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SYSTEM INSTALLATION MANUAL

CAS 67ATCAS IISYSTEM

MANUAL NUMBER 006-05340-0007REVISION 7 SEPTEMBER, 2004

WARNINGThe enclosed technical data is eligible for export under License Designation NLR and is to be used solely by the individual/organization to whom it is addressed. Diversion contrary to U.S. law is prohibited.

COPYRIGHT NOTICE

©1993-1999, 2004 Honeywell International Inc.

REPRODUCTION OF THIS PUBLICATION OR ANY PORTION THEREOF BY ANY MEANS WITHOUT THE EXPRESS WRITTEN PERMISSION OF HONEYWELL IS PROHIBITED, EXCEPT TO THE EXTENT REQUIRED FOR INSTALLATION OR MAINTENANCE OF THE RECIPIENT’S EQUIPMENT. FOR FURTHER INFORMATION CONTACT THE MANAGER, TECHNICAL PUBLICATIONS, HONEYWELL, ONE TECHNOLOGY CENTER, 23500 WEST 105th STREET OLATHE KS 66061 TELEPHONE: (913) 712-0400.

NCAS 67A TCAS II SYSTEM INSTALLATION MANUAL

T-1 006-05340-0007 Rev. 7 Sept/200434-40-01

System Installation Manual

Including:TPU 67A TCAS II Processor

006-05340-0007

CAS 67A TCAS IITraffic Alert and Collision Avoidance System

CM 67A Configuration ModuleCM 2000 Configuration ModuleANT 67A Directional Antenna

CTA-81D Mode S/TCAS Control UnitCTA-81A Mode S/TCAS Control UnitCD 671C Mode S/TCAS Control UnitKFS 578A Mode S/TCAS Control UnitMST 67A Mode S TransponderGC 362A TCAS Graphics Processor

IVA-81A TA/RA/VSI DisplayIVA-81B RA/VSI DisplayIVA-81C, IVA-81D TA/RA/VSI Display

PS-550 Mode S/TCAS Control Unit PS-578A Mode S/TCAS Control Unit


PN-1 006-05340-0007 Rev. 7 Sept/200434-40-01

NOTE

IF ANY UNUSUAL OR SPECIFIC SERVICE PROBLEMS ARISE, CONTACT HONEYWELL,23500 WEST 105TH STREET, OLATHE, KANSAS, 66061. NO EQUIPMENT SHALL BERETURNED TO THE CUSTOMER SERVICE DEPARTMENT UNTIL A RETURNAUTHORIZATION (RA) FORM IS REQUESTED AND RECEIVED FROM HONEYWELL.

PROPRIETARY NOTICE

This document contains proprietary information andsuch information may not be disclosed to others forany purpose, nor used for manufacturing purposeswithout written permission from Honeywell.


REVISION HIGHLIGHTS

006-05340-0007 Rev. 7

Sept/2004

This is a complete reprint. All pages are revised and reformatted.

General highlights include updates to PS-550/PS-578 Control Heads and updates to general control head information. Updated TCAS II system drawing. Updated environmental qualification information. Updated “TCASDIAG for Windows” appen-dix and antenna test appendix.

Specific changes to content are denoted by revision bar.

RH-1 006-05340-0007 Rev. 7 Sept/200434-40-01


THIS PAGE IS RESERVED

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RECORD OF REVISIONS

REV.NO.

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RECORD OF REVISIONS (cont.)

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RECORD OF TEMPORARY REVISIONS

T.R.NO.

DATEDATE

INSERTEDBY

DATEREMOVED

BY

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Revision TR-05340-1

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RECORD OF TEMPORARY REVISIONS (cont.)

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TCAS II SERVICE LITERATURE LIST

The following are installation bulletins applicable to the CAS 67A TCAS II sys-tem.

The following is service literature information applicable to the CAS 67A system and TPU 67A unit. For current service literature information for related units and/or systems, refer to the Installation or Maintenance Manual of the applica-ble unit.

BULLETIN NUMBER DATE COVERAGE

IB 372

IB 398

IB 438

IB 439

IB 447

IB 452

IB 456

IB 457

IB 458

APR/1995

JUL/1997

APR/1999

MAR/1999

MAY/1999

JAN/2000

NOV/2000

NOV/1999

FEB/2000

TO CORRECT ERROR IN TPU CONFIG MODULE PROCEDURE

TCASDIAG GUIDE FOR FIELD REFERENCE

INFORMATION ON TCAS I AND II RETURN-TO-SERVICE FOLLOWING COMPONENT REPAIR OR REPLACEMENT

APPROVAL FOR THE REPLACEMENT OF IVA 81A INDICATORS WITH IVA 81C INDICATORS

CLARIFICATION OF CAS 67A TCAS II SYSTEM AND ACAS II SYSTEM PILOT S GUIDES

INTERCHANGEABILITY OF IVA 81A C AND D TA/VSI TCAS INDICATORS

TCASDIAG FOR WINDOWS AND TCAS PROCESSOR FIELD DIAGNOSTIC PROGRAM FOR USER MANUAL

TCASDIAG GUIDE

CLARIFICATION OF THE ALTITUDE INTERFACE TO THE TCAS PROCES-SOR AND/OR MST 67A TRANSPONDER

BULLETIN NUMBER DATE COVERAGEEFFECTIVE

S/N

SA CAS 67A-101 OCT/1997 ADDITION OF RAIN EROSION FILM TO ANTENNA N.A.

SA CAS 67A-102 JAN/1998 TEST PROCEDURES FOR SWR AND CABLE LOSS FOR ECS RF TROUBLESHOOTER KIT

N.A.

SA TPU 67A-101 OCT/1996 FAULT CODE GUIDE N.A.

SA TPU 67A-102 FEB/1999 REPLACEMENT FOR OBSOLETE PIN DIODES N.A.

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SA TPU 67A-103 JUN/2000 REPLACEMENT FOR OBSOLETE FLASH AND REAL-TIME CLOCK N.A.

SA TPU 67A-104 JAN/2002 REPLACEMENT RECEIVER ASSEMBLY N.A.

SB TPU 67A-4 MAY/1997 STABILIZE SWITCHING SPEED OF DISCRETE INPUT CIR-CUITS

10505

SB TPU 67A-5 SEP/1998 ADDITIONAL LIGHTNING PROTECTION FOR THE UNIT S +28 VDC POWER LINES

10960

SB TPU 67A-6 OCT/1998 MANUFACTURING EFFICIENCY IMPROVEMENT 10903

SB TPU 67A-7 MAR/2002 UNIT MOD 13 ALLEVIATE TIMING ISSUES IN CONFIGURA-TION MODULE INTERFACE

11130

SB TPU 67A-8 MAR/2002 INCREASE TPU MEANTIME BETWEEN FAILURES 11131

SB TPU 67A-9 APR/2002 PREVENT COLD INDUCED AUDIO FAILURES 11132

SB TPU 67A-10 JUN/2000 THIS BULLETIN HAS BEEN SUPERSEDED 11390

SB TPU 67A-11 APR/2001 INCREASE POWER-HANDLING CAPABILITY AND RELIABIL-ITY OF -250VDC MONITOR CIRCUIT

VERSIONDEPENDENT

SB TPU 67A-12 NOV/2001 PREVENT ACCIDENTAL WRITES TO THE FLASH MEMORY DUR-ING NORMAL OPERATION

VERSIONDEPENDENT

SB TPU-67A-13 JAN/2003 REPLACE TPU S OBSOLETE COMPUTER BOARD VERSIONDEPENDENT

SB TPU 67A-14 JUN/2002 INCORPORATE REPLACEMENT FOR OBSOLETE REFERENCE BOARD PART NUMBER 200-08874-0000

VERSIONDEPENDENT

SB TPU 67A-15 JUN/2002 INCORPORATE REPLACEMENT FOR OBSOLETE SWITCH DRIVER BOARD PART NUMER 200-08530-0000

VERSIONDEPENDENT

SB TPU 67A-16 JUN/2002 INCORPORATE REPLACEMENT OF POWER SUPPLY BOARD #2 PART NUMBER 200-08523-0000

VERSIONDEPENDENT

SB TPU 67A-17 JUN/2002 INCORPORATE REPLACEMENT OF OBSOLETE VIDEO BOARD PART NUMBER 200-08875-0000

VERSIONDEPENDENT

SB TPU 67A-18 AUG/2002 PREVENT THE TPU 67A FRO INTERFERING WITH THE PRI-MUS DME DURING EQUIPMENT START-UP

VERSIONDEPENDENT

SB TPU 67A-19 FEB/2003 UNIT WILL NOT INITIALIZE AND LED DISPLAY ON THE SIDE OF THE PROCESSOR IS BLANK

VERSIONDEPENDENT

SB TPU 67A-20 DEC/2002 REPLACEMENT OF INTERCONNECT BD DUE TO ERRONEOUS EXTERNAL FAULT CODES

VERSIONDEPENDENT

SB TPU 67A-21 MAR/2003 REPLACE THREE TRANSORBS ON INTERCONNECT BOARD WITH A LOWER VOLTAGE VARIETY

VERSIONDEPENDENT


S/N

SB-2 006-05340-0007 Rev. 7 Sept/200434-40-01


SB TPU 67A-22 AUG/2003 REPLACES OBSOLETE RECEIVER ASSY PART NUMBER 200-09882-0000 WITH 200-09882-0010

VERSIONDEPENDENT

SB TPU 67A-23 SEP/2003 GIVES ADDITIONAL PROTECTION FROM ARCING BETWEEN THE SWITCH DRIVER BOARD AND THE MAINFRAME CASTING AND INCREASES CONDUCTIVITY AT CERTAIN PIN CONNEC-TIONS

VERSIONDEPENDENT

SB TPU 67A-24 SEP/2003 GIVES ADDITIONAL PROTECTION FROM ARCING TO THE RF BOARD THE IF BOARD THE TRANSMIT MODULATOR BOARD AND THE REFERENCE BOARD

VERSIONDEPENDENT

SB TPU 67A-M1 MAR/2001 INCORPORATE SOFTWARE 12/01 (CHANGE 7) VERSIONDEPENDENT

SWB TPU 67A-SW1 AUG/1995 TO INCORPORATE 01/02 SOFTWARE N.A.

SWB TPU 67A-SW2 AUG/1995 TO INCORPORATE 01/03 SOFTWARE N.A.

SWB TPU 67A-SW3 OCT/1996 TO INCORPORATE 01/11 SOFTWARE 10423

SWB TPU 67A-SW4 MAR/2002 INCORPORATE SOFTWARE LEVEL 01/12 VERSIONDEPENDENT

SWB TPU 67A-SW5 JUN/2000 INCORPORATE SOFTWARE 01/13 COMPATIBLE WITH NEW FLASH OR REAL-TIME CLOCK

N.A.

SWB TPU 67A-SW6 JUN/2000 INCORPORATE SOFTWARE 11/03. CORRECTS INCORRECT TCAS FAIL MESSAGE WHILE UNIT IN STANDBY MODE. ALSO COMPATIBLE WITH NEW FLASH OR REAL-TIME CLOCK

VERSIONDEPENDENT

SWB TPU 67A-SW7 DEC/2001 INCORPORATE SOFTWARE 11/04. ENABLES UNIT TO INTER-FACE WITH COLLINS TDR 94D TRANSPONDERS

VERSIONDEPENDENT


S/N

SB-3 006-05340-0007 Rev. 7 Sept/200434-40-01



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LIST OF EFFECTIVE PAGES

SUBJECT PAGE DATE

Title Page * T-1 Sept/2004Proprietary Notice * PN-1 Sept/2004

Revision Highlights * RH-1 Sept/2004* RH-2 Sept/2004

Record of Revisions * RR-1 Sept/2004* RR-2 Sept/2004

Record of Temporary Revisions * RTR-1 Sept/2004* RTR-2 Sept/2004

List of Service Bulletins * SB-1 Sept/2004* SB-2 Sept/2004* SB-3 Sept/2004* SB-4 Sept/2004

List of Effective Pages * LEP-1 Sept/2004* LEP-2 Sept/2004* LEP-3 Sept/2004* LEP-4 Sept/2004* LEP-5 Sept/2004* LEP-6 Sept/2004* LEP-7 Sept/2004* LEP-8 Sept/2004* LEP-9 Sept/2004* LEP-10 Sept/2004* LEP-11 Sept/2004* LEP-12 Sept/2004* LEP-13 Sept/2004* LEP-14 Sept/2004

Table of Contents * TC-1 Sept/2004* TC-2 Sept/2004* TC-3 Sept/2004* TC-4 Sept/2004* TC-5 Sept/2004* TC-6 Sept/2004* TC-7 Sept/2004* TC-8 Sept/2004* TC-9 Sept/2004

“F” INDICATES FOLDOUT PAGES; * INDICATES PAGES CHANGED IN LATEST REVISION LEP-1 006-05340-0007 Rev. 7 Sept/200434-40-01


Table of Contents (cont). * TC-10 Sept/2004* TC-11 Sept/2004* TC-12 Sept/2004* TC-13 Sept/2004* TC-14 Sept/2004

Introduction * INTRO-1 Sept/2004* INTRO-2 Sept/2004

Description and Operation * 1 Sept/2004* 2 Sept/2004

F * 3 Sept/2004* 4 Blank* 5 Sept/2004* 6 Sept/2004* 7 Sept/2004* 8 Sept/2004* 9 Sept/2004* 10 Sept/2004* 11 Sept/2004* 12 Sept/2004* 13 Sept/2004* 14 Sept/2004* 15 Sept/2004* 16 Sept/2004* 17 Sept/2004* 18 Sept/2004* 19 Sept/2004* 20 Sept/2004* 21 Sept/2004* 22 Sept/2004* 23 Sept/2004* 24 Sept/2004* 25 Sept/2004* 26 Sept/2004* 27 Sept/2004* 28 Sept/2004* 29 Sept/2004* 30 Sept/2004* 31 Sept/2004* 32 Sept/2004* 33 Sept/2004* 34 Sept/2004* 35 Sept/2004* 36 Sept/2004



Description and Operation (cont). * 37 Sept/2004* 38 Sept/2004* 39 Sept/2004* 40 Sept/2004* 41 Sept/2004* 42 Sept/2004* 43 Sept/2004* 44 Sept/2004* 45 Sept/2004* 46 Sept/2004* 47 Sept/2004* 48 Sept/2004* 49 Sept/2004* 50 Sept/2004* 51 Sept/2004* 52 Sept/2004* 53 Sept/2004* 54 Sept/2004* 55 Sept/2004* 56 Sept/2004* 57 Sept/2004* 58 Sept/2004* 59 Sept/2004* 60 Sept/2004* 61 Sept/2004* 62 Sept/2004* 63 Sept/2004* 64 Sept/2004* 65 Sept/2004* 66 Sept/2004* 67 Sept/2004* 68 Sept/2004* 69 Sept/2004* 70 Sept/2004* 71 Sept/2004* 72 Sept/2004* 73 Sept/2004* 74 Sept/2004* 75 Sept/2004* 76 Sept/2004* 77 Sept/2004* 78 Sept/2004* 79 Sept/2004* 80 Sept/2004* 81 Sept/2004



Description and Operation (cont). * 82 Sept/2004* 83 Sept/2004* 84 Sept/2004* 85 Sept/2004* 86 Sept/2004* 87 Sept/2004* 88 Sept/2004* 89 Sept/2004* 90 Sept/2004* 91 Sept/2004* 92 Sept/2004* 93 Sept/2004* 94 Sept/2004* 95 Sept/2004* 96 Sept/2004* 97 Sept/2004* 98 Sept/2004* 99 Sept/2004* 100 Sept/2004* 101 Sept/2004* 102 Sept/2004* 103 Sept/2004* 104 Sept/2004* 105 Sept/2004* 106 Sept/2004* 107 Sept/2004* 108 Sept/2004* 109 Sept/2004* 110 Sept/2004* 111 Sept/2004* 112 Sept/2004* 113 Sept/2004* 114 Sept/2004* 115 Sept/2004* 116 Sept/2004* 117 Sept/2004* 118 Sept/2004* 119 Sept/2004* 120 Sept/2004

F * 121 Sept/2004* 122 Blank

F * 123 Sept/2004* 124 Blank* 125 Sept/2004* 126 Sept/2004



Description and Operation (cont). * 127 Sept/2004* 128 Sept/2004* 129 Sept/2004* 130 Sept/2004* 131 Sept/2004* 132 Sept/2004* 133 Sept/2004* 134 Sept/2004* 135 Sept/2004* 136 Sept/2004* 137 Sept/2004* 138 Sept/2004* 139 Sept/2004* 140 Sept/2004* 141 Sept/2004* 142 Sept/2004* 143 Sept/2004* 144 Sept/2004* 145 Sept/2004* 146 Sept/2004* 147 Sept/2004* 148 Sept/2004* 149 Sept/2004* 150 Sept/2004* 151 Sept/2004* 152 Sept/2004* 153 Sept/2004* 154 Sept/2004* 155 Sept/2004* 156 Sept/2004* 157 Sept/2004* 158 Sept/2004* 159 Sept/2004* 160 Sept/2004* 161 Sept/2004* 162 Sept/2004* 163 Sept/2004* 164 Sept/2004

F * 165 Sept/2004* 166 Blank

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F * 171 Sept/2004



Description and Operation (cont). * 172 Blank

Fault Isolation * 1001 Sept/2004* 1002 Sept/2004* 1003 Sept/2004* 1004 Sept/2004* 1005 Sept/2004* 1006 Sept/2004* 1007 Sept/2004* 1008 Sept/2004* 1009 Sept/2004* 1010 Sept/2004* 1011 Sept/2004* 1012 Sept/2004* 1013 Sept/2004* 1014 Sept/2004* 1015 Sept/2004* 1016 Sept/2004* 1017 Sept/2004* 1018 Sept/2004* 1019 Sept/2004* 1020 Sept/2004* 1021 Sept/2004* 1022 Sept/2004* 1023 Sept/2004* 1024 Sept/2004* 1025 Sept/2004* 1026 Sept/2004* 1027 Sept/2004* 1028 Sept/2004* 1029 Sept/2004* 1030 Sept/2004

Maintenance Practices * 2001 Sept/2004* 2002 Sept/2004* 2003 Sept/2004* 2004 Sept/2004* 2005 Sept/2004* 2006 Sept/2004* 2007 Sept/2004* 2008 Sept/2004* 2009 Sept/2004* 2010 Sept/2004* 2011 Sept/2004* 2012 Sept/2004



Maintenance Practices (cont). * 2013 Sept/2004* 2014 Sept/2004* 2015 Sept/2004* 2016 Sept/2004* 2017 Sept/2004* 2018 Sept/2004* 2019 Sept/2004* 2020 Sept/2004* 2021 Sept/2004* 2022 Sept/2004* 2023 Sept/2004* 2024 Sept/2004* 2025 Sept/2004* 2026 Sept/2004* 2027 Sept/2004* 2028 Sept/2004* 2029 Sept/2004* 2030 Sept/2004* 2031 Sept/2004* 2032 Sept/2004* 2033 Sept/2004* 2034 Sept/2004* 2035 Sept/2004* 2036 Sept/2004* 2037 Sept/2004* 2038 Sept/2004* 2039 Sept/2004* 2040 Sept/2004* 2041 Sept/2004* 2042 Sept/2004* 2043 Sept/2004* 2044 Sept/2004* 2045 Sept/2004* 2046 Sept/2004* 2047 Sept/2004* 2048 Sept/2004* 2049 Sept/2004* 2050 Sept/2004* 2051 Sept/2004* 2052 Sept/2004* 2053 Sept/2004* 2054 Sept/2004* 2055 Sept/2004* 2056 Sept/2004* 2057 Sept/2004



Maintenance Practices (cont). * 2058 Sept/2004* 2059 Sept/2004* 2060 Sept/2004* 2061 Sept/2004* 2062 Sept/2004* 2063 Sept/2004* 2064 Sept/2004* 2065 Sept/2004* 2066 Sept/2004* 2067 Sept/2004* 2068 Sept/2004* 2069 Sept/2004* 2070 Sept/2004* 2071 Sept/2004* 2072 Sept/2004* 2073 Sept/2004* 2074 Sept/2004* 2075 Sept/2004* 2076 Sept/2004* 2077 Sept/2004* 2078 Sept/2004* 2079 Sept/2004* 2080 Sept/2004* 2081 Sept/2004* 2082 Sept/2004* 2083 Sept/2004* 2084 Sept/2004* 2085 Sept/2004* 2086 Sept/2004* 2087 Sept/2004* 2088 Sept/2004* 2089 Sept/2004* 2090 Sept/2004* 2091 Sept/2004* 2092 Sept/2004

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Maintenance Practices (cont). F * 2103 Sept/2004* 2104 Blank

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F * 2147 Sept/2004



Maintenance Practices (cont). * 2148 BlankF * 2149 Sept/2004

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Maintenance Practices (cont). F * 2193 Sept/2004* 2194 Blank

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Diagnostic Appendices * APP-1 Sept/2004* APP-2 Sept/2004* APP-3 Sept/2004* APP-4 Sept/2004* APP-5 Sept/2004* APP-6 Sept/2004* APP-7 Sept/2004* APP-8 Sept/2004* APP-9 Sept/2004* APP-10 Sept/2004* APP-11 Sept/2004* APP-12 Sept/2004* APP-13 Sept/2004* APP-14 Sept/2004* APP-15 Sept/2004* APP-16 Sept/2004* APP-17 Sept/2004* APP-18 Sept/2004



Diagnostic Appendices (cont). * APP-19 Sept/2004* APP-20 Sept/2004* APP-21 Sept/2004* APP-22 Sept/2004* APP-23 Sept/2004* APP-24 Sept/2004* APP-25 Sept/2004* APP-26 Sept/2004* APP-27 Sept/2004* APP-28 Sept/2004* APP-29 Sept/2004* APP-30 Sept/2004* APP-31 Sept/2004* APP-32 Sept/2004* APP-33 Sept/2004* APP-34 Sept/2004* APP-35 Sept/2004* APP-36 Sept/2004* APP-37 Sept/2004* APP-38 Sept/2004* APP-39 Sept/2004* APP-40 Sept/2004* APP-41 Sept/2004* APP-42 Sept/2004* APP-43 Sept/2004* APP-44 Sept/2004* APP-45 Sept/2004* APP-46 Sept/2004* APP-47 Sept/2004* APP-48 Sept/2004* APP-49 Sept/2004* APP-50 Sept/2004* APP-51 Sept/2004* APP-52 Sept/2004* APP-53 Sept/2004* APP-54 Sept/2004* APP-55 Sept/2004* APP-56 Sept/2004* APP-57 Sept/2004* APP-58 Sept/2004* APP-59 Sept/2004* APP-60 Sept/2004* APP-61 Sept/2004* APP-62 Sept/2004* APP-63 Sept/2004



Diagnostic Appendices (cont). * APP-64 Sept/2004* APP-65 Sept/2004* APP-66 Sept/2004* APP-67 Sept/2004* APP-68 Sept/2004* APP-69 Sept/2004* APP-70 Sept/2004* APP-71 Sept/2004* APP-72 Sept/2004* APP-73 Sept/2004* APP-74 Sept/2004* APP-75 Sept/2004* APP-76 Sept/2004* APP-77 Sept/2004* APP-78 Sept/2004* APP-79 Sept/2004* APP-80 Sept/2004* APP-81 Sept/2004* APP-82 Sept/2004* APP-83 Sept/2004* APP-84 Sept/2004* APP-85 Sept/2004* APP-86 Sept/2004* APP-87 Sept/2004* APP-88 Sept/2004* APP-89 Sept/2004* APP-90 Sept/2004



TABLE OF CONTENTS

ITEM PAGE

SYSTEM DESCRIPTION

1. General ...............................................................1

2. System Configuration ..................................................1

A. TPU 67A TCAS II Processor .......................................2

B. CM 67A/CM 2000 Configuration Module .............................9

C. ANT 67A Directional Antenna ....................................10

D. L-Band Omnidirectional Antenna .................................13

E. IVA-81A TA/RA/VSI ..............................................14

F. IVA-81B RA/VSI .................................................19

G. IVA-81C/IVA-81D TA/RA/VSI ......................................21

H. GC 362A TCAS Graphics Processor ................................24

I. MST 67A Mode S Transponder .....................................26

J. KFS 578A Mode S/TCAS II Control Unit Configurations ............31

K. PS-578A Mode S/TCAS II Control Unit Configurations .............34

L. PS-550 Mode S/TCAS II Control Unit Configurations ..............41

M. CD 671C Control Unit ...........................................44

N. CTA-81A Control Unit ...........................................47

O. CTA-81D Control Unit ...........................................50

P. Optional Displays and Control Units ............................51

3. Environmental Certification ..........................................51

4. Related Publications .................................................93

5. CAS 67A TCAS II Installation Kits ....................................95

A. TPUDIAG/TCASDIAG Config. Module/Diagnostic Software Kits .......95

B. TPU 67A Installation Kit (New Installation) ....................95

C. TPU 67A Installation Kit (TCAS I to TCAS II Upgrade) ...........97

D. ANT 67A Antenna Adapter Kits ...................................98

E. Omnidirectional Antenna Installation Kit .......................98

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ITEM PAGE

F. IVA-81A/IVA-81B/IVA-81C/IVA-81D Installation Kits ..............99

G. GC 362A Installation Kit ......................................100

H. MST 67A Installation Kit ......................................100

I. KFS 578A / PS-578A Installation Kit ...........................101

J. PS-578A Configuration Programming Harness .....................101

K. PS-550 Connector Assembly .....................................102

L. CD 671C Installation Kit ......................................102

M. CTA-81A/CTA-81D Installation Kit ..............................103

6. System Description ..................................................103

A. General .......................................................103

B. TCAS II Functional Overview ...................................103

C. System Integration ............................................105

7. System Component Functions ..........................................125

A. TCAS Processor ................................................125

B. Directional Antenna ...........................................136

C. TCAS Omnidirectional Antenna ..................................137

D. TA/RA/VSI Display .............................................139

E. RA/VSI Display ................................................142

F. Mode S Transponder ............................................144

G. Control Units .................................................146

8. System Control and Indicator Functions ..............................147

A. General .......................................................147

B. TCAS Input Power Control ......................................147

C. TCAS II Control Units .........................................148

D. GC 362A TCAS Graphics Processor ...............................160

E. TA/RA/VSI .....................................................161

F. RA/VSI ........................................................162

G. Weather Radar/TCAS Display ....................................163

H. Optional Aural/Lamp Advisory Outputs ..........................163

I. Audio Message Alerts ..........................................163

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ITEM PAGE

J. TCAS Processor and Mode S Transponder Fault Indicators ........163

K. Optional Advisory Cancel Switch ...............................164

L. Range Selection and Range Rings ...............................164

FAULT ISOLATION

1. General ............................................................1001

2. Fault Isolation ....................................................1001

A. General ......................................................1001

B. Fault Isolation Using the Mode S/TCAS Control Unit ...........1003

C. Fault Isolation Using TCAS Processor LED Fault Codes .........1006

D. Fault Isolation Using the Diagnostic Computer ................1014

INSTALLATION AND MAINTENANCE

1. General ............................................................2001

2. Unpacking ..........................................................2001

3. Pre-Installation Testing ...........................................2001

4. Equipment Changes and Markings .....................................2001

5. Equipment Location and Interwiring .................................2002

A. General ......................................................2002

B. Location of Equipment ........................................2002

C. Interwiring and Cable Fabrication ............................2006

6. Equipment Installation .............................................2046

A. TPU 67A TCAS Processor Installation ..........................2046

B. Configuration Module Installation ............................2047

C. TCAS Directional Antenna Installation ........................2047

D. TCAS Omnidirectional Antenna Installation ....................2048

E. IVA-81A/C/D TA/RA/VSI and IVA-81B RA/VSI Installation ........2048

F. Transponder and Mounting Tray Installation ...................2049

G. KFS 578A/PS-578A/PS-550/CD 671C Control Unit Installation ....2049

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ITEM PAGE

H. GC 362A TCAS Graphics Processor Installation .................2049

7. Inspection and System Checkout .....................................2049

A. System Interwiring Check .....................................2050

B. Visual Inspection ............................................2051

C. Post-Installation Test .......................................2053

D. Flight Test (Required for STC) ...............................2082

8. Removal and Replacement ............................................2083

A. TPU 67A TCAS Processor .......................................2083

B. Directional Antenna ..........................................2083

C. Omnidirectional Antenna ......................................2084

D. TCAS Control Unit ............................................2084

E. 3ATI Traffic Displays ........................................2084

F. GC 362A TCAS Graphics Processor ..............................2085

G. CM 67A/CM 2000 Configuration Module ..........................2085

9. Maintenance Procedures .............................................2086

A. In-Aircraft Adjustments ......................................2086

B. System Protection ............................................2086

C. Lubrication ..................................................2086

D. Cleaning .....................................................2086

10. Aircraft Maintenance Programs ......................................2086

A. General ......................................................2086

B. Honeywell TCAS Maintenance Recommendations ...................2087

11. ANT 67A Directional Antenna Adapter Plate Installation .............2087

A. General Information ..........................................2087

B. Installation Procedure A .....................................2088

C. Installation Procedure B .....................................2089

D. Recommended Materials ........................................2090

E. Bonding Requirements .........................................2091

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DIAGNOSTIC APPENDICES

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Figure 1 CAS 67A TCAS II System Components ............................3

Figure 2 TPU 67A Environmental Qualification Form ....................52

Figure 3 CM 67A Environmental Qualification Form .....................57

Figure 4 CM 2000 Environmental Qualification Form ....................60

Figure 5 ANT 67A Environmental Qualification Form ....................63

Figure 6 CD 671C Environmental Qualification Form ....................64

Figure 7 KFS 578A Environmental Qualification Form (-0000) ...........66

Figure 8 KFS 578A Environmental Qualification Form (-0010) ...........67

Figure 9 PS-578A Environmental Qualification Form ....................69

Figure 10 PS-550 Environmental Qualification Form .....................72

Figure 11 CTA 81() Environmental Qualification Form ...................75

Figure 12 MST 67A Environmental Qualification Form (-0000) ............82



Figure 15 GC 362A Environmental Qualification Form ....................88

Figure 16 IVA 81A/B Environmental Certification Categories ............90

Figure 17 IVA 81C Environmental Qualification Form ....................91

Figure 18 IVA 81D Environmental Qualification Form ....................92

Figure 19 PS-578A Configuration Programming Harness ..................102

Figure 20 TPU 67A TCAS II Processor, Inputs/Outputs ..................121

Figure 21 Mode S and ATCRBS Mode C Interrogation Formats .............132

Figure 22 Mode S and ATCRBS Mode C Transponder Reply Message Formats .133

Figure 23 TCAS Directional Antenna Transmit/Receive Beam Patterns ....138

Figure 24 IVA-81A/IVA-81C/IVA-81D TA/RA/VSI ..........................140

Figure 25 IVA-81B RA/VSI .............................................143

Figure 26 KFS 578A Control Unit Controls .............................148

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Figure 27 PS-578A Control Unit Controls ..............................149

Figure 28 PS-550 Control Unit Controls ...............................150

Figure 29 CD 671C Control Unit Controls ..............................151

Figure 30 CTA-81 ( ) Control Unit Controls ...........................152

Figure 31 GC 362A TCAS Graphics Processor, TCAS and Radar Displays ...165

Figure 32 Collins IND270 Indicator, TCAS and Radar Displays ..........167

Figure 33 Honeywell WI650 Radar Indicator, TCAS and Radar Displays ...169

Figure 34 Honeywell P90 Radar Indicator, TCAS and Radar Displays .....171

Figure 1001 TCAS Test Pattern .........................................1003

Figure 2001 TPU 67A TCAS Processor Rear Connector Key & Pin Locations .2010

Figure 2002 IVA-81A/B/C/D Rear Connector Locations ....................2021

Figure 2003 IVA-81A/B/C/D Electrical Connector Pin Locations ..........2022

Figure 2004 KFS 578A Control Unit, Rear Connectors ....................2025

Figure 2005 PS-578A Mode S/TCAS Control Unit Rear Connector (J1) ......2028

Figure 2006 PS-578A Mode S/TCAS Control Unit Rear Connector (J2) ......2031

Figure 2007 PS-550 Mode S/TCAS Control Unit Rear Connector ............2032

Figure 2008 CD 671C Control Unit, Rear Connectors .....................2036

Figure 2009 GC 362A TCAS Graphics Processor, Rear Connector ...........2039

Figure 2010 TCAS Bearing Measurements .................................2079

Figure 2011 ANT 67A Directional Antenna Adapter and Moldable Shim .....2092

Figure 2012 TPU 67A TCAS II Processor Outline Drawing .................2093

Figure 2013 CM 67A/CM 2000 Configuration Module Outline Drawing .......2095

Figure 2014 ANT 67A Directional Antenna Outline Drawing ...............2097

Figure 2015 IVA 81A (TA/RA/VSI) Outline Drawing .......................2101

Figure 2016 IVA 81B (RA/VSI) Outline Drawing ..........................2105

Figure 2017 IVA 81C (TCAS) Outline Drawing ............................2107

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Figure 2018 IVA 81D (TCAS) Outline Drawing ............................2109

Figure 2019 GC 362 TCAS Graphics Processor Outline Drawing ............2111

Figure 2020 KFS 578A Control Unit Outline Drawing .....................2113

Figure 2021 PS-578A Control Unit Outline Drawing ......................2115

Figure 2022 PS-550 Control Unit Outline Drawing .......................2117

Figure 2023 CD 671C Control Unit Outline Drawing ......................2119

Figure 2024 TPU 67A Interconnect Drawing Family .......................2121

Figure 2025 TPU 67A Pinout Drawing ....................................2123

Figure 2026 TCAS II Configuration Pins Interface Drawing ..............2125

Figure 2027 TCAS II Discrete Interface Drawing ........................2127

Figure 2028 TCAS Radar/Baro Altitude Interface Drawing ................2131

Figure 2029 Attitude/Heading Interface Drawing ........................2139

Figure 2030 Antenna/Suppression Interface Drawing .....................2141

Figure 2031 Power Interface Drawing ...................................2143

Figure 2032 Lear 31/EFS 40/50 TCAS Interface Drawing ..................2145

Figure 2033 GC 362/Bendix TCAS Interface Drawing ......................2147

Figure 2034 GC 362/Honeywell TCAS Interface Drawing ...................2153

Figure 2035 GC 362/Collins TCAS Interface Drawing .....................2159

Figure 2036 RA Display (ARINC 429 Low Speed) Interface Drawing ........2163

Figure 2037 TA/RA Display (ARINC 429 High Speed) Interface Drawing ....2165

Figure 2038 Citation VB Honeywell EFIS/TCAS Interface Drawing .........2183

Figure 2039 Jetstream 41 Honeywell EFIS/TCAS Interface Drawing ........2187

Figure 2040 Diagnostic/Data Recorder Interface Drawing ................2191

Figure 2041 TCAS II ATE Interface Drawing .............................2193

Figure 2042 MST 67A Mode S Interface Drawing ..........................2195

Figure 2043 Collins TDR-94D Mode S Interface Drawing ..................2197

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Figure 2044 Honeywell Primus II/TCAS Interface Drawing ................2199

Figure 2045 CAS 67A TCAS II System Interface Drawing ..................2207

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ITEM PAGE

Table 1 CAS 67A TCAS II System Components ............................1

Table 2 TPU 67A TCAS II Processor Versions ...........................2

Table 3 TPU 67A TCAS II Processor Features ...........................2

Table 4 TPU 67A TCAS II Processor Specifications .....................5

Table 5 CM 67A/CM 2000 Configuration Module Versions .................9

Table 6 CM 67A/CM 2000 Configuration Module Features .................9

Table 7 CM 67A/CM 2000 Configuration Module Specifications ...........9

Table 8 ANT 67A Directional Antenna Versions ........................10

Table 9 ANT 67A Directional Antenna Features ........................10

Table 10 ANT 67A Directional Antenna Specifications ..................11

Table 11 Omnidirectional Antenna Versions ............................13

Table 12 Omnidirectional Antenna Features ............................13

Table 13 IVA-81A TA/RA/VSI Versions ..................................14

Table 14 IVA-81A TA/RA/VSI Features ..................................17

Table 15 IVA-81A TA/RA/VSI Specifications ............................18

Table 16 IVA-81B RA/VSI Versions .....................................19

Table 17 IVA-81B RA/VSI Features .....................................19

Table 18 IVA-81B RA/VSI Specifications ...............................20

Table 19 IVA-81C TA/RA/VSI Versions ..................................21

Table 20 IVA-81C TA/RA/VSI Features ..................................21

Table 21 IVA-81D TA/RA/VSI Versions ..................................22

Table 22 IVA-81D TA/RA/VSI Features ..................................22

Table 23 IVA-81C/IVA-81D TA/RA/VSI Specifications ....................23

Table 24 GC 362A TCAS Graphics Processor Versions ....................24

Table 25 GC 362A TCAS Graphics Processor Features ....................24

Table 26 GC 362A TCAS Graphics Processor Specifications ..............25

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ITEM PAGE

Table 27 MST 67A Mode S Transponder Versions .........................26

Table 28 MST 67A Mode S Transponder Features .........................27

Table 29 MST 67A Mode S Transponder Specifications ...................28

Table 30 KFS 578A Control Unit Versions ..............................31

Table 31 KFS 578A Control Unit Features ..............................32

Table 32 KFS 578A Control Unit Specifications ........................33

Table 33 KFS 578A - PS-578A Configuration Cross-Reference (TCAS II) ..34

Table 34 PS-578A Control Unit Versions ...............................38

Table 35 PS-578A Control Unit Features ...............................39

Table 36 PS-578A Control Unit Specifications .........................40

Table 37 PS-550 Control Unit Versions ................................41

Table 38 PS-550 Control Unit Features ................................42

Table 39 PS-550 Control Unit Specifications ..........................43

Table 40 CD 671C Control Unit Versions ...............................44

Table 41 CD 671C Control Unit Features ...............................45

Table 42 CD 671C Control Unit Specifications .........................46

Table 43 CTA-81A Control Unit Versions ...............................47

Table 44 CTA-81A Control Unit Features ...............................48

Table 45 CTA-81A/CTA-81D Control Unit Specifications .................49

Table 46 CTA-81D Control Unit Versions ...............................50

Table 47 CTA-81D Control Unit Features ...............................50

Table 48 Optional Displays and Control Units .........................51

Table 49 Related Publications ........................................93

Table 50 TPUDIAG/TCASDIAG Config. Module/Diagnostic Software Kits ....95

Table 51 TPU 67A TCAS II Processor Installation Kit ..................96

Table 52 TPU 67A TCAS II Processor Upgrade Installation Kit ..........97

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ITEM PAGE

Table 53 TPU 67A TCAS II Processor Upgrade Installation Kit ..........97

Table 54 ANT 67A Antenna Adapter Kits ................................98

Table 55 IVA-81A/IVA-81B/IVA-81C/IVA-81D Installation Kit ............99



Table 58 GC 362A Installation Kit ...................................100

Table 59 MST 67A Installation Kit ...................................100

Table 60 KFS 578A / PS-578A Installation Kit ........................101

Table 61 CD 671C Installation Kit ...................................102

Table 62 CTA-81A/CTA-81D Installation Kit ...........................103

Table 63 TCAS II System Integration Matrix ..........................105

Table 64 Control Unit Control and Indicator Functions ...............153

Table 1001 TCAS/Weather Radar Display Fault Annunciations ............1006

Table 1002 Catastrophic Single Letter Failure Codes ..................1007

Table 1003 TCAS Processor Fault Codes ................................1008

Table 2001 TPU 67A TCAS Processor, Rear Connector Pin Names ..........2011

Table 2002 Configuration Module, Connector Pin Names .................2019

Table 2003 IVA-81A/B/C/D Electrical Connector Pin Names ..............2023

Table 2004 KFS 578A Control Unit Connector (P5782) Pin Definitions ...2026

Table 2005 KFS 578A Control Unit Connector Pin Names (P5781) .........2026

Table 2006 PS-578A Control Unit Connector (J1) Pin Definitions .......2029

Table 2007 PS-578A Control Unit Connector (J2) Pin Definitions .......2031

Table 2008 PS-550 Control Unit Connector Pin Name Definitions ........2033

Table 2009 CD 671C Control Unit, Connector Pin Names .................2037

Table 2010 GC 362A TCAS Graphics Proc. -0101, Connector Pin Names ....2040


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ITEM PAGE


Table 2013 Inspection/Check Procedure ................................2051

TC-14 006-05340-0007 Rev. 7 Sept/200434-40-01


INTRODUCTION

This manual includes description, installation, fault isolation, and flight-line checkout procedures for the Honeywell CAS 67A (TCAS II) Traffic Alert and Col-lision Avoidance System.The conditions and tests required for the TSO and MOPS approval of this article are minimum performance standards. It is the responsibility of those installing this article either on or with a specified type or class of aircraft to determine that the aircraft installation conditions are within the TSO and MOPS standards. These articles must have separate approval for installation in an aircraft. Any features in this equipment outside the requirements of this applicable TSO and MOPS must be evaluated and approved as part of the installation approval. The article may be installed only if performed under 14 CFR part 43 or the applicable airworthiness requirements.

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INTRO-2 006-05340-0007 Rev. 7 Sept/200434-40-01


SYSTEM DESCRIPTION

1. General

“SYSTEM DESCRIPTION” contains functional descriptions, equipment part numbers, and specifications for the Honeywell CAS 67A TCAS II Traffic Alert and Collision Avoidance System.

The CAS 67A TCAS II system monitors airspace around its "own" aircraft by interrogating an "intruder" aircraft’s transponder. The TCAS processor computes the range, differential altitude, bearing and closure rate of the intruder. It then compares this data to its own position and determines the potential for collision. Audio messages and visual displays of traf-fic advisories (TAs) and collision resolution advisories (RAs) are pro-duced when required.

2. System Configuration

Components of the CAS 67A TCAS II system are listed in Table 1 CAS 67A TCAS II System Components and shown in Figure 1 CAS 67A TCAS II System Components. Versions, features, and specifications of system components are listed in following paragraphs.

NOTE: Some part numbers may not be currently available. Consult the current Honeywell catalog or contact a Honeywell representative for equipment availability.

PROCESSOR TPU 67A TCAS II Processor andCM 67A/CM 2000 Configuration Module

ANTENNA(TOP)

ANT 67A Directional Antenna

ANTENNA(BOTTOM)

ANT 67A Directional AntennaOR: L-band Omnidirectional antenna (dc shorted) optional

DISPLAYS Dual resolution advisory displays and a traffic display required:Two IVA-81A/IVA-81C/IVA-81D TA/RA/VSI Traffic Advisory/Resolution Advisory/Vertical Speed Indicators.OR: IVA-81B RA/VSI Resolution Advisory/Vertical Speed Indicator and a radar/traffic display via GC 362A TCAS Graphics Processor.OR: KAD 480T Air Data System and an EFIS 40/50 MFD Display via symbol generator.

TRANSPONDER MST 67A ATC Mode S (diversity) Transponder

CONTROL UNIT KFS 578A/PS-578A/PS-550 Mode S Transponder/TCAS Control UnitOR: CD 671C Mode S Transponder/TCAS Control UnitOR: CTA-81A/CTA-81D Mode S Transponder/TCAS Control UnitOR: RMS 555 Radio Management System

Table 1 CAS 67A TCAS II System Components

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A. TPU 67A TCAS II Processor

Listed below are versions, features, and specifications of the TPU 67A TCAS II processor.

HONEYWELLPART NUMBER

VERSIONNUMBER

PRIMARYPOWER

SINGLE OR DUALDIRECTIONAL ANT

EXTENDEDENVIRONMENTALPROTECTION

SECONDARY ATT/HDGINPUT

CHANGE 7SOFTWAREACAS II

066-01146 -0101 28 Vdc X

-0201 28 Vdc X X X

-1111 28 Vdc X X

-1211 28 Vdc X X X X

Table 2 TPU 67A TCAS II Processor Versions

FEATURE DESCRIPTION

Basic Unit TCAS II transmitter-receiver. Primary component of CAS 67A system. Contains circuitry necessary for functions of a TCAS II system and interfacing with configuration module, antennas, graphic processors, controls, and displays.

Primary Power 28 Vdc power input

Single or DualDirectional Antenna

Designed for installations having top-mounted directional antenna, and bottom-mounted directional or omnidirectional antenna.

Extended Environmental Protection

TPU 67A p/n’s 066-01146-0201,-1211 have been TSO’d with additional environmental testing (Radio Frequency Susceptibility [Radiated and Conducted], Emission of Radio Frequency Energy, and Lightning Induced Transient Susceptibility categories). Refer to Figure 2 TPU 67A Environmental Qualification Form for details.

Attitude/Heading Secondary Input

TPU 67A p/n’s 066-01146-0201,-1211 have an additional secondary ARINC429 AHRS/IRU Attitude/Heading Input Port.

NOTE: One or two directional antennas may be used in a TCAS II system. A top-mounted ANT 67A is always required. For intruder bearing to be determined on the bottom-antenna an ANT 67A must be used on bottom of aircraft.

Table 3 TPU 67A TCAS II Processor Features

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006-05340-0007 Rev. 7 Sept/200434-40-01

Figure 1 CAS 67A TCAS II System Components


Table 4 TPU 67A TCAS II Processor Specifications (Sheet 1 of 4)

CHARACTERISTIC DESCRIPTION

Form Factor 4 MCU ARINC 600 (1/2 long ATR)

Physical Dimensions See Figure 2012 TPU 67A TCAS II Processor Outline Drawing

Weight See Figure 2012 TPU 67A TCAS II Processor Outline Drawing

Power Requirements

Primary +28 Vdc (22-30 Vdc), 70 watts (maximum)

Reference 26 Vac synchro reference power (ARINC 413A)

Altitude Category A2 15,000 ft; F2 55,000 ft

Temperature Range

Operating -55 °C to +70 °C

Storage -55 °C to +85 °C

Cooling Convection

Surveillance Capacity 45 aircraft. Some TCAS display up to 30 of the closest-range intruders.

Voice Synthesizer Output Speaker: 6.5 watts into 8 ohms.Headphones: 40 milliwatts (nominal) into 600 ohms (strap selectable).

Receiver Frequency 1087 to 1093 MHz

Minimum Trigger Level (MTL) -74 dBm ±2 dB at antenna end of coax

Decoding Ratio

Input at -78 dBm or less at antenna

10% maximum

Input at MTL +3 dB to -21 dBm 99% minimum

Out-of-Band Rejection(reply signal level requiredto provide 90% decoding ratio)

At 1084.5 and 1095.5 MHz 3 dB above MTL minimum

At 1075 and 1105 MHz 40 dB above MTL minimum

At 1065 and 1115 MHz 60 dB above MTL minimum

Dynamic Minimum TriggerLevel (DMTL) Threshold

ATCRBS MTL + 13 dB

Mode S MTL + 10 dB

Minimum Pulse Width 300 µsec

Maximum Pulse Rise Time 0.50 µsec

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Table 4 TPU 67A TCAS II Processor Specifications (Sheet 2)


Delay Difference (between top and bottom antenna channels,including transmission lines)

0.05 µsec

Transmitter:

Frequency 1030.00 ±0.01 MHz

Warm up time 3 minutes for frequency stabilization

Input VSWR: 1.35:1

Rf Peak Output Power at unit connector

Omni Antenna

Minimum +47.0 dBm (50 W)

Maximum +51.0 dBm (126 W)

Directional Antenna

(per port)

Minimum +47 dBm (50 W)

Maximum +51 dBm (126 W)

Nominal +49 dBm (79 W)

Unwanted Output Power (inactive state)

-70 dBm maximum

Interrogation Repetition Interval

1 second

Broadcast Interrogation Interval

10 seconds in each direction (nominal)

Interrogation Interval Jitter

Mode S and ATCRBS Mode C +0.1 to -0.1 seconds about the nominal 1-second interval.

TCAS Broadcast -1.0 to +1.0 seconds about the nominal 10-second interval.

Transmitter Delay Difference (between top and bottom antenna channels, including transmission lines)

0.050 µsec maximum

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Transmitter (Cont.)

Transmitter Pulse Characteristics

Mode C Only All-Call

(S1, P1, P2, P3, P4)

Pulse Duration 0.80 ±0.05 µsec

Rise Time 0 to 0.10 µsec

Decay Time 0 to 0.20 µsec

Pulse Spacing

P1 to P2 2.00 ±0.10 µsec

P1 to P3 21.00 ±0.10 µsec

P3 to P4 2.00 ±0.04 µsec

S1 to P1 2.00 ±0.10 µsec

Mode S

Pulse Duration

P1, P2 0.80 ±0.05 µsec

P6 (short) 16.250 ±0.125 µsec

P6 (long) 30.250 ±0.125 µsec

Rise Time 0.05 to 0.10 µsec

Decay Time 0.05 to 0.20 µsec

S1 Pulse 10 dB below the P1 pulse in the current set of pulses. The level is dependent on the whisper-shout level.

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Transmitter Pulse

Pulse Spacing

P1 to P2 2.00 ±0.04 µsec

P2 to P6 sync phase reversal

2.75 ±0.04 µsec

P6 leading edge to P6 sync phase reversal

1.25 ±0.04 µsec

High Resolution Whisper-Shout Mode C Power Levels

S1 Pulse 2 dB or 3 dB below the P1 pulse in the current set of pulses. The level is dependent on the whisper-shout level.

Minimum Basic Whisper-Shout Mode C Power Levels

(066-01146-1111,-1211 only)

Connectors ARINC 404. See Figure 2001 TPU 67A TCAS Processor Rear Connector Key & Pin Locations

TSO C119a p/n 066-01146-0101,-0201C119b p/n 066-01146-1111,-1211

Environmental Certification See Figure 2 TPU 67A Environmental Qualification Form

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B. CM 67A/CM 2000 Configuration Module

Listed below are versions, features, and specifications of the CM 67A/CM 2000 configuration module.

Table 6 CM 67A/CM 2000 Configuration Module Features

Table 7 CM 67A/CM 2000 Configuration Module Specifications


VERSION NUMBER

BASIC UNIT INITIALIZED W/ DEFAULTS

NUMBER OFMOUNTING SCREWS

TSOCOMPLIANCE

071-00097 -1000 CM 67A X 2 C63c, C119a

-0100 CM 2000 2 C63c, C119a

Table 5 CM 67A/CM 2000 Configuration Module Versions

FEATURE DESCRIPTION

Basic Unit Contains two 9356 EEPROMS stored with hardware strap and bearing calibration information. Screw mounted within two (2) feet of wire harness from the TCAS processor rack.


Physical Dimensions See Figure 2013 CM 67A/CM 2000 Configuration Module Outline Drawing

Weight See Figure 2013 CM 67A/CM 2000 Configuration Module Outline Drawing

Components Solid state, no mechanical parts

Mounting Remote. See Figure 2013 CM 67A/CM 2000 Configuration Module Outline Drawing

Power Requirements +5 Vdc, via TPU 67A TCAS II processor

Temperature -55 °C to +70 °C

Electrical Connector See Figure 2013 CM 67A/CM 2000 Configuration Module Outline Drawing

TSO C119a and C63c

Environmental Certification See Figure 3 CM 67A Environmental Qualification Formor Figure 4 CM 2000 Environmental Qualification Form

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C. ANT 67A Directional Antenna

Listed below are versions, features, and specifications of the ANT 67A directional antenna.

Table 8 ANT 67A Directional Antenna Versions

Table 9 ANT 67A Directional Antenna Features


VERSION NUMBER

ANTENNA SHAPE

COAX CONN BASIC SHAPE

NUMBER OFMOUNTING SCREWS

071-01548 -0100 Teardrop 1.50" Flat 4

-0200 Teardrop 0.73" Flat 4

FEATURE DESCRIPTION

Basic Unit Four-element passive array. Screw mounted to aircraft fuselage. Radiates 1030 MHz, pulse-modulated inputs from TPU 67A TCAS processor. Detects radiated 1090 MHz, pulse-modulated signals.

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Table 10 ANT 67A Directional Antenna Specifications (Sheet 1 of 2)


Form Factor ARINC 735 (teardrop shape)

Physical Dimensions See Figure 2014 ANT 67A Directional Antenna Outline Drawing

Weight See Figure 2014 ANT 67A Directional Antenna Outline Drawing

Antenna Base Types Flat base (071-01548-0100,-0200)

Altitude Category F2 55,000 ft.

Temperature Range



Antenna Mounting Footprint See Figure 2014 ANT 67A Directional Antenna Outline Drawing

Antenna Mounting Mounts directly to aircraft using mounting instructions, defined in Figure 2011 ANT 67A Directional Antenna Adapter and Moldable Shim, Figure 2014 ANT 67A Directional Antenna Outline Drawing, and paragraph 11. ANT 67A Directional Antenna Adapter Plate Installation.

An antenna adapter is required for mounting flat-base antenna on a curved surface.

Exterior Material High-strength composite

Number of Antenna Array Elements Four

Polarization Vertical

Power Requirements None

Transmission Frequency 1030 ±1 MHz

Receiving Frequency 1090 ±3 MHz

Connectors See Figure 2014 ANT 67A Directional Antenna Outline Drawing

Quantity Four

Type See Figure 2014 ANT 67A Directional Antenna Outline Drawing

Pressurization Withstands a pressure differential of 25 P.S.I.A.

Lighting Protection Meets swept zone 2A lightning strikerequirements

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Table 10 ANT 67A Directional Antenna Specifications (Sheet 2)


Main Beam Characteristics

Operational Beam Positions 4

Half Power Azimuth Beam Width (measured over -15 to +20 elevation)

> 90 degrees

Steering Quantization 90°

Omni Beam Characteristics

Operational Beam Positions 360°

Beam Null Compared to Main Beam (at each elevation from -15 to +20)

> 9 dB

Input Port VSWR 1.35:1 maximum

Antenna Cable Loss Requirement 2.5 ± 0.5 dB at 1030 MHz for each coaxial cable including connectors

Antenna Cable Differential Phase Delay 135° maximum electrical length

Maximum Peak Input Power 1000 W pulsed

Maximum Average Input Power 10 W continuous

ARINC Characteristic ARINC 735

TSO C118 and C119a

Environmental Certification See Figure 5 ANT 67A Environmental Qualification Form

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D. L-Band Omnidirectional Antenna

Listed below are versions and features of the omnidirectional an-tenna.

Table 11 Omnidirectional Antenna Versions

Table 12 Omnidirectional Antenna Features

VENDOR NAME MODEL VENDOR PARTNUMBER

LRUDESCRIPTION

IMPEDANCE/ RF/DC

TSOCOMPLIANCE

Dorne &Margolin

DMNI 50-Series

DMNI 50-2-2 L-Band 50 Ω/Short C66a, C74c

FEATURE DESCRIPTION

Basic Unit Screw mounted to aircraft fuselage. Radiates 1030 MHz, pulse-modulated inputs from TPU 67A TCAS processor. Detects radiated 1090 MHz, pulse-modulated signals. Vertically polarized.

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E. IVA-81A TA/RA/VSI

Listed below are versions, features, and specifications of the IVA-81A TA/RA/VSI.

Table 13 IVA-81A TA/RA/VSI Versions (Sheet 1 of 4)

HONEYWELL PART NUMBER

VERSION NUMBER

FACE PLATE

PRIMARY POWER

PANELLIGHTING

UP⋅DNRANGECONTROL

TASELECTSWITCH

DIM(POT)

SWIDENT

066-50001 -8101 Black 115 Vac 5 Vac/Vdc 01/06

-8102 Gray 115 Vac 5 Vac/Vdc 01/06

-8103 Brown 115 Vac 5 Vac/Vdc 01/06

-8104 Blue 115 Vac 5 Vac/Vdc 01/06

-8105 Black 115 Vac 5 Vac/Vdc X 01/06

-8106 Gray 115 Vac 5 Vac/Vdc X 01/06

-8107 Brown 115 Vac 5 Vac/Vdc X 01/06

-8108 Blue 115 Vac 5 Vac/Vdc X 01/06

-0901 Black 115 Vac 5 Vac/Vdc X X 01/06

-1001 Gray 115 Vac 5 Vac/Vdc X X 01/06

-1101 Brown 115 Vac 5 Vac/Vdc X X 01/06

-1201 Blue 115 Vac 5 Vac/Vdc X X 01/06

-1301 Black 28 Vdc 5 Vac/Vdc 01/06

-1401 Gray 28 Vdc 5 Vac/Vdc 01/06

-1501 Black 28 Vdc 5 Vac/Vdc X 01/06

-1601 Gray 28 Vdc 5 Vac/Vdc X 01/06

-1701 Black 28 Vdc 5 Vac/Vdc X X 01/06

-1801 Gray 28 Vdc 5 Vac/Vdc X X 01/06

-1901 Black 28 Vdc 28 Vdc 01/06

-2001 Gray 28 Vdc 28 Vdc 01/06

-2101 Black 28 Vdc 28 Vdc X 01/06

-2201 Gray 28 Vdc 28 Vdc X 01/06

-2301 Black 28 Vdc 28 Vdc X X 01/06

-2401 Gray 28 Vdc 28 Vdc X X 01/06




Page 14 006-05340-0007 Rev. 7 Sept/200434-40-01


Table 13 IVA-81A TA/RA/VSI Versions (Sheet 2)


VERSION NUMBER

FACE PLATE

PRIMARY POWER

PANELLIGHTING

UP⋅DNRANGECONTROL

TASELECTSWITCH

DIM(POT)

SWIDENT

066-50001 -2802 Gray 28 Vdc 5 Vac/Vdc X X 02/03

-2902 Black 28 Vdc 28 Vdc X 02/03

-3002 Gray 28 Vdc 28 Vdc X 02/03

-3102 Black 28 Vdc 28 Vdc X X 02/03

-3202 Gray 28 Vdc 28 Vdc X X 02/03







-2304 Black 28 Vdc 28 Vdc X X 04/03

-2404 Gray 28 Vdc 28 Vdc X X 04/03





-2904 Black 28 Vdc 28 Vdc X 04/03

-3004 Gray 28 Vdc 28 Vdc X 04/03

-3104 Black 28 Vdc 28 Vdc X X 04/03

-3204 Gray 28 Vdc 28 Vdc X X 04/03

-3304 Black 115 Vac 5 Vac/Vdc X 04/03

-3404 Gray 115 Vac 5 Vac/Vdc X 04/03





Page 15 006-05340-0007 Rev. 7 Sept/200434-40-01




SOFTWARE RANGE SELECTION OPTIONS BY SOFTWARE TYPE

RANGE OPTION: 01/06 02/03 03/03 04/03 05/03 06/01

Fixed at 6.5 nm X X X X X XFixed at 10.0 nm X X3, 5, 10, 15 nm X X XTransponder Panel X X X X X X5, 10, 20, 40 nm X X X3, 5, 10, 20, 40 nm X1, 3, 5, 10, 20, 40 nm X X

OPTIONS BY SOFTWARE TYPE

FUNCTION: 01/06 02/03 03/03 04/03 05/03 06/01

RLS Capability X XType “A” Flags/ MSGs X XBLS Compensation X X X X

NVIS Compatible X XDay/Night Display X X

NON-Standard ARINC 419 X X X

E-TCAS Compatible XVertical Speed m/sec X

Strap selectable Dim Knob X X X X

TSO’d X X X X

Page 16 006-05340-0007 Rev. 7 Sept/200434-40-01


Table 14 IVA-81A TA/RA/VSI Features

FEATURE DESCRIPTION

Basic Unit Displays resolution advisories, traffic advisories, and indicates vertical speed.

Faceplate Choice of faceplate colors

Primary Power Choice of 115 Vac or 28 Vdc versions

Panel Lighting Choice of 5 Vac/Vdc or 28 Vdc versions

UP/DNRange Control

Pushbutton range control mounted on front panel of TA/RA/VSI display. The range control allows the selection of 1, 3, 5, 10, 15, 20, or 40 nautical mile display ranges. Specific ranges and range groups available are defined by the software version in use.

TA SEL Switch Declutters all traffic symbols from display. If a TA or RA occurs, the All Traffic is automatically displayed.

BRT Control Allows manual adjustment of display brightness

Page 17 006-05340-0007 Rev. 7 Sept/200434-40-01


Table 15 IVA-81A TA/RA/VSI Specifications


Form Factor 3 ATI x 7.5 inches deep

Components Solid state. No mechanical parts

Physical Dimensions See Figure 2015 IVA 81A (TA/RA/VSI) Outline Drawing

Weight See Figure 2015 IVA 81A (TA/RA/VSI) Outline Drawing

Mounting Front, panel mount

Primary Power 115 V 400 Hz, 22 W; or 28 Vdc, 29 W.

Reference Power +/-12 Vdc reference power if altitude rate source input is ARINC 575 analog.

26 Vac reference power if altitude rate source input is ARINC 565 analog.

Lighting Power 5 Vac or 5 Vdc, 195 mA; or 28 Vdc, 135 mA.

Operating Temperature Range -15 °C to + 70 °C

Number of Intruder Symbol 3-30 Maximum determined by TCAS processorprogram strap configuration.

Display High resolution, full color dot matrix LCD. Combination vertical speed and traffic display.

Vertical Speed Input The IVA-81A meets the requirements of both type B and type C VSI indicators, pneumatic or air data electrical input. Both ARINC 500 and 700 series air data input accepted.

Data Input High-speed ARINC 429

Front-Mounted Range Control Optional

Front-Mounted TA SEL Switch and BRT Control

Optional

Pneumatic Connector (Located on indicator rear panel)

See Figure 2002 IVA-81A/B/C/D Rear Connector Locations

Electrical Connector (Located on indicator rear panel)

See Figure 2003 IVA-81A/B/C/D Electrical Connector Pin Locations

TSO C119a, C8c

Environmental Certification See Figure 16 IVA 81A/B Environmental Certification Categories

Page 18 006-05340-0007 Rev. 7 Sept/200434-40-01


F. IVA-81B RA/VSI

Listed below are versions, features, and specifications of the IVA-81B RA/VSI.

Table 16 IVA-81B RA/VSI Versions

Table 17 IVA-81B RA/VSI Features


VERSION NUMBER

FACE PLATE

PRIMARY POWER

PANELLIGHTING

066-50002 -8101 Black 115 Vac 5 Vac/Vdc

-8102 Gray 115 Vac 5 Vac/Vdc

-8103 Brown 115 Vac 5 Vac/Vdc

-8104 Blue 115 Vac 5 Vac/Vdc

-0901 Gray 115 Vac 5 Vac/Vdc

-1001 Brown 115 Vac 5 Vac/Vdc

FEATURE DESCRIPTION

Basic Unit Displays resolution advisories and indicates vertical speed


Primary Power Choice of 115 Vac or 28 Vdc versions

Panel Lighting Choice of 5 Vac/Vdc or 28 Vdc versions

Page 19 006-05340-0007 Rev. 7 Sept/200434-40-01


Table 18 IVA-81B RA/VSI Specifications



Components Electromechanical and solid state

Physical Dimensions See Figure 2016 IVA 81B (RA/VSI) Outline Drawing

Weight See Figure 2016 IVA 81B (RA/VSI) Outline Drawing

Mounting Front, panel mount

Primary Power 115 V 400 Hz, 20 W; or 28 Vdc, 29 W

Reference Power +/-12 Vdc reference power if altitude rate source input is ARINC 575 analog.

26 Vac reference power if altitude rate source input is ARINC 565 analog.

Lighting Power 5 Vac or 5 Vdc; or 28 Vdc


Display Lamps around the periphery of a fixed vertical speed scale and electromechanical needle. Combination vertical speed and resolution advisory display.

Vertical Speed Input The IVA-81B meets the requirements of both type B and type C VSI indicators, pneumatic or air data electrical input.

Data Input from TCAS High speed ARINC 429


Pneumatic Connector See Figure 2002 IVA-81A/B/C/D Rear Connector Locations

Electrical Connector See Figure 2003 IVA-81A/B/C/D Electrical Connector Pin Locations

TSO C119a, C8c

Environmental Certification See Figure 16 IVA 81A/B Environmental Certification Categories

Page 20 006-05340-0007 Rev. 7 Sept/200434-40-01


G. IVA-81C/IVA-81D TA/RA/VSI

Listed below are versions, features, and specifications of the IVA-81C (P/N 066-50053-XXXX) and IVA-81D (P/N 066-01171-XXXX) TA/RA/VSI.

Table 19 IVA-81C TA/RA/VSI Versions

Table 20 IVA-81C TA/RA/VSI Features


VERSION NUMBER

BEZEL PRIMARYPOWER

RANGECONTROLUP⋅DN

TASELECTSWITCH

LIGHTING BUS BRIGHT CONTROL (DIM POT)

066-50053 -2704 Black 28 V dc X 5 V ac or dc X

-2804 Gray 28 V dc X 5 V ac or dc X

FEATURE DESCRIPTION


UP/DNRange Control

Pushbutton range control mounted on front panel of TA/RA/VSI display. The range control allows selection of 3, 5, 10, 20, or 40 nautical mile display ranges. Specific ranges and range groups available are defined by the software version in use.

TA SEL Switch Declutters all traffic symbols from display. If a TA or RA occurs, All Traffic is automatically displayed.

BRT Control Allows manual adjustment of display brightness.

Page 21 006-05340-0007 Rev. 7 Sept/200434-40-01


* Honeywell part number 066-01171-XXXX where -xxxx = Version Number** NVIS-compatible Version, remaining versions have a light sensor.

Table 21 IVA-81D TA/RA/VSI Versions

Table 22 IVA-81D TA/RA/VSI Features

HONEYWELLPARTNUMBER

VERSION NUMBER*

SOFTWAREVERSION

BEZEL PRIMARYPOWER

RANGECONTROLUP⋅DN

TASELECTSWITCH

LIGHTING BUS BRIGHT CONTROL

(DIM POT)

066-01171 -0901 01/06 Black 115 V ac X 5 V ac or dc X

-0903 03/03 Black 115 V ac X 5 V ac or dc X


-1001 01/06 Gray 115 V ac X 5 V ac or dc X


-1101 01/06 Brown 115 V ac X 5 V ac or dc X

-1704 04/03 Black 28 V dc X 5 V ac or dc X

-1804 04/03 Gray 28 V dc X 5 V ac or dc X

-2304 04/03 Black 28 V dc X 28 V dc X



-2804 04/03 Gray 28 V dc X 5 V ac or dc X

-3104 04/03 Black 28 V dc X 28 V dc X

-3404 04/03 Gray 115 V ac 5 V ac or dc X



-3704** 06/01 Black 28 V dc X 5 V ac or dc X

-3706** 06/01 Black 115 V ac X 5 V ac or dc X

-8102 01/06 Gray 115 V ac 5 V ac or dc

FEATURE DESCRIPTION


UP/DNRange Control

Pushbutton range control mounted on front panel of TA/RA/VSI display. The range control allows selection of 3, 5, 10, 20, or 40 nautical mile display ranges. Specific ranges and range groups available are defined by the software version in use.

TA SEL Switch Declutters all traffic symbols from display. If a TA or RA occurs, All Traffic is automatically displayed.

BRT Control Allows manual adjustment of display brightness.

Page 22 006-05340-0007 Rev. 7 Sept/200434-40-01


Table 23 IVA-81C/IVA-81D TA/RA/VSI Specifications



Components Solid state. No mechanical parts

Overall Dimensions See Figure 2017 IVA 81C (TCAS) Outline Drawing or Figure 2018 IVA 81D (TCAS) Outline Drawing

Maximum Weight See Figure 2017 IVA 81C (TCAS) Outline Drawing or Figure 2018 IVA 81D (TCAS) Outline Drawing

Mounting Front, panel mount, Marmon clamp or equivalent

Power Requirements

Primary 115 V ac 400 Hz, or 28 V dc. Maximum power dissipation 40 watts (short term at cold temperature), at full brightness including display warm-up at low temperature.

Lighting 5 V ac or dc or 28 V dc

Reference +12 V dc if altitude rate source input is ARINC 575 analog. 26 V ac if altitude rate source input is ARINC 565 analog.


Number of Intruder Symbol3-30

Maximum determined by TCAS processorprogram strap configuration

Display High resolution, full color dot matrix LCD. Combination vertical speed, and traffic display

Vertical Speed Input The IVA 81C / IVA 81D meet the requirements of both type B and type C VSI indicators. Pneumatic or air data electrical input. Both ARINC 500 and 700 series air data input accepted.

Data Input High-speed ARINC 429


Front-Mounted TA SEL Switch and BRT Control

Optional

Pneumatic Connector (Located on indicator rear panel)

See Figure 2002 IVA-81A/B/C/D Rear Connector Locations

Electrical Connector (Located on indicator rear panel)

See Figure 2003 IVA-81A/B/C/D Electrical Connector Pin Locations

TSO C118, C119a, C8d (81C)

C118, C119b, C8d (81D)

Software Certification DO-178B, Level B

Environmental Certification See Figure 17 IVA 81C Environmental Qualification Form or Figure 18 IVA 81D Environmental Qualification Form

Page 23 006-05340-0007 Rev. 7 Sept/200434-40-01


H. GC 362A TCAS Graphics Processor

Listed below are versions, features, and specifications of the GC 362A TCAS graphics processor.

Table 24 GC 362A TCAS Graphics Processor Versions

Table 25 GC 362A TCAS Graphics Processor Features


VERSION NUMBER

PRIMARYPOWER

REMOTE SWITCH

RADAR INDICATOR

071-01505 -0102* 28 Vdc X RDS/RDR SERIES, HONEYWELL PRIMUS**

-0103 28 Vdc X RDS/RDR SERIES, HONEYWELL PRIMUS**

-0203 28 Vdc X RDS/RDR SERIES, COLLINS**

* Version -0102 replaced by version -0103.** See Table 25 GC 362A TCAS Graphics Processor Features for model compatibility.

FEATURE DESCRIPTION

Basic Unit Remote mounted graphics processor, converts high speed 429 from ARINC 735 processor for display on weather radar indicator.


Remote Switch Discrete switch that allows for manual mode control of the graphic processor. Modes available are WX Radar Only, WX Radar/TCAS overlay, and TCAS Only.

TCAS Processor Compatible with Honeywell TPU 67A

Radar Systems: All versions compatible with Honeywell RDS 81, RDS 82, RDS 84, RDS 86, RDR 2000, and RDR 2100.

-0102 Compatible with Honeywell Primus 200, 300SL, 400, 800 and P90 series radars.

-0103 Compatible with Honeywell Primus 200, 300SL, 400, 650, 800, 870 and P90 series radars.

-0203 Compatible with Collins IND-270 radar indicator.

Page 24 006-05340-0007 Rev. 7 Sept/200434-40-01


Table 26 GC 362A TCAS Graphics Processor Specifications


Physical Dimensions See Figure 2019 GC 362 TCAS Graphics Processor Outline Drawing

Weight See Figure 2019 GC 362 TCAS Graphics Processor Outline Drawing

Mounting Remote

Power Requirements 28 Vdc, 0.9 A max.

TSO C105

Temperature:



Data Input High Speed ARINC 429

Altitude 55,000 ft.

Symbology:

Red-filled square (TCAS II only) Resolution Advisory (RA) intruder

Yellow-filled square Traffic Advisory (TA)

White-filled diamond Proximity intruder

White unfilled diamond Non-threat intruder

Self-test Capability Initiated by TCAS system with label 270 set to functional test.

Environmental Certification See Figure 15 GC 362A Environmental Qualification Form

Page 25 006-05340-0007 Rev. 7 Sept/200434-40-01


I. MST 67A Mode S Transponder

Listed below are versions, features, and specifications of the MST 67A Mode S transponder.

Table 27 MST 67A Mode S Transponder Versions


VERSION NUMBER

PRIMARY POWER

BITE DIVER-SITY

BURST TUNING

REMOTEIDENT

DATA LINK

FLIGHT IDREPORTING

066-01143 -0301* 14-28 V FULL X 2

-0601 14-28 V FULL X X X 2

-1101 14-28 V LIMITED X 3 X

-1301 14-28 V FULL X 3 X

-1602 14-28 V FULL X 3 X

* Version -0301 replaced by version -0601.

NOTE: Antenna diversity is necessary for a TCAS configuration.

Page 26 006-05340-0007 Rev. 7 Sept/200434-40-01


Table 28 MST 67A Mode S Transponder Features

FEATURE DESCRIPTION

Basic Unit Provides microprocessor controlled processing of ATCRBS and Mode S interrogations and replies. Provides ATC transponder functions for ATCRBS Mode A, ATCRBS Mode C, and SPI. Processes Mode S interrogations and replies in accordance with RTCA DO-181A and ARINC 718. Interfaces with TCAS and various data sources. Contains automatic self-test.

Primary Power 13.75 to 28 Vdc power input.

BITE The Built In Test Equipment will annunciate faults. The faults will be displayed externally by the control unit or internally by an LED segment on the I/O processor board.

Antenna Diversity Provides improved air-to-air surveillance and communication by employing two antennas; one mounted on the top, and the other mounted on the bottom. Antenna selection is automatic, and accomplished on the basis of the relative strengths of the detected interrogation signals.

TCAS Compatibility Versions with antenna diversity are certified compatible with TCAS operation.

Burst Tuning Compatible with “burst mode” control word format, where tuning data is transmitted only during tuning activity and not refreshed in between.

Remote Ident Allows for IDENT transmission from a source other than a control unit.

Data Link Level 2 limited capability that supports TCAS only, as defined by DO-181A MOPS.

Level 3 (Comm A/B and Comm C ELM) datalink and Flight ID reporting, with separate ADLP input/output ARINC 429 ports, as defined by DO-181A MOPS and ARINC 718.

Flight IDReporting

Flight ID ARINC 429 input port, as defined by DO-181A MOPS and ARINC 718.

Page 27 006-05340-0007 Rev. 7 Sept/200434-40-01


Table 29 MST 67A Mode S Transponder Specifications (Sheet 1 of 3)


TSO Compliance C112 2A1 101 011 (-0301, -0601 versions)C112 3A2 121 011 (-1101, -1301, -1602 versions)

Form Factor 1 MCU ARINC 600 (1/4 ATR short).

Physical Dimensions See MST 67A Install Manual 34-54-01, outline drawing

Weight See MST 67A Install Manual 34-54-01, outline drawing

Power Requirements +13.75-28 Vdc, 45 watts max.

Temperature Range A2 -15 °C to +70 °C

F2 -55 °C to +85 °C

Maximum Humidity 95%

Cooling No forced air cooling required

Vibration Constant total excursion of 0.02" from 5 to 50 Hz with a maximum acceleration of 1.5 G. Constant acceleration of 0.5 G from 50 to 200 Hz.

Shock Rigid mounting 6 G operational, 15 G crash safety.

Connector ARINC 404A

Transmitter Power 400 watts (nominal)

Transmit Reply RateCapability

Rate limits of replies:ATCRBS 750 PRF, Mode S 50 PRF.

Transmit Frequency 1090 ±1 MHz

Input VSWR 1.5:1

Receive Frequency 1030 ±0.2 MHz

Altitude Inputs Dual ARINC 575 Air Data (ARINC 419), Dual ARINC 706 Air Data (ARINC 429), Dual ARINC 407 Synchro, Dual Gillham (Mode C Gray Code)

Control Inputs Dual ARINC 720 (ARINC 429)

Maintenance Inputs Per ARINC 604 (ARINC 429)

Datalink I/O Per ARINC 718 (ARINC 429)

Flight ID Input Per ARINC 718 (ARINC 429)

TCAS I/O Per ARINC 735 (High Speed ARINC 429)

Page 28 006-05340-0007 Rev. 7 Sept/200434-40-01


Table 29 MST 67A Mode S Transponder Specifications (Sheet 2)


Squitter Transmitted at 1 ±0.2 sec random, full self verification of every squitter’s data and occurrence.

Suppression ARINC 718

Receiver Sensitivity and Dynamic Range

The MTL for ATCRBS and ATCRBS/Mode S All-Call interrogations will be -73 ±4 dB.

The MTL for Mode S format interrogations will be -74 ±3 dB.

The reply efficiency will be at least 90% for all Mode S interrogations between MTL +3 dB and -21 dB.

The reply efficiency will be not more than 10% for interrogations at signal levels below -81 dB.

The variation of the MTL between ATCRBS Mode A and Mode C interrogations will not exceed 1 dB.

The reply efficiency will be at least 90% for ATCRBS and ATCRBS/Mode S All-Call interrogations between MTL +3 dB and -21 dB.

Receiver Sensitivity Variations with Frequency

The RF input level required to produce 90% replies will not vary more than 1 dB, nor will it increase above -69 dBm level for standard ATCRBS interrogation signals between 1029.8 and 1030.2 MHz.

Receiver Selectivity The standard ATCRBS interrogation signal required to trigger the transponder below 1005 MHz and above 1055 MHz will be at least 60 dB stronger than that required to trigger the transponder at 1030 MHz with the same reply efficiency.

Unwanted RF Output When not transmitting, the transponder will not emit more than -70 dBm at any frequency within 3 MHz of 1090 MHz. This “not transmitting” period of time allows for 10 µsec transition zones preceding and following any transmission.

ATCRBS Reply Pulse Shape All ATCRBS reply pulses and the SPI pulse will have rise times between 0.05 and 0.1 µsec and decay times between 0.05 and 0.2 µsec. Each pulse will have a duration of 0.45 ±0.1 µsec.

Page 29 006-05340-0007 Rev. 7 Sept/200434-40-01


Table 29 MST 67A Mode S Transponder Specifications (Sheet 3)


ATCRBS Reply Pulse Amplitude Variation

The pulse amplitude of any one ATCRBS reply pulse relative to another in any one reply train will not exceed 1 dB.

Mode S Reply Pulse Amplitude Variation

The pulse amplitude of any one Mode S reply pulse relative to another in any one reply train will not exceed 2 dB.

Mode S Reply Pulse Shape All Mode S reply pulses will have a rise time ≤0.1 µsec and a fall time ≤0.2 µsec. Each pulse will have a duration of 0.5 ±0.05 µsec.

The shape will also be consistent with the following spectrum requirements:Deviation from RelativeCarrier (MHz) Amplitude (dB)1.3 ≤ Freq < 7.0 37.0 ≤ Freq < 23 2023 ≤ Freq < 78 4078 ≤ Freq 60

EnvironmentalCertification

See Figure 12 MST 67A Environmental Qualification Form (-0000), Figure 13 MST 67A Environmental Qualification Form (-0010),or Figure 14 MST 67A Environmental Qualification Form (-0020).

Page 30 006-05340-0007 Rev. 7 Sept/200434-40-01


J. KFS 578A Mode S/TCAS II Control Unit Configurations

Listed below are versions, features, and specifications of the KFS 578A control unit that are compatible with TCAS II.

* -XX04 software versions provide "POP-UP” display mode as a switched or strap option and “Select (SLCT)” range as a strap option.

Table 30 KFS 578A Control Unit Versions


VERSION FACE PLATE

PANELLIGHTING

ON/OFF SWITCH

DUAL XPNDR 1/2

TCAS RANGE SWITCH

TDR 94D COMPAT-IBLE

“POPUP” COMPAT-IBLE

071-01507 -1701 Black 28 Vdc X Normal

-1801 Gray 28 Vdc X Normal

-1901 Black 5 Vac/Vdc X Normal

-2001 Gray 5 Vac/Vdc X Normal

-2201 Gray 28 Vdc Normal

-2301 Black 5 Vac/Vdc Normal

-3502 Black 5 Vac/Vdc X X EXTND

-4102 Black 28 Vdc X EXTND

-4202 Gray 28 Vdc X EXTND

-4302 Black 5 Vac/Vdc X EXTND

-4402 Gray 5 Vac/Vdc X EXTND

-4902 Black 28 Vdc X X No

-5002 Gray 28 Vdc X X No

-5102 Black 5 Vac/Vdc X X No

-5202 Gray 5 Vac/Vdc X X No

-3303 Black 28 Vdc X X EXTND X

-3403 Gray 28 Vdc X X EXTND X

-3503 Black 5 Vac/Vdc X X EXTND X

-3603 Gray 5 Vac/Vdc X X EXTND X

-4903 Black 28 Vdc X X No X

-5003 Gray 28 Vdc X X No X

-5103 Black 5 Vac/Vdc X X No X

-5203 Gray 5 Vac/Vdc X X No X

-5503 Black 5 Vac/Vdc X No X

-5603 Gray 5 Vac/Vdc X No X

-4304 Black 5 Vac/Vdc X EXTND/SLCT X X

-4404 Gray 5 Vac/Vdc X EXTND/SLCT X X

Page 31 006-05340-0007 Rev. 7 Sept/200434-40-01


Table 31 KFS 578A Control Unit Features

FEATURE DESCRIPTION

Basic Unit Microprocessor based control unit for controlling a transponder. The unit contains all controls required for transponder operation including: TEST, STANDBY, ON (transponder), ALTITUDE, VFR and IDENT. Some versions are compatible with the Collins TDR 94D.



Panel Lighting Choice of 5 Vac/Vdc or 28 Vdc version dimming source

ON/OFF Switch Turns the system ON or OFF

Dual Xpndr 1/2 Provides control of two individually selected transponders

TCAS RangeControl Switch

Selects the TCAS traffic display range according to the KFS 578A version configuration: -NORMAL 3, 5, 10, or 15 nm; -EXTENDED (EXTND) 3, 5, 10, 15, 20, or 40 nm; -SELECT (SLCT) 5, 10, 20, or 40 nm. “Select” range is an installation strap option available on -XX04 versions. Refer to Table 2005 KFS 578A Control Unit Connector Pin Names (P5781).-NO RANGE control units annunciate on the display.

TCAS The TCAS configuration contains the following elements:

ABOVE/NORMAL/BELOW: Selects relative altitude display limits for non-threat category aircraft on traffic display.

TA: Places the TCAS in the Traffic Advisory Only mode.

TA/RA: Places the TCAS in the Traffic Advisory/ResolutionAdvisory mode.

FL: TCAS Flight Level function causes the TCAS indicator to change displayed altitude from Relative Altitude (intruder to own aircraft) to absolute altitude.

POP-UP On -XX04 units an external strap or switch is required to select one of two options: MANUAL or AUTO mode. In Honeywell EFIS in-stallations, the Traffic display can be brought up on the Multi-Functional Display (MFD) by a deep toggle of the TCAS button lo-cated on the EFIS controller. If the "AUTO" mode is active, the Traffic display can "POP-UP", initiated by the presence of traf-fic.

Page 32 006-05340-0007 Rev. 7 Sept/200434-40-01


Table 32 KFS 578A Control Unit Specifications


Physical Dimensions See Figure 2020 KFS 578A Control Unit Outline Drawing

Weight See Figure 2020 KFS 578A Control Unit Outline Drawing

Mounting Front panel rail mount

Power Requirements

Primary 28 Vdc, 350 mA, 10 W.

Display 27.5 Vdc, 10.5 W.

Lighting 5 Vac 400 Hz or 5 Vdc, 300 mA, 1.5 W; or 28 Vdc, 75 mA, 2.1 W.

Temperature



Cooling No forced cooling required

Operational Characteristics ARINC 718

Data Output Low speed ARINC 429

TSO Compliance TSO C112

Environmental Certification See Figure 7 KFS 578A Environmental Qualification Form (-0000) or Figure 8 KFS 578A Environmental Qualification Form (-0010)

Page 33 006-05340-0007 Rev. 7 Sept/200434-40-01


K. PS-578A Mode S/TCAS II Control Unit Configurations

Listed below is a KFS 578A to PS-578A cross-reference for units com-patible with TCAS II.

KFS 578A071-01507

KFSLAMP

PS-578A071-01618

FACEPLATE

DISPLAYCOLOR

DUAL XPNDR1/2

ON/OFFSWITCH

TCASRANGECONTROL

-1701 28V -0026 BLK White YES NO 2 Limited

-0126 BLK Amber

-0226 BLK NVIS

-1801 28V -0025 GRY White YES NO 2 Limited

-0125 GRY Amber

-0225 GRY NVIS

-1901 5V -0026 BLK White YES NO 2 Limited

-0126 BLK Amber

-0226 BLK NVIS

-2001 5V -0025 GRY White YES NO 2 Limited

-0125 GRY Amber

-0225 GRY NVIS

-2201 28V -0027 GRY White NO NO 2 Limited

-0127 GRY Amber

-0227 GRY NVIS

-2301 5V -0028 BLK White NO NO 2 Limited

-0128 BLK Amber

-0228 BLK NVIS

-3502 5V -0022 BLK White YES YES 2 Extended

-0122 BLK Amber

-0222 BLK NVIS

-4102 28V -0026 BLK White YES NO 2 Extended

-0126 BLK Amber

-0226 BLK NVIS

-4202 28V -0025 GRY White YES NO 2 Extended

-0125 GRY Amber

-0225 GRY NVIS

Table 33 KFS 578A - PS-578A Configuration Cross-Reference (TCAS II)

Page 34 006-05340-0007 Rev. 7 Sept/200434-40-01


-4302 5V -0026 BLK White YES NO 2 Extended

-0126 BLK Amber

-0226 BLK NVIS

-4402 5V -0025 GRY White YES NO 2 Extended

-0125 GRY Amber

-0225 GRY NVIS

-4902 28V -0022 BLK White YES YES 2 No

-0122 BLK Amber

-0222 BLK NVIS

-5002 28V -0021 GRY White YES YES 2 No

-0121 GRY Amber

-0221 GRY NVIS


-0122 BLK Amber

-0222 BLK NVIS


-0121 GRY Amber

-0221 GRY NVIS


-0122 BLK Amber

-0222 BLK NVIS

-3403 28V -0021 GRY White YES YES 2 Extended

-0121 GRY Amber

-0221 GRY NVIS


-0122 BLK Amber

-0222 BLK NVIS

-3603 5V -0021 GRY White YES YES 2 Extended

-0121 GRY Amber

-0221 GRY NVIS


-0122 BLK Amber

-0222 BLK NVIS

KFS 578A071-01507

KFSLAMP

PS-578A071-01618

FACEPLATE

DISPLAYCOLOR

DUAL XPNDR1/2

ON/OFFSWITCH

TCASRANGECONTROL


Page 35 006-05340-0007 Rev. 7 Sept/200434-40-01



-0121 GRY Amber

-0221 GRY NVIS


-0122 BLK Amber

-0222 BLK NVIS


-0121 GRY Amber

-0221 GRY NVIS

-5503 5V -0024 BLK White NO YES 2 No

-0124 BLK Amber

-0224 BLK NVIS

-5603 5V -0023 GRY White NO YES 2 No

-0123 GRY Amber

-0223 GRY NVIS

-4304 5V -0026 BLK White YES NO 2 Select

-0126 BLK Amber

-0226 BLK NVIS

-4404 5V -0025 GRY White YES NO 2 Select

-0125 GRY Amber

-0225 GRY NVIS

KFS 578A071-01507

KFSLAMP

PS-578A071-01618

FACEPLATE

DISPLAYCOLOR

DUAL XPNDR1/2

ON/OFFSWITCH

TCASRANGECONTROL


Page 36 006-05340-0007 Rev. 7 Sept/200434-40-01


NOTE: The PS-578A is configured by grounding (*FCDE) ATE Test J1 pin 24 using the configuration programming harness at initial power up, and dialing in a KFS 578A version number with the A/N/B Rotary Selector or Range Rotary Selector.

Refer to Figure 19 PS-578A Configuration Programming Har-ness to fabricate the configuration programming harness. Refer to Table 33 KFS 578A - PS-578A Configuration Cross-Reference (TCAS II) for compatible PS-578A replacements for KFS 578A units and for range control options.

NOTE: PS-578A versions that emulate KFS 578A -XX04 versions provide “Select” range and "POP-UP” display mode as in-stallation strap or switch options. Refer to Table 2006 PS-578A Control Unit Connector (J1) Pin Definitions.

NOTE: Range Control is configured by grounding ATE Test (FCDE) J1 pin 24 at power up, and choosing a compatible KFS 578A version number with the desired range option by dialing the A/N/B Rotary Selector or Range Rotary Selector.

Page 37 006-05340-0007 Rev. 7 Sept/200434-40-01


Listed below are versions, features, and specifications of the PS-578A control units that are compatible with TCAS II.

Table 34 PS-578A Control Unit Versions


VERSION FACEPLATE

DISPLAYCOLOR

DUALXPNDR1/2

ON/OFF SWITCH

LAMP VOLTS

071-01618 -0021 Gray White Yes Yes 5vac/5vdc or 28vdc

-0022 Black White Yes Yes 5vac/5vdc or 28vdc

-0023 Gray White No Yes 5vac/5vdc or 28vdc

-0024 Black White No Yes 5vac/5vdc or 28vdc

-0025 Gray White Yes No 5vac/5vdc or 28vdc

-0026 Black White Yes No 5vac/5vdc or 28vdc

-0027 Gray White No No 5vac/5vdc or 28vdc

-0028 Black White No No 5vac/5vdc or 28vdc

-0121 Gray Amber Yes Yes 5vac/5vdc or 28vdc

-0122 Black Amber Yes Yes 5vac/5vdc or 28vdc

-0123 Gray Amber No Yes 5vac/5vdc or 28vdc

-0124 Black Amber No Yes 5vac/5vdc or 28vdc

-0125 Gray Amber Yes No 5vac/5vdc or 28vdc

-0126 Black Amber Yes No 5vac/5vdc or 28vdc

-0127 Gray Amber No No 5vac/5vdc or 28vdc

-0128 Black Amber No No 5vac/5vdc or 28vdc

-0221 Gray NVIS Yes Yes 5vac/5vdc or 28vdc

-0222 Black NVIS Yes Yes 5vac/5vdc or 28vdc

-0223 Gray NVIS No Yes 5vac/5vdc or 28vdc

-0224 Black NVIS No Yes 5vac/5vdc or 28vdc

-0225 Gray NVIS Yes No 5vac/5vdc or 28vdc

-0226 Black NVIS Yes No 5vac/5vdc or 28vdc

-0227 Gray NVIS No No 5vac/5vdc or 28vdc

-0228 Black NVIS No No 5vac/5vdc or 28vdc

Page 38 006-05340-0007 Rev. 7 Sept/200434-40-01


Table 35 PS-578A Control Unit Features

FEATURE DESCRIPTION

Basic Unit Microprocessor based transponder control unit. The unit contains all controls required for transponder operation including: TEST, STANDBY, ON (transponder), ALTITUDE, VFR and IDENT.

Faceplate A choice of faceplate colors are available

ON/OFF Switch Turns the control unit ON or OFF

1/2 Dual Provides control of two, individually selected transponders

TCAS RangeControlSwitch

Selects the TCAS traffic display range according to the emulated KFS 578A configuration:

-NORMAL 3, 5, 10, or 15 nm; -EXTENDED 3, 5, 10, 15, 20, or 40 nm; -SELECT 5, 10, 20, or 40 nm. “Select” range is an installation strap option available to units emulating KFS 578A -XX04 versions. Refer to Table 2006 PS-578A Control Unit Connector (J1) Pin Definitions.-NO RANGE control units flash “RNG CNTRL” for 1 sec and “ON DSPL” for 1 sec when the Range rotary is activated.



TA: Places the TCAS in the Traffic Advisory mode.

TA/RA: Places the TCAS in the Traffic Advisory/Resolution Advisory mode.


POP-UP On units emulating KFS 578A -XX04 versions an external switch or strap is required to select one of two options: MANUAL or AUTO mode. In Honeywell EFIS installations, the Traffic display can be brought up on the Multi-Functional Display (MFD) by a deep toggle of the TCAS button located on the EFIS controller. If the "AUTO" mode is active, the Traffic display can "POP-UP," initiated by the presence of traffic.

FID Pushbutton Allows entry of alpha numeric flight identification and annunciates “FID” on display.

Lamp Voltage Lamps can be powered by 5 Vac, 5 Vdc, or 28 Vdc dimming source.

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Table 36 PS-578A Control Unit Specifications


Dimensions: See Figure 2021 PS-578A Control Unit Outline Drawing

Weight: See Figure 2021 PS-578A Control Unit Outline Drawing

Center of Gravity: See Figure 2021 PS-578A Control Unit Outline Drawing

Power Requirements: 28 Vdc at 7 watts, maximum

Connectors: One 29-pin sub-D, one 9-pin sub-D. See Figure 2005 PS-578A Mode S/TCAS Control Unit Rear Connector (J1) and Figure 2006 PS-578A Mode S/TCAS Control Unit Rear Connector (J2)

Temperature: Operating Storage

-20 °C to +70 °C-55 °C to +85 °C

Cooling: No forced cooling required

TSO: C112, C119b

Environmental Certification: See Figure 9 PS-578A Environmental Qualification Form

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L. PS-550 Mode S/TCAS II Control Unit Configurations

Listed below are versions, features, and specifications of the PS-550 control units that are compatible with TCAS II.

Table 37 PS-550 Control Unit Versions


VERSION FACEPLATE

DISPLAYCOLOR

DUALXPNDR1/2

ON/OFF SWITCH

LAMP VOLTS RANGE CONTROLOPTION*

071-01619 -0021 Gray White Yes Yes 5vac/5vdc or 28vdc Yes

-0022 Black White Yes Yes 5vac/5vdc or 28vdc Yes

-0023 Gray White No Yes 5vac/5vdc or 28vdc Yes

-0024 Black White No Yes 5vac/5vdc or 28vdc Yes

-0025 Gray White Yes No 5vac/5vdc or 28vdc Yes

-0026 Black White Yes No 5vac/5vdc or 28vdc Yes

-0027 Gray White No No 5vac/5vdc or 28vdc Yes

-0028 Black White No No 5vac/5vdc or 28vdc Yes

-0121 Gray Amber Yes Yes 5vac/5vdc or 28vdc Yes

-0122 Black Amber Yes Yes 5vac/5vdc or 28vdc Yes

-0123 Gray Amber No Yes 5vac/5vdc or 28vdc Yes

-0124 Black Amber No Yes 5vac/5vdc or 28vdc Yes

-0125 Gray Amber Yes No 5vac/5vdc or 28vdc Yes

-0126 Black Amber Yes No 5vac/5vdc or 28vdc Yes

-0127 Gray Amber No No 5vac/5vdc or 28vdc Yes

-0128 Black Amber No No 5vac/5vdc or 28vdc Yes

-0221 Gray NVIS Yes Yes 5vac/5vdc or 28vdc Yes

-0222 Black NVIS Yes Yes 5vac/5vdc or 28vdc Yes

-0223 Gray NVIS No Yes 5vac/5vdc or 28vdc Yes

-0224 Black NVIS No Yes 5vac/5vdc or 28vdc Yes

-0225 Gray NVIS Yes No 5vac/5vdc or 28vdc Yes

-0226 Black NVIS Yes No 5vac/5vdc or 28vdc Yes

-0227 Gray NVIS No No 5vac/5vdc or 28vdc Yes

-0228 Black NVIS No No 5vac/5vdc or 28vdc Yes

*Discrete options for TCAS traffic display range control include: Normal 3, 5, 10, 15 nm; Extended 3, 5, 10, 15, 20, 40 nm; or Range Disabled. Refer to Table 2008 PS-550 Control Unit Connector Pin Name Definitions.

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Table 38 PS-550 Control Unit Features

FEATURE DESCRIPTION

Basic Unit Microprocessor based control unit for controlling a transponder. The unit contains all controls required for transponder operation including: TEST, STANDBY, ON (transponder), ALTITUDE, VFR and IDENT. Compatible with the COLLINS TDR-94D transponder.

1/2 Dual Provides control of two individually selected transponders

TCAS Range Switch

Selects the TCAS nautical mile traffic display according to the installed discrete range option (see Table 2008 PS-550 Control Unit Connector Pin Name Definitions):-NORMAL 3, 5, 10, 15 nm-EXTENDED 3, 5, 10, 15, 20, 40 nm-RANGE DISABLED. INOP is displayed as TCAS Range switch is rotated.



TA: Places the TCAS in the Traffic Advisory mode.

TA/RA: Places the TCAS in the Traffic Advisory/ResolutionAdvisory mode.


MODE Pushbutton

ATC Mode - allows entry of the four-digit ATC code.

FID Mode - allows entry of alpha numeric flight identification and annunciates “FID” on display.

TFC Mode - (Collins TDR-94D) selects traffic display operating mode: pop-up (AUTO) or full-time display (ON) and annunciates on display.

FL Mode (Honeywell MST 67A) - allows selection of relative (REL) or absolute (ABS) altitude to be displayed.

ADC Mode - selects which air data computer is used by TCAS and annunciates “ADC” and “1” or “2” on display.

Lamp Voltage Lamps can be powered by 5 Vac, 5 Vdc, or 28 Vdc dimming source.

Lighting Brightness Control

Dim and bright values for panel lighting and LCD backlighting may be adjusted independently.

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Table 39 PS-550 Control Unit Specifications

Dimensions: See Figure 2022 PS-550 Control Unit Outline Drawing

Weight: See Figure 2022 PS-550 Control Unit Outline Drawing

Center of Gravity: See Figure 2022 PS-550 Control Unit Outline Drawing

Power Requirements: 28 Vdc at 7 watts, maximum

Connector: One 65 pin. See Figure 2007 PS-550 Mode S/TCAS Control Unit Rear Connector

Temperature: Operating Storage

-20 °C to +70 °C-55 °C to +85 °C

Cooling: No forced cooling required.

TSO: C112, C119b

Environmental Certification: See Figure 10 PS-550 Environmental Qualification Form

Page 43 006-05340-0007 Rev. 7 Sept/200434-40-01


M. CD 671C Control Unit

Listed below are versions, features, and specifications of the CD 671C control unit.

Table 40 CD 671C Control Unit Versions


VERSION NUMBER

FACEPLATE

PRIMARY POWER

PANEL LIGHTINGCHOICE

DUALXPNDR1/2

TCASRANGE SWITCH

T/Wx SWITCH

071-01542 -0601 Black 28 Vdc 5 Vac/Vdc, 28 Vdc X X X

-0701 Black 28 Vdc 5 Vac/Vdc, 28 Vdc X X

-0801* Black 28 Vdc 5 Vac/Vdc, 28 Vdc X X

-0901 Black 28 Vdc 5 Vac/Vdc, 28 Vdc X

-1601 Black 28 Vdc 5 Vac/Vdc, 28 Vdc X X



-1901 Black 28 Vdc 5 Vac/Vdc, 28 Vdc

-2601 Gray 28 Vdc 5 Vac/Vdc, 28 Vdc X X X

-2701 Gray 28 Vdc 5 Vac/Vdc, 28 Vdc X X


-2901 Gray 28 Vdc 5 Vac/Vdc, 28 Vdc X




-3901 Gray 28 Vdc 5 Vac/Vdc, 28 Vdc

* Dim Select

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Table 41 CD 671C Control Unit Features

FEATURE DESCRIPTION

Basic Unit Microprocessor based unit contains all controls required for transponder operation including: TEST, STANDBY, ON (transponder), ALTITUDE, VFR and IDENT. Compatible with the Collins TDR 94D transponder.



Panel Lighting All versions can use either 5 Vac/Vdc, or 28 Vdc lamp dimming source.

ON/OFF Turns the system ON or OFF

Dual XPNDR 1/2 Provides control of two, individually selected transponders

TCAS Range Switch Selects nautical mile ranges for the traffic display. Nautical mile range scales are 3, 5, 10, 15, 20, and 40.



TA: Places the TCAS in the Traffic Advisory Only mode.

TA/RA: Places the TCAS in the Traffic Advisory/Resolution Advisory mode.

T/Wx: On the weather radar display selects Weather only, Weather with TCAS traffic, or Traffic Only mode.


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Table 42 CD 671C Control Unit Specifications


Physical Dimensions See Figure 2023 CD 671C Control Unit Outline Drawing

Weight See Figure 2023 CD 671C Control Unit Outline Drawing

Mounting Front panel rail mount

Power Requirements

Primary 28 Vdc; 350 mA, 10 W

Lighting 5 Vac 400 Hz, 5 Vdc, or 28 Vdc

Temperature:




Display RCTN LCD

Data Output Low-speed ARINC 429


Front-Mounted TCAS/WX Control Optional

Connector Dual filtered sub-miniature twenty-five pin female. See Figure 2008 CD 671C Control Unit, Rear Connectors

TSO C112

Software Criticality Level DO-178A, Level 2 (Essential)

Environmental Certification: See Figure 6 CD 671C Environmental Qualification Form

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N. CTA-81A Control Unit

Listed below are versions, features, and specifications of the CTA-81A control unit.

Table 43 CTA-81A Control Unit Versions

HONEYWELLPART NO.

VERSION FACE PLATE

PRIMARYPOWER

TCAS RANGE SWITCH

ABOVE/NORM/BELOW SWITCH

ALT 1/2SWITCH

ATC 1/2SWITCH

ATCFAILLAMPVOLTS

XPNDRFAILINPUT

071-01503 -0101 Black 115 Vac 3-15 X X 12-28 OPEN

-0201 Gray 115 Vac 3-15 X X 12-28 OPEN

-1301 Black 115 Vac No X 12-28 OPEN

-1401 Gray 115 Vac No X 12-28 OPEN

-2101 Black 115 Vac 3-15 X X 12-28 OPEN

-2201 Gray 115 Vac 3-15 X X 12-28 OPEN

-2501 Black 115 Vac No X X 12-28 OPEN

-2601 Gray 115 Vac No X X 12-28 OPEN

-3801 Gray 115 Vac 5-40 X X 12-28 OPEN

-3901 Gray 115 Vac 5-40 X X 12-28 OPEN

-4001 Black 115 Vac 5-40 X X 12-28 OPEN

-4201 Black 115 Vac 5-40 X X 12-28 OPEN

-5901 Gray 115 Vac No X X 12-28 OPEN

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Table 44 CTA-81A Control Unit Features

FEATURE DESCRIPTION

Basic Unit A microprocessor based transponder control unit for two Mode S transponders and a TCAS processor.


Primary Power 115 Vac input power

Panel Lighting 5 Vac/Vdc dimming source

TCAS RANGE Switch Four position rotary switch. Depending on unit version, selects either 3, 5, 10, or 15 nautical mile ranges or 5, 10, 20, or 40 nautical mile ranges for the traffic display.

ABOVE/NORM/BELOWSwitch

Selects relative altitude display limits: normal, above normal, or below normal.

ALT 1/2 Switch Selects either altitude source 1 or 2

ATC 1/2 Switch Selects either transponder 1 or 2

ATC FAIL Lamp Voltage The ATC FAIL lamp lights when the selected transponder 1 or 2 fails. The ATC FAIL lamp is powered by 12-28 Vdc.

XPNDR FAIL Input An OPEN from the MST 67A transponder (Transponder Failure Discrete #2) causes the ATC FAIL lamp to light.

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Table 45 CTA-81A/CTA-81D Control Unit Specifications


Physical Dimensions See MST 67A Installation Manual 34-54-01, outline drawings

Weight See MST 67A Installation Manual 34-54-01, outline drawings

Mounting Dzus mounted per ARINC 718

Power Requirements

Primary 115 Vac, 400 Hz, 6 W

Display and Panel Lighting 0-5 Vac 400 Hz, or 0-5 Vdc, 10.5 W

ATC Fail Lamp 12-28 Vdc, 0.3 W

Temperature




Operational Characteristics ARINC 718/735

Data Output ARINC 429, 12.5 to 14 kbits/sec

TSO Compliance TSO C112

Environmental Certification See Figure 11 CTA 81() Environmental Qualification Form

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O. CTA-81D Control Unit

Listed below are versions and features of the CTA-81D control unit. For unit specifications refer to Table 45 CTA-81A/CTA-81D Control Unit Specifications.

Table 46 CTA-81D Control Unit Versions

Table 47 CTA-81D Control Unit Features

HONEYWELLPARTNUMBER

VERSION PRIMARYPOWER

FACE PLATE

TCAS RANGE SWITCH

ABOVE/NORM/BELOW SWITCH

ALT 1/2SWITCH

ATC 1/2SWITCH

ATCFAILLAMPVOLTS

XPNDRFAILINPUT

071-01561 -0101 115 Vac Gray 5-40 X X 12-28 OPEN

-0201 115 Vac Gray No X X 12-28 OPEN

FEATURE DESCRIPTION

Basic Unit A microprocessor based transponder control unit for two Mode S transponders and a TCAS processor, compatible with the Collins TDR 94D.

Primary Power 115 Vac input power

Panel Lighting 5 Vac/Vdc dimming source

Faceplate A gray faceplate is available

TCAS RANGE Switch Four position rotary switch. Selects 5, 10, 20, or 40 nautical mile ranges for the traffic display.

ABOVE/NORM/BELOWSwitch

Selects relative altitude display limits: normal, above normal, or below normal.

ALT 1/2 Switch Selects either altitude source 1 or 2.

ATC 1/2 Switch Selects either transponder 1 or 2.

ATC FAIL LampVoltage

The ATC FAIL lamp lights when the selected transponder 1 or 2 fails. The ATC FAIL lamp is powered by 12-28 Vdc.

XPNDR FAIL Input An OPEN from the MST 67A transponder (Transponder Failure Discrete #2) causes the ATC FAIL lamp to light.

Page 50 006-05340-0007 Rev. 7 Sept/200434-40-01


P. Optional Displays and Control Units

Listed below are versions of optional displays and control units. Features and specifications are described in separate manuals listed in Related Publications, Table 49 Related Publications.

Table 48 Optional Displays and Control Units

3. Environmental Certification

TCAS II equipment meets the environmental conditions of the Radio Techni-cal Commission for Aeronautics (RTCA) document number DO-160B/C/D, "Envi-ronmental Conditions and Test Procedures for Airline Electronic/Electri-cal Equipment and Instruments." Environmental certification categories for TCAS II equipment are defined in this section. For environmental cer-tification categories of other TCAS related equipment refer to manuals listed in Table 49 Related Publications.

SYSTEMCOMPONENT

LRU MANUFACTURER/MODEL DESIGNATOR

LRU DESCRIPTION LRU PART NUMBER

Display Honeywell SG-465 Symbol Generator 066-04021-1108 066-04021-1109 066-04021-1110 066-04021-1408 066-04021-1409 066-04021-1410

Honeywell SG-464 Symbol Generator 066-04020-1108 066-04020-1109

Control Unit Honeywell KDA 557 Radio Management Unit 066-04029-0101

Page 51 006-05340-0007 Rev. 7 Sept/200434-40-01


Figure 2 TPU 67A Environmental Qualification Form (Dwg. No. 004-00923-4800, Sheet 1 of 5)

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Figure 2 TPU 67A Environmental Qualification Form (Dwg. No. 004-00923-4800, Sheet 2)

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Figure 3 CM 67A Environmental Qualification Form (Dwg. No. 004-00924-4800, Sheet 1 of 3)

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Figure 3 CM 67A Environmental Qualification Form (Dwg. No. 004-00924-4800, Sheet 2)

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Figure 3 CM 67A Environmental Qualification Form (Dwg. No. 004-00924-4800, Sheet 3)

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Figure 4 CM 2000 Environmental Qualification Form (Dwg. No. 004-09109-0000, Sheet 1 of 3)

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Figure 4 CM 2000 Environmental Qualification Form (Dwg. No. 004-09109-0000, Sheet 2)

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Figure 4 CM 2000 Environmental Qualification Form (Dwg. No. 004-09109-0000, Sheet 3)

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Figure 5 ANT 67A Environmental Qualification Form (S72-1735 Series)

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Figure 6 CD 671C Environmental Qualification Form (Dwg. No. 004-09117-0000, Sheet 1 of 2)

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Figure 6 CD 671C Environmental Qualification Form (Dwg. No. 004-09117-0000, Sheet 2)

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Figure 7 KFS 578A Environmental Qualification Form (-0000) (Dwg. No. 004-09079-0000)

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Figure 8 KFS 578A Environmental Qualification Form (-0010) (Dwg. No. 004-09079-0010, Sheet 1 of 2)

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Figure 8 KFS 578A Environmental Qualification Form (-0010) (Dwg. No. 004-09079-0010, Sheet 2)

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Figure 9 PS-578A Environmental Qualification Form (G7534-(),Sheet 1 of 3)

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Figure 9 PS-578A Environmental Qualification Form (G7534-(),Sheet 2)

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Figure 9 PS-578A Environmental Qualification Form (G7534-(),Sheet 3)

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Figure 10 PS-550 Environmental Qualification Form (G7514-(),Sheet 1 of 3)

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Figure 10 PS-550 Environmental Qualification Form (G7514-(),Sheet 2)

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Figure 10 PS-550 Environmental Qualification Form (G7514-(),Sheet 3)

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NOTE: Sheet 1 of this document is not applicable to the CTA 81 () unit but is provided for document completeness and clarity.

Figure 11 CTA 81() Environmental Qualification Form (Dwg. No. 004-09048-0000, Sheet 1 of 7)

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Figure 11 CTA 81() Environmental Qualification Form (Dwg. No. 004-09048-0000, Sheet 2)

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Figure 12 MST 67A Environmental Qualification Form (-0000) (Dwg. No. 004-09067-0000)

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Figure 13 MST 67A Environmental Qualification Form (-0010) (Dwg. No. 004-09067-0010, Sheet 1 of 2)

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Figure 13 MST 67A Environmental Qualification Form (-0010) (Dwg. No. 004-09067-0010, Sheet 2)

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Figure 14 MST 67A Environmental Qualification Form (-0020) (Dwg. No. 004-09067-0020, Sheet 1 of 3)

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Figure 15 GC 362A Environmental Qualification Form (Dwg. No. 004-09077-0000, Sheet 1 of 2)

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Figure 15 GC 362A Environmental Qualification Form (Dwg. No. 004-09077-0000, Sheet 2)

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Figure 16 IVA 81A/B Environmental Certification Categories

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Figure 17 IVA 81C Environmental Qualification Form

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Figure 18 IVA 81D Environmental Qualification Form

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4. Related Publications

Listed below are publications related to the CAS 67A TCAS II system and test equipment supporting the system.

NOTE: See original manufacturer’s publications for non-Honeywell units.

Table 49 Related Publications (Sheet 1 of 2)

PUBLICATION HONEYWELLPART NUMBER

ATAIDENTIFICATIONNUMBER

TPU 67A TCAS II ProcessorComponent Maintenance Manual 006-05404-( ) 34-40-14

TPU 67A TCAS II ProcessorIllustrated Parts Catalog 006-05405-( ) 34-40-15

CAS 67A TCAS II Pilot’s Guide

For a CD ROM version order:

006-08499-0000(Rev 2 or later)690-00001-( )

CAS 67A ACAS II Pilot’s Guide 006-18201-0000

CAS-81 TCAS System Maintenance ManualIncluding ANT-81A, TPU-81A, IVA-81A, IVA-81B, and ITA-81A.

I.B. 1181 34-45-00

IVA-81A Traffic Advisory/ResolutionAdvisory Vertical Speed Indicator(TA/RA/VSI) Component Maintenance Manual

I.B. 1181D 34-45-20

IVA-81B Resolution Advisory/Vertical Speed Indicator (RA/VSI)Component Maintenance Manual

I.B. 1181E 34-45-25

IVA-81C Traffic Advisory/ResolutionAdvisory Vertical Speed Indicator(TA/RA/VSI) Component Maintenance Manual

80-5123call 800.788.5118to order

33-45-40

IVA-81D Traffic Advisory/ResolutionAdvisory Vertical Speed Indicator(TA/RA/VSI) Component Maintenance Manual

80-5181call 800.788.5118to order

33-45-41

MST 67A Mode S ATC TransponderSystem Installation Manual

006-00681-( ) 34-54-01

MST 67A Mode S ATC TransponderComponent Maintenance Manual

006-05377-( ) 34-54-02

KFS 578A Mode S Control Unit Component Maintenance Manual

006-05378-( ) 34-54-03

CD 671C Mode S/TCAS Control UnitComponent Maintenance Manual

006-05375-( ) 34-54-05

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Table 49 Related Publications (Sheet 2)

PUBLICATION HONEYWELLPART NUMBER

ATAIDENTIFICATIONNUMBER

GC 362A TCAS Graphics ProcessorComponent Maintenance Manual

006-05320-( )

RDS 81 Color Weather Radar SystemInstallation ManualMaintenance Manual

006-00954-( )006-05997-( )


006-00955-( )006-05913-( )


006-00902-( )006-05998-( )


006-00903-( )006-05996-( )

RDR-1E/RDR-1ED Radar SystemMaintenance Manual

I.B. 1101-1 34-23-00

RDR-1F Radar SystemMaintenance Manual

I.B. 1102 34-42-00

RDR-4A Weather Radar SystemMaintenance Manual

I.B. 1104 34-41-00

SG 464/SG 465 EFIS Symbol GeneratorMaintenance Manual

006-05232-( )

KMD 550/850 Installation Manual 006-10608-() N.A.

KMD 550/850 Component Maintenance Manual 006-15608-() 31-60-01

RMS 555 Radio Management SystemInstallation ManualRMU 556 Maintenance ManualKDA 557 Maintenance Manual

006-00675-( )006-05308-( )006-05373-( )

45-00-0145-00-02

KAD 480 Air Data System 006-00662-( )

RDR 2000 Color Weather Radar SystemInstallation Manual

006-00643-( )

Collins TDR-94/94D Mode S TransponderInstallation Manual

523-0775652-00211A

Gables PS-578 ATC/TCAS Installation ManualContact Gables, CAGEC 99837

IST.G7534-( ) N.A.

Gables PS-550 ATC/TCAS Installation ManualContact Gables, CAGEC 99837

IST.G7514-( ) N.A.

Page 94 006-05340-0007 Rev. 7 Sept/200434-40-01


5. CAS 67A TCAS II Installation Kits

Listed below are installation kits required to install CAS 67A TCAS II system components.

A. TPUDIAG/TCASDIAG Config. Module/Diagnostic Software Kits

Kits provide software for configuration and diagnosis of the TCAS II system.

NOTE: The diagnostic program should be used with procedures in the DIAGNOSTIC APPENDICES.

Table 50 TPUDIAG/TCASDIAG Config. Module/Diagnostic Software Kits

B. TPU 67A Installation Kit (New Installation)

Kit provides hardware for mounting one TPU 67A TCAS II processor in a new installation.

NOTE: Only a Honeywell approved mounting rack may be used for the TPU 67A installation. The kit p/n 050-03078-0010 in-cludes the approved mounting rack p/n 047-09855-0004, item (13) below. Other approved racks include:ECS p/n 6073-101 insertion/extractor w/ self limiting hold down, ECS p/n 6073-102 insertion no self limiting hold down, phone 1-800-327-9473; Hollingshead Interna-tional Inc. p/n 10904-101/-102, phone 213-921-3438; PIC p/n 180001 insertion/extractor w/self limiting hold down, PIC p/n 180002 insertion no self limiting hold down, phone 1-800-742-3191.

NOTE: Keying of the signal connector shell must reflect Figure 2025 TPU 67A Pinout Drawing.

KIT PART NUMBER DESCRIPTION UM QUANTITY

1 222-00358-00() TPUDIAG 5.25" diskette for TPU 67A SW version 01/09 and below.

EA 1

2 222-00359-00() TPUDIAG 3.5" diskette for TPU 67A SW version 01/09 and below.

EA 1

3 222-00386-00() TCASDIAG 3.5" diskette for TPU 67A SW version 01/10 and above.

EA 1

4 222-30003-00() TCASDIAG for Windows CD-ROM for TPU 67A SW version 01/10 and above.

EA 1

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NOTE: Only Honeywell approved signal connector shell with floating hardware and connector shim must be used for TPU 67A installation.

Table 51 TPU 67A TCAS II Processor Installation Kit (P/N 050-03078-0010)

ITEM PART NUMBER DESCRIPTION UM QUANTITY

1 030-01094-0002 Ground connector housing, 12/24 pin EA 1

2 030-01157-0011 Crimp connector, 20 ga. EA 22

3 030-01171-0000 9 pin D-Sub mating connector EA 2

4 030-01173-0000 25 pin D-Sub mating connector EA 1

5 030-01311-0000 Signal connector pin, ITT Cannon type 030-2259-000

EA 212

6 030-01432-0000 Ground connector pin EA 24

7 030-02351-0000 9 Pin submin. connector hood for RS-232 EA 1

8 030-02351-0002 25 Pin submin. mating connector hood EA 1

9 030-02707-0002 ARINC 404A signal connector shell, type DPX2 W/H

EA 1

10 030-03157-0000 ARINC 404A RF connector shell, type ITT Cannon DPX4W8-33S-0001 or Radiall 616799008.

EA 1

11 047-09592-0001 Connector shim EA 1

12 047-09831-0002 Ground tab EA 1

13 047-09855-0004 Mounting rack EA 1

14 071-00097-0100or 071-00097-1000

CM 2000 Configuration Moduleor CM 67A Configuration Module

EA 1

15 075-05108-0001 Rack spacer EA 2

16 089-05878-0010 PHP 4-40 X 5/8 ground connector screw EA 2

17 089-06008-0004 FHP 4-40 X 1/4 ground tab screw EA 2

18 089-06008-0007 FHP 4-40 X 7/16 screw EA 14

19 089-06012-0005 FHP 6-32 X 5/16 screw EA 4

20 089-06014-0020 FHP 8-32 X 1.25 screw EA 4

21 092-05792-0002 Extractor type hold down EA 2

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C. TPU 67A Installation Kit (TCAS I to TCAS II Upgrade)

Kit provides hardware for mounting one TPU 67A TCAS II processor as an upgrade replacement for a TCAS I processor.

Table 52 TPU 67A TCAS II Processor Upgrade Installation Kit (P/N 050-03078-0001)

Kit provides hardware for mounting one TPU 67A TCAS II processor as an upgrade replacement for a TCAS I processor (Gulfstream).

Table 53 TPU 67A TCAS II Processor Upgrade Installation Kit (P/N 050-03078-0020) (Gulfstream)


1 030-01157-0011 Crimp connector, 20 ga. EA 10

2 030-01171-0000 9 Pin D-Sub mating connector EA 1

3 030-02351-0000 9 Pin D-Sub connector for RS-232 EA 1

4 071-00097-0100or 071-00097-1000

CM 2000 Configuration Moduleor CM 67A Configuration Module

EA 1


1 050-03078-0001 TPU 67A Upgrade Kit EA 1

2 047-09592-0001 Shim EA 1

3 047-09855-0004 Mounting rack EA 1

4 089-06012-0005 Screw FHP 6-32X5/16 EA 4

5 092-05792-0002 Extractor type T Hinge EA 2

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D. ANT 67A Antenna Adapter Kits

Kits provide adapter plates for mounting antenna base on a curved surface.

NOTE: An antenna mounting adapter p/n 047-50357-000() must be used on curved mounting surfaces to minimize side-element distortion and insure optimum bearing accuracy.

NOTE: It is recommended that prefabricated cables be used in the CAS 67A TCAS system. Those cables provide the highest level of confidence. There are several sources for ca-bles. Please contact one of the following companies: Ad-ams-Russell, phone 508-338-5210; ECS, phone 1- 800-327-9473; Hollingshead, phone 213-921-3438; PIC W & C, phone 1-800-742-3191.

Table 54 ANT 67A Antenna Adapter Kits

E. Omnidirectional Antenna Installation Kit

Customer must obtain kit from the omnidirectional antenna manufac-turer. Refer to Table 11 Omnidirectional Antenna Versions for om-nidirectional antenna manufacturer and part number.

NOTE: When an omnidirectional antenna is used as the bottom an-tenna, the three unused bottom antenna coaxes connected to the TPU 67A processor must be connected to 50 Ω ter-minations. Please contact one of the following companies for 50 Ω terminations: M/A Comm p/n 3002-6113-0000, Phone 1-800-998-4500; PIC Wire & Cable p/n K240001; Pasternack p/n PE6032.

KIT PART NUMBER DESCRIPTION UM QUANTITY

1 047-50357-0001 Adapter plate, 29" - 35" radius, 4 hole EA 1




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F. IVA-81A/IVA-81B/IVA-81C/IVA-81D Installation Kits

Kits provide parts for assembling a cable to connect the TA/RA/VSI or RA/VSI to the TCAS processor and other external equipment.

NOTE: IVA-81A/IVA-81C/IVA-81D units require a mounting clamp (3 ATI format), which is not supplied in the installation kit.

CAUTION: MAKE SURE THE SELECTED MOUNTING CLAMP DOES NOT COVER THE VENTILATION HOLES ON THE UNIT.

Table 55 IVA-81A/IVA-81B/IVA-81C/IVA-81D Installation Kit (P/N 05050001-0501) 115 Vac Unit/5 V Dim Source

Table 56 IVA-81A/IVA-81B/IVA-81C/IVA-81D Installation Kit (P/N 05050001-0502) 28 Vdc Unit/28 Vdc Dim Source

Table 57 IVA-81A/IVA-81B/IVA-81C/IVA-81D Installation Kit (P/N 05050001-0503) 28 Vdc Unit/5 V Dim Source


1 03024473-0001 Connector M83723-75R2041N EA 1

2 03024473-0002 Connector strain relief M85049-52-1-20N EA 1


1 03024473-0003 Connector M83723-75R20416 EA 1



1 03024473-0004 Connector M83723-75R20417 EA 1


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G. GC 362A Installation Kit

Kit provides the following:

Table 58 GC 362A Installation Kit (P/N 050-02978-0001)

H. MST 67A Installation Kit


Table 59 MST 67A Installation Kit (P/N 050-02979-0000)


1 071-04022-0001 Rack assembly EA 1

2 030-01157-0011 Crimp connector, 20 G EA 49

3 030-01176-0000 Hood and lever assembly EA 1

4 030-01188-0000 Female polarizing pin EA 1



1 030-00413-0000 Coax plug RG 214, No. 1 (P671B1/P671B2)ITT Cannon 249-5123-000 or Radiall 610-108-0001.

EA 2

2 030-03106-0000 Connector hood ARINC 404A, type DPX2MA (P671A), Radiall DSX2H24X35X0001.Mounting hardware:Four (4) screws p/n 089-06008-0007

EA 1

3 030-01311-0000 Connector pin (use with connector hood p/n 030-03106-0000). ITT Cannon 030-2259-000.

EA 106

4 047-09406-0014 Mounting rack EA 1

5 075-05090-0001 SpacerMounting hardware:Two (2) screws p/n 089-06014-0020,frontTwo (2) screws p/n 089-05909-0020,rear

EA 2

6 090-00953-0000 Rear hold down EA 1

7 092-05792-0002 Hold down assembly mounting hardware:Two (2) screws p/n 089-06012-0004

EA 1

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I. KFS 578A / PS-578A Installation Kit


Table 60 KFS 578A / PS-578A Installation Kit (P/N 050-02934-0001)

J. PS-578A Configuration Programming Harness


1 030-01222-0000 29 Pin connector hood and lever EA 1

2 030-01174-0000 29 Pin connector (P5781) EA 1

3 030-02351-0000 9 Pin hood and lever assembly EA 1

4 092-00052-0002 Nut anchor EA 2

5 030-01171-0000 9 Pin connector (P5782) EA 1


7 030-01188-0000 Female polarizing pin EA 2

ITEM PART NUMBER DESCRIPTION UM QTY

1 030-01174-0000 Sub-D 29 pin female connectorPositronic p/n RD29F00000-782.0

EA 1

2 030-01157-0011 Crimp connector pins (female) 20GPositronic p/n FC6020D-14

EA 3

3 030-01188-0000 Female polarizing pinTed Mfg Corp p/n 104202

EA 1

4 030-01161-0000 Sub-D 29 pin male connectorPositronic p/n RD29M00000-782.0

EA 1

5 030-01184-0011 Crimp connector pins (male) 20GPositronic p/n MC6020D-14

EA 2

6 030-01222-0000(Optional)

Sub-D 29 pin connector hood and lever assy. Positronic p/n D29000JVL0

EA 2

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Figure 19 PS-578A Configuration Programming Harness

K. PS-550 Connector Assembly


L. CD 671C Installation Kit


Table 61 CD 671C Installation Kit (050-03206-0000)

ITEM PART NUMBER DESCRIPTION UM QTY

1 MS27484T20F2SA 65 pin connector EA 1



2 030-01188-0000 Female polarizing pins EA 2


4 030-01173-0000 25 Pin D-Sub connector (P6711) EA 1

5 030-01173-0000 25 Pin D-Sub connector (P6712) EA 1

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M. CTA-81A/CTA-81D Installation Kit


Table 62 CTA-81A/CTA-81D Installation Kit (P/N 050-02818-0000)

6. System Description

A. General

Components of the Honeywell CAS 67A TCAS II System are listed in Table 1 CAS 67A TCAS II System Components and shown in Figure 1 CAS 67A TCAS II System Components.

B. TCAS II Functional Overview

The basic TCAS II system performs traffic alert and collision avoid-ance functions to provide safe separation between own aircraft and other aircraft equipped with Mode S, ATCRBS Mode C, or ATCRBS Mode A/C transponders.

NOTE: Mode A/C transponders are Mode A transponders that re-spond to Mode C interrogations.

TCAS II operation can be separated into the following functions:

(1) Surveillance Function

Detects the presence of Mode S or ATCRBS Mode A/C transponder equipped aircraft that are within TCAS surveillance limits.

Compares raw replies with existing track files in order to update current track information or to create new track files.


1 030-03051-0000 24 Pin connector (LP) EA 1

2 030-03051-0001 24 Pin connector (RP) EA 1

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(2) Tracking Function

Maintains tracking information files on Mode S, ATCRBS Mode C, and ATCRBS Mode A/C transponder equipped intruder aircraft. Tracking information includes range, relative bearing (if valid information is received from a directional antenna) and relative altitude (if target aircraft is reporting altitude). When that information is available, TCAS II computes relative position, closing range, and altitude change rate.

NOTE: Surveillance and tracking functions are performed by listening for Mode S squitters, Mode S and Mode C interrogation transmissions, and Mode S and Mode C reply receptions on both the top and bottom TCAS antennas.

(3) Collision Avoidance Computation and Resolution Advisory Dis-play Function

If an RA threat aircraft is present, TCAS determines the ap-propriate vertical maneuvering for own aircraft that will at-tain or maintain safe miss distance between own aircraft and intruder aircraft while creating the least deviation from own aircraft’s vertical rate. Communicates advised maneuver to the pilot by means of a resolution advisory display on the TA/RA/VSI or RA/VSI units.

(4) Threat Potential Evaluation Function

Determines threat potential of intruder aircraft based on com-putations using tracking data.

Categorizes intruders as resolution advisories (RAs), traffic advisories (TAs), proximity advisories (PAs), or non-threats (other traffic).

(5) Traffic Advisory Display Function

Provides a display of TA, proximity, or non-threat category traffic that are present in the surrounding airspace. The traffic display depicts the position and threat potential of intruder aircraft, which alerts the flight crew to potential-ly dangerous situations. Depending on the aircraft equipment, the traffic display may appear on a TA/RA/VSI unit, or an op-tional radar indicator, or dedicated TCAS display unit, or EFIS MFD display.

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(6) Aural Alert Function

Provides voice message advisory alerts on the cockpit audio system.

(7) Air-to-Air Coordination Function

If intruder aircraft is TCAS II equipped and becomes a threat, a maneuvering coordination data link is established with the intruder. This data link ensures that the resolution adviso-ries in both TCAS II equipped aircraft are coordinated and compatible. The coordination links are established between the two TCAS II systems via the Mode S transponders.

C. System Integration

Table 63 TCAS II System Integration Matrix (Sheet 1 of 16)

BUS#

PARAMETERDESCRIPTION

SOURCE OF DATA TRANSMISSION DESCRIPTIONFOR DATA

RECIPIENT OF DATA

1 XT Coordination

Mode S Transponder

XPONDER RCV 1A (P67A1 B80)XPONDER RCV 1B (P67A1 B81)XPONDER RCV 2A (P67A1 B82)XPONDER RCV 2B (P67A1 B83)

ARINC 718/735 (429) DataTransponder/TCAS Coordination

NOTE: Mode S transponder #2 inputs are the same as transponder #1.

TCAS Processor

2 Control Data Mode S/TCASControl Unit

Control Data Input Port 1A (P671A 15)Control Data Input Port 1B (P671A 16)

Control Data Input Port 2A (P671A 27)Control Data Input Port 2B (P671A 28)

Control Data PortSelect #1/#2 (P671A 42) (Gnd = Port #1)

ARINC 718/735 (429) Data Mode S Transponder

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Table 63 TCAS II System Integration Matrix (Sheet 2)

BUS#



RECIPIENT OF DATA

3 Altitude Data Air Data SystemBaro Altitude #1/#2

Baro Alt Port 1A (P671A 3)Baro Alt Port 1B (P671A 4)Baro Alt Port 2A (P671A 13)Baro Alt Port 2B (P671A 14)

ARINC 706 (429) DataARINC 575 (419) Data

Mode S Transponder

4 Altitude Data Encoding Altimeter #1 (#1-A1, P671A 44) (#1-A2, P671A 45) (#1-A4, P671A 46) (#1-B1, P671A 47) (#1-B2, P671A 48) (#1-B4, P671A 49) (#1-C1, P671A 58) (#1-C2, P671A 59) (#1-C4, P671A 60) (#1-D2, P671A 61) (#1-D4, P671A 62)

Encoding Altimeter #2

(#2-A1, P671A 63) (#2-A2, P671A 64) (#2-A4, P671A 65) (#2-B1, P671A 71) (#2-B2, P671A 72) (#2-B4, P671A 73) (#2-C1, P671A 74) (#2-C2, P671A 75) (#2-C4, P671A 76) (#2-D2, P671A 77) (#2-D4, P671A 78)

Gillham (11 wire) Interface

• Gillham Common = Aircraft Ground.

• Low = 3 V or 1.5 kΩ• High = greater than 18 V or 1.5 kΩ to 100 kΩ.

Mode S Transponder

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BUS#



RECIPIENT OF DATA

7 Altitude Data Synchro Altitude Source #1/#2

ARINC 718 Xpndr Pins:

Coarse X (TP 4A)Coarse Y (TP 4B)Coarse Z (TP 4C)

H (TP 4D)

C (TP 4E)

Fine X (TP 4F)Fine Y (TP 4G)Fine Z (TP 4H)

Altitude Flag (TP 4J)

Coarse X (MP 7A)Coarse Y (MP 7B)Coarse Z (MP 7C)

H (MP 7D)

C (MP 7E)

Fine X (MP 7F)Fine Y (MP 7G)Fine Z (MP 7H)

Synchro Flag (MP 7J)

ARINC 565 (XYZ/Synchro) Data

NOTE: For use with ARINC 718 Mode S Transponders.

• Synchro ALT #1• Synchro ALT #1• Synchro ALT #1

• Synchro reference volts ALT #1• Synchro common ALT #1


• Synchro altitude system failure status (Altitude Flag)


• Synchro reference volts ALT #2• Synchro common ALT #2


• Synchro altitude system failure status (Altitude Flag)

Mode S Transponder

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NOTE: In the following matrix, G = Aircraft ground,O = Open.


BUS#



RECIPIENT OF DATA

9 Altitude Data Baro Altitude TypeType A (P671A 85)Type B (P671A 86)

Per Definition Matrix below Mode S Transponder

BAROTYPEA

ALTITUDE

B

DEFINITION

(G= Aircraft Ground, O= Open)

G G Gillham Data

G O Not Assigned. NOTE: Synchro Data ARINC 718 Transponder.

O G ARINC 575 (ARINC 419)

O O ARINC 706 (ARINC 429)

BUS#



RECIPIENT OF DATA

8 Altitude Data Baro Altitude Source Select

MST 67A (P671A 87)

ARINC 718 Transponder (MP - 6E)

• Open = Baro Alt Port #1 Active• Gnd = Baro Alt Port #2 Active

Mode S Transponder

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BUS#



RECIPIENT OF DATA

5 Discrete(Input)

Aircraft Address CodeDiscretes: 0 = Open 1 = Ground

Add 01, (P671 5)Add 02, (P671 6)Add 03, (P671 7)Add 04, (P671 8)Add 05, (P671 9)Add 06, (P671 10)Add 07, (P671 11)Add 08, (P671 17)Add 09, (P671 18)Add 10, (P671 19)Add 11, (P671 20)Add 12, (P671 21)Add 13, (P671 22)Add 14, (P671 23)Add 15, (P671 24)Add 16, (P671 25)Add 17, (P671 31)Add 18, (P671 32)Add 19, (P671 33)Add 20, (P671 34)Add 21, (P671 35)Add 22, (P671 36)Add 23, (P671 37)Add 24, (P671 38)

24 Bit Address Code - Assigned by FAA for N registered air craft, Phone (405) 954-3116.

Mode S Transponder

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NOTE: In the following matrix, G = Aircraft ground / O = Open.


BUS#



RECIPIENT OF DATA

6 Discrete(Input)

Maximum AirspeedLimits

A = (P671A 50)B = (P671A 51)C = (P671A 52)

Per Definition Matrix below Mode S Transponder

(A) RI15

MAX AIRSPEED (B) RI16

(C) RI17

DEFINITION

(G= Aircraft Ground, O= Open)

O O O No Maximum Airspeed Available

O O G 75 kts. < Airspeed

O G O 75 kts. ≤ Airspeed < 150 kts

O G G 150 kts. ≤ Airspeed < 300 kts

G O O 300 kts. ≤ Airspeed < 600 kts

G O G 600 kts. ≤ Airspeed < 1200 kts

G G O 1200 kts. ≤ Airspeed

G G G Not Assigned

BUS#



RECIPIENT OF DATA

10 Discrete(Input)

Climb Inhibits 1500 fpm climb limit. TCAS Processor

Climb INH 1 (P67A1 B87)

• Gnd on either Input #1 or #2 inhibits climb.

Climb INH 2 (P67A1 B88)

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BUS#



RECIPIENT OF DATA

11 Discrete(Input)

Increase ClimbInhibits

INC Climb INH 1 (P67A1 A98)INC Climb INH 2 (P67A1 A99)

2500 fpm climb limit.

• Gnd on both Input #1 and #2 inhibits climb.

TCAS Processor

21 Discrete(Input)

Landing Gear (P67A1 A21)

• Ground = Landing Gear Extended• Open = Landing Gear Retracted

TCAS Processor

22 Discrete(Input)

Air/Ground Switch (P67A1 A22)

• Ground = Aircraft on ground• Open = Aircraft airborne

TCAS Processor

12 Discrete(Input)

Advisory Inhibits

#1 (P67A1 A17)#2 (P67A1 A18)

• Ground on Advisory Inhibit Discrete: #1 = STANDBY mode #2 = Aural Inhibit mode

TCAS Processor

13 Discrete(Input)

Advisory/AnnunciatorCancel (P67A1 A72)

• Ground = Advisory Annun. Cancellation• Open = No Cancellation

TCAS Processor

15 Discrete (Input)

RA Valid #1/#2(P67A1 B85)(P67A1 B86)

• Ground = Display Valid• Open = Display Failure• Unused = Open

TCAS Processor

14 Discrete (Input)

TA Valid #1/#2(P67A1 A34)(P67A1 A35)

• Ground = Display Valid• Open = Display Failure• Unused = Open

TCAS Processor

17 Discrete (Input)

Test Mode (ATE) (P67A1 A12)

ATE Factory Test Mode

• Gnd = Factory Test Mode Enabled• Open = Normal operation

NOTE: For aircraft installations pin A12 MUST be open.

TCAS Processor

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BUS#



RECIPIENT OF DATA

16 Discrete (Input)

Calibration Enable (P67A1 B59)

CALENB ATE Test Function

• Gnd = Calibration Enabled• Open = Normal operation

NOTE: For aircraft installations pin B59 MUST be open.

TCAS Processor

18 Discrete (Input)

ATE Enable (P67A1 B89)

ATE Test Function Enable

• Gnd = ATE Enabled (parallel lines)• Open = Normal Operation (only configuration module lines enabled)

NOTE: For aircraft installations pin B89 MUST be open.

TCAS Processor

19 Discrete(Input)

On/Off (P67A1 A11)

• Ground = Power ON• Open = Power OFF

TCAS Processor

20 Discrete(Input)

Functional Test (P67A1 A20)

Initiates functional self-test• Ground = Functional Test• Open = Normal operation

TCAS Processor

30 Power Input Aircraft Power

+28 Vdc A/C Power (P67A1 A5) (P67A1 A6) (P67A1 A7) (P67A1 A8)

+28 Vdc Power Input (4 lines) TCAS Processor

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BUS#



RECIPIENT OF DATA

31 Power Input Aircraft Ground

GND (P67A1 A1)GND (P67A1 A2)GND (P67A1 A3)GND (P67A1 A4)GND (P67A1 A9)GND (P67A1 A10)GND (P67A1 B32)GND (P67A1 B57)GND (P67A1 B98)

Aircraft Ground Plane (9 lines)

TCAS Processor

24 RadioAltimeter

Radio Altimeter/Analog

ARINC 552A Data from analog radio altimeter. Input impedance 55 kΩ.

TCAS Processor

Rad Alt #1 + (Hi) (P67A1 A36)

• AGL altitude from analog radio altimeter #1

Rad Alt #1 - (Low) (P67A1 A38)

Rad Alt Valid #1 (P67A1 A37)

• Radio altimeter #1 valid. VALID = 20-30 Vdc

Rad Alt #2 + (Hi) (P67A1 A65)

• AGL altitude from analog radio altimeter #2

Rad Alt #2 - (Low) (P67A1 B19)

Rad Alt Valid #2 (P67A1 A39)

• Radio altimeter #2 valid. VALID = 20-30 Vdc

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BUS#



RECIPIENT OF DATA

25 RadioAltimeter

Radio Altimeter/Digital

Rad Altim 1A (P67A1 B40)

Rad Altim 1B (P67A1 B41)

Rad Altim 2A (P67A1 B42)

Rad Altim 2B (P67A1 B43)

ARINC 707 (429) data from digital radio altimeter

• ARINC 429 data from digital radio altimeter #1




TCAS Processor

23 RadioAltimeter

Radio AltimeterSource Select #1/#2 (P67A1 A66)

• Open = Input Port #1 Active• Ground = Input Port #2 Active

TCAS Processor

26 Heading (Magnetic)

Aircraft HeadingSystem (D/G)

Synchro Data, Valid, 26 VacARINC 407 3-wire synchro

TCAS Processor

Hdg Y (P67A1 B103)Hdg X (P67A1 B104)Hdg Z (P67A1 B105)

• Synchro heading• Synchro heading• Synchro heading

Hdg H (P67A1 B102)Hdg C (P67A1 B20)

• Synchro reference voltage• Synchro common

Heading Valid(P67A1 A86)

• Synchro heading system failure status. VALID = 20-30 Vdc

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BUS#



RECIPIENT OF DATA

27 Attitude(Roll and Pitch)

Aircraft AttitudeSystem (V/G)

Synchro Data, Valid, 26 VacARINC 407 3-wire synchro

TCAS Processor

Pitch X (P67A1 A91)Pitch Y (P67A1 A92)Pitch Z (P67A1 A93)

• Synchro attitude



Roll X (P67A1 A94)Roll Y (P67A1 A95)Roll Z (P67A1 A96)

• Synchro attitude• Synchro attitude• Synchro attitude

H (P67A1 A97)C (P67A1 B101)

• Synchro reference voltage• Synchro common

Valid (P67A1 A85) • Synchro attitude system failure status. VALID = 20-30 Vdc

28 Attitude/Heading

Inertial Navigation System /AHRS

ARINC 704/705 (High Speed 429) magnetic heading from AHRS.

TCAS Processor

Hdg/Att 1A (P67A1 B97)Hdg/Att 1B (P67A1 B93)

Hdg/Att 2A (P67A1 B69)Hdg/Att 2B (P67A1 B70)

• HDG/ATT 2A/2B available only w/ TPU 67A versions 066-01146-0201,-1211.

29 Performance Data

Flight Management System

FMS 1A (P67A1 B55)FMS 1B (P67A1 B7)

ARINC 702 (429) (Reserved) TCAS Processor

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BUS#



RECIPIENT OF DATA

32 TX Coordination

TCAS Processor

XPDR TX 1A (P67A1 B67)XPDR TX 1B (P67A1 B68)XPDR TX 2A (P67A1 B54)XPDR TX 2B (P67A1 B56)

ARINC 718/735 (429) DataTransponder/TCAS Coordination

Mode S Transponder

33 Antenna/Mode S(Two Required)

Mode S Transponder

Top Antenna (P671B 2)

Bottom Antenna (P671B 1)

Omnidirectional Bi-directional

34 Discrete (Output)

TCAS Processor (P67A1 B37)

FAN ON (Reserved)

Output for cooling fan where forced air cooling is not available.

Fan


TCAS Processor (P67A1 A90)

TA AURAL TRAFFIC

• Ground = Active• Open = Not active

Active for TA advisory.

Audio ToneGenerator/AudioDistribution Center

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TCAS Processor

(P67A1 A87) (P67A1 B58) (P67A1 B106)

VISUAL ANNUNCIATION TRAFFICActive for Traffic Advisory.

VISUAL ANNUNCIATION PREVENTIVEActive for Preventive Resolution Advisory.

VISUAL ANNUNCIATION CORRECTIVEActive for Corrective Resolution Advisory.

• Ground = Active• Open = Not active• Self Test = Not Active

VisualAnnunciator


TCAS Processor (P67A1 B6)

TA DISPLAY ENABLE

• Ground = Active• Open = Not active

Signals some multifunctional traffic displays to display TCAS traffic.

TA Display


TCAS Processor (P67A1 A89)

TCAS VALID

• Ground = TCAS System Valid• Open = TCAS System Fault

Monitors TCAS system status.

FaultAnnunciator

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39 ATE Interface TCAS Processor

ATE A0 (P67A1 B10)ATE A1 (P67A1 B9)ATE A2 (P67A1 B8)ATE D0 (P67A1 B18)ATE D1 (P67A1 B17)ATE D2 (P67A1 B31)ATE D3 (P67A1 B25)ATE D4 (P67A1 B12)ATE D5 (P67A1 B24)ATE D6 (P67A1 B11)ATE D7 (P67A1 B23)ATE CLK (P67A1 B53)

ATE Interface

ATE pins out 3 address lines (A0-A2), and eight data lines (D0-D7)

• Test Mode - ATE factory test pins.• ATE Enable - activates ATE interface.• Cal Enable - enables processor to write to EEPROM.

Reserved for factory and field configuration.

Automatic Test Equipment

40 Flight Data Recorder

TCAS Processor RS 422 Interface PersonalComputer

RS 422 DAT + (P67A1 B2)RS 422 DAT - (P67A1 B3)RS 422 CLK + (P67A1 B4)RS 422 CLK - (P67A1 B13)

41 Diagnostic Interface

Diagnostic Computer

TCAS 232 TX (P67A1 B1)TCAS 232 RX (P67A1 B66)TERM RDY (P67A1 B99)TCAS 232 RDY (P67A1 B100)

RS 232 Interface, fault data Bi-directional

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42 Configuration Module

Configuration Module

Config Mod CS1 (P67A1 B9)

Config Mod CS2 (P67A1 B10)

Config Mod +5 Vdc (P67A1 B8)

Config Mod Data In (P67A1 B90)

Config Mod Data Out (P67A1 B18)

Config Mod CLK (P67A1 B23)

ATE Data Lines A0/A2, D0, D7 serial interface.

Hardware strapping information from configuration module:TA/RA Block Transfer ProgramDisplay Intruder LimitPerformance Limit ProgramAltitude LimitAudio LevelsHeading TypeAttitude TypeRadio Altitude TypeLeft/Right Display (SKID) EnableTransponder (Mode S Diversity)Aircraft Antenna ConfigurationInhibit Functional TestDisplay All TrafficGround Display ModeAudio ProgramDisplay Intruders On-GroundRadio Altimeter InstallationGillham Altitude CompareEnhanced Extended TestPass Intruder FilesSecond A429 AHRS/IRU

Bi-directional

43 Suppression Suppression System (P67A1 A13)

TCAS Processor will accept and respond to suppression pulses from other avionics equipment.

Bi-directional

44 Displays TCAS Processor

TA/RA Display TX 1A (P67A1 B30)TA/RA Display TX 1B (P67A1 B16)TA/RA Display TX 2A (P67A1 B28)TA/RA Display TX 2B (P67A1 B29)

ARINC 735 (429) Hi Speed Data

NOTE: If a combined RA/TA display is used, both TA valid and RA valid must be tied to Display Valid discrete IVA-81A/B/C/D pin 29.

TA/RA Display

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45 Displays TCAS Processor

RA Display TX 1A (P67A1 B35)RA Display TX 1B (P67A1 B36)

RA Display TX 2A (P67A1 B33)RA Display TX 2B (P67A1 B34)

ARINC 735 (429) Low Speed Data RA Display

46 AudioInterface (Speaker)

TCAS Processor

Spk Hi (P67A1 A67)Spk Lo (P67A1 A68)

Speaker (8 Ω) output Speaker

47 AudioInterface (Headphone)

TCAS Processor

PH Hi (P67A1 A69)PH Lo (P67A1 A70)

Headphone (600 Ω ) output. Headphone

48 Top Antenna TCAS Processor

(P67A2 A1 Top J1)(P67A2 B1 Top J2)(P67A2 C1 Top J3)(P67A2 D1 Top J4)

4 Element Directional Bi-directional

49 BottomAntenna

TCAS Processor

(P67A2 A2 Bot J1)(P67A2 B2 Bot J2)(P67A2 C2 Bot J3)(P67A2 D2 Bot J4)

4 Element Directional antennaOr Omnidirectional (Optional)50 Ω Load (dc short) antenna.

Bi-directional

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Figure 20 TPU 67A TCAS II Processor, Inputs/Outputs (Sheet 1 of 2)

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Figure 20 TPU 67A TCAS II Processor, Inputs/Outputs (Sheet 2)


7. System Component Functions

A. TCAS Processor

(1) General

The microprocessor based TPU 67A TCAS processor is the master control unit in the TCAS II system. It consists of a combined computerized control system and L-band receiver/transmitter. Operation of the TCAS system is controlled by TCAS software resident in the computer control memory.

(2) TCAS Processor Inputs/Outputs

The TCAS processor routinely reads and stores the following own aircraft information (refer to Figure 20 TPU 67A TCAS II Processor, Inputs/Outputs):

(a) Own aircraft heading, pitch, roll, and radio altimeter inputs.

This information in conjunction with own pressure alti-tude data allows TCAS to determine own aircraft position and flight path which is needed for tracking, RA and TA advisory, and traffic display computations.

(b) Own aircraft pressure altitude data received on the ARINC 429 data bus from Mode S transponder.

Pressure altitude is input to the TCAS processor from own aircraft’s pressure altitude source. Pressure al-titude is used to determine own aircraft altitude rel-ative to intruder’s reported altitude and own aircraft flight level altitudes.

(c) Mode control requests and traffic display control in-puts from the Mode S transponder via the ARINC 429 data bus.

The Mode S transponder receives this data from the tran-sponder control unit. This information is a factor in TCAS sensitivity level determinations and traffic dis-play format.

(d) Own aircraft identification (transponder I.D.) received on the ARINC 429 data bus from own Mode S transponder.

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Own aircraft identification is input to the transponder via 24 discrete bit strapped inputs. Own aircraft I.D. is used by the TCAS II processor during air-to-air co-ordination routines.

(e) Own aircraft maximum airspeed data received on the ARINC 429 data bus from own Mode S transponder.

Own aircraft maximum airspeed is input to the transpon-der via three discrete bit strapped inputs. This in-formation is used in maximum closing rate projections. (TPU 67A 066-01146-0101,-0201 only).

(f) Discrete input from weight-on-wheel (Air-Ground) strut switch.

Notifies TCAS as to whether own aircraft is in-flight or on-the-ground. Used in conjunction with the ground display mode strap. (TPU 67A 066-01146-0101,-0201 only).

(g) Discrete input from landing gear.

Allows TCAS to determine when the landing gear is ex-tended. Bottom directional antenna operates in omni mode when landing gear is extended.

(h) Advisory Inhibit discrete inputs from ground proximity and wind shear system (if applicable).

(i) Discrete input from optional Advisory Cancel switch.

(j) Continuity/resistance checks on top and bottom TCAS an-tenna ports.

This information allows TCAS processor to determine if an omni or directional antenna is used as the bottom TCAS antenna and if the antenna cables are properly con-nected to the top and bottom antennas. The four ports for each directional antenna should reflect specific and different resistance values due to port identifica-tion resistors mounted inside the directional antenna.

(k) System validity inputs.

If a failure is detected on any of the following inputs, TCAS generates failure annunciation data to the resolu-tion advisory and traffic displays.

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1 Discrete failure status inputs from the TA units or other optional display units.

NOTE: In the event of a display unit failure, the display will set its "display val-id" output discrete to invalid and at-tempt to display status of the fault it has detected, if it is not prevented from doing so by the nature of the fault (i.e., certain faults will result in a blank display and not allow the display of any data).

2 Loss of continuity through the TCAS antennas.

3 Failure status data or loss of data on the ARINC 429 data link from the Mode S transponder.

4 Internal TCAS processor failures including fail-ure of internal power supplies.

5 Invalid data from the Radio Altimeter, ATT, HDG, etc.

(l) TCAS System degradation.

If a particular failure degrades TCAS operation, the TCAS processor stops all TCAS processing and displays an appropriate annunciation on the display units. TCAS processor self-tests and failure annunciations are de-scribed in detail in the INSTALLATION AND MAINTENANCE, and FAULT ISOLATION sections of this manual.

(3) Configuration Module

The configuration module interface has the following discrete lines: DATA IN, DATA OUT, CHIP SELECT 1, CHIP SELECT 2, CLOCK, VCC (+5 Vdc), and GROUND. Upon power up the TPU 67A will down-load the configuration module data and compute a data check-sum. This checksum will be stored in the configuration module during the installation setup/configuration write; the CAS 67A system will fail if the checksum does not match.

A compatibility code within the module will be monitored to assure its compatibility with the current TCAS II processor software. A failure will be annunciated if there is a com-patibility problem between the software and the module.

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In addition to the bearing calibration data (if required), the following hardware strapping information will be acquired from the configuration module:

(a) TA/RA Block Transfer Program: ARINC 735 protocol or Hon-eywell BCAS (EFIS) protocol.

(b) Display Intruder Limit: Three (minimum)≤ Display In-truder Limit ≤ 31 (no limit), incremented by one.

(c) Performance Limit Program: 1500 FPM cannot climb deter-mined by FMS or Altitude Limit.

(d) Altitude Limit: 0 ≤ Altitude Limit ≤ 62000 feet, incre-mented by 2000 feet. An even number between 0 and 62000 indicates the maximum altitude at which the aircraft is capable of climbing at 1500 fpm. This limit is active only when the Performance Limit Program input is active.

(e) Speaker Airborne Audio Level: 0.0625, 0.125, 0.25, 0.5, 1.0, 2.0, 4.0, or 6.5 watts.

(f) Speaker On-Ground Audio Level: 0.0625, 0.125, 0.25, 0.5, 1.0, 2.0, 4.0, or 6.5 watts.

(g) Headphone Airborne Audio Level: 1.25, 2.5, 5.0, 10.0, 20.0, 40.0, 80.0, or 100 mW.

(h) Headphone On-Ground Audio Level: 1.25, 2.5, 5.0, 10.0, 20.0, 40.0, 80.0, or 100 mW.

(i) Heading Type: Synchro Data or ARINC 429 Data.

(j) Attitude Type: Synchro Data or ARINC 429 Data.

(k) Radio Altitude Type: ARINC 429, Honeywell (KRA 405, -10mV/ft), Honeywell (RT 220/300, -4 mV/ft), Collins (ALT 50/55, dual slope), or ARINC 552A data.

(l) Left/Right Display (SDI) Enable: Enabled or Not en-abled.

(m) Transponder (Mode S Diversity) Installation: Single or Dual.

(n) Aircraft Antenna Configuration Program: Dual direction-al antenna or Directional and monopole antenna/dc short circuit.

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(o) Inhibit Functional Test: Inhibit airborne test or Allow airborne test.

(p) Display All Traffic: Display all traffic when TA or RA is present ("POPUP" mode) or Display all traffic all of the time.

(q) Ground Display Mode: TCAS in standby mode on-Ground or TCAS in TA only mode on-Ground.

(r) Audio Program: No delay in voice, Audio tone output one second prior to voice, or Voice muting.

(s) Display Intruders On-Ground Program: Inhibit on-ground intruders or Allow on-ground intruders.

(t) Radio Altimeter Installation Source Select:

1 Single radio altimeter installed.

2 Dual radio altimeter/ Manual selection.

3 Dual radio altimeter/ Auto reversion.

(u) Gillham Altitude Compare Function: Enabled or Not en-abled.

(v) Enhanced Extended Functional Test program: Enabled or Not enabled.

(w) Intruder File Transmission Program: Allow file transfer during “POPUP” mode or Not allow file transfer during “POPUP” (i.e. normal).

(x) Attitude/Heading #2 AHRS/IRU Program Option (available on TPU 67A p/n 066-01146-0201,-1211 only): Single AHRS source (either ARINC 429 or synchro) or Dual AHRS/ auto reversion (ARINC 429 only, secondary synchro ports not available).

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(4) TCAS Processor Functions

The TCAS processor controls the following real-time functions of TCAS:

(a) The TPU 67A receives 1030 MHz TCAS broadcasts through the transponder via ARINC 429 bus (TCAS receivers re-ceive at 1090 MHz). The TPU 67A 1030 MHz receiver is not used with TCAS II. The TCAS processor formats and transmits broadcast messages. Broadcast messages are transmitted at 1030 MHz by each TCAS system to notify other TCAS equipped aircraft that own TCAS equipped air-craft is present.

Broadcast messages are transmitted on the TCAS direc-tional and omni antennas. Each TCAS, including own TCAS, keeps track of the number of broadcast messages being received. This provides each TCAS with the number of TCAS equipped aircraft within broadcast range. This number is used in TCAS interference limiting formulas, the resultant of which is used to control the power out-put levels and rates employed for TCAS Mode S interro-gations.

TCAS reduces the number of TCAS Mode S interrogations and also reduces the power output levels as the number of TCAS equipped aircraft (number of broadcast recep-tions) increases. This reduces the detectable interro-gation load on Mode S transponders in situations where numerous TCAS equipped aircraft are present in the same airspace volume. The effect of reducing the number of air-to-air interrogations and associated transmit power levels is a reduction of unsolicited replies (fruit overload) received by ground stations.

(b) The TCAS processor listens for Mode S transponder squit-ter messages from other aircraft. Mode S transponders indicate their presence by transmitting a 1090 MHz squitter message once every second. The TCAS processor listens for squitters on the TCAS directional and omni antennas.

(c) If a valid Mode S squitter message is detected, the TCAS processor commences to interrogate the intruder. If an interrogated Mode S equipped aircraft is within TCAS Mode S tracking range and altitude, the Mode S equipped intruder is placed into track.

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Mode S track updates are then executed which involve the TCAS processor formatting and then transmitting 1030 MHz Mode S interrogation messages on the directional an-tenna and/or the omni antenna, and receiving 1090 MHz Mode S reply messages on the directional antenna and/or the omni antenna. The TCAS processor selects one of four directional antenna beams to be used for direction-al message transmission and reception.

(d) The TCAS processor performs ATCRBS search, track ini-tialization, and track updates. If an ATCRBS equipped aircraft is within TCAS ATCRBS tracking range and alti-tude, the ATCRBS equipped intruder is placed into track. ATCRBS search, track initialization, and track update operations involve the TCAS processor formatting and then transmitting 1030 MHz ATCRBS interrogations, and receiving 1090 MHz ATCRBS replies on the directional an-tenna and/or the omni antenna. The TCAS processor se-lects one of four directional antenna beams to be used for ATCRBS directional message transmission and recep-tion.

NOTE: Mode S and ATCRBS Mode C interrogation and reply message formats are shown in Figure 21 Mode S and ATCRBS Mode C Interrogation For-mats and Figure 22 Mode S and ATCRBS Mode C Transponder Reply Message Formats.

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Figure 21 Mode S and ATCRBS Mode C Interrogation Formats

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Figure 22 Mode S and ATCRBS Mode C Transponder Reply Message Formats

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(e) The TCAS processor performs functions that determine range, bearing, and altitude of intruder aircraft based on information computed from or contained in the reply messages. Bearing can only be determined for intruder replies received on the directional antenna. Altitude can only be determined if the intruder is reporting al-titude in its transponder’s reply message.

(f) Based on the information that can be extracted from or computed from the reply, the TCAS processor evaluates the threat potential of the intruder by calculating in-truder closing rate and position relative to own air-craft. Based on this evaluation, the TCAS processor categorizes the intruder as a non-threat, proximity, traffic advisory, or resolution advisory.

(g) For resolution advisory category aircraft, the TCAS II processor computes the proper advisory to maintain or establish safe separation between own aircraft and in-truder aircraft. The TCAS II processor then outputs resolution advisory data on the ARINC 429 data bus to the TA/RA/VSI or RA/VSI units, outputs RA traffic symbol position and alert data on the ARINC 429 data bus to the TA/RA/VSI or dedicated display unit, and outputs reso-lution advisory alert voice messages to the cockpit au-dio system, and alert outputs for optional tone gener-ators and/or lamps.

(h) For traffic advisory category aircraft, the TCAS pro-cessor outputs TA traffic symbol position and alert data on the ARINC 429 data bus to the TA display, outputs traffic advisory alert voice messages to the cockpit au-dio system, and alert outputs for optional tone gener-ators and/or lamps.

(i) For proximity and non-threat category aircraft, the TCAS processor outputs proximity or non-threat traffic symbol position data on the ARINC 429 data bus to the traffic advisory display. (Voice alerts are not gener-ated for proximity or non-threat category aircraft).

(j) For resolution advisory category aircraft that are also TCAS II equipped, the TCAS processor establishes a co-ordination data link with threat aircraft. This coor-dination link involves own TCAS processor transmitting coordination messages to threat aircraft’s transponder via own TCAS antennas and receiving coordination mes-sage replies from threat aircraft’s transponder.

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Once the TCAS II equipped threat aircraft has detected own aircraft as a threat, the same process is initiated from the threat aircraft via own Mode S transponder and a full two-way coordination data link is established. The coordination data assure non-conflicting maneuver-ing between TCAS II equipped aircraft that are mutual threats to one another.

(k) During each TCAS 1030 MHz transmission on the direction-al or omni antenna, the TCAS processor generates a sup-pression pulse to other L-band equipment on own air-craft.

(l) The TCAS processor reduces fruit and synchronous garble interference by the following interference limiting methods:

1 An ATCRBS P2 sidelobe suppression pulse is trans-mitted as an omnidirectional pattern on the di-rectional antenna to control the effective beam width. Refer to Figure 23 TCAS Directional An-tenna Transmit/Receive Beam Patterns.

2 A sequence of ATCRBS interrogations are transmit-ted at different power levels (whisper-shout lev-els). These whisper-shout levels divide the sur-rounding airspace into range segments.

Systems with the TPU 67A 066-01146-0101, -0201 use the maximum number of whisper-shout levels (24) when interrogating in the forward direction on the directional antenna.

Systems with the TPU 67A 066-01146-1111, -1211 use the maximum number of whisper-shout levels (24) when interrogating in the forward direction on the directional antenna only in high density Mode C environments.

3 Interrogating more than once to check reply va-lidity.

4 Transmitting a P2 ATCRBS suppression pulse in Mode S interrogation transmissions.

5 Transmitting a P4 Mode S suppression pulse during ATCRBS interrogation transmissions.

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(m) The TCAS processor also provides communication inter-faces with a TCAS data recorder

(n) The TCAS processor also controls:

1 Scheduling for interrogations performed on the directional and omni antennas.

2 TCAS sensitivity level operating modes.

3 Generation of coasting data during periods when tracking data is temporarily lost.

(4) Power Requirements

The TCAS processor receives 28 Vdc primary power and 26 Vac synchro reference input power from aircraft power sources.

B. Directional Antenna

(1) General

The ANT 67A Directional Antenna allows bearing of intruder aircraft to be determined by providing the means for the TCAS processor to transmit interrogations and receive reply recep-tions on one of four antenna beams.

By selecting the beam, the TCAS processor electronically points the antenna in a surveillance direction during TCAS transmit and receive operations.

(2) TCAS Directional Antenna Description

The directional antenna is an electronically steerable phased array consisting of four top loaded monopole elements.

Unlike mechanically steered antennas, the antenna pattern can be pointed in one of four directions without physically moving the antenna. This is achieved by independently varying the phase to each of the four antenna elements contained in the directional antenna. The phasing of these signals directly affect the beam, therefore, the phase match of the coax cables is very important.

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The four beam forming elements are located on the perimeter of the antenna, and the whole assembly is contained in an aerodynamic plastic enclosure just over one inch in height. The top directional antenna is mounted at or near the longi-tudinal centerline of the aircraft ± 5 degrees and as far for-ward as is practical. The bottom directional antenna or omni antenna (if used) is co-located as near as possible to the vertical plane of the top directional antenna.

During TCAS receptions, each of the four directional antenna elements receives any 1090 MHz signal that passes by the el-ement. The phasing of these received signals is determined by the direction from which the RF energy is received. These signals are directed onto the same four cables that connect transmit signals between the TCAS processor and directional antenna.

Each of the four ports of the directional antenna contains a resistor located across the antenna element to ground. Each of the four resistors is a different value. The TCAS proces-sor periodically performs a continuity check on the antenna ports and should see the correct resistance value (via an A/D converter) if the port is not shorted or not open. The di-rectional antenna is a passive device and does not require aircraft power.

C. TCAS Omnidirectional Antenna

TCAS may use one omni antenna mounted on the bottom of the aircraft instead of a directional antenna.

The omni antenna is a L-band monopole and is identical to the omni antennas presently used for DME and ATC transponders. The TCAS omni antenna must be the dc short type, L-band.

The TCAS omni antenna connects to the TPU 67A TCAS processor (P67A2 A2 BOTJ1). This connection is made via a coaxial cable. The three remaining unit bottom antenna coaxes must be connected to 50 Ω ter-minations.

The TCAS processor routinely performs continuity checks on the om-nidirectional antenna and associated cables.

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Figure 23 TCAS Directional Antenna Transmit/Receive Beam Patterns

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D. TA/RA/VSI Display

(1) General

The IVA-81A, IVA-81C, and IVA-81D Traffic Advisory/ Resolu-tion Advisory/Vertical Speed Indicator displays use a high resolution, sunlight readable, full color, liquid crystal display (LCD) to display traffic information. The active ma-trix LCD display gives a flicker free, parallax free display.

The center of the display is a horizontal situation presenta-tion of the traffic around the aircraft including intruder al-titude, and vertical direction. Traffic is divided into four categories by threat risk and differentiated on the display by symbol color and shape as shown in Figure 24 IVA-81A/IVA-81C/IVA-81D TA/RA/VSI.

Text messages are displayed for TCAS and display modes and intruder information.

Display brightness level is controlled by a combination of be-zel and remote light sensors and by the lighting bus input. An optional bezel mounted brightness control is also avail-able.

Traffic display range control can be provided remotely from the control unit or locally via an optional bezel mounted range control.

Traffic display data (TA data) is received via a high-speed ARINC 429 data bus from the TCAS processor.

An optional traffic select (TA SEL) switch allows decluttering the display of aircraft symbols.

The TA/RA/VSI accepts air data ARINC 565 or ARINC 575 analog inputs, ARINC 575 digital or ARINC 429 high and low speed in-puts, and pneumatic vertical speed input.

Vertical maneuvering resolution advisory data (RA data) and traffic advisory data (TA data) are received via a high-speed ARINC 429 data bus from the TCAS processor.

Built-in-test circuits continuously monitor for TA unit fail-ures. Failure status is reported to the TCAS processor via discrete DISPLAY VALID signal lines.

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Figure 24 IVA-81A/IVA-81C/IVA-81D TA/RA/VSI

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(2) Resolution Advisory Display

The resolution advisory commands displayed on the TA/RA/VSI (or RA/VSI) are the primary indications used for vertical ma-neuvering guidance. TCAS II resolution advisories on the two TA/RA/VSI (or RA/VSI) units indicate vertical speeds to be used or avoided in order to maintain or achieve safe vertical separation.

A pointer and vertical speed scale, which are standard VSI features, indicate the present vertical speed of own aircraft. For TCAS guidance, the TA/RA/VSI displays red and green com-mand arcs on a liquid crystal display along with the vertical speed scale and pointer.

The red and green RA command indications provide corrective or preventive resolution advisory maneuvering guidance to the pilot.

(3) Traffic Display

The TA/RA/VSI traffic display provides a display of surround-ing intruder aircraft that are equipped with Mode S or ATCRBS Mode A/C transponders, are detected on a directional antenna, and are within the display range and altitude window.

NOTE: The TCAS processor interface also supports traffic displays on a dedicated TCAS traffic display or a PPI radar display modified for TCAS. The unit se-lected to display traffic depends on equipment cur-rently present in the aircraft and other user re-quirements. The TCAS processor supplies traffic display and resolution advisory data outputs on two separate high-speed ARINC 429 data bus outputs.

Graphics provided on the traffic display alert the pilot to traffic advisory and resolution advisory conditions and an-nunciate TCAS operational modes and failure conditions. The selected traffic display functions as a self-sufficient pe-ripheral device driven by the TCAS processor through a single high-speed ARINC 429 data bus.

Traffic displays are considered secondary displays in the overall TCAS II system. (Resolution advisories on the TA/RA/VSI and RA/VSI are considered the primary TCAS II displays). The traffic display aids the pilot in visually acquiring an intruder aircraft prior to resolution advisory threat condi-tions.

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Traffic display data from the TCAS processor, via the high-speed ARINC data link, includes the following:

(a) Intruder aircraft range.

NOTE: Up to 30 intruder data sets may be supplied depending on traffic conditions.

(b) Intruder aircraft relative altitude (if available)

(c) Intruder aircraft bearing (if available)

(d) Intruder category (resolution advisory threat, traffic advisory, proximity, or non-threat)

(e) Own aircraft altitude

(f) Own aircraft TCAS operating mode (sensitivity level)

(g) Own aircraft heading (EFIS display only)

(h) Advisory alert information

(i) TCAS failure status information

(j) Display range limit control, ABOVE/NORM/BELOW non-threat altitude display limit control, and relative/flight level altitude display control data originating from the TCAS/transponder control unit and received by the traffic display via the Mode S transponder and TCAS processor.

(k) Other strapped control data such as maximum number of intruders to be displayed, etc.

Refer to paragraph 8. System Control and Indicator Func-tions for traffic display indications and annuncia-tions.

E. RA/VSI Display

The IVA-81B Resolution Advisory/Vertical Speed Indicator (RA/VSI) display is shown in Figure 25 IVA-81B RA/VSI. It consists of:

• An electromechanically driven pointer to display vertical speed.

• A resolution advisory arc of red and green high brightness LEDs.

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• An electromechanical TCAS flag, for indicating normal, fail con-ditions, and RA mode OFF conditions.

• Vertical speed failure flag.

The IVA-81B replaces an existing size 3 Air Transport Indicator (3ATI) vertical speed indicator.

Figure 25 IVA-81B RA/VSI

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The resolution advisory LEDs are mounted under a coated surface which makes them invisible when unlighted. The VSI face is matte black with a matte white vertical speed scale. The vertical speed pointer is driven by a two-phase motor. The position is controlled by the processed data supplied by the display computer.

The RA/VSI accepts air data ARINC 565 or ARINC 575 analog inputs, ARINC 575 digital, ARINC 429 high and low speed data, or a pneumatic vertical speed input.

Vertical speed maneuvering resolution advisory data (RA data) is re-ceived via a high-speed ARINC 429 data bus from the TCAS processor.

NOTE: Traffic is not displayed on an RA/VSI.

Built-in test circuits continuously monitor for RA/VSI unit fail-ures. Failure status is reported to the TCAS processor via discrete DISPLAY VALID signal lines.

The resolution advisories (RAs) on the electrical/electro-mechani-cal display of the RA/VSI are identical to the RAs on the LCD display of the TA/RA/VSI.

F. Mode S Transponder

The Mode S transponder is discussed in this manual to aid under-standing of overall TCAS operation. For additional information re-fer to the applicable Mode S transponder system maintenance manual.

(1) Mode S Transponder Functions

The microprocessor based Mode S transponder performs the fol-lowing functions in the TCAS II system:

(a) Automatically transmits 1090 MHz Mode S squitter mes-sages every second. These squitter messages notify oth-er TCAS equipped aircraft and ground stations that own Mode S equipped aircraft is present.

(b) Receives broadcast messages from other TCAS equipped aircraft and notifies own TCAS processor that broadcast message was received.

(c) Replies to 1030 MHz Mode S interrogations from other TCAS equipped aircraft.

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(d) Replies to 1030 MHZ Mode A, Mode C, and Mode S interro-gations from ATC ground stations with a 1090 MHz message in the traditional manner.

(e) Transmits 1090 MHz resolution advisory air-to-air coor-dination message data (received from the TCAS proces-sor) during threat conditions between own and other TCAS equipped aircraft.

(f) Provides the following data to the TCAS processor via an ARINC 429 data link:

1 Own aircraft identification code, pressure alti-tude, and maximum airspeed data.

2 TCAS broadcast information and air-to-air resolu-tion advisory coordination information received from other TCAS equipped aircraft.

3 TCAS sensitivity level and other mode control data received by own Mode S transponder from own transponder/TCAS control unit.

4 TCAS sensitivity level control data from Mode S ground control stations at 1030 MHz (future ap-plication).

5 Mode S ARINC 604 maintenance status.

(g) Receives TCAS capability, TCAS validity, sensitivity level, and TCAS coordination update data from the TCAS processor via the ARINC 429 data link and inserts this data into 1090 MHz coordination messages. Replies to interrogations from Mode S ground stations will be a future application.

(2) Mode S Transponder BITE

The Mode S transponder contains built-in-test-equipment soft-ware that continuously monitors for transponder internal failures, transponder control unit failures, and ARINC 429 data failures.

Failure status is reported to the TCAS processor via the ARINC 429 data link. The transponder reports failure status to the FAIL lamp on the transponder control unit via a discrete out-put signal.

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(3) Mode S Transponder Power

The Mode S transponder receives 28 Vdc primary input power and 26 Vac synchro altitude reference power from aircraft power sources. The transponder receives a suppression pulse from the TPU 67A TCAS processor during transmissions.

G. Control Units

The control units are discussed in this paragraph to aid understand-ing of overall TCAS operation. For additional information on the Mode-S operation of the KFS 578A, PS-578A, PS-550, CD 671C, or CTA-81A/CTA-81D control units refer to the MST 67A Installation Manual, ATA #34-54-01.

(1) The control unit allows the pilot to do the following:

(a) Select TCAS operating modes; control range, above/below altitude limits, and flight level versus relative alti-tude displays on the TCAS traffic display unit.

(b) Activate or deactivate the Mode S transponder.

(c) Select the ATC transponder identification code.

(d) Insert a special pattern identifier code (IDENT) into transponder replies to ground station interrogations.

(e) Initiate TCAS functional test.

(f) Select which transponder is active in a dual transponder system.

(g) Select altitude source.

(2) The KFS 578A, PS-578A, PS-550, and CD 671C illuminate “FAIL” on the display to indicate a transponder fail condition. The CTA-81A/CTA-81D illuminate a FAIL lamp to indicate a transpon-der fail condition.

(3) The Mode S/TCAS transponder control unit transfers control data to the Mode S transponder via an ARINC 429 data link. The Mode S/TCAS control unit FAIL lamp/display receives a failure status input from the Mode S transponder.

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(4) The KFS 578A, PS-578A, PS-550, and CD 671C control units re-quire 28 Vdc input power and 5 Vdc/Vac and 28 Vdc panel light-ing power from aircraft power sources (depending on unit and configuration).

(5) The CTA-81A/CTA-81D receives 115 Vac input power and 5 Vac 400 Hz panel lighting power from aircraft power sources.

(6) The KFS 578A, PS-578A, PS-550, CD 671C, and CTA-81A/CTA-81D control units are shown in Figure 26 KFS 578A Control Unit Controls, Figure 27 PS-578A Control Unit Controls, Figure 28 PS-550 Control Unit Controls, Figure 29 CD 671C Control Unit Controls, and Figure 30 CTA-81 ( ) Control Unit Controls re-spectively. Their functions are described in Table 64 Control Unit Control and Indicator Functions.

8. System Control and Indicator Functions

A. General

The primary manual controls used to operate the TCAS II are con-tained on the Mode S transponder/TCAS control unit.

NOTE: Control and indicator functions of the KFS 578A, PS-578A, PS-550, CD 671C, and CTA-81A/CTA-81D control units are described in this section.

TCAS advisory and/or operational status indications are shown by the TA/RA/VSI, RA/VSI, dedicated traffic display, cockpit audio sys-tem, and transponder/TCAS control unit.

Control of traffic advisory display range selection can be provided remotely from the transponder/TCAS control unit or locally via a front panel range selector switch, or switches, depending upon type of display unit used and display unit configuration strapping.

B. TCAS Input Power Control

Twenty eight volts dc or 115 Vac/400 Hz primary power, 26 Vac ref-erence power, and 5 Vac or Vdc or 28 Vdc background panel lighting power are applied to the TCAS system by closing aircraft circuit breakers.

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C. TCAS II Control Units

The KFS 578A, PS-578A, PS-550, CD 671C, and CTA-81A/CTA-81D control units are the master controls for both TCAS and the Mode S transpon-der. The CTA-81A/CTA-81D control unit is suitable for dual (Mode S) installations. The KFS 578A, PS-578A, PS-550, and CD 671C con-trol units are available in configurations suitable for dual (Mode S) or single (Mode S) installations.

Figure 26 KFS 578A Control Unit Controls(Typical)

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Figure 27 PS-578A Control Unit Controls(Typical)

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Figure 28 PS-550 Control Unit Controls(Typical)

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Figure 29 CD 671C Control Unit Controls(Typical)

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Figure 30 CTA-81 ( ) Control Unit Controls (Typical)

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Table 64 Control Unit Control and Indicator Functions (Sheet 1 of 7)

CONTROL/INDICATOR FUNCTION

1/2 Switch(KFS 578A/PS-578A/PS-550/CD 671C)ATC 1-2 Switch(CTA-81A/CTA-81D)

Selects one of two Mode S transponders to be under control of the control unit. The non-selected Mode S transponder is placed in either STANDBY or OFF mode.

ALT 1-2 Switch(CTA-81A)ALT ON / ALT OFF(CTA-81D)

Selects one of two Mode S transponder altitude source input ports.

Function Selector Switch: Rotary switch. Controls operating modes of Mode S transponder and requests TCAS operating modes.

TST/TEST Position Initiates TCAS and Mode S transponder functional self-test. If TCAS processor Functional Test Inhibit program pin is strapped, TCAS functional test is inhibited while aircraft is airborne. The TCAS flag displays “TCAS” on the RA/VSI display for the duration of the functional test (approximately 8 seconds). The traffic display displays "TEST." A test pattern appearing on the traffic display allows verification of each type of intruder symbol. During the first three seconds a lamp test is performed on all segments of the RA/VSI. If a failure is detected during functional test, the TCAS flag continues to display “TCAS”. Following the lamp test, a test fixed command is displayed until end of test.

SBY/STBY Position In-flight or on-the-ground places Mode S transponder and TCAS in STANDBY mode (TCAS sensitivity level #1). In STANDBY mode, transponder’s power is turned on but transponder does not transmit squitters or reply to interrogations. In STANDBY mode, all TCAS broadcast, surveillance, and tracking operations are disabled and the traffic display is blanked except for a "TCAS STBY" mode annunciation.

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Table 64 Control Unit Control and Indicator Functions (Sheet 2)


Function Selector Switch(Cont.)

ON Position (KFS 578A/PS-578A/ PS-550/CD 671C) ALT OFF Position (CTA-81A/CTA-81D)

In-Flight - Turns on Mode S transponder to fully active state and places TCAS in STANDBY mode (TCAS sensitivity level #1). Mode S transponder transmits squitters and replies to Mode S and ATCRBS Mode C and Mode A interrogations. The Mode S transponder’s reply to Mode C and Mode S interrogations does not contain an altitude report. The transponder’s reply to Mode A interrogations contains the ATC transponder code (normal Mode A reply). All TCAS broadcasts, surveillance, and tracking functions are disabled. Traffic display screen is blanked except for a "TCAS STBY" mode annunciation.

On-the-Ground - Mode S transponder squitters and replies to Mode S interrogations. Depending on Mode S transponder strapping, transponder replies or does not reply to ATCRBS Mode C and Mode A interrogations. The transponder’s reply to ATCRBS and Mode S interrogations does not contain an altitude report. The transponder’s reply to Mode A interrogations contains the ATC transponder code. TCAS is in STANDBY mode (TCAS sensitivity level #1). Traffic display screen is blanked except for a "TCAS STBY" annunciation.

ALT Position (KFS 578A/PS-578A/CD 671C) XPDR Position PS-550 ALT ON Position (CTA-81A/CTA-81D)

In-Flight - Same effect on Mode S transponder and TCAS as ON or ALT OFF position (in-flight) except Mode S transponder reports altitude in its Mode C and Mode S replies.

On-the-Ground - Same effect on Mode S transponder and TCAS as ON or ALT OFF position (on-the-ground) except transponder reports altitude in its Mode C and Mode S replies (if strapped to respond to Mode C when on-the-ground).

VFR Position Annunciates ATC and VFR, and displays stored ATC code. The ATC code can be changed by encoder knobs.

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TA Position (TA ONLY Mode)

In-Flight - Turns on Mode S transponder to fully active state and places TCAS in TA ONLY mode (traffic advisory only mode) (TCAS sensitivity level #2). Mode S transponder transmits squitters and replies fully to Mode S and ATCRBS Mode C and Mode A interrogations. TCAS broadcasts and performs all Mode S and ATCRBS surveillance and tracking functions. TCAS provides traffic displays for TA, proximity, and non-threat category aircraft but does not categorize or display any aircraft as an RA threat symbol. TCAS provides traffic advisory alerts but does not issue resolution advisory alerts (i.e. voice RA alerts or RA indications on the traffic display are not generated). A TA ONLY annunciation appears on the traffic display.

On-the-Ground - Mode S transponder squitters and replies fully to Mode S interrogations. Depending on transponder strapping, transponder replies fully or does not reply to ATCRBS Mode C and Mode A interrogations. Depending on TCAS strapping, TCAS either goes into TA ONLY mode or STANDBY mode (traffic display screen is blanked except a "TCAS STBY" mode annunciation appears on traffic display).

TA/RA Position In-Flight - Turns on Mode S transponder to fully active state. If own aircraft is above 1000 feet AGL, TCAS enters sensitivity level #4 through #7 dependent on own aircraft altitude. The Mode S transponder transmits squitters and replies fully to Mode S and ATCRBS Mode C and Mode A interrogations. TCAS broadcasts and performs all Mode S and ATCRBS surveillance and tracking functions. TCAS provides traffic displays for RA, TA, Proximity, and non-threat category aircraft, issues RA and TA alerts, and issues resolution advisories on the TA/RA/VSI or RA/VSI. A TA/RA annunciation appears on the PPI or dedicated traffic display. A Mode annunciation is not provided on the TA/RA/VSI for TA/RA mode.

NOTE: If own aircraft is below 1000 feet AGL, TCAS defaults to TA ONLY mode.

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TA/RA Position (Cont.)

On-the Ground - Mode S transponder squitters and replies fully to Mode S interrogations. Depending on transponder strapping, transponder replies fully or does not reply to ATCRBS Mode C and Mode A interrogations or Mode S interrogations. TCAS defaults to TA ONLY mode (TCAS sensitivity level #2) and functions as described for the TA position (on-the-ground) of the Function Selector Switch in this table.

MODE Pushbutton (PS-550)(Note 8)

ATC Mode - (default mode) allows entry of the four-digit ATC code.FID Mode - allows entry of alpha numeric flight identification and annunciates “FID” on display.TFC Mode (Collins TDR-94D) - selects traffic display operating mode: pop-up (AUTO) or full-time display (ON) and annunciates on display.FL Mode (Honeywell MST 67A) - allows selection of relative (REL) or absolute (ABS) altitude to be displayed.ADC Mode - selects which air data computer is used by TCAS and annunciates “ADC” and “1” or “2” on display.

FL Pushbutton Switch Spring-loaded pushbutton switch. When pressed and released, replaces relative altitude annunciations for intruder aircraft on traffic display with flight-level altitude annunciations for a period of 15 seconds. During the 15 second period, own aircraft flight-level altitude also appears on the traffic display. After 15 seconds, own aircraft flight-level altitude disappears from display and intruder aircraft altitude annunciations revert back to relative altitude annunciations.If during the 15 second period after the FL switch is pressed and released, a new RA or TA category aircraft is detected by TCAS, the 15 second flight-level display is disabled and relative altitudes reappear.

TCAS RANGE Switch Rotary switch, clockwise increases range and counter clockwise decreases range. Selects 3 - 40 nautical mile range scaling for the traffic display. The selected display scaling is annunciated as 40 nmi, 20 nmi, 15 nmi, 10 nmi, 5 nmi, 3 nmi, or 1 nmi on the traffic display. Specific ranges and range groups available are defined by the software version in use.

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FID Pushbutton PS-578A

ATC Mode - (default mode) allows entry of the four-digit ATC code.FID Mode - allows entry of alpha numeric flight identi-fication and annunciates “FID” on display.

ABOVE/NORM/BELOW Switch:(Arrow symbols on(KFS 578A/PS-578A/PS-550/CD 671C)

Three position toggle switch. Selects relative altitude display limits for non-threat category aircraft (open-white diamond symbols) on the traffic display.

ABOVE Position Selects display of non-threat aircraft up to +8700 feet (+9000 feet MOPS Change 7) above own aircraft and down to -2700 feet below own aircraft. ABOVE is annunciated on screen of traffic display. An up carrot is shown on the control unit.

NORM Position Selects display of non-threat aircraft up to 2700 feet above own aircraft and down to 2700 feet below own aircraft on traffic display. An up/down carrot is shown on the control unit.

BELOW Position Selects display of non-threat aircraft down to -8700 feet (-9000 feet MOPS Change 7) below own aircraft and up to +2700 feet above own aircraft. BELOW is annunciated on screen of traffic display. A down carrot is shown on the control unit.

IDENT Pushbutton:(KFS 578A/PS-578A/CD 671C)SEL ID Pushbutton (PS-550)ATC IDENTCTA-81A/CTA-81D)

When this switch is pressed and released, a Special ATC IDENT Position Identifier (SPI) is inserted temporarily into transponder Mode S replies to interrogations from ground stations. The SPI pulse is not used by TCAS.

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Code Select Knobs Allows selection of transponder identification code. The transponder inserts this code into replies to Mode A interrogations and Mode S ATC identification requests from ground stations. The ATC IDENT code is not used by TCAS.

ATC IDENT Code Display Displays transponder ATC identification code selected by the Code Select Knobs and annunciates which xponder is selected by the ATC 1-2 Switch.

FAIL(KFS 578A/PS-578A/PS-550/CD 671C)

Illuminates on the display.

FAIL (KFS 578A, CD 671C) Illuminates on the display for failure of the selected Mode S transponder.

CP FAIL (PS-578A, PS-550) Illuminates on the display for internal control panel fail modes.

XPDR FAIL (PS-578A,PS-550) Illuminates on the display for failure of the selected Mode S transponder.

ATC FAIL Lamp CTA-81A/D

Illuminates (amber) for failure of the selected Mode S transponder.

T/Wx (CD 671C) Three position rotary switch used to control traffic advisories displayed on a weather radar indicator. The annunciations appearing on the weather radar display are "WX" for weather only; "TCAS" for TCAS only; "T/WX" for TCAS and weather information.

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NOTE 1: TCAS operating modes are requested from the transponder/TCAS control unit [i.e. TA/RA mode is requested by rotating function selector switch to TA/RA]. The TCAS processor may or may not enter the requested mode dependent on prevailing conditions. For example: If TA/RA mode is requested from the control unit and own aircraft is below 1000 feet AGL, TCAS automatically defaults to TA ONLY mode (TCAS sensitivity level #2) regardless of the TA/RA mode request from the panel.

NOTE 2: TCAS can be strapped to display either all traffic all the time or only when a TA or RA is present.

NOTE 3: Holding the FL switch pressed for longer than 15 seconds will not display flight level altitudes for any longer than 15 seconds.

NOTE 4: The range at which resolution or traffic advisories are generated by TCAS is unaffected by the TCAS RANGE switch.

NOTE 5: The presence of intruder aircraft that are categorized as RA (resolution advisory threats) or TA (traffic advisories) that are beyond the selected display range is indicated by 1/2 target symbols at edge of screen. The position of the 1/2 symbol represents approximate bearing of the intruder. The 1/2 symbol color and shape represents whether the off-scale intruder is an RA (1/2 red square for off-scale RA) or TA (1/2 yellow circle for off-scale TA). When this occurs, the aircraft symbol can be displayed by increasing the selected range on the TCAS RANGE switch.

NOTE 6: RA (threat), TA (traffic advisory), and proximity category aircraft displays are unaffected by the ABOVE/NORM/BELOW switch. (RA and TA aircraft within ±8700 feet (±9000 feet MOPS Change 7) of own aircraft are displayed regardless of the ABOVE/NORM/BELOW switch position. Proximity category aircraft are always within ±1200 feet altitude of own aircraft.)

NOTE 7: TCAS RANGE switch is not provided on all versions of the KFS 578A, CD 671C, or CTA-81A/CTA-81D. When a TA/RA/VSI or dedicated traffic display having optional range selectors is used, range selection is made at the traffic display. Other versions have range selections to 40 nautical miles.

NOTE 8: The MODE pushbutton at the right center of unit sets the unit in ATC, FID, ADC, TFC, or FL operating mode and annunciates on the LCD panel.

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D. GC 362A TCAS Graphics Processor

The GC 362A TCAS Graphics Computer is a remote mounted graphics pro-cessor that converts high speed ARINC 429 from an ARINC 735 compat-ible TCAS processor to display on the Honeywell RDS 81, RDS 82, RDS 84, RDS 86, RDR 2000, and RDR 2100 color weather radar systems, cer-tain Honeywell Primus series radar systems, and Collins WXR270 se-ries radar system.

When interfaced to a CAS 67A TCAS II system, the GC 362A will display traffic information on the radar indicator. The unit has three dis-play modes that may be controlled by an external pushbutton or through 429 control via external control unit. This option is se-lected by the state of the “mode select” pin (P3621-10).

Option 1: In the Radar/TCAS Overlay mode, the weather information is overlaid with the TCAS information.

Option 2: In TCAS Only mode, a full time 360° TCAS traffic display is presented and the weather information is not displayed.

Option 3: In the Radar Display mode, the radar display is in the normal weather display mode unless a TA or RA is detected by the TCAS system. During detection, the display will switch to either TCAS Only display mode or the Radar/TCAS Overlay display mode for the duration of the intruder presence, then return to the Radar Dis-play mode. The choice of the switched mode is controlled by the selected state of the “POP-UP” external strap.

External red, green, and blue inputs are provided for use with a NAV graphics computer such as the GC 360A or GC 361A. This allows nav-igation graphics to be presented from various navigation systems.

NOTE: The CAS 67A TCAS II Pilot’s Guide, p/n 006-08499-(), de-scribes the radar/TCAS display operation in detail.

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E. TA/RA/VSI

The TA/RA/VSI displays resolution advisory maneuvering information to the pilot during threat conditions. The TA/RA/VSI also provides a display of airspace traffic conditions within the traffic display range and altitude limits.

(1) Resolution Advisories

Resolution advisories can be corrective or preventive and pos-itive or negative.

A corrective advisory requires a vertical maneuver and is al-ways displayed with red and green arcs. The red arc repre-sents the vertical speed rates that are not acceptable in the presence of the RA and the green arc represents the vertical speeds that should be flown during a corrective advisory. A preventive advisory requires no maneuver and is represented with only a red arc. Refer to CAS 67A TCAS II Pilot’s Guide, p/n 006-08499-().

The limits of the red arc are provided to the TA/RA/VSI from the TCAS via the 429 bus. The limits of the green arc are not provided from TCAS. The green arc will be immediately adja-cent to the red arc and have a width approximately equal to the space between 1500 ft/min and 2000 ft/min.

It is possible to display two red arcs simultaneously with an RA such as “don’t climb greater than 1000 feet“ and “don’t descend greater than 2000 feet.” Since only one action can be corrective, the green arc will be immediately adjacent to the red arc representing the corrective advisory. If both actions are preventive then only the red arcs are present.

(2) Traffic Display

The traffic display provides the following information:

• Standard symbology consisting of own aircraft symbol and a two mile range ring marker.

• Resolution advisory, traffic advisory, proximity, and non-threat category aircraft symbols that depict range, bear-ing (if tracking is occurring on a directional antenna), and altitude (if intruder is reporting altitude).

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• Text message annunciations of TAs and RAs that cannot be displayed by a symbol because bearing is not available, of TAs and RAs that are outside the range scaling of the traf-fic display, of display operating modes, and of fail con-ditions.

NOTE: The CAS 67A TCAS II Pilot’s Guide, p/n 006-08499-(), de-scribes the TA/RA/VSI operation in detail.

F. RA/VSI

The RA/VSI displays resolution advisories similar to the TA/RA/VSI but does not provide a traffic display.

The RA/VSI provides resolution advisories that indicate vertical speeds to be avoided in order to maintain or achieve safe vertical separation.

An electromechanical pointer and vertical speed scale, which are standard VSI features, indicate the present vertical speed of own aircraft. The RA/VSI includes a microprocessor based control unit and curved red and green eyebrow lamp segments around the periphery of the vertical speed scale.

Maneuvering resolution advisories are annunciated on the RA/VSI by illuminating an associated number of the red lamp segments to indi-cate he vertical speed rates to be avoided and green arcs to indicate the vertical speeds that should be flown during an advisory. Refer to the CAS 67A TCAS II Pilot’s Guide, p/n 006-08499-(),

The VSI used for TCAS applications is also equipped with flags that indicate TCAS operating conditions.

The Honeywell manufactured RA/VSI receives resolution advisory and flag control data from the TCAS processor via a high-speed ARINC 429 data link.

RA/VSI display units are used as the resolution advisory display when TCAS traffic displays are provided on another display such as a radar/TCAS display or dedicated TCAS traffic display.

NOTE: The CAS 67A TCAS II Pilot’s Guide, p/n 006-08499-(), de-scribes the RA/VSI operation in detail.

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G. Weather Radar/TCAS Display

The radar/TCAS display provides its normal separate weather radar display and can be manually controlled to present a separate TCAS traffic display or a combined weather radar/TCAS presentation.

The radar/TCAS display integration into the TCAS II system is de-scribed in separate manuals listed in Table 49 Related Publications

NOTE: The CAS 67A TCAS II Pilot’s Guide, p/n 006-08499-(), de-scribes the radar/TCAS display operation in detail.

H. Optional Aural/Lamp Advisory Outputs

Optional aural and lamp traffic advisory and resolution advisory outputs are available and may be activated by connecting external tone generators and/or indicator lamps to the appropriate rear con-nector pins on the TCAS processor.

The aural advisory outputs are used to generate tones that accompany corrective, preventive, and traffic advisories generated by the TCAS processor. The activated aural advisory discrete output is gener-ated for a 1.0 ±0.2 second period. When the aural advisory discrete outputs are used in an installation, the audio output program should be configured (by configuration module) to provide a 1.0 ±0.2 second delay of the synthesized voice output in order to be properly phased with the aural advisories.

The lamp advisory outputs can be used to operate annunciator lights that identify the advisory as a corrective, preventive, or traffic advisory. The activated output remains on for the duration of the advisory unless canceled.

I. Audio Message Alerts

Audio message alerts provided by TCAS on the cockpit audio system are described in the CAS 67A TCAS II Pilot’s Guide, p/n 006-08499-(), revision 2 or later.

J. TCAS Processor and Mode S Transponder Fault Indicators

These panel indicators provide a fault isolation maintenance “aid” in failure situations where the traffic advisory display subsystem has failed and is incapable if displaying TCAS failure annuncia-tions. Refer to FAULT ISOLATION and INSTALLATION AND MAINTENANCE sections of this manual for details.

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K. Optional Advisory Cancel Switch

This momentary switch cancels active advisory alert conditions.

L. Range Selection and Range Rings

Depending upon TCAS configuration, traffic advisory display range selection is controlled either externally, via data input to the display on the ARINC 429 bus, or internally, using a front panel selector switch (weather/traffic display) or optional front panel pushbutton switches (TA/RA/VSI or dedicated traffic display). Range rings displayed are a function of range selected, regardless of whether range selection is made remotely or locally.

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Figure 31 GC 362A TCAS Graphics Processor, TCAS and Radar Displays

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Figure 32 Collins IND270 Indicator, TCAS and Radar Displays

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Figure 33 Honeywell WI650 Radar Indicator, TCAS and Radar Displays

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Figure 34 Honeywell P90 Radar Indicator, TCAS and Radar Displays


FAULT ISOLATION

1. General

Fault isolation is the process of locating the source of a TCAS failure at the LRU or aircraft wiring level. Fault isolation for TCAS involves observation of TCAS failure indicators and use of functional self-test. After the fault has been isolated, the appropriate aircraft repair proce-dures are used to correct the problem. See the INSTALLATION AND MAINTE-NANCE section for details.

TCAS failures can be indicated by failure annunciations on the radar/TCAS display or dedicated traffic unit display, an electromechanical fail flag on the RA/VSI unit, and failure indicator lamps on the front panels of the TCAS LRU components. TCAS failures are detected and failures indicated through full-time TCAS built-in test equipment monitoring or manually ini-tiated TCAS self-test.

TCAS faults and fault codes can be viewed on the left side of the TCAS processor (as viewed from the front) or on a diagnostic computer with the appropriate diagnostic programs. Real-time failures can be observed and fault memory can be searched for recurring problems by the diagnostic com-puter. TCAS faults can be recorded and analyzed using special recording programs with dedicated computer equipment.

For these reasons, it is very important that the TCAS installation con-tains accessible diagnostic and recorder connections. Additionally, the diagnostic computer is necessary for system checkout and installation fault isolation.

2. Fault Isolation

Fault isolation is typically performed on the ground, as a result of fail-ures indicated during post-installation or preflight testing, or malfunc-tions that were observed during flight operation.

A. General

(1) The TCAS processor is capable of detecting any malfunctions of TCAS components that degrade or prevent possible collision avoidance protection. A failure of the TCAS system during normal operation results in the following actions by the TCAS processor:

• Provides an indication to flight crew that an abnormal con-dition exists. Typically, a yellow "TCAS" flag will an-nunciate on the traffic display.

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• Causes any Mode S transmissions that report own aircraft status to indicate that own aircraft has no on-board res-olution advisory capability.

• Prevents interrogations by own aircraft TCAS.

• Deactivates the normal TCAS display functions.

NOTE: Refer to the pilot’s guide for specific failure in-dications that will appear on RA/VSI, TA/RA/VSI, dedicated TCAS display, etc.

(2) There are three methods for initiating and observing function-al self-test results or failure causes of the Mode S/TCAS sys-tem:

• The first method is to initiate self-test at the Mode S/TCAS control unit. Detected failures are annunciated on the traffic display, with the exception of the IVA-81A/IVA-81C/IVA-81D TA/RA/VSI.

• The second method is to observe self-test fault codes an-nunciated on the TPU side-panel LED indicator (located in-side the cover of the processor).

• The third method is to use a diagnostic computer program to view faults in real-time or to recover faults stored in fault memory.

(3) Before performing TCAS system self-test, ensure that the fol-lowing aircraft systems are powered and operating with no failure flags on the appropriate cockpit instruments:

• Mode S transponder system

• Encoding Altitude Sources (Air Data Systems)

• Radio Altimeter Systems

• Attitude (Vertical Gyro) Systems

• Heading (Compass) Systems

(4) If the attitude and heading data supplied to the TCAS system are from an AHRS, IRS, or INS they must be aligned and be in an operational mode.

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B. Fault Isolation Using the Mode S/TCAS Control Unit

NOTE: If a TCAS/Weather Radar display is used as the traffic display, the radar system should be in SBY or TST before the next step for about 5 seconds to allow the display to warm up.

(1) In a dual Mode S-equipped aircraft, set the transponder select switch to #1 position to test the number one transponder. Se-lect the test mode, observe for the fail annunciation.

(2) If there are no malfunctions, the test sequence will be as follows:

(a) A test pattern appears on the traffic display to allow verification of each type of intruder symbol. The traf-fic display shows the TCAS traffic test pattern and "TEST" is displayed. See Figure 1001 TCAS Test Pattern.

Figure 1001 TCAS Test Pattern

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(b) For aircraft equipped with RA/VSI:

1 During the first few seconds of the test, the RA/VSI red and green lamps (climb/descend indica-tors) illuminate sequentially. The TCAS flag is in view throughout the test period.

2 After the RA/VSI sequential lamp test, the red and green climb/descend lamps display a fixed test command representing a typical resolution adviso-ry throughout the remainder of the test sequence.

NOTE: Loss of valid vertical speed input will cause the VSI flag to appear on the RA/VSI. If a TA/RA/VSI is used, the legend “VSI” will ap-pear on the display. A TCAS processor fail-ure will cause the TCAS flag to appear on the RA/VSI, and TCAS to be displayed on the TA/RA/VSI.

(c) For aircraft equipped with TA/RA/VSI:

The TA/RA/VSI indicates a fixed Resolution Advisory and the traffic symbol test pattern. A “TEST” is indicated.

(d) For aircraft equipped with a radar/TCAS or dedicated display:

Both displays indicate the TCAS display test pattern and “TEST” is displayed.

(e) At the successful conclusion of self-test, the TCAS pro-cessor outputs onto the audio bus the synthesized voice message, "TCAS SYSTEM TEST OK."

(3) If there is a failure detected during self-test, the voice message output from the TCAS processor is, "TCAS SYSTEM TEST FAIL." The radar/TCAS display or dedicated display will an-nunciate the failed system component(s).

Possible traffic display fault annunciations are as follows:

• TCAS PROCESSOR•

• UPPER ANTENNA

• LOWER ANTENNA

• RADIO ALT #1

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• RADIO ALT #2•

• RADIO ALT #1 and #2

• XPNDR DATA BUS #1

• XPNDR DATA BUS #2

• TRAFFIC DISPLAY

• RA DISPLAY #1

• RA DISPLAY #2

• RA DISPLAY #1 AND #2

• SELECTED XPNDR

• XPNDR TOP ANTENNA

• XPNDR BOTTOM ANTENNA

• XPNDR CONTROL DATA

• XPNDR ALT DATA #1 and #2

• #1 XPNDR ALT DATA

• #2 XPNDR ALT DATA

• ATTITUDE

• HEADING

• GP RAM

• NO TCAS 429 DATA

• TCAS FAIL

(4) If the self-test results were not successful, perform the fol-lowing:

(a) If a TCAS/Weather Radar display is used, check and record fault annunciations. Refer to Table 1001 TCAS/Weather Radar Display Fault Annunciations for fault isolation procedures.

(b) In non-TCAS/Weather Radar display aircraft, view the LED on the left side of the TPU 67A unit for further clarification of problem, refer to Table 1003 TCAS Pro-cessor Fault Codes.

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(c) Use a diagnostic computer to view the fault conditions of the TCAS Processor.

CAUTION: REMOVE POWER PRIOR TO REPLACING A TCAS SYSTEM COMPONENT. DAMAGE TO THE EQUIPMENT MAY OTH-ERWISE RESULT.

(5) In a dual Mode S-equipped aircraft, set the transponder select switch to #2 position to test the number two transponder. Se-lect the test mode, observe any fail annunciations.

C. Fault Isolation Using TCAS Processor LED Fault Codes

The TCAS processor fault codes are displayed on an LED indicator located at top center on the left side of the TCAS processor (inside the top cover).

(1) Normally, with no fault, the seven LED segments light one at a time in a figure eight pattern. The decimal also blinks.

(2) Typically, the fault codes shown in Table 1003 TCAS Processor Fault Codes are associated with external inputs to the TCAS processor. Use these fault codes for fault isolation of the TCAS system in the aircraft.

FAULT ANNUNCIATION FAULT ISOLATION

#1 ALT DATA#2 ALT DATAALT DATA #1 and #2

Check altitude source and associated wiring.Check proper altitude type is selected.

CONTROL DATA Check TCAS control unit.

TCAS PROCESSOR Replace TCAS processor.

UPPER ANTENNALOWER ANTENNA

Check antenna and associated wiring. Use diagnostic computer to determine failed antenna connection.

ATTITUDEHEADING

Check attitude & heading sources and associated wiring. Check proper attitude type is selected.

TCAS FAIL/NO TCASTRAFFIC DISPLAY

Check power and associated wiring. Replace traffic display unit.

TA DISPLAY #2TA DISPLAY #1 and #2

Check vertical speed source (on TA/RA/VSI), power, and associated wiring. Replace traffic display unit.

RADIO ALT #1 or #2 Check selected radio altimeter source. Radio altimeter #2 will be indicated on single radio altimeter installations. Check proper altitude type selected.

Table 1001 TCAS/Weather Radar Display Fault Annunciations

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The following legend and abbreviations apply to Table 1003 TCAS Processor Fault Codes.

F-UUU-xx - OS_DEFAULT_INTERRUPT_SERVICE_SW_EXCEPT - 80960KB Unassigned Interrupt, xx is the vector of the undefined interrupt.

SPM - System Performance MonitoringCS - Cold StartWS - Warm Start (power interruption < 1 sec)FT - Functional Test

The fault codes listed apply to -0101/-0201/-1111/-1211 ex-cept as follows:F-85-00 - applies to -1111/-1211 onlyF-85-01 - applies to -1111/-1211 onlyF-89-37 - applies to -1111/-1211 onlyF-90-03 - applies to -1111/-1211 only

NOTE: Additional fault classes and codes may be indicat-ed. Typically, any codes not shown in Table 1003 TCAS Processor Fault Codes indicate an internal TCAS processor failure. A single letter code, as shown below, indicates a catastrophic internal TCAS processor failure. All fault codes and unit serial number should be recorded to share with Honeywell Product Support.

NOTE: Fault codes that indicate problems with the antenna or antenna cables will require additional trouble-shooting to determine the cause of the fault. The DIAGNOSTIC APPENDICES list the necessary test equipment and recommended procedures for trouble-shooting the antenna system.

CODE FAILURE

A RAM address line stuck low

d RAM address line stuck high

F CPU reserved RAM data test

b Program memory boot block checksum failure

C CPU Instruction

H Program memory main block checksum failure

Table 1002 Catastrophic Single Letter Failure Codes

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SYMBOL CLASS CODE FAILURE

F 01 01 RAM data (SPM) - RAM on computer board not reliable

F 01 02 RAM data (CS, WS, FT) - RAM on computer board not reliable

F 01 05 Voice EPROM - Xilinx/Voice memory EPROM on I/O board failed checksum

F 01 07 ATAN EPROM - deleted with TPU67A2.10 release - part no longer on 8876 computer bd.

F 01 08 EEPROM - Factory Cal and Fault Log EEPROM on computer bd. fails checksum

F 01 09 POWER SUPPLY +3.3 V - voltage divider on I/O board reading out of spec.

F 01 10 POWER SUPPLY +6 V - voltage divider on I/O board reading out of spec.

F 01 11 POWER SUPPLY +10.5 V - voltage divider on I/O board reading out of spec.

F 01 12 POWER SUPPLY -10.5 V - voltage divider on I/O board reading out of spec.



F 01 15 POWER SUPPLY -250 V - voltage divider on I/O board reading out of spec.

F 01 18 Transmit Power - TX power read on I/O board is reading out of spec.

F 01 19 Power Supply +2.5V ref. / 5 V - voltage divider on I/O board reading out of spec.

F 01 20 429 TA/RA #1 Transmit - wrap around receiver not receiving transmitted 429 data on computer bd.

F 01 21 429 TA/RA #2 Transmit - wrap around receiver not receiving transmitted 429 data on computer bd.

F 01 22 429 XPNDR #1 Transmit - wrap around receiver not receiving transmitted 429 data on computer bd.

F 01 23 429 XPNDR #2 Transmit - wrap around receiver not receiving transmitted 429 data on computer bd.

F 01 24 429 RA #1 Transmit - wrap around receiver not receiving transmitted 429 data on computer bd.

F 01 25 429 RA #2 Transmit - wrap around receiver not receiving transmitted 429 data on computer bd.

F 02 01 Top Antenna - matching resistor on I/O bd not correct or 50 ohm loads not connected

F 02 02 Bottom Antenna - matching resistor on I/O bd not correct or 50 ohm loads not connected

F 02 04 Roll - 429 (computer bd) or Synchro (I/O bd) data invalid based on selected source

F 02 05 Pitch - 429 (computer bd) or Synchro (I/O bd) data invalid based on selected source

F 02 06 Heading (SPM) - 429 (computer bd) or Synchro (I/O bd) data invalid based on selected source

Table 1003 TCAS Processor Fault Codes

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F 02 07 Heading (CS) - 429 (computer bd) or Synchro (I/O bd) data invalid based on selected source

F 02 08 Radio Altimeter (SPM) - 429 (computer bd) or Analog (I/O bd) data invalid based on selected source

F 02 09 Radio Altimeter (CS) - 429 (computer bd) or Analog (I/O bd) data invalid based on selected source

F 02 11 RA Display Integrity - One display valid line to RA #1 or #2 must be valid (I/O bd)

F 02 12 TA Display Integrity - One display valid line to TA #1 or #2 must be valid (I/O bd)

F 02 13 XPNDR #1 failure - 429 (computer bd) data invalid

F 02 14 XPNDR #2 failure - 429 (computer bd) data invalid

F 02 15 XPNDR #1 - Control Panel failure - 429 (computer bd) data invalid, specifically label 013, 015, and 016

F 02 16 XPNDR #1 - Altitude failure - 429 (computer bd) data invalid, specifically label 203

F 02 17 XPNDR #1 - Gillham Compare failure - must be strapped for gillham compare to be done by TCAS in the config. module and have gillham inputs from port 1 and 2 differ by more than 500 feet

F 02 18 XPNDR #2 - Control Panel failure - 429 (computer bd) data invalid, specifically label 013, 015, and 016

F 02 19 XPNDR #2 - Altitude failure - 429 (computer bd) data invalid, specifically label 203

F 02 20 XPNDR #2 - Gillham Compare failure - must be strapped for gillham compare to be done by TCAS in the config. module and have gillham inputs from port 1 and 2 differ by more than 500 feet

F 04 01 VIDEO Ram data (CS, WS, FT) - Ram on video bd. not reliable

F 04 02 VIDEO Ram address stuck low - video bd.

F 04 03 VIDEO Ram address stuck high - video bd.

F 04 04 VIDEO Suppression Latch Clear Error - Video bd suppression latch will not clear

F 04 05 VIDEO Suppression Latch Mode C Error - Video bd suppression latch will not set

F 04 06 VIDEO Suppression Latch Mode S Error - Video bd suppression latch will not set

F 04 07 VIDEO Set End of Interrogation (EOI) - EOI line on video bd will not set

F 04 08 VIDEO Clear EOI - EOI line on video bd will not clear

F 04 09 VIDEO Top/Bottom Switch - Top Error video bd.

F 04 10 VIDEO Top/Bottom Switch - Bottom Error video bd.

F 04 11 VIDEO MS_ATCX True error - Mode S/Mode C bit, ATCX bit video bd.


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F 04 12 VIDEO MS_ATCX False error - Mode S/Mode C bit, ATCX bit video bd.

F 04 13 VIDEO SQ_MODEX True error - Squitter Mode bit, video bd.

F 04 14 VIDEO SQ_MODEX False error - Squitter Mode bit, video bd.

F 04 15 VIDEO EXT_CNTL True error - External control bit on video bd.

F 04 16 VIDEO EXT_CNTL False error - External control bit on video bd.

F 04 17 VIDEO MD3X Mode C error - MD3X bit on video bd

F 04 18 VIDEO MD3X Mode S error - MD3X bit on video bd

F 10 XX Software task duration failure - XX is !MultiTask task number (software problem)

F 20 XX Software task frequency failure - XX is !MultiTask task number (software problem)

F 81 00 Bite Ram Data Exception - software error

F 81 01 Bite Task in Progress - BITE test not completed before starting again, software error

F 81 02 Bite Software Monitor - Invalid MT! task number during SW monitor test, software error

F 81 03 TPU Initialization Timeout Error - Initialization taking too long, bad cable cal. at startup causes this failure, see also F-89-33 through F-89-36. Additionally, previous releases to 01/10 had this problem due to high suppression bus activity during cal.

F 82 00 MT_RELMEM_ERROR-MT! memory error, software error

F 82 01 MT_PERIOD_ERROR-MT! periodic event error, software error

F 82 02 MT_TASK_ERROR-MT! task initialization error, software error. Also have received in the factory when 429 inputs on xpndr channels on 8876 computer boards.

F 82 03 MT_RETURN_ERROR - Return from MT! error, software error

F 82 04 MT_GENERAL_ERROR - Invalid MT! task number, software error

F 82 05 CRIT_REG_ERROR - Incorrect critical region type requested, software error

F 82 06 MT_INVALID_SLOT - Invalid task slot number, software error

F 82 07 PWR_BAD_PDR_RAM_CS_ - RAM copy of Power Down Record has bad checksum

F 82 08 PWR_BAD_BITE_CS_- BITE fault record has bad checksum

F 82 09 PWR_BAD_VIDEO_CS - Video warm start record has bad checksum

F 82 10 BAD_EEPROM_WRITE - Error writing to EEPROM

F 84 01 INVALID_RANGE_EXCEPTION - software error

F 84 02 DMA_422_TIMEOUT_EXCEPTION - DMA interrupt does not occur or is not seen at end of 422 transmission

F 84 03 INVALID_DISPLAY_TACODE - software error


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F 85 00 OS_DEFAULT_FAULT_SERVICE_SW_EXCEPT - An internal 80960 KB fault - possible software problem - Fault LED will display F-FAL-tt-ss-aaaaaaaa where tt is fault type, ss is fault sub-type, and aaaaaaaa is the address where the fault occurred

F 85 01 OS_DEFAULT_INTERRUPT_SERVICE_SW_EXCEPT - Interrupt without assigned handler executed - Fault LED will display F-UUU-xx where xx is the vector of the undefined interrupt

F 85 02 OS_DEFAULT_SPT_SERVICE_SW_EXCEPT - software error

F 85 03 OS_RETURN_FROM_MAIN_SW_EXCEPT - software error

F 85 04 OS_DMA_1030_SW_EXCEPT - 1030 Receive DMA buffer size exceeded, DMA on computer bd or software error

F 85 05 RECEIVE COORDINATION_QUEUE_OVERRUN - software error

F 85 06 DMA VOICE TIMEOUT - DMA interrupt does not occur or is not seen at end of voice message

F 85 07 RECEIVE NON-COORDINATION_QUEUE_OVERRUN - software error

F 85 08 Configuration Module Compatibility Code - Cfg module needs to be reprogrammed, ensure that ATE enable discrete input is disabled unless interface is necessary to chamber or RGS

F 85 09 Configuration Module Checksum Failure - Cfg module needs to be reprogrammed, ensure that ATE enable discrete input is disabled unless interface is necessary to chamber or RGS

F 85 50 I/O Voice Mailbox Exception - !Multitask mailbox system not working, software error

F 85 51 I/O Data Recorder Mailbox Exception - !Multitask mailbox system not working, software error

F 85 52 BITE Failure Mailbox Exception - !Multitask mailbox system not working, software error

F 85 53 BITE LED Write Mailbox Exception - !Multitask mailbox system not working, software error

F 85 54 OS 429 Mailbox Exception - !Multitask mailbox system not working, software error

F 85 55 OS CPROC EXEC Mailbox Exception - !Multitask mailbox system not working, software error

F 85 56 OS CFG MODULE Mailbox Exception - !Multitask mailbox system not working, software error

F 85 57 VIDEO CFG MODULE Mailbox Exception - !Multitask mailbox system not working, software error

F 86 00 SURV: SHOULD _NOT_BE_HERE - software error

F 86 01 SURV: NOT_ADDED_TO_HASH - too many Mode S address squitters which have a common bit pattern

F 86 02 SURV: BAD_PARAMETER - software error


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F 86 03 SURV: IDENTICAL_TIMESTAMPS - TISI did not increment timestamps, software problem

F 87 01 TRACK_TOO_FEW_INITIAL - software error

F 87 02 TRACK_ITF_NUMS_OVRFLW - software error

F 88 00 UTIL_INVALID_MODES_UF0_FIELD - software error

F 88 01 UTIL_INVALID_MODES_UF16_FIELD - software error

F 88 02 UTIL_INVALID_MODES_DF0_FIELD - software error

F 88 03 UTIL_INVALID_MODES_DF11_FIELD - software error

F 88 04 UTIL_INVALID_MODES_MSG_TYPE - software error

F 89 01 MODES_EOI_STUCK_EXCEPTION - EOI should transition at end of interrogation on video bd

F 89 03 MODES_PROC_REPLIES2_EXCEPTION - software error

F 89 04 MODES_INTERROGATE1_EXCEPTION - software error

F 89 07 MODEC_TRANSMIT_EXCEPTION - software error

F 89 08 MODEC_PROCESS_RX_EXCEPTION - software error

F 89 09 MODEC_BUFFER_FULL_EXCEPTION - too many valid Mode C replies received for buffer to be processed by Surveillance

F 89 10 MODEC_INTERROGATE_EXCEPTION - software error

F 89 11 SWAP_SWITCH_EXCEPTION - software error

F 89 12 PHASE_SHIFT_EXCEPTION - software error

F 89 13 RANGE_COUNTER1_EXCEPTION - software error

F 89 14 RANGE_COUNTER2_EXCEPTION - software error

F 89 15 WS_SEQUENCE_TYPE_EXCEPTION - software error

F 89 16 VPSDATA_FIND_NULL_EXCEPTION1 - software error

F 89 18 VPSDATA_CABLE_CAL_EXCEPTION - software error

F 89 23 MODEC_SUPPRESSION EXCEPTION - glitch on suppression bus can cause problem

F 89 25 MODES_SUPPRESSION EXCEPTION - glitch on suppression bus can cause problem

F 89 27 MODEC_EOI_STUCK_EXCEPTION - EOI should transition at end of interrogation on video bd

F 89 28 DMA_COUNT1_EXCEPTION - too many replies or malfunctioning DMA operation

F 89 29 DMA_COUNT2_EXCEPTION - too many replies or malfunctioning DMA operation

F 89 30 VILIMIT_DEFAULT_EXCEPTION - software error

F 89 31 EEPROM write of video data failed - EEPROM on computer bd not writable

F 89 32 EEPROM read of video data failed - EEPROM on computer bd not readable

F 89 33 VPSDATA_DYN_RANGE_T_EXCEPTION - cable calibration failure on top antenna caused by dynamic range too low (improperly aligned)


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F 89 34 VPSDATA_ZERO_COUNTS_T_EXCEPTION - cable calibration failure on top antenna caused by too many zero counts (improperly aligned)

F 89 35 VPSDATA_DYN_RANGE_B_EXCEPTION - cable calibration failure on bottom antenna caused by dynamic range too low (improperly aligned)

F 89 36 VPSDATA_ZERO_COUNTS_B_EXCEPTION - cable calibration failure on bottom antenna caused by too many zero counts (improperly aligned)

F 89 37 INCORRECT_INEQUALITY_SELECTION - incorrect interference limiting inequality selected, software error

F 90 00 COORDINATION UNLOCK TIMEOUT - in coordination lock too long, software error

F 90 01 COORDINATION LOCK TIMEOUT - waiting for coordination lock too long, software error

F 90 02 TOO MANY INITIAL INTENTS - software error

F 90 03 CAS BARO ALTITUDE FAILURE - CAS logic has determined that own aircraft baro altitude is not credible


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D. Fault Isolation Using the Diagnostic Computer

(1) The 9-pin diagnostic test connector must be installed and ac-cessible in the aircraft, to use the diagnostic computer.

(2) Diagnostic Software

(a) TPU Diagnostic/Configuration Module Set-up Software for TPU 67A unit SW version 01/09 and below is provided on 3.5 inch diskette p/n 222-00359-00() and 5.25 inch dis-kette p/n 222-00358-00(). TPU diagnostic software must be loaded onto a diagnostic computer having the require-ments listed in the TPUDIAG - TPU Field Diagnostic Pro-gram User Instructions ( DIAGNOSTIC APPENDICES). Refer to instructions on the diskette for operation of the TPU diagnostic software.

(b) TCAS Diagnostic/Configuration Module Set-up Software for TPU 67A unit SW version 01/10 and above is provided on 3.5 inch diskette p/n 222-00386-00(). TCAS diagnos-tic software must be loaded onto a diagnostic computer having the requirements listed in the TCASDIAG - TCAS Field Diagnostic Program User Instructions ( DIAGNOSTIC APPENDICES). Refer to instructions on the diskette for operation of the TCAS diagnostic software.

(c) TCAS Diagnostic/Configuration Module Set-up Software for TPU 67A unit SW version 01/10 and above is provided on CD-ROM p/n 222-30003-00(), TCASDIAG for Windows. TCAS diagnostic software must be loaded onto a diagnos-tic computer having the requirements listed in the TCAS-DIAG - TCAS Field Diagnostic Program User Instructions ( DIAGNOSTIC APPENDICES). Refer to instructions on the CD-ROM for operation of the TCAS diagnostic software.

(3) The diagnostic software performs two basic functions:

• Reads and displays the current status of TPU Input Data

• Reads and writes to disk, the contents of the TPU Diagnos-tic Log

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(4) The following is a sample of the Input/Output Data Dump.

(5) Description of TCAS Input/Output Parameters

Mag. Heading (Deg.) displays a digital value between 0.00° and ±180.00° (+ RT); or between 0.00° and ±360.00° (+ RT) for TPU 67A unit SW version 01/11 and higher. This value should be reasonably stable and reflect the compass reading in the cock-pit.

************** I/O Dump *********************

Mag. Heading (Deg.): 0.00 Pitch (Deg.): 0.00

Heading Status: VAL Pitch Status: VAL

Heading Type: 429 Attitude Type: ARINC 429

Enc. Altitude (ft.): 8000.00 Roll (Deg.): 0.00

Enc. Alt. Status: VAL Roll Status: VAL

Enc. Alt. Resolution: Fine Rad. Alt. (ft.): 4000.00

XNDR Source: Port #1 Rad. Alt. Status: VAL

Landing Gear (A21): Retracted Rad. Alt. Type: 429 Rad. Alt.

Air/Ground (A22): Airborne Rad. Alt Source (A66): Port #1

Aircraft (Mode S) Address: N200ZC A19445 (HEX) 50312105 (Octal)

Airborne Funct Test: Allowed Max. Airspeed: 150-300 kts.

Performance Limit: Enabled Display Intruder Limit: No Limit

Functional Test (A20): INACTIVE Adv. Inhibits #1 - #2: OPEN OPEN

Aural Output: No Tone or Muting Intruder File Format: ARINC 735

Altitude Limit: 60000 Adv./Annunciator Cancel: NO (OPEN)

Attitude/Heading Source: Port #1 Display All Traffic: YES

Own A/C Sensitivity: 5 Gnd Display Mode: TA ONLY

Air Volume: 40 mW, 4.0 W Gnd Volume: 40 mW, 4.0 W

Climb Inhibit 1-2 OPEN OPEN Inc Climb Inhib 1-2: OPEN OPEN

TA Flag #1, #2 (A34, 35): VAL VAL RA Flag #1, #2 (B85,86): VAL VAL

Top antenna (J1-J4): 7f 80 80 80 Bottom antenna (J1-J4): 00 01 01 03

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Heading Status indicates VAL (Valid) or INV (Invalid). A Val-id indicates all the heading parameters meet the electrical requirements. An Invalid may indicate an invalid flag; de-termined by the Analog Flag A 86 or Binary label 014/320 in-puts. An invalid may also indicate an incorrect 26 Vac 400 Hz reference input.

Heading Type (A 23) will indicate either ARINC 429 or synchro data. Program option 0 = ARINC 429; option 1 = Synchro.

Enc. Altitude (ft.) Encoding Altitude is a digital value be-tween -1,000 ft. and 127,000 feet. This value should be rea-sonably stable and reflect the 29.92" altimeter reading in the cockpit. Additionally, this value should match the encoded altitude being broadcast by the transponder.

Enc. Alt. Status indicates VAL (Valid) or INV (Invalid).

Enc. Alt. Resolution indicates coarse or fine from transpon-der.

XNDR Source indicates which Mode S, diversity transponder is active, #1 or #2.

Landing Gear (A 21) indicates Extended or Retracted. Extended is shown when a GND is on the designated pin.

Air/Ground (A 22) also called WOW indicates On-Ground or Air-borne. On-Ground is shown when a GND is on the designated pin.

Pitch (Deg.) displays a digital value between 0.00° and ±180.00° (+ UP) for TPU 67A unit SW version 01/10 and lower; or (+ UP/- DOWN) for TPU 67A unit SW version 01/11 and higher. This value should be reasonably stable and reflect the atti-tude reading in the cockpit.

Pitch Status indicates VAL (Valid) or INV (Invalid). A Valid indicates all the pitch attitude parameters meet the electri-cal requirements. An Invalid may indicate an invalid flag; determined by the Analog Flag, A 85, or binary label 324 in-put. An Invalid may also indicate an incorrect 26 Vac 400 Hz reference input.

Attitude Type (A 24, 25) will indicate Synchro or ARINC 429 data. Synchro indicates 3-wire ARINC 407 attitude input. Program option 0 = ARINC 429, option 1 = Synchro.

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Roll (Deg.) displays a digital value between 0.00° and ±180.00° (+RT Bank) for TPU 67A unit SW version 01/10 and low-er; or (-LT/+RT) for TPU 67A unit SW version 01/11 and higher. This value should be reasonably stable and reflect the atti-tude reading in the cockpit.

Roll Status indicates VAL (Valid) or INV (Invalid). A Valid indicates all the roll attitude parameters meet the electrical requirements. An Invalid may indicate an invalid flag; de-termined by the Analog, A 85, or binary label 325 input. An Invalid may also indicate an incorrect 26 Vac 400 Hz reference input.

Rad. Alt. (Radio Altitude) is the height above the ground in feet. This value is usually between -20 ft. and 2,500 ft on analog systems and up to 4,000 ft. on some digital 429 sys-tems.

Rad. Alt. Status indicates VAL (Valid) or INV (Invalid). A Valid indicates the selected radio altitude source is valid. An Invalid may indicate an invalid flag; determined by the Analog Flag, A 37/39, or ARINC label 164/165 inputs.

Rad. Alt. Type (A 53, 40, 42) will indicate ARINC 429, KRA 405, SPERRY, COLLINS, ARINC 552A data. This program option should agree with the voltage scale used from the radio alti-tude source; i.e., the KRA 405 has outputs to match the KING, SPERRY or COLLINS voltage scales. Configure the TPU 67A for COLLINS when using a Collins (dual slope) output from the KRA 405 unit. Program option 0 = ARINC 552A, option 1 = Collins (ALT50/55), option 2 = Sperry, option 3 = King (KRA 405), op-tion 4 = ARINC 429.

Rad. Alt Source (A 66) indicates Port #1 or Port #2 as the source. A GND on pin A 66 will select port #2, otherwise port #1 is the radio altitude source.

Aircraft (Mode S) Address will indicate the ICAO aircraft ad-dress. If the aircraft is US registered the "N" field will show the N number. The HEX and Octal values will also be in-dicated. Insure that these values correspond with the air-craft being tested.

Airborne Functional Test (A 31) indicates Allowed or Inhibit-ed. Program option 0 = Not inhibited; option 1 = Inhibited. Typically, option 0 is used.

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Performance Limit (1500 fpm) cannot climb determined by FMS or by Altitude Limit. Program option 0 = not limited; option 1 = Performance limited by altitude limits.

Functional Test (A 20) also called FT will indicate Inactive or GND to reflect the state of the discrete switch input.

Aural Output Function No delay in voice, audio tone output 1 second prior to voice, or voice muting.

Altitude Limit indicates the maximum altitude at which the aircraft is capable of climbing at 1500 fpm. Indicated as an even number between 0 and 62000 feet. This limit will be ac-tive only when Performance Limit is active.

Attitude/Heading Source is used as the Heading/Attitude Source Port Identifier for TPU 67A p/n 066-01146-0201,-1211. It is not used by TPU 67A p/n 066-01146-0101,-1111.

Own A/C Sensitivity indicates Standby, 1-7. The processor de-termines this value by altitude.

Max. Airspeed (B 74, 75, 76) indicates NO MAX, < 75 kts, 75-150 kts, 150-300 kts, 300-600 kts, 600-1200 kts, > 1200 kts, or Invalid. The configuration should reflect the aircraft type; typically turbo-props are 150 to 300 kts and jets are 300 to 600 kts.

Display Intruder Limit (B 77, 78, 79) indicates MAX. (30), 24, 20, 16, 12, 8, 4, MIN. (3). Program options limit the number of intruders that can be displayed. Typically radar indica-tors are set to Max. (30) and the 3 ATI indicators are set to 12 intruders.

Adv. Inhibits #1 - #2 (A 17, 18) will indicate OPEN when in-active and GND when the appropriate input is grounded. Typ-ically, these straps are OPEN except during a GPWS or Wind Shear inhibit condition.

Intruder File Format indicates the intruder file format (BCAS or ARINC 735) TCAS will transmit. Program option 0 = ARINC 735, option 1 = Honeywell BCAS format. Typically option 0 is used.

Adv./Annunciator Cancel (A 72) indicates NO (OPEN) or YES (GND). Typically this switch is not used.

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Display All Traffic (A 32) indicates YES (OPEN) or NO (GND). When program option 1 is selected (and other conditions are met) all traffic is only displayed during a TA or RA. When option 0 is selected all traffic is displayed. Typically op-tion 1 is used.

Ground Display Mode (A33) indicates TA ONLY; or STANDBY. Pro-gram option 0 = TA ONLY mode on ground. Program option 1 = STANDBY on ground. Typically option 0 is used.

Air Volume will indicate the speaker audio level program op-tion in watts. Program options: 0=4, 1=2, 2=1, 3=0.5, 4=0.25, 5=0.125, 6=0.0625, or 7=6.5 watts are the values that will be annunciated. Four watts is the default indication. The head-phone audio level program option in milli-Watts (mW) 0=40, 1=20, 2=10, 3=5, 4=2.5, 5=1.25, 6=100, or 7=80 mW are the val-ues that will be annunciated. Forty mW is the default indi-cation. Insure this value agrees with the design specifica-tion.

Ground Volume (A 76, 77, 78) (A 82, 83, 84) program options for the speaker and headphone audio output levels are the same as listed under Air Volume above. Insure this value agrees with the design specification.

Climb Inhibit 1-2 (B87,88) indicates when the aircraft cannot climb at a rate of 1500 fpm. If input #1 and #2 are grounded, climb is inhibited.

Increase Climb Inhibit 1-2 (A98, 99) indicates when the air-craft cannot climb at a rate of 2500 fpm. If inputs #1 and #2 are grounded, increase climb is inhibited.

TA Flag #1, #2 (A34, 35) and RA Flag #1, #2 (B85, 86) indicates INV (Invalid) when the appropriate pin is invalid or open and Valid when the input is LO or grounded. At least one TA and one RA input must be Valid for TCAS to operate (display traf-fic).

Top & Bottom Antenna Elements (J1 - J4) annunciates a HEX val-ue that indicates the status of the antenna elements. A HEX value between 72H and 8DH is annunciated if the processor con-firms the correct directional antenna element resistance. If ANT 67A directional antennas are installed and a different value is shown, then the antenna installation must be inspect-ed to determine the fault.

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A HEX value between 00H and 0DH is indicated on Bottom ele-ments J2 - J4 when the 50 ohm terminations are correct for a bottom omni antenna installation. The J1 antenna element should indicate 00H (Short Circuit). A TCAS tester is re-quired to verify that the bottom omni TCAS antenna is trans-mitting properly.

(6) TPU Diagnostic Log

The TPU Diagnostic Log contains data that is accumulated over the operating history of the TPU unit. This data is stored in non-volatile memory and is maintained when the TPU is turned off. Using the TPU Diagnostic Program, the Diagnostic Log is read from the TPU and stored in a file for later view-ing, printing, or importing into a spreadsheet.

The Diagnostic Log contains three types of information: unit configuration information, cumulative operating history, and power cycle log.

(a) Unit Configuration Information: Information contained in this section includes the unit part number, the unit serial number, and the software version identification data.

(b) Cumulative Operating History: This section contains information that is accumulated over the lifetime of the TPU unit. This information includes:

1 Current Hobbs Meter: This is the total time that the unit has been running in terms of hours and tenths of hours.

2 Minimum Temperature: This is the minimum inter-nal operating temperature that the TPU unit has experienced. The Hobbs at Minimum Temperature is the value of the Hobbs meter when the minimum tem-perature occurred.

3 Maximum Temperature: This is the maximum internal operating temperature that the TPU unit has expe-rienced. The Hobbs at Maximum Temperature is the value of the Hobbs meter when the maximum temper-ature occurred.

4 Cumulative Power Cycles: This is the total number of times that the TPU has been powered on and off.

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5 Operating Temperature: This is a histogram of in-ternal temperatures that the TPU has been operat-ing in. Specifically, it contains the amount of time that the TPU has operated in each temperature range. When added together, the operating time spent in each temperature range will equal the Current Hobbs Meter.

(c) Power Cycle Log: This section contains information from the 25 most recent power cycles. A power cycle is mea-sured from when power is applied to TPU to the time when it is removed. Power cycles are printed from the most recent to the oldest. Information stored in the Diag-nostic Log for each power cycle includes:

1 Cold Start: This is the value of the Hobbs meter when the power cycle started. In addition to this, the internal operating temperature at cold start is also recorded.

2 Temperature Extremes: Minimum and maximum inter-nal operating temperatures detected during the power cycle are recorded. In addition, the Hobbs Meter value of when these extremes were detected are also recorded.

3 Functional Test Data: Each time a pilot-selected functional test is performed, the TPU records in-formation from the functional test. This infor-mation includes: the number of functional tests performed, the internal operating temperature during the most recent functional test (not printed if no functional tests have been per-formed), and the Hobbs Meter value during the most recent functional test (not printed if no func-tional tests have been performed).

4 Power Interruption Data: If the TPU experiences a momentary power interruption (less than 1 sec-ond), it will record the Hobbs Meter value of the most recent power interruption and the internal operating temperature of the most recent power interruption. If no power interruptions have oc-curred during the power cycle, then these entries will not be printed. TPU also keeps track of the number of power interruptions during the power cycle.

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5 Power Failure Data: When TPU is turned off (or ex-ternal power is removed), the TPU will record the Hobbs meter value at the time of the power failure and the internal operating temperature.

(d) Fault Data: During each power cycle, the TPU will record the three highest priority failures (if any oc-curred) in the Diagnostic Log. The following informa-tion is recorded for each fault:

1 Description: An English description of the fault that occurred.

2 Class/Code: The type of fault that occurred as de-scribed in paragraph 2 D. Fault Isolation Using the Diagnostic Computer.

3 Priority: Priority of the fault.

4 Number of Occurrences (#): The number of times that the fault occurred.

5 Hobbs at most recent: The Hobbs meter value when the most recent fault occurred.

6 Temperature at most recent: The internal operat-ing temperature of the most recent fault.

(7) The following is a sample of the TPU Diagnostic Log Format:

DIAGNOSTIC LOG DUMP:--------------------Unit Configuration:-------------------Unit KPN: 066-01146-0101 or 0201Unit Serial Number: #####EEPROM Unit Config Checksum: 201Software PN: 125-00###-0###

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Software Version: TPU ##.#

CUMULATIVE DATA---------------Current Hobbs Meter :125.0 hrsMinimum Temp. Experienced :-12 CHobbs at Minimum Temp. :10.0 hrsMaximum Temp. Experienced :55° CHobbs at Maximum Temp. :105.0 hrsCumulative Power Cycles :25Operating Temperature--------------------- < -65° C :0.0 hrs>= -65° C to < -55° C :0.0 hrs>= -55° C to < -45° C :0.0 hrs>= -45° C to < -35° C :0.0 hrs>= -35° C to < -25° C :0.0 hrs>= -25° C to < -15° C :0.0 hrs>= -15° C to < -5° C :1.0 hrs>= -5° C to < 5° C :5.0 hrs>= 5° C to < 15° C :50.0 hrs>= 15° C to < 25° C :50.0 hrs>= 25° C to < 35° C :17.0 hrs>= 35° C to < 45° C :1.9 hrs>= 45° C to < 55° C :0.1 hrs>= 55° C to < 65° C :0.0 hrs>= 65° C to < 75° C :0.0 hrs>= 75° C to < 85° C :0.0 hrs>= 85° C to < 95° C :0.0 hrs>= 95° C to < 105° C :0.0 hrs>= 105° C to < 115° C :0.0 hrs>= 115° C :0.0 hrs

POWER CYCLE LOG (newest to oldest)---------------------------------POWER CYCLE RECORD #12----------------------Hobbs at cold start :24.0 hrs

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Temp. at cold start :42° CHobbs at Minimum Temp :124.0 hrsMinimum Temperature :42° CHobbs at Maximum Temp :124.5 hrsMaximum Temperature :48° C# of Func Tst Performed :0Hobbs at Last Func Tst :N/ATemp. at Last Func Tst :N/A# of Pwr Interruptions :0Hobbs at Last Pwr Int :N/ATemp. at Last Pwr Int :N/AHobbs at Power Fail :125.0 hrsTemp. at Power Fail :46 CDiagnostic Log Status :0xff

Fault Data----------Fault 1 Description: Heading failure during SPM Class :0x2 Code :0x6 Priority :0x1 # of Occurrences :1 Hobbs at most recent :124.1 hrs Temp. at most recent :45 C

POWER CYCLE RECORD #11----------------------Hobbs at cold start :120.0 hrsTemp. at cold start :40 CHobbs at Minimum Temp :122.0 hrsMinimum Temperature :20 CHobbs at Maximum Temp :122.0 hrsMaximum Temperature :40 C# of Func Tst Performed :1Hobbs at Last Func Tst :123.5 hrsTemp. at Last Func Tst :20 C# of Pwr Interruptions :2

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Hobbs at Last Pwr Int :123.7 hrsTemp. at Last Pwr Int :20 CHobbs at Power Fail :124.0 hrsTemp. at Power Fail :20 CDiagnostic Log Status :0xffFault Data----------No faults in this power cycle

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(8) The following is a sample of the TCAS Diagnostic Log Format for TPU 67A versions 066-01146-0101,-0201:

TPU Serial #: Pxxxxx, Tail #: Nxxxxx, S/W ver: 01/11---------- 05-06-97 ---------- 09:25:00 ----------DIAGNOSTIC LOG DUMP:--------------------Unit Configuration:-------------------Unit KPN: 066-01146-0101, -0201Unit Serial#: #####EEPROM Unit Config Checksum: 167Unit Software ID: 206-00277-xxxxSoftware Version: TPU67A Ver x.xxConfiguration Module Compatibility Code: 3CUMULATIVE DATA---------------Current Hobbs Meter : 24.9 hrsMinimum Temp. Experienced: 27 CHobbs at Minimum Temp. : 19.7 hrsMaximum Temp. Experienced: 49 CHobbs at Maximum Temp. : 17.7 hrsCumulative Power Cycles : 62Operating Temperature--------------------- < -65 C : 0.0 hrs>= -65 C to < -55 C : 0.0 hrs>= -55 C to < -45 C : 0.0 hrs>= -45 C to < -35 C : 0.0 hrs>= -35 C to < -25 C : 0.0 hrs>= -25 C to < -15 C : 0.0 hrs>= -15 C to < -5 C : 0.0 hrs>= -5 C to < 5 C : 0.0 hrs>= 5 C to < 15 C : 0.0 hrs>= 15 C to < 25 C : 0.0 hrs>= 25 C to < 35 C : 0.5 hrs>= 35 C to < 45 C : 5.1 hrs>= 45 C to < 55 C : 18.5 hrs>= 55 C to < 65 C : 0.0 hrs>= 65 C to < 75 C : 0.0 hrs>= 75 C to < 85 C : 0.0 hrs>= 85 C to < 95 C : 0.0 hrs>= 95 C to < 105 C : 0.0 hrs>= 105 C to < 115 C : 0.0 hrs>= 115 C : 0.0 hrs

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POWER CYCLE LOG (newest to oldest)----------------------------------POWER CYCLE RECORD #1---------------------- Cold Start : 0.5 hrs / 44 C Min. Temp. : 0.5 hrs / 44 C Max. Temp. : 0.9 hrs / 49 C # Func. Tst. : 0 # Pwr Int. : 0 Power Fail : 0.9 hrs / 46 C Fault Data ---------- Fault 1 -- F 02 04, priority 1, 1 occurrence Description : Attitude - Roll failure Hobbs / Temp. : 0.9 hrs / 48 C (most recent) Aircraft was : Airborne (with landing gear retracted) Xpndr Source : Port #1 Altitude : 2000 (to nearest 1000 ft) Rad Altitude : 0 (to nearest 100 ft) -- Usable Fault 2 -- F 02 05, priority 1, 1 occurrence Description : Attitude - Pitch failure Hobbs / Temp. : 0.9 hrs / 48 C (most recent) Aircraft was : Airborne (with landing gear retracted) Xpndr Source : Port #1 Altitude : 2000 (to nearest 1000 ft) Rad Altitude : 0 (to nearest 100 ft) -- Usable Fault 3 -- F 02 16, priority 1, 1 occurrence Description : Transponder #1 Altitude failure Hobbs / Temp. : 0.9 hrs / 48 C (most recent) Aircraft was : Airborne (with landing gear retracted) Xpndr Source : Port #1 Altitude : 2000 (to nearest 1000 ft) Rad Altitude : 0 (to nearest 100 ft) -- Usable

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(9) The following is a sample of the TCAS Diagnostic Log Format for TPU 67A versions 066-01146-1111,-1211:

TPU Serial #: Pxxxxx, Tail #: Nxxxxx, S/W ver: 11/01---------- 02-19-99 ---------- 10:07:41 ----------DIAGNOSTIC LOG DUMP:--------------------Unit Configuration:-------------------Unit KPN: 066-01146-1211Unit Serial#: EXXXXEEPROM Unit Config Checksum: 167Software KPN: 125-00812-0000Software Version: TPU6xA Ver x.xxConfiguration Module Compatibility Code: 3CUMULATIVE DATA---------------Current Hobbs Meter : 24.9 hrsMinimum Temp. Experienced: 27 CHobbs at Minimum Temp. : 19.7 hrsMaximum Temp. Experienced: 49 CHobbs at Maximum Temp. : 17.7 hrsCumulative Power Cycles : 62Operating Temperature--------------------- < -65 C : 0.0 hrs>= -65 C to < -55 C : 0.0 hrs>= -55 C to < -45 C : 0.0 hrs>= -45 C to < -35 C : 0.0 hrs>= -35 C to < -25 C : 0.0 hrs>= -25 C to < -15 C : 0.0 hrs>= -15 C to < -5 C : 0.0 hrs>= -5 C to < 5 C : 0.0 hrs>= 5 C to < 15 C : 0.0 hrs>= 15 C to < 25 C : 0.0 hrs>= 25 C to < 35 C : 0.5 hrs>= 35 C to < 45 C : 5.1 hrs>= 45 C to < 55 C : 18.5 hrs>= 55 C to < 65 C : 0.0 hrs>= 65 C to < 75 C : 0.0 hrs>= 75 C to < 85 C : 0.0 hrs>= 85 C to < 95 C : 0.0 hrs>= 95 C to < 105 C : 0.0 hrs>= 105 C to < 115 C : 0.0 hrs>= 115 C : 0.0 hrs

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POWER CYCLE LOG (newest to oldest)----------------------------------POWER CYCLE RECORD #1---------------------- Cold Start : 0.5 hrs / 44 C Min. Temp. : 0.5 hrs / 44 C Max. Temp. : 0.9 hrs / 49 C # Func. Tst. : 0 # Pwr Int. : 0 Power Fail : 0.9 hrs / 46 C Fault Data ---------- Fault 1 -- F 02 04, priority 1, 1 occurrence Description : Attitude - Roll failure Hobbs / Temp. : 0.9 hrs / 48 C (most recent) Aircraft was : Airborne (with landing gear retracted) Xpndr Source : Port #1 Altitude : 2000 (to nearest 1000 ft) Rad Altitude : 0 (to nearest 100 ft) -- Usable Fault 2 -- F 02 05, priority 1, 1 occurrence Description : Attitude - Pitch failure Hobbs / Temp. : 0.9 hrs / 48 C (most recent) Aircraft was : Airborne (with landing gear retracted) Xpndr Source : Port #1 Altitude : 2000 (to nearest 1000 ft) Rad Altitude : 0 (to nearest 100 ft) -- Usable Fault 3 -- F 02 16, priority 1, 1 occurrence Description : Transponder #1 Altitude failure Hobbs / Temp. : 0.9 hrs / 48 C (most recent) Aircraft was : Airborne (with landing gear retracted) Xpndr Source : Port #1 Altitude : 2000 (to nearest 1000 ft) Rad Altitude : 0 (to nearest 100 ft) -- Usable

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INSTALLATION AND MAINTENANCE

1. General

This section provides installation and maintenance information for the Honeywell CAS 67A TCAS II system. Components of the CAS 67A TCAS II system are listed in Table 1 CAS 67A TCAS II System Components and shown in Figure 1 CAS 67A TCAS II System Components.

CAUTION: ALL TCAS INSTALLATIONS MUST INCLUDE A BEARING ACCURACY TEST US-ING A RAMP TESTER. THIS TEST IS REQUIRED REGARDLESS OF THE NUM-BER OF IDENTICAL TCAS INSTALLATIONS PRECEDING THE CURRENT ONE.

Maintenance information for the GC 362A TCAS Graphics Processor and asso-ciated radar systems are described in separate manuals. Installation and maintenance information for the Mode S transponder/TCAS control units and associated equipment are described in the applicable Mode S transponder manual. Refer to Table 49 Related Publications.

Mechanical outline drawings and electrical interconnection drawings sup-port the installation instructions. Those drawings, located at rear of this section, should be reviewed by the installing agency. Any require-ments peculiar to a particular airframe should be established before the CAS 67A TCAS II installation is begun.

2. Unpacking

Use care when unpacking the CAS 67A TCAS II system components. Open ship-ping cartons and carefully remove all items. Check the contents to ensure that all items identified on the packing list are included. Visually in-spect each component for damage incurred during shipment. Inspect for dents, deep abrasions, chipped paint, etc. If any component is damaged, notify the transportation carrier immediately.

3. Pre-Installation Testing

All components of the CAS 67A TCAS II system have been adjusted and tested before shipment. Pre-installation testing is not required. If pre-in-stallation bench testing of a unit is desired, refer to bench test section of the appropriate maintenance manual. For a list of maintenance manuals refer to Table 49 Related Publications.

4. Equipment Changes and Markings

Honeywell uses a standardized marking system to identify mod changes to equipment.

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5. Equipment Location and Interwiring

A. General

The following paragraphs contain information for equipment location and interwiring of the CAS 67A TCAS II system. Figure 1 CAS 67A TCAS II System Components shows the relationship of TCAS system com-ponents.

The CAS 67A TCAS II system should be installed in the aircraft by standard workmanship and engineering practices according to in-structions in this manual.

Forced air cooling is not required, if there is adequate free air movement around the TCAS processor on all sides. Any enclosed com-partment housing a TCAS processor should be vented to allow free air flow.

The installer should make a thorough visual inspection and perform the post-installation and operational checks of the system to ensure that the system has been properly and safely installed in the air-craft.

CAUTION: AFTER INSTALLATION OF THE CABLING AND BEFORE INSTALLATION OF THE EQUIPMENT, SUPPLY AIRCRAFT PRIMARY POWER TO THE UNIT CONNECTORS AND CHECK THAT POWER IS APPLIED ONLY TO THE PINS SPECIFIED IN THE INTERFACE DIAGRAMS.

B. Location of Equipment

(1) TCAS Antenna Location

NOTE: The following antenna location procedure is provid-ed to achieve certifiable system performance.

The CAS 67A TCAS II system uses a top-mounted directional an-tenna and a bottom-mounted directional or an L-band omnidi-rectional antenna. Refer to Figure 2014 ANT 67A Directional Antenna Outline Drawing.

Installation of the directional antenna MUST include the ap-propriate antenna adapter plate for curved surfaces, to insure acceptable bearing accuracy.

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Refer to Figure 2011 ANT 67A Directional Antenna Adapter and Moldable Shim, Figure 2014 ANT 67A Directional Antenna Outline Drawing, and paragraph 11. ANT 67A Directional Antenna Adapter Plate Installation for antenna adapter plate installation in-formation.

NOTE: TCAS requires that the antenna installation guide-lines be followed. Optimum bearing accuracy can be achieved only by following these directions.

Antenna locations must be chosen to make both antennas appear at the same range and bearing from the interrogator.

The centerline of the top and bottom-mounted TCAS antennas should be located as close as possible to the aircraft cen-terline. Refer to Figure 2014 ANT 67A Directional Antenna Outline Drawing for airframe radius, directional antenna adapter plate part numbers, and maximum distance from airframe centerline.

The top directional TCAS antenna MUST be the most forward an-tenna and be as far forward on the constant radius portion of the fuselage as possible.

Obstructions and ground plane discontinuities, such as door hatches, cowlings, and unriveted airframe skin overlaps must be at least 18 inches from the nearest edge of any TCAS an-tenna. Other antennas, particularly high profile and L-band transponder antennas, cannot be located in front of or within 30 inches (edge to edge) of any TCAS directional antenna. This will ensure a minimum of 20 dB isolation at 1090 MHz, while minimizing far-field path distortion in the forward quadrants. The bottom directional TCAS antenna must not ex-ceed a distance of 25 feet (center to center) from the top directional TCAS antenna.

In addition, it is strongly recommended that the bottom di-rectional TCAS antenna be installed forward of the main land-ing gear.

Except for the above mentioned requirements, location of the CAS 67A equipment is not critical and may vary with different aircraft types, provided that the environment is compatible with equipment design.

Care should be taken to avoid mounting the components near equipment operating with high pulse current or high power out-puts, such as radar and satellite communications equipment.

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The equipment should be installed in a location convenient for operation, inspection and maintenance, and in an area free from excessive vibration, heat, and noise-generating sources.

NOTE: When standard installation requirements are imprac-tical or impossible to meet, variations in TCAS an-tenna location and installation may be necessary. Modifications to the Honeywell antenna adapter plate by the installer are not authorized, other than drilling mounting holes. It is the responsi-bility of the installation agency to ensure that bearing accuracy requirements are achieved.

NOTE: Transponders that do not meet the requirements of DO 181A for TCAS must have at least 40 dB isolation between the TCAS antenna and the transponder anten-na. This is approximately eight feet. Check with the manufacturer of the transponder for compliance with DO 181A specifications.

(2) TCAS Processor Location

Care should be exercised to avoid mounting the components near equipment operating with high pulse current or high power out-puts such as radar and satellite communications equipment.

The equipment should be installed in a location convenient for operation, inspection, and maintenance, and in an area free from excessive vibration, heat, and noise generating sources.

Length of cables from the TCAS processor mounting tray con-nector to other system units, except for the TCAS antennas is not critical. TCAS unit interfaces are designed with high impedance inputs, low impedance outputs, and low noise sus-ceptibility characteristics. Air space should be provided be-tween and around the unit. Figure 2012 TPU 67A TCAS II Pro-cessor Outline Drawing shows TCAS processor dimensions.

Diagnostic and Recording Test connections should be conve-niently accessible for system testing and fault isolation. These test connections should be available inside the cabin to accommodate any flight test or system troubleshooting re-quirements.

NOTE: Refer to the interface diagrams, Figure 2024 TPU 67A Interconnect Drawing Family and paragraph 5.C. (5) Antenna Cable Type Selection for TCAS processor to antenna wiring particulars and interconnects.

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The configuration module is mounted according to installation considerations outlined in Figure 2013 CM 67A/CM 2000 Config-uration Module Outline Drawing.

(4) Display Units

The display units are normally mounted in the instrument panel in front of the primary viewer to provide maximum visibility. There should be adequate space on all sides of the installed display units for ventilation. Outline drawings for the TCAS traffic displays are shown in Figure 2015 IVA 81A (TA/RA/VSI) Outline Drawing, Figure 2016 IVA 81B (RA/VSI) Outline Drawing. Figure 2017 IVA 81C (TCAS) Outline Drawing, and Figure 2018 IVA 81D (TCAS) Outline Drawing.

NOTE: Installation instructions for the TCAS/Weather Ra-dar display are contained in separate system main-tenance manuals listed in Table 49 Related Publi-cations.

(5) Control Units

The TCAS control unit is usually mounted within easy reach of the flight crew. Outline drawings for the TCAS control units are shown in Figure 2020 KFS 578A Control Unit Outline Draw-ing, Figure 2021 PS-578A Control Unit Outline Drawing, Figure 2022 PS-550 Control Unit Outline Drawing, and Figure 2023 CD 671C Control Unit Outline Drawing. See also the SYSTEM DE-SCRIPTION section of this manual.

NOTE: Installation instructions for the combination TCAS/Transponder control units are contained in separate manuals listed in Table 49 Related Publications.

(6) TCAS Graphics Processor

The graphics processor unit should be installed in a location providing accessibility for inspection and maintenance. The area should be free from excessive vibration, heat, and noise generating sources. Outline drawing for the graphics proces-sor is shown in Figure 2019 GC 362 TCAS Graphics Processor Outline Drawing.

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C. Interwiring and Cable Fabrication

(1) General

Cabling must be fabricated according to interface diagrams, see Figure 2024 TPU 67A Interconnect Drawing Family. The length of the wires to parallel pins should be approximately the same length, so that the best distribution of current can be effected.

Honeywell recommends that all wires shown on the interface di-agrams, including spares, be included in the fabricated har-ness. However, if full wiring is not desired, the installer should ensure that the minimum wiring requirements for the features and functions to be used are incorporated.

Wires for optional functions are shown on the interface dia-grams. The actual use of these wires will depend upon the installation, customer requirements and capability of the units installed.

When the cables are installed in the aircraft, they must be supported firmly enough to prevent movement and should be carefully protected against chafing. Additional protection should also be provided in all locations where the cables may be subject to abuse.

In wire bundles, the cabling should not be tied tightly to-gether as this tends to increase the possibility of noise pickup and similar interference. When routing cables through the airframe, the cables should cross high-level lines at a right angle.

The installer must be knowledgeable of any system variations peculiar to the installation. Furthermore, the installer should use ARINC Characteristic 735 as a guide and reference throughout the fabrication and installation of the cabling in the aircraft.

Notes on the interface diagrams describe wire sizes and other particulars related to the CAS 67A TCAS II system interwiring. Antenna cabling has unique requirements described in para-graph 5.C. (5) Antenna Cable Type Selection.

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(2) Interface Capability and Requirements

Figures in the SYSTEM DESCRIPTION section of this manual list the types of external avionics equipment that can be connected to the TCAS II system and describe the types of signals. De-termine the types of aircraft equipment to be connected to the TCAS II system.

(3) Primary Power and Circuit Breaker Requirements

The CAS 67A TCAS II system operates primarily from the air-craft’s 28 Vdc power system. The displays use 5 Vac 400 Hz/5 Vdc or 28 Vdc lighting power. A 26 Vac 400 Hz input is provided for reference for the synchro-to-digital converters. Power dissipation varies with the system configuration. Power connections are shown in interface diagrams. Circuit breaker requirements for each component and wire sizes are also de-fined.

(4) Suppression Pulse Requirements and Wiring

Connections for the suppression pulse from the TCAS processor are dependent on aircraft equipment and wiring (see Figure 2025 TPU 67A Pinout Drawing, Figure 2030 Antenna/Suppression Interface Drawing, Figure 2042 MST 67A Mode S Interface Draw-ing, Figure 2043 Collins TDR-94D Mode S Interface Drawing, Figure 2044 Honeywell Primus II/TCAS Interface Drawing, and Figure 2045 CAS 67A TCAS II System Interface Drawing). Typ-ically, the suppression pin is connected from the TCAS pro-cessor to the suppression inputs on the L-band transponder and DME equipment.

(5) Antenna Cable Type Selection

NOTE: When an omnidirectional antenna is used as the bot-tom antenna, the three unused bottom antenna coaxes connected to the TPU 67A processor must be connect-ed to 50 Ω terminations. Please contact one of the following companies for 50 Ω terminations: M/A Comm p/n 3002-6113-0000, Phone 1-800-998-45000; PIC Wire & Cable p/n K240001; Pasternack p/n PE6032.

NOTE: Always compare the following information with in-formation on the aircraft interface diagrams.

The following TCAS processor-to-antenna cable installation requirements must be adhered to:

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(a) The total dB loss in any of the coaxial cable runs and associated interconnects between the TCAS Processor and each antenna port connector must not be less than 2 dB and must not be greater than 3 dB at 1030 MHz.

(b) The electrical lengths of the four coax cables for ei-ther the top or the bottom directional antennas must match within 135°.

(c) The VSWR ratio must be less than 1.35:1.

The round-trip (receive/transmit) delay imposed by any individual cable run and associated interconnects be-tween the TCAS processor and top antenna as opposed to the round-trip (receive/transmit) delay imposed by any cable run and interconnects between the TCAS processor and the bottom antenna must be seen by the TCAS as an effective delay difference of less than 50 nanoseconds.

Before selecting the type of TCAS processor-to-antenna coaxial cable and the connectors required, the install-er must determine the length of the coax cable. First, identify the antenna mounting location and the proces-sor mounting location. Then determine the cable routing between the TCAS Processor rear connector and the four RF connectors on the directional antenna. The four ca-bles to a directional antenna should follow the same routing paths and have the same number of disconnects per path.

Once the physical length of the cables to the top and bottom antenna has calculated, the coax cable type can be determined. The dB loss limitations for the cable assemblies must meet the 2.5 dB ±0.5 dB requirement and not exceed the 50 nanosecond maximum delay difference requirement between the top and bottom antenna cable runs. After the coax cable type is known, the coax con-nector type can be determined.

The specifications for the coax cables requires very ex-acting procedures and an expensive network analyzer to test the necessary parameters. Experience indicates that it is best to buy prefab coax cable assemblies for the TCAS directional antenna. These cables will provide the highest level of confidence for maintaining the re-quired specifications. Several fabricators of the coax cables for TCAS antennas are available.

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For additional information see the SYSTEM DESCRIPTION section of this manual.

(6) Connectors

Mating connectors for the TCAS units are identified on the appropriate outline drawing. Associated connector kits are specified in the SYSTEM DESCRIPTION section of this manual.

(a) TCAS Processor Connectors

The TPU 67A mounted connector mates with a low-inser-tion-force, ARINC 404 connector with polarization pro-jections that prevent improper connector insertion. The mating connector has six Size A shells. Four Size A shells have 2 Size 1 RF coax contacts each and two of the Size A shells have 106 No. 22 contacts (like DPX 106).

This mating connector is specified in the TPU 67A out-line drawing, Figure 2012 TPU 67A TCAS II Processor Out-line Drawing, and is part of the TCAS processor mounting tray.

The rear connector, shown in Figure 2001 TPU 67A TCAS Processor Rear Connector Key & Pin Locations, is divided into six sections. System interface diagrams define the external inputs to each pin of the six plug sections. Tables in the SYSTEM DESCRIPTION section describe the signals.

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Figure 2001 TPU 67A TCAS Processor Rear Connector Key & Pin Locations

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Connector P67A1 Insert A

PIN # SIGNAL NAME DESCRIPTION

A 001 GND Plane Input Ground




A 005 +28 Vdc Aircraft PWR Input Power






A 011 ON(x) Input Discrete

A 012* ATE Test Mode(x) Input Discrete

A 013 Suppression I/O Suppression Signal

A 014 N/C No Connection

A 015* Discrete Input (Reserved) Input Discrete


A 017* ADV Inhibit 1(x) Input Discrete

A 018* ADV Inhibit 2(x) Input Discrete


A 020* Function Test(x) Input Discrete

A 021* Landing Gear Input Discrete

A 022* Air/GND(x) Input Discrete




A 026* Spare Dis Input 1 Input Discrete

* Diode protected (x) = ground active

Table 2001 TPU 67A TCAS Processor, Rear Connector Pin Names (Sheet 1 of 9)

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A 034* TA Valid #1(x) Input Discrete

A 035* TA Valid #2(x) Input Discrete

A 036 Radio Alt #1 + Input Signal

A 037* Rad Alt Val #1 Input Signal

A 038 Radio Alt #1 - Input Signal

A 039* Rad Alt Val #2 Input Signal


A 041* Gill Alt 1 - D4 Input Signal


A 043* Gill Alt 2 - B2 Input Signal

A 044* Gill Alt 1 - A2 Input Signal





A 049* Gill Alt 1 - C1 Input Signal






Table 2001 TPU 67A TCAS Processor, Rear Connector Pin Names (Sheet 2)

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A 065* Radio Alt #2 + Input Signal

A 066* Rad Alt Source 1/2(x) Input Source Select

A 067 SPK Hi Output Signal 8 Ω

A 068 SPK Lo Output Signal 8 Ω

A 069 PH Hi Output Signal 600 Ω

A 070 PH Lo Output Signal 600 Ω


A 072* ADV/ANNUN Cancel(x) Input Discrete











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A 085* Attitude Valid Input Signal

A 086* Heading Valid Input Signal

A 087 VIS ANNUN Traffic(x) Output Signal

A 088 Programmable Output Output (Reserved)

A 089 TCAS Valid(x) Output Discrete

A 090 TA Aural Traffic(x) Output Signal

A 091 Attitude Pitch X Input Signal 50 kΩ

A 092 Attitude Pitch Y Input Signal 50 kΩ

A 093 Attitude Pitch Z Input Signal 50 kΩ

A 094 Attitude Roll X Input Signal 50 kΩ

A 095 Attitude Roll Y Input Signal 50 kΩ

A 096 Attitude Roll Z Input Signal 50 kΩ

A 097 Attitude H Input Signal 50 kΩ

A 098* INC Climb INH 1 Input Discrete

A 099* INC Climb INH 2 Input Discrete










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Connector P67A1 Insert B


B 001 TCAS 232 TX Diagnostic Function

B 002 RS 422 DAT + Recorder Function

B 003 RS 422 DAT - Recorder Function

B 004 RS 422 CLK + Recorder Function

B 005* Discrete Input (Reserved) Input Discrete

B 006 TA Display Enable(x) Output Discrete

B 007 FMS 1B (Reserved) Flight Management System

B 008 ATE A2/Config Mod +5 Vdc ATE Test/Config Module

B 009 ATE A1/Config Mod CS1 ATE Test/Config Module

B 010 ATE A0/Config Mod CS2 ATE Test/Config Module

B 011 ATE D6 ATE Test Function


B 013 RS 422CLK - Recorder Function

B 014 N/C No Connection


B 016 TA/RA TX 1B Output 429 Signal


B 018 ATE D0/Config Mod Data Out ATE Test/Config Module

B 019 Radio Alt #2 - Input Signal

B 020 Heading C Input Signal

B 021 Discrete Input (Reserved) Input Discrete

B 022 Discrete Input (Reserved) Input Discrete

B 023 ATE D7/Config Mod CLK ATE Test/Config Module







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B 028 TA/RA TX 2A Output 429 Signal

B 029 TA/RA TX 2B Output 429 Signal

B 030 TA/RA TX 1A Output 429 Signal


B 032 GND Plane Input Ground

B 033 RA 429 TX 2A Output Signal

B 034 RA 429 TX 2B Output Signal

B 035 RA 429 TX 1A Output Signal

B 036 RA 429 TX 1B Output Signal

B 037 Fan On (Reserved) Output Signal



B 040 Rad Altim 1A Input 429 Signal

B 041 Rad Altim 1B Input 429 Signal

B 042 Rad Altim 2A Input 429 Signal

B 043 Rad Altim 2B Input 429 Signal










B 053 ATE CLK ATE Test Function

B 054 XPDR TX 2A Output Signal



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B 055 FMS 1A (Reserved) Flight Management

B 056 XPDR TX 2B Output Signal


B 058 VIS ANNUN Preventive(x) Output

B 059 CALENB (Cal Enable)(x) ATE Test Function (N/C)







B 066 TCAS 232 RX Diagnostic Function

B 067 XPDR TX 1A Output Signal

B 068 XPDR TX 1B Output Signal

B 069 HDG/ATT 2A (-0201,-1211 Units) Input 429 Control

B 070 HDG/ATT 2B (-0201,-1211 Units) Input 429 Control












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B 080 XPONDER RCV 1A Input Signal

B 081 XPONDER RCV 1B Input Signal

B 082 XPONDER RCV 2A Input Signal

B 083 XPONDER RCV 2B Input Signal

B 084 LS SPR 429 RX 1A (Reserved) Input 429 Signal

B 085 RA Valid #1(x) Input Discrete

B 086 RA Valid #2(x) Input Discrete

B 087* Climb INH 1 Input Discrete

B 088* Climb INH 2 Input Discrete

B 089* ATE Enable(x) ATE Function (N/C)

B 090 Config Module Data In Configuration Module



B 093 HDG/ATT 1B Input 429 Signal

B 094 LS SPR 429 RX 1B (Reserved) Input 429 Signal

B 095 LS SPR 429 RX 2A (Reserved) Input 429 Signal

B 096 LS SPR 429 RX 2B (Reserved) Input 429 Signal

B 097 HDG/ATT 1A Input 429 Signal


B 099 Term RDY Diagnostic Function

B 100 TCAS 232 RDY Diagnostic Function

B 101 Attitude C Input Signal 50 kΩ

B 102 Heading H Input Signal 50 kΩ

B 103 Heading Y Input Signal 50 kΩ

B 104 Heading X Input Signal 50 kΩ

B 105 Heading Z Input Signal 50 kΩ

B 106 VIS ANNUN Corrective(x) Output



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(b) Configuration Module Connector

The electrical connector for the configuration module must be wired to the rear connector. The connector is a standard nine pin D-Sub connector.

Table 2002 Configuration Module, Connector Pin Names

Connector P67A2

COAX # SIGNAL NAME DESCRIPTION

A1 Top Directional Antenna J1 (Yell) Input Signal

A2 Bottom Omni(50Ω)/or DirectionalAntenna J1 (Yell)

Input Signal

B1 Top Directional Antenna J2 (Blk) Input Signal

B2 Bottom Directional Antenna J2 (Blk) Input Signal

C1 Top Directional Antenna J3 (Blu) Input Signal

C2 Bottom Directional Antenna J3 (Blu) Input Signal

D1 Top Directional Antenna J4 (Red) Input Signal

D2 Bottom Directional Antenna J4 (Red) Input Signal


Connector P101


1 Power Ground Ground

2 Chip Select 1 (CS1)

3 No Connection

4 Data From Module

5 VCC (+5 Vdc) Power Input

6 Clock

7 No Connection

8 Data To Module

9 Chip Select 2 (CS2)

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(c) Directional Antenna Connectors

Four coaxial cables using TNC connectors connect the di-rectional antenna connectors A1 through D2 to the TCAS processor. See Figure 2014 ANT 67A Directional Antenna Outline Drawing, Figure 2030 Antenna/Suppression Inter-face Drawing, and paragraph 6. B. Directional Antenna for particulars.

(d) 3ATI Traffic Display Connectors

The pneumatic and electrical connectors for the IVA-81A/IVA-81C/IVA-81D (TA/RA/VSI) and IVA-81B (RA/VSI) are mounted on the rear panel of the units as shown in Figure 2002 IVA-81A/B/C/D Rear Connector Locations. The pneumatic connector used on the IVA-81A/IVA-81B/IVA-81C/IVA-81D, attaches to a pneumatic tube from a static pressure source in the aircraft. The 41-pin elec-trical connector connects to the TCAS processor, air-craft power sources, and configuration straps. The TA/RA/VSI can also connect to various analog or digital vertical rate sources, if the pneumatic input is not used.

Electrical connector keying on units powered by 115 V 400 Hz is different from keying on units powered by 28 Vdc to preclude inadvertent installation of an improper unit. Keying is also different among those 28 Vdc units designed for 5 Vac or Vdc panel lighting and those de-signed for 28 Vdc panel lighting.

The electrical connector pin locations and signal def-initions are shown in Figure 2003 IVA-81A/B/C/D Elec-trical Connector Pin Locations and Table 2003 IVA-81A/B/C/D Electrical Connector Pin Names, and Figure 2036 RA Display (ARINC 429 Low Speed) Interface Drawing and Figure 2037 TA/RA Display (ARINC 429 High Speed) Inter-face Drawing. Outline drawings Figure 2015 IVA 81A (TA/RA/VSI) Outline Drawing, Figure 2016 IVA 81B (RA/VSI) Outline Drawing, Figure 2017 IVA 81C (TCAS) Outline Drawing, and Figure 2018 IVA 81D (TCAS) Outline Drawing provide connector part numbers and additional informa-tion.

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Figure 2002 IVA-81A/B/C/D Rear Connector Locations

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Figure 2003 IVA-81A/B/C/D Electrical Connector Pin Locations

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PIN SIGNAL NAME I/O DESCRIPTION

4023

H or +C or -

II

115 Vac 400 Hz or 28 Vdc(Depending on unit version)

22 Chassis Ground O TA/VSI Case Ground

39 DC Common O Ground

2524

HILO

II

Remote Light Sensor Input

109

HC

II

Dimming Power Input(5 Vac, 5 Vdc, or 28 Vdc)

2712

AB

II

Digital Primary Vertical Speed Input (#1) Low Speed/High Speed 429 ADC/IRS.

8 +28 Vdc/Open I Vertical Speed Valid Input ADC/IRS, ARINC 565, 575

3014

AB

II

Digital Secondary Vertical Speed Input (#2) Low Speed/High Speed 429 ADC/IRS.

46

HILO

II

ARINC 565 Vertical Speed Input

516

HC

II

26 Vac Reference

132

+ Vdc REF- Vdc REFDC Rate Signal

III

ARINC 575 Analog Input

2611

AB

II

TCAS Data Input High Speed 429

29 Open/Ground (Valid=Ground) 0 Display Status Output

Table 2003 IVA-81A/B/C/D Electrical Connector Pin Names (Sheet 1 of 2)

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NOTE: For additional connector pin information see Figure 2037 TA/RA Display (ARINC 429 High Speed) Interface Drawing .


20 28 VDC/Gnd Open I Source Select Strap #2

19 Spare

18 NVIS Discrete (066-01171-3704/-3706)

41 Open/Gnd (Test) I Lamp Test

15 O Strap Common

31 Gnd/Open I Source Select Strap #1

2813

AB

OO

Altitude Rate Output Low Speed ARINC 429

721

AB

II

Reserved Input Low Speed ARINC 429

32 CS0I BIT 0 Configuration Strap









Table 2003 IVA-81A/B/C/D Electrical Connector Pin Names (Sheet 2)

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(e) KFS 578A Control Unit Connectors

The KFS 578A Control Unit has one 29-pin (P5781) and one 9-pin (P5782) connector mounted on the rear of the unit. The connectors are keyed to prevent improper connector insertion. The connectors are shown in Figure 2004 KFS 578A Control Unit, Rear Connectors and the signals con-nected to each pin are defined in Table 2004 KFS 578A Control Unit Connector (P5782) Pin Definitions and Ta-ble 2005 KFS 578A Control Unit Connector Pin Names (P5781).

Interface diagrams that define the input and output sig-nal connections to the KFS 578A Control Unit are found in the MST 67A Mode S Transponder Installation Manual.

Figure 2004 KFS 578A Control Unit, Rear Connectors

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Table 2004 KFS 578A Control Unit Connector (P5782) Pin Definitions


1 Shield Ground/429 Common I ARINC 429 Common

2 Polarizer Key Polarizer Key

3 429 Input #1 (A) I Low Speed ARINC 429

4 429 Input #1 (B) I Low Speed ARINC 429



7 429 Output (A) O Low Speed ARINC 429

8 429 Output (B) O Low Speed ARINC 429

9 Spare


1 28Vdc Unit Power I 28 Vdc power input

2 Aircraft Ground I Aircraft ground

3 28Vdc Lighting I 28 Vdc A/C lighting bus input

4 5Vdc Lighting I 5 Vdc/Vac A/C lighting bus in

5 Low Lighting I Lighting bus common

6 Antenna Transfer #1 Output O Gnd = Xpndr #1 Selected/ActiveOpen = Xpndr #1 Not Selected

7 Standby (not)/On #1 O Gnd = Xpndr #1 Standby/ActiveOpen = Xpndr #1 On


9 Remote Function Test (not)/ (External Range Configuration)

I Remote Function Test:Gnd = ActivatedOpen = Not Activated.

External Range Configuration:(-XX04 unit versions)Gnd = Select RangeOpen = Extended Range.

10 I Reserved - Reply Input

Table 2005 KFS 578A Control Unit Connector Pin Names (P5781) (Sheet 1 of 2)

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11 Control Disable (not) I Control Unit Disable:Gnd = ActivatedOpen = Not Activated.

12 Master (not)/Slave I Gnd = MasterOpen = Slave

13 Emergency (not) I Squawk Code 7700:Gnd = ActivatedOpen = Not Activated.

14 Spare

15 External Standby/(Manual/Auto)

I External Standby:Gnd = Standby ActiveOpen = Inactive

Manual/Auto:(-XX04 Unit versions)Gnd = Auto Pop-UpOpen = Manual

16 Dim Select I Gas Discharge Display Dimming:Gnd = Follows A/C lighting busOpen = Follows photocell+28 Vdc = Maximum brightness.

17

18

19 Transponder 1 Fail DSC #2 I Gnd = Normal operationOpen = Transponder 1 failure


21 External Ident I Gnd = ActivatedOpen = Not Activated

22 Spare

23 Spare

24 ATE Test I Gnd = ActivatedOpen = Not Activated

25 Warning and Caution (not) O A/C Warning/Caution Panel:Gnd = Unit FailureOpen = Valid (No Failure)

26 Polarizer Key Polarizer key

27 Antenna Transfer #2 output O Gnd = Xpndr #2 Selected/ActiveOpen = Xpndr #2 Not Selected

28 On #1(not) O On transponder #1

29 On #2(not) O On transponder #2 (dual)

Table 2005 KFS 578A Control Unit Connector Pin Names (P5781) (Sheet 2 of 2)

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(f) PS-578A Mode S/TCAS Control Unit Connectors

The PS-578A control unit has one 29-pin (J1) and one 9-pin (J2) connector mounted on the rear of the unit. The connectors are keyed to prevent improper connector in-sertion. The connectors are shown in Figure 2005 PS-578A Mode S/TCAS Control Unit Rear Connector (J1) and Figure 2006 PS-578A Mode S/TCAS Control Unit Rear Con-nector (J2) and the signals connected to each pin are defined in Table 2006 PS-578A Control Unit Connector (J1) Pin Definitions and Table 2007 PS-578A Control Unit Connector (J2) Pin Definitions.

The interwiring diagrams define the input and output signal connections to the Mode S/TCAS control unit con-nectors.

Figure 2005 PS-578A Mode S/TCAS Control Unit Rear Connector (J1)

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Table 2006 PS-578A Control Unit Connector (J1) Pin Definitions (Sheet 1 of 2)


1 28Vdc Unit Power I 28 Vdc power input

2 Aircraft Ground I Aircraft ground

3 28Vdc Lighting I 28 Vdc A/C lighting bus input

4 5Vdc Lighting I 5 Vdc/Vac A/C lighting bus in

5 Low Lighting I Lighting bus common




9 Remote Function Test (not)/ (External Range Configuration)

I Remote Function Test:Gnd = ActivatedOpen = Not Activated.

External Range Configuration:(KFS 578A -XX04 emulations)Gnd = Select RangeOpen = Extended Range.

10 I Reserved - Remote Reply In

11 Control Disable (not) I Control Unit Disable:Gnd = ActivatedOpen = Not Activated.

12 Master (not)/Slave I Gnd = MasterOpen = Slave


14 Spare

15 External Standby/(Manual/Auto)

I External Standby:Gnd = Standby ActiveOpen = Inactive

Manual/Auto:(KFS 578A -XX04 emulations)Gnd = Auto Pop-UpOpen = Manual

16 Dim Select I Display Brightness:Gnd = Follows A/C lighting busOpen = Follows photocell

17

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Table 2006 PS-578A Control Unit Connector (J1) Pin Definitions (Sheet 2 of 2)


18




22 Spare

23 Spare

24 (*FCDE)/ ATE Test I (*FCDE):Gnd (at power On) = Activated.Rotate Range or A/N/B knobs to emulate KFS 578A version #.

ATE Test:Gnd = ActivatedOpen = Not Activated

25 Warning and Caution (not) O A/C Warning/Caution Panel:Gnd = Unit FailureOpen = Valid (No Failure)

26 Polarizer Key Polarizer key

27 Antenna Transfer #2 output O Gnd = Xpndr #2 Selected/ActiveOpen = Xpndr #2 Not Selected

28 On #1(not) O On transponder #1


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Figure 2006 PS-578A Mode S/TCAS Control Unit Rear Connector (J2)

Table 2007 PS-578A Control Unit Connector (J2) Pin Definitions


1 Shield Ground/429 Common I ARINC 429 Common






7 429 Output (A) O Low Speed ARINC 429

8 429 Output (B) O Low Speed ARINC 429

9 Spare

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(g) PS-550 Mode S/TCAS Control Unit Connector

The electrical connector for the PS-550 control unit are mounted on the rear panel of the unit. The connector (J1) is keyed to prevent improper connector insertion. The connector is shown in Figure 2007 PS-550 Mode S/TCAS Control Unit Rear Connector and the signals connected to each pin are defined in Table 2008 PS-550 Control Unit Connector Pin Name Definitions.

The interwiring diagrams define the input and output signal connections to the control unit connector.

Figure 2007 PS-550 Mode S/TCAS Control Unit Rear Connector

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Table 2008 PS-550 Control Unit Connector Pin Name Definitions (Sheet 1 of 3)


1 28Vdc Unit Power I +28 Vdc aircraft power

2

3 28Vdc Unit Power I +28 Vdc aircraft power

4 429 Output (B) O Low speed ARINC 429

5 429 Output (A) O Low speed ARINC 429

6 Reserved

7 Reserved

8 Antenna Transfer #2 Output O


10 429 Input #1 (B) I Low speed ARINC 429

11 429 Input #1 (A) I Low speed ARINC 429

12 429 Input #2 (B) I Low speed ARINC 429

13 429 Input #2 (A) I Low speed ARINC 429

14 Reserved

15 Reserved

16 Reserved

17 Reserved



20 Remote Functional Test (not)/ Ext Range Config

I Remote Test (Pin 24 Open):Gnd = Remote Test activeOpen = Normal operation

Extended Range (Pin 24 Gnd):Gnd = Extended Range activeOpen = Normal Range


22 Reserved

23 Reserved

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24 Software 040X In I Gnd (power On) = Activated:pin 20 = Extended Range pin 53 = Manual/Auto mode.

Open (power On) = Not Active: pin 20 = Remote Funct Testpin 53 = Standby.

25 Reserved

26 Standby (not)/On #2 O Standby switching (dual)

27 Strap Common I Ground

28 Reserved

29 Reserved

30 Reserved

31 Reserved

32 Aircraft Ground I Ground

33 Reserved

34 Reserved

35 Reserved

36 Reserved

37 Reserved

38 Chassis Ground I Ground

39 Reserved

40 Reserved

41 Warning and Caution (not) O A/C Warning/Caution Panel:Gnd = Unit FailureOpen = No Failure

42 Range Control Enable In I Open = Normal 3, 5, 10, 15 nm.

Open (+Pin 24 Gnd, +Pin 20 Gnd) = Extended 3,5,10,15,20,40 nm.

Gnd = Range control disabled.

43 Aircraft Ground I Ground

44 Standby (not)/On #1 O Standby switching

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45 FCDE Test I External ATE bench test enable



48 28Vdc Lighting I +28 Vdc lighting bus

49 Reserved

50 5Vdc Lighting I +5 Vdc lighting bus

50 5Vac Lighting I 5 Vac lighting bus

51

52 Remote Reply In I Reply outputs from transponder

53 External Standby Input/(Manual/Auto Input)

I Ext Standby (Pin 24 Open):Gnd = Standby activatedOpen = Standby not activated.

Manual/Auto (Pin 24 Gnd):Gnd = Manual Traffic activatedOpen = Auto Traffic activated.

54 Reserved

55 Reserved

56 Honeywell/Collins Configuration In I Gnd = Honeywell (MST 67A)Open = Collins (TDR-94D)

57 Reserved

58 Reserved

59 Aircraft Ground Ground

60 Spare

61 Reserved

62 Low Lighting I Lighting Common

63

64

65 On #1(not) O On Transponder #1

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(h) CD 671C Control Unit Connectors

The two 24-pin electrical connectors for the CD 671C control unit are mounted on the rear panel of the unit. The connectors are keyed (pin 2, pin 25) to prevent im-proper connector insertion. The connectors are shown in Figure 2008 CD 671C Control Unit, Rear Connectors and the signals connected to each pin are defined in Table 2009 CD 671C Control Unit, Connector Pin Names.

Interface diagrams that define the input and output signal connections to the CD 671C control unit are found in the MST 67A Mode S Transponder Installation Manual.

Figure 2008 CD 671C Control Unit, Rear Connectors

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Connector P6711


1 Antenna Transfer #1 O Antenna Switching

2 Standby/On #1 O Standby Switching

3 Transponder #2 Fail #3 I Transponder #1 Fail (Fail=Open; No Fail=18-33 V dc)

4 Standby/On #2 O Standby Switching (Dual)

5 Transponder #1 Fail #3 I Transponder #1 Fail (Fail=Open; No Fail=18-33 V dc)

6 Warning and Caution O Warning and Caution (Computer)

7 Transponder #2 Fail #2 I Transponder #2 Fail (Fail=Open)

8 Antenna Transfer #2 O Antenna Switching


10 On #2 O On Transponder #2 (Dual)

11 Aircraft Ground I Aircraft Ground



14 Transponder #1 Fail #1 I Transponder #1 Fail (Fail=5 V)

15 ATE Test I External ATE Test Enable


17 Reply Input I Reserved

18 External Ident I External Ident


20 Control Disable I Control Unit Disable


22 Spare Input Discrete #2

23 Spare

24 Emergency I Squawk Code 7700


Table 2009 CD 671C Control Unit, Connector Pin Names (Sheet 1 of 2)

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Connector P6712


1 ARINC 429 #1 (A) O Low Speed

2 Polarizer Key

3 ARINC 429 #1 (B) O Low Speed

4 ARINC 429 #2 (A) O Low Speed


6 ARINC 429 #2 (B) O Low Speed

7 ARINC 429 Control (A) O Low Speed (Altitude Data)


9 ARINC 429 Control (B) O Low Speed (Altitude Data)


11 External Standby I External Standby


13 Master/Slave I Master/Slave

14 Remote Functional Test I Remote Functional Test


16 Spare Input Discrete


18 28 Vdc Lighting Bus I 28 Vdc Lighting Bus

19 5 Vdc Lighting Bus I 5 Vdc Lighting Bus

20 Lighting Low I Lighting Common

21 5 Vac Lighting Bus I 5 Vac Lighting Bus

22 On #1 O On Transponder #1 (Dual)


24 28 Vdc Aircraft Power I 28 Vdc Aircraft Power


Table 2009 CD 671C Control Unit, Connector Pin Names (Sheet 2)

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(i) GC 362A TCAS Graphics Processor Connector

The 50-pin-electrical connector (P3621) for the GC362A Graphics Processor Unit is located on the front panel of the unit. The connector is keyed (pin 42) to prevent improper connector insertion. The connector is shown in Figure 2009 GC 362A TCAS Graphics Processor, Rear Connector and the connector pins are defined in Table 2010 GC 362A TCAS Graphics Proc. -0101, Connector Pin Names, Table 2011 GC 362A TCAS Graphics Proc. -0103, Connector Pin Names and Table 2012 GC 362A TCAS Graphics Proc. -0203, Connector Pin Names.

Interface diagrams Figure 2033 GC 362/Bendix TCAS In-terface Drawing, Figure 2034 GC 362/Honeywell TCAS In-terface Drawing, and Figure 2035 GC 362/Collins TCAS In-terface Drawing define the input and output signal con-nections to the TCAS Graphics Processor connectors.

Figure 2009 GC 362A TCAS Graphics Processor, Rear Connector

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Connector P3621


1 Polarizer Pin

2 Program 1 I Indicator Sweep Characteristic

3 Program 2 I Indicator Manufacturer


5 HS429+ I 429 High Speed +

6 HS429- I 429 High Speed -

7 LS429+ I 429 Low Speed +

8 LS429- I 429 Low Speed -

9 CMIN I Circle Mode In (NAV Interface)

10 Mode I Pushbutton Wx/TCAS Mode Select

11 RNG0 I Honeywell/Collins Range 0



14 EXTRED- I External Red In -

15 EXTRED+ I External Red In +

16 EXTGRN- I External Green In -

17 EXTGRN+ I External Green In +

18 EXTBLU- I External Blue In -

19 EXTBLU+ I External Blue In +

20 EXTSEL- I External Select In -

21 EXTSEL+ I External Select In +

22 EXT EXT I External External Enable(NAV Graphics Active)

23 EXTENA O External Enable Out

24 Visual O Display Valid

25 Red + O Red Out +

Table 2010 GC 362A TCAS Graphics Proc. -0101, Connector Pin Names (Sheet 1 of 2)

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Connector P3621


26 Red - O Red Out -

27 GRN + O Green Out +

28 GRN - O Green Out -

29 BLUE + O Blue Out +

30 BLUE - O Blue Out -

31 SEL - O Select Out -

32 SEL + O Select Out +

33 SSBY O Honeywell Standby

34 SVR + I Honeywell Vertical Ret. +

35 SVR - I Honeywell Vertical Ret. -

36 SHR + I Honeywell Horizontal Ret.+

37 SHR - I Honeywell Horizontal Ret.-

38 BVR + I Bendix Vertical Ret.+

39 BVR - I Bendix Vertical Ret.-

40 GND I Aircraft Ground


42 Polarizer Pin

43 No Connection

44 Aircraft Power I + 28 V dc Aircraft Power


46 POP I Pop Up Discrete

47 DISP I Display Discrete

48 No Connection

49 No Connection

50 SGND I Shield Ground

Table 2010 GC 362A TCAS Graphics Proc. -0101, Connector Pin Names (Sheet 2)

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Connector P3621


1 Polarizer Pin





















22 EXT EXT I External External Enable(NAV Graphics Active)





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Connector P3621









33 SSBY O Honeywell/Collins Standby

34 SVR + I Honeywell/Collins Vertical Ret. +

35 SVR - I Honeywell/Collins Vertical Ret. -

36 SHR + I Honeywell/Collins Horizontal Ret.+

37 SHR - I Honeywell/Collins Horizontal Ret.-





42 Polarizer Pin

43 No Connection





48 RNG3 I Honeywell Range 3

49 No Connection



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Connector P3621


1 Polarizer Pin





















22 EXT EXT I External External Enable (NAV Graphics Active)





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Connector P3621









33 SSBY O Collins Standby

34 SVR + I Collins Vertical Ret. +

35 SVR - I Collins Vertical Ret. -

36 SHR + I Collins Horizontal Ret.+

37 SHR - I Collins Horizontal Ret.-





42 Polarizer Pin

43 No Connection





48 No Connection

49 No Connection



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(j) TCAS/Weather Radar Display Connectors

See TCAS/Weather Radar display manuals referenced in the SYSTEM DESCRIPTION section of this manual.

(k) Omni Antenna Connector

Connectors for the coaxial cable connection from the TCAS processor to the omni antenna may be N-type female or blade type connectors dependent on user installation requirements.

6. Equipment Installation

A. TPU 67A TCAS Processor Installation

NOTE: To allow for inspection or repair of the connector assem-bly wiring, sufficient lead length should be left so the rear connector assembly may be pulled forward several inches when the mounting hardware for the rear connector assembly is removed. Also a bend should be made in the harness (at the rear connectors) to allow water droplets, that might form on the harness due to condensation, to drip off at the bend and not collect in the connector.

CAUTION: DO NOT INSTALL THE PROCESSOR IN A CLOSED, HOT ENVIRONMENT THAT MAKES THE AMBIENT TEMPERATURE RISE ABOVE TSO LIMITS FOR THE UNIT WHEN OPERATING.

The mounting tray connector must be wired according to the interface diagrams and the manufacturer’s instructions. Mounting of the TCAS processor is accomplished by use of its associated mounting tray. When locating the mount in the aircraft, allow at least two inches free space on the top and sides of unit to provide sufficient clear-ance for sway and ease of removal of the TCAS processor. Clean and prepare all mounting surfaces to insure a good electrical bond be-fore installing the mounting tray.

Once the mounting tray is installed, the TCAS processor unit may easily be installed into the mounting tray. Place the TPU 67A on the mounting base and slide it backward until the electrical con-nector is fully engaged. Then secure the front of the unit to the mount by tightening the two knurled screw clamps (located on front of the mount) until they are firmly seated over the hold-down hooks on the front of the TCAS processor.

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B. Configuration Module Installation

The configuration module connector must be wired according to Figure 2026 TCAS II Configuration Pins Interface Drawing. Mounting of the configuration module is accomplished by use of its integrated mount-ing bracket. Refer to Figure 2013 CM 67A/CM 2000 Configuration Mod-ule Outline Drawing for additional mounting considerations. Clean and prepare all mounting surfaces to insure a good electrical bond before installing the configuration module.

C. TCAS Directional Antenna Installation

NOTE: To ensure proper bearing performance, an approved Honey-well antenna adapter plate is required.

(1) Directional Antenna Positioning and Wiring Requirements

Refer to paragraph 5.B. (1) TCAS Antenna Location, 5.C. (5) Antenna Cable Type Selection, and 5.C.(6) (c) Directional An-tenna Connectors.

(2) Directional Antenna Adapter Plate

Before mounting the antenna adapter plate ensure the aircraft mounting surface is clean and prepared for a good electrical bond. See Figure 2011 ANT 67A Directional Antenna Adapter and Moldable Shim, Figure 2014 ANT 67A Directional Antenna Outline Drawing, and paragraph 11. ANT 67A Directional Antenna Adapter Plate Installation for details.

(3) Directional Antenna Footprint Drilling and Mounting

Before mounting the antenna ensure the antenna adapter plate surface is clean. The directional antenna is mounted on the aircraft by 4 mounting screws. A three inch center hole (or four one inch holes) must be provided on the aircraft for at-taching the four coaxial cables to the antenna connectors. An "O" ring gasket is installed around the outside circumference of the center hole. An approved lock-tight sealant should be applied to each mounting screw.

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After the antenna is installed, an approved silicon should be applied around the outer circumference of the antenna to seal the antenna to the aircraft fuselage. For mounting hole di-mensions, mounting screw type, antenna footprint patterns, antenna adapter plate patterns and other mounting details re-fer to Figure 2011 ANT 67A Directional Antenna Adapter and Moldable Shim, Figure 2014 ANT 67A Directional Antenna Outline Drawing, and paragraph 11. ANT 67A Directional Antenna Adapter Plate Installation for antenna adapter plate installation in-formation.

When the antenna has been mounted, connect the four coaxial cables from the TCAS processor to the bottom of the antenna.

(4) Electrical Bonding

Electrical bonding resistance of installed antenna to air-craft skin should not exceed 0.01 Ohm dc and provide even RF bonding to the airframe.

D. TCAS Omnidirectional Antenna Installation

(1) Antenna Positioning and Wiring Requirements

Refer to paragraph 5.B. (1) TCAS Antenna Location and 5.C. (5) Antenna Cable Type Selection.

(2) Mounting

Refer to manufacturer’s installation documentation.

E. IVA-81A/C/D TA/RA/VSI and IVA-81B RA/VSI Installation

Install the IVA-81A/IVA-81C/IVA-81D TA/RA/VSI or IVA-81B RA/VSI traffic display unit in a location suitable for viewing and ease of operation in the cockpit. The IVA-81A/IVA-81C/IVA-81D TA/RA/VSI and IVA-81B RA/VSI traffic display uses customer supplied screw clamp fasteners to secure it to the instrument panel. Use the outline drawings in Figure 2015 IVA 81A (TA/RA/VSI) Outline Drawing, Figure 2016 IVA 81B (RA/VSI) Outline Drawing, Figure 2017 IVA 81C (TCAS) Outline Drawing, or Figure 2018 IVA 81D (TCAS) Outline Drawing as a guide to position the display unit and to cut and drill the instru-ment panel.

Attach the electrical connector to the rear of the unit. If an op-tional aircraft pressure source is used as an input to the IVA-81A/IVA-81C/IVA-81D TA/RA/VSI or IVA-81B RA/VSI, attach the pneumatic tube to the rear of the unit.

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F. Transponder and Mounting Tray Installation

Install the tray-mounted MST 67A transponder in a location free from excessive heat and vibration which provides convenient access for inspection and maintenance. To achieve maximum performance, the MST 67A should be installed adjacent to other receivers or boxes with similar functions. Forced-air cooling may be provided, but is not required.

G. KFS 578A/PS-578A/PS-550/CD 671C Control Unit Installation

Install the Mode S/TCAS control unit in a location suitable for viewing and ease of operation in the cockpit during flight. Use the outline drawings in Figure 2020 KFS 578A Control Unit Outline Draw-ing, Figure 2021 PS-578A Control Unit Outline Drawing, Figure 2022 PS-550 Control Unit Outline Drawing or Figure 2023 CD 671C Control Unit Outline Drawing as a guide to position the unit and to cut and drill the instrument panel.

Attach the electrical connector to the rear of the unit.

H. GC 362A TCAS Graphics Processor Installation

When configuring the GC 362A in a Honeywell Primus weather radar installation, pin 3 must be grounded. Not all Honeywell indicators have a System Trigger output. Those indicators must be modified to provide that function. Refer to Honeywell Sales Bulletin #26-85. Some Honeywell indicators cannot be modified to provide a System Trigger output. In that case, another Honeywell indicator that pro-vides that feature must be installed.

Refer to the Figure 2033 GC 362/Bendix TCAS Interface Drawing, Fig-ure 2034 GC 362/Honeywell TCAS Interface Drawing, and Figure 2035 GC 362/Collins TCAS Interface Drawing when fabricating the wire har-ness. Refer to Figure 2019 GC 362 TCAS Graphics Processor Outline Drawing for mounting dimensions.

7. Inspection and System Checkout

During installation, three stages of testing are required to ensure proper operation of CAS 67A TCAS II system components:

• First, a system interwiring check is performed before installation of the TCAS processor and display units. Verify that aircraft and TCAS II system interconnections are correct before power is applied.

• Second, a visual inspection of the equipment and connections is made after the units are installed.

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• Third, a post-installation test is used to apply power and functionally check out the system. Successful completion of the post-installation test verifies proper operation of the CAS 67A TCAS II system.

A. System Interwiring Check

CAUTION: AFTER INSTALLATION OF THE CABLING AND BEFORE INSTALLATION OF THE EQUIPMENT, SUPPLY AIRCRAFT PRIMARY POWER TO THE UNIT CONNECTORS AND CHECK THAT POWER IS APPLIED ONLY TO THE PINS SPECIFIED IN THE INTERFACE DIAGRAMS.

Check the following aircraft system interconnections:

(1) Check that all cables and interwiring are installed according to paragraph 5. C. Interwiring and Cable Fabrication.

(2) Mag. Heading Input

(3) Attitude Input

(4) Mode S Transponder

• Encoding Altimeter Input

• Airspeed Strap

• Aircraft (Mode S) Address.

(5) Traffic Display Configuration Straps

• Display Configuration

• Vertical Speed Source Strap

(6) TA/RA/VSI Vertical Speed Source Strap


(8) Check wiring for proper destinations, opens, and shorts using the interface diagrams.

(9) Check or verify RF cables for electrical length matching, in-sertion loss and VSWR. Confirm that the four RF antenna coax cables meet 2.5 ±0.5 dB insertion loss requirements, the elec-trical length characteristics match within 135° and VSWR is 1.35:1 or better.

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(10) Check the transponder and DME interface.

Some installations may use a common control for the transpon-der and the TCAS. In that case the TCAS control comes from the transponder control unit.

CAUTION: IN CONFIGURATIONS WHERE TWO MODE S TRANSPONDERS ARE USED, THE INACTIVE TRANSPONDER MUST REMAIN IN “STANDBY” WITH THE POWER ON TO PREVENT A TCAS FLAG DURING TRANSPONDER SOURCE CHANGES. IN ADDITION, BOTH TRANSPONDERS MUST BE THE SAME TYPE.

B. Visual Inspection

Check that all units and cables are mounted according to Inspection/Check Procedure, Table 2013 Inspection/Check Procedure.

Table 2013 Inspection/Check Procedure is a visual inspection/check procedure that should be performed after system installation as part of a system checkout.

In addition, the procedure should be used as a periodic maintenance inspection check.

NOTE: For TCAS units not covered in this manual, refer to the installation section of the associated maintenance manual for proper inspection procedures.

EQUIPMENT INSPECTION/CHECK PROCEDURE

Mounting Rack • Inspect mating connector shell for floating hardware and connector shim on the TCAS rack.

• Inspect connectors and interwiring of transponder and graphics processor rack.

TPU 67A TCAS ProcessorMode S Transponder andConfiguration Module

• •

Inspect unit for any sign of damage.Check that unit is PROPERLY installed and that retaining mechanism and connectors are securely tightened.

Directional Antenna • Inspect antenna for any sign of damage.

• Check that antenna is PROPERLY installed and all mounting screws are firmlytightened.

• Ensure the four coaxial connectors are properly mated to antenna.

Table 2013 Inspection/Check Procedure

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Omnidirectional Antenna Transponder and TCAS (if installed)

• •

Inspect antenna for any sign of damage.Check that antenna is PROPERLY installed and all mounting screws are firmlytightened.

• Ensure that RF connector is securelytightened.

• If installed for TCAS, check that three (3) unused bottom antenna coaxes connected to the TPU 67A processor are connected to 50 Ω terminations.

Mode S/TCAS Control Unit • Inspect control unit for any sign ofdamage.

• Check that control unit is properly installed and all mounting screws arefirmly tightened.

• Ensure that connector is securelytightened.

Traffic Displays and/orTCAS/Radar Display

• •

Inspect display for any sign of damage.Inspect face of unit for cracks or scratches.

• Ensure that unit fits securely against the instrument panel when the locking clamps are engaged.

• Ensure that connectors are properlyconnected to rear of unit.

Table 2013 Inspection/Check Procedure

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C. Post-Installation Test

The post-installation test verifies the proper operation of the CAS 67A TCAS II system after the units have been initially installed. Thereafter, the procedure can be used as an operational check. The procedure is composed of a pretest setup, self-test, ground test, and ramp test. The following tests are performed on the ground.

(1) Test Equipment Required

The following ground test equipment is required for the tests:

• AST Bravo Computer or equivalent w/ Diagnostic Programs (See the DIAGNOSTIC APPENDICES for TCASDIAG and TPUDIAG - TPU 67A Field Diagnostic Program User Instructions).

• TCAS Ramp Test Set: TCAS 201, or equivalent

• Mode S Transponder Ramp Test Set: IFR 601, or equivalent.

• Pitot-Static Test Set

• Radio Altimeter Test Set, or equivalent

• Volt-Ohmmeter (DVM) (optional)

• 429 Bus reader (optional)

(2) Facilities Required

Many of the tests can be performed indoors. The TCAS scenario tests should be done in an area where the local traffic and signal multipath are not a factor. The bearing accuracy tests should be conducted outside, away from other operating air-craft. A 115 Vac 60 Hz power may be required for the test equipment.

WARNING: ADVISE THE LOCAL AIR TRAFFIC CONTROL BEFORE TESTING THE TRANSPONDERS OR TCAS SYSTEM WITH A SYNTHETIC ALTITUDE, TO ACKNOWLEDGE POSSIBLE INTERACTION WITH OTHER TCAS EQUIPPED AIRCRAFT.

(3) Pretest Setup

This section and the self-test section confirm the proper op-eration of the TCAS control unit and traffic displays. This section sets initial conditions required for self-test of the system.

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The pretest checks the CAS 67A system input power, configures the operational controls, and verifies the system is ready for testing. It is assumed that the person performing these tests has a working knowledge of the CAS 67A TCAS II system and of TCAS control and display units, and is qualified to perform these tests on the aircraft.

(a) Ensure that all aircraft systems are secure and safe. Check power bus meter to confirm that aircraft 28 Vdc and 26 Vac 400 Hz power sources are operational.

(b) Check that aircraft 5 Vac/Vdc or 28 Vdc panel background lighting power source and dimmer control is operational by adjusting the cockpit dimmer switch for proper cock-pit panel background illumination.

(c) Initial set-up:

1 Check that the transponder, TCAS, and Radar sys-tems are OFF. If applicable, the selected encod-ing altitude source should be #1. If applicable, the ADC (Air Data Computer) source should be set to normal.

2 Apply power to the aircraft systems.

Operate appropriate aircraft circuit breakers to apply power to TCAS processor, traffic advisory displays and all other aircraft equipment con-nected to the TCAS processor subsystem. Check that circuit breakers remain closed (pushed-in).

3 Allow enough time for equipment warm-up. Equip-ment in the TCAS II system requires one minute for equipment warm-up. External sensors may require more than one minute warm-up time.

(d) Configuration Strapping:

Aircraft configuration strapping is stored in the con-figuration module via a personal computer executing TPUDIAG/TCASDIAG software across the RS-232 port. Fol-low instructions for configuration programming in the TPUDIAG/TCASDIAG DIAGNOSTIC APPENDICES of this manual.

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(e) On the Traffic Display:

1 Adjust the "BRT" control for optimum viewing.

2 If a TCAS Graphics Processor is installed, on the Radar Indicator traffic display:

Select the Weather "TST" mode.

Adjust the "BRT" control for optimum viewing.

(f) On the Mode S/TCAS control unit:

1 Select the PWR switch to ON. (Some versions are ON at system power up).

2 Select the SBY switch to SBY mode.

3 Select the ABOVE/NORM/BELOW switch to "NORM".

4 Select the T/WX switch to "TCAS", if applicable.

5 Select Range to the 5 nautical mile (nm) range.

NOTE: In some installations the range must be selected on the traffic display.

(g) On the traffic display screen the following should be visible:

1 No "TCAS" flag annunciation.

2 "TCAS STBY."

3 The TA/VSI vertical speed needle should indicate 0 fpm.

4 Check that brightness of traffic display can be controlled by the appropriate control. Bright-ness of traffic display may be controlled by the aircraft dimmer switch or by the BRT control on the display unit.

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(h) On the Mode S/TCAS control unit select ON position, the following conditions should exist:

1 Traffic display should indicate "TA" or "TA ONLY."

2 No faults or fail annunciations are present on traffic display.

3 Traffic may be displayed on the traffic display depending upon the TCAS strapping configuration and whether traffic exists in the area:

• Non-threat Traffic, displayed as an open white diamond.

• Proximity Intruder traffic, displayed as a filled white diamond.

• Traffic Advisory (TA) traffic, displayed as a filled yellow circle.

• Resolution Advisory (RA) traffic, displayed as a filled red square.

(4) Self-Test

On the TCAS control unit, initiate the TCAS II system self-test. The following events should occur during the test pe-riod:

On the traffic display a test pattern will be displayed that allows verification of each type of intruder symbol that can be displayed.

See Figure 1001 TCAS Test Pattern for a picture of the test pattern. During the self-test, the word "TEST" is displayed in the lower left corner of the display. The following sym-bols are displayed:

(a) Resolution Advisory (solid red square) will appear at 3 o’clock, range of 2 nm, at 200 feet relative altitude, above (+02) with no VS arrow.

(b) Traffic Advisory (solid yellow circle) will appear at 9 o’clock, range of 2 miles, at 200 feet relative alti-tude, below (-02) with ascending arrow.

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(c) Proximity traffic (solid white diamond, or Honeywell - Cyan) will appear at 1 o’clock, range 3.6 miles, at 1000 feet relative altitude, below (-10) with descending ar-row.

(d) Non-Threat traffic (open white diamond, or Honeywell - Cyan) will appear at 11 o’clock, range of 3.6 miles, at 1000 feet relative altitude, above (+10) with no arrow.

At the conclusion of a successful self-test, a synthesized voice announces, "TCAS System Test OK." Should a failure be detected during self test, the audio message says, "TCAS Sys-tem Test Fail."

(5) Ground Test

These ground tests are necessary to meet the requirements of AC 20-131A. While the tests are organized in a sequential fashion, they may be completed in a random order to accommo-date other conditions. The person performing these tests should be familiar with the TCAS equipment, the aircraft in-stallation and the supporting test equipment.

NOTE: In the test results space " ", enter "P" for Passed, "F" for Failed and/or fill in the results or comments. If the section does not apply, write "N/A".

(a) TCAS Power Checks

1 Verify aircraft power to TCAS.

2 Pull the 5 amp TCAS processor circuit breaker.

3 Verify that the "TCAS" flag appears on the traffic display.

4 Reset the circuit breaker. Verify that the flag clears.

Pass/Fail _______

5 Pull the 1 amp Mode S/TCAS Control circuit break-er.


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Pass/Fail

8 Pull the 5 amp Mode S transponder(s) circuit breaker.



Pass/Fail

11 Pull the Traffic Display or TCAS Graphic Proces-sor circuit breaker.

NOTE: The above circuit breaker should be for the unit providing a valid to the TCAS Processor at pin(s) A34, A35 or B85, B86.

12 Verify that the appropriate flag appears INVALID.


Pass/Fail

14 Disable or turn off the 26 Vac 400 Hz reference voltage.


16 Reset the 26 Vac 400 Hz reference voltage. Verify that the flag clears.

Pass/Fail

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(b) Mode S/TCAS Control Functions

1 On the TCAS control unit exercise all the TCAS control functions and observe for correct opera-tion.

Select the TA/RA switch to ON mode.

2 On traffic display screen, check that "TA" or "TA ONLY" annunciation is displayed.

Pass/Fail

3 Test the ABOVE/NORMAL/BELOW function as follows:

a On the TCAS control unit, select ABOVE/NOR-MAL/BELOW to ABOVE. On traffic display screen, "ABOVE" should be annunciated. Traffic 2700 ft. below to 8700 ft. above can be displayed.

Traffic Display

b Select BELOW. The screen should annunciate "BELOW" in place of the "ABOVE" annuncia-tion. Traffic 8700 ft. below to 2700 ft. above can be displayed.

Traffic Display

c Set switch to NORMAL. The screen area that annunciated "ABOVE" or "BELOW" should be blank. Traffic 2700 ft. below to 2700 ft. above can be displayed.

Traffic Display

4 On the traffic display, check the TCAS ranges to observe the range annunciations and range rings.

NOTE: Not all ranges are available in every configuration.

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a Set TCAS RANGE switch to 3 nautical miles. The following properly scaled range rings should be visible:

Two and three nautical mile range rings.

Radar Indicator

b Set TCAS RANGE switch to 5 nautical miles. The following properly scaled range rings should be visible:

Two and five nautical mile range rings.

Radar Indicator

c Set TCAS RANGE switch to 10 nautical miles. The following properly scaled range rings should be visible:

Two, five and ten nautical mile range rings.

Radar Indicator

d Set TCAS RANGE switch to 15 nautical miles. The following properly scaled range rings should be visible:

Two, five and fifteen nautical mile range rings.

Radar Indicator

e Set TCAS RANGE switch to 20 nautical miles. The following properly scaled range rings should be visible:

Two, five, ten and twenty nautical mile range rings.

Radar Indicator

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f Set TCAS RANGE switch to 40 nautical miles. The following properly scaled range rings should be visible:

Two, five, twenty and forty nautical mile range rings.

Radar Indicator

NOTE: On the traffic display unit, an outer ring represents maximum nautical mile (nm) display scal-ing as selected on the RANGE switch.

5 If applicable, test the FL (Flight Level) func-tion as follows:

a Press the FL switch.

b Observe that the traffic display indicates "FL" in the upper left hand corner. It will be FL --- (flagged) on most displays unless encoding altitude source is higher than 18,000 ft.

Pass/Fail

6 If applicable, check that the traffic modes (T/WX) can be selected on the color radar indicator as follows:

a Select the T/WX switch to indicate "WX" (Weather Only).

Observe that the traffic display (radar in-dicator) annunciates "TA AUTO," but unless TA traffic is present only the radar pic-ture is displayed.

b Select the T/WX switch to "T/WX" (TCAS and Weather).

Observe that the traffic display annunci-ates "TA" or "TA ONLY" and shows both traf-fic and weather if the radar is ON.

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c Select "TCAS" (TCAS ONLY) with the T/WX switch.

Observe that the traffic display annunci-ates "TA" or "TA ONLY" and shows TCAS traf-fic but no weather is displayed.

Pass/Fail

7 TCAS Sensor Input Checks

Confirm the sensor input to TCAS by using a diag-nostic computer program. Additionally, the fault source can be viewed on the radar indicator or by reading the LED fault code on the processor.

a Mag. Heading Interface

Verify the heading source interface to the TCAS Processor. Confirm the heading source and measure the inputs at the TPU 67A TCAS Processor. Refer to the drawings for the proper pin assignments.

The TCAS and heading system should be oper-ating normally for the following test. Connect the Diagnostic computer to the TPU 67A through the RS 232 port. Run the TCAS II I/O Data screen and observe the follow-ing on the Diagnostic computer.

Monitor the heading source in the cockpit. Observe the Mag. Heading readout on the computer. The computer readout should agree to within a few degrees with the cockpit heading display. Record a heading:Between 0° and 120° Between 121° and 240° Between 241° and 359°

The Heading Status on the computer should indicate VALID. The Heading Type should indicate Synchro or ARINC 429.

Flag the heading source by pulling the cir-cuit breaker.

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Verify that the Heading Status goes IN-VALID.

Verify that the "TCAS" flag appears on the traffic display.

Reset the circuit breaker. Verify that the TCAS flag clears.

Pass/Fail

b Encoding Altitude

Verify that the encoding altitude is prop-erly interfaced to the TCAS processor. Confirm that the encoding altitude of the transponder and TCAS agree.

CAUTION: PRECAUTIONS MUST BE TAKEN TO IN-SURE THAT THE ALTITUDE TEST OF THE TRANSPONDER DOES NOT INTER-FERE WITH OTHER TCAS EQUIPPED AIRCRAFT. SHIELDING THE TRAN-SPONDER AND TCAS ANTENNAS IS THE BEST WAY TO PREVENT INTERFERENCE WITH OTHER AIRCRAFT.

The TCAS, transponder and encoding altitude source(s) should be operating normally for the following test. Connect the Diagnostic computer to the TPU 67A through the RS 232 port. Run the TCAS II I/O Data screen and observe the following on the Diagnostic computer.

Monitor the altitude source in the cockpit. Set the baro to 29.92". Observe the Enc. Al-titude readout. The computer readout should agree to within 50 ft. of the cockpit al-timeter. The encoding altitude on the tran-sponder test set should agree with the di-agnostic computer readout.

The Enc. Alt. Status on the computer should indicate VALID.

The Enc. Alt. Resolution should indicate coarse or fine.

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The XPNDR Source should indicate # 1. (Se-lect #1 if necessary).

Confirm the following Encoding Altitudes at the altimeter, diagnostic computer and transponder:

Altitude at 2,000 ft.

Computer screen indicates ft.Transponder indicates ft.






Computer screen indicates ft.Transponder indicates ft

CAUTION: THE ABOVE TEST STEP CHECKS BOTH LOGIC STATES FOR ALL GILLHAM LINES. OTHER TESTS MAY BE ADE-QUATE FOR SOME INSTALLATIONS.

Flag the encoding altitude source by pull-ing the circuit breaker.

Verify that the Enc. Alt. Status goes IN-VALID.



Enc. Altitude Source #1 Pass/Fail

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If applicable, select the other encoding altitude source and repeat steps 2 and 3.

Enc. Altitude Source #2 Pass/Fail

c Attitude Interface

Verify the attitude interface to the TCAS Processor. Confirm the pitch and roll at-titude source and measure the inputs at the TPU 67A TCAS Processor.

The TCAS and attitude system should be op-erating normally for the following test. Connect the Diagnostic computer to the TPU 67A through the RS 232 port. Run the TCAS II I/O Data screen and observe the follow-ing on the computer screen.

Monitor the attitude source in the cockpit. Observe the Pitch and Roll attitude read-outs. The computer screen readouts should agree to within a few degrees of the cockpit heading display. Record a roll and pitch attitude other than (0.0°) . Is it consistent with the aircraft’s attitude?

The Pitch and Roll Status on the computer should indicate VALID.

The Attitude Type should indicate SYNCHRO or ARINC 429.

Flag the attitude source by pulling the circuit breaker.

Verify that the Pitch and Roll Status goes INVALID.



Pass/Fail

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d Radio Altimeter Interface

Verify that the radio altimeter is properly interfaced to the TCAS processor. Confirm the radio altitude configuration straps and measure the input at the TPU 67A TCAS pro-cessor.

The TCAS and radio altimeter source(s) should be operating normally for the fol-lowing test. Connect the Diagnostic com-puter to the TPU 67A through the RS 232 port. Run the TCAS II I/O Data screen and observe the following on the computer.

Monitor the radio altimeter source in the cockpit. Observe the Radio Altimeter read-out. The computer readout should agree with the cockpit radio altimeter indicator. If the computer display is too erratic, measure the voltage with an alternate test.

The Rad. Alt. Status on the computer should indicate VALID.

The Rad. Alt. Type should indicate ARINC 429, KING, SPERRY, COLLINS, or ARINC 552.

The Rad. Alt. Source should indicate # 1. (Select #1 if necessary).

Using the radio altimeter self-test, con-firm the following:

With Radio altitude source at 0 ft. (on- ground), the computer indicates ft.

When Radio altimeter self-test (40-50’) is pressed, the computer indicates ft.

Do these readings agree with the cockpit display?

Yes/No _______

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Alternate Method

Using a radio altimeter tester, confirm the following:

When the Radio altitude is at 0 ft., the Di-agnostic computer indicates ft.

When the Radio altitude is at 1,000 ft., the Diagnostic computer indicates ft.



Flag the Rad. Altimeter source by pulling the circuit breaker.

Verify that the Rad. Alt. Status goes IN-VALID.



Rad. Altimeter Source #1 Pass/Fail

If applicable, select the other Rad. Alti-tude source and repeat steps above.

Rad. Altimeter Source #2 Pass/Fail

e Aircraft Address & Airspeed Strapping and Logic Discretes

Determine that the configuration straps and logic discretes are correct. Verify the changes in logic discrete when the aircraft function is exercised. Use a Diagnostic computer program or a DVM to confirm the strap connections and logic changes.

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Refer to the drawings for the proper pin as-signments and the FAULT ISOLATION section for a description for the Diagnostic com-puter program.

The TCAS and related aircraft system should be operating normally for the following test. Connect the Diagnostic computer to the TPU 67A through the RS 232 port. Run the TCAS II I/O Data screen and observe the following on the Diagnostic computer.

The aircraft (MODE S) address for N- has an Octal code of and a Hex code of .

The computer screen shows A/C Address as N , Octal _______ and HEX _______

PASS/FAIL _______

The proper aircraft airspeed strapping for aircraft N- should be (150 - 300 kts) or (300-600 kts).

The computer screens shows Max. Airspeed as

PASS/FAIL

Disable the WOW logic, and check that the air/ground, (A22) mode changes from "ON-GROUND" (GND) to "AIRBORNE" (OPEN).

PASS/FAIL

Disable the landing gear logic and check that the gear position (A21) changes from "EXTENDED" (GND) to "RETRACTED" (OPEN).

PASS/FAIL

f Additional Strapping and Logic Discretes

Determine the additional configuration straps and logic discretes are correct. Refer to supporting drawings and documenta-tion if necessary to confirm the following items.

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The TCAS and related aircraft system should be operating normally for the following test. Connect the Diagnostic computer to the TPU 67A through the RS 232 port. Run the TCAS II I/O Data screen and observe the following on the Diagnostic computer.

The proper SPK AIR AUD (A73, A74, A75) strapping should be Watts.

Speaker Airborne Audio strapping is

The proper SPK GND AUD (A76, A77, A78) strapping should be Watts.

Speaker Ground Audio strapping is .

The proper PHN AIR AUD (A79, A80, A81) strapping should be mWatts.

Phone Airborne Audio strapping is .

The proper PHN GND AUD (A82, A83, A84) strapping should be mWatts.

Phone Ground Audio strapping is .

Confirm that ADVISORY INHIBIT #2 (A18) changes from Inhibited (GND) to Not-Inhib-ited (OPEN) when testing the GPWS. ADVISO-RY INHIBIT #1 (A17) is not connected.

PASS/FAIL .

The proper DISPLAY INTRUDER LIMIT (B77, B78, B79) strapping should be for intruders (Max.).

The PERFORMANCE LIMIT should be _______.

The CLIMB INHIBIT should be _______.

The INCREASE CLIMB INHIBIT should be _______.

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The INTRUDER FILE FORMAT should be _______.

The INTRUDER DISPLAY LIMIT is _______.

AIRBORNE FUNCTIONAL TEST should be _______.

AURAL OUTPUT FUNCTION should be _______.

ADV./ANN. CANCEL (A72) should be .

DISPLAY ALL TRAFFIC (A32) should be .

GROUND DISPLAY MODE (A33) should be .

ALT LIMIT should indicate _______.

Top Antenna elements (J1 - J4) indicate _______.

The HEX value of the antenna elements should indicate between 72 Hex and 8D Hex.

Bottom Antenna elements (J1 - J4) indicate _______.

The HEX value of the antenna elements should indicate between 72 Hex and 8D Hex. The value of the omni antenna elements J2 - J4 should indicate between 00 Hex and 0D Hex. Omni antenna, J1, should indicate near OO Hex.

Did all items PASS/FAIL?

(6) Ramp Test

This test requires the use of a TCAS Ramp Tester. Specific instructions for operating the ramp tester are contained in the applicable operator’s manual. Use the TCAS Ramp Tester to exercise the TCAS with various intruder aircraft scenarios. Monitor the displays and aural messages to verify that system response is correct.

(a) RA/TA Intruder Tests

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Evaluate proper operation of the TCAS system by observ-ing resolution advisories, traffic advisories, proxim-ity traffic, and "other" traffic. Confirm that the voice announcement is correct and occurs at the proper time.

At this time it will be necessary to have the appropri-ate systems operational.

WARNING: PRECAUTIONS MUST BE TAKEN TO INSURE THAT THIS TEST DOES NOT INTERFERE WITH OTHER TCAS EQUIPPED AIRCRAFT.

1 Apply static pressure to the airplane using the pitot-static tester. Increase the altitude to 20,000 ft.

NOTE: The TCAS and Transponder controls should be in Standby until the test al-titude is set. 20,000 ft. is selected to accommodate step 7. Other pressure altitudes may be used, if necessary.

2 Apply a radio altitude signal to the aircraft us-ing the radio altimeter test set or equivalent. Increase the radio altitude to 2,750 ft. or great-er, or above radio altimeter’s operational range.

3 Disable the WOW logic and put the aircraft systems into the "AIRBORNE" mode. The landing gear logic should remain in the "EXTENDED" or DOWN position.

4 Put the TCAS and transponder control units in the ON position. Select #1 Transponder.

5 Set up the TCAS ramp test set.

Using the TCAS ramp test set, create a scenario to simulate an approaching Mode C transponder equipped aircraft beginning at 10 nm, at an alti-tude of 20,100 feet, at a closure rate of +450 kts, and an altitude rate of 0 fpm. An alternate scenario may be required for some test sets.

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6 Initiate the intruder test on the TCAS ramp tester.

Verify that the intruder symbol corresponds to the scenario in bearing, distance, and relative altitude. Confirm that the audio announcement agrees with the scenario.

The intruder symbol will begin as an open white diamond with a relative altitude tag of +01. The bearing should be from the direction of the test antenna. The intruder will become proximity traffic at 6 nm; the white diamond will be filled. When the intruder becomes a TA (traffic advisory) the symbol will change to a yellow circle. Fi-nally, the intruder will become a red square when it becomes an RA (resolution advisory).

The TA/RA/VSI will command a 1500 fpm descent when the intruder becomes an RA. If no corrective ac-tion is taken, a corrective RA will be indicated by a 2500 fpm “INCREASE DESCENT” command.

For systems with TPU 67A 066-01146-0101,-0201:A "TRAFFIC, TRAFFIC" voice announcement should occur around 5.75 nm. Another command of “DE-SCEND, DESCEND, DESCEND” should occur around 3.9 nm. An “INCREASE DESCENT, INCREASE DESCENT” mes-sage will be annunciated at around 1 nm.

A “CLEAR OF CONFLICT” message will be issued when the threat has passed.

For systems with TPU 67A 066-01146-1111,-1211:A "TRAFFIC, TRAFFIC" voice announcement should occur around 5.75 nm. Another command of “DE-SCEND, DESCEND” should occur around 3.9 nm. An “INCREASE DESCENT, INCREASE DESCENT” message will be annunciated at around 1 nm. A “CLEAR OF CON-FLICT” message will be issued when the threat has passed.

Traffic Display(s) _______ Announcement

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7 Initiate a second intruder test on the TCAS ramp tester.

Using the TCAS ramp test set, create a second sce-nario to simulate an approaching Mode C transpon-der equipped aircraft beginning at 10 nm, at an altitude of 19900 feet, at a closure rate of +450 kts, and an altitude rate of 0 fpm.

Verify that the intruder symbol corresponds to the scenario in bearing, distance, and relative altitude. Confirm that the audio announcement agrees with the scenario.

The intruder symbol will begin as an open white diamond with a relative altitude tag of -01. The bearing should be from the direction of the test antenna. The intruder will become proximity traffic at 6 nm; the white diamond will be filled. When the intruder becomes a TA (traffic advisory) the symbol will change to a yellow circle. Fi-nally, the intruder will become a red square when it becomes an RA (resolution advisory).

The TA/RA/VSI will command a 1500 fpm climb when the intruder becomes an RA. If no corrective ac-tion is taken, a corrective RA will be indicated by a 2500 fpm “INCREASE CLIMB” command.

For systems with TPU 67A 066-01146-0101,-0201:A "TRAFFIC, TRAFFIC" voice announcement should occur around 5.75 nm. Another command of “CLIMB, CLIMB, CLIMB” should occur around 3.9 nm.

An “INCREASE CLIMB, INCREASE CLIMB” message will be annunciated at around 1 nm. A “CLEAR OF CON-FLICT” message will be issued when the threat has passed.

For systems with TPU 67A 066-01146-1111,-1211: A "TRAFFIC, TRAFFIC" voice announcement should oc-cur around 5.75 nm. Another command of “CLIMB, CLIMB” should occur around 3.9 nm. An “INCREASE CLIMB, INCREASE CLIMB” message will be annunciat-ed at around 1 nm. A “CLEAR OF CONFLICT” message will be issued when the threat has passed.

Traffic Display(s) _______ Announcement

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While simulating a pressure altitude of more than 18,000 ft. MSL, press the "FL" (Flight Level) switch on the TCAS control unit. Verify the prop-er operation of the flight level mode on the traf-fic displays.

Traffic Display(s) ______ Radar Indicator

(b) GPWS & Wind Shear Inhibit Tests

If installed, verify that the GPWS, Wind Shear warnings, and TCAS voice alerts are compatible. Also verify that the GPWS and Wind Shear warnings have been prioritized over the TCAS voice alerts.

Set up the TCAS ramp tester.

1 Apply static pressure to the airplane using the pitot-static tester. Increase the altitude to 20,000 ft.

NOTE: Field elevation is adequate for this test if the pitot-static tester is not available.

2 Apply a radio altitude signal to the aircraft us-ing the radio altimeter test set of equivalent. Increase the radio altitude to 2,750 ft. or great-er.

3 Disable the WOW logic and put the aircraft systems into the “AIRBORNE” mode.

4 Put the TCAS/transponder control unit in the TA/RA position. The TCAS must be in “TA/RA” mode.


As soon as the TCAS ramp tester triggers a TA or an RA, press the GPWS test switch or simulate a GPWS advisory. Verify the TCAS audio is inter-rupted and the TCAS mode annunciation on the traf-fic display is “TA ONLY.”

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NOTE: If the GPWS test is inhibited when the radio altitude height is above ground level, it will be necessary to simulate a GPWS scenario to perform this test.

PASS/FAIL


As soon as the TCAS ramp tester triggers a TA or an RA, press the Wind Shear test switch or simu-late a Wind Shear advisory. Verify the TCAS audio is interrupted and the TCAS mode annunciation on the traffic display is “TA ONLY.”

PASS/FAIL

(c) GPWS & Wind Shear Inhibit (Alternate) Test

Another test to check the Advisory Inhibit inputs can be performed with the Diagnostic computer.

1 Initiate the TCAS self-test.

2 As soon as the "TCAS SYSTEM TEST OK" message be-gins, press the GPWS test switch or simulate a GPWS advisory. Verify the TCAS audio is inter-rupted.

PASS/FAIL .

3 Initiate the TCAS self-test.

4 As soon as the "TCAS SYSTEM TEST OK" message be-gins, press the Wind Shear test switch or simulate a Wind Shear advisory. Verify the TCAS audio is interrupted.

PASS/FAIL .

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(d) TCAS Bearing Accuracy Test (Required for STC Approval)

The bearing accuracy test evaluates the performance of the top directional antenna and bottom directional an-tenna for 360° coverage at 30° degree increments. The IFR TCAS-201 Ramp Tester is used to generate an intruder to test bearing accuracy of the TCAS system. The air-craft must be placed on a compass rose with 30° degree increments marked off at a 50 foot radius from the top antenna and a 6 foot radius from the bottom antenna.

NOTE: When checking the TCAS bearing accuracy, the test antenna must be within line-of-sight of the directional antenna under test. The ac-curacy to the top directional antenna should be checked while the test antenna is 50 to 75 ft. distant, and the landing gear logic is "EXTENDED" (DOWN). When measuring the accu-racy of the bottom antenna, the test antenna should not be within line-of-sight of the top directional antenna. Use either the fuselage to block the top directional antenna and po-sition the test antenna 8 to 12 ft. from the bottom antenna or shield the top directional antenna from the test antenna with echosorb or equivalent. The landing gear logic must simulate "RETRACTED" (UP) when checking the bearing accuracy of the bottom antenna. If the gear position logic is "EXTENDED" (DOWN) TAs and RAs will appear as "No Bearing" tar-gets because the bottom antenna is locked in omni directional mode.

1 Initialize Configuration Module Strapping

Initialize strapping information stored in the configuration module via a personal computer ex-ecuting TPUDIAG/ TCASDIAG software across the RS-232 port. Follow instructions from the TPUDIAG/TCASDIAG DIAGNOSTIC APPENDICES for strap config-uration programming.

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CAUTION: THE CONFIGURATION MODULE STRAPPING IN-FORMATION MUST BE INITIALIZED BEFORE THE SYSTEM WILL PERFORM PROPERLY.

TO INITIALIZE THE STRAPPING INFORMA-TION, USE THE TPUDIAG/TCASDIAG SOFT-WARE AND CHOOSE OPTION 3 FROM THE MAIN MENU AND THEN OPTION 1 FROM THE “CON-FIGURATION MODULE ACCESS” MENU, AND FOLLOW THE INSTRUCTIONS. ADDITIONAL-LY, OPTIONS 3 AND 4 FROM THE CONFIGU-RATION MODULE ACCESS MENU MUST BE USED TO ZERO THE BEARING TABLES (P/N 071-00097-0100 ONLY). FOLLOW THE BEARING TABLES ZEROING PROCEDURE INCLUDED IN THE DIAGNOSTIC APPENDICES.

2 System Set Up

Position the aircraft outside on a heading of north on the compass rose away from hangars and other aircraft.

Static pressure to the aircraft using the pitot-static tester is not required unless local condi-tions make it necessary.

Apply a radio altitude signal to the aircraft us-ing the radio altimeter test set or equivalent. Increase the radio altitude to 1,000 feet or greater.

Disable the WOW logic to put the aircraft systems in the "AIRBORNE" mode.

Put the TCAS control unit in the ON position. The TCAS must be in the "TA" mode.

Set up an intruder test scenario on the TCAS ramp tester according to the top antenna or bottom an-tenna procedures below.

3 Top Directional Antenna Bearing Test

Set ramp tester to Mode C (ATCRBS) intruder, UUT horizontal distance 50 feet, UUT vertical dis-tance one foot, altitude reporting ON.

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Set intruder 2.1 nm range, zero range rate, co-altitude to aircraft being tested, and zero alti-tude rate. Position ramp test directional anten-na at same relative altitude as the top antenna, 50 feet from the TCAS antenna and directed toward the TCAS antenna for all readings.

Initiate the intruder test and measure the rela-tive bearing to the intruder on the traffic dis-play at each 30° degree increment listed on Figure 2010 TCAS Bearing Measurements, in a clockwise direction.

The largest acceptable TCAS II bearing error is ±15°.

4 Bottom Directional Antenna Bearing Test

When testing the bottom directional antenna, set the landing gear logic to "RETRACTED" (GEAR UP).

Set ramp tester to Mode C (ATCRBS) intruder, UUT horizontal distance 6 feet, UUT vertical distance one foot, altitude reporting ON. Set intruder 2.1 nm range, zero range rate, co-altitude to air-craft being tested, and zero altitude rate. Po-sition ramp test directional antenna at same rel-ative altitude as the bottom antenna, 6 feet from the TCAS antenna and directed toward the TCAS an-tenna for all readings.

Do not allow obstructions, such as landing gear, between ramp tester and bottom antenna.

Initiate the intruder test and measure the rela-tive bearing to the intruder on the traffic dis-play at each 30° degree increment listed on Figure 2010 TCAS Bearing Measurements, in a clockwise direction.

The largest acceptable TCAS II bearing error is ±15°.

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Figure 2010 TCAS Bearing Measurements

NOTE 1: Bearing Error equals the heading to TCAS ramp tester less the relative bearing of intruder. Relative bearing to the intruder should be a positive number measured clock-wise from north on the traffic display unit.

NOTE 2: The largest acceptable TCAS II bearing error is ±15°, ex-cept between 135° and 225° (aft of the wings) where the error may be greater.

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5 Bearing Correction Procedure

NOTE: Perform only if accuracy is out of specification.

If the top or bottom directional antenna bearing error is greater than ±15° a bearing correction procedure contained in the TPUDIAG/TCASDIAG Diag-nostic Procedures must be used. The bearing cor-rection procedure uses specific airframe bearing error data stored in the configuration module to correct airframe induced bearing error. (See DI-AGNOSTIC APPENDICES).

6 Bottom TCAS Omnidirectional Antenna

Perform a TA and/or RA intruder test with the ramp tester to produce a NO BEARING TA or RA. Check power and frequency of the bottom omni antenna.

(e) Radar Indicator Test

If installed, check that the traffic mode can be select-ed on the color radar indicator. Verify that the traf-fic symbols displayed on the radar indicator are the correct color and range. Check that the pattern is the proper size.

Traffic Only ("TA/RA" or “TA ONLY”) Pass/Fail _______.

Traffic and Weather Pass/Fail _______.

Weather Only Pass/Fail _______.

Navigation Overlay, if applicable Pass/Fail _______.

(f) TCAS Power & Frequency Tests

Perform the Power and Frequency tests shown in the TCAS 201 Operator’s Guide (pp 27 - 29).

(g) EMI & RFI Tests (Required for STC)

Electromagnetic Interference (EMI)/ Radio Frequency In-terference (RFI). Determine if there is any mutual in-terference with any other aircraft system.

PASS/FAIL ______.

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(h) Suppression Check

Determine that the system suppression is active.

(7) GC 362A Post Installation Test

(a) Mode Selection

Press the external mode select button or T/Wx control unit push button until TA AUTO or TA/RA AUTO (Radar Only Mode) appears in the lower left corner of the display.

Press the button again and TA ONLY or TA/RA (Weather/TCAS Overlay Mode) will appear in the lower left of the display.

Press the button again and TA ONLY or TA/RA (TCAS Only Mode) will remain in the lower left of the display.

(b) Failure Annunciation

A failure annunciation will be displayed if the GC 362A detects or is instructed of a failure in the TCAS sys-tem. When in the Radar Only mode or Radar/TCAS mode, a failure will result in a yellow failure annunciation be-ing displayed in the upper left corner of the display unit. All other TCAS information will be removed from the display. Normal operation of the weather radar sys-tem will continue but TCAS operation will be inhibited until the failure is corrected. Failure operation in the TCAS only mode is described below.

The following annunciations will be displayed when the GC 362A detects a failure:

TCAS - Displayed in the event of a TCAS processor fail-ure or a failure of any component of the TCAS system that the TCAS processor detects during a self test.

GP - FAIL Displayed in the event of a failure of the BITE test in the GC 362A.

(c) Displayed Fault Messages

When the TCAS processor detects a system failure, se-lecting the TCAS Only display mode will cause the indi-cator to display a message indicating which component has failed.

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All TCAS intruder, mode, and range data will be removed from the display. A yellow "TCAS SYSTEM FAIL" message will be displayed at the top of the display.

One or more of the following fault messages may be dis-played:

The appropriate failure annunciation messages will be displayed until the fault has been removed or the dis-play mode is changed. Additional failures will be dis-played if they occur while the fault list is displayed.

The fault display will not occur if the failure is one that will not allow the display mode to be cycled. A component failure that causes loss of the 429 mode con-trol will remove all displayed TCAS information, select the radar display mode, and display the "TCAS" failure annunciation described above.

D. Flight Test (Required for STC)

Conduct a flight test of TCAS II according to the requirements of FAA Advisory Circular AC 20-131A.

TCAS PROCESSOR - FAIL

UPPER ANTENNA - FAIL

LOWER ANTENNA - FAIL

RADIO ALT. #1/#2 - FAIL

#1/#2 XPNDR DATA BUS - FAIL

ATTITUDE - FAIL

HEADING - FAIL

TRAFFIC DISPLAY - FAIL

RA DISPLAY #1/#2 - FAIL

SELECTED XPNDR - FAIL

XPNDR TOP ANTENNA - FAIL

XPNDR LOWER ANTENNA - FAIL

XPNDR TCAS DATA - FAIL

XPNDR CONTROL DATA - FAIL

#1/#2 XPNDR ALT DATA - FAIL

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8. Removal and Replacement

A. TPU 67A TCAS Processor

(1) Removal

(a) Loosen retaining screw clamps, located on front of the TCAS processor mount, that secure the TPU 67A to the mount.

(b) Gently pull the TPU 67A forward until unit disconnects from rear connector on mounting tray and unit slips out of guide pins on mount. Remove unit from mount.

(2) Reinstallation

(a) Slide TPU 67A onto mount and then gently push unit to-ward rear until guide pins are aligned and connector is fully engaged.

(b) Engage and tighten retaining screw clamps to secure unit firmly in place.

B. Directional Antenna

(1) Removal

(a) Detach four coaxial cables from connectors J1-J4.

(b) Remove four screws securing antenna to airframe. Remove antenna and antenna "O" ring.

(2) Reinstallation

(a) Clean aircraft antenna mounting surface.

(b) Install new antenna "O" ring.

(c) Secure antenna to aircraft using four screws. Apply ap-proved lock-tight sealant to mounting screws.

(d) Connect the four coaxial cables to corresponding con-nectors J1-J4 on the antenna.

(e) Apply approved sealing silicon around outer edge of an-tenna to seal antenna to aircraft fuselage.

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C. Omnidirectional Antenna

(1) Removal

Refer to antenna manufacturer’s documentation.

(2) Reinstallation

Refer to antenna manufacturer’s documentation.

D. TCAS Control Unit

(1) Removal

(a) Loosen fasteners at front of unit.

(b) Pull unit forward from cockpit panel and detach mating cable connector from rear of unit.

(2) Reinstallation

(a) Reconnect cable connector to rear of unit.

(b) Gently reinsert unit into cockpit panel.

(c) Tighten fasteners at front of unit.

E. 3ATI Traffic Displays

(1) Removal

(a) Loosen clamp fasteners on front of unit.

(b) Pull unit forward from cockpit panel and detach mating cable connector (and if applicable, the pneumatic tube) from rear of unit.

(2) Reinstallation

(a) Reconnect cable connector (and if applicable, the pneu-matic tube) to rear of unit.

(b) Gently reinsert unit into cockpit panel.

(c) Tighten clamp fasteners on front of unit.

(d) If applicable, perform leakage test of the static line.

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(e) Ensure that unit is secure and check that rear cable is not twisted or kinked.

F. GC 362A TCAS Graphics Processor

(1) Removal

(a) Remove the wiring harness connector from the mating con-nector on the front of the unit.

(b) Loosen retaining screw clamps, located on front of the TCAS graphics processor mount, that secure unit to the mount.

(c) Gently pull unit forward until unit disconnects from rear connector on mounting tray and unit slips out of guide pins on mount. Remove unit from mount.

(2) Reinstallation

(a) Slide unit onto mount and then gently push unit toward rear until rear lip engages the clasp.

(b) Engage and tighten retaining screw clamps to secure unit firmly in place.

(c) Insert the wiring harness connector into the unit mating connector.

G. CM 67A/CM 2000 Configuration Module

(1) Removal

(a) Remove two mounting screws.

(b) Detach mating cable connector from unit.

(2) Reinstallation

(a) Attach mating cable connector to unit.

(b) Insert and tighten two mounting screws.

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9. Maintenance Procedures

A. In-Aircraft Adjustments

All alignment and adjustment procedures are accomplished during bench maintenance. When unit performance indicates an adjustment or an alignment is required the technician should remove the unit from the aircraft, then reference should be made to the related Com-ponent Maintenance Manual.

B. System Protection

There are no fuses integral to the TCAS equipment. The system is protected by circuit breakers located at the circuit breaker panel in the aircraft.

C. Lubrication

There are no moving parts in the TCAS. No lubrication is required.

D. Cleaning

When deemed necessary, depending upon the environment to which the equipment is exposed and the intensity of use, periodic cleaning should be performed. The exterior of the units should be wiped with a lint-free cloth dampened with an approved cleaning agent.

NOTE: Any cleaning of equipment interiors should be done only when performing bench overhaul of system components.

10. Aircraft Maintenance Programs

A. General

Maintenance procedures for TCAS are stipulated in FAA Advisory Cir-cular AC 120-55, "Air Carrier Operational Approval and Use of TCAS II." These procedures include initial activation or return-to-ser-vice, TCAS-related maintenance records, maintenance training, and other maintenance program responsibilities. Also covered in this advisory circular are approaches for obtaining FAA approval to use TCAS in operations, including airworthiness approval, operational approval, approval methods, and other operational issues.

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B. Honeywell TCAS Maintenance Recommendations

The CAS 67A TCAS II system has been designed for "On Condition" main-tenance. Automatic performance monitoring and self-test are con-tinuously performed by the TPU 67A TCAS Processor BITE to detect malfunctions that degrade or preclude TCAS protection to a high de-gree of confidence. When properly installed and interfaced with approved aircraft signal sources, it meets or exceeds the FAA AC 20-131A.

Further confirmation of satisfactory operation of visual displays and aural annunciations can be determined by periodic operation of the manual self-test function as selected by the mode selector switch on the Mode S/TCAS control unit.

Refer to paragraph 2. C. Fault Isolation Using TCAS Processor LED Fault Codes in the FAULT ISOLATION section of this manual for a de-scription of the functional test sequence and acceptable indications during self-test.

After major aircraft maintenance cycles, additional system opera-tion should be checked with a TCAS Ramp Test Set. Confirm that the TCAS system performs to the criteria of FAA Advisory Circular AC 20-131A (or later amendments); or according to the Operator’s Approved Maintenance Program.

11. ANT 67A Directional Antenna Adapter Plate Installation

This procedure outlines the installation of the adapter plate, (p/n 047-50357-0001 through -0004), of 2024-T4 Alclad, to the skin of the aircraft. The gap between the adapter plate and the skin determines whether Proce-dure A or B is required for the installation of the adapter plate.

A. General Information

The ANT 67A adapter is available in four different versions to ac-commodate a broad range of aircraft skin curvatures. The following list describes the range of radial curvatures that each adapter plate will fit:

ADAPTER P/N VERSION SKIN CURVATURE (RADIAL)

047-50357 -0001 29 to 35 inches

-0002 36 to 45 inches

-0003 46 to 65 inches

-0004 66 to 95 inches

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The installation procedure requires the use of the adapter plate as the fixture to locate the pilot holes on the proposed centerline for the antenna location.

The adapter plate is mounted in places on the skin with cleco fas-teners so a determination can be made as to which installation pro-cedure A or B will be required.

If the edge gap between the adapter plate and the aircraft skin can be closed without stressing the aircraft skin or distorting the flat section of the adapter plate in excess of ±0.010 inches follow Pro-cedure A. If the installer is unable to comply with the above cri-teria, Procedure B must be used.

Measure the outboard centerline gap described as dimension "T" on ANT 67A outline drawing (p/n 155-06003-0000, Sheet 2) for use in Procedure B.

B. Installation Procedure A

Attach the adapter plate and complete the drilling and cleco attach-ment. If corrosion or damage is detected on the mounting surface, mask off area adjacent to adapter plate and strip paint from skin on suspect area. Treat corrosion and/or damage in accordance with approved practices regarding pressurized structures. Upon approval of skin preparation, attach the adapter plate and complete the drilling and riveting attachment.

(1) Drilling and Riveting Instructions

(a) Drill and cleco for final rivet diameter from the cen-terline outboard.

(b) Drill the attachment holes for the four nut plates.

(c) With a 1.125 inch transfer punch, locate the centers for the four connectors and cut out the connector clearances ("F holes").

(d) Remove adapter plate to countersink and de-burr all holes. Clean and brush alodine on all exposed metal surfaces of adapter plate.

(e) De-burr all holes on aircraft and clean mounting surface in accordance with application of BMS5-95 sealant. Clean and brush alodine on all exposed surfaces on air-craft skin.

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(f) Apply a faying surface seal of BMS5-95 to the faying surfaces of the skin and adapter. Apply BMS5-95 to fas-teners and install wet. Complete the riveting operation and install nut plates per installation drawing. Remove excess sealant from edges, exposed surfaces, and con-nector clearance holes to allow inspection for cracks and corrosion.

C. Installation Procedure B

This installation procedure provides for shims to be added between adapter plate and aircraft skin. The shims are to be used to fill edge gaps created by a mismatch in curvature between the adapter plate and the aircraft skin.

(1) Shim Fabrication, Drilling, and Riveting Instructions

Fabricate the edge gap shims of 2024-T4 Alclad per drawing within "T" ±0.010 inch thickness and identify as L, R.

Fabricate 0.125 inch stiffener plate per drawing dimensions. Attach stiffener plate to adapter with eight 3/32 flush rivets per stiffener drawing dimensions. Transfer stiffener holes to adapter plate. Drill and countersink back side of adapter plate.

(2) Attach adapter, stiffener plate and shims to skin, drill and cleco at centerline and edge. If corrosion or damage is de-tected on the mounting surface, mask off area adjacent to adapter and strip paint from sheetmetal. Treat corrosion and/or damage in accordance with approved practices regarding pressurized structures.

(3) Prepare the mounting surface and adjacent area of aircraft skin to the adapter plate with aluminum duct tape (Figure 2011 ANT 67A Directional Antenna Adapter and Moldable Shim), re-drill holes identified in step (2) above and apply MS122 re-lease material to duct tape surface. Prepare adapter plate surface and shims by cleaning with acetone followed by appli-cation of BR127. Note, caution should be taken not to get BR127 on antenna mounting surface of adapter plate. Apply sufficient quantity of DMS4-828, moldable shim material to adapter plate and shims to fill the measured gap. If a com-pound gap exists, apply additional DMS4-828 to close the gap. An approximate material application is illustrated in the in-stallation drawing.

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(4) Attach the adapter with stiffener plate to the aircraft skin with cleco fasteners at the centerline rivet holes. Carefully cleco the left and right shim to the outboard edge rivet holes. Allow several minutes for the pressure of assembly to flow out excessive DMS4-828 material. After DMS4-828 has stopped flowing, remove all excessive material, clean with MEK and blend edges as indicated on installation drawing. A plas-tic knife is recommended to remove excessive material and blend along the edge of the adapter plate and edges of the 1.125 inch connector holes.

(5) After the specified cure time of DMS4-828, drill and cleco for final rivet diameter from the centerline outboard.

(6) Drill the attachment holes for the four nut plates.

(7) Using a 1.125 inch transfer punch, locate the centers for the four connectors and cut out the connector clearance ("F" holes) through aircraft skin.

(8) Remove adapter plate to countersink and de-burr all holes. Carefully drill out 3/32 rivet tails to remove stiffener plate. Clean and brush alodine on all exposed surfaces in-cluding shims. Allow specified cure time for DMS4-828 mate-rial.

(9) De-burr all holes on aircraft skin and clean mounting surface in accordance with BMS5-95 sealant specification. Clean and brush alodine on all exposed surfaces.

(10) Apply a faying surface seal of BMS5-95 to the faying surfaces of aircraft skin and adapter plate. Install fasteners wet with BMS5-95 sealant. Complete the riveting operation and in-stall nut plates per installation drawing. Remove excess sealant from edges, exposed surfaces, and connector holes to expose sheet metal surrounding each hole to allow for physical inspection of cracks and corrosion.

D. Recommended Materials

• DMS4-828, Moldable Shim Material, Dynamold, Inc.

• MS122, Release Material, Miller Stevenson or DC-4, Dow Corning

• BR127, Metal Preparation, American Cynamid

• BMS5-95, Aircraft Sealant, PRC Corporation

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• Alodine per MIL-C-5541

• Acetone

• MEK (Methyl Ethyl Keystone)

E. Bonding Requirements

The DC resistance between the adapter plate surface and the adjacent skin surface must measure less than 10 milliohms.

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Figure 2011 ANT 67A Directional Antenna Adapter and Moldable Shim P/N 004-50119

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Figure 2012 TPU 67A TCAS II Processor Outline Drawing (Dwg. No. 155-05828-0000 Rev. AB)

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Figure 2013 CM 67A/CM 2000 Configuration Module Outline Drawing (Dwg. No. 155-06018-0000 Rev. AA)

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Figure 2014 ANT 67A Directional Antenna Outline Drawing (Dwg. No. 155-06003-0000 Rev. AB, Sheet 1 of 2)

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Figure 2014 ANT 67A Directional Antenna Outline Drawing (Dwg. No. 155-06003-0000 Rev. AB, Sheet 2 of 2)

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Figure 2015 IVA 81A (TA/RA/VSI) Outline Drawing (Dwg. No. 066-50001 Rev. T, Sheet 1 of 2)

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Figure 2015 IVA 81A (TA/RA/VSI) Outline Drawing (Dwg. No. 066-50001 Rev. T, Sheet 2 of 2)

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Figure 2016 IVA 81B (RA/VSI) Outline Drawing (Dwg. No. 066-50002 Rev. L)

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Figure 2017 IVA 81C (TCAS) Outline Drawing (Dwg. No. 066-50053-01 Rev. E)

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Figure 2018 IVA 81D (TCAS) Outline Drawing (Dwg. No. 066-01171-90 Rev. A)

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Figure 2019 GC 362 TCAS Graphics Processor Outline Drawing (Dwg. No. 155-05794-0000 Rev. AA)

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Figure 2020 KFS 578A Control Unit Outline Drawing (Dwg. No. 155-05789-0000 Rev. 1)

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Figure 2021 PS-578A Control Unit Outline Drawing

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Figure 2022 PS-550 Control Unit Outline Drawing (Dwg. No. G7514-()-Dim, Ref 03-19-03)

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Figure 2023 CD 671C Control Unit Outline Drawing (Dwg. No. 155-06001-0000 Rev. 1)

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Figure 2024 TPU 67A Interconnect Drawing Family (Dwg. No. 155-05989-0000 Rev. 2)

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Figure 2025 TPU 67A Pinout Drawing (Dwg. No. 155-05989-0001 Rev. AB)

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Figure 2026 TCAS II Configuration Pins Interface Drawing (Dwg. No. 155-05989-0002 Rev. AA)

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Figure 2027 TCAS II Discrete Interface Drawing (Dwg. No. 155-05989-0003 Rev. AA, Sheet 1 of 2)

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Figure 2027 TCAS II Discrete Interface Drawing (Dwg. No. 155-05989-0003 Rev. AA, Sheet 2 of 2)

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Figure 2028 TCAS Radar/Baro Altitude Interface Drawing (Dwg. No. 155-05990-0004 Rev. AA, Sheet 1 of 4)

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Figure 2029 Attitude/Heading Interface Drawing (Dwg. No. 155-05990-0005 Rev. AA)

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Figure 2030 Antenna/Suppression Interface Drawing (Dwg. No. 155-05990-0006 Rev. 5)

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Figure 2031 Power Interface Drawing (Dwg. No. 155-05990-0007 Rev. 4)

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Figure 2032 Lear 31/EFS 40/50 TCAS Interface Drawing (Dwg. No. 155-05990-0011 Rev. 5)

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Figure 2033 GC 362/Bendix TCAS Interface Drawing (Dwg. No. 155-01628-0000 Rev. 8, Sheet 1 of 3)

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Figure 2034 GC 362/Honeywell TCAS Interface Drawing (Dwg. No. 155-01628-0001 Rev. 8, Sheet 1 of 3)

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Figure 2035 GC 362/Collins TCAS Interface Drawing (Dwg. No. 155-01628-0002 Rev. AA, Sheet 1 of 2)

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Figure 2035 GC 362/Collins TCAS Interface Drawing (Dwg. No. 155-01628-0002 Rev. AA, Sheet 2 of 2)

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Figure 2036 RA Display (ARINC 429 Low Speed) Interface Drawing (Dwg. No. 155-05990-0013 Rev. 3)

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Figure 2037 TA/RA Display (ARINC 429 High Speed) Interface Drawing (Dwg. No. 155-05990-0014 Rev. AD, Sheet 1 of 9)

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Figure 2038 Citation VB Honeywell EFIS/TCAS Interface Drawing (Dwg. No. 155-05990-0015 Rev. 2, Sheet 1 of 2)

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Figure 2038 Citation VB Honeywell EFIS/TCAS Interface Drawing (Dwg. No. 155-05990-0015 Rev. 2, Sheet 2 of 2)

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Figure 2039 Jetstream 41 Honeywell EFIS/TCAS Interface Drawing (Dwg. No. 155-05990-0016 Rev. 2, Sheet 1 of 2)

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Figure 2039 Jetstream 41 Honeywell EFIS/TCAS Interface Drawing (Dwg. No. 155-05990-0016 Rev. 2, Sheet 2 of 2)

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Figure 2040 Diagnostic/Data Recorder Interface Drawing (Dwg. No. 155-05990-0020 Rev. 6)

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Figure 2041 TCAS II ATE Interface Drawing (Dwg. No. 155-05990-0030 Rev. 4, Sht 2)

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Figure 2042 MST 67A Mode S Interface Drawing (Dwg. No. 155-05990-0060 Rev. AA)

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Figure 2043 Collins TDR-94D Mode S Interface Drawing (Dwg. No. 155-05990-0061 Rev. AA)

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Figure 2044 Honeywell Primus II/TCAS Interface Drawing (Dwg. No. 155-05990-0062 Rev. AA, Sheet 1 of 4)

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Figure 2045 CAS 67A TCAS II System Interface Drawing (Dwg. No. 155-05989-0090 Rev. AA, Sheet 1 of 6)

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DIAGNOSTIC APPENDICES

TPUDIAG-TCAS Processor Field Diagnostic Program User Instructions

TCASDIAG-TCAS Processor Field Diagnostic Program User Instructions (DOS)

TCASDIAG-TCAS Processor Field Diagnostic Program User Instructions (Windows)

TCAS Antenna System Test Procedures

WARNING: DO NOT USE THE “TPUDIAG - TCAS PROCESSOR FIELD DIAGNOSTIC PRO-GRAM” OR “TCASDIAG - TCAS PROCESSOR FIELD DIAGNOSTIC PROGRAM” WHILE AIRBORNE. THE PROGRAM IS USED ONLY WHILE THE AIRCRAFT IS ON THE GROUND. THE SYSTEM IS DEGRADED TO PERFORM MAINTENANCE FUNCTIONS AND IS NOT AIRWORTHY WHILE RUNNING THE DIAGNOSTIC SOFTWARE.

NOTE: The diagnostic tests are performed with TPU 67A installed in aircraft.

NOTE: The TPUDIAG-TCAS and TCASDIAG-TCAS diagnostic tests are DOS based programs and must be run from the DOS prompt.

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