Honeywell 9PGTPA-100A TPA-100A TCAS II Processor User Manual Title1 Draft

Honeywell International Inc. TPA-100A TCAS II Processor Title1 Draft

Users Manual

34-45-47Title Page T-11 Dec 2003Pub. No. 012-0680-001Printed in U.S.A.HoneywellAerospace Electronics SystemsP.O. Box 97001Redmond, Washington 98073-9701U.S.AMaintenance ManualCAS-100Collision Avoidance SystemThis document contains technical data and is subject to U.S. export regulations.These commodities, technology, or software were exported from the United States in accordance with the export administration regulations. Diversion contrary to U.S. law is prohibited.
MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMCopyright 2003 HoneywellAll Rights ReservedTitle Page T-21 Dec 200334-45-47PROPRIETARY NOTICEThis document and the information disclosed herein are proprietary data of Honeywell. Neither this document nor the information contained herein shall be used, reproduced, or disclosed to others without the written authorization of Honeywell, except to the extent required for installation or mainte-nance 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 Honeywell. The information disclosed herein fall within exemption (b) (4) of 5 usc 552 and the prohibitions of 18 usc 1905.S2003Honeywell is a U.S. registered trademark of Honeywell. All other marks are owned by their respective companies.
Page RR-11 Dec 2003MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.34-45-47RECORD OF REVISIONSFor each revision, put the revised pages in your manual and discard the superseded pages.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 H shows Honeywell is the incorporator.Revision Number Revision Date Date Put In Manual By Revision Number Revision Date Date Put In Manual By
Page RR-21 Dec 2003MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.34-45-47THIS PAGE LEFT BLANK
Page RTR-11 Dec 2003MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.34-45-47RECORD OF TEMPORARY REVISIONSInstructions on each page of a temporary revision tell you where to put the pages in your manual. Remove temporary revision pages only when discard instructions are given. For each temporary revision, put the applicable data in the record columns on this page.* The initial H is this column shows Honeywell has done this task.Temporary Revision Number Temporary Revision Date Temporary Revision Status Date Put in Manual By* Date Removed from Manual By*
Page RTR-21 Dec 2003MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.34-45-47THIS PAGE LEFT BLANK
Page SBL-11 Dec 2003.MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMSERVICE BULLETIN LISTUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.34-45-47Service BulletinIdentifiedModDate Included in this Manual Description
Page SBL-21 Dec 2003MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.34-45-47THIS PAGE LEFT BLANK
MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMLIST OF EFFECTIVE PAGESLEP-11 Dec 2003F Indicates a foldout page.Subheading and Page Date Subheading and Page DateUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.34-45-47TitleT-1 1 Dec 2003T-2 1 Dec 2003Record of RevisionsRR-1 1 Dec 2003RR-2 1 Dec 2003Record of Temporary RevisionsRTR-1 1 Dec 2003RTR-2 1 Dec 2003Service Bulletin ListSBL-1 1 Dec 2003SBL-2 1 Dec 2003List of Effective PagesLEP-1 1 Dec 2003LEP-2 1 Dec 2003LEP-3 1 Dec 2003LEP-4 1 Dec 2003LEP-5 1 Dec 2003LEP-6 1 Dec 2003Table of ContentsTC-1 1 Dec 2003TC-2 1 Dec 2003TC-3 1 Dec 2003TC-4 1 Dec 2003TC-5 1 Dec 2003TC-6 1 Dec 2003TC-7 1 Dec 2003TC-8 1 Dec 2003TC-9 1 Dec 2003TC-10 1 Dec 2003Introduction INTRO-1 1 Dec 2003 INTRO-2 1 Dec 2003 INTRO-3 1 Dec 2003 INTRO-4 1 Dec 2003 INTRO-5 1 Dec 2003 INTRO-6 1 Dec 2003 INTRO-7 1 Dec 2003 INTRO-8 1 Dec 2003 0 1 Dec 2003 00 1 Dec 2003Description and Operation1 1 Dec 20032 1 Dec 20033 1 Dec 20034 1 Dec 20035 1 Dec 20036 1 Dec 20037 1 Dec 20038 1 Dec 20039 1 Dec 200310 1 Dec 200311 1 Dec 200312 1 Dec 200313 1 Dec 200314 1 Dec 200315 1 Dec 200316 1 Dec 200317 1 Dec 200318 1 Dec 200319 1 Dec 200320 1 Dec 200321 1 Dec 200322 1 Dec 2003
MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMLIST OF EFFECTIVE PAGESLEP-21 Dec 2003F Indicates a foldout page.Subheading and Page Date Subheading and Page DateUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.34-45-4723 1 Dec 200324 1 Dec 200325 1 Dec 200326 1 Dec 200327 1 Dec 200328 1 Dec 200329 1 Dec 200330 1 Dec 200331 1 Dec 200332 1 Dec 200333 1 Dec 200334 1 Dec 200335 1 Dec 200336 1 Dec 200337 1 Dec 200338 1 Dec 200339 1 Dec 200340 1 Dec 2003F 41/42 1 Dec 200343 1 Dec 200344 1 Dec 200345 1 Dec 200346 1 Dec 200347 1 Dec 200348 1 Dec 200349 1 Dec 200350 1 Dec 200351 1 Dec 200352 1 Dec 200353 1 Dec 200354 1 Dec 200355 1 Dec 200356 1 Dec 200357 1 Dec 200358 1 Dec 200359 1 Dec 200360 1 Dec 2003F 61/62 1 Dec 2003F 63/64 1 Dec 2003F 65/66 1 Dec 200367 1 Dec 200368 1 Dec 200369 1 Dec 200370 1 Dec 200371 1 Dec 200372 1 Dec 200373 1 Dec 200374 1 Dec 200375 1 Dec 200376 1 Dec 2003F 77/78 1 Dec 200379 1 Dec 200380 1 Dec 200381 1 Dec 200382 1 Dec 200383 1 Dec 200384 1 Dec 200385 1 Dec 200386 1 Dec 200387 1 Dec 200388 1 Dec 200389 1 Dec 2003
MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMLIST OF EFFECTIVE PAGESLEP-31 Dec 2003F Indicates a foldout page.Subheading and Page Date Subheading and Page DateUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.34-45-4790 1 Dec 200391 1 Dec 200392 1 Dec 200393 1 Dec 200394 1 Dec 200395 1 Dec 200396 1 Dec 200397 1 Dec 200398 1 Dec 200399 1 Dec 2003100 1 Dec 2003101 1 Dec 2003102 1 Dec 2003103 1 Dec 2003104 1 Dec 2003105 1 Dec 2003106 1 Dec 2003107 1 Dec 2003108 1 Dec 2003109 1 Dec 2003110 1 Dec 2003F 111/112 1 Dec 2003F 113/114 1 Dec 2003Testing and Fault Isolation1001 1 Dec 20031002 1 Dec 20031003 1 Dec 20031004 1 Dec 20031005 1 Dec 20031006 1 Dec 20031007 1 Dec 20031008 1 Dec 20031009 1 Dec 20031010 1 Dec 20031011 1 Dec 20031012 1 Dec 20031013 1 Dec 20031014 1 Dec 20031015 1 Dec 20031016 1 Dec 20031017 1 Dec 20031018 1 Dec 20031019 1 Dec 20031020 1 Dec 20031021 1 Dec 20031022 1 Dec 20031023 1 Dec 20031024 1 Dec 20031025 1 Dec 20031026 1 Dec 20031027 1 Dec 20031028 1 Dec 20031029 1 Dec 20031030 1 Dec 20031031 1 Dec 20031032 1 Dec 20031033 1 Dec 20031034 1 Dec 20031035 1 Dec 20031036 1 Dec 2003Maintenance Practices2001 1 Dec 20032002 1 Dec 20032003 1 Dec 2003
MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMLIST OF EFFECTIVE PAGESLEP-41 Dec 2003F Indicates a foldout page.Subheading and Page Date Subheading and Page DateUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.34-45-472004 1 Dec 20032005 1 Dec 20032006 1 Dec 20032007 1 Dec 20032008 1 Dec 20032009 1 Dec 20032010 1 Dec 20032011 1 Dec 20032012 1 Dec 20032013 1 Dec 20032014 1 Dec 20032015 1 Dec 20032016 1 Dec 20032017 1 Dec 20032018 1 Dec 20032019 1 Dec 20032020 1 Dec 20032021 1 Dec 20032022 1 Dec 20032023 1 Dec 20032024 1 Dec 20032025 1 Dec 20032026 1 Dec 20032027 1 Dec 20032028 1 Dec 20032029 1 Dec 20032030 1 Dec 20032031 1 Dec 20032032 1 Dec 20032033 1 Dec 20032034 1 Dec 20032035 1 Dec 20032036 1 Dec 20032037 1 Dec 20032038 1 Dec 20032039 1 Dec 20032040 1 Dec 20032041 1 Dec 20032042 1 Dec 20032043 1 Dec 20032044 1 Dec 20032045 1 Dec 20032046 1 Dec 20032047 1 Dec 20032048 1 Dec 20032049 1 Dec 20032050 1 Dec 20032051 1 Dec 20032052 1 Dec 20032053 1 Dec 20032054 1 Dec 20032055 1 Dec 20032056 1 Dec 20032057 1 Dec 20032058 1 Dec 2003F 2059/2060 1 Dec 2003F 2061/2062 1 Dec 2003F 2063/2064 1 Dec 2003F 2065/2066 1 Dec 2003F 2067/2068 1 Dec 2003F 2069/2070 1 Dec 2003F 2071/2072 1 Dec 2003
MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMLIST OF EFFECTIVE PAGESLEP-51 Dec 2003F Indicates a foldout page.Subheading and Page Date Subheading and Page DateUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.34-45-47F 2073/2074 1 Dec 2003F 2075/2076 1 Dec 2003F 2077/2078 1 Dec 2003F 2079/2080 1 Dec 2003F 2081/2082 1 Dec 2003F 2083/2084 1 Dec 2003F 2085/2086 1 Dec 2003F 2087/2088 1 Dec 2003F 2089/2090 1 Dec 2003F 2091/2092 1 Dec 2003F 2093/2094 1 Dec 20032095 1 Dec 20032096 1 Dec 2003F 2097/2098 1 Dec 2003F 2099/2100 1 Dec 2003F 2101/2102 1 Dec 2003F 2103/2104 1 Dec 20032105 1 Dec 20032106 1 Dec 20032107 1 Dec 20032108 1 Dec 20032109 1 Dec 20032110 1 Dec 20032111 1 Dec 20032112 1 Dec 20032113 1 Dec 20032114 1 Dec 20032115 1 Dec 20032116 1 Dec 20032117 1 Dec 20032118 1 Dec 20032119 1 Dec 20032120 1 Dec 20032121 1 Dec 20032122 1 Dec 20032123 1 Dec 20032124 1 Dec 20032125 1 Dec 20032126 1 Dec 20032127 1 Dec 20032128 1 Dec 20032129 1 Dec 20032130 1 Dec 2003
MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMLEP-61 Dec 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.34-45-47THIS PAGE LEFT BLANK
Page TC-11 Dec 2003MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.34-45-47 Subject PageINTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .INTRO-11. Proprietary, Export, and Precautionary Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .INTRO-1A. Proprietary Notice . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .INTRO-1B. Export Notice . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .INTRO-1C. Special Precautions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .INTRO-12. Content Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .INTRO-2A. How to Use This Manual . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .INTRO-2B. Verification . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .INTRO-4C. Symbols . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .INTRO-5D. Weights and Measurements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .INTRO-5E. Acronyms and Abbreviations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .INTRO-6DESCRIPTION AND OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1A. Purpose of Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1B. Equipment Part Numbers. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3C. TCAS Accessories. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14D. Aircraft Equipment Required But Not Supplied By Honeywell . . . . . . . . . . . . . . . . . . . . . 15E. Aircraft Optional (Non Essential) Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17F. Related Publications. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .182. System Configurations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18A. System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18B. TPA-100A TCAS Processor . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 193. System Leading Particulars . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .19A. TCAS Surveillance Volumes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 (1) Range Tracking Volumes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 (2) Altitude Tracking Volumes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .20B. TCAS Sensitivity Level - Operating Modes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20C. Component Leading Particulars . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26 (1) Leading Particulars . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .26(2) Environmental Certification . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 36TABLE OF CONTENTS
MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMPage TC-21 Dec 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.34-45-474. System Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .37A. General. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .37B. CAS-100 Functional Overview . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37(1) Surveillance Function . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37(2) Tracking Function . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38(3) Threat Potential Evaluation Function . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .38(4) Collision Avoidance Computation and Resolution Advisory Display Function . . . . . . 38(5) Traffic Advisory Display Function . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .38(6) Aural Alert Function . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38(7) Air-to-Air Coordination Function . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39(8) Data Recording Function . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39(9) Data Loader Function . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 395. System Component Description and Functions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39A. TCAS Processor. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .39(1) General. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .39(2) TCAS Processor Description and Basic Functions . . . . . . . . . . . . . . . . . . . . . . . . . . 39(3) Real-Time TCAS Functions Controlled by Processor. . . . . . . . . . . . . . . . . . . . . . . . . 44(4) Power Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .50(5) Rear Connector . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 51(6) Leading Particulars. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 51B. Directional Antenna . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .51(1) General. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .51(2) TCAS Directional Antenna Description and Basic Functions . . . . . . . . . . . . . . . . . . .51C. TA/VSI Display . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 54(1) General. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .54(2) Resolution Advisory Display . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 54(3) Traffic Display . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .55D. RA/VSI Display. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 56E. ITA-81A Traffic Display. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .57F. PPI Traffic Advisory Display Option . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .57G. Mode S Transponder . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .57H. CTA-100( ) Control Unit. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .58 I. TCAS and Mode S Transponder Omnidirectional Antennas . . . . . . . . . . . . . . . . . . . . . . 59Subject Page
Page TC-31 Dec 2003MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.34-45-476. Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 59A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 59 (1) Complete Block Diagrams and Description of Input/Output Signals. . . . . . . . . . . . . 59 (2) TCAS Failure Monitoring. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 59B. Detailed Block Diagrams and Description of Input/Output Signals . . . . . . . . . . . . . . . . . 59 C. TCAS Failure Monitoring . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .817. Controls and Indicators . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 82 A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 82 B. TCAS Input Power Control . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 82 C. CTA-81( ) Control Unit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 82 D. CTA-100A Control Unit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 82 E. TA/VSI . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 104 (1) Resolution Advisories . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 104 (2) Traffic Display . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 104 F. RA/VSI . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 107 G. Dedicated TCAS Traffic Display . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 107 H. PPI Radar/TCAS Display. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 109 I. Optional Aural/Lamp Advisory Outputs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 109 J. Audio Message Alerts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 109 K. TCAS Processor and Mode S Transponder Front Panel Indicators and TEST Switch . 109 L. Optional Advisory Cancel Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 109 M. Range Selection and Range Rings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 110TESTING AND FAULT ISOLATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10011. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10012. Fault Isolation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1001A. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1001B. Using Transponder/TCAS Control Unit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1002(1) Dual Mode S Equipped Aircraft . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1002(2) No Malfunctions Reported . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1002(3) Failure Detected During Self-Test . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1004(4) Test Results Not to Specifications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1004(5) Dual Mode S Equipped Aircraft . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1004(6) Selt-Test Using CTA-81( ) Indicators . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1005Subject Page
MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMPage TC-41 Dec 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.34-45-47C. Using TCAS Processor Front-Panel Buttons and LCD Display . . . . . . . . . . . . . . . . . . 1008(1) General. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1008(2) Unit OK/System Failed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1010(3) System OK/Failed Display Screen . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1010(4) Unit, System, and Input Active Fault Relationship . . . . . . . . . . . . . . . . . . . . . . . . .1018(5) Stored Faults . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1022(6) Configuration Display Screen . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1024(7) Inputs Display Screen. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1025MAINTENANCE PRACTICES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20011. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20012. Unpacking . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20013. Pre Installation Testing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20014. Equipment Changes and Markings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20015. Installation Planning . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2002A. General. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2002B. Location of Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2002(1) TCAS Processor Location . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2002(2) TCAS Antenna Location . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2002(3) Display Units (TA/VSI, RA/VSI, and Dedicated Display) . . . . . . . . . . . . . . . . . . . .2003C. Interwiring and Cable Fabrication . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2003(1) General. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2003(2) Interface Capability and Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2004(3) Primary Power and Circuit Breaker Requirements. . . . . . . . . . . . . . . . . . . . . . . . .2004(4) Suppression Pulse Requirements and Wiring . . . . . . . . . . . . . . . . . . . . . . . . . . . .2004(5) Antenna Cable Type Selection and Antenna Delay Program Straps . . . . . . . . . . .2004(6) Connectors . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2008D. Wire Strapping Options . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2027(1) TPA-100A TCAS Processor Straps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2027(2) IVA-81A/D TA/VSI and IVA-81B RA/VSI Straps. . . . . . . . . . . . . . . . . . . . . . . . . . .20296. Equipment Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2030A. TPA-100A TCAS Processor Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2030B. TCAS Directional Antenna Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2030(1) Directional Antenna Positioning and Wiring Specifications . . . . . . . . . . . . . . . . . . 2030(2) Directional Antenna Footprints Drilling and Mounting . . . . . . . . . . . . . . . . . . . . . . 2030Subject Page
Page TC-51 Dec 2003MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.34-45-47(3) Directional Antenna Adapter Installation for 8-hole, Flat Base Antenna . . . . . . . . 2031C. TCAS Omni Antenna Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2035(1) Antenna Positioning and Wiring Specifications . . . . . . . . . . . . . . . . . . . . . . . . . . . 2035(2) Mounting. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2035D. TA/VSI and RA/VSI Unit Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2035E. Dedicated TCAS Traffic Display. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2035F. Mode S Transponder System Component Installation . . . . . . . . . . . . . . . . . . . . . . . . . 20357. Inspection, System Checkout, and Flight Test Procedures. . . . . . . . . . . . . . . . . . . . . . . . 2036A. Inspection. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2036(1) Individual Unit Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2036B. System Checkout. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2037(1) General. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2037(2) System Interwiring Check. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2037(3) Visual Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2038(4) Post Installation Test Using Self-Test Function . . . . . . . . . . . . . . . . . . . . . . . . . . . 2038(5) Ramp Test (Optional) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2040(6) Antenna Test . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2051(7) ARINC 429 Installation Checkout Data Words . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2051C. Flight Test . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20538. Removal and Replacement. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2054A. TPA-100A TCAS Processor . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2054(1) Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2054(2) Reinstall . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2054B. Directional Antenna . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2054(1) Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2054(2) Reinstall . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2054C. TA/VSI and RA/VSI . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2054(1) Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2054(2) Reinstall . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2055D. Dedicated TCAS Traffic Display . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2055(1) Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2055(2) Reinstall . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2055Subject Page
MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMPage TC-61 Dec 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.34-45-47E. TRA-67 ATC Mode S Transponder System Component . . . . . . . . . . . . . . . . . . . . . . . 2055 (1) Removal and Reinstall . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2055F. Omni Antenna . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2055(1) Removal and Reinstall . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .20559. Maintenance Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2056A In-Aircraft Adjustments . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2056B. System Protection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2056C. Lubrication . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2056D. Cleaning. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 205610. Aircraft Maintenance Programs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2057A. General. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2057B. Honeywell TCAS Maintenance Recommendations . . . . . . . . . . . . . . . . . . . . . . . . . . . 2057Subject Page
MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.34-45-47Page TC-71 Dec 2003List of Illustrations Figure PageFigure Intro-1 Symbols. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Intro-5Figure 1 CAS-100 Collision Avoidance System Components . . . . . . . . . . . . . . . . . . . . . . . 0Figure 2 CAS-100 Sensitivity Level Altitude Layers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21Figure 3 Typical Resolution Advisory and Traffic Advisory Volumes for Sensitivity Levels 24Figure 4 Collision Avoidance System Simplified Block Diagram . . . . . . . . . . . . . . . . . . . . 41Figure 5 ATCRBS Mode C and Mode S Interrogation Formats . . . . . . . . . . . . . . . . . . . . . 46Figure 6 ATCRBS/Mode S Transponder Reply Message Formats . . . . . . . . . . . . . . . . . . 47Figure 7 TCAS Transmit and Receive Beam Patterns for Directional Antenna. . . . . . . . . 52Figure 8 TCAS Processor System Interconnect Block Diagram . . . . . . . . . . . . . . . . . . . . 61Figure 9 IVA-81A/D and IVA-81B RA/VSI System Interconnect Block Diagram . . . . . . . . 77Figure 10 CTA-81A Control Unit (Typical) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 83Figure 11 CTA-81B Control Unit (Typical) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 90Figure 12 CTA-100A Controllers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 98Figure 13 TA/VSI Controls and Indicators . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 105Figure 14 RA/VSI Controls and Indicators. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 108Figure 15 ITA-81A Traffic Display Controls and Indicators . . . . . . . . . . . . . . . . . . . . . . . . 111Figure 16 PPI Radar/TCAS Display Controls and Indicators. . . . . . . . . . . . . . . . . . . . . . . 113Figure 1001 Test Pattern . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1003Figure 1002 TCAS Processor Front Panel LCD and Pushbuttons . . . . . . . . . . . . . . . . . . . 1009Figure 1003 Typical Main Menu Screen . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1010Figure 1004 Start Test/Test Inhibited Sample Flow Diagram . . . . . . . . . . . . . . . . . . . . . . . . 1021Figure 1005 Typical First and Last Pages of Stored Faults Display Screen . . . . . . . . . . . . 1022Figure 1006 Stored Faults LCD Screen Example . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1023Figure 1007 Typical Configuration Display Screen . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1024Figure 1008 Typical Input Display Screens (Pages 1-3) . . . . . . . . . . . . . . . . . . . . . . . . . . . 1025Figure 1009 Example of Discrete Screen . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1028Figure 1010 Digital Radio Altitude Display Screen Example . . . . . . . . . . . . . . . . . . . . . . . . 1032Figure 1011 Analog Radio Altitude Display Screen Example . . . . . . . . . . . . . . . . . . . . . . . 1032Figure 1012 Pressure Altitude Display Screen Example . . . . . . . . . . . . . . . . . . . . . . . . . . . 1033Figure 1013 Roll Display Screen Example . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1033
MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.34-45-47Page TC-81 Dec 2003Figure 1014 Pitch Display Screen Example . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1034Figure 1015 Heading Display Screen Example. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1034Figure 1016 Climb Inhibit Display Screen Example . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1035Figure 1017 Air/Ground Display Screen Example. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1035Figure 1018 Typical Mode S Transponder Display Screen . . . . . . . . . . . . . . . . . . . . . . . . . .1036Figure 1019 Continuous Wave Interference Display Screen. . . . . . . . . . . . . . . . . . . . . . . . .1036Figure 2001 TPA-100A TCAS Processor Aft Connector . . . . . . . . . . . . . . . . . . . . . . . . . . . .2009Figure 2002 IVA-81A/D, TA/VSI and IVA-81B, RA/VSI Aft Connector Locations . . . . . . . . .2022Figure 2003 TA/VSI and RA/VSI Electrical Connector Pin I/O . . . . . . . . . . . . . . . . . . . . . . .2023Figure 2004 ITA-81A Aft Connector . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2026Figure 2005 Adapter and Moldable Shim Assembled on the Airframe . . . . . . . . . . . . . . . . .2034Figure 2006 TPA-100A TCAS Processor Outline Drawing . . . . . . . . . . . . . . . . . . . . . . . . . .2059Figure 2007 ANT-81A Directional Antenna (Four-Element Array, Curved Base)Outline Drawing. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2063Figure 2008 ANT-81A Directional Antenna (Four-Element Array, Flat Base,Four Mounting Screws) Outline Drawing. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2065Figure 2009 ANT-81A Directional Antenna (Four-Element Array, Flat Base,Eight Mounting Screws) Outline Drawing . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2067Figure 2010 ANT-81A Directional Antenna Adapter for 8-Hole, Flat Base AntennaInstallation Drawing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2069Figure 2011 IVA-81A Traffic Advisory/Vertical Speed Indicator (TA/VSI)Outline Drawing. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2071Figure 2012 IVA-81B Resolution Advisory/Vertical Speed Indicator (RA/VSI)Outline Drawing. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2077Figure 2013 IVA-81D Traffic Advisory/Vertical Speed Indicator (TA/VSI)Outline Drawing. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2079Figure 2014 ITA-81A Traffic Display Outline Drawing. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2083Figure 2015 CAS-100 Interwiring Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2087Figure Page
MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.34-45-47Page TC-91 Dec 2003List of Tables Table PageTable Intro-1 Related Publications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .INTRO-2Table 1 TCAS System Components (Honeywell Supplied) . . . . . . . . . . . . . . . . . . . . . . . . . 4Table 2 TCAS Accessories . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14Table 3 Aircraft Equipment Required But Not Supplied By Honeywell . . . . . . . . . . . . . . . 15Table 4 CAS-100 and Aircraft Optional Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17Table 5 TPA-100A TCAS Processor Available Configurations . . . . . . . . . . . . . . . . . . . . . 19Table 6 TPA-100A TCAS Processor Features. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19Table 7 TCAS Sensitivity Level Determinations. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22Table 8 TPA-100A TCAS Processor Leading Particulars . . . . . . . . . . . . . . . . . . . . . . . . . 26Table 9 ANT-81A TCAS Directional Antenna Leading Particulars. . . . . . . . . . . . . . . . . . . 28Table 10 IVA-81A TA/VSI Leading Particulars . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30Table 11 IVA-81B RA/VSI Leading Particulars . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32Table 12 IVA-81D TA/VSI Leading Particulars. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33Table 13 ITA-81A Traffic Display Leading Particulars . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35Table 14 DO-160D Environmental Certification Categories. . . . . . . . . . . . . . . . . . . . . . . . . 36Table 15 TPA-100A TCAS Processor Inputs and Outputs . . . . . . . . . . . . . . . . . . . . . . . . . 67Table 16 IVA-81A/D TA/VSI and IVA-81B RA/VSI Inputs and Outputs . . . . . . . . . . . . . . . . 79Table 17 ITA-81A Traffic Display Inputs and Outputs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 81Table 18 CTA-81A Control Unit Controls and Indicators . . . . . . . . . . . . . . . . . . . . . . . . . . . 84Table 19 CTA-81B Control Unit Controls and Indicators . . . . . . . . . . . . . . . . . . . . . . . . . . . 91Table 20 CTA-100A Control Unit Controls and Indicators . . . . . . . . . . . . . . . . . . . . . . . . . . 99Table 21 TA/VSI RAs and Audio Messages . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 106Table 22 Range Rings Displayed vs. Selected Range . . . . . . . . . . . . . . . . . . . . . . . . . . . 110Table 1001 Mode S Line Maintenance Troubleshooting Procedure . . . . . . . . . . . . . . . . . . 1006Table 1002 TCAS Line Maintenance Troubleshooting Procedure. . . . . . . . . . . . . . . . . . . . 1007Table 1003 Unit Internal Faults . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1011Table 1004 System and Input Faults . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1015Table 1005 Program Pin Faults . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1017Table 1006 Active Unit, System, and Input Faults, and Display Status Indication . . . . . . . . 1020Table 1007 Program Pins . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1026Table 1008 Discrete Pin Numbers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1029Table 1009 Advisory Inhibit and TCAS Mode Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1031Table 2001 TPA-100A TCAS Processor Description of Aft Connector Pins . . . . . . . . . . . . 2011Table 2002 TA/VSI, RA/VSI Electrical Connector Pin Name Definitions . . . . . . . . . . . . . . . 2024Table 2003 Dedicated TCAS Traffic Display Connector Pin Name Definitions . . . . . . . . . . 2026
MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.34-45-47Page TC-101 Dec 2003Table 2004 Inspection/Check Procedure. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2036Table 2005 Upper TCAS Antenna Bearing Accuracy Chart . . . . . . . . . . . . . . . . . . . . . . . . 2047Table 2006 Lower TCAS Antenna Bearing Accuracy Chart . . . . . . . . . . . . . . . . . . . . . . . . 2048Table 2007 Input Discretes and Program Pin Information. . . . . . . . . . . . . . . . . . . . . . . . . . 2052Table 2008 IVA-81A Configuration Matrix, Software Version -01 and -03. . . . . . . . . . . . . . 2111Table 2009 IVA-81A Configuration Matrix, Software Version -02 . . . . . . . . . . . . . . . . . . . . 2113Table 2010 IVA-81A Configuration Matrix, Software Version -04 . . . . . . . . . . . . . . . . . . . . 2115Table 2011 IVA-81A Configuration Matrix, Software Version -05 . . . . . . . . . . . . . . . . . . . . 2117Table 2012 IVA-81A Configuration Matrix, Software Version -06 . . . . . . . . . . . . . . . . . . . . 2119Table 2013 IVA-81D Configuration Matrix, Software Version -02 and -04 . . . . . . . . . . . . . 2121Table 2014 IVA-81D Configuration Matrix, Software Version -03 . . . . . . . . . . . . . . . . . . . . 2123Table 2015 IVA-81D Configuration Matrix, Software Version -05 . . . . . . . . . . . . . . . . . . . . 2125Table 2016 IVA-81D Configuration Matrix, Software Version -06 . . . . . . . . . . . . . . . . . . . . 2127Table 2017 IVA-81B Configuration Matrix . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2129Table Page
Page INTRO-11 Dec 2003MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.34-45-471. Proprietary, Export, and Precautionary DataA. Proprietary Notice(1) This document and the information disclosed herein are proprietary data of Honeywell. Neither this document nor the information contained herein shall be used, reproduced, or disclosed to others without the written authorization of Honeywell, except to the extent required for installation or maintenance of the recipient’s equipment. FREEDOM OF INFORMATION ACT (5 USC 552) AND DISCLOSURE OF CONFIDENTIAL INFORMATION GENERALLY (18 USC 1905).(2) This document is being furnished in confidence by Honeywell. The information disclosed herein fall within exemption (b) (4) of 5 usc 552 and the prohibitions of 18 usc 1905. Copyright 2003 Honeywell. All Rights Reserved.(3) Honeywell is a U.S. registered trademark of Honeywell. All other marks are owned by their respective companies.B. Export Notice(1) This document contains unrestricted technical data and is being exported under license exception TSUOTS in accordance with EAR Section 740.13(a).(2) These commodities, technology, or software were exported from the United States in accordance with the export administration regulation. Diversion contrary to U.S. law is prohibited. ECCN: 7E994 Schedule B#4901.99.0050C. Special Precautions(1) Warnings, cautions, and notes in this manual give the data that follows:• A WARNING is an operation or maintenance procedure or condition that, if not obeyed, can cause injury or death.• A CAUTION is an operation or maintenance procedure or condition that, 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.(2) All personnel who operate equipment and do maintenance specified in this manual must know and obey the safety precautions. The warning and cautions that follow apply to all parts of this manual.WARNING:BEFORE YOU USE A MATERIAL, REFER TO THE MANUFACTURES’ MATERIAL SAFETY DATA SHEETS FOR SAFETY INFORMATION. SOME MATERIALS CAN BE DANGEROUS.CAUTION: MATERIALS THAT ARE NOT EQUIVALENT TO MATERIALS SPECIFIED BY HONEYWELL. MATERIALS THAT ARE NOT EQUIVALENT CAN CAUSE DAMAGE TO THE EQUIPMENT AND CAN VOID THE WARRANTY.INTRODUCTION
Page INTRO-21 Dec 2003MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.34-45-47CAUTION: THE CAS-100 COLLISION AVOIDANCE SYSTEM CONTAINS ITEMS THAT ARE ELECTROSTATIC DISCHARGE SENSITIVE (ESDS). IF YOU DO NOT OBEY THE NECESSARY CONTROLS, A FAILURE OR UNSTATISFACTORY OPERATION OF THE UNIT CAN OCCUR FROM ELECTROSTATIC DISCHARGE. USE APPROVED INDUSTRY PRECAUTIONS TO KEEP THE RISK OF DAMAGE TO A MININUM WHEN YOU TOUCH, REMOVE, OR INSERT PARTS OR ASSEMBLIES.2. Content DataA. How to Use This Manual(1) The instructions in this manual give the data necessary to do all recommended maintenance functions to put the CAS-100 Collision Avoidance System (CAS-100) in serviceable condition. Standard maintenance procedures that technicians are thought to know are not given in this manual.(2) Refer to the table of contents to see which subheadings are included in this manual. The table of contents identifies those subheadings that are not applicable or require no special instructions.(3) We recommend that the tests in TESTING AND FAULT ISOLATION be done before the unit is disassembled. These tests can tell the condition of the CAS-100 or most probable cause of any malfunction. Should any malfunction occur, repair as necessary.(4) Related publications that are referred to in this manual are identified in Table Intro-1.Table Intro-1. Related PublicationsPUBLICATION PUBLICATION No. ATA No.TPA-100A TCAS Processor,Part No. 940-0300-0200,Component Maintenance Manual012-0739-001 34-45-47CTA-100A Control Panel,Part No. 1042000,Component Maintenance Manual012-0738-001 34-45-49TPT-81A TCAS Interface Test Panel,Part No. 071-50004-8101,Component Maintenance ManualI.B.1181AT 34-45-02CTA-81A Control Unit,Part No. 071-01477-XXXX, 071-01503-XXXX,Component Maintenance ManualI.B. 1181B 34-45-10ANT-81A Directional Antenna Array,Part No. 071-50001-XXXX,Component Maintenance ManualI.B. 1181C 34-45-15
Page INTRO-31 Dec 2003MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.34-45-47Table Intro-1. Related Publications (cont)PUBLICATION PUBLICATION No. ATA No.AXT-81A TCAS Auxiliary Test Panel,Part No. 071-50012-8101,Component Maintenance ManualI.B. 1181CT 34-45-04IVA-81A Traffic Advisory/Vertical Speed Indicator, (TA/VSI), Part No. 066-50001-XXXX,Component Maintenance ManualI.B. 1181D 34-45-20IVA-81A Traffic Advisory/Vertical Speed Indicator (TA/VSI), Part No. 066-50001-XXXX, Illustrated Parts CatalogI.B. 1181D-1 34-45-21IVA-81B Resolution Advisory/Vertical Speed Indicator, Part No. 066-50002-XXXX, Component Maintenance ManualI.B. 1181E 34-45-25CTA-81B Control Unit,Part No. 071-01480-XXXX, 071-01492-XXXX,Component Maintenance ManualI.B 1181F 34-45-11ITA-81A Traffic Display,Part No. 066-50003-XXXX,Component Maintenance ManualI.B. 1181G 34-45-30CTA-81C Control Unit,Part No. 071-01515-XXXX,Component Maintenance ManualI.B. 1181J 34-45-12TRA-67 Mode S Transponder System,Maintenance ManualI.B. 1167 34-54-11TRA-67A ATC Transponder,Part No. 066-01127-XXXX,Component Maintenance ManualI.B. 1167A-1 34-56-36CNA-67A Control Unit,Part No. 071-01478-XXXX,Component Maintenance ManualI.B. 1167B 34-54-22PPI-1T Weather Radar Indicator,Part No. 2041232-XXXX,Component Maintenance ManualI.B. 1102T 34-41-22PPI-1U Weather Radar Indicator,Part No. 2041215-XXXX,Component Maintenance ManualI.B. 1101U 34-41-23PPI-4B Weather Radar Indicator with TCAS Option, Part No. 2041222-XXXX,Component Maintenance ManualI.B. 1104B-1 34-41-23
Page INTRO-41 Dec 2003MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.34-45-47Table Intro-1. Related Publications (cont)B. Verification(1) Verification of these technical instructions is done by performance or by simulation of the necessary procedures. Checks of the manual by the engineering staff make sure the instructions and description data agree with the applicable engineering specifications and drawings and are accurate and sufficient. The level of verification for this manual is shown in the list that follows.PUBLICATION PUBLICATION No. ATA No.Standard Repair Procedures for Honeywell Avionics Equipment Instruction ManualA09-1100-004Abbreviations for Use on Drawings and in Text* ASME Y14.38-1999(Formerly ASME Y1.1-1989)Graphic Symbols for Electrical and Electronics Diagrams*ANSI Y32.2 (1974)Standard Letter Symbols for Units of Measurement*ANSI/IEEE Standard (Std) 260 (1978)Graphic Symbols for Logic Functions* ANSI/IEEE STD 91 (1984)NOTES:1. You can order a Honeywell publication from Honeywell as follows: Telephone No. (425) 885-8367 Fax No. (425) 885-8722 Email: Sandra.Slick@honeywell.com2. *Available from the American National Standards Institute, New York, NYSubheading Level of VerificationTesting and Fault Isolation By performance, 1 Dec 2003
Page INTRO-51 Dec 2003MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.34-45-47C. Symbols(1) The symbols in Figure Intro-1 may be used to identify static sensitive (ESDS) and moisture sensitive devices.Figure Intro-1. SymbolsD. Weights and Measurements(1) All weights and measurements are in U.S. values and S.I. (metric values).(2) The letter symbols for units of measurement are the same as shown in the GPO Style Manual and in ANSI/IEEE Std 260.
Page INTRO-61 Dec 2003MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.34-45-47E. Acronyms and Abbreviations(1) The acronyms and abbreviations that follow help the reader identify terms and definitions used by Honeywell.(2) The letter symbols for units of measurement are the same as shown in the GPO Style Manual and in ANSI/IEEE Std 260.Term DefinitionADS-B Automatic Dependent Surveillance - BroadcastAEEC Airlines Electronic Engineering CommitteeAGL above ground levelAHRS attitude/heading reference systemANSI American National Standards InstituteARINC Aeronautical Radio, IncorporatedASME American Society of Mechanical EngineersATC Air Traffic ControlATCRBS Air Traffic Control Radar Beacon SystemATE automatic test equipmentBITE built-in-test equipmentCAS Collision Avoidance SystemCFDS centralized fault display systemCRT cathode ray tubeDME distance measuring equipmentDPSK differential phase shift keyingDTIF display traffic information fileERP effective radiated powerESDS electrostatic discharge sensitiveFAA Federal Aviation AdministrationFDR flight data recorderFPM feet per minuteGPWS ground proximity warning system
Page INTRO-71 Dec 2003MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.34-45-47Hg mercuryID identificationIEEE Institute of Electrical and Electronics EngineersI/O input/outputLBP left bottom plugLCD liquid crystal displayLED light-emitting diodeLMP left middle plugLRU line replaceable unitLTP left top plugMSL mean sea levelMTL minimum trigger levelNAR non-altitude reportingNM nautical mileNo. numberPC personal computerPPI plane position indicatorRA resolution advisoryRBP right bottom plugRF radio frequencyRMP right middle plugRTCA Radio Technical Commission for AeronauticsRTP right top plugS.I. International System of UnitsSPI special position indentifierStd standardTA traffic advisoryTA/VSI traffic advisory/vertical speed indicatorTerm Definition
Page INTRO-81 Dec 2003MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.34-45-47TCAS Traffic Alert and Collision Avoidance SystemTNC threaded N connectorTSO Technical Standing OrderVSI vertical speed indicatorVSWR voltage standing wave ratioTerm Definition
MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEM012-0680-001 Page 0 1 Dec 200334-45-47Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.CAS-100 Collision Avoidance System ComponentsFigure 1
MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEM012-0680-001 Page 00 1 Dec 200334-45-47Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.THIS PAGE LEFT BLANK
Page 1 1 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.DESCRIPTION AND OPERATION1. GeneralThis section contains data for the function and the operation of the Honeywell CAS-100 Collision Avoidance System, hereafter referred as the CAS-100, TCAS, or by its full nomenclature. The CAS-100 components are shown in Figure 1.A. Purpose of EquipmentCAS-100 is an airborne traffic alert and collision avoidance advisory system that operates without the support from Air Traffic Control (ATC) ground stations. The system senses nearby intruder aircraft equipped with transponders that reply to the Air Traffic Control Radar Beacon System (ATCRBS), Mode C, or Mode S interrogations. The danger potential of intruder aircraft to own aircraft is continuously monitored and analyzed by the Traffic Alert and Collision Avoidance System (TCAS). The nearby transponder-equipped aircraft are shown on a traffic advisory display. The TCAS system gives traffic advisory alerts and vertical maneuvering resolution advisories during danger conditions to prevent airborne collisions.NOTE: The vertical maneuvering resolution advisories given by TCAS are calculated and given against the intruder aircraft that report altitude data in their transponder messages. Traffic advisories are given for nonaltitude reporting (NAR) aircraft only.A traffic advisory display warns the flight crew to the position of nearby aircraft threats and possible threats. This warning improves the ability of the flight crew to see the intruder aircraft before answering the resolution advisory. The resolution advisories are shown around the edge of a Traffic Advisory/Vertical Speed Indicator.A Resolution Advisory/Vertical Speed Indicator displays only resolution advisories around its edge. The indicator can be used if the traffic advisories are shown on another display unit.Detection and tracking of intruder aircraft is performed by transmission and receptions from a top-mounted TCAS directional antenna. This function can also be performed with a bottom-mounted TCAS omnidirectional or bottom-mounted TCAS directional antenna.TCAS finds the aircraft that uses a Mode S transponder by listening for the Mode S squitter transmissions. Mode S transponders tell their presence by transmitting a squitter message one time for each second. TCAS also finds the aircraft equipped with transponders that do not reply to Mode S interrogations, but do reply to Mode C interrogations. TCAS must search for Mode C equipped intruder aircraft, because Mode C transponders do not transmit squitter messages. When the presence of a Mode S or Mode C intruder is made sure, TCAS starts to track the intruder. TCAS can track a total of 30 Mode S and Mode C intruders.
Page 21 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Repetitious TCAS interrogations in the Mode S and the Mode C formats monitor the aircraft positions. The transponders reply after a set interval when interrogated. The measurement of time between interrogation transmission and reply reception lets TCAS find the range of the intruder. If the intruder transponder uses an altimeter input, TCAS receives the intruder altitude reports in the replies and can find the altitude of the intruder. Transmission and reception procedures for the TCAS directional antennas let TCAS find the bearing of intruder. (If an omnidirectional antenna is used as the TCAS bottom antenna, and the intruder is monitored on the bottom antenna, the intruder bearing cannot be determined. As a result, the traffic display unit will not display the intruder aircraft position.).TCAS classifies intruders as nonthreat, proximity, traffic advisory (TA), or resolution advisory (RA) threat category aircraft. This classification is based on closing rates and relative position calculated from the reply data. TCAS gives one or more of the following visual and aural aids to the pilot:• If a directional antenna is tracking the intruder, TCAS displays an intruder aircraft symbol on the traffic advisory display. The symbol position on the display shows relative range and bearing of the intruder. The symbol shape and color identifies if the aircraft is categorized as a nonthreat, proximity, traffic advisory or resolution advisory threat. If the intruder is reporting altitude, intruder relative altitude is shown on the display.NOTE: TCAS only categorizes and displays an intruder aircraft as an RA threat if the intruder is reporting altitude. Nonaltitude reporting aircraft are referred to as NARs.• If the intruder is tracked on a bottom TCAS omni antenna and is categorized as a TA or RA, TCAS gives a TA NO BEARING or RA NO BEARING annunciation on the traffic advisory display.• If the intruder is categorized as a TA, TCAS gives an aural traffic advisory alert on the cockpit audio system.• If the intruder is categorized as a RA, TCAS gives an aural resolution advisory alert on the cockpit audio system. This RA category causes a visual vertical maneuvering resolution advisory on the vertical speed indicators (TA/VSIs or RA/VSIs).A TCAS-equipped aircraft includes a Mode S air traffic control transponder and a transponder/TCAS control unit. The Mode S transponder does the functions required by TCAS and the non-TCAS functions of existing ATCRBS (Modes A and A/C) transponders. During a condition where two TCAS equipped aircraft are threats to each other, the TCAS and Mode S transponder in each aircraft, establish an air-to-air resolution advisory coordination data link. This link is established to prevent the generation of a similar vertical maneuvering resolution advisories in the two aircraft.
Page 3 1 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.TCAS equipment operates at the same transmit and receive frequencies as ground stations (1030 MHz transmit and 1090 MHz receive). TCAS and ground stations operate at transmit and receive frequencies that are inverse to transponder transmit and receive frequencies shown below:TCAS interrogates only in Mode C and Mode S by transmitting 1030-MHz messages through the top and bottom TCAS antennas. TCAS receives 1090-MHz messages from Mode S and ATCRBS Mode A or Mode C transponders through the top directional antenna and the bottom TCAS omni or directional antenna.If TCAS receives a Mode C reply from a Mode A transponder or a Mode C transponder that is not supplied with altitude data, it will process the reply as a NAR reporting Mode C equipped aircraft.TCAS does not interrogate in Mode A. However, an aircraft equipped with a minimal transponder that replies to Mode A interrogations, will reply to Mode C interrogations with no altitude-encoded data present in the reply. TCAS tracks such aircraft in bearing and range, and will display the aircraft a nonthreat intruder, proximity intruder, or traffic advisory. However, a resolution advisory will not be generated since the correction maneuver (e.g., fly up, fly down) cannot be determined without intruder altitude data. B. Equipment Part NumbersThe required and optional TCAS equipment, including aircraft systems are:• TCAS processor (required equipment)• Top-mounted directional antenna (required equipment)• Bottom-mounted omni or directional antenna (required equipment)• Installation selectable combinations of resolution advisory (TA/VSI or RA/VSI) and traffic advisory displays [TA/VSI, plane position indicator (PPI), dedicated, etc.] (required equipment)• Mode S transponder (required equipment)• Required aircraft equipment• Optional aircraft equipment.System Transmit Frequency Receive FrequencyMode S Transponder 1090 MHz 1030 MHzMode A/C ATCRBS Transponder 1090 MHz 1030 MHzTCAS 1030 MHz 1090 MHzGround Station 1030 MHz 1090 MHz
Page 41 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 1 lists the equipment type, the Honeywell part numbers, and provides a brief description of the TPA-100A TCAS processor, directional antenna array, omnidirectional antenna, TA/VSI indicator unit, RA/VSI indicator unit, dedicated TCAS traffic display, Mode S transponder, and Mode S transponder/TCAS control units. Table 2 lists accessories for the TPA-100A processor.NOTE: Many of the units required by the CAS-100 Collision Avoidance System are part of the CAS-81 Collision Avoidance System or TRA-67 Mode S Transponder System. Currently, the only CAS-100 Collision Avoidance System units are the 4MCU and 6MCU TPA-100A TCAS Processor (The 6MCU TPA-100A TCAS Processor Unit is a direct replacement for the TPA-81A TCAS Processor Unit and the CTA-100A TCAS/Mode S Control Panel is a direct replacement for the CTA-81A Control Panel). The TPA-100A TCAS processor is examined in detail in this manual. Other TCAS equipment is examined to a level necessary for understanding total CAS-100 operation. The Mode S transponder and its control units, directional antenna, TA/VSI, RA/VSI, and dedicated TCAS traffic display are examined in detail in separate manuals recorded in Table Intro-1.Table 1. TCAS System Components (Honeywell Supplied)Equipment TypeHoneywellPart Number DescriptionTCAS Processor TPA-100A940-0300-001940-0400-001The TCAS processor is a tray-mounted ARINC 735A assembly. The processor contains the circuits that control the TCAS system and an L-band rf transmitter/receiver.The TCAS processor controls all surveillance, data acquisition, tracking, advisory, and air-to-air maneuvering coordination functions in the CAS-100 system.The TCAS processor selects directional antenna beams. The processor supplies and transfers pulsed 1030-MHz rf surveillance interrogation data to the TCAS top and bottom antennas and receives 1090-MHz rf reply data from the TCAS antennas. The TCAS processor also examines the reply data and determines the threat potential of intruder aircraft.The TCAS processor supplies ARINC 429 traffic and resolution advisory display data output to the TA/VSI, RA/VSI, and other optional display units. The processor also supplies ARINC 429 control and housekeeping data to the Mode S transponder subsystem.The TCAS processor receives ARINC 429 data that includes coordination, pressure altitude, TCAS control, own identification, and own maximum airspeed from the Mode S transponder.
Page 5 1 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 1. TCAS System Components (Honeywell Supplied) (cont) EquipmentHoneywellPart Number DescriptionTCAS Processor (cont)TPA-100A (cont) 940-0300-001940-0400-001The TCAS processor receives own-aircraft data from on-board aircraft equipment on these inputs: magnetic heading, and pitch and roll attitude on an attitude heading reference system (AHRS) 429 bus or X, Y, Z synchro inputs; radio altitude from 429 digital or analog radio altimeters; discrete inputs from the aircraft switches and straps; discrete advisory inhibit inputs from ground proximity and wind shear warning systems; discrete input from an advisory cancel switch.The TCAS processor outputs a suppression pulse to on-board L-band rf equipment and receives suppression pulses from the same L-band equipment.Voice audio advisory outputs are provided to a cockpit speaker and headphones, and discrete advisory alert outputs are provided to optional tone generators and lamps. Straps are available to select loudness for the speaker and headphones.The TCAS processor input/output (I/O) is equipped to communicate with a centralized fault display system (CFDS) or maintenance computer through a bi-directional ARINC 429 data link and gives airborne test equipment (ATE) equipment test points. ARINC 429 data can be supplied to a digital flight recorder and an ARINC 573 output port is available for a nondigital flight recording.
Page 61 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 1. TCAS System Components (Honeywell Supplied) (cont) Equipment TypeHoneywellPart Number DescriptionTCAS Processor (cont)TPA-100A (cont) 940-0300-001940-0400-001The TCAS processor monitors the failure status input from external equipment and continuously does built-in-test diagnostics. When functional test is started from the Mode S transponder/TCAS control unit, the TCAS processor does extensive system functional test diagnostics.The front panel liquid crystal display (LCD) has two controls to give the maintenance personnel the ability to check the equipment.The processor contains a front panel Personal Computer (PC) card slot where internal signal data can be recorded on a PC card or data from the PC card can be loaded into the processor. The TCAS processor receives 115 V, 360 to 800 Hz or 28 V dc primary power and 26 V ac synchro reference power from the aircraft power sources.DIRECTIONAL ANTENNAANT-81ANOTE 1.071-50001 ARINC 735A assembly screw-mounted directly to fuselage of aircraft. Contains an array of four passive, steerable, radiating elements installed at 0°, 90°, 180°, and 270° in the relation to the forward axis of the antenna. During Mode S and ATCRBS Mode C interrogation message transmissions, the directional antenna receives 1030 MHz pulses on the four cabled input from the TCAS processor.
Page 7 1 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 1. TCAS System Components (Honeywell Supplied) (cont)Equipment TypeHoneywellPart Number DescriptionDirectional Antenna (cont)ANT-81A (cont) 071-50001 During TCAS receptions, each of the four directional antenna elements accepts any 1090-MHz rf signal that is present. The phasing of these received signals is calculated by the direction that the rf energy is received. These signals are directed on the same four cables that connect transmit signals between the TCAS processor and directional antenna. The ANT-81A is a passive device and does not require input power.TCAS Omni AntennaOne TCAS Omnidirectional AntennaNOTE 2.Customer Supplied The antenna is installed directly to bottom of the aircraft. The antenna is an L-band, blade type dipole antenna. The antenna connects to the TCAS processor through an rf cable. The antenna must have a dc ground for TCAS antenna monitoring. Omni antenna must be approved to one or more of these Technical Standard Order (TSO) specifications: C66b, C74, C112, C119 TA/VSI (Traffic Advisory/Vertical Speed Indicator)IVA-81A/IVA-81DNOTE 3.IVA-81A: 066-50001IVA-81D: 066-01171Front-panel attached, solid-state display unit. High-resolution, full-color, dot matrix LCD. The unit shows the vertical speed of own aircraft, position of surrounding aircraft traffic, and vertical maneuvering RAs.
Page 81 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 1. TCAS System Components (Honeywell Supplied) (cont)Equipment TypeHoneywellPart Number DescriptionTA/VSI (Traffic Advisory/Vertical Speed Indicator) (cont)IVA-81A/IVA-81D (cont) IVA-81A: 066-50001IVA-81D: 066-01171The vertical speed display operates from pneumatic or air data electrical input. The display receives RA, traffic, and TCAS mode data on a high-speed ARINC 429 bus through the TPA-100A TCAS processor. RA command data is shown around the edge of the vertical speed scale.Built-in-test continuously monitors for a loss of primary power, internal IVA-81A/D failures, altitude rate input failures, and gives a discrete display valid status signal to the TCAS processor. The strap inputs are supplied to set the vertical speed input source and system variables. The IVA-81A/D receives 115 V, 400 Hz or 28 V dc primary power and 5 V ac or dc or 28 V dc panel lighting power from the aircraft power sources. The IVA-81A/D requires a ±12 V reference input if an ARINC 575 altitude rate input is used or a 26 V ac reference input if an ARINC 565 analog altitude rate input is used.
Page 9 1 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 1. TCAS System Components (Honeywell Supplied) (cont)Equipment TypeHoneywellPart Number DescriptionRA/VSI (Resolution Advisory/Vertical Speed Indicator)IVA-81BNOTE 4.066-50002 The indicator is a front-panel attached, electro-mechanical display unit. The unit displays vertical speed with a stationary vertical speed scale. A moving electromechanical scale displays vertical maneuvering advisories (RAs) with curved lamp segments around the edge of the vertical speed scale (does not give a display of adjacent intruder traffic). The vertical speed display operates from pneumatic or air data electrical input. The display receives RA and TCAS mode data on a high-speed ARINC 429 bus from the TPA-100A TCAS processor.Built-in-test continuously monitors for missing primary power, internal IVA-81B failures, altitude rate input failures, and supplies a discrete display valid status signal to the TCAS processor.The IVA-81B receives 115 V, 400 Hz primary power and 5 V ac or dc panel lighting power from the aircraft power sources. The IVA-81B requires a ±12 V reference input if a ARINC 575 altitude rate input is used or a 26 V ac reference input if a ARINC 565 analog altitude rate input is used.
Page 101 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 1. TCAS System Components (Honeywell Supplied) (cont)Equipment TypeHoneywellPart Number DescriptionDedicated TCAS Traffic DisplayITA-81A 066-50003 The ITA-81A is a front-panel attached cathode ray tube (CRT) TCAS display unit. The display receives the traffic and TCAS mode data on a high-speed ARINC 429 bus from the TPA-100A TCAS processor. The unit displays an aircraft symbol and range rings with TCAS traffic and mode.The ITA-81A receives 115 V 400 Hz primary power and 5 V ac panel lighting power from the aircraft power sources.TRA-67 Transponder Subsystem TRA-67A Mode STransponderNOTE 5.066-01127 The TRA-67A transponder is a tray attached ARINC 718A assembly. The transponder contains a microprocessor based Mode S/ATCRBS transponder control and processing unit. The unit also contains an L-band rf transmitter/receiver, and various synchro discrete and digital interface networks.A Mode S transponder transmits 1090-MHz Mode S or ATCRBS reply messages when it receives appropriate 1030-MHz Mode S or ATCRBS interrogations from other TCAS equipped aircraft or air traffic control ground stations. Mode S interrogations contain a unique aircraft address identification. Only the Mode S transponder assigned to that address will reply. ATCRBS interrogations do not contain a transponder address. If the transponder is connected to equipment that measures pressure altitude, the Mode S or ATCRBS Mode C reply will contain the pressure altitude.
Page 11 1 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 1. TCAS System Components (Honeywell Supplied) (cont)Equipment TypeHoneywellPart Number DescriptionTRA-67 Transponder Subsystem (cont) TRA-67A Mode S Transponder (cont)066-01127 Once for each second of time, Mode S transponders automatically transmit a squitter message that contains its aircraft address identification. These squitter messages tell other TCAS equipped aircraft and ground stations that the Mode S equipped aircraft is present.The Mode S transponder in TCAS equipped aircraft is connected to the TCAS processor with a two-direction ARINC 429 data link. Many data link communications between the TCAS processor and Mode S transponder are continuously interchanged.The CTA-81( ) Control Unit gives on-board control for manually selecting Mode S transponder and TCAS operating modes. Mode control data from the control unit is connected into the Mode S transponder and moved to the TCAS processor through ARINC 429 data links.A change to TCAS operating modes (i.e. sensitivity levels) can be requested from future Mode S ground stations through the messages received by the Mode S transponder. The Mode S transponder moves this mode control request data to the TCAS processor through the ARINC 429 data link. The TCAS processor routinely moves operating mode status data to the Mode S transponder. When a request from a ground station is made, the operating mode status data is put in(to) a message transmitted from the Mode S transponder.
Page 121 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 1. TCAS System Components (Honeywell Supplied) (cont)Equipment TypeHoneywellPart Number DescriptionTRA-67 Transponder Subsystem (cont)Through the directional TCAS antenna, all TCAS equipped aircraft at intervals transmit a message that tells other TCAS equipped aircraft that a TCAS equipped aircraft is present. The Mode S transponders receive the broadcast messages and tell the TCAS processor through the ARINC 429 data link that a broadcast message was received.The ARINC 429 data link is also used to move the maximum airspeed, pressure altitude, aircraft address identification, and TCAS coordination message data from the transponder to the TCAS processor. The TCAS processor also moves housekeeping and coordination update data to the transponder.Built-in-test equipment software continuously monitors for internal transponder failures, transponder control unit failures, transponder antenna failures, pressure altitude input failures, and ARINC 429 data failures. Detailed transponder subsystem failure status is reported to the TCAS processor through the 429 data link. A failure of the transponder or transponder control unit causes the FAIL light on the transponder control unit to come on.
Page 13 1 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 1. TCAS System Components (Honeywell Supplied) (cont)Equipment TypeHoneywellPart Number DescriptionTRA-67 Transponder Subsystem (cont)TRA-67A Mode S (cont) 066-01127 The Mode S transponder receives 115 V 400 Hz from an aircraft power source. If a synchro altitude source input is used, the transponder receives 26 V ac synchro reference power from an aircraft power source.The transponder is connected to the aircraft suppression bus.Mode S Transponder /TCAS Control Units CTA-81A CTA-81B071-01477071-01503071-01480071-01492The Mode S Transponder/TCAS Control Units are panel-mounted ARINC 718/735A assemblies. The units contain a front mounted transponder/ TCAS mode control, altitude reporting on/off control, transponder ATC identification code select controls, and a special identifier pushbutton. The unit also contains a transponder failure indicator and ATC IDENT code display.The Mode S transponder/TCAS control unit moves the control data and failure status data to the Mode S transponder. The control unit FAIL annunciator receives the failure status from the Mode S transponder through a discrete monitor signal line.The Mode S transponder/TCAS control unit receives 115 V 400 Hz and lighting power from the aircraft power sources. A separate fault lamp source is necessary and cannot be turned fully off (day/night). CTA-100A NOTE 6.1042000-101 through -499 for Keypad entry models.1042000-501 through -999 for Rotary Control entry models.The CTA-100A is designed to be a drop-in functional replacement for the Honeywell CTA-81A, 81B, 81C, and 81D controllers. The controller provides data from the front panel to the system using ARINC 429 databuses and discrete interface signals.Two Transponder Omnidirectional AntennasThe antennas are attached directly to the top and bottom of the aircraft. The units have an L-band blade type dipole antenna. The antennas are connected to the Mode S transponder through rf cables. Omni antennas must be approved to a minimum one of these TSO specifications: C66b, C74, C112, C119
Page 141 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 1. TCAS System Components (Honeywell Supplied) (cont)C. TCAS AccessoriesTable 2 lists accessories for the TPA-100A processor. Accessories for the dedicated display, directional antenna, TA/VSI, RA/VSI, and the Mode S transponder system are shown in applicable maintenance manuals. Refer to Table 5. Table 2. TCAS AccessoriesNOTES:1. One or two directional antennas can be used in a CAS-100 system. A top-mounted ANT-81A is always necessary. To find intruder bearing on bottom antenna, an ANT-81A must be installed on the bottom of the aircraft.2. Used if ANT-81A directional antenna is not used for bottom TCAS antenna.3. IVA-81A/D used if traffic displays are not provided on another display unit (i.e. PPI or TCAS dedicated traffic display unit) or if user requires RA and TA displays on the same unit.4. IVA-81B is used if pointer traffic resolution displays are given on another display unit (i.e. PPI or TCAS dedicated traffic display unit) and user does not require RA and TA displays on the same unit.5. The fundamentals of TRA-67 Mode S Transponder System operation in the CAS-100 system are shown in this manual. For more Mode S transponder and Mode S transponder control unit details, refer to TRA-67 ATC Mode S Transponder System Manual, I.B. 1167 and related Component Maintenance Manuals (refer to Table Intro-1. in the INTRODUCTION section).6. The purpose and function for the different control units are given in paragraph 7 (Controls and Indicators) in this section of this manual.Equipment TypeHoneywellPart Number DescriptionTCAS ProcessorInstallation Kit-Connector 050-50000-0501 The installation kit supplies parts for assembling the TCAS processor mounting tray connector.TCAS Processor Coax Termination Kit (requires four per directional antenna)The termination kit supplies parts for connecting the directional antenna cable to the TCAS Processor mounting tray.Cable Type:RG-214RG-393AA-5886AA-5887, FC-28AA-5888ECS-311201050-50005-0501050-50005-0502050-50005-0503050-50005-0504050-50005-0505050-50005-0506
Page 15 1 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.D. Aircraft Equipment Required But Not Supplied By HoneywellTable 3. lists aircraft equipment not supplied by Honeywell, but required for CAS-100 operation.Table 3. Aircraft Equipment Required But Not Supplied By HoneywellAircraft Equipment Description115 V 360-800 Hz or 28 V dc Power Source The primary power source for TA/VSI, RA/VSI, dedicated TCAS traffic display, and Mode S Transponder System. The primary power source for TCAS Processor (115 V 360-800 Hz or 28 V dc)26 V 400 Hz Reference Power Source Synchro reference voltage for attitude (pitch and roll) and heading gyros.5 V ac or dc or 28 V dc Lighting Bus Panel lighting power source for TA/VSI, RA/VSI, and dedicated TCAS traffic display.5 V ac or 28 V dc Power Source (separate) Fault lamp power for Mode S transponder/TCAS control unit.ARINC 429 Attitude/Heading Reference System (digital)Supplies the aircraft pitch, roll, and heading on an ARINC 429 digital input to the TCAS processor.ORMagnetic Compass Unit, Pitch Gyro, and Roll Gyro (synchro)Supplies the aircraft heading, pitch, and roll on three isolated 3-wire, synchro input to the TCAS processor for each ARINC 407.Radio Altimeter, digital type (one or two) Supplies the aircraft altitude on an ARINC 429 digital input to the TCAS processor.ORRadio Altimeter, analog type (one or two) Supplies the aircraft radio altitude on a 2-wire, dc analog input to the TCAS processor (see Figure 2015 in the MAINTENANCE PRACTICES section for all types of altimeters that may be connected).
Page 161 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 3. Aircraft Equipment Required But Not Supplied By Honeywell (cont)Aircraft Equipment DescriptionAircraft Switches Landing Gear Switch Supplies the aircraft landing gear extended or retracted discrete status input to the TCAS processor.Air/Ground Switch Supplies the aircraft on-the-ground/ in-flight discrete status input to the TCAS processor.Suppression Bus Supplies mutual suppression of L-bandequipment on the aircraft including the TCAS processor bi-directional bus.Static Input Source (pneumatic) Supplies the aircraft static pressure source input to the TA/VSI or RA/VSI.ORAltitude Rate Source (electrical) Supplies the aircraft altitude rate on an electrical ARINC 429, ARINC 565, or ARINC 575 input to the TA/VSI or RA/VSI.Pressure Altimeter Source Supplies the aircraft pressure altitude input to the Mode S transponder. Refer to the applicable Mode S transponder system maintenance manual for the types of pressure altimeters that can be used with the Mode S transponder.Cockpit Speaker Audio speaker, 8 ohms, 4 watts nominal. Annunciates voice advisory messages from the voice synthesizer in TPA-81A TCAS processor.Miscellaneous Installation Hardware Assembly brackets, wire, cables, nuts, bolts, screws, and etc.
Page 17 1 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.E. Aircraft Optional (Nonessential) EquipmentTable 4 lists TCAS and aircraft equipment that is optional for each user specification.Table 4. CAS-100 and Aircraft Optional EquipmentOptionalAircraft Equipment DescriptionCockpit Headphones Augments cockpit speaker by providing headset annunciations for verbal advisory alert messages from the voice synthesizer in TPA-100A TCAS Processor.External Tone Generator and/or Warning Indicator LampsSupply more visual and audible tone annunciations for advisory alerts from TPA-100A TCAS Processor.Advisory Cancel Switch Lets flight crew to cancel verbal advisory alerts on the cockpit speaker, cockpit headphones, tone generators, and alert lamps.PPI Modified to Provide TCAS Traffic Displays NOTESupplies isolated or total displays of weather/map data and TCAS traffic data. The display modes are selectable from the changed PPI control panel.ARINC 429 (Digital) orARINC 573 (Non Digital) Flight Recorder Records TCAS data. The digital data is received on a low-speed ARINC 429 data bus from the TPA-100A TCAS Processor. The nondigital data is received as ARINC 573 parallel data from the TPA-100A TCAS Processor.ARINC 429 CFDS or Maintenance ComputerProvides and receives the test diagnostic data on a low-speed ARINC 429 bus into the TPA-100A TCAS Processor and shows fault analysis data received on a low-speed ARINC 429 bus from the TPA-100A TCAS Processor.Data Recorder PCMCIA card to monitor the internal signals.
Page 181 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 4. CAS-100 and Aircraft Optional Equipment (cont)F. Related PublicationsTable Intro-1. lists related publications including the subsystems and units comprising the CAS-100 Collision Avoidance System and test equipment supporting the system.2. System ConfigurationsA. SystemThe total CAS-100 system configuration is dependent on the equipment available in the applicable aircraft.The following text gives the available configurations and features for the TCAS processor.NOTE: Available configurations and features for the Mode S transponder and the control units, are shown in isolated manuals (refer to Related Publications, Table Intro-1.).OptionalAircraft Equipment DescriptionPerformance Management ComputerSupplies the aircraft climb rate performance limit discrete input to the TPA-100A TCAS Processor.Wind Shear System and/orGround Proximity System Supplies the TCAS advisory inhibit discrete input to the TPA-100A TCAS Processor during wind shear or ground proximity alarm conditions.ARINC 615 Data Loader (airborne or portable)Reprograms the TCAS processor program memory without requiring physical access to the unit. Programming is done through ARINC 429 input and output ports on the TCAS processor rear connector or a dedicated data loader connector on the front panel. The data loading can be done at the low-speed or high-speed ARINC 429 data transfer rate. A data loader adapter cable (Honeywell Part No. 300-80179-0501) is supplied to connect a portable data loader to the TCAS processor front panel connector.NOTE: PPI display shows independently or total radar and TCAS traffic on the same display.
Page 19 1 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.B. TPA-100A TCAS ProcessorTable 5 lists the available configurations of the TCAS processor and the related features. Table 6 contains or references a short description of the processor features that are not self-explanatory.Table 5. TPA-100A TCAS Processor, Available ConfigurationsTable 6. TPA-100A TCAS Processor Features3. System Leading ParticularsA. TCAS Surveillance VolumesSurveillance volume is that volume of airspace for other aircraft with Mode S or ATCRBS transponders that are tracked by own aircraft TCAS.(1) Range Tracking VolumesThe shape and size of the range tracking volume depends on:• If Mode S or ATCRBS transponders are being interrogated• If tracking is occurring on a directional or OMNI antenna • The attenuation levels applied to the transmitted pulses from the TCAS processor's transmitter.NOTE: The TCAS processor decreases range tracking volumes in high density areas to decrease the number of receptions to be processed by TCAS and for interference limiting.PartNumbers940-0300 and940-0400FeaturesBasicUnit-001 XFeature DescriptionBasic Unit Supplies primary function and control for CAS-100. Long range active surveillance.Passive (ADS-B) only surveillance.DTIF (Strap selectable).ARINC 615-3 DL.PCMCIA.Front panel LCD maintenance interface.4 or 6 MCU.
Page 201 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.(2) Altitude Tracking VolumesTCAS tracks other transponder equipped aircraft that are in a relative altitude range of ±10,000 feet. NOTE: The display altitude volumes are different from the internal tracking volumes. The typical display volumes are ±8700 feet.B. TCAS Sensitivity Level - Operating ModesTCAS logic separates the adjacent airspace into the altitude layers as shown in Figure 2. A different sensitivity limit level for issuing RAs and TAs is applied to each altitude layer. Lower altitudes have less sensitive RA and TA limit levels to prevent unwanted advisories in the higher traffic densities anticipated at lower flight levels, i.e. terminal areas.The following TCAS sensitivity level, resolution advisory, and traffic advisory specifications data is given as an aid to help the reader understand basic TCAS operation. The data in this manual can be superseded by the data in the Minimum Operational Performance Standards document and the latest Honeywell software documentation.
Page 21 1 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.CAS-100 Sensitivity Level Altitude LayersFigure 2
Page 221 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 7 gives data related to sensitivity level determinations and Figure 3 gives data related to the conditions for resolution and traffic advisory limits compared to sensitivity levels. This data is used as a reference during this manualTable 7. TCAS Sensitivity Level DeterminationsMode DescriptionSensitivityLevel 0Sensitivity level is set in automatic mode by the altitude or by the ground command. Sensitivity level 0 is set manually when the control unit function switch is in the TA/RA mode position (in-flight). This selection sets all TCAS surveillance, tracking, and resolution advisory functions.SensitivityLevel 1 TCAS stops all surveillance, tracking, and resolution advisory functions in sensitivity level 1. The traffic advisory display is blanked, but for a STANDBY mode annunciation. The conditions for sensitivity level 1 are any one of the following:(1) CTA-100A or KFS-578A Control Unit function switch is set to TEST, STBY, ALT OFF, or ALT ON.(2) CTA-100A Control Unit function switch is set to ATC 1 TEST, ATC 1 STBY, ATC 1 ON, or any ATC 2 position, or ALT SOURCE switch set to OFF position.(3) TCAS is in STANDBY mode or TEST mode.(4) TCAS has failed. SensitivityLevel 2 TCAS does surveillance and tracking functions in sensitivity level 2. TCAS gives traffic advisories only. The conditions for sensitivity level 2 are any one of the following:(1) Own aircraft is in-flight and TA or TA/RA is below 1000 feet above ground level (AGL).(2) Own aircraft is in-flight and transponder/TCAS control unit is set to TA.(3) Own aircraft is on the ground and transponder/TCAS control unit is set to TA or TA/RA.
Page 23 1 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 7. TCAS Sensitivity Level Determinations (cont)Mode DescriptionSensitivityLevel 3, 4,5, 6, and 7TCAS does surveillance and tracking functions in sensitivity levels 3 through 7. TCAS gives resolution and traffic advisories in these levels. NOTEThe conditions for sensitivity level 3 through 7 are from own aircraft altitude as follows:(1) Sensitivity level 3 - Own aircraft altitude is between 1,000 and 2,350 feet AGL (radio altitude).(2) Sensitivity level 4 - Own aircraft altitude is between 2,350 feet AGL and 5,000 feet mean sea level (MSL) (pressure altitude).(3) Sensitivity level 5 - Own aircraft altitude is not higher than 10,000 feet MSL. (4) Sensitivity level 6 - Own aircraft altitude is 10,000 to 20,000 feet MSL.(5) Sensitivity level 7 - Own aircraft altitude is above 20,000 feet MSL.NOTE: The transponder TCAS control panel must be set to the TA/RA mode for sensitivity levels 3 through 7.
Page 241 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Typical Resolution Advisory and Traffic Advisory Volumes for Sensitivity LevelsFigure 3 (Sheet 1 of 2)
Page 25 1 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.These two conditions cause a Traffic Advisories (TAs) problem:1. TCAS calculates that at the current closure rate and distance, the time separating own aircraft and intruder aircraft is less than TA Alarm TimeANDthe altitude difference between own aircraft and intruder aircraft is less than the TA Relative Altitude Threshold.2. The separation in slant range between own aircraft and intruder aircraft is less than minimum TA Protection Volume. These two conditions cause Resolution Advisories (RAs) to be issued:1. TCAS calculates that at the current closure rate and distance, the time separating own aircraft and intruder aircraft is less than RA Alarm Time.ANDthe altitude difference between own aircraft and intruder aircraft is less than the RA Relative Altitude Threshold.2. The separation in slant range between own aircraft and intruder aircraft is less than minimum RA Protection Volume. Determining if the Resolution Advisory is Corrective or Preventive: The resolution advisory is corrective if the altitude difference between own aircraft and the intruder aircraft is less than the Corrective RA Relative Altitude Threshold.Typical Resolution Advisory and Traffic Advisory Volumes for Sensitivity LevelsFigure 3 (Sheet 2 of 2)
Page 261 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.C. Component Leading Particulars(1) Leading ParticularsLeading particulars for the TPA-100A TCAS Processor are given in Table 8. Leading particulars for the ANT-81A Directional Antenna are given in Table 9. Leading particulars for the IVA-81A TA/VSI are given in Table 10. Leading particulars for the IVA-81B RA/VSI are given in Table 11. Leading particulars for the IVA-81D TA/VSI are given in Table 12. Leading particulars for the ITA-81A Traffic Display are given in Table 13. Leading particulars for the Mode S transponder components are given in TRA-67 Mode S ATC Transponder System Maintenance Manual I.B. 1167.Table 8. TPA-100A TCAS Processor, Leading ParticularsCharacteristic DescriptionTSO C-119bForm Factor 4 or 6 MCU, ARINC Specification 600Weight (Approximate) 14 lb (6.3 kg) Overall Dimensions See Outline Drawing, Figure 2006 in the MAINTENANCE PRACTICES section of this manual.Power Requirements 115 V, 400 Hz, 110 watts and 26 V ac synchro reference power per ARINC 413A28 V dc 160 Watts Cooling ARINC Specification 600. Forced air cooling is optional.Temperature Range Operating -55C to +70C Storage -55C to +85C TransmitterFrequency 1030.00 ± 0.01MHzRadio Frequency (RF) Peak Output Power at Rear Connector54.0 ± 2 dBmInterrogation Repetition Interval 1 secondPulse Width, Rise and Fall Times DO-185AReceiverFrequency 1087 to 1093 MHz Minimum Trigger Level (MTL) For Standard ACAS -74 dBm ± 2 dBm at Antenna For Extended Performance -84 dBm ± 2 dBm at Antenna
Page 27 1 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 8. TPA-100A TCAS Processor Leading Particulars (cont)Characteristic Description Receiver (cont)Dynamic Minimum TriggerLevel (DMTL) ThresholdATCRBS MTL + 13 dBMinimum Pulse Width 300 nsecMaximum Pulse Rise Time 0.5 µsecDelay Difference (between top and bottom antenna channels, including transmission lines) 0.050 µsec General Requirements:Surveillance Volume Range Tracking VolumesThe shape and dimension of the range tracking volume is dependent on:• the Mode S or ATCRBS transponders are being interrogated• tracking is occurring on a directional or omni antenna• attenuation levels applied to the transmitted pulses from the TCAS processor transmitter. NOTE Altitude Tracking Volumes TCAS II tracks other transponder-equipped aircraft that are in a relative range of ± 10,000 feet. Surveillance Capacity Minimum of 60 tracks. The 30 closest intruders go to Collision Avoidance Algorithms. Processor Mode S Address Capacity Minimum of 150 addresses of defected Mode S equipped aircraft. System Delay Resolution advisory within 1.5 seconds after threat intruder is detected.Voice Synthesizer Output Power (speaker)4 Watts into 8 ohms (pin programmable to lower output) Phone Output 40 mW into 600 ohms (pin programmable to lower output)NOTE: The TCAS processor reduces range tracking in high density areas to reduce the number of receptions to be processed by TCAS and for interference limiting.
Page 281 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 9. ANT-81A TCAS Directional Antenna Leading Particulars Characteristic Description Form Factor ARINC 735A (teardrop shape)Antenna Base Types Curved base (071-50001-8104)Flat base (071-50001-8102, -8103)Temperature RangeOperating -55C to +70CStorage -55C to +85CMaximum Weight 2.0 lb (0.91 kg)Overall Dimensions See Outline Drawings, Figures 2007 thru 2009.Antenna Mounting Footprint See Figure 2010.Antenna Mounting Mounts directly to aircraft using mounting screws defined in Figures 2007 thru 2009. An antenna adapter (Figure 2010) is available for mounting flat-base antenna on a curved surface.Exterior Material High-strength compositeNumber of Antenna Array Elements FourPolarization VerticalPower Requirements NoneTransmission Frequency 1030 ±1 MHzReceiving Frequency 1090 ±3 MHzConnectorsQuantity FourType See Outline Drawings, Figures 2007 thru 2009.Pressurization Withstands a pressure differential of 25 P.S.I.A.Lightning Protection Meets swept zone 2A lightning strike requirements.
Page 29 1 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 9. ANT-81A TCAS Directional Antenna Leading Particulars (cont)Characteristic DescriptionMain Beam CharacteristicsOperational Beam Positions 4Half Power Azimuth Beam Width (measured over -15 to +20 elevation)≥ 90°Steering Quantization 90°Omni Beam CharacteristicsOperational Beam Positions 360°Beam Null Compared to Main Beam (at each elevation from -15 to +20)≥ 9 dBInput Port VSWR 1.5:1 maximumAntenna Cable Loss Requirement 2.5 ± 0.5 dB at 1030 MHz for each coaxial cable including connectors.Antenna Cable Differential Phase Delay One-half wavelength maximum (approximately 5 inches)Maximum Peak Input Power 1000W pulsedMaximum Average Input Power 10W continuousARINC Characteristic ARINC 735ATSO C119a (C119b for change 7 units)Environmental Certification In addition to environmental requirements defined in Table 14, an altitude immersion environmental requirement requires that the antenna not outgas at an altitude of 55,000 feet when submersed in water for 30 minutes.
Page 301 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 10. IVA-81A TA/VSI Leading ParticularsCharacteristic DescriptionForm Factor 3ATI x 7.5 inches deepComponents Solid state, no mechanical partsMaximum Weight 2.75 lb (1.25 kg)Overall Dimensions See Outline Drawing, Figure 2011.Mounting Front, panel mountPower Requirements 115 V, 400 Hz, 28 Watts (maximum), or 28 V dc primary power±12 V dc reference power if altitude rate source input is ARINC 575 analog26 V ac reference power if altitude rate source input is ARINC 565 analog5 V ac or dc or 28 V dc lighting powerOperating Temperature Range -15C to +70CNumber of Intruder Aircraft Displayed Determined by TCAS processor TA/RA display symbols maximum program strap configuration.Display High resolution, full color dot matrix LCD. Combination vertical speed, RA, and traffic display.Vertical Speed Input The IVA-81A meets the requirements of both type B and type C VSI indicators. Pneumatic or air data electrical input. Both ARINC 500 and 700 series air data input accepted.Inputs from TCAS High-speed ARINC 429Front-Mounted Range Control OptionalFront-Mounted TA SEL Switch and BRT ControlOptional
Page 31 1 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 10. IVA-81A TA/VSI Leading Particulars (cont)Characteristic DescriptionPneumatic Connector (located on indicator rear panel)See Outline Drawing, Figure 2011.Electrical Connector (located on indicator rear panel)See Outline Drawing, Figure 2011.TSO C119a, C8cEnvironmental Certification Refer to Table 14.
Page 321 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 11. IVA-81B RA/VSI Leading ParticularsCharacteristic DescriptionForm Factor 3ATI x 7.5 inches deepComponents Electromechanical and solid stateMaximum Weight 2.9 lb (1.3 kg)Overall Dimensions See Outline Drawing, Figure 2012.Mounting Front, panel mountPower Requirements 115 V 400 Hz, 20 watts primary power±12 V dc reference power if altitude rate source input is ARINC 575 analog26 V ac reference power if altitude rate source is ARINC 565 analog5 V ac or dc lighting powerOperating Temperature Range -15C to +70CDisplay Lamps around the periphery of a fixed vertical speed scale and electro-mechanical needle. Combination vertical speed and RA display.Vertical Speed Input The IVA-81B meets the requirements of both type B and type C VSI indicators. Pneumatic or air data electrical input.Inputs from TCAS High-speed ARINC 429Pneumatic Connector See Outline Drawing, Figure 2012.Electrical Connector See Outline Drawing, Figure 2012.TSO C119a, C8cEnvironmental Certification Refer to Table 14.
Page 33 1 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 12. IVA-81D TA/VSI Leading ParticularsCharacteristic DescriptionForm Factor 3ATI x 7.5 inches deepComponents Solid state, no mechanical partsMaximum Weight 3.0 lb (1.4 kg)Overall Dimensions See Outline Drawing, Figure 2013.Mounting Front, panel mount; Marmon clamp or equivalentSoftware Certification D0-178B, Level BPower RequirementsPrimary 115 V, 400 Hz or 28 V dc primary power. Maximum power dissipation of 40 Watts (short term at cold temperature), at full brightness including display warm-up at low temperature.Lighting 5 V ac or dc, or 28 V dcReference ±12 V dc if altitude rate source input is ARINC 575 analog26 V ac if altitude rate source is ARINC 565 analogOperating Temperature Range -20C to +70CNumber of Intruder Aircraft Displayed Maximum number determined by TCAS processor program strap configuration.Display High resolution, full color dot matrix LCD. Combination vertical speed and traffic display.Vertical Speed Input The IVA-81D meets the requirements of both type B and type C VSI indicators. Pneumatic or air data electrical input. Both ARINC 500 and 700 series air data input accepted.
Page 341 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 12. IVA-81D TA/VSI Leading Particulars (cont)Characteristic DescriptionData Input High-speed ARINC 429Front-mounted Range Control OptionalFront-mounted TA SEL Switch and BRT Con-trolOptionalPneumatic Connector (located on indicator rear panel)See Outline Drawing, Figure 2013.Electrical Connector (located on indicator rear panel)See Outline Drawing, Figure 2013.TSO C118, C119b, C8dEnvironmental Certification Refer to Table 14.
Page 35 1 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 13. ITA-81A Traffic Display Leading ParticularsCharacteristic DescriptionMaximum Weight 8 lb (3.7 kg)Overall Dimensions See Outline Drawing, Figure 2014.Mounting Dzus MountingPower Input Requirements 115 V, 400 Hz, 35 W nominalOperating Temperature Range -15C to +55CCooling Convection (forced-air cooling not required)Type of Display Rectangular CRT, X-Y scanScan Rate 65 HzInputs from TCAS High-speed ARINC 429Display Enable (grounded input enables unit’s power supply)Output to TCAS Display Valid (ground = valid, open = failure)Electrical Connector MS-3120E-14-19P (ITT Cannon KPT02-14-19P)Environmental Certification Refer to Table 14.
Page 361 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.(2) Environmental CertificationCAS-100 equipment meets the environmental conditions of the Radio Technical Commission for Aeronautics document number DO-160D, Environmental Conditions and Test Procedures for Airline Electronic/Electrical Equipment and Instruments. Environmental certification categories for CAS-100 equipment are defined in Table 14.Table 14. DO-160D Environmental Certification CategoriesCertificationCategory: A2F2Y B B B H2U E X X X X X Z BZ A Z C WWW M A3C3 X A ACategory InterpretationDO-160DSectionNumber Category Description 4 A2F2Y Temperature and Altitude Y=300 Min. without forced air cooling 5 B Temperature Variation 6 B Humidity7B Shock 8H2 Vibration 9 E Explosion Proofness 10 X Waterproofness X= Not Applicable11 X Fluids Susceptibility12 X Sand and Dust13 X Fungus Resistance14 X Salt Spray15 Z Magnetic Effect16 AB Power Input17 A Voltage Spikes18 Z Audio Frequency Conducted Susceptibility, Power Inputs19 C Induced Signal Susceptibility20 WWW RF Susceptibility21 M Spurious RF Emission22 A3C3 Lightning Induced Transients Susceptibility23 X Lightning Direct Effect24 A Icing25 A Electrostatic Discharge
Page 37 1 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4. System DescriptionA. GeneralThe Honeywell TCAS system includes the following equipment:• TPA-100A TCAS Processor• ANT-81A Directional Antenna• IVA-81A/D Traffic Advisory/Vertical Speed Indicator (TA/VSI)• IVA-81B Resolution Advisory/Vertical Speed Indicator (RA/VSI)• Omnidirectional Antenna• Mode S Transponder System which includes a Mode S transponder, transponder/TCAS control unit, and two omnidirectional antennas• Optional PPI or dedicated TCAS traffic display unit, required aircraft equipment, and optional aircraft equipment.NOTE: The TPA-100A TCAS Processor is examined in this manual. Other TCAS equipment is examined to a level necessary for understanding total TCAS operation. Mode S Transponder System components are included in separate manuals recorded in Table Intro-1. B. CAS-100 Functional OverviewThe basic CAS-100 system does traffic alert and collision avoidance functions to give safe separation between own aircraft and other aircraft equipped with Mode S transponders, ATCRBS Mode C transponders, or ATCRBS Mode A/C transponders.NOTE: Mode A/C transponders are Mode A transponders that respond to Mode C interrogations. CAS-100 operation can be separated into the these primary functions:(1) Surveillance Function• Detects the presence of Mode S or ATCRBS Mode A/C transponder equipped aircraft that are in TCAS surveillance limits.• Determines initial range, relative bearing (if detection occurs on a directional antenna), and relative altitude (if aircraft is reporting altitude).• Calculates closing range rate.• Determines if the aircraft should be put in track.
Page 381 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.(2) Tracking Function• Tracks maximum 45 combined Mode S and Mode A/C transponder equipped intruder aircraft. Tracks range of intruder aircraft. Tracks intruder relative bearing if tracking is occurring on a directional antenna. Tracks intruder relative altitude if intruder is reporting altitude.• Calculates estimated intruder relative position.• Calculates closing range rate.• Calculates altitude change rate if intruder is reporting altitude.• Estimates miss distance.NOTE: Surveillance and tracking functions are performed by listening for Mode S squitters, Mode S and ATCRBS Mode C interrogation transmissions, and Mode S and ATCRBS Mode C reply receptions on the top and bottom TCAS antennas.(3) Threat Potential Evaluation Function• Determines the threat potential of intruder aircraft based on results using tracking data.• Categorizes intruders as RAs, TAs, proximities, or nonthreats.(4) Collision Avoidance Computation and Resolution Advisory Display Function When an RA threat aircraft is present, TCAS finds the applicable vertical maneuvering for own aircraft to get or keep a safe miss distance between own aircraft and intruder aircraft. This maneuvering is done while creating the least change from own aircraft vertical rate. TCAS communicates the recommended maneuver to the pilot with a resolution advisory display on the TA/VSI or RA/VSI units.(5) Traffic Advisory Display FunctionGives a display of RA, TA, proximity, or nonthreat category traffic that are present in the adjacent airspace. The traffic display shows the position and the threat potential of intruder aircraft which alerts the flight crew to potentially dangerous conditions. Depending on the aircraft equipment, the traffic display can come into view on a TA/VSI unit or an optional PPI or dedicated TCAS display unit.(6) Aural Alert FunctionGives voice message advisory alerts on the cockpit audio system.
Page 39 1 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.(7) Air-to-Air Coordination FunctionA maneuvering coordination data link is established with the intruder if the intruder aircraft is TCAS equipped and becomes a threat . This data link makes sure that the resolution advisories in the two TCAS equipped aircraft are controlled and compatible. The control links are established between the two TCAS systems through the Mode S transponder.(8) Data Recording FunctionTCAS history data is at intervals moved from the processor to the recorder if the optional data recorder is attached to the PCMCIA card interface on the TCAS processor.(9) Data Loader FunctionA TCAS processor with the data loader function can receive a software update without opening the unit if an ARINC 615-3 data loader is connected. Also, there is an option to load data through a PCMCIA card put into the PCMCIA card interface slot on the front of the processor.5. System Component Description and FunctionsA. TCAS Processor(1) GeneralThe TPA-100A TCAS processor is the primary control unit in the CAS-100 system. The processor has a combined computerized control system and L-band receiver/transmitter. The operation of the TCAS system is controlled by TCAS software in the computer control memory.(2) TCAS Processor Description and Basic Functions (See Figure 4.) The TCAS processor routinely reads and keeps the following own aircraft data:(a) Own aircraft heading, pitch, roll, and radio altimeter input. This data with the pressure altitude data lets TCAS find own aircraft position and flight path. The data is used during tracking, RA and TA advisory, and traffic display computations.(b) Own aircraft pressure altitude data received on the ARINC 429 data bus from the Mode S transponder. The pressure altitude is input to the transponder from own aircraft pressure altitude source. The pressure altitude is used to find own aircraft altitude related to intruder reported altitude and own aircraft flight level altitudes.(c) The mode control requests and traffic display control inputs from the Mode S transponder through the ARINC 429 data bus. The Mode S transponder receives this data from the transponder control panel (and may in the future also receive the control input from the ground stations). This data is a factor in TCAS sensitivity level determinations and traffic display formats.
Page 401 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.(d) Own aircraft identification (ID) code (transponder ID) received on the ARINC 429 data bus from own Mode S transponder. Own aircraft identification is input to the transponder through 24 discrete bit strapped inputs. Own aircraft identification is used by the TCAS processor during air-to-air coordination procedures.(e) Own aircraft maximum airspeed data received on the ARINC 429 data bus from own Mode S transponder. Own aircraft maximum airspeed is input to the transponder through three discrete bit strapped inputs. This data is used in the maximum closing rate projections and RA computations.(f) Antenna delay strap input. These 3 discrete input are used during TCAS range computations to adjust for the cable delay differences between the top and the bottom antennas.(g) Performance limit input. These inputs are used as factors in RA computations. The performance limit inputs include:1Performance limit discrete input or ARINC 429 input from performance management computer.2Five discrete altitude limit program strap inputs (2000, 4000, 8000, 16000, and 32000).3Four discrete 1500 fpm Climb Inhibit inputs which are configured by the user to limit the RAs to performance functions of the aircraft. (Example: Wing flap retracted/extended switch can be connected to these input or the Increased Climb Inhibit input depending on the properties of the aircraft.)4Four discrete 2500 fpm Increased Climb Inhibit input which are configured by the user to limit RAs to performance functions of aircraft.NOTE: Although not specifically a part of performance limits, the discrete input from the landing gear retracted/extended switch can be for performance limit input shown in paragraphs 4 and 5 above. But, this input is for other functions, for example making a bottom directional antenna operate as an omni antenna in gear-down conditions.(h) Discrete input from weight-on-gear (Air-Ground) strut switch. Tells TCAS if own aircraft is in-flight or on-the-ground.(i) Advisory Delay discrete input from ground proximity and wind shear system (if applicable).(j) Discrete input from optional Advisory Cancel switch.
MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEM1 Dec 200334-45-47Collision Avoidance System Simplified Block DiagramFigure 4Page 41/42Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 431 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.(k) Five discrete input from RA/TA Intruder Display Limit straps. These straps determine the maximum number of aircraft that can be shown on the traffic display (from 1 to 30).(l) Discrete input from Ground Display Mode strap. This input determines if the traffic is shown when own aircraft is on-the-ground.(m) Discrete input from RA/TA Display All Traffic Mode strap. This input determines if all targets are shown at all times or when an RA or TA is present.(n) Continuity/resistance checks on the top and bottom TCAS antenna ports. This data lets the TCAS processor find if an omni or directional antenna is used as the bottom TCAS antenna. The data also lets the processor find if the antenna cables are correctly connected to the top and the bottom antennas. The four ports for each directional antenna must reflect special and different resistance values because of port identification resistors attached in the directional antenna.(o) System validity inputs. If a failure is found on any of the following input, TCAS supplies the failure annunciation data to the resolution advisory and traffic displays.1Discrete failure status input from the TA/VSI units, RA/VSI units, or other optional display units.NOTE: In the event of a display unit failure, the display sets its display valid output discrete to invalid and tries to show status of the fault found. The fault is shown if the properties of the fault allow (for example, specific faults cause a blank display and do not allow the display of data).NOTE: Loss of a TA/VSI will be reported on the maintenance bus.NOTE: The TCAS processor will automatically go into the standby mode if both radio altimeters, both RA/VSI units, or both TA/VSI units fail.2Loss of continuity through the TCAS antennas.3Failure status data or loss of data on the ARINC 429 data link from the Mode S transponder.4Internal TCAS processor failures that include failure of internal power supplies.5Incorrect data from the radio altimeter if one is connected, or incorrect data from both radio altimeters if two are connected.(p) The TCAS processor stops all TCAS processing and shows an applicable annunciation on the display units if a particular failure decreases the TCAS operation. TCAS processor self-tests and failure annunciations are given in the MAINTENANCE PRACTICES and FAULT ISOLATION sections of this manual.
Page 441 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.(q) Six discrete input from synthesized Audio Level Control straps. Three of these straps determine the audio output levels to the speaker and phones when the aircraft is airborne. The other three straps determine the audio output levels when the aircraft is on the ground.(r) Discrete input from Functional Test Inhibit Strap. This input determines if the TCAS functional test is inhibited when the aircraft is airborne.(s) Discrete input from Transponder Interface Select Strap. This input shows if one or two transponders are installed on the aircraft.(t) Discrete input from Radio Altimeter Interface Select Strap. This input shows if one or two radio altimeters are installed.(u) Discrete input from RA Status Inhibit Strap. This input determines if RA display status is in operation or prevented.(v) Discrete input from On-Ground Intruder Disable Strap. This input determines if intruders found to be ON GROUND will be shown when own aircraft is below 1750 feet (radio altitude).(3) Real-Time TCAS Functions Controlled by Processor(a) The TCAS processor formats and transmits the messages and listens for broadcasts. Messages are transmitted at 1030 MHz by each TCAS system to tell other TCAS equipped aircraft that own TCAS equipped aircraft is present. The messages are transmitted on the TCAS directional and omni antennas. Each TCAS, including own TCAS, keeps track of the number of broadcast messages received by its Mode S transponder. This supplies each TCAS with the number of TCAS equipped aircraft in broadcast range. This number is used in TCAS interference limiting formulas, which is for controlling the power output levels and rates for TCAS Mode S interrogations. TCAS decreases the number of TCAS Mode S interrogations and also decreases the power output levels as the number of TCAS equipped aircraft (number of broadcast receptions) increases. This decreases the detectable interrogation load on Mode S transponders in the conditions where numerous TCAS equipped aircraft are present in the same airspace volume. The effect of reducing the number of air-to-air interrogations and their transmit power levels is a decrease of unsolicited replies (fruit overload) received by the ground stations.(b) The TCAS processor listens for Mode S transponder squitter messages from other aircraft. The Mode S transponders show their presence by transmitting a 1090 MHz squitter message once each second. The TCAS processor listens for squitters on the TCAS directional and omni antennas.
Page 451 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.(c) The TCAS processor starts to interrogate the intruder if a correct Mode S squitter message is sensed. The Mode S equipped intruder is put into the track if an interrogated Mode S equipped aircraft is in TCAS Mode S tracking range and altitude. The mode S track changes are then done. These changes include the TCAS processor formatting and transmitting 1030 MHz Mode S interrogation messages on the directional antenna and/or the omni antenna. The processor also receives 1090 MHz Mode S reply messages on the directional antenna and/or the omni antenna. The TCAS processor sets one directional antenna beam to use for directional message transmission and reception.(d) The TCAS processor does ATCRBS search, track initialization, and track changes. The ATCRBS equipped intruder is put into the track if an ATCRBS equipped aircraft is in TCAS ATCRBS tracking range and altitude. ATCRBS search, track initialization, and track update operations include the TCAS processor formatting and then transmitting 1030 MHz ATCRBS interrogations, and receiving 1090 MHz ATCRBS replies on the directional antenna and/or the omni antenna. The TCAS processor sets one directional antenna beam to use for ATCRBS directional message transmission and reception. NOTE: Mode S and ATCRBS interrogation and reply message formats are shown in Figures 5 and 6.(e) The TCAS processor does functions that find the range, bearing, and altitude of intruder aircraft from the data calculated from or contained in the reply messages. The bearing can be found for the intruder replies received on the directional antenna. The altitude can be found if the intruder is reporting altitude in its transponder reply message.(f) Based on the data extracted or calculated from the reply, the TCAS processor examines the threat potential of the intruder by calculating the intruder closing rate and position related to own aircraft. From this analysis, the TCAS processor categorizes the intruder as a nonthreat, proximity, traffic advisory, or resolution advisory.
Page 461 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.ATCRBS Mode C and Mode S Interrogation FormatsFigure 5
Page 471 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.ATCRBS/Mode S Transponder Reply Message FormatsFigure 6
Page 481 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.(g) The TCAS processor calculates the correct resolution advisory to keep or make sure of the safe separation between own and threat category aircraft. The TCAS processor then outputs resolution advisory data on the ARINC 429 buses to the TA/VSI or RA/VSI units. RA traffic symbol position and alert data is output on the ARINC 429 data bus to the TA/VSI or PPI display unit. Last, resolution advisory alert voice messages and alert outputs are sent to the cockpit audio system for optional tone generators and/or lamps.(h) The TCAS processor outputs TA traffic symbol position and alert data on the ARINC 429 data bus to the TA/VSI or PPI display for the traffic advisory category aircraft. The processor also outputs traffic advisory alert voice messages and alert output for optional tone generators and/or lamps to the cockpit audio system.(i) The TCAS processor outputs proximity or nonthreat traffic symbol position data on the ARINC 429 data bus to the traffic advisory display for proximity and nonthreat category aircraft. (The voice alerts are not supplied for proximity or nonthreat category aircraft.)(j) The TCAS processor establishes a coordination data link with the threat category aircraft that are also TCAS equipped. The TCAS processor transmits coordination messages and receives coordination messages from the threat aircraft transponders through own TCAS antennas. Once the TCAS equipped threat aircraft has sensed own aircraft as a threat, the same procedure is started through own Mode S transponder. A full two-way coordination data link is established. The coordination data assure nonconflicting maneuvering between TCAS-equipped aircraft that are threats to each other.(k) During each TCAS 1030 MHz transmission on the directional or omni antenna, the TCAS processor supplies a suppression pulse to other L-band equipment on own aircraft.(l) The TCAS processor decreases fruit and synchronous interference by the following interference limiting procedures:1An ATCRBS P2 sidelobe suppression pulse is transmitted as an P2 pattern on the directional antenna to control the effective beam width.2A sequence of ATCRBS interrogations are transmitted at different power levels (whisper-shout levels). These whisper-shout levels divide the adjacent airspace into the range segments. The maximum number of whisper-shout levels (24) are used when interrogating in the forward direction on the directional antenna.3Interrogating more than once to check reply validity.4Transmitting a P2 ATCRBS suppression pulse in Mode S interrogation transmissions.5Transmitting a P4 Mode S suppression pulse during ATCRBS interrogation transmissions.
Page 491 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.(m) The TCAS processor also controls:1Scheduling for interrogations done on the directional and omni antennas.2TCAS sensitivity level operating modes.3Generation of coasting data during the periods when tracking data is temporarily not found.NOTE: For more details, refer to applicable Mode S Transponder manual, recorded in Table Intro-1.(n) Use of ADS-B data by the TCAS Processor will track and display other 1090 MHz based ADS-B aircraft if the following are true:1The ADS-B program pin, RMP5E is strapped.2The Mode-S transponder(s) connected to the TCAS support the XGD protocol, for example (0,5), (0,6), (0,8), (0,9), (1,0), (1,7), (1,8) to (1,C), (2,0), (3,0), (4,0), (5,0), and (6,0).3The Mode-S transponder(s) connected to the TCAS implement, as a minimum, BDS registers (0,5) own aircraft position, (0, 6) own surface position, and (0,9) own velocity.(o) When the ADS-B program pin is strapped the TPA-100A will:1Output on both high-speed display output busses2Request own aircraft position and velocity data from own transponder.(p) The following is a brief summary about the Display Traffic Information File (DTIF):1The TPA-100A implements the definition of ARINC 735A supplement 1 - Attachment 20 with one exception. In the DTIF, the range data type is encoded with better resolution. This is currently approved by an Airlines Electronic Engineering Committee (AEEC) subcommittee but has not been formally adopted into a supplement of ARINC 735A.2The DTIF is transmitted in addition to the standard TCAS intruder display.3The DTIF has a consolidated list of TCAS and passive tracked aircraft.4The DTIF contains data that could be used by displays to give additional traffic data to the crew.5When relative range, relative altitude, and relative bearing data on another aircraft is available from TCAS surveillance and passive Automatic Dependent Surveillance-Broadcast (ADS-B), the DTIF relative position data will be based on TCAS surveillance.
Page 501 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.(q) If the ADS-B program pin is strapped as part of the installation approval process, the use and display of passive/ADS-B data must be validated. Part of this process will include:1Ensure that the existing displays which do not process the DTIF output do still correctly receive and process the standard TCAS traffic file.2The consolidation and symbology associated with the DTIF must be approved and certified.(r) The TCAS processor also supplies communication interfaces with the following optional units:1Flight recorder2CFDS or maintenance computer3ATE equipment 4Data loader. (s) The transmitter and receiver of the TCAS processor are calibrated automatically during power up, initiated functional test, and periodically. The calibration adjusts for phase shifts added by the cables, relative phase error in the receiver circuitry, and temperature effects.(t) TCAS processors contain an Antenna System Built-In Test Equipment (BITE) test that operates when power is applied to the TCAS processor. The first function of the Antenna System test is to detect the correct input impedence to each element of the top/bottom directional antenna. The second function is to interrogate the performance characteristics of the antenna. The test measures phase coupling differences between elements J2 & J4 and J1 & J3. Failure of this test requires removal of the antenna.(4) Power RequirementsThe TCAS processor receives 115 V 360-800 Hz or 28 V dc primary power and 26 V ac synchro reference input power from the aircraft power sources.CAUTION: TO ELIMINATE RISK OF DAMAGE TO EQUIPMENT, 28 V DC AND 400 HZ CANNOT BE SUPPLIED TO THE TPA-100A AT THE SAME TIME.
Page 511 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.(5) Rear ConnectorA six section rear connector supplies the system connects to the TCAS processor. The six sections of the connector are shown left bottom plug (LBP), right bottom plug (RBP), left middle plug (LMP), right middle plug (RMP), left top plug (LTP), and right top plug (RTP). The Figure 8 shows the external devices connected to each of the six sections of the connector. The system Interwiring Diagram, Figure 2015 in the Maintenance Practices section of this manual, shows the specified pin connections into the TPA-100A TCAS processor.(6) Leading ParticularsTCAS processor leading particulars are given in Table 8. Refer to TPA-100A Component Maintenance Manual for more data.B. Directional Antenna(1) GeneralThe ANT-81A Directional Antenna (Figures 2007, 2008, 2009, and 2010) lets the bearing of intruder aircraft be determined by allowing the TCAS processor to transmit the interrogations and receive replies on one of four antenna beams. By selecting the beam, the TCAS processor electronically points the antenna in a surveillance direction during TCAS transmit and receive operations.(2) TCAS Directional Antenna Description and Basic FunctionsThe directional antenna is an electronically steerable phased array that has four top loaded monopole elements.Different from mechanically steered antennas, the antenna pattern can be pointed in one of four directions without moving the antenna. This movement is achieved by independently changing the drive level and phase to the four antenna elements contained in the directional antenna.The four beam forming elements are found on the edge of the antenna, and the full assembly is contained in an aerodynamic fiberglass enclosure just over one inch in height. The top directional antenna must be installed at, or near, the longitudinal centerline of the aircraft + 5 degrees and as far forward as practical. The bottom directional antenna or omni antenna (if used) must be put as near as possible to the vertical plane of the top directional antenna. During TCAS transmission, the directional antenna (top or bottom) radiates 1030 MHz main beam patterns under control of the four antenna element drive signals from the TPA-100A TCAS processor (see beam patterns in Figure 7).
Page 521 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.TCAS Transmit and Receive Beam Patterns for Directional Antenna Figure 7 All pulses in a TCAS (Mode S) message transmission from the directional antenna are radiated as a directional main beam pattern. To get the main beam pattern, the four signals representing each transmit pulse are phase shifted by the TCAS processor. The phase shifting set on the four elements shows the direction of the main beam to be transmitted (one of four beams). The resultant 1030 MHz signals radiated from the four elements of the antenna mix and cancel in a procedure that makes a main beam directional pattern for pulses transmitted.In a TCAS/ATCRBS interrogation transmission, the TCAS message is transmitted from the directional main beam with the exception of the ATCRBS suppression pulse (P2) which is designed to meet the DO185A requirement that a transponder not reply to more than two quadrants or beams as shown in Figure 7.To make the P2 pattern for the ATCRBS suppression pulse, the four signals representing the suppression pulse from the TCAS processor to the four elements of the antenna are of equal phase and amplitude. This causes the P2 pattern being radiated for the ATCRBS suppression pulse.
Page 531 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.ATCRBS Mode A/C transponders in the adjacent airspace that sense a suppression beam signal larger in amplitude than the main beam signal, are prevented from replying to the interrogation. The result of the ATCRBS P2 hold back is to control the good TCAS interrogation beam width and thus limit interference from unwanted ATCRBS receptions. The effective beam width can be narrowed by increasing the amplitude of the suppression P2 pattern output or decreasing the amplitude of the main beam pattern output (and vice-versa).During TCAS receptions, each of the four directional antenna elements receives any 1090 MHz signal that passes by the element. The phasing of these received signals is determined by the direction that the rf energy is received. These signals are received on the same four cables that connect transmit signals between the TCAS processor and directional antenna.Many filters are used in the TCAS processor for noise suppression and pulse shaping of the received signals. Phase detectors in the TCAS processor then examine the relative phasing of the four signals from the antenna and make an analog voltage that shows the bearing of the replying intruder aircraft.The main beam pointing angle can be redirected in microseconds to any of the four 90 pointing positions.Four coaxial cables with type Threaded N Connector (TNC) plugs on the antenna end connect the directional antenna to the TCAS processor.Each of the four ports of the directional antenna contains a resistor found across the antenna element to ground. Each of the four resistors is a different value. The TCAS processor at intervals does a continuity check on the antenna ports and must see the correct resistance value (through an A/D converter) if the port is not shorted or not open.The directional antenna is a passive device and does not require aircraft power.
Page 541 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.C. TA/VSI Display(1) GeneralThe IVA-81A/D Resolution Advisory/Traffic Advisory/Vertical Speed Indicator (TA/VSI) display is a high resolution, sunlight readable, full color, liquid crystal display (LCD) (Figures 2011, 2012, and 2013). The indicator lets resolution advisory and traffic data be shown in the space previously for display of vertical speed only. Vertical speed is shown on a standard circular dial with a pointer. Resolution advisories are shown as red or red/green arcs (eyebrows) on the applicable part of the circular vertical speed dial.The center of the display is a horizontal situation presentation of the traffic around the aircraft that includes intruder altitude and vertical direction. Traffic is divided into four categories by the threat risk and identified on the display by the symbol color and shape.The text messages are shown for TCAS and display modes, intruder data, and vertical rate input validity.The display intensity level is controlled by a group of bezel and remote light sensors and by the lighting bus input. An optional bezel attached intensity control is also available.Traffic display range control can be supplied at a distance from a Control Unit or locally through an optional bezel attached range control.An optional traffic select (TA SEL) switch lets deselection of traffic format when a TA or RA is present.The TA/VSI accepts air data ARINC 565 or ARINC 575 analog input, ARINC 575 digital or ARINC 429 high and low speed input, and pneumatic vertical speed input.(2) Resolution Advisory DisplayThe resolution advisory commands shown on the TA/VSI (or RA/VSI) are the primary indications for vertical maneuvering guidance. TCAS resolution advisories on the two TA/VSI (or RA/VSI) units show vertical speeds to be used or prevented to keep or get safe vertical separation.A pointer and vertical speed scale, which are standard VSI features, show the present vertical speed of own aircraft. For TCAS guidance, the TA/VSI shows red and green command arcs on a liquid-crystal display with the vertical speed scale and pointer.The red and green RA command indications give corrective or preventive resolution advisory maneuvering guidance to the pilot (see Controls and Indicators, paragraph 7).
Page 551 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.(3) Traffic DisplayThe TA/VSI traffic display shows adjacent intruder aircraft that have Mode S or ATCRBS Mode A/C transponders, are sensed on a directional antenna, and are in the display range.NOTE: The TCAS processor interface also supports traffic displays on a dedicated TCAS traffic display or a PPI radar display changed for TCAS. The unit set to show traffic depends on equipment present in the aircraft and other user specifications. The TCAS processor gives traffic display and resolution advisory data output on two isolated high-speed ARINC 429 data bus outputs.Graphics supplied on the traffic display alert the pilot to traffic advisory conditions, resolution advisory conditions, and show the TCAS operational modes and failure conditions. The selected traffic display functions as a self-sufficient auxiliary device controlled by the TPA-100A TCAS processor through one high-speed ARINC 429 data bus. The traffic displays are secondary displays in the total CAS-100 system. (Resolution advisories on the TA/VSI and RA/VSI are the primary TCAS displays). The traffic display helps the pilot visually acquire a threat intruder aircraft before resolution advisory threat conditions.The traffic display data from the TPA-100A TCAS processor through the high-speed ARINC 429 data link includes the following:(a) Intruder aircraft range(b) Intruder aircraft relative altitude (if available)(c) Intruder aircraft bearing (if available)(d) Intruder category (resolution advisory threat; traffic advisory; proximity; or nonthreat)(e) Own aircraft altitude, in Flight Level (FL) mode only(f) Own aircraft operating mode (sensitivity level)(g) Own aircraft heading (EFIS display only)(h) Advisory alert data(i) TCAS failure status data
Page 561 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.(j) Display range limit control, ABOVE/NORM/BELOW nonthreat altitude display limit control, and relative/flight level altitude display control data originating from the transponder/TCAS control unit and received by the traffic display through the Mode S transponder and TCAS processor. (k) Other strapped control data (For example, maximum number of intruders to be shown)Refer to Controls and Indicators, paragraph 7, for traffic display indications and annunciations.D. RA/VSI Display The IVA-81B Resolution Advisory/Vertical Speed Indicator (RA/VSI) display. It consists of:• An electro-mechanically driven pointer (to show vertical speed)• A resolution advisory arc of red and green high intensity light-emitting diodes (LEDs)• An electro-mechanical TCAS flag (To show normal and fail conditions and RA mode OFF conditions)• Vertical speed failure flagThe resolution advisory LEDs are installed below a coated surface which makes them not seen when unlighted. The VSI face is matte black with a matte white vertical speed scale. The vertical speed pointer is controlled by a two-phase motor. The position is controlled by the processed data supplied by the display computer.The RA/VSI accepts the air data ARINC 565 or ARINC 575 analog input, ARINC 575 digital, ARINC 429 high and low speed data, or a pneumatic vertical speed input.Vertical maneuvering resolution advisory data (RA data) is received through a high-speed ARINC 429 data bus from the TCAS processor.NOTE: Traffic is not shown on an RA/VSI.Built-in test circuits continuously monitor for RA/VSI unit failures. Failure status is reported to the TCAS processor through discrete DISPLAY VALID signal lines.The resolution advisories (RAs) on the electrical/electro-mechanical display of the RA/VSI are identical to the RAs on the LCD display of the TA/VSI [see paragraph 5.C.(2)].
Page 571 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.E. ITA-81A Traffic DisplayThe ITA-81A Traffic Display is a CRT display for TCAS traffic data only (Figure 2014). The ITA-81A receives traffic display data from the TCAS processor through a high-speed ARINC 429 data bus. The ITA-81A does not show resolution advisories. Refer to Table 17 for the ITA-81A Traffic Display Input and Output.F. PPI Traffic Advisory Display OptionThe TCAS/PPI is a group of two displays. The first is the usual radar displays of weather, map, or auxiliary data. The second is TCAS traffic data. Each display can be presented independently or overlaid. By combining the radar and TCAS displays, the pilot can monitor traffic while avoiding weather. The PPI receives traffic display data from the TCAS processor through a high-speed ARINC 429 data bus. The PPI does not show resolution advisories. G. Mode S TransponderThe Mode S Transponder does the following functions in the CAS-100 system:• Automatically transmits 1090 MHz Mode S squitter messages each second. These squitter messages tell other TCAS equipped aircraft and ground stations that own Mode S equipped aircraft is present.• Receives transmit messages from other TCAS equipped aircraft and tells own TCAS processor that transmit message was received.• Replies to 1030 MHz Mode S interrogations from other TCAS equipped aircraft.• Replies to 1030 MHz Mode A, Mode C, and Mode S interrogations from ATC ground stations with a 1090 MHz message in the standard procedure.• Transmits 1090 MHz resolution advisory air-to-air coordination message data (received from the TCAS processor) during threat conditions between own and other TCAS equipped aircraft.
Page 581 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.• Supplies the following data to the TPA-100A TCAS Processor through a ARINC 429 data link:-- Own aircraft identification code, pressure altitude, and maximum airspeed data.-- TCAS broadcast data and air-to-air resolution advisory coordination data received from other TCAS equipped aircraft.-- TCAS sensitivity level and other mode control data received by own Mode S transponder from own transponder/TCAS control unit.-- TCAS sensitivity level control data from Mode S ground control stations at 1030 MHz (future application).-- Mode S ARINC 604 Maintenance status.• Receives TCAS capability, TCAS validity, sensitivity level, and TCAS coordination update data from the TCAS processor through the ARINC 429 data link and inserts this data into 1090 MHz coordination messages. H. CTA-100( ) Control UnitThe CTA-100( ) Control Units are examined in this manual to a depth necessary to know total TCAS operation. For more data, refer to TRA-67 Mode S Transponder System Maintenance Manual, I.B. 1167. The microprocessor based CTA-100( ) Control Unit lets the pilot do the following: • Start or stop the Mode S transponder.• Select TCAS operating modes, control range, above/below altitude limits, and flight level compared to related altitude displays on the TCAS traffic display unit.• Set the ATC transponder identification code.• Insert a special pattern identifier code (IDENT) into transponder messages to ground station interrogations.• Start TCAS functional test.• Set which transponder is in operation in a two transponder system.• Set the altitude source (optional).• The CTA-81( ) contains an annunciator lamp that shows if a transponder FAIL condition is present.
Page 591 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.The Mode S transponder/TCAS control unit moves the control data to the Mode S transponder through an ARINC 429 data link. The transponder/TCAS control unit FAIL lamp receives a failure status discrete input from the Mode S transponder.CTA-100( ) controls and indicators are shown in Figures 10 and 11 and are functionally given in Tables 18 and 19.I. TCAS and Mode S Transponder Omnidirectional AntennasTCAS can use one omni antenna installed on the bottom of the aircraft instead of a directional antenna. The Mode S transponder uses two omni antennas; one antenna installed on the bottom of the aircraft and the other antenna installed on the top of the aircraft.These omni antennas are L-band monopoles and are the same to those omni antennas used for distance measuring equipment (DME) and ATC transponders.The BITE circuits routinely do continuity checks on the omni antennas and their cables.6. OperationA. GeneralThe data in this section gives a description of CAS-100 operation that includes:(1) Complete Block Diagrams and Description of Input/Output Signals.(2) TCAS Failure Monitoring.NOTE: All data in this manual is superseded by the latest engineering software and hardware documentation.B. Detailed Block Diagrams and Description of Input/Output SignalsThe Figure 8 is a block diagram of the CAS-100 system unit connects to the TPA-100A TCAS Processor. The Table 10 gives the TCAS Processor input/output signals. Interwiring diagram, Figure 2015 in the MAINTENANCE PRACTICES section, gives specified connect pin numbers on the TCAS processor and shows the pins on the Mode S transponders and indicators that connect to the TCAS processor.The Figure 9 is a block diagram of the system unit connects to the IVA-81A/D TA/VSI and IVA-81B RA/VSI. The Table 11 gives the TA/VSI and RA/VSI input/output signals. Interwiring diagram, Figure 2015 in the MAINTENANCE PRACTICES section gives specified connect pin numbers on the TA/VSI and RA/VSI.The total system connects for the Mode S transponder and control units are shown in the applicable maintenance manual.Specific connect pin numbers on the TCAS processor and a PPI or dedicated display are given on the Interwiring diagram, Figure 2015 in the MAINTENANCE PRACTICES section. The system connects into the optional PPI are shown in the associated maintenance manual recorded in Table Intro-1.
Page 601 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Refer to Table 15 for the TPA-100A TCAS Processor input and output. The IVA-81A/D TA/VSI and IVA-81B RA/VSI input and output are shown in Table 16. Table 17 shows the input and output of the ITA-81A Traffic Display.
MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEM34-45-47TCAS Processor System Interconnect Block DiagramFigure 8 (Sheet 1 of 3)Page 61/621 Dec 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEM34-45-47TCAS Processor System Interconnect Block DiagramFigure 8 (Sheet 2 of 3)Page 63/641 Dec 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEM34-45-47TCAS Processor System Interconnect Block DiagramFigure 8 (Sheet 3 of 3)Page 65/661 Dec 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 671 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 15. TPA-100A TCAS Processor Inputs and OutputsSource OrDestinationProcessor I/O SignalName and TypeGeneralDescriptionTCAS ANTENNA RELATED I/ODirectional Antenna Top and bottom directional antenna. Four rf, bi-directional, transmit/ receive channels.1030-MHz differential phase shift keying modulated TCAS transmit messages from the TCAS processor to the directional antenna and 1090-MHz received messages from the directional antenna to the TCAS processor.Bottom TCAS Omni AntennaBottom Omni Antenna. One rf, bi-directional, transmit/receive channel. (Same channel as the element No. 1 port used for the directional antenna.)1030-MHz differential phase shift keying modulated transmit messages from TCAS processor to omni antenna and 1090-MHz received messages from the omni antenna to TCAS processor.Three Strapped Pins on Processor Rear Connector Antenna Delay Straps. Three discretes. Supply calibration data base inputs to TCAS processor to adjust for the difference in the cable lengths between top and bottom antenna.MODE S TRANSPONDER RELATED I/OMode S Transponder No. 1 and No. 2 Coordination Data. 429 high-speed, transmit bus and ARINC 429 high-speed receive bus.ARINC Real-time and periodic data from TCAS processor to the transponder includes TCAS equipment and control change data. Real time and periodic data from transponder to processor. The data from the transponder to the processor includes TCAS control, own barometric altitude, own identification, own maximum airspeed, broadcast and coordination data. If the ADS-B program pin is strapped, TCAS will request own position and velocity data from the transponder.Strap Pin on Processor Rear ConnectorDiscrete input from Transponder Interface Select StrapTells TCAS processor if one or two transponders are installed.
Page 681 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 15. TPA-100A TCAS Processor Inputs and Outputs (cont)Source OrDestinationProcessor I/O SignalName and TypeGeneralDescriptionOWN ATTITUDE AND HEADING RELATED I/OSynchro Magnetic Compass System Heading Synchro X, Y, Z Heading Own heading data to TCAS processor from the aircraft synchro heading system.Discrete Heading Valid Synchro heading system failure status to TCAS processor.26 V ac Reference Input Heading synchro reference voltage to TCAS processor.Pitch and Roll Gyros Pitch Synchro X, Y, Z Own synchro pitch attitude data to TCAS processor from pitch gyro.Discrete Pitch/Roll Valid Own pitch gyro and roll gyro failure status to TCAS processor.Roll Synchro X, Y, Z Own synchro roll attitude data to TCAS processor from roll gyro.26 V ac Reference Input Reference voltage for pitch and roll synchro input to TCAS processor. Attitude/Heading Reference System (AHRS or IRS)AHRS ARINC 429 high-speed pitch/roll/magnetic heading input Own digital ARINC 429 digital pitch/roll/ magnetic heading to TCAS processor from AHRS system.
Page 691 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 15. TPA-100A TCAS Processor Inputs and Outputs (cont)Source OrDestinationProcessor I/O SignalName and TypeGeneralDescriptionOWN ALTITUDE RELATED I/OAnalog Radio Altimeter No. 1± Analog Radio Altitude No. 1 Input AGL altitude data to TCAS processor from analog radio altimeter No. 1.Discrete Radio Altitude No. 1 Valid Radio altimeter No. 1 failure status input to TCAS processor.Analog Radio Altimeter No. 2 ± Analog Radio Altitude No. 2 AGL altitude data to TCAS processor from analog radio altimeter No. 2.Discrete Radio Altitude No. 2 Valid Radio altitude No. 2 failure status input to TCAS processor. ARINC 429 Digital Radio Altimeter No. 1ARINC 429 Digital Radio Altitude No. 1 ARINC 429 data from digital radio altimeter No. 1 to TCAS processor.ARINC 429 Digital Radio Altimeter No. 2ARINC 429 Digital Radio Altitude No. 2ARINC 429 data from digital radio altimeter No. 2 to TCAS processor.Three Strapped Pins on Processor Rear ConnectorThree discretes from Analog Radio Altimeter Select StrapsSpecify the type of analog radio altimeter that is connected to the Analog Radio Altitude No. 1 and No. 2 input (for example, King, Sperry, Collins, ARINC 552A, etc.).Strap Pin on Processor Rear ConnectorDiscrete input from Radio Altimeter Interface Select StrapTells TCAS processor if one or two radio altimeters are installed.OWN AIRCRAFT PERFORMANCE LIMIT AND FLIGHT STATUS RELATED I/OOptional Performance Management ComputerClimb Performance Limit Discrete Tells TCAS processor that after considering own altitude, attitude, cargo weight factors, etc. a performance management computer has found if it is possible or not possible for own aircraft to climb at a rate of 1500 feet for each minute.Climb Performance Limit ARINC 429 Digital equivalent of climb performance discrete from a performance management computer.
Page 701 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 15. TPA-100A TCAS Processor Inputs and Outputs (cont)Source OrDestinationProcessor I/O SignalName and TypeGeneralDescriptionOWN AIRCRAFT PERFORMANCE LIMIT AND FLIGHT STATUS RELATED I/O ContFive Strapped Pins on Processor Rear ConnectorFive discretes from Altitude Limit StrapsShow the maximum altitude at which own aircraft can get a climb rate of 1500 feet for each minute.Air/Ground Strut Switch Air/Ground Strut Discrete Air/Ground Strut Discrete Strap Pin on Processor Rear ConnectorDiscrete input from Functional Test Inhibit Strap Sets on inhibits functional test when the aircraft is airborne.Landing Gear Retracted/Extended SwitchLanding Gear Up/Down Discrete Tells TCAS processor if own aircraft landing gear is retracted or extended.Optional Aircraft Equipment that Monitor the Aircraft Factors Relating to 1500 Feet For Each Minute Climb Rate PerformanceClimb Inhibit 1, 2, 3 and 4. Four discrete inputs.Tell the TCAS processor that conditions exist to prevent or not prevent an own aircraft climb rate of 1500 feet for each minute.Optional Aircraft Equipment that Monitor the Aircraft Factors Relating to 2500 Feet For Each Minute Climb Rate PerformanceIncrease Climb Inhibit 1, 2, 3 and 4. Four discrete inputs.Tell the TCAS processor that conditions exist to prevent or not prevent an own aircraft climb rate of 2500 feet for each minute.TCAS Valid Monitor TCAS System Valid Output DiscreteAvailable to accommodate retrofit installations where instrumentation may need to monitor TCAS system status.RA AND TA DISPLAY RELATED I/OTA/VSI No. 1 or RA/VSI No. 1, PPI, or dedicated display.Display No. 1, high-speed ARINC 429, RA and TA data wordsResolution advisory, traffic display, operating mode, and failure data from TCAS processor to TA/VSI No. 1, the RA/VSI No. 1, a PPI, or a dedicated display.Display Status No. 1 Discrete TA/VSI No. 1 or RA/VSI No. 1 failure status output to TCAS processor.
Page 711 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 15. TPA-100A TCAS Processor Inputs and Outputs (cont)Source OrDestinationProcessor I/O SignalName and TypeGeneralDescriptionRA AND TA DISPLAY RELATED I/O (cont)TA/VSI No. 1 or RA/VSI No. 1, PPI, or dedicated display. (cont)Display Status No. 3 Discrete (Optional for maintenance reporting.)Failure status output of PPI or dedicated display connected to TA/RA Display No. 1 high-speed ARINC 429 bus.TA/VSI No. 2 or RA/VSI No. 2, PPI or dedicateddisplay Display No. 2, high-speed ARINC 429, RA and TA data wordsResolution advisory, traffic display, operating mode, and failure status data from TCAS processor to TA/VSI No. 2, or RA/VSI No. 2, a PPI, or a dedicated display.Display Status No. 2 Discrete TA/VSI No. 2 or RA/VSI No. 2 failure status output to TCAS processor.Display Status No. 4 Discrete (Optional for maintenance reporting.)Failure status output of PPI or dedicated display connected to TA/RA Display No. 2 high-speed ARINC 429 bus.RA/VSI No. 1 (RA/VSI that accepts low-speed data 429 input data)Display No. 1, low-speed ARINC 429 RA data wordsResolution advisory, operating mode, and failure status from TCAS processor to low-speed 429 RA/VSI No. 1 or optional flight recorder.Display Status No. 1 Discrete RA/VSI No. 1 failure status output to TCAS processor.RA/VSI No. 2 (RA/VSI that accepts low-speed 429 input data)Display No. 2 low-speed ARINC 429 RA data wordsResolution advisory operating mode, and failure status data from TCAS processor to low-speed 429 RA/VSI No. 2.
Page 721 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 15. TPA-100A TCAS Processor Inputs and Outputs (cont)Source OrDestinationProcessor I/O SignalName and TypeGeneralDescriptionRA AND TA DISPLAY RELATED I/O (cont)RA/VSI No. 2 (RA/VSI that accepts low-speed 429 input data) (cont)Display Status No. 2 Discrete RA/VSI No. 2 failure status output to TCAS processor.Five Strapped Pins on Processor Rear ConnectorIntruder Display Limit Straps. Five Discrete InputsShow the maximum number of intruder aircraft (0-30) to be shown on the traffic displays.One Strapped Pin on Processor Rear ConnectorGround Display Mode Strap DiscreteControls if traffic is shown when own aircraft is on-the-ground. If strapped to not show traffic on-the-ground, TCAS goes to STANDBY on-the- ground.One Strapped Pin on Processor Rear ConnectorRA/TA Display Mode Strap DiscreteShows either all traffic or TA/RA and near traffic only (for example, nonthreat traffic not shown).Optional Ground Proximity SystemGround Proximity (GPWS) Advisory Delay DiscretePuts TCAS into the TA only mode (sensitivity level 2) and prevents all audio and aural advisories.Optional Wind Shear System No. 1 and No. 2Wind Shear Advisory Delay No. 1 and No. 2 DiscretesPuts TCAS into the standby mode (sensitivity level 1) until wind shear condition is over.Optional Advisory Alert Cancel Switch Advisory Alert Cancel Discrete When pushed and released, this switch cancels active advisory alert conditions. Cockpit Speaker and Optional Cockpit Headphones Audio HI and LO outputs. Speaker output - 8 ohms, 8 watts maximum. Headphone output - 600 ohms, 80 milliwatts maximum. (Adjustable using audio level program straps, below. See Figure 2005, Note 15 in MAINTENANCE PRACTICES section for adjustment ranges.)Supplies the voice advisory message alerts to cockpit speaker and optional headset.
Page 731 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 15. TPA-100A TCAS Processor Inputs and Outputs (cont)Source OrDestinationProcessor I/O SignalName and TypeGeneralDescriptionRA AND TA ALERT RELATED I/OThree Strapped Pins on Processor Rear ConnectorAudio Level Program Straps (Airborne). Three Discrete Input.For adjusting synthesized voice output of the TCAS processor when the aircraft is airborne.Three Strapped Pins on Processor Rear Connector Audio Level Program Straps (On Ground). Three Discrete Input. For adjusting synthesizer voice output of the TCAS processor when aircraft is on the ground.Audio Tone Generators Aural Advisory Alerts. Three discrete outputs for Corrective RA Tone, Preventive RA Tone, and TA Tone alerts. (1 second ground, 20 milliamp maximum). Supply TA and RA alert output that start optional tone generators found externally in the aircraft.Strapped Pin on Processor Rear Connector. Audio tone Enable Program Strap. Discrete Input. When strapped, supplies interval of voice output 1 second to aural advisory output. When open, drives aural advisory discrete output. Annunciator Lamps Visual Annunciator output. Three discrete output for Corrective RA Lamp, Preventive RA Lamp, and TA Lamp alerts. (On = ground, 200 milliamp maximum).Supply TA and RA alert output that start serviceable lamp indicators found externally in the aircraft. Strapped Pin on Processor Rear Connector. NOTE 1.On Ground Intruder Disable Strap. Discrete Input. Determines if own aircraft is below 1750 feet (radio altitude), intruders found to be ON GROUND will be shown.Strapped Pin on Processor Rear ConnectorRA Status Inhibit Strap. Discrete Input.Finds if RA display status is in operation or prevented.
Page 741 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 15. TPA-100A TCAS Processor Inputs and Outputs (cont)Source OrDestinationProcessor I/O SignalName and TypeGeneralDescriptionMAINTENANCE RELATED I/OMaintenance Computer or Centralized Failure Display System (CFDS)Maintenance Data. ARINC 429 high-speed transmit and ARINC 429 high-speed receive bus.Maintenance digital 429 data from maintenance computer or CFDS to TCAS processor and maintenance digital 429 data from TCAS processor to maintenance computer or CFDS. Automatic Test Equipment (ATE)ATE Test Pins. Twenty discrete output.TCAS processor status output to ATE monitors. Not necessary for the aircraft installation.Data Loader Data loader high or low-speed ARINC 429 transmit bus and receive bus. Four discrete input (3 space).Data for software updates.NONDIGITAL FLIGHT RECORDER RELATED I/OOptional Flight Recorder (NonDigital Type)ARINC 573 Resolution Advisory (RA) WordResolution advisory data word output from TCAS processor to the aircraft nondigital flight recorder.NOTE 2.
MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMPage 75 1 Dec 2003 34-45-47Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 15. TPA-100A TCAS Processor Inputs and Outputs (cont)Source OrDestinationProcessor I/O SignalName and TypeGeneralDescriptionSUPPRESSION BUS RELATED I/OOwn Aircraft L-Band EquipmentSuppression Pulse input/output Bi-directional bus. An input pulse suppresses the TCAS receiver. An output suppression pulse suppresses other L-band equipment in the aircraft.POWER RELATED I/OOwn Aircraft Power Supplies Fan On TCAS Processor Assembly Tray 115 V 400 Hz or 28 V dc and 26 V ac reference power input.115 V 400 Hz output (or from 28 V dc source).Provide power to the TCAS processor from own aircraft power sources.Supplies energizing power from the TCAS processor to the cooling fan on the processor assembly tray.NOTES:1. Not used with Change 7 units. On ground intruders never shown.2. An ARINC 429 output is also supplied for an optional digital-type flight recorder. See the output to RA/VSI No. 1.
Page 761 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.THIS PAGE LEFT BLANK
MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEM34-45-47IVA-81A/D and IVA-81B RA/VSI System Interconnect Block DiagramFigure 9Page 77/781 Dec 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 791 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 16. IVA-81A/D TA/VSI and IVA-81B RA/VSI Inputs and OutputsSource OrDestinationI/O SignalName and TypeGeneralDescriptionTCAS PROCESSOR RELATED I/OTCAS Processor TCAS Data High-Speed ARINC 429 (Two Ports)Traffic display and resolution advisory data from TCAS processor to TA/VSI or RA/VSI No. 1 or No. 2. (The RA/VSI uses only that data for resolution advisories.) Display Status No. 1 Discrete and Display Status No. 2 DiscreteSupplies TA/VSI or RA/VSI No. 1 or No. 2 failure status to TCAS processor.VERTICAL RATE SOURCE RELATED I/O (One of the following input can be selected)Aircraft Static Pressure SourceStatic Pressure Source Pneumatic InputPressure altitude from an aircraft static pressure port.Aircraft ARINC 565 ac Analog Rate Source and Reference VoltageAltitude Rate. AC Analog with 26 V ac High and Low ReferenceAnalog altitude rate which is converted by the TA/VSI or RA/VSI into vertical speed pointer position on the VSI. Aircraft ARINC 575 dc Analog Rate Source and Reference VoltageAltitude Rate. DC Analog with +12 and -12 V dc Reference Same as above.Aircraft Digital ARINC 429 (Label 212) Rate SourceAltitude Rate Data. Low-speed ARINC 429Digital vertical speed related data which is converted by the TA/VSI or RA/VSI into vertical speed pointer position on the VSI.Aircraft Digital ARINC 429 (Label 365) Rate SourceInertial Vertical Speed Data. High-speed ARINC 429 Same as above.
Page 801 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 16. IVA-81A/D TA/VSI and IVA-81B RA/VSI Inputs and Outputs (cont) Source OrDestinationI/O SignalName and TypeGeneralDescriptionVERTICAL RATE SOURCE RELATED I/O (cont)Aircraft Digital ARINC 575 (Label 212) Rate SourceAltitude Rate Data. Digital ARINC 575. Low-speed ARINC 419Same as above.Aircraft Digital ARINC 419 (Label 212) Rate SourceAltitude Rate Data. Low-speed digital vertical speed, ARINC 419.Nonstandard ARINC 419 interface used with a general aircraft that has an air data computer which transmits ARINC 419 Label 212 at an internal rate slower than the maximum of 67 milli-seconds.Vertical Speed Source Vertical Speed Valid Discrete Supplies failure status from set analog vertical rate source unit to the VSI.ALTITUDE RATE OUTPUTIVA-81A/D or IVA-81B Digital Altitude Rate Output Buffered altitude rate output for use by remote indicators. CONFIGURATION AND SOURCE SELECT STRAPPING RELATED I/ONine Configuration Straps and Two Source Select Straps on TA/VSI or RA/VSI Rear ConnectorCS0-CS8 Configuration Straps and Source Select No. 1 and No. 2 Straps. Eleven discrete input.Show the type of vertical rate source input to the TA/VSI, RA/VSI, and other system particulars.POWER RELATED I/OOwn Aircraft Power Supplies115 V 400 Hz or 28 V dc Supplies the primary power to TA/VSI and RA/VSI.LAMP TESTLamp Test Source Lamp Test Discrete IVA-81A/D turns on LCD display. IVA-81B turns on TCAS eyebrow lights.Own Aircraft Dimmer Bus 5 V ac or dc or 28 V dc Controls panel background lighting on TA/VSI and RA/VSI.
Page 811 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 17. ITA-81A Traffic Display Inputs and OutputsC. TCAS Failure MonitoringThe TCAS system includes extensive Built-In-Test Equipment (BITE) monitoring. BITE does full-time monitoring of the TCAS system components. Primary failures are shown on the screen of the PPI or dedicated traffic display, and on different FAIL lamps and flags throughout the system. BITE monitoring is totally transparent to the pilot and does not effect the TCAS operation unless a failure is found. When a primary system failure is found, specified LRU (line replaceable unit) failures are shown on the PPI or dedicated traffic display. If a PPI weather/traffic display is used in a weather mode, TCAS FAIL will be annunciated. When the display is set to TCAS mode, the specified LRU failure(s) is shown.BITE monitors the internal operation of the system components and I/O data links.When a TCAS FAIL condition is found, TCAS stops all surveillance and tracking functions.NOTE: A complete description of BITE monitoring operations and their failure annunciations and indicators, is contained in the TESTING AND FAULT ISOLATION and in the MAINTENANCE PRACTICES sections of this manual.Source OrDestinationI/O SignalName and TypeGeneralDescriptionTCAS PROCESSOR RELATED I/OTCAS Processor TCAS Data High-Speed ARINC 429 Traffic display data from TCAS processor to dedicated TCAS traffic display. Display Status No. 3 Discrete Supplies dedicated display failure status to TCAS processor. Traffic Alert Display Enable Discrete TCAS processor discrete output sets the power supply of dedicated display.POWER RELATED I/OOwn Aircraft PowerSupplies115 V 400 Hz Supplies the primary power to dedicated TCAS traffic display. Own Aircraft DimmerBus 5 V ac Controls panel background lighting on dedicated display.
Page 821 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.7. Controls and IndicatorsA. GeneralThe primary manual controls used to operate the CAS-100 system are contained on the transponder/TCAS control units.NOTE: TCAS advisory and/or serviceable status indications are given on the TA/VSI, RA/VSI, PPI, dedicated traffic display, cockpit audio system, transponder/TCAS control unit, front panel of the TCAS processor, and front panel of the Mode S transponder unit.It is possible to supply the control of traffic advisory display range selection at a distance from the transponder/TCAS control unit or locally through a front panel range selector switch or switches. The control is supplied depending upon type of display unit used and display unit configuration strapping.B. TCAS Input Power Control115 V 400 Hz or 28 V dc primary power, 26 V ac reference power, and 5 V ac or dc or 28 V dc background panel lighting power are applied to TCAS by closing aircraft circuit breakers. TCAS does not contain a power on/off switch or fuses.C. CTA-81( ) Control UnitSee Figures 10 and 11. The CTA-81( ) Control Unit is the primary control for both TCAS and the transponder. The CTA-81A Control Unit is used in the installations containing two TRA-67A Mode S transponders. The CTA-81B is used in the installations containing one TRA-67A Mode S transponder and one ATCRBS transponder. The Tables 18 and 19 give the functions of the controls and indicators on the control units.D. CTA-100A Control UnitSee Figure 12. The CTA-100A is an upgraded and enhanced microprocessor-based transponder control panel for controlling maximum two TRA-67A ATC transponders and the TPA-81A/TPA-100A TCAS processors. The CTA-100A controller is supplied with two basic front panel configurations, a rotary control version and a keypad entry version. The CTA-100A can facilitate the front panel interchangeability. It is made in all functional configurations of the CTA-81( ) control panels with the same connector configuration and is applicable for a one-for-one component change-out. The Table 20 gives the functions of the controls and indicators on the control unit.
Page 831 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.CTA-81A Control Unit (Typical)Figure 10 Refer to Table 18 for the CTA-81A Control Unit controls and indicators.
Page 841 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 18. CTA-81A Control Unit Controls and IndicatorsControl/Indicator(See Figure 10) FunctionATC 1-2 Switch Sets one of two Mode S transponders to be under control of the CTA-81A Control Unit. The nonselected Mode S transponder is put in STANDBY mode.ALT 1-2 Switch The switch sets one of two Mode S transponder altitude source input ports. Function Selector Switch Rotary switch. Controls the operating modes of Mode S transponder and requests the TCAS operating modes.NOTE 1. TEST Position Holding switch in the spring-loaded TEST position for one second starts the TCAS and Mode S transponder functional self-test. If the TCAS processor Functional Test Inhibit program pin is strapped, the TCAS functional test is prevented while the aircraft is airborne. The TCAS flag shows TCAS on the RA/VSI display during the functional test (approximately 12 seconds). The traffic display shows TEST. A test pattern shown on the traffic display allows verification of each type of intruder symbol. During the first three seconds a lamp test is done on all segments of the RA/VSI. If a failure is found during functional test, the TCAS flag continues to display TCAS. Following the lamp test, a test fixed command is shown until the end of test. STBY Position In-flight or on-the-ground puts the Mode S transponder and TCAS in STANDBY mode (TCAS sensitivity level No. 1). In STANDBY mode, transponder power is turned on but the transponder does not transmit squitters or reply to interrogations. In STANDBY mode, all TCAS broadcast, surveillance, and tracking operations are made unserviceable and the traffic display is erased but for a TCAS STBY mode annunciation.
Page 851 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 18. CTA-81A Control Unit Controls and Indicators (cont)Control/Indicator(See Figure 10) FunctionFunction Selector Switch(cont)ALT OFF Position (cont) In-Flight - Turns on Mode S transponder to fully active state and places TCAS in STANDBY mode (TCAS sensitivity level No. 1).The Mode S transponder transmits squitters and replies to Mode S, ATCRBS Mode C, and Mode A interrogations. The Mode S transponder reply to Mode C and Mode S does not contain an altitude report. The transponder reply to Mode A contains the ATC transponder code (normal Mode A reply). All TCAS broadcast, surveillance, and tracking functions are made unserviceable. The traffic display screen is erased but for a TCAS STBY mode annunciation. On-the-Ground - Mode S transponder squitters and replies to Mode S interrogations. Depending on Mode S transponder strapping, the transponder replies or not to ATCRBS Mode C and Mode A interrogations. The transponder reply to ATCRBS and Mode S interrogations does not contain an altitude report. The transponder reply to Mode A interrogations contains the ATC transponder code. TCAS is in STANDBY mode (TCAS sensitivity level No. 1). The traffic display screen is erased but for a TCAS STBY annunciation.ALT ON Position In-Flight - Same effect on the Mode S transponder and TCAS as ALT OFF position (in-flight) other than the Mode S transponder reports altitude in its Mode C and Mode S replies.On-the-Ground - Same effect on the Mode S transponder and TCAS as ALT OFF position (on-the-ground) other than the transponder reports altitude in its Mode C and Mode S replies (if strapped to respond to Mode C when on-the-ground).
Page 861 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 18. CTA-81A Control Unit Controls and Indicators (cont)Control/Indicator(See Figure 10) FunctionFunction Selector Switch(Cont.)TA Position (TA ONLY Mode) (Cont.)In-Flight - Turns the Mode S transponder to the operation condition and puts the TCAS in TA ONLY mode (traffic advisory only mode) (TCAS sensitivity level No. 2). The Mode S transponder transmits squitters and replies fully to Mode S, ATCRBS Mode C, and Mode A interrogations. TCAS broadcasts and does all Mode S and ATCRBS surveillance and tracking functions. TCAS gives traffic displays for TA, proximity, and nonthreat category aircraft (NOTE 2. for exception). TCAS does not categorize or display one aircraft as a RA threat symbol. TCAS gives the traffic advisory alerts, but does not give resolution advisory alerts (for example, voice RA alerts or RA indications on the traffic display are not supplied). A TA ONLY annunciation comes into the view on the traffic display.On-the-Ground - Mode S transponder squitters and replies to Mode S interrogations. Depending on transponder strapping, transponder replies fully or does not reply to ATCRBS Mode C and Mode A interrogations. Depending on TCAS strapping, TCAS goes into TA ONLY mode or STANDBY mode (traffic display screen is erased except for a TCAS STBY mode annunciation shown on the traffic display).TA/RA Position In-Flight - Turns on the Mode S transponder to the operation condition. If own aircraft is above 500 feet AGL, TCAS goes into sensitivity level No. 4 through No. 7 dependent on own aircraft altitude (see Table 7). The Mode S transponder transmits squitters and replies fully to Mode S and ATCRBS
Page 871 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 18. CTA-81A Control Unit Controls and Indicators (cont)Control/Indicator(See Figure 10) FunctionFunction Selector Switch (Cont.)TA/RA Position (Cont.)Mode C and Mode A interrogations. TCAS broadcasts and does all Mode S and ATCRBS surveillance and tracking functions. TCAS supplies traffic displays for RA, TA, proximity, and nonthreat category aircraft (see NOTE 2.), transmits RA and TA alerts, and transmits resolution advisories on the TA/VSI or RA/VSI. A TA/RA annunciation comes into the view on the PPI or dedicated traffic display. A mode annunciation is not given on the TA/VSI for TA/RA mode. (NOTE 3.)On-the-Ground - Mode S transponder squitters and replies fully to Mode S interrogations. Depending on transponder strapping, transponder replies fully or does not reply to ATCRBS Mode C and Mode A interrogations or Mode S interrogations. TCAS defaults to TA ONLY mode (TCAS sensitivity level No. 2) and functions as shown for the TA position (on-the-ground) of the Function Selector Switch in this table. FL Pushbutton Switch Spring-loaded pushbutton switch. When pushed and released, replaces relative altitude annunciations for the intruder aircraft on the traffic display with own aircraft flight-level altitude annunciations for a period of 15 seconds. During the 15 second period, own aircraft flight-level altitude also shows on the traffic display. After 15 seconds, own aircraft flight-level altitude goes out of view from the display and intruder aircraft altitude annunciations change to relative altitude annunciations.(NOTE 4.)If during the 15 second period after the FL switch is pushed and released, a new RA or TA category aircraft is detected by TCAS, the 15 second flight-level display is made unserviceable and relative altitudes reappear.
Page 881 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 18. CTA-81A Control Unit Controls and Indicators (cont)Control/Indicator(See Figure 10) FunctionTCAS RANGE Switch Four position rotary switch. Sets 15, 10, 5, or 3 nautical mile (NM) range scale for the traffic display. The set display scale is annunciated 15 NM, 10 NM, 5 NM, or 3 NM on the traffic display.(NOTES 5., 6., and 8.)ABOVE/NORM/BELOW Switch Three position toggle switch. Sets relative altitude display limits for nonthreat category aircraft (open-white diamond symbols) on the traffic display.(NOTE 7.) ABOVE Position Sets display of nonthreat aircraft maximum +8700 feet above own aircraft and down to -2700 feet below own aircraft. ABOVE is annunciated on the traffic display. NORM Position Sets display of nonthreat aircraft maximum +2700 feet above own aircraft and down to -2700 feet below own aircraft on the traffic display. BELOW Position Sets display of nonthreat aircraft down to -8700 feet below own aircraft and maximum +2700 feet above own aircraft. BELOW is annunciated on the traffic display. ATC IDENT Pushbutton SwitchWhen this switch is pushed and released, in 18 seconds a Special Position Identifier (SPI) is inserted for 18 seconds into the transponder Mode A, DF-4, DF-5, DF-20 and DF-21 Mode S replies to interrogations from ground stations. If the switch is held pushed longer than 18 seconds, the SPI bit is transmitted while the switch is pushed, plus an additional 18 seconds after the switch is released. The SPI pulse is not used by TCAS.
Page 891 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 18. CTA-81A Control Unit Controls and Indicators (cont)Control/Indicator(See Figure 10) FunctionCode Select Knobs Lets selection of transponder identification code. The transponder inserts this code into replies to Mode A interrogations and Mode S ATC identification requests from ground stations. The ATC IDENT code is not used by TCAS.ATC IDENT Code Display Shows transponder ATC identification code set by the Code Select Knobs and annunciates which transponder is selected by the ATC 1-2 Switch.ATC FAIL Illuminates (amber) for some failure conditions found by the Mode S transponder (refer to TRA-67 ATC Mode S Transponder System Maintenance Manual I.B. 1167 for the details).NOTES:1: TCAS operating modes are requested from the transponder/TCAS control unit (i.e. TA/RA mode is requested by turning the function selector switch to TA/RA). The TCAS processor can or can not go into the requested mode dependent on prevailing conditions. For example: If TA/RA mode is requested from the control unit and own aircraft is below 500 feet AGL, TCAS automatically defaults to TA ONLY mode (TCAS sensitivity level No. 2) regardless of the TA/RA mode request from the panel.2. TCAS can be strapped to show all traffic, all the time or when a TA or RA is present.3. If own aircraft is below 500 feet AGL, TCAS defaults to TA ONLY mode.4. Holding the FL switch pushed for longer than 15 seconds will not show flight level altitudes for longer than 15 seconds.5. The range at which resolution or traffic advisories are generated by TCAS is unaffected by the TCAS RANGE switch.6. The presence of intruder aircraft categorized RA or TA that are more than the set display range is indicated by 1/2 target symbols at the edge of the screen. An RA OFF scale or TA OFF scale annunciation on the traffic display is shown. The position of the 1/2 symbol shows the approximate bearing of the intruder. The 1/2 symbol color and shape shows if the off-scale intruder is an RA or TA (1/2 red square for off-scale RA; 1/2 yellow circle for off-scale TA). When this occurs, the aircraft symbol can be shown by increasing the set range on the TCAS RANGE switch.7. RA, TA, and proximity category aircraft displays are inaffected by the ABOVE/NORM/BELOW switch (RA and TA aircraft in +8700 feet of own aircraft are shown regardless of the ABOVE/NORM/BELOW switch position. Proximity category aircraft are always in +1200 feet altitude of own aircraft).8. TCAS RANGE switch is not supplied on all versions of the CTA-81A. When a PPI, TA/VSI, or dedicated traffic display having optional range selectors is used, range selection is made at the traffic display. Other versions have range selections to 40 nautical miles.
Page 901 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.CTA-81B Control Unit (Typical) (Used With One Mode S Transponder and One ATCRBS Transponder)Figure 11 Refer to Table 19 for the CTA-81B Control Unit controls and indicators.
Page 911 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 19. CTA-81B Control Unit Controls and IndicatorsControl/Indicator(See Figure 11) FunctionFunction Selector Switch Rotary switch. Controls operating modes of one Mode S transponder (ATC 1 positions) and one ATCRBS transponder (ATC 2 positions). Requests TCAS operating modes (NOTES 1. and 2.) ATC 1 TEST Position Holding the switch in spring-loaded TEST position for one second starts the TCAS and Mode S transponder Functional self-test. If TCAS processor Functional Test Inhibit program pin is strapped, TCAS functional test is prevented while the aircraft is airborne. The TCAS flag shows TCAS on the RA/VSI display during the functional test (approximately 12 seconds). The traffic display shows TEST. A test pattern shown on the traffic display lets verification of each type of intruder symbol. During the first three seconds of the functional test, a lamp test is done on all segments of the RA/VSI. If a failure is found during functional test, the TCAS flag continues to show TCAS. Following the lamp test, a set test command is shown until end of test. ATC 1 STBY Position The ATC 1 STBY position puts the Mode S transponder, ATCRBS transponder, and TCAS in STANDBY mode. The Mode S transponder power is applied, but does not transmit squitters or reply to interrogations in STANDBY mode. In STANDBY mode, all TCAS broadcast, surveillance, and tracking operations are made unserviceable and the traffic display is erased but for a TCAS STBY annunciation. The ATCRBS transponder is on in STANDBY mode, but does not respond to interrogations.
Page 921 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 19. CTA-81B Control Unit Controls and Indicators (cont)Control/Indicator(See Figure 11) FunctionFunction Selector Switch (cont) ATC 1 ON Position In-Flight - Turns on the Mode S transponder to full on condition, removes power from ATCRBS transponder, and puts the TCAS in STANDBY mode (TCAS sensitivity level No. 1). The Mode S transponder transmits squitters and replies to Mode S, ATCRBS Mode C, and Mode A interrogations.The Mode S transponder reply to the Mode C and Mode S interrogations does not contain an altitude report if the ALT SOURCE switch is set to the OFF position. The transponder reply to Mode A interrogations contains the ATC transponder code (normal Mode A reply). All the TCAS broadcast, surveillance, and tracking functions are made unserviceable. The traffic display screen is erased, but for a TCAS STBY annunciation.On-the-Ground - Power is not applied to ATCRBS transponder. The Mode S transponder squitters and replies fully to the Mode S interrogations. Depending on the Mode S transponder strapping, the transponder replies or does not reply to ATCRBS Mode C and Mode A interrogations. The transponder reply to ATCRBS and Mode S interrogations will not contain an altitude report if the ALT SOURCE switch is set to the OFF position. The transponder reply to Mode A interrogations contains the ATC transponder code. TCAS is in STANDBY mode (sensitivity level No. 1). The traffic display screen is erased but for a TCAS STBY annunciation. ATC 1 TA Position In-Flight - Turns on the Mode S transponder to full on condition, removes power from the ATCRBS transponder, and puts the TCAS in TA ONLY mode (traffic advisory only mode).
Page 931 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 19. CTA-81B Control Unit Controls and Indicators (cont)Control/Indicator(See Figure 11) FunctionFunction Selector Switch(cont) ATC 1 TA Position (cont)(TCAS sensitivity level No. 2). The Mode S transponder transmits squitters and replies to the Mode S, ATCRBS Mode C, and Mode A interrogations. The TCAS broadcasts and does all the Mode S and ATCRBS surveillance and tracking functions. The TCAS supplies the traffic displays for TA, proximity, and nonthreat category aircraft (NOTE 3 for exception), but does not categorize or show one aircraft as a RA threat symbol. The TCAS gives the traffic advisory alerts, but does not give resolution advisory alerts (for example, voice RA alerts or RA indications on the traffic display are not given). A TA ONLY mode annunciation comes into view on the traffic display.On-the-Ground - Power is not applied to ATCRBS transponder. The Mode S transponder squitters and replies fully to the Mode S interrogations. Depending on the Mode S transponder strapping, the transponder replies fully or does not reply to ATCRBS Mode C and Mode A interrogations. Depending on the TCAS strapping, TCAS goes into STANDBY mode (traffic display screen is erased, but for a TCAS STBY annunciation), or is in TA mode (TA ONLY mode annunciation shows on the traffic display). TA ONLY mode operation on-the-ground is same as TCAS TA ONLY mode operation in-flight as shown above. ATC 1 TA/RA Position In-Flight - Turns on the Mode S transponder to full on condition and removes the power from ATCRBS transponder. If own aircraft is above 500 feet AGL, the TCAS goes into sensitivity level No. 4 through No. 7 dependent on own aircraft altitude (refer to Table 7).
Page 941 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 19. CTA-81B Control Unit Controls and Indicators (cont)Control/Indicator(See Figure 11) FunctionFunction Selector Switch(cont) ATC 1 TA/RA Position (cont)The Mode S transponder transmits squitters and replies fully to the Mode S, ATCRBS Mode C, and Mode A interrogations. The TCAS broadcasts and does all the Mode S and ATCRBS surveillance and tracking functions. The TCAS gives the traffic displays for RA, TA, proximity, and nonthreat category aircraft (NOTE 3.), gives RA and TA alerts, and transmits resolution advisories on the TA/VSI or RA/VSI.(NOTE 4.)On-the-Ground - The Mode S transponder squitters and replies fully to Mode S interrogations. Depending on the Mode S transponder strapping, the transponder replies fully or does not reply to the Mode S, ATCRBS Mode C, and Mode A interrogations. The power is removed from ATCRBS transponder. The TCAS defaults to TA ONLY mode (TCAS sensitivity level No. 2) and functions as shown for the Function Selector switch ATC 1 TA Position (on-the-ground), in this table. ATC 2 ON Position Puts the Mode S transponder and the TCAS in STANDBY mode and turns on the ATCRBS transponder to full on condition. ATC 2 STBY Position Puts the Mode S transponder, the TCAS, and the ATCRBS transponder in STANDBY mode. ATC 2 TEST Position Starts functional test for the ATCRBS transponder. Refer to the ATCRBS transponder maintenance manual for the details. The Mode S transponder and TCAS stay in STANDBY.
Page 951 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 19. CTA-81B Control Unit Controls and Indicators (cont)Control/Indicator(See Figure 11) FunctionALT SOURCE 1/2 Switch Sets one of two barometric altimeter sources to the activated Mode S or ATCRBS transponder. The OFF POSITION makes unserviceable the altitude squawk (two altitude sources only). FL Pushbutton Switch Spring-loaded pushbutton switch. When pushed and released, the relative altitude annunciations for the intruder aircraft are replaced on the traffic display with flight-level altitude annunciations for a period of 15 seconds. During the 15 second period, own aircraft flight-level altitude also comes into view on the traffic display. After 15 seconds, own aircraft flight-level altitude goes out of view from the display and the intruder aircraft altitude annunciations change to relative altitude annunciations. (NOTE 5.)If a new RA or TA category aircraft is detected by the TCAS during the 15 second period, the 15 second flight-level display is made unserviceable and relative altitudes reappear.TCAS RANGE Switch Four position rotary switch. Sets 15, 10, 5, or 3 nautical mile range scale for the traffic display. The set display scale is shown as 15 NM, 10 NM, 5 NM, or 3 NM on the traffic display. (NOTES 6., 7., and 9.)ABOVE/NORM/BELOW Switch Three position toggle switch. Sets relative altitude display limits for nonthreat category aircraft (open-white diamond symbols) on the traffic display. (NOTE 8.) ABOVE Position Sets display of nonthreat aircraft maximum +8700 feet above own aircraft and down to -2700 feet below own aircraft. ABOVE is shown on the traffic display.
Page 961 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 19. CTA-81B Control Unit Controls and Indicators (cont) Control/Indicator(See Figure 11) Function NORM Position Selects display of nonthreat aircraft up to +2700 feet above own aircraft and down to -2700 feet below own aircraft on traffic display. BELOW Position Selects display of nonthreat aircraft down to -8700 feet below own aircraft and up to -2700 feet above own aircraft. BELOW is annunciated on the traffic display screen.ATC IDENT PushbuttonSwitchWithin 18 seconds after the switch is pushed and released, an SPI is put into the transponder Mode A and DF-4, DF-5, DF-20 and DF-21 Mode S replies to the interrogations from ground stations. The SPI is shown for 18 seconds. If the switch is held pushed longer than 18 seconds, the SPI bit is transmitted while the switch is pushed, plus an additional 18 seconds after the switch is released. The SPI pulse is not used by the TCAS.Code Select Knobs Lets selection of transponder identification code. The transponder inserts this code into replies to Mode A interrogations or Mode S ATC identification requests from ground stations. The ATC IDENT code is not used by TCAS.ATC IDENT Code Display Shows transponder ATC identification code set by the Code Select Knobs and shows which transponder is selected by the function selector switch. The display gives an R annunciation when selected transponder is replying to interrogations.ATC FAIL Indicator Lamp Illuminates (amber) for some failure conditions found by the Mode S transponder (refer to TRA-67 ATC Mode S Transponder System Maintenance Manual I.B. 1167 for the details).
Page 971 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 19. CTA-81B Control Unit Controls and Indicators (cont)Control/Indicator(See Figure 11) FunctionNOTES:1. The TCAS operating modes are requested from the transponder/TCAS control unit (For example, TA/RA mode is requested by turning function selector switch to TA/RA). The TCAS processor can or can not go into the requested mode dependent on prevailing conditions. For example: If TA/RA mode is requested from the control unit and own aircraft is below 500 feet AGL, the TCAS automatically defaults to TA ONLY mode (TCAS sensitivity level No. 2) regardless of the TA/RA mode request from the panel.2. In-flight or on-the-ground status of own aircraft is calculated with the weight-on-gear (air/ground) strut switch input to the transponder and TCAS processor.3. The TCAS can be strapped to show all the traffic, all the time or only when a TA or RA is present.4. If own aircraft is below 500 feet AGL, the TCAS automatically ignores the TA/RA position of the switch and defaults to TA ONLY mode. The TCAS functions as shown for the ATC 1 TA position (in-flight) of the Function Selector Switch in this table.5. Holding the FL switch pushed for longer than 15 seconds will not show flight level altitudes for longer than 15 seconds.6. The range at which RAs or TAs are generated by the TCAS is unaffected by the TCAS RANGE switch.7. The presence of the intruder aircraft that are categorized as RA or TA and are more than the set display range, is shown by 1/2 target symbols at the edge of the screen. The position of the 1/2 symbol shows the approximate bearing of the intruder. The 1/2 symbol color and shape shows if the off-scale intruder is an RA or TA (1/2 red square for off-scale RA; 1/2 yellow circle for off-scale TA). When this occurs, the aircraft symbol can be shown by increasing the set range on the TCAS RANGE switch.8. RA, TA, and proximity category aircraft displays are unaffected by the ABOVE/NORM/BELOW switch. (RA and TA aircraft within +8700 feet of own aircraft are shown regardless of the ABOVE/NORM/BELOW switch position. Proximity category aircraft are always within +1200 feet altitude of own aircraft).9. The TCAS RANGE switch is not supplied on all versions of the CTA-81B. When a PPI, TA/VSI, or dedicated traffic display having optional range selectors is used, range selection is made at the traffic display. Other versions have range selection to 40 nautical miles.
Page 981 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.CTA-100A ControllersFigure 12
MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMPage 99 1 Dec 200334-45-47Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 20. CTA-100A Control Unit Controls and IndicatorsControl/Indicator(See Figure 12) FunctionMode Select Switch Rotary switch. Supplies mode control for the transponders and TCAS processor. The mode selector switch can put the transponders into standby mode or active mode with altitude interrogation on or off. The mode selector switch is also used to set the TA (Traffic Advisory) or TA/RA (Traffic Advisory/Resolution Advisory) modes for the TCAS processor. The position of the mode selector switch finds the correct ARINC 429 control data to transmit to the Mode S transponders and the TCAS processor. The switch supplies a momentary TEST position, which lets the personnel start a TCAS system test. (NOTE 1.) TEST Position The TEST mode is to start the TCAS system test. The TEST mode position is a momentary switch position. When the rotary switch is held in the TEST position for a minimum of one second, the CTA-100A outputs SSM = FUNCTIONAL TEST on all ARINC 429 labels. When the rotary switch is released, the CTA-100A starts the previous SSM transmission. STANDBY Position The Standby/On discrete output for transponder No. 1 and transponder No. 2 are set to standby.
Page 1001 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 20. CTA-100A Control Unit Controls and Indicators (cont)Control/Indicator(See Figure 12) FunctionMode Select Switch (cont) ALT OFF Position The STANDBY/On discrete output is set to ON for the set transponder. BIT 11 of ARINC label 016 is set to 1 to inhibit altitude reporting. ALT ON Position The STANDBY/On discrete output is set to ON for the set transponder. BIT 11 of ARINC label 016 is set to 0 to enable altitude reporting. TA Position In-Flight - Turns on the Mode S transponder to full on condition and puts the TCAS in TA ONLY mode (traffic advisory only mode) (TCAS sensitivity level No. 2). The Mode S transponder transmits squitters and replies fully to Mode S, ATCRBS Mode C, and Mode A interrogations. The TCAS broadcasts and does all Mode S and ATCRBS surveillance and tracking functions. The TCAS gives the traffic displays for TA, proximity, and nonthreat category aircraft (NOTE 2. for exception), but does not categorize or show one aircraft as a RA threat symbol. The TCAS gives the traffic advisory alerts, but does not give resolution advisory alerts (for example, voice RA alerts or RA indications on the traffic display are not given). A TA ONLY annunciation comes into view on the traffic display.On-the-Ground - The Mode S transponder squitters and replies fully to Mode S interrogations. Depending on transponder strapping, transponder replies fully or does not reply to ATCRBS Mode C and Mode A interrogations. Depending on the TCAS strapping, TCAS goes into TA ONLY mode or STANDBY mode (traffic display screen is erased but for a TCAS STBY mode annunciation shows on the traffic display). TA/RA Position In-Flight - Turns on the Mode S transponder to full on condition. If own aircraft is above 500 feet AGL, the TCAS goes into sensitivity level No. 4 through No. 7 dependent on own aircraft altitude (refer to Table 7). The Mode S transponder transmits squitters and replies fully to Mode S, ATCRBS Mode C, and Mode A interrogations. The TCAS broadcasts and does all Mode S and ATCRBS surveillance and tracking functions. The TCAS gives traffic displays for RA, TA, proximity, and nonthreat category aircraft (NOTE 2.), issues RA and TA alerts, and gives resolution advisories on the TA/VSI or RA/VSI. A TA/RA annunciation shows on the PPI or dedicated traffic display. A mode annunciation is not given on the TA/VSI for TA/RA mode.
MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMPage 101 1 Dec 200334-45-47Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 20. CTA-100A Control Unit Controls and Indicators (cont)Control/Indicator(See Figure 12) FunctionMode Select Switch (cont) TA/RA Position (cont)(NOTE 3.)On-the-Ground - The Mode S transponder squitters and replies fully to Mode S interrogations. Depending on transponder strapping, the transponder replies fully or does not reply to ATCRBS Mode C, Mode A, or Mode S interrogations. The TCAS defaults to TA ONLY mode (TCAS sensitivity level No. 2) and functions as shown for the TA position (on-the-ground) of the Function Selector Switch in this table. IDENT Pushbutton The IDENT pushbutton is used to show the aircraft identification symbol shown on the ATC display. The IDENT button has priority over all other CTA-100A functions. Whenever the IDENT button is operated, the CTA-100A must cancel the current task, transmit the IDENT command, and default to the ATC code display mode.ATC SELECT Pushbutton The ATC SELECT pushbutton is used to set either Transponder No. 1 or Transponder No. 2 in the TCAS system. Each operation of the ATC SELECT pushbutton alternately sets the Transponder No. 1 or Transponder No. 2. The indication of the set transponder is given by annunciators indicating either a 1 or 2. The CTA-100A controls the annunciatiors and transponder selection status.ALT Select Pushbutton The ALT 1/2 select pushbutton is used by the personnel to set the No. 1 or No. 2 Mode S transponder altitude source input. Each operation of the ALT 1/2 select pushbutton alternately sets the No. 1 or No. 2 input. The indication of the set transponder is given by annunciators indicating either a 1 or 2. The CTA-100A software controls the annunciators and altitude source input selection status.(NOTE 4.)DISPLAY Screen The CTA-100A controller has a display with eight alpha-numeric characters. The display supplies white segments against a black background. For an NVIS compatible version, green segments against a black background are used. The display intensity is controlled by an ambient light sensor to make sure readability in all ambient light conditions.
Page 1021 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 20. CTA-100A Control Unit Controls and Indicators (cont)Control/Indicator(See Figure 12) FunctionABOVE/BELOW Pushbutton The ABOVE/BELOW pushbutton is used to set relative altitude display limits for nonthreat category aircraft on the traffic display. (NOTE 4.)RNG DN PushbuttonRNG UP PushbuttonThe RANGE pushbutton is used to set the nautical mile range scale for the TCA display. Each operation of the RANGE pushbutton toggles through a pre-specified set of mile ranges. When the RANGE pushbutton is operated, the CTA-100A will toggle to the subsequent highest range value.(NOTE 4.)FCN Pushbutton The function of the FCN pushbutton is to set the function modes that use the CTA-100A display. When the FCN pushbutton is pushed, the CTA-100A sets and shows the subsequent available function mode.RIGHT (>) Pushbutton The RIGHT pushbutton shows current Flight identification when Flight ID mode is set on the display. The pushbutton is also used to set to the subsequent character position for Flight ID data entry before the timeout period.LEFT (<) Pushbutton The LEFT pushbutton shows the current Flight identification when The Flight ID mode is set in the display. The selection will backspace over previous character in ATC data entry mode and backspace over previous character in The Flight ID mode. The LEFT pushbutton starts the data entry mode for Flight ID when the current Flight ID value is on the display -- backspaces over all but the first two characters.
MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMPage 103 1 Dec 200334-45-47Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 20. CTA-100A Control Unit Controls and Indicators (cont) Control/Indicator(See Figure 12) FunctionENT Pushbutton The ENT pushbutton is for showing current Flight identification when the Flight ID mode is set in the display. The ENT pushbutton will confirm the Flight ID data entry and send the value along the ARINC 429 databus. Selection of ENT will confirm the ATC code data entry for rotary control versions of the CTA-100A.NUMERIC KEYPAD (Keypad CTA-100A version only)The NUMERIC KEYPAD consists of pushbuttons for each number 0 through 9 and lets a procedure for entering transponder codes and/or flight identification data into the CTA-100A display. The NUMERIC KEYPAD buttons 0 through 7 have priority over all other CTA-100A functions other than for the Flight ID data entry mode. When a button (0-7) is operated, the CTA-100A will cancel the current task, and immediately change into ATC code data entry mode. The numeric pushbutton that was initially pushed will become the first digit of the new ATC code.FAIL Annunciator The FAIL annunciator will come on when the set transponder and related TRANSPONDER FAIL (No. 1 or No. 2) discrete input is in operation. The annunciator color will be amber.ROTARY CONTROL Knob (Rotary control CTA-100A version only)The data entry of the ATC code will use the dual concentric rotary control. The data is recorded one digit at a time, using the outer knob to forward to the subsequent digit. An underline is used to identify each digit that requires entry. The inner knob is used to move through the numbers 0-7 for each digit of the ATC code. After each digit entry, any clockwise turn of the outer knob will forward the data entry one digit to the right. The outer knob can be used to backspace over incorrectly recorded data. For each detent in the counterclockwise direction, the display will backspace one digit. After the ATC four digit code has been entered into the display, the code will be accepted into the system one of three procedures. The ENT pushbutton can be actuated, the outer knob selector can be rotated clockwise, or a 5.0 +/- 0.1 second timeout period stops if none of the two items has occurred.NOTES:1. In-flight or on-the-ground status of own aircraft is determined by the weight-on-gear (air/ground) strut switch input to the transponder and TCAS processor.2. The TCAS can be strapped to show all the traffic, all the time or only when a TA or RA is present.3. If own aircraft is below 500 feet AGL, the TCAS defaults to TA ONLY mode.4. Not installed on all versions of CTA-100A.
Page 1041 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.E. TA/VSIThe TA/VSI displays resolution advisory maneuvering data to the pilot during threat conditions. The TA/VSI also supplies a display of airspace traffic conditions in the traffic display range and altitude volume limits. See Figure 13.(1) Resolution AdvisoriesResolution advisories can be corrective or preventive and positive or negative.A corrective advisory requires a vertical maneuver and is always shown with red and green arcs. The red arc shows the vertical speed rates that are not permitted in the presence of the RA. The green arc shows the vertical speeds that must be flown during a corrective advisory. A preventive advisory requires no maneuver and is represented with only a red arc. (Refer to the TCAS Pilot Manual.)The limits of the red arc are supplied to the TA/VSI from the TCAS through the 429 bus. The limits of the green arc are not supplied from TCAS. The green arc will be immediately adjacent to the red arc and have a width of approximately equal to the space between 1500 ft/min and 2000 ft/min.It is possible to show two red arcs at the same time with an RA for example, do not climb more than 1000 feet and do not descend more than 2000 feet. Since one procedure can be corrective, the green arc will be immediately adjacent to the red arc representing the corrective advisory. If the two procedures are preventive, only the red arcs are present. (Refer to Table 21 for TA/VSI RAs and Audio Messages.)(2) Traffic DisplayThe traffic display supplies the following data:• The standard symbol has own aircraft symbol, and a two mile range ring marker.• Resolution advisory, traffic advisory, proximity, and nonthreat category aircraft symbols that show the range, bearing (if tracking is occurring on a directional antenna), and altitude (if the intruder aircraft is reporting altitude).• Numerous text message annunciations relating to the presence of TAs and RAs that can not be displayed by a symbol because bearing is not available. TAs and RAs that are outside the range scale of the traffic display show operating modes and fail conditions.NOTE: A pilot manual supplied by Honeywell gives the TA/VSI operation in detail.
Page 1051 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.TA/VSI Controls and IndicatorsFigure 13
Page 1061 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 21. TA/VSI RA’s and Audio MessagesResolution Advisory Audio MessageCLIMB Climb, ClimbDESCENT Descend, DescendCROSSOVERCLIMBClimb, Crossing Climb--Climb, Crossing ClimbCROSSOVERDESCENTDescend, Crossing Descend--Descend, Crossing DescendVERTICAL SPEED RESTRICTED(CLIMBING OR DESCENDING)Adjust Vertical Speed, AdjustANY WEAKENING ORSOFTENING OF AN RAAdjust Vertical SpeedPREVENTATIVE ADVISORY Monitor Vertical SpeedMAINTAIN EXISTINGVERTICAL SPEEDMaintain Vertical Speed,MaintainMAINTAIN EXISTING VERTICALSPEED WHILE CROSSINGTHREAT'S ALTITUDEMaintain Vertical Speed,Crossing MaintainTHE FOLLOWING RESOLUTION ADVISORIES REQUIRE2.5 SECONDS RESPONSE TIME AND UP TO 0.35 G.CHANGE FROM CLIMB TO DESCENTDescend, Descend NOW--Descend, Descend NOWCHANGE FROM DESCENT TO CLIMBClimb, Climb NOW--Climb, Climb NOWINCREASE CLIMB RATE Increase Climb--Increase ClimbINCREASE DESCENT RATE Increase Descent--Increase Descent
Page 1071 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.F. RA/VSIThe RA/VSI shown in Figure 14 gives resolution advisories same as the TA/VSI, but does not supply a traffic display.The RA/VSI gives resolution advisories that show the vertical speeds to be avoided to keep or get safe vertical separation.An electro-mechanical pointer and vertical speed scale, which are standard VSI features, show the present vertical speed of own aircraft. The RA/VSI includes a microprocessor based control unit and curved red and green eyebrow lamp segments around the edge of the vertical speed scale. Maneuvering resolution advisories are shown on the RA/VSI by illuminating a related number of the red lamp segments. These advisories show the vertical speed rates to be avoided. Green arcs are illuminated to show the vertical speeds that must be flown during an advisory. (Refer to the TCAS pilot manual.)The VSI for the TCAS applications has flags that show the TCAS operating conditions.The Honeywell made RA/VSI receives resolution advisory and flag control data from the TPA-100A TCAS processor through a high-speed ARINC 429 data link.RA/VSI display units are used as the resolution advisory display when TCAS traffic displays are given on a different display, for example, a PPI Radar/TCAS display or dedicated TCAS traffic display.NOTE: A pilot manual supplied by Honeywell gives the RA/VSI operation in detail.G. Dedicated TCAS Traffic DisplayThe ITA-81A Traffic Display shown in Figure 15 gives a traffic display same as the TA/VSI, but does not give resolution advisories. As shown in Figure 15, the traffic display can be operated as a pop-up display, showing all intruders when a TA or RA is in progress. To push the optional TCAS AUTO pushbutton erases the screen and stays blank (but for the mode annunciation) until TA or RA traffic comes into view. Then all TCAS traffic is shown. To push the TCAS AUTO pushbutton again returns the display to full-time display mode. Other optional controls on this unit are RANGE Select push-buttons and ABOVE/BELOW push-buttons.NOTE: A pilot manual supplied by Honeywell describes the dedicated TCAS traffic display operation in detail.
Page 1081 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.RA/VSI Controls and IndicatorsFigure 14 Two FlagsTCAS Flag Color Description RA OFF Black RA OFF on White Shows an impairment of the TCAS function which is due to a loss of essential aircraft data, or TCAS data, indicator power OFF, TCAS in STBY mode or TCAS in TA mode. Also appears when VSI appears. NORMAL Black Shows normal operation of TCAS functions. TCAS Black TCAS on Amber Shows a loss of, or invalid digital TCAS data or SSM set to Failure Warning. VS Flag NORMAL Black Shows normal operation of VSI functions. VSI Black VSI on Amber Shows a loss of or invalid digital Vertical Speed data, invalid flag for analog data sources, detected internal failures of the RA/VSI, or power loss to the RA/VSI.
Page 1091 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.H. PPI Radar/TCAS DisplayThe PPI Radar/TCAS display shown in Figure 16 gives its usual separate weather radar display and can be manually controlled to show an isolated TCAS traffic display or a total weather radar/TCAS presentation.The PPI Radar/TCAS display integration into the CAS-100 system is given in isolated manuals recorded in Table Intro-1.NOTE: A pilot manual supplied by Honeywell gives the PPI Radar/TCAS display operation in detail.I. Optional Aural/Lamp Advisory OutputsOptional aural and lamp traffic advisory and resolution advisory output are available. The advisories can be activated by connecting the external tone generators and/or indicator lamps to the applicable rear connector pins on the TCAS processor.The aural advisory output is to supply tones that accompany corrective, preventive, and traffic advisories given by the TCAS processor. The started aural advisory discrete output is given for a 1.0 ± 0.2 second period. When the aural advisory discrete output is for an installation, the Audio Tone Enable Program pin must be strapped. This strap supplies a 1.0 ± 0.2 second interval of the synthesized voice output to be properly phased with the aural advisories. The lamp advisory output can be to operate annunciator lights that identify the advisory as a corrective, preventive, or traffic advisory. The output stays on during the advisory unless cancelled (see paragraph J., below).J. Audio Message AlertsAudio message alerts given by TCAS on the cockpit audio system are shown in Figure 13.K. TCAS Processor and Mode S Transponder Front Panel Indicators and TEST Switch These front panel indicators and TEST switches give a fault isolation maintenance aid in the failure conditions where the traffic advisory display subsystem is defective and cannot show the TCAS failure annunciations. Refer to the TESTING AND FAULT ISOLATION and the MAINTENANCE PRACTICES sections of this manual for the details.L. Optional Advisory Cancel SwitchThis momentary switch cancels in operation advisory alert conditions.
Page 1101 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.M. Range Selection and Range RingsThe traffic advisory display range selection is controlled externally, through the data input to the display on the ARINC 429 bus, or internally, using a front panel selector switch (PPI weather/traffic display). The range selection can be controlled by optional front panel pushbutton switches (TA/VSI or dedicated traffic display). The Range rings shown are a function of range set if the range selection is made at a distance or locally. Table 22 summarizes range ring distances for each possible range that can be selected on the different types of traffic displays available.NOTE: The Range selections more than 34 nautical miles are only possible on PPI weather/traffic displays. For these displays, the range ring data in Table 22 is applicable when the display is in the TCAS mode, which shows only TCAS data.Table 22. Range Rings Displayed vs. Selected RangeSelected Range (NM)Range Rings (NM)2 3 510152025 30 403XX5XX10 X X X15 XXX20 X X X25 X X X30 X X X40 X X X50 X X X60 X X X80 X X X100 X X X120 X X150 X X160 X X180 X X200 X X240 X300 X320 X
MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEM34-45-47 ITA-81A Traffic Display Controls and IndicatorsFigure 15Page 111/1121 Dec 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEM34-45-47 PPI Radar/TCAS Display Controls and IndicatorsFigure 16Page 113/1141 Dec 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.
Page 10011 Dec 200334-45-47 MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.TESTING AND FAULT ISOLATION1. GeneralFault isolation is the function to find the source of a TCAS failure at the assembly level (black box level) or the aircraft wiring level. Fault isolation for CAS-100 includes the performance of TCAS functional tests and the inspection of the TCAS failure indicators. Then the fault isolation includes the performance of applicable removal and replacement, or the aircraft wiring repair procedures to correct the problem.CAS-100 failures can be indicated by the failure annunciations on the PPI Radar/TCAS display or dedicated traffic display unit CRT. The failures are also shown by an electro-mechanical fail flag on the RA/VSI unit, and failure indicator lamps on the front panels of the TCAS components. TCAS failures are sensed, and the applicable failure indicator is started. The failure indicator is started as a result of full-time TCAS Built-In-Test Equipment that monitors and because of manually started TCAS Functional Self-Test monitoring.Fault isolation is usually done on the ground, as a result of failures shown during post-installation, preflight testing, or malfunctions that were seen during the flight operation.2. Fault IsolationA. GeneralThe TCAS processor can find the malfunctions of the TCAS components that decrease or prevent possible collision avoidance protection. The Mode S transponder can find the malfunctions in the Mode S transponder system that decrease usual TCAS functions. During a transponder system failure, the transponder causes the transponder FAIL or ATC FAIL indicator on the control unit to light. The transponder also communicates the failure status to the TCAS processor. A failure of the Mode S or TCAS system during usual operation causes these effects by the TCAS processor:• Gives an indication to the flight crew that an unusual condition exists.• Causes Mode S transmissions that report own aircraft status to show that own aircraft has no on-board resolution capability.• Prevents interrogations by own aircraft TCAS.• Stops the usual TCAS display functions.NOTE: Refer to pilot manual for specified failure indications that show on TA/VSI, RA/VSI, dedicated TCAS traffic display, etc.
Page 10021 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.There are two different procedures to start and monitor functional self test of the TCAS/Mode S system. The first is started at the transponder/TCAS control unit and the sensed failures are shown on the traffic display, but for the IVA-81A/D TA/VSI. The second procedure is started in the equipment bay using the two buttons found on the front panel of the TCAS processor, and then monitoring the TCAS Processor front panel LED display.Prior to performing TCAS/Mode S system self test, make sure that these aircraft systems are energized and operate without the failure flags on the applicable cockpit instruments:• Air Data Systems• Radio Altimeter Systems• Altitude (Vertical Gyro) Systems• Heading (Compass) SystemsIf the attitude and point data supplied to the TCAS system is from an AHRS, IRS, or INS, they must be aligned and in operate mode.B. Using Transponder/TCAS Control UnitNOTE: If a PPI Radar/TCAS display is used as the traffic display and has a TCAS mode on the selector switch, it must be turned to the TCAS position for the test. If not, the selector switch must turn to the OFF position to let the traffic display set discrete (from the TCAS processor) and turn the display ON. It takes approximately 5 seconds for the display to get warm after the test is started.(1) Dual Mode S Equipped AircraftThe aircraft with two Mode S units, set the transponder selector on the CTA-81A Control Unit to Position 1 to test transponder 1. Turn the function selector counterclockwise to the TEST position (ATC 1 TEST position on CTA-81B) and hold the switch in this position for the minimum one second. The self-test continues automatically for approximately 12 seconds. On the CTA-81 ( ) Control Unit, the display window shows ATC12R and the ATC FAIL lamp comes on for approximately 3 seconds.(2) No Malfunctions ReportedIf there are no malfunctions, the test sequence will be as follows:(a) A test pattern comes into view on the displays to check each type of intruder symbol. See Figure 1001.(b) For the aircraft that have RA/VSI:1During the first seconds of the test, the RA/VSI red and green circumference lamps (climb/descend indicators) come on together. The TCAS flag is in the view during the test period.
Page 10031 Dec 200334-45-47 MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Test PatternFigure 1001 2After the RA/VSI sequence lamp test, the red and green climb/descend lamps show a set test command that shows a typical resolution advisory during the remaining test sequence.NOTE: The missing correct vertical speed input causes the VSI flag to come into the view on the RA/VSI. If a TA/VSI is used, the legend VSI comes into the view on the display. A TCAS processor failure causes the TCAS flag to come into the view on the RA/VSI, and the TCAS to come into the view on the TA/VSI.(c) For the aircraft that have TA/VSIThe TA/VSI shows a set Resolution Advisory and the traffic symbol test pattern. A TEST message is shown.(d) For the aircraft that have PPI Radar/TCAS or dedicated display:The PPI or dedicated display shows the TCAS display test pattern and TEST is shown.(e) At the correct end of the self-test, the TCAS processor output on the audio bus starts the synthesized voice message, TCAS System Test OK.
Page 10041 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.(3) Failure Detected During Self-TestIf a failure is found during self-test, the voice message output from the TCAS processor is, TCAS System Test Fail. The PPI Radar/TCAS display or dedicated display will show the failed system component(s). Possible traffic display fault annunciations are as follows:• TCAS PROCESSOR • XPNDR TOP ANT• UPPER ANTENNA • XPNDR LOWER ANT• LOWER ANTENNA • XPNDR TCAS DATA• RADIO ALT No. 1 • XPNDR CONTROL DATA• RADIO ALT No. 2 • XPNDR CONTROL DATA• RADIO ALT No. 1 and No. 2 • XPNDR CONTROL DATA• No. 1 XPNDR DATA BUS • No. 1 XPNDR ALT DATA• No. 2 XPNDR DATA BUS • No. 2 XPNDR ALT DATA• TRAFFIC DISPLAY • ATTITUDE•RA DISPLAY No. 1• RA DISPLAY No. 2 • HEADING• RA DISPLAY No. 1 and No. 2 • NO TCAS (NO DATA on some versions)• TCAS FAIL(4) Test Results Not to SpecificationIf self test results are not to specification, do these:(a) If PPI or dedicated display is used, check and record the fault annunciation(s). For the Mode S transponder system and TCAS line maintenance troubleshooting procedures, refer to Tables 1001 and 1002.(b) Do the Mode S and TCAS processor self tests on the front of each unit to make the problem clear in non-PPI or dedicated display aircraft.(5) Dual Mode S Equipped AircraftSet the transponder selector on the CTA-81A to 2 to test transponder 2 in an aircraft with two Mode S units. Turn the function selector to TA for 10 seconds (minimum), then do again step 2.B.(1).
Page 10051 Dec 200334-45-47 MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.(6) Self-Test Using CTA-81( ) IndicatorsThe following self-test data applies to the CTA-81( ) indicators:(a) Control unit ATC FAIL lamp monitors the transponder functions only.(b) On the control unit, letter R comes on in the TEST. The letter R comes on in the ATC-2 position for the aircraft that have a non-Mode S transponder. The letter R does not come on during usual Mode S operation in ATC-1 or ATC-2.(c) The TCAS will not operate when the ATC FAIL lamp comes on. The TCAS system must have a serviceable Mode S transponder selected to function correctly.CAUTION:REMOVE THE POWER BEFORE REPLACING A MODE S OR TCAS SYSTEM COMPONENT. DAMAGE TO THE EQUIPMENT CAN RESULTRefer to Table 1001 and Table 1002 for Line Maintenance Troubleshooting Procedures.
Page 10061 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 1001. Mode S Line Maintenance Troubleshooting Procedure(Fault Indication on PPI or Dedicated Display).Fault Annunciation RemedyXPNDR TOP ANTXPNDR LOWER ANTCheck: Coaxial connectors, Coax cable, Coax Switches, Coax switch circuit defective, Transponder antenna No. 1 XPNDR ALT DATANo. 2 XPNDR ALT DATAXPNDR ALT DATA No. 1 and No. 2Check: Altitude source, Associated wiring SELECTED XPNDR XPNDR CONTROL DATACheck: Mode S transponder/control unit - Denotes loss/incorrect data not covered by other fault codes XPNDR TCAS DATA No. 1 XPNDR DATA BUSNo. 2 XPNDR DATA BUSCheck: Max airspeed program pins, Data bus wires (4), Mode S address wires, Suppression coax cable, Power wires/circuit breaker NOTE: If fault is shown, do front-panel test of Mode S transponder unit to make these problems clear.
Page 10071 Dec 200334-45-47 MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 1002. TCAS Line Maintenance Troubleshooting Procedure(Fault Indication on PPI or Dedicated Display)Fault Annunciation RemedyTCAS PROCESSORUPPER ANTENNALOWER ANTENNAATTITUDE HEADING Do the TCAS processor self test(paragraph 2.C.) for specifics. TCAS FAIL/NO TCASTRAFFIC DISPLAY PPI or dedicated display failure. RA DISPLAY No. 1 One RA DISPLAY or RADIO ALT FAULT will not show in a two system display unless other faults are shown. RA DISPLAY No. 2RA DISPLAY No. 1 and No. 2 Check ADCs, VSIs, wiring, power. RADIO ALT No. 1 and No. 2 TD FAILCheck the two radio altimeters. PPI defective. NOTE: If fault is shown, do front-panel test of TCAS processor (paragraph 2.C.) to make these problems clear.
Page 10081 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.C. Using TCAS Processor Front-Panel Buttons and LCD DisplayNOTE: Refer to applicable Mode S transponder system maintenance manual for front-panel self tests of Mode S transponder.(1) GeneralThe TPA-100A TCAS Processor front panel contains a four-line, 16 character for each line Liquid Crystal Display (LCD) and two pushbutton controls as shown in Figure 1002. The left pushbutton is the Scroll button and the right button is the Select button.If none of the two pushbuttons is operated for one minute, the Main Menu is shown. See Figure 1005 for a typical Main Menu. The first line of each display contains a title and the page number is shown with the number of pages that comprise that display.Any line that has an asterisk (*) in the first column shows that the line is selectable. The caret (>) shows the location of a selectable item if the Select pushbutton is pushed. When an item is chosen, a different menu is shown. Any line that does not have an asterisk or a caret is a text line and can not be selected.The Scroll pushbutton moves the caret down the page to the subsequent selectable item or to the subsequent page if that is where the next selectable item is located. When the caret has cycled through all the selectable items on all pages of the menu, it returns to the top selectable item on the first page of the menu.To return to the previous selection, push and hold the Scroll button while the Select button is pushed. Repeating this procedure causes the display to go back to the previous selection.
Page 10091 Dec 200334-45-47 MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.TCAS Processor Front Panel LCD and PushbuttonsFigure 1002
Page 10101 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.The Figure 1003 shows a typical Main Menu screen. If the Select button is pushed, the system status menu is shown. If the Scroll button is pushed one time, the caret moves to START TEST. If the Scroll button is pushed again, the caret moves to STORED FAULTS on page 2 of the menu.(Typical Pages 1 and 2 of Menu Screen)Typical Main Menu ScreenFigure 1003 NOTE: The caret is located at SYSTEM OK. (2) Unit OK/System FailedIf SYSTEM FAILED is the active selectable item on the Main Menu, to push the Select pushbutton starts a display entitled FAULTS. The display lists the text of all the unit faults that have occurred. Refer to Table 1003 for a list of possible unit faults.(3) System OK/Failed Display ScreenWhen SYSTEM FAILED is the active selectable item, the system faults are active and the input faults can be active at the same time. When the Select button is pushed, the text for all active system and input faults are shown. The display title will be INPUT FLTS. See Table 1004 for a list of the system and the input faults.See Table 1005 for a list of the program pin faults. The program pins being shorted to ground cause these faults except for BINT and BLIM. The BINT fault is caused by strapping fewer than 3 intruders to be shown. The BLIM fault is caused by the altitude limit program pins (RMP 6E through RMP 6J) being open.When SYSTEM OK is the active selectable item, only input faults are in operation. To push the Select button causes the input fault text to be shown. The display title will be INPT FLTS.
Page 10111 Dec 200334-45-47 MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 1003. Unit Internal FaultsInternal Faults Fault IdentificationDM CPU MCE PCI SP Fault CPU1DM CPU MCE PCI IO Fault CPU2DM CPU MCE PCI 429 Fault CPU3DM CPU MCE PCI Unknown Fault CPU4DM CPU Processor Transaction Fault CPU5DM CPU Memory Refresh Overflow Fault CPU6DM CPU Memory Select Fault CPU7DM CPU ECC Multi-bit Fault CPU8DM CPU Processor Unknown Fault CPU9SW Execution Error SWn (where n = A to Z and identifies task)DM BIT ADC Fault BADCDM ref 2.5 VREFSynthesizer Initialization SYN1DM SDRAM Data RAMDDM SDRAM Program RAMPDM 12 P12DM min12 PM12DM 5 P5DM 30Mon P30TRM 7 P7DM 3.3 PD33DM 2 PD2DM 2.5 PD25TRM min40 PR40TRM min5 PRM5TRM 3.3 PR33
Page 10121 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 1003. Unit Internal Faults (cont) Internal Faults Fault IdentificationTRM 5 PR5TTM min8 PTM8TTM 3.3 ref PT3RTTM 30v ref PT30TTM 32v e4 PT24TTM 32v e3 PT23TTM 32v e2 PT22TTM 32v e1 PT21TTM 2.5 PT25TTM 6 PT6TTM 3.3 PT3TTM 6v Bias PT6BDM IO A/D Slow Conversion DA1DM IO A/D Invalid Ground DA2DM IO A/D Invalid 2.5 V ref DA3DM Invalid Voice Program (CRC) DV2DM Invalid Voice Program(Version) DV3DM Invalid Configuration Data DCFGDM Voice Synthesizer Initialization DV1DM TA/RA # 1 Loop Around Missing DL1DM TA/RA # 1 Loop Around Bad Data DL2DM TA/RA # 2 Loop Around Missing DL3DM TA/RA # 2 Loop Around Bad Data DL4DM RA # 1/2 Loop Around Missing DL5DM RA # 1/2 Loop Around Bad Data DL6DM TX Coord Bus # 1 Loop Around Missing DL9DM TX Coord Bus # 1 Loop Around Bad DL10DM TX Coord Bus # 2 Loop Around Missing DL11
Page 10131 Dec 200334-45-47 MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 1003. Unit Internal Faults (cont)Internal Faults Fault IdentificationDM TX Coord Bus # 2 Loop Around Bad DL12DM 429 TA/RA Disp 1 FIFO Busy Error DF1DM 429 TA/RA Disp 2 FIFO Busy Error DF2DM 429 RA Disp FIFO Busy Error DF3DM 429 TX 1 Immediate Reg Error DF4DM 429 TX 2 Immediate Reg Error DF5DM ATCRBS Loop Around DSP1DM Mode S Loop Around DSP2DM SP Reply Data FIFO DSP3DM SP Reply Bearing FIFO DSP4DM SP Squitter Data FIFO DSP5DM SP Squitter Bearing FIFO DSP6DM SP DPSK Loop Around Fail DSP7DM SP Mode Decode (Mode S) DSP8DM SP Mode Decode (Mode C) DSPADM SP Missing EOI DSP9Bias Ctl Offset Voltage TB00Bias Ctl Chan 1 - Lo TBD1Bias Ctl Chan 1 - Hi TBF1Bias Ctl Chan 2 - Lo TBD2Bias Ctl Chan 2 - Hi TBF2Bias Ctl Chan 3 - Lo TBD3Bias Ctl Chan 3 - Hi TBF3Bias Ctl Chan 4 - Lo TBD4Bias Ctl Chan 4 - Hi TBF4TX Output Power Low - Channel 1 T1PWTX Output Power Low - Channel 2 T2PW
Page 10141 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 1003. Unit Internal Faults (cont)Internal Faults Fault IdentificationTX Output Power Low - Channel 3 T3PWTX Output Power Low - Channel 4 T4PW1030 TX Frequency 1030TTM Power Leveling TLVLTTM Power Attenuation - Monotonicity TATTCal PS1 Fault TPS1Cal PS3 Fault TPS3Cal PS4 Fault TPS4RX Cal Fault Top 1090 RCT0RX Cal Fault Bot 1090 RCB0TX Cal Top Fault TCTTX Cal Bot Fault TCBTop Bottom Antenna Phase Error TBCL
Page 10151 Dec 200334-45-47 MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 1004. System and Input FaultsFront Panel Text Fault DescriptionTop Ant Fail 1. TX Cal Delta 24 or 31 Top (Antenna Failure)Top Ant E1 1.1 Top Antenna Element 1 failedTop Ant E2 1.2 Top Antenna Element 2 failedTop Ant E3 1.3 Top Antenna Element 3 failedTop Ant E4 1.4 Top Antenna Element 4 failedBott Ant Fail 2. TX Cal Delta 24 or 31 Bot (Antenna Failure)Bott Ant E1 2.1 Bottom Antenna Element 1 failedBott Ant E2 2.2 Bottom Antenna Element 2 failedBott Ant E3 2.3 Bottom Antenna Element 3 failedBott Ant E4 2.4 Bottom Antenna Element 4 failedRadio Alt 1 3. Radio Altitude 1 (for A330, A340, and Boeing)Radio Alt 2 4. Radio Altitude 2 (for A330, A340, and Boeing)Radio Alt 1 3a. Radio Altitude 1 (for A320)Radio Alt 2 4a. Radio Altitude 2 (for A320)Transponder 1 5. Mode-S Transponder 1Transponder 2 6. Mode-S Transponder 2Roll Att Data 7. Roll AnglePitch Att Data 8. Pitch AngleHeading Data 9. Magnetic HeadingTA/VSI 1 10. TA/VSI 1TA/VSI 2 11. TA/VSI 2RA Display 1 12. RA/VSI 1RA Display 2 13. RA/VSI 2CMC Bus 14. CFDIU (for A320)CMC Bus 14. CMC (for A330, A340, and Boeing)ATC Ctl Panel 15. Mode-S Control Panel (for A330 and A340)ATC Ctl Panel 15.1 Mode-S Control Panel (for A320 and Boeing)
Page 10161 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 1004. System and Input Faults (cont)Front Panel Text Fault DescriptionFMC 16. FMC (for aircraft type not A330 and not A340)FMC 16.1 FMC (for A340 and A330)Suppression Line 17. Suppression LineTCAS Unit Failed 18. TCAS Unit FaultPower Interrupt 19. Power Supply InterruptedProgram Pin 20. Program Pin
Page 10171 Dec 200334-45-47 MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 1005. Program Pin FaultsFront Panel Text Fault DescriptionPP RMP 12A Analog Radio Altimeter Prgm, RMP 12APP RMP 12B Analog Radio Altimeter Prgm, RMP 12BPP RMP 12C Analog Radio Altimeter Prgm, RMP 12CPP RBP 7D Audio Tone Enable Program, RBP 7DPP RBP 7E Ground Display Mode, RBP 7EPP RBP 7F Display All Traffic Program, RBP 7FPP RBP 7G Cable Delay Program Sign, RBP 7GPP RBP 7H Cable Delay Program MSB, RBP 7HPP RBP 7J Cable Delay Program LSB, RBP 7JPP RBP 8F TA/RA Display Symbols Max Prgm, RBP 8FPP RBP 8G TA/RA Display Symbols Max Prgm, RBP 8GPP RBP 8H TA/RA Display Symbols Max Prgm, RBP 8HPP RBP 8J TA/RA Display Symbols Max Prgm, RBP 8JPP RBP 8K TA/RA Display Symbols Max Prgm, RBP 8KPP RBP 8E Functional Test Inhibit Prgm, RBP 8EPP RBP 7A Audio Level Prgm, RBP 7APP RBP 7B Audio Level Prgm, RBP 7BPP RBP 7C Audio Level Prgm, RBP 7C
Page 10181 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 1005. Program Pin Faults (cont)(4) Unit, System, and Input Active Fault RelationshipTable 1006 shows the relation in unit, system, input active faults, and the status on the display. The asterick (*) shows that the text is selectable. The display screen shows START TEST or TEST INHIBIT. See Figure 1004. The test is prevented in specific conditions when the Air/Ground Discrete = Air. When the Air/Ground Discrete = Ground, START TEST is shown.To push the Select button when the caret is adjacent to the Start Test selectable item, causes the Test In Progress screen to come into the view and the test to start. Front Panel Text Fault DescriptionPP RMP 6E Altitude Limit Prgm, RMP 6EPP RMP 6F Altitude Limit Prgm, RMP 6FPP RMP 6G Altitude Limit Prgm, RMP 6GPP RMP 6H Altitude Limit Prgm, RMP 6HPP RMP 6J Altitude Limit Prgm, RMP 6JPP TARA <3 Intrd TA/RA Display Limit Program Pins set less than 3 IntrudersPP Alt Limit Opn Altitude Limit Program Pins All OpenPP RBP 7K Program Pin Common, RBP 7KPP RMP 6K Aircraft Alt. Limit Prgm Common, RMP 6KPP RBP 8A Audio Level On Ground, RBP 8APP RBP 8B Audio Level On Ground, RBP 8BPP RBP 8C Audio Level On Ground, RBP 8CPP RBP 4G RA Valid Discrete Disable Program Pin, RBP 4GPP RBP 6J Transponder Interface Select, RBP 6JPP RBP 6K Rad Alt Interface Select, RBP 6KPP RMP 5E ADS-B (Intruder File Enable) Program Pin
Page 10191 Dec 200334-45-47 MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.The three possible results of the test are:(a) No faults (unit and system ok)(b) System or input faults (unit ok, system failed)(c) Internal faults (unit failed/system failed)To push the Select button with the caret at SYSTEM FAILED or UNIT FAILED causes a display screen with the entries that include the applicable found faults. When faults are found, START TEST is selectable and a retest is possible. The selection of GO BACK causes the previous screen with a selectable item to be shown. That previous screen is the same as it was when previously visited. A GO BACK is possible when the user pushes a Select button with an in operation selectable item. To go back to the previous screen, hold the Scroll button and push the Select button.
Page 10201 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 1006. Active Unit, System and Input Faults, and Display Status IndicationActive UnitFaultsActive SystemFaultsActive InputFaultsUnit (Status)System/Input (Status)No No No Unit OKSystem OKNo No Yes Unit OK*Inputs FaultedNo Yes No Unit OK*System FailedNo Yes Yes Unit OK*System FailedYes No No *Unit Failed*System FailedYes No Yes *Unit Failed*System FailedYes Yes No *Unit Failed*System FailedYes Yes Yes *Unit Failed*System Failed
Page 10211 Dec 200334-45-47 MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Start Test/Test Inhibited Sample Flow DiagramFigure 1004
Page 10221 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.(5) Stored FaultsTo push the Select button when STORED FAULTS (see main menu Figure 1003) is the active selectable item, causes the Stored Faults screen to be shown (Figure 1005). The fault data is shown five legs back from the most recent fault to the oldest fault. The title of the Stored Fault Display shows in which leg the stored fault is found. The title shows the current leg minus the number of legs to where the fault is kept. For example, LEG-2 shows the fault is found two legs back from the present leg. If the current leg equals the leg with the fault, then the title is INBOUND. The date and time the first fault of the flight leg occurred is shown in the screen title.PHASE shows the flight phase (1-16) of the faults first occurrence in the flight leg. OCCUR shows the number of occurrences of the fault in the fault leg. The Figure 1006 is an example of a stored fault procedure. Typical First and Last Pages of Stored Faults Display ScreenFigure 1005
Page 10231 Dec 200334-45-47 MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document. Stored Faults LCD Screen ExampleFigure 1006
Page 10241 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.(6) Configuration Display ScreenTo push the Select button when the Configuration is the Active Selectable Item on the Menu screen causes the Configuration Screen to come into the view. A representation of a two page Configuration screen is shown in Figure 1007.The screen title is CONFIG. The lines two, three, and four of page 1/2 contain the software part number(s). To push the Scroll button causes page 2/2 of the CONFIG screen to come into the view. The hardware part number and the unit serial number are shown on the screen. The Active Selectable Item is GO BACK. To push the Select button while the caret is at GO BACK causes a return to the Menu screen. Typical Configuration Display ScreenFigure 1007
Page 10251 Dec 200334-45-47 MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.(7) Inputs Display Screen To push the Select button when Input is the Active Selectable Item on the Menu Screen causes the Input select screen page 1/3 to come into the view. See Figure 1008. Refer to Table 1007 for Program Pin displayed text and fault descriptions.(a) Program Pins Display ScreenTypical Input Display Screens (Pages 1-3)Figure 1008
Page 10261 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 1007. Program PinsProgramPin Display Text Fault DescriptionPP RBP 6J Single Xpdr One Transponder Program Pin shows how many transponders are installed:*O = Both Transponders Installed*1 = One Transponder InstalledPP RBP 6K Single RA One Radio Altitude Program Pin shows how many Radio Altimeters are installed:*O = Both Altimeters Installed*1 = One Altimeter InstalledPP RBP 7A Airborne Audio Level # 1 Airborne Audio Level Program Pins find the speaker and phones audio level output when the aircraft is airborne by strapping one or more Airborne Audio Level Program Pins to Program Pin Common RBP7K (See NOTE)PP RBP 7B Airborne Audio Level # 2PP RBP 7C Airborne Audio Level # 3PP RBP 7D Audio Advisory Discrete Audio Advisory Discrete Program Pins show if there is an interval in the Synthesizer Voice output when an advisory is given: *O = No Delay*1 = 1 ± 0.2 second delay (an audio tone is output prior to the issuance of a voice command) PP RBP 7E Ground Display Mode Ground Display Mode Program Pin shows the correct mode for TCAS when the aircraft is on the ground:*O = TA Only mode (Sensitivity Level = 2, RAs prevented)*1 = Standby Mode (Sensitivity Level = 1)PP RBP 7F Display All Traffic Display All Traffic/Threat Program Pin calculates the traffic that is shown:*O = Display All Traffic *1 = Display TA/RA Traffic OnlyPP RBP 7G Cable Delay Sign The Cable Delay Program Pins show the differential interval between the top and the bottom antenna.PP RBP 7H Cable Delay MSBPP RBP 7J Cable Delay LSB
Page 10271 Dec 200334-45-47 MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 1007. Program Pins (cont) * 0 = Open, 1 = Ground (Connected to Program Pin Common (RBP7K)NOTE: For more program pin data see the Wire Strapping Options paragraph in the MAINTENANCE PRACTICES section of this manual.ProgramPin Display Text Fault DescriptionPP RBP 8A On Ground Audio Level No. 1 Ground Audio Level Program Pins find the speaker and phones audio level output when the aircraft is on the ground by strapping one or more Ground Audio Level Program Pins to Program Pin Common RBP7K.PP RBP 8B On Ground Audio Level No. 2PP RBP 8C On Ground Audio Level No. 3PP RBP 8E Self Test Inhibit Test Inhibit Program Pin shows when to prevent functional test when airborne:*O = Functional Test In Air Permitted*1 = Functional Test In Air PreventedPP RBP 8F Disp Intruder Limit 16 TA/RA Display Intruder Limit Program Pins limit the number of intruders that can be shown (all pins = maximum traffic can be displayed = 31). There are five straps to limit the number of intruders that are shown (0-31). The pins connected to RBP7K are not shown. PP RBP 8G Disp Intruder Limit 8PP RBP 8H Disp Intruder Limit 4PP RBP 8J Disp Intruder Limit 2PP RBP 8K Disp Intruder Limit 1PP RMP 6E Altitude Limit 2000 ft Altitude Limit Program Pins show the altitude Performance Limits of an aircraft. If no straps are installed the altitude Performance Limit is zero feet. If all straps are installed the Performance Limit is 62,000 feet.PP RMP 6F Altitude Limit 4000PP RMP 6G Altitude Limit 8000PP RMP 6H Altitude Limit 16000PP RMP 6J Altitude Limit 32000PP RMP 12A RA Type Straps A Radio Altimeter Type Straps Program Pins show the type of radio altimeter that supplies altitude data to the TCAS system. PP RMP 12B RA Type Straps BPP RMP 12C RA Type Straps C
Page 10281 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.(b) Discretes Display ScreenFigure 1009 is an example of a Discrete screen. The line 1 contains the screen title, the line 2 shows the pin number followed by Open or Ground. The lines 3 and 4 are reserved for the name of the discrete. On the last Discrete page the Active Selectable Item GO BACK is shown. Table 1008 lists the discrete pins, the text shown, and a short description of the discrete.Example of Discrete ScreenFigure 1009
Page 10291 Dec 200334-45-47 MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 1008. Discrete Pin NumbersDiscrete Pin Number Display Text Discrete DescriptionRBP5A Advisory Inhibit 1 The four input to TCAS prevent annunciations when more important events occur. The source of the four input are Input 1, Aircraft System; Input 2, Windshear System 1; Input 3, Windshear 2; Input 3, EGPWC.RBP5B Advisory Inhibit 2RBP5C Advisory Inhibit 3RBP5D Advisory Inhibit 4 See Table 1009.RBP5E Increase Climb Inhibit 1 The following logic applies to the four Increase Climb Inhibit Input to the TCAS from the system.RBP5F Increase Climb Inhibit 2RBP5G Increase Climb Inhibit 3 (Increase Climb Inhibit 1 AND Increase Climb Inhibit 2) OR (Increase Climb Inhibit 3 AND Increase Climb Inhibit 4) = Cannot climb at 2500 feet for each minute.RBP5H Increase Climb Inhibit 4The low is the in operation condition.RMP1J Climb Inhibit 1 TCAS is Climb Inhibited when the logic is as follows: (Climb Inhibit 1 AND Climb Inhibit 2) OR (Climb Inhibit 3 AND Climb Inhibit 4). The low is the in operation condition.RMP13G Climb Inhibit 2RBP5J Climb Inhibit 3RBP5K Climb Inhibit 4 The Climb Inhibit discretes are influenced by the landing gear position, flap position, and other aircraft configurations that give climb performance.RBP6A Data Loader Enable Data loader enable discrete input to TCAS from the data loader.RMP3D Advisory/Annunc Cancel This discrete input gives the procedure for cancelling current aural advisory, synthesized voice, and visual annunciator alerts. This is an option of the flight crew. When cancelled it stays cancelled until the currently active advisory becomes inactive and then active again or the current active advisory is replaced by a different advisory.Where 0 = Open = No Advisory Cancel 1 = Ground = Advisory Cancel
Page 10301 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 1008. Discrete Pin Numbers (cont)NOTE: Advisory Inhibit and TCAS Mode Data is shown in Table 1009.Discrete Pin Number Display Text Discrete DescriptionRMP5K Air/Ground 1 The Air/Ground Discrete Input for the Air/Ground relay.The normal failure mode is the airborne condition.The following applies:RMP5K RTP5J Definition 1 1 a/c on ground, don’t inhibit ATCRBS replies 1 0 a/c on ground, don’t inhibit ATCRBS replies 0 1 a/c on ground, inhibit ATCRBS replies 0 1 a/c airborne, don’t inhibit ATCRBS repliesWhere 0 = Open 1 = GroundRMP6D Performance Limit The performance limit shows to TCAS when the aircraft can no longer get a 1500 feet per minute climb. When the input is GROUND the performance is not limited. When the input is OPEN the climb is limited if the altitude of the aircraft is above the value set by the Altitude Limit Program (See below).Limit Input RMP6D Relative Altitude Climb Limited Yes Open Below No Yes Open Above Yes No Gnd Below No No Gnd Above NoRMP7E TA Display No. 1 Status The TA Display Status input are connected to their related Traffic Display Status output (valid).RMP7J TA Display No. 2 StatusIf any of the Display Status discretes are not necessary they must be attached to ground as necessary for the installation.RMP14C RA Display No. 1 Status The RA Display 1 and 2 Status discretes indicate the validity of the resolution displays. They are connected to their respective RA Display Status output (valid).RMP13E RA Display No. 2 StatusRMP13F Landing Gear This pin shows the position of the landing gear. The usual mode is the RETRACTED position.Where 0 = Gear Retracted = Open 1 = Gear Extended = Ground
Page 10311 Dec 200334-45-47 MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Table 1009. Advisory Inhibit and TCAS Mode Data NOTE: Advisory Inhibit 1 has precedence over the other Advisory Inhibit input.(c) TCAS Data Display ScreenTo push the Select button when the TCAS Data is the Active Selectable Item on the Input select screen causes the TCAS Data screen 1/8 to be shown.The TCAS Data screen shows the validity and the value of input data for the following input used by TCAS:• Digital Radio Altitude• Analog Radio AltitudeThe priority of Radio Altitude sources is: 1. Digital Radio Altitude No. 1 3. Analog Radio Altitude No. 1 2. Digital Radio Altitude No. 2 4. Analog Radio Altitude No. 2• Pressure Altitude• Roll• Pitch• Heading• Climb Inhibit Increase Climb Inhibit Discretes• Air/Ground Discrete• Landing Gear DiscreteAdvisory InhibitNo.1 No.2 No.3 No.4 TCAS Mode1 X X X Standby (SL=1)01XXTA Only (SL=2)0X1XTA Only (SL=2)0XX1TA Only (SL=2)0000NormalWhere 0 = Open1 = GroundX = Don't care
Page 10321 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1Digital Radio AltitudeThe Figure 1010 shows an example of a Digital Radio Altitude screen. The line 2 shows the correct radio altitude from the No. 1 digital data source. The plus (+) sign in position 16 of line 2 shows that Altitude No. 1 source is the active input. If the Altitude No. 1 data was incorrect, then INVALID would be shown on the line two. The line 3 shows the Altitude No. 2 data in the same procedure that line 2 shows the Altitude No. 1 data.Digital Radio Altitude Display Screen ExampleFigure 1010 2Analog Radio Altitude The Figure 1011 shows an example of an Analog Radio Altitude screen. The line two shows that analog radio altitude No. 1 data is incorrect. If the analog altitude No. 1 data were correct then the altitude would be shown on the line 2. A plus sign (+) in position 16 of line 3 shows that altitude source is the active input. Line 3 shows the correct altitude from analog altitude No. 2 and the plus sign shows that analog radio altitude No. 2 is the active altitude source.Analog Radio Altitude Display Screen ExampleFigure 1011
Page 10331 Dec 200334-45-47 MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.3Pressure AltitudeThe pressure altitude data is supplied to TCAS from the transponder through XT Coordination No. 1 and No. 2 ARINC 429 data bus (Data Word Label 203). The Figure 1012 shows a sample Pressure Altitude screen. The line two contains the altitude data from XT Coordination No. 1 pressure altitude data source. In this example the data source is correct (altitude = 2400 ft.) and the plus sign shows that the XPDR No. 1 is the active source. If that data were correct then line two can show INVALID. The line three indications are almost the same except that they are for XPDR No. 2.Pressure Altitude Display Screen ExampleFigure 1012 4RollAn example of a Roll display is shown in Figure 1013. The line two shows the data from ARINC 429 Mag Heading/Attitude data bus (label 325). The (+) indicated that data source is the active source. If the roll data from the 429 data source is not correct, then line two can show INVALID. The line three shows the data from a roll attitude synchro. In this case the data is incorrect. Roll Display Screen ExampleFigure 1013
Page 10341 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.5PitchAn example of a Pitch display screen is shown in Figure 1014. The line two shows the data from ARINC 429 Mag Heading/Allotted data bus (label 324). The (+) shows that source is the active source. If the Pitch data from the 429 data source is not correct, then line two can show INVALID. The line three shows the data from a Pitch attitude synchro. In this case the data is correct. Pitch Display Screen ExampleFigure 1014 6HeadingThere are two types of heading data, one is ARINC 429 and the other is synchro. There are two types of ARINC 429 heading data, true and magnetic. An example of a Heading display is shown in Figure 1015. The second line shows the true heading data from ARINC 429 label 314. The (+) indicated that data source is the active source. If the data from one of the data sources is not correct, then it can show INVALID (as shown on the line three). The line three shows Magnetic heading data from ARINC 429 data source (label 320). The line four shows the data from the Magnetic Synchro data source. In this case the data is incorrect.Heading Display Screen ExampleFigure 1015
Page 10351 Dec 200334-45-47 MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.7Climb InhibitAn example of a Climb Inhibit display screen is shown in Figure 1016. The second line shows if climb is inhibited or not (yes or no). The line three shows if increased climb is inhibited (yes or no).Climb Inhibit Display Screen ExampleFigure 1016 8Air/Ground and Landing GearAn example of an Air/Ground and Landing Gear display screen is shown in Figure 1017. The second line shows if Air/Ground Input Discretes show Ground, Air, or invalid. The line three shows if Landing Gear Discrete Input shows the gear is RETRAC or EXTEND. The Active Selectable Item is GO BACK.Air/Ground Display Screen ExampleFigure 1017
Page 10361 Dec 200334-45-47MAINTENANCE MANUALCAS-100 COLLISION AVOIDANCE SYSTEMUse or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.(d) Mode-S AddressTo push the Select button when Mode-S Address is the Active Selectable Item on the Input screen causes the Mode-S Address display screen to display. The Figure 1018 shows an example of the Mode-S Address screen. Line two shows the hexadecimal address of transponder No. 1 received from XT Coordination No. 1 (pins RMP 14F and RMP 14G) ARINC 429 data bus (labels 275 and 276). If the data words are not received, no address will be shown and that area of the screen will stay blank.Typical Mode S Transponder Display ScreenFigure 1018 (e) Continuous Wave InterferenceTo push the Select button when the Continuous Wave (CW) Interference is the Active Selectable Item on the Input Screen causes the CW Interference display screen to be shown. The Figure 1019 shows an example of a CW Interference display screen. Line two shows the external CW Internal. If the external CW Interference is between -1 and 0, then NONE will be shown. GO BACK is the Active Selectable Item. Continuous Wave Interference Display ScreenFigure 1019

Navigation menu