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SYSTEM INSTALLATION MANUAL

CAS 67A TCAS II SYSTEM MANUAL NUMBER 006-05340-0007 REVISION 7 SEPTEMBER, 2004

WARNING The 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.

N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

System Installation Manual 006-05340-0007 CAS 67A TCAS II Traffic Alert and Collision Avoidance System

Including: TPU 67A TCAS II Processor CM 67A Configuration Module CM 2000 Configuration Module ANT 67A Directional Antenna IVA-81A TA/RA/VSI Display IVA-81B RA/VSI Display IVA-81C, IVA-81D TA/RA/VSI Display GC 362A TCAS Graphics Processor MST 67A Mode S Transponder KFS 578A Mode S/TCAS Control Unit CD 671C Mode S/TCAS Control Unit CTA-81A Mode S/TCAS Control Unit CTA-81D Mode S/TCAS Control Unit PS-550 Mode S/TCAS Control Unit PS-578A Mode S/TCAS Control Unit

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

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

PROPRIETARY NOTICE This document contains proprietary information and such information may not be disclosed to others for any purpose, nor used for manufacturing purposes without written permission from Honeywell.

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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” appendix and antenna test appendix. Specific changes to content are denoted by revision bar.

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RECORD OF REVISIONS REV. NO.

REVISION DATE

DATE INSERTED

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BY

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RECORD OF REVISIONS (cont.) REV. NO.

REVISION DATE

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DATE INSERTED

BY

DATE REMOVED

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RECORD OF TEMPORARY REVISIONS T.R. NO.

DATE

DATE INSERTED

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BY

BY

Complete through Revision TR-05340-1

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

RECORD OF TEMPORARY REVISIONS (cont.) REV. NO.

REVISION DATE

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DATE INSERTED

BY

DATE REMOVED

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL TCAS II SERVICE LITERATURE LIST The following are installation bulletins applicable to the CAS 67A TCAS II system. BULLETIN NUMBER

DATE

COVERAGE

IB 372

APR/1995

TO CORRECT ERROR IN TPU CONFIG MODULE PROCEDURE

IB 398

JUL/1997

TCASDIAG GUIDE FOR FIELD REFERENCE

IB 438

APR/1999

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

IB 439

MAR/1999

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

IB 447

MAY/1999

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

IB 452

JAN/2000

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

IB 456

NOV/2000

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

IB 457

NOV/1999

TCASDIAG GUIDE

IB 458

FEB/2000

CLARIFICATION OF THE ALTITUDE INTERFACE TO THE TCAS PROCESSOR AND/OR MST 67A TRANSPONDER

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 applicable unit. BULLETIN NUMBER

DATE

COVERAGE

EFFECTIVE 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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BULLETIN NUMBER

EFFECTIVE S/N

DATE

COVERAGE

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 CIRCUITS

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 CONFIGURATION 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 RELIABILITY OF -250VDC MONITOR CIRCUIT

VERSION DEPENDENT

SB TPU 67A-12

NOV/2001

PREVENT ACCIDENTAL WRITES TO THE FLASH MEMORY DURING NORMAL OPERATION

VERSION DEPENDENT

SB TPU-67A-13

JAN/2003

REPLACE TPU S OBSOLETE COMPUTER BOARD

VERSION DEPENDENT

SB TPU 67A-14

JUN/2002

INCORPORATE REPLACEMENT FOR OBSOLETE REFERENCE BOARD PART NUMBER 200-08874-0000

VERSION DEPENDENT

SB TPU 67A-15

JUN/2002

INCORPORATE REPLACEMENT FOR OBSOLETE SWITCH DRIVER BOARD PART NUMER 200-08530-0000

VERSION DEPENDENT

SB TPU 67A-16

JUN/2002

INCORPORATE REPLACEMENT OF POWER SUPPLY BOARD #2 PART NUMBER 200-08523-0000

VERSION DEPENDENT

SB TPU 67A-17

JUN/2002

INCORPORATE REPLACEMENT OF OBSOLETE VIDEO BOARD PART NUMBER 200-08875-0000

VERSION DEPENDENT

SB TPU 67A-18

AUG/2002

PREVENT THE TPU 67A FRO INTERFERING WITH THE PRIMUS DME DURING EQUIPMENT START-UP

VERSION DEPENDENT

SB TPU 67A-19

FEB/2003

UNIT WILL NOT INITIALIZE AND LED DISPLAY ON THE SIDE OF THE PROCESSOR IS BLANK

VERSION DEPENDENT

SB TPU 67A-20

DEC/2002

REPLACEMENT OF INTERCONNECT BD DUE TO ERRONEOUS EXTERNAL FAULT CODES

VERSION DEPENDENT

SB TPU 67A-21

MAR/2003

REPLACE THREE TRANSORBS ON INTERCONNECT BOARD WITH A LOWER VOLTAGE VARIETY

VERSION DEPENDENT

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BULLETIN NUMBER

DATE

COVERAGE

EFFECTIVE S/N

SB TPU 67A-22

AUG/2003

REPLACES OBSOLETE RECEIVER ASSY PART NUMBER 20009882-0000 WITH 200-09882-0010

VERSION DEPENDENT

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 CONNECTIONS

VERSION DEPENDENT

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

VERSION DEPENDENT

SB TPU 67A-M1

MAR/2001

INCORPORATE SOFTWARE 12/01 (CHANGE 7)

VERSION DEPENDENT

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

VERSION DEPENDENT

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

VERSION DEPENDENT

SWB TPU 67A-SW7

DEC/2001

INCORPORATE SOFTWARE 11/04. ENABLES UNIT TO INTERFACE WITH COLLINS TDR 94D TRANSPONDERS

VERSION DEPENDENT

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL LIST OF EFFECTIVE PAGES SUBJECT

PAGE

DATE

Title Page Proprietary Notice

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Revision Highlights

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RH-1 RH-2

Sept/2004 Sept/2004

Record of Revisions

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Record of Temporary Revisions

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Sept/2004 Sept/2004

List of Service Bulletins

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List of Effective Pages

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LEP-1 LEP-2 LEP-3 LEP-4 LEP-5 LEP-6 LEP-7 LEP-8 LEP-9 LEP-10 LEP-11 LEP-12 LEP-13 LEP-14

Sept/2004 Sept/2004 Sept/2004 Sept/2004 Sept/2004 Sept/2004 Sept/2004 Sept/2004 Sept/2004 Sept/2004 Sept/2004 Sept/2004 Sept/2004 Sept/2004

Table of Contents

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TC-1 TC-2 TC-3 TC-4 TC-5 TC-6 TC-7 TC-8 TC-9

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL Table of Contents (cont).

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TC-10 TC-11 TC-12 TC-13 TC-14

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Introduction

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INTRO-1 INTRO-2

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Description and Operation

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Fault Isolation

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Maintenance Practices

* * * * * * * * * * * *

2001 2002 2003 2004 2005 2006 2007 2008 2009 2010 2011 2012

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

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Diagnostic Appendices

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

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL Diagnostic Appendices (cont).

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APP-64 APP-65 APP-66 APP-67 APP-68 APP-69 APP-70 APP-71 APP-72 APP-73 APP-74 APP-75 APP-76 APP-77 APP-78 APP-79 APP-80 APP-81 APP-82 APP-83 APP-84 APP-85 APP-86 APP-87 APP-88 APP-89 APP-90

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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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6.

7.

8.

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

System Description ..................................................103 A.

General .......................................................103

B.

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

C.

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

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

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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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

6.

A.

General ......................................................2002

B.

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

C.

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

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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PAGE H.

7.

8.

9.

10.

11.

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

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

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

Maintenance Procedures .............................................2086 A.

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

B.

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

C.

Lubrication ..................................................2086

D.

Cleaning .....................................................2086

Aircraft Maintenance Programs ......................................2086 A.

General ......................................................2086

B.

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

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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PAGE DIAGNOSTIC APPENDICES

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PAGE

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 13

MST 67A Environmental Qualification Form (-0010) ............83

Figure 14

MST 67A Environmental Qualification Form (-0020) ............85

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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PAGE

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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PAGE

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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PAGE

Figure 2044

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

Figure 2045

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

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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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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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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 56

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

Table 57

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

Table 2011

GC 362A TCAS Graphics Proc. -0103, Connector Pin Names ....2042

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PAGE

Table 2012

GC 362A TCAS Graphics Proc. -0203, Connector Pin Names ....2044

Table 2013

Inspection/Check Procedure ................................2051

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

INTRODUCTION

This manual includes description, installation, fault isolation, and flight-line checkout procedures for the Honeywell CAS 67A (TCAS II) Traffic Alert and Collision 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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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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 traffic advisories (TAs) and collision resolution advisories (RAs) are produced 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 and CM 67A/CM 2000 Configuration Module

ANTENNA (TOP)

ANT 67A Directional Antenna

ANTENNA (BOTTOM)

ANT 67A Directional Antenna OR: 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 OR: OR: OR:

578A/PS-578A/PS-550 Mode S Transponder/TCAS Control Unit CD 671C Mode S Transponder/TCAS Control Unit CTA-81A/CTA-81D Mode S Transponder/TCAS Control Unit RMS 555 Radio Management System

Table 1 CAS 67A TCAS II System Components

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL A.

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

HONEYWELL PART NUMBER 066-01146

VERSION NUMBER

PRIMARY POWER

SINGLE OR DUAL DIRECTIONAL ANT

-0101

28 Vdc

X

-0201

28 Vdc

X

-1111

28 Vdc

X

-1211

28 Vdc

X

EXTENDED ENVIRONMENTAL PROTECTION

SECONDARY ATT/HDG INPUT

X

X

CHANGE 7 SOFTWARE ACAS II

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 Dual Directional 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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Figure 1 CAS 67A TCAS II System Components

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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 required to 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 Trigger Level (DMTL) Threshold ATCRBS

MTL + 13 dB

Mode S

MTL + 10 dB

Minimum Pulse Width

300 µsec

Maximum Pulse Rise Time

0.50 µsec

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

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CHARACTERISTIC

DESCRIPTION

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

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

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

CHARACTERISTIC

DESCRIPTION

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.

Table 4 TPU 67A TCAS II Processor Specifications (Sheet 3)

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

CHARACTERISTIC

DESCRIPTION

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 whispershout 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,-0201 C119b p/n 066-01146-1111,-1211

Environmental Certification

See Figure 2 TPU 67A Environmental Qualification Form

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

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL B.

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

HONEYWELL PART NUMBER

VERSION NUMBER

BASIC UNIT INITIALIZED W/ DEFAULTS

071-00097

-1000

CM 67A

-0100

CM 2000

X

NUMBER OF MOUNTING SCREWS

TSO COMPLIANCE

2

C63c, C119a

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.

Table 6 CM 67A/CM 2000 Configuration Module Features

CHARACTERISTIC

DESCRIPTION

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 Form or Figure 4 CM 2000 Environmental Qualification Form

Table 7 CM 67A/CM 2000 Configuration Module Specifications

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL C.

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

HONEYWELL PART NUMBER

VERSION NUMBER

ANTENNA SHAPE

COAX CONN

BASIC SHAPE

NUMBER OF MOUNTING SCREWS

071-01548

-0100

Teardrop

1.50"

Flat

4

-0200

Teardrop

0.73"

Flat

4

Table 8 ANT 67A Directional Antenna Versions

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.

Table 9 ANT 67A Directional Antenna Features

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL CHARACTERISTIC

DESCRIPTION

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 Operating

-55 °C to +70 °C

Storage

-55 °C to +85 °C

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 flatbase 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 strike requirements

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

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

CHARACTERISTIC

DESCRIPTION

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

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

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL D.

L-Band Omnidirectional Antenna Listed below are versions and features of the omnidirectional antenna.

VENDOR NAME

MODEL

VENDOR PART NUMBER

LRU DESCRIPTION

IMPEDANCE/ RF/DC

TSO COMPLIANCE

Dorne & Margolin

DMNI 50Series

DMNI 50-2-2

L-Band

50 Ω/Short

C66a, C74c

Table 11 Omnidirectional Antenna Versions FEATURE

DESCRIPTION

Basic Unit

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

Table 12 Omnidirectional Antenna Features

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL E.

IVA-81A TA/RA/VSI Listed below are versions, features, and specifications of the IVA81A TA/RA/VSI. UP⋅DN RANGE CONTROL

TA SELECT SWITCH

HONEYWELL PART NUMBER

VERSION NUMBER

FACE PLATE

PRIMARY POWER

PANEL LIGHTING

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

-2502

Black

28 Vdc

5 Vac/Vdc

X

02/03

-2602

Gray

28 Vdc

5 Vac/Vdc

X

02/03

-2702

Black

28 Vdc

5 Vac/Vdc

X

02/03

X

DIM (POT)

SW IDENT

Table 13 IVA-81A TA/RA/VSI Versions (Sheet 1 of 4) 006-05340-0007 Rev. 7

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

HONEYWELL PART NUMBER

VERSION NUMBER

FACE PLATE

PRIMARY POWER

PANEL LIGHTING

UP⋅DN RANGE CONTROL

066-50001

-2802

Gray

28 Vdc

5 Vac/Vdc

X

-2902

Black

28 Vdc

-3002

Gray

-3102

TA SELECT SWITCH

DIM (POT)

SW IDENT

X

02/03

28 Vdc

X

02/03

28 Vdc

28 Vdc

X

02/03

Black

28 Vdc

28 Vdc

X

X

02/03

-3202

Gray

28 Vdc

28 Vdc

X

X

02/03

-0903

Black

115 Vac

5 Vac/Vdc

X

X

03/03

-1003

Gray

115 Vac

5 Vac/Vdc

X

X

03/03

-0904

Black

115 Vac

5 Vac/Vdc

X

X

04/03

-1004

Gray

115 Vac

5 Vac/Vdc

X

X

04/03

-1704

Black

28 Vdc

5 Vac/Vdc

X

X

04/03

-1804

Gray

28 Vdc

5 Vac/Vdc

X

X

04/03

-2304

Black

28 Vdc

28 Vdc

X

X

04/03

-2404

Gray

28 Vdc

28 Vdc

X

X

04/03

-2504

Black

28 Vdc

5 Vac/Vdc

X

04/03

-2604

Gray

28 Vdc

5 Vac/Vdc

X

04/03

-2704

Black

28 Vdc

5 Vac/Vdc

X

X

04/03

-2804

Gray

28 Vdc

5 Vac/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

-3504

Black

115 Vac

5 Vac/Vdc

X

X

04/03

-3604

Gray

115 Vac

5 Vac/Vdc

X

X

04/03

-3705

Black

115 Vac

5 Vac/Vdc

X

X

05/03

-3706

Black

115 Vac

5 Vac/Vdc

X

X

06/01

Table 13 IVA-81A TA/RA/VSI Versions (Sheet 2) 006-05340-0007 Rev. 7

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

SOFTWARE RANGE SELECTION OPTIONS BY SOFTWARE TYPE RANGE OPTION:

01/06

02/03

03/03

04/03

05/03

06/01

X

X

X

X

X

X

X

X

X

X

05/03

06/01

NVIS Compatible

X

X

Day/Night Display

X

X

X

X

Fixed at 6.5 nm

X

Fixed at 10.0 nm

X

3, 5, 10, 15 nm

X

X

X

Transponder Panel

X

X

X

5, 10, 20, 40 nm

X

X

X

X

X

3, 5, 10, 20, 40 nm 1, 3, 5, 10, 20, 40 nm

Table 13 IVA-81A TA/RA/VSI Versions (Sheet 3)

OPTIONS BY SOFTWARE TYPE FUNCTION:

01/06

02/03

03/03

RLS Capability

X

X

Type “A” Flags/ MSGs

X

X

BLS Compensation

X

X

X

NON-Standard ARINC 419

04/03

X

X

X

E-TCAS Compatible Vertical Speed m/sec

X

Strap selectable Dim Knob TSO’d

X

X

X

X X

X

X

X

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

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

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/DN Range 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

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

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

CHARACTERISTIC

DESCRIPTION

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 processor program 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

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

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL F.

IVA-81B RA/VSI Listed below are versions, features, and specifications of the IVA81B RA/VSI. HONEYWELL PART NUMBER

VERSION NUMBER

FACE PLATE

PRIMARY POWER

PANEL LIGHTING

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

Table 16 IVA-81B RA/VSI Versions

FEATURE

DESCRIPTION

Basic Unit

Displays resolution 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

Table 17 IVA-81B RA/VSI Features

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL CHARACTERISTIC

DESCRIPTION

Form Factor

3 ATI x 7.5 inches deep

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

Operating Temperature Range

-15 °C to + 70 °C

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

CHARACTERISTIC

DESCRIPTION

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

Table 18 IVA-81B RA/VSI Specifications

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL G.

IVA-81C/IVA-81D TA/RA/VSI Listed below are versions, features, and specifications of the IVA81C (P/N 066-50053-XXXX) and IVA-81D (P/N 066-01171-XXXX) TA/RA/ VSI.

HONEYWELL PART NUMBER

VERSION NUMBER

BEZEL

PRIMARY POWER

RANGE CONTROL UP⋅DN

066-50053

-2704

Black

28 V dc

-2804

Gray

28 V dc

TA SELECT SWITCH

LIGHTING BUS

BRIGHT CONTROL (DIM POT)

X

5 V ac or dc

X

X

5 V ac or dc

X

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

FEATURE

DESCRIPTION

Basic Unit

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

UP/DN Range 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.

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

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Page 21 Sept/2004

N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL HONEYWELL PART NUMBER

VERSION NUMBER*

SOFTWARE VERSION

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

-0904

04/03

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

-1004

04/06

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

-2702

02/03

Black

28 V dc

X

5 V ac or dc

X

-2704

04/03

Black

28 V dc

X

5 V ac or 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

-3504

04/03

Black

115 V ac

X

5 V ac or dc

X

-3604

04/03

Gray

115 V ac

X

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

* **

BEZEL

PRIMARY POWER

RANGE CONTROL UP⋅DN

TA SELECT SWITCH

LIGHTING BUS

BRIGHT CONTROL (DIM POT)

5 V ac or dc

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

FEATURE

DESCRIPTION

Basic Unit

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

UP/DN Range 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.

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

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Page 22 Sept/2004

N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL CHARACTERISTIC

DESCRIPTION

Form Factor

3 ATI x 7.5 inches deep

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.

Operating Temperature Range

-20 °C to + 70 °C

Number of Intruder Symbol 3-30

Maximum determined by TCAS processor program 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 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

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

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

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Page 23 Sept/2004

N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL H.

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

HONEYWELL PART NUMBER

VERSION NUMBER

PRIMARY POWER

REMOTE SWITCH

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**

* **

RADAR INDICATOR

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

Table 24 GC 362A TCAS Graphics Processor Versions

FEATURE

DESCRIPTION

Basic Unit

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

Primary Power

28 Vdc power input

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.

Table 25 GC 362A TCAS Graphics Processor Features

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL CHARACTERISTIC

DESCRIPTION

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: Operating

-55 °C to +70 °C

Storage

-55 °C to +85 °C

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

Table 26 GC 362A TCAS Graphics Processor Specifications

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL I.

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

HONEYWELL PART NUMBER

VERSION NUMBER

PRIMARY POWER

BITE

DIVERSITY

BURST TUNING

REMOTE IDENT

DATA LINK

FLIGHT ID REPORTING

066-01143

-0301*

14-28 V

FULL

X

-0601

14-28 V

FULL

X

-1101

14-28 V

LIMITED

X

3

X

-1301

14-28 V

FULL

X

3

X

-1602

14-28 V

FULL

X

3

X

2 X

X

2

* Version -0301 replaced by version -0601. NOTE:

Antenna diversity is necessary for a TCAS configuration.

Table 27 MST 67A Mode S Transponder Versions

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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 DO181A 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 ID Reporting

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

Table 28 MST 67A Mode S Transponder Features

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL CHARACTERISTIC

DESCRIPTION

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 Rate Capability

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)

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

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

CHARACTERISTIC

DESCRIPTION

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.

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

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

CHARACTERISTIC

DESCRIPTION

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 Relative Carrier (MHz) Amplitude (dB) 1.3 ≤ Freq < 7.0 3 7.0 ≤ Freq < 23 20 23 ≤ Freq < 78 40 78 ≤ Freq 60

Environmental Certification

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).

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

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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.

HONEYWELL VERSION PART NUMBER

FACE PLATE

PANEL LIGHTING

ON/OFF SWITCH

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

-4102

Black

-4202

X

DUAL XPNDR 1/2

TCAS RANGE TDR 94D SWITCH COMPATIBLE

“POPUP” COMPATIBLE

X

EXTND

28 Vdc

X

EXTND

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

* -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

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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.

Faceplate

Choice of faceplate colors

Primary Power

28 Vdc power input

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 Range Control 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 nonthreat category aircraft on traffic display. TA: Places the TCAS in the Traffic Advisory Only mode. TA/RA: Places the TCAS in the Traffic Advisory/Resolution Advisory 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 installations, the Traffic display can be brought up on the MultiFunctional 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.

Table 31 KFS 578A Control Unit Features

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

CHARACTERISTIC

DESCRIPTION

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 Operating

-35 °C to +55 °C

Storage

-55 °C to +85 °C

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)

Table 32 KFS 578A Control Unit Specifications

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL K.

PS-578A Mode S/TCAS II Control Unit Configurations Listed below is a KFS 578A to PS-578A cross-reference for units compatible with TCAS II.

KFS 578A 071-01507 -1701

-1801

-1901

-2001

-2201

-2301

-3502

-4102

-4202

KFS LAMP 28V

28V

5V

5V

28V

5V

5V

28V

28V

PS-578A 071-01618

FACE PLATE

DISPLAY COLOR

-0026

BLK

White

-0126

BLK

Amber

-0226

BLK

NVIS

-0025

GRY

White

-0125

GRY

Amber

-0225

GRY

NVIS

-0026

BLK

White

-0126

BLK

Amber

-0226

BLK

NVIS

-0025

GRY

White

-0125

GRY

Amber

-0225

GRY

NVIS

-0027

GRY

White

-0127

GRY

Amber

-0227

GRY

NVIS

-0028

BLK

White

-0128

BLK

Amber

-0228

BLK

NVIS

-0022

BLK

White

-0122

BLK

Amber

-0222

BLK

NVIS

-0026

BLK

White

-0126

BLK

Amber

-0226

BLK

NVIS

-0025

GRY

White

-0125

GRY

Amber

-0225

GRY

NVIS

DUAL XPNDR 1/2

ON/OFF SWITCH

TCAS

RANGE CONTROL

YES

NO

2

Limited

YES

NO

2

Limited

YES

NO

2

Limited

YES

NO

2

Limited

NO

NO

2

Limited

NO

NO

2

Limited

YES

YES

2

Extended

YES

NO

2

Extended

YES

NO

2

Extended

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

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL KFS 578A 071-01507 -4302

-4402

-4902

-5002

-5102

-5202

-3303

-3403

-3503

-3603

-4903

KFS LAMP 5V

5V

28V

28V

5V

5V

28V

28V

5V

5V

28V

PS-578A 071-01618

FACE PLATE

DISPLAY COLOR

-0026

BLK

White

-0126

BLK

Amber

-0226

BLK

NVIS

-0025

GRY

White

-0125

GRY

Amber

-0225

GRY

NVIS

-0022

BLK

White

-0122

BLK

Amber

-0222

BLK

NVIS

-0021

GRY

White

-0121

GRY

Amber

-0221

GRY

NVIS

-0022

BLK

White

-0122

BLK

Amber

-0222

BLK

NVIS

-0021

GRY

White

-0121

GRY

Amber

-0221

GRY

NVIS

-0022

BLK

White

-0122

BLK

Amber

-0222

BLK

NVIS

-0021

GRY

White

-0121

GRY

Amber

-0221

GRY

NVIS

-0022

BLK

White

-0122

BLK

Amber

-0222

BLK

NVIS

-0021

GRY

White

-0121

GRY

Amber

-0221

GRY

NVIS

-0022

BLK

White

-0122

BLK

Amber

-0222

BLK

NVIS

DUAL XPNDR 1/2

ON/OFF SWITCH

TCAS

RANGE CONTROL

YES

NO

2

Extended

YES

NO

2

Extended

YES

YES

2

No

YES

YES

2

No

YES

YES

2

No

YES

YES

2

No

YES

YES

2

Extended

YES

YES

2

Extended

YES

YES

2

Extended

YES

YES

2

Extended

YES

YES

2

No

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

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL KFS 578A 071-01507 -5003

-5103

-5203

-5503

-5603

-4304

-4404

KFS LAMP 28V

5V

5V

5V

5V

5V

5V

PS-578A 071-01618

FACE PLATE

DISPLAY COLOR

-0021

GRY

White

-0121

GRY

Amber

-0221

GRY

NVIS

-0022

BLK

White

-0122

BLK

Amber

-0222

BLK

NVIS

-0021

GRY

White

-0121

GRY

Amber

-0221

GRY

NVIS

-0024

BLK

White

-0124

BLK

Amber

-0224

BLK

NVIS

-0023

GRY

White

-0123

GRY

Amber

-0223

GRY

NVIS

-0026

BLK

White

-0126

BLK

Amber

-0226

BLK

NVIS

-0025

GRY

White

-0125

GRY

Amber

-0225

GRY

NVIS

DUAL XPNDR 1/2

ON/OFF SWITCH

TCAS

RANGE CONTROL

YES

YES

2

No

YES

YES

2

No

YES

YES

2

No

NO

YES

2

No

NO

YES

2

No

YES

NO

2

Select

YES

NO

2

Select

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

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

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 Harness to fabricate the configuration programming harness. Refer to Table 33 KFS 578A - PS-578A Configuration CrossReference (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 installation 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.

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

Listed below are versions, features, and specifications of the PS578A control units that are compatible with TCAS II. HONEYWELL PART NUMBER

VERSION

FACE PLATE

DISPLAY COLOR

DUAL XPNDR 1/2

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

Table 34 PS-578A Control Unit Versions

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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 Range Control Switch

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

TCAS

The TCAS configuration contains the following elements:

-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.

ABOVE/NORMAL/BELOW: Selects relative altitude display limits for non-threat category aircraft on traffic display. TA: Places the TCAS in the Traffic Advisory mode. TA/RA: Places the TCAS in the Traffic Advisory/Resolution Advisory 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 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 MultiFunctional 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.

Table 35 PS-578A Control Unit Features

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

CHARACTERISTIC

DESCRIPTION

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 PS578A 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

Table 36 PS-578A Control Unit Specifications

006-05340-0007 Rev. 7

34-40-01

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL L.

PS-550 Mode S/TCAS II Control Unit Configurations Listed below are versions, features, and specifications of the PS550 control units that are compatible with TCAS II.

HONEYWELL VERSION PART NUMBER

FACE PLATE

DISPLAY COLOR

DUAL XPNDR 1/2

ON/OFF SWITCH

LAMP VOLTS

RANGE CONTROL OPTION*

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.

Table 37 PS-550 Control Unit Versions

006-05340-0007 Rev. 7

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

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.

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 mode. TA/RA: Places the TCAS in the Traffic Advisory/Resolution Advisory mode. FL: TCAS Flight Level function causes the TCAS indicator to change displayed altitude from Relative Altitude (intruder to own aircraft) to absolute altitude.

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.

Table 38 PS-550 Control Unit Features

006-05340-0007 Rev. 7

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

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

Table 39 PS-550 Control Unit Specifications

006-05340-0007 Rev. 7

34-40-01

Page 43 Sept/2004

N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL M.

CD 671C Control Unit Listed below are versions, features, and specifications of the CD 671C control unit. DUAL XPNDR 1/2

TCAS RANGE SWITCH

T/Wx SWITCH

5 Vac/Vdc, 28 Vdc

X

X

X

28 Vdc

5 Vac/Vdc, 28 Vdc

X

Black

28 Vdc

5 Vac/Vdc, 28 Vdc

X

-0901

Black

28 Vdc

5 Vac/Vdc, 28 Vdc

X

-1601

Black

28 Vdc

5 Vac/Vdc, 28 Vdc

-1701

Black

28 Vdc

5 Vac/Vdc, 28 Vdc

-1801

Black

28 Vdc

5 Vac/Vdc, 28 Vdc

-1901

Black

28 Vdc

5 Vac/Vdc, 28 Vdc

-2601

Gray

28 Vdc

5 Vac/Vdc, 28 Vdc

X

-2701

Gray

28 Vdc

5 Vac/Vdc, 28 Vdc

X

-2801

Gray

28 Vdc

5 Vac/Vdc, 28 Vdc

X

-2901

Gray

28 Vdc

5 Vac/Vdc, 28 Vdc

X

-3601

Gray

28 Vdc

5 Vac/Vdc, 28 Vdc

-3701

Gray

28 Vdc

5 Vac/Vdc, 28 Vdc

-3801

Gray

28 Vdc

5 Vac/Vdc, 28 Vdc

-3901

Gray

28 Vdc

5 Vac/Vdc, 28 Vdc

HONEYWELL PART NUMBER

VERSION NUMBER

FACE PLATE

PRIMARY POWER

PANEL LIGHTING CHOICE

071-01542

-0601

Black

28 Vdc

-0701

Black

-0801*

X X X

X X

X X

X X

X X

X X

X

* Dim Select

Table 40 CD 671C Control Unit Versions

006-05340-0007 Rev. 7

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Page 44 Sept/2004

N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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.

Faceplate

Choice of faceplate colors

Primary Power

28 Vdc power input

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.

TCAS

The TCAS configuration contains the following elements: ABOVE/NORMAL/BELOW: Selects relative altitude display limits for nonthreat category aircraft on traffic display. 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. FL: TCAS Flight Level function causes the TCAS indicator to change displayed altitude from Relative Altitude (intruder to own aircraft) to absolute altitude.

Table 41 CD 671C Control Unit Features

006-05340-0007 Rev. 7

34-40-01

Page 45 Sept/2004

N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL CHARACTERISTIC

DESCRIPTION

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: Operating

-35 °C to +55 °C

Storage

-55 °C to +85 °C

Cooling

No forced cooling required

Display

RCTN LCD

Data Output

Low-speed ARINC 429

Front-Mounted Range Control

Optional

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

Table 42 CD 671C Control Unit Specifications

006-05340-0007 Rev. 7

34-40-01

Page 46 Sept/2004

N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL N.

CTA-81A Control Unit Listed below are versions, features, and specifications of the CTA81A control unit. ATC 1/2 SWITCH

ATC FAIL LAMP VOLTS

XPNDR FAIL INPUT

X

X

12-28

OPEN

X

X

12-28

OPEN

No

X

12-28

OPEN

115 Vac

No

X

12-28

OPEN

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

12-28

OPEN

-3901

Gray

115 Vac

5-40

X

12-28

OPEN

-4001

Black

115 Vac

5-40

X

12-28

OPEN

-4201

Black

115 Vac

5-40

X

12-28

OPEN

-5901

Gray

115 Vac

No

X

12-28

OPEN

HONEYWELL PART NO.

VERSION

FACE PLATE

PRIMARY POWER

TCAS RANGE SWITCH

071-01503

-0101

Black

115 Vac

3-15

-0201

Gray

115 Vac

3-15

-1301

Black

115 Vac

-1401

Gray

-2101

ABOVE/ NORM/ BELOW SWITCH

ALT 1/2 SWITCH

X X X X X

Table 43 CTA-81A Control Unit Versions

006-05340-0007 Rev. 7

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Page 47 Sept/2004

N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL FEATURE

DESCRIPTION

Basic Unit

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

Faceplate

Choice of faceplate colors

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/BELOW Switch

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.

Table 44 CTA-81A Control Unit Features

006-05340-0007 Rev. 7

34-40-01

Page 48 Sept/2004

N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL CHARACTERISTIC

DESCRIPTION

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 Operating

-35 °C to +55 °C

Storage

-55 °C to +85 °C

Cooling

No forced cooling required

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

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

006-05340-0007 Rev. 7

34-40-01

Page 49 Sept/2004

N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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.

HONEYWELLP ART NUMBER

VERSION

PRIMARY POWER

FACE PLATE

TCAS RANGE SWITCH

071-01561

-0101

115 Vac

Gray

5-40

-0201

115 Vac

Gray

No

ATC 1/2 SWITCH

ATC FAIL LAMP VOLTS

XPNDR FAIL INPUT

X

X

12-28

OPEN

X

X

12-28

OPEN

ABOVE/ NORM/ BELOW SWITCH

ALT 1/2 SWITCH

Table 46 CTA-81D Control Unit Versions

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/BELOW Switch

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.

Table 47 CTA-81D Control Unit Features

006-05340-0007 Rev. 7

34-40-01

Page 50 Sept/2004

N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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.

SYSTEM COMPONENT

LRU MANUFACTURER/ MODEL DESIGNATOR

LRU DESCRIPTION

LRU PART NUMBER

Display

Honeywell SG-465

Symbol Generator

066-04021-1108 06604021-1109 066-040211110 066-04021-1408 066-04021-1409 06604021-1410

Honeywell SG-464

Symbol Generator

066-04020-1108 06604020-1109

Honeywell KDA 557

Radio Management Unit

066-04029-0101

Control Unit

Table 48 Optional Displays and Control Units

3.

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

006-05340-0007 Rev. 7

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Page 51 Sept/2004

N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

Figure 2 TPU 67A Environmental Qualification Form (Dwg. No. 004-00923-4800, Sheet 1 of 5) 006-05340-0007 Rev. 7

34-40-01

Page 52 Sept/2004

N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

Figure 2 TPU 67A Environmental Qualification Form (Dwg. No. 004-00923-4800, Sheet 2) 006-05340-0007 Rev. 7

34-40-01

Page 53 Sept/2004

N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

Figure 2 TPU 67A Environmental Qualification Form (Dwg. No. 004-00923-4800, Sheet 3) 006-05340-0007 Rev. 7

34-40-01

Page 54 Sept/2004

N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

Figure 2 TPU 67A Environmental Qualification Form (Dwg. No. 004-00923-4800, Sheet 4) 006-05340-0007 Rev. 7

34-40-01

Page 55 Sept/2004

N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

Figure 2 TPU 67A Environmental Qualification Form (Dwg. No. 004-00923-4800, Sheet 5) 006-05340-0007 Rev. 7

34-40-01

Page 56 Sept/2004

N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

Figure 3 CM 67A Environmental Qualification Form (Dwg. No. 004-00924-4800, Sheet 1 of 3) 006-05340-0007 Rev. 7

34-40-01

Page 57 Sept/2004

N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

Figure 3 CM 67A Environmental Qualification Form (Dwg. No. 004-00924-4800, Sheet 2) 006-05340-0007 Rev. 7

34-40-01

Page 58 Sept/2004

N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

Figure 3 CM 67A Environmental Qualification Form (Dwg. No. 004-00924-4800, Sheet 3) 006-05340-0007 Rev. 7

34-40-01

Page 59 Sept/2004

N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

Figure 4 CM 2000 Environmental Qualification Form (Dwg. No. 004-09109-0000, Sheet 1 of 3) 006-05340-0007 Rev. 7

34-40-01

Page 60 Sept/2004

N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

Figure 4 CM 2000 Environmental Qualification Form (Dwg. No. 004-09109-0000, Sheet 2) 006-05340-0007 Rev. 7

34-40-01

Page 61 Sept/2004

N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

Figure 4 CM 2000 Environmental Qualification Form (Dwg. No. 004-09109-0000, Sheet 3) 006-05340-0007 Rev. 7

34-40-01

Page 62 Sept/2004

N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

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

006-05340-0007 Rev. 7

34-40-01

Page 63 Sept/2004

N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

Figure 6 CD 671C Environmental Qualification Form (Dwg. No. 004-09117-0000, Sheet 1 of 2) 006-05340-0007 Rev. 7

34-40-01

Page 64 Sept/2004

N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

Figure 6 CD 671C Environmental Qualification Form (Dwg. No. 004-09117-0000, Sheet 2) 006-05340-0007 Rev. 7

34-40-01

Page 65 Sept/2004

N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

Figure 7 KFS 578A Environmental Qualification Form (-0000) (Dwg. No. 004-09079-0000) 006-05340-0007 Rev. 7

34-40-01

Page 66 Sept/2004

N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

Figure 8 KFS 578A Environmental Qualification Form (-0010) (Dwg. No. 004-09079-0010, Sheet 1 of 2) 006-05340-0007 Rev. 7

34-40-01

Page 67 Sept/2004

N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

Figure 8 KFS 578A Environmental Qualification Form (-0010) (Dwg. No. 004-09079-0010, Sheet 2) 006-05340-0007 Rev. 7

34-40-01

Page 68 Sept/2004

N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

Figure 9 PS-578A Environmental Qualification Form (G7534-(),Sheet 1 of 3) 006-05340-0007 Rev. 7

34-40-01

Page 69 Sept/2004

N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

Figure 9 PS-578A Environmental Qualification Form (G7534-(),Sheet 2) 006-05340-0007 Rev. 7

34-40-01

Page 70 Sept/2004

N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

Figure 9 PS-578A Environmental Qualification Form (G7534-(),Sheet 3) 006-05340-0007 Rev. 7

34-40-01

Page 71 Sept/2004

N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

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

006-05340-0007 Rev. 7

34-40-01

Page 72 Sept/2004

N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

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

006-05340-0007 Rev. 7

34-40-01

Page 73 Sept/2004

N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

Figure 10 PS-550 Environmental Qualification Form (G7514-(),Sheet 3) 006-05340-0007 Rev. 7

34-40-01

Page 74 Sept/2004

N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

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)

006-05340-0007 Rev. 7

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

Figure 11 CTA 81() Environmental Qualification Form (Dwg. No. 004-09048-0000, Sheet 2) 006-05340-0007 Rev. 7

34-40-01

Page 76 Sept/2004

N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

Figure 11 CTA 81() Environmental Qualification Form (Dwg. No. 004-09048-0000, Sheet 3) 006-05340-0007 Rev. 7

34-40-01

Page 77 Sept/2004

N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

Figure 11 CTA 81() Environmental Qualification Form (Dwg. No. 004-09048-0000, Sheet 4) 006-05340-0007 Rev. 7

34-40-01

Page 78 Sept/2004

N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

Figure 11 CTA 81() Environmental Qualification Form (Dwg. No. 004-09048-0000, Sheet 5) 006-05340-0007 Rev. 7

34-40-01

Page 79 Sept/2004

N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

Figure 11 CTA 81() Environmental Qualification Form (Dwg. No. 004-09048-0000, Sheet 6) 006-05340-0007 Rev. 7

34-40-01

Page 80 Sept/2004

N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

Figure 11 CTA 81() Environmental Qualification Form (Dwg. No. 004-09048-0000, Sheet 7) 006-05340-0007 Rev. 7

34-40-01

Page 81 Sept/2004

N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

Figure 12 MST 67A Environmental Qualification Form (-0000) (Dwg. No. 004-09067-0000) 006-05340-0007 Rev. 7

34-40-01

Page 82 Sept/2004

N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

Figure 13 MST 67A Environmental Qualification Form (-0010) (Dwg. No. 004-09067-0010, Sheet 1 of 2) 006-05340-0007 Rev. 7

34-40-01

Page 83 Sept/2004

N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

Figure 13 MST 67A Environmental Qualification Form (-0010) (Dwg. No. 004-09067-0010, Sheet 2) 006-05340-0007 Rev. 7

34-40-01

Page 84 Sept/2004

N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

Figure 14 MST 67A Environmental Qualification Form (-0020) (Dwg. No. 004-09067-0020, Sheet 1 of 3) 006-05340-0007 Rev. 7

34-40-01

Page 85 Sept/2004

N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

Figure 14 MST 67A Environmental Qualification Form (-0020) (Dwg. No. 004-09067-0020, Sheet 2) 006-05340-0007 Rev. 7

34-40-01

Page 86 Sept/2004

N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

Figure 14 MST 67A Environmental Qualification Form (-0020) (Dwg. No. 004-09067-0020, Sheet 3) 006-05340-0007 Rev. 7

34-40-01

Page 87 Sept/2004

N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

Figure 15 GC 362A Environmental Qualification Form (Dwg. No. 004-09077-0000, Sheet 1 of 2) 006-05340-0007 Rev. 7

34-40-01

Page 88 Sept/2004

N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

Figure 15 GC 362A Environmental Qualification Form (Dwg. No. 004-09077-0000, Sheet 2) 006-05340-0007 Rev. 7

34-40-01

Page 89 Sept/2004

N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

Figure 16 IVA 81A/B Environmental Certification Categories

006-05340-0007 Rev. 7

34-40-01

Page 90 Sept/2004

N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

Figure 17 IVA 81C Environmental Qualification Form

006-05340-0007 Rev. 7

34-40-01

Page 91 Sept/2004

N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

Figure 18 IVA 81D Environmental Qualification Form

006-05340-0007 Rev. 7

34-40-01

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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.

PUBLICATION

HONEYWELL PART NUMBER

ATA IDENTIFICATION NUMBER

TPU 67A TCAS II Processor Component Maintenance Manual

006-05404-( )

34-40-14

TPU 67A TCAS II Processor Illustrated 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 Manual Including ANT-81A, TPU-81A, IVA-81A, IVA-81B, and ITA-81A.

I.B. 1181

34-45-00

IVA-81A Traffic Advisory/Resolution Advisory 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/Resolution Advisory Vertical Speed Indicator (TA/RA/VSI) Component Maintenance Manual

80-5123 call 800.788.5118 to order

33-45-40

IVA-81D Traffic Advisory/Resolution Advisory Vertical Speed Indicator (TA/RA/VSI) Component Maintenance Manual

80-5181 call 800.788.5118 to order

33-45-41

MST 67A Mode S ATC Transponder System Installation Manual

006-00681-( )

34-54-01

MST 67A Mode S ATC Transponder Component 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 Unit Component Maintenance Manual

006-05375-( )

34-54-05

Table 49 Related Publications (Sheet 1 of 2) 006-05340-0007 Rev. 7

34-40-01

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

PUBLICATION

HONEYWELL PART NUMBER

GC 362A TCAS Graphics Processor Component Maintenance Manual

006-05320-( )

RDS 81 Color Weather Radar System Installation Manual Maintenance Manual

006-00954-( ) 006-05997-( )

RDS 82 Color Weather Radar System Installation Manual Maintenance Manual

006-00955-( ) 006-05913-( )

RDS 84 Color Weather Radar System Installation Manual Maintenance Manual

006-00902-( ) 006-05998-( )

RDS 86 Color Weather Radar System Installation Manual Maintenance Manual

006-00903-( ) 006-05996-( )

ATA IDENTIFICATION NUMBER

RDR-1E/RDR-1ED Radar System Maintenance Manual

I.B. 1101-1

34-23-00

RDR-1F Radar System Maintenance Manual

I.B. 1102

34-42-00

RDR-4A Weather Radar System Maintenance Manual

I.B. 1104

34-41-00

SG 464/SG 465 EFIS Symbol Generator Maintenance 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 System Installation Manual RMU 556 Maintenance Manual KDA 557 Maintenance Manual

006-00675-( ) 006-05308-( ) 006-05373-( )

45-00-01 45-00-02

KAD 480 Air Data System

006-00662-( )

RDR 2000 Color Weather Radar System Installation Manual

006-00643-( )

Collins TDR-94/94D Mode S Transponder Installation Manual

523-0775652 -00211A

Gables PS-578 ATC/TCAS Installation Manual Contact Gables, CAGEC 99837

IST.G7534-( )

N.A.

Gables PS-550 ATC/TCAS Installation Manual Contact Gables, CAGEC 99837

IST.G7514-( )

N.A.

Table 49 Related Publications (Sheet 2)

006-05340-0007 Rev. 7

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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.

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

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 includes 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 International 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.

006-05340-0007 Rev. 7

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL NOTE:

Only Honeywell approved signal connector shell with floating hardware and connector shim must be used for TPU 67A installation.

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 030-2259000

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

071-00097-0100 or 071-00097-1000

CM 2000 Configuration Module or 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

Table 51 TPU 67A TCAS II Processor Installation Kit (P/N 050-03078-0010)

006-05340-0007 Rev. 7

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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.

ITEM

PART NUMBER

DESCRIPTION

UM

QUANTITY

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

071-00097-0100 or 071-00097-1000

CM 2000 Configuration Module or CM 67A Configuration Module

EA

1

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). ITEM

PART NUMBER

DESCRIPTION

UM

QUANTITY

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

Table 53 TPU 67A TCAS II Processor Upgrade Installation Kit (P/N 050-03078-0020) (Gulfstream)

006-05340-0007 Rev. 7

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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 cables. Please contact one of the following companies: Adams-Russell, phone 508-338-5210; ECS, phone 1- 800-3279473; Hollingshead, phone 213-921-3438; PIC W & C, phone 1-800-742-3191.

KIT

PART NUMBER

DESCRIPTION

UM

QUANTITY

1

047-50357-0001

Adapter plate, 29" - 35" radius, 4 hole

EA

1

2

047-50357-0002

Adapter plate, 36" - 45" radius, 4 hole

EA

1

3

047-50357-0003

Adapter plate, 46" - 65" radius, 4 hole

EA

1

4

047-50357-0004

Adapter plate, 66" - 95" radius, 4 hole

EA

1

Table 54 ANT 67A Antenna Adapter Kits

E.

Omnidirectional Antenna Installation Kit Customer must obtain kit from the omnidirectional antenna manufacturer. Refer to Table 11 Omnidirectional Antenna Versions for omnidirectional antenna manufacturer and part number. NOTE:

006-05340-0007 Rev. 7

When an omnidirectional antenna is used as the bottom antenna, the three unused bottom antenna coaxes connected to the TPU 67A processor must be connected to 50 Ω terminations. Please contact one of the following companies for 50 Ω terminations: M/A Comm p/n 3002-6113-0000, Phone 1-800-998-4500; PIC Wire & Cable p/n K240001; Pasternack p/n PE6032.

34-40-01

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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.

ITEM

PART NUMBER

DESCRIPTION

UM

QUANTITY

1

03024473-0001

Connector M83723-75R2041N

EA

1

2

03024473-0002

Connector strain relief M85049-52-1-20N

EA

1

Table 55 IVA-81A/IVA-81B/IVA-81C/IVA-81D Installation Kit (P/N 05050001-0501) 115 Vac Unit/5 V Dim Source

ITEM

PART NUMBER

DESCRIPTION

UM

QUANTITY

1

03024473-0003

Connector M83723-75R20416

EA

1

2

03024473-0002

Connector strain relief M85049-52-1-20N

EA

1

Table 56 IVA-81A/IVA-81B/IVA-81C/IVA-81D Installation Kit (P/N 05050001-0502) 28 Vdc Unit/28 Vdc Dim Source

ITEM

PART NUMBER

DESCRIPTION

UM

QUANTITY

1

03024473-0004

Connector M83723-75R20417

EA

1

2

03024473-0002

Connector strain relief M85049-52-1-20N

EA

1

Table 57 IVA-81A/IVA-81B/IVA-81C/IVA-81D Installation Kit (P/N 05050001-0503) 28 Vdc Unit/5 V Dim Source

006-05340-0007 Rev. 7

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL G.

GC 362A Installation Kit Kit provides the following:

ITEM

PART NUMBER

DESCRIPTION

UM

QUANTITY

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

5

030-02351-0004

Hood and lever assembly

EA

1

Table 58 GC 362A Installation Kit (P/N 050-02978-0001)

H.

MST 67A Installation Kit Kit provides the following:

ITEM

PART NUMBER

DESCRIPTION

UM

QUANTITY

1

030-00413-0000

Coax plug RG 214, No. 1 (P671B1/P671B2) ITT Cannon 249-5123-000 or Radiall 610-1080001.

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 03003106-0000). ITT Cannon 030-2259-000.

EA

106

4

047-09406-0014

Mounting rack

EA

1

5

075-05090-0001

Spacer Mounting hardware: Two (2) screws p/n 089-06014-0020,front Two (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

Table 59 MST 67A Installation Kit (P/N 050-02979-0000)

006-05340-0007 Rev. 7

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL I.

KFS 578A / PS-578A Installation Kit Kit provides the following:

ITEM

PART NUMBER

DESCRIPTION

UM

QUANTITY

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

6

030-01157-0011

Crimp connector, 20 G

EA

36

7

030-01188-0000

Female polarizing pin

EA

2

Table 60 KFS 578A / PS-578A Installation Kit (P/N 050-02934-0001)

J.

PS-578A Configuration Programming Harness

ITEM

PART NUMBER

DESCRIPTION

UM

QTY

1

030-01174-0000

Sub-D 29 pin female connector Positronic p/n RD29F00000-782.0

EA

1

2

030-01157-0011

Crimp connector pins (female) 20G Positronic p/n FC6020D-14

EA

3

3

030-01188-0000

Female polarizing pin Ted Mfg Corp p/n 104202

EA

1

4

030-01161-0000

Sub-D 29 pin male connector Positronic p/n RD29M00000-782.0

EA

1

5

030-01184-0011

Crimp connector pins (male) 20G Positronic 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

006-05340-0007 Rev. 7

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

Figure 19 PS-578A Configuration Programming Harness

K.

PS-550 Connector Assembly Kit provides the following:

ITEM

PART NUMBER

DESCRIPTION

UM

QTY

1

MS27484T20F2SA

65 pin connector

EA

1

L.

CD 671C Installation Kit Kit provides the following:

ITEM

PART NUMBER

DESCRIPTION

UM

QUANTITY

1

030-01157-0011

Crimp connector, 20 G

EA

48

2

030-01188-0000

Female polarizing pins

EA

2

3

030-02351-0002

Hood and lever assembly

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

Table 61 CD 671C Installation Kit (050-03206-0000)

006-05340-0007 Rev. 7

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL M.

CTA-81A/CTA-81D Installation Kit Kit provides the following:

ITEM

PART NUMBER

DESCRIPTION

UM

QUANTITY

1

030-03051-0000

24 Pin connector (LP)

EA

1

2

030-03051-0001

24 Pin connector (RP)

EA

1

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 avoidance 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 respond 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.

006-05340-0007 Rev. 7

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL (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:

(3)

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.

Collision Avoidance Computation and Resolution Advisory Display Function If an RA threat aircraft is present, TCAS determines the appropriate vertical maneuvering for own aircraft that will attain 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 computations 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 potentially dangerous situations. Depending on the aircraft equipment, the traffic display may appear on a TA/RA/VSI unit, or an optional radar indicator, or dedicated TCAS display unit, or EFIS MFD display.

006-05340-0007 Rev. 7

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL (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 advisories 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

BUS #

PARAMETER DESCRIPTION

SOURCE OF DATA

TRANSMISSION DESCRIPTION FOR DATA

RECIPIENT OF DATA

1

XT Coordination

Mode S Transponder

ARINC 718/735 (429) Data Transponder/TCAS Coordination

TCAS Processor

2

Control Data

XPONDER (P67A1 XPONDER (P67A1 XPONDER (P67A1 XPONDER (P67A1

RCV 1A B80) RCV 1B B81) RCV 2A B82) RCV 2B B83)

Mode S/TCAS Control Unit

NOTE: Mode S transponder #2 inputs are the same as transponder #1.

ARINC 718/735 (429) Data

Mode S Transponder

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 Port Select #1/#2 (P671A 42) (Gnd = Port #1)

Table 63 TCAS II System Integration Matrix (Sheet 1 of 16)

006-05340-0007 Rev. 7

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

BUS #

PARAMETER DESCRIPTION

SOURCE OF DATA

3

Altitude Data Air Data System Baro Altitude #1/#2 Baro Alt Port (P671A 3) Baro Alt Port (P671A 4) Baro Alt Port (P671A 13) Baro Alt Port (P671A 14)

4

Altitude Data Encoding (#1-A1, (#1-A2, (#1-A4, (#1-B1, (#1-B2, (#1-B4, (#1-C1, (#1-C2, (#1-C4, (#1-D2, (#1-D4,

TRANSMISSION DESCRIPTION FOR DATA

RECIPIENT OF DATA

ARINC 706 (429) Data ARINC 575 (419) Data

Mode S Transponder

Gillham (11 wire) Interface

Mode S Transponder

1A 1B 2A 2B

Altimeter #1 P671A 44) P671A 45) P671A 46) P671A 47) P671A 48) P671A 49) P671A 58) P671A 59) P671A 60) P671A 61) P671A 62)

• Gillham Common = Aircraft Ground. • Low = 3 V or 1.5 kΩ • High = greater than 18 V or 1.5 kΩ to 100 kΩ.

Encoding Altimeter #2 (#2-A1, (#2-A2, (#2-A4, (#2-B1, (#2-B2, (#2-B4, (#2-C1, (#2-C2, (#2-C4, (#2-D2, (#2-D4,

P671A P671A P671A P671A P671A P671A P671A P671A P671A P671A P671A

63) 64) 65) 71) 72) 73) 74) 75) 76) 77) 78)

Table 63 TCAS II System Integration Matrix (Sheet 2) 006-05340-0007 Rev. 7

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

BUS #

PARAMETER DESCRIPTION

SOURCE OF DATA

7

Altitude Data Synchro Altitude Source #1/#2

TRANSMISSION DESCRIPTION FOR DATA

RECIPIENT OF DATA

ARINC 565 (XYZ/Synchro) Data

Mode S Transponder

ARINC 718 Xpndr Pins:

NOTE: For use with ARINC 718 Mode S Transponders.

Coarse X (TP 4A) Coarse Y (TP 4B) Coarse Z (TP 4C)

• Synchro ALT #1 • Synchro ALT #1 • Synchro ALT #1

H (TP 4D)

• Synchro reference volts ALT #1 • Synchro common ALT #1

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)

• Synchro ALT #1 • Synchro ALT #1 • Synchro ALT #1 • Synchro altitude system failure status (Altitude Flag) • Synchro ALT #2 • Synchro ALT #2 • Synchro ALT #2 • Synchro reference volts ALT #2 • Synchro common ALT #2 • Synchro ALT #2 • Synchro ALT #2 • Synchro ALT #2 • Synchro altitude system failure status (Altitude Flag)

Table 63 TCAS II System Integration Matrix (Sheet 3) 006-05340-0007 Rev. 7

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL BUS #

PARAMETER DESCRIPTION

SOURCE OF DATA

9

Altitude Data Baro Altitude Type Type A (P671A 85) Type B (P671A 86)

NOTE:

TRANSMISSION DESCRIPTION FOR DATA

RECIPIENT OF DATA

Per Definition Matrix below

Mode S Transponder

In the following matrix, G = Aircraft ground, O = Open.

BARO TYPE A

ALTITUDE

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)

B

DEFINITION (G= Aircraft Ground, O= Open)

BUS #

PARAMETER DESCRIPTION

SOURCE OF DATA

8

Altitude Data Baro Altitude Source Select

TRANSMISSION DESCRIPTION FOR DATA

RECIPIENT OF DATA

• Open = Baro Alt Port #1 Active • Gnd = Baro Alt Port #2 Active

Mode S Transponder

MST 67A (P671A 87) ARINC 718 Transponder (MP - 6E)

Table 63 TCAS II System Integration Matrix (Sheet 4)

006-05340-0007 Rev. 7

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

BUS #

PARAMETER DESCRIPTION

SOURCE OF DATA

TRANSMISSION DESCRIPTION FOR DATA

RECIPIENT OF DATA

5

Discrete (Input)

Aircraft Address Code Discretes: 0 = Open 1 = Ground

24 Bit Address Code - Assigned by FAA for N registered air craft, Phone (405) 954-3116.

Mode S Transponder

Add Add Add Add Add Add Add Add Add Add Add Add Add Add Add Add Add Add Add Add Add Add Add Add

01, 02, 03, 04, 05, 06, 07, 08, 09, 10, 11, 12, 13, 14, 15, 16, 17, 18, 19, 20, 21, 22, 23, 24,

(P671 (P671 (P671 (P671 (P671 (P671 (P671 (P671 (P671 (P671 (P671 (P671 (P671 (P671 (P671 (P671 (P671 (P671 (P671 (P671 (P671 (P671 (P671 (P671

5) 6) 7) 8) 9) 10) 11) 17) 18) 19) 20) 21) 22) 23) 24) 25) 31) 32) 33) 34) 35) 36) 37) 38)

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PARAMETER DESCRIPTION

SOURCE OF DATA

TRANSMISSION DESCRIPTION FOR DATA

RECIPIENT OF DATA

6

Discrete (Input)

Maximum Airspeed Limits

Per Definition Matrix below

Mode S Transponder

A = (P671A 50) B = (P671A 51) C = (P671A 52)

NOTE:

In the following matrix, G = Aircraft ground / O = Open.

(A) RI15

MAX AIRSPEED (B) RI16

(C) RI17

DEFINITION

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

(G= Aircraft Ground, O= Open)

BUS #

PARAMETER DESCRIPTION

SOURCE OF DATA

TRANSMISSION DESCRIPTION FOR DATA

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 #

PARAMETER DESCRIPTION

SOURCE OF DATA

TRANSMISSION DESCRIPTION FOR DATA

RECIPIENT OF DATA

11

Discrete (Input)

Increase Climb Inhibits

2500 fpm climb limit.

TCAS Processor

INC Climb INH 1 (P67A1 A98) INC Climb INH 2 (P67A1 A99)

• Gnd on both Input #1 and #2 inhibits climb.

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

TCAS Processor

#1 (P67A1 A17) #2 (P67A1 A18)

• Ground on Advisory Inhibit Discrete: #1 = STANDBY mode #2 = Aural Inhibit mode

13

Discrete (Input)

Advisory/Annunciator Cancel (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

TCAS Processor

• Gnd = Factory Test Mode Enabled • Open = Normal operation NOTE: For aircraft installations pin A12 MUST be open.

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BUS #

PARAMETER DESCRIPTION

SOURCE OF DATA

TRANSMISSION DESCRIPTION FOR DATA

RECIPIENT OF DATA

16

Discrete (Input)

Calibration Enable (P67A1 B59)

CALENB ATE Test Function

TCAS Processor

• Gnd = Calibration Enabled • Open = Normal operation NOTE: For aircraft installations pin B59 MUST be open.

18

Discrete (Input)

ATE Enable (P67A1 B89)

ATE Test Function Enable

TCAS Processor

• Gnd = ATE Enabled (parallel lines) • Open = Normal Operation (only configuration module lines enabled) NOTE: For aircraft installations pin B89 MUST be open.

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 Power Input (4 lines)

TCAS Processor

+28 Vdc (P67A1 (P67A1 (P67A1 (P67A1

A/C Power A5) A6) A7) A8)

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PARAMETER DESCRIPTION

SOURCE OF DATA

TRANSMISSION DESCRIPTION FOR DATA

RECIPIENT OF DATA

31

Power Input

Aircraft Ground

Aircraft Ground Plane (9 lines)

TCAS Processor

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

GND GND GND GND GND GND GND GND GND 24

Radio Altimeter

(P67A1 (P67A1 (P67A1 (P67A1 (P67A1 (P67A1 (P67A1 (P67A1 (P67A1

A1) A2) A3) A4) A9) A10) B32) B57) B98)

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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PARAMETER DESCRIPTION

SOURCE OF DATA

TRANSMISSION DESCRIPTION FOR DATA

RECIPIENT OF DATA

25

Radio Altimeter

Radio Altimeter /Digital

ARINC 707 (429) data from digital radio altimeter

TCAS Processor

Rad Altim 1A (P67A1 B40)

• ARINC 429 data from digital radio altimeter #1

Rad Altim 1B (P67A1 B41)

• ARINC 429 data from digital radio altimeter #1

Rad Altim 2A (P67A1 B42)

• ARINC 429 data from digital radio altimeter #2

Rad Altim 2B (P67A1 B43)

• ARINC 429 data from digital radio altimeter #2

23

Radio Altimeter

Radio Altimeter Source Select #1/#2 (P67A1 A66)

• Open = Input Port #1 Active • Ground = Input Port #2 Active

TCAS Processor

26

Heading (Magnetic)

Aircraft Heading System (D/G)

Synchro Data, Valid, 26 Vac ARINC 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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PARAMETER DESCRIPTION

SOURCE OF DATA

TRANSMISSION DESCRIPTION FOR DATA

RECIPIENT OF DATA

27

Attitude (Roll and Pitch)

Aircraft Attitude System (V/G)

Synchro Data, Valid, 26 Vac ARINC 407 3-wire synchro

TCAS Processor

Pitch X (P67A1 A91) Pitch Y (P67A1 A92) Pitch Z (P67A1 A93)

• Synchro attitude • Synchro attitude • Synchro attitude

28

29

Attitude/ Heading

Performance Data

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

Inertial Navigation System /AHRS

ARINC 704/705 (High Speed 429) magnetic heading from AHRS.

Hdg/Att (P67A1 Hdg/Att (P67A1

1A B97) 1B B93)

Hdg/Att (P67A1 Hdg/Att (P67A1

2A B69) 2B B70)

Flight Management System

TCAS Processor

• HDG/ATT 2A/2B available only w/ TPU 67A versions 066-01146-0201,-1211. ARINC 702 (429) (Reserved)

TCAS Processor

FMS 1A (P67A1 B55) FMS 1B (P67A1 B7)

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PARAMETER DESCRIPTION

SOURCE OF DATA

TRANSMISSION DESCRIPTION FOR DATA

RECIPIENT OF DATA

32

TX Coordination

TCAS Processor

ARINC 718/735 (429) Data Transponder/TCAS Coordination

Mode S Transponder

Omnidirectional

Bi-directional

Fan

XPDR TX (P67A1 XPDR TX (P67A1 XPDR TX (P67A1 XPDR TX (P67A1 33

Antenna/ Mode S (Two Required)

1A B67) 1B B68) 2A B54) 2B B56)

Mode S Transponder Top Antenna (P671B 2) Bottom Antenna (P671B 1)

34

35

Discrete (Output)

TCAS Processor (P67A1 B37)

FAN ON (Reserved)

Discrete (Output)

TCAS Processor (P67A1 A90)

TA AURAL TRAFFIC

Output for cooling fan where forced air cooling is not available.

• Ground = Active • Open = Not active Active for TA advisory.

Audio Tone Generator/ Audio Distribution Center

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PARAMETER DESCRIPTION

SOURCE OF DATA

TRANSMISSION DESCRIPTION FOR DATA

RECIPIENT OF DATA

36

Discrete (Output)

TCAS Processor

VISUAL ANNUNCIATION TRAFFIC Active for Traffic Advisory.

Visual Annunciator

(P67A1 A87) (P67A1 B58) (P67A1 B106)

VISUAL ANNUNCIATION PREVENTIVE Active for Preventive Resolution Advisory. VISUAL ANNUNCIATION CORRECTIVE Active for Corrective Resolution Advisory. • Ground = Active • Open = Not active • Self Test = Not Active

37

Discrete (Output)

TCAS Processor (P67A1 B6)

TA DISPLAY ENABLE

TA Display

• Ground = Active • Open = Not active Signals some multifunctional traffic displays to display TCAS traffic.

38

Discrete (Output)

TCAS Processor (P67A1 A89)

TCAS VALID • Ground = TCAS System Valid • Open = TCAS System Fault

Fault Annunciator

Monitors TCAS system status.

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PARAMETER DESCRIPTION

SOURCE OF DATA

39

ATE Interface TCAS Processor ATE ATE ATE ATE ATE ATE ATE ATE ATE ATE ATE ATE

40

Flight Data Recorder

A0 (P67A1 B10) A1 (P67A1 B9) A2 (P67A1 B8) D0 (P67A1 B18) D1 (P67A1 B17) D2 (P67A1 B31) D3 (P67A1 B25) D4 (P67A1 B12) D5 (P67A1 B24) D6 (P67A1 B11) D7 (P67A1 B23) CLK (P67A1 B53)

TCAS Processor

TRANSMISSION DESCRIPTION FOR DATA

RECIPIENT OF DATA

ATE Interface

Automatic Test Equipment

ATE pins out 3 address lines (A0A2), 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. RS 422 Interface

Personal Computer

RS 232 Interface, fault data

Bi-directional

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)

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PARAMETER DESCRIPTION

SOURCE OF DATA

42

Configuration Configuration Module 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)

TRANSMISSION DESCRIPTION FOR DATA

RECIPIENT OF DATA

ATE Data Lines A0/A2, D0, D7 serial interface.

Bi-directional

Hardware strapping information from configuration module: TA/RA Block Transfer Program Display Intruder Limit Performance Limit Program Altitude Limit Audio Levels Heading Type Attitude Type Radio Altitude Type Left/Right Display (SKID) Enable Transponder (Mode S Diversity) Aircraft Antenna Configuration Inhibit Functional Test Display All Traffic Ground Display Mode Audio Program Display Intruders On-Ground Radio Altimeter Installation Gillham Altitude Compare Enhanced Extended Test Pass Intruder Files Second A429 AHRS/IRU

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

ARINC 735 (429) Hi Speed Data

TA/RA Display

TA/RA Display (P67A1 B30) TA/RA Display (P67A1 B16) TA/RA Display (P67A1 B28) TA/RA Display (P67A1 B29)

TX 1A TX 1B TX 2A

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.

TX 2B

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BUS #

PARAMETER DESCRIPTION

SOURCE OF DATA

TRANSMISSION DESCRIPTION FOR DATA

RECIPIENT OF DATA

45

Displays

TCAS Processor

ARINC 735 (429) Low Speed Data

RA Display

Speaker (8 Ω) output

Speaker

Headphone (600 Ω ) output.

Headphone

4 Element Directional

Bi-directional

4 Element Directional antenna Or Omnidirectional (Optional) 50 Ω Load (dc short) antenna.

Bi-directional

RA Display TX 1A (P67A1 B35) RA Display TX 1B (P67A1 B36) RA Display TX 2A (P67A1 B33) RA Display TX 2B (P67A1 B34) 46

47

48

Audio Interface (Speaker)

TCAS Processor

Audio Interface (Headphone)

TCAS Processor

Top Antenna

TCAS Processor

Spk Hi (P67A1 A67) Spk Lo (P67A1 A68)

PH Hi (P67A1 A69) PH Lo (P67A1 A70)

(P67A2 (P67A2 (P67A2 (P67A2 49

Bottom Antenna

A1 B1 C1 D1

Top Top Top Top

J1) J2) J3) J4)

TCAS Processor (P67A2 (P67A2 (P67A2 (P67A2

A2 B2 C2 D2

Bot Bot Bot Bot

J1) J2) J3) J4)

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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)

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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 altitude 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 altitude is used to determine own aircraft altitude relative to intruder’s reported altitude and own aircraft flight level altitudes.

(c)

Mode control requests and traffic display control inputs from the Mode S transponder via the ARINC 429 data bus. The Mode S transponder receives this data from the transponder control unit. This information is a factor in TCAS sensitivity level determinations and traffic display format.

(d)

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Own aircraft identification (transponder I.D.) received on the ARINC 429 data bus from own Mode S transponder.

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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 coordination 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 transponder via three discrete bit strapped inputs. This information 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 extended. 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 antenna 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 connected to the top and bottom antennas. The four ports for each directional antenna should reflect specific and different resistance values due to port identification 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 resolution advisory and traffic displays.

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Discrete failure status inputs from the TA units or other optional display units. NOTE:

(l)

In the event of a display unit failure, the display will set its "display valid" output discrete to invalid and attempt 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 failure of internal power supplies.

5

Invalid data from the Radio Altimeter, ATT, HDG, etc.

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 described 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 download the configuration module data and compute a data checksum. 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 compatibility problem between the software and the module.

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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 Honeywell BCAS (EFIS) protocol.

(b)

Display Intruder Limit: Three (minimum)≤ Display Intruder Limit ≤ 31 (no limit), incremented by one.

(c)

Performance Limit Program: 1500 FPM cannot climb determined by FMS or Altitude Limit.

(d)

Altitude Limit: 0 ≤ Altitude Limit ≤ 62000 feet, incremented 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 enabled.

(m)

Transponder (Mode S Diversity) Installation: Single or Dual.

(n)

Aircraft Antenna Configuration Program: Dual directional antenna or Directional and monopole antenna/dc short circuit.

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL (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 enabled.

(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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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 receive 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 aircraft is present. Broadcast messages are transmitted on the TCAS directional 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 output levels and rates employed for TCAS Mode S interrogations. 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 receptions) increases. This reduces the detectable interrogation 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 squitter 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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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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 antenna 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 directional message transmission and reception. (d)

The TCAS processor performs ATCRBS search, track initialization, and track updates. If an ATCRBS equipped aircraft is within TCAS ATCRBS tracking range and altitude, 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 antenna and/or the omni antenna. The TCAS processor selects one of four directional antenna beams to be used for ATCRBS directional message transmission and reception. NOTE:

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Mode S and ATCRBS Mode C interrogation and reply message formats are shown in Figure 21 Mode S and ATCRBS Mode C Interrogation Formats 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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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL (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 altitude 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 intruder closing rate and position relative to own aircraft. 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 intruder 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 resolution advisory alert voice messages to the cockpit audio system, and alert outputs for optional tone generators and/or lamps.

(h)

For traffic advisory category aircraft, the TCAS processor 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 audio system, and alert outputs for optional tone generators 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 generated for proximity or non-threat category aircraft).

(j)

For resolution advisory category aircraft that are also TCAS II equipped, the TCAS processor establishes a coordination data link with threat aircraft. This coordination link involves own TCAS processor transmitting coordination messages to threat aircraft’s transponder via own TCAS antennas and receiving coordination message replies from threat aircraft’s transponder.

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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 maneuvering between TCAS II equipped aircraft that are mutual threats to one another. (k)

During each TCAS 1030 MHz transmission on the directional or omni antenna, the TCAS processor generates a suppression pulse to other L-band equipment on own aircraft.

(l)

The TCAS processor reduces fruit and synchronous garble interference by the following interference limiting methods: 1

An ATCRBS P2 sidelobe suppression pulse is transmitted as an omnidirectional pattern on the directional antenna to control the effective beam width. Refer to Figure 23 TCAS Directional Antenna Transmit/Receive Beam Patterns.

2

A sequence of ATCRBS interrogations are transmitted at different power levels (whisper-shout levels). These whisper-shout levels divide the surrounding 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.

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3

Interrogating more than once to check reply validity.

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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(4)

(m)

The TCAS processor also provides communication interfaces 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.

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 receptions 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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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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 longitudinal centerline of the aircraft ± 5 degrees and as far forward 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 element. 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 processor 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 directional 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 terminations. The TCAS processor routinely performs continuity checks on the omnidirectional antenna and associated cables.

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Figure 23 TCAS Directional Antenna Transmit/Receive Beam Patterns

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TA/RA/VSI Display (1)

General The IVA-81A, IVA-81C, and IVA-81D Traffic Advisory/ Resolution Advisory/Vertical Speed Indicator displays use a high resolution, sunlight readable, full color, liquid crystal display (LCD) to display traffic information. The active matrix LCD display gives a flicker free, parallax free display. The center of the display is a horizontal situation presentation of the traffic around the aircraft including intruder altitude, 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/IVA81C/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 bezel and remote light sensors and by the lighting bus input. An optional bezel mounted brightness control is also available. 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 inputs, 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 failures. 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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Resolution Advisory Display The resolution advisory commands displayed on the TA/RA/VSI (or RA/VSI) are the primary indications used for vertical maneuvering 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 command 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 surrounding 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 selected to display traffic depends on equipment currently present in the aircraft and other user requirements. 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 annunciate TCAS operational modes and failure conditions. The selected traffic display functions as a self-sufficient peripheral 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 conditions.

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL Traffic display data from the TCAS processor, via the highspeed 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 nonthreat 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 Functions for traffic display indications and annunciations.

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 conditions, 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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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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 received 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 failures. Failure status is reported to the TCAS processor via discrete DISPLAY VALID signal lines. The resolution advisories (RAs) on the electrical/electro-mechanical 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 understanding of overall TCAS operation. For additional information refer to the applicable Mode S transponder system maintenance manual. (1)

Mode S Transponder Functions The microprocessor based Mode S transponder performs the following functions in the TCAS II system: (a)

Automatically transmits 1090 MHz Mode S squitter messages every second. These squitter messages notify other 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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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL (d)

Replies to 1030 MHZ Mode A, Mode C, and Mode S interrogations from ATC ground stations with a 1090 MHz message in the traditional manner.

(e)

Transmits 1090 MHz resolution advisory air-to-air coordination message data (received from the TCAS processor) 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:

(g)

(2)

1

Own aircraft identification code, pressure altitude, and maximum airspeed data.

2

TCAS broadcast information and air-to-air resolution 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 application).

5

Mode S ARINC 604 maintenance status.

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.

Mode S Transponder BITE The Mode S transponder contains built-in-test-equipment software 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 output signal.

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL (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 understanding of overall TCAS operation. For additional information on the Mode-S operation of the KFS 578A, PS-578A, PS-550, CD 671C, or CTA81A/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 altitude 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 transponder 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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8.

(4)

The KFS 578A, PS-578A, PS-550, and CD 671C control units require 28 Vdc input power and 5 Vdc/Vac and 28 Vdc panel lighting 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 respectively. Their functions are described in Table 64 Control Unit Control and Indicator Functions.

System Control and Indicator Functions A.

General The primary manual controls used to operate the TCAS II are contained 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 system, 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 reference 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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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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 transponder. The CTA-81A/CTA-81D control unit is suitable for dual (Mode S) installations. The KFS 578A, PS-578A, PS-550, and CD 671C control 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) 006-05340-0007 Rev. 7

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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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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

SBY/STBY 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. 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.

Table 64 Control Unit Control and Indicator Functions (Sheet 1 of 7) 006-05340-0007 Rev. 7

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CONTROL/INDICATOR

FUNCTION

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.

VFR Position

Annunciates ATC and VFR, and displays stored ATC code. The ATC code can be changed by encoder knobs.

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).

Table 64 Control Unit Control and Indicator Functions (Sheet 2)

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CONTROL/INDICATOR

FUNCTION

Function Selector Switch (Cont.) 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.

Table 64 Control Unit Control and Indicator Functions (Sheet 3)

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FUNCTION

Function Selector Switch (Cont.) 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.

Table 64 Control Unit Control and Indicator Functions (Sheet 4)

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CONTROL/INDICATOR

FUNCTION

FID Pushbutton PS-578A

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.

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 IDENT CTA-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.

Table 64 Control Unit Control and Indicator Functions (Sheet 5)

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CONTROL/INDICATOR

FUNCTION

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.

Table 64 Control Unit Control and Indicator Functions (Sheet 6)

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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.

Table 64 Control Unit Control and Indicator Functions (Sheet 7) 006-05340-0007 Rev. 7

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL D.

GC 362A TCAS Graphics Processor The GC 362A TCAS Graphics Computer is a remote mounted graphics processor that converts high speed ARINC 429 from an ARINC 735 compatible TCAS processor to display on the Honeywell RDS 81, RDS 82, RDS 84, RDS 86, RDR 2000, and RDR 2100 color weather radar systems, certain Honeywell Primus series radar systems, and Collins WXR270 series 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 display modes that may be controlled by an external pushbutton or through 429 control via external control unit. This option is selected 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 Display 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 navigation graphics to be presented from various navigation systems. NOTE:

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The CAS 67A TCAS II Pilot’s Guide, p/n 006-08499-(), describes the radar/TCAS display operation in detail.

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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 positive or negative. A corrective advisory requires a vertical maneuver and is always displayed with red and green arcs. The red arc represents 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 adjacent 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 nonthreat category aircraft symbols that depict range, bearing (if tracking is occurring on a directional antenna), and altitude (if intruder is reporting altitude).

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NOTE: F.

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 traffic display, of display operating modes, and of fail conditions. The CAS 67A TCAS II Pilot’s Guide, p/n 006-08499-(), describes the TA/RA/VSI operation in detail.

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 indicate 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:

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The CAS 67A TCAS II Pilot’s Guide, p/n 006-08499-(), describes the RA/VSI operation in detail.

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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 described in separate manuals listed in Table 49 Related Publications NOTE:

H.

The CAS 67A TCAS II Pilot’s Guide, p/n 006-08499-(), describes the radar/TCAS display operation in detail.

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 connector 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 generated 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 annunciations. Refer to FAULT ISOLATION and INSTALLATION AND MAINTENANCE sections of this manual for details.

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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

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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 procedures are used to correct the problem. See the INSTALLATION AND MAINTENANCE 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 initiated 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 computer. 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 contains 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 failures indicated during post-installation or preflight testing, or malfunctions 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: •

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Provides an indication to flight crew that an abnormal condition exists. Typically, a yellow "TCAS" flag will annunciate on the traffic display.

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL •

Causes any Mode S transmissions that report own aircraft status to indicate that own aircraft has no on-board resolution advisory capability.

•

Prevents interrogations by own aircraft TCAS.

•

Deactivates the normal TCAS display functions.

NOTE:

(2)

(3)

(4)

Refer to the pilot’s guide for specific failure indications that will appear on RA/VSI, TA/RA/VSI, dedicated TCAS display, etc.

There are three methods for initiating and observing functional self-test results or failure causes of the Mode S/TCAS system: •

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/IVA81C/IVA-81D TA/RA/VSI.

•

The second method is to observe self-test fault codes annunciated on the TPU side-panel LED indicator (located inside 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.

Before performing TCAS system self-test, ensure that the following 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

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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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. Select 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 traffic 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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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL (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 indicators) 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 advisory throughout the remainder of the test sequence.

NOTE:

(c)

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 appear on the display. A TCAS processor failure will cause the TCAS flag to appear on the RA/VSI, and TCAS to be displayed on the TA/ RA/VSI.

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)

(3)

At the successful conclusion of self-test, the TCAS processor outputs onto the audio bus the synthesized voice message, "TCAS SYSTEM TEST OK."

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 annunciate 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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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL •

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

(4)

•

XPNDR ALT DATA #1 and #2

•

#1 XPNDR ALT DATA

•

#2 XPNDR ALT DATA

•

ATTITUDE

•

HEADING

•

GP RAM

•

NO TCAS 429 DATA

•

TCAS FAIL

If the self-test results were not successful, perform the following: (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 Processor Fault Codes.

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL (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 OTHERWISE RESULT.

FAULT ANNUNCIATION

FAULT ISOLATION

#1 ALT DATA #2 ALT DATA ALT 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 ANTENNA LOWER ANTENNA

Check antenna and associated wiring. Use diagnostic computer to determine failed antenna connection.

ATTITUDE HEADING

Check attitude & heading sources and associated wiring. Check proper attitude type is selected.

TCAS FAIL/NO TCAS TRAFFIC DISPLAY

Check power and associated wiring. Replace traffic display unit.

TA DISPLAY #2 TA 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 (5)

C.

In a dual Mode S-equipped aircraft, set the transponder select switch to #2 position to test the number two transponder. Select the test mode, observe any fail annunciations.

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.

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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 CS WS FT -

System Performance Monitoring Cold Start Warm Start (power interruption < 1 sec) Functional Test

The fault codes listed apply to -0101/-0201/-1111/-1211 except as follows: F-85-00 - applies to -1111/-1211 only F-85-01 - applies to -1111/-1211 only F-89-37 - applies to -1111/-1211 only F-90-03 - applies to -1111/-1211 only NOTE:

Additional fault classes and codes may be indicated. 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.

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

NOTE:

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Fault codes that indicate problems with the antenna or antenna cables will require additional troubleshooting to determine the cause of the fault. The DIAGNOSTIC APPENDICES list the necessary test equipment and recommended procedures for troubleshooting the antenna system.

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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

13

POWER SUPPLY +30 V - voltage divider on I/O board reading out of spec.

F

01

14

POWER SUPPLY +50 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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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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.

Table 1003 TCAS Processor Fault Codes

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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-8936. 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

Table 1003 TCAS Processor Fault Codes

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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

Table 1003 TCAS Processor Fault Codes

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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)

Table 1003 TCAS Processor Fault Codes

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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

Table 1003 TCAS Processor Fault Codes

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL D.

Fault Isolation Using the Diagnostic Computer (1)

The 9-pin diagnostic test connector must be installed and accessible in the aircraft, to use the diagnostic computer.

(2)

Diagnostic Software

(3)

(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 diskette p/n 222-00358-00(). TPU diagnostic software must be loaded onto a diagnostic computer having the requirements listed in the TPUDIAG - TPU Field Diagnostic Program 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 diagnostic 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 diagnostic computer having the requirements listed in the TCASDIAG - TCAS Field Diagnostic Program User Instructions ( DIAGNOSTIC APPENDICES). Refer to instructions on the CD-ROM for operation of the TCAS diagnostic software.

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 Diagnostic Log

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL (4)

The following is a sample of the Input/Output Data Dump.

************** 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

(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 cockpit.

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL Heading Status indicates VAL (Valid) or INV (Invalid). A Valid indicates all the heading parameters meet the electrical requirements. An Invalid may indicate an invalid flag; determined by the Analog Flag A 86 or Binary label 014/320 inputs. 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 between -1,000 ft. and 127,000 feet. This value should be reasonably 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 transponder. 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 Airborne. 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 attitude reading in the cockpit. Pitch Status indicates VAL (Valid) or INV (Invalid). A Valid indicates all the pitch attitude parameters meet the electrical requirements. An Invalid may indicate an invalid flag; determined by the Analog Flag, A 85, or binary label 324 input. 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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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL Roll (Deg.) displays a digital value between 0.00° and ±180.00° (+RT Bank) for TPU 67A unit SW version 01/10 and lower; or (-LT/+RT) for TPU 67A unit SW version 01/11 and higher. This value should be reasonably stable and reflect the attitude 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; determined 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 systems. 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 altitude 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), option 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 address. If the aircraft is US registered the "N" field will show the N number. The HEX and Octal values will also be indicated. Insure that these values correspond with the aircraft being tested. Airborne Functional Test (A 31) indicates Allowed or Inhibited. Program option 0 = Not inhibited; option 1 = Inhibited. Typically, option 0 is used.

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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 active 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 determines this value by altitude. Max. Airspeed (B 74, 75, 76) indicates NO MAX, < 75 kts, 75150 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 indicators 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 inactive and GND when the appropriate input is grounded. Typically, 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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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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 option 1 is used. Ground Display Mode (A33) indicates TA ONLY; or STANDBY. Program 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 option 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 headphone 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 values that will be annunciated. Forty mW is the default indication. Insure this value agrees with the design specification. 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 aircraft 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 traffic). Top & Bottom Antenna Elements (J1 - J4) annunciates a HEX value that indicates the status of the antenna elements. A HEX value between 72H and 8DH is annunciated if the processor confirms 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 inspected to determine the fault.

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL A HEX value between 00H and 0DH is indicated on Bottom elements 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 required to verify that the bottom omni TCAS antenna is transmitting 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 viewing, 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:

006-05340-0007 Rev. 7

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 internal operating temperature that the TPU unit has experienced. The Hobbs at Minimum Temperature is the value of the Hobbs meter when the minimum temperature occurred.

3

Maximum Temperature: This is the maximum internal operating temperature that the TPU unit has experienced. The Hobbs at Maximum Temperature is the value of the Hobbs meter when the maximum temperature 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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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 5

(c)

006-05340-0007 Rev. 7

Operating Temperature: This is a histogram of internal temperatures that the TPU has been operating 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.

Power Cycle Log: This section contains information from the 25 most recent power cycles. A power cycle is measured 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 Diagnostic 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 internal 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 information from the functional test. This information 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 performed), and the Hobbs Meter value during the most recent functional test (not printed if no functional tests have been performed).

4

Power Interruption Data: If the TPU experiences a momentary power interruption (less than 1 second), 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 occurred 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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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 5

(d)

(7)

Power Failure Data: When TPU is turned off (or external power is removed), the TPU will record the Hobbs meter value at the time of the power failure and the internal operating temperature.

Fault Data: During each power cycle, the TPU will record the three highest priority failures (if any occurred) in the Diagnostic Log. The following information 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 described 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 operating temperature of the most recent fault.

The following is a sample of the TPU Diagnostic Log Format:

DIAGNOSTIC LOG DUMP: -------------------Unit Configuration: ------------------Unit KPN: 066-01146-0101 or 0201 Unit Serial Number: ##### EEPROM Unit Config Checksum: 201 Software PN: 125-00###-0###

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL Software Version: TPU ##.# CUMULATIVE DATA --------------Current Hobbs Meter Minimum Temp. Experienced Hobbs at Minimum Temp. Maximum Temp. Experienced Hobbs at Maximum Temp. Cumulative Power Cycles Operating Temperature --------------------< -65° C >= -65° C to < -55° C >= -55° C to < -45° C >= -45° C to < -35° C >= -35° C to < -25° C >= -25° C to < -15° C >= -15° C to < -5° C >= -5° C to < 5° C >= 5° C to < 15° C >= 15° C to < 25° C >= 25° C to < 35° C >= 35° C to < 45° C >= 45° C to < 55° C >= 55° C to < 65° C >= 65° C to < 75° C >= 75° C to < 85° C >= 85° C to < 95° C >= 95° C to < 105° C >= 105° C to < 115° C >= 115° C

:0.0 hrs :0.0 hrs :0.0 hrs :0.0 hrs :0.0 hrs :0.0 hrs :1.0 hrs :5.0 hrs :50.0 hrs :50.0 hrs :17.0 hrs :1.9 hrs :0.1 hrs :0.0 hrs :0.0 hrs :0.0 hrs :0.0 hrs :0.0 hrs :0.0 hrs :0.0 hrs

POWER CYCLE LOG (newest to oldest) --------------------------------POWER CYCLE RECORD #12 ---------------------Hobbs at cold start

:24.0 hrs

006-05340-0007 Rev. 7

:125.0 hrs :-12 C :10.0 hrs :55° C :105.0 hrs :25

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL Temp. at cold start Hobbs at Minimum Temp Minimum Temperature Hobbs at Maximum Temp Maximum Temperature # of Func Tst Performed Hobbs at Last Func Tst Temp. at Last Func Tst # of Pwr Interruptions Hobbs at Last Pwr Int Temp. at Last Pwr Int Hobbs at Power Fail Temp. at Power Fail Diagnostic Log Status

:42° C :124.0 hrs :42° C :124.5 hrs :48° C :0 :N/A :N/A :0 :N/A :N/A :125.0 hrs :46 C :0xff

Fault Data ---------Fault 1 Description: Heading failure during SPM Class Code Priority # of Occurrences Hobbs at most recent Temp. at most recent

:0x2 :0x6 :0x1 :1 :124.1 hrs :45 C

POWER CYCLE RECORD #11 ---------------------Hobbs at cold start Temp. at cold start Hobbs at Minimum Temp Minimum Temperature Hobbs at Maximum Temp Maximum Temperature # of Func Tst Performed Hobbs at Last Func Tst Temp. at Last Func Tst # of Pwr Interruptions

:120.0 :40 C :122.0 :20 C :122.0 :40 C :1 :123.5 :20 C :2

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hrs hrs hrs

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL Hobbs at Last Pwr Int Temp. at Last Pwr Int Hobbs at Power Fail Temp. at Power Fail Diagnostic Log Status Fault Data ---------No faults in this power cycle

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:123.7 hrs :20 C :124.0 hrs :20 C :0xff

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL (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, -0201 Unit Serial#: ##### EEPROM Unit Config Checksum: 167 Unit Software ID: 206-00277-xxxx Software Version: TPU67A Ver x.xx Configuration Module Compatibility Code: 3 CUMULATIVE DATA --------------Current Hobbs Meter : 24.9 hrs Minimum Temp. Experienced: 27 C Hobbs at Minimum Temp. : 19.7 hrs Maximum Temp. Experienced: 49 C Hobbs at Maximum Temp. : 17.7 hrs Cumulative Power Cycles : 62 Operating 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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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL (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: 066-01146-1211 Unit Serial#: EXXXX EEPROM Unit Config Checksum: 167 Software KPN: 125-00812-0000 Software Version: TPU6xA Ver x.xx Configuration Module Compatibility Code: 3 CUMULATIVE DATA --------------Current Hobbs Meter : 24.9 hrs Minimum Temp. Experienced: 27 C Hobbs at Minimum Temp. : 19.7 hrs Maximum Temp. Experienced: 49 C Hobbs at Maximum Temp. : 17.7 hrs Cumulative Power Cycles : 62 Operating 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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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

THIS PAGE IS RESERVED

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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 USING A RAMP TESTER. THIS TEST IS REQUIRED REGARDLESS OF THE NUMBER OF IDENTICAL TCAS INSTALLATIONS PRECEDING THE CURRENT ONE.

Maintenance information for the GC 362A TCAS Graphics Processor and associated 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 support the installation instructions. Those drawings, located at rear of this section, should be reviewed by the installing agency. Any requirements 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 shipping cartons and carefully remove all items. Check the contents to ensure that all items identified on the packing list are included. Visually inspect 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-installation 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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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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 components. The CAS 67A TCAS II system should be installed in the aircraft by standard workmanship and engineering practices according to instructions 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 compartment 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 aircraft. CAUTION:

B.

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.

Location of Equipment (1)

TCAS Antenna Location NOTE:

The following antenna location procedure is provided to achieve certifiable system performance.

The CAS 67A TCAS II system uses a top-mounted directional antenna and a bottom-mounted directional or an L-band omnidirectional antenna. Refer to Figure 2014 ANT 67A Directional Antenna Outline Drawing. Installation of the directional antenna MUST include the appropriate antenna adapter plate for curved surfaces, to insure acceptable bearing accuracy.

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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 information. NOTE:

TCAS requires that the antenna installation guidelines 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 centerline. 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 antenna 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 antenna. 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 exceed a distance of 25 feet (center to center) from the top directional TCAS antenna. In addition, it is strongly recommended that the bottom directional TCAS antenna be installed forward of the main landing 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 outputs, such as radar and satellite communications equipment.

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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.

(2)

NOTE:

When standard installation requirements are impractical or impossible to meet, variations in TCAS antenna 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 responsibility 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 antenna. This is approximately eight feet. Check with the manufacturer of the transponder for compliance with DO 181A specifications.

TCAS Processor Location Care should be exercised to avoid mounting the components near equipment operating with high pulse current or high power outputs 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 connector 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 susceptibility characteristics. Air space should be provided between and around the unit. Figure 2012 TPU 67A TCAS II Processor Outline Drawing shows TCAS processor dimensions. Diagnostic and Recording Test connections should be conveniently accessible for system testing and fault isolation. These test connections should be available inside the cabin to accommodate any flight test or system troubleshooting requirements. NOTE:

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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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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL (3)

Configuration Module The configuration module is mounted according to installation considerations outlined in Figure 2013 CM 67A/CM 2000 Configuration 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:

(5)

Installation instructions for the TCAS/Weather Radar display are contained in separate system maintenance manuals listed in Table 49 Related Publications.

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 Drawing, 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 DESCRIPTION section of this manual. NOTE:

(6)

Installation instructions for the combination TCAS/ Transponder control units are contained in separate manuals listed in Table 49 Related Publications.

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 processor is shown in Figure 2019 GC 362 TCAS Graphics Processor Outline Drawing.

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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 diagrams, including spares, be included in the fabricated harness. 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 diagrams. 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 together 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 paragraph 5.C. (5) Antenna Cable Type Selection.

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL (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. Determine 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 aircraft’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 defined.

(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 Drawing, 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). Typically, the suppression pin is connected from the TCAS processor 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 bottom antenna, the three unused bottom antenna coaxes connected to the TPU 67A processor must be connected 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 information on the aircraft interface diagrams.

The following TCAS processor-to-antenna cable installation requirements must be adhered to:

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL (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 either 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 between 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 installer must determine the length of the coax cable. First, identify the antenna mounting location and the processor mounting location. Then determine the cable routing between the TCAS Processor rear connector and the four RF connectors on the directional antenna. The four cables 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 connector type can be determined. The specifications for the coax cables requires very exacting 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 required specifications. Several fabricators of the coax cables for TCAS antennas are available.

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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-insertion-force, ARINC 404 connector with polarization projections 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 outline drawing, Figure 2012 TPU 67A TCAS II Processor Outline 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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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

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

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL Connector P67A1 Insert A PIN #

SIGNAL NAME

DESCRIPTION

A 001

GND Plane

Input Ground

A 002

GND Plane

Input Ground

A 003

GND Plane

Input Ground

A 004

GND Plane

Input Ground

A 005

+28 Vdc Aircraft PWR

Input Power

A 006

+28 Vdc Aircraft PWR

Input Power

A 007

+28 Vdc Aircraft PWR

Input Power

A 008

+28 Vdc Aircraft PWR

Input Power

A 009

GND Plane

Input Ground

A 010

GND Plane

Input Ground

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 016*

Discrete Input (Reserved)

Input Discrete

A 017*

ADV Inhibit 1(x)

Input Discrete

A 018*

ADV Inhibit 2(x)

Input Discrete

A 019*

Discrete Input (Reserved)

Input Discrete

A 020*

Function Test(x)

Input Discrete

A 021*

Landing Gear

Input Discrete

A 022*

Air/GND(x)

Input Discrete

A 023*

Discrete Input (Reserved)

Input Discrete

A 024*

Discrete Input (Reserved)

Input Discrete

A 025*

Discrete Input (Reserved)

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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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL Connector P67A1 Insert A PIN #

SIGNAL NAME

DESCRIPTION

A 027*

Spare Dis Input 2

Input Discrete

A 028*

Spare Dis Input 3

Input Discrete

A 029*

Spare Dis Input 4

Input Discrete

A 030*

Spare Dis Input 5

Input Discrete

A 031*

Discrete Input (Reserved)

Input Discrete

A 032*

Discrete Input (Reserved)

Input Discrete

A 033*

Discrete Input (Reserved)

Input Discrete

A 034*

TA Valid #1(x)

Input Discrete

A 035*

TA Valid #2(x)

Input Discrete

A 036

Radio Alt #1 +

Input Signal

Rad Alt Val #1

Input Signal

A 038

Radio Alt #1 -

Input Signal

A 039*

Rad Alt Val #2

Input Signal

A 040*

Discrete Input (Reserved)

Input Discrete

A 041*

Gill Alt 1 - D4

Input Signal

A 042*

Discrete Input (Reserved)

Input Discrete

A 043*

Gill Alt 2 - B2

Input Signal

A 044*

Gill Alt 1 - A2

Input Signal

A 045*

Gill Alt 1 - A4

Input Signal

A 046*

Gill Alt 1 - B1

Input Signal

A 047*

Gill Alt 1 - B2

Input Signal

A 048*

Gill Alt 1 - B4

Input Signal

A 049*

Gill Alt 1 - C1

Input Signal

A 050*

Gill Alt 1 - C2

Input Signal

A 051*

Gill Alt 1 - C4

Input Signal

A 052*

Gill Alt 1 - D2

Input Signal

A 053*

Discrete Input (Reserved)

Input Discrete

A

037*

* Diode protected (x) = ground active

Table 2001 TPU 67A TCAS Processor, Rear Connector Pin Names (Sheet 2)

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL Connector P67A1 Insert A PIN #

SIGNAL NAME

DESCRIPTION

A 054*

Gill Alt 2 - A1

Input Signal

A 055*

Gill Alt 2 - A2

Input Signal

A 056*

Gill Alt 2 - A4

Input Signal

A 057*

Gill Alt 2 - B1

Input Signal

A 058*

Gill Alt 1 - A1

Input Signal

A 059*

Gill Alt 2 - B4

Input Signal

A 060*

Gill Alt 2 - C1

Input Signal

A 061*

Gill Alt 2 - C2

Input Signal

A 062*

Gill Alt 2 - C4

Input Signal

A 063*

Gill Alt 2 - D2

Input Signal

A 064*

Gill Alt 2 - D4

Input Signal

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 071*

Discrete Input (Reserved)

Input Discrete

A 072*

ADV/ANNUN Cancel(x)

Input Discrete

A 073*

Discrete Input (Reserved)

Input Discrete

A 074*

Discrete Input (Reserved)

Input Discrete

A 075*

Discrete Input (Reserved)

Input Discrete

A 076*

Discrete Input (Reserved)

Input Discrete

A 077*

Discrete Input (Reserved)

Input Discrete

A 078*

Discrete Input (Reserved)

Input Discrete

A 079*

Discrete Input (Reserved)

Input Discrete

A 080*

Discrete Input (Reserved)

Input Discrete

* Diode protected (x) = ground active

Table 2001 TPU 67A TCAS Processor, Rear Connector Pin Names (Sheet 3)

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL Connector P67A1 Insert A PIN #

SIGNAL NAME

DESCRIPTION

A 081*

Discrete Input (Reserved)

Input Discrete

A 082*

Discrete Input (Reserved)

Input Discrete

A 083*

Discrete Input (Reserved)

Input Discrete

A 084*

Discrete Input (Reserved)

Input Discrete

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

A 100*

Spare Dis Input 6

Input Discrete

A 101*

Spare Dis Input 7

Input Discrete

A 102*

Discrete Input (Reserved)

Input Discrete

A 103*

Discrete Input (Reserved)

Input Discrete

A 104*

Discrete Input (Reserved)

Input Discrete

A 105*

Discrete Input (Reserved)

Input Discrete

A 106*

Discrete Input (Reserved)

Input Discrete

* Diode protected (x) = ground active

Table 2001 TPU 67A TCAS Processor, Rear Connector Pin Names (Sheet 4)

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL Connector P67A1 Insert B PIN #

SIGNAL NAME

DESCRIPTION

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 012

ATE D4

ATE Test Function

B 013

RS 422CLK -

Recorder Function

B 014

N/C

No Connection

B 015

N/C

No Connection

B 016

TA/RA TX 1B

Output 429 Signal

B 017

ATE D1

ATE Test Function

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

B 024

ATE D5

ATE Test Function

B 025

ATE D3

ATE Test Function

B 026

N/C

No Connection

B 027

N/C

No Connection

* Diode protected (x) = ground active

Table 2001 TPU 67A TCAS Processor, Rear Connector Pin Names (Sheet 5)

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL Connector P67A1 Insert B PIN #

SIGNAL NAME

DESCRIPTION

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 031

ATE D2

ATE Test Function

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

038*

Discrete Input (Reserved)

Input Discrete

B 039*

Discrete Input (Reserved)

Input Discrete

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 044*

Discrete Input (Reserved)

Input Discrete

B 045*

Discrete Input (Reserved)

Input Discrete

B 046*

Discrete Input (Reserved)

Input Discrete

B 047*

Discrete Input (Reserved)

Input Discrete

B 048*

Discrete Input (Reserved)

Input Discrete

B 049*

Discrete Input (Reserved)

Input Discrete

B 050*

Discrete Input (Reserved)

Input Discrete

B 051*

Discrete Input (Reserved)

Input Discrete

B 052*

Discrete Input (Reserved)

Input Discrete

B 053

ATE CLK

ATE Test Function

B 054

XPDR TX 2A

Output Signal

B

* Diode protected (x) = ground active

Table 2001 TPU 67A TCAS Processor, Rear Connector Pin Names (Sheet 6)

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL Connector P67A1 Insert B PIN #

SIGNAL NAME

DESCRIPTION

B 055

FMS 1A (Reserved)

Flight Management

B 056

XPDR TX 2B

Output Signal

B 057

GND Plane

Input Ground

B 058

VIS ANNUN Preventive(x)

Output

B 059

CALENB (Cal Enable)(x)

ATE Test Function (N/C)

B 060*

Discrete Input (Reserved)

Input Discrete

B 061*

Discrete Input (Reserved)

Input Discrete

B 062*

Discrete Input (Reserved)

Input Discrete

B 063*

Discrete Input (Reserved)

Input Discrete

B 064*

Discrete Input (Reserved)

Input Discrete

B 065*

Discrete Input (Reserved)

Input Discrete

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

B 071*

Discrete Input (Reserved)

Input Discrete

B 072*

Discrete Input (Reserved)

Input Discrete

B 073*

Discrete Input (Reserved)

Input Discrete

B 074*

Discrete Input (Reserved)

Input Discrete

B 075*

Discrete Input (Reserved)

Input Discrete

B 076*

Discrete Input (Reserved)

Input Discrete

B 077*

Discrete Input (Reserved)

Input Discrete

B 078*

Discrete Input (Reserved)

Input Discrete

B 079*

Discrete Input (Reserved)

Input Discrete

* Diode protected (x) = ground active

Table 2001 TPU 67A TCAS Processor, Rear Connector Pin Names (Sheet 7)

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL Connector P67A1 Insert B PIN #

SIGNAL NAME

DESCRIPTION

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 091*

Discrete Input (Reserved)

Input Discrete

B 092*

Discrete Input (Reserved)

Input Discrete

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 098

GND Plane

Input Ground

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

* Diode protected (x) = ground active

Table 2001 TPU 67A TCAS Processor, Rear Connector Pin Names (Sheet 8)

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL Connector P67A2 COAX #

SIGNAL NAME

DESCRIPTION

A1

Top Directional Antenna J1 (Yell)

Input Signal

A2

Bottom Omni(50Ω)/or Directional Antenna 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

Table 2001 TPU 67A TCAS Processor, Rear Connector Pin Names (Sheet 9)

(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. Connector P101

PIN #

SIGNAL NAME

DESCRIPTION

1

Power Ground

Ground

2

Chip Select 1 (CS1)

3

No Connection

4

Data From Module

5

VCC (+5 Vdc)

6

Clock

7

No Connection

8

Data To Module

9

Chip Select 2 (CS2)

Power Input

Table 2002 Configuration Module, Connector Pin Names

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL (c)

Directional Antenna Connectors Four coaxial cables using TNC connectors connect the directional antenna connectors A1 through D2 to the TCAS processor. See Figure 2014 ANT 67A Directional Antenna Outline Drawing, Figure 2030 Antenna/Suppression Interface Drawing, and paragraph 6. B. Directional Antenna for particulars.

(d)

3ATI Traffic Display Connectors The pneumatic and electrical connectors for the IVA81A/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 electrical connector connects to the TCAS processor, aircraft 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 designed for 28 Vdc panel lighting. The electrical connector pin locations and signal definitions are shown in Figure 2003 IVA-81A/B/C/D Electrical 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) Interface 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 information.

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

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

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

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

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL PIN

SIGNAL NAME

I/O

DESCRIPTION

40 23

H or + C or -

I I

115 Vac 400 Hz or 28 Vdc (Depending on unit version)

22

Chassis Ground

O

TA/VSI Case Ground

39

DC Common

O

Ground

25 24

HI LO

I I

Remote Light Sensor Input

10 9

H C

I I

Dimming Power Input (5 Vac, 5 Vdc, or 28 Vdc)

27 12

A B

I I

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

30 14

A B

I I

Digital Secondary Vertical Speed Input (#2) Low Speed/High Speed 429 ADC/IRS.

4 6

HI LO

I I

ARINC 565 Vertical Speed Input

5 16

H C

I I

26 Vac Reference

1 3 2

+ Vdc REF - Vdc REF DC Rate Signal

I I I

ARINC 575 Analog Input

26 11

A B

I I

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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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL PIN

SIGNAL NAME

I/O

DESCRIPTION

20

28 VDC/Gnd Open

I

Source Select Strap #2

19

Spare

18

NVIS Discrete (066-01171-3704/-3706)

41

Open/Gnd (Test)

15

I

Lamp Test

O

Strap Common

31

Gnd/Open

I

Source Select Strap #1

28 13

A B

O O

Altitude Rate Output Low Speed ARINC 429

7 21

A B

I I

Reserved Input Low Speed ARINC 429

32

CS0I

BIT 0

Configuration Strap

33

CS1I

BIT 1

Configuration Strap

34

CS2I

BIT 2

Configuration Strap

17

CS3I

BIT 3

Configuration Strap

35

CS4I

BIT 4

Configuration Strap

36

CS5I

BIT 5

Configuration Strap

37

CS6I

BIT 6

Configuration Strap

38

CS7I

BIT 7

Configuration Strap

19

CS8I

BIT 8

Configuration Strap

Table 2003 IVA-81A/B/C/D Electrical Connector Pin Names (Sheet 2) NOTE:

For additional connector pin information see Figure 2037 TA/RA Display (ARINC 429 High Speed) Interface Drawing .

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL (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 connected to each pin are defined in Table 2004 KFS 578A Control Unit Connector (P5782) Pin Definitions and Table 2005 KFS 578A Control Unit Connector Pin Names (P5781). Interface diagrams that define the input and output signal 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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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

PIN

SIGNAL NAME

I/O I

DESCRIPTION

1

Shield Ground/429 Common

ARINC 429 Common

2

Polarizer Key

3

429 Input #1 (A)

I

Low Speed ARINC 429

4

429 Input #1 (B)

I

Low Speed ARINC 429

5

429 Input #2 (A)

I

Low Speed ARINC 429

6

429 Input #2 (B)

I

Low Speed ARINC 429

7

429 Output (A)

O

Low Speed ARINC 429

8

429 Output (B)

O

Low Speed ARINC 429

Polarizer Key

9

Spare

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

PIN

SIGNAL NAME

I/O

DESCRIPTION

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/Active Open = Xpndr #1 Not Selected

7

Standby (not)/On #1

O

Gnd = Xpndr #1 Standby/Active Open = Xpndr #1 On

8

Standby (not)/On #2

O

Gnd = Xpndr #2 Standby/Active Open = Xpndr #2 On

9

Remote Function Test (not)/ (External Range Configuration)

I

Remote Function Test: Gnd = Activated Open = Not Activated. External Range Configuration: (-XX04 unit versions) Gnd = Select Range Open = 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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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL PIN

SIGNAL NAME

I/O

DESCRIPTION

11

Control Disable (not)

I

Control Unit Disable: Gnd = Activated Open = Not Activated.

12

Master (not)/Slave

I

Gnd = Master Open = Slave

13

Emergency (not)

I

Squawk Code 7700: Gnd = Activated Open = Not Activated.

14 15

Spare External Standby/ (Manual/Auto)

I

External Standby: Gnd = Standby Active Open = Inactive Manual/Auto: (-XX04 Unit versions) Gnd = Auto Pop-Up Open = Manual

16

Dim Select

I

Gas Discharge Display Dimming: Gnd = Follows A/C lighting bus Open = Follows photocell +28 Vdc = Maximum brightness.

19

Transponder 1 Fail DSC #2

I

Gnd = Normal operation Open = Transponder 1 failure

20

Transponder 2 Fail DSC #2

I

Gnd = Normal operation Open = Transponder 2 failure

21

External Ident

I

Gnd = Activated Open = Not Activated

17 18

22

Spare

23

Spare

24

ATE Test

I

Gnd = Activated Open = Not Activated

25

Warning and Caution (not)

O

A/C Warning/Caution Panel: Gnd = Unit Failure Open = Valid (No Failure)

26

Polarizer Key

27

Antenna Transfer #2 output

O

Gnd = Xpndr #2 Selected/Active Open = Xpndr #2 Not Selected

28

On #1(not)

O

On transponder #1

29

On #2(not)

O

On transponder #2 (dual)

Polarizer key

Table 2005 KFS 578A Control Unit Connector Pin Names (P5781) (Sheet 2 of 2)

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL (f)

PS-578A Mode S/TCAS Control Unit Connectors The PS-578A control unit has one 29-pin (J1) and one 9pin (J2) connector mounted on the rear of the unit. The connectors are keyed to prevent improper connector insertion. The connectors are shown in Figure 2005 PS578A Mode S/TCAS Control Unit Rear Connector (J1) and Figure 2006 PS-578A Mode S/TCAS Control Unit Rear Connector (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 connectors.

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

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

PIN

SIGNAL NAME

I/O

DESCRIPTION

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/Active Open = Xpndr #1 Not Selected

7

Standby (not)/On #1

O

Gnd = Xpndr #1 Standby/Active Open = Xpndr #1 On

8

Standby (not)/On #2

O

Gnd = Xpndr #2 Standby/Active Open = Xpndr #2 On

9

Remote Function Test (not)/ (External Range Configuration)

I

Remote Function Test: Gnd = Activated Open = Not Activated. External Range Configuration: (KFS 578A -XX04 emulations) Gnd = Select Range Open = Extended Range.

10

I

Reserved - Remote Reply In

11

Control Disable (not)

I

Control Unit Disable: Gnd = Activated Open = Not Activated.

12

Master (not)/Slave

I

Gnd = Master Open = Slave

13

Emergency (not)

I

Squawk Code 7700: Gnd = Activated Open = Not Activated.

14 15

Spare External Standby/ (Manual/Auto)

I

External Standby: Gnd = Standby Active Open = Inactive Manual/Auto: (KFS 578A -XX04 emulations) Gnd = Auto Pop-Up Open = Manual

16

Dim Select

I

Display Brightness: Gnd = Follows A/C lighting bus Open = Follows photocell

17

Table 2006 PS-578A Control Unit Connector (J1) Pin Definitions (Sheet 1 of 2)

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

PIN

SIGNAL NAME

I/O

DESCRIPTION

18 19

Transponder 1 Fail DSC #2

I

Gnd = Normal operation Open = Transponder 1 failure

20

Transponder 2 Fail DSC #2

I

Gnd = Normal operation Open = Transponder 2 failure

21

External Ident

I

Gnd = Activated Open = Not Activated

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 = Activated Open = Not Activated

25

Warning and Caution (not)

O

A/C Warning/Caution Panel: Gnd = Unit Failure Open = Valid (No Failure)

26

Polarizer Key

27

Antenna Transfer #2 output

O

Gnd = Xpndr #2 Selected/Active Open = Xpndr #2 Not Selected

28

On #1(not)

O

On transponder #1

29

On #2(not)

O

On transponder #2 (dual)

Polarizer key

Table 2006 PS-578A Control Unit Connector (J1) Pin Definitions (Sheet 2 of 2)

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

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

PIN

SIGNAL NAME

I/O

1

Shield Ground/429 Common

2

Polarizer Key

3

429 Input #1 (A)

I

Low Speed ARINC 429

4

429 Input #1 (B)

I

Low Speed ARINC 429

5

429 Input #2 (A)

I

Low Speed ARINC 429

6

429 Input #2 (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

I

DESCRIPTION ARINC 429 Common Polarizer Key

Spare

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

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL (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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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

PIN 1

SIGNAL NAME

I/O

DESCRIPTION

28Vdc Unit Power

I

+28 Vdc aircraft power

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

2

6

Reserved

7

Reserved

8

Antenna Transfer #2 Output

O

9

Antenna Transfer #1 Output

O

Gnd = Xpndr #1 Selected/Active Open = Xpndr #1 Not Selected

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

18

Transponder 2 Fail DSC #2

I

Gnd = Normal operation Open = Transponder 2 failure

19

Transponder 1 Fail DSC #2

I

Gnd = Normal operation Open = Transponder 1 failure

20

Remote Functional Test (not)/ Ext Range I Config

Remote Test (Pin 24 Open): Gnd = Remote Test active Open = Normal operation Extended Range (Pin 24 Gnd): Gnd = Extended Range active Open = Normal Range

21

External Ident

I

Gnd = Activated Open = Not Activated

22

Reserved

23

Reserved

Table 2008 PS-550 Control Unit Connector Pin Name Definitions (Sheet 1 of 3)

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

PIN 24

SIGNAL NAME Software 040X In

I/O I

DESCRIPTION Gnd (power On) = Activated: pin 20 = Extended Range pin 53 = Manual/Auto mode. Open (power On) = Not Active: pin 20 = Remote Funct Test pin 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 Failure Open = 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

Table 2008 PS-550 Control Unit Connector Pin Name Definitions (Sheet 2 of 3)

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

PIN

SIGNAL NAME

I/O

DESCRIPTION

45

FCDE Test

I

External ATE bench test enable

46

On #2(not)

O

On transponder #2 (dual)

47

Emergency (not)

I

Squawk Code 7700: Gnd = Activated Open = Not Activated.

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

52

Remote Reply In

I

Reply outputs from transponder

53

External Standby Input/ (Manual/Auto Input)

I

Ext Standby (Pin 24 Open): Gnd = Standby activated Open = Standby not activated.

51

Manual/Auto (Pin 24 Gnd): Gnd = Manual Traffic activated Open = 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

On #1(not)

O

On Transponder #1

63 64 65

Table 2008 PS-550 Control Unit Connector Pin Name Definitions (Sheet 3 of 3)

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL (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 improper 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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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL Connector P6711 PIN

SIGNAL NAME

I/O

DESCRIPTION

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

9

Transponder #1 Fail #2

I

Transponder #2 Fail (Fail=Open)

10

On #2

O

On Transponder #2 (Dual)

11

Aircraft Ground

I

Aircraft Ground

12

Transponder #2 Fail #1

I

Transponder #2 Fail (Fail=Open)

13

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

16

Aircraft Ground

I

Aircraft Ground

17

Reply Input

I

Reserved

18

External Ident

I

External Ident

19

Aircraft Ground

I

Aircraft Ground

20

Control Disable

I

Control Unit Disable

21

Aircraft Ground

I

Aircraft Ground

22

Spare Input Discrete #2

23

Spare

24

Emergency

I

Squawk Code 7700

25

Polarizer Key

Polarizer Key

Table 2009 CD 671C Control Unit, Connector Pin Names (Sheet 1 of 2)

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL Connector P6712 PIN

SIGNAL NAME

I/O

DESCRIPTION

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

5

Aircraft Ground

I

Aircraft Ground

6

ARINC 429 #2 (B)

O

Low Speed

7

ARINC 429 Control (A)

O

Low Speed (Altitude Data)

8

Aircraft Ground

I

Aircraft Ground

9

ARINC 429 Control (B)

O

Low Speed (Altitude Data)

10

Aircraft Ground

I

Aircraft Ground

11

External Standby

I

External Standby

12

Aircraft Ground

I

Aircraft Ground

13

Master/Slave

I

Master/Slave

14

Remote Functional Test

I

Remote Functional Test

15

Aircraft Ground

I

Aircraft Ground

16

Spare Input Discrete

17

Aircraft Ground

I

Aircraft Ground

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)

23

Aircraft Ground

I

Aircraft Ground

24

28 Vdc Aircraft Power

I

28 Vdc Aircraft Power

25

Aircraft Ground

I

Aircraft Ground

Table 2009 CD 671C Control Unit, Connector Pin Names (Sheet 2)

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL (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 Interface Drawing, Figure 2034 GC 362/Honeywell TCAS Interface Drawing, and Figure 2035 GC 362/Collins TCAS Interface Drawing define the input and output signal connections to the TCAS Graphics Processor connectors.

Figure 2009 GC 362A TCAS Graphics Processor, Rear Connector

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL Connector P3621 PIN

SIGNAL NAME

I/O

DESCRIPTION

1

Polarizer Pin

2

Program 1

I

Indicator Sweep Characteristic

3

Program 2

I

Indicator Manufacturer

4

Program 3

I

Indicator Sweep Characteristic

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

12

RNG1

I

Honeywell/Collins Range 1

13

RNG2

I

Honeywell/Collins Range 2

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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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL Connector P3621 PIN

SIGNAL NAME

I/O

DESCRIPTION

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

41

GND

I

Aircraft Ground

42

Polarizer Pin

43

No Connection

44

Aircraft Power

I

+ 28 V dc Aircraft Power

45

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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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL Connector P3621 PIN

SIGNAL NAME

I/O

DESCRIPTION

1

Polarizer Pin

2

Program 1

I

Indicator Sweep Characteristic

3

Program 2

I

Indicator Manufacturer

4

Program 3

I

Indicator Sweep Characteristic

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

12

RNG1

I

Honeywell/Collins Range 1

13

RNG2

I

Honeywell/Collins Range 2

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 2011 GC 362A TCAS Graphics Proc. -0103, Connector Pin Names (Sheet 1 of 2)

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL Connector P3621 PIN

SIGNAL NAME

I/O

DESCRIPTION

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/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.-

38

BVR +

I

Bendix Vertical Ret.+

39

BVR -

I

Bendix Vertical Ret.-

40

GND

I

Aircraft Ground

41

GND

I

Aircraft Ground

42

Polarizer Pin

43

No Connection

44

Aircraft Power

I

+ 28 V dc Aircraft Power

45

Aircraft Power

I

+ 28 V dc Aircraft Power

46

POP

I

Pop Up Discrete

47

DISP

I

Display Discrete

48

RNG3

I

Honeywell Range 3

49

No Connection

50

SGND

I

Shield Ground

Table 2011 GC 362A TCAS Graphics Proc. -0103, Connector Pin Names (Sheet 2)

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL Connector P3621 PIN

SIGNAL NAME

I/O

DESCRIPTION

1

Polarizer Pin

2

Program 1

I

Indicator Sweep Characteristic

3

Program 2

I

Indicator Manufacturer

4

Program 3

I

Indicator Sweep Characteristic

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

12

RNG1

I

Honeywell/Collins Range 1

13

RNG2

I

Honeywell/Collins Range 2

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 2012 GC 362A TCAS Graphics Proc. -0203, Connector Pin Names (Sheet 1 of 2)

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL Connector P3621 PIN

SIGNAL NAME

I/O

DESCRIPTION

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

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.-

38

BVR +

I

Bendix Vertical Ret.+

39

BVR -

I

Bendix Vertical Ret.-

40

GND

I

Aircraft Ground

41

GND

I

Aircraft Ground

42

Polarizer Pin

43

No Connection

44

Aircraft Power

I

+ 28 V dc Aircraft Power

45

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 2012 GC 362A TCAS Graphics Proc. -0203, Connector Pin Names (Sheet 2)

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL (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 assembly 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 clearance for sway and ease of removal of the TCAS processor. Clean and prepare all mounting surfaces to insure a good electrical bond before 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 connector 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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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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 mounting bracket. Refer to Figure 2013 CM 67A/CM 2000 Configuration Module 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: (1)

To ensure proper bearing performance, an approved Honeywell antenna adapter plate is required. 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 Antenna 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 attaching 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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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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 dimensions, mounting screw type, antenna footprint patterns, antenna adapter plate patterns and other mounting details 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 information. 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 aircraft 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 instrument panel. Attach the electrical connector to the rear of the unit. If an optional 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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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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 Drawing, 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 provides that feature must be installed. Refer to the Figure 2033 GC 362/Bendix TCAS Interface Drawing, Figure 2034 GC 362/Honeywell TCAS Interface Drawing, and Figure 2035 GC 362/Collins TCAS Interface Drawing when fabricating the wire harness. 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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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL •

A.

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. 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

(7)

Configuration Module

(8)

Check wiring for proper destinations, opens, and shorts using the interface diagrams.

(9)

Check or verify RF cables for electrical length matching, insertion loss and VSWR. Confirm that the four RF antenna coax cables meet 2.5 ±0.5 dB insertion loss requirements, the electrical length characteristics match within 135° and VSWR is 1.35:1 or better.

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL (10)

Check the transponder and DME interface. Some installations may use a common control for the transponder and the TCAS. In that case the TCAS control comes from the transponder control unit. CAUTION:

B.

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.

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 Mounting Rack

INSPECTION/CHECK PROCEDURE •

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 Processor Mode S Transponder and Configuration 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 firmly tightened.

•

Ensure the four coaxial connectors are properly mated to antenna.

Table 2013 Inspection/Check Procedure

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL Omnidirectional Antenna Transponder and TCAS (if installed)

Mode S/TCAS Control Unit

Traffic Displays and/or TCAS/Radar Display

• •

Inspect antenna for any sign of damage. Check that antenna is PROPERLY installed and all mounting screws are firmly tightened.

•

Ensure that RF connector is securely tightened.

•

If installed for TCAS, check that three (3) unused bottom antenna coaxes connected to the TPU 67A processor are connected to 50 Ω terminations.

•

Inspect control unit for any sign of damage.

•

Check that control unit is properly installed and all mounting screws are firmly tightened.

•

Ensure that connector is securely tightened.

• •

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 properly connected to rear of unit.

Table 2013 Inspection/Check Procedure

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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:

(2)

•

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)

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 aircraft. A 115 Vac 60 Hz power may be required for the test equipment. WARNING:

(3)

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.

Pretest Setup This section and the self-test section confirm the proper operation of the TCAS control unit and traffic displays. This section sets initial conditions required for self-test of the system.

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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 cockpit panel background illumination.

(c)

Initial set-up: 1

Check that the transponder, TCAS, and Radar systems are OFF. If applicable, the selected encoding 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 connected to the TCAS processor subsystem. Check that circuit breakers remain closed (pushed-in).

3

(d)

Allow enough time for equipment warm-up. Equipment in the TCAS II system requires one minute for equipment warm-up. External sensors may require more than one minute warm-up time.

Configuration Strapping: Aircraft configuration strapping is stored in the configuration module via a personal computer executing TPUDIAG/TCASDIAG software across the RS-232 port. Follow instructions for configuration programming in the TPUDIAG/TCASDIAG DIAGNOSTIC APPENDICES of this manual.

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL (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:

(g)

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In some installations the range must be selected on the traffic display.

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. Brightness of traffic display may be controlled by the aircraft dimmer switch or by the BRT control on the display unit.

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL (h)

(4)

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.

Self-Test On the TCAS control unit, initiate the TCAS II system selftest. The following events should occur during the test period: 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 symbols 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 altitude, below (-02) with ascending arrow.

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL (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 arrow.

(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 System 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 accommodate other conditions. The person performing these tests should be familiar with the TCAS equipment, the aircraft installation and the supporting test equipment. 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".

NOTE:

(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 _______

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5

Pull the 1 amp Mode S/TCAS Control circuit breaker.

6

Verify that the "TCAS" flag appears on the traffic display.

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 7

Reset the circuit breaker. Verify that the flag clears. Pass/Fail

8

Pull the 5 amp Mode S transponder(s) circuit breaker.

9

Verify that the "TCAS" flag appears on the traffic display.

10

Reset the circuit breaker. Verify that the flag clears. Pass/Fail

11

Pull the Traffic Display or TCAS Graphic Processor 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.

13

Reset the circuit breaker. Verify that the flag clears. Pass/Fail

14

Disable or turn off the 26 Vac 400 Hz reference voltage.

15

Verify that the "TCAS" flag appears on the traffic display.

16

Reset the 26 Vac 400 Hz reference voltage. Verify that the flag clears. Pass/Fail

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL (b)

Mode S/TCAS Control Functions 1

On the TCAS control unit exercise all the TCAS control functions and observe for correct operation. 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/NORMAL/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" annunciation. 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:

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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:

5

On the traffic display unit, an outer ring represents maximum nautical mile (nm) display scaling as selected on the RANGE switch.

If applicable, test the FL (Flight Level) function 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 indicator) annunciates "TA AUTO," but unless TA traffic is present only the radar picture is displayed.

b

Select the T/WX switch to "T/WX" (TCAS and Weather). Observe that the traffic display annunciates "TA" or "TA ONLY" and shows both traffic and weather if the radar is ON.

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL c

Select "TCAS" (TCAS ONLY) with the T/WX switch. Observe that the traffic display annunciates "TA" or "TA ONLY" and shows TCAS traffic but no weather is displayed. Pass/Fail

7

TCAS Sensor Input Checks Confirm the sensor input to TCAS by using a diagnostic 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 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 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 circuit breaker.

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL Verify that the Heading Status goes INVALID. 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 properly interfaced to the TCAS processor. Confirm that the encoding altitude of the transponder and TCAS agree. CAUTION:

PRECAUTIONS MUST BE TAKEN TO INSURE THAT THE ALTITUDE TEST OF THE TRANSPONDER DOES NOT INTERFERE WITH OTHER TCAS EQUIPPED AIRCRAFT. SHIELDING THE TRANSPONDER 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. Altitude readout. The computer readout should agree to within 50 ft. of the cockpit altimeter. The encoding altitude on the transponder test set should agree with the diagnostic 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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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL The XPNDR Source should indicate # 1. (Select #1 if necessary). Confirm the following Encoding Altitudes at the altimeter, diagnostic computer and transponder: Altitude at 2,000 ft. Computer screen indicates Transponder indicates

ft.

ft.

Altitude at 7,800 ft. Computer screen indicates Transponder indicates

ft.

ft.

Altitude at 19,100 ft. Computer screen indicates Transponder indicates

ft.

ft.

Altitude at 31,800 ft. Computer screen indicates Transponder indicates CAUTION:

ft

ft.

THE ABOVE TEST STEP CHECKS BOTH LOGIC STATES FOR ALL GILLHAM LINES. OTHER TESTS MAY BE ADEQUATE FOR SOME INSTALLATIONS.

Flag the encoding altitude source by pulling the circuit breaker. Verify that the Enc. Alt. Status goes INVALID. Verify that the "TCAS" flag appears on the traffic display. Reset the circuit breaker. Verify that the TCAS flag clears. Enc. Altitude Source #1 Pass/Fail

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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 attitude source and measure the inputs at the TPU 67A TCAS Processor. The TCAS and attitude 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 computer screen. Monitor the attitude source in the cockpit. Observe the Pitch and Roll attitude readouts. 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. Verify that the "TCAS" flag appears on the traffic display. Reset the circuit breaker. Verify that the TCAS flag clears. Pass/Fail

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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 processor. The TCAS and radio altimeter 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 computer. Monitor the radio altimeter source in the cockpit. Observe the Radio Altimeter readout. 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, confirm the following: With Radio altitude source at 0 ft. (onft. ground), the computer indicates 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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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL Alternate Method Using a radio altimeter tester, confirm the following: When the Radio altitude is at 0 ft., the Diagnostic computer indicates ft. When the Radio altitude is at 1,000 ft., the Diagnostic computer indicates ft. When the Radio altitude is at 2,000 ft., the Diagnostic computer indicates ft. When the Radio altitude is at 2,500 ft., the Diagnostic computer indicates ft. Flag the Rad. Altimeter source by pulling the circuit breaker. Verify that the Rad. Alt. Status goes INVALID. Verify that the "TCAS" flag appears on the traffic display. Reset the circuit breaker. Verify that the TCAS flag clears. Rad. Altimeter Source #1 Pass/Fail If applicable, select the other Rad. Altitude 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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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL Refer to the drawings for the proper pin assignments and the FAULT ISOLATION section for a description for the Diagnostic computer 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 Nhas an Octal code of a Hex code of .

and

The computer screen shows A/C Address as N , Octal _______ and HEX _______ PASS/FAIL _______ The proper aircraft airspeed strapping for aircraft Nshould 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 "ONGROUND" (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 documentation if necessary to confirm the following items.

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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-Inhibited (OPEN) when testing the GPWS. ADVISORY 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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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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)

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RA/TA Intruder Tests

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL Evaluate proper operation of the TCAS system by observing resolution advisories, traffic advisories, proximity 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 appropriate systems operational. WARNING:

1

PRECAUTIONS MUST BE TAKEN TO INSURE THAT THIS TEST DOES NOT INTERFERE WITH OTHER TCAS EQUIPPED AIRCRAFT.

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 altitude 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 using the radio altimeter test set or equivalent. Increase the radio altitude to 2,750 ft. or greater, 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 altitude 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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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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. Finally, 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 action 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 “DESCEND, DESCEND, DESCEND” should occur around 3.9 nm. An “INCREASE DESCENT, INCREASE DESCENT” message 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 “DESCEND, DESCEND” should occur around 3.9 nm. An “INCREASE DESCENT, INCREASE DESCENT” message will be annunciated 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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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 7

Initiate a second intruder test on the TCAS ramp tester. Using the TCAS ramp test set, create a second scenario to simulate an approaching Mode C transponder 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. Finally, 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 action is taken, a corrective RA will be indicated by a 2500 fpm “INCREASE CLIMB” command. For systems with TPU A "TRAFFIC, TRAFFIC" occur around 5.75 nm. CLIMB, CLIMB” should

67A 066-01146-0101,-0201: voice announcement should Another command of “CLIMB, occur around 3.9 nm.

An “INCREASE CLIMB, INCREASE CLIMB” message 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 “CLIMB, CLIMB” should occur around 3.9 nm. An “INCREASE CLIMB, INCREASE CLIMB” message will be annunciated 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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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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 proper operation of the flight level mode on the traffic 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 using the radio altimeter test set of equivalent. Increase the radio altitude to 2,750 ft. or greater.

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.

5

Initiate the intruder test on the TCAS ramp tester. 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 interrupted and the TCAS mode annunciation on the traffic display is “TA ONLY.”

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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 6

Initiate the intruder test on the TCAS ramp tester. As soon as the TCAS ramp tester triggers a TA or an RA, press the Wind Shear test switch or simulate 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 begins, press the GPWS test switch or simulate a GPWS advisory. Verify the TCAS audio is interrupted. PASS/FAIL

3

Initiate the TCAS self-test.

4

As soon as the "TCAS SYSTEM TEST OK" message begins, press the Wind Shear test switch or simulate a Wind Shear advisory. Verify the TCAS audio is interrupted. PASS/FAIL

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL (d)

TCAS Bearing Accuracy Test (Required for STC Approval) The bearing accuracy test evaluates the performance of the top directional antenna and bottom directional antenna 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 aircraft 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:

1

When checking the TCAS bearing accuracy, the test antenna must be within line-of-sight of the directional antenna under test. The accuracy 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 accuracy 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 position 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" targets because the bottom antenna is locked in omni directional mode. Initialize Configuration Module Strapping Initialize strapping information stored in the configuration module via a personal computer executing TPUDIAG/ TCASDIAG software across the RS232 port. Follow instructions from the TPUDIAG/ TCASDIAG DIAGNOSTIC APPENDICES for strap configuration programming.

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL CAUTION:

THE CONFIGURATION MODULE STRAPPING INFORMATION MUST BE INITIALIZED BEFORE THE SYSTEM WILL PERFORM PROPERLY. TO INITIALIZE THE STRAPPING INFORMATION, USE THE TPUDIAG/TCASDIAG SOFTWARE AND CHOOSE OPTION 3 FROM THE MAIN MENU AND THEN OPTION 1 FROM THE “CONFIGURATION MODULE ACCESS” MENU, AND FOLLOW THE INSTRUCTIONS. ADDITIONALLY, OPTIONS 3 AND 4 FROM THE CONFIGURATION MODULE ACCESS MENU MUST BE USED TO ZERO THE BEARING TABLES (P/N 07100097-0100 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 pitotstatic tester is not required unless local conditions make it necessary. Apply a radio altitude signal to the aircraft using 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 antenna procedures below.

3

Top Directional Antenna Bearing Test Set ramp tester to Mode C (ATCRBS) intruder, UUT horizontal distance 50 feet, UUT vertical distance one foot, altitude reporting ON.

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL Set intruder 2.1 nm range, zero range rate, coaltitude to aircraft being tested, and zero altitude rate. Position ramp test directional antenna 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 relative bearing to the intruder on the traffic display 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 aircraft being tested, and zero altitude rate. Position ramp test directional antenna at same relative altitude as the bottom antenna, 6 feet from the TCAS antenna and directed toward the TCAS antenna for all readings. Do not allow obstructions, such as landing gear, between ramp tester and bottom antenna. Initiate the intruder test and measure the relative bearing to the intruder on the traffic display 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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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

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 clockwise from north on the traffic display unit.

NOTE 2:

The largest acceptable TCAS II bearing error is ±15°, except between 135° and 225° (aft of the wings) where the error may be greater.

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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 Diagnostic Procedures must be used. The bearing correction procedure uses specific airframe bearing error data stored in the configuration module to correct airframe induced bearing error. (See DIAGNOSTIC 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 selected on the color radar indicator. Verify that the traffic 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 Interference (RFI). Determine if there is any mutual interference with any other aircraft system. PASS/FAIL ______.

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL (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 system. When in the Radar Only mode or Radar/TCAS mode, a failure will result in a yellow failure annunciation being 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 system 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 failure 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, selecting the TCAS Only display mode will cause the indicator to display a message indicating which component has failed.

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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 displayed: 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

The appropriate failure annunciation messages will be displayed until the fault has been removed or the display mode is changed. Additional failures will be displayed 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 control 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.

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 8.

Removal and Replacement A.

TPU 67A TCAS Processor (1)

(2)

B.

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.

Reinstallation (a)

Slide TPU 67A onto mount and then gently push unit toward rear until guide pins are aligned and connector is fully engaged.

(b)

Engage and tighten retaining screw clamps to secure unit firmly in place.

Directional Antenna (1)

(2)

Removal (a)

Detach four coaxial cables from connectors J1-J4.

(b)

Remove four screws securing antenna to airframe. Remove antenna and antenna "O" ring.

Reinstallation (a)

Clean aircraft antenna mounting surface.

(b)

Install new antenna "O" ring.

(c)

Secure antenna to aircraft using four screws. Apply approved lock-tight sealant to mounting screws.

(d)

Connect the four coaxial cables to corresponding connectors J1-J4 on the antenna.

(e)

Apply approved sealing silicon around outer edge of antenna to seal antenna to aircraft fuselage.

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL C.

Omnidirectional Antenna (1)

Removal Refer to antenna manufacturer’s documentation.

(2)

Reinstallation Refer to antenna manufacturer’s documentation.

D.

TCAS Control Unit (1)

(2)

E.

Removal (a)

Loosen fasteners at front of unit.

(b)

Pull unit forward from cockpit panel and detach mating cable connector from rear of unit.

Reinstallation (a)

Reconnect cable connector to rear of unit.

(b)

Gently reinsert unit into cockpit panel.

(c)

Tighten fasteners at front of unit.

3ATI Traffic Displays (1)

(2)

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.

Reinstallation (a)

Reconnect cable connector (and if applicable, the pneumatic 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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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL (e) F.

GC 362A TCAS Graphics Processor (1)

(2)

G.

Ensure that unit is secure and check that rear cable is not twisted or kinked.

Removal (a)

Remove the wiring harness connector from the mating connector 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.

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.

CM 67A/CM 2000 Configuration Module (1)

(2)

Removal (a)

Remove two mounting screws.

(b)

Detach mating cable connector from unit.

Reinstallation (a)

Attach mating cable connector to unit.

(b)

Insert and tighten two mounting screws.

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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 Component 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:

10.

Any cleaning of equipment interiors should be done only when performing bench overhaul of system components.

Aircraft Maintenance Programs A.

General Maintenance procedures for TCAS are stipulated in FAA Advisory Circular AC 120-55, "Air Carrier Operational Approval and Use of TCAS II." These procedures include initial activation or return-to-service, 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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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL B.

Honeywell TCAS Maintenance Recommendations The CAS 67A TCAS II system has been designed for "On Condition" maintenance. Automatic performance monitoring and self-test are continuously performed by the TPU 67A TCAS Processor BITE to detect malfunctions that degrade or preclude TCAS protection to a high degree of confidence. When properly installed and interfaced with approved aircraft signal sources, it meets or exceeds the FAA AC 20131A. 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 description of the functional test sequence and acceptable indications during self-test. After major aircraft maintenance cycles, additional system operation should be checked with a TCAS Ramp Test Set. Confirm that the TCAS system performs to the criteria of FAA Advisory Circular AC 20131A (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 04750357-0001 through -0004), of 2024-T4 Alclad, to the skin of the aircraft. The gap between the adapter plate and the skin determines whether Procedure 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 accommodate 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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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL 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 fasteners so a determination can be made as to which installation procedure 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 Procedure A. If the installer is unable to comply with the above criteria, 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 attachment. 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 centerline 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 aircraft skin.

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL (f)

C.

Apply a faying surface seal of BMS5-95 to the faying surfaces of the skin and adapter. Apply BMS5-95 to fasteners and install wet. Complete the riveting operation and install nut plates per installation drawing. Remove excess sealant from edges, exposed surfaces, and connector clearance holes to allow inspection for cracks and corrosion.

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 detected 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), redrill holes identified in step (2) above and apply MS122 release material to duct tape surface. Prepare adapter plate surface and shims by cleaning with acetone followed by application 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 compound gap exists, apply additional DMS4-828 to close the gap. An approximate material application is illustrated in the installation drawing.

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

D.

(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 plastic 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 including shims. Allow specified cure time for DMS4-828 material.

(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 install 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.

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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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

E.

•

Alodine per MIL-C-5541

•

Acetone

•

MEK (Methyl Ethyl Keystone)

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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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

Figure 2011 ANT 67A Directional Antenna Adapter and Moldable Shim P/N 004-50119 006-05340-0007 Rev. 7

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

Figure 2012 TPU 67A TCAS II Processor Outline Drawing (Dwg. No. 155-05828-0000 Rev. AB)

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

Figure 2013

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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) 006-05340-0007 Rev. 7

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Figure 2014 ANT 67A Directional Antenna Outline Drawing (Dwg. No. 155-06003-0000 Rev. AB, Sheet 2 of 2) 006-05340-0007 Rev. 7

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

Figure 2015 IVA 81A (TA/RA/VSI) Outline Drawing (Dwg. No. 066-50001 Rev. T, Sheet 1 of 2)

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

Figure 2015 IVA 81A (TA/RA/VSI) Outline Drawing (Dwg. No. 066-50001 Rev. T, Sheet 2 of 2)

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

Figure 2016 IVA 81B (RA/VSI) Outline Drawing (Dwg. No. 066-50002 Rev. L)

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

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) 006-05340-0007 Rev. 7

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Figure 2019 GC 362 TCAS Graphics Processor Outline Drawing (Dwg. No. 155-05794-0000 Rev. AA)

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

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) 006-05340-0007 Rev. 7

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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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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

Figure 2025 TPU 67A Pinout Drawing (Dwg. No. 155-05989-0001 Rev. AB)

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N CAS 67A TCAS II SYSTEM INSTALLATION MANUAL

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) 006-05340-0007 Rev. 7

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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 2028 TCAS Radar/Baro Altitude Interface Drawing (Dwg. No. 155-05990-0004 Rev. AA, Sheet 2 of 4) 006-05340-0007 Rev. 7

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Figure 2028 TCAS Radar/Baro Altitude Interface Drawing (Dwg. No. 155-05990-0004 Rev. AA, Sheet 3 of 4)

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Figure 2028 TCAS Radar/Baro Altitude Interface Drawing (Dwg. No. 155-05990-0004 Rev. AA, Sheet 4 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 2033 GC 362/Bendix TCAS Interface Drawing (Dwg. No. 155-01628-0000 Rev. 8, Sheet 2 of 3) 006-05340-0007 Rev. 7

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Figure 2033 GC 362/Bendix TCAS Interface Drawing (Dwg. No. 155-01628-0000 Rev. 8, Sheet 3 of 3) 006-05340-0007 Rev. 7

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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 2034 GC 362/Honeywell TCAS Interface Drawing (Dwg. No. 155-01628-0001 Rev. 8, Sheet 2 of 3)

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Figure 2034 GC 362/Honeywell TCAS Interface Drawing (Dwg. No. 155-01628-0001 Rev. 8, Sheet 3 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

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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) 006-05340-0007 Rev. 7

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Figure 2037 TA/RA Display (ARINC 429 High Speed) Interface Drawing (Dwg. No. 155-05990-0014 Rev. AD, Sheet 2 of 9) 006-05340-0007 Rev. 7

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Figure 2037 TA/RA Display (ARINC 429 High Speed) Interface Drawing (Dwg. No. 155-05990-0014 Rev. AD, Sheet 3 of 9) 006-05340-0007 Rev. 7

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Figure 2037 TA/RA Display (ARINC 429 High Speed) Interface Drawing (Dwg. No. 155-05990-0014 Rev. AD, Sheet 4 of 9) 006-05340-0007 Rev. 7

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Figure 2037 TA/RA Display (ARINC 429 High Speed) Interface Drawing (Dwg. No. 155-05990-0014 Rev. AD, Sheet 5 of 9) 006-05340-0007 Rev. 7

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Figure 2037 TA/RA Display (ARINC 429 High Speed) Interface Drawing (Dwg. No. 155-05990-0014 Rev. AD, Sheet 6 of 9) 006-05340-0007 Rev. 7

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Figure 2037 TA/RA Display (ARINC 429 High Speed) Interface Drawing (Dwg. No. 155-05990-0014 Rev. AD, Sheet 7 of 9) 006-05340-0007 Rev. 7

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Figure 2037 TA/RA Display (ARINC 429 High Speed) Interface Drawing (Dwg. No. 155-05990-0014 Rev. AD, Sheet 8 of 9)

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Figure 2037 TA/RA Display (ARINC 429 High Speed) Interface Drawing (Dwg. No. 155-05990-0014 Rev. AD, Sheet 9 of 9) 006-05340-0007 Rev. 7

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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) 006-05340-0007 Rev. 7

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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 2044 Honeywell Primus II/TCAS Interface Drawing (Dwg. No. 155-05990-0062 Rev. AA, Sheet 2 of 4) 006-05340-0007 Rev. 7

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Figure 2044 Honeywell Primus II/TCAS Interface Drawing (Dwg. No. 155-05990-0062 Rev. AA, Sheet 3 of 4)

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Figure 2044 Honeywell Primus II/TCAS Interface Drawing (Dwg. No. 155-05990-0062 Rev. AA, Sheet 4 of 4) 006-05340-0007 Rev. 7

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Figure 2045 CAS 67A TCAS II System Interface Drawing (Dwg. No. 155-05989-0090 Rev. AA, Sheet 1 of 6) 006-05340-0007 Rev. 7

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Figure 2045 CAS 67A TCAS II System Interface Drawing (Dwg. No. 155-05989-0090 Rev. AA, Sheet 2 of 6)

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Figure 2045 CAS 67A TCAS II System Interface Drawing (Dwg. No. 155-05989-0090 Rev. AA, Sheet 3 of 6)

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Figure 2045 CAS 67A TCAS II System Interface Drawing (Dwg. No. 155-05989-0090 Rev. AA, Sheet 4 of 6)

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Figure 2045 CAS 67A TCAS II System Interface Drawing (Dwg. No. 155-05989-0090 Rev. AA, Sheet 5 of 6) 006-05340-0007 Rev. 7

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Figure 2045 CAS 67A TCAS II System Interface Drawing (Dwg. No. 155-05989-0090 Rev. AA, Sheet 6 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 PROGRAM” 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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