ACSS an L 3 Communications and Thales T3K-6M TCAS II User Manual a
ACSS an L-3 Communications and Thales Company TCAS II a
User Manual
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| Document ID | 718686 |
| Application ID | 1rmRCbYNHxFWcwhXvCywsQ== |
| Document Description | User Manual |
| Short Term Confidential | No |
| Permanent Confidential | No |
| Supercede | No |
| Document Type | User Manual |
| Display Format | Adobe Acrobat PDF - pdf |
| Filesize | 209.88kB (2623518 bits) |
| Date Submitted | 2006-10-22 00:00:00 |
| Date Available | 2007-01-18 00:00:00 |
| Creation Date | 2005-12-19 20:00:15 |
| Producing Software | Acrobat Distiller 6.0 (Windows) |
| Document Lastmod | 2005-12-19 20:00:15 |
| Document Title | a |
| Document Creator | BroadVision, Inc. |
| Document Author: | Larry Hicks |
Aviation Communication and Survelliance Systems 19810 North 7th Avenue Phoenix, Arizona 85027−4400 U.S.A. TCAS 3000 Traffic Alert and Collision Avoidance System System Description and Installation Manual 34−43−23 TITLE PAGE T-1 PRINTED IN U.S.A. PUB. NO. 8003529−001REVISION − 15 DECEMBER 2005 SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System PROPRIETARY NOTICE This document and the information disclosed herein are proprietary data of ACSS. Neither this document nor the information contained herein shall be used, reproduced, or disclosed to others without the written authorization of ACSS, except to the extent required for installation or maintenance of the recipient’s equipment. NOTICE − FREEDOM OF INFORMATION ACT (5 USC 552) AND DISCLOSURE OF CONFIDENTIAL INFORMATION GENERALLY (18 USC 1905) This document is being furnished in confidence by ACSS. The information disclosed herein falls within exemption (b) (4) of 5 USC 552 and the prohibitions of 18 USC 1905. S2005 ACSS is a U.S. registered trademark. All other marks are owned by their respective companies. 34−43−23 TITLE PAGE T-2 15 DECEMBER 2005 Copyright 2005 ACSS All Rights Reserved SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System RECORD OF REVISIONS For each revision, put the revised pages in your manual and discard the superseded pages. Write the revision number and date, date put in manual, and the incorporator’s initials in the applicable columns on the Record of Revisions. The initial A shows ACSS is the incorporator. Revision Number Revision Date Date Put in Manual 34−43−23 By Page RR−1 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Blank Page Page RR−2 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System RECORD OF TEMPORARY REVISIONS Read the location instructions on each temporary revision page to know where to put the pages in your manual. Remove temporary revision pages only when discard instructions are given. For each temporary revision, give the correct data in the applicable columns. Temporary Revision No. Temporary Revision Date Date Put in Manual By * Date Removed from Manual By * * The initial A in this column shows ACSS has done the task. 34−43−23 Page RTR−1 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Blank Page Page RTR−2 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System SERVICE BULLETIN LIST Service Bulletin Identified Mod Date Included in this Manual 34−43−23 Description Page SBL−1/(Page SBL−2 blank) 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System LIST OF EFFECTIVE PAGES Original Subheading and Page − .. Revision Title T−1 T−2 − − Record of Revisions RR−1 RR−2 − − Record of Temporary Revisions RTR−1 RTR−2 − − Service Bulletin List SBL−1 SBL−2 − − List of Effective Pages LEP−1 LEP−2 LEP−3 LEP−4 − − − − Table of Contents TC−1 TC−2 TC−3 TC−4 TC−5 TC−6 TC−7 TC−8 TC−9 TC−10 − − − − − − − − − − 15 Dec 2005 Subheading and Page Revision Introduction INTRO−1 INTRO−2 INTRO−3 INTRO−4 INTRO−5 INTRO−6 − − − − − − System Description 1−1 1−2 1−3 1−4 1−5 1−6 1−7 1−8 1−9 1−10 1−11 1−12 1−13 1−14 F 1−15/1−16 1−17 1−18 1−19 1−20 1−21 1−22 1−23 1−24 1−25 1−26 1−27 1−28 − − − − − − − − − − − − − − − − − − − − − − − − − − − Hindicates changed, added, or deleted page. F indicates right foldout page with blank back. 34−43−23 Page LEP−1 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Subheading and Page 1−29 1−30 1−31 1−32 1−33 1−34 1−35 1−36 1−37 1−38 1−39 1−40 1−41 1−42 1−43 1−44 1−45 1−46 1−47 1−48 1−49 1−50 1−51 1−52 1−53 1−54 1−55 1−56 1−57 1−58 1−59 1−60 1−61 1−62 1−63 1−64 Revision − − − − − − − − − − − − − − − − − − − − − − − − − − − − − − − − − − − − Mechanical Installation 2−1 2−2 2−3 2−4 2−5 − − − − − Page LEP−2 15 Dec 2005 Subheading and Page 2−6 F 2−7/2−8 F 2−9/2−10 F 2−11/2−12 F 2−13/2−14 F 2−15/2−16 F 2−17/2−18 2−19 2−20 F 2−21/2−22 F 2−23/2−24 F 2−25/2−26 F 2−27/2−28 F 2−29/2−30 F 2−31/2−32 F 2−33/2−34 F 2−35/2−36 F 2−37/2−38 F 2−39/2−40 F 2−41/2−42 F 2−43/2−44 F 2−45/2−46 F 2−47/2−48 F 2−49/2−50 F 2−51/2−52 F 2−53/2−54 F 2−55/2−56 Revision − − − − − − − − − − − − − − − − − − − − − − − − − − − Electrical Installation 3−1 3−2 F 3−3/3−4 F 3−5/3−6 F 3−7/3−8 F 3−9/3−10 F 3−11/3−12 F 3−13/3−14 F 3−15/3−16 3−17 3−18 3−19 3−20 3−21 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. − − − − − − − − − − − − − − SYSTEM DESCRIPTION AND INSTALLATION MANUAL Subheading and Page 3−22 3−23 3−24 3−25 3−26 3−27 3−28 3−29 3−30 3−31 3−32 3−33 3−34 3−35 3−36 3−37 3−38 3−39 3−40 3−41 3−42 3−43 3−44 3−45 3−46 3−47 3−48 3−49 3−50 3−51 3−52 3−53 3−54 3−55 3−56 3−57 3−58 TCAS 3000 Traffic Alert and Collision Avoidance System Loading/Gradient Specifications 4−1 4−2 4−3 4−4 Revision − − − − − − − − − − − − − − − − − − − − − − − − − − − − − − − − − − − − − − − − − Subheading and Page 4−5 4−6 4−7 4−8 4−9 4−10 4−11 4−12 4−13 4−14 4−15 4−16 4−17 4−18 4−19 4−20 4−21 4−22 4−23 4−24 4−25 4−26 4−27 4−28 4−29 4−30 4−31 4−32 4−33 4−34 4−35 4−36 4−37 4−38 4−39 4−40 4−41 4−42 4−43 4−44 4−45 4−46 4−47 34−43−23 Revision − − − − − − − − − − − − − − − − − − − − − − − − − − − − − − − − − − − − − − − − − − − Page LEP−3 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Subheading and Page 4−48 4−49 4−50 4−51 4−52 4−53 4−54 4−55 4−56 Revision − − − − − − − − − Adjustment/Test 5−1 5−2 5−3 5−4 5−5 5−6 5−7 5−8 5−9 5−10 5−11 5−12 5−13 5−14 − − − − − − − − − − − − − − Fault Isolation 6−1 6−2 6−3 6−4 6−5 6−6 6−7 6−8 6−9 6−10 6−11 6−12 6−13 6−14 6−15 6−16 − − − − − − − − − − − − − − − − Page LEP−4 15 Dec 2005 Subheading and Page 6−17 6−18 6−19 6−20 6−21 6−22 6−23 6−24 Revision − − − − − − − − Maintenance Practices 7−1 7−2 7−3 7−4 7−5 7−6 7−7 7−8 7−9 7−10 7−11 7−12 − − − − − − − − − − − − Inspection/Check 8−1 8−2 − − Cleaning/Painting 9−1 9−2 9−3 9−4 9−5 9−6 − − − − − − Repairs 10−1 10−2 − − 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System TABLE OF CONTENTS Section Page INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO−1 1. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO−1 2. Reference Documents . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO−1 3. Weights and Measurements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO−1 4. Acronyms and Abbreviations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO−2 5. Special Precautions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO−5 SYSTEM DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−1 1. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−1 2. System Components . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−1 3. System Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−7 A. System Functional Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−7 B. System Configurations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−11 Component Descriptions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−17 A. RT−950/951 TCAS Computer Unit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−17 (1) System Interfaces . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−21 (2) Discrete Inputs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−24 (3) Program Inputs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−24 (4) Discrete Outputs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−24 (5) Self−Test Function . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−24 Directional Antenna . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−25 C. ACSS Mode S/TCAS Control Panels . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−28 (1) Functional Description and Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−29 D. Gables ATC/TCAS Dual Mode S Transponder Control Panel . . . . . . . . . . . . . . . . 1−30 (1) Functional Description and Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−32 VSI/TRA Display . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−34 (1) Functional Description and Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−36 (2) Software Considerations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−37 (3) Built−In Test Equipment (BITE) and Self−Test Capability . . . . . . . . . . . . . . . 1−37 Pressure Transducer Module . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−40 G. XS−950 Mode S Data Link Transponder . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−42 H. RCZ−852 Diversity Mode S Transponder . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−47 4. B. E. F. 34−43−23 Page TC−1 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Section Page 5. System Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−51 A. Operational Modes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−51 (1) TCAS Modes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−51 (2) Non−TCAS Modes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−52 (3) Extended Test Mode . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−52 Display Symbology . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−53 (1) Colors . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−53 (2) Traffic Identification . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−54 (3) Data Tags . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−54 (4) VSI Scale Overlays . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−55 (5) Reference Graphics and Annunciations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−55 C. Aural Messages . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−55 (1) Requirements and Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−55 (2) Traffic Advisory (TA) Message . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−56 (3) Resolution Advisory (RA) Messages . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−56 (4) Enhanced RA Messages . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−57 D. Operating Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−58 (1) Pre−Flight Test . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−58 (2) TCAS Mode Activation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−59 (3) TCAS Mode Deactivation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−59 MECHANICAL INSTALLATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2−1 1. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2−1 2. Equipment and Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2−1 3. Mechanical Installation Design . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2−1 A. RT−950/951 TCAS Computer Unit Provisions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2−1 B. Antenna Provisions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2−2 (1) Directional Antenna Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2−2 (2) Omnidirectional Antenna Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2−2 C. Control Panel Provisions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2−3 D. VSI/TRA Provisions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2−3 E. 2−3 B. Pressure Transducer Module (PTM) Provisions . . . . . . . . . . . . . . . . . . . . . . . . . . . Page TC−2 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Page Section F. Transponder Provisions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2−4 (1) Mode S Data Link Transponder Provisions . . . . . . . . . . . . . . . . . . . . . . . . . . . 2−4 (2) Diversity Mode S Transponder Provisions . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2−4 (3) ATC Transponder Antenna Provisions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2−4 ELECTRICAL INSTALLATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3−1 1. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3−1 2. Equipment and Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3−1 3. Electrical Installation Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3−1 4. Electrical Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3−1 A. RT−950/951 TCAS Computer Units . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3−1 B. TCAS Antennas . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3−1 C. Control Panels . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3−23 D. VSI/TRA Displays . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3−31 E. Pressure Transducer Module . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3−39 F. Transponders . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3−40 (1) XS−950 Data Link Transponder . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3−40 (2) RCZ−852 Diversity Mode S Transponder . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3−49 LOADING/GRADIENT SPECIFICATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4−1 1. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4−1 2. Loading and Gradient Specifications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4−1 ADJUSTMENT/TEST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5−1 1. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5−1 2. Equipment and Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5−1 3. Initial Harness Checkout (New Installations Only) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5−1 A. TCAS Computer Unit Harness Checkout . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5−1 B. TCAS Controller and Display Unit Harness Checkout . . . . . . . . . . . . . . . . . . . . . . 5−1 C. LRU Preinstallation Power Checkout . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5−2 D. Initial System Installation Operational Test . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5−2 34−43−23 Page TC−3 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Section 4. Page System Self−Tests . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5−3 A. Cockpit Display Test Modes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5−3 (1) Short Test Mode . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5−3 (2) Extended Test Mode . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5−4 TCAS Computer Unit Self−Test . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5−5 5. Return to Service Test . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5−6 6. Operational Software Loading Using an ARINC Portable Data Loader . . . . . . . . . . . 5−6 A. Current Software Verification . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5−6 B. Operational Software Loading (While Installed on Aircraft) . . . . . . . . . . . . . . . . . . 5−6 C. Compact Flash Card (while installed on aricraft) . . . . . . . . . . . . . . . . . . . . . . . . . . . 5−7 (1) Procedure for Uploading OPS SW Through Compact Flash Card . . . . . . . . 5−7 D. Updated Software Verification . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5−11 (1) Software Verification Using Cockpit Systems ONLY . . . . . . . . . . . . . . . . . . . . 5−11 (2) Software Verification Using a Stand−Alone PC ONLY . . . . . . . . . . . . . . . . . . 5−11 (3) Software Verification Using a Software Verification Fixture ONLY . . . . . . . . 5−13 (4) Software Verification Using a Remote Connected VSI/TRA ONLY . . . . . . . 5−13 FAULT ISOLATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6−1 1. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6−1 2. Equipment and Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6−1 3. Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6−1 A. CMC or CFDS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6−1 B. TCAS Display System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6−1 C. TCAS Aural and VSI/TRA Annunciations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6−3 D. TCAS Test Menu and System Status Pages . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6−6 (1) TCAS Test Menu . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6−6 (2) System Status Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6−7 (3) Display Status Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6−8 (4) RAD/ALT Status Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6−9 (5) Transponder (XPDR) Status Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6−10 (6) Programming Pins Status Pages . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6−11 (7) Help Reference Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6−16 (8) Suppression Bus Fail Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6−17 B. Page TC−4 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Page Section (9) Suppression Bus Clear Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6−18 (10) Antenna Port Status Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6−18 (11) Option Pins Status Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6−19 (12) Part Numbers Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6−20 E. TCAS Computer Unit Self−Test . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6−20 F. Directional Antenna Test / Fault Isolation Procedure . . . . . . . . . . . . . . . . . . . . . . . 6−23 MAINTENANCE PRACTICES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7−1 1. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7−1 2. Equipment and Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7−1 3. Procedure for the RT−950/951 TCAS Computer Unit . . . . . . . . . . . . . . . . . . . . . . . . . . 7−2 A. Removal and Installation Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7−2 B. Adjustment Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7−2 C. Repair Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7−2 D. Return to Service Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7−2 Procedure for the Directional Antenna . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7−3 A. Removal and Installation Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7−3 B. Adjustment Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7−4 C. Repair Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7−4 D. Return to Service Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7−4 Procedure for the Omnidirectional Antenna . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7−4 A. Removal and Installation Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7−4 B. Adjustment Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7−5 C. Repair Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7−5 D. Return to Service Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7−5 Procedure for the Control Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7−5 A. Removal and Installation Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7−5 B. Adjustment Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7−5 C. Repair Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7−5 D. Return to Service Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7−5 Procedure for the VSI/TRA Display . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7−6 A. Removal and Installation Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7−6 B. Adjustment Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7−6 4. 5. 6. 7. 34−43−23 Page TC−5 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Section Page C. Repair Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7−6 D. Return to Service Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7−6 Procedure for the Pressure Transducer Module . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7−7 A. Removal and Installation Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7−7 B. Adjustment Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7−7 C. Repair Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7−7 D. Return to Service Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7−7 Procedure for the Transponder . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7−8 A. Removal and Installation Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7−8 B. Adjustment Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7−8 C. Repair Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7−8 D. Return to Service Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7−9 10. Instructions for Continued Airworthiness, FAR Part 25.1529 . . . . . . . . . . . . . . . . . . . . 7−10 INSPECTION/CHECK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8−1 1. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8−1 2. Equipment and Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8−1 3. Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8−1 A. Check TCAS Computer Unit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8−1 B. Check Antennas . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8−1 C. Check Control Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8−1 D. Check VSI/TRA Display . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8−2 E. Check Transponders . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8−2 CLEANING/PAINTING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9−1 1. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9−1 2. Equipment and Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9−1 3. Cleaning . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9−2 A. Clean TCAS Computer Unit and Mounting Tray . . . . . . . . . . . . . . . . . . . . . . . . . . . 9−2 B. Clean Antennas . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9−2 C. Clean Control Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9−2 D. Clean VSI/TRA Display . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9−3 E. Clean Transponders . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9−3 Painting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9−2 8. 9. 4. Page TC−6 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System A. TCAS Directional Antennas . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9−3 (1) Scope . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9−3 (2) Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9−3 (3) Performance Verification Testing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9−4 Other TCAS System LRUs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9−5 REPAIRS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10−1 1. 10−1 B. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . List of Illustrations Figure Page Figure 1−1. TCAS ll Advisory Capabilities . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−8 Figure 1−2. TCAS/Mode S Communication . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−9 Figure 1−3. TA/RA Airspace Coverage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−10 Figure 1−4. Basic TCAS ll Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−11 Figure 1−5. Typical System Configurations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−12 Figure 1−6. TCAS 3000 System Block Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−15 Figure 1−7. RT−950 TCAS Computer Unit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−17 Figure 1−8. RT−951 TCAS Computer Unit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−18 Figure 1−9. Directional Antenna . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−27 Figure 1−10. ACSS Control Panels . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−28 Figure 1−11. Typical Gables ATC/TCAS Control Panel . . . . . . . . . . . . . . . . . . . . . . . . . . 1−31 Figure 1−12. Typical VSI/TRA Display Formats . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−35 Figure 1−13. VSI/TRA Interface Diagram (41−Pin Version) . . . . . . . . . . . . . . . . . . . . . . . 1−38 Figure 1−14. VSI/TRA Interface Diagram (55−Pin Version) . . . . . . . . . . . . . . . . . . . . . . . 1−39 Figure 1−15. Pressure Transducer Module . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−40 Figure 1−16. XS−950 Data Link Transponder . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−42 Figure 1−17. RCZ−852 Diversity Mode S Transponder . . . . . . . . . . . . . . . . . . . . . . . . . . 1−47 Figure 1−18. TCAS ll Display Test Pattern . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−59 Figure 2−1. RT−950 TCAS Computer Unit Outline and Installation Drawing . . . . . . . 2−7 Figure 2−2. RT−951 TCAS Computer Unit Outline and Installation Diagram . . . . . . . 2−11 Figure 2−3. RT−951 TCAS Computer Unit Outline and Installation Diagram . . . . . . . 2−15 Figure 2−4. TCAS Directional and Omnidirectional Antenna Locations . . . . . . . . . . . 2−19 Figure 2−5. Directional Antenna Angular Orientation . . . . . . . . . . . . . . . . . . . . . . . . . . . 2−20 Figure 2−6. Directional Antenna Outline and Installation Diagram . . . . . . . . . . . . . . . . 2−21 34−43−23 Page TC−7 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System List of Illustrations (cont) Figure Page Figure 2−7. Directional Antenna Baseplate Outline and Installation Diagram . . . . . . 2−31 Figure 2−8. Control Panel (Dual Mode S) Outline and Installation Diagram . . . . . . . . 2−35 Figure 2−9. Control Panel (ATCRBS−Mode S) Outline and Installation Diagram . . . 2−37 Figure 2−10. Gables G7130−XX Control Panel Outline and Installation Diagram . . . . 2−39 Figure 2−11. VSI/TRA Outline and Installation Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . 2−41 Figure 2−12. Pressure Transducer Module Outline and Installation Diagram . . . . . . . . 2−43 Figure 2−13. XS−950 Data Link Transponder Outline and Installation Diagram . . . . . 2−49 Figure 2−14. RCZ−852 Mode S Transponder Outline and Installation Diagram . . . . . 2−53 Figure 3−1. Typical Installation Types . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3−2 Figure 3−2. TCAS System Interconnect Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3−3 Figure 3−3. TCAS Computer Unit ARINC 600 Connector (P1) Layout . . . . . . . . . . . . 3−17 Figure 3−4. Contact Arrangement for CU Left Top Plug (LTP) Insert . . . . . . . . . . . . . . 3−18 Figure 3−5. Contact Arrangement for CU Left Middle Plug (LMP) Insert . . . . . . . . . . 3−18 Figure 3−6. Contact Arrangement for Left Bottom Plug (LBP) Insert . . . . . . . . . . . . . . 3−19 Figure 3−7. Contact Arrangement for Right Middle Plug (RMP) Insert . . . . . . . . . . . . 3−20 Figure 3−8. Contact Arrangement for Right Bottom Plug (RBP) Insert . . . . . . . . . . . . 3−21 Figure 3−9. TCAS Computer Unit Data Loader Connector (J1) Pin Layout . . . . . . . . 3−22 Figure 3−10. VSI/TRA 41−Pin Connector Layout . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3−34 Figure 3−11. VSI/TRA 55−Pin Connector Layout . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3−38 Figure 3−12. Strap Assembly . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3−55 Figure 5−1. VSI/TRA Fault Warning Display . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5−3 Figure 5−2. Compact Flash Card Access Port and LRU Identification Label . . . . . . . 5−8 Figure 5−3. Compact Flash Card Ejector Location . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5−9 Figure 5−4. RS−232 PC to TCAS Interface Cable . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5−12 Figure 6−1. TCAS Test Menu Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6−6 Figure 6−2. Typical System Status Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6−7 Figure 6−3. Typical Display Status Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6−8 Figure 6−4. Typical RAD/ALT Status Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6−9 Figure 6−5. Typical Transponder (XPDR) Status Page . . . . . . . . . . . . . . . . . . . . . . . . . 6−10 Figure 6−6. Typical Program Pins 1/3 Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6−11 Figure 6−7. Typical Program Pins 2/3 Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6−13 Figure 6−8. Typical Program Pins 3/3 Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6−14 Page TC−8 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System List of Illustrations (cont) Figure Page Figure 6−9. Help Reference Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6−16 Figure 6−10. Suppression Bus Fail Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6−17 Figure 6−11. Suppression Bus Clear Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6−18 Figure 6−12. Typical Antenna Port Status Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6−18 Figure 6−13. Typical Option Pins Status Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6−19 Figure 6−14. Typical Option Pins Status Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6−20 34−43−23 Page TC−9 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System List of Tables Table Page Acronyms and Abbreviations Table . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO−2 Table 1−1. System Components Supplied by ACSS . . . . . . . . . . . . . . . . . . . . . . . . . . 1−2 Table 1−2. System Components Not Supplied by ACSS ...................... 1−3 Table 1−3. Directional Antenna Configurations .............................. 1−3 Table 1−4. Control Panel Configurations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−5 Table 1−5. VSI/TRA Display Configurations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1−6 Table 1−6. RT−950/951 TCAS Computer Unit Leading Particulars Table 1−7. ACSS Control Panel Leading Particulars ............. 1−19 ......................... 1−29 Table 1−8. Gables G7130 Series Control Panel Leading Particulars . . . . . . . . . . . . 1−31 Table 1−9. VSI/TRA Leading Particulars 1−36 Table 1−10. Pressure Transducer Module Leading Particulars .................. 1−41 Table 1−11. XS−950 Data Link Transponder Leading Particulars . . . . . . . . . . . . . . . . 1−43 Table 1−12. RCZ−852 Diversity Mode S Transponder Leading Particulars ....... 1−48 Table 1−13. TCAS Traffic Symbols .......................................... 1−53 Table 3−1. ACSS Dual Mode S Control Panel Interconnect Data . . . . . . . . . . . . . . . 3−23 Table 3−2. ACSS ATCRBS−Mode S Control Panel Interconnect Data .......... 3−26 Table 3−3. Gables G7130−XX ATC/TCAS Control Panel Interconnect Data Table 3−4. .................................... ..... 3−29 41−Pin VSI/TRA Interconnect Data .............................. 3−31 Table 3−5. 55−Pin VSI/TRA Interconnect Data .............................. 3−35 Table 3−6. Pressure Transducer Module Interconnect Data Table 3−7. XS−950 Data Link Transponder Interconnect Data Table 3−8. RCZ−852 Diversity Mode S Transponder Interconnect Data Table 3−9. Strap Assembly Strap Assignments Table 3−10. Strap Assembly Programming Instructions Table 4−1. RT−950/951 TCAS Computer Unit Loading/Gradient Specifications Table 4−2. ACSS Dual Mode S Control Panel Interface Descriptions ................... 3−39 ................. 3−41 ......... 3−49 .............................. 3−54 ........................ 3−55 .. 4−2 ........... 4−23 Table 4−3. ACSS ATCRBS−Mode S Control Panel Interface Descriptions . . . . . . . 4−25 Table 4−4. Gables Control Panel Interface Descriptions ...................... 4−28 Table 4−5. 41−Pin VSI/TRA Interface Descriptions ........................... 4−31 Table 4−6. 55−Pin VSI/TRA Interface Descriptions ........................... 4−36 Table 4−7. Pressure Transducer Module Interface Descriptions . . . . . . . . . . . . . . . . 4−42 Table 4−8. XS−950 Data Link Transponder Interface Descriptions 4−43 Page TC−10 15 Dec 2005 ............. 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System List of Tables (cont) Table Page Table 4−9. RCZ−852 Diversity Mode S Transponder Interface Descriptions ..... 4−52 Table 5−1. Equipment and Materials ....................................... 5−1 Table 5−2. Computer Unit Harness Checkout Table 5−3. Extended Test Menu Selections Table 5−4. Compact Flash Upload / LED Correlation ......................... 5−9 Table 6−1. TCAS Aural and VSI/TRA Annunciations ......................... 6−3 Table 6−2. System Status Page Fault Messages ............................ 6−7 Table 6−3. Computer Unit Self−Test Execution .............................. 6−21 Table 6−4. Computer Unit Fault Reporting and Corrective Actions ............. 6−22 Table 6−5. Antenna Wiring Resistance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6−23 Table 7−1. Materials Table 9−1. Equipment and Materials Table 10−1. LRU Maintenance Manuals ............................... 5−1 ................................. 5−5 ..................................................... 7−1 ....................................... 9−1 ..................................... 10−1 34−43−23 Page TC−11 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System INTRODUCTION 1. General This manual provides general system installation and maintenance instructions and theory of operation for the TCAS 3000 Traffic Alert and Collision Avoidance System. It also provides interface information and interconnect diagrams to permit a general understanding of the overall system. The purpose of this manual is to help you install, operate, maintain and troubleshoot the TCAS 3000 Traffic Alert and Collision Avoidance System in the aircraft. Common system maintenance procedures are not presented in this manual. The best established shop and flight line practices should be used. NOTE : The conditions and tests required for Technical Standard Order (TSO) approval of this article are minimum performance standards. It is the responsibility of those installing this article either on or within a specific type or class of aircraft to determine that the aircraft installation conditions are within the TSO standards. The article may be installed only if the installation is performed in accordance with the applicable airworthiness and production requirements. 2. Reference Documents Publications on subsystems installed as part of the TCAS 3000 Traffic Alert and Collision Avoidance System are identified in the list that follows: ACSS Publication Number Document Title Mode S Data Link Transponder System Description and Installation Manual A09−3839−001 PRIMUS ll SRZ−85X Series Integrated Radio System Operation and Installation Manual (Used if transponders or control panel is part of PRIMUS II Integrated Radio System) A15−3800−001 (Honeywell) Handling, Storage, and Shipping Procedures Instruction Manual for ACSS Avionics Equipment A09−1100−001 3. Weights and Measurements Weights and measurements in this manual use both U.S. and S.I. (metric) values. 4. Acronyms and Abbreviations The letter symbols for abbreviations are the same as shown in ANSI/IEEE Std 260 and ASME Y1.1, except as identified in the acronyms and abbreviations table. 34−43−23 Page INTRO−1 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Acronyms and Abbreviations Table Term Definition ac alternating current ADC air data computer ADL airborne data loader ADLP airborne data link processor ADS−B automatic dependent surveillance broadcast AGL above ground level ALT altitude AMM aircraft maintenance manual AMN ACSS Material Number ANT antenna ATC air traffic control ATCRBS air traffic control radar beacon system ATN Aircraft Telecommunications Network BITE built−in test equipment BOT bottom CAS collision avoidance system CFDIU centralized fault display interface unit CFDS central fault display system CMC central maintenance computer CMM component maintenance manual COMM communication CU computer unit DADC digital air data computer dc direct current DISP display DLP data link processor EFIS electronic flight instrument system ELM extended length message EPROM erasable programmable read−only memory FAA Federal Aviation Administration FPM feet per minute Page INTRO−2 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Acronyms and Abbreviations Table (cont) Term Definition HDG heading I/O input/output INH inhibit IPC illustrated parts catalog IRS inertial reference system LBP left bottom plug LCD liquid crystal display LMP left middle plug LRU line replaceable unit LTP left top plug MCU modular concept unit MEL minimum equipment list Mode S mode select transponder MTBF mean time between failures MTL minimum trigger level PDL portable data loader PMS performance management system POST power−on self−test PROG program PTM pressure transducer module RA resolution advisory RAD ALT radio altimeter RBP right bottom plug RCB radio communication bus RMP right middle plug RMU radio management unit RNG range RTP right top plug SPI special pulse identifier SSM sign status matrix 34−43−23 Page INTRO−3 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Acronyms and Abbreviations Table (cont) Term Definition STBY standby TA traffic advisory TCAS traffic alert and collision avoidance system TRA traffic resolution advisory TSO Technical Standard Order VSI vertical speed indicator VSWR voltage standing wave radio WOW weight−on−wheels XPDR/XPNDR transponder Page INTRO−4 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System 5. Special Precautions Warnings, cautions, and notes in this manual give the data that follows: • A WARNING is an operation or maintenance procedure or condition, which, if not obeyed, can cause injury or death • A CAUTION is an operation or maintenance procedure or condition, which, if not obeyed, can cause damage to the equipment • A NOTE gives data to make the work easier or gives directions to go to a procedure. All personnel who operate and do maintenance on the TCAS components and on the applicable test equipment, must know and obey the safety precautions. The warnings and cautions that follow apply to all parts of this manual. WARNING: HIGH VOLTAGES MAY BE PRESENT ON SYSTEM INTERCONNECT CABLES. MAKE SURE THAT SYSTEM POWER IS OFF BEFORE YOU DISCONNECT LRU MATING CONNECTORS. CAUTION: ACSS HAS PREPARED AN AIRWORTHINESS CRITICAL REQUIREMENTS ANALYSIS FOR THIS AIRBORNE EQUIPMENT TO MAKE SURE THAT IT WILL NOT CAUSE A DANGEROUS IN−FLIGHT CONDITION. SPECIFIC PARTS, TESTS, AND PROCEDURES THAT ARE IDENTIFIED AS INSTALLATION CRITICAL IN THE ANALYSIS ARE CHANGED TO AIRWORTHINESS CRITICAL IN THIS MANUAL. IT IS NECESSARY TO DO THESE PROCEDURES AND TESTS TO GET THE APPROVED RESULTS. CAUTION: THE TCAS 3000 SYSTEM CONTAINS LRUS THAT ARE ELECTROSTATIC DISCHARGE SENSITIVE (ESDS). IF YOU DO NOT OBEY THE NECESSARY CONTROLS, A FAILURE OR UNSATISFACTORY OPERATION OF THE UNIT CAN OCCUR FROM ELECTROSTATIC DISCHARGE. USE APPROVED INDUSTRY PRECAUTIONS TO KEEP THE RISK OF DAMAGE TO A MINIMUM WHEN YOU TOUCH, REMOVE, OR INSTALL LRUS. 34−43−23 Page INTRO−5 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Blank Page Page INTRO−6 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System SYSTEM DESCRIPTION 1. General The purpose of the TCAS 3000 Traffic Alert and Collision Avoidance System is to determine the range, altitude, and bearing of other aircraft equipped with Mode S/Air Traffic Control Radar Beacon System (ATCRBS) transponders, with respect to the location of own aircraft. It also monitors the trajectory of these aircraft for the purpose of determining if any of them constitute a potential collision hazard. The TCAS is responsible for estimating the projected intruder track and determining if a potential conflict exists. If so, the system displays an advisory to the pilot. The system also provides guidance for the optimum vertical avoidance maneuver. Complementary avoidance maneuvers between two TCAS equipped aircraft are ensured by coordination of mutual intentions with the other aircraft through the Mode S transponders. 2. System Components Table 1−1 gives the components that are supplied by ACSS. Table 1−2 gives the components that are necessary, but are not supplied by ACSS. Table 1−3 thru Table 1−5 provide additional component descriptions as follows: • Table 1−3. Directional Antenna Configurations • Table 1−4. Control Panel Configurations • Table 1−5. VSI/TRA Display Configurations. 34−43−23 Page 1−1 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 1−1. System Components Supplied by ACSS Component Model No. ACSS Part No. TCAS Computer Unit (6−MCU size unit) −−−− 9003000−10yyy (Note 1.) TCAS Computer Unit (4−MCU size unit) −−−− 9003000−55yyy, −65yyy (Note 1.) Directional Antenna (See Table 1−3 for configuration descriptions) −− 7514081−VAR or 7514060−VAR Control Panel (See Table 1−4 for configuration descriptions) −− 4052190−VAR VSI/TRA Display (See Table 1−5 for configuration descriptions) −− 4067241−VAR Pressure Transducer Module (PTM) −− 4067487−901 (Note 2.) PTM Mounting Bracket, Right Angle −− 4067487−901 PTM Mounting Plate, 3−ATI Panel Mount −− 4067492−VAR (Note 3.) XS−950 7517800−xxyyy Mode S Data Link Transponder (4−MCU size unit) Diversity Mode S Transponder RCZ−852 Installation Kit for RCZ−852 Mode S Transponder (Contains mounting tray, 106 pin ARINC 404 mating connector and two TNC RF jack connectors) IK−415 7510700−850/−951 7510707−968 NOTES: 1. The last three digits of the five digit dash number (yyy) correspond to the unit software version. 2. The PTM is only required on installations that use a ACSS VSI/TRA display where no electrical vertical speed data in a compatible format is available. 3. The 3−ATI panel mount comes in three different color options: −901 (gray), −902 (brown), and −903 (black). Page 1−2 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 1−2. System Components Not Supplied by ACSS Component Comments Gables G7130 Series ATC/TCAS Dual Transponder Control Panel (Note 1.) General aviation type controller that operates from 28 V dc aircraft power (Note 2.) Gables G6990, G6991, G6992, G6993, and 7490 Series Mode S/TCAS Control Panels (Note 1.) Commercial aviation type controllers that operate from 115 V ac aircraft power (Note 2.) Omnidirectional TCAS Antenna (Note 3.) ATC blade antenna, dc shorted, TSO C119a compliant,1030 to 1090 MHz. Installer to supply antenna. Omnidirectional ATC Antennas (Note 4.) ATC blade antenna, dc shorted, TSO C112 compliant, 1030 to 1090 MHz. Installer to supply antenna. Mounting Tray, TCAS Computer (6−MCU size unit) ARINC 600 6−MCU Mount, cooling air required. Installer to supply mount. Mounting Tray, TCAS Computer (4−MCU size unit) ARINC 600 4−MCU Mount, no cooling air required. Installer to supply mount. Mounting Tray, Data Link Transponder (4−MCU size unit) ARINC 600 4−MCU Mount, cooling air recommended but not required. Installer to supply mount. NOTES: 1. Refer to Table 1−4 for individual part number descriptions. 2. For additional information, pricing and availability contact: Gables Engineering, Inc. 247 Greco Avenue, Coral Gables, Florida 33146 Telephone (305) 774−4400 Fax (305) 774−4465 3. A bottom omnidirectional antenna can be used as an optional replacement for the directional antenna. 4. A diversity transponder installation requires both a top and bottom ATC antenna. Table 1−3. Directional Antenna Configurations Antenna Part Number Description 7514081−901 Directional antenna with flat base, four hole mounting pattern, and 1.560−inch connector extension length 7514081−902 Directional antenna with flat base, eight hole mounting pattern, and 1.560−inch connector extension length 7514081−903 Directional antenna with a curved 61.52−inch radius base, eight hole mounting pattern, and 1.560−inch connector extension length 7514081−904 Directional antenna with a curved 66.52−inch radius base, eight hole mounting pattern, and 1.560−inch connector extension length 34−43−23 Page 1−3 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 1−3. Directional Antenna Configurations (cont) Antenna Part Number Description 7514081−905 Directional antenna with a curved 74.02−inch radius base, eight hole mounting pattern, and 1.560−inch connector extension length 7514081−906 Directional antenna with a curved 77.78−inch radius base, eight hole mounting pattern, and 1.560−inch connector extension length 7514081−907 Directional antenna with a curved 99.02−inch radius base, eight hole mounting pattern, and 1.560−inch connector extension length 7514081−908 Directional antenna with a curved 111.02−inch radius base, four hole mounting pattern, and 1.560−inch connector extension length 7514081−909 Directional antenna with a curved 118.52−inch radius base, eight hole mounting pattern, and 1.560−inch connector extension length 7514081−910 Directional antenna with a flat base, eight hole mounting pattern, and 0.705−inch connector extension length 7514081−911 Directional antenna with a curved 77.78−inch radius base, eight hole mounting pattern, special 0.015−inch Teflon gasket, and 1.560−inch connector extension length 7514081−912 Directional antenna with a curved 111.02−inch radius base, eight hole mounting pattern, special 0.015−inch Teflon gasket, and 1.560−inch connector extension length 7514081−913 Directional antenna with a flat base, four hole mounting pattern, and 0.705−inch connector extension length 7514081−914 Directional antenna with a curved 53.02−inch radius base, eight hole mounting pattern, and 0.705−inch connector extension length 7514081−915 Directional antenna with a curved 44.80−inch radius base, eight hole mounting pattern, and 0.705−inch connector extension length 7514081−916 Directional antenna with a curved 42.00−inch radius base, eight hole mounting pattern, and 0.705−inch connector extension length 7514081−917 Directional antenna with a curved 85.06−inch radius base, eight hole mounting pattern, and 1.560−inch connector extension length 7514060−901 Directional antenna with no adapter plate and 1.560−inch connector extension length. Installer must supply adapter plate to mate with aircraft fuselage. 7514060−902 Directional antenna with no adapter plate and 0.705−inch connector extension length. Installer must supply adapter plate to mate with aircraft fuselage. Page 1−4 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 1−4. Control Panel Configurations Control Panel Part Number Description 4052190−902 Control Panel, Dual Mode S/TCAS, Brown Bezel 4052190−903 Control Panel, Single Mode S−Single ATCRBS/TCAS, Brown Bezel 4052190−904 Control Panel, Dual Mode S/TCAS, Gray Bezel 4052190−905 Control Panel, Single Mode S−Single ATCRBS/TCAS, Gray Bezel 4052190−906 Control Panel, Dual Mode S/TCAS, Black Bezel 4052190−907 Control Panel, Single Mode S−Single ATCRBS/TCAS, Black Bezel 4052190−908 Control Panel, Dual Mode S/TCAS, Dark Gray Bezel 4052190−909 Control Panel, Single Mode S−Single ATCRBS/TCAS, Dark Gray Bezel Gables Control Panels Gables G7130−02 Control Panel, Dual Mode S/TCAS, Rotary knob 4096 code entry, Black Bezel, Operates from +28 V dc aircraft power Gables G7130−05 Control Panel, Dual Mode S/TCAS, Rotary knob 4096 code entry, Gray Bezel, Operates from +28 V dc aircraft power Gables G7130−06 Control Panel, Dual Mode S/TCAS, Rotary knob 4096 code entry, Black Bezel, Extended Range (80, 120 Mi), Operates from +28 V dc aircraft power Gables G7130−07 Control Panel, Dual Mode S/TCAS, Rotary knob 4096 code entry, Gray Bezel, Extended Range (80, 120 Mi), Operates from +28 V dc aircraft power Gables G6990−XX Control Panel, Dual Mode S/TCAS, Pushbutton 4096 code entry, Operates from 115 V ac aircraft power Gables G6991−XX Control Panel, Single Mode S−Single ATCRBS/TCAS, Pushbutton 4096 code entry, Operates from 115 V ac aircraft power Gables G6992−XX Control Panel, Dual Mode S/TCAS, Rotary knob 4096 code entry, Operates from 115 V ac aircraft power Gables G6993−XX Control Panel, Single Mode S−Single ATCRBS/TCAS, Rotary knob 4096 code entry, Operates from 115 V ac aircraft power Gables G7490−XX Control Panel, Dual Mode S/TCAS, Push Button 4096 code entry, Operates from 115 V ac aircraft power 34−43−23 Page 1−5 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 1−5. VSI/TRA Display Configurations VSI/TRA Part Number 4067241−84X −840 −841 −842 −843 −844 −845 4067241−86X −860 −861 −862 −863 −864 −865 4067241−88X −880 −881 −882 −883 −884 −885 4067241−89X −890 −891 −892 −893 −894 −895 Page 1−6 15 Dec 2005 Description The VSI/TRA Display provides continuous TCAS symbology and non−ARINC display control features: 6, 14, 40 mile ranges and above/normal/below display volumes. It has pin programmable altitude band, range, lighting curve, and VSI source selection. Gray bezel, 55−pin connector (contains bootstrap function) Black bezel, 55−pin connector (contains bootstrap function) Brown bezel, 55−pin connector (contains bootstrap function) Gray bezel, 41−pin connector Black bezel, 41−pin connector Brown bezel, 41−pin connector This VSI/TRA Display provides a single range default (6.0 miles), continuous or “POP−UP” TCAS symbology, and a test mode display. ARINC display control features include: 6, 12, 14, 20, and 40 mile ranges and above/normal/below display volumes. It has pin programmable VSI source selection, lighting curve, format mode, and traffic filter. Gray bezel, 41−pin connector Black bezel, 41−pin connector Brown bezel, 41−pin connector Gray bezel, 55−pin connector (contains bootstrap function) Black bezel, 55−pin connector (contains bootstrap function) Brown bezel, 55−pin connector (contains bootstrap function) This VSI/TRA Display provides a single range default (6.0 miles), continuous or “POP−UP” TCAS symbology, and a test mode display. ARINC display control features include: 6, 12, 14, 20, and 40 mile ranges and above/normal/below display volumes. It has pin programmable VSI source selection, lighting curve, format mode, traffic filter, and a 1.6, 3.2, 5.0, or 6.4 second time constants. Gray bezel, 41−pin connector Black bezel, 41−pin connector Brown bezel, 41−pin connector Gray bezel, 55−pin connector (contains bootstrap function) Black bezel, 55−pin connector (contains bootstrap function) Brown bezel, 55−pin connector (contains bootstrap function) This VSI/TRA Display provides a single range default (6.0 miles), continuous or “POP−UP” TCAS symbology, and a test mode display. ARINC display control features include: 6, 12, 14, 20, and 40 mile ranges and above/normal/below display volumes. It has pin programmable VSI display (English/Metric) VSI source selection, format mode, traffic filter, and a 1.6, 3.2, 5.0, or 6.4 second time constants. Gray bezel, 41−pin connector Black bezel, 41−pin connector Brown bezel, 41−pin connector Gray bezel, 55−pin connector (contains bootstrap function) Black bezel, 55−pin connector (contains bootstrap function) Brown bezel, 55−pin connector (contains bootstrap function) 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System 3. System Description The TCAS 3000 is an onboard advisory system designed to act as a backup to the air traffic control (ATC) radar and the “see and avoid” procedures. By computing the closure rate and altitude of all transponder equipped aircraft in the surrounding airspace, the TCAS can anticipate a potential midair collision before it has a chance to materialize. TCAS 3000 continually plots local air traffic on the associated display, and in the event of a conflicting flightpath, guides the pilot towards the correct avoidance maneuver. If the intruding aircraft is also equipped with a TCAS II compatible system, the two systems can communicate their mutual intentions through the Mode S transponders. The coordinated advisories that result allow the two pilots to execute complementary avoidance maneuvers. TCAS 3000 complies with ARINC Characteristic 735A and TSO−C119−b. A. System Functional Description Vertical guidance to avoid midair collisions is accomplished by interrogating the Mode A, Mode C, and Mode S transponders of potential threat aircraft, tracking their responses, and providing advisories to the flight crew to assure vertical separation. Two levels of advisories are provided: • Traffic advisories (TA), indicate the range, bearing, and relative altitude of the intruder to aid in visual acquisition of the intruder • Resolution advisories (RA) indicate a vertical maneuver to be performed or avoided in order to assure safe separation. Traffic advisories can be displayed on ACSS Vertical Speed Indicator/Traffic and Resolution Advisory (VSI/TRA) display, Electronic Flight Instrument System (EFIS) or any instrument that displays the appropriate symbology and conforms to the definition of ARINC Characteristic 735. Resolution advisories can be displayed on the ACSS VSI/TRA display, EFIS or any other indicator that displays the appropriate symbology and conforms to the definition of ARINC Characteristic 735. Figure 1−1 shows the various types of intruder equipment and the resulting advisories. It should be noted that Mode A equipped intruders result in detection and display of TAs only. An intruder not equipped with a transponder is invisible to TCAS. Communication with another TCAS equipped aircraft is provided by an onboard diversity Mode S transponder. Only one onboard Mode S transponder is required for TCAS operation. However, the ACSS TCAS 3000 operates with either of two onboard Mode S transponders, one of which operates as a spare. The transponder in use is selectable from the cockpit. Figure 1−2 shows the communication between two TCAS equipped aircraft. 34−43−23 Page 1−7 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System COORDINATION AND RAs TCAS II RAs MODE−S/TCAS I TCAS II RAs SL COMMAND ATCRBS (MODE−C) RA BROADCAST MESSAGE TAs ATCRBS (MODE−A) RA MESSAGE ATC MODE−S RADAR MODE− S RECEIVER AD−51674−R1@ Figure 1−1. TCAS ll Advisory Capabilities Page 1−8 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System TCAS CU TCAS CU MODE S XPDR MODE S XPDR GROUND STATION AD−53001@ Figure 1−2. TCAS/Mode S Communication The TCAS 3000 generates both RAs and TAs when the TA/RA mode is selected. The two types of advisories correspond to time−based protection zones around the aircraft. The airspace around the TCAS aircraft where an RA is annunciated represents the warning area, while the larger airspace which results in a TA being annunciated is the caution area. Figure 1−3 contrasts the airspace covered by the two types of advisories. The onboard equipment listed below must be linked to the TCAS 3000 as shown in Figure 1−4. • Mode S transponder with associated antennas • Radio altimeter • Air Data Computer (ADC) (digital or analog). If an ADC does not support vertical speed rate data, an optional PTM must be used if the display is a ACSS VSI/TRA. • ATC/TCAS control panel. A separate control panel is not the only method of control for the TCAS. Other components, such as a Honeywell Radio Management Unit (RMU) as part of a Primus II Integrated Radio System, can be used. • Omnidirectional antenna. The TCAS 3000 accepts two types of bottom antennas: A standard directional antenna or an optional ATC−type omnidirectional antenna. If an omnidirectional antenna is installed, it must be supplied by the installer. If a directional antenna is installed at both top and bottom antenna locations, a bottom omnidirectional antenna is not needed. 34−43−23 Page 1−9 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Figure 1−3. TA/RA Airspace Coverage Page 1−10 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System TCAS 3000 UNITS AIRCRAFT INTERFACE UNITS NOTE: DASHED BOXES / LINES DENOTE OPTIONAL ALTERNATE COMPONENTS. THE PTM IS AN ALTERNATE FOR THE ADC AND THE EFIS IS AN ALTERNATE FOR THE VSI/TRA. AD−31666−R2@ Figure 1−4. Basic TCAS ll Installation B. System Configurations The TCAS 3000 may be installed in several different configurations depending on the transponders used and the choice of antennas and displays. Some typical configurations are shown in Figure 1−5. Other combinations are feasible. Figure 1−6 shows the signals and overall interconnects for a typical TCAS 3000 installation with dual transponders. • Configuration A shows the TCAS linked to dual Mode S transponders. The system operates with either transponder, depending on the control panel selection. The second transponder is used as a backup. • Configuration B shows the TCAS linked to a single transponder Mode S transponder system. • Configuration C shows the TCAS linked to a single Mode S transponder (active) and an ATCRBS transponder (backup). The TCAS only operates when the Mode S transponder is selected. 34−43−23 Page 1−11 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Figure 1−5 (Sheet 1). Typical System Configurations Page 1−12 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Configuration C Figure 1−5 (Sheet 2). Typical System Configurations 34−43−23 Page 1−13 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Blank Page Page 1−14 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System TO/FROM AIRCRAFT FUNCTIONS (OTHER THAN TCAS) TOP ANTENNA BP 2 INPUT POWER TP BP MODE S/ATCRBS TCAS 2000 TRANSPONDER SYSTEM SYSTEM COAX 5 VAC PNL LTG 115V, 400 HZ INPUT PWR TP MODE S TP TRANSPONDER MP,TP TOP DIRECTIONAL ANTENNA DISCRETE 2 DISCRETE 3 MP,TP 429 BUS TP MP TCAS/MODE S CONTROL PANEL RP LP 1 DISCRETE COAX 429 BUS 2 LP LTP 23 DISCRETE 2 INPUT POWER XT 429 BUS 1 TX 429 BUS 1 429 BUS 2 DISCRETE 1 ATCRBS TRANSPONDER (OPTIONAL BACKUP) TCAS CU XT 429 BUS 2 TX 429 BUS 2 3 DISCRETE RMP RMP 2 429 BUS 2 DISCRETE COAX 2 INPUT POWER 12 RBP 32 MUTUAL SUPPRESSION BUS COAX BOTTOM ANTENNA TO AIRCRAFT MUTUAL SUPPRESSION BUS 429 BUS OR ANALOG DISCRETE 3 429 BUS OR ANALOG DISCRETE 3 2 429 BUS RADIO RADIO ALTIMETER ALTIMETER NO. 2 NO. 1 OPTIONAL TCAS 3000 System Block Diagram 34−43−23 Page 1−15/(1−16 blank) 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. DISCRETE 429 BUS TO MISC AIRCRAFT FUNCTIONS RA DISPLAY LBP LMP INPUT PWR (115V, 400 HZ OR 28V DC) COAX RA/TA DISPLAY AUDIO/VISUAL ANNUNCIATOR LMP CONFIGURATION STRAPS LBP BOTTOM DIRECTIONAL ANTENNA Figure 1−6. RA DISPLAY TA DISPLAY 1 DISCRETE BACKUP MODE S TRANSPONDER RA/TA DISPLAY 1 COAX BOTTOM OMNI ANTENNA (OPTIONAL) AD−53000@ SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System 4. Component Descriptions A. TCAS 3000 Computer Unit The TCAS Computer Unit (CU) is the heart of the TCAS 3000 system. It contains the RF transmitter and the receivers necessary to interrogate and receive replies from other transponder equipped aircraft. Dual microprocessors are utilized to implement the surveillance and collision avoidance algorithms. The algorithms determine whether an intruder aircraft should be considered a threat and then determine the appropriate vertical response to avoid a midair or near midair collision. In addition, output data is provided to drive displays that inform the flight crew what action to take or avoid. An interface is provided with an onboard Mode S transponder in order to communicate with other TCAS ll equipped aircraft. The ACSS TCAS Computer Unit also provides past and present LRU and system status through the front panel mounted TEST switch and PASS/FAIL annunciators. Software updates can be incorporated into the computer by an ARINC 615 data loader port through either the connector mounted on the front panel of the computer or the port provided on the LRU rear connector or with a compact flash card inserted into the slot on the front of the LRU. Figure 1−7 shows a graphical view of the 6MCU TCAS Computer Unit and Figure 1−8 shows a graphical view of the 4MCU TCAS Computer Unit. Table 1−6 provides items and specifications that are particular to the computer. Figure 1−7. 6MCU TCAS Computer Unit 34−43−23 Page 1−17 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Figure 1−8. 4MCU TCAS Computer Unit Page 1−18 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 1−6. TCAS 3000 Computer Unit Leading Particulars Item Specification Dimensions (maximum): • Height . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.64 in. (194.1 mm) • Width (4MCU) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.90 in. (124.5 mm) • Width (6MCU) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.52 in. (191.0 mm) • Length (4MCU) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15.26 in. (387.6 mm) • Length (6MCU) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15.76 in. (400.3 mm) Weight (maximum): • 4MCU DC only version . . . . . . . . . . . . . . . . . . . . . . . . . 14.0 lb (6.37 kg) • 4MCU DC/AC version . . . . . . . . . . . . . . . . . . . . . . . . . . 14.7 lb (6.66 kg) 17.6 lb (8.00 kg) • 6MCU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Operating Voltage: • dc Voltage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . +20.5 V dc minimum, +27.5 V dc nominal, +32.2 V dc maximum • ac Voltage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 97 V rms minimum, 115 V rms nominal, 134 V rms maximum at 400 80 Hz Power Consumption . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 70 Watts standby, 100 Watts maximum Circuit Breaker Ratings: • 115 V ac Circuit Breaker . . . . . . . . . . . . . . . . . . . . . . . 5 Amp Typical • 28 V dc Circuit Breaker . . . . . . . . . . . . . . . . . . . . . . . . 10 Amp Typical Mating Connector: • P1 (Rear Connector) . . . . . . . . . . . . . . . . . . . . . . . . . . . Radial Part No. 620−800−066 • J1 (Front Connector) . . . . . . . . . . . . . . . . . . . . . . . . . . ACSS Part No. 4004295−160, ITT Part No. KJ6F18A53P Mounting: • 6MCU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ARINC 600 6−MCU Tray Assembly • 4MCU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ARINC 600 4−MCU Tray Assembly TSO: • All units . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . C119b ETSO . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . C119b Software Development Specification . . . . . . . . . . . . . . . DO−178B, Level B Environmental Specifications . . . . . . . . . . . . . . . . . . . . . . DO−160D Environmental Category [A2F2]YBB [CLMY][E1]XXXXXZ [EBZ]A[EZ]ZRZA3EXX 34−43−23 Page 1−19 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 1−6. TCAS 3000 Computer Unit Leading Particulars (cont) Item Specification • Temperature / Altitude [A2F2]: − Operating Temperature . . . . . . . . . . . . . . . . . . . . . . −55 to +70 degrees C − Ground Survival Temperature . . . . . . . . . . . . . . . . −55 to +85 degrees C − Altitude . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Sea Level to 55,000 feet − Loss of Cooling . . . . . . . . . . . . . . . . . . . . . . . . . . . . . +40 degrees C for 300 minutes minimum RF Transmitter Characteristics: • Transmitter Frequency . . . . . . . . . . . . . . . . . . . . . . . . . 1030 ± 0.01 MHz • RF Peak Output Power: − Minimum . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 53.3 dBm (210 Watts) − Nominal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 55.3 dBm (335 Watts) − Maximum . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 57.3 dBm (540 Watts) • Unwanted Output Power in an Inactive State . . . . . . −72 dBm • Pulse Timing Characteristics: − Pulse Rise Time . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0.05 to 0.10 microseconds − Pulse Fall Time . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0.05 to 0.20 microseconds − ATCRBS S1, P1, P3, P4 Duration . . . . . . . . . . . . 0.08 ± 0.05 microseconds − Mode S P1, P2 Duration . . . . . . . . . . . . . . . . . . . . . 0.08 ± 0.05 microseconds − Mode S P6 Duration . . . . . . . . . . . . . . . . . . . . . . . . 16.25 ± 0.125 microseconds (short) 30.25 ± 0.125 microseconds (long) • Whisper−Shout Characteristics: − Range . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0 to 26 dB attenuation by 1 dB steps − Absolute Tolerance . . . . . . . . . . . . . . . . . . . . . . . . . . Relative to the 0 dB step, the attenuation of each step does not exceed the nominal attenuation by more than ±2 dB − Relative Tolerance . . . . . . . . . . . . . . . . . . . . . . . . . . Step increments are ±0.5 dB and monotonic RF Receiver Characteristics: • Receiver Frequency Range . . . . . . . . . . . . . . . . . . . . . 1087 to 1093 MHz • Receiver MTL Over Frequency . . . . . . . . . . . . . . . . . . (Normal Operation) −77 ± 2 dBm (≥90% Mode S and ATCRBS replies decoded) • Receiver Dynamic Range . . . . . . . . . . . . . . . . . . . . . . (Normal Operation) −77 to −23 dBm (≥99% Mode S and ATCRBS replies for signal levels greater than MTL +3 dB) Page 1−20 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 1−6. TCAS 3000 Computer Unit Leading Particulars (cont) Item Specification • Extended Range Reception Capability . . . . . . . . . . . (Optional Mode) −82 ± 2 dBm (≥90% Mode S squitter replies decoded) • Low Level Receiver Signal Rejection . . . . . . . . . . . . . (Normal Operation) −81 dBm (≤10% Mode S and ATCRBS replies decoded) • Receiver Signal Processing . . . . . . . . . . . . . . . . . . . . . Amplitude Mono−pulse • System Bearing Accuracy . . . . . . . . . . . . . . . . . . . . . . Error less than 9 degrees RMS, 27 degrees peak from −10 to +10 degrees elevation (1) System Interfaces The TCAS 3000 Computer Unit supports the external system interfaces that follow. Unless otherwise specified, the specifications apply to both the 6−MCU and 4−MCU computers. All interfaces are per ARINC 735A. (a) Radio Altimeter Interface The TCAS 3000 Computer Unit accepts either analog or digital radio altimeter inputs. For each type of input, dual input ports are provided. Each of the military radio altimeter types provide two outputs that are connected to the TCAS CU input pins. The two altimeter outputs are the Analog Data Output and Analog Data Reliability signal. The TCAS CU uses the Data Reliability signal in conjunction with the Analog Data Output to determine radio altimeter failures. A condition exists for several military radio altimeters known as Out of Track. This condition occurs when the radio altimeter has not failed and the altimeter is not reading a valid altitude. Altitude data for an Out of Track condition should be considered invalid and not used. The digital radio altimeter interface accepts inputs from an ARINC 707 radio altimeter on ARINC 429 low speed input busses. (b) Mode S Transponder Interface The TCAS 3000 computer contains two sets of ARINC 429 high speed busses for communication with two Mode S transponders. It uses ARINC 718−A/735 communication protocol (2 inputs, 2 outputs). (c) Onboard Maintenance System Interface The TCAS 3000 computer contains a set of ARINC 429 low speed busses for communication with an onboard maintenance system (1 input, 1 output). The unit interfaces with all major airframe manufacturers maintenance computer systems. Since the maintenance computer protocol for each airframe manufacturer is different, the TCAS 3000 automatically detects the type of airframe from the data received from the maintenance computer and sets its protocol accordingly. 34−43−23 Page 1−21 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System (d) Data Loader Interface The TCAS 3000 computer contains a set of ARINC 429 busses and discrete inputs that interface to either an airborne data loader (ADL) through pins on the rear connector, or a portable data loader (PDL) through the 53−pin circular connector on the front panel of the unit. The computer works with ARINC 615 data loader protocol (high speed bus). The unit software part number can be output on the data loader port by grounding a discrete input. (e) RS−232 / Compact Flash Card Data Recorder Interface The Data Recorder Interface can be utilized for either internal or external data recording. The TAWS/RWS event log contains event information due to TAWS or windshear cautions or warnings (internal data recording). The log can hold approximately three events that last up to 45 seconds each (assuming GCAM Event, GCAM parameter data, and GFM parameter data selected for recording). The event log data may be downloaded to a Laptop PC over the RS−232 port, or downloaded to a Compact Flash card using the slot on the front of the unit. The external data recording provides the capability to perform real−time recording of various T2CAS input, output, and internal data. This data may be recorded using the Compact Flash card or RS−232 interface. In addition, the RS−232 interface allows for LRU maintenance and troubleshooting. The maintenance log and RA event log can also be downloaded to a PC using this port. The RS−232 interface is connected to the 53−pin PDL connector on the front of the unit. (f) TCAS Display Bus interface The TCAS 3000 computer has four sets of ARINC output busses for display of traffic and resolution advisories. The TA/RA Display No. 1 and No. 2 busses are high speed ARINC 429 busses that contain both traffic information and resolution advisory information. The busses function according to either the ARINC 735 characteristics, or can optionally be set for the Honeywell EFIS characteristics through a program input pin (RMP−12C). For each bus, a valid discrete input is provided that indicates whether the display is functional. The RA Display No. 1 and No. 2 busses are low speed ARINC 429 busses that contain only resolution advisory information. The busses function according to the ARINC 735 characteristics. For each bus, a valid discrete is provided that indicates whether the display is functional. The RA Display No. 1 and No. 2 busses can be configured for a 429 Data Recorder function by grounding programming pin (RMP−11D). In this mode, the busses are configured for high speed operation. Page 1−22 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System (g) Performance Management Bus Interface The TCAS 3000 computer contains a low speed ARINC 429 bus input (RMP−6A,6B) that is reserved for connection to a performance management system. The input is provisioned to obtain maximum rate of climb information from a FMS or Performance Management System (PMS.) The input is provided for future system enhancements and is currently not used. (h) Magnetic Heading/Attitude Bus Interface The TCAS 3000 computer contains a high speed ARINC 429 bus input (RMP−7A, 7B) that is reserved for connection to an Inertial Reference System (IRS). The input lets aircraft heading and attitude data be input for the purpose of providing for future horizontal maneuvers. This function has not been implemented on TCAS II installations, so these pins are reserved for future use. (i) Compact Flash Flight Data Recorder Interface The TCAS 3000 computer contains a Compact Flash card interface that provides flight data recording capability. (j) ARINC 573 Flight Data Recorder Interface The TCAS 3000 computer contains 12 discrete outputs that can be connected to an ARINC 573 flight data recorder. The outputs are used to record information during a resolution advisory event. (k) ARINC 429 Flight Data Recorder Interface The TCAS 3000 computer contains an interface for an ARINC 429 flight data recorder. The flight data recorder function is activated by grounding a discrete input pin (RMP−11D) on the rear connector. With the discrete input grounded, flight data is output as high speed ARINC 429 data on the RA Display No. 1 and No. 2 busses. With the discrete grounded, the normal RA Display bus operation is not available. (l) Voice Audio Outputs The TCAS 3000 computer contains two analog audio outputs that provide TCAS aural traffic advisories and resolution advisories. The 8−Ohm output has the capability to supply up to 4 Watts RMS into a speaker. The 600−Ohm output has the capability to supply up to 80 milliwatts RMS into an audio distribution system. (m) RS−232 Interface The TCAS 3000 computer has an RS−232 input/output for connection to a personal computer. The interface allows for LRU maintenance and troubleshooting. The maintenance log and RA event log can also be downloaded to a PC using this port. The RS−232 interface is connected to the 53−pin PDL connector on the front of the unit. 34−43−23 Page 1−23 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System (n) Altitude Alerter Interface The TCAS 3000 computer contains an ARINC 429 low speed input bus that is reserved for receiving selected altitude information from an altitude control source or flight control computer. The TCAS computer uses the selected altitude information to inhibit the weakening of a resolution advisory by determining the selected altitude limits for the aircraft. (o) Reserved ARINC 429 Bus Interface The TCAS 3000 computer has four sets of reserved ARINC 429 input busses that can be configured as either high speed or low speed. These busses allow for future upgrades to the TCAS 3000 system without hardware modification. (2) Discrete Inputs The TCAS 3000 has various discrete inputs available for implementing various TCAS functions. The input logic status is defined according to ARINC 735 definition. (3) Program Inputs The TCAS 3000 has various program inputs available for unit configuration and installation programming. Input logic status is defined according to ARINC 735 definition. (4) Discrete Outputs The TCAS 3000 has a number of discrete outputs that are used for unit status annunciation and data output functions. The output logic status is defined according to ARINC 735 definition. (5) Self−Test Function By momentarily pushing the TEST switch on the front panel of the TCAS Computer Unit, maintenance personnel can display fault data for the current and preceding flight legs. When TEST is initially activated, all annunciators (pass/fail lamps on front of unit) are ON for a 3−second lamp test, then current fault data is displayed for 10 seconds. If no further activations of the TEST switch are made, the LRU display cycle is terminated at the end of the 10−second fault display period, and all annunciators are extinguished. If during the 10−second fault display period, the TEST button is activated again, the fault display period is aborted, a 2−second lamp test cycle is done, and the fault data recorded for the preceding flight leg is displayed for 10 seconds. This procedure can be repeated up to 10 times to obtain recorded data from the previous 10 flight legs. If the TEST button is not activated again during the fault display period, the fault display cycle is terminated at the end of the 10−second fault display period and all annunciators are extinguished. If an attempt is made to display fault data for the preceding flight leg when the tenth preceding flight leg fault data is displayed, all annunciators flash for a 3−second period at a 2.5−Hz rate, after which all annunciators are extinguished. Page 1−24 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System When less than 10 flight legs have been flown since the TCAS Computer Unit was shop tested and recertified, less than 10 previous flight legs of recorded fault data may be available for display. In this case, if an attempt is made to display fault data for the preceding flight leg when the earliest flight leg is displayed, all annunciators flash for 3 seconds at a 2.5−Hz rate and then all annunciators are extinguished. The TCAS PASS and TCAS FAIL annunciators indicate the status of the TCAS Computer Unit only. All other annunciators reflect the condition of the respective sub−system. During troubleshooting, the TCAS Computer should not be removed if the TCAS PASS lamp is on. B. Directional Antenna The TCAS directional antenna, Figure 1−9, is a four−element, vertically polarized, monopole array capable of transmitting in four selectable directions at 1030 MHz. The antenna is capable of receiving replies from all directions simultaneously with bearing information at 1090 MHz, using amplitude−ratio monopulse techniques. The antenna consists of a molded radome with radiating/receiving elements and is completely filled with a rigid foam. The antenna assembly uses five or nine screws to attach the radome and either four or eight screws to attach the antenna to the aircraft fuselage. The ACSS directional antenna has a small frontal area. The circular radome has a 3:1 elliptical leading edge and an extremely low profile height of only 0.806 inch. This yields excellent aerodynamic performance with a minimum possibility of icing, which could be a hazard for rear mounted engines. For TCAS 3000 system installations, the top antenna must be a directional antenna. The bottom antenna can be either a directional or omnidirectional antenna. The TCAS Computer Unit has the capability of automatically sensing which version is installed. The directional antenna mounting screws (not included with the directional antenna) are standard #10−32 UNF−2A pan head, corrosion−resistant (stainless) steel screws in accordance with Military Specification MS51958. The appropriate length is determined by the installer allowing 0.5−inch for the thickness of the antenna and adapter plate. A washer must be installed under the head of each mounting screw. The washer must be made of passivated, corrosion−resistant steel in accordance with MIL−S−5059 or MIL−S−6721. The Air Force−Navy Aeronautical Standard part number is AN960C10L. The washer has an outer diameter of 0.438 inch, an inner diameter of 0.203 inch, and a thickness of 0.032 inch. 34−43−23 Page 1−25 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System An O−ring (included with the directional antenna) is required to be installed between the directional antenna and the aircraft fuselage. The Navy Aeronautical Standard part number for the O−ring is NAS 1611−240. The ACSS part number for the O−ring is 4000171−240. NOTE: For directional antennas, ACSS Part No. 7514060−90X, the customer must provide an adapter plate for mounting to the aircraft. For details of the antenna base plate, to which the adapter must mate, refer to Section 2. Directional antennas, ACSS Part No. 7514081−9XX, come with a preinstalled adapter plate. The average unit weight of an antenna with adapter plate is approximately 3.0 pounds. Page 1−26 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Figure 1−9. Directional Antenna 34−43−23 Page 1−27 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System C. ACSS Mode S/TCAS Control Panels The ACSS control panels for the transponder and TCAS systems provide mode control for dual or single ATC Mode S Transponders and TCAS ll systems. Figure 1−10 shows a typical front panel layout of the two configurations. It is usually mounted in the aircraft instrument panel or the pedestal. Table 1−7 gives items and specifications particular to the unit. Figure 1−10. ACSS Control Panels Page 1−28 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 1−7. ACSS Control Panel Leading Particulars Item Specification Dimensions (maximum): • Height . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.25 in. (57.2 mm) • Width . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.75 in. (146.1 mm) • Length . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.00 in. (127.0 mm) Weight (maximum) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.1 lb (0.953 kg) Power Requirements: • Primary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 115 V, 400 Hz (2.0 Watts maximum) • Lighting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 V, 400 Hz (3.0 Watts maximum) Mating Connectors: • J1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . M83723/75R1624S7 • J2 (Dual Mode S Version) . . . . . . . . . . . . . . . . . . . . . . M83723/75R1624S8 • J2 (ATCRBS/Mode S Version) . . . . . . . . . . . . . . . . . . MS3476L2041S Mounting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Unit Dzus Fasteners (1) Functional Description and Operation Communication with Mode S transponders is accomplished through an ARINC 429 bus as defined in ARINC Characteristic 718−A. Control panel functions include 4096 ident code selection and display, altitude source and reporting inhibit selection, selection between two onboard transponders, TCAS TA or TA/RA advisory selection, and selection of TCAS test. A listing of the control panel switch functions is as follows: (a) ALT RPGT Switch − 1, OFF, 2 Used to select between altitude sources 1 and 2, or to disable altitude reporting in transponder replies. (b) XPDR FAIL − Annunciator The illumination of the annunciator is an indication of a performance monitor failure detection. (c) Mode Control − Rotary Switch Disables reply capability in STANDBY mode. Enables MODE S transponder in ON mode. Enables ATCRBS transponder in ATC mode. The TA mode enables the TCAS computer, in conjunction with the Mode S transponder, to provide traffic advisories. The TA/RA mode enables the TCAS computer, in conjunction with the Mode S transponder, to provide traffic and resolution advisories. The TA and TA/RA modes are electrically tied to the ON mode and enable the Mode S transponder when selected. 34−43−23 Page 1−29 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System (d) XPDR − Selector Switch (Dual Mode S Versions Only) Selects the transponder, 1 or 2, that is used for reporting replies. (e) TA DSPLY − OFF, AUTO, ON Controls the operation of the navigation or traffic advisory display for a TCAS system. (f) TCAS TEST − Button Used to select the TCAS system self−test function. (g) IDENT − Button When pushed, this button causes an ATCRBS reply, or Mode S UF−4 and UF−5 replies, to contain a special identifier pulse (SPI) as an identifier to the ground according to ARINC 718−A Draft 5 of Supplement 4. (h) 4096 Ident Code − Dual Concentric Rotary Knobs Each rotary switch is used to set each individual digit of the four−digit ident code. The left inner knob selects the thousands digit, left outer knob selects the hundreds digit, right inner knob selects the tens digit, and the right outer knob selects the ones digit. D. Gables ATC/TCAS Dual Mode S Transponder Control Panel The Gables ATC/TCAS Mode S control panel is used to independently control two Mode S transponders, and to interface with a Mode S installation with TCAS capabilities. The control panel contains two isolated electronic modules each dedicated to a given transponder. Each module derives its input ATC code data from two dual concentric knobs. The selected code is then displayed on a four digit Liquid Crystal Display (LCD), and subsequently transmitted to each transponder. ID−53838−R2 Figure 1−11 shows a typical front panel layout of a Gables G7130 series control panel. Table 1−8 gives items and specifications that are particular to these units. Page 1−30 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Figure 1−11. Typical Gables ATC/TCAS Control Panel Table 1−8. Gables G7130/G7490 Series Control Panel Leading Particulars Item Specification Dimensions (maximum): • Height . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.25 in. (57.2 mm) • Width . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.75 in. (146.1 mm) • Length . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.80 in. (147.3 mm) Weight (maximum) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.0 lb (0.907 kg) Power Requirements: • Primary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . +28 V dc, 0.25 Amps maximum current • Display and Overlay Lighting . . . . . . . . . . . . . . . . . . . 5 V, 400 Hz, 2.3 Amps maximum Display Type . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Four Digit, Dichroic LCD Code Select Range . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0000 to 7777 (octal) Transmitted ARINC 429 Labels . . . . . . . . . . . . . . . . . . . 013, 015, 016, 031 (octal) TSO . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . C112/C119 Environmental Specifications . . . . . . . . . . . . . . . . . . . . . /A2D1/BB/MB·/XXXXXXZZAZZRZ/xxZZ Mating Connectors: • J1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . M83723/75R16247 or MS24266R16B24S7 • J2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . M83723/75R16248 or MS24266R16B24S8 Mounting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Four Unit Dzus Fasteners 34−43−23 Page 1−31 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System (1) Functional Description and Operation Communication with Mode S transponders is accomplished through an ARINC 429 bus as defined in ARINC Characteristic 718−A. Control panel functions include 4096 ident code selection and display, altitude source and reporting inhibit selection, selection between two onboard transponders, TCAS TA or TA/RA advisory selection, range selection (in nautical miles) and a system functional test selection. A description of the front panel annunciator and switch functions follows: (a) Transponder Code Display The control panel has a single LCD display that is common to both modules within the unit. The display shows the ATC code selected by the user and consequently transmitted to the transponders. Input to the display is controlled by the system select switch (XPNDR 1−2). In addition, certain fault indications are also indicated on the display. After a functional test has been initiated, PASS shows on the display after a successful test, or it shows FAIL if a high level failure is detected under normal operating conditions. It also shows which transponder is active by displaying ATC 1 or 2. (b) ATC Code Selection The ATC four digit code is selected with two dual concentric sets of knobs. Each knob is dedicated to a single liquid crystal display (LCD) digit on the LCD code display. The two smaller knobs control the inner digits of the LCD (tens and hundreds) while the two larger knobs control the outer most digits (units and thousands). (c) XPNDR 1−2 Switch The XPNDR switch is a two position switch that allows the selection of one Mode−S module in the control panel, and the activation of its associated transponder (System 1 or System 2). (d) Mode Control Selector Switch The rotary switch labeled STBY−ALT RPTG OFF−XPNDR−TA ONLY−TA/RA allows the operator to activate the TCAS system by selecting TA, or traffic and resolution advisory (TA/RA). When STBY is selected, both transponders are selected inactive or in standby mode. Altitude reporting off (ALT RPTG OFF) selection disables the altitude data sources interrupting transmission of aircraft altitude and location information to ground controllers. (e) ABV/N/BLW Switch The ABV/N/BLW switch selects an altitude range (from aircraft) for traffic display on the TCAS displays. Range limits are 9900 feet above and 2700 feet below the aircraft when in ABV mode and 2700 feet above and 9900 below the aircraft when in BLW mode. When the normal (N) position is selected, the display range is 2700 feet above and below the aircraft. Page 1−32 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System (f) Traffic Display Switch The TRAFFIC AUTO−MAN switch is a two position rotary switch that controls the TCAS traffic display mode of operation. When the AUTO mode is selected, the TCAS computer sets the TCAS displays to pop−up mode under a traffic/resolution advisory condition. If the MAN mode is selected, then the TCAS displays will be constantly activated advising of any near by traffic detected within the horizontal and vertical range limits. (g) Range Switch The RANGE switch is a four or six position rotary switch used to select among different nautical mile (NM) traffic advisory horizontal range displays. (h) IDENT Key The IDENT key is a momentary button. When pushed, the IDENT key causes an ATCRBS reply or Mode S UF−4 and UF−5 replies to contain a special pulse identifier pulse (SPI) as an identifier to be transmitted to ground controllers in accordance with ARINC 718−A Draft 5 of Supplement 4. (i) Flight Level Button The FL button is a momentary button used to select between relative and absolute altitude information. When absolute is selected, this mode is enabled for approximately 20 seconds and then reverts back to relative. (j) Test Button The TEST button enables the user to initiate a system functional test. When the TEST button is pushed, the control panel initiates an internal test while a functional test output is also transmitted through ARINC 429 labels. When installed with a TCAS system, an extended test can be initiated by continuously pushing the TEST button for at least eight seconds. (k) XPNDR FAIL Annunciator The XPNDR FAIL annunciator displays the functional status of the active transponder. The fail annunciator lights only when a failed transponder is selected on the XPNDR 1−2 switch. (l) FID Switch The Keypad is used to create or enter the Flight ID for output by the transponder. The display will show the Flight ID code that has been entered by the crew. The FID light will illuminate when in this mode. When FID mode is selected, all keys are active. The active keys are used to create the Aircraft Flight ID code for transmission to ATC. 34−43−23 Page 1−33 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System For 0 thru 9, press the appropriate digit to enter a new code. When the first digit of a new code is pressed, the digit display field is cleared, the display shows that digit in the left−most digit field with the other digits blanked and the FID indicator will flash. CLR can be pressed while in the process of entering digits to clear the digit field and allow entry of a new code. Pressing CLR again will result in the display of the previously active code. Upon completing entry of the FID cod, pressing ENT results in transmission of the new FID in about five (5) seconds. If the ATC mode is selected before pressing ENT, the partial entry is retained in memory and the FID indicator continues to flash. Upon returning to the FID mode, the new FID code entry process can be completed. The FID indicator will stop lashing when ENT is pressed. For letters A−Z, repeatedly press the appropriate key until the desired letter appears in the display. The first press of any key will cause the digit to appear in the display. The second press of the same key within 2 seconds will cause the digit to change to the first letter on that key. The third press of the same key within 2 seconds will cause the letter to change to the second letter on that key. The next press within 2 seconds will cause the letter to change to the third letter on the key pad (if applicable). The next press within 2 seconds will cause the letter to change back to the digit on the key. Waiting 2 seconds between key presses, or pressing another key at any time, will advance the cursor to the next character space or will cause the digit of the key pressed to appear in the next location on the display. Flight ID can be between 1 and 8 characters in length. E. VSI/TRA Display The VSI/TRA display, Figure 1−12, is used to display current vertical speed and TCAS traffic/warning information. The display consists of a full color, active matrix, liquid crystal display panel. The display quality compares favorably to CRT displays but requires less power, weight, and volume than a CRT with a similar display area. Table 1−9 gives items and specifications particular to the unit. Figure 1−13 contains an interface block diagram of the 41−pin version VSI/TRA and Figure 1−14 contains an interface block diagram of the 55−pin (bootstrap) version of the VSI/TRA. Page 1−34 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Figure 1−12. Typical VSI/TRA Display Formats 34−43−23 Page 1−35 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 1−9. VSI/TRA Leading Particulars Item Specification Dimensions (maximum): • Height . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.26 in. (82.8 mm) • Width . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.26 in. (82.8 mm) • Length . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9.42 in. (239.3 mm) Weight (maximum) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.0 lb (1.81 kg) Power Requirements: • Primary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 115 V, 400 Hz; 18 Watts nominal, 31 Watts maximum • External Circuit Breaker Rating . . . . . . . . . . . . . . . . . . 1 Amp at 115 V ac Display Type . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Liquid Crystal Mating Connectors: • J1 (41 Pin Version) . . . . . . . . . . . . . . . . . . . . . . . . . . . . M83723/75R−20−41N • J1 (55 Pin Version) . . . . . . . . . . . . . . . . . . . . . . . . . . . . M83723/75R−22−55N Mounting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3−ATI Clamp, Marmon NH1004994−30 or MSP 64311B Environmental Specifications (DO−160B) . . . . . . . . . . . (A2F1)AKXXXXXXAEAEZZZK (1) Functional Description and Operation The VSI/TRA has three functions. It continuously displays rate of climb or rate of descent. Traffic information is displayed and resolution advisory information is displayed against vertical speed to allow the flight crew to avoid threats. The vertical speed display is generated from signals applied directly to the indicator. The VSI/TRA is designed to be used in place of a conventional vertical speed indicator. Four possible sources exist for vertical speed data including ARINC 429 data, DC analog signals in accordance with ARINC 575 (approximately 500 mV per 1000 ft/min), ac analog signals in accordance with ARINC 565 (approximately 250 mV per 1000 ft/min), and ARINC 429 signals from the ACSS Pressure Transducer Module. The VSI/TRA computes vertical rate from electrical static pressure when a remote static sensor is used. These four program pin selectable configurations provide compatibility with most aircraft. Bootstrapping of vertical speed inputs as currently implemented on L−1011, A300, A310 and A300−600 aircraft, is provided with a larger 55−pin unit connector. These units have a unique dash number assigned to them. Various dash number VSI/TRA Displays are available that provide unique design characteristics, which include VSI rate filter programming and selection of an English or metric rate scale. Table 1−5 contain a listing of all the VSI/TRA configurations. Page 1−36 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System The VSI/TRA also displays symbology corresponding to traffic in the vicinity of the aircraft. Threat information is received from the TCAS Computer Unit on a dedicated high−speed ARINC 429 bus. The display uses the bearing, altitude, and range data for each threat to provide an indication of the proximity of the threat. Allowable (nonilluminated or green illuminated bands) and prohibited (red illuminated bands) vertical rates are displayed based on information received from the TCAS computer unit. The VSI/TRA can be pin programmed to provide vertical speed data only, vertical speed and resolution advisory data, or vertical speed, resolution advisory and traffic advisory data. Display of the TCAS system fault status is provided on the VSI/TRA in response to extended TCAS control panel TEST activation. Display dimming is controlled from several inputs consisting of an internal light sensor mounted on the bezel of the LRU, a remote light sensor, and the aircraft dimming bus. The display is dimmed by varying the brightness of the LCD panel backlighting. (2) Software Considerations VSI/TRA software is developed to a DO−178A category of Level ll (essential). The software continually monitors and displays vertical speed and TCAS information. Output discretes supply user components with the status of the LRU. TCAS valid indicates that the LRU is displaying valid TCAS information. On the 55−pin version, VSI valid indicates that the LRU is displaying valid vertical speed information. This is needed to support the bootstrap feature, which is exclusive to the 55−pin version of the VSI/TRA display. (3) Built−In Test Equipment (BITE) and Self−Test Capability The LRU has input discretes that allow a calibration and test program to be run. This mode allows the display to be adjusted and various diagnostic tests to be performed. These tests and adjustments can only be done in a shop on a dedicated test fixture. When the LRU application program is operating in the aircraft, the background loop continuously monitors the power supply status, the ROM integrity, and the analog range limits. A failure results in the setting of bad status output discretes. A cold start will continuously be attempted until the LRU passes the built−in test. There is a dedicated self−test input for both versions of the VSI/TRA Display. When this pin is activated, the unit will display symbology that aids in the detection of unit faults. 34−43−23 Page 1−37 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System TCAS CU 1 TA/RA VALID 2 PRIMARY 429 3 PTM PWR VSI/TRA DISPLAY 3 AC ADC #1 3 DC ADC ADC VALID ARINC 429 2 PTM PWR 3 #1 PTM ARINC 429 2 OR: DADC #1 ARINC 565 3 VALID 1 OR: AC ADC #1 ARINC 575 3 VALID 1 OR: DC ADC #1 #1 STATIC PRESSURE PORT 41 PIN VERSION VALID 1 ARINC 575 3 ADC VALID VSI/TRA DISPLAY #2 VALID 1 ARINC 565 3 DC ADC AC ADC ARINC 429 2 PRIMARY 429 PTM PWR ARINC 429 2 PTM PWR 3 DC ADC #2 OR: AC ADC #2 OR: DADC #2 OR: #2 PTM #2 STATIC PRESSURE PORT TA/RA VALID TCAS CU AD−53003@ Figure 1−13. VSI/TRA Interface Diagram (41−Pin Version) Page 1−38 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System TCAS CU #1 BOOTSTRAP MANUAL CONTROLLER NORM ALT VSI/TRA DISPLAY #1 PRIMARY 429 PTM PWR SECONDARY 429 IRS AC ADC DC ADC BOOTSTRAP VS SIGNAL #2 #1 BOOTSTRAP VS SIGNAL #1 #2 ARINC 429 2 ARINC 565 3 VALID 1 ARINC 575 3 VALID 1 VALID 1 ARINC 575 3 SOURCE ALT SELECT VALID 1 ARINC 565 3 BS CMD #2 BOOTSTRAP MANUAL CONTROLLER ARINC 429 2 PTM PWR 3 ARINC 429 2 ADC VALID 1 1 2 4 4 BS CMD SOURCE SELECT NORM 1 1 2 4 4 ADC VALID VSI/TRA DISPLAY #2 ARINC 429 2 DC ADC AC ADC IRS SECONDARY 429 PRIMARY 429 PTM PWR ARINC 429 2 ARINC 429 2 PTM PWR 3 #1 PTM OR: DADC #1 AND/OR: IRS #1 OR: AC ADC #1 OR: DC ADC #1 DC ADC #2 OR: AC ADC #2 AND/OR: IRS #2 OR: DADC #2 OR: #2 PTM TA/RA VALID TCAS CU #1 STATIC PRESSURE PORT 55 PIN VERSION (W/BOOTSTRAP) #2 STATIC PRESSURE PORT AD−53004@ Figure 1−14. VSI/TRA Interface Diagram (55−Pin Version) 34−43−23 Page 1−39 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System F. Pressure Transducer Module The Pressure Transducer Module (PTM) converts static pressure to a low speed ARINC 429 signal used by the VSI/TRA to calculate altitude rate. Figure 1−15 shows a graphical view of the PTM. The PTM can be mounted in any pressurized area of the aircraft. Table 1−10 gives items and specifications particular to the unit. AD−53005@ Figure 1−15. Pressure Transducer Module Page 1−40 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 1−10. Pressure Transducer Module Leading Particulars Item Specification Dimensions (maximum): • Height . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.6 in. (40.6 mm) • Width . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.8 in. (71.1 mm) • Length . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.5 in. (190.5 mm) Weight (maximum) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.0 lb (0.091 kg) Power Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . ±12 V DC derived from VSI/TRA ±15 V power supply Power Consumption . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.0 Watts nominal Mating Connectors: • J1 (Electrical Connector) . . . . . . . . . . . . . . . . . . . . . . . 15 Pin Round, M83723/75A1415N • (Pneumatic Fitting) . . . . . . . . . . . . . . . . . . . . . . . . . . . . Flareless nipple, NAS 1760−06 Mounting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A mounting bracket is available for use in a limited access area or an ARINC 408A 3−ATI round plate is available for mounting in the instrument panel The PTM contains a pressure sensor packaged in a TO−8 header case and measures by a strain gage mechanism. The pressure sensor converts pressure that range from 3.0 to 33.0 inHg into a differential output voltage. Contained within the sensor are the strain sensing element, sensor heater, and temperature sensing diode. The PTM meets the specifications that follow after the altitude rate has been calculated from the static pressure source: • The input pressure range is from 3.0 to 33.0 inHg, which covers the altitude range of −2,000 to +50,000 feet • The applied altitude rate ranges from 0 to ±6000 ft/min • The PTM is capable of detecting and input pressure variation of 25 ft/min • The PTM is capable of tracking input signals of 40 ft/sec without performance degradation. The PTM is designed to send a power down message to the VSI/TRA. This is the only BITE capability of this unit. 34−43−23 Page 1−41 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System G. XS−950 Mode S Data Link Transponder The XS−950 Data Link Transponder provides surveillance functions to ground based and airborne interrogators, and communication functions to various onboard systems. The transponder contains data link functions that allow it to function as part of the Aircraft Telecommunications Network (ATN). The data link functions allow communication with a Communication Management Unit (CMU) through a Mode S Airborne Data Link Processor (ADLP). The transponder also contains Mode S specific functions that are dedicated links to onboard systems. The XS−950 Transponder has the capability to be upgraded to provide an internal airborne data link processor (ADLP) function. The XS−950 Transponder conforms to the ARINC 718−A Mode S Transponder Characteristic for form, fit and function, and is backward compatible with existing ARINC 718−A installations. It is certified to ICAO level IV data link capability and can be upgraded to level V data link capability. The XS−950 Data Link Transponder is packaged in a 4−MCU (Modular Concept Unit) outline as defined in ARINC Characteristic 600−7. The unit is able to utilize ARINC 404 cooling air moving through the LRU in a downward direction as well as ARINC 600 cooling air moving through the LRU in an upward direction. The rear connector receptacle is an ARINC 600 size 2 shell assembly with inserts and contacts as defined in ARINC Characteristic 718−A. The unit also features a fixed carrying handle and self−test button with discrete LRU STATUS annunciators. Figure 1−16 shows a graphical view of the XS−950 Data Link Transponder and Table 1−11 gives items and specifications that are particular to the transponder. Figure 1−16. XS−950 Data Link Transponder Page 1−42 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 1−11. XS−950 Data Link Transponder Leading Particulars Item Specification Dimensions (maximum): • Height . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7.6 in. (192 mm) • Width . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.9 in. (124.5 mm) • Length . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15.2 in. (386 mm) Weight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11.5 lb (5.2 kg) Power Requirements (115 V ac version): • Operating Voltage . . . . . . . . . . . . . . . . . . . . . . . . . . . . 97 to 134 V rms, 115 V rms nominal • Operating Frequency . . . . . . . . . . . . . . . . . . . . . . . . . 320 to 480 Hz, 400 Hz nominal • Power Consumption: − Standby Mode (No Replies) . . . . . . . . . . . . . . . . . 40 Watts maximum − Active mode (Maximum Load) . . . . . . . . . . . . . . . 85 Watts maximum • External Circuit Breaker Rating . . . . . . . . . . . . . . . . . 5 A at 115 V ac, 400 Hz Power Requirements (28 V dc version): • Operating Voltage . . . . . . . . . . . . . . . . . . . . . . . . . . . . +18.0 to +32.2 V dc, +27.5 V dc nominal • Power Consumption: − Standby Mode (No Replies) . . . . . . . . . . . . . . . . . 40 Watts maximum − Active mode (Maximum Load) . . . . . . . . . . . . . . . 85 Watts maximum • External Circuit Breaker Rating . . . . . . . . . . . . . . . . . 7 A at 28 V dc Mating Connector . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Radial Part No. NSXN2P203X0005 Mounting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ARINC 600 4MCU Tray Assembly TSO . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . C112, CL043, 121, F11 Environmental Specifications: . . . . . . . . . . . . . . . . . . . . DO−160C Environmental Category − 115 V ac version . . . . . . . . . . . . . . . . . . . . . . . . . . . [A2E1]−BB[CLMY]XXXXXXZEAEZRZA3E3XX − 28 V dc version . . . . . . . . . . . . . . . . . . . . . . . . . . . [A2E1]−BB[CLMY]XXXXXXZ[BZ]AZZRZA3E3XX • Temperature / Altitude [A2E1]: − Operating Temperature . . . . . . . . . . . . . . . . . . . . . −55 to +70 degrees C − Ground Survival Temperature . . . . . . . . . . . . . . . −55 to +85 degrees C − Altitude . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Sea Level to 70,000 feet − Loss of Cooling . . . . . . . . . . . . . . . . . . . . . . . . . . . . +40 degrees C for 30 minutes minimum 34−43−23 Page 1−43 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 1−11. XS−950 Data Link Transponder Leading Particulars(cont) Item Specification • Vibration [CLMY]: − Category C . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Fixed wing turbojet engine, fuselage mounting − Category L . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Fixed wing reciprocating and turboprop multi and single engine over 12,500 pounds, fuselage mounting − Category M . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Fixed wing reciprocating and turboprop multi and single engine less than 12,500 pounds, instrument panel/console and equipment rack mounting − Category Y . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Helicopter, reciprocating and turbojet, fuselage mounting Operating Modes: • STANDBY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Ready but not replying • ATC ON . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Transponder Modes A and S, no altitude reporting • ATC ALT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Transponder Modes A, C, and S. Altitude reporting is enabled Transmitter Frequency . . . . . . . . . . . . . . . . . . . . . . . . . 1090 ±1.0 MHz Transmitter Power . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 640 Watts maximum peak pulse, 250 Watts minimum Receiver Frequency . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1030 MHz Minimum Trigger Level (MTL) . . . . . . . . . . . . . . . . . . . . −76 ± 3 dBm Mutual Suppression . . . . . . . . . . . . . . . . . . . . . . . . . . . . Bidirectional, accepts +18 to +70 volt pulse input; provides +28 volt nominal output Controller Interface: • Circuit Configuration . . . . . . . . . . . . . . . . . . . . . . . . . . Two ARINC 429 control data input ports. 12.5 K bits/s (low−speed ARINC) • Bus Protocol . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Bus protocol meets requirements defined in ARINC 718−A for receiving transponder and TCAS control information. TCAS II Interface: • Circuit Configuration . . . . . . . . . . . . . . . . . . . . . . . . . . ARINC 429 input and output bus. 100 K bits/s (high−speed ARINC) • Bus Protocol . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Bus protocol meets requirements defined in ARINC 718−A and ARINC 735A−1 for standard transponder to TCAS interface Page 1−44 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 1−11. XS−950 Data Link Transponder Leading Particulars(cont) Item Specification Airborne Data Link Processor (ADLP) Interface: • Circuit Configuration . . . . . . . . . . . . . . . . . . . . . . . . . . COMM−A/B messages have an ARINC 429 input and output bus. COMM−C/D messages have an ARINC 429 input and output bus. Both sets of busses are 100 K bits/s (high−speed ARINC). • Bus Protocol . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Bus protocol meets requirements defined in ARINC 718−A for standard transponder to ADLP bus interface. Altimeter Interface: • Digital Air Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ARINC 429 or 575 data format. 12.5 K bits/s (low−speed ARINC). Two altimeter inputs (left and right altimeters). • Synchro Altitude . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ARINC 407 data format. Fine and course 3−wire synchro inputs and a synchro valid flag discrete input. Two sets of synchro altimeter inputs (left and right altimeters). • Analog Altitude (−20012, −65012 Only) . . . . . . . . . . Three wire proportional input with valid flag discrete input. Two altimeter inputs (left and right altimeters). Discrete input to enable altitude comparison. • Encoding Altimeter . . . . . . . . . . . . . . . . . . . . . . . . . . . Gillham altitude data format. 11−wire discrete input. Two altimeter inputs (left and right altimeters). • Altitude Selection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Altitude source (left and right) selected by discrete input. Airframe Parameter Data Interface: • Circuit Configuration . . . . . . . . . . . . . . . . . . . . . . . . . . ARINC 429 input busses. High (100K bits/s) or Low (12.5 K bits/s). Speed, auto−detected by transponder. • Bus Protocol . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Aircraft parameters required to support Elementary and Enhanced Surveillance (ELS/EHS) as well as Extended Squitter. Bus protocal and input ports as defined in ARINC 718−A, minimum subset.. Aircraft Air/Ground Status Interface . . . . . . . . . . . . . . . Two discrete inputs used to indicate the aircraft air/ground status. Maintenance Computer Interface: • Circuit Configuration . . . . . . . . . . . . . . . . . . . . . . . . . . ARINC 429 input and output bus. 12.5 K bits/s (low−speed ARINC). 34−43−23 Page 1−45 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 1−11. XS−950 Data Link Transponder Leading Particulars(cont) Item Specification • Bus Protocol . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . The maintenance computer interface meets protocol requirements for all model Airbus, Boeing, and McDonnell Douglas maintenance computers. Onboard Software Uploading / Maintenance Log Downloading: • Circuit Configuration . . . . . . . . . . . . . . . . . . . . . . . . . . Portable Data Loader thru ARINC 615 Front Panel Connector ARINC 429 input and output bus (100 K bits/s) PDL Link A discrete input RS−232 input/output bus (38.4 K bits/s) at 53−pin PDL connector Airborne Data Loader thru Unit Rear Connector ARINC 429 input and output bus (100 K bits/s) ADL Link A discrete input • Bus Protocol . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Software uploads thru ARINC 429 PDL (front panel) port or ARINC 429 ADL (rear connector) port per the protocol in ARINC 615 high−speed data loader Maintenance log downloads thru ARINC 429 PDL port or ARINC 429 ADL port per the protocol in ARINC 615 high−speed data loader Software uploads and maintenance log downloads can be accomplished through the PDL front panel port with an RS−232 interface bus and a PC with terminal emulation software Page 1−46 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System H. RCZ−852 Diversity Mode S Transponder The RCZ−852 Diversity Mode S Transponder is an airborne transponder designed to perform both conventional and advanced air traffic control (ATC) functions. It receives coded radar signals from ATC ground stations and other aircraft and transmits coded replies. The replies contain information such as aircraft identity, altitude, and data communication messages. The transponder works with the air traffic control radar beacon system (ATCRBS) and mode select (Mode S) system to provide enhanced surveillance and communications capability required for air traffic control system automation and onboard collision avoidance systems. It has antenna diversity and is defined as a Class 3A transponder with TCAS interface capability. The RCZ−852 Diversity Mode S Transponder has the capabilities that follow: • Surveillance functions of both ATCRBS and Mode S ground sensors • Surveillance functions of airborne interrogators • Bi−directional air−to−air information exchanges, COMM−U/V • Ground−to−Air data uplink, COMM−A • Air−to−Ground data downlink, COMM−B • Multisite message protocol • Ground−to−Air extended length message (ELM), COMM−C. The transponder does not support COMM−D extended length message (ELM) communication. Figure 1−17 shows a graphical view of the RCZ−852 Diversity Mode S Transponder and Table 1−12 gives items and specifications that are particular to the transponder. Figure 1−17. RCZ−852 Diversity Mode S Transponder 34−43−23 Page 1−47 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 1−12. RCZ−852 Diversity Mode S Transponder Leading Particulars Item Specification Dimensions (maximum): • Height . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.38 in. (86 mm) • Width . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.10 in. (104 mm) • Length . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14.1 in. (358 mm) Weight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.0 lb (2.27 kg) Power Requirements: • Operating Voltage . . . . . . . . . . . . . . . . . . . . . . . . . . . . +18.0 to +30.3 V dc, +27.5 V dc nominal • Power Consumption: − Standby Mode (No Replies) . . . . . . . . . . . . . . . . . 28 Watts nominal − Active Mode (Maximum Load) . . . . . . . . . . . . . . . 55 Watts maximum • External Circuit Breaker Rating . . . . . . . . . . . . . . . . . 5 A at +27.5 V dc Mating Connector . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ACSS Part No. 7500294−106, Tri−Star Part No. TRAP−106P−26(200); Cannon Part No. DPXAMA−21000−2491 (Part of Installation Kit, ACSS Part No. 7510707−968) Mounting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Mount Assembly, ACSS Part No. 7517455−902 TSO . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . C112 Environmental Specifications . . . . . . . . . . . . . . . . . . . . . DO−160B Environmental Category /A2E1/B/JLMY/E1XXXXXZ/BZ/AZZ • Temperature / Altitude [A2E1]: − Operating Temperature . . . . . . . . . . . . . . . . . . . . . −55 to +70 degrees C − Ground Survival Temperature . . . . . . . . . . . . . . . −55 to +85 degrees C − Altitude . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Sea Level to 70,000 feet − Decompression . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8,000 to 70,000 feet − Overpressure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . −15,000 feet • Vibration [JLMY]: − Category J . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Fixed wing turbojet, subsonic and supersonic, fuselage mounting − Category L . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Fixed wing reciprocating and turboprop multi and single engine over 12,500 pounds, fuselage mounting Page 1−48 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 1−12. RCZ−852 Diversity Mode S Transponder Leading Particulars (cont) Item Specification − Category M . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Fixed wing reciprocating and turboprop multi and single engine less than 12,500 pounds, instrument panel/console and equipment rack mounting − Category Y . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Helicopter, reciprocating and turbojet, fuselage mounting Operating Modes: • STANDBY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Ready but not replying. • ATC ON . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Transponder Modes A and S. No altitude reporting. • ATC ALT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Transponder Modes A, C, and S. Altitude reporting is enabled. Transmitter Frequency . . . . . . . . . . . . . . . . . . . . . . . . . 1090 ± 0.5 MHz Transmitter Power . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 500 Watts peak pulse, 250 Watts minimum Receiver Frequency . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1030 MHz Minimum Trigger Level (MTL) . . . . . . . . . . . . . . . . . . . . −77 ± 3 dBm Mutual Suppression . . . . . . . . . . . . . . . . . . . . . . . . . . . . Bidirectional, accepts +18 to +70 volt pulse input, provides +28 volt nominal output Controller interface: • Circuit Configuration . . . . . . . . . . . . . . . . . . . . . . . . . . Two ARINC 429 control data input ports. 12.5 K bits/s (low−speed ARINC) • Bus Protocol . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Bus protocol meets requirements defined in ARINC 718−A for receiving transponder and TCAS control information. TCAS II Interface: • Circuit Configuration . . . . . . . . . . . . . . . . . . . . . . . . . . ARINC 429 input and output bus. 100 K bits/s (high−speed ARINC). • Bus Protocol . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Bus protocol meets requirements defined in ARINC 718−A and ARINC 735 for standard transponder to TCAS interface. Airborne Data Link Processor (ADLP) Interface: • Circuit Configuration . . . . . . . . . . . . . . . . . . . . . . . . . . COMM−A/B messages have an ARINC 429 input and output bus. COMM−C/D messages have an ARINC 429 input and output bus. Both sets of busses are 100 K bits/s (high−speed ARINC). • Bus Protocol . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Bus protocol meets requirements defined in ARINC 718−A for standard transponder to ADLP bus interface. 34−43−23 Page 1−49 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 1−12. RCZ−852 Diversity Mode S Transponder Leading Particulars (cont) Item Specification • Exception . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . COMM−D messages are not processed by this transponder. Altimeter Interface: • Digital Air Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ARINC 429 or 575 data format. 12.5 K bits/s (low−speed ARINC). Two altimeter inputs (left and right altimeters). • IAC Air Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Radio System Bus (RSB) interface supplies the Honeywell Integrated Avionics Computer (IAC) digital air data information. Two altimeter inputs (left and right altimeters). • Encoding Altimeter . . . . . . . . . . . . . . . . . . . . . . . . . . . Gillham altitude data format. 11−wire discrete input. Two altimeter inputs (left and right altimeters). • Altitude Selection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Altitude source (left or right) selected by a discrete input. Flight Identifier Interface: • From Radio Management (RMU) . . . . . . . . . . . . . . . Flight identifier input from the RMU in RSB data format. • From Flight Management System (FMS) . . . . . . . . Flight identifier input from the FMS in ARINC 429 data format. 12.5 K bits/s (low−speed ARINC). Aircraft Air/Ground Status Interface . . . . . . . . . . . . . . . Two discrete inputs used to indicate the aircraft air/ground status. Antenna Selection Interface . . . . . . . . . . . . . . . . . . . . . . A discrete output supplies a GROUND when transponder is active. RCB Interface: • Circuit Configuration . . . . . . . . . . . . . . . . . . . . . . . . . . 2−wire full duplex RS−232 serial link to/from internal radio communications bus (RCB). • Transmission Rate . . . . . . . . . . . . . . . . . . . . . . . . . . . 187.5 K baud • Transmission Format . . . . . . . . . . . . . . . . . . . . . . . . . 1 start bit, 8 data bits and 1 stop bit Shop Flash Memory Programming Interface: • Circuit Configuration . . . . . . . . . . . . . . . . . . . . . . . . . . 2−wire full duplex RS−232 serial port • Transmission Rate . . . . . . . . . . . . . . . . . . . . . . . . . . . 19.2 K baud • Transmission Format . . . . . . . . . . . . . . . . . . . . . . . . . 1 start bit, 7 data bits, odd parity and 1 stop bit Page 1−50 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System 5. System Operation The principal modes of operation and display features of the TCAS 3000 are discussed in the paragraphs that follow. In−flight procedures with display examples are contained in the TCAS Pilot’s Manual, ACSS Publication No. C28−3841−005. A. Operational Modes The TCAS 3000 can operate in several different modes, depending on control panel selection. Several control panels are available. Only the ACSS single Mode S control panel is discussed. Other control panels provide similar features. Four switches directly affect the TCAS operational mode: TCAS/XPDR mode selector, TA DSPLY selector, ALT RPTG selector, and TCAS TEST switch. To distinguish the modes that provide TCAS advisories from those that do not, the operational modes are discussed under TCAS modes and non−TCAS modes. The non−TCAS modes are annunciated TCAS OFF at the center of the display. The extended test mode is mentioned for reference. A detailed description of its use can be found in the FAULT ISOLATION section. (1) TCAS Modes The TA/RA and the TA−only modes are the two TCAS operational modes. The TA/RA mode gives traffic information and warnings of hazardous traffic conflicts, while the TA mode gives only traffic information. A third mode, the TEST mode, can be temporarily activated from any mode including standby (STBY). The TEST mode does not inhibit the generation of advisories. Functions available in the operational and test modes are as follows: (a) TA/RA Mode This mode is the normal operation mode providing full TCAS coverage. In this mode, TCAS tracks all aircraft in the surrounding airspace and generates traffic advisories or resolution advisories, as the situation requires. Figure 1−3 contrasts the airspace covered for each kind of advisory. For normal TA/RA operation, the TA/DSPLY selector must be set to AUTO or ON and the ALT/RPTG selector must be set to 1 or 2. (b) TA Mode The TA mode provides only surveillance of the surrounding airspace. In this mode, TCAS tracks all proximate aircraft and generates traffic advisories; no resolution advisories are issued in this mode. The flight crew uses the TA−only mode when resolution advisories would be a nuisance, or when flying over an area where only TCAS surveillance is allowed. Also, the system automatically selects this mode when the aircraft is flying under 1000 feet above ground level (AGL). The TA mode is annunciated TA ONLY at the upper left corner of the display. 34−43−23 Page 1−51 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System (c) Test Mode Pushing the TEST button on the control panel starts a self−test program which verifies proper operation of the TA and RA displays and of the aural advisories on the audio system. The test mode does not affect normal TCAS operation, provided the selected transponder remains in normal operation during the test cycle. Should a TA or RA occur during the test sequence, the test aborts, and the advisory is announced and displayed. The test mode just described excludes extended self−tests performed on the ground, where TCAS is inoperative. (2) Non−TCAS Modes The control panel selections that follow disable TCAS operation and all advisories: • MODE S ON activates a Mode S transponder only • STBY sets the selected transponder in standby mode • ATC activates an ATCRBS transponder only • ALT RPTG set to OFF inhibits altitude reporting. When TCAS is inoperative as a result of control panel selection, TCAS OFF is annunciated on the display. When TCAS is inoperative due to a system failure, TA FAIL, RA FAIL, or TCAS FAIL is annunciated on the display. In addition, if the transponder or the altitude data source fails, the XPDR FAIL light on the control panel comes on. (3) Extended Test Mode The purpose of the extended test mode is to facilitate diagnosis in the event self−test has failed. Like self−test, this mode is enabled by pushing the TCAS TEST button, but only when TCAS is inoperative. The aircraft must be on the ground, and the transponder must be set to STBY. Holding TCAS TEST pushed for longer than eight seconds in this condition activates the extended tests. This feature is not available on all systems. Refer to the TESTING AND FAULT ISOLATION section for system requirements and test description. Page 1−52 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System B. Display Symbology The TCAS modes use color−coded symbols and data tags to map air traffic and locate threat aircraft on the VSI/TRA display. Four traffic symbols are used: solid circle, solid square, solid diamond, and hollow diamond. See Figure 1−18 for examples. A different color is assigned to each symbol type, as listed in Table 1−13. Table 1−13. TCAS Traffic Symbols NOTE: Graphic Symbol Color Display Function Solid Circle Amber Traffic Advisory (TA) Solid Square Red Resolution Advisory (RA) Solid Diamond Blue Proximate Traffic Hollow Diamond Blue Other Traffic TCAS traffic information displayed on EFIS displays such as crew alerting system display, navigation display, electronic horizontal situation display or multifunction display, is similar to that on combined VSI/TRA indicators. Traffic symbology is identical to that displayed on the VSI/TRA. (1) Colors (a) Amber Represents a moderate threat to a TCAS−equipped aircraft. A visual search is recommended to prepare for intruder avoidance. Amber is used only in conjunction with a traffic advisory. (b) Red Represents an immediate threat to a TCAS−equipped aircraft. Prompt action is required to avoid the intruder. This color is only used in conjunction with a resolution advisory. (c) Blue Represents proximate traffic and other traffic the TCAS surveillance logic has in its track file. (d) White Used only for mode annunciations and for reference graphics, including aircraft home position, range ring, and VSI scale. 34−43−23 Page 1−53 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System (2) Traffic Identification (a) Traffic Advisory Intruder aircraft entering the caution area, 20 to 48 seconds from the TCAS 3000 collision area are represented as a solid amber circle. This type of traffic results in a traffic advisory. (b) Resolution Advisory Intruder aircraft entering the warning area, 15 to 35 seconds from the TCAS 3000 collision area are represented as a solid red square. This type of traffic results in a resolution advisory. (c) Proximate Traffic Aircraft within 6.0 nautical miles and "1200 feet vertically are represented as a solid cyan diamond. Proximate traffic is shown to improve situational awareness in the event of a potential conflict with higher priority RA or TA aircraft. (d) Other Traffic Any transponder replying to traffic not classified as an intruder or proximate traffic, and within "2700 feet vertically and the range of the display are represented as hollow cyan diamonds (only in view with the traffic switch ON and no TA or RA in process). The predicted flightpaths of proximate and other traffic do not penetrate the collision area of the TCAS aircraft. (3) Data Tags A data tag, made up of a two−digit number, a plus (+) or a minus (−) sign, and may also include an arrow, appears either above or below the intruder aircraft symbol. The data tag appears in the same color as the advisory. (a) Two−digit Number (Relative Altitude) Represents the relative altitude difference, in hundreds of feet, either above or below the TCAS aircraft of an intruder aircraft. For an intruder above the TCAS aircraft, the data tag is placed above the traffic symbol and preceded by a plus (+) sign; for one below, the tag is placed below the traffic symbol and be preceded by a minus (−) sign. (b) Plus (+) or Minus (−) Sign Appears adjacent to the relative altitude number and indicates whether the displayed aircraft is above (plus) or below (minus) the TCAS aircraft. (c) Arrow A vertical arrow is placed to the immediate right of the traffic symbol if the intruder is either climbing (up arrow) or descending (down arrow) in excess of 500 feet per minute. Page 1−54 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System (4) VSI Scale Overlays During a resolution advisory, red and green bands overlay the VSI scale. The red band indicates what vertical speed range is to be avoided by the pilot (prohibited vertical speed). The green band indicates the vertical speed the pilot is to attain to achieve safe separation from a threat aircraft (recommended vertical speed). The red/green band reflects the RA in progress and acts as a vertical speed advisory for the pilot. (5) Reference Graphics and Annunciations A white airplane symbol is displayed in the lower center of the VSI representing the aircraft own position. A white range ring made up of 12 dots, each corresponding to a normal clock position, is included. The range ring surrounds the airplane with a radius of 2 nautical miles and is intended to assist in interpreting TCAS traffic information. The scale of the VSI display is 6.0 nautical miles to the top display edge of the VSI (ahead of the aircraft), 4 miles to the left and right edges, and 2.5 nautical miles to the bottom (behind the aircraft). Annunciations in white letters serve as a reminder of the current operation mode. They include TCAS OFF, TA only and RA only. Fault annunciations in amber letters replace the mode annunciations in case of system failure. They include TCAS FAIL, RA FAIL, VSI FAIL, and TA FAIL (traffic display failure). Figure 1−12 shows a typical failure display. C. Aural Messages The TCAS generates aural alerts or messages announced over the aircraft audio system. These messages accompany the visual TA or RA display and are softened or strengthened, depending on the urgency of the situation. The TCAS audio level is preset and is not adjustable by the aircrew. If a logic change occurs before a message is completed and a new message is initiated, the original alert is terminated and the new alert announced immediately. (1) Requirements and Limitations The following is a list of the requirements and limitations for issuing an aural advisory by the TCAS Computer Unit: (a) Voice announcements are inhibited below 500 feet above ground level (AGL). (b) The CANCEL BUTTON, halts voice announcements after the CANCEL BUTTON is activated. An aural advisory in progress is terminated and not repeated after deactivation of the CANCEL BUTTON. (c) During TCAS computer unit self−test, an aural advisory confirms proper operation of the aural advisory system by annunciating the message “TCAS TEST”. The aural advisory system annunciates the pass/fail status of any monitored functions with the messages “TCAS TEST PASS” and “TCAS TEST FAIL”, respectively. 34−43−23 Page 1−55 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System (d) An aural advisory tone will precede each aural advisory when the audio tone enable program pin has been activated. (e) TCAS computer unit aural alerts are inhibited when the advisory inhibit discrete input No. 4 is grounded. An aural advisory in progress is disabled after the grounding of advisory inhibit discrete No. 4. The truncated message is annunciated in its entirety once the inhibit discrete has been released. This capability is used to defer all advisory (TA and RA), aural alert, and visual alert outputs until another, higher priority announcement/alert is completed. (f) Increases and decreases in the threat level are aurally annunciated. However, decreases in threat level are annunciated once and are not preceded by setting the audio tone discrete. For example, a vertical speed restriction following a climb RA is annunciated once. (2) Traffic Advisory (TA) Message The traffic advisory aural alert, TRAFFIC − TRAFFIC is spoken once, and then inhibited until the next TA occurs. This alert occurs when TCAS predicts an intruder will enter the collision area within 20 to 48 seconds. Simultaneously, the TCAS traffic display shows the location of the intruder. (3) Resolution Advisory (RA) Messages Resolution advisories indicate evasive vertical maneuvers calculated to increase separation between the TCAS aircraft and the intruder (corrective advisory), or to indicate certain changes in vertical speed are not recommended (preventive). Resolution advisory messages made up of a single word are repeated three times; longer messages are repeated twice. RAs are annunciated on the TCAS computer unit using the voice messages listed below as determined by Collision Avoidance System (CAS) data. The following messages will not immediately follow another message from this paragraph if it causes a reversal of sense. For example, a “CLIMB, CLIMB, CLIMB” message cannot immediately follow a :”DESCEND, DESCEND, DESCEND” message. (a) “CLIMB, CLIMB, CLIMB”: Climb at the rate shown on the VSI or other suitable indicator. The −XX003 TCAS CU message is “CLIMB, CLIMB”. (b) “DESCEND, DESCEND, DESCEND”: Descend at the rate shown on the VSI or other suitable indicator. The −XX003 TCAS CU message is :”DESCEND, DESCEND”. (c) “MONITOR VERTICAL SPEED”: Verify that vertical speed is out of the illuminated red VSI arc, or comply with another suitable indicator. Additional messages are “MAINTAIN VERTICAL SPEED, MAINTAIN: MAINTAIN VERTICAL SPEED, CROSSING MAINTAIN”: or “ADJUST VERTICAL SPEED, ADJUST”. Safe separation is based upon maintaining the current vertical speed. (d) “ADJUST VERTICAL SPEED, ADJUST”: Reduce vertical speed to a speed out of the illuminated red arc. Page 1−56 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System (e) “ADJUST VERTICAL SPEED, ADJUST”: Reduce vertical speed to a speed out of the illuminated red arc. (f) “ADJUST VERTICAL SPEED, ADJUST”: Reduce climb or descent rate. (g) “MAINTAIN VERTICAL SPEED, MAINTAIN”: Safe separation is based upon maintaining the current vertical speed. (h) “MAINTAIN VERTICAL SPEED, CROSSING, MAINTAIN”: Maintain vertical speed while crossing the intruder’s flight path. (i) “CLEAR OF CONFLICT”: Range is increasing, and separation is adequate; return to assigned clearance. (j) “CLIMB, CROSSING CLIMB—CLIMB, CROSSING CLIMB”: Safe separation is best be achieved by climbing through intruder’s flight path. (k) “DESCEND, CROSSING DESCEND, DESCEND, CROSSING DESCEND”: Safe separation is best achieved by descending through the intruder’s flight path. (4) Enhanced RA Messages Enhanced RAs are annunciated on the TCAS computer unit using the voice messages listed below as designated by the CAS data when the initial resolution advisory does not provide sufficient vertical separation. These messages are annunciated to convey a sense of urgency. The following messages can immediately follow a message from the previous paragraph and have a reversal of sense. NOTE: These advisories are expected to occur only on rare occasions, usually when an intruder suddenly changes its current flightpath. (Maneuvering intruder) (a) “INCREASE CLIMB, INCREASE CLIMB”: (Received after a “CLIMB” advisory) Indicates additional climb rate required to achieve safe vertical separation from a maneuvering intruder. (b) “INCREASE DESCENT, INCREASE DESCENT”: (Repeated two times, received after “DESCEND” advisory) Indicates additional descent rate required to achieve safe vertical separation from a maneuvering intruder. (c) “CLIMB, CLIMB NOW!—CLIMB,CLIMB NOW!”: (Received after a “DESCEND” resolution advisory) Indicates a reversal in sense is required to achieve safe vertical separation from a maneuvering intruder. (d) “DESCEND, DESCEND NOW!—DESCEND, DESCEND NOW!”: (Received after a “CLIMB” resolution advisory) Indicates a reversal in sense is required to achieve safe vertical separation from a maneuvering intruder. D. Operating Procedures Basic TCAS operating procedures on the ground include pre−flight test, TCAS activation before takeoff, and TCAS deactivation after landing. In−flight procedures are contained in the pilot’s manual. 34−43−23 Page 1−57 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System (1) Pre−Flight Test The VSI/TRA self−test feature provides a convenient method to test the TCAS system before takeoff. NOTE: Self−test can be initiated at any time, on the ground or in flight (if not disabled in air by grounding pin RBP−8E), by momentarily pushing TCAS TEST. If TAs and RAs occur while self−test is activated in flight, the test aborts, and the advisories are processed and displayed. To perform self−test, push the TCAS TEST button on the control panel and monitor the sequence that follows: • Aural annunciation TCAS TEST is heard on audio system. • Test pattern with fixed traffic and advisory symbols appears on the display for eight seconds. • Make sure the test pattern is as shown in Figure 1−18. The test pattern includes: − An RA symbol at 3 o’clock, 2 nm, 200 ft above, in level flight − A TA symbol at 9 o’clock, 2 nm, 200 ft below, climbing − A proximate traffic symbol at 3.6 nm, 33 degrees right of the aircraft heading (approximately 1 o’clock), 1000 ft below, descending − A non−threat intruder (other traffic symbol) at 3.6 nm, 33 degrees left of the aircraft heading (approximately 11 o’clock), 1000 ft above, in level flight − Red and green resolution advisory VSI overlay indicating a don’t descend, don’t climb > 2000 ft/min advisory − TCAS TEST or RA OFF annunciation, depending on the capabilities of the display. • After 8 seconds, TCAS TEST PASS is announced, and the test pattern is replaced with the normal VSI display. • If self−test fails, TCAS TEST FAIL is announced, and TCAS FAIL appears on the display. To obtain failure data, perform the extended test mode procedure in the next section. Page 1−58 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System (2) TCAS Mode Activation Prior to takeoff, activate TCAS as follows: • Set TCAS/XPDR mode selector to TA/RA • Set TA/DSPLY to AUTO • Set ALT/RPTG to 1 or 2. (3) TCAS Mode Deactivation After clearing the runway following landing, set the TCAS/XPDR mode selector to STBY to disable Mode S communication. Figure 1−18. TCAS ll Display Test Pattern 34−43−23 Page 1−59/(1−60 blank) 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System MECHANICAL INSTALLATION 1. General This section contains information on how and where to mount each component of the TCAS 3000 system. For new installations, plan installation in two stages. First, determine location of the LRUs in the aircraft. Next, determine the length of RF and electrical interconnections for selected locations. NOTE : The TCAS 3000 LRU, ACSS Part No. 9003000−10XXX can functionally replace a TCAS 2000 LRU, Part No. 4066010−904, −905, or −907, in existing installations. Certification approval must be obtained. TCAS 2000 LRUs, Part No. 4066010−904, −905, −907, −910, or 7517900−10XXX may replace the TCAS 3000 if properly demonstrated and certified. 2. Equipment and Materials For new TCAS 3000 installations, refer to Table 1−1 for RCZ−852 Transponder Installation Kit information and Table 1−2 for mounting tray information. For all other components, refer to the applicable Outline and Installation drawing in this section for mounting information. The Outline and Installation drawings show connector and connector contact pin/socket part number information, where applicable. 3. Mechanical Installation Design NOTE : To assure proper grounding of the TCAS 3000 system, the aircraft surface to which all mountings or units are attached must be clean bare metal. Mount to the airframe with a resistance of 5 milliohms or less. A. TCAS 3000 Computer Unit Provisions Mechanical installation data for the TCAS 3000 Computer Unit (6−MCU) is shown in Figure 2−1. Data for the TCAS 3000 Computer Unit (4−MCU) is shown in Figure 2−2. The computer unit can be mounted in any convenient location in the aircraft; however, it must be located so as to maintain an antenna coaxial cable insertion loss of 2.5 ± 0.5 dB in accordance with DO−185. This is approximately within 50 feet of the antenna unless low loss coaxial cable is used. Top and bottom coaxial delay timing differences can be compensated for by use of the antenna delay program pins. The TCAS Computer Unit, Part No. 9003000−10XXX, is mounted in an ARINC 600 6−MCU mounting tray. The computer unit requires external cooling air in accordance with ARINC 600 or ARINC 404 to maintain the highest possible Mean Time Between Failures (MTBF). In those installations where this is not available, a mounting tray with an integral fan is required. The TCAS Computer Unit, Part No. 9003000−55XXX or 65XXX, is mounted in an ARINC 600 4−MCU mounting tray. This unit contains an internal temperature controlled fan, so it does not require any external cooling. 34−43−23 Page 2−1 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System B. Antenna Provisions The TCAS top directional antenna should, ideally, be the most forward antenna on the top of the aircraft and should be located as close to the longitudinal centerline as possible. See Figure 2−4. A 5−degree tilt angle is allowed laterally, with 2−degree positive and 5−degree negative tilt angles allowed longitudinally. See Figure 2−5. If a bottom directional antenna is used, it should also be the most forward antenna on the fuselage bottom. Tilt angle allowances are the same as on the top antenna. A bottom omnidirectional antenna need not be the most forward antenna, but it should be separated by at least 20−inches from any other L−band antenna. Since the bottom antenna may be either a directional (standard) or an omnidirectional (optional) antenna, dual notation is shown in the wiring diagram. Only one coax cable is needed for an omnidirectional antenna installation. (1) Directional Antenna Installation The top directional antenna mounting and installation data is given in Figure 2−6. Figure 2−6 contains the maximum radius dimensions for the various curved antenna base part number units, the number of aircraft mounting holes and the length of the connector extension for the various part number units. The antenna must be electrically bonded (less than 5.0 milliohms bonding resistance) to the airframe to provide a good ground contact for lightning protection. The directional antenna must be separated by a least 30−inches from any other L−band antenna, and 60−inches is preferred. If a bottom directional antenna is used, it should be the most forward antenna on the fuselage bottom with tilt angle allowances the same as for a top mounted antenna. An O−ring (included with the directional antenna) is required to be installed between the directional antenna and the aircraft fuselage. The Navy Aeronautical Standard part number for the O−ring is NAS 1611−240. The ACSS part number for the O−ring is 4000171−240. NOTE: For directional antennas, ACSS Part No. 7514060−90X, the customer must provide an adapter plate for mounting to the aircraft. The antenna base plate, to which the adapter must mate, is detailed in Figure 2−7. Directional antennas, ACSS Part No. 7514081−9XX, come with a preinstalled adapter plate. (2) Omnidirectional Antenna Installation The bottom omnidirectional antenna is a standard ATC type antenna. It should be qualified to TSO C119a and be dc grounded per MIL−A−90941, B−5087B. All L−band antennas must be separated by at least 20−inches. Only one coax cable is required for installation. The omnidirectional antenna is not supplied by ACSS. To install, follow the manufacturer ’s installation instructions. Page 2−2 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System C. Control Panel Provisions Mechanical installation data for the ACSS ATC/TCAS Control Panels is shown in Figure 2−8 and Figure 2−9. The control panel is supplied in either a dual Mode S/TCAS configuration shown in Figure 2−8, or an ATCRBS−Mode S/TCAS configuration shown in Figure 2−9. Mechanical installation data a typical Gables GXXXX Series ATC/TCAS control panel is shown in Figure 2−10. It should be noted that various other types of controllers (Radio Management Units or EFIS Display Controllers) can be used to control the TCAS display. If a controller other than a ACSS ATC/TCAS control panel is used, refer to that particular unit’s manual for installation data. D. VSI/TRA Provisions Mechanical installation data for the ACSS VSI/TRA display is shown in Figure 2−11. The VSI/TRA is usually used as a direct replacement for the existing 3−ATI form VSI indicator currently mounted in the cockpit. Replacement of the installation clamp may be necessary if the previous clamp is less than 2−inches deep. Some older aircraft clamps do not provide sufficient mechanical support. If a ACSS VSI/TRA is used as the TCAS display source, and an Air Data Computer is not available to provide vertical speed signals to the display, the installation must include a ACSS PTM to supply air data signals to the VSI/TRA. These signals are derived from a static pneumatic input. E. Pressure Transducer Module (PTM) Provisions Mechanical installation data for the PTM is shown in Figure 2−12. The PTM is configured to be mounted on a mounting bracket designed for use in a restricted access area or on a mounting plate for mounting in an ARINC 408A 3ATI round instrument panel space. The PTM is conduction, radiation, and natural convection cooled. It does not require any external cooling as long as it is installed in a pressurized area where the ambient temperature is within the established temperature range of the device. 34−43−23 Page 2−3 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System F. Transponder Provisions This paragraph contains the mechanical installation data for the ACSS Mode S Data Link Transponder, Part No. 7517800−XXYYY and ACSS Diversity Mode S Transponder, Part No. 7510700−850/−951. It also contains provisions for installing the ATC transponder antennas. (1) Mode S Data Link Transponder Provisions Mechanical installation data for the ACSS Mode S Data Link Transponder, Part No. 7517800−XXYYY is shown in Figure 2−13. The transponder can be mounted in any convenient location in the aircraft; however, it should be mounted within 30 feet of the antennas unless low loss coaxial cable is used to maintain a worst case loss of 3dB per ARINC 718−A. Top and bottom antenna coaxial run length differences can be compensated for by use of the antenna delay program pins on the transponder. The unit can utilize external cooling air in accordance with ARINC 600 or ARINC 404 or operate in convection−cooled environments. The transponder is mounted in an ARINC 600 4−MCU tray assembly. (2) Diversity Mode S Transponder Provisions Mechanical installation data for the ACSS RCZ−852 Diversity Mode S Transponder, Part No. 7510700−850/−951 is shown in Figure 2−14. The transponder can be mounted in any convenient location in the aircraft that allows the unit to be upright during normal flight. The exact location should allow the cabling between the unit, control panel, and antennas to be as short as possible. The location of the mounting tray (part of installation kit, Part No. 7510707−968) should allow adequate space for installation of the transponder, provide reasonable accessibility for servicing, and allow space on top, sides, and rear of unit for adequate ventilation. The location must also provide a solid mechanical mount to prevent vibration amplification. The mounting tray should be electrically bonded to the aircraft frame by a low resistance path of less than 2.5 milliohms. (3) ATC Transponder Antenna Provisions When installing transponder antennas, a TSO’d antenna should be selected. The antenna must be vertically polarized and operate in the frequency range of 960 to 1220 MHz. Antenna impedance must be 50 ohms. Voltage standing wave ratio (VSWR) shall not exceed 1.5:1. Selection of a grounded or lightning protected type antenna is required to pass the transponder bite continuity detection circuitry, if enabled. In dual transponder antenna installations it is important to provide adequate isolation from each other to prevent receiver front−end damage. A 20−inch minimum separation of Mode S antennas from other L−Band antennas, including TCAS antennas, must be maintained. The maximum cable length for RG−214/U is 30 feet (9.144 meters). Allow adequate cable length so bends in cable have a minimum 3−inch (76 mm) radius. Selection of coax cable assemblies with moisture barrier protection is highly recommended to minimize the effects of humidity and corrosion. Page 2−4 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System When you install ATC antennas, the mounting area must provide a solid mechanical base for the antenna as well as clearance for the connector. A doubler plate is usually required when the antenna is mounted on an unsupported large fuselage area. Never weaken aircraft structure for the sake of a good location. Refer to the aircraft manufacturer’s specifications; reinforcements for antennas are often built into the aircraft structure. Doubler plates or shims, if used, must be metallic and shaped to interface the antenna base with the contour of the aircraft fuselage. ATC antennas are not supplied by ACSS. All antenna installations should be in accordance with manufacturer installation instructions. A weather sealant should be applied around the periphery of the antenna base to prevent seepage of water and condensation and preclude corrosion. If a sealant or aerodynamic smoother is used, it should be applied after the antenna has been bolted down. 34−43−23 Page 2−5 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Blank Page Page 2−6 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Figure 2−1 (Sheet 1). TCAS 3000 Computer Unit Outline and Installation Drawing 34−43−23 Page 2−7/(2−8 blank) 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Figure 2−1 (Sheet 2). TCAS 3000 Computer Unit Outline and Installation Drawing 34−43−23 Page 2−9/(2−10 blank) 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Figure 2−2 (Sheet 1). TCAS 3000 Computer Unit Outline and Installation Diagram 34−43−23 Page 2−11/(2−12 blank) 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Figure 2−2 (Sheet 2). TCAS 3000 Computer Unit Outline and Installation Diagram 34−43−23 Page 2−13/(2−14 blank) 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Figure 2−3 (Sheet 1). TCAS 3000 Computer Unit Outline and Installation Diagram 34−43−23 Page 2−15/(2−16 blank) 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Figure 2−3 (Sheet 2). TCAS 3000 Computer Unit Outline and Installation Diagram 34−43−23 Page 2−17/(2−18 blank) 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System AD−53006@ Figure 2−4. TCAS Directional and Omnidirectional Antenna Locations 34−43−23 Page 2−19 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Figure 2−5. Directional Antenna Angular Orientation Page 2−20 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Figure 2−6 (Sheet 1). Directional Antenna Outline and Installation Diagram 34−43−23 Page 2−21/(2−22 blank) 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Figure 2−6 (Sheet 2). Directional Antenna Outline and Installation Diagram 34−43−23 Page 2−23/(2−24 blank) 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Figure 2−6 (Sheet 3). Directional Antenna Outline and Installation Diagram 34−43−23 Page 2−25/(2−26 blank) 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Figure 2−6 (Sheet 4). Directional Antenna Outline and Installation Diagram 34−43−23 Page 2−27/(2−28 blank) 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Figure 2−6 (Sheet 5). Directional Antenna Outline and Installation Diagram 34−43−23 Page 2−29/(2−30 blank) 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System 4X Ø 0.250 +0.004 −0.001 Ø 0.370 0.050 +0.000 −0.005 EQUALLY SPACED Ø 0.028 M A B 4X Ø 0.516 +0.006 −0.002 DETAIL EQUALLY SPACED 0.50 Ø 4.012 +0.000 −0.010 Ø 0.014 M A B Ø 7.895 Ø 7.375 Ø 6.855 Ø 1.900 45º Ø 9.232 J1 J4 Ø 9.266 Ø 2.880 0.50 Ø 4.180 ? 0.002 J3 0.50 J2 Ø 8.760 −B− 4X Ø 0.250 +0.004 −0.001 2X 28.5º Ø 0.028 M A B 4.480 Ø 5.000 0.010 x 45º 67.5º 0.50 0.120 4X Ø 0.250 +0.004 −0.001 Ø 0.370 0.050 +0.000 −0.005 5X 45º NOTE: Customer supplied adapter plates must mate with this surface. 0.120 Ø 0.028 M A B 0.455 −A− Figure 2−7 (Sheet 1). Directional Antenna Baseplate Outline and Installation Diagram 34−43−23 Page 2−31/(2−32 blank) 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. ID−39469 E7514061, SH2 Ø 5.520 SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System −A− 0.020 0.030 5X 0.020 x 45º (Ø 9.150) 0.232 +0.010 −0.000 (Ø 7.895) 2X 0.005 +0.005 45º −0.000 (Ø 6.855) (Ø 5.520) R 0.06 32 0.080 +0.006 −0.000 32 (Ø 4.480) 32 (Ø 4.012) (Ø 3.378) ID−39470 E514061, SH3 R 0.010 +0.015 −0.000 0.365 TO DATUM A −A− DETAIL Figure 2−7 (Sheet 2). Directional Antenna Baseplate Outline and Installation Diagram 34−43−23 Page 2−33/(2−34 blank) 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Figure 2−8. Control Panel (Dual Mode S) Outline and Installation Diagram 34−43−23 Page 2−35/(2−36 blank) 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Figure 2−9. Control Panel (ATCRBS−Mode S) Outline and Installation Diagram 34−43−23 Page 2−37/(2−38 blank) 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Figure 2−10. Gables G7130−XX Control Panel Outline and Installation Diagram 34−43−23 Page 2−39/(2−40 blank) 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System (2X 1.960) (2X 3.920) CONVERSION TABLE TOP VIEW 0.005 0.010 0.015 0.0425 0.090 0.100 0.125 0.135 0.177 0.225 0.428 0.438 0.453 4X 0.13 0.25 0.38 1.08 2.29 2.54 3.18 3.43 4.50 5.72 10.87 11.13 11.51 1.530 1.590 1.605 1.960 3.060 3.175 3.210 3.260 3.885 3.900 3.920 3.970 8.190 38.86 40.39 40.77 49.78 77.72 80.65 81.53 82.80 98.68 99.06 99.57 100.84 208.03 0.177 THRU RECOMMENDED PANEL CUTOUT (PIN 1) (2X 3.885) (2X 3.970) 0.10 0.10 1.590 .225 .135 NOTES: 1. MAXIMUM WEIGHT 4.0 LBS (1.81 KG). CONNECTOR J1 (41 PIN) MATES WITH M83723/75R2041N OR EQUIVALENT 41−PIN CONNECTOR BACKSHELL IS M85049/52−1−20N OR EQUIVALENT 2. DIMENSIONS SHOWN ARE IN INCHES. REFER TO METRIC CONVERSION TABLE FOR CORRESPONDING DIMENSIONS IN MILLIMETERS. 3. 1.590 CONNECTOR J1 (55 PIN) MATES WITH M83723/75R2255N OR EQUIVALENT 55−PIN CONNECTOR BACKSHELL IS M85049/52−1−22N OR EQUIVALENT DENOTES APPROXIMATE CENTER OF GRAVITY. AD−31673−R1@ Figure 2−11. VSI/TRA Outline and Installation Diagram 34−43−23 Page 2−41/(2−42 blank) 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Figure 2−12 (Sheet 1). Pressure Transducer Module Outline and Installation Diagram 34−43−23 Page 2−43/(2−44 blank) 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Figure 2−12 (Sheet 2). Pressure Transducer Module Outline and Installation Diagram 34−43−23 Page 2−45/(2−46 blank) 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Figure 2−12 (Sheet 3). Pressure Transducer Module Outline and Installation Diagram 34−43−23 Page 2−47/(2−48 blank) 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Figure 2−13 (Sheet 1). XS−950 Data Link Transponder Outline and Installation Diagram 34−43−23 Page 2−49/(2−50 blank) 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Figure 2−13 (Sheet 2). XS−950 Data Link Transponder Outline and Installation Diagram 34−43−23 Page 2−51/(2−52 blank) 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Figure 2−14 (Sheet 1). RCZ−852 Mode S Transponder Outline and Installation Diagram 34−43−23 Page 2−53/(2−54 blank) 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System 5 7 J1 CONNECTOR HPN 7500294−106 J3 RF CONNECTOR P/O HPN 7517437−901 MATES WITH CUSTOMER SUPPLIED TNC PLUG A5P2 RF CONNECTOR HPN 7500335−012 A3P1 CONNECTOR HPN 7500295−106 94 12 106 11 W1 HARNESS ASSY HPN 7510297−903 HEX NUT HPN 0921−001 FLAT WASHER HPN 7500501 SCREW HPN 2504188−131 SLEEVE HPN 7510288 4 REQD A5P1 RF CONNECTOR HPN 7500335−012 J2 RF CONNECTOR P/O HPN 7517437−901 MATES WITH CUSTOMER SUPPLIED TNC PLUG VIEW CC−CC VIEW BB−BB REAR VIEW OF RCZ−852 WITHOUT TRAY ASSY .575 11.750 2.00 MAX .880 TERMINATION TABLE FROM W1P1−1 W1P1−2 W1P1−3 W1P1−4 W1P1−6 W1P1−7 W1P1−8 TO J1−104 J1−92 J1−90 J1−103 J1−91 J1−93 J1−105 11 WIRE W1W1 (GRN) W1W2 (ORN) W1W3 (RED) W1W4 (BLK) W1W6 (BLU) W1W7 (WHT) W1W8 (YEL) 2.600 VIEW AA−AA 4X .206 .200 .014 E7510706−14−AE(R) AD−53837,SH3@ Figure 2−14 (Sheet 2). RCZ−852 Mode S Transponder Outline and Installation Diagram 34−43−23 Page 2−55/(2−56 blank) 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System ELECTRICAL INSTALLATION 1. General This section gives electrical installation procedures, power distribution, and interconnect information for each component on the TCAS 3000 system. 2. Equipment and Materials For new TCAS 3000 installations, refer to Table 1−1 for RCZ−852 Transponder Installation Kit information. For all other components, refer to the applicable Outline and Installation Diagram in the MECHANICAL INSTALLATION section for mating connector part numbers. 3. Electrical Installation Procedure The information necessary to provide the electrical interconnections is contained in the following paragraphs. Refer to Section 4, LOADING/GRADIENT SPECIFICATIONS, for a list of the signal names used in the interconnect diagrams and tables. 4. Electrical Installation A. TCAS 3000 Computer Units Figure 3−1 shows some general types of TCAS system installations, using various combinations of controllers (control panels) and transponders. The electrical installation of the TCAS Computer Units is detailed in Figure 3−2. The various installation options require different electrical connections as described on the interconnect diagram and the paragraphs that follow. The TCAS Computer Unit uses programming and configuration straps to select or deselect various TCAS functions. Refer to the notes in Figure 3−2 to determine applicable installation wiring. The TCAS Computer Unit ARINC 600 connector layout is shown in Figure 3−3. The contact arrangement for the various connector plugs are shown in Figure 3−4 thru Figure 3−8. Figure 3−9 shows the connector pin layout for the DATA LOADER connector located on the front of the computer unit. B. TCAS Antennas The electrical installation for the TCAS antennas is shown in Figure 3−2. Figure 3−4 shows the TCAS computer contact arrangement for the top directional antenna and Figure 3−5 shows the TCAS computer contact arrangement for the bottom antenna. 34−43−23 Page 3−1 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Figure 3−1. Typical Installation Types Page 3−2 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Figure 3−2 (Sheet 1). TCAS System Interconnect Diagram 34−43−23 Page 3−3/(3−4 blank) 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Figure 3−2 (Sheet 2). TCAS System Interconnect Diagram 34−43−23 Page 3−5/(3−6 blank) 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Figure 3−2 (Sheet 3). TCAS System Interconnect Diagram 34−43−23 Page 3−7/(3−8 blank) 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Figure 3−2 (Sheet 4). TCAS System Interconnect Diagram 34−43−23 Page 3−9/(3−10 blank) 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Figure 3−2 (Sheet 5). TCAS System Interconnect Diagram 34−43−23 Page 3−11/(3−12 blank) 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Figure 3−2 (Sheet 6). TCAS System Interconnect Diagram 34−43−23 Page 3−13/(3−14 blank) 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Figure 3−2 (Sheet 7). TCAS System Interconnect Diagram 34−43−23 Page 3−15/(3−16 blank) 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Figure 3−3. TCAS 3000 Computer Unit ARINC 600 Connector (P1) Layout 34−43−23 Page 3−17 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Figure 3−4. Contact Arrangement for CU Left Top Plug (LTP) Insert Figure 3−5. Contact Arrangement for CU Left Middle Plug (LMP) Insert Page 3−18 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System 28 V DC POWER RETURN 115 V AC POWER (H) 115 V AC FAN (H) 115 V AC POWER (C) SIGNAL GND 10 28 V DC POWER 13 CHASSIS GND 12 SUPPRESSION PULSE ID−39562 SUPPRESSION PULSE 11 115 V AC FAN (C) Figure 3−6. Contact Arrangement for Left Bottom Plug (LBP) Insert 34−43−23 Page 3−19 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Figure 3−7. Contact Arrangement for Right Middle Plug (RMP) Insert Page 3−20 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Figure 3−8. Contact Arrangement for Right Bottom Plug (RBP) Insert 34−43−23 Page 3−21 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System TCAS COMPUTER UNIT DATA LOADER CONNECTOR J2 DATA LOADER MATING CONNECTOR P2 NOTE: VIEWS SHOWN ARE OF MATING SURFACES AD−53014@ Figure 3−9. TCAS 3000 Computer Unit Data Loader Connector (J1) Pin Layout Page 3−22 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System C. Control Panels Table 3−1 thru Table 3−3 contain interconnect information for the various control panels. Table 3−1 contains the interconnect data for the ACSS Dual Mode S/TCAS Control Panel, Part No. 4052190−902, −904, −906 and −908. Table 3−2 contains the interconnect data for the ACSS ATCRBS−Mode S/TCAS Control Panel, Part No. 4052190−903, −905, −907 and −909. Table 3−3 contains the interconnect data for the Gables G7130 series control panels. Table 3−1. ACSS Dual Mode S Control Panel Interconnect Data I/O Description Connector Pin Connects To (I) 5 V ac Panel Lighting (C) J1−1 (20) Acft Lighting Source (I) 5 V ac Panel Lighting (H) J1−2 (20) Acft Lighting Source (I) 115 V ac Input Power (H) J1−3 (20) Acft 115 V ac Supply (I) 115 V ac Return (C) J1−4 (20) Acft ac Ground (O) Antenna Transfer Discrete J1−5 (22) Antenna Relay (I) J1−6 (22) Acft dc Ground (O) Standby/On J1−7 (22) Transponder No.1 (I) Chassis Ground J1−8 (22) Airframe Ground (I) Functional Test J1−9 (22) Remote Test Switch J1−10 (22) Remote Warn System (22) Transponder No.1 (22) Transponder No.1 (20) 28 V dc, 2A Source dc Ground (O) Warning & Caution (I) Spare J1−11 XPDR Fail No.2 Input J1−12 Spare J1−13 Spare J1−14 Reserved J1−15 (O) Alt Source Select Discrete J1−16 Notes Spare J1−17 Monitor Lamp Pwr J1−18 Spare J1−19 (I) XPDR Fail No.1 Input J1−20 (22) See J1−12 (I) Lamp Test J1−21 (22) Rmt Lamp Test Switch (O) ARINC 429 (A) Out J1−22 (22) Transponder No.1 (O) ARINC 429 (B) Out J1−23 (22) Transponder No.1 (I) GND 34−43−23 GND Page 3−23 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 3−1. ACSS Dual Mode S Control Panel Interconnect Data (cont) I/O Description Connector Pin Connects To Notes Reserved J1−24 Spare J2−1 Spare J2−2 (I) 115 V ac Input Power (H) J2−3 (20) Acft 115 V ac Supply (I) 115 V ac Return (C) J2−4 (20) Acft ac Ground (O) Antenna Transfer Discrete J2−5 (22) Antenna Relay (I) J2−6 (22) Acft dc Ground (O) Standby/On Discrete J2−7 (22) Transponder No.2 (I) Chassis Ground J2−8 (22) Airframe Ground Spare J2−9 Spare J2−10 Spare J2−11 XPDR Fail No.2 Input J2−12 (22) Transponder No.2 Spare J2−13 Spare J2−14 Reserved J2−15 (22) Transponder No.2 (22) See J2−12 Transponder No.2 Transponder No.2 (I) dc Ground (O) Alt Source Select Discrete (I) J2−16 Spare J2−17 Spare J2−18 Spare J2−19 XPDR Fail No.1 Input J2−20 Spare J2−21 (O) ARINC 429 (A) Out J2−22 (22) (O) ARINC 429 (B) Out J2−23 (22) GND Page 3−24 15 Dec 2005 GND 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 3−1. ACSS Dual Mode S Control Panel Interconnect Data (cont) I/O Description Reserved Connector Pin Connects To Notes J2−24 NOTES: 1. Connect either J1−5 or J2−5 to an antenna switching relay if one set of ATC antennas is used in a dual transponder installation. 2. Tie chassis ground to aircraft frame. 3. Two wire shielded cable. Tie shields to aircraft dc ground. 4. Connector pins J1−12 and J1−20 and pins J2−12 and J2−20 are tied together in the controller. 34−43−23 Page 3−25 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 3−2. ACSS ATCRBS−Mode S Control Panel Interconnect Data I/O Description Connector Pin Connects To (I) 5 V ac Pnl Lighting (C) J1−1 (20) Acft Lighting Source (I) 5 V ac Pnl Lighting (H) J1−2 (20) Acft Lighting Source (I) 115 V ac Input Power (H) J1−3 (20) Acft 115V ac Supply (I) 115 V ac Return (C) J1−4 (20) Acft ac Ground (O) Antenna Transfer Discrete J1−5 (22) Antenna Relay (I) J1−6 (22) Acft dc Ground (O) Standby/On J1−7 (22) Mode S Transponder (I) Chassis Ground J1−8 (22) Airframe Ground (I) Functional Test J1−9 (22) Remote Test Switch J1−10 (22) Remote Warn System (22) Mode S Transponder (22) Mode S Transponder (20) 28 V dc, 2A Source dc Ground (O) Warning & Caution (I) Spare J1−11 XPDR Fail No.2 Input J1−12 Spare J1−13 Spare J1−14 Reserved J1−15 (O) Alt Source Select Discrete J1−16 Notes Spare J1−17 Monitor Lamp Power J1−18 Spare J1−19 (I) XPDR Fail No.1 Input J1−20 (22) See J1−12 (I) Lamp Test J1−21 (22) Rmt Lamp Test Switch (O) ARINC 429 (A) Out J1−22 (22) Mode S Transponder (O) ARINC 429 (B) Out J1−23 (22) Mode S Transponder (I) GND Reserved J1−24 Spare J2−A Spare J2−B Spare J2−C Spare J2−D Page 3−26 15 Dec 2005 GND 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 3−2. ACSS ATCRBS−Mode S Control Panel Interconnect Data (cont) I/O Description Connector Pin Spare J2−E Spare J2−F Spare J2−G Spare J2−H Spare J2−J Spare J2−K (O) Alt No. 1 Spare (O) Alt No. 2 Spare (O) Altitude Common Spare (O) Transponder No. 2 On J2−L Connects To (22) Altitude Digitizer No. 1 (22) Altitude Digitizer No. 2 (22) ATCRBS Transponder (22) ATCRBS Transponder J2−M J2−N J2−P J2−R J2−S J2−T Spare J2−U Spare J2−V Spare J2−W (O) Mode A Reply Pulse (A1) J2−X (22) ATCRBS Transponder (O) Mode A Reply Pulse (A2) J2−Y (22) ATCRBS Transponder (O) Mode A Reply Pulse (A4) J2−Z (22) ATCRBS Transponder (O) Mode A Reply Pulse (B1) J2−a (22) ATCRBS Transponder (O) Mode A Reply Pulse (B2) J2−b (22) ATCRBS Transponder (O) Mode A Reply Pulse (B4) J2−c (22) ATCRBS Transponder (O) Mode A Reply Pulse (C1) J2−d (22) ATCRBS Transponder (O) Mode A Reply Pulse (C2) J2−e (22) ATCRBS Transponder (O) Mode A Reply Pulse (C4) J2−f (22) ATCRBS Transponder (O) Mode A Reply Pulse (D1) J2−g (22) ATCRBS Transponder (O) Mode A Reply Pulse (D2) J2−h (22) ATCRBS Transponder (O) Mode A Reply Pulse (D4) J2−i (22) ATCRBS Transponder (O) Ident Output J2−j (22) ATCRBS Transponder (22) ATCRBS Transponder (I) Notes Spare J2−k ATC Fail J2−m 34−43−23 Page 3−27 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 3−2. ACSS ATCRBS−Mode S Control Panel Interconnect Data (cont) I/O (I) Description Connector Pin dc Ground J2−n Spare J2−p Spare J2−q (O) Alt Rptg On Connects To (22) Acft dc Ground J2−r (22) ATCRBS Transponder (O) Test Output J2−s (22) ATCRBS Transponder (O) Transponder No. 1 On J2−t Notes NC NOTES: 1. Connect to antenna coax switching relay if one set of ATC antennas is used in a dual transponder installation. 2. Tie chassis ground to aircraft frame. 3. Two wire shielded cable. Tie shields to aircraft dc ground. 4. Connector pins J1−12 and J1−20 are tied together in the Control Panel. Page 3−28 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 3−3. Gables G7130−XX ATC/TCAS Control Panel Interconnect Data I/O Description Connector Pin Connects To (I) 5 V ac Pnl Lighting (H) J1−1 (20) Acft Lighting Source (I) 5 V ac Pnl Lighting (L) J1−2 (20) Acft Lighting Source (I) +28 V dc Input Power (H) J1−3 (20) Acft 28 V dc Power (I) +28 V dc Return (L) J1−4 (20) Acft dc Ground (O) Antenna Transfer Discrete J1−5 (22) Antenna Relay (I) J1−6 (22) Acft dc Ground (O) Standby/On Output Disc J1−7 (22) Transponder No. 1 (I) Chassis Ground J1−8 (22) Airframe Ground (I) Functional Test J1−9 (22) Remote Test Switch J1−10 (22) Remote Warn Sys dc Ground (O) Warning & Caution 1, 2 Reserved J1−11 (I) XPDR Fail Logic No.2 J1−12 (22) Transponder No. 1 (I) Ident Input J1−13 (22) Remote IDENT Switch (I) XPDR Fail (High Level) J1−14 NC (O) Air/Gnd Switched Discrete J1−15 NC (O) Alt Source Select Discrete J1−16 (22) Transponder No.1 (20) Acft 28 V dc Power J1−17 Monitor Lamp Power J1−18 Reserved J1−19 (I) XPDR Configuration J1−20 (I) Lamp Test J1−21 (22) (O) ARINC 429 (A) Out J1−22 (22) (O) ARINC 429 (B) Out J1−23 (22) NC Rmt Lamp Test SW Transponder No.1 Transponder No.1 (22) WOW Switch GND (I) 2, 4 Reserved (I) Notes GND Air/Gnd Discrete J1−24 Reserved J2−1 Reserved J2−2 (I) +28V dc Input Power (H) J2−3 (20) Acft 28 V dc Power (I) +28V dc Return (L) J2−4 (20) Acft dc Ground 34−43−23 Page 3−29 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 3−3. Gables G7130−XX ATC/TCAS Control Panel Interconnect Data (cont) I/O Description Connector Pin Connects To (O) Antenna Transfer Discrete J2−5 (22) Antenna Relay (I) J2−6 (22) Acft dc Ground (O) Standby/On Discrete J2−7 (22) Transponder No.2 (I) Chassis Ground J2−8 (22) Airframe Ground (I) Functional Test J2−9 (22) Remote Test SW J2−10 (22) Remote Warn Sys dc Ground (O) Warning & Caution Reserved J2−11 (I) XPDR Fail Logic No.2 J2−12 (22) Transponder No.2 (I) Ident Input J2−13 (22) Remote Ident SW (I) XPDR Fail (High Level) J2−14 NC Notes 1, 2 2, 4 (O) Air/Gnd Switched Discrete J2−15 (22) NC (O) Alt Source Select Discrete J2−16 (22) Transponder No.2 (20) Acft 28 V dc Power Gnd/Open Rmt Lamp Test SW Reserved J2−17 Monitor Lamp Pwr J2−18 Reserved J2−19 (I) XPDR Configuration J2−20 (I) Lamp Test J2−21 (22) (O) ARINC 429 (A) Out J2−22 (22) Transponder No.2 (O) ARINC 429 (B) Out J2−23 (22) Transponder No.2 Acft WOW Switch (I) NC GND (I) Air/Gnd Discrete J2−24 (22) GND NOTES: 1. Connect either J1−5 or J2−5 to an antenna switching relay if one set of ATC antennas is used in a dual transponder installation. 2. Refer to Loading Gradient Specifications in Table 4−4. 3. Tie chassis ground to aircraft frame. 4. 28 V dc discrete input from Collins TDR−94D transponder. 5. Two wire shielded cable. Tie shields to aircraft dc ground. Page 3−30 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System D. VSI/TRA Displays Table 3−4 and Table 3−5 contain the interface information for the various ACSS VSI/TRA displays. Table 3−4 contains interconnect data for the 41−pin connector units. Table 3−5 contains the interconnect data for the 55−pin connector (bootstrap) units. Figure 3−10 and Figure 3−11 show the connector pin layouts for the VSI/TRA. Figure 3−10 shows the 41−pin connector configuration and Figure 3−11 shows the 55−pin connector configuration. Table 3−4. 41−Pin VSI/TRA Interconnect Data I/O Description Connector Pin Connects To Notes (I) VS +dc Ref J1−1 (22) ARINC 575 ADC (I) VS dc Rate J1−2 (22) ARINC 575 ADC (I) VS −dc Ref J1−3 (22) ARINC 575 ADC (I) Primary VS (HI) J1−4 (22) ARINC 565 ADC or IRS (I) Primary VS (LO) J1−6 (22) ARINC 565 ADC or IRS GND (I) VS 26 V ac Ref (HI) J1−5 (I) Reserved ARINC Bus (A) J1−7 (I) Reserved ARINC Bus (B) J1−21 (I) VS VALID NO.1 (I) GND (22) ARINC 565 ADC or IRS J1−8 (22) ARINC 565/575 ADC or IRS 5 V Lamp Dimming (LO) J1−9 (22) Acft Lamp Dim Ckt (I) 5 V Lamp Dimming (HI) J1−10 (22) Acft Lamp Dim Ckt (I) TCAS TA/RA ARINC 429 (B) J1−11 (22) TCAS Computer (I) TCAS TA/RA ARINC 429 (A) J1−26 (22) TCAS Computer (I) VS No.1 ARINC 429 (B) J1−12 (22) Digital ADC No.1 or PTM No.1 (I) VS No.1 ARINC 429 (A) J1−27 (22) Digital ADC No.1 or PTM No.1 GND GND Spare GND GND J1−13 34−43−23 Page 3−31 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 3−4. 41−Pin VSI/TRA Interconnect Data (cont) I/O Description Connector Pin Connects To (I) VS No.2 ARINC 429 (B) J1−14 (22) Digital ADC No.2 or PTM No.2 (I) VS No.2 ARINC 429 (A) J1−30 (22) Digital ADC No.2 or PTM No.2 GND GND Notes (I) Config Strap Common J1−15 (22) Config Strap Logic Gnd (I) VS 26 V ac Ref (C) J1−16 (22) ARINC 565 ADC or IRS (I) Config Strap No.3 (CS3) J1−17 (22) Gnd/Open (O) PTM Common J1−18 (20) Pressure Xdcr Mdl (O) PTM Pwr Out (−15 V dc) J1−19 (20) Pressure Xdcr Mdl (O) PTM Pwr Out (+15 V dc) J1−20 (20) Pressure Xdcr Mdl GND GND (I) Chassis Ground J1−22 (22) Airframe Ground (I) 115 V ac Return (C) J1−23 (20) Acft ac Ground (I) Remote Light Sensor (LO) J1−24 (22) Acft Rmt Light Sensor (I) Remote Light Sensor (HI) J1−25 (22) Acft Rmt Light Sensor GND Spare GND J1−28 (O) RA Valid Out J1−29 (22) TCAS Computer (I) Source Sel Discrete In J1−31 (22) Gnd/Open (I) Config Strap No.0 (CS0) J1−32 (22) Gnd/Open (I) Config Strap No.1 (CS1) J1−33 (22) Gnd/Open (I) Config Strap No.2 (CS2) J1−34 (22) Gnd/Open (I) Config Strap No.4 (CS4) J1−35 (22) Gnd/Open (I) Config Strap No.5 (CS5) J1−36 (22) Gnd/Open (I) Config Strap No.6 (CS6) J1−37 (22) Gnd/Open (I) Config Strap No.7 (CS7) J1−38 (22) Gnd/Open Page 3−32 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 3−4. 41−Pin VSI/TRA Interconnect Data (cont) I/O Description Connector Pin Connects To (I) dc Ground J1−39 (22) Acft dc Ground (I) 115 V ac Input Power (H) J1−40 (20) Acft 115 V ac Supply (I) Config Strap No.8 (CS8) J1−41 (22) Gnd/Open Notes NOTES: 1. Two wire shielded cable. Tie shields to aircraft dc ground. 2. Three wire shielded cable. Tie shields to aircraft dc ground. 3. Tie chassis ground to aircraft frame. 34−43−23 Page 3−33 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System 41 23 40 22 24 39 21 20 38 25 10 19 37 26 11 18 36 27 12 17 35 16 13 28 14 15 34 29 33 30 31 32 AD−53015@ Figure 3−10. VSI/TRA 41−Pin Connector Layout Page 3−34 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 3−5. 55−Pin VSI/TRA Interconnect Data Connector Pin I/O Description Connects To (I) Secondary ARINC 565 VS (LO) Input J1−1 (22) Cross−Side VSI/TRA (I) Secondary ARINC 565 VS (HI) Input J1−6 (22) Cross−Side VSI/TRA (I) VS dc Rate J1−2 (22) ARINC 575 ADC (I) VS −dc Ref J1−3 (22) ARINC 575 ADC (O) Bootstrap Ref Output J1−4 (22) Cross−Side VSI/TRA (I) VS No.2 Valid Discrete In J1−5 (22) Cross−Side VSI/TRA (I) Second 26 V ac Ref In J1−7 (22) Cross−Side VSI/TRA (I) VS +dc Ref J1−8 (22) ARINC 575 ADC (I) Primary 26 V ac Ref (H) J1−9 (22) ARINC 565 ADC (I) Primary VS (LO) J1−10 (22) ARINC 565 ADC (I) Primary VS (HI) J1−11 (22) ARINC 565 ADC GND GND (I) VS No.1 Valid Discrete In Notes GND GND J1−12 (22) ARINC 565/575 ADC (O) R/C Bootstrap (LO) Output J1−13 (22) Cross−Side VSI/TRA (O) R/C Bootstrap (HI) Output J1−14 (22) Cross−Side VSI/TRA GND (O) Bootstrap Command Out J1−15 GND NC Spare J1−16 (I) Config Strap No.5 (CS5) J1−17 (22) Gnd/Open (I) Config Strap No.6 (CS6) J1−18 (22) Gnd/Open (I) Config Strap No.7 (CS7) J1−19 (22) Gnd/Open (I) Chassis Ground J1−20 (22) Airframe Ground (I) dc Ground J1−21 (22) Acft dc Ground (I) Config Strap No.8 (CS8) J1−22 (22) Gnd/Open (I) Remote Light Sensor (HI) J1−23 (22) (I) Remote Light Sensor (LO) J1−24 (22) GND 34−43−23 Acft Rmt Light Sensor Acft Rmt Light Sensor GND Page 3−35 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 3−5. 55−Pin VSI/TRA Interconnect Data (cont) I/O Description Connector Pin Connects To Notes (I) TCAS ARINC 429 (A) J1−25 (22) TCAS Computer (I) TCAS ARINC 429 (B) J1−44 (22) TCAS Computer GND GND (I) VS No.2 ARINC 429 (A) J1−26 (22) Digital ADC No.2 or PMT No.2 (I) VS No.2 ARINC 429 (B) J1−45 (22) Digital ADC No.2 or PMT No.2 Inertial Reference Sys Inertial Reference Sys GND (I) IRS ARINC 429 (A) J1−27 (22) (I) IRS ARINC 429 (B) J1−46 (22) GND GND GND (O) RA Valid Discrete Out J1−28 (22) TCAS Computer (I) Source Select No.2 J1−29 (22) Gnd/Open Spare J1−30 (I) Source Select No.1 J1−31 (22) Gnd/Open (I) Config Strap No.0 (CS0) J1−32 (22) Gnd/Open (I) Config Strap No.1 (CS1) J1−33 (22) Gnd/Open (I) Config Strap No.2 (CS2) J1−34 (22) Gnd/Open (I) Config Strap No.3 (CS3) J1−35 (22) Gnd/Open (I) Config Strap No.4 (CS4) J1−36 (22) Gnd/Open (I) Config Strap Common J1−37 (22) Config Strap Logic Gnd (I) 115 V ac Return (C) J1−38 (20) Acft ac Ground Spare J1−39 115 V ac Input Power (H) J1−40 (20) Acft 115 V ac Supply Spare J1−41 (I) 5 V Lamp Dimming (HI) J1−42 (22) Acft Lamp Dim Ckt (I) 5 V Lamp Dimming (LO) J1−43 (22) Acft Lamp Dim Ckt (I) VS No.1 ARINC 429 (A) J1−47 (22) (I) Page 3−36 15 Dec 2005 Digital ADC No.1 or PTM No.1 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 3−5. 55−Pin VSI/TRA Interconnect Data (cont) I/O (I) Description VS No.1 ARINC 429 (B) Connector Pin J1−48 Connects To (22) GND GND Digital ADC No.1 or PTM No.1 Notes (O) VSI Valid Output Discrete J1−49 (22) Cross−Side VSI/TRA (O) PTM Pwr Out (−15 V dc) J1−50 (20) Pressure Xdcr Mdl (O) PTM Common J1−51 (20) Pressure Xdcr Mdl (O) PTM Pwr Out (+15 V dc) J1−52 (20) Pressure Xdcr Mdl GND Spare J1−53 Spare J1−54 Spare J1−55 GND NOTES: 1. Two wire shielded cable. Tie shields to aircraft dc ground. 2. Tie chassis ground to aircraft frame. 3. Three wire shielded cable. Tie shields to aircraft dc ground. 34−43−23 Page 3−37 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System 40 41 43 10 24 11 25 44 26 27 45 46 12 13 28 47 29 17 15 34 33 48 52 32 31 30 53 35 16 14 54 36 18 55 37 19 23 38 20 21 22 42 39 51 50 49 AD−53016@ Figure 3−11. VSI/TRA 55−Pin Connector Layout Page 3−38 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System E. Pressure Transducer Module Table 3−6 contains the interconnect data for the ACSS Pressure Transducer Module (PTM). Table 3−6. Pressure Transducer Module Interconnect Data I/O Description Connector Pin Connects To (I) Chassis Ground J1−1 (I) External Reset J1−2 NC J1−3 NC (O) Fault Discrete (22) Notes Airframe Reserved, Test Point J1−4 (I) +15 V dc Input Power J1−5 (22) VSI/TRA (I) Power Ground J1−8 (22) VSI/TRA (I) −15 V dc Input Power J1−11 (22) VSI/TRA VSI/TRA VSI/TRA GND Reserved, Test Point J1−6 (O) ARINC 429 (A) Xmit J1−7 (22) (O) ARINC 429 (B) Xmit J1−13 (22) GND Reserved, Test Point J1−9 Reserved, Test Point J1−10 Reserved, Test Point J1−12 Reserved, Test Point J1−14 Spare J1−15 GND GND NOTES: 1. Tie chassis ground (J1−1) to aircraft frame. 2. Three wire shielded cable. Tie shields to aircraft dc ground. 3. Two wire shielded cable. Tie shields to aircraft dc ground. 34−43−23 Page 3−39 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System F. Transponders Table 3−7 thru Table 3−10 contain the interface information for the ACSS transponders. The transponders use altimetry data supplied in one of the following formats: ARINC 429 (from a digital ADC), ARINC 575, Synchro, or Gillham code. Altimetry data from one of these source types must be connected to the transponder. If a single altimetry source is used, it should be wired to both sets of transponder inputs. All Mode S transponders require a unique 24−bit code (Mode S address) assigned to each aircraft. For aircraft registered in the United States, it is necessary to have a specific address code assigned. These address codes are presently issued by: Federal Aviation Administration FAA Aircraft Registry P.O. Box 25504 Oklahoma City, OK 73125 Tel: (405) 954−3116 Fax: (405) 954−3548 If the aircraft is registered in a country other than the United States, contact the aviation authority of the country in which the aircraft is registered. The Mode S address is usually issued as an 8−digit octal number. To strap the address code correctly, each digit must be converted to a corresponding binary number. (For example: 7 octal = 111 binary, 1 octal = 001 binary.) Once the 8−digit octal code is converted to a 24−bit binary number, the straps (address pins) must be grounded or left open according to this binary number representation. Each binary 0 represents an open strap and each binary 1 represents a grounded strap. An example of an octal code number being converted to a binary number is shown below: Octal address code = 1 2 3 4 5 6 7 0 In binary this number is: (MSB) 001 010 011 100 101 110 111 000 (LSB) (1) XS−950 Data Link Transponder Table 3−7 contains the interconnect data for the XS−950 Data Link Transponder, Part No. 7517800−XXYYY. If additional XS−950 Data Link Transponder installation or operational information is required, refer to Mode S Data Link Transponder System Description and Installation Manual, ACSS Pub. No. A09−3839−001. Page 3−40 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 3−7. XS−950 Data Link Transponder Interconnect Data I/O Description Connector Pin Connects To Notes (I) Mode C Pulse A1 #2 P1A−1A (22) Encoding Altm #2 (I) Mode C Pulse A2 #2 P1A−1B (22) Encoding Altm #2 (I) Mode C Pulse A4 #2 P1A−1C (22) Encoding Altm #2 (I) Mode C Pulse B1 #2 P1A−1D (22) Encoding Altm #2 (I) Mode C Pulse B2 #2 P1A−1E (22) Encoding Altm #2 (I) Mode C Pulse B4 #2 P1A−1F (22) Encoding Altm #2 (I) Mode C Pulse C1 #2 P1A−1G (22) Encoding Altm #2 (I) Mode C Pulse C2 #2 P1A−1H (22) Encoding Altm #2 (I) Mode C Pulse C4 #2 P1A−1J (22) Encoding Altm #2 (I) Mode C Pulse D2 #2 P1A−1K (22) Encoding Altm #2 (I) ARINC 429 (A) COMM A/B P1A−2A Input from ADLP or ARINC 429(A) FMC/GNSS input (22) Airborne Data Link Processor or FMC/GNSS (I) ARINC 429 (B) COMM A/B P1A−2B Input from ADLP or ARINC 429(A) FMC/GNSS input (22) Airborne Data Link GND Processor or FMC/GNSS (I) ARINC 429 (A) COMM C/D P1A−2C Input from ADLP or ARINC 429(A) IRS/FMS/Data Concentrator (22) Airborne Data Link Processor or IRS/FMS/Data Concentrator (I) ARINC 429 (B) Comm C/D Input from ADLP or ARINC 429(A) IRS/FMS/Data Concentrator (22) Airborne Data Link GND Processor or IRS/FMS/Data Concentrator P1A−2D GND GND (O) ARINC 429 (A) COMM C/D P1A−2E Output to ADLP or ARINC 429(A) General output Bus (22) Airborne Data Link Processor (O) ARINC 429 (B) COMM C/D P1A−2F Output to ADLP or ARINC 429(A) General output Bus (22) Airborne Data Link GND Processor Reserved P1A−2G Reserved P1A−2H GND 34−43−23 Page 3−41 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 3−7. XS−950 Data Link Transponder Interconnect Data (cont) I/O (I) Description Connector Pin Reserved P1A−2J Mode C Pulse D4 #2 P1A−2K Reserved P1A−3A Connects To (22) Encoding Altm #2 Notes (O) XPDR Fail Discrete Out #2 P1A−3B (22) Control Panel (I) Cable Delay Prog Top/Bot P1A−3C (22) Gnd/Open (I) Cable Delay Program B P1A−3D (22) Gnd/Open (I) Cable Delay Program A P1A−3E (22) Gnd/Open (I) Cable Delay Prog Common P1A−3F (22) Program Logic Gnd (I) SDI Program A P1A−3G (22) Gnd/Open (I) SDI Program B P1A−3H (22) Gnd/Open (I) SDI Common P1A−3J (22) Program Logic Gnd (I) Mode C Pulse Common #2 P1A−3K (22) Encoding Altm #2 (I) Syn Alt In #1: Coarse X P1A−4A (22) ARINC 565 ADC #1 (I) Syn Alt In #1: Coarse Y P1A−4B (22) ARINC 565 ADC #1 (I) Syn Alt In #1: Coarse Z P1A−4C (22) ARINC 565 ADC #1 (I) Syn Alt In #1: 26 V Ref (H) P1A−4D (22) ARINC 565 ADC #1 (I) Syn Alt In #1: 26 V Ref (C) P1A−4E (22) ARINC 565 ADC #1 (I) Syn Alt In #1: Fine X P1A−4F (22) ARINC 565 ADC #1 (I) Syn Alt In #1: Fine Y P1A−4G (22) ARINC 565 ADC #1 (I) Syn Alt In #1: Fine Z P1A−4H (22) ARINC 565 ADC #1 (I) Syn Alt In #1: Flag P1A−4J (22) ARINC 565 ADC #1 Reserved P1A−4K (22) (I) Max True Airspeed Prog A P1A−5A (22) Gnd/Open (I) Max True Airspeed Prog B P1A−5B (22) Gnd/Open (I) Max True Airspeed Prog C P1A−5C (22) Gnd/Open (I) Max True AS Common P1A−5D (22) Program Logic Gnd (I) ARINC 429 (A) TX Coord P1A−5E (22) TCAS Computer (I) ARINC 429 (B) TX Coord P1A−5F (22) TCAS Computer GND Page 3−42 15 Dec 2005 GND 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 3−7. XS−950 Data Link Transponder Interconnect Data (cont) I/O Description Connector Pin Connects To Notes (O) ARINC 429 (A) XT Coord P1A−5G (22) TCAS Computer (O) ARINC 429 (B) XT Coord P1A−5H TCAS Computer (22) GND GND (I) Air/Gnd Discrete Input #2 P1A−5J (22) Control Panel (I) Air/Gnd Discrete Input #1 P1A−5K (22) Control Panel (I) ARINC 429 (A) FMC #1/General in #2 P1A−6A (22) FMC (I) ARINC 429 (B) FMC #1/General in #2 P1A−6B (22) FMC (I) ARINC 429 (A) ADL Input P1A−6C (22) (I) ARINC 429 (B) ADL Input P1A−6D (22) GND GND GND ARINC 615 Airborne Data Loader ARINC 615 Airborne GND Data Loader (O) ARINC 429 (A) ADL Out P1A−6E (22) ARINC 615 Airborne Data Loader (O) ARINC 429 (B) ADL Out P1A−6F (22) ARINC 615 Airborne GND Data Loader GND (I) ADL Input Link A P1A−6G (22) (I) ARINC 575 (A) ADC In #1 P1A−6H (22) (I) ARINC 575 (B) ADC In #1 P1A−6J (22) ARINC 615 Airborne Data Loader GND ARINC 575 ADC #1 ARINC 575 ADC #1 GND (I) Single/Dual Antenna Prog P1A−6K (22) (I) ARINC 429 (A) Control Data Input Port A P1A−7A (22) Control Panel (I) ARINC 429 (B) Control Data Input Port A P1A−7B (22) Control Panel Reserved P1A−7C Control Data Port Select In P1A−7D (I) Gnd/Open GND (22) 34−43−23 GND Gnd/Open Page 3−43 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 3−7. XS−950 Data Link Transponder Interconnect Data (cont) I/O Description Connector Pin Connects To (I) ARINC 429 (A) Control Data Input Port B P1A−7E (22) Control Panel (I) ARINC 429 (B) Control Data Input Port B P1A−7F (22) Control Panel (I) STBY/ON Discrete Input P1A−7G (22) (I) ARINC 429 (A) ADC #1 In P1A−7H (22) (I) ARINC 429 (B) ADC #1 In P1A−7J (22) GND GND Control Panel GND ARINC 706 ADC #1 ARINC 706 ADC #1 GND Reserved P1A−7K (I) Top Antenna RF Input P1A−71 coax Top Antenna (I) Mode S Adrs Bit A1 (MSB) P1B−1A (22) Gnd/Open (I) Mode S Address Bit A2 P1B−1B (22) Gnd/Open (I) Mode S Address Bit A3 P1B−1C (22) Gnd/Open (I) Mode S Address Bit A4 P1B−1D (22) Gnd/Open (I) Mode S Address Bit A5 P1B−1E (22) Gnd/Open (I) Mode S Address Bit A6 P1B−1F (22) Gnd/Open (I) Mode S Address Bit A7 P1B−1G (22) Gnd/Open (I) Mode S Address Bit A8 P1B−1H (22) Gnd/Open (I) Mode S Address Bit A9 P1B−1J (22) Gnd/Open (I) Mode S Address Bit A10 P1B−1K (22) Gnd/Open (I) Mode S Address Bit A11 P1B−2A (22) Gnd/Open (I) Mode S Address Bit A12 P1B−2B (22) Gnd/Open (I) Mode S Address Bit A13 P1B−2C (22) Gnd/Open (I) Mode S Address Bit A14 P1B−2D (22) Gnd/Open (I) Mode S Address Bit A15 P1B−2E (22) Gnd/Open (I) Mode S Address Bit A16 P1B−2F (22) Gnd/Open (I) Mode S Address Bit A17 P1B−2G (22) Gnd/Open (I) Mode S Address Bit A18 P1B−2H (22) Gnd/Open (I) Mode S Address Bit A19 P1B−2J (22) Gnd/Open Page 3−44 15 Dec 2005 Notes 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 3−7. XS−950 Data Link Transponder Interconnect Data (cont) I/O Description Connector Pin Connects To Notes (I) Mode S Address Bit A20 P1B−2K (22) Gnd/Open (I) Mode S Address Bit A21 P1B−3A (22) Gnd/Open (I) Mode S Address Bit A22 P1B−3B (22) Gnd/Open (I) Mode S Address Bit A23 P1B−3C (22) Gnd/Open (I) Mode S Adrs Bit A24 (LSB) P1B−3D (22) Gnd/Open (I) Mode S Adrs Bit Common P1B−3E (22) Address Logic Gnd Reserved P1B−3F Reserved P1B−3G Functional Test Discrete In P1B−3H (22) Remote Test Switch (O) Alt Comparison Fail Discrete Output P1B−3J (22) Control Panel (O) XPDR Fail Discrete Out #1 P1B−3K (22) (I) Mode C Pulse A1 #1 P1B−4A (22) Encoding Altm #1 (I) Mode C Pulse A2 #1 P1B−4B (22) Encoding Altm #1 (I) Mode C Pulse A4 #1 P1B−4C (22) Encoding Altm #1 (I) Mode C Pulse B1 #1 P1B−4D (22) Encoding Altm #1 (I) Mode C Pulse B2 #1 P1B−4E (22) Encoding Altm #1 (I) Mode C Pulse B4 #1 P1B−4F (22) Encoding Altm #1 (I) Mode C Pulse C1 #1 P1B−4G (22) Encoding Altm #1 (I) Mode C Pulse C2 #1 P1B−4H (22) Encoding Altm #1 (I) Mode C Pulse C4 #1 P1B−4J (22) Encoding Altm #1 (I) Mode C Pulse D2 #1 P1B−4K (22) Encoding Altm #1 (I) ARINC 429 (A) ADC #2 In P1B−5A (22) ARINC 706 ADC #2 (I) ARINC 429 (B) ADC #2 In P1B−5B (22) ARINC 706 ADC #2 (I) NC GND Control Panel GND (I) ARINC 575 (A) ADC #2 In P1B−5C (22) ARINC 575 ADC #2 (I) ARINC 575 (B) ADC #2 In P1B−5D (22) ARINC 575 ADC #2 Airborne Data Link Processor GND (O) ARINC 429 (A) Comm A/B Output to ADLP P1B−5E (22) 34−43−23 GND Page 3−45 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 3−7. XS−950 Data Link Transponder Interconnect Data (cont) I/O Description Connector Pin Connects To (O) ARINC 429 (B) Comm A/B Output to ADLP P1B−5F (22) (I) Extended Squitter disable discrete input P1B−5G (22) (I) Mode S Data Link Program P1B−5H (22) Gnd/Open (I) Antenna Bite Program P1B−5J (22) Gnd/Open (I) Mode C Pulse D4 #1 P1B−5K (22) Encoding Altm #1 (I) ARINC 429 (A) Maintenance Data Input P1B−6A (22) (I) ARINC 429 (B) Maintenance Data Input P1B−6B (22) GND Airborne Data Link GND Processor Gnd/Open GND Onboard Maint Computer System Onboard Maint GND Computer System (O) ARINC 429 (A) Maintenance Data Output P1B−6C (22) (O) ARINC 429 (B) Maintenance Data Output P1B−6D (22) (I) Air Data Source Select Discrete Input P1B−6E (22) Gnd/Open (I) Alt Type Select Prog B P1B−6F (22) Gnd/Open (I) Alt Type Select Prog A P1B−6G (22) Gnd/Open (I) Alt Type Select Common P1B−6H (22) Program Logic Gnd Reserved P1B−6J GND Onboard Maint Computer System Onboard Maint GND Computer System (I) Mode C Pulse Common #1 P1B−6K (22) Encoding Altm #1 (I) Syn Alt In #2: Coarse X P1B−7A (22) ARINC 565 ADC #2 (I) Syn Alt In #2: Coarse Y P1B−7B (22) ARINC 565 ADC #2 (I) Syn Alt In #2: Coarse Z P1B−7C (22) ARINC 565 ADC #2 (I) Syn Alt In #2: 26 V Ref (H) P1B−7D (22) ARINC 565 ADC #2 (I) Syn Alt In #2: 26 V Ref (C) P1B−7E (22) ARINC 565 ADC #2 (I) Syn Alt In #2: Fine X P1B−7F (22) ARINC 565 ADC #2 (I) Syn Alt In #2: Fine Y P1B−7G (22) ARINC 565 ADC #2 (I) Syn Alt In #2: Fine Z P1B−7H (22) ARINC 565 ADC #2 (I) Syn Alt In #2: Flag P1B−7J (22) ARINC 565 ADC #2 Reserved P1B−7K Page 3−46 15 Dec 2005 Notes 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 3−7. XS−950 Data Link Transponder Interconnect Data (cont) I/O Description Connector Pin Connects To (I) Bottom Antenna RF Input P1B−71 coax Bottom Antenna (I) 115 V ac Input Power (H) P1C−1 (20) Acft 115 V ac Sup Spare P1C−2 (I) +28 V dc Return (L) P1C−3 (16) Acft dc Ground (I) XPDR OFF (NO) P1C−4 Spare P1C−5 Notes NC (O) Fan +28 V dc P1C−6 (22) Fan + (I) 115 V ac Return (L) P1C−7 (20) Acft ac Ground (I) Signal Ground P1C−8 (16) Acft ac Ground (O) Fan Return (L) P1C−9 (I) +28 V dc Input Power P1C−10 (16) +28V Acft Power (I) Chassis Ground P1C−11 (16) Airframe Ground Fan − I/O Suppression Pulse P1C−12 coax L−Band Suppression Bus I/O Suppression Pulse P1C−13 coax L−Band Suppression Bus The interconnect data that follows is for the ARINC 615 Portable Data Loader (PDL) connector J1 located on the front panel of the transponder. The transponder’s operational software can be updated (upload to transponder) through this connector. In addition, the contents of the fault log can be extracted for analysis and troubleshooting (download from transponder). The 53 pin front panel PDL connector contains both an ARINC 429 high speed bus interface for connection to an ARINC 615 PDL, and an RS−232 bus interface for connection to a personal computer (PC) through a standard serial port. Only the pins used by the transponder are shown. The PDL standard interface cable should be 10 feet in length (3 meters) and be terminated with a connector type MS27473T−18A−53S at the data loader end and connector type MS27473T−18A−53P at the transponder end. (I) ARINC 429 (A) PDL Input J1−1 (22) ARINC 615 PDL (I) ARINC 429 (B) PDL Input J1−2 (22) ARINC 615 PDL (I) Bus Shield J1−5 (22) Chassis Ground (O) ARINC 429 (A) PDL Out J1−8 (22) ARINC 615 PDL (O) ARINC 429 (B) PDL Out J1−9 (22) ARINC 615 PDL (O) Bus Shield J1−16 (22) Chassis Ground PDL Link A J1−18 (22) ARINC 615 PDL PDL Link B J1−19 (22) ARINC 615 PDL 34−43−23 Page 3−47 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 3−7. XS−950 Data Link Transponder Interconnect Data (cont) I/O Description Connector Pin Connects To Notes (O) 115 V ac Power Out (H) J1−20 (22) ARINC 615 PDL (O) Chassis Ground J1−21 (22) ARINC 615 PDL (O) 115 V ac Power Out (C) J1−22 (22) ARINC 615 PDL (O) +28 V dc Power Out J1−37 (22) ARINC 615 PDL (O) +28 V dc Return J1−38 (22) ARINC 615 PDL (I) J1−40 (22) RS−232 Interface J1−41 (22) RS−232 Interface Logic Common (Gnd) J1−48 (22) RS−232 Interface Logic Common (Gnd) J1−49 (22) RS−232 Interface (I) PDL Function Discrete #1 J1−50 (22) ARINC 615 PDL (I) PDL Function Discrete #2 J1−51 (22) ARINC 615 PDL (I) PDL Function Discrete #3 J1−52 (22) ARINC 615 PDL (I) PDL Function Discrete #4 J1−53 (22) ARINC 615 PDL RS−232 PDL Input (O) RS−232 PDL Output NOTES: 1. 2. 3. 4. 5. 6. 7. Two wire shielded cable. Tie shields to aircraft dc ground. Tie chassis ground to aircraft frame. Two wire shielded cable. Tie shield to pin 5. Two wire shielded cable. Tie shield to pin 16. The 115 V ac (H) and 115 V ac (C) should be shielded or twisted and shielded with an insulating jacket over the shield. The shield should be connected to chassis ground (pin 21). There is a +28 V dc output available from the transponder, however most ARINC 615 Data Loaders do not have the capability to operate from 28 Volt power. If the RS−232 interface is going to be used, these pins should be connected to a standard serial port (usually a 9−pin D connector). Page 3−48 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System (2) RCZ−852 Diversity Mode S Transponder Table 3−8 contains the interconnect data for the RCZ−852 Diversity Mode S Transponder, Part No. 7510700−850/−951. Prior to final installation of the transponder mounting tray, the strap assembly, Figure 3−12, located on the back of each mounting tray must be programmed to incorporate the aircraft Mode S address and the desired options. Information for programming the strap assembly is contained in Table 3−9 and Table 3−10. Programming of the strap assembly consists of removing or installing a string of jumper wires that provide a 48−bit serial data word for encoding the system configuration. In Table 3−10, the output is grounded if the corresponding W* (jumper wire) is installed for a particular bit, and open if the jumper wire is cut out. The strap assembly is shipped with all 48−bit jumpers installed. If a jumper is inadvertently cut out or a parameter change requires a jumper to be reinstalled, a suitable piece of AWG 24 bus wire should be used. Table 3−8. RCZ−852 Diversity Mode S Transponder Interconnect Data I/O Description Connector Pin (O) XPDR +28 V FAN RTN J1−1 NC (O) XPDR +28 V FAN PWR J1−2 NC I/O MUT SUP (P) J1−3 (24) GND GND Connects To Notes L−Band Suppression Bus Spare J1−4 Spare J1−5 Spare J1−6 (I) XPDR +28V RTN J1−7 (22) Acft dc Ground (I) XPDR +28V PWR J1−8 (22) Acft 28 V Supply (I) XPDR +28V PWR J1−9 (22) Acft 28 V Supply Spare J1−10 PROGRAM ENA (PO) J1−11 NC J1−12 NC (I) (O) XPDR TX RS232 Reserved J1−13 Reserved J1−14 Reserved J1−15 Reserved J1−16 (I) dc GROUND J1−17 (22) Acft dc Ground (I) dc GROUND J1−18 (22) Acft dc Ground 34−43−23 Page 3−49 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 3−8. RCZ−852 Diversity Mode S Transponder Interconnect Data (cont) I/O Description Connector Pin Connects To (I) dc GROUND J1−19 (22) Acft dc Ground (I) XPDR +28V RTN J1−20 (22) Acft dc Ground (I) dc GROUND J1−21 (22) Acft dc Ground Spare J1−22 (O) XPDR VALID (PO) J1−23 NC (I) XPDR RX RS232 J1−24 NC (O) PROGRAM +15V J1−25 NC (O) XPDR to TCAS 429 (A) J1−26 (22) GND (O) XPDR to TCAS 429 (B) J1−27 (22) GND TCAS Computer TCAS Computer GND Notes GND (O) XPDR to DLP A/B 429 (A) J1−28 (22) Airborne Data Link Processor (O) XPDR to DLP A/B 429 (B) J1−29 (22) Airborne Data Link Processor Airborne Data Link Processor Airborne Data Link Processor GND (O) XPDR to DLP C/D 429 (A) J1−30 (22) (O) XPDR to DLP C/D 429 (B) J1−31 (22) GND GND GND (I) ADC1 to XPDR 429/575A J1−32 (22) ARINC 429 or 575 ADC #1 (I) ADC1 to XPDR 429/575B J1−33 (22) ARINC 429 or 575 ADC #1 GND GND (I) CTL1 to XPDR 429 (A) J1−34 (22) Control Panel (I) CTL1 to XPDR 429 (B) J1−35 (22) Control Panel GND Reserved J1−36 Reserved J1−37 Reserved J1−38 Reserved J1−39 Page 3−50 15 Dec 2005 GND 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 3−8. RCZ−852 Diversity Mode S Transponder Interconnect Data (cont) I/O Description Connector Pin Connects To Notes (I) TCAS to XPDR 429 (A) J1−40 (22) TCAS Computer (I) TCAS to XPDR 429 (B) J1−41 (22) TCAS Computer GND GND (I) DLP A/B to XPDR 429 (A) J1−42 (22) Airborne Data Link Processor (I) DLP A/B to XPDR 429 (B) J1−43 (22) Airborne Data Link Processor Airborne Data Link Processor Airborne Data Link Processor ARINC 429/575 Digital ADC ARINC 429/575 Digital ADC GND (I) DLP C/D to XPDR 429 (A) J1−44 (22) (I) DLP C/D to XPDR 429 (B) J1−45 (22) GND (I) ADC2 to XPDR 429/575A J1−46 (22) (I) ADC2 to XPDR 429/575B J1−47 (22) GND GND GND GND (I) CTL2 to XPDR 429 (A) J1−48 (22) Control Panel (I) CTL2 to XPDR 429 (B) J1−49 (22) Control Panel GND GND (O) XPDR to CTL 429 (A) J1−50 (22) Control Panel 2, 3 (O) XPDR to CTL 429 (B) J1−51 (22) Control Panel 2, 3 GND GND Reserved J1−52 (I) ENC ALT1 C1 (N) J1−53 (24) Encoding Altm #1 (I) ENC ALT1 C2 (N) J1−54 (24) Encoding Altm #1 (I) ENC ALT1 C4 (N) J1−55 (24) Encoding Altm #1 (I) ENC ALT1 D2 (N) J1−56 (24) Encoding Altm #1 (I) ENC ALT1 D4 (N) J1−57 (24) Encoding Altm #1 (I) ENC ALT1 A1 (N) J1−58 (24) Encoding Altm #1 (I) ALT COMP ENA (NO) J1−59 (24) Gnd/Open (I) ALT SRC SEL2 (NO) J1−60 (24) Gnd/Open 34−43−23 Page 3−51 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 3−8. RCZ−852 Diversity Mode S Transponder Interconnect Data (cont) I/O (I) Description Connector Pin Connects To CTL SRC SEL1 (NO) J1−61 (24) Reserved J1−62 Reserved J1−63 (I) FMS to XPDR 429 (A) J1−64 (22) (I) FMS to XPDR 429 (B) J1−65 (22) GND Notes Gnd/Open Flt Management Sys Flt Management Sys GND Reserved J1−66 (I) ENC ALT1 A2 (N) J1−67 (24) Encoding Altm #1 (I) ENC ALT1 A4 (N) J1−68 (24) Encoding Altm #1 (I) ENC ALT1 B1 (N) J1−69 (24) Encoding Altm #1 (I) ENC ALT1 B2 (N) J1−70 (24) Encoding Altm #1 (I) ENC ALT1 B4 (N) J1−71 (24) Encoding Altm #1 (I) XPDR STANDBY (NO) J1−72 (24) Control Panel (I) SQUAT SWITCH 1 (NO) J1−73 (24) Control Panel or Acft Squat Switch (I) XPDR OFF (NO) J1−74 (I) SQUAT SWITCH 2 (NO) J1−75 Control Panel or Acft Squat Switch XPDR TX RCB (P) J1−76 NC XPDR TX RCB (N) J1−77 NC XPDR RX RCB (P) J1−78 NC XPDR RX RCB (N) J1−79 NC (I) ENC ALT2 C1 (N) J1−80 (24) Encoding Altm #2 (I) ENC ALT2 C2 (N) J1−81 (24) Encoding Altm #2 (I) ENC ALT2 C4 (N) J1−82 (24) Encoding Altm #2 (I) ENC ALT2 D2 (N) J1−83 (24) Encoding Altm #2 (I) ENC ALT2 D4 (N) J1−84 (24) Encoding Altm #2 (I) ENC ALT2 A1 (N) J1−85 (24) Encoding Altm #2 Reserved J1−86 Reserved J1−87 Reserved J1−88 Page 3−52 15 Dec 2005 NC (24) 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 3−8. RCZ−852 Diversity Mode S Transponder Interconnect Data (cont) I/O Description Reserved Connector Pin Connects To Notes J1−89 (O) XPDR STRAP +5V J1−90 (26) Strap Board (Red) (O) XPDR STRAP CLK (N) J1−91 (26) Strap Board (Blue) (O) XPDR STRAP LOAD (N) J1−92 (26) Strap Board (Orn) (I) XPDR STRAP DATA (P) J1−93 (26) Strap Board (Wht) (I) ENC ALT2 A2 (N) J1−94 (24) Encoding Altm #2 (I) ENC ALT2 A4 (N) J1−95 (24) Encoding Altm #2 (I) ENC ALT2 B1 (N) J1−96 (24) Encoding Altm #2 (I) ENC ALT2 B2 (N) J1−97 (24) Encoding Altm #2 (I) ENC ALT2 B4 (N) J1−98 (24) Encoding Altm #2 (O) XPDR ACTIVE (NO) J1−99 (24) Antenna Switching Relay (O) XPDR VALID (NO) J1−100 (24) Reserved Control Panel J1−101 (O) ALT VALID (NO) J1−102 (24) Control Panel (O) XPDR STRAP GND J1−103 (26) Strap Board (Blk) (O) XPDR STRAP PGM (N) J1−104 (26) Strap Board (Grn) (O) XPDR STRAP PGM (P) J1−105 (26) Strap Board (Yel) − POLARIZATION PIN J1−106 NC (I) Bottom Antenna RF Input J2 coax Bottom Antenna (I) Top Antenna RF Input J3 coax Top Antenna NOTES: 1. Use AWG−24 single conductor, shielded wire. Attach shield to ground loop E1 or E2 on back of mounding tray. 2. Two wire shielded cable. Tie shields to ground loop E1 or E2 located on back of mounting tray. 3. This ARINC 429 output is required on some Collins Control Panels that require a feedback loop to make sure the transponder is working properly. 4. Refer to interface descriptions in Table 4−9. 5. This output is connected only if the control panel has an ALT FAIL input function. 34−43−23 Page 3−53 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 3−9. Strap Assembly Strap Assignments Strap Number Strap Number Name NAME W1 System Position B0 W25 Mode S Address B16 W2 System Position B1 W26 Mode S Address B17 W3 Parity W27 Mode S Address B18 W4 Parity W28 Mode S Address B19 W5 Squat Switch Polarity W29 Mode S Address B20 W6 Maximum Airspeed B0 W30 Mode S Address B21 W7 Maximum Airspeed B1 W31 Mode S Address B22 W8 Maximum Airspeed B2 W32 Mode S Address B23 W9 Mode S Address B0 W33 Altitude Source B0 W10 Mode S Address B1 W34 Altitude Source B1 W11 Mode S Address B2 W35 DLP Installed W12 Mode S Address B3 W36 TCAS II Installed W13 Mode S Address B4 W37 Antenna Cable Installation B0 W14 Mode S Address B5 W38 Antenna Cable Installation B1 W15 Mode S Address B6 W39 TCAS TA Display Enable W16 Mode S Address B7 W40 TCAS I Installed W17 Mode S Address B8 W41 Altitude Resolution W18 Mode S Address B9 W42 Reserved W19 Mode S Address B10 W43 Reserved W20 Mode S Address B11 W44 Reserved W21 Mode S Address B12 W45 Reserved W22 Mode S Address B13 W46 Reserved W23 Mode S Address B14 W47 Reserved W24 Mode S Address B15 W48 Reserved NOTE: The strap logic levels are as follows: GND = Jumper wire installed (Uncut) OPEN = Jumper wire not installed (Cut) Page 3−54 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System W1 W26 W14 W39 W27 W15 W3 W40 W28 W16 W4 W41 W29 W17 W5 W30 W18 9 16 81 14 9 16 81 W42 16 W38 16 W13 W25 W37 W6 W20 W8 W45 W33 81 W21 9 16 W32 W7 W44 W19 9 16 W31 81 W43 W9 W10 W34 W22 W47 W35 W23 W11 W48 W36 W24 W12 W46 W1 DETAIL A E8 E7 E6 E4 E3 E2 E1 W49 JUMPER WIRE (50 REQD) SEE DETAIL A W2 W50 AD−15341−R1@ Figure 3−12. Strap Assembly Table 3−10. Strap Assembly Programming Instructions Strap Number W1 W2 Functional Description SYSTEM (SIDE) POSITION: (B0, B1) The System (Side) Position straps define which system position the transponder is located at. Normal practice is to designate the captain’s or pilot’s system as Side 1, the copilot’s system as Side 2, and the engineer’s, center, or backup system as Side 3. The straps are defined as follows: Strap Number W1 W2 Definition Gnd Open Gnd Open W3 W4 Gnd Gnd Open Open Side 1 Side 2 Side 3 Reserved PARITY The Parity straps are used to make sure the strap data is valid. Straps W3 and W4 are parity bits and must be programmed as follows: After all other straps have been programmed, count the number of Gnd (Uncut) straps in positions W1, W2 and W5 thru W48. If the number of uncut straps is even, cut strap W3. If the number of uncut straps is odd, cut strap W4. NOTES: 1. To have correct parity, either jumper W3 or W4 has to be cut, but not both. 2. If parity is invalid, the transponder fails the Power−On Self−Test (POST) and discontinues operation. 34−43−23 Page 3−55 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 3−10. Strap Assembly Programming Instructions (cont) Strap Number Functional Description W5 SQUAT SWITCH POLARITY The Squat Switch Polarity strap is used to indicate the logic or signal sense of the aircraft squat switch on ground condition. If the squat switch is closed when the aircraft is on the ground, jumper W5 must be installed (Uncut). If the squat switch is closed when the aircraft is airborne, jumper W5 must be Open (Cut). W6 W7 W8 AIRCRAFT MAXIMUM TRUE AIRSPEED RANGE: (B0, B1, B2) The Aircraft Maximum True Airspeed Range straps are used to define the aircraft’s maximum airspeed capability. The straps are defined as follows: Strap Number W6 W7 W8 Definition Gnd Open Gnd Open Gnd Open Gnd Open Gnd Gnd Open Open Gnd Gnd Open Open Gnd Gnd Gnd Gnd Open Open Open Open No Data Available 75 Knots or Less 76 to 150 Knots 151 to 300 Knots 301 to 600 Knots 601 to 1200 Knots Over 1200 Knots Not Assigned W9 thru W32 (LSB − MSB) MODE S ADDRESS: (B0 THRU B23) The Mode S Address is a unique 24−bit code assigned to each aircraft. Straps W9 thru W32 are used to program this 24−bit binary number. The straps must be set according to this binary number representation. Each binary 1 represents a Cut strap and each binary 0 represents an Uncut strap. Strap W9 represents the least significant digit of the binary number and strap W32 represents the most significant digit of the binary number. The initial board condition with all jumpers is a 0 address. NOTE: An address of all 0’s or all 1’s is an illegal address, and can cause the aircraft to be invisible to TCAS II equipped aircraft in flight. Never use an illegal address for an installed system. W33 W34 ALTITUDE SOURCE: (B0, B1) The Altitude Source straps select the type of altitude information used by the transponder. Altitude information can be generated by an encoding altimeter in the form of Gray aka Gillham code, or by a digital Air Data Computer. The straps are defined as follows: Strap Number W33 W34 Definition Gnd Gnd Gillham Gray Code Altitude Source Open Gnd ARINC 429 Altitude Source Gnd Open ARINC 575 Altitude Source Open Open RSB Altitude Source NOTE: The RSB altitude source is a valid selection only when the transponder receives tuning information from an RCB bus. Page 3−56 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 3−10. Strap Assembly Programming Instructions (cont) Strap Number Functional Description W35 DLP INSTALLED The DLP Installed strap specifies whether the transponder is connected to an Airborne Data Link Processor system. The strap is selected as follows: Gnd = DLP is not installed Open = DLP is installed W36 TCAS II INSTALLED The TCAS II Installed strap specifies whether the transponder is connected to a TCAS II system. The strap is selected as follows: Gnd = TCAS II is not installed Open = TCAS II is installed NOTE: If both TCAS II and TCAS I (strap W40) are set (Grounded), the transponder will default to TCAS II operation. Both straps should not be cut. W37 W38 ANTENNA CABLE INSTALLATION: (B0, B1) The Antenna Cable Install straps are used to set the system for either a single (bottom) antenna installation, or a diversity installation. In the diversity installation, the straps adjust for the difference in RF propagation times through the upper and lower antenna cables which occur because of their dissimilar lengths. The antenna cable delay is selected as follows: Strap Number W37 W38 Definition Gnd Gnd Single (bottom) Antenna Installation Open Gnd Top > Bottom Cable Length, Differential Delay >40 nanoseconds Gnd Open Bottom > Top Cable Length, Differential Delay >40 nanoseconds Open Open Differential Delay is <40 nanoseconds NOTE: The differential delay is equal to two times the length (in feet) of the difference between the top and bottom antenna cable lengths, times the characteristic delay (nanoseconds / feet) of the cable type in use. W39 TCAS TA DISPLAY ENABLE The TCAS Display Enable strap allows the TCAS display to be either tunable or fixed. The strap is not processed by the transponder, but is used by a RMU when an RSB tuning source is selected. The strap is not used by ARINC tuning sources. The strap definition is as follows: Gnd = TA Display is tunable (ON / OFF / AUTO POP−UP) modes selectable Open = TA Display is not selectable (AUTO POP−UP mode only) W40 TCAS I INSTALLED The TCAS I Installed strap specifies whether the transponder is connected to a TCAS I system. The strap is selected as follows: Gnd = TCAS I is not installed Open = TCAS I is installed NOTE: If both TCAS I and TCAS II (strap W36) are set (Grounded), the transponder will default to TCAS II operation. Both straps should not be cut. 34−43−23 Page 3−57 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 3−10. Strap Assembly Programming Instructions (cont) Strap Number W41 Functional Description ALTITUDE RESOLUTION The Altitude Resolution strap allows the transponder output to the TCAS (label 203) to be either 100 foot resolution or 1 foot resolution. The strap definition is as follows: Gnd = 1 Foot Resolution Open = 100 Foot Resolution NOTE: Most ARINC altitude inputs require 1 foot resolution. W42 thru W48 W49 W50 RESERVED FUNCTION These straps are not used. The jumpers should be installed (Uncut). Jumpers W49 and W50 are not part of the 48−bit serial data pulse train and are not used on RCZ−852 Transponder installations. The jumpers should be installed (Uncut). Page 3−58 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System LOADING/GRADIENT SPECIFICATIONS 1. General This section contains the loading and gradient specifications for the input and output signals of each component of the TCAS 3000 system. 2. Loading and Gradient Specifications Component Table No. TCAS 3000 Computer Unit Loading/Gradient Specifications Table 4−1 ACSS Dual Mode S Control Panel Loading/Gradient Specifications Table 4−2 ACSS ATCRBS−Mode S Control Panel Loading/Gradient Specifications Table 4−3 Gables Control Panel Loading/Gradient Specifications Table 4−4 41−Pin VSI/TRA Loading/Gradient Specifications Table 4−5 55−Pin VSI/TRA Loading/Gradient Specifications Table 4−6 Pressure Transducer Module Loading/Gradient Specifications Table 4−7 XS−950 Data Link Transponder Loading/Gradient Specifications Table 4−8 RCZ−852 Diversity Mode S Transponder Loading/Gradient Specifications Table 4−9 34−43−23 Page 4−1 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−1. TCAS 3000 Computer Unit Loading/Gradient Specifications Connector Pin Designation Functional Description TCAS Computer Unit Right Middle Plug (RMP) RMP−1A, RMP−1B, RMP−1C, RMP−1D Reserved Discrete Outputs RMP−1E TA Display Enable Discrete Output (NO) This output is a ground/open type discrete used by the weather radar display to place the radar in standby mode. A ground on this pin enables the weather radar display. RMP−1F Corrective Aural Advisory Discrete Output (NO) This aural advisory discrete output is a ground/open type discrete used to control external equipment that generate tones to accompany TCAS advisories. The output is active whenever a corrective advisory (RA that requires a corrective maneuver) is issued. The output remains active for the duration of the synthesized voice unless it is cancelled by the cancel discrete at RMP−3D. Only one aural advisory is active at a time. The corrective discrete and preventative discrete at RMP−1K are mutually exclusive. The active state is ground and the inactive state is open. This pin is reserved on the −XX001 TCAS CU. RMP−1G, RMP−1H Reserved RMP−1J Climb Inhibit No. 1 Discrete Input (NO) This input is a ground/open type discrete used to provide information to the TCAS CU whether to assume the aircraft cannot achieve a climb rate of 1500 feet per minute (FPM). The climb inhibit discrete inputs are designed in pairs (No. 1 and No. 2 at RMP−13G, or No. 3 at RBP−5J and No. 4 at RBP−5K) but can be wired as a single input or in conjunction with other aircraft operations to achieve airframe customization of the climb inhibit feature. The 1500 FPM climb inhibit function is assumed whenever No. 1 and No. 2 are ground or No. 3 and No. 4 are ground. RMP−1K Preventive Aural Advisory Discrete Output (NO) Same as RMP−1F, except this discrete is active whenever a preventative advisory (RA that directs the flight crew to avoid certain maneuvers or maintain flight path) is issued. RMP−2A Traffic Aural Advisory Discrete Output (NO) Same as RMP−1F, except this discrete is active during a traffic advisory when information is being given to the flight crew regarding other aircraft in the immediate vicinity. No suggested maneuver is issued. This output is inhibited if either the corrective or preventative output is active. RMP−2B, RMP−2C Reserved RMP−2D Advisory/Announce Common This is the return line for the aural and visual advisory discrete outputs. Page 4−2 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−1. TCAS 3000 Computer Unit Loading/Gradient Specifications (cont) Connector Pin Designation RMP−2E Functional Description Spare Pin RMP−2F, 2G 8−Ohm Audio Output: (RMP−2F [HI], RMP−2G [LO]) This is a synthesized voice output supplied by the TCAS computer unit. Its level is programmable up to 4 Watts into an 8−ohm speaker. All aural traffic and resolution advisories are announced over this output. See RBP−7A for audio level programming. RMP−2H, 2J Radio Altimeter No. 1 ARINC 552/Analog Input: (RMP−2H [HI], RMP−2J [LO]) Normal aircraft configurations include either two digital or two analog radio altimeter sources. The TCAS computer unit attempts to establish which type is present in order to obtain data from one of the two available sources. TCAS first checks the radio altimeter No. 1 valid flag at RMP−2K. If No. 1 is not valid then No. 2 valid is checked at RBP−3C. If neither are valid then TCAS checks digital source No. 1 for valid data on the ARINC 429 bus at RMP−13H and RMP−13J. If none of the above are valid then the TCAS checks the digital source No. 2 for valid data on the ARINC 429 bus at RBP−3D and RBP−3E. This process is repeated until a valid flag or data is detected. Until a valid source is found, the TCAS computer unit inhibits all surveillance, CAS, and TA/RA display functions, records failures in maintenance memory, and sets the TCAS system status discrete output at RMP−13K to invalid. The TCAS computer unit uses radio altitude to inhibit advisories and aural annunciation when in close proximity to the ground. This analog input No. 1, as well as analog input No. 2, can accept data as a dc voltage from several types of radio altimeters. The type of radio altimeter is selected using the program pins RMP−12B and RMP−12H thru RMP−12K. RMP−2K Radio Altimeter No. 1 Valid Input (PO) See RMP−2H. A valid condition is greater than 18.5 V dc. An invalid is open circuit. RMP−3A Corrective Visual Advisory Discrete Output (NO) The visual advisory discrete outputs are ground/open type discretes used to operate the annunciator lights on the displays. This output is activated whenever a corrective aural advisory is issued. The output remains active for the duration of the advisory unless cancelled by the cancel discrete at RMP−3D. Only one visual advisory is active at a time. The active state is ground and the inactive state is open. RMP−3B Preventive Visual Advisory Discrete Output (NO) Same as RMP−3A, except this discrete is activated whenever a preventative aural advisory is issued. RMP−3C Traffic Visual Advisory Discrete Output (NO) Same as RMP−3A, except this discrete is active during a traffic advisory. RMP−3D Cancel Discrete Input (NO) This input discrete provides a means of canceling aural and visual alerts. It should be connected to a cancel button (momentary ground type), if used. Groundprox/Windshear has priority over the cancel button. Open is the inactive state and a momentary ground (less than 50 ohms) produces the active state, canceling any active aural or visual alert. 34−43−23 Page 4−3 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−1. TCAS 3000 Computer Unit Loading/Gradient Specifications (cont) Connector Pin Designation RMP−3E RMP−3F, 3G Functional Description Spare Pin 600−Ohm Audio Output: [RMP−3F (HI), RMP−3G (LO)] This is a synthesized voice output supplied by the TCAS computer unit. Its level is programmable up to 80 milliwatts into a 600−ohm audio distribution system. All aural traffic and resolution advisories are annunciated over this output. See RBP−7A for audio level programming. RMP−3H Spare Pins RMP−3J, RMP−3K Reserved for future use. RMP−4A Reserved for future use. RMP−4B Reserved for future use. RMP−4C Reserved for future use. RMP−4D Shield Ground Reserved for future use. RMP−4E Reserved for future use. RMP−4F Reserved for future use. RMP−4G Reserved for future use. RMP−4H Reserved for future use. RMP−4J Reserved for future use. RMP−4K Attitude Valid Discrete Input Reserved for future use. Page 4−4 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−1. TCAS 3000 Computer Unit Loading/Gradient Specifications (cont) Connector Pin Designation Functional Description RMP−5A Reserved for future use. RMP−5B Reserved for future use. RMP−5C Reserved for future use. RMP−5D Reserved for future use. RMP−5E ADS−B Program Input Intruder File Enable RMP−5F ADS−B Program Input GP Bus enable RMP−5G ADS−B Program Input Future Spare RMP−5H Reserved for future use. RMP−5J Reserved for future use. RMP−5K Air Ground Discrete Input (NO): (Weight−On−Wheels) This discrete input to the TCAS computer unit indicates the status of the Air/Ground or Weight−On−Wheels (WOW) switch. TCAS filters this input to make sure it remains in a steady state a minimum of 4 seconds before an Air/Ground transition is recorded. An open indicates the aircraft is airborne and a ground indicates the aircraft is on the ground. Inputs should be diode isolated from each other. RMP−6A, 6B ARINC 429 Performance Limit Input: [RMP−6A (A), RMP−6B (B)] This input is provided for future applications to receive climb rate performance limit information from an external device such as a Flight Management Computer. RMP−6C Magnetic Heading Valid Discrete Input Reserved for future use. RMP−6D Performance Limit Discrete Input (NO) This input provides the TCAS computer unit with an input from the Flight Management Computer (or equivalent) which indicates when the aircraft cannot achieve a 1500 FPM climb rate. When this input is ground, the climb rate is not limited and no action is needed by the TCAS computer unit. When this input is open, the climb rate is limited when the aircraft is above the value set by the altitude limit program pins (RMP−6E thru RMP−6J). 34−43−23 Page 4−5 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−1. TCAS 3000 Computer Unit Loading/Gradient Specifications (cont) Connector Pin Designation Functional Description RMP−6E 2000 FT Altitude Limit Program Pin (NO) This pin, along with pins RMP−6F thru RMP−6J, select the “can’t climb” altitude in 2,000−foot increments up to 62,000 feet. This is the altitude the aircraft is not able to achieve a 0.25 G vertical acceleration to a 1500 FPM climb rate for an altitude gain of 750 feet above a certain altitude under all circumstances. The “can’t climb” altitude is selected by connecting jumper wires from altitude limit program pins to the program common pin (RMP−6K). RMP−6F 4000 FT Altitude Limit Program Pin (NO) See RMP−6E. RMP−6G 8000 FT Altitude Limit Program Pin (NO) See RMP−6E. RMP−6H 16000 FT Altitude Limit Program Pin (NO) See RMP−6E. RMP−6J 32000 FT Altitude Limit Program Pin (NO) See RMP−6E. RMP−6K Program Common See RMP−6E. RMP−7A, 7B ARINC 429 Magnetic Heading/Attitude Input: [RMP−7A (A), RMP−7B (B)] Reserved for future use RMP−7C, 7D ARINC 429 TA/RA Display No. 1 Output: [RMP−7C (A), RMP−7D (B)] This is one of two ARINC 429 high speed bus outputs that supplies data to the TA/RA display such as a VSI/TRA or EFIS. The other output (TA/RA Display No. 2) is at RMP−7G and −7H. The TA/RA Display No. 1 outputs are also connected to the front (PDL) connector, which is used to supply display information to maintenance displays. See J1−33 and J1−34. RMP−7E TA/RA Display No. 1 Status Discrete Input (NO) Two display status discrete inputs are provided by the TCAS computer unit at RMP−7E (TA/RA Display No. 1) and RMP−7J (TA/RA Display No. 2). A ground on either of these inputs is interpreted by TCAS to mean the display associated with that input is operating normally and is capable of displaying the TA/RA information, and that its data bus is active. An open indicates the inability of the display to present advisories or indicates its data bus is inactive. RMP−7F Spare Pin RMP−7G, 7H ARINC 429 TA/RA Display No. 2 Output: [RMP−7G (A), RMP−7H (B)] See RMP−7C and −7D. RMP−7J TA/RA Display No. 2 Status Discrete Input (NO) See RMP−7E. RMP−7K Spare Pin Page 4−6 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−1. TCAS 3000 Computer Unit Loading/Gradient Specifications (cont) Connector Pin Designation Functional Description RMP−8A, 8B ARINC 429 Data Loader Input: [RMP−8A (A), RMP−8B (B)] These pins are used when the TCAS computer unit is communicating with an ARINC 603 or 615 airborne data loader (ADL) through the rear ARINC 600 connector. The data loader programs the program memory in the TCAS computer unit per the data loader function specified. The ADL and portable data loader (PDL) ARINC 429 inputs have separate receiver busses to allow for simultaneous connection of the ADL and PDL. These pins are also connected to the front (PDL) connector on the front of the unit. See J1−1 and J1−2. RMP−8C,8D TA/RA Display Control ARINC 429 Input #1: [RMP−8C (A), RMP−8D (B)] RMP−8E, 8F ARINC 429 Bus Input: [RMP−8E (A), RMP−8F (B)] Reserved for future use. RMP−8G, 8H TA/RA Display Control ARINC 429 Input #2: [RMP−8G (A), RMP−8H (B)] RMP−8J, 8K ARINC 429 ADS−B No. 2 Input: [RMP−8J (A), RMP−8K (B)] Reserved for future use. RMP−9A, 9B ARINC 429 Data Loader Output: [RMP−9A (A), RMP−9B (B)] These pins are used when the TCAS computer unit is communicating with an ARINC 603 or 615 airborne data loader (ADL) through the rear ARINC 600 connector. This connection is used to transmit data to the ADL during data loading operations. These pins are also connected to the front (PDL) connector on the front of the unit. See J1−8 and J1−9. RMP−9C, 9D ARINC 429 ADS−B No. 1 Output: [RMP−9C (A), RMP−9D (B)] Reserved for future use. RMP−9E, 9F ARINC 429 Bus Output: [RMP−9E (A), RMP−9F (B)] Reserved for future use. RMP−9G, 9H ARINC 429 Bus Output: [RMP−9G (A), RMP−9H (B)] Reserved for future use. RMP−9J, 9K ARINC 429 ADS−B No. 2 Output: [RMP−9J (A), RMP−9K (B)] Reserved for future use. 34−43−23 Page 4−7 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−1. TCAS 3000 Computer Unit Loading/Gradient Specifications (cont) Connector Pin Designation Functional Description RMP−10A RMP−10B RMP−10C ADS−B Program Inputs Reserved for future use. RMP−10D Single Mode S Transponder Input This pin must be grounded when system is configured with a single Mode S transponder. Failure to ground this program pin in a single Mode S installation will result in XPNDR bus faults displayed on fault data LEDs. RMP−10E Thru RMP−10J Reserved Program Inputs Reserved for future use. RMP−10K ADS−B Surveillance Program Input This program pin enables passive surveillance using ADS−B DF−17 extended squitters. A ground on this pin enables ADS−B surveillance and an open disables ADS−B surveillance. RMP−11A Reserved Program Input Reserved for future use. RMP−11B Traffic Display of Flight ID Program Input This program pin allows traffic display of flight identification information from a transponder to be output on the TA/TA displays. A ground on this pin enables this function and an open disables the function. RMP−11C Male Voice Program Input This program input is intended to allow audio annunciation to be selectable for either male or female genders. A ground on this pin selects the male voice and an open selects the female voice. RMP−11D Flight Data Recorder ARINC 429 and Extended Maintenance Log Program Input This program pin is used to specify whether the ARINC 429 Flight Data Recorder (FDR) is to be used. An open on this pin means that the FDR is not utilized. A ground indicates that flight data is output as high−speed ARINC 429 data on RA Display No. 1 and No. 2 busses. While the FDR is enabled, normal low−speed RA display bus operation is not available. A ground also enables RA/TA events recording in memory. RMP−11E Thru RMP−11K Reserved Data Bus Inputs Reserved for future use. RMP−12A Reserved Program Input Reserved for future use. Page 4−8 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−1. TCAS 3000 Computer Unit Loading/Gradient Specifications (cont) Connector Pin Designation RMP−12B Functional Description Radio Altimeter Type Select Program Input No. 4 (NO) The TCAS computer unit uses radio altitude to inhibit advisories and aural annunciation when in close proximity to the ground. This analog input No. 1, as well as analog input No. 2 can accept data as a dc voltage from several types of radio altimeters. Program pin RMP−12B is used, along with program pins RMP−12H, −12J, and −12K, to identify the type of analog radio altimeter installed. ARINC 552, Collins BCA, and metric type radio altimeters can be selected. In addition radio altimeter inputs can be selected which include AHV−6, NR−AS−10A, LPIA, and APN−232 CARA. The program pin inputs use ground/open logic levels. All unassigned program pin combinations are invalid and should not be selected. Pin RMP−6K can be used to supply a ground. Program Pin RMP−12K RMP−12J RMP−12H RMP−12B Altimeter Type Open Open Open Open Open Open Open Open Ground Ground Ground Ground Ground Ground Ground Ground Open Open Open Open Ground Ground Ground Ground Open Open Open Open Ground Ground Ground Ground Open Open Ground Ground Open Open Ground Ground Open Open Ground Ground Open Open Ground Ground Open Ground Open Ground Open Ground Open Ground Open Ground Open Ground Open Ground Open Ground ARINC 552/552A Collins BCA Metric Altimeter No. 1 Unassigned Metric Altimeter No. 2 Unassigned Metric Altimeter No. 3 Unassigned Metric Altimeter No. 4 Unassigned Military AHV6 (Linear) Military AHV6 (Log) Military NR−AS−10A (Alternate) Military APN−232 CARA Military LPIA Military NR−AS−10A (Curve Fit) Each of the military radio altimeter types provide two outputs that are connected to the TCAS computer unit input pins. The two altimeter outputs are the Analog Data Output and Analog Data Reliability Signal. The Data Reliability Signal is connected to RMP−2K for source No. 1 and RBP−3C for source No. 2, except for altimeter type LPIA. For radio altimeter type LPIA, the Analog Data Output must be connected to RMP−2H (HI) and RMP−2J (LO), the Analog Data Reliability Signal must be connected to RBP−3A (HI) and RBP−3B (LO), and the inputs RMP−2K and RMP−3C are set high (greater than 18.5 V). The metric radio altimeters are defined as follows: Metric Altimeter Definition No. 1 No. 2 No. 3 No. 4 Metric unit− 1000 meter range, 25 mV/M scaling Metric unit− 1000 meter range, 20 mV/M scaling Metric unit− 1500 meter range, 20 mV/M scaling Metric unit− 750 meter range, 50 mV/M scaling 34−43−23 Page 4−9 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−1. TCAS 3000 Computer Unit Loading/Gradient Specifications (cont) Connector Pin Designation Functional Description RMP−12C RA/TA Block Transfer Program Input (NO) This program input determines the type of block transfer that is made from the TCAS computer unit to the TA/RA displays. If this pin is grounded, the TCAS computer unit transmits in ACSS BCA EFIS format. If the TCAS computer unit senses an open at this pin, it transmits in ARINC 735 format. RMP−12D Reserved Program Input RMP−12E Reserved Program Input RMP−12F Spare Pin RMP−12G Option Parity Program Input The TCAS computer unit uses nine discrete program input pins to determine which options have been selected by the installer. Eight of these pins are used to determine option selections. The ninth pin (RMP−12G) is used to determine parity for the eight option selection pins (RMP−10G, −10H, −10J, −10K, −11A, −11B, −11C, and −11D). To determine parity, count the number of option pins that are grounded. If the number of pins that are grounded is an odd number (1, 3, 5, 7), ground pin RMP−12G. If the number of grounded pins in the option group is an even number (0, 2, 4, 6, 8), leave pin RMP−12G open. RMP−12H Analog Radio Altimeter Type Select Program Input No. 3 (NO) See RMP−12B. RMP−12J Analog Radio Altimeter Type Select Program Input No. 2 (NO) See RMP−12B. RMP−12K Analog Radio Altimeter Type Select Program Input No. 1 (NO) See RMP−12B. RMP−13A, 13B RA Display No. 1/ARINC 429 Data Recorder Output: [RMP−13A (A), RMP−13B (B)] These ARINC 429 outputs are configured to output either RA information or for use as an ARINC 429 data recorder function. The output is configured by program pin RMP−11D. When RMP−11D is open (standard configuration), the bus is configured for low−speed ARINC 429 operation and RA information is output according to the format specified for the RA display bus in ARINC 735. When RMP−11D is grounded, the bus is configured for high−speed ARINC 429 operation and the output supplies TA and RA information to a 429 data recorder. RMP−13C, 13D RA Display No. 2/ARINC 429 Data Recorder Output: [RMP−13C (A), RMP−13D (B)] See RMP−13A. RMP−13E Page 4−10 15 Dec 2005 RA Display No. 2 Status Discrete Input (NO) This input provides the functional status of RA Display No. 2. A ground on this pin indicates a valid display. If this discrete is not used by the RA Display, connect to aircraft ground to prevent RA DISPLAY No. 2 fail message during self−test. 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−1. TCAS 3000 Computer Unit Loading/Gradient Specifications (cont) Connector Pin Designation Functional Description RMP−13F Landing Gear Discrete Input (NO) The TCAS computer unit monitors this discrete that indicates the landing gear position. An open indicates the gear is retracted (gear is up) and a ground indicates the gear is extended (gear is down). RMP−13G Climb Inhibit No. 2 Discrete Input (NO) See RMP−1J. RMP−13H, 13J Radio Altimeter No. 1 Input: [RMP−13H (A), RMP−13J (B)] This input is provided for ARINC 429 altitude inputs from an ARINC 707 digital radio altimeter. Radio altitude data is used for computation of sensitivity level, inhibit descend advisories, and inhibit aural annunciation when in close proximity to the ground. Also see RMP−2H. RMP−13K TCAS System Valid Discrete Output (NO) This discrete output indicates the health status of the TCAS computer unit to other avionics systems that monitor TCAS system status. This output is used in retrofit installations where instrumentation needs to monitor TCAS status. A ground at this pin indicates normal TCAS operation. An open indicates a TCAS fault. RMP−14A, 14B ARINC 429 TX Coordination Bus No. 2 Output: [RMP−14A (A), RMP−14B (B)] This differential pair output is a high speed ARINC 429 bus (100K bits/second nominal), that transmits data from the TCAS computer unit to the No. 2 Mode S Transponder. The labels on this bus are as follows: 273, 274, 275. RMP−14C RA Display No. 1 Status Discrete Input (NO) This input provides the functional status of RA Display No. 1. A ground on this pin indicates a valid display. If this discrete is not used by the RA display, connect to aircraft ground to prevent RA DISPLAY No. 1 fail message during self−test. RMP−14D, 14E Selected Altitude701/720 ARINC 429 Bus Input Reserved for future use. RMP−14F, 14G ARINC 429 XT Coordination No. 1 Input: [RMP−14F (A), RMP−14G (B)] This differential pair input is a high speed ARINC 429 bus (100K bits/second nominal), that receives data from the No. 1 Mode S Transponder. The labels on this bus are as follows: 013, 015, 016, 203, 271, 272, 273, 274, 275, 276, 277, 350. RMP−14H, 14J ARINC 429 XT Coordination No. 2 Input: [RMP−14H (A), RMP−14J (B)] This differential pair input is a high speed ARINC 429 bus (100K bits/second nominal), that receives data from the No. 2 Mode S Transponder. The labels on this bus are as follows: 013, 015, 016, 203, 271, 272, 273, 274, 275, 276, 277, 350. RMP−14K Spare Pin 34−43−23 Page 4−11 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−1. TCAS 3000 Computer Unit Loading/Gradient Specifications (cont) Connector Pin Designation RMP−15A thru RMP−H Functional Description Reserved for future use. RMP−15J, 15K ARINC 429 TX Coordination No. 1 Output: [RMP−15J (A), RMP−15K (B)] This differential pair output is a high speed ARINC 429 bus (100K bits/second nominal), that transmits data from the TCAS computer unit to the No. 1 Mode S Transponder. The labels on this bus are as follows: 273, 274, 275. TCAS Computer Unit Right Bottom Plug (RBP) RBP−1A Thru RBP−1G Reserved for future use. RBP−1H RA Data Word 270 Bit 18 Discrete Output This discrete output provides RA information to the ARINC 573 flight recorder. The output goes to the “ground” state each time its associated bit within the advisory field of the RA output words changes from a “zero” condition to a “one” condition. The output remains in the “ground” state for as long as the associated RA bit remains non−zero. This output is read by the flight recorder as either a series or shunt output. RBP−1J RA Data Word 270 Bit 19 Discrete Output See RBP−1H. RBP−1K RA Data Word 270 Bit 20 Discrete Output See RBP−1H. RBP−2A Thru RBP−2G Spare Pins RBP−2H RA Data Word 270 Bit 21 Discrete Output See RBP−1H. RBP−2J RA Data Word 270 Bit 22 Discrete Output See RBP−1H. RBP−2K RA Data Word 270 Bit 23 Discrete Output See RBP−1H. RBP−3A, 3B RBP−3C RBP−3D, 3E Page 4−12 15 Dec 2005 Radio Altimeter No. 2 ARINC 552/Analog Input: [RBP−3A (HI), RBP−3B (LO)] See RMP−2H and −2J. Radio Altimeter No. 2 Valid Discrete Input (PO) See RMP−2H. Valid condition is greater than 18.5 V dc. Invalid is open. Radio Altimeter No. 2 Input: [RBP−3D (A), RBP−3E (B)] See RMP−13H. Also see RMP−2H. 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−1. TCAS 3000 Computer Unit Loading/Gradient Specifications (cont) Connector Pin Designation Functional Description RBP−3F, RBP−3G Spare Pins RBP−3H RA Data Word 270 Bit 24 Discrete Output See RBP−1H. RBP−3J RA Data Word 270 Bit 25 Discrete Output See RBP−1H. RBP−3K RA Data Word 270 Bit 26 Discrete Output See RBP−1H. RBP−4A Thru RBP−4F Reserved Discrete Inputs Reserved for future use. RBP−4G RA Display Test Inhibit Program Pin This program pin is used to determine if RA discrete monitoring will be inhibited during self−test. If this pin is connected to program common (ground), RA discrete self−test monitoring is inhibited. An open on this pin indicates RA discretes monitoring during self−test. RBP−4H RA Data Word 270 Bit 27 Discrete Output See RBP−1H. RBP−4J RA Data Word 270 Bit 28 Discrete Output See RBP−1H. RBP−4K RA Data Word 270 Bit 29 Discrete Output See RBP−1H. 34−43−23 Page 4−13 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−1. TCAS 3000 Computer Unit Loading/Gradient Specifications (cont) Connector Pin Designation RBP−5A Functional Description Advisory Inhibit Discrete Input No. 1 (NO) Four discrete inputs at RBP−5A, −5B, −5C, and −5D provide the capability for the TCAS computer unit to defer all advisory (TA), aural alert and visual alert outputs until another, higher priority announcement or alert is completed. An open at all four of these discrete inputs indicates normal advisory/alert operation. These discrete inputs become active by connection to program common (ground) at RBP−7K. No new TA information can be placed on the RA or RA/TA busses during a period of Advisory Inhibit. If an advisory condition, which occurred during a period of Advisory Inhibit, remains when the TCAS computer unit returns to normal operation, it is annunciated. The Advisory Inhibit inputs and their effect on the advisory/alert priority system are as follows: Discrete No. Pin No. Mode RBP−5A RBP−5B RBP−5C RBP−5D Forced Standby Force TA Only (no voice/tone) Force TA Only (no voice/tone) Force TA Only (no voice/tone) Priority Discrete No. 1 (RBP−5A) has priority over No. 2 (RBP−5B), No. 3 (RBP−5C) and No. 4 (RBP−5D). Discrete No. 1 forces TCAS into STANDBY mode. Discretes No. 2, No. 3, and No. 4 force TCAS into TA mode with no voice or tone annunciations. RBP−5B Advisory Inhibit Discrete Input No. 2 (NO) See RBP−5A. RBP−5C Advisory Inhibit Discrete Input No. 3 (NO) See RBP−5A. RBP−5D Advisory Inhibit Discrete Input No. 4 (NO) See RBP−5A. RBP−5E Increase Climb Inhibit Discrete Input No. 1 (NO) This input is a ground/open type discrete used to provide information to the TCAS CU whether to assume that the aircraft cannot achieve a climb rate of 2500 feet per minute (FPM). The climb inhibit discrete inputs are designed in pairs (No. 1 and No. 2 at RBP−5F, or No. 3 at RBP−5G and No. 4 at RBP−5H) but can be wired as a single input or in conjunction with other aircraft operations to achieve airframe customization of the climb inhibit feature. The 2500 FPM climb inhibit function is assumed whenever No. 1 and No. 2 are ground or No. 3 and No. 4 are ground. RBP−5F Increase Climb Inhibit Discrete Input No. 2 (NO) See RBP−5E. RBP−5G Increase Climb Inhibit Discrete Input No. 3 (NO) See RBP−5E. RBP−5H Increase Climb Inhibit Discrete Input No. 4 (NO) See RBP−5E. RBP−5J Climb Inhibit Discrete Input No. 3 (NO) See RMP−1J. Page 4−14 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−1. TCAS 3000 Computer Unit Loading/Gradient Specifications (cont) Connector Pin Designation Functional Description RBP−5K Climb Inhibit Discrete Input No. 4 (NO) See RMP−1J. RBP−6A Airborne Data Loader Link A Discrete Input This discrete input, along with Data Loader Discrete Inputs No. 2, 3, and 4 (pins RBP−6B, RBP−6C, and RBP−6D, respectively), is a ground/open type discrete that specifies what type of data loader (ARINC 603 or ARINC 615) is attached. The TCAS computer unit has separate receiver busses and separate data loader enable discrete inputs to support simultaneous connections to an ADL and PDL. A ground on pin RBP−6A indicates that an airborne data loader is connected to the rear connector of the TCAS computer unit. A ground on pin J1−18, PDL Link A Discrete Input, indicates that a portable data loader is connected to the front connector of the TCAS computer unit. The data loader discrete inputs at RBP−6B, RBP−6C, and RBP−6D are also connected to the data loader discrete inputs on the front connector (pins J1−51, J1−52, and J1−53, respectively). Listed below is an active discrete (selected) indicated by a ground and an inactive discrete (not selected) indicated by an open. RBP−6A J1−18 J1−51/ J1−52/ J1−53/ RBP−6B RBP−6C RBP−6D Function Ground Ground Open Open −− Ground Open Ground Open −− ARINC 615 ADL ARINC 603 ADL ARINC 615 PDL ARINC 603 PDL SW Part Number is output Open Open Ground Ground −− Open Ground Open Ground −− RBP−6B Data Loader Discrete Input No. 2 See RBP−6A. RBP−6C Data Loader Discrete Input No. 3 See RBP−6A. RBP−6D Data Loader Discrete Input No. 4 See RBP−6A. Open Open Open Open Ground RBP−6E, 6F ARINC 429 CFDS Output: [RBP−6E (A), RBP−6F (B)] This differential pair output is a low speed ARINC 429 bus (12.5K bits/second nominal), that transmits data to an onboard maintenance computer or a central fault display system. RBP−6G, 6H ARINC 429 CFDS Input: [RBP−6G (A), RBP−6H (B)] This differential pair input is a low speed ARINC 429 bus (12.5K bits/second nominal), that receives data from an onboard maintenance computer or a central fault display system. RBP−6J Single Mode S Program Pin Ground this pin when the computer is connected to a single mode S transponder. RBP−6K Single Radio Altimeter Program Pin Ground this pin when the computer is connected to a single radio altimeter. 34−43−23 Page 4−15 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−1. TCAS 3000 Computer Unit Loading/Gradient Specifications (cont) Connector Pin Designation RBP−7A Functional Description Audio Level Program Pin No. 1 (NO) Two synthesized voice outputs with programmable output levels are provided by the TCAS computer unit. The output at RMP−2F and −2G supply high level (up to 4 Watts) audio signals to an 8 ohm speaker. The second output at RMP−3F and −3G supply low level (up to 80 milliwatts) audio signals to a 600 ohm audio distribution system. All aural traffic and resolution advisories can be annunciated over these outputs unless cancelled by a Cancel Discrete (RMP−3D). Listed below are the audio level program pin configurations and the resulting output levels: RBP−7A (MSB) Open Open Open Open Ground Ground Ground Ground Program Pin RBP−7B RBP−7C (LSB) Open Open Ground Ground Open Open Ground Ground Low Level Output dBm mW Open Ground Open Ground Open Ground Open Ground 16 13 10 −2 19 40 20 10 2.5 1.25 0.625 80 High Level Output dBm −3 −6 −9 −12 Not Used 0.5 0.25 0.125 0.0625 Not Used RBP−7B Audio Level Program Pin No. 2 (NO) See RBP−7A. RBP−7C Audio Level Program Pin No. 3 (NO) See RBP−7A. RBP−7D Audio Tone Enable Program Pin (NO) If this programming pin is connected to program common, (RBP−7K), all voice announcements are delayed by one second and are preceded by a tone. If pin is left open, no delays or tones occur. RBP−7E Ground Display Mode Program Pin (NO) The TCAS computer unit monitors this programming pin to select the TCAS ground display mode while the aircraft is on the ground. If the aircraft is on the ground and this pin is connected to program common (RBP−7K), TCAS goes into standby mode. If this pin is left open and the aircraft is on the ground, TCAS displays traffic only. Aural and voice annunciations are inhibited while the aircraft is on the ground. NOTE: TCAS does not display any traffic that it locates on the ground. TCAS aircraft has WOW and intruder aircraft reports the same altitude or a lower altitude. RBP−7F Display All Traffic Program Pin (NO) The TCAS computer unit monitors this program pin to select either the all traffic display mode or the TA/RA only mode. If this pin is open, all traffic is displayed. If this pin is connected to program common (RBP−7K), the TCAS displays only TA/RA type intruders. Page 4−16 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−1. TCAS 3000 Computer Unit Loading/Gradient Specifications (cont) Connector Pin Designation RBP−7G Functional Description Cable Delay Signal Program Pin (NO) The cable delay program pins (RBP−7G, RBP−7H, and RBP−7J) convey to the TCAS computer unit the amount of delay differential between the top and bottom antenna cables. Pin RBP−7G determines whether a time delay is added to the top or bottom. If this pin is open, the time delay is added to the top. If this pin is ground (connected to program pin RBP−7K), the time delay is added to the bottom. The cable delay logic is given below. Program common for the cable delay program pins is RBP−7K. RBP−7H (MSB) RBP−7J (LSB) Differential Delay Adjustment Open Open Ground Ground Open Ground Open Ground 0−50 nsec 51−150 nsec 151−250 nsec 251−350 nsec No Change Add 100 nsec delay Add 200 nsec delay Add 300 nsec delay RBP−7H Cable Delay MSB Program (NO) See RBP−7G. RBP−7J Cable Delay LSB Program Pin (NO) See RBP−7G. RBP−7K Program Common This is the ground source for use with program pins. RBP−8A Thru RBP−8D Reserved Program Pins RBP−8E Self−Test Test Inhibit Program Pin (NO) This program pin determines if self−test will be inhibited while airborne. If grounded, this pin inhibits self−test while airborne. If open, self−test is enabled while airborne. RBP−8F TA/RA Display Symbol Maximum 16 Program Pin (NO) The TCAS computer unit establishes the number of intruder symbols to be displayed on the TA display through the program pins RBP−8F, −8G, −8H, −8J, and −8K. This number can vary between 0 and 31, depending on the programming that is a summation of the selected pins. Connecting one of these pins to program common (RBP−7K) indicates the associated pin is not selected and that its value is not included in the summation. Leaving the pin open designates the associated pin is selected and its value is included in the summation. The encoded number is placed within the RTS data word (label 357) and sent to the display. The display should then limit the intruder symbols to this number. RBP−8G TA/RA Display Symbol Maximum 8 Program Pin (NO) See RBP−8F. RBP−8H TA/RA Display Symbol Maximum 4 Program Pin (NO) See RBP−8F. 34−43−23 Page 4−17 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−1. TCAS 3000 Computer Unit Loading/Gradient Specifications (cont) Connector Pin Designation Functional Description RBP−8J TA/RA Display Symbol Maximum 2 Program Pin (NO) See RBP−8F. RBP−8K TA/RA Display Symbol Maximum 1 Program Pin (NO) See RBP−8F. RBP−9A Thru RBP−10K Reserved Factory Test Pins Leave these pins unconnected for aircraft installations. TCAS Computer Unit Left Top Plug (LTP) LTP−1 Top Antenna 0 Degree Port J1 on the antenna is color−coded yellow. This antenna port is called the 0 degree port because it produces a transmission pattern in the forward quadrant of the aircraft. J1 is physically located toward the rear of the antenna and to the rear of the aircraft when antenna is properly installed. The TCAS computer unit checks the built−in dc to ground resistance of this antenna port. It must detect approximately 1000 ohms or TCAS fails its antenna test. LTP−2 Top Antenna 270 Degree Port J2 on the antenna is color−coded black. This antenna port is called the 270 degree port because it produces a transmission pattern in the left wing quadrant of the aircraft. J2 is physically located toward the right wing of the aircraft when antenna is properly installed. The TCAS computer unit checks the built−in dc to ground resistance of this antenna port. It must detect approximately 8000 ohms or it reports antenna test failure. LTP−3 Top Antenna 180 Degree Port J3 on the antenna is color−coded blue. This antenna port is called the 180 degree port because it produces a transmission pattern in the rear quadrant of the aircraft. J3 is physically located toward the front of the antenna and to the front of the aircraft when antenna is installed properly. The TCAS computer unit checks the built−in dc to ground resistance of this antenna port. It must detect approximately 4000 ohms or it reports antenna test failure. LTP−4 Top Antenna 90 Degree Port J4 on the antenna is color−coded red. This antenna port is called the 90 degree port because it produces a transmission pattern in the right wing quadrant of the aircraft. J4 is physically located toward the left wing of the aircraft when antenna is properly installed. The TCAS computer unit checks the built−in dc to ground resistance of this antenna port. It must detect approximately 2000 ohms or it reports antenna test failure. TCAS Computer Unit Left Middle Plug (LMP) LMP−1 Page 4−18 15 Dec 2005 Bottom Antenna 0 Degree Port J1 on the antenna is color−coded yellow. Same as top antenna 0 degree port (LTP−1). In addition, this port is used as the omnidirectional antenna connection. The TCAS computer unit determines that a bottom omnidirectional antenna is installed if it detects less than 500 Ohms (50 ohms typical) to ground on this pin and an open circuit (>13K Ohms) at LMP− 2, −3, and −4 or a dc short (<500 Ohms) if unused ports are terminated at back of mounting tray. 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−1. TCAS 3000 Computer Unit Loading/Gradient Specifications (cont) Connector Pin Designation Functional Description LMP−2 Bottom Antenna 90 Degree Port J2 on the antenna is color−coded black. This antenna port is called the 90 degree port because it produces a transmission pattern in the right wing quadrant of the aircraft. J2 is physically located toward the left wing of the aircraft when antenna is properly installed. The TCAS computer unit checks the built in dc to ground resistance of this antenna port. It must detect approximately 8000 ohms or it reports antenna test failure. LMP−3 Bottom Antenna 180 Degree Port J3 on the antenna is color−coded blue. Same as top antenna 180 degree port (LTP−3). LMP−4 Bottom Antenna 270 Degree Port J4 on the antenna is color−coded red. This antenna port is called the 270 degree port because it produces a transmission pattern in the left wing quadrant of the aircraft. J4 is physically located toward the right wing of the aircraft when properly installed. The TCAS computer unit checks the built in dc to ground resistance of this antenna port. It must detect approximately 2000 ohms or it reports antenna test failure. TCAS Computer Unit Left Bottom Plug (LBP) LBP−1 115 V ac Power Input (H) This pin along with the 115 V ac Power Input (C) line (pin LBP−7) provides the 115 V ac power requirements for the TCAS computer unit. NOTE: The TCAS computer unit operates with either 115 V ac, 400 Hz, or 28 V dc input power. If 115 V ac is used, the power should be connected through a 5 Amp circuit breaker, and the pins for the 28 V dc input should be left unconnected. LBP−2 Spare Pin LBP−3 +28 V dc Power Return (LO) See LBP−10. LBP−4 Spare Pin LBP−5 Fan 115 V ac Power Output (H) This pin along with the Fan 115 V ac Output Power (C) line (pin LBP−9) provides 115 V ac power for an external fan. LBP−6 Spare Pin LBP−7 115 V ac Power Input (C) See LBP−1. LBP−8 Signal Ground Connect to Aircraft Signal Ground. LBP−9 Fan 115 V ac Power Output (C) See LBP−5. 34−43−23 Page 4−19 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−1. TCAS 3000 Computer Unit Loading/Gradient Specifications (cont) Connector Pin Designation Functional Description LBP−10 +28 V dc Power Input (HI) This pin along with the TCAS computer unit 28 V dc Power Return line (LBP−3) provide the +28 V dc power requirements for the TCAS computer unit. NOTE: This TCAS computer unit operates with either 115 V ac, 400 Hz, or 28 V dc input power. If +28 V dc is used, the power should be connected through a 10 Amp circuit breaker, and the pins for the 115 V ac input should be left unconnected. LBP−11 Chassis Ground Connect to aircraft frame. LBP−12 Mutual Suppression Pulse Bus Input The TCAS computer unit joins the mutual suppression bus daisy chained through TCAS and other RF transmitting equipment on board the aircraft. TCAS receives suppression pulses from other LRUs on this bus, which is used to suppress the TCAS receivers during such transmissions. This prevents the TCAS computer unit from interpreting these transmissions as valid replies from an intruder aircraft. When not suppressed, the TCAS computer unit transmits its own suppression pulses on the same bus in order to suppress the receivers in other L−band systems on the aircraft. This pin is designated as the input. Pin LBP−13 is directly connected to this pin internally and functions as the output. L−Band suppression coax must be RG−142, RG400, or equivalent coaxial cable which meets the operational characteristics required by ARINC 735. LBP−12 and LBP−13 are connected internally. Connection to only one pin is required. LBP−13 Mutual Suppression Pulse Bus Output See LBP−12. The Interface descriptions that follow are for the 53−pin Data Loader connector J1 mounted on the front panel of the TCAS computer unit. These descriptions are used to make up the cable that is used to interface between the TCAS computer unit and an ARINC 615 Portable Data Loader (PDL), a RS−232 PC Serial Port, a RS−422 Flight Data Recorder, or an ARINC 429 Maintenance Display. J1−1, 2 ARINC 429 PDL Bus Input: [J1−1 (A), J1−2 (B)] This differential pair input is a high−speed ARINC 429 bus (100K bits/second nominal) that is used to input data from the data loader to the TCAS computer unit. The standards for this interface are defined in ARINC 615 Airborne Computer High Speed Data Loader. These pins should be connected to pins 1 and 2 of the PDL cable interface. J1−3, J1−4 Spare Pins J1−5 Output Bus Shields The shields from the output bus (J1−8, 9) should be connected to this pin. J1−6, J1−7 ARINC 615 Data Loader Ethernet: [J1−6 TD+,J1−7 TD−] Page 4−20 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−1. TCAS 3000 Computer Unit Loading/Gradient Specifications (cont) Connector Pin Designation Functional Description J1−8, 9 ARINC 429 Data Loader/PDL Recorder Bus Output: [J1−8 (A), J1−9 (B)] This differential pair output is a high−speed ARINC 429 bus (100K bits/second nominal) that is used to output data from the TCAS computer unit to the data loader. The standards for this interface are defined in ARINC 615 Airborne Computer High Speed Data Loader. These pins should be connected to pins 8 and 9 of the PDL cable interface. J1−10 thru J1−15 ARINC 615 Data Loader Reserved J1−16 Input Bus Shields The shields from the input bus (J1−1, 2) should be connected to this pin. J1−17 Spare Pin J1−18 PDL Link A Discrete Input This is a ground/open discrete from an portable ARINC 615 or ARINC 603 data loader which indicates, to the TCAS computer unit, that a data loader is connected. A ground indicates a data loader is connected. J1−19 PDL Link B Common Connect this pin to pin 19 of the PDL cable interface. J1−20, 22 115 V ac Power Output: [J1−20 (H), J1−22 (C)] These power output pins provide the 115 V ac operating power for the data loader. The 115 V ac (H) and 115 V ac (C) interconnect wires should be shielded or twisted and shielded with an insulating jacket over the shield. The shield should be connected to chassis ground (J1−21). J1−21 Chassis Ground Connect 115 V ac power shields to this pin. J1−23 ARINC 615 Data Loader Ethernet Input (RD+) J1−24 thru J1−32 Reserved J1−33,34 J1−35, J1−36 ARINC 429 TA/RA Display No. 1 Output: [J1−33 (A), J1−34 (B)] This bus can be used to connect to a maintenance display. These pins are also connected to the ARINC 600 connector on the rear of the unit (RMP−7C and −7D). Reserved 34−43−23 Page 4−21 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−1. TCAS 3000 Computer Unit Loading/Gradient Specifications (cont) Connector Pin Designation J1−37, 38 Functional Description 28 V dc Power Output: [J1−37 (HI), J1−38 (LO)] These power output pins provide the 28 V dc operating power for the data loader. These pins are used only if the data loader operates from a +28 V dc source. J1−39 Reserved J1−40 RS−232 Data Input This pin is used to receive RS−232 data from a portable maintenance terminal. J1−41 RS−232 Data Output This pin is used to transmit RS−232 data to a portable maintenance terminal. J1−42 Thru J1−47 Spare Pins J1−48, J1−49 Logic Common Common lines for the RS−232 Data Input/Output lines. These two pins are tied together in the TCAS computer unit. J1−50 Reserved Pin J1−51 Data Loader Link No. 2 Discrete Input Pins J1−51 and J1−52 are ground/open discretes from a portable data loader, which are used to specify what type of data loader (ARINC 603 or ARINC 615) is connected to the TCAS computer unit. These two pins are also connected to the ARINC 600 connector on the rear of the unit (RBP−6B and −6C respectively). J1−52 Data Loader Link No. 3 Discrete Input See J1−51. J1−53 Data Loader Link No. 4 Discrete Input This is a ground/open discrete from a Portable Data Loader (PDL) that is used to transmit the software part number on the Data Loader output bus when grounded, The landing gear indicates extended, and the air/ground indicates ground. This pin is also connected to the ARINC 600 connector on the rear of the unit (RBP−6D). Page 4−22 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−2. ACSS Dual Mode S Control Panel Interface Descriptions Connector Pin Designation J1−1,2 J1/J2−3,4 Functional Description PANEL AND DISPLAY LIGHTING INPUT: (J1−1 LOW, J1−2 HIGH) 5 V ac, 3.0 Watts maximum lighting input for front panel and display lighting. Lighting is provided by incandescent lamps. 115 V ac INPUT POWER: (J1/J2−3 HIGH, J1/J2−4 LOW) The control panel is powered from a 115 V ac power bus. Two identical but isolated power supplies provide the power requirements to each individual electronic module which independently control, transponder 1 and 2. Maximum power is 2.0 Watts. J1/J2−5 ANTENNA TRANSFER DISCRETE OUTPUT: (J1/J2−5) These discrete outputs are used to provide the ability to switch a RF relay for dual transponder installations that have only one set of antennas. The outputs from J1 and J2 are linked to the XPDR 1−2 switch. The output is OPEN when the transponder is in standby (inactive) mode, and GROUND when the transponder is in an active operational mode. J1/J2−6 DC GROUND INPUT: (J1/J2−6) Reference for all discrete inputs/outputs. Tied to aircraft dc ground. J1/J2−7 STANDBY/ON OUTPUT: (J1/J2−7) These discrete outputs (STANDBY/ON) will mimic the XPDR switch position placing one transponder in Standby and the other in the ON (active) mode. Both transponders will never be in the ON mode simultaneously. This output is low (GROUND) when in Standby mode and OPEN when in the ON mode. This output can sink 100 mA maximum. Connect pin to transponder STANDBY / ON Discrete Input. J1/J2−8 CHASSIS GROUND INPUT: (J1/J2−8) Tied to airframe. Also used to connect ARINC 429 cable shields to the chassis. J1−9 FUNCTIONAL TEST INPUT: (J1−9) Functional test can also be initiated using this discrete input. When J1−9 is grounded, a functional test similar to pushing the TCAS TEST button on the front panel is initiated. J1−10 WARNING AND CAUTION OUTPUT: (J1−10) This discrete output provides a low signal to a remote master warning system when the control panel receives a Monitor Lamp fault indication from the active transponder. Otherwise, it provides 7 to 30 V dc or a resistance of >100 K Ohms to ground. This output can sink 20 mA maximum. J1/J2−12 XPDR FAIL #2 INPUT: (J1/J2−12) The control panel XPDR FAIL annunciator is controlled by this input. When the transponder is operating normally this input remains grounded. Otherwise, the transponder opens this input to indicate a transponder failure. The control panel then turns the annunciator ON to alert the user of a transponder malfunction. The transponder fail annunciator turns on only when the failed transponder is selected by the XPDR 1−2 switch. Connect this pin to the transponder XPDR FAIL #2 Discrete Output. 34−43−23 Page 4−23 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−2. ACSS Dual Mode S Control Panel Interface Descriptions (cont) Connector Pin Designation Functional Description J1/J2−16 AIR DATA SOURCE OUTPUT: (J1/J2−16) Ground/Open output that is dependent on the front panel ALT RPTG and XPDR switch positions. This discrete output is enabled when altitude reporting is selected in the ON mode. When altitude reporting is selected OFF, the J1/J2−16 output remains in the OPEN state. This discrete output is connected to the transponder AIR DATA SOURCE SELECT Discrete Input. J1−18 MONITOR LAMP POWER INPUT: (J1−18) This input is used as the input power source for the XPDR FAIL annunciator on the front panel of the control panel. The input supply voltage is a dimmable 26 V dc at 200 mA maximum. J1/J2−20 XPDR FAIL #1 DISCRETE INPUT: (J1/J2−20) This pin is tied directly to control panel pin J1/J2−12. See pin 12. J1−21 LAMP TEST INPUT: (J1−21) To initiate a lamp test, pin J1−21 must be grounded through a remote test switch. All segments in the control panel LCD display are ON for as long as this input is grounded. ARINC 429 labels are not affected by the activation of a lamp test mode. J1/J2−22, 23 ARINC 429 OUTPUTS: (J1/J2−22, 23) Communication between the control panel and the transponder is done over a two wire low speed, odd parity, ARINC 429 compatible bus. Selected ATC code, operating mode, and system parameters are communicated to the transponder over these lines. Transmission of labels 013, 015, 016, and 031 is done every 150 milliseconds. Connect these pins to one of the two transponder ARINC 429 CONTROL DATA Input Ports. Page 4−24 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−3. ACSS ATCRBS−Mode S Control Panel Interface Descriptions Connector Pin Designation Functional Description J1−1, 2 PANEL AND DISPLAY LIGHTING INPUT: (J1−1 LOW, J1−2 HIGH) 5 V ac, 3.0 Watts maximum lighting input for front panel and display lighting. Lighting is provided by incandescent lamps. J1−3, 4 115 V ac INPUT POWER: (J1−3 HIGH, J1−4 LOW) The control panel is powered from a 115 V ac power bus. A single power supply provides the power requirements for the control panel. Maximum power is 2.0 Watts. J1−5 ANTENNA TRANSFER DISCRETE OUTPUT: (J1−5) This discrete output is used to provide the ability to switch a RF relay for dual transponder installations that have only one set of antennas. The output is OPEN when the transponder is in standby (inactive) mode, and GROUND when the transponder is in an active operational mode. J1−6 DC GROUND INPUT: (J1−6) Reference for all discrete inputs/outputs. Tied to aircraft dc ground. J1−7 STANDBY/ON OUTPUT: (J1−7) This discrete output (STANDBY/ON) will mimic the XPDR switch position placing one transponder in Standby and the other in the ON (active) mode. Both transponders will never be in the ON mode simultaneously. This output is low (GROUND) when in Standby mode and OPEN when in the ON mode. This output can sink 100 mA maximum. Connect this pin to transponder STANDBY/ON Discrete Input. J1−8 CHASSIS GROUND INPUT: (J1−8) Tied to airframe. Also used to connect ARINC 429 cable shields to the chassis. J1−9 FUNCTIONAL TEST INPUT: (J1−9) Functional test can also be initiated using this discrete input. When J1−9 is grounded through a remote test switch, a functional test similar to pushing the TCAS TEST button on the front panel is initiated. J1−10 WARNING AND CAUTION OUTPUT: (J1−10) This discrete output provides a low signal to a remote master warning system when the control panel receives a Monitor Lamp fault indication from the active transponder. Otherwise it provides 7 to 30 V dc or a resistance of >100 K ohms to ground. This output can sink 20 mA maximum. J1−12 XPDR FAIL #2 INPUT: (J1−12) The control panel XPDR FAIL annunciator is controlled by this input. When the transponder is operating normally this input remains grounded. Otherwise, the transponder opens this input to indicate a transponder failure. The control panel then turns the annunciator ON to alert the user of a transponder malfunction. The transponder fail annunciator turns on only when the failed transponder is selected by the control panel Mode switch. Connect this pin to the transponder XPDR FAIL #2 Discrete Output. 34−43−23 Page 4−25 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−3. ACSS ATCRBS−Mode S Control Panel Interface Descriptions (cont) Connector Pin Designation J1−16 Functional Description AIR DATA SOURCE OUTPUT: (J1−16) Ground/Open output dependent on the front panel ALT RPTG switch position. This discrete output is enabled (Grounded) when altitude reporting is selected in the ON mode. When altitude reporting is selected OFF, the J1−16 output is in an Open state. This discrete output is connected to the transponder AIR DATA SOURCE SELECT Discrete Input. J1−18 MONITOR LAMP POWER INPUT: (J1−18) This input is used as the input power source for the XPDR FAIL annunciator on the front panel of the control panel. The input supply voltage is a dimmable 26 V dc at 200 mA maximum. J1−20 XPDR FAIL #1 DISCRETE INPUT: (J1−20) This pin is tied directly to control panel pin J1−12. See pin 12. J1−21 LAMP TEST INPUT: (J1−21) To initiate a lamp test, pin J1−21 must be grounded through a remote test switch. All segments in the control panel LCD display will be ON for as long as this input is grounded. ARINC 429 labels are not affected by the activation of a lamp test mode. J1−22, 23 ARINC 429 OUTPUTS: (J1/J2−22, 23) Communication between the control panel and the Mode S transponder is done over a two wire low speed, odd parity, ARINC 429 compatible bus. Selected ATC code, operating mode, and system parameters are communicated to the transponder over these lines. Transmission of labels 013, 015, 016, and 031 is done every 150 milliseconds. Connect these pins to one of the two transponder ARINC 429 CONTROL DATA Input Ports. CONNECTOR J2 INTERFACE DESCRIPTIONS J2−L ALTITUDE NO.1 OUTPUT: (J2−L) This discrete output along with pin J2−N and J2−R outputs are used in conjunction with the ALT RPTG switch on the control panel to enable one of two sources of altitude reporting data to be selected. These outputs are used only if two altitude sources are used. Connect this pin to Altitude Digitizer No.1 COMMON output. J2−N ALTITUDE NO.2 OUTPUT: (J2−N) See pin J2−L. Connect pin J2−N to Altitude Digitizer No.2 COMMON output. J2−R ALTITUDE COMMON: (J2−R) See pin J2−L. Connect pin J2−R to the ATCRBS transponder Altitude Common input. J2−T TRANSPONDER NO. 2 ON OUTPUT: (J2−T) This discrete output puts the ATCRBS transponder in either a standby or active mode. It is used in conjunction with the Mode switch on the front panel of the control panel. The output uses Ground/Open logic, where an Open specifies Standby and a Ground specifies an Active mode (ATC On). Connect this pin to the ATCRBS transponder ON input. Page 4−26 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−3. ACSS ATCRBS−Mode S Control Panel Interface Descriptions (cont) Connector Pin Designation Functional Description J2−X, Y, Z, a, MODE A REPLY CODE PULSE OUTPUTS: b, c, d, e, f, These 4096 Reply Code outputs are manually set by the reply code knobs on the front of g, h and i the control panel and are used for replies to Mode A interrogations. These pins should be connected to the ATCRBS transponder Mode A interface. J2−j IDENT OUTPUT: (J2−j) This discrete output provides a low signal (Ground) to an ATCRBS transponder whenever the IDENT button is pushed on the Control Panel. Connect this pin to the ATCRBS transponder Ident (SPI) discrete input. J2−m ATC FAIL INPUT: (J2−m) This discrete input is used to control the control panel XPDR FAIL annunciator when an ATCRBS transponder is being used. When the transponder is operating normally, this input is open (resistance greater than 100K ohms to ground). If a transponder failure has occurred, this input is greater than 4.0 V dc at 100 mA of current. Connect this pin to the transponder ATC FAIL output. J2−r ALTITUDE REPORTING ON OUTPUT: (J2−r) Ground/Open output that is dependent on the front panel ALT RPTG switch position. This discrete output is enabled when altitude reporting is selected in the ON mode. When altitude reporting is selected OFF, the output at pin J2−r will be in the OPEN state. This discrete output is connected to the transponder ALTITUDE REPORTING ON/OFF Discrete Input. J2−s TEST OUTPUT: (J2−s) This discrete output provides a low signal (Ground) to an ATCRBS transponder whenever the TCAS TEST button is pushed on the Control Panel. The control panel Mode switch must be in the ATC position to initiate an ATCRBS transponder test. J2−t TRANSPONDER NO. 1 ON: (J2−t) This discrete output puts a Mode S transponder in either a standby or active mode. It is used in conjunction with the Mode switch on the front panel of the Control Panel. The output uses Ground/Open logic where an Open specifies Standby and a Ground specifies an Active mode (ON, TA, or TA/RA). This pin is not used with ACSS Mode S Transponders. 34−43−23 Page 4−27 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−4. Gables Control Panel Interface Descriptions Connector Pin Designation J1−1,2 J1/J2−3, 4 Functional Description PANEL AND DISPLAY LIGHTING INPUT: (J1−1 HIGH, J1−2 LOW) 5 V ac, 2.3 Amp maximum lighting input for front panel and display lighting. Lighting is provided by incandescent lamps. +28 V dc INPUT POWER: (J1/J2−3 HIGH, J1/J2−4 LOW) The control panel is powered from a +28 V dc power bus. Two identical but isolated power supplies provide the power requirements to each individual electronic module that independently control transponder 1 and 2. Maximum current is 2.5 Amps dc. J1/J2−5 ANTENNA TRANSFER DISCRETE OUTPUT: (J1/J2−5) This discrete output is used to provide the ability to switch a RF relay for dual transponder installations that have only one set of antennas. These outputs from J1 and J2 are linked to the XPNDR 1−2 switch. The output is OPEN when the transponder is in standby (inactive) mode, and GROUND when the transponder is in an active operational mode. J1/J2−6 DC GROUND INPUT: (J1/J2−6) Reference for all discrete inputs/outputs. Tied to aircraft dc ground. J1/J2−7 STANDBY/ON OUTPUT: (J1/J2−7) These discrete outputs (STANDBY/ON) will mimic the XPNDR switch position placing one transponder in Standby and the other in the ON (active) mode. Both transponders will never be in the ON mode simultaneously. This output is (GROUND) when in Standby mode and OPEN when in the ON mode. This output can sink 100 mA maximum. Connect pin to transponder STANDBY / ON Discrete Input. J1/J2−8 CHASSIS GROUND INPUT: (J1/J2−8) Tied to airframe. Also used to connect ARINC 429 cable shields to the chassis. J1/J2−9 FUNCTIONAL TEST INPUT: (J1/J2−9) Functional test can also be initiated using this input discrete. When J1/J2−9 is grounded, a functional test similar to pushing the TEST button on the front panel is done. J1/J2−10 WARNING AND CAUTION OUTPUT: (J1/J2−10) This discrete output provides a low signal to a remote master warning system when the control panel receives a Monitor Lamp fault indication from the active transponder. Otherwise it provides 7 to 30 V dc or a resistance of >100K ohms to ground. This output can sink 20 mA maximum. J1/J2−12 TRANSPONDER FAIL #2 INPUT: (J1/J2−12) The G7130−XX ATC/TCAS control panel transponder fail annunciator is controlled by this input. When the transponder is operating normally this input remains grounded. Otherwise, the transponder opens this input to indicate a transponder failure. The control panel turns the annunciator ON to alert the user of a transponder malfunction. The transponder fail annunciator turns on only when the failed transponder is selected by the XPNDR 1−2 switch. Connect this pin to the transponder XPDR FAIL #2 Discrete Output. Page 4−28 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−4. Gables Control Panel Interface Descriptions (cont) Connector Pin Designation Functional Description J1/J2−13 IDENT INPUT: (J1/J2−13) The IDENT discrete input provides another means of activating the IDENT function. This input allows the control panel to interface with an external IDENT switch located in the cockpit. When the input is grounded, the IDENT function is activated; otherwise it should remain open. J1/J2−14 TRANSPONDER FAIL LOGIC DISCRETE INPUT: (TDR−94D ONLY) (J1/J2−14) This input allows the control panel to use 28 volt logic from a Collins TDR−94D transponder to control the transponder fail annunciator. This input should not be used unless a Collins TDR−94D transponder is used with this control panel. J1/J2−15 AIR/GROUND SW DISCRETE OUTPUT: (J1/J2−15) This output is directly connected to the AIR/GND discrete input (J1/J2−24). This output can be routed directly to the transponder to disable it (Standby), and terminate ATC code replies. J1 discrete logic operates independently from J2. J1/J2−16 AIR DATA SOURCE OUTPUT: (J1/J2−16) Ground/Open output that is dependent on the front panel ALT RPTG and XPNDR switch positions. This discrete output is enabled when altitude reporting is selected in the ON mode. When altitude reporting is selected OFF, the J1/J2−16 output remains in the OPEN state. This discrete output is connected to the transponder AIR DATA SOURCE SELECT Discrete Input. J1/J2−18 MONITOR LAMP POWER INPUT: (J1/J2−18) These inputs are used as the input power source for the transponder fail annunciator on the front panel of the control panel. The input supply voltage is a dimmable 26 V dc at 200 mA maximum. J1/J2−20 TRANSPONDER STRAPPING CONFIGURATION: (J1/J2−20) This discrete input programs the control panel to operate, and be able to properly interface to one of two types of transponder configurations. If this input is left OPEN then the control panel operates in accordance with ACSS transponder specifications. If the input is GROUNDED, it is programmed to operate in accordance with Collins transponder specifications. J1/J2−21 LAMP TEST INPUT: (J1/J2−21) To initiate a lamp test, J1 or J2 pin 21 must be grounded through an external switch. All segments and annunciators in the control panel LCD (except RPLY and decimal points) are ON for as long as this input is grounded. ARINC 429 labels are not affected by the activation of a lamp test mode. 34−43−23 Page 4−29 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−4. Gables Control Panel Interface Descriptions (cont) Connector Pin Designation Functional Description J1/J2−22, 23 ARINC 429 OUTPUTS: (J1/J2−22,23) Communication between the control panel and the transponder is done over a two wire low speed, odd parity, ARINC 429 compatible bus. Selected ATC code, operating mode, and system parameters are communicated to the transponder over these lines. Transmission of labels 013, 015, 016, and 031 is done every 150 milliseconds. Connect these pins to one of the two transponder ARINC 429 CONTROL DATA Input Ports. J1/J2−24 AIR/GROUND INPUT DISCRETE: (J1/J2−24) The control panel accepts input from two independent Air/Ground (WOW) switches for applications that require automatic disabling of the transponder upon landing. This input is wired directly to the AIR/GROUND SW Discrete Output (J1/J2−15). Page 4−30 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−5. 41−Pin VSI/TRA Interface Descriptions Connector Pin Designation Functional Description J1−1 VERTICAL SPEED +DC REFERENCE INPUT: Pins 1,2, and 3 are inputs to the VSI/TRA from an ARINC 575 air data computer indicating vertical speed. Pin 1 is a +12 V dc regulated reference voltage from the ADC. Pin 3 is a −12 V dc regulated reference voltage from the ADC. Pin 2 receives a +10 to −10 V dc rate signal from the ADC. Also see pins 31, 32, and 33. J1−2 VERTICAL SPEED DC RATE INPUT: See pin 1. J1−3 VERTICAL SPEED −DC REFERENCE INPUT: See pin 1. J1−4, 6 ARINC 565 VERTICAL SPEED AC INPUT: (J1−4 HIGH, J1−6 LOW) Pins 4, 5, 6, and 16 are inputs to the VSI/TRA from an ARINC 565 air data computer or IRS. A 26 V ac, 400 Hz reference signal is received on pin 5, (HI) and pin 16, (LO). Pin 4, (HI) and pin 6, (LO) provides an amplitude modulated 400 Hz signal with a maximum voltage of " 6.25 volts. The RMS value of this signal is used by the VSI/TRA to compute and display the vertical rate. The phase of this signal is compared with the reference signal to determine if the rate is positive or negative. An in−phase signal equals a positive rate, an out−of− phase signal indicates a negative rate. Also see pins 8, 31, 32 J1−5 VERTICAL SPEED 26 V ac, 400 HZ REFERENCE INPUT (HI): See pins 4 and 16. J1−8 VERTICAL SPEED VALID DISCRETE INPUT: The VSI/TRA receives a 28 V dc signal from an ARINC 575 or 565 air data computer indicating its valid operation. An “open” at this pin indicates an invalid vertical speed signal from the ADC. This pin is only used when pins (1, 2, 3) or (4, 5, 6, and 16) are used. Also see pins 1 and 4. J1−9, 10 5−VOLT LAMP DIMMING INPUT: (J1−9 LOW, J1−10 HIGH) The VSI/TRA monitors the cockpit lamp voltage bus at pins 9 and 10. This voltage may be either ac or dc. The back lighting in the VSI/TRA is adjusted by and tracks this voltage from 0.5 volts to 5 volts. If this input falls below 0.5 volts or is absent, the VSI/TRA sets itself to a nominal level to prevent the display from going dark due to loss or failure of the lamp dimming bus. J1−11 ARINC 429 (B) TCAS TA/RA DATA BUS INPUT: Paired with pin 26. These pins connect to a TCAS computer unit. J1−12 ARINC 429 (B) VERTICAL SPEED NO. 1 INPUT BUS: Paired with pin 27. These pins connect to Digital ADC No. 1 or PTM No 1. J1−14 ARINC 429 (B) VERTICAL SPEED NO. 2 INPUT: Paired with pin 30. These pins connect to Digital ADC No. 2 or PTM No. 2. J1−15 CONFIGURATION STRAP COMMON INPUT: This pin is the return line for the configuration strapping pins J1−17, J1−32 thru 38, and J1−41. 34−43−23 Page 4−31 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−5. 41−Pin VSI/TRA Interface Descriptions (cont) Connector Pin Designation Functional Description J1−16 VERTICAL SPEED 26 V ac, 400 HZ REFERENCE INPUT (LO): See pins 4 and 5. J1−17 CONFIGURATION STRAP #3 INPUT (NO): The VSI/TRA utilizes configuration strapping so unique aspects of any given installation may be identified and its functions supported. Each configuration strap (CS), and its associated function, becomes active when connected to program common, (J1−15). The inactive state of CS3 is open. This pin is monitored but unused in the −84X units. In −86X units it is paired with pin J1−34 (CS2) to configure the Lighting Curve and in −88X and −89X units it is paired with pin J1−41 (CS8) to select the desired Filter Time Constant. See pins 34 and 41. J1−18 PRESSURE TRANSDUCER MODULE POWER OUTPUT (COMMON): An optional ACSS PTM may be used in an installation to supply ARINC 429 vertical speed information to the VSI/TRA. Pins 18, 19, and 20 supply input power to the PTM. Pin J1−18 is the power return pin and is connected to PTM pin 8. J1−19 PRESSURE TRANSDUCER MODULE −15 V dc POWER OUTPUT: See pin 18. Connects to PTM pin 11. J1−20 PRESSURE TRANSDUCER MODULE +15 V dc POWER OUTPUT: See pin 18. Connects to PTM pin 5. J1−22 CHASSIS GROUND INPUT: Connected to aircraft frame. Also used to connect ARINC cable shields to the chassis. J1−23 115 V ac, 400 HZ POWER INPUT (COMMON): See pin 40. Connect to aircraft AC ground. J1−24, 25 REMOTE LIGHT SENSOR INPUT: (J1−24 LOW, J1−25 HIGH) This input at pins 24 and 25 provides a means of controlling the VSI/TRA back lighting via a remote light sensor already present in some aircraft (Douglas and Boeing). The VSI/TRA has its own built−in sensor and therefore a remote light sensor need not be used in all installations. Program the VSI/TRA for a remote light sensor, as described under pin 34. J1−26 ARINC 429 (A) TCAS TA/RA DATA INPUT: Traffic and Resolution Advisory data is supplied to the VSI/TRA from the TCAS computer unit via this high speed ARINC 429 data bus. Paired with pin 11. J1−27 ARINC 429 (A) VERTICAL SPEED NO. 1 INPUT: This is the primary ARINC 429 input bus to the VSI/TRA. This pin accepts high or low speed ARINC 429 vertical speed data (Label 212). Its use is determined by the source select discrete and configuration straps CS0 and CS1 (pins 31, 32, and 33 respectively). Paired with pin 12. J1−29 TA/RA VALID DISCRETE OUTPUT (NO): This output discrete indicates the ability of the VSI/TRA to perform as a resolution advisory and/or a traffic advisory display. If the VSI/TRA fails, this discrete presents an open. Normal operation causes a ground. This discrete is monitored by the TCAS computer unit. Page 4−32 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−5. 41−Pin VSI/TRA Interface Descriptions (cont) Connector Pin Designation Functional Description J1−30 ARINC 429 (A) VERTICAL SPEED NO. 2 INPUT: This is the secondary ARINC 429 input bus to the VSI/TRA. This pin accepts high or low speed ARINC 429 vertical speed data (Label 212). Its use is determined by the source select discrete and configuration straps CS0 and CS1 (pins 31, 32 and 33 respectively). Paired with pin 14. J1−31 SOURCE SELECT DISCRETE INPUT (NO): This discrete input is used in conjunction with configuration straps CS0 and CS1 to program the VSI/TRA to accept and use the vertical speed data being supplied. In some installations, this discrete is connected to a switch in the cockpit and is used to select between primary and secondary ARINC 429 vertical speed inputs. It is hard wired to configuration strap common if ac or dc analog vertical speed inputs are used. Cycle power to update to the new configuration. The following applies: O = Open, G = Ground. Pin SS CS0 CS1 31 32 33 Definition ARINC 429 HS Primary ARINC 429 HS Secondary Pressure Transducer Module (PTM) ARINC 575 dc ARINC 565 ac ARINC 429 LS Primary ARINC 429 LS Secondary J1−32 CONFIGURATION STRAP #0 INPUT (NO): See pin 31. J1−33 CONFIGURATION STRAP #1 INPUT (NO): See pin 31. 34−43−23 Page 4−33 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−5. 41−Pin VSI/TRA Interface Descriptions (cont) Connector Pin Designation J1−34 Functional Description CONFIGURATION STRAP #2 INPUT (NO): For −84X and −88X units, this pin programs the VSI/TRA to use the remote light sensor input at pins 24 and 25. If CS2 is open, a Boeing Airplane Company remote light sensor type (−10 to +10 V) is expected at pins 24 and 25. If grounded a Douglas Aircraft Company remote light sensor type (0 to 18 V) is programmed. Also see pin 25. For −89X units, CS2 is used to program the VSI display for English or Metric. If pin J1−34 is open, information is displayed in English. If grounded, the information is displayed in Metric. For −86X units, CS2 is used with CS3 (pin 17) to program the Lighting Curve. The following applies: O = Open, G = Ground Pin CS2 CS3 34 17 J1−35 Definition Boeing (Normal Configuration) McDonnell Douglas Invalid (Displays VSI/TRA Red X fault if wired) Invalid (Displays VSI/TRA Red X fault if wired) CONFIGURATION STRAP #4 INPUT (NO): For −86X, −88X, and −89X units, CS4 is paired with CS5 (pin 36) to program the VSI/TRA to display VSI only, VSI/RA or VSI/RA/TA. The following applies: O = Open, G = Ground Pin CS4 CS5 35 36 Definition VSI/RA/TA VSI/RA VSI Only Invalid For −84X units, CS4 is paired with CS3 (pin 17) to program the Display Range Format. The following applies: O = Open, G = Ground Pin CS4 CS3 35 17 Page 4−34 15 Dec 2005 Definition 14 Nautical Mile Range 6 Nautical Mile Range 40 nautical Mile Range 6 Nautical Mile Range 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−5. 41−Pin VSI/TRA Interface Descriptions (cont) Connector Pin Designation J1−36 Functional Description CONFIGURATION STRAP #5 INPUT (NO): For −86X, −88X, and −89X units, see pin 35. For −84X units, CS5 is paired with CS6 (pin 37) to program the Altitude Band. The following apply: O = Open, G = Ground Pin CS5 CS6 36 37 Definition Normal −A to +A Above −A to +B Below −B to +A Unrestricted Range J1−37 CONFIGURATION STRAP #6 INPUT (NO): For −84X units this pin is paired with CS5 to program the altitude band. See pin 36. For −86X, −88X, and −89X units, CS6 is used to program the Traffic Filter. If pin 37 is Open, the VSI/TRA is programmed to NOT display other traffic. If pin 37 is grounded, other traffic is displayed. J1−38 CONFIGURATION STRAP #7 INPUT (NO): This configuration strap is used during factory test to take the VSI/TRA out of flight mode and into test mode when grounded. This pin must be left unwired, “Open” in all aircraft installations. J1−39 DC GROUND INPUT: To be connected to aircraft dc Ground. J1−40 115 V ac, 400 HZ POWER INPUT (HI): This pin, along with its return line (pin 23) supplies power to the VSI/TRA. Connect power through a 1 Amp circuit breaker. J1−41 CONFIGURATION STRAP #8 INPUT (NO): For −88X and −89X units, CS8 is paired with CS3 (pin 17) to program the Filter Time Constant. The following apply: O = Open, G = Ground Pin CS8 CS3 41 17 Definition 5.0 Second Delay 6.4 Second Delay 3.2 Second Delay 1.6 Second Delay 34−43−23 Page 4−35 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−6. 55−Pin VSI/TRA Interface Descriptions Connector Pin Designation J1−1, 6 Functional Description SECONDARY ARINC 565 VERTICAL SPEED BUS INPUT: [J1−6 (HI), J1−1 (LO)] This two wire bus input receives ARINC 565 vertical speed data from the cross−side display when the bootstrap mode is activated. This bus input is connected to the R/C Bootstrap Output bus on the cross−side display as follows: J1−6 of the on−side display is connected to J1−14 of the cross−side display. J1−1 of the on−side display is connected to J1−13 of the cross−side display. J1−2 VERTICAL SPEED DC RATE INPUT: Pins 2, 3 and 8 are inputs to the VSI/TRA from an ARINC 575 air data computer indicating vertical speed. Pin 2 receives a +10 to −10 V dc rate signal from the ADC. Pin 3 is a −12 V dc regulated reference voltage from the ADC and pin 8 is a +12 V dc regulated reference voltage from the ADC. Also see pins 29, 31, 32, and 33. J1−3 VERTICAL SPEED −DC REFERENCE INPUT: See pin 2. J1−4 BOOTSTRAP REFERENCE OUTPUT: This output sends the bootstrap ARINC 565 ac reference voltage to the cross−side display. The output is connected to the Secondary 26 V ac Reference Input (pin 7) of the cross−side display. J1−5 VERTICAL SPEED NO. 2 VALID DISCRETE INPUT: This discrete input receives bootstrap ARINC 565 vertical speed valid data from the cross−side display. The input is connected to the Vertical Speed Output (pin 49) of the cross−side display. J1−7 SECONDARY 26 V ac REFERENCE INPUT: This input receives the bootstrap ARINC 565 ac reference voltage from the cross−side display. The input is connected to the Bootstrap Reference Output (pin 40) of the cross−side display. J1−8 VERTICAL SPEED +DC REFERENCE INPUT: See pin 2. J1−9 PRIMARY VERTICAL SPEED 26 V ac, 400 HZ REFERENCE INPUT: See pins 10, 11. J1−10, 11 Page 4−36 15 Dec 2005 PRIMARY VERTICAL SPEED ARINC 565 AC INPUT: (J1−11 HIGH, J1−10 LOW) Pins 9, 10, 11, and 12 are inputs to the VSI/TRA from an ARINC 565 air data computer or IRS. A 26 V ac, 400 Hz reference signal is received on pin 9 (HI). Pin 11 (HI) and pin 10 (LO) provide an amplitude modulated 400 Hz signal with a maximum voltage of " 6.25 volts. The RMS value of this signal is used by the VSI/TRA to compute and display the vertical rate. The phase of this signal is compared with the reference signal to determine if the rate is positive or negative. An in−phase equals a positive rate, an out−of−phase signal indicates a negative rate. Also see pins 12, 29, 31, 32, and 33. 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−6. 55−Pin VSI/TRA Interface Descriptions (cont) Connector Pin Designation Functional Description J1−12 VERTICAL SPEED NO. 1 VALID DISCRETE INPUT: The VSI/TRA receives a 28 V dc signal from an ARINC 575 or 565 air data computer indicating its valid operation. An “Open” at this pin indicates an invalid vertical speed signal from ADC #1. This pin is only used when pins ( 2, 3, 8) or (9, 10, 11) are used and on the #1 VSI/TRA display. Also see pins 2, 10, and 11. J1−13, 14 R/C BOOTSTRAP OUTPUT: [J1−14 (HI), J1−13 (LO)] This two wire bus output sends ARINC 565 vertical speed data to the cross−side display when the bootstrap mode is activated. These pins are connected to the ARINC 565 Secondary Vertical Speed Input bus on the cross−side display as follows: J1−14 of the on−side display is connected to J1−6 of the cross−side display. J1−13 of the on−side display is connected to J1−1 of the cross−side display. J1−15 BOOTSTRAP COMMAND OUTPUT: This pin is connected to the Source Select #2 (SS2) discrete input, pin 29, within the VSI/TRA. The output provides an Open/28 V dc discrete that can be used to annunciate the bootstrap function. This output is normally not used. J1−17 CONFIGURATION STRAP #5 INPUT (NO): For −84X units, CS5 is paired with CS6 (pin 37) to program the altitude band. The following apply: O = Open, G = Ground CS5 CS6 Pin 17 18 Definition Normal −A to +A Above −A to +B Below −B to +A Unrestricted Range For −86X, −88X and −89X units, CS5 is paired with CS4 (pin 36) to program the Display Format. The following apply: O = Open, G = Ground Pin CS5 CS4 17 36 Definition VSI/RA/TA VSI/RA VSI Only Invalid J1−18 CONFIGURATION STRAP #6 INPUT (NO): For −84X units, see pin 17. For −86X, −88X, and −89X units CS6 is used to program the Traffic Filter. If pin 18 is Open, the VSI/TRA is programmed to not display other traffic. If pin 18 is grounded, other traffic will be displayed. J1−19 CONFIGURATION STRAP #7 INPUT (NO): This configuration strap is used during factory test to take the VSI/TRA out of flight mode and into test mode when grounded. This pin must be left unwired, “Open” in all aircraft installations. 34−43−23 Page 4−37 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−6. 55−Pin VSI/TRA Interface Descriptions (cont) Connector Pin Designation Functional Description J1−20 CHASSIS GROUND INPUT: Connected to aircraft frame. Also used to connect ARINC cable shields to the chassis. J1−21 DC GROUND INPUT: To be connected to aircraft dc Ground. J1−22 CONFIGURATION STRAP #8 INPUT (NO): For −84X and −86X units, CS8 is not used and pin J1−22 must remain Open. For −88X and −89X units, CS8 is paired with CS3 (pin 35) to program the Filter Time Constant. The following apply: O = Open, G = Ground Pin CS8 CS3 22 35 J1−23,24 Definition 5.0 Second Delay 6.4 Second Delay 3.2 Second Delay 1.6 Second Delay REMOTE LIGHT SENSOR INPUT: (J1−23 HIGH, J1−24 LOW ) This input at pins 23 and 24 provides a means of controlling the VSI/TRA back lighting via a remote light sensor already present in some aircraft (Douglas and Boeing). The VSI/TRA has its own built−in sensor and therefore a remote light sensor need not be used in all installations. Program the VSI/TRA for a remote light sensor, as described under pin 34 and 35. J1−25, 44 ARINC 429 TCAS BUS INPUT: [J1−25 (A), J1−44 (B)] This differential pair input is a high speed ARINC 429 bus (100K bit/second nominal) that receives Traffic and Resolution Advisory data supplied by the TCAS computer unit. J1−26, 45 ARINC 429 VERTICAL SPEED NO. 2 BUS INPUT: [J1−26 (A), J1−45 (B)] This differential pair input is a low speed bus (12.5K bits/second nominal) that receives ARINC 429 vertical speed data from the secondary (#2) digital ADC or the #2 PTM. J1−27, 46 ARINC 429 INERTIAL REFERENCE SYSTEM BUS INPUT: [J1−27 (A), J1−46 (B)] This differential pair input is a low speed ARINC 429 bus (12.5K bits/second nominal) that receives vertical speed data from an Inertial Reference System. J1−28 Page 4−38 15 Dec 2005 RA VALID DISCRETE OUTPUT: This output discrete indicates the ability of the VSI/TRA to perform as a resolution advisory and/or a traffic advisory display. If the VSI/TRA fails, this discrete presents an open. Normal operation causes a ground. This discrete is monitored by the TCAS computer unit. 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−6. 55−Pin VSI/TRA Interface Descriptions (cont) Connector Pin Designation J1−29 Functional Description SOURCE SELECT #2 DISCRETE INPUT: This discrete input is used in conjunction with source select discrete #1 (SS1) and configuration straps CS0 and CS1 to program the VSI/TRA to accept and use the vertical speed data being supplied. The following applies: O = Open, G = Ground, 28V = 28 V dc and X = Don’t Care. SS2 SS1 CS0 CS1 Pin 29 31 32 33 Definition 28V 28V ARINC 429 HS Primary ARINC 429 HS Secondary Pressure Transducer Module (PTM) ARINC 575 ADC A310 ADC Secondary A310 ADC Primary ARINC 565 ac Secondary ARINC 565 ac Primary ARINC 429 LS Primary ARINC 429 LS Secondary J1−31 SOURCE SELECT #1 DISCRETE INPUT (NO): See pin 29. J1−32 CONFIGURATION STRAP #0 INPUT (NO): See pin 29. J1−33 CONFIGURATION STRAP #1 INPUT (NO): See pin 29. J1−34 CONFIGURATION STRAP #2 INPUT (NO): For −84X and −88X units, this pin programs the VSI/TRA to use the remote light sensor input at pins 23 and 24. If CS2 is open, a Boeing Airplane Company remote light sensor type (−10 to +10 V) is expected at pins 23 and 24. If pin 34 is grounded, a McDonnell Douglas Aircraft Company remote light sensor type (0 to 18 V) is programmed. Also see pins 23/24. For −89X units, CS2 is used to program the VSI display for English or Metric. If pin J1−34 is open, information is displayed in English. If pin 34 is grounded, the information is displayed in Metric. For −86X units, CS2 is used with CS3 (pin 17) to program the lighting curve. The following applies: O = Open, G = Ground CS2 CS3 Pin 34 35 Definition Boeing (Normal Configuration) McDonnell Douglas Invalid (Displays VSI/TRA Red X fault if wired) Invalid (Displays VSI/TRA Red X fault if wired) 34−43−23 Page 4−39 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−6. 55−Pin VSI/TRA Interface Descriptions (cont) Connector Pin Designation J1−35 Functional Description CONFIGURATION STRAP #3 INPUT (NO): For −86X units, CS3 is paired with CS2 to program the Lighting Curve. See pin 34. For −88X and −89X units, CS3 is paired with CS8 to program the Filter Time Constant. See pin 22. For −84X units, CS3 is paired with CS4 (pin 36) to program the display Range Format. The following applies: O = Open, G = Ground CS3 CS4 Pin 35 36 Definition 14 Nautical Mile Range 6 Nautical Mile Range 40 Nautical Mile Range 6 Nautical Mile Range J1−36 CONFIGURATION STRAP #4 INPUT (NO): For −84X units, CS4 is paired with CS3 to program the Range Format. See pin 35. For −86X, −88X, and −89X units, CS4 is paired with CS5 to program the Display Format. See pin 17. J1−37 CONFIGURATION STRAP COMMON INPUT: This pin is the return line for the configuration strapping pins J1−17, 18, 19, 22, and J1−32 thru 36. The VSI/TRA uses configuration strapping so unique aspects of any given installation may be identified and its functions supported. Each configuration strap (CS) and its associated function becomes active when connected to program common (J1−37). J1−38 115 V ac, 400 HZ POWER INPUT (COMMON): See pin 40. Connect to aircraft AC ground. J1−40 115 V ac, 400 HZ POWER INPUT (HIGH): This pin, along with its return line (pin 38) supplies power to the VSI/TRA. Connect power through a 1 Amp circuit breaker. J1−42, 43 5−VOLT LAMP DIMMING INPUT: (J1−42 LOW, J1−43 HIGH) The VSI/TRA monitors the cockpit lamp voltage bus at pins 42 and 43. This voltage may be either ac or dc. The back lighting in the VSI/TRA is adjusted by and tracks this voltage from 0.5 volts to 5 volts. If this input falls below 0.5 volts or is absent, the VSI/TRA sets itself to a nominal level to prevent the display from going dark due to loss or failure of the lamp dimming bus. J1−47, 48 ARINC 429 VERTICAL SPEED NO. 1 BUS INPUT: [J1−47 (A), J1−48 (B)] This differential pair input is a low speed bus (12.5K bits/second nominal) that receives ARINC 429 vertical speed data from the primary (#1) digital ADC or the #1 PTM. J1−49 VERTICAL SPEED VALID DISCRETE OUTPUT: This discrete output sends bootstrap ARINC 565 vertical speed valid data to the cross−side display. The output is connected to the Vertical Speed Valid Input (pin J1−5) of the cross−side display. Page 4−40 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−6. 55−Pin VSI/TRA Interface Descriptions (cont) Connector Pin Designation Functional Description J1−50 PRESSURE TRANSDUCER MODULE −15 V dc POWER OUTPUT: An optional ACSS PTM may be used in an installation to supply vertical speed information to the VSI/TRA. Pins 50, 51, and 52 supply input power to the PTM. Pin J1−50 is the −15 V dc output pin and is connected to PTM pin 11. J1−51 PRESSURE TRANSDUCER MODULE POWER OUTPUT (COMMON): Connects to PTM pin 8. See pin 50. J1−52 PRESSURE TRANSDUCER MODULE +15 V dc POWER OUTPUT: Connects to PTM pin 5. See pin 50. 34−43−23 Page 4−41 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−7. Pressure Transducer Module Interface Descriptions Connector Pin Designation Functional Description J1−1 CHASSIS GROUND INPUT: Tied to aircraft frame. Also used to connect ARINC 429 cable shields to the chassis. J1−2 EXTERNAL RESET INPUT: This pin is used by factory test only. Do not connect this pin in aircraft installations. J1−3 FAULT DISCRETE OUTPUT: This pin is used by factory test only. Do not connect this pin in aircraft installations. J1−5 +15 V dc POWER INPUT: This power input is supplied by the VSI/TRA. The PTM receives ±15 V dc from the VSI/TRA. The ±12 V dc used by the PTM is derived from this source. J1−7 VERTICAL SPEED ARINC 429 (A) BUS OUTPUT: Bus output that is paired with J1−13 to transmit vertical speed information to the VSI/TRA. J1−8 ±15 V dc POWER GROUND INPUT: This pin is the ±15 V dc return from the VSI/TRA. It must be connected to the VSI/TRA. Also see pins 5 and 11. J1−11 −15 V dc POWER INPUT: See pin 5. J1−13 VERTICAL SPEED ARINC 429 (B) BUS OUTPUT: See pin 7. Page 4−42 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−8. XS−950 Data Link Transponder Interface Descriptions Connector Pin Designation Functional Description P1A−1A THRU ENCODING ALTIMETER #2 INPUTS: P1A−1K, AND These Mode C pulse discrete inputs allow for altitude inputs from an encoding altimeter P1A−2K that contains a discrete 11 wire interface. The standards for this interface are defined in ARINC Characteristic 572, “Air Traffic Control Transponder”. The inputs use ground/open logic levels. NOTE: Two encoding altimeters are required if the transponder is used with TCAS. P1A−2A, 2B ARINC 429 ADLP TO COMM A/B BUS INPUT: [P1A−2A (A), P1A−2B (B)] or ARINC 429 FMC/GNSS Input Four ARINC 429 busses are provided for interfacing to a Mode S Airborne Data Link Processor (ADLP). The COMM A/B input and output busses are used for the transfer of standard length messages to and from the ADLP. The COMM C/D input and output busses are used for the transfer of extended length messages (ELM) to and from the ADLP. P1A−2A and 2B can also be configured to a FMC/GNSS input. The standard for this interface is defined on ARINC 718−A. For additional information on the FMC/GNSS input, refer to ARINC 743A. This input is configured by grounding or oponing P1B−5H. P1A−2C, 2D ARINC 429 ADLP TO COMM C/D BUS INPUT: [P1A−2C (A), P1A−2D (B)] or ARINC 429 IRS/RMS/Data Concentrator See pins P1A−2A, −2B P1A−2E, 2F ARINC 429 COMM C/D TO ADLP BUS OUTPUT: [P1A−2E (A), P1A−2F (B)] or ARINC 429 General Output Bus See pins P1A−2A, −2B P1A−3B XPDR FAIL DISCRETE OUTPUT #2: This discrete output is set to annunciate an internal transponder failure or the Mode S address is illegal (All 0’s or 1’s). A ground logic threshold (<3.0 V dc) is output when the transponder is operating normally, and an open logic threshold (resistance >100K ohms to unit ground) when a failure has occurred. The output is capable of sinking 200 mA of current. Connect this pin to the Control Panel XPDR FAIL #2 input. 34−43−23 Page 4−43 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−8. XS−950 Data Link Transponder Interface Descriptions (cont) Connector Pin Designation P1A−3C, P1A−3D, P1A−3E, P1A−3F Functional Description CABLE DELAY PROGRAM INPUTS: The Cable Delay Program Inputs are used to compensate for the difference in propagation delays in the transponder due to antenna transmission line length differences between the top and bottom antennas. The inputs use ground/open logic levels. The Cable Delay Program Common (pin P1A−3F) can be used to supply a ground. Program Pin Differential Transponder P1A−3C P1A−3D P1A−3E Delay Adjustment Open Open Open Open Open Open Ground Ground Open Ground Open Ground 0−50 nsec 51−150 nsec 151−250 nsec 251−350 nsec No Change Add Delay to Top Channel Add Delay to Top Channel Add Delay to Top Channel Ground Open Open 0−50 nsec No Change Ground Open Ground 51−150 nsec Add Delay to Bottom Channel Ground Ground Open 151−250 nsec Add Delay to Bottom Channel Ground Ground Ground 251−350 nsec Add Delay to Bottom Channel The differential delay column is the difference in the round trip cable delay between the top and bottom antenna cables. The differential delay can be calculated as follows: [Top length in feet − Bottom length in feet] X [Characteristic Delay (nsec/foot)] X 2. P1A−3G, P1A−3H, P1A−3J P1A−4A THRU P1A−4J Page 4−44 15 Dec 2005 SDI PROGRAM INPUTS: The SDI program inputs are used to identify the system number in the installation. The inputs use ground/open logic levels. The SDI Common (pin P1A−3J) can be used to supply a ground. Program Pin P1A−3G P1A−3H Definition Open Open Ground Ground Not Applicable (SDI = 00) LRU System #1 (SDI = 01) LRU System #2 (SDI = 10) LRU System #3 (SDI = 11) Open Ground Open Ground ARINC 565 ANALOG AIR DATA COMPUTER #1 INPUTS: These input pins allow for altitude information from an Analog Synchro Altitude Interface to be connected to the transponder. The standards for this interface are defined in ARINC 565, “Subsonic Air Data System”. 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−8. XS−950 Data Link Transponder Interface Descriptions (cont) Connector Pin Designation P1A−5A, P1A−5B, P1A−5C, P1A−5D Functional Description MAXIMUM TRUE AIRSPEED PROGRAM INPUTS: The Maximum True Airspeed inputs are used for strapping the maximum cruise airspeed capability of the aircraft. The inputs use ground/open logic levels. The Max True Airspeed Common (pin P1A−5D) can be used to supply a ground. P1A−5A Open Ground Open Ground Open Ground Open Ground Program Pin P1A−5B P1A−5C Open Open Ground Ground Open Open Ground Ground Open Open Open Open Ground Ground Ground Ground Definition No Maximum Airspeed Available Maximum Airspeed ≤75 Knots Maximum Airspeed >75 and ≤150 Knots Maximum Airspeed >150 and ≤300 Knots Maximum Airspeed >300 and ≤600 Knots Maximum Airspeed >600 and ≤1200 Knots Maximum Airspeed >1200 Knots Not Assigned P1A−5E, 5F ARINC 429 TX COORDINATION BUS INPUT: (P1A−5E [A], P1A−5F [B]) Two high speed ARINC 429 busses (100K bits/second nominal) are provided to interface between the transponder and a TCAS computer unit. The standards for this interface are defined in ARINC Characteristic 735, “Traffic Alert and Collision Avoidance System”. P1A−5G, 5H ARINC 429 XT COORDINATION BUS OUTPUT: (P1A−5G [A], P1A−5H [B]) See pins P1A−5E, 5F. P1A−5J AIR / GROUND #2 DISCRETE INPUT: This pin and AIR / GROUND #1 Discrete Input (pin P1A−5K) provide a method for the transponder to automatically determine the Air/Ground status of the aircraft. The status is used in replies to Mode S interrogations and to inhibit replies to certain types of interrogations. Both inputs use ground/open logic, where a Ground specifies an “On the Ground” condition and an Open specifies an “In the Air” condition. When this pin is connected to the Air/Ground Relay (Squat Switch), the transponder will not reply to ATCRBS, ATCRBS/Mode S All Call, or Mode S All Call when the input is set for “On the Ground”. This input should be connected to the Air/Ground Relay for normal operation. P1A−5K AIR / GROUND #1 DISCRETE INPUT: See pin P1A−5J. When this pin is connected to the Air/Ground Relay (Squat Switch), the transponder replies to all types of interrogations irregardless of the state of the input. This input allows the transponder to reply during a ramp test. P1A−6A, 6B FMC #1/Gineral In #2 This differential pair input supports common existing FMC configurations where flight ID is available on the FMC General Purpose output bus but the other Enhanced data is only available on a display bus. 34−43−23 Page 4−45 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−8. XS−950 Data Link Transponder Interface Descriptions (cont) Connector Pin Designation Functional Description P1A−6C, 6D ARINC 615 AIRBORNE DATA LOADER BUS INPUT: (P1A−6C [A], P1A−6D [B]) The Airborne Data Loader interface consists of two high speed ARINC 429 busses (100K bits/second nominal) and a ground/open logic discrete (pin P1A−6G). The interface allows for operational transponder software to be loaded into the unit through an onboard data loader. The standards for this interface are defined in ARINC 615 “Airborne Computer High Speed Data Loader”. P1A−6E, 6F ARINC 615 AIRBORNE DATA LOADER BUS OUTPUT: (P1A−6E [A], P1A−6F [B]) See pins P1A−6C, 6D P1A−6G P1A−6H, 6J P1A−6K ADL INPUT LINK A DISCRETE INPUT: See pins P1A−6C, 6D ARINC 575 AIR DATA COMPUTER #1 INPUT: (P1A−6H [A], P1A−6J [B]) This differential pair input is a low speed ARINC 575 bus (12.5K bits/second nominal) that can be used to input altitude information from an ARINC 575 Air Data System. The standards for this interface are defined in ARINC Characteristic 575, “Subsonic Air Data System (Digital) DADS”. SINGLE / DUAL ANTENNA PROGRAM INPUT: This pin allows for installation of the transponder in a system with a single bottom mounted antenna or dual top and bottom mounted antennas. The input uses ground/open logic as follows: Ground = Single Bottom Mounted Antenna Configuration Open = Diversity Antenna Configuration P1A−7A, 7B P1A−7D ARINC 429 CONTROL DATA PORT A BUS INPUT: (P1A−7A [A], P1A−7B [B]) The control panel data can be input into the transponder on either of two low speed ARINC 429 busses. (Ports A and B). The control data is contained in labels 013, 015, and 016. The port is selected by the CONTROL DATA PORT SELECT Discrete Input (pin PIA−7D). CONTROL DATA PORT SELECT INPUT: See pins P1A−7A, 7B. This discrete input is used to select which port is used to input control data to the transponder. This input uses a ground/open logic as follows: Ground Specifies Port A Open Specifies Port B P1A−7E, 7F P1A−7G Page 4−46 15 Dec 2005 ARINC 429 CONTROL DATA PORT B BUS INPUT: (P1A−7E [A], P1A−7F [B]) See pins P1A−7A, 7B. STANDBY / ON DISCRETE INPUT: This discrete input is connected to the Control Panel STANDBY/ON output. The input selects the active or standby status of the transponder. A ground causes the transponder to be in standby, and an open causes the transponder to be active. 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−8. XS−950 Data Link Transponder Interface Descriptions (cont) Connector Pin Designation P1A−7H, 7J Functional Description ARINC 429 ADC #1 BUS INPUT: (P1A−7H [A], P1A−7J [B]) The altitude information for the transponder can be obtained from an ARINC 706 Air Data System through two low speed ARINC 429 data busses. The standards for this interface are defined in ARINC Characteristic 706, “Mark 5 Subsonic Air Data System”. This differential pair input is a low speed ARINC 429 bus that inputs uncorrected pressure altitude (ARINC label 203) from an altitude source. Also see pins P1B−5A, 5B. P1A−71 TOP ANTENNA RF INPUT: RF input from top antenna. P1B−1A THRU P1B−3E MODE S ADDRESS INPUTS: The Mode S Address is a unique 24−bit code assigned to each aircraft. Pins P1B−1A thru P1B−3E are used to program this 24−bit binary number. The inputs must be set according to this binary number representation. Each binary 1 represents a Grounded pin and each binary 0 represents an Open pin. Pin P1B−1A represents the most significant bit (MSB) of the binary number and pin P1B−3D represents the least significant bit (LSB) of the binary number. NOTE: An address of all 0’s or all 1’s is an illegal address, and can cause the aircraft to be invisible to TCAS II equipped aircraft in flight. Never use an illegal address for an installed system. P1B−3H FUNCTIONAL TEST DISCRETE INPUT: This discrete input is used to put the transponder in a functional test mode. The functional test that is performed by the transponder is equivalent to a test that is initiated from the control panel. The input uses ground/open logic as follows: Ground = Initiate Functional Test Open = Normal Operation P1B−3J ALTITUDE COMPARISON FAIL DISCRETE OUTPUT: This discrete output annunciates a comparison failure in the altitude data for the transponder if Gillham altitude data is selected. The output annunciates a failure if the two altitude sources are not within 500 feet. The output drives a ground logic threshold (voltage of less than 3.0 V dc) when the altitude is valid, and an open logic threshold (resistance is greater than 100K ohms to unit ground) when a failure has occurred. The output is capable of sinking 200 mA of current. P1B−3K XPDR FAIL DISCRETE OUTPUT #1: This discrete output is set to annunciate an internal transponder failure or that the Mode S address is illegal (All 0’s or 1’s). The output will source a voltage of greater than 5.0 V dc at 100 mA of current when a failure has occurred, and an open circuit (resistance of greater than 100k ohms to unit ground) when the transponder is operating normally. The output contains diode isolation. Connect this pin to the Control Panel XPDR FAIL #1 input. P1B−4A THRU ENCODING ALTIMETER #1 INPUTS: P1B−4K, AND First of two Encoding Altimeter interfaces. See pins P1A−1A thru 4K and P1A−2K. P1B−5K 34−43−23 Page 4−47 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−8. XS−950 Data Link Transponder Interface Descriptions (cont) Connector Pin Designation Functional Description P1B−5A, 5B ARINC 429 AIR DATA COMPUTER #2 BUS INPUT: (P1B−5A [A], P1B−5B [B]) Second ARINC 429 Air Data Computer bus input. See pins P1A−7H, 7J. P1B−5C, 5D ARINC 575 AIR DATA COMPUTER #2 BUS INPUT: (P1B−5C [A], P1B−5D [B]) Second ARINC 575 Air Data Computer bus input. See pins P1A−6H, 6J. P1B−5E, 5F ARINC 429 COMM A/B TO ADLP BUS OUTPUT: (P1B−5E [A], P1B−5F [B]) See pins P1A−2A, 2B. P1B−5G Extended Squitter Disable This input is used to disable all Extended Squitter functions: Ground = All functions disabled Open = All functions enabled P1B−5H MODE S DATA LINK PROGRAM INPUT: This program input specifies if the transponder is connected to an Airborne Data Link Processor (ADLP) Unit. The input uses ground/open logic as follows: Ground = ADLP is Installed Open = ADLP is not installed P1B−5J ANTENNA BITE PROGRAM INPUT: This program input specifies if the transponder is to perform a built−in test to the antenna subsystem. The transponder performs a continuity check of the antenna to make sure it is not an open circuit. The input uses ground/open logic as follows: Ground = Enables Antenna Subsystem Test Open = Disables Antenna Subsystem Test P1B−6A, 6B ARINC 429 MAINTENANCE DATA BUS INPUT: (P1B−6A [A], P1B−6B [B]) Two low speed ARINC 429 busses (12.5K bits/second nominal) are provided to interface between the transponder and an onboard maintenance system. The maintenance computer interface is designed to work with all airframe models and types. P1B−6C, 6D ARINC 429 MAINTENANCE DATA BUS OUTPUT: (P1B−6C [A], P1B−6D [B]) See pins P1B−6A, 6B. P1B−6E Page 4−48 15 Dec 2005 AIR DATA SOURCE SOURCE SELECT DISCRETE INPUT: The transponder contains dual inputs for all types of altitude sources. This discrete input specifies which of the two inputs are used to obtain altitude information. Ground = Altitude Source No. 2 Open = Altitude Source No. 1 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−8. XS−950 Data Link Transponder Interface Descriptions (cont) Connector Pin Designation P1B−6F, P1B−6G, P1B−6H Functional Description ALTITUDE TYPE SELECT PROGRAM INPUT: The Altitude Type Select program pins are used to configure the transponder for the type of altitude source that is connected to it. The inputs use ground/open logic. The Altitude Type Select Common (pin P1B−6H) can be used to supply a ground. Program Pin P1B−6F P1B−6G Definition Ground Ground Open Open Selects Gillham Altitude Source Selects ARINC 575 Altitude Source Selects ARINC 407 Synchro Altitude Source Selects ARINC 429 Altitude Source Ground Open Ground Open P1B−7A THRU P1B−7J ARINC 565 ANALOG AC AIR DATA COMPUTER #2 INPUTS: Second ARINC 565 Analog AC Air Data Computer Input. See pins P1A−4A Thru 4J. P1B−71 BOTTOM ANTENNA RF INPUT: RF input from bottom antenna. P1C−1 XPDR 115 V ac INPUT POWER: (H) This pin along with the XPDR 115 V ac RETURN line (pin P1C−7) provides the 115 V ac power requirements for the transponder. NOTE: Only −10XXX thru −54XXX transponders accept 115 V ac, 400 Hz input power. If the 115 V ac version is used, the power should be connected through a 5 amp circuit breaker, and the pins for the 28 V dc input (P1C−10 and P1C−3) should be left unconnected. P1C−3 XPDR +28 V dc RETURN: (L) See pin P1C−10. P1C−4 XPDR OFF (NO) INPUT: This discrete input is used to turn the transponder power supply OFF. It should not be connected in aircraft installations. P1C−6 FAN +28 V dc OUTPUT: (+) The 28 V dc version of the transponder can control an externally mounted 28 volt fan to provide cooling air for the transponder. The Fan +28 V dc Output (P1C−6) should be connected to the positive input of the fan, and the Fan Return (NO) Output (P1C−9) should be connected to the negative input of the fan. The output has the capability to drive a fan that draws up to 200 mA of current. The fan is turned on when the internal transponder temperature rises above 30 degrees centigrade. In the 115 V ac version of the transponder, the outputs are not used. P1C−7 XPDR 115 V ac RETURN: (C) See pin P1C−1. P1C−8 SIGNAL GROUND INPUT: Connect to Aircraft Signal Ground. 34−43−23 Page 4−49 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−8. XS−950 Data Link Transponder Interface Descriptions (cont) Connector Pin Designation Functional Description P1C−9 FAN RETURN (NO): (−) See pin P1C−6. P1C−10 XPDR +28 V dc INPUT POWER: (H) This pin along with the +28 V dc RETURN line (P1C−3) provide the 28 V dc power requirements for the transponder. NOTE: Only −55XXX thru −99XXX transponders accept 28 V dc input power. If the 28 V dc version is used, the power should be connected through an 8 amp circuit breaker, and the pins for the 115 V ac input (P1C−1 and P1C−7) should be left unconnected. P1C−11 CHASSIS GROUND INPUT: Connect to aircraft frame. P1C−12, P1C−13 MUTUAL SUPPRESSION BUS INPUT/OUTPUT: L−Band suppression coax must be RG−142 or equivalent coaxial cable. P1C−12 and P1C−13 are connected internally. Connection to only one pin is required. The Interface descriptions that follow are for the 53−pin ARINC 615 Portable Data Loader connector J1 mounted on the front panel of the transponder. These descriptions are used to make up the cable that is used to interface between the transponder and the ARINC 615 Data Loader or a RS−232 PC Serial Port. J1−1, 2 XPDR ARINC 429 PDL BUS INPUT: (J1−1 [A], J1−2 [B]) This differential pair input is a high speed ARINC 429 bus (100K bits/second nominal) is used to input data from the data loader to the transponder. The standards for this interface are defined in ARINC 615 “Airborne Computer High Speed Data Loader”. These pins should be connected to pins 1 and 2 of the PDL cable interface. J1−5 INPUT BUS SHIELD: The shields from the input bus (J1−1, 2) should be connected to this pin. J1−8, 9 XPDR ARINC 429 PDL BUS OUTPUT: (J1−8 [A], J1−9 [B]) This differential pair output is a high speed ARINC 429 bus (100K bits/second nominal) used to output data from the transponder to the data loader. The standards for this interface are defined in ARINC 615 “Airborne Computer High Speed Data Loader”. These pins should be connected to pins 8 and 9 of the PDL cable interface. J1−16 OUTPUT BUS SHIELD: The shields from the output bus (J1−8, 9) should be connected to this pin. J1−18 PDL LINK A: Connect this pin to pin 18 of the PDL cable interface. J1−19 PDL LINK B: Connect this pin to pin 19 of the PDL cable interface. Page 4−50 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−8. XS−950 Data Link Transponder Interface Descriptions (cont) Connector Pin Designation J1−20, 22 Functional Description 115 V ac POWER OUTPUT: (J1−20 [H], J1−22 [C]) These power output pins provide the 115 V ac operating power for the data loader. NOTE: Only the 115 V ac version transponders provide this output. If a 28 V dc version transponder is installed, either the data loader must be able to operate from 28 V dc or the data loader 115 V ac input power must be connected to a source external to the transponder. The 115 V ac (H) and 115 V ac (C) should be shielded or twisted and shielded with an insulating jacket over the shield. The shield should be connected to chassis ground (pin 21). J1−21 CHASSIS GROUND: Connect 115 V ac power shields to this pin. J1−37, 38 28 V dc POWER OUTPUT: (J1−37 [HI], J1−38 [LO]) These power output pins provide the 28 V dc operating power for the data loader. These pins are used only if the data loader operates from 28 V dc. J1−40 J1−41 J1−48,49 RS−232 PDL INPUT: RS−232 PDL OUTPUT LOGIC COMMON (Gnd) These pins would be connected to an RS−232 Serial Port as follows. Most RS−232 Serial Ports use either a 9 pin RS−232 (COM) connector or a 25 pin RS−232 (COM) connector. ARINC 615 PC COM1 OR COM2 PC COM1 OR COM2 CONNECTOR PIN 9 PIN CONNECTOR 25 PIN CONNECTOR 40 41 48 or 49 NOTE: J1−50 J1−51 J1−52 J1−53 PDL PDL PDL PDL PC TX (pin 3) PC RX (pin 2) Ground (pin 5) PC TX (pin 2) PC RX (pin 3) Ground (pin 7) When using a RS−232 interface, transponder pin J1−18 (Link A) and pin J1−19 (Link B) must be connected (tied together) to do a software upload. The pins should be open to verify the software status. FUNCTION FUNCTION FUNCTION FUNCTION DISCRETE DISCRETE DISCRETE DISCRETE #1 #2 #3 #4 INPUT: INPUT: INPUT: INPUT: These pins are used to receive discrete functional information from the data loader. These pins should be connected to the PDL cable interface. 34−43−23 Page 4−51 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−9. RCZ−852 Diversity Mode S Transponder Interface Descriptions Connector Pin Designation J1−1, 2 Functional Description XPDR +28 V FAN PWR & +28V FAN RTN: (J1−1 LOW, J1−2 HIGH) The fan discrete outputs supply a switched, filtered +28 volts for a dc fan. The RCZ−852 Transponder has an internal fan built into the unit, so external cooling is not required. Pins J1−1 and J1−2 should not be connected. J1−3 MUTUAL SUPPRESSION BUS I/O: This bus is a single conductor, shielded bidirectional line that connects to all aircraft L−Band equipment. It is used to desensitize the associated receiver inputs while transmitting. J1−7 XPDR +28 V RTN: See pins 8, 9. J1−8 J1−9 XPDR +28 V PWR: These pins along with there return lines (J1−7 and J1−20) provide the 28 volt power requirements for the transponder. J1−11 PROGRAM ENABLE INPUT: Bench test function. Do not connect this pin in aircraft installations. J1−12 XPDR RS232 TX OUTPUT: Bench test function. Do not connect this pin in aircraft installations. J1−17, J1−18 J1−19, J1−21 DC GROUND INPUT: To be connected to aircraft dc ground. J1−23 XPDR VALID (PO) OUTPUT: This discrete outputs the status of the transponder continuous monitor tests. It is the same as the XPDR VALID (NO) output (J1−100) except the discrete is a positive/open logic. A +28 V dc (200 mA maximum) is provided when the transponder is operational and an active transponder mode is selected. An Open (>100K ohms resistance to ground) output is provided when the transponder has failed or the standby mode is selected. J1−24 XPDR RS232 RX INPUT: Bench test function. Do not connect this pin in aircraft installations. J1−25 PROGRAM +15 V OUTPUT: Bench test function. Do not connect this pin in aircraft installations. J1−26, 27 XPDR TO TCAS ARINC 429 BUS OUTPUT: (J1−26 [A], J1−27 [B]) This differential pair output is a high speed ARINC 429 bus (100K bits/second nominal) that sends data to the TCAS computer unit. The data bus conforms to the ARINC 718−A and ARINC 735 standards for TCAS to transponder interface. J1−28, 29 XPDR TO DLP A/B ARINC 429 BUS OUTPUT: (J1−28 [A], J1−29[B]) This differential pair output is a high speed ARINC 429 bus (100K bits/second nominal) that sends data to an airborne data link processor (ADLP) system. The data bus is used to transfer COMM−A and COMM−B messages between the two systems and conforms to the ARINC 718−A standard for ADLP to transponder interface. Page 4−52 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−9. RCZ−852 Diversity Mode S Transponder Interface Descriptions (cont) Connector Pin Designation Functional Description J1−30,31 XPDR TO DLP C/D ARINC 429 BUS OUTPUT: (J1−30 [A], J1−31 [B]) This differential pair output is a high speed ARINC 429 bus (100K bits/second nominal) that sends data to an airborne data link processor (ADLP) system. The data bus is used to transfer COMM−C and COMM−D messages between the two systems and conforms to the ARINC 718−A standard for ADLP to transponder interface. J1−32, 33 ADC1 TO XPDR ARINC 429/575 BUS INPUT: (J1−32 [A], J1−33 [B]) This differential pair input is a low speed ARINC 429 or 575 bus that inputs uncorrected pressure altitude (ARINC label 203) from an altitude source. The input accepts either ARINC 429 or 575 data format, which is selected by the altitude source straps (W33, W34) on the Strap Assembly. The ALT SRC SEL2 (NO) discrete, pin 60, selects either ADC1 or ADC2. J1−34, 35 CTL1 TO XPDR ARINC 429 BUS INPUT: (J1−34 [A], J1−35 [B]) The transponder can receive data from the control panel(s) on the CTL1 TO XPDR and CTL2 TO XPDR data busses. The bus used, is selected by the CTL SRC SEL1 (NO) DISCRETE. See pin 61. The data bus not selected will not be processed. These differential pair inputs are low speed ARINC 429 busses (12.5K bits/second nominal) that transmits tuning information from the control panel to the transponder. The transponder expects to receive ARINC labels 016 and 031 at an update rate of 100 to 200 milliseconds. Also see CTL2 TO XPDR ARINC 429 bus input (pins 48 and 49). J1−40, 41 TCAS TO XPDR ARINC 429 BUS INPUT: (J1−40 [A], J1−41 [B]) This differential pair input is a high speed ARINC 429 bus (100K bit/second nominal) that receives data from a TCAS computer unit. The data bus conforms to the ARINC 718−A and ARINC 735 standards for TCAS to transponder interface. J1−42, 43 DLP A/B TO XPDR ARINC 429 BUS INPUT: (J1−42 [A], J1−43 [B]) This differential pair input is a high speed ARINC 429 bus (100K bits/second nominal) that receives data from an airborne data link processor (ADLP) system. The data bus is used to transfer COMM−A and COMM−B messages between the two systems and conforms to the ARINC 718−A standard for ADLP to transponder interface. J1−44, 45 DLP C/D TO XPDR ARINC 429 BUS INPUT: (J1−44 [A], J1−45 [B]) This differential pair input is a high speed ARINC 429 bus (100K bits/second nominal) that receives data from an airborne data link processor (ADLP) system. The data bus is used to transfer COMM−C and COMM−D messages between the two systems and conforms to the ARINC 718−A standard for ADLP to transponder interface. J1−46,47 ADC2 TO XPDR ARINC 429/575 BUS INPUT: (J1−46 [A], J1−47 [B]) See pins J1−32, 33 J1−48, 49 CTL2 TO XPDR ARINC 429 BUS INPUT: (J1−48 [A], J1−49 [B]) See pins J1−34, 35 J1−50, 51 XPDR TO CTL ARINC 429 BUS OUTPUT: (J1−50 [A], J1−51 [B]) This differential pair output is a low speed ARINC 429 bus (12.5K bits/second) that transmits control panel input data back to the control panel for verification purposes. These output pins are connected only on some Collins control panels that require feedback from the transponder to make sure it is operating properly. 34−43−23 Page 4−53 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−9. RCZ−852 Diversity Mode S Transponder Interface Descriptions (cont) Connector Pin Designation J1−53 thru 58, J1−67 thru 71 J1−59 Functional Description ENCODING ALTIMETER NO.1 ELEVEN BIT INPUT: Transponder input from Encoding Altimeter No. 1. These eleven lines from the altitude encoder comprise an 11−bit word representative of the aircraft altitude. ALT COMP ENA (NO) DISCRETE INPUT: This discrete input enables or disables altitude comparison when dual Gillham altitude sources are selected via the ALTITUDE SOURCE strap. If comparison is enabled (J1−59 Grounded), the two altitude sources (ENC ALT1 and ENC ALT2) are compared, and are considered valid if they are within 500 feet. If the altitude comparison is enabled and it fails, the altitude data is considered invalid in Mode S replies and altitude data sent to TCAS. If comparison is disabled (J1−59 Open), only the selected altitude source is used. This discrete has no effect if ARINC 429 or 575 altitude sources are used. NOTE: For installations with TCAS that use Gillham encoding altimeter sources, two encoding altimeter sources must be used, and pin J1−59 must be enabled (Grounded). J1−60 ALT SRC SEL2 (NO) DISCRETE INPUT: This discrete input allows selection of one of two altitude sources. An Open causes the transponder to use altitude source No.1, and a Ground causes the transponder to use altitude source No.2. The altitude data sent to TCAS and used for transponder replies is derived from the selected source. J1−61 CTL SRC SEL1 (NO) DISCRETE INPUT: This discrete input is used to select one of two ARINC 429 control tuning ports. A Ground on this pin causes the transponder to use CTL1 TO XPDR bus for tuning data, and an Open causes the transponder to use CTL2 TO XPDR bus for tuning data. The input is used only when the transponder tuning source is an ARINC 429 source in a stand−alone transponder system. When an RSB tuning source is used, the input is ignored. J1−64, 65 FMS TO XPDR ARINC 429 BUS INPUT: (J1−64 [A], J1−65 [B]) This differential pair input is a low speed ARINC 429 bus (12.5K bits/second nominal) that receives basic transponder control data (label 031) and AIS flight ID (labels 233, 234, 235, and 236) from a Flight Management System (FMS). J1−72 XPDR STANDBY (NO) INPUT: This discrete input is connected to the Control Panel STANDBY/ON output. The input selects the active or standby status of the transponder. A ground causes the transponder to be in Standby, and an Open causes the transponder to be active. The input is used only when the transponder tuning source is an ARINC 429 source in a stand−alone transponder system. When an RCB tuning source is used, the input is ignored. NOTE: If using a Collins CTL−92 Controller, this pin is not used. Page 4−54 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−9. RCZ−852 Diversity Mode S Transponder Interface Descriptions (cont) Connector Pin Designation J1−73 Functional Description SQUAT SWITCH 1 (NO) DISCRETE INPUT: This discrete input is used in conjunction with SQUAT SWITCH 2 discrete input (pin 75). The squat switch inputs tell the transponder if the aircraft is on the ground or in the air. The two inputs have different affects on transponder operation, and the status of the two are combined. SQUAT SWITCH 1 (NO) causes the transponder to indicate the in the air/ on the ground condition in replies to interrogations. SQUAT SWITCH 2 (NO) in addition to performing the function of SQUAT SWITCH 1 (NO), also inhibits replies to ATCRBS, ATCRBS/Mode S All−Call, and Mode S All−Call interrogations when the aircraft is “on the ground”. The air/ground polarity is set by the SQUAT SWITCH POLARITY strap. The matrix that follows, shows how the discretes affect the transponder operation: Squat Sw Polarity Strap Squat Switch Inputs 1 (NO) 2 (NO) Transponder Operation Air/Ground ATCRBS/All−Call Status Replies Gnd Gnd Gnd Gnd Open Open Open Open Gnd Gnd Open Open Gnd Gnd Open Open On Ground On Ground On Ground In Air In Air On Ground On Ground On Ground Gnd Open Gnd Open Gnd Open Gnd Open Disabled Enabled Disabled Enabled Enabled Disabled Enabled Disabled J1−74 XPDR OFF (NO) INPUT: This discrete input is used to turn the transponder power supply OFF. It should not be connected in aircraft installations. J1−75 SQUAT SWITCH 2 (NO) DISCRETE INPUT: See pin 73. J1−80 thru 85 J1−94 thru 98 ENCODING ALTIMETER NO. 2 ELEVEN BIT INPUT: Transponder input from Encoding Altimeter No. 2. These eleven (11) lines from the altitude encoder comprise an 11−bit word representative of the aircraft altitude. J1−90 XPDR STRAP +5 VOLT OUTPUT: Connect Strap Board connector pin W1P1−3 (red wire) to J1−90. This output pin provides the +5 volt input power required by the Strap Assembly. J1−91 XPDR STRAP CLOCK (N) OUTPUT: Connect Strap Board connector pin W1P1−6 (blue wire) to J1−91. This output consists of 48 clock pulses that serially shift the system options data out of the Strap Assembly shift registers. J1−92 XPDR STRAP LOAD (N) OUTPUT: Connect Strap Board connector pin W1P1−2 (orange wire) to J1−92. This output is used to load the system options status into the Strap Assembly shift registers during initial system power−up. 34−43−23 Page 4−55 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 4−9. RCZ−852 Diversity Mode S Transponder Interface Descriptions (cont) Connector Pin Designation Functional Description J1−93 XPDR STRAP DATA (P) INPUT: Connect Strap Board connector pin W1P1−7 (white wire) to J1−93. This input receives the serial data from the Strap Assembly that is used to program the desired system options and Mode S address. J1−99 XPDR ACTIVE (NO) OUTPUT: This discrete output can be connected to an RF relay for systems that use a single antenna connected to two transponders for the purpose of switching the antenna to the active transponder. A Ground (200 mA maximum) output is provided when an Active transponder mode is selected. An Open (>100K ohms to ground) output is provided when Standby mode is selected. J1−100 XPDR VALID (NO) OUTPUT: This discrete outputs the status of the transponder continuous monitor tests. A Ground (200 mA maximum) output is provided when the transponder is operational and an active transponder mode is selected. An Open (>100K ohms resistance to ground) output is provided when the transponder has failed or the Standby mode is selected. This pin should be connected to the Control Panel XPDR FAIL input. J1−102 ALT VALID (NO) OUTPUT: This discrete outputs the status of the altitude source when the transponder is in an active mode and altitude reporting is enabled. A Ground (200 mA maximum) is output when the selected altitude source is valid and the transponder is in an altitude reporting mode. An Open (>100K ohms resistance to ground) output is provided when the selected altitude source is invalid or the transponder is in Standby or not in an altitude reporting mode. This pin should be connected to the Control Panel ALT FAIL input if applicable. J1−103 XPDR STRAP GROUND OUTPUT: Connect Strap Board connector pin W1P1−4 (black wire) to J1−103. This output is the return line for the +5 volt output. See pin 90. J1−104 RESERVED FUNCTION: Connect Strap Board connector pin W1P1−1 (green wire) to J1−104. J1−105 RESERVED FUNCTION: Connect Strap Board connector pin W1P1−8 (yellow wire) to J1−105. J2 BOTTOM ANTENNA RF INPUT: RF input signal from bottom antenna. J3 TOP ANTENNA RF INPUT: RF input signal from top antenna. Page 4−56 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System ADJUSTMENT/TEST 1. General The procedures that follow are designed to check for proper operation and satisfactory installation of the TCAS 3000 Traffic Alert and Collision Avoidance System components. Should any failures occur when you do the check out procedures, refer to FAULT ISOLATION as required. 2. Equipment and Materials Table 5−1. Equipment and Materials Name Description Source Digital Multimeter Fluke Model 29 Digital Multimeter John Fluke Mfg Co Inc, Everett, WA TCAS Ramp Tester TCAS−201 Reply Generator Traffic Alert and Collision Avoidance System Test Set IFR Systems, Inc. Wichita, KS NOTE: Equivalent alternatives are permitted for equipment in this list. 3. Initial Harness Checkout (New Installations Only) A. TCAS Computer Unit Harness Checkout Check the TCAS computer unit’s mounting tray connector pins referenced in Table 5−2, to make sure they are not connected or shorted to ground. A ground on these pins can cause damage or degrade system performance. Table 5−2. Computer Unit Harness Checkout Connector Pin No. Pin Function P1C−1 (LBP) 115 V AC (H) TCAS Power P1C−5 (LBP) 115 V AC (H) External Fan P1C−10 (LBP) 28 V AC TCAS Power B. TCAS Controller and Display Unit Harness Checkout Refer to the applicable controller and display unit interconnect diagrams to do continuity measurements and to ensure confidence in wiring for these units. 34−43−23 Page 5−1 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System C. LRU Preinstallation Power Checkout Before you do any operational tests, a power−on check is recommended to reduce the possibility of damage to newly installed system components due to miswired power leads. (1) Make sure all TCAS system components are removed from their mounting trays or that their aircraft mating connector(s) are disconnected. (2) Connect external power to aircraft. (3) Close all TCAS system 115 V, 400 Hz circuit breakers, if applicable, and check for 115 V ac at the appropriate LRU mating connector pins. Refer to the applicable interconnect diagrams for LRU pin numbers. (4) Close all TCAS system 28 V dc circuit breakers, if applicable, and check for 28 V dc at the appropriate LRU mating connector pins. Refer to the applicable interconnect diagrams for LRU pin numbers. (5) If power is misapplied on any connector pin, open the circuit breaker and rework miswired harness. (6) Remove aircraft power. D. Initial System Installation Operational Test The initial checkout of a newly installed system should start with a system self−test and then be followed by a ramp test. The system self−test procedures are referenced in paragraph 4.A. The ramp tests should include a Scenario Test and a Power and Frequency Test. Refer to the applicable TCAS Ramp Tester Operation Manual for procedures to do these tests. If a ACSS VSI/TRA is used as the display instrument, it contains a feature that displays some typical installation errors. See Figure 5−1. If an error is detected during initial installation checkout, the VSI/TRA displays the error as follows: (1) Removes all symbology from the display (2) Displays a red X that covers the entire screen (3) Displays a two digit error code as follows: • 00 = Invalid discrete setting at power−up • 01 = Invalid light curve setting specified at power−up • 03 = Bad checksum detected at power−up • 04 = Illegal op−code test failed • 05 = Unsupported test failed. (4) Strobes the watchdog timer to keep the red X and status displayed. NOTE: Page 5−2 15 Dec 2005 If the VSI/TRA displays error code 10, 11, 12, 29, 30, 31, or 40 an internal VSI/TRA failure has been detected. 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Figure 5−1. VSI/TRA Fault Warning Display 4. System Self−Tests A. Cockpit Display Test Modes The TCAS 3000 System provides two types of test modes; a short functional test mode and an extended maintenance test. Both test modes can be activated by the TEST button or switch on the ATC/TCAS Control Panel. The short test mode can also be activated by a central maintenance computer (CMC) or a central fault display interface unit (CFDIU). The extended test mode can only be initiated at the end of the short test. The short test mode is inhibited in the air if the Self−Test Inhibit programming pin (RBP−8E) is grounded. (1) Short Test Mode The short test mode provides a flight deck initiated functional test of the TCAS RA and TA displays and associated TCAS interfaces. It also provides an aural annunciation of the TCAS system status. The short test mode is available in all TCAS operational modes (Standby, TA Only, or TA/RA) when on the ground. If a TA or RA occurs while airborne, the test is terminated and normal operating status is resumed. The test mode is also terminated if any of the Advisory Inhibit discrete inputs (grounds) are received on pins RBP−5A, RBP−5B, RBP−5C, or RBP−5D. Push and hold the TEST button/switch on the ATC/TCAS controller for a few seconds to start the test. When the test mode becomes active, the words “tcas test” are transmitted once aurally. In addition to the TCAS test pattern, RA indications and a red TCAS TEST annunciation are displayed on the applicable display(s). Refer to Figure 1−18 for a typical test pattern display on the VSI/TRA. 34−43−23 Page 5−3 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System At the completion of the test (8−seconds), the words “tcas test pass” should be transmitted once aurally. In addition, the test pattern is removed from the display(s) and a TCAS PASS annunciation is displayed. If the test fails, the words “tcas test fail” are transmitted once aurally and a TCAS FAIL annunciation is displayed on the applicable display(s). If the TCAS short test fails, do the TCAS Computer Unit Self−Test procedures referenced in paragraph 4.B. to determine which LRU or subsystem is not functioning properly. To troubleshoot the system, refer to the procedures in the FAULT ISOLATION section. (2) Extended Test Mode The extended test mode provides a flight deck initiated test that displays various pages of text information that is selected by the ATC Mode S control panel 4096 code switches. This test mode is accessible only when on the ground and cannot be initiated while airborne. The extended test mode is used for maintenance purposes only. It displays various pages of text information containing the TCAS software part number, fault messages, status of program pins, analog and digital inputs, and other aircraft parameters. To start the test, push and hold the TEST button/switch on the ATC/TCAS controller for a minimum of 9 seconds. In addition the conditions that follow must occur: • TCAS is in Standby • The selected transponder is in Standby • Aircraft is on the ground (The AIR/GND discrete [RMP−5K] is grounded) • Landing gear is extended (Landing Gear discrete [RMP−13F] is grounded). Once the extended test mode is established, the 4096 code switches on the ATC/TCAS controller are used to select the desired maintenance page for display. Table 5−3 lists the extended mode page names and numbers and the corresponding 4096 Ident Code number. Page 5−4 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 5−3. Extended Test Menu Selections 4096 Ident Code Number Page Page Name 0000 System Status 0001 Display Status 0002 Rad/Alt Status 0003 Xpdr Status 0004 Program Pins 1/3 0005 Program Pins 2/3 0006 Program Pins 3/3 0007 Help Reference 0011 11 Antenna Port Status 0012 12 Option Pins Status 0013 13 Part Numbers All Other Codes Blank TCAS Test Menu To view the TCAS test menu and system status pages along with the troubleshooting messages, refer to the FAULT ISOLATION section. To exit the extended test mode, set the ATC/TCAS mode selector switch to Mode S ON. B. TCAS Computer Unit Self−Test (1) With all power off, reinstall the TCAS computer unit in its mounting tray. Make sure the TCAS control panel and display(s) are also installed. (2) Apply aircraft power and close all applicable TCAS system circuit breakers. (3) Set the ATC/TCAS controller mode switch to Mode S ON. (4) Push the PUSH TO TEST button on the TCAS computer unit front panel. The test sequence that follows should occur: • All TCAS computer unit front panel annunciators come on for a 3−second lamp test • If the TCAS is operational, the TCAS PASS green annunciator comes on for a 10−second display period and then goes off. • If the TCAS is not operational, one or more of the red fault annunciators comes on for a 10−second display period. (5) If a fault is detected, refer to the Fault Isolation section for troubleshooting information. 34−43−23 Page 5−5 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System 5. Return to Service Test Any time a TCAS LRU is removed and replaced following repair or maintenance, a return to service test is required. The System Self−Test procedures referenced in paragraph 4.A. are sufficient to check all system parameters. 6. Operational Software Loading Using an ARINC Portable Data Loader When updating the TCAS 3000 Computer Unit with an ARINC portable data loader PDL, verify the current TCAS 3000 Computer Unit software part number prior to continuing for cockpit system only. A. Current Software Verification NOTE: Software verification using cockpit systems ONLY. Verify the current software part number according to the extended maintenance capabilities on status page code 0000 in the FAULT ISOLATION section of this manual or the individual aircraft maintenance manual (refer to the onboard maintenance system program). B. Operational Software Loading (While Installed on Aircraft) (1) Verify that the system inputs for AIR/GROUND (RMP−5K) and GEAR UP/DOWN (RMP−13F) are grounded. (2) Obtain an ARINC PDL and the appropriate interface cable for connecting the data loader to the J1 (front) connector of the TCAS 3000 Computer Unit. The following PDLs have been tested and found to be satisfactory for performing this task: • DEMO Systems − Part No. 30100 (Revision A and later versions) • Teledyne − Part No. 2230915−01−D • SFIM − Part No. YV68A110. Other part numbers from these suppliers and ARINC 615 data loaders from other manufacturers may perform the task successfully. However, ACSS can not verify their usability. (3) Shut off the PDL and remove power from the TCAS 3000 Computer Unit. Connect the cable between the PDL and the J1 front connector on the TCAS 3000 Computer Unit. (4) Apply power to the TCAS 3000 Computer Unit. (5) Turn on the PDL. (6) Obtain the operational software. Insert disk No. 1 of the operational software into the PDL for program uploading (or follow the applicable instructions for the PDL). Page 5−6 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System (7) After the PDL indicates that the disk upload was successful, repeat step (6) for multiple disks, if necessary. (8) Wait at least 20 seconds after the last disk has finished uploading. Then turn off the PDL, remove power from the TCAS 3000 Computer Unit, and disconnect the interface cable. (9) Apply power to the TCAS 3000 Computer Unit and ensure the TCAS system is fully operational. Push the PUSH TO TEST button located on the front panel. The green LED indicator on the front of the panel lights at the end of the test cycle (approximately 8 seconds) to show the TCAS system is functional. C. Compact Flash Card − (While Installed on Aircraft) (1) Procedure For Uploading OPS SW Through Compact Flash Card (a) Obtain the operational software. (b) Verify that the aircraft is “on the ground” prior to performing an upload. The OPS SW cannot be uploaded while the aircraft is airborne. (c) Apply power to the TCAS 3000 computer unit. (d) Open the CF card protective door located on the left side. (See Figure 5−2) (e) Insert the CF card with the label facing the TCAS 3000 Computer unit front panel LEDs. (See Figure 5−2) (f) All LEDs will illuminate, which indicates TCAS 3000 Computer unit restart. (g) All LEDs will extinguish and the XFER IN PROCESS LED will start to blink. The blinking XFER IN PROCESS LED indicates that the unit is reading the CF card. (h) The XFER IN PROCESS LED will indicate continuous green. The continuous XFER IN PROCESS LED indicates that the unit is loading the contents of the CF card. The loading process takes over one minute. (i) Step NO TAGNO TAG(f), step NO TAGNO TAG(g), and step NO TAGNO TAG(h) may repeat if the DL or FPGA files on the CF card are different than those previously loaded on the TCAS 3000 Computer unit. If the files are not changed, step NO TAGNO TAG(f), step NO TAGNO TAG(g), and step NO TAGNO TAG(h) only occur once. (j) When the upload is successful, the CF Load Status LED changes to a continuous green indication. (k) An unsuccessful upload is indicated by amber LEDs displayed during the upload process. The LED correlations are listed in Table 5−4. (l) Once the upload is successful, remove the CF card from the TCAS 3000 Computer unit front panel. (See Figure 5−3) 34−43−23 Page 5−7 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System (m) Close the compact flash (CF) card protective door. (n) All LEDs will illuminate, which indicates a TCAS 3000 Computer unit restart. (o) When all LEDs are extinguished, the unit is ready. Figure 5−2. Compact Flash Card Access Port and LRU Identification Label NOTES: 1. Image is shown as an example and may not be the same computer. 2. When inserting compact flash cards, make sure that the part numbers on label are facing in the correct direction as shown in Figure 5−2. Align the card with the slot and push in firmly. When removing, use finger to push the ejector at the bottom of the slot until the card pops out slightly on its own. After that, pull the card freely out of the slot. 3. Page 5−8 15 Dec 2005 Remove and replace software identification label as detailed in the Accomplishment Summary of this Service Bulletin. 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Figure 5−3. Compact Flash Card Ejector Location Table 5−4. Compact Flash Upload / LED Correlation Triggering Event CF Status LED CF Card Inserted XFER IN PROCESS LED Blink Fault Type Logged Ending Event CF UPLOAD REQUEST CRC 1 completed Corrupt CF header Red CF FILE ERROR CF Card removed Upload Card Inserted while Airborne Red CF FILE ERROR CF Card removed Incorrect Configuration Error Red CF FILE ERROR CF Card removed Major/Minor Incompatibility Red CF FILE ERROR CF Card removed File Header CRC error Red CF FILE ERROR CF Card removed 34−43−23 Page 5−9 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 5−4. Compact Flash Upload / LED Correlation (cont) Triggering Event CF Status LED XFER IN PROCESS LED Fault Type Logged Ending Event File does not exist error Red CF FILE ERROR CF Card removed Multiple file error Red CF FILE ERROR CF Card removed File Image CRC error (CRC 1) Red CF FILE ERROR CF Card removed CF LOAD CF Card error is detected or upload completed or restart CRC 1 completed Green Aborted Upload Red CF WRITE ERROR 10 seconds after card removal Airborne Upload Red CF FILE ERROR CF Card removed CF FILE ERROR CF Card error is detected or upload completed or restart Ground−to−air transition during upload Green (per normal uploading sequence) Flash Copy CRC fails to match CF File CRC (CRC 2) Red CF WRITE ERROR Card removal Flash Copy 2 fails to match CRC at Copy 1 location Red FLASH EPROM ERROR Card removal APM Calculated CRC doesn’t match CF File CRC. Red APM WRITE ERROR − CF Upload Card removal APM Calculated CRC doesn’t match APM embedded CRC. Red APM DATA FAULT − CF Upload Card removal APM write to Flash unsuccessful Red APM COPY WRITE Card removal − CF Upload APM Calculated CRC doesn’t match APM embedded CRC Red APM Copy CRC − CF Upload Card removal Green CF UPLOAD SET COMPLETE Card removal All files loaded successful Page 5−10 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System D. Updated Software Verification (1) Software Verification Using Cockpit Systems ONLY Verify the updated software part number according to the TCAS 3000 extended maintenance capabilities on status page code 0000 in the FAULT ISOLATION section of this manual or the individual aircraft maintenance manual (refer to the onboard maintenance system program). (2) Software Verification Using a Stand−Alone PC ONLY Verify the updated software part number using a stand−alone PC according to the following procedure. (a) Obtain PC software Part No. PS4088035−101. (b) Obtain or build an RS−232 cable. (Refer to Figure 5−4.) (c) Shut off the PC. (d) Remove power from the TCAS 3000 Computer Unit. (e) Connect the RS−232 cable from the PC (9−pin connector) to the J1 front connector on the TCAS 3000 Computer Unit. (f) Apply power to the TCAS 3000 Computer Unit. (g) Power on the PC to Microsoft Windows operation. (h) On the PC, go to START => PROGRAMS => ACSS TOOLS and double click “TCAS Part Number”. (i) Verify the updated TCAS software part number. (j) Shut down the PC and remove power. (k) Remove power from the TCAS 3000 Computer Unit. (l) Disconnect the RS−232 cable from the J1 front connector on the TCAS 3000 Computer Unit. 34−43−23 Page 5−11 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System 53 PIN 10 FEET MAX 9 PIN ”D” TCAS 2000 53 PIN MALE 9 PIN ”D” FEMALE 40 41 49 TX BLACK RX WHITE GND SHIELD NOTES: 1. Mating J1 front connector on the TCAS 2000 RT−950/−951 Computer Unit: HI 4004295−160 or ITT KJ6F18A53P or MS27473E18A53P or JT06RE−18−53P Standard 9−pin, D−submini connector with female contacts. 3. A single, twisted−pair, shielding wire using the shield as the common ground is a popular wiring choice. ID−39471 2. Mating connector to the PC: Figure 5−4. RS−232 PC to TCAS Interface Cable Page 5−12 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System (3) Software Verification Using a Software Verification Fixture ONLY NOTE: Software versions prior to Change 7 can not be displayed on the Software Verification Fixture. (a) Obtain Software Verification Fixture (Part No. T326948−901) with associated adapter cable (Part No. 200F−00084). (b) Remove power to the TCAS 3000 Computer Unit. (c) Connect the adapter cable (Part No. 200F−00084) to the TCAS 3000 Computer Unit and the software verification fixture. (d) Apply power to the TCAS 3000 Computer Unit. (e) Enable the software verification fixture and verify the appropriate software part number is displayed in the 15−digit display. (f) Perform a TCAS system self−test and verify that TCAS TEST PASS is annunciated. NOTE: The TCAS TEST FAIL message may be annunciated if an LRU that supplies input to the TCAS 3000 Computer Unit is not powered on. (g) If the software part number is not displayed, repeat step (a) thru step (f). (4) Software Verification Using a Remote Connected VSI/TRA ONLY On some aircraft configurations, software verification may be performed using a remote connected VSI/TRA (Part No. 4067241−861, −862, or −863) display attached through adapter cable (Part No. 200F−00083) to the J1 front connector of the TCAS 3000 Computer Unit during the extended test mode. Verify the particular aircraft configuration can support a cockpit initiated self−test and be recognized at the 8−second time period after activation. NOTE: CMC/CFDS activated self−test will not be recognized at the 8−second time period, only an approved TCAS control panel. 34−43−23 Page 5−13 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Blank Page Page 5−14 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System FAULT ISOLATION 1. General The TCAS 3000 Traffic Alert and Collision Avoidance System has three optional procedures for fault detection and isolation to the LRU level. The first option uses the aircraft’s CMC or central fault display system (CFDS) if the aircraft is equipped with an onboard maintenance system. The second option uses a digital interface between the TCAS Computer Unit and the display system (EFIS, multifunction display or VSI/TRA flat panel display). The third option uses the annunciators located on the front panel of the computer unit. The annunciators are activated by a self−test function within the TCAS Computer Unit. Select the procedural option for fault isolation from paragraph 3., Procedure, which is applicable to the type of aircraft and the equipment installed. 2. Equipment and Materials NOTE : Equivalent alternatives are permitted for equipment in this list. Digital Multimeter − Fluke Model 29, John Fluke Mfg Co. Inc., Everett, WA 3. Procedure A. CMC or CFDS Fault information can be displayed from an onboard maintenance system when the aircraft is so equipped. Fault data is accessible only when the aircraft is on the ground. Faults that occur at any time, on the ground or while airborne, are stored in fault memory and reported to the CMC or CFDS. All displayed information is in the English language with abbreviated terms used only as necessary. Refer to the appropriate CMC or CFDS support manual for fault retrieval procedures. B. TCAS Display System The TCAS display system can be used to display system status and fail messages in the cockpit, making it more convenient to use than the computer unit front panel annunciators for a quick checkout of the TCAS system. In contrast with the computer unit self−test, which records and stores faults from previous flights, the display system test shows only current status and failure data. 34−43−23 Page 6−1 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System To access the cockpit display test modes, do the procedures that follow: NOTES: 1. Fault detection with diagnostics can only be done on the ground. The pilot has the option to do a pass/fail test while airborne if this feature is not inhibited. 2. This procedure is valid when used with either a single or dual control panel. (1) Make sure the aircraft configuration indicates Aircraft On Ground and Gear Extended. (2) Set the Mode Select switch on the ATC/TCAS control panel to STBY. (3) Push and hold the TCAS TEST button for a minimum of 9 seconds. (4) Set the transponder 4096 Ident Code Number to any code except 0000 thru 0007, 0011, 0012, 0013. NOTE: Do not use codes 7500, 7600, or 7700; these code are reserved for emergency operation. (5) Make sure the TCAS TEST MENU is being displayed on the TCAS display. It should match the screen shown in Figure 6−1. (6) Set the transponder 4096 Ident Code Number to 0000. (7) If the system passes, a maintenance page similar to that shown on Figure 6−2 is displayed. A failure results in a referral to one or more specific ident codes. Set the indicated code on the ATC/TCAS Control Panel and follow the instructions given. (8) If the system passes, set the mode switch on the ATC/TCAS Control Panel to MODE S ON. This allows you to exit the expanded test mode. If a failure is indicated, set the transponder 4096 Ident Code to the codes indicated by the automatic referral system. The remaining screens shown on Figure 2−4 thru Figure 2−14 are examples of the other maintenance pages. (9) Set system power to OFF and correct faults by replacing indicated LRUs or by repairing faulty wiring harness. (10) Test system as required after repair. Page 6−2 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System C. TCAS Aural and VSI/TRA Annunciations TCAS aural and VSI/TRA annunciations are given in Table 6−1. Table 6−1. TCAS Aural and VSI/TRA Annunciations VSI/TRA Annunciation Upper Left Upper Right Center Color Condition Aural TRAFFIC Display Control ON Mode Normal Range ring and own aircraft in view at all times, along with qualifying traffic. TRAFFIC Display Control AUTO Mode Normal Range ring and own aircraft come up with traffic when a TA or RA exists. Transponder Only Mode None TCAS OFF White TCAS is not operational. STANDBY Mode None TCAS OFF White TCAS is not operational, transponder is in standby. Vertical Speed Input Failure to Single VSI (Dual VSI Aircraft) Normal Yellow Vertical speed needle removed from display with failed data. No RAs posted on failed side. TCAS is operational on remaining side. VSI Input Failure to Both (Dual VSI Aircraft) or Single VSI (Single VSI Aircraft) None Yellow Vertical speed needle removed from both VSIs (dual VSI aircraft) or only VSI (single VSI aircraft). No RA information posted. TCAS is not operational. White or Yellow Traffic alerts are the only information displayed. No RAs. (The color changes from white to yellow when a TA actually occurs.) TCAS FAIL Yellow TCAS is not operational. TCAS OFF White TCAS is not operational. TCAS OFF White TCAS is not operational. TA Only Mode Traffic − Traffic only Transponder or Altitude Source Fail None Altitude Reporting OFF ATCRBS Transponder Selected None RA FAIL on failed side VSI FAIL on failed side VSI FAIL on both sides TCAS FAIL on both sides TA ONLY 34−43−23 Notes Page 6−3 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 6−1. TCAS Aural and VSI/TRA Annunciations (cont) VSI/TRA Annunciation Condition Aural Upper Left Upper Right RA Only (TA Display Control to OFF) RA Fail RA FAIL Traffic Display Failure Center Color Notes RA ONLY White VSI/TRA displays resolution advisories only. Yellow No resolution advisories displayed. TD FAIL Yellow No traffic advisories displayed. VSI FAIL Single VSI/TRA Failure (Dual VSI Aircraft) Normal X across failed display Red On failed side, all symbology removed and replaced with a large red X and hex−coded failure number. TCAS operational on good side. Dual VSI/TRA Failure (or Single on Single VSI Aircraft) None X across both displays Red All symbology removed from both displays and replaced with a large red X and failure code. TCAS is not operational. Normal Display full white Cockpit Lamp Test During cockpit lamp test, display goes full white and displays no symbology. TCAS SELF TEST (Note 1.) TCAS Test Mode (First Second) TCAS TEST TCAS Test Mode (2 to 8 Seconds) TCAS Test Mode (at 8 Seconds) Page 6−4 15 Dec 2005 TCAS TEST PASS/ FAIL TCAS TEST White TCAS system self test. TCAS TEST White TCAS test pattern shown. TCAS TEST TCAS test pattern removed and TCAS returns to normal operation unless the test switch is held, the aircraft is on the ground, and TCAS is in STBY. 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 6−1. TCAS Aural and VSI/TRA Annunciations (cont) VSI/TRA Annunciation Condition Aural Upper Left Upper Right Center Color Notes TCAS EXTENDED SELF TEST (MAINTENANCE ONLY) (Note 2.) TCAS Extended Test Mode (Test Switch Held at 7 Seconds for 2 Seconds and Aircraft on the Ground Only) System information pages White Current status of the TCAS system, transponder, antennas, radio altimeters. barometric altitude, etc is presented in a series of pages called by selection of 4096 code. NOTES: 1. Self Test should only be run in STANDBY mode in flight or on the ground. 2. Extended Self Test provides maintenance information on seven screens selected using 4096 code. This mode is available only on the ground and in STANDBY. Extended Self Test ends automatically with a TCAS/Transponder mode change or if the aircraft becomes airborne. 34−43−23 Page 6−5 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System D. TCAS Test Menu and System Status Pages The extended test mode provides maintenance information on the TCAS display. Pages are selected by 4096 codes on the transponder control panel. The extended test mode is accessible only on the ground, with the transponder in standby. To start the extended test mode, select STBY and push the transponder control panel TCAS TEST switch for 8 seconds. To exit the extended test mode, move the transponder mode control out of STBY. (1) TCAS Test Menu The TCAS Menu Page, Figure 6−1, can be displayed whenever a TCAS suppression bus failure is not indicated and the 4096 Ident Code is any code other than 0000 thru 0007, 0011, 0012, or 0013. If a TCAS suppression bus failure is indicated, all 4096 Ident Codes other than 0000 thru 0007, 0010 thru 0013 and 0510 can be used to select the TCAS Test Menu. Figure 6−1. TCAS Test Menu Page Page 6−6 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System (2) System Status Page Selection of code 0000 displays the System Status page, Figure 6−2. This page displays the PASS or FAIL status of the TCAS system and the current version of the operating software loaded into the TCAS computer. Figure 6−2. Typical System Status Page In the event of a detected system failure, one or more of the messages in Table 6−2 are displayed. Lines 6 thru 10 of the display screen are used to display the five highest priority faults within the TCAS system. A maximum of five messages can be displayed. Table 6−2. System Status Page Fault Messages Priority Message Description SUPP FAULT GOTO 0010 Suppression bus failure. Select page 0010 for more information. TCAS CU FAIL ANT FAIL TOP Antenna failure. Message field will display TOP, BOT or BOTH to indicate which antenna failed. DISP FAIL GOTO 0001 TCAS has lost valid signal from display. Select page 0001 for more information. RALT INACT GOTO 0002 TCAS has lost valid signal from radio altimeter. Select page 0002 for more information. XPDR FAIL GOTO 0003 TCAS has lost valid signal from Mode S transponder. Select page 0003 for more information. ANT FAIL GOTO 0011 One of the antenna ports connected to the TCAS CU has failed. Select page 0011 for more information. OPT FAIL GOTO 0012 TCAS computer unit has failed BITE test. Parity for the option selections has failed. Select page 0012 for more information. 34−43−23 Page 6−7 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System (3) Display Status Page Selection of code 0001 displays the Display Status page, Figure 6−3. This page displays the current status of the Resolution Advisory and Traffic Advisory displays. AD−53901,SH2@ Figure 6−3. Typical Display Status Page The message contents for the Display Status page are determined as follows: RA DISPLAY #1 PASS Indicates valid signal (ground/low) is present at TCAS CU pin RMP−14C. Fail is displayed if this signal is an open/high. TA DISPLAY #1 PASS Indicates valid signal (ground/low) is present at TCAS CU pin RMP−7E. FAIL is displayed if this signal is an open/high. RA DISPLAY #2 PASS Indicates valid signal (ground/low) is present at TCAS CU pin RMP−13E. FAIL is displayed if this signal is an open/high. TA DISPLAY #2 PASS Indicates valid signal (ground/low) is present at TCAS CU pin RMP−7J. FAIL is displayed if this signal is an open/high. RNG SELECT 6NM Indicates current range selection for the traffic display. For installations using control panels without range select switches, range defaults to 6NM. ALT SELECT NORM Indicates current selection of vertical display limits for traffic display − NORM, BELOW, or ABOVE. For installations that use control panels without ABV−NORM−BLW switch, limits default to NORM. ALT TAG Page 6−8 15 Dec 2005 RELATIVE Indicates current selection on control panel for type of traffic symbol altitude indication, RELATIVE or FLT LVL. Default is RELATIVE if no switch is available on control panel. 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System (4) RAD/ALT Status Page Selection of code 0002 displays the RAD/ALT Status page, Figure 6−4. This page displays the status of the selected radio altimeter interface to the TCAS. AD−53901,SH3@ Figure 6−4. Typical RAD/ALT Status Page The first information line (line 3) of the RAD/ALT STATUS page indicates which of the two radio altimeter ports is being used by the TCAS computer. The TCAS computer attempts to use radio altimeter No. 1 first. If it determines this input is invalid, it automatically switches to radio altimeter No. 2. The current status of the two radio altimeter ports is displayed on lines 5 and 6. If a signal is valid, the radio altitude value is displayed in either “FT” for English type altimeters, or “M” for Metric type altimeters. If one of the radio altitude signals is determined to be invalid, the altitude value is replaced by INACT. Radio altitude INACT indicates the radio altimeter has failed, is not powered, or is not connected. The radio altimeter input is determined to be invalid if, for an analog radio altimeter input, 28 V dc valid is not present at TCAS CU pin RMP−2K for Radio Alt #1 or pin RMP−3C for Radio Alt #2, or for a digital radio altimeter input, the sign status matrix (SSM) of the radio altimeter output indicates not valid or no data is present on the digital bus. If the radio altimeter output is greater than 2200 feet (source is valid, but data is invalid), the radio altitude value is replaced by OVR RNG. When both radio altitude sources are invalid, line 3 is blank. 34−43−23 Page 6−9 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System (5) Transponder (XPDR) Status Page Selection of code 0003 displays the XPDR Status page, Figure 6−5. This page displays data for the transponder selected at the time the extended test mode was entered. AD−53901,SH4@ Figure 6−5. Typical Transponder (XPDR) Status Page The message contents for the XPDR Status page are determined as follows: XPDR #1 MODE S ADDR: PRESS. ALT ALT REPORTING PASS Indicates PASS or FAIL status of the selected transponder (XPDR #1 or XPDR #2) as indicated by the digital transmission from that transponder. FAIL is displayed if no data is received on the bus. 8E78A0H Indicates the Mode S address (in hexadecimal format) of the selected transponder as determined by program pins at the rear connector of the transponder. (See Note 1.) 1133FT Indicates the last pressure altitude being reported by the selected Mode S transponder before the TCAS system was placed into STBY. This value is not updated while in extended test mode. ON Indicates current position of altitude reporting switch on Mode S/TCAS control panel − ON or OFF. S/W PN PS7021601−903 (See Note 2.) NOTES: 1. If the transponder detects either all 1’s or all 0’s, the following message will appear − ILLEGAL ADDRESS −. In addition, a fail message will appear on the front of the transponder and on Extended Test. The message reads CHECK DISCRETE ADDR WIRING ON XPDR PINS MP1A THROUGH MP3D. 2. The S/W PN information, line 8 of the display screen, displays general text supplied by the ACSS ATDL transponder via label 356 (block transfer), which is equipped to supply the text to the display. If a transponder is installed that does not have this feature, line 8 is blank. Page 6−10 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System (6) Programming Pins Status Pages The following three displays indicate the status of various option programming pins located in the rear connector of the TCAS computer. The 1s and 0s following a programming option indicate the GROUND or OPEN status for those programming pins. Each 1 and 0 is associated with a program pin. A one (1) indicates the pin is grounded by connecting to a program common pin on the TCAS connector or to an aircraft ground. A zero (0) indicates the pin is left open. Selection of code 0004 displays the first of three pages that define program pin status. See Figure 6−6. Figure 6−6. Typical Program Pins 1/3 Page 34−43−23 Page 6−11 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Programming pins on the TCAS computer associated with each of the functions defined on the page 1 display are listed below. Where more than one program pin is indicated, the listed connector pins correspond to the display digits read from left to right. A one (1) indicates the associated pin is grounded. A zero (0) indicates open. CLIMB INH 0000 Climb Inhibit inputs: RMP−1J, RMP−13G, RBP−5J, RBP−5K. INC CLIMB INH 0000 Increase Climb Inhibit inputs: RBP−5E, RBP−5F, RBP−5G, RBP−5H ADVISORY INH 0000 Advisory Inhibit inputs: RBP−5A, RBP−5B, RBP−5C, RBP−5D RADIO ALT TYPE 0000 Analog Radio Altimeter Type: RMP−12B ARINC 552/552A (0), Collins BCA (1) VOICE DELAY ENABLE 0 Voice Delay option: RBP−7D Enabled = (1), Disabled = (0) AUDIO PROG PINS CANCEL DISCRETE DTIF PIN Page 6−12 15 Dec 2005 000 Audio output level selection inputs: RBP−7A, RBP−7B, RBP−7C 0 Advisory Cancel Discrete option: RMP−3D (0) allows advisories to be cancelled. A (1) does not allow advisories to be cancelled. 0 TBD 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Selection of code 0005 displays the second of three pages that define the Program Pins status. See Figure 6−7. AD−53901,SH6@ Figure 6−7. Typical Program Pins 2/3 Page Programming pins on the TCAS computer associated with each of the functions defined on the Program Pins 2/3 page are listed below. Where more than one program pin is indicated, the listed connector pins correspond to the display digits read from left to right. A one (1) indicates the associated pin is grounded. A zero (0) indicates open. BCA EFIS CABLE DELAY PROG TEST MODE 0 RA/TA block transfer program that determines the type of data transfer from the TCAS CU to the TA/RA displays: A (1) indicates ACSS BCA EFIS format. A (0) indicates ARINC 735 format: RMP−12C. 000 RF delay compensation program for antenna cable length difference (top versus bottom): RBP−7G, RBP−7H, RBP−7J 0000 Shop test function (all 0s for flight mode): RBP−9D, RBP−9E, RBP−9F, RBP−9G FUNCT TEST INH 0 Inhibits cockpit self−test when airborne (0 for no inhibit): RBP−8E SIM SOFT ENABLE 0 Simulator Software Enable input: RBP−10K Should always be (0) for flight mode MAX # INTRUDER 00000 Select maximum number of traffic symbols displayed on VSI. Value for each digit, from left to right, is 16, 8, 4, 2, 1. The maximum number is the sum of not selected values (0s): RBP−8F, RBP−8G, RBP−8H, RBP−8J, RBP−8K. DISP THREATS ONLY 0 Selects display of traffic only when TAs or RAs occur: (0 indicates display of any traffic): RBP−7F. GND DISPLAY MODE 0 Selects TCAS OFF automatically with aircraft ON GROUND (0 indicates TCAS active ON GROUND): RBP−7E. 34−43−23 Page 6−13 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Selection of code 0006 displays the third of three pages that define the Program Pins status. See Figure 6−8. Figure 6−8. Typical Program Pins 3/3 Page Page 6−14 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Programming pins on the TCAS computer associated with each of the functions defined on the Program Pins 3/3 page are listed below. Where more than one program pin is indicated, the listed connector pins correspond to the display digits read from left to right. A one (1) indicates the associated pin is grounded and a zero (0) indicates open, except for RCZ−852 MAX TAS where a one (1) indicates an open and a zero (0) indicates a ground. ALT LIMIT 00000 Shows selected altitude above which TCAS will not give CLIMB commands. Value for each digit, from left to right, is 32000, 16000, 8000, 4000, and 2000 feet. Altitude is the sum of selected values (1s): RMP−6J, RMP−6H, RMP−6G, RMP−6F, RMP−6E. PERF LIMIT 0 Selects CLIMB command altitude limit control from external performance computer: A ground (1) indicates performance/climb rate is not limited. An open (0) indicates performance/climb rate is limited: RMP−6D. SINGLE TRANS− PONDER 0 Shows if the TCAS 3000 is configured for a single transponder. (1) indicates a single transponder . (0) indicates not a single transponder. MAX TAS 000 Shows the selected maximum airspeed operating range of aircraft. This data is obtained from ARINC label 276 of the selected transponder. Refer to the appropriate Mode S transponder installation manual. NOTE: Line 8 of the Program Pins 3/3 display indicates which transponder is currently selected. 34−43−23 Page 6−15 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System (7) Help Reference Page Selection of code 0007 displays the Help Reference page, Figure 6−9. This page serves as a reference to assist aircraft maintenance personnel in checking the functionality of dual transponders. AD−53901,SH8@ Figure 6−9. Help Reference Page In addition to the recommended procedure, the number 2 transponder must be selected on the Mode S/TCAS control panel and the mode select switch placed in TA only or TA/RA mode momentarily prior to restarting self-test to enter extended maintenance mode. Page 6−16 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System (8) Suppression Bus Fail Page The Suppression Bus Fail page, Figure 6−10, is displayed only when a TCAS suppression bus failure is indicated and the 4096 Ident Code is 0010. This page displays information about detected suppression bus failures. It briefly describes the problem and instructs maintenance personnel to change the 4096 Ident Code to display the Suppression Bus Clear page for clearing instructions. If there is no suppression bus failure, the main menu (0000) is displayed. AD−53901,SH9@ Figure 6−10. Suppression Bus Fail Page The flight crew may report a unique problem of an intruder displayed which appears to be co−altitude, located on the own aircraft symbol. In many of these cases, TCAS may issue a TA followed by an RA. After the flightcrew has initiated the advisory, the intruder may not appear to change relative to the own aircraft symbol. In this type of report, a failure in the mutual suppression bus, which connects the own aircraft transponder to the TCAS CU, could result in the TCAS CU developing an intruder track file on its own associated transponder. Simply performing a DC continuity test of the connection between the TCAS CU and the transponders may not identify the problem. In many cases, a connector termination or pushed back pin may be the cause. That is why it is very important to be monitoring the suppression signal from the active source, on both ends. The following is one method to monitor the signal. Remove the TCAS CU and the non−selected transponder. With an oscilloscope, monitor the signal at the TCAS CU rack rear connector for the Mode S transponder suppression signal related to the squitter message sent every second by the selected operational transponder. Repeat the same test with the second transponder after removing the first transponder. To test the TCAS CU suppression pulse, install the TCAS CU, remove the No. 1 transponder and monitor the TCAS suppression pulse during the time of the UF16 broadcast or the WSS while in the air (if possible). This TCAS suppression signal should also be present on the No. 2 transponder. 34−43−23 Page 6−17 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System (9) Suppression Bus Clear Page The Suppression Bus Clear page, Figure 6−11, is displayed only when a TCAS suppression bus failure is indicated and the 4096 Ident Code is 0510. This page briefly describes how to clear suppression bus failures from the fault record by exiting the extended test mode with this page displayed. When the TCAS extended test is exited, the failure indication is cleared and a Suppression Bus Clear code is recorded in the current flight leg. AD−53901,SH10@ Figure 6−11. Suppression Bus Clear Page (10) Antenna Port Status Page Selection of code 0011 displays the Antenna Port Status page, Figure 6−12. This page displays the current operational status of the top and bottom TCAS antennas. The status of each port is indicated as PASS when valid and FAIL when invalid. Information lines 8, 9, and 10 are not displayed when an omnidirectional bottom antenna is installed. AD−53901,SH11@ Figure 6−12. Typical Antenna Port Status Page Page 6−18 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System (11) Option Pins Status Page Selection of code 0012 displays a page that defines the TCAS computer option pins. See Figure 6−13. Figure 6−13. Typical Option Pins Status Page Option pins on the TCAS computer associated with each of the functions defined on the Option Pins Status page are listed below. Where more than one option pin is indicated, the listed connector pins correspond to the display digits read from left to right. There are eight option pins available on the TCAS computer for selection of various options. The OPT PINS are as follows: RMP−10G, −10H, −10J, −10K, −11A, −11B, −11C, and −11D. NOTE: OPT PINS RMP−10G, −10H, −10J, and −10K are reserved for future enhancements and are used for parity check only. The PARITY line (line 4) displays the status of the parity program pin (RMP−12G). Pin RMP−12G must be grounded (1) when the number of OPT PINS grounded is an odd number (1, 3, 5, 7). If number of OPT PINS grounded is an even number (0, 2, 4, 6, 8), then pin RMP−12G should be open (0). The STATUS line (line 5) displays FAIL if the option pins parity is incorrect or PASS if parity is correct. The ENHANCEMENTS line (line 6) displays the status of the Flight Data Recorder ARINC 429 and Extended Maintenance Log Program input status (Pin RMP−11D). This option enables the use of the Flight Data Recorder and the down loading of the extended maintenance log through a PDL connected to connector J1 located on the front of the TCAS computer. If pin RMP−11D is open, the Flight Data Recorder is not used and normal RA display bus operation occurs. If pin RMP−11D is grounded, high speed ARINC 429 flight data is output on the RA Display #1 and #2 busses and maintenance log data can be downloaded through a portable data loader. 34−43−23 Page 6−19 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System The MALE VOICE line (line 7) displays the Male Voice Program input status (Pin RMP−11C). This option allows audio annunciation to be selectable for either male or female gender. If pin RMP−11C is grounded, the male voice option is enabled (ON). If pin RMP−11C is open, the female voice option is enabled (OFF). The DISPLAY FLT ID line (line 8) displays the Flight ID Program input status (Pin RMP−11B). This program allows flight identification from the transponder to be output on traffic display busses. If pin RMP−11B is grounded, Flight ID Display is enabled (ON). If pin RMP−11B is open, Flight ID Display is disabled (OFF). The ADS−B SURV line (line 9) displays the ADS−B surveillance program input status (Pin RMP−10K). This program allows the passive tracking of intruders who squitter ADS−B squitters containing position information. If pin RMP−10K is grounded, the ADS−B surveillance option is enabled (ON). If pin RMP−10K is open, the ADS−B surveillance option is disabled (OFF). To activate this option, the TCAS CU must also have hardware MOD C installed. (12) Part Numbers Page Selection of code 0013 displays the Part Numbers Page, Figure 6−14. This page displays the software part numbers loaded on the TCAS Computer. Figure 6−14. Typical Option Pins Status Page E. TCAS Computer Unit Self−Test The TCAS computer unit detects system faults and displays them on its front panel annunciators. Its flight leg memory stores system status and fault information for 10 consecutive flight legs. A flight leg is the interval between weight−off−wheels and weight− on−wheels during which TCAS is operative. By recalling the stored data, ground maintenance personnel can evaluate in−flight performance on the ground and fault isolate a current or previous failure to a specific LRU or LRU interface. Table 6−3 summarizes how the TCAS computer unit self−test is activated at power−up, during operation, and during commanded self−test. The computer unit can activate the commanded self−test only when the aircraft is on the ground. Page 6−20 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 6−4 lists the functions of the computer unit’s status annunciators and the corresponding troubleshooting actions. If the annunciators indicate an antenna problem, the antenna connections should be checked by measuring the antenna resistance values at the computer unit mounting tray. The resistance values listed in Table 6−5 are measured between the center conductor and shield on each LTP and LMP antenna connector. Table 6−3. Computer Unit Self−Test Execution Test Sequence Activation Test Indications Power On Self−Test Self−Test is activated with each application of system power No indication unless a fault is detected. System status/fault data is stored in memory for 10 consecutive flight legs. Data can be recalled by doing the commanded self−test on the ground. Continuous Self−Test Executed automatically as part of normal TCAS inflight operation No indication unless a fault is detected. System status/fault data is stored in memory for 10 consecutive flight legs. Data can be recalled by doing the commanded self−test on the ground. Commanded Self−Test Push the front panel PUSH TO TEST button • All front panel lamps come on during a 3−second lamp test. • If the TCAS is operational, the TCAS PASS green lamp comes on for a 10−second display period and then goes off. • If the TCAS is not operational, one or more red fault lamps come on for a 10−second display period. Refer to Table 6−4 for corrective action. Push the PUSH TO TEST button again before the previous 10−second display period has elapsed • Previous fault display is aborted Push the PUSH TO TEST button before the end of each succeeding display period • Status/fault data recorded during a total of 10 flight legs (maximum) is displayed • All lamps come on during a 1−second lamp test • Status/fault data recorded during the preceding flight leg is displayed for 10−seconds. • When data from the earliest recorded flight leg has been displayed, all lamps flash at a 2.5−Hz rate for 3−seconds if the PUSH TO TEST button is pushed. This indicates the end of recorded test data. 34−43−23 Page 6−21 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 6−4. Computer Unit Fault Reporting and Corrective Actions Status Annunciator Failure Possible corrective Action TCAS PASS The TCAS Computer Unit passes its own internal BITE test TCAS computer unit is operational. If other annunciators are on, the problem is in the indicated subsystem or aircraft wiring. TCAS FAIL The TCAS Computer Unit has failed its own internal BITE test Replace the TCAS computer unit. TOP ANT The top antenna DC resistance test indicates a failure Remove the TCAS computer unit. Use a multimeter to measure the DC resistances indicated in Table 6−5 for the top antenna. Repair antenna cables or replace the antenna as required. BOT ANT The bottom antenna DC resistance test indicates a failure Remove the TCAS computer unit. Use a multimeter to measure the DC resistance indicated in Table 6−5 for the bottom antenna. Repair antenna cable(s) or replace the antenna as required. HDG Heading input function not used Not applicable TA DISP Traffic advisory display discrete signals No.1 or No.2 indicate a failure Check wiring and power to TA display. (On both sides of the cockpit, if two are installed.) Make sure that RA/TA valid discrete 1 and 2 (RMP−7E and RMP−7J) are <3.5 V dc to ground. Repair wiring or replace display as required. RA DISP Resolution advisory display discrete signals No.1 or No.2 indicate a failure Check wiring and power to RA displays. Make sure that RA valid discrete 1 and 2 (RMP−14C and RMP−13E) are <3.5 V dc to ground. Repair wiring or replace display as required. RAD ALT Radio altitude source No.1 or No.2 is invalid or has failed Check wiring and power to the radio altimeters. For analog radio altimeters, make sure the RAD ALT No.1 and No.2 valid discrete (RMP−2K and RBP−3C) are >18.5 V dc. Repair wiring or replace radio altimeter as required. XPDR BUS Mode S Transponder No.1 or No.2 is invalid or has failed. Check wiring and power to the transponders. Check for data on XT 429 bus No.1 and No.2 (RMP−14F/G and RMP−14H/J). Repair wiring or replace transponder as required. If the Single Mode S Transponder program pin (RMP−10D) is not grounded in installations. Computer Units, a XPDR Bus Fault may be displayed. Attitude input function not used. Not applicable ATT Page 6−22 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System F. Directional Antenna Test / Fault Isolation Procedure NOTE: These procedures are recommended only if a TCAS computer bite or extended test failure of the top or bottom directional antenna has occurred. (1) Review extended maintenance or flight leg BITE data to determine which antenna has failed. (2) Remove TCAS computer unit from mounting tray. Visually examine all antenna coax cable connectors at the mounting tray side as well as the LRU connectors. Remove any foreign material discovered and reinstall the LRU. (3) Do a system self−test to determine if the fault has cleared. If the failure continues, remove the TCAS computer unit and proceed. (4) Do a continuity test at the LRU end of each antenna cable. The resistance values should be as specified in Table 6−5. (5) If an open circuit, short circuit, or unacceptable resistance measurement is detected on the directional antenna path, a failure has occurred in the connector, coax cable, or directional antenna. (6) Locate the directional antenna that has a suspected failure. Remove the coax cable from the antenna port that is suspected to have failed. Isolate which section of the antenna system is at fault by a process of elimination. The resistance values of the antenna ports should be as specified in Table 6−5. (7) Remove and replace the appropriate failed component in accordance with approved Aircraft Maintenance Manual procedures. Table 6−5. Antenna Wiring Resistance Connector Section Antenna Pin DC Resistance Top Directional Antenna LTP 1000 ± 100 Ohms 8060 ± 800 Ohms 4020 ± 400 Ohms 2000 ± 200 Ohms Bottom Directional Antenna LMP 1000 ± 100 Ohms 8060 ± 800 Ohms 4020 ± 400 Ohms 2000 ± 200 Ohms Optional Bottom Omnidirectional Antenna LMP 0 to 50 Ohms (50 Ohms maximum) Infinite (>50K Ohms) Infinite (>50K Ohms) Infinite (>50K Ohms) 34−43−23 Page 6−23 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System NOTE: The procedures that follow are recommended for intermittent antenna system failures or if the continuity tests have not identified a failed component in the antenna system or if the flight crew detects an unacceptable visual discrepancy between an intruder aircraft and its displayed location. (8) If the displayed location of an intruder aircraft is believed to be in error, appropriate ramp test equipment can be used to simulate intruder aircraft to check the suspected discrepancy while on the ground. (9) Remove the suspected TCAS directional antenna and terminate the antenna side of the cable with a 50 ohm termination (Omni−Spectra Part Number 3102−6100−00 or equivalent TNC jack with VSWR ≤1.15 : 1). (10) Perform a thorough inspection for moisture or contamination of all coax cable assemblies. (11) Remove the TCAS LRU and do a VSWR check on the coax cable from the TCAS computer tray side. Use approved VSWR test equipment and operating procedures. The measured VSWR should be less than 2.0 : 1. (12) If the VSWR test fails, isolate failed antenna coax section. Remove/repair appropriate cable and/or connector. (13) If VSWR test complies, return the directional antenna to the manufacturer for further testing. Install a new directional antenna in accordance with Aircraft Maintenance Manual procedures. Page 6−24 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System MAINTENANCE PRACTICES 1. General This section provides instructions for removing, reinstalling, and adjusting each LRU of the TCAS 3000 that has been previously installed by the aircraft manufacturer or completion center. Where applicable, instructions for replacing lamps, knobs, and set screws are included. Adjustment information is called out as required. CAUTION: SHOULD ANY INSTALLATION CRITICAL CASES ARISE WITH THE REINSTALLATION OF ANY UNIT, YOU MUST COMPLY 100 PERCENT WITH THE INSTRUCTION. CAUTION: TO PREVENT DAMAGE TO EQUIPMENT, TURN AIRCRAFT POWER OFF WHEN REMOVING OR INSTALLING LRUS. When removing or installing any TCAS LRU, prepare the aircraft for safe ground maintenance. Open and tag all applicable system circuit breakers. 2. Equipment and Materials CAUTION: BEFORE YOU USE A MATERIAL, REFER TO THE MANUFACTURERS’ MATERIAL SAFETY DATA SHEETS FOR SAFETY INFORMATION. SOME MATERIALS CAN BE DANGEROUS. Maintenance materials identified with a ACSS Material Number (AMN) are given in Table 7− 1. Table 7− 1. Materials Name HMN 9722878 Description Sealing compound, temperature−resistant, high−adhesion, two component, polysulfide synthetic rubber (MIL−S−8802, Type I − dichromate cured sealing materials, Class B1/2 − spreadable) — PR−1422 (base and accelerator) Source Courtaulds Aerospace, Glendale, CA NOTES: 1. Equivalent alternatives are permitted for materials in this list. 2. The HMN codes in the list of materials identify the HMN given to each material. No additional special equipment or materials, other than those commonly used in the shop, are required to install the units in existing trays and clamps, and to adjust the system. Do not over tighten mounting screws. Where torque values are not given, it is acceptable to finger tighten the mounting screws. 34−43−23 Page 7−1 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System 3. Procedure for the TCAS 3000 Computer Unit A. Removal and Installation Procedure (1) Remove the TCAS computer unit. (a) Loosen mounting tray hold−down knobs. (b) Slowly pull forward on the computer unit handle to separate computer unit and mounting tray connectors. The computer unit is now free to be removed from the mounting tray. (c) Place electrostatic protective covers on the computer unit and the mounting tray electrical connectors. (2) Reinstall the TCAS computer unit. (a) Remove protective plastic covers from aircraft connectors. Remove electrostatic protective covers from computer unit electrical connectors. (b) Slide computer unit into mounting tray. CAUTION: DO NOT FORCE FIT. IF MATING IS DIFFICULT, REMOVE THE COMPUTER UNIT AND EXAMINE THE CONNECTOR FOR PINS THAT ARE BENT OR OUT OF ALIGNMENT. ALSO CHECK THE ALIGNMENT OF THE RECEPTACLE IN THE MOUNTING TRAY. (c) Carefully apply firm pressure until the computer unit connectors mate with the connector receptacles on the mounting tray. (d) Tighten mounting tray hold−down knobs to make sure all connectors are fully engaged. B. Adjustment Procedure Not Applicable. C. Repair Procedure Not Applicable. D. Return to Service Procedures Do the Return to Service Test Procedures referenced in the ADJUSTMENT/TEST section of this manual. Page 7−2 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System 4. Procedure for the Directional Antenna A. Removal and Installation Procedure (1) Remove the directional antenna. (a) If applicable, use a phenolic scraper to remove aerodynamic sealant around periphery of antenna. (b) Remove four or eight (quantity depends on dash number of antenna) non−Torx drive screws used to attach antenna to fuselage. See Figure 2−6 for location and number of mounting holes for each dash number antenna. (c) Carefully lift antenna from fuselage avoiding any damage to the coaxial cables. (d) Disconnect coaxial cables from antenna connectors J1, J2, J3, and J4. (e) Put protective covers on the aircraft coaxial cable connectors and the antenna coax connectors. (2) Reinstall the directional antenna. (a) If applicable, remove any existing aerodynamic sealant from antenna and clean antenna mounting area. (b) Put supplied o−ring in antenna o−ring groove. If antenna is supplied with a Teflon gasket, install gasket between antenna and fuselage. (c) Remove protective covers from antenna and aircraft coaxial mating connectors. (d) Examine antenna and coaxial mating connectors to make sure they are clean and secure. (e) Orient antenna with respect to airframe (arrow painted on radome must point forward). Connect four aircraft coaxial cables to antenna. Refer to Figure 2−6 for wiring information. Note the color bands on the antenna connectors and cables: yellow = J1, black = J2, blue = J3, and red = J4. NOTE: (f) Do not apply a sealant between antenna base and fuselage. Application of a sealant will reduce lightning protection. Align antenna mounting holes with holes in fuselage (note the non−symmetric hole pattern). (g) Attach antenna to fuselage with four or eight (quantity depends on dash number of antenna) non−Torx drive screws and flat washers. See tables 3 and 4 of Figure 2−6 for dash number mounting information. Apply a sealant to the screw threads before installing them. Torque mounting screws to 22 ± 3 inch−pounds (2.5 ± 0.2 Newton−Meters). (h) Apply an aerodynamic sealant around periphery of the antenna base to prevent seepage of water and condensation and to preclude corrosion. 34−43−23 Page 7−3 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System B. Adjustment Procedure Not Applicable. C. Repair Procedure The ACSS TCAS Directional Antenna is a non−repairable item. If the antenna is damaged or determined to be faulty, it must be replaced with a new antenna. D. Return to Service Procedures Do the Return to Service Test Procedures referenced in the ADJUSTMENT/TEST section of this manual. 5. Procedure for the Omnidirectional Antenna A. Removal and Installation Procedure (1) Remove the Omnidirectional Antenna. (a) If applicable, use a phenolic scraper to remove aerodynamic sealant around periphery of antenna baseplate. (b) If applicable, remove sealant from antenna mounting screw holes. (c) Remove retaining screws used to attach antenna to aircraft fuselage. (d) Carefully pull antenna from fuselage. (e) Disconnect coaxial cable from antenna connector. (f) Put protective covers on the aircraft coaxial cable connector and the antenna connector. (2) Reinstall the Omnidirectional Antenna. (a) If applicable, remove any existing aerodynamic sealant from antenna mounting surface and clean antenna mounting area. (b) Remove and clean sealant from baseplate and baseplate cutout. (c) Remove protective covers from antenna and coaxial cable connectors. (d) Examine antenna and coaxial cable connectors to make sure they are clean and secure. (e) Connect aircraft coaxial cable to antenna connector. (f) Apply a coating of sealant under heads of antenna mounting screws and position antenna on fuselage mounting surface. Attach antenna to fuselage with mounting screws. (g) Apply an aerodynamic sealant around the periphery of the antenna baseplate. Page 7−4 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System B. Adjustment Procedure Not Applicable. C. Repair Procedure Most omnidirectional antennas are non−repairable. If the antenna is damaged or determined to be faulty, it must be replaced with a new antenna. D. Return to Service Procedures Do the Return to Service Test Procedures referenced in the ADJUSTMENT/TEST section of this manual. 6. Procedure for the Control Panel A. Removal and Installation Procedure (1) Remove the Control Panel. (a) Disengage Dzus fasteners on control panel. (b) Pull control panel out of aircraft mounting location and disconnect aircraft cable connectors. Control panel is now free to be removed from aircraft. (c) Put electrostatic protective covers on control panel and aircraft mating electrical connectors. (2) Reinstall the Control Panel. (a) Remove protective covers from control panel and aircraft mating connectors. (b) Connect aircraft cables to control panel connectors J1 and J2. (c) Insert control panel into mounting location. (d) Engage Dzus fasteners on the control panel to attach it to aircraft structure. B. Adjustment Procedure Not Applicable. C. Repair Procedure Any repair procedures should be in accordance with the manufacturer’s repair instructions. D. Return to Service Procedures Do the Return to Service Test Procedures referenced in the ADJUSTMENT/TEST section of this manual. 34−43−23 Page 7−5 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System 7. Procedure for the VSI/TRA Display A. Removal and Installation Procedure (1) Remove the VSI/TRA Display. (a) Loosen screws of instrument panel mounting clamp. NOTE: Most installation clamps require the top screws be loosened to remove the instrument. Other clamps require the diagonal screws be loosened. Refer to the aircraft maintenance manual (AMM) for specific application. (b) Pull the VSI/TRA out of the instrument panel and disconnect J1 mating connector. (c) Put electrostatic protective covers on display and aircraft mating electrical connectors. (2) Reinstall the VSI/TRA Display. (a) Remove protective covers from display and aircraft mating connectors. (b) Connect aircraft cable to VSI/TRA connector J1. (c) Insert the display into the instrument panel and push all the way back against panel. (d) Tighten the four instrument mounting clamp screws. B. Adjustment Procedure Not Applicable. C. Repair Procedure Not Applicable. D. Return to Service Procedures Do the Return to Service Test Procedures referenced in the ADJUSTMENT/TEST section of this manual. Page 7−6 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System 8. Procedure for the Pressure Transducer Module A. Removal and Installation Procedure (1) Remove the Pressure Transducer Module. (a) Disconnect aircraft electrical mating connector from PTM connector J1. (b) Disconnect pneumatic fitting from PTM. (c) Loosen the two captive fasteners used to attach the PTM to its mounting bracket or plate and remove unit. (2) Reinstall the Pressure Transducer Module. (a) Attach PTM to mounting bracket or plate with two captive screws. (b) Connect pneumatic line to fitting on PTM. (c) Connect aircraft electrical cable to PTM connector J1. B. Adjustment Procedure Not Applicable. C. Repair Procedure Not Applicable. D. Return to Service Procedures Do the Return to Service Test Procedures referenced in the ADJUSTMENT/TEST section of this manual. 34−43−23 Page 7−7 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System 9. Procedure for the Transponder A. Removal and Installation Procedure (1) Remove Transponder (a) Loosen mounting tray hold−down knobs. (b) Slowly pull forward on the unit handle to separate transponder and mounting tray connectors. The transponder is now free to be removed from the mounting tray. (c) Place electrostatic protective covers on the transponder and the mounting tray electrical connectors. (2) Reinstall Transponder (a) Remove protective plastic covers from mounting tray connectors and transponder electrical connectors. (b) Slide transponder into mounting tray. CAUTION: DO NOT FORCE FIT. IF MATING IS DIFFICULT, REMOVE THE UNIT AND EXAMINE THE CONNECTORS FOR PINS THAT ARE BENT OR OUT OF ALIGNMENT. ALSO CHECK THE ALIGNMENT OF THE RECEPTACLE IN THE MOUNTING TRAY. (c) Carefully apply firm pressure until the transponder connectors mate with the connector receptacles on the mounting tray. (d) Tighten mounting tray hold−down knobs making sure all connectors are fully engaged. B. Adjustment Procedure Not Applicable. C. Repair Procedure Not Applicable. Page 7−8 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System D. Return to Service Procedures (1) For installations using serial data bus (ARINC 429) altitude data: (a) The POST (automatic on power on) and PAST self test (initiated from the control panel) are the only required Return to Service tests for the transponder. (b) After the transponder passes these tests, the appropriate logbook entries may be made and the unit is ready for use. (2) For installations using parallel (Gillham code) altitude data: (a) The POST (automatic on power on) and PAST self test (initiated from the control panel) must be passed. (b) Connect an air data tester to the aircraft pitot/static system and set up a transponder ramp tester. (c) Setup the air data tester to output the following altitudes. The transponder’s encoded altitude must correspond. • 11,700 feet • 24,400 feet • 30,800 feet. NOTE: These three altitudes check the operation of all parallel altitude wires. (d) After the transponder passes these tests, the appropriate logbook entries may be made and the unit is ready for use. 34−43−23 Page 7−9 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System 10. Instructions for Continued Airworthiness, FAR Part 25.1529 Maintenance requirements and instructions for Continued Airworthiness of the TCAS 3000 Traffic Alert and Collision Avoidance System components are contained in the paragraphs that follow: Installation of the TCAS 3000 on an aircraft by Supplemental Type Certificate or Form 337 obligates the aircraft operator to include the maintenance information provided by this manual in the operator’s AMMl and the operator’s Aircraft Scheduled Maintenance Program. A. Maintenance information for the TCAS 3000 (system description, removal, installation, testing, etc.) is contained in this manual. B. LRU part numbers and other necessary part numbers contained in this manual should be placed into the aircraft operator’s appropriate aircraft illustrated parts catalog (IPC). C. Wiring diagram information contained in this manual should be placed into the aircraft operator’s appropriate aircraft Wiring Diagram Manuals. D. The TCAS 3000 components are considered on−condition units and no additional maintenance is required other than a check for security and operation at normal inspection intervals. E. If a system component is inoperative, remove unit, secure cables and wiring, collar applicable switches and circuit breakers, and placard them inoperative. Revise equipment list and weight and balance as applicable prior to flight and make a log book entry that unit was removed (refer to FAR Part 91.213 or the aircraft’s Minimum Equipment List [MEL]). F. The TCAS 3000 components can be repaired only at a factory authorized repair center or an appropriately rated FAA Part 145 repair station. G. Once repaired, reinstall the LRU in the aircraft in accordance with the original Form 337 approved data or instructions in this manual. Do a Return to Service test of the system and approve it for return to service with a log book entry in accordance with the requirements specified in FAR Part 43.9. Page 7−10 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System H. Scheduled maintenance program tasks to be added to the aircraft operator’s appropriate aircraft maintenance program are as follows: (1) Recommended periodic scheduled servicing tasks: None required. (2) Recommended periodic inspections are as follows: • The TCAS directional antennas used with the TCAS 3000 should be removed and the underlying structure inspected for deterioration and corrosion during zonal inspections usually performed in conjunction with heavy maintenance D checks. • The ATC transponder(s) used with this system have test and inspections that are required by FAR 91.413 to be completed every 24 months. (3) Recommended periodic scheduled preventative maintenance tests (Tests to determine system condition and/or latent failures): • The ACSS TCAS 3000 Computer Unit is designed to detect its own failures as well as failures external to the computer unit itself. This BITE is continuously being executed on a periodic basis. No formal periodic maintenance is required for the TCAS computer unit or the VSI/TRA display. • The ACSS RCZ−852 Diversity Mode S Transponder is designed to detect its own failures. This BITE is continuously being executed on a periodic basis. No formal periodic maintenance is required for the transponder other than the 24 month recertification test required by FAR 91.413. 34−43−23 Page 7−11 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Blank Page Page 7−12 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System INSPECTION/CHECK 1. General The visual check procedures that follow are recommended for the TCAS 3000 Traffic Alert and Collision Avoidance System components after they have been installed in the aircraft. 2. Equipment and Materials None 3. Procedure CAUTION: BEFORE YOU DO ANY OF THE PROCEDURES THAT FOLLOW, MAKE SURE THAT ALL TCAS SYSTEM CIRCUIT BREAKERS ARE PULLED. A. Check TCAS Computer Unit (1) Visually examine all external surfaces for possible damage. Check dust cover and external connectors for dust, corrosion, or damage. (2) Check external parts for loose or damaged hardware. (3) Make visual check of wiring and connectors for damage. B. Check Antennas (1) Visually examine all external surfaces for possible damage. (2) Check cabling for breaks, burned areas, and damaged insulation. C. Check Control Panel (1) Visually examine all external surfaces for possible damage. (2) Check external parts (connectors, control knobs, annunciators) for looseness or damage. (3) Check that controller is securely mounted (Dzus fasteners properly engaged). (4) Check controls for smooth, positive action. 34−43−23 Page 8−1 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System D. Check VSI/TRA Display (1) Visually examine all external surfaces for possible damage. Check dust cover and external connector for dust or damage. (2) Check that display is securely mounted (locking mechanism is properly engaged). (3) Check that LCD glass is not scratched or cracked. E. Check Transponders (1) Visually examine all external surfaces for possible damage. Check dust cover and external connectors for dust, corrosion, or damage. (2) Check external parts for loose or damaged hardware. (3) Make visual check of wiring and connectors for damage. Page 8−2 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System CLEANING/PAINTING 1. General While the TCAS 3000 Traffic Alert and Collision Avoidance System is installed in the aircraft, cleaning is limited to the procedures given below. Painting and more extensive cleaning should be done during shop maintenance when the LRUs can be disassembled. Detailed instructions are given in each applicable component−level maintenance manual. 2. Equipment and Materials WARNING: BEFORE YOU USE A MATERIAL, REFER TO THE MANUFACTURERS’ MATERIAL SAFETY DATA SHEETS FOR SAFETY INFORMATION. SOME MATERIALS CAN BE DANGEROUS. Table 9−1 gives the equipment and materials required for cleaning and painting. Table 9−1. Equipment and Materials Name Description Source Abrasive paper No. 600, nonconductive abrasive Optional source Air supply Air ionizing nozzle gun attachment for compressed air (20 psi) Optional source Cleaning brush Soft, natural−bristle (camel’s hair) Optional source Glass cleaner Ammoniated Optional source Lens tissue Non−linting Optional source Sandpaper Grit sizes 220 and 400 Optional source AMN 110C878 Catalyst, polyurethane — No. V66V44(−4) Sherwin−Williams Co, Cleveland, OH AMN 110C978 Reducer, polyurethane — No. R7K84 Sherwin−Williams Co, Cleveland, OH AMN 1130778 Solvent — Isopropyl alcohol (99%), semigrade Optional source AMN 6008676 Lint free cloth — Bluewipes, No. TX512 Texwipe Co, Upper Saddle River, NJ 34−43−23 Page 9−1 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Table 9−1. Equipment and Materials (cont) Name Description Source AMN 94C2178 Coating, Prolane 2.8TPLUS Sherwin−Williams Co, polyurethane, semigloss WHT, Cleveland, OH FED−STD−595, Color No. 27925 — No. F63EXW968−4380 AMN 9460078 Primer, coating, epoxy, low VOC (MIL−P−23377, Type I, Class 2) Optional source NOTES: 1. Equivalent alternatives are permitted for equipment and materials in this list. 2. The AMN codes in the list of materials identify the ACSS Material Number (AMN) given to each material. 3. Cleaning CAUTION: IF YOU CLEAN ELECTROSTATIC SENSITIVE COMPONENTS WITH PRESSURIZED AIR, MAKE SURE THE HOSE HAS AN AIR IONIZING NOZZLE OR GUN. AN ELECTROSTATIC CHARGE CAN CAUSE DAMAGE TO THE LRU COMPONENT PARTS IF THE NOZZLE OR GUN ATTACHMENT IS NOT USED. A. Clean TCAS Computer Unit and Mounting Tray (1) Loosen mounting tray hold−down clamps and pull TCAS computer unit out of mounting tray. (2) Clean mounting tray with cloth or brush dampened with solvent, then dry with cloth or compressed air. (3) Clean all dust and foreign matter from front panel and cover air vents with a clean cloth or brush dampened with solvent or clean with compressed air. B. Clean Antennas Clean antennas with a cloth dampened with solvent. Dry with a clean cloth or use compressed air. C. Clean Control Panel (1) Clean dust and foreign matter from cover and connectors with a brush dampened with solvent, then dry with a clean cloth or compressed air. (2) Clean front of control panel with a mild glass cleaner and soft cotton cloth. Page 9−2 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System D. Clean VSI/TRA Display (1) Clean front panel of display with a mild glass cleaner and soft cotton cloth. (2) Clean the glass face with a mild glass cleaner and lens tissue. E. Clean Transponders Clean transponders with a cloth dampened with solvent. Dry with a clean cloth or use compressed air. 4. Painting A. TCAS Directional Antennas (1) Scope This procedure covers the removal and re−application of coating to the TCAS directional antenna. Localized touch−up is allowable and preferred using airbrush techniques to ensure minimal paint thickness. The touch−up may be applied either with the antenna on the aircraft or removed from the aircraft. (2) Procedure WARNING: SOLVENTS AND COATINGS ARE COMBUSTIBLE. KEEP AWAY FROM HEAT AND OPEN FLAME. (a) Clean Scrape away all filleting and adhesive material from area to be coated. Remove surface contamination using isopropyl alcohol or reducer. (b) Scuff Sand If the entire antenna is to be recoated, sand to primer with 220 grit sandpaper. An orbital sander is preferred. For localized touch−up, feather sand areas of exposed radome material to provide a smooth transition to the painted surface. (c) Final Sand If the entire antenna is to be recoated, sand primer and through−holes using 400 grit sandpaper or Scotch−Brite so the primer is removed except in swirls wherever possible. (d) Final Clean Clean the surface to be coated with isopropyl alcohol or reducer. 34−43−23 Page 9−3 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System (e) Prime NOTE: The pot life of the primer after mixing components is 8 hours. Cover each Torx screw head with an adhesive dot to prevent paint from being applied to the screw heads. Mix epoxy primer components in a 1:1 ratio under slow agitation. Allow 15 minutes before spraying. Spray one light coat − wet film thickness of 1.5 mils. • Viscosity − 18 to 20 seconds No. 2 Zahn test • Gun orifice − 363−A needle or equivalent • Fluid pressure − 5 to 10 psi recommended • Air pressure − 50 psi recommended. (f) Primer Cure Allow the primer to air dry for a minimum of one hour and a maximum of 4 hours before applying the top coat. (g) Paint Mix paint in a base (coating) to catalyst ratio of 6:1 under slow agitation. NOTE: The percentage of reducer used can vary to meet the applicable color standard. Spray one light tack coat and allow to dry 15 minutes. • Viscosity − 20 to 22 seconds No. 2 Zahn test • Gun orifice − 363−A needle or equivalent • Fluid pressure − 5 to 10 psi recommended • Air pressure − 50 psi recommended. Apply final top coat − total wet film thickness of 3.5 to 4.0 mils. (h) Drying Cycle The antenna must air dry overnight or be baked at 85 degrees Celsius for 30 minutes minimum before flying. Remove the adhesive dots from the heads of the Torx screws. (3) Performance Verification Testing Perform a ramp test per approved aircraft maintenance procedure on the TCAS system to ensure the bearing accuracy is within specification after the coating application. Page 9−4 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System B. Other TCAS System LRUs Except for minor touch up, painting should only be done after the LRU has been removed from the aircraft or during shop maintenance. Painting procedures and materials are given in the applicable LRU component maintenance manual (CMM). 34−43−23 Page 9−5 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Blank Page Page 9−6 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System REPAIRS 1. General Major repairs to the TCAS 3000 system components are made only during shop maintenance when the equipment is removed from the aircraft. Detailed instructions for repair and adjustment of each of the repairable LRUs are presented in the applicable component maintenance manuals given in Table 10−1. Table 10−1. LRU Maintenance Manual ACSS Component Maintenance Manual (CMM) ATA Number A09−3841−002 34−43−11 Control Panel Part No. 4052190−902, −904, −906, −908 15−3841−01 34−43−01 Control Panel Part No. 4052190−903, −905, −907, −909 15−3841−03 34−43−05 VSI/TRA Indicator Part No. 4067241−8XX 15−2254−01 22−54−01 Pressure Transducer Module Part No. 4067487−901 15−3841−06 34−43−03 XS−950 Mode S Data Link Transponder Part No. 7517800−XXYYY A09−3839−002 34−52−08 RCZ−852 Diversity Mode S Transponder Part No. 7510700−850 A09−3800−15 23−81−01 LRU TCAS 3000 Computer Unit Part No. 7517900−10YYY, −55YYY, 71YYY 34−43−23 Page 10−1 15 Dec 2005 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. SYSTEM DESCRIPTION AND INSTALLATION MANUAL TCAS 3000 Traffic Alert and Collision Avoidance System Blank Page Page 10−2 15 Dec 2005 34−43−23 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
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