatically switches to the

non-selected altitude port for valid reporting

a l t i t u de d a t a i f t h e a lt i t u de d a t a a t t h e

selected source is interrupted or invalid.

2 . E xist in g swit ch , S 1 7, wit h con n e ct ion t o

U U T pin P2-14 is redefined. This switch

previously functioned a s t he ALT INP U T

P ORT S E L a n d swit ch e d t h e a l t i t u d e in p u t t o

either port A or port B . In -003 units,a l t i t u d e d a t a is re qu ire d a t b ot h p o rt s

simultaneously therefore this switching

function is cha nged (see 3. below). The new

function, S OU RCE SE LEC T, C TL/SE L,

functions with the exist ing alt itude source

select pins P2-41 and P2-42 as follows:

S S * AS 0 AS 1 Al t i t ud e Ty p e S e le ct e d

1 0 0 AR INC 429 on AR INC por ts A a nd B

1 0 1 C S DB on C S D B por t s A a nd B

1 1 0 AR INC 575 on AR INC por ts A a nd B

1 1 1 AR INC 572 (G illh am ) on t he G illh am

parallel port0 0 0 P or t A a lt it ud e on t he s elect ed con tr ol

bus (either ARINC 429 or C SDB ) and

port B altitude type ARINC 429 on

ARINC port B.

0 0 1 P or t A a lt it ud e on t he s elect ed con tr ol

bus (ei ther ARINC 429 or CSB B) a nd

p or t B a l t i t u d e t y pe C S D B o n C S D B

port B.


bus (either ARINC 429 or C SDB ) and

port B altitude type ARINC 575 on

ARINC port B.


bus (ei ther ARINC 429 or CSDB ) and

port B al t i tude type Gil lham on theGil lham pa ral lel port .

* CTL = active low (ground on P2-48) and

S E L = o pe n .

3. ALTER NATE DI G ITAL ALTITU DE

S OU RCE in pu t ja ck J 5 is a d d e d a n d e xist in g

swit ch S 1 6 is e xp a n d e d t o a l low t w o a l t i t u d e

sources to be connected simultaneously. S16

allows selection of the a ppropriat e input port

depending on t he ty pe of da ta being supplied.

S16 also controls the select discretes P2-41

(AS0) and P 2-42 (AS1) (see 2. above). Da ta

supplied on t he ALTER NATE DI G ITAL

ALTITUDE SOURCE is switched to port B;

e it h e r ARI N C o r CS D B .

4. E xist in g a l t i t u d e in pu t ja ck J 4 is

relabeled as P RIMARY DI G ITAL ALTITU DE

S OUR CE . S w it ch S 1 6 con t ro ls t h econnection of this input to th e a ppropriat e

UUT port A (either ARINC or CSDB).

5. S w it ch S 5 7, RE P ORTI N G AL T S E L ,

P A/P B , is add ed. This sw itch contr ols the

discrete P 2-48 wh ich selects t he alt itude port

used for a lt itude reporting (Modes C an d S ).

When P 2-48 is grounded, port B dat a is used

for a lt itude reporting. When open port A

d a t a is u se d .

6. TCAS IN an d TCAS OU T input jacks, J 6

and J 7, are added to allow monitoring of the

TCAS data.

7. DATALINK IN a nd D ATALINK OUTjacks, J 8 an d J 9, are a dded to a llow airborne

d a t a l in k bu s m o n it o rin g . Use rs sh o u ld se e

t h is a d d it ion a s o pt ion a l a t t h is t im e b e ca u se

the airborne datalink function has not been

industry defined and therefore is not fully

implemented. I t is presented here prima rily

so that builders of this test panel can allow

for the eventual addit ion of this function if

a n d w h e n it is requ ire d. P a rt o f t h is ch a n g e

also includes t he a ddit ion of sw itch S58.

This sw itch supplies a ground t o P 2-60 to

enable/select t he air borne da ta link function.

8. Tha t portion of S12 which supplies theground to pins P 2-56, -57, a nd -58 has been

changed slightly. The common wa s

connected to ground. I t sh ould instead be

connected t o P 2-52 which is ava ilable at

switch S16.

9. The common for t he G illham code

switches should be connected to P1-12.

10 . Th e XF E E D I N a n d OU T la m p s, D S 3

a n d D S 4 , a n d sw it ch S 3 p osi t ion la b e lin g

wa s reversed on the 6 J anua ry 1992 issue of

t h e t e st p a n e l sch e m a t ic dia g ra m . N o wirin g

changes are needed.

11. Check the panel layout, f igure 5-3

carefully. You will f ind a few minor label

changes.

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5.9 F L I G H T L I N E T E S T , T E S T P A N E L

A S S E M B L Y I N S T R U C T I O N S

5.9.1 I n t r o d u ct i o n

This paragraph provides the instructions and

m a t e ria l l is t in g n e ce ssa ry t o a ssem b le t h eFlightline Test P an el shown in figure 5-10. A

number of test equipment suppliers ma y offer

a product item equivalent these

specificat ions. I f so, you should feel free to

p u rch a se su ch a n i t e m . Ot h e rwise, it ca n b e

loca l ly f a b rica t e d u sin g t h e d a t a in t h is

p a ra g ra p h .

5 .9 .2 F l i g h t l i n e T est P a n el A ssem b l y

a n d U se

This test panel allows access to all input and

output signals to and from the applicablecontrol; CTL-92 ATC Control, CTL-92A ATC

Control, CTL-92T ATC and TCAS Control,

TTC-920G Tra nspond er-TCAS C ontr ol, RTU -

870A Radio Tuning Unit, and RTU-870T

Ra dio Tuning U nit (TCAS). U sing this test

p a n e l on t h e f lig h t lin e, wit h a d vm a n d a

bus reader, can help to isolate a problem to

either the control or the transponder unit

an d t hus increase t he probability of correctly

removing the faulty unit in a multi-unit

syst e m . I t is in t e n d ed t h a t a ra m p t e st er b e

used for ATC ground sta t ion simulat ion.

The test panel consists of a panel with

several test points for individual signal

testing and phono jacks and switching for

d a t a b u s m o n it o rin g a n d d a t a wo rd in je ct ion .

When using t he panel, you w ill select the

proper interconnecting cables a nd test panel

overlay, depending on t he contr ol present in

the insta llat ion. The respective overlay

reflects t he test point a nd oth er i/o signal

identificat ion peculiar to tha t control. The

numbers or let ters under each test point are

the connector pin numbers of the ATC controlinvolved.

Figure 5-10 is the test setup diagram

showing the test panel connected between the

a irp la n e h a r n e ss con t ro l h e a d m a t in g

con n e ct o r a n d t h e con t ro l h ea d . I n t h e ca se

of the CTL-92T, you should be a wa re th at the

ATC control da ta originat es in the C TL-

92/92A as C SD B dat a. This is supplied to

the CTL-92T where it is converted to ARINC

4 29 d a t a , TCAS d a t a is a d d e d , a n d t h ecomposite data is then supplied to the

transponder and subsequently to the TCAS.

Therefore, the communication between the

CTL-92T a nd th e C TL-92/92A is in CS D B ,

wh ile the communicat ion betw een t he CTL-

92T a nd the tr a nsponder/TCAS is in ARIN C

429.

Figure 5-11 is the suggested panel la yout of

the components; banana jacks, switches,

indicat or lam ps, etc. I f you decide to

f a b rica t e you r o wn p a n e l a n d w ish t o re t a in

t h e o ve ra l l p a n el ve rsa t i l it y , b e a w a re t h a tthe overlays are intended to be selectable.

The design a llows the overlay to rest on top

of the panel and therefore must f it the

component placement r at her closely. Figure

13 through 19 is a series of diagrams

showing the various overlays; each applicable

to a given contr ol type. With suita ble size

adjustment, f igure 5-11 can be used a s a

template. The overlays m ust (then) also be

size adjusted.

Four D -type connectors ar e locat ed on t he

edge of the pan el; two on each side. These

connectors ma te w ith the ca ble connectors.

The 25-pin connectors carry only the digital

data lines using shielded wiring while the 50-

pin connectors car ry a ll other input/output

functions. You ma y choose to use only a

single connector t o car ry a ll i/o.

Figure 5-12 is t he schematic dia gra m of th e

t e st p a n e l. Use t h is d ia g ra m a s t h e g u id e for

wiring the panel. Table 5-19 is a list of the

p a rt s n e e d ed t o a sse m b le t h e t e st p a n e l. S e e

paragraph 5.8 for a list ing of suppliers.Figur es 5-20 th rough 5-25 show t he cables

a n d wirin g . S e lect t h e ca b les n e e de d

depending on w hich of the va rious controls;

CTL-92, C TL-92A, C TL-92T C ontr ols, RTU -

870A, or RTU -870T Ra dio Tuning U nits ,

TTC -920G Tra ns ponder /TC AS C ont rol, or

Gables 429 control.

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Fl ight l ine Test Set up Diagr am

Figur e 5-10

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Fl ight l ine Test Panel , Panel Layout Diagr am

Figur e 5-11

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Fl i ght l i ne Test Panel ,

Schemat ic Diagr am


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Schemat ic Diagr am


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Fl ight l ine Test Panel ,

Schemat ic Diagr am


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Schemat ic Diagr am


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Table 5-19. Fl i ght l i ne Test Panel Par t s List

ITEM REF DES QTY MANUFACTURER COLLINS PART

NUMBERNAME PN

Lamp Holder DS1,2,5,6, 2 Chicago Miniature

Lamp, Inc.

LH73/1 included in 262-2828-

0X0 CPN

Lamp lens, red LDS5,6 2 GE Co. LC12RN2 262-2828-030

Lamp lens, yellow LDS1,2 2 LC12YN2

Lamp, 28 V DS1-2 2 385 262-2171-010

Lamp, assy, 115

V

DS3-4 2 LeeCraft, SnapLite 262-2852-050

Toggle switch

DPDT, on/on

S3-S10 8 C & K

Components, Inc.

7101SYZQE 266-5321-150

Momentary

switch, SP, Push-

on

S1,S2 2 8121SHZGE 266-5404-010

Stereo Phono

jack, 1/4-inch

J3-J10 8 Switchcraft Inc. PJ-055B Not available from

Collins

Banana jack, 1/4" TP1-45 45 E.F. Johnson Co. blk: 108-0903-001

yel: 108-0907-001

(other colors are optional)

blk: 360-0241-000

yel: 358-0245-000

50-pin D-submin,

conn (socket)

J1A, J2A 2 ITT Cannon DDMF-50S-A176 371-0182-000

25-pin D-submin,

conn (socket)

J1B, J2B 2 DDMF-25S-A176 371-0166-000

Chassis 1 Bud Industries,

Inc.

AC 424 021-0347-050

Chassis, bottom

panel

1 BPA-1519 Not available from

Collins

BNC to TNC

adapter

Needed to

adapt ATC-

601 rf cable to

antenna cable

connector for

direction-

connection

method only.

1 M/A-COM Omni

Spectra, Inc.

3182-2320-00 Not available from

Collins

Control head

cables

Locally fabricated See figures 5-19

through 5-24

Bus reader

cables

Locally fabricated See figure 5-9

Tip jack test

leads

As required

for use with

dvm

Not available from

Collins

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Panel Over lay f or CTL - 92/ 92A

Figur e 5-13

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Panel Over l ay f or CTL - 92T

Figur e 5-14

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Panel Over lay f or RTU- 870A/ T Test ing

Figur e 5-15

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Panel Over l ay f or T TC- 920G Test ing

Figur e 5-16

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Cable B: Connector information:

J 1: KP T2E20-41P YDV, CP N: 371-8625-440

P 1A: D D 50P C37, CP N 371-0118-000;

H ood: C P N 371-0187-000

P 1B : M243083-3, C P N 371-0170-000

Hood: CP N 371-0815-000

Cable A: Connector informat ion:

P 1: MS 3126E20-41SY, C P N 359-0305-590, or

MS 3116E20,41SY, C P N 371-6110-000

P 2A: D D 50P C37, CP N 371-0118-000;

H ood: C P N 371-0187-000

P 2B : M243083-3, C P N 371-0170-000

Hood: CP N 371-0815-000

S i g n a l n a m e/description

FromJ 1

ToP1-A

ToP 1-B

FromP2-A

FromP2-B

ToP 1

Wire s ize/ty pe (both cables)

D a t a bus 1A (from XP D R) V 1 1 V S hielded, t w ist ed pa ir

D a t a bus 1B (from XP D R) U 14 14 U S hielded, t w ist ed pa ir

S hield for U /V T 25 25 T S hield

D a t a bus 2A (from XP D R) a 2 2 a S hielded, t w ist ed pa ir

D a t a bus 2B (from XP D R) Z 15 15 Z S hielded, t w ist ed pa ir

S hield for a /Z Y 12 12 Y S hield

D a t a bus 1A (t o XP D R) S 3 3 S S hielded, t w ist ed pa ir

D a t a bus 1B (t o XP D R) R 16 16 R S hielded, t w ist ed pa ir

S hield for S /R P 24 24 P S hield

D a t a bus 2A (t o XP D R) N 4 4 N S hielded, t w ist ed pa ir

D a t a bus 2B (t o XP D R) M 17 17 M S hielded, t w ist ed pa ir

S hield for N/M L 11 11 L S hield

28 V dc pw r no. 1 (+ ) t 1 1 t 22 AWG

28 V dc pw r no. 2 (+ ) G 3 3 G 22 AWG

D c pw r gnd s 50 50 s 22 AWG

D c pw r gnd s 17 17 s 22 AWG

C ha ssis gnd D 33 33 D 22 AWG

5 V light ing, hi A 7 7 A 26 AWG

28 V light ing, hi r 40 40 r 26 AWG

Light ing common q 39 39 q 26 AWG

CTL- 92/ 92A Cont r ol , Fl ight l ine Test Cables, Assembly Diagr am and Wir e List


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C TL-92/92A C a ble B (cont ’d) C TL-92/92A C a ble A (cont ’d)

S i g n a l n a m e

/description

From

J 1

To

P 1-A

To

P1-B

From

P 2-A

From

P2-B

To

P 1

Wire siz e/ty pe

D im ming bus n 6 6 n 26 AWG

S elf-t est discr et e, input /out put E 38 38 E 26 AWG

I dent discret e input b 5 5 b 26 AWG

Remote tuning select, discrete

input

K 21 21 K 26 AWG

No. 1 XPD R in stby, discrete

output

W 42 42 W 26 AWG

No. 2 XPD R in stby, discrete

output

X 10 10 X 26 AWG

28 V dc, sw out put , no. 1 k 28 28 k 26 AWG

28 V dc, sw out put , no. 2 j 43 43 j 26 AWG

D ua l select (C TL -002 only ) m 8 8 m 26 AWG

No. 1 XP D R off, discret e out put B 11 11 B 26 AWG

No. 2 XP D R off, discret e out put C 27 27 C 26 AWG

Alt code A1 c 29 29 c 26 AWG

Alt code A2 e 30 30 e 26 AWG

Alt code A4 d 45 45 d 26 AWG

Alt code B 1 i 46 46 i 26 AWG

Alt code B 2 h 14 14 h 26 AWG

Alt code B 4 f 15 15 f 26 AWG

Alt code C 1 J 31 31 H 26 AWG

Alt code C 2 H 32 32 H 26 AWG

Alt code C 4 F 47 47 F 26 AWG

Alt code D 4 p 4 4 p 26 AWG

Alt code common g 37 37 g 26 AWG

CTL- 92/ 92A Cont r ol , Fl ight l ine Test Cables, Assembly Diagr am and Wir e List

Fi gur e 5-19 (sheet 2)

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J 1: 27508E20B 2P A, CP N 859-0004-010

P 1A: D D 50P C37, CP N 371-0118-000;

H ood: C P N 371-0187-000

P 1B : M243083-3, C P N 371-0170-000

Hood: CP N 371-0815-000


P 1: K J 6F20B SA, C P N: 350-0601-020

St ra in relief: MS27506F20-2, C P N 359-0637-070

P 2A: D D 50P C37, CP N 371-0118-000;

H ood: C P N 371-0187-000

P 2B : M243083-3, C P N 371-0170-000

Hood: CP N 371-0815-000

S i g n a l n a m e

/description

From

J 1

To

P1-A

To

P 1-B

From

P2-A

From

P2-B

To

P 1


C S D B da t a in , 1A (from C TL) 23 1 1 23 S hielded t w ist ed pa ir

C S D B da t a in , 1B (from C TL) 22 14 14 22 S hielded t w ist ed pa ir

S hield for 23/22 25 25 S hield for 23/22

ARINC 429 in, 1A (from ARINC

CTL)

15 2 2 15 Shielded t w ist ed pa ir

ARINC 429 in, 1B (from ARINC

CTL)

14 15 15 14 S hielded t w ist ed pa ir


C S D B da t a out , 1A (t o C TL) 16 3 3 16 S hielded t w ist ed pa ir

C S D B da t a out , 1B (t o C TL) 17 16 16 17 S hielded t w ist ed pa ir


ARINC 429 out, 1A (to ARINC

CTL)


ARINC 429 out, 1B (to ARINC

CTL)



ARI NC 429 in, 1A (from XP D R) 11 5 5 11 S hielded t w ist ed pa ir

ARI NC 429 in, 1B (from XP D R) 10 18 18 10 S hielded t w ist ed pa ir


ARI NC 429 in, 2A (from XP D R) 13 6 6 13 S hielded t w ist ed pa ir

ARI NC 429 in, 2B (from XP D R) 12 19 19 12 S hielded t w ist ed pa ir


CTL - 92T Cont r ol , Fl i ght l i ne Test Cables, Assembly Diagr am and Wir e Li st


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C TL-92T C a ble B (cont ’d) C TL-92T C a ble A (cont ’d)

S i g n a l n a m e

/description

From

J 1

To

P 1-A

To

P1-B

From

P 2-A

From

P2-B

To

P 1

Wire siz e/ty pe

ARI NC 429 ou t , 1A (t o XP D R) 5 7 7 5 S hielded t w ist ed pa ir

ARI NC 429 ou t , 1B (t o XP D R) 4 20 20 4 S hielded t w ist ed pa ir


ARI NC 429 ou t , 2A (t o XP D R) 6 8 8 13 S hielded t w ist ed pa ir

ARI NC 429 ou t , 2B (t o XP D R) 7 21 21 12 S hielded t w ist ed pa ir


28 V dc pw r input no. 1 (+ ) 1 1 1 1 22 AWG




P w r gnd 59 50 50 59 22 AWG

P w r gnd 60 20 20 60 22 AWG

P w r gnd 32 17 17 32 22 AWG

S elf-t est input 46 38 38 46 26 AWG

I dent input 21 5 5 21 26 AWG

28 V light ing input , hi 48 40 40 48 26 AWG

5 V light ing input , hi 50 7 7 50 26 AWG

Light ing comm on 62 39 39 62 26 AWG

S t ra p no. 1 53 8 8 53 26 AWG

S t ra p no. 2 49 21 21 49 26 AWG

S t ra p no. 3 52 9 9 52 26 AWG

S t ra p no. 4 51 22 22 51 26 AWG

S t ra p no. 5 47 23 23 47 26 AWG

S t ra p no. 6 24 24 24 24 26 AWG

S t ra p comm on 27 41 41 27 26 AWG

ATC no. 1 select , input 19 42 42 19 26 AWG

ATC no. 2 select , input 18 10 10 18 26 AWG

28 V sw it ched out put 25 11 11 25 2 6 AWG

CTL-92T Control, Flightline Test Cables, Assembly Diagram and Wire List


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C TL-92T C a ble B (cont ’d) C TL-92T C a ble A (cont ’d)

S i g n a l n a m e

/description

From

J 1

To

P1-A

To

P 1-B

From

P2-A

From

P2-B

To

P 1

Wire siz e/ty pe

Reply la mp out put (+ ) 33 28 28 33 26 AWG

Reply la mp out put (-) 41 43 43 41 26 AWG

Alt it ude report ing input 20 44 44 20 26 AWG

ATC code A1 44 29 29 44 26 AWG

ATC code A2 26 30 30 26 26 AWG

ATC code A4 45 45 45 45 26 AWG

ATC code B 1 56 46 46 56 26 AWG

ATC code B 2 55 14 14 55 26 AWG

ATC code B 4 57 15 15 57 26 AWG

ATC code C 1 39 31 31 39 26 AWG

ATC code C 2 42 32 32 42 26 AWG

ATC code C 4 54 47 47 54 26 AWG

ATC code D 1 61 48 48 61 26 AWG

ATC code D 2 37 49 49 37 26 AWG

ATC code D 4 63 4 4 63 26 AWG

ATC code comm on 64 37 37 64 26 AWG

CTL-92T Control, Flightline Test Cables, Assembly Diagram and Wire List


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Cable B: Connector informat ion:

J 1: MS 27508E 20F-2P, CP N: 359-0667-280

P1A: DD 50P C37, CPN 371-0118-000;

Hood: CP N 371-0187-000

P 1B : M243083-3, C P N 371-0170-000

Hood: CP N 371-0815-000


P 1: MS 27493T20f-2S, CP N 359-0601-020

Strain relief: MS27506F20-2, CPN 359-0637-070

P2A: DD 50P C37, CPN 371-0118-000;

Hood: CP N 371-0187-000

P 2B : M243083-3, C P N 371-0170-000

Hood: CP N 371-0815-000

S i g n a l n a m e

/description

From

J 1

To

P 1-A

To

P1-B

From

P 2-A

From

P2-B

To

P 1


ARI NC 429, D a t a I nput , A, A 28 1 1 28 S hielded t w ist ed pa ir

ARI NC 429, D a t a I nput , A, B 29 14 14 29 S hielded t w ist ed pa ir

S hield 30 25 25 30 S hield

ARI NC 429, D a t a I nput , B , A 31 2 2 31 S hielded t w ist ed pa ir

ARI NC 429, D a t a I nput , B , B 32 15 15 32 S hielded t w ist ed pa ir


ARI NC 429, D a t a I nput , C , A 34 5 5 34 S hielded t w ist ed pa ir

ARI NC 429, D a t a I nput , C , B 35 18 18 5 S hielded t w ist ed pa ir


ARI NC 429, D a t a Out put , A, A 44 4 4 44 S hielded t w ist ed pa ir

ARI NC 429, D a t a Out put , A, B 45 17 17 45 S hielded t w ist ed pa ir


ARI NC 429, D a t a Out put , B , A 47 7 7 47 S hielded t w ist ed pa ir

ARI NC 429, D a t a Out put , B , B 48 20 20 48 S hielded t w ist ed pa ir


ARI NC 429, D a t a Out put , C , A 50 8 8 50 S hielded t w ist ed pa ir

ARI NC 429, D a t a Out put , C , B 51 21 21 51 S hielded t w ist ed pa ir


28 V dc pw r input , No. 1 (+ ) 1 1 1 1 22 AWG

28 V dc pw r input , No. 2 (+ ) 7 3 3 7 22 AWG

R T U - 87 0 A / T R a d i o T u n i n g U n i t , F l i g h t l i n e T es t C a b l es, A s sem b l y D i a g r a m a n d W i r e L i st


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RTU -870A/T C a ble B (cont ’d) RTU -870A/T C a ble A (cont ’d)

S i g n a l n a m e

/description

From

J 1

To

P1-A

To

P 1-B

From

P2-A

From

P2-B

To

P 1

Wire siz e/ty pe

P ow er ground 3 50 50 3 22 AWG

G round (connect t o P 1-A 50) 17 17 22 AWG

S t ra p comm on 53 23 23 53 22 AWG

(comm on - connect t o P 1-A 23) 13 13 22 AWG (connect t o J 1-A 23)

(comm on - connect t o P 1-A 23) 37 37 22 AWG (connect t o J 1-A 23)

115 V a c light ing, hi 5 36 36 5 26 AWG

Light ing common 4 16 16 4 26 AWG

D im ming input (+ 28 V dc) 8 6 6 8 26 AWG

D im comm on 10 39 39 10 26 AWG

Remot e ident input 11 5 5 11 26 AWG

C ross-side RTU disa ble 63 8 8 63 26 AWG

Reversiona ry da t a displa y ena ble 39 21 21 39 26 AWG

MB sense ena ble 61 9 9 61 26 AWG

ATC 1 select 13 22 22 13 26 AWG

RTU side 2 select 64 23 23 64 26 AWG

Remot e t un e ena ble 12 24 24 12 26 AWG

RTU on/off 9 25 25 9 26 AWG

L E ng da t a no. 1, A 37 42 42 37 S hielded t w ist ed pa ir

L E ng da t a no. 1, B 38 10 10 38 S hielded t w ist ed pa ir

S hield for 37/38 40 2 2 40 S hield for 37/38

R E ng da t a no. 2, A 41 11 11 41 S hielded t w ist ed pa ir

R E ng da t a no. 2, B 42 27 27 42 S hielded t w ist ed pa ir

S hield for 41/42 43 19 19 43 S hield for 41/42

RTU t est m ode ena ble 60 28 28 60 26 AWG

R T U - 87 0 A / T R a d i o T u n i n g U n i t , F l i g h t l i n e T est C a b l es, A s sem b l y D i a g r a m a n d W i r e L i st


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RTU -870A/T C a ble B (cont ’d) RTU -870A/T C a ble A (cont ’d)

S i g n a l n a m e

/description

From

J 1

To

P 1-A

To

P1-B

From

P 2-A

From

P2-B

To

P 1

Wire siz e/ty pe

Na v ra dio t est inhibit 58 43 43 58 26 AWG

MLS no. 1 select 16 44 44 16 26 AWG

MLS no. 2 select 62 12 12 62 26 AWG

D ME no. 2 deselect 59 29 29 59 26 AWG

AD F no. 2 deselect 57 30 30 57 26 AWG

U H F no. 1 select 17 45 45 17 26 AWG

U H F no. 2 select 18 46 46 18 26 AWG

TAC AN no. 1 select 19 14 14 37 26 AWG

TAC AN no. 2 select 20 15 15 20 26 AWG

TC AS on boa rd select 21 31 31 21 2 6 AWG

AD F TC -X select 23 32 32 23 26 AWG

I nv TAC AN inhibit select 24 47 47 24 26 AWG

C omm ext ended freq select 54 48 48 54 26 AWG

Na v ext ended freq select 55 49 49 55 26 AWG

AD F ext ended freq select 56 4 4 56 26 AWG

R T U - 87 0 A / T R a d i o T u n i n g U n i t , F l i g h t l i n e T es t C a b l es, A s sem b l y D i a g r a m a n d W i r e L i st


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J 1: MI L-C-26500, C P N 359-4118-240

J 2: MI L-C-26500, C P N 359-4118-250

P 1A: D D 50P C37, CP N 371-0118-000;

H ood: C P N 371-0187-000

P 1B : M243083-3, C P N 371-0170-000

Hood: CP N 371-0815-000


P 1: MD24266R76B24S7, CP N 359-4068-030

P 2: MS24266R16B24S8, CP N 359-4095-700

St ra in relief: MS27506F20-2, C P N 359-0637-070

P 2A: D D 50P C37, CP N 371-0118-000;

H ood: C P N 371-0187-000

P 2B : M243083-3, C P N 371-0170-000

Hood: CP N 371-0815-000

S i g n a l n a m e

/description

From

J 1/J 2

To

P1-A

To

P 1-B

From

P2-A

From

P2-B

To

P 1/P 2


ARI NC 429 t o XP D R no. 1, 2A J 1-22 7 7 P 1-22 S hielded t w ist ed pa ir

ARI NC 429 t o XP D R no. 1, 2B J 1-23 20 20 P 1-23 S hielded t w ist ed pa ir

S hield for J 1-22/23 22 22 S hield for P 1-22/23

ARI NC 429 t o XP D R no. 2, 2A J 2-22 8 8 P 2-22 S hielded t w ist ed pa ir

ARI NC 429 t o XP D R no. 2, 2B J 2-23 21 21 P 2-22 S hielded t w ist ed pa ir

S hield for J 2-22/23 9 9 S hield for P 2-22/23

115 V a c pw r no. 1, H i J 1-3 34 34 P 1-3 22 AWG

115 V a c pw r no. 1, L o J 1-4 18 18 P 1-4 22 AWG

115 V a c pw r no. 2, H i J 2-3 36 36 P 2-3 22 AWG

115 V a c pw r no. 2, L o J 2-4 16 16 P 2-4 22 AWG

S elf-t est input J 1-9 38 38 P 1-9 26 AWG

Monit or la mp t est input J 1-21 5 5 P 1-21 26 AWG

28 V light ing, H i J 2-1 40 40 P 2-1 26 AWG

28 V light ing, Lo J 2-2 39 39 P 2-2 26 AWG

5 V light ing, H i J 1-1 7 7 P 2-1 26 AWG

5 V light ing, Lo J 1-2 6 6 P 1-2 26 AWG

Ant enna select , no. 1 J 1-5 8 8 P 1-5 26 AWG

Ant enna t ra nsfer common J 2-10 21 21 P 2-10 26 AWG

Ant enna select , no. 2 J 2-5 9 9 P 2-5 26 AWG

TT C- 920G TCAS/ T r ansponder Cont r ol , Fl ight l ine Test Cables, Assembly Diagr am and Wir e Li st


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TTC -920G C a ble B (cont ’d) TTC -920G C a ble A (cont ’d)

S i g n a l n a m e

/description

From

J 1 /J 2

To

P 1-A

To

P1-B

From

P 2-A

From

P2-B

To

P 1/P 2

Wire siz e/ty pe

Air/gnd no. 1, input J 1-24 22 22 P 1-24 26 AWG

Air/gnd no. 1, out put J 1-15 23 23 P 1-15 26 AWG

Air/gnd no. 2, input J 2-24 24 24 P 2-24 26 AWG


Monit or la m p pw r, input 12/28 V J 1-18 26 26 P 1-18 26 AWG

S igna l comm on, no. 1 J 1-6 41 41 P 1-6 26 AWG

S igna l comm on, no. 2 J 2-6 13 13 P 2-6 26 AWG

XP D R fa il w a r n, no. 1 J 1-12 42 42 P 1-12 26 AWG

XP D R fa il w a r n, no. 2 J 2-12 11 11 P 2-12 26 AWG

XP D R fa il w a r n out put J 1-10 10 10 P 2-10 26 AWG

XP D R in st by, no. 1 J 1-7 27 27 P 1-7 26 AWG

XP D R in st by, no. 2 J 2-7 28 28 P 2-7 26 AWG

Alt erna t e AD select , no. 1 J 1-16 43 43 P 1-16 26 AWG

Alt erna t e AD select , no. 2 J 2-16 44 44 P 2-16 26 AWG

C ha ssis gnd, no. 1 J 1-8 4 4 P 1-8 26 AWG

C ha ssis gnd, no. 2 J 2-8 37 37 P 2-8 26 AWG



XP D R fa il, discret e no. 1 J 1-20 45 45 P 1-20 26 AWG

XP D R fa il, discret e no. 2 J 2-20 46 46 P 2-20 26 AWG

TTC-920G TCAS/Tra nsponder C ontrol, Flight line Test Ca bles, Assembly D iagra m an d Wire L ist


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7/22/2019 TDR 94 5230775652


7/22/2019 TDR 94 5230775652


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