ACSS an L 3 Communications and Thales TT-950 TCAS II User Manual Part 1

ACSS an L-3 Communications and Thales Company TCAS II Part 1

Contents

User Manual Part 1

Aviation Communication and Surveillance Systems19810 North 7th AvenuePhoenix, Arizona 85027--4400U.S.A.15 FEBRUARY 200334-43-20Page T--1PRINTED IN U.S.A. PUB. NO. 8000451--001T2CASTraffic and Terrain Collision AvoidanceSystemSystem Description andInstallation Manual
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page T--2PROPRIETARY NOTICEThis document and the information disclosed herein are proprietary data of ACSS. Neither thisdocument nor the information contained herein shall be used, reproduced, or disclosed to otherswithout the written authorization of ACSS, except to the extent required for installation ormaintenance of the recipient’s equipment.NOTICE -- FREEDOM OF INFORMATION ACT (5 USC 552) AND DISCLOSURE OFCONFIDENTIAL INFORMATION GENERALLY (18 USC 1905)This document is being furnished in confidence by ACSS. The information disclosed herein fallswithin exemption (b) (4) of 5 USC 552 and the prohibitions of 18 USC 1905.S2003ACSS is a U.S. registered trademark.All other marks are owned by their respective companies.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page RR--1RECORD OF REVISIONSFor each revision, put the revised pages in your manual and discard the superseded pages. Writethe revision number and date, date put in manual, and the incorporator’s initials in the applicablecolumns on the Record of Revisions. The initial A shows ACSS is the incorporator.RevisionNumber Revision Date Date Put in Manual By
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T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page RTR--1RECORD OF TEMPORARY REVISIONSRead the location instructions on each temporary revision page to know where to put the pages inyour manual. Remove temporary revision pages only when discard instructions are given. Foreach temporary revision, give the correct data in the applicable columns.TemporaryRevision No.TemporaryRevision DateDate Putin Manual By *Date Removedfrom Manual By ** The initial A in this column shows ACSS has done the task.
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T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.Page SBL--1SERVICE BULLETIN LISTService Bulletin IdentifiedModDate Includedin this Manual Description
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T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.LEP--1LIST OF EFFECTIVE PAGESOriginal -- 15 Feb 2003Subheading and Page RevisionSubheading and Page Revision Subheading and Page RevisionTitleT--1T--2 ----Record of RevisionsRR--1 --RR--2 --Record of Temporary RevisionsRTR--1 --RTR--2 --Service Bulletin ListSBL--1 --SBL--2 --List of Effective PagesLEP--1 --LEP--2 --LEP--3 --LEP--4 --LEP--5 --LEP--6 --Table of ContentsTC--1 --TC--2 --TC--3 --TC--4 --TC--5 --TC--6 --TC--7 --TC--8 --TC--9 --T C -- 1 0 --T C -- 11 --T C -- 1 2 --T C -- 1 3 --T C -- 1 4 --IntroductionINTRO--1 --INTRO--2 --INTRO--3 --INTRO--4 --INTRO--5 --INTRO--6 --System Description1--1 --1--2 --1--3 --1--4 --1--5 --1--6 --1--7 --1--8 --1--9 --1--10 --1--11 --1--12 --1--13 --1--14 --1--15 --1--16 --1--17 --1--18 --F 1--19/1--20 --1--21 --1--22 --1--23 --Hindicates changed, added, or deleted page.F indicates right foldout page with blank back.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.LEP--21--24 --1--25 --1--26 --1--27 --1--28 --1--29 --1--30 --1--31 --1--32 --1--33 --1--34 --1--35 --1--36 --F 1--37/1--38 --1--39 --1--40 --1--41 --1--42 --1--43 --1--44 --1--45 --1--46 --1--47 --1--48 --1--49 --1--50 --1--51 --1--52 --1--53 --1--54 --1--55 --1--56 --1--57 --1--58 --1--59 --1--60 --1--61 --1--62 --1--63 --1--64 --1--65 --1--66 --1--67 --1--68 --1--69 --1--70 --1--71 --1--72 --1--73 --1--74 --1--75 --1--76 --1--77 --1--78 --1--79 --1--80 --1--81 --1--82 --1--83 --1--84 --1--85 --1--86 --Mechanical Installation2--1 --2--2 --2--3 --2--4 --2--5 --2--6 --2--7 --2--8 --2--9 --2--10 --F 2 -- 11 / 2 -- 1 2 --F 2--13/2--14 --F 2--15/2--16 --F 2--17/2--18 --F 2--19/2--20 --F 2--21/2--22 --F 2--23/2--24 --F 2--25/2--26 --F 2--27/2--28 --F 2--29/2--30 --Subheading and Page RevisionSubheading and Page Revision Subheading and Page Revision
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T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.LEP--44--28 --4--29 --4--30 --4--31 --4--32 --4--33 --4--34 --4--35 --4--36 --4--37 --4--38 --4--39 --4--40 --4--41 --4--42 --4--43 --4--44 --4--45 --4--46 --4--47 --4--48 --4--49 --4--50 --4--51 --4--52 --4--53 --4--54 --4--55 --4--56 --4--57 --4--58 --4--59 --4--60 --4--61 --4--62 --4--63 --4--64 --4--65 --4--66 --4--67 --4--68 --4--69 --4--70 --4--71 --4--72 --4--73 --4--74 --4--75 --4--76 --4--77 --4--78 --4--79 --4--80 --4--81 --4--82 --4--83 --4--84 --4--85 --4--86 --4--87 --4--88 --4--89 --4--90 --4--91 --4--92 --4--93 --4--94 --Adjustment/Test5--1 --5--2 --5--3 --5--4 --5--5 --5--6 --5--7 --5--8 --5--9 --5--10 --5--11 --5--12 --5--13 --5--14 --5--15 --Subheading and Page RevisionSubheading and Page Revision Subheading and Page Revision
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.LEP--55--16 --5--17 --5--18 --Fault Isolation6--1 --6--2 --6--3 --6--4 --6--5 --6--6 --6--7 --6--8 --6--9 --6--10 --6--11 --6--12 --6--13 --6--14 --6--15 --6--16 --6--17 --6--18 --6--19 --6--20 --6--21 --6--22 --6--23 --6--24 --6--25 --6--26 --6--27 --6--28 --6--29 --6--30 --6--31 --6--32 --Maintenance Practices7--1 --7--2 --7--3 --7--4 --7--5 --7--6 --7--7 --7--8 --7--9 --7--10 --7--11 --7--12 --Inspection/Check8--1 --8--2 --Cleaning/Painting9--1 --9--2 --9--3 --9--4 --9--5 --9--6 --Repairs10--1 --10--2 --Appendix AA--1 --A--2 --A--3 --A--4 --A--5 --A--6 --Appendix BB--1 --B--2 --F B -- 3 / B -- 4 --F B -- 5 / B -- 6 --Subheading and Page RevisionSubheading and Page Revision Subheading and Page Revision
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T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.TC--1TABLE OF CONTENTSSection PageINTRODUCTION INTRO--1..............................................................1. General INTRO--1..................................................................2. Reference Documents INTRO--1.....................................................3. Weights and Measurements INTRO--2................................................4. Acronyms and Abbreviations INTRO--2...............................................5. Special Precautions INTRO--6.......................................................SYSTEM DESCRIPTION 1--1......................................................1. General 1--1..................................................................2. System Components 1--2......................................................3. System Description 1--6........................................................A. System Functional Description 1--6..........................................(1) TCAS Functional Description 1--6.......................................(2) TAWS Functional Description 1--11.......................................(3) RWS Functional Description 1--13........................................(4) GPS Functional Description 1--13.........................................B. System Configurations 1--13.................................................(1) TCAS System Configuration 1--14........................................(2) TAWS/RWS System Configuration 1--14...................................4. Component Descriptions 1--21...................................................A. TT--950/951/952 T2CAS Computer Unit 1--21..................................(1) System Interfaces 1--26.................................................(2) Discrete Inputs 1--33....................................................(3) Program Inputs 1--33...................................................(4) Discrete Outputs 1--33..................................................(5) Self--Test Function 1--34.................................................B. Airplane Personality Module Interface 1--35....................................C. Directional Antenna 1--35....................................................D. GPS Antenna and Coax 1--39................................................E. Gables ATC/TCAS Dual Mode S Transponder Control Panel 1--41................(1) Functional Description and Operation 1--42................................F. TAWS Control Panel 1--44...................................................
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.TC--2Section PageG. VSI/TRA Display 1--44......................................................(1) Functional Description and Operation 1--46................................(2) Software Considerations 1--47...........................................(3) Built--In--Test Equipment (BITE) and Self--Test Capability 1--47...............H. TAWS Terrain Hazard Display 1--49...........................................(1) Functional Description and Operation 1--49................................I. XS--950 Mode S Data Link Transponder 1--51.................................J. RCZ--852 Diversity Mode S Transponder 1--56.................................5. System Operation 1--60.........................................................A. TCAS Operation 1--60......................................................(1) Operational Modes 1--60................................................(2) Display Symbology 1--62................................................(3) Aural Messages 1--64...................................................(4) Operating Procedures 1--67..............................................B. TAWS/RWS Operation 1--68.................................................(1) TAWS Operational Modes 1--68..........................................(2) RWS Operational Mode 1--73............................................(3) TAWS Display Symbology 1--73..........................................(4) TAWS/RWS Aural Messages 1--78........................................(5) Operating Procedures 1--81..............................................MECHANICAL INSTALLATION 2--1.................................................1. General 2--1..................................................................2. Equipment and Materials 2--1...................................................3. Mechanical Installation Design 2--1..............................................A. TT--950/951/952 T2CAS Computer Unit Provisions 2--1........................B. Airplane Personality Module Provisions 2--2..................................C. Antenna Provisions 2--2....................................................(1) Directional Antenna Installation 2--2.....................................(2) Omnidirectional Antenna Installation 2--3.................................D. GPS Antenna and Coax Provisions 2--3......................................E. TCAS Control Panel Provisions 2--5.........................................F. TAWS/RWS Control Panel Provisions 2--5....................................
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.TC--3Section PageG. VSI/TRA Provisions 2--5....................................................H. TAWS Terrain Hazard Display Provisions 2--5.................................I. Transponder Provisions 2--8................................................(1) Mode S Data Link Transponder Provisions 2--8...........................(2) Diversity Mode S Transponder Provisions 2--8............................(3) ATC Transponder Antenna Provisions 2--9................................ELECTRICAL INSTALLATION 3--1.................................................1. General 3--1..................................................................2. Equipment and Materials 3--1...................................................3. Electrical Installation Procedure 3--1.............................................4. Electrical Installation 3--1.......................................................A. TT--950/951/952 T2CAS Computer Units 3--1.................................B. APM 3--1.................................................................C. TCAS Antennas 3--2.......................................................D. GPS Antenna and Coax 3--4................................................E. Control Panels 3--12........................................................F. Thales VSI/TRA Display 3--14................................................G. TAWS Terrain Hazard Display 3--18...........................................H. Transponders 3--20.........................................................(1) XS--950 Data Link Transponder 3--20.....................................(2) RCZ--852 Diversity Mode S Transponder 3--29.............................LOADING/GRADIENT SPECIFICATIONS 4--1........................................1. General 4--1..................................................................2. TCAS Interface Description 4--1.................................................TAWS/RWS PINOUTS AND PIN DEFINITIONS 4--49...................................3. TAWS/RWS Specifications 4--49.................................................A. TAWS/RWS Pinout and Pin Descriptions (Non--Configurable) 4--50...............B. TAWS/RWS Data Configuration 4--54.........................................(1) ASDB 4--54............................................................(2) APM 4--55.............................................................
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.TC--4Section PageC. APM/ASDB Configurable Pinout and Pin Description 4--63......................(1) Programmable Analog Input Pins 4--63....................................(2) Programmable Digital Input/Output Pins 4--68..............................(3) Programmable Discrete Input/Output Pins 4--72............................D. TAWS/RWS Input Data Signals 4--75.........................................(1) Vertical Speed (Digital/Analog) 4--75......................................(2) Ground Speed 4--76....................................................(3) True Track Angle 4--76..................................................(4) Radio Altitude (Digital/Analog) 4--77......................................(5) Flight Path Angle 4--78..................................................(6) Current Aircraft Weight 4--78.............................................(7) Aircraft Position Latitude/Longitude 4--78..................................(8) Aircraft Altitude 4--79....................................................(9) Navigation Accuracy 4--79...............................................(10) Static Air Temperature 4--80.............................................(11) Roll Angle 4--80........................................................(12) Computed Airspeed 4--80...............................................(13) Selected Runway Heading 4--80.........................................(14) Glideslope Deviation (Digital/Analog) 4--80................................(15) Localizer Deviation (Digital/Analog) 4--81..................................(16) Selected Decision Height 4--81...........................................(17) Minimum Descent Altitude 4--82..........................................(18) Body Longitudinal Acceleration (Digital/Analog) 4--82.......................(19) Body Normal Acceleration (Digital/Analog) 4--82............................(20) Pitch Angle 4--82.......................................................(21) Flap Angle 4--82........................................................(22) Slat Angle 4--83........................................................(23) True Airspeed 4--83.....................................................(24) Angle of Attack (AOA) Left/Right 4--83....................................(25) Magnetic Heading 4--83.................................................(26) True Display Orientation Left 4--84........................................(27) True Display Orientation Right 4--84......................................(28) Display Range Left/Right 4--84...........................................
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.TC--5Section PageE. TAWS/RWS Discrete Inputs 4--85............................................(1) Landing Gear Down 4--85...............................................(2) Landing Flap 4--85......................................................(3) Terrain Inhibit 4--85.....................................................(4) Steep Approach 4--85...................................................(5) Glideslope Inhibit 4--85..................................................(6) Glideslope Cancel 4--85.................................................(7) Decision Height /Minimum Descent Altitude Selection (DH/MDA) 4--86........(8) Below Decision Height 4--86.............................................(9) Aircraft On Ground 4--86................................................(10) ILS Back Course 4--86..................................................(11) Altitude Callout Disable 4--86............................................(12) Engine Out 4--86.......................................................F. TAWS/RWS Digital Output Data 4--86.........................................(1) GCAM Event Data 4--86.................................................(2) GCAM Data 4--88......................................................(3) GCAM General Purpose 4--88...........................................(4) Terrain Awareness Display Output 4--88...................................(5) OMS Fault Summary Word 4--89.........................................G. TAWS/RWS Discrete Output Data 4--91.......................................(1) Ground Discrete Parameters 4--91........................................(2) Ground Discrete Monitor Parameters 4--92................................ADJUSTMENT/TEST 5--1..........................................................1. General 5--1..................................................................2. Equipment 5--1...............................................................3. Initial Harness Checkout (New Installations Only) 5--1.............................A. T2CAS Computer Unit Harness Checkout 5--1................................B. T2CAS Controller and Display Unit Harness Checkout 5--1.....................C. LRU Preinstallation Power Checkout 5--2.....................................D. Initial System Installation Operational Test 5--2................................
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.TC--6Section Page4. System Self--Tests 5--3.........................................................A. TCAS Flight Deck Display Test Modes 5--3...................................(1) Short Test Mode 5--3...................................................(2) Extended Test Mode 5--4...............................................B. TAWS/RWS Flight Deck Display Test Modes 5--5..............................(1) Standard Test Mode 5--5...............................................(2) Extended Test Mode 5--7...............................................C. T2CAS Computer Unit Self--Test 5--9.........................................5. Return to Service Test 5--11.....................................................6. Operational Software Loading Using an ARINC Portable DataLoader, RS232 Port or Compact Flash Card 5--11..................................A. Current Software Verification 5--12............................................(1) TCAS Software Verification 5--12.........................................(2) TAWS/RWS Software Verification 5--12....................................B. Portable Data Loader -- TCAS Operational Software Loading(While Installed on Aircraft) 5--12.............................................C. Compact Flash Card -- TAWS/RWS Operational Software/ACD/ASDBLoading (While Installed on Aircraft) 5--13.....................................D. RS232 -- TAWS/RWS APM Configuration Data and APMApplication Data Loading 5--15...............................................E. Updated Software Verification 5--15...........................................(1) Software Verification Using Flight Deck Systems ONLY 5--15................(2) TCAS Software Verification Using a Stand--Alone PC ONLY 5--15............(3) TAWS/RWS Software Verification Using a Stand--Alone PC ONLY 5--17.......(4) TCAS Software Verification Using a Software Verification Fixture ONLY 5--18..(5) TCAS Software Verification Using a Remote Connected VSI/TRA ONLY 5--18.FAULT ISOLATION 6--1...........................................................1. General 6--1..................................................................2. Equipment and Materials 6--1...................................................3. Procedure 6--1................................................................A. CMC or CFDS 6--1........................................................B. Flight Deck Initiated Self--Test/Fault Display Systems 6--1......................(1) TCAS 6--1............................................................(2) TAWS/RWS 6--2.......................................................
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.TC--7Section PageC. T2CAS Aural and Visual Annunciations 6--4..................................(1) TCAS Aural and VSI/TRA Annunciations 6--4.............................(2) TAWS/RWS Aural and Visual Annunciations 6--6..........................D. T2CAS Test Menu and System Status Pages 6--7.............................(1) TCAS Test Menu and System Status Pages 6--7..........................(2) TAWS/RWS Test Menu and System Status Pages 6--20.....................E. T2CAS Computer Unit Self--Test 6--25.........................................F. Directional Antenna Test / Fault Isolation Procedure 6--29.......................MAINTENANCE PRACTICES 7--1..................................................1. General 7--1..................................................................2. Equipment and Materials 7--1...................................................3. Procedure for the TT--950/951/952 T2CAS Computer Unit 7--2......................A. Removal and Installation Procedure 7--2.....................................B. Adjustment Procedure 7--2.................................................C. Repair Procedure 7--2.....................................................D. Return to Service Procedures 7--2...........................................4. Procedure for the APM 7--2.....................................................A. Removal and Installation Procedure 7--2.....................................B. Adjustment Procedure 7--3.................................................C. Repair Procedure 7--3.....................................................D. Return to Service Procedures 7--3...........................................5. Procedure for the Directional Antenna 7--4.......................................A. Removal and Installation Procedure 7--4.....................................B. Adjustment Procedure 7--5.................................................C. Repair Procedure 7--5.....................................................D. Return to Service Procedures 7--5...........................................6. Procedure for the Omnidirectional Antenna 7--5...................................A. Removal and Installation Procedure 7--5.....................................B. Adjustment Procedure 7--6.................................................C. Repair Procedure 7--6.....................................................D. Return to Service Procedures 7--6...........................................
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.TC--8Section Page7. Procedure for the GPS Antenna 7--7.............................................A. Removal and Installation Procedure 7--7.....................................B. Adjustment Procedure 7--7.................................................C. Repair Procedure 7--7.....................................................D. Return to Service Procedures 7--7...........................................8. Procedure for the Control Panel 7--7.............................................A. Removal and Installation Procedure 7--7.....................................B. Adjustment Procedure 7--7.................................................C. Repair Procedure 7--7.....................................................D. Return to Service Procedures 7--7...........................................9. Procedure for the VSI/TRA Display 7--8..........................................A. Removal and Installation Procedure 7--8.....................................B. Adjustment Procedure 7--8.................................................C. Repair Procedure 7--8.....................................................D. Return to Service Procedures 7--8...........................................10. Procedure for the Transponder 7--9..............................................A. Removal and Installation Procedure 7--9.....................................B. Adjustment Procedure 7--9.................................................C. Repair Procedure 7--9.....................................................D. Return to Service Procedures 7--10...........................................11. Instructions for Continued Airworthiness, FAR Part 25.1529 7--11....................INSPECTION/CHECK 8--1.........................................................1. General 8--1..................................................................2. Equipment and Materials 8--1...................................................3. Procedure 8--1................................................................A. Check T2CAS Computer Unit 8--1...........................................B. Check Antennas 8--1......................................................C. Check Control Panel 8--1...................................................D. Check VSI/TRA Display 8--2................................................E. Check Transponders 8--2...................................................
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.TC--9Section PageCLEANING/PAINTING 9--1.........................................................1. General 9--1..................................................................2. Equipment and Materials 9--1...................................................3. Cleaning 9--2.................................................................A. Clean T2CAS Computer Unit and Mounting Tray 9--2..........................B. Clean Antennas 9--2.......................................................C. Clean Control Panel 9--2...................................................D. Clean VSI/TRA Display 9--3................................................E. Clean Transponders 9--3...................................................4. Painting 9--3..................................................................A. TCAS Directional Antennas 9--3.............................................(1) Scope 9--3............................................................(2) Procedure 9--3........................................................(3) Performance Verification Testing 9--4....................................B. Other T2CAS System LRUs 9--5.............................................REPAIRS 10--1....................................................................1. General 10--1..................................................................APPENDIX A A--1.................................................................APPENDIX B B--1.................................................................
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.TC--10List of IllustrationsFigure PageFigure 1--1. TCAS ll Advisory Capabilities 1--8.....................................Figure 1--2. TCAS/Mode S Communication 1--9...................................Figure 1--3. TA/RA Airspace Coverage 1--10.......................................Figure 1--4. Basic TCAS ll Installation 1--11........................................Figure 1--5. Typical System Configurations 1--15....................................Figure 1--6. T2CAS System Aircraft Interface 1--17..................................Figure 1--7. TCAS Function System Block Diagram 1--19............................Figure 1--8. TT--950/TT--952 T2CAS Computer Unit (TT--951 Similar) 1--22............Figure 1--9. T2CAS Airplane Personality Module (APM) 1--35.........................Figure 1--10. Directional Antenna 1--37.............................................Figure 1--11. Typical T2CAS GPS Antenna Coax Sub Kit 1--40........................Figure 1--12. Typical Gables ATC/TCAS Control Panel 1--41..........................Figure 1--13. Typical VSI/TRA Display Formats 1--45.................................Figure 1--14. VSI/TRA Interface Diagram (41--Pin) 1--48..............................Figure 1--15. Typical T2CAS Single Terrain Hazard Display Interface 1--50..............Figure 1--16. XS--950 Data Link Transponder 1--51..................................Figure 1--17. RCZ--852 Diversity Mode S Transponder 1--56..........................Figure 1--18. TCAS ll Display Test Pattern 1--68.....................................Figure 1--19. Mode 1 -- Excessive Descent Rate Envelope 1--69.......................Figure 1--20. Mode 2 -- Excessive Terrain Closure Rate Envelope 1--69.................Figure 1--21. Mode 3 -- Excessive Altitude Loss After Take Off Envelope 1--70...........Figure 1--22. Mode 4 -- Unsafe Terrain Clearance Envelope 1--71......................Figure 1--23. Mode 5 -- Excessive Glide Path Deviation Envelope 1--71.................Figure 1--24. Excessive Bank Angle Envelope 1--72..................................Figure 1--25. Windshear Detection 1--73............................................Figure 1--26. Terrain Slices 1--74...................................................Figure 1--27. Terrain Display Background 1--75......................................Figure 1--28. Alert Line 1--76......................................................Figure 1--29. Terrain Hazard Display Upon Caution Alert 1--76.........................Figure 1--30. Terrain Hazard Display Upon A Pull--up Warning 1--77....................Figure 1--31. Terrain Hazard Display Upon An Avoid Terrain Warning 1--78..............Figure 1--32. Standard Self--Test of TAWS/Windshear Functional Areas 1--82...........
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.TC--11List of Illustrations (cont)Figure PageFigure 1--33. TAWS Display Test Pattern 1--83.......................................Figure 2--1. ACSS King Air C90 TAWS Control Panel/GlareshieldSwitch Annunciators 2--6............................................Figure 2--2. Typical Five--Button B737/757/767 Annunciator Switch Panels 2--7.......Figure 2--3. Typical Single Terrain Hazard Display Annunciator Switch Panel 2--8......Figure 2--4. GPS Antenna Outline and Installation Drawing 2--11.....................Figure 2--5. APM Outline and Installation Drawings 2--13............................Figure 2--6. TT--950/952 T2CAS Computer Unit Outline and Installation Drawing 2--17..Figure 2--7. TT--951 T2CAS Computer Unit Outline and Installation Diagram 2--25......Figure 2--8. XS--950 Data Link Transponder Outline and Installation Diagram 2--29.....Figure 2--9. RCZ--852 Mode S Transponder Outline and Installation Diagram 2--33.....Figure 2--10. TCAS Directional and Omnidirectional Antenna Locations 2--39...........Figure 2--11. Directional Antenna Angular Orientation 2--40...........................Figure 2--12. Directional Antenna Outline and Installation Diagram 2--41................Figure 2--13. Directional Antenna Baseplate Outline and Installation Diagram 2--51......Figure 2--14. Gables G130--XX Control Panel Outline and Installation Diagram 2--55.....Figure 2--15. VSI/TRA Outline and Installation Diagram 2--57..........................Figure 3--1. Typical TCAS Installation Types 3--3..................................Figure 3--2. T2CAS Computer Tray Mating Connector 3--5..........................Figure 3--3. Contact Arrangement for CU Left Top Plug (LTP) Insert 3--6..............Figure 3--4. Contact Arrangement for CU Left Middle Plug (LMP) Insert 3--6..........Figure 3--5. Contact Arrangement for Left Bottom Plug (LBP) Insert 3--7..............Figure 3--6. Contact Arrangement for Right Top Plug (RTP) Insert 3--8...............Figure 3--7. Contact Arrangement for Right Middle Plug (RMP) Insert 3--9............Figure 3--8. Contact Arrangement for Right Bottom Plug (RBP) Insert 3--10............Figure 3--9. TCAS Computer Unit Data Loader Connector (J1) Pin Layout 3--11........Figure 3--10. VSI/TRA 41--Pin Connector Layout 3--17...............................Figure 3--11. Typical T2CAS Single Terrain Hazard Display Interface 3--19..............Figure 3--12. Strap Assembly 3--35.................................................Figure 5--1. VSI/TRA Fault Warning Display 5--3...................................Figure 5--2. Extended Self--Test of TAWS/Windshear Functional Areas 5--8...........Figure 5--3. RS--232 PC to TCAS Interface Cable 5--17..............................
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.TC--12List of Illustrations (cont)Figure PageFigure 6--1. TCAS Test Menu Page 6--7..........................................Figure 6--2. Typical System Status Page 6--8......................................Figure 6--3. Typical Display Status Page 6--9......................................Figure 6--4. Typical RAD/ALT Status Page 6--10....................................Figure 6--5. Typical Transponder (XPDR) Status Page 6--11.........................Figure 6--6. Typical Program Pins 1/3 Page 6--12...................................Figure 6--7. Typical Program Pins 2/3 Page 6--13...................................Figure 6--8. Typical Program Pins 3/3 Page 6--14...................................Figure 6--9. Help Reference Page 6--16...........................................Figure 6--10. Suppression Bus Fail Page 6--16......................................Figure 6--11. Suppression Bus Clear Page 6--18.....................................Figure 6--12. Typical Antenna Port Status Page 6--18................................Figure 6--13. Typical Option Pins Status Page 6--19..................................Figure 6--14. Extended Self--Test Page (Page 1) 6--21................................Figure 6--15. Extended Self--Test Page (Page 1 of 6) 6--22............................Figure 6--16. Part Numbers Page 1 (Page 2 of 6) 6--23...............................Figure 6--17. Part Numbers Page 2 (Page 3 of 6) 6--23...............................Figure 6--18. Part Numbers Page 3 (Page 4 of 6) 6--24...............................Figure 6--19. Part Numbers Page 4 (Page 5 of 6) 6--24..............................Figure 6--20. Part Numbers Page 5 (Page 6 of 6) 6--25...............................Figure B--1. T2CAS King Air C90 Interface Block Diagram B--5.......................
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.TC--13List of TablesTable PageAcronyms and Abbreviations Table INTRO--2.............................................Table 1--1. System Components Manufactured by ACSS 1--2.....................Table 1--2. System Components Not Manufactured by ACSS 1--3.................Table 1--3. Directional Antenna Configurations 1--4..............................Table 1--4. Control Panel Configurations 1--5....................................Table 1--5. VSI/TRA Display Configurations 1--5..................................Table 1--6. TT--950/951/952 T2CAS Computer Unit Leading Particulars 1--23.........Table 1--7. GPS Antenna Coax Kit Parts List 1--40.................................Table 1--8. Gables G7130 Series Control Panel Leading Particulars 1--42............Table 1--9. VSI/TRA Leading Particulars 1--46....................................Table 1--10. XS--950 Data Link Transponder Leading Particulars 1--52................Table 1--11. RCZ--852 Diversity Mode S Transponder Leading Particulars 1--57.......Table 1--12. TCAS Traffic Symbols 1--62..........................................Table 1--13. TAWS/RWS Aural Alerts 1--78........................................Table 1--14. Aural Annunciation 1--84.............................................Table 2--1. Coax Cable/Connector Loss 2--4.....................................Table 3--1. Gables G7130--XX ATC/TCAS Control Panel Interconnect Data 3--12.....Table 3--2. 41--Pin VSI/TRA Interconnect Data 3--14..............................Table 3--3. XS--950 Data Link Transponder Interconnect Data 3--21.................Table 3--4. RCZ--852 Diversity Mode S Transponder Interconnect Data 3--29.........Table 3--5. Strap Assembly Strap Assignments 3--34..............................Table 3--6. Strap Assembly Programming Instructions 3--35........................Table 4--1. TT--950/951/952 T2CAS Computer Unit Interface Description 4--2.......Table 4--2. Gables Control Panel Interface Description 4--26.......................Table 4--3. 41--Pin VSI/TRA Interface Description 4--29............................Table 4--4. XS--950 Data Link Transponder Interface Description 4--35..............Table 4--5. RCZ--852 Diversity Mode S Transponder Interface Description 4--44......Table 4--6. TAWS/RWS Non--Configurable Pinout 4--50............................Table 4--7. Callout Configuration Items 4--56......................................Table 4--8. Operator Selectable Options -- Default Settings 4--57....................Table 4--9. APM/ASDB Programmable Analog Inputs 4--63.........................Table 4--10. Analog Input Voltage Ranges 4--66....................................
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.TC--14List of Tables (cont)Table PageTable 4--11. Analog Input Impedance 4--67........................................Table 4--12. 3W Synchro AC References 4--67.....................................Table 4--13. APM/ASDB Programmable Digital Inputs 4--68..........................Table 4--14. APM/ASDB Programmable Digital Outputs 4--69........................Table 4--15. Source Destination Identifier (SDI) 4--70................................Table 4--16. Sign Status Matrix (SSM) [BNR] 4--70..................................Table 4--17. Sign Status Matrix (SSM) [BCD] 4--71..................................Table 4--18. APM/ASDB Programmable Discrete Inputs 4--72........................Table 4--19. APM/ASDB Programmable Discrete Outputs 4--73......................Table 4--20. Navigation Accuracy 4--79............................................Table 4--21. True Display Orientation Left 4--84.....................................Table 4--22. True Display Orientation Right 4--84...................................Table 4--23. A429 Output Bus GCAM Event Data Labels 4--87.......................Table 4--24. OMS Label 350 Discretes 4--89.......................................Table 4--25. OMS Label 351 Discretes 4--90.......................................Table 4--26. OMS Label 352 Discretes 4--91.......................................Table 5--1. Equipment 5--1....................................................Table 5--2. Computer Unit Harness Checkout 5--1...............................Table 5--3. Extended Test Menu Selections 5--5.................................Table 5--4. Compact Flash Upload / LED correlation 5--13..........................Table 6--1. TCAS Aural and VSI/TRA Annunciations 6--4.........................Table 6--2. System Status Page Fault Messages 6--8............................Table 6--3. Computer Unit Self--Test Execution 6--26..............................Table 6--4. TCAS Fault Reporting and Corrective Actions 6--28.....................Table 6--5. Antenna Wiring Resistance 6--29......................................Table 7-- 1. Materials 7--1.....................................................Table 9--1. Equipment and Materials 9--1.......................................Table 10--1. LRU Maintenance Manual 10--1......................................Table B--1. Aircraft Configuration B--3...........................................
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.INTRO--1INTRODUCTION1. GeneralThis manual provides general system installation and maintenance instructions and theory ofoperation for the T2CAS Traffic and Terrain Collision Avoidance System. It also providesinterface information and interconnect diagrams to permit a general understanding of theoverall system.The purpose of this manual is to help install, operate, maintain and troubleshoot the T2CASTraffic and Terrain Collision Avoidance System in the aircraft. Common system maintenanceprocedures are not presented in this manual. The best established shop and flight linepractices should be used.NOTE:The conditions and tests required for Technical Standard Order (TSO) approval ofthis article are minimum performance standards. It is the responsibility of thoseinstalling this article either on or within a specific type or class of aircraft to determinethat the aircraft installation conditions are within the TSO standards. The article maybe installed only if the installation is performed in accordance with the applicableairworthiness and production requirements.2. Reference DocumentsPublications on subsystems installed as part of the T2CAS Traffic and Terrain CollisionAvoidance System are identified in the list that follows:Document TitleHoneywellPublication NumberMode S Data Link Transponder System Description and InstallationManualA09--3839--001PRIMUS ll SRZ--85X Series Integrated Radio System Operation andInstallation Manual (Used if transponders or control panel is part ofPRIMUS II Integrated Radio System)A15--3800--01Handling, Storage, and Shipping Procedures Instruction Manual forAvionics EquipmentA09--1100--01
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.INTRO--23. Weights and MeasurementsWeights and measurements in this manual use both U.S. and S.I. (metric) values.4. Acronyms and AbbreviationsThe letter symbols for abbreviations are the same as shown in ANSI/IEEE Std 260 and ASMEY1.1, except as identified in the acronyms and abbreviations table.Acronyms and Abbreviations TableTerm Definitionac alternating currentACD APM configuration dataADC air data computerADIRS air data inertial reference systemADL airborne data loaderADLP airborne data link processorADS--B automatic dependent surveillance broadcastAGL above ground levelAHRS attitude heading and reference systemALT altitudeAMM aircraft maintenance manualANT antennaAPM airplane personality moduleATC air traffic controlATCRBS air traffic control radar beacon systemATN Aircraft Telecommunications NetworkASDB aircraft specific databaseBITE built--in test equipmentBOT bottomBNR binaryCAS collision avoidance systemCFDIU centralized fault display interface unitCFDS central fault display systemCFIT controlled flight into terrainCMC central maintenance computer
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.INTRO--3Acronyms and Abbreviations Table (cont)Term DefinitionCMM component maintenance manualCPA collision prediction and alertingCOMM communicationCRC cyclic redundancy checkCU computer unitDADC digital air data computerdc direct currentDISP displayDH/MDA decision height/minimum descent altitudeDLP data link processorDSWC digital stall warning computerEFIS electronic flight instrument systemELM extended length messageEPROM erasable programmable read--only memoryFAA Federal Aviation AdministrationFDR flight data recorderFPM feet per minuteFMS flight management systemGCAM ground collision avoidance moduleGPS global positioning systemGPWS Ground Proximity Warning SystemHDG headingHMN Honeywell Material NumberI/O input/outputINH inhibitIPC illustrated parts catalogIRS inertial reference systemLBP left bottom plugLCD liquid crystal displayLMP left middle plugLRU line replaceable unit
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.INTRO--4Acronyms and Abbreviations Table (cont)Term DefinitionLSB least significant bitLTP left top plugMCU modular concept unitMEL minimum equipment listMode S mode select transponderMSB most significant bitMTBF mean time between failuresMTL minimum trigger levelOMS on--board maintenance systemPDL portable data loaderPMS performance management systemPOST power--on self--testPROG programPTM pressure transducer moduleRA resolution advisoryRAD ALT radio altimeterRBP right bottom plugRCB radio communication busRMP right middle plugRMU radio management unitRNG rangeRTP right top plugRWS reactive windshearSDI source destination identifierSPI special pulse identifierSSM sign status matrixSTBY standbyTA traffic advisoryTAWS terrain awareness warning systemTCAS traffic alert and collision avoidance systemT2CAS traffic and terrain collision avoidance system
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.INTRO--5Acronyms and Abbreviations Table (cont)Term DefinitionTRA traffic resolution advisoryTSO Technical Standard OrderVSI vertical speed indicatorVSWR voltage standing wave radioWOW weight--on--wheelsXPDR transponder
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.INTRO--65. Special PrecautionsWarnings, cautions, and notes in this manual give the data that follows:•A WARNING is an operation or maintenance procedure or condition, which, if not obeyed,can cause injury or death•A CAUTION is an operation or maintenance procedure or condition, which, if not obeyed,can cause damage to the equipment•A NOTE gives data to make the work easier or gives directions to go to a procedure.All personnel who operate and do maintenance on the TCAS components and on theapplicable test equipment, must know and obey the safety precautions. The warnings andcautions that follow apply to all parts of this manual.WARNING: HIGH VOLTAGES MAY BE PRESENT ON SYSTEM INTERCONNECT CABLES. MAKESURE THAT SYSTEM POWER IS OFF BEFORE YOU DISCONNECT LRU MATINGCONNECTORS.CAUTION: ACSS HAS PREPARED AN AIRWORTHINESS CRITICAL REQUIREMENTS ANALYSISFOR THIS AIRBORNE EQUIPMENT TO MAKE SURE THAT IT WILL NOT CAUSE ADANGEROUS IN--FLIGHT CONDITION. SPECIFIC PARTS, TESTS, AND PROCEDURESTHAT ARE IDENTIFIED AS INSTALLATION CRITICAL IN THE ANALYSIS ARE CHANGEDTO AIRWORTHINESS CRITICAL IN THIS MANUAL. IT IS NECESSARY TO DO THESEPROCEDURES AND TESTS TO GET THE APPROVED RESULTS.CAUTION: THE T2CAS SYSTEM CONTAINS LRUS THAT ARE ELECTROSTATIC DISCHARGESENSITIVE (ESDS). IF YOU DO NOT OBEY THE NECESSARY CONTROLS, A FAILUREOR UNSATISFACTORY OPERATION OF THE UNIT CAN OCCUR FROM ELECTROSTATICDISCHARGE. USE APPROVED INDUSTRY PRECAUTIONS TO KEEP THE RISK OFDAMAGE TO A MINIMUM WHEN YOU TOUCH, REMOVE, OR INSTALL LRUS.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--1SYSTEM DESCRIPTION1. GeneralThe T2CAS Traffic and Terrain Collision Avoidance System combines a terrain awarnesswarning system (TAWS) with the existing TCAS 2000 line replaceable unit (LRU) to form acombined system (T2CAS). Optionally, the T2CAS may contain Reactive Windshear (RWS)and/or global positioning satellite (GPS) functions within the same LRU. The integration of thefunctions provides significant cost and space advantages to the customer. Theimplementation method used preserves the independence of the TCAS, TAWS ReactiveWindshear and GPS functions within the T2CAS LRU. The system reliability for the T2CASLRU is greater than a federated system with separate TCAS, TAWS and RWS LRUs.The TCAS function, within T2CAS, determines the range, altitude, and bearing of other aircraftequipped with Mode S/Air Traffic Control Radar Beacon System (ATCRBS) transponders, withrespect to the location of own aircraft. It also monitors the trajectory of these aircraft for thepurpose of determining if any of them constitute a potential collision hazard. The TCASfunction is responsible for estimating the projected intruder track and determining if a potentialconflict exists. If so, the system displays an advisory to the pilot. The system also providesguidance for the optimum vertical avoidance maneuver. Complementary avoidancemaneuvers between two TCAS equipped aircraft are ensured by coordination of mutualintentions with the other aircraft through the Mode S Transponders. T2CAS TCAS meets therequirements of TSO--C119b.The T2CAS TAWS function, within the T2CAS, provides both Collision Prediction and Alerting(CPA) as well as conventional Ground Proximity Warning System (GPWS) modes ofoperation. The CPA uses data provided by the Flight Management Computer, the GPSreceiver, and other aircraft subsystems to predict a 3--D flight path based upon a curve--fitextrapolation of the most recent position and velocity data received. This predicted flight pathis then compared with the internal terrain profile of the immediate area and the CPA algorithmcomputes an assessment of the potential threat of aircraft collision with terrain. Whenoperative, CPA replaces RTCA DO--161A reactive modes 1 and 2 since it offers superiorsafety margins for controlled flight into terrain (CFIT) prevention due to its predictivecapabilities. Since modes 1 and 2 are the primary source of nuisance alerts, suppressingthese alerts greatly reduces the nuisance alert rate and thus improves pilot confidence in thesystem. T2CAS TAWS meets the requirements of TSO--C151a Class A.A Reactive Windshear function is integrated in T2CAS when necessary to meet the aircraftapplication, and meets the requirements of TSO--C117a.The T2CAS RWS function incorporates a Reactive Windshear feature as part of its basicfunctionality. It conforms to the Windshear Warning capabilities described in TSO C117awithout the guidance feature. The reactive Windshear Warning algorithm continuouslymonitors wind factors that affect aircraft performance on both take--off and landing approach,in order to identify the presence of a severe low--level, downburst/microburst--type shear. Ifthese wind factors cause aircraft performance to decrease to a predetermined level, an audiowarning is sounded, indicating to the crew that the aircraft net performance capability isdeteriorating and rapidly approaching a critical state. In addition to the warning, theWindshear Warning algorithm provides a caution when an increasing--performance Windshearis detected, thus giving advance warning of decreasing--performance windshear.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--22. System ComponentsTable 1--1 gives the components that are supplied by ACSS. Table 1--2 gives the componentsthat are necessary, but are not manufactured by ACSS.Table 1--3 thru Table 1--5 provide additional component descriptions as follows:•Table 1--3. Directional Antenna Configurations•Table 1--4. Control Panel Configurations•Table 1--5. VSI/TRA Display Configurations.Table 1--1. System Components Manufactured by ACSSComponent Model No. ACSS Part No.T2CAS Computer Unit (6--MCU size unit without GPS) TT--950 9000000--10001T2CAS Computer Unit (6--MCU size unit with GPS) TT--952 9000000--20001T2CAS Computer Unit (4--MCU size unit without GPS) TT--951 9000000--55001Directional Antenna (See Table 1--3 for configurationdescriptions)-- -- 7514081--VAR or7514060--VARGPS Antenna (Required with T2CAS Model TT--952) -- -- AT575--143WAC--T N C F -- 0 0 0 -- 0 6 -- N MorAT575--143WAC--T N C F -- 0 0 0 -- 3 0 -- N MTAWS Terrain Display (3 ATI or 5 ATI) -- -- TBD -- Not yetavailable for deliveryTAWS Control Panel -- -- N/A -- InstallationspecificAPM AP--950 9000001--10001Mode S Data Link Transponder (4--MCU size unit) XS--950 7517800--xxyyyDiversity Mode S Transponder RCZ--852 7510700--850Installation Kit for RCZ--852 Mode S Transponder(Contains mounting tray, 106 pin ARINC 404 matingconnector and two TNC RF jack connectors)IK--415 7510707--968NOTE: The 3--ATI panel mount comes in three different color options: --901 (gray), --902 (brown),and --903 (black).
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--3Table 1--2. System Components Not Manufactured by ACSSComponent CommentsGables G7130 Series ATC/TCAS Dual Transponder ControlPanel (Note 1.)General aviation type controller thatoperates from 28 V dc aircraft power(Note 2.)Gables G6990, G6991, G6992 and G6993 SeriesMode S/TCAS Control Panels (Note 1.)Commercial aviation type controllersthat operate from 115 V ac aircraftpower (Note 2.)Gables G7491Flight ID Control PanelCommercial aviation type Flight IDControl Panel that operates from 115V ac aircraft power (Note 2.)Omnidirectional TCAS Antenna (Note 4.) ATC blade antenna, dc shorted, TSOC119b compliant,1030 to 1090 MHz.Installer to supply antenna.Omnidirectional ATC Antennas (Note 5.) ATC blade antenna, dc shorted, TSOC112 compliant, 1030 to 1090 MHz.Installer to supply antenna.GPS Antenna Coax Cable TBDThales VSI/TRA (Note 3.) High resolution LCD flat panel VerticalSpeed Indicator with TCAS II data inRA and TA modes.Mounting Tray, T2CAS Computer (6--MCU size unit) ARINC 600 6--MCU Mount, cooling airrequired. Installer to supply mount.Mounting Tray, T2CAS Computer (4--MCU size unit) ARINC 600 4--MCU Mount, no coolingair required. Installer to supply mount.Mounting Tray, Data Link Transponder (4--MCU size unit) ARINC 600 4--MCU Mount, cooling airrecommended but not required.Installer to supply mount.NOTES:1. Refer to Table 1--4 for individual part number descriptions.2. For additional information, pricing and availability contact:Gables Engineering, Inc. 247 Greco Avenue, Coral Gables, Florida 33146Telephone (305) 774--4400Fax (305) 774--44653. For additional information, pricing and availability contact:Thales Communications, Inc.Aviation Electronics Division22605 Gateway Center DriveCLARKSBURG, MD 20871--2001, USATelephone +1 (240) 864--76394. A bottom omnidirectional antenna can be used as an optional replacement for the directionalantenna.5. A diversity transponder installation requires both a top and bottom ATC antenna.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--4Table 1--3. Directional Antenna ConfigurationsAntennaPart Number Description7514081--901 Directional antenna with flat base, four hole mounting pattern, and 1.560--inchconnector extension length7514081--902 Directional antenna with flat base, eight hole mounting pattern, and 1.560--inchconnector extension length7514081--903 Directional antenna with a curved 61.52--inch radius base, eight hole mountingpattern, and 1.560--inch connector extension length7514081--904 Directional antenna with a curved 66.52--inch radius base, eight hole mountingpattern, and 1.560--inch connector extension length7514081--905 Directional antenna with a curved 74.02--inch radius base, eight hole mountingpattern, and 1.560--inch connector extension length7514081--906 Directional antenna with a curved 77.78--inch radius base, eight hole mountingpattern, and 1.560--inch connector extension length7514081--907 Directional antenna with a curved 99.02--inch radius base, eight hole mountingpattern, and 1.560--inch connector extension length7514081--908 Directional antenna with a curved 111.02--inch radius base, four hole mountingpattern, and 1.560--inch connector extension length7514081--909 Directional antenna with a curved 118.52--inch radius base, eight hole mountingpattern, and 1.560--inch connector extension length7514081--910 Directional antenna with a flat base, eight hole mounting pattern, and 0.705--inchconnector extension length7514081--911 Directional antenna with a curved 77.78--inch radius base, eight hole mountingpattern, special 0.015--inch Teflon gasket, and 1.560--inch connector extensionlength7514081--912 Directional antenna with a curved 111.02--inch radius base, eight hole mountingpattern, special 0.015--inch Teflon gasket, and 1.560--inch connector extensionlength7514081--913 Directional antenna with a flat base, four hole mounting pattern, and 0.705--inchconnector extension length7514081--914 Directional antenna with a curved 53.02--inch radius base, eight hole mountingpattern, and 0.705--inch connector extension length7514081--915 Directional antenna with a curved 44.80--inch radius base, eight hole mountingpattern, and 0.705--inch connector extension length7514081--916 Directional antenna with a curved 42.00--inch radius base, eight hole mountingpattern, and 0.705--inch connector extension length7514081--917 Directional antenna with a curved 85.06--inch radius base, eight hole mountingpattern, and 1.560--inch connector extension length
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--5Table 1--4. Control Panel ConfigurationsGables Control PanelsGables G7130--02 Control Panel, Dual Mode S/TCAS, Rotary knob 4096 code entry, Black Bezel,Operates from +28 V dc aircraft powerGables G7130--05 Control Panel, Dual Mode S/TCAS, Rotary knob 4096 code entry, Gray Bezel,Operates from +28 V dc aircraft powerGables G7130--06 Control Panel, Dual Mode S/TCAS, Rotary knob 4096 code entry, Black Bezel,Extended Range (80, 120 Mi), Operates from +28 V dc aircraft powerGables G7130--07 Control Panel, Dual Mode S/TCAS, Rotary knob 4096 code entry, Gray Bezel,Extended Range (80, 120 Mi), Operates from +28 V dc aircraft powerGables G6990--XX Control Panel, Dual Mode S/TCAS, Pushbutton 4096 code entry, Operates from 115V ac aircraft powerGables G6991--XX Control Panel, Single Mode S--Single ATCRBS/TCAS, Pushbutton 4096 code entry,Operates from 115 V ac aircraft powerGables G6992--XX Control Panel, Dual Mode S/TCAS, Rotary knob 4096 code entry, Operates from 115V ac aircraft powerGables G6993--XX Control Panel, Single Mode S--Single ATCRBS/TCAS, Rotary knob 4096 code entry,Operates from 115 V ac aircraft powerGables G7491--XX Control Panel, Flight ID (Only), Operates from 115 V ac aircraft powerTable 1--5. VSI/TRA Display ConfigurationsVSI/TRAPart Number DescriptionThales VSI/TRA The VSI/TRA Display provides continuous TCAS symbology and non--ARINC displaycontrol features: mile ranges and above/normal/below display volumes. It has pinprogrammable altitude band, range, lighting curve, and VSI source selection.457400xxyyyy xx = Hardware Version as defined in Table TBDyyyy = Software Version as defined in Table TBD
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--63. System DescriptionThe T2CAS is a safety system that combines TCAS, Terrain Awareness and Warning System(TAWS), and optionally Reactive Windshear (RWS) and/or GPS functions in a single LRU.The TCAS function is an onboard advisory system designed to act as a backup to the airtraffic control (ATC) radar and the “see and avoid” procedures. By computing the closure rateand altitude of all transponder equipped aircraft in the surrounding airspace, the TCAS cananticipate a potential midair collision before it has a chance to materialize.TCAS continually plots local air traffic on the associated display, and in the event of aconflicting flightpath, guides the pilot towards the correct avoidance maneuver. If the intrudingaircraft is also equipped with a TCAS II compatible system, the two systems can communicatetheir mutual intentions through the Mode S transponders. The coordinated advisories thatresult allow the two pilots to execute complementary avoidance maneuvers.TCAS complies with ARINC Characteristic 735a (TCAS) and the requirements of TSO--C119b.The TAWS function within T2CAS features an innovative design aimed at preventing CFIT(Controlled Flight Into Terrain) accidents by providing timely aircrew alerts. The alerts arebased upon predicted terrain clearance profiles calculated with present aircraft climbcapabilities. This represents a significant advance in capability from the present GroundProximity Warning System (GPWS) technology, and a significant improvement in CFIT safetymargins over existing Terrain Awareness and Warning System (TAWS) designs:•By providing warnings based on remaining time before pilot response is required and notbased on remaining time to terrain impact•By covering more operational situations•By drastically minimizing nuisance alerts.As an optional part of the TAWS system, T2CAS incorporates a Reactive Windshear featureas part of its basic functionality. It conforms to the Windshear Warning capabilities describedin TSO C117a without the guidance feature. The Reactive Windshear function monitors windfactors that affect aircraft performance on both take--off and landing approach, in order toidentify the presence of a severe low--level, downburst/microburst--type windshear.A. System Functional Description(1) TCAS Functional DescriptionSituational awareness is provided to the flight crew by aiding in visually acquiringintruding aircraft and discriminating between the intruding aircraft, threat aircraft, andother traffic in the airspace.Vertical guidance to avoid midair collisions is accomplished by interrogating the ModeA, Mode C, and Mode S transponders of potential threat aircraft, tracking theirresponses, and providing advisories to the flight crew to assure vertical separation.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--7The first two levels of situational awareness include:•Non--threat Traffic, indicates other targets within the range of the display whoserelative altitude is greater than ±1200 ft. vertically or a distance greater than sixnautical miles from own aircraft.•Proximity Traffic, indicates the target is within ±1200 ft. vertically or within sixnautical miles of own aircraft.The two levels of advisories include:•Traffic advisories (TA) indicate the range, bearing, and relative altitude of theintruder to aid in visual acquisition of the intruder.•Resolution advisories (RA) indicate a vertical maneuver to be performed oravoided in order to assure safe separation.Traffic advisories can be displayed on a Vertical Speed Indicator/Traffic andResolution Advisory (VSI/TRA) display, Electronic Flight Instrument System (EFIS) orany instrument that displays the appropriate symbology and conforms to thedefinition of ARINC Characteristic 735A.Resolution advisories can be displayed on the VSI/TRA display, EFIS or any otherindicator that displays the appropriate symbology and conforms to the definition ofARINC Characteristic 735A.Figure 1--1 shows the various types of intruder equipment and the resultingadvisories. It should be noted that Mode A equipped intruders result in detection anddisplay of TAs only. An intruder not equipped with a transponder is invisible to TCAS.Communication with another TCAS equipped aircraft is provided by an onboarddiversity Mode S transponder. Only one onboard Mode S transponder is required forTCAS operation. However, the ACSS TCAS operates with either of two onboardMode S transponders, one of which operates as a spare. The transponder in use isselectable from the Flight Deck. Figure 1--2 shows the communication between twoTCAS equipped aircraft.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--8Figure 1--1. TCAS ll Advisory Capabilities
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--9Figure 1--2. TCAS/Mode S CommunicationThe TCAS function generates both RAs and TAs when the TA/RA mode is selected.The two types of advisories correspond to time--based protection zones around theaircraft. The airspace around the TCAS aircraft where an RA is annunciatedrepresents the warning area, while the larger airspace which results in a TA beingannunciated is the caution area. Figure 1--3 contrasts the airspace covered by thetwo types of advisories.The onboard equipment listed below must be linked to the TCAS function as shownin Figure 1--4.•Mode S transponder with associated antennas•Radio altimeter•Air Data Computer (ADC) (digital or analog). If an ADC does not support verticalspeed rate data, the static line can be run directly into the Thales VSI/TRA.•ATC/TCAS control panel. A separate control panel is not the only method ofcontrol for the TCAS. Other components, such as a Radio Management Unit(RMU) can be used.•Omnidirectional antenna. The TCAS function accepts two types of bottomantennas: A standard directional antenna or an optional ATC--typeomnidirectional antenna. If an omnidirectional antenna is installed, it must besupplied by the installer. If a directional antenna is installed at both top andbottom antenna locations, a bottom omnidirectional antenna is not needed.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--10Figure 1--3. TA/RA Airspace Coverage
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--11Figure 1--4. Basic TCAS ll Installation(2) TAWS Functional DescriptionThe T2CAS TAWS function provides guidance to prevent Controlled Flight IntoTerrain (CFIT). This is accomplished by using vertical speed, ground speed, trackangle, flight path angle, latitude, longitude, flap status, steep approach status, staticair temperature, roll angle, pressure altitude and radio altitude inputs along with abuilt--in database for determination of alerts and display of terrain information.The following advanced functional capabilities are featured in the T2CAS TAWSfunction.(a) Collision Prediction and Alerting (CPA) ModeThis mode provides medium--term (caution) and short--term (warning) alertswhen the predicted flight path will bring the aircraft dangerously close to nearbyterrain. When operative, CPA replaces RTCA DO--161A reactive modes 1 and 2since it offers superior safety margins for CFIT prevention due to its predictivecapabilities.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--12T2CAS uses data provided by the Flight Management Computer, the GPSreceiver, and other aircraft subsystems to predict a 3--D flight path based upon acurve--fit extrapolation of the most recent position and velocity data received.This predicted flight path is then compared with the internal terrain map of theimmediate area and an assessment of the potential threat of aircraft collision withterrain is computed by the Collision Prediction and Alerting (CPA) algorithm.(b) Conventional GPWS Modes of Operation.1Mode 1: Excessive rate of descent with respect to terrainWhen the CPA mode is inoperative, this mode provides not only a reactiveshort--term warning as defined in RTCA DO--161A, but also a reactivemedium--term caution when the current flight path is descending toward theterrain ahead of the aircraft at an excessive rate.2Mode 2: Excessive closure rate to terrainWhen the CPA mode is not operative, this mode provides a reactiveshort--term warning as defined in RTCA DO--161A when the current flightpath and the terrain ahead of the aircraft are closing at an excessive rate.3Mode 3: Excessive altitude loss after take--offT2CAS meets the requirement for Mode 3 alerts as defined in RTCADO--161A. This mode provides an alert when there is a loss of altitude aftertake--off or during a missed approach. The mode uses the radar altimeter todetermine proximity to the ground and the barometric altimeter to determinealtitude loss. If an excessive loss of altitude occurs after take--off, a warningis issued.4Mode 4: Incorrect aircraft configuration with regard to terrainT2CAS meets the requirement for Mode 4 alerts as defined in RTCADO--161A. Mode 4 usually applies during the landing phase of flight andresults in the annunciation of an alert in the event of insufficient terrainclearance when the aircraft is not in the proper landing configuration. Mode4 consists of the following two submodes:•Mode 4A, when the landing gear is up•Mode 4B, when the landing gear is down, but the flaps are not in landingconfiguration.5Mode 5: Excessive glide path deviationT2CAS meets the requirement for Mode 5 alerts as defined in RTCADO--161A. Mode 5 applies in the event of an excessive descent below theinstrument glide path when making a front--course approach with the geardown. In a back--course landing configuration, Mode 5 is automaticallyinhibited.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--136Call--outs and excessive bank angleAs defined in RTCA DO--161A, T2CAS produces call--outs and alerts fordescent below a set of predefined altitudes and for excessive bank angle.(c) Terrain DisplayThe T2CAS TAWS function provides two outputs to ARINC 708A compatibledisplays to provide terrain--related information to the crew through the weatherradar or EFIS displays in order to enhance flight crew situational awareness.When no threat is perceived, the TAWS display shows with different levels ofcolors, the height of the surrounding terrain relative to the aircraft altitude andtaking into account the aircraft flight path angle. Upon detection of a potentialCFIT threat, the terrain texture is modified on the terrain map in order to identifythe location and level (caution/warning) of the threat.(3) RWS Functional DescriptionT2CAS may incorporate optionally a Reactive Windshear feature as part of its basicfunctionality. This feature conforms to the Windshear Warning capabilities describedin TSO C117a without the guidance feature. The reactive Windshear Warningalgorithm continuously monitors wind factors that affect aircraft performance on bothtake--off and landing approach, in order to identify the presence of a severelow--level, downburst/microburst--type windshear.If these wind factors cause aircraft performance to decrease to a predeterminedlevel, an audio warning is sounded, indicating to the crew that the aircraft netperformance capability is deteriorating and rapidly approaching a critical state. Inaddition to the warning, the Windshear Warning algorithm provides a caution whenan increasing--performance Windshear is detected, thus giving advance warning ofdecreasing--performance windshear.(4) GPS Functional DescriptionThe T2CAS may optionally incorporate a Global Positioning System (GPS) receiver.The GPS receiver is a CCA that is independent of both TCAS and TAWS/RWS, andhas an independent processor and I/O circuitry. The GPS receiver is manufacturedand supplied to ACSS by CMC Electronics. The GPS receiver is capable of providingposition information to the T2CAS as well as to other aircraft systems.B. System ConfigurationsThe T2CAS may be installed in different aircraft configurations depending on the currentTCAS, TAWS/RWS and GPS equipment installed on the aircraft. The T2CAS uses anAirplane Personality Module (APM) to hold aircraft specific configuration data for TAWSand RWS functions. The APM is used in place of program pin inputs to provide systemconfiguration. An Aircraft Specific Database (ASDB) provides the aircraft specificinterface requirements for the T2CAS System and is loaded into the APM at the time ofsystem installation.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--14Further breakdown of the TCAS and TAWS/RWS system configurations are detailed inthe sections 1 and 2 that follow.(1) TCAS System ConfigurationThe T2CAS unit’s TCAS function may be installed in several different configurationsdepending on the transponders used and the choice of antennas and displays.Some typical configurations are shown in Figure 1--5. Other combinations arefeasible. Figure 1--7 shows the signals and overall interconnects for a typical T2CASinstallation with dual transponders.•Configuration A shows the TCAS function linked to dual Mode S transponders.The system operates with either transponder, depending on the control panelselection. The second transponder is used as a backup.•Configuration B shows the TCAS function linked to a single transponder Mode Stransponder system.•Configuration C shows the TCAS function to a single Mode S transponder (active)and an ATCRBS transponder (backup). The TCAS only operates when the ModeS transponder is selected.(2) TAWS/RWS System ConfigurationFigure 1--6 illustrates a typical aircraft installation of the T2CAS. The system isdesigned as an integrated safety solution, available as a replacement to the existingTCAS 2000 LRU. Figure 1--7 is a TCAS Function System block diagram.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--15Figure 1--5 (Sheet 1). Typical System Configurations
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--16Figure 1--5 (Sheet 2). Typical System Configurations
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--17Figure 1--6. T2CAS System Aircraft Interface
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--18Blank Page
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--19/(1--20 blank)Figure 1--7. TCAS Function System Block Diagram
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--214. Component DescriptionsA. TT--950/951/952 T2CAS Computer UnitThe T2CAS Computer Unit (CU) is the heart of the T2CAS system consisting of anexisting TCAS 2000 LRU with a TAWS/Reactive Windshear function implemented on aseparate circuit card assembly (CCA). The TAWS/RWS function uses a processor and I/Ocircuitry that is independent from the TCAS function’s processor and I/O. As such, thesoftware programs for TCAS and TAWS/RWS are independent from each other. Byhaving independent hardware, I/O and software for TCAS and TAWS/RWS, the possibilityof a common mode failure causing the loss of both functions is significantly reduced.The TCAS function (CCA) contains the RF transmitter and the receivers necessary tointerrogate and receive replies from other transponder equipped aircraft. Dualmicroprocessors are utilized to implement the surveillance and collision avoidancealgorithms. The algorithms determine whether an intruder aircraft should be considered athreat and then determine the appropriate vertical response to avoid a midair or nearmidair collision. In addition, output data is provided to drive displays that inform the flightcrew what action to take or avoid.The TCAS function also provides an interface to the onboard Mode S transponder inorder to communicate with other TCAS ll equipped aircraft in the airspace.The TAWS/RWS function (CCA) consists primarily of the Ground Collision AvoidanceModule (GCAM). The GCAM contains the core TAWS/Windshear algorithms which utilizeA/C state data, performance database variables and Terrain/Airport database informationto calculate required TAWS/Windshear alarms, build a terrain display buffer, and thenpass the data back to the platform. The resulting terrain information is then output toARINC 708A compatible weather radar or EFIS displays.The T2CAS CU also provides past and present LRU and system status through the frontpanel mounted TEST switch and PASS/FAIL annunciators. Software updates can beincorporated into the computer by an ARINC 603 or 615 data loader port through eitherthe connector mounted on the front panel of the computer or the port provided on theLRU rear connector.Figure 1--8 shows a graphical view of the TT--950/TT--952 T2CAS Computer Unit and theTT--951 T2CAS Computer Unit. Table 1--6 provides the leading particulars.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--22Figure 1--8. TT--950/TT--952 T2CAS Computer Unit (TT--951 Similar)
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--23Table 1--6. TT--950/951/952 T2CAS Computer Unit Leading ParticularsItem SpecificationDimensions (maximum):•Height ....................................... 7.64 in. (194.0 mm)•Width (TT--950/TT--952) ........................ 7.52 in. (191.0 mm)•Width (TT--951) ............................... 4.90 in. (124.5 mm)•Length ....................................... 15.26 in. (387.6 mm)Weight (maximum):•TT--950 ...................................... 17.60 lb (8.0 kg)•TT--951 ...................................... 15.40 lb (7.0 kg)•TT--952 ...................................... 18.60 lb (8.45 kg)Operating Voltage:•dcVoltage.................................... +20.5 V dc minimum, +27.5 V dcnominal, +32.2 V dc maximum•ac Voltage (TT--950/TT--952 only) ............... 97 V rms minimum, 115 V rms nominal,134 V rms maximum at 400 ¦80 HzPower Consumption (TT--950/TT--951) ............. 70 Watts standby, 100 Watts operationalPower Consumption (TT--952) .................... 83 Watts standby, 113 Watts operationalCircuit Breaker Ratings:•115VacCircuitBreaker ....................... 5 Amp Typical•28VdcCircuitBreaker ........................ 10 Amp TypicalMating Connector:•P1 (Rear Connector) ........................... Radiall Part No. 620--800--066•J1 (Front Connector) .......................... ACSS Part No. 4004295--160,ITT Part No. KJ6F18A53PCooling Requirements:•6 MCU Units (TT--950/952):-- Cooling Requirements ....................... ARINC 600 (blow through) or ARINC404 (draw through)-- MinimumCoolingAirflowRate ................ 54.7 pounds/hour (24.86 Kg/hour)-- PressureDrop(atminairflowrate) ............ 0.2 ±0.12 inches (5 ±3 millimeters) ofwater•4 MCU Units (TT--951):-- Cooling Requirements ....................... NONE -- Unit has an internal fan forcooling. No forced air cooling is requiredor accepted.-- FanOn(controlledbytemperaturesensor) ..... Temp sensor > +45 Deg C
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--24Table 1--6. TT--950/951/952 T2CAS Computer Unit Leading Particulars (cont)Item Specification-- FanOff(controlledbytemperaturesensor) ..... Temp sensor < +25 Deg CMounting:•TT--950/TT--952 ............................... ARINC 600 6--MCU Tray Assembly•TT--951 ...................................... ARINC 600 4--MCU Tray AssemblyTSO:AllUnits(TCAS/TAWS) ..........................All Units (with Reactive Windshear) ................TT--952(withGPS) .............................C119b (with deviation)2, C151AC117AC129ASoftwareDevelopmentSpecification ............... DO--178B, Level BEnvironmental Specifications (TT--950/--952) ........ DO--160D (with deviation)1Environmental Category [(A2)(F2)Y]BBB[(HBR)(RB1)(SM)]EXXXXXZ[EBZ]A[EZ]Z[RR]M[A3E3]XXAEnvironmental Specifications (TT--951) ............. DO--160D (with deviation)1Environmental Category [(A2)(F2)X]BBB[(HBR)(RB1)(SM)]EXXXXXZ[BZ]AZZ[RR]M[A3E3]XXA•Temperature / Altitude [A2F2]:-- OperatingTemperature ...................... --55 to +70 degrees C-- Ground Survival Temperature ................ --55 to +85 degrees C-- Altitude .................................... Sea Level to 55,000 feet-- LossofCooling ............................. +40 degrees C for 300 minutes minimumRF Transmitter Characteristics:•Transmitter Frequency ......................... 1030 ±0.01 MHz•RF Peak Output Power:-- Minimum................................... 53.3 dBm (210 Watts)-- Nominal ................................... 55.3 dBm (335 Watts)-- Maximum .................................. 57.3 dBm (540 Watts)•UnwantedOutputPowerinanInactiveState...... --72 dBm
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--25Table 1--6. TT--950/951/952 T2CAS Computer Unit Leading Particulars (cont)Item Specification•Pulse Timing Characteristics:-- PulseRiseTime ............................ 0.05 to 0.10 microseconds-- PulseFallTime ............................. 0.05 to 0.20 microseconds-- ATCRBS S1,P1,P3,P4Duration ............ 0.08 ±0.05 microseconds-- ModeSP1,P2Duration ..................... 0.08 ±0.05 microseconds-- ModeSP6Duration ........................ 16.25 ±0.125 microseconds (short)30.25 ±0.125 microseconds (long)•Whisper--Shout Characteristics:-- Range ..................................... 0 to 26 dB attenuation by 1 dB steps-- AbsoluteTolerance .......................... Relative to the 0 dB step, the attenuationof each step does not exceed thenominal attenuation by more than ±2dB-- RelativeTolerance .......................... Step increments are ±0.5 dB andmonotonicRF Receiver Characteristics:•Receiver Frequency Range ..................... 1087 to 1093 MHz•Receiver MTL Over Frequency ..................(Normal Operation)-- 7 7 ±2dBm (≥90% Mode S andATCRBS replies decoded)•Receiver Dynamic Range ......................(Normal Operation)--77 to --23 dBm (≥99% Mode S andATCRBS replies for signal levels greaterthanMTL+3dB)•Extended Range Reception Capability ...........(Optional Mode)-- 8 2 ±2dBm (≥90% Mode S squitterreplies decoded)•Low Level Receiver Signal Rejection .............(Normal Operation)--81 dBm (≤10% Mode S and ATCRBSreplies decoded)•Receiver Signal Processing ..................... Amplitude Mono--pulse•SystemBearingAccuracy ...................... Error less than 9 degrees RMS, 27degrees peak from --10 to +10 degreeselevationNOTES:1. The TCAS--II function within the unit meets all DO--160D EnvironmentalRequirements except for RF Radiated Emissions, Category M (DO--160D para.21.4) in the frequency ranges 100--150MHz and 1215--6000MHz. In thesefrequency ranges it meets the requirements for RF Radiated Emissions ofDO--160C, Category Z. The unit was tested to DO--160D change 1 testprocedures.2. The TCAS--II function within the unit has 2 FAA approved software deviations. Thedeviations do not affect the installation or performance of the system. The details of thedeviations will be furnished by ACSS upon request by the customer.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--26(1) System InterfacesThe T2CAS Computer Unit supports the external system interfaces that follow.Unless otherwise specified, the specifications apply to both the TT--950/TT--952(6--MCU) and TT--951 (4--MCU) computers. All interfaces are per ARINC 735A.(a) Common System InterfacesThis section defines external system interfaces that are common to both theTCAS function and TAWS/RWS function1Radio Altimeter InterfaceThe T2CAS Computer Unit accepts either analog or digital radio altimeterinputs. For each type of input, dual input ports are provided. The externalconnector pins for Analog/Digital Radio Altitude Inputs #1 and #2 are sharedby TCAS and TAWS/RWS, which both have independent circuitry.The T2CAS CU analog radio altimeter interface accepts either ARINC 552A,Collins BCA analog input, or metric analog input formats. The T2CAS CUalso accepts additional radio altimeter inputs that meet the minimum TAWSinput signal requirements. The type of input format is selected by programdiscrete inputs RMP--12B, --12H, --12J, and --12K. Each analog inputcontains a valid discrete used to validate the analog input.Each of the military radio altimeter types provide two outputs that areconnected to the T2CAS CU input pins. The two altimeter outputs are theAnalog Data Output and Analog Data Reliability signal. The T2CAS CUuses the Data Reliability signal in conjunction with the Analog Data Output todetermine radio altimeter failures.A condition exists for several military radio altimeters known as Out of Track.This condition occurs when the radio altimeter has not failed and thealtimeter is not reading a valid altitude. Altitude data for an Out of Trackcondition should be considered invalid and not used.The digital radio altimeter interface accepts inputs from an ARINC 707 radioaltimeter on ARINC 429 low speed input buses.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--27(b) TCAS System Interfaces1Mode S Transponder InterfaceThe T2CAS computer contains two sets of ARINC 429 high speed buses forcommunication with two Mode S transponders. It uses ARINC 718A/735Acommunication protocol (2 inputs, 2 outputs).2Onboard Maintenance System InterfaceThe TCAS function contains a set of ARINC 429 low speed buses forcommunication with an onboard maintenance system (1 input, 1 output).The unit interfaces with all major airframe manufacturers maintenancecomputer systems. Since the maintenance computer protocol for eachairframe manufacturer is different, the TCAS function automatically detectsthe type of airframe from the data received from the maintenance computerand sets its protocol accordingly.3Data Loader InterfaceThe TCAS function contains a set of ARINC 429 buses and discrete inputsthat interface to either an airborne data loader (ADL) through pins on therear connector, or a portable data loader (PDL) through the 53--pin circularconnector on the front panel of the unit. The computer works with ARINC603 data loader protocol (low speed bus) or ARINC 615 data loader protocol(high speed bus). The ADL and PDL ARINC 429 inputs have separate dataloader buses to allow for connection of both types of data loaders. It alsohas separate data loader enable discrete inputs. The type of data loaderprotocol (603 or 615) is selected by a discrete input. The unit software partnumber can be output on the data loader port by grounding a discrete input.The aural voice commands are contained in Flash Erasable ProgrammableRead--Only Memory (EPROM) on the TCAS. Each software load contains inaddition to program code, voice command data. Changes to voicecommands can be made through a software load instead of removal of theLRU from the aircraft for hardware modification.4TCAS Display Bus InterfaceThe TCAS function has four sets of ARINC output buses for display of trafficand resolution advisories.The TA/RA Display No. 1 and No. 2 buses are high speed ARINC 429 busesthat contain both traffic information and resolution advisory information. Thebuses function according to either the ARINC 735A characteristics, or canoptionally be set for the Honeywell EFIS characteristics through a programinput pin (RMP--12C). For each bus, a valid discrete input is provided thatindicates whether the display is functional.The RA Display No. 1 and No. 2 buses are low speed ARINC 429 buses thatcontain only resolution advisory information. The buses function accordingto the ARINC 735A characteristics. For each bus, a valid discrete isprovided that indicates whether the display is functional.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--28The RA Display No. 1 and No. 2 buses can be configured for a 429 DataRecorder function by grounding programming pin (RMP--11D). In this mode,the buses are configured for high speed operation.5Performance Management Bus InterfaceThe TCAS function contains a low speed ARINC 429 bus input (RMP--6A,6B) that is reserved for connection to a performance management system.The input is provisioned to obtain maximum rate of climb information from aFMS or Performance Management System (PMS.) The input is provided forfuture system enhancements and is currently not used.6Magnetic Heading/Attitude Bus InterfaceThe TCAS function contains a high speed ARINC 429 bus input (RMP--7A,7B) reserved for connection to an Inertial Reference System (IRS) orAttitude Heading and Reference System (AHRS). The input lets aircraftheading and attitude data be input for the purpose of providing for futurehorizontal maneuvers. This function has not been implemented on TCAS IIinstallations, so these pins are reserved for future use.7RS--422 Data Recorder InterfaceThe TCAS function contains an RS--422 interface connected to a datarecorder. The interface consists of two RS--422 input buses and twoRS--422 output buses, with a program input to select internal or externalclock operation. The RS--422 input buses input a reply enable signal and anexternal recorder clock. The RS--422 output buses output the recorder dataand internal 125 KHz clock reference. The interface also contains aprogram pin for enabling or disabling the data recorder function. TheRS--422 data recorder inputs and outputs are connected to pins on the frontpanel 53--pin PDL connector.8ARINC 573 Flight Data Recorder InterfaceThe TCAS function contains 12 discrete outputs connected to an ARINC573 flight data recorder. The outputs are used to record information during aresolution advisory event.9ARINC 429 Flight Data Recorder InterfaceThe TCAS function contains an interface for an ARINC 429 flight datarecorder. The flight data recorder function is activated by grounding adiscrete input pin (RMP--11D) on the rear connector. With the discrete inputgrounded, flight data is output as high speed ARINC 429 data on the RADisplay No. 1 and No. 2 Buses. With the discrete grounded, the normal RADisplay bus operation is not available.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--2910 Voice Audio OutputsThe TCAS function contains two analog audio outputs that provide TCASaural traffic advisories and resolution advisories. The 8--ohm output has thecapability to supply up to 8 Watts RMS into a speaker. The 600--ohm outputhas the capability to supply up to 80 milliwatts RMS into an audio distributionsystem.11 RS--232 InterfaceThe TCAS function has an RS--232 input/output for connection to a personalcomputer. The interface allows for LRU maintenance and troubleshooting.The maintenance log and RA event log can also be downloaded to a PCusing this port. The RS--232 interface is connected to the 53--pin PDLconnector on the front of the unit.12 Altitude Alerter InterfaceThe TCAS function contains an ARINC 429 low speed input bus that isreserved for receiving selected altitude information from an altitude controlsource or flight control computer. The TCAS function uses the selectedaltitude information to inhibit the weakening of a resolution advisory bydetermining the selected altitude limits for the aircraft.13 Reserved ARINC 429 Bus InterfaceThe TCAS function has four sets of reserved ARINC 429 input busesconfigured as either high speed or low speed. These buses allow for futureupgrades to the TCAS system without hardware modification.(c) TAWS/RWS System Interfaces1Onboard Maintenance System InterfaceThe TAWS/RWS function contains a set ASDB defined ARINC 429 lowspeed buses for communication with an onboard maintenance system (1input, 1 output). The unit interfaces with all major airframe manufacturersmaintenance computer systems. Since the maintenance computer protocolfor each airframe manufacturer is different, the T2CAS computer usesinformation from the Aircraft Personality Module (APM) to determine whatOMS system, if any, is installed.2Data Loader InterfaceThe TAWS/RWS function is provisioned for interface with an ARINC 615Adata loader (Ethernet 10 Base--T). The front Portable Data Loaderconnector contains the signals required by the ARINC 615A specification.The interface will be used to upload future software updates to theTAWS/RWS system.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--30The T2CAS also contains an access port on the front of the unit that acceptsa Type I Compact PC Flash card. The Compact PC card is commerciallyavailable and can hold up to 300 Megabytes of memory. The Compact PCcard is electrically compatible with PCMCIA Flash cards and can be insertedin a PCMCIA card slot on a PC using an adapter, or a USB serial port withan adapter. The Compact PC Flash card is used for updating theTAWS/RWS operational software and terrain database. In addition, theCompact PC Flash card may be used as a data recorder for the purpose ofcertification flight tests. T2CAS is designed so the Compact PC card mayremain inserted in the unit during flight tests.3TAWS Display interfaceThe TAWS function contains two Digital 453 picture bus outputs that transmitterrain display data to ARINC 708A compatible weather radar displays orEFIS displays. The bus outputs can be configured with independent rangeselections. The Mode and Range selections are input to the system on anARINC 429 bus.The TAWS function also has two ARINC 429 bus outputs that contain datafor alerts and annunciation of system status.4RS--232/ Compact Flash Card Data Recorder InterfaceThe Data Recorder Interface can utilized for either internal or external Datarecording.The TAWS/RWS Event log contains event information due to TAWS orWindshear cautions or warnings (internal Data recording). The log can holdapproximately three events that last up to 45 seconds each (assumingGCAM Event, GCAM Parameter data and GFM parameter data selected forrecording). The event log data may be downloaded to a Laptop PC over theRS--232 port, or downloaded to a Compact Flash card using the slot on thefront of the unit.The external Data recording provides the capability to perform real--timerecording of various T2CAS input, output and internal data. This data maybe recorded using the Compact Flash Card or RS--232 interface. Using a300Mbyte Compact Flash card, the system can store up to 15 hours of flighttest data.In addition, the RS--232 interface allows for LRU maintenance andtroubleshooting. The maintenance log and RA event log can also bedownloaded to a PC using this port. The RS--232 interface is connected tothe 53--pin PDL connector on the front of the unit.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--315Flight Data RecordingThere is currently no output to the Flight Data Recorder.6Voice Audio OutputsThe TAWS/RWS function contains two analog audio outputs that provideTAWS/RWS aural terrain avoidance advisories and windshear advisories.The 8--Ohm output has the capability to supply up to 8 Watts RMS into aspeaker. The 600--Ohm output has the capability to supply up to 80milliwatts RMS into an audio distribution system.7Air Data InterfaceThe TAWS/RWS function uses Vertical Speed, Static Air Temperature,Computed Air Speed, Corrected/Uncorrected Barometric Altitude from an airdata system. In addition, TAWS/RWS uses True Airspeed (TAS) oninstallations where T2CAS is performing the RWS function.The TAWS/RWS function accepts up to two Digital ARINC 429 inputs fromDigital Air Data Systems. Some of the supported system interfaces includeARINC 706 Air Data Computer (ADC), ARINC 575 ADC, ARINC 738 AirData Inertial Reference System (ADIRS), and other non--ARINC standardinterfaces that meet the minimum input signal requirements for TAWS/RWS.TAWS/RWS can accept analog air data inputs from an ARINC 565 or ARINC575 Air Data System and other non--ARINC standard interfaces. Analogsystem inputs can be in the form of 2--wire DC absolute, 2--wire DCratio--metric, 2--Wire AC ratio--metric, 3--Wire AC Synchro, 3--Wire ACSine/Cosine.8Inertial Reference InterfaceTAWS/RWS function uses Ground Speed, True Track Angle, Flight PathAngle, Latitude, Longitude, Altitude MSL, Roll Angle, Pitch Angle, InertialVertical Speed, and True Heading from an inertial system.Additionally, TAWS/RWS uses Body Longitudinal and Normal Accelerationon installations where TAWS/RWS is performing the RWS function.TAWS/RWS accepts up to two Digital ARINC 429 inputs from an ARINC 704Inertial Reference System (IRS), ARINC 705 Attitude Heading andReference System (AHRS), ARINC 738 Air Data Inertial Reference System(ADIRS), Global Positioning and Inertial Reference System (GPIRS) andother non--ARINC standard interfaces that meet the minimum input signalrequirements for TAWS/RWS.TAWS/RWS can accept analog inputs for Body Longitudinal and NormalAcceleration, Pitch and Roll, Magnetic Track, Variation and Heading. Theanalog input sources can be 2--Wire DC Absolute and 3--Wire AC Synchro.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--329FMC InterfaceThe TAWS/RWS function uses Ground Speed, True Track Angle, Flight PathAngle, Aircraft Weight, Latitude, Longitude and True Heading from an FMCsystem.TAWS/RWS can accept up to two Digital ARINC 429 inputs from an ARINC702 Flight Management Computer system or other non--ARINC standardinterfaces.10 GPS/GNSSThe TAWS/RWS function uses Vertical Speed, Ground Speed, True TrackAngle, Latitude, Longitude, Altitude MSL, WGS 84 altitude and TrueHeading from a GPS System.NOTE: World Geodetic System (WGS) 84 altitude is another type of MSLaltitude.TAWS/RWS accepts up to two Digital ARINC 429 inputs from an ARINC 743or ARINC 743A GPS System, or other non--standard ARINC interfaces thatmeet the minimum input signal requirements for TAWS/RWS11 ILS/MLSThe TAWS/RWS function uses Selected Runway Heading, Glide SlopeDeviation, Localizer Deviation, and ILS Select from an Instrument LandingSystem (ILS) or Microwave Landing System (MLS).TAWS/RWS can accept up to three Digital ARINC 429 inputs from an ARINC710 ILS receiver, ARINC 727 MLS receiver, or other non--ARINC standardinterfaces.TAWS/RWS can accept up to two Analog Glide Slope and two AnalogLocalizer inputs from an ARINC 547 or ARINC 578 ILS receiver as a 2--WireDC absolute input.12 Angle Of AttackOn installations where T2CAS is performing the RWS function, theTAWS/RWS function uses the aircraft angle of attack for the Windshearcomputation.TAWS/RWS can accept up to two ARINC 429 inputs from a source such asa Digital Stall Warning Computer (DSWC) or other data concentratordevices.TAWS/RWS can accept analog angle of attack information in the form of3--Wire AC Synchros, 2--Wire DC absolute and 2--Wire DC ratio--metricinputs.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--3313 Decision HeightThe TAWS/RWS function uses selected Decision Height and/or MinimumDescent Altitude for the generation of audio call--outs. TAWS/RWS canaccept ARINC 429 inputs or a discrete input.14 Decision Height/Minimum Descent Altitude SwitchA Flight Deck switch can be used to select either Decision Height orMinimum Descent Altitude for audio call--out altitude determination.15 Flap/Slat SettingsTAWS/RWS function uses Flap/Slat settings for TAWS and Windshear alerts.TAWS/RWS can accept ARINC 429 Flap/Slat Setting inputs from a sourcesuch as a Digital Stall Warning Computer (DSWC) or other data concentratordevices. TAWS/RWS also accepts Analog inputs in the form of 3--Wire ACSynchros, DC absolute, DC ratio--metric and Discrete Inputs.16 Weight and Balance System (WBS)The TAWS/RWS function obtains Current Aircraft Weight from an A429Digital Weight and Balance System source.(2) Discrete InputsThe T2CAS has various discrete inputs available for implementing various TCAS andTAWS/RWS functions. For the TCAS function, the input logic status is defined inaccordance with ARINC 735A. For the TWAS/RWS function, the input definition isdefined by the ASDB for the specific aircraft type.(3) Program InputsThe T2CAS has various program inputs available for TCAS unit configuration andinstallation programming. Input logic status is defined according to ARINC 735Adefinition.The T2CAS utilizes the ASDB database for TAWS/RWS unit configuration andinstallation programming.The ASDB defines the assignment of the connector pins to each signal, the criteriafor determining the value and status of each signal and the signal specific filteringand processing requirements.(4) Discrete OutputsThe T2CAS TAWS function contains 13 discrete outputs that are used to provideannunciation of alerts and system status. For the TCAS function, the output logicstatus is defined in accordance with ARINC 735A. For the TAWS/RWS function, theoutput definition is defined by the ASDB for the specific aircraft type.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--34(5) Self--Test Function(a) TCAS and TAWS/RWS Maintenance Self--TestBy momentarily pushing the TEST switch on the front panel of the T2CASComputer Unit, maintenance personnel can display fault data for the current andpreceding flight legs. When TEST is initially activated, all annunciators (pass/faillamps on front of unit) are ON for a 3--second lamp test, then current fault data isdisplayed for 10 seconds. If no further activations of the TEST switch are made,the LRU display cycle is terminated at the end of the 10--second fault displayperiod, and all annunciators are extinguished.If during the 10--second fault display period, the TEST button is activated again,the fault display period is aborted, a 2--second lamp test cycle is done, and thefault data recorded for the preceding flight leg is displayed for 10 seconds. Thisprocedure can be repeated up to 10 times to obtain recorded data from theprevious 10 flight legs. If the TEST button is not activated again during the faultdisplay period, the fault display cycle is terminated at the end of the 10--secondfault display period and all annunciators are extinguished. If an attempt is madeto display fault data for the preceding flight leg when the tenth preceding flightleg fault data is displayed, all annunciators flash for a 3--second period at a2.5--Hz rate, after which all annunciators are extinguished.When less than 10 flight legs have been flown since the T2CAS Computer Unitwas shop tested and recertified, less than 10 previous flight legs of recordedfault data may be available for display. In this case, if an attempt is made todisplay fault data for the preceding flight leg when the earliest flight leg isdisplayed, all annunciators flash for 3 seconds at a 2.5--Hz rate and then allannunciators are extinguished.The TCAS PASS, TCAS FAIL, and TAWS Pass/Fail status annunciators indicatethe status of the T2CAS Computer Unit only. All other annunciators reflect thecondition of the respective sub--system.(b) TCAS Self--TestThe T2CAS TCAS self--test is initiated from a self--test button on theTCAS/MODE S control panel. The T2CAS TCAS self--test may also be initiatedfrom the Central Maintenance Computer.(c) TAWS/RWS/GPS Self--testThe T2CAS TAWS/RWS/GPS self--test is initiated from a self--test discrete inputinterface. The TAWS/RWS/GPS self--test discrete is further defined in the ASDB.The T2CAS TAWS/RWS/GPS self--test may also be initiated from the CentralMaintenance Computer.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--35B. Airplane Personality Module InterfaceThe Airplane Personality Module (APM) is defined in ARINC Report 607, Attachment 3 --see Figure 1--9. A serial digital interface between the T2CAS Computer and the APMallows the APM to be programmed with aircraft and system configurations during theinitial installation of the T2CAS computer. In addition, the serial digital interface allows theAPM to be read during every subsequent power--on to configure the computer for properoperation. The APM is used to hold/provide information for the T2CAS configurationdatabase, for example, registration number, aircraft type, equipment installed, et cetera.Moreover, the APM contains the Aircraft Specific Database which defines theInput/Output definition for the specific aircraft type, the aircraft climb performance data tosupport of the TAWS functionality and the windshear algorithm coefficient data.Figure 1--9. T2CAS Airplane Personality Module (APM)C. Directional AntennaThe T2CAS TCAS directional antenna, Figure 1--10, is a four--element, verticallypolarized, monopole array capable of transmitting in four selectable directions at 1030MHz. The antenna is capable of receiving replies from all directions simultaneously withbearing information at 1090 MHz, using amplitude--ratio monopulse techniques.The antenna consists of a molded radome with radiating/receiving elements and iscompletely filled with a rigid foam. The antenna assembly uses five or nine screws toattach the radome and either four or eight screws to attach the antenna to the aircraftfuselage.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--36The ACSS directional antenna has a small frontal area. The circular radome has a 3:1elliptical leading edge and an extremely low profile height of only 0.806 inch. This yieldsexcellent aerodynamic performance with a minimum possibility of icing, which could be ahazard for rear mounted engines.For T2CAS TCAS system installations, the top antenna must be a directional antenna.The bottom antenna can be either a directional or omnidirectional antenna. The T2CASComputer Unit has the capability of automatically sensing which version is installed.The directional antenna mounting screws are standard #10--32 UNF--2A pan head,corrosion--resistant (stainless) steel screws in accordance with Military SpecificationMS51958. The appropriate length is determined by the installer allowing 0.5--inch for thethickness of the antenna and adapter plate. A washer must be installed under the headof each mounting screw. The washer must be made of passivated, corrosion--resistantsteel in accordance with MIL--S--5059 or MIL--S--6721. The Air Force--Navy AeronauticalStandard part number is AN960C10L. The washer has an outer diameter of 0.438 inch,an inner diameter of 0.203 inch, and a thickness of 0.032 inch.An O--ring (included with the directional antenna) is required to be installed between thedirectional antenna and the aircraft fuselage. The National Aerospace Standard partnumber for the O--ring is NAS 1611--240. The ACSS part number for the O--ring is4000171--240.NOTE: For directional antennas, ACSS Part No. 7514060--90X, the customer mustprovide an adapter plate for mounting to the aircraft. For details of the antennabase plate, to which the adapter must mate, refer to Section 2. Directionalantennas, ACSS Part No. 7514081--9XX, come with a preinstalled adapter plate.The average unit weight of an antenna with adapter plate is approximately 3.0 pounds.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--37/(1--38 blank)Figure 1--10. Directional Antenna
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--39D. GPS Antenna and CoaxFor T2CAS installations that include the optional internal GPS module, a compatibleARINC 743A active GPS antenna and coax interface shall be included in the T2CASinstallation design.The antenna used for the GNSSA Receiver Module is required to meet the requirementsof RTCA/DO--228, Change 1, and TSO--C144. A potentially suitable antenna is listedbelow, although antennas are available from different vendors:•Manufacture: AeroAntenna•Part Number: AT575--143WAC--TNCF--000--26--NM•Description: 26 dB gain, 12 volt, Active AntennaThe range of antenna gains which are acceptable is dependent on the coax length andresulting dBs of loss. Generally, an antenna gain of 20 -- 30 dB is desired. Higher gainantennas introduce the amplification of noise as well as the desired signal. This cansaturate the GPS input circuitry, reducing its effectiveness. If the antenna gain is low andthe resulting limit of allowable cable loss is exceeded, excessive signal degradation willoccur and the GNSSA Receiver Module may not be able to meet its performancespecifications.Do--228 Change 1 compliant antennas are required. Change 1 introduced rejection at 5to 10 dB higher that the original DO--228 requirements at the SATCOM frequency.Therefore system performance under interference can not be assured with thenon--Change 1 compliant antennas. When subjected to DO229 normal interferencelevels, system performance can be degraded.Figure 1--11 shows a typical T2CAS GPS antenna coax sub kit with the sub kit parts listedin Table 1--7. Figure 2--4 shows AeroAntenna’s AT575--143 active GPS antenna seriesoutline drawing.The GPS coax installation should include one disconnect near the T2CAS computer trayto facilitate the removal of the equipment shelf from the aircraft. The T2CAS computerprovides +12 Vdc to the active GPS antenna through the coax’s center conductor.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--40Figure 1--11. Typical T2CAS GPS Antenna Coax Sub KitTable 1--7. GPS Antenna Coax Kit Parts ListItem NumberNomenclatureorDescription Part Number Number Required1TNC STRAIGHT PLUG See Note 22ARINC SIZE 5 CONTACT See Note 13TNC BULKHEAD JACK See Note 14GPS COAX See Note See Note5CLAMP MS25281--R4 See Note6SCREW, HEX--HD, 10--32 X .38 NAS1801--3--6 See Note7STAND--OFF CLIP 294243--12C See Note8WASHER #10 X .032 THK, ALUM NAS1149D0332J See NoteNOTE: The part numbers and/or quantity of listed parts are dependent on the installationdesign.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--41E. Gables ATC/TCAS Dual Mode S Transponder Control PanelThe Gables ATC/TCAS Mode S control panel is used to independently control two ModeS transponders, and to interface with a Mode S installation with TCAS capabilities.The control panel contains two isolated electronic modules each dedicated to a giventransponder. Each module derives its input ATC code data from two dual concentricknobs. The selected code is then displayed on a four digit Liquid Crystal Display (LCD),and subsequently transmitted to each transponder.Figure 1--12 shows a typical front panel layout of a Gables G7130 series control panel.Table 1--8 gives items and specifications that are particular to these units.Figure 1--12. Typical Gables ATC/TCAS Control Panel
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--42Table 1--8. Gables G7130 Series Control Panel Leading ParticularsItem SpecificationDimensions (maximum):•Height ...................................... 2.25 in. (57.2 mm)•Width ....................................... 5.75 in. (146.1 mm)•Length ...................................... 5.80 in. (147.3 mm)Weight (maximum) ............................. 2.0 lb (0.907 kg)Power Requirements:•Primary ..................................... +28 V dc, 0.25 Amps maximum current•DisplayandOverlayLighting................... 5 V, 400 Hz, 2.3 Amps maximumDisplayType................................... Four Digit, Dichroic LCDCode Select Range ............................. 0000 to 7777 (octal)Transmitted ARINC 429 Labels ................... 013, 015, 016, 031 (octal)TSO .......................................... C112/C119EnvironmentalSpecifications..................... /A2D1/BB/MB·/XXXXXXZZAZZRZ/xxZZMating Connectors:•J1 .......................................... M83723/75R16247 or MS24266R16B24S7•J2 ......................................... M83723/75R16248 or MS24266R16B24S8Mounting ...................................... Four Unit Dzus Fasteners(1) Functional Description and OperationCommunication with Mode S transponders is accomplished through an ARINC 429bus as defined in ARINC Characteristic 718. Control panel functions include 4096ident code selection and display, altitude source and reporting inhibit selection,selection between two onboard transponders, TCAS TA or TA/RA advisory selection,range selection (in nautical miles) and a system functional test selection. Adescription of the front panel annunciator and switch functions follows:(a) Transponder Code DisplayThe control panel has a single four digit LCD display common to both moduleswithin the unit. The display shows the ATC code selected by the user andconsequently transmitted to the transponders. Input to the display is controlledby the system select switch (XPDR 1--2).In addition, certain fault indications are also indicated on the display. After afunctional test has been initiated, PASS shows on the display after a successfultest, or it shows FAIL if a high level failure is detected under normal operatingconditions. It also shows which transponder is active by displaying ATC 1 or 2.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--43(b) ATC Code SelectionThe ATC four digit code is selected with two dual concentric sets of knobs. Eachknob is dedicated to a single liquid crystal display (LCD) digit on the LCD codedisplay. The two smaller knobs control the inner digits of the LCD (tens andhundreds) while the two larger knobs control the outer most digits (units andthousands).(c) XPDR 1--2 SwitchThe XPDR switch is a two position switch that allows the selection of oneMode--S module in the control panel, and the activation of its associatedtransponder (System 1 or System 2).(d) Mode Control Selector SwitchThe rotary switch labeled STBY--ALT RPTG OFF--XPDR--TA ONLY--TA/RAallows the operator to activate the TCAS system by selecting TA, or traffic andresolution advisory (TA/RA). When STBY is selected, both transponders areselected inactive or in standby mode. Altitude reporting off (ALT RPTG OFF)selection disables the altitude data sources interrupting transmission of aircraftaltitude and location information to ground controllers.(e) ABV/N/BLW SwitchThe ABV/N/BLW switch selects an altitude range (from aircraft) for traffic displayon the TCAS displays. Range limits for software versions prior to Change 7 are7000 feet above and 2700 feet below the aircraft when in ABV mode and 2700feet above and 7000 below the aircraft when in BLW mode. Range limits for theChange 7 software version are 9900 feet above and 2700 feet below the aircraftwhen in ABV mode and 2700 feet above and 9900 below the aircraft when inBLW mode. When the normal (N) position is selected, the display range is 2700feet above and below the aircraft.(f) Traffic Display SwitchThe TRAFFIC AUTO--MAN switch is a two position rotary switch that controls theTCAS traffic display mode of operation. When the AUTO mode is selected, theTCAS computer sets the TCAS displays to pop--up mode under atraffic/resolution advisory condition. If the MAN mode is selected, then the TCASdisplays will be constantly activated advising of any near by traffic detectedwithin the horizontal and vertical range limits.(g) Range SwitchThe RANGE switch is a four or six position rotary switch used to select amongdifferent nautical mile (NM) traffic advisory horizontal range displays.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--44(h) IDENT KeyThe IDENT key is a momentary button. When pushed, the IDENT key causesan ATCRBS reply or Mode S UF--4 and UF--5 replies to contain a special pulseidentifier pulse (SPI) as an identifier to be transmitted to ground controllers inaccordance with ARINC 718 Draft 5 of Supplement 4.(i) Flight Level ButtonThe FL button is a momentary button used to select between relative andabsolute altitude information. When absolute is selected, this mode is enabledfor approximately 20 seconds and then reverts back to relative.(j) Test ButtonThe TEST button enables the user to initiate a system functional test. When theTEST button is pushed, the control panel initiates an internal test while afunctional test output is also transmitted through ARINC 429 labels.When installed with a TCAS system, an extended test can be initiated bycontinuously pushing the TEST button for at least eight seconds.(k) XPDR FAIL AnnunciatorThe XPDR FAIL annunciator displays the functional status of the activetransponder. The fail annunciator lights only when a failed transponder isselected on the XPDR 1--2 switch.F. TAWS Control PanelThe TAWS controls are used to control the displayed terrain data and TAWS inhibitfeatures. The TAWS control panels may be installed in a single or dual configurationdepending on the TAWS display capabilities.The TAWS controls can be mounted on a single control panel or they can be discreteswitches individually mounted at a convenient location in the Flight Deck. The TAWScontrols may be part of the electronic display menu selection in installations where TAWSinformation is displayed on an EFIS or electronic display.G. VSI/TRA DisplayThe VSI/TRA display, Figure 1--13, is used to display current vertical speed and TCAStraffic/warning information. The display consists of a full color, active matrix, liquid crystaldisplay panel. The display quality compares favorably to CRT displays but requires lesspower, weight, and volume than a CRT with a similar display area. Table 1--9 gives itemsand specifications particular to the unit. Figure 1--14 contains an interface block diagramof the 41--pin VSI/TRA.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--45Figure 1--13. Typical VSI/TRA Display Formats
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--46Table 1--9. VSI/TRA Leading ParticularsItem SpecificationDimensions (maximum):•Height ....................................... 3.26 in. (82.8 mm)•Width ........................................ 3.26 in. (82.8 mm)•Length ....................................... 7.5 in. (190.0 mm)Weight (maximum) .............................. 3.3lb(1.5kg)Power Requirements:•Primary ...................................... 115 V, 400 Hz; 17 Watts nominal (Day),12 Watts nominal (Night),20 Watts maximum•ExternalCircuitBreakerRating.................. 1Ampat115VacDisplayType.................................... Liquid CrystalMating Connectors:•J1(41Pin) ................................... M83723/72R--20--41--6Mounting ....................................... 3--ATI Clamp, Marmon NH1004994--30or MSP 64311B(1) Functional Description and OperationThe VSI/TRA has three functions. It continuously displays rate of climb or rate ofdescent. Traffic information is displayed and resolution advisory information isdisplayed against vertical speed to allow the flight crew to avoid threats.The vertical speed display is generated from signals applied directly to the indicator.The VSI/TRA is designed to be used in place of a conventional vertical speedindicator. Four possible sources exist for vertical speed data including ARINC 429data, DC analog signals in accordance with ARINC 575 (approximately 500 mV per1000 ft/min), ac analog signals in accordance with ARINC 565 (approximately 250mV per 1000 ft/min), and ARINC 429 signals from the ACSS Pressure TransducerModule. The VSI/TRA computes vertical rate from electrical static pressure when aremote static sensor is used. These four program pin selectable configurationsprovide compatibility with most aircraft.Various dash number VSI/TRA Displays are available that provide unique designcharacteristics, which include VSI rate filter programming and selection of an Englishor metric rate scale. Table 1--5 contains a listing of all the VSI/TRA configurations.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--47The VSI/TRA also displays symbology corresponding to traffic in the vicinity of theaircraft. Threat information is received from the TCAS function on a dedicatedhigh--speed ARINC 429 bus. The display uses the bearing, altitude, and range datafor each threat to provide an indication of the proximity of the threat. Allowable(nonilluminated or green illuminated bands) and prohibited (red illuminated bands)vertical rates are displayed based on information received from the TCAS function.The VSI/TRA can be pin programmed to provide vertical speed data only, verticalspeed and resolution advisory data, or vertical speed, resolution advisory and trafficadvisory data. Display of the TCAS system fault status is provided on the VSI/TRA inresponse to extended TCAS control panel TEST activation.Display dimming is controlled from several inputs consisting of an internal light sensormounted on the bezel of the LRU, a remote light sensor, and the aircraft dimmingbus. The display is dimmed by varying the brightness of the LCD panel backlighting.(2) Software ConsiderationsVSI/TRA software is developed to a DO--178A category of Level ll (essential). Thesoftware continually monitors and displays vertical speed and TCAS information.Output discretes supply user components with the status of the LRU. TCAS validindicates that the LRU is displaying valid TCAS information.(3) Built--In--Test Equipment (BITE) and Self--Test CapabilityThe LRU has input discretes that allow a calibration and test program to be run. Thismode allows the display to be adjusted and various diagnostic tests to be performed.These tests and adjustments can only be done in a shop on a dedicated test fixture.When the LRU application program is operating in the aircraft, the background loopcontinuously monitors the power supply status, the ROM integrity, and the analogrange limits. A failure results in the setting of bad status output discretes. A coldstart will continuously be attempted until the LRU passes the built--in--test. There is adedicated self--test input for both versions of the VSI/TRA Display. When this pin isactivated, the unit will display symbology that aids in the detection of unit faults.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--48Figure 1--14. VSI/TRA Interface Diagram (41--Pin)
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--49H. TAWS Terrain Hazard DisplayT2CAS installations require at least one TAWS terrain hazard display. ARINC 708A andARINC 429 WXR display and EFIS interfaces are supported. Figure 1--15 shows atypical single ARINC 708A terrain hazard display interface. T2CAS’ dual--independentterrain hazard display I/O supports dual ARINC 708A and dual ARINC 429 terrain hazarddisplay systems.(1) Functional Description and OperationThe terrain hazard display function enhances situational awareness by providing adisplay of terrain--related hazardous situations in front of the aircraft on existingARINC 708A compatible weather radar or EFIS flight deck displays. The display maybe either the EFIS Navigation Display (for EFIS--equipped aircraft) or the weatherradar display. A crew--activated switch is used to select/deselect the terrain image onthe display.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--50Figure 1--15. Typical T2CAS Single Terrain Hazard Display Interface
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--51I. XS--950 Mode S Data Link TransponderThe XS--950 Data Link Transponder provides surveillance functions to ground based andairborne interrogators, and communication functions to various onboard systems. Thetransponder contains data link functions that allow it to function as part of the AircraftTelecommunications Network (ATN). The data link functions allow communication with aCommunication Management Unit (CMU) through a Mode S Airborne Data LinkProcessor (ADLP). The transponder also contains Mode S specific functions that arededicated links to onboard systems. The XS--950 Transponder has the capability to beupgraded to provide an internal airborne data link processor (ADLP) function.The XS--950 Transponder conforms to the ARINC 718A Mode S TransponderCharacteristic for form, fit and function, and is backward compatible with existing ARINC718 installations. It is certified to ICAO level IV data link capability and can be upgradedto level V data link capability.The XS--950 Data Link Transponder is packaged in a 4--MCU (Modular Concept Unit)outline as defined in ARINC Characteristic 600--7. The unit is able to utilize ARINC 404cooling air moving through the LRU in a downward direction as well as ARINC 600cooling air moving through the LRU in an upward direction. The rear connectorreceptacle is an ARINC 600 size 2 shell assembly with inserts and contacts as defined inARINC Characteristic 718A. The unit also features a fixed carrying handle and self--testbutton with discrete LRU STATUS annunciators.Figure 1--16 shows a graphical view of the XS--950 Data Link Transponder andTable 1--10 gives items and specifications particular to the transponder.Figure 1--16. XS--950 Data Link Transponder
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--52Table 1--10. XS--950 Data Link Transponder Leading ParticularsItem SpecificationDimensions (maximum):•Height ...................................... 7.6 in. (192 mm)•Width ...................................... 4.9 in. (124.5 mm)•Length ..................................... 15.2 in. (386 mm)Weight ....................................... 11.5 lb (5.2 kg)Power Requirements (115 V ac version):•OperatingVoltage ............................ 97 to 134 V rms, 115 V rms nominal•Operating Frequency ......................... 320 to 480 Hz, 400 Hz nominal•Power Consumption:-- Standby Mode (No Replies) ................. 40 Watts maximum-- Active mode (Maximum Load) ............... 85 Watts maximum•ExternalCircuitBreakerRating................. 5 A at 115 V ac, 400 HzPower Requirements (28 V dc version):•OperatingVoltage ............................ +18.0 to +32.2 V dc, +27.5 V dc nominal•Power Consumption:-- Standby Mode (No Replies) ................. 40 Watts maximum-- Active mode (Maximum Load) ............... 85 Watts maximum•ExternalCircuitBreakerRating................. 7 A at 28 V dcMating Connector .............................. Radiall Part No. NSXN2P203X0005Mounting ...................................... ARINC 600 4MCU Tray AssemblyTSO .......................................... C112, CL043, 121, F11EnvironmentalSpecifications: .................... DO--160C Environmental Category-- 115Vacversion ........................... [A2E1]--BB[CLMY]XXXXXXZEAEZRZA3E3XX-- 28Vdcversion ........................... [A2E1]--BB[CLMY]XXXXXXZ[BZ]AZZRZA3E3XX•Temperature / Altitude [A2E1]:-- OperatingTemperature ..................... --55 to +70 degrees C-- Ground Survival Temperature ............... --55 to +85 degrees C-- Altitude ................................... Sea Level to 70,000 feet-- LossofCooling ............................ +40 degrees C for 30 minutes minimum
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--53Table 1--10. XS--950 Data Link Transponder Leading Particulars(cont)Item Specification•Vibration [CLMY]:-- Category C ............................... Fixed wing turbojet engine, fuselage mounting-- Category L ............................... Fixed wing reciprocating and turboprop multi andsingle engine over 12,500 pounds, fuselagemounting-- Category M ............................... Fixed wing reciprocating and turboprop multi andsingle engine less than 12,500 pounds, instrumentpanel/console and equipment rack mounting-- Category Y ............................... Helicopter, reciprocating and turbojet, fuselagemountingOperating Modes:•STANDBY................................... Ready but not replying•ATCON .................................... Transponder Modes A and S, no altitude reporting•ATCALT ................................... Transponder Modes A, C, and S. Altitude reportingis enabledTransmitter Frequency ......................... 1090 ±1.0 MHzTransmitterPower ............................. 640 Watts maximum peak pulse, 250 WattsminimumReceiver Frequency ............................ 1030 MHzMinimum Trigger Level (MTL) .................... -- 7 6 ±3dBmMutual Suppression ............................ Bidirectional, accepts +18 to +70 volt pulse input;provides +28 volt nominal outputController Interface:•CircuitConfiguration .......................... Two ARINC 429 control data input ports. 12.5 Kbits/s (low--speed ARINC)•BusProtocol................................. Bus protocol meets requirements defined in ARINC718 for receiving transponder and TCAS controlinformation.TCAS II Interface:•CircuitConfiguration .......................... ARINC 429 input and output bus. 100 K bits/s(high--speed ARINC)•BusProtocol................................. Bus protocol meets requirements defined in ARINC718 and ARINC 735 for standard transponder toTCAS interface
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--54Table 1--10. XS--950 Data Link Transponder Leading Particulars(cont)Item SpecificationAirborne Data Link Processor (ADLP) Interface:•CircuitConfiguration .......................... COMM--A/B messages have an ARINC 429 inputand output bus.COMM--C/D messages have an ARINC 429 inputand output bus.Both sets of busses are 100 K bits/s (high--speedARINC).•BusProtocol................................. Bus protocol meets requirements defined in ARINC718 for standard transponder to ADLP bus interface.Altimeter Interface:•DigitalAirData............................... ARINC 429 or 575 data format. 12.5 K bits/s(low--speed ARINC). Two altimeter inputs (left andright altimeters).•SynchroAltitude ............................. ARINC 407 data format. Fine and course 3--wiresynchro inputs and a synchro valid flag discreteinput. Two sets of synchro altimeter inputs (left andright altimeters).•Analog Altitude (--20012, --65012 Only) .......... Three wire proportional input with valid flag discreteinput. Two altimeter inputs (left and right altimeters).Discrete input to enable altitude comparison.•EncodingAltimeter ........................... Gillham altitude data format. 11--wire discrete input.Two altimeter inputs (left and right altimeters).Discrete input to enable altitude comparison.•AltitudeSelection............................. Altitude source (left and right) selected by discreteinput.Flight Identifier Interface:•CircuitConfiguration .......................... ARINC 429 input bus. 12.5 K bits/s (low--speedARINC).•BusProtocol................................. Flight identification field consists of eight ISO--5characters input to the transponder in four ARINC429 labels (233, 234, 235, 236) per the requirementsdefined in ARINC 718.Aircraft Air/Ground Status Interface ............... Two discrete inputs used to indicate the aircraftair/ground status.Maintenance Computer Interface:•CircuitConfiguration .......................... ARINC 429 input and output bus. 12.5 K bits/s(low--speed ARINC).•BusProtocol................................. The maintenance computer interface meets protocolrequirements for all model Airbus, Boeing, andMcDonnell Douglas maintenance computers.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--55Table 1--10. XS--950 Data Link Transponder Leading Particulars(cont)Item SpecificationOnboard Software Uploading / Maintenance LogDownloading:•CircuitConfiguration .......................... Portable Data Loader thru ARINC 615 Front PanelConnectorARINC 429 input and output bus (100 K bits/s) PDLLink A discrete inputRS--232 input/output bus (38.4 K bits/s) at 53--pinPDL connectorAirborne Data Loader thru Unit Rear ConnectorARINC 429 input and output bus (100 K bits/s) ADLLink A discrete input•BusProtocol................................. Software uploads thru ARINC 429 PDL (front panel)port or ARINC 429 ADL (rear connector) port per theprotocol in ARINC 615 high--speed data loaderMaintenance log downloads thru ARINC 429 PDLport or ARINC 429 ADL port per the protocol inARINC 615 high--speed data loaderSoftware uploads and maintenance log downloadscan be accomplished through the PDL front panelport with an RS--232 interface bus and a PC withterminal emulation software
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--56J. RCZ--852 Diversity Mode S TransponderThe RCZ--852 Diversity Mode S Transponder is an airborne transponder designed toperform both conventional and advanced air traffic control (ATC) functions. It receivescoded radar signals from ATC ground stations and other aircraft and transmits codedreplies. The replies contain information such as aircraft identity, altitude, and datacommunication messages.The transponder works with the air traffic control radar beacon system (ATCRBS) andmode select (Mode S) system to provide enhanced surveillance and communicationscapability required for air traffic control system automation and onboard collisionavoidance systems. It has antenna diversity and is defined as a Class 3A transponderwith TCAS interface capability. The RCZ--852 Diversity Mode S Transponder has thecapabilities that follow:•Surveillance functions of both ATCRBS and Mode S ground sensors•Surveillance functions of airborne interrogators•Bi--directional air--to--air information exchanges, COMM--U/V•Ground--to--Air data uplink, COMM--A•Air--to--Ground data downlink, COMM--B•Multisite message protocol•Ground--to--Air extended length message (ELM), COMM--C.The transponder does not support COMM--D extended length message (ELM)communication.Figure 1--17 shows a graphical view of the RCZ--852 Diversity Mode S Transponder andTable 1--11 gives items and specifications particular to the transponder.Figure 1--17. RCZ--852 Diversity Mode S Transponder
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--57Table 1--11. RCZ--852 Diversity Mode S Transponder Leading ParticularsItem SpecificationDimensions (maximum):•Height ...................................... 3.38 in. (86 mm)•Width ...................................... 4.10 in. (104 mm)•Length ..................................... 14.1 in. (358 mm)Weight ....................................... 5.0 lb (2.27 kg)Power Requirements:•OperatingVoltage ............................ +18.0 to +30.3 V dc, +27.5 V dc nominal•Power Consumption:-- Standby Mode (No Replies) ................. 28 Watts nominal-- Active Mode (Maximum Load) ............... 55 Watts maximum•ExternalCircuitBreakerRating................. 5 A at +27.5 V dcMating Connector .............................. Radiall Part No. NSXN2P203X0005 (Part ofInstallation Kit, ACSS Part No. 7510707--968)Mounting ...................................... Mount Assembly, ACSS Part No. 7517455--902TSO .......................................... C112EnvironmentalSpecifications..................... DO--160B Environmental Category/A2E1/B/JLMY/E1XXXXXZ/BZ/AZZ•Temperature / Altitude [A2E1]:-- OperatingTemperature ..................... --55 to +70 degrees C-- Ground Survival Temperature ............... --55 to +85 degrees C-- Altitude................................... Sea Level to 70,000 feet-- Decompression ............................ 8,000 to 70,000 feet-- Overpressure ............................. --15,000 feet•Vibration [JLMY]:-- Category J ............................... Fixed wing turbojet, subsonic and supersonic,fuselage mounting-- Category L ............................... Fixed wing reciprocating and turboprop multi andsingle engine over 12,500 pounds, fuselagemounting-- Category M ............................... Fixed wing reciprocating and turboprop multi andsingle engine less than 12,500 pounds, instrumentpanel/console and equipment rack mounting-- Category Y ............................... Helicopter, reciprocating and turbojet, fuselagemounting
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--58Table 1--11. RCZ--852 Diversity Mode S Transponder Leading Particulars (cont)Item SpecificationOperating Modes:•STANDBY................................... Ready but not replying.•ATCON .................................... Transponder Modes A and S. No altitude reporting.•ATCALT ................................... Transponder Modes A, C, and S. Altitude reportingis enabled.Transmitter Frequency ......................... 1090 ±0.5 MHzTransmitterPower ............................. 500 Watts peak pulse, 250 Watts minimumReceiver Frequency ............................ 1030 MHzMinimum Trigger Level (MTL) .................... -- 7 7 ±3dBmMutual Suppression ............................ Bidirectional, accepts +18 to +70 volt pulse input,provides +28 volt nominal outputController interface:•CircuitConfiguration .......................... Two ARINC 429 control data input ports. 12.5 Kbits/s (low--speed ARINC)Radio System Bus (RSB)•BusProtocol................................. Bus protocol meets requirements defined in ARINC718 for receiving transponder and TCAS controlinformation.The Radio System Bus (RSB) is designed to workwith the Honeywell Radio Management Unit.TCAS II Interface:•CircuitConfiguration .......................... ARINC 429 input and output bus. 100 K bits/s(high--speed ARINC).•BusProtocol................................. Bus protocol meets requirements defined in ARINC718 and ARINC 735 for standard transponder toTCAS interface.Airborne Data Link Processor (ADLP) Interface:•CircuitConfiguration .......................... COMM--A/B messages have an ARINC 429 inputand output bus.COMM--C/D messages have an ARINC 429 inputand output bus.Both sets of busses are 100 K bits/s (high--speedARINC).•BusProtocol................................. Bus protocol meets requirements defined in ARINC718 for standard transponder to ADLP bus interface.•Exception ................................... COMM--D messages are not processed by thistransponder.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--59Table 1--11. RCZ--852 Diversity Mode S Transponder Leading Particulars (cont)Item SpecificationAltimeter Interface:•DigitalAirData............................... ARINC 429 or 575 data format. 12.5 K bits/s(low--speed ARINC). Two altimeter inputs (left andright altimeters).•IACAirData ................................. Radio System Bus (RSB) interface supplies theHoneywell Integrated Avionics Computer (IAC)digital air data information. Two altimeter inputs (leftand right altimeters).•EncodingAltimeter ........................... Gillham altitude data format. 11--wire discrete input.Two altimeter inputs (left and right altimeters).Discrete input to enable altitude comparison.•AltitudeSelection............................. Altitude source (left or right) selected by a discreteinput.Flight Identifier Interface:•From Radio Management (RMU) ............... Flight identifier input from the RMU in RSB dataformat.•From Flight Management System (FMS) ........ Flight identifier input from the FMS in ARINC 429data format. 12.5 K bits/s (low--speed ARINC).Aircraft Air/Ground Status Interface ............... Two discrete inputs used to indicate the aircraftair/ground status.Antenna Selection Interface ...................... A discrete output supplies a GROUND whentransponder is active.RCB Interface:•CircuitConfiguration .......................... 2--wire full duplex RS--232 serial link to/from internalradio communications bus (RCB).•TransmissionRate ........................... 187.5 K baud•TransmissionFormat ......................... 1startbit,8databitsand1stopbitShop Flash Memory Programming Interface:•CircuitConfiguration .......................... 2--wire full duplex RS--232 serial port•TransmissionRate ........................... 19.2 K baud•TransmissionFormat ......................... 1 start bit, 7 data bits, odd parity and 1 stop bit
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--605. System OperationA. TCAS OperationThe principal modes of operation and display features of the TCAS function arediscussed in the paragraphs that follow. In--flight procedures with display examples arecontained in the T2CAS Pilot’s Manual, ACSS Publication No. 8000264--001.(1) Operational ModesThe TCAS function can operate in several different modes, depending on controlpanel selection. Several control panels are available. Only the ACSS single Mode Scontrol panel is discussed. Other control panels provide similar features.Four switches directly affect the TCAS operational mode: TCAS/XPDR modeselector, TA DSPLY selector, ALT RPTG selector, and TCAS TEST switch. Todistinguish the modes that provide TCAS advisories from those that do not, theoperational modes are discussed under TCAS modes and non--TCAS modes. Thenon--TCAS modes are annunciated TCAS OFF at the center of the display.The extended test mode is mentioned for reference. A detailed description of its usecan be found in the FAULT ISOLATION section.(a) TCAS ModesThe TA/RA and the TA--only modes are the two TCAS operational modes. TheTA/RA mode gives traffic information and warnings of hazardous traffic conflicts,while the TA mode gives only traffic information. A third mode, the TEST mode,can be temporarily activated from any mode including standby (STBY). TheTEST mode does not inhibit the generation of advisories. Functions available inthe operational and test modes are as follows:1TA/RA ModeThis mode is the normal operation mode providing full TCAS coverage. Inthis mode, TCAS tracks all aircraft in the surrounding airspace andgenerates traffic advisories or resolution advisories, as the situation requires.Figure 1--3 contrasts the airspace covered for each kind of advisory.For normal TA/RA operation, the TA/DSPLY selector must be set to AUTO orON and the ALT/RPTG selector must be set to 1 or 2.2TA ModeThe TA mode provides only surveillance of the surrounding airspace. In thismode, TCAS tracks all proximate aircraft and generates traffic advisories; noresolution advisories are issued in this mode.The flight crew uses the TA--only mode when resolution advisories would bea nuisance, or when flying over an area where only TCAS surveillance isallowed. Also, the system automatically selects this mode when the aircraftis flying under 1000 feet above ground level (AGL).The TA mode is annunciated TA ONLY at the upper left corner of the display.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--613Test ModePushing the TEST button on the control panel starts a self--test programwhich verifies proper operation of the TA and RA displays and of the auraladvisories on the audio system.The test mode does not affect normal TCAS operation, provided theselected transponder remains in normal operation during the test cycle.Should a TA or RA occur during the test sequence, the test aborts, and theadvisory is announced and displayed.The test mode just described excludes extended self--tests performed on theground, where TCAS is inoperative.(b) Non--TCAS ModesThe control panel selections that follow disable TCAS operation and alladvisories:•MODE S ON activates a Mode S transponder only•STBY sets the selected transponder in standby mode•ATC activates an ATCRBS transponder only•ALT RPTG set to OFF inhibits altitude reporting.When TCAS is inoperative as a result of control panel selection, TCAS OFF isannunciated on the display. When TCAS is inoperative due to a system failure,TA FAIL, RA FAIL, or TCAS FAIL is annunciated on the display. In addition, if thetransponder or the altitude data source fails, the XPDR FAIL light on the controlpanel comes on.(c) Extended Test ModeThe purpose of the extended test mode is to facilitate diagnosis in the eventself--test has failed. Like self--test, this mode is enabled by pushing the TCASTEST button, but only when TCAS is inoperative. The aircraft must be on theground, and the transponder must be set to STBY. Push and hold the TCASTEST button for longer than eight seconds to activate the extended tests. Thisfeature is not available on all systems. Refer to the TESTING AND FAULTISOLATION section for system requirements and test description.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--62(2) Display SymbologyThe TCAS modes use color--coded symbols and data tags to map air traffic andlocate threat aircraft on the VSI/TRA display.Four traffic symbols are used: solid circle, solid square, solid diamond, and hollowdiamond. See Figure 1--18 for examples. A different color is assigned to eachsymbol type, as listed in Table 1--12.Table 1--12. TCAS Traffic SymbolsGraphic Symbol Color Display FunctionSolid Circle Amber Traffic Advisory (TA)Solid Square Red Resolution Advisory (RA)Solid Diamond Blue Proximate TrafficHollow Diamond Blue Other TrafficNOTE: TCAS traffic information displayed on EFIS displays such as crew alertingsystem display, navigation display, electronic horizontal situation display ormultifunction display, is similar to that on combined VSI/TRA indicators. Trafficsymbology is identical to that displayed on the VSI/TRA.(a) Colors1AmberRepresents a moderate threat to a TCAS--equipped aircraft. A visual searchis recommended to prepare for intruder avoidance. Amber is used only inconjunction with a traffic advisory.2RedRepresents an immediate threat to a TCAS--equipped aircraft. Promptaction is required to avoid the intruder. This color is only used in conjunctionwith a resolution advisory.3BlueRepresents proximate traffic and other traffic the TCAS surveillance logichas in its track file.4WhiteUsed only for mode annunciations and for reference graphics, includingaircraft home position, range ring, and VSI scale.(b) Traffic Identification1Traffic Advisory
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--63Intruder aircraft entering the caution area, 20 to 48 seconds from the TCAS2000 collision area are represented as a solid amber circle. This type oftraffic results in a traffic advisory.2Resolution AdvisoryIntruder aircraft entering the warning area, 15 to 35 seconds from the TCAS2000 collision area are represented as a solid red square. This type oftraffic results in a resolution advisory.3Proximate TrafficAircraft within 6.0 nautical miles and 1200 feet vertically are representedas a solid cyan diamond. Proximate traffic is shown to improve situationalawareness in the event of a potential conflict with higher priority RA or TAaircraft.4Other TrafficAny transponder replying to traffic not classified as an intruder or proximatetraffic, and within 2700 feet vertically and the range of the display arerepresented as hollow cyan diamonds (only in view with the traffic switch ONand no TA or RA in process). The predicted flightpaths of proximate andother traffic do not penetrate the collision area of the TCAS aircraft.(c) Data TagsA data tag, made up of a two--digit number, a plus (+) or a minus (--) sign, andmay also include an arrow, appears either above or below the intruder aircraftsymbol. The data tag appears in the same color as the advisory.1Two--digit Number (Relative Altitude)Represents the relative altitude difference, in hundreds of feet, either aboveor below the TCAS aircraft of an intruder aircraft. For an intruder above theTCAS aircraft, the data tag is placed above the traffic symbol and precededby a plus (+) sign; for one below, the tag is placed below the traffic symboland be preceded by a minus (--) sign.2Plus (+) or Minus (--) SignAppears adjacent to the relative altitude number and indicates whether thedisplayed aircraft is above (plus) or below (minus) the TCAS aircraft.3ArrowA vertical arrow is placed to the immediate right of the traffic symbol if theintruder is either climbing (up arrow) or descending (down arrow) in excessof 500 feet per minute.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--64(d) VSI Scale OverlaysDuring a resolution advisory, red and green bands overlay the VSI scale. Thered band indicates what vertical speed range is to be avoided by the pilot(prohibited vertical speed). The green band indicates the vertical speed the pilotis to attain to achieve safe separation from a threat aircraft (recommendedvertical speed). The red/green band reflects the RA in progress and acts as avertical speed advisory for the pilot.(e) Reference Graphics and AnnunciationsA white airplane symbol is displayed in the lower center of the VSI representingthe aircraft own position. A white range ring made up of 12 dots, eachcorresponding to a normal clock position, is included. The range ring surroundsthe airplane with a radius of 2 nautical miles and is intended to assist ininterpreting TCAS traffic information.The scale of the VSI display is 6.0 nautical miles to the top display edge of theVSI (ahead of the aircraft), 4 miles to the left and right edges, and 2.5 nauticalmiles to the bottom (behind the aircraft).Annunciations in white letters serve as a reminder of the current operation mode.They include TCAS OFF, TA only and RA only. Fault annunciations in amberletters replace the mode annunciations in case of system failure. They includeTCAS FAIL, RA FAIL, VSI FAIL, and TA FAIL (traffic display failure). Figure 1--14shows a typical failure display.(3) Aural MessagesThe TCAS generates aural alerts or messages announced over the aircraft audiosystem. These messages accompany the visual TA or RA display and are softenedor strengthened, depending on the urgency of the situation. The TCAS audio level ispreset and is not adjustable by the aircrew.If a logic change occurs before a message is completed and a new message isinitiated, the original alert is terminated and the new alert announced immediately.(a) Requirements and LimitationsThe following is a list of the requirements and limitations for issuing an auraladvisory by the T2CAS Computer Unit:1Voice announcements are inhibited below 500 feet above ground level(AGL).2The CANCEL BUTTON, which is reserved for future use on the --XX001T2CAS CUs only, halts voice announcements after the CANCEL BUTTON isactivated. An aural advisory in progress is terminated and not repeated afterdeactivation of the CANCEL BUTTON.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--653During T2CAS computer unit self--test, an aural advisory confirms properoperation of the aural advisory system by annunciating the message “TCASTEST”. The aural advisory system annunciates the pass/fail status of anymonitored functions with the messages “TCAS TEST PASS” and “TCASTEST FAIL”, respectively.4An aural advisory tone will precede each aural advisory when the audio toneenable program pin has been activated.5T2CAS computer unit TCAS aural alerts are inhibited when the advisoryinhibit discrete input No. 4 is grounded. An aural advisory in progress isdisabled after the grounding of advisory inhibit discrete No. 4. The truncatedmessage is annunciated in its entirety once the inhibit discrete has beenreleased. This capability is used to defer all advisory (TA and RA), auralalert, and visual alert outputs until another, higher priorityannouncement/alert is completed.6Increases and decreases in the threat level are aurally annunciated.However, decreases in threat level are annunciated once and are notpreceded by setting the audio tone discrete. For example, a vertical speedrestriction following a climb RA is annunciated once.(b) Traffic Advisory (TA) MessageThe traffic advisory aural alert, TRAFFIC -- TRAFFIC is spoken once, and theninhibited until the next TA occurs. This alert occurs when TCAS predicts anintruder will enter the collision area within 20 to 48 seconds. Simultaneously, theTCAS traffic display shows the location of the intruder.(c) Resolution Advisory (RA) MessagesResolution advisories indicate evasive vertical maneuvers calculated to increaseseparation between the TCAS aircraft and the intruder (corrective advisory), or toindicate certain changes in vertical speed are not recommended (preventive).Resolution advisory messages made up of a single word are repeated threetimes; longer messages are repeated twice.RAs are annunciated on the T2CAS computer unit using the voice messageslisted below as determined by Collision Avoidance System (CAS) data. Thefollowing messages will not immediately follow another message from thisparagraph if it causes a reversal of sense. For example, a “CLIMB, CLIMB”message cannot immediately follow a :”DESCEND, DESCEND” message.1“CLIMB, CLIMB”: Climb at the rate shown on the VSI or other suitableindicator.2“DESCEND, DESCEND”: Descend at the rate shown on the VSI or othersuitable indicator.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--663“MONITOR VERTICAL SPEED”: Verify that vertical speed is out of theilluminated red VSI arc, or comply with another suitable indicator. AdditionalT2CAS CU messages are “MAINTAIN VERTICAL SPEED, MAINTAIN:MAINTAIN VERTICAL SPEED, CROSSING MAINTAIN”: or “ADJUSTVERTICAL SPEED, ADJUST”. Safe separation is based upon maintainingthe current vertical speed.4“ADJUST VERTICAL SPEED, ADJUST”: Reduce climb or descent rate.5“MAINTAIN VERTICAL SPEED, MAINTAIN”: Safe separation is based uponmaintaining the current vertical speed.6“MAINTAIN VERTICAL SPEED, CROSSING, MAINTAIN”: Maintain verticalspeed while crossing the intruder’s flight path. This advisory is implementedon --XX003 TCAS CUs.7“CLEAR OF CONFLICT”: Range is increasing, and separation is adequate;return to assigned clearance.8“CLIMB, CROSSING CLIMB—CLIMB, CROSSING CLIMB”: Safe separationis best be achieved by climbing through intruder’s flight path.9“DESCEND, CROSSING DESCEND, DESCEND, CROSSING DESCEND”:Safe separation is best achieved by descending through the intruder’s flightpath.(d) Enhanced RA MessagesEnhanced RAs are annunciated on the T2CAS computer unit using the voicemessages listed below as designated by the CAS data when the initial resolutionadvisory does not provide sufficient vertical separation. These messages areannunciated to convey a sense of urgency. The following messages canimmediately follow a message from the previous paragraph and have a reversalof sense.NOTE: These advisories are expected to occur only on rare occasions, usuallywhen an intruder suddenly changes its current flightpath. (Maneuveringintruder)1“INCREASE CLIMB, INCREASE CLIMB”: (Received after a “CLIMB”advisory) Indicates additional climb rate required to achieve safe verticalseparation from a maneuvering intruder.2“INCREASE DESCENT, INCREASE DESCENT”: (Repeated two times,received after “DESCEND” advisory) Indicates additional descent raterequired to achieve safe vertical separation from a maneuvering intruder.3“CLIMB, CLIMB NOW!—CLIMB,CLIMB NOW!”: (Received after a“DESCEND” resolution advisory) Indicates a reversal in sense is required toachieve safe vertical separation from a maneuvering intruder.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--674“DESCEND, DESCEND NOW!—DESCEND, DESCEND NOW!”: (Receivedafter a “CLIMB” resolution advisory) Indicates a reversal in sense is requiredto achieve safe vertical separation from a maneuvering intruder.(4) Operating ProceduresBasic TCAS operating procedures on the ground include pre--flight test, TCASactivation before takeoff, and TCAS deactivation after landing. In--flight proceduresare contained in the pilot’s manual.(a) Pre--Flight TestThe VSI/TRA self--test feature provides a convenient method to test the TCASsystem before takeoff.NOTE: Self--test can be initiated at any time, on the ground or in flight (if notdisabled in air by grounding pin RBP--8E), by momentarily pushingTCAS TEST. If TAs and RAs occur while self--test is activated in flight,the test aborts, and the advisories are processed and displayed.To perform self--test, push the TCAS TEST button on the control panel andmonitor the sequence that follows:•Aural annunciation TCAS TEST is heard on audio system.•Test pattern with fixed traffic and advisory symbols appears on the display foreight seconds.•Make sure the test pattern is as shown in Figure 1--18. The test patternincludes:-- An RA symbol at 3 o’clock, 2 nm, 200 ft above, in level flight-- A TA symbol at 9 o’clock, 2 nm, 200 ft below, climbing-- A proximate traffic symbol at 3.6 nm, 33 degrees right of the aircraftheading (approximately 1 o’clock), 1000 ft below, descending-- A non--threat intruder (other traffic symbol) at 3.6 nm, 33 degrees left of theaircraft heading (approximately 11 o’clock), 1000 ft above, in level flight-- Red and green resolution advisory VSI overlay indicating a don’t descend,don’t climb > 2000 ft/min advisory-- TCAS TEST or RA OFF annunciation, depending on the capabilities of thedisplay.-- After 8 seconds, TCAS TEST PASS is announced, and the test pattern isreplaced with the normal VSI display.-- If self--test fails, TCAS TEST FAIL is announced, and TCAS FAIL appearson the display. To obtain failure data, perform the extended test modeprocedure in the next section.(b) TCAS Mode ActivationPrior to takeoff, activate TCAS as follows:
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--68•Set TCAS/XPDR mode selector to TA/RA•Set TA/DSPLY to AUTO•Set ALT/RPTG to 1 or 2.(c) TCAS Mode DeactivationAfter clearing the runway following landing, set the TCAS/XPDR mode selectorto STBY to disable Mode S communication.Figure 1--18. TCAS ll Display Test PatternB. TAWS/RWS OperationThe principal modes of operation and display features of the TAWS/RWS function arediscussed in the paragraphs that follow. In--flight procedures with display examples arecontained in the T2CAS Pilot’s Manual, ACSS Publication No. 8000264--001.(1) TAWS Operational ModesThe T2CAS TAWS function provides both conventional GPWS and CollisionPrediction & Alerting (CPA) modes of operation.The conventional GPWS modes of operation are as follows:(a) Mode 1: Excessive Rate of Descent with respect to TerrainWhen the CPA mode is inoperative, this mode provides, as defined in RTCADO--161A, a reactive medium--term caution and a reactive short--term warningwhen the current flight path is descending toward the terrain ahead of the aircraftat an excessive rate. Figure 1--19 shows Mode 1 -- Excessive Descent RateEnvelope.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--69Figure 1--19. Mode 1 -- Excessive Descent Rate Envelope(b) Mode 2: Excessive Closure Rate to TerrainWhen the CPA mode is inoperative, this mode provides, as defined in RTCADO--161A, a reactive medium--term caution and a reactive short--term warningwhen the current flight path and the terrain ahead of the aircraft are closing at anexcessive rate. Figure 1--20 shows Mode 2 -- Excessive Terrain Closure RateEnvelope.Figure 1--20. Mode 2 -- Excessive Terrain Closure Rate Envelope
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--70(c) Mode 3: Excessive Altitude Loss after Take--offThis mode provides, as derived from RTCA DO--161A, an alert when there is aloss of altitude after take--off or during a missed approach. Figure 1--21 showsMode 3 -- Loss of Altitude After Take Off Envelope.Figure 1--21. Mode 3 -- Excessive Altitude Loss After Take Off Envelope(d) Mode 4: Incorrect Aircraft Configuration with regard to TerrainT2CAS meets the requirement for Mode 4 alerts as defined in RTCA DO--161A.Mode 4 applies during the landing phase of flight and results in the annunciationof an alert in the event of insufficient terrain clearance when the aircraft is not inthe proper landing configuration. Mode 4 consists of the following twosub--modes:•Mode 4A, when the landing gear is up•Mode 4B, when the landing gear is down, but the flaps are not in landingconfigurationFigure 1--22 shows Mode 4 -- Unsafe Terrain Clearance Envelope.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--71Figure 1--22. Mode 4 -- Unsafe Terrain Clearance Envelope(e) Mode 5: Excessive Glide Path DeviationT2CAS meets the requirement for Mode 5 alerts as defined in RTCA DO--161A.Mode 5 applies in the event of an excessive descent below the instrument glidepath when making a front--course approach with the gear down. In aback--course landing configuration, mode 5 is automatically inhibited.Figure 1--23 shows Mode 5 -- Excessive Glide Path Deviation Envelope.Figure 1--23. Mode 5 -- Excessive Glide Path Deviation Envelope(f) Altitude Call--outsThe T2CAS TAWS function produces call--outs and alerts for descent below a setof customer defined altitudes.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--72(g) Excessive Bank AngleThe T2CAS TAWS function produces call--outs and alerts for descent below a setof predefined altitudes and for excessive bank angle. Figure 1--24 showsExcessive Bank Angle Envelope.Figure 1--24. Excessive Bank Angle EnvelopeThe CPA mode of operation provides medium--term (caution) and short--term(warning) alerts to inform the crew that the flight path they are following is hazardousdue to the presence of terrain ahead. The objective of the CPA function is to warnthe crew of an impending controlled flight into terrain with sufficient time for them toassess the situation and safely avoid the terrain hazard. All CPA predictions arebased on the assumption that the operational escape maneuver in case of a terrainhazard will be a ”pull up” evasive action. CPA predictions model a conservative pullup escape maneuver based on current aircraft climb capability.The T2CAS CPA function provides alerts in the following CFIT situations:•Hazardous descent rate with respect to terrain•Hazardous closure rate with respect to terrain•Hazardous terrain ahead situation during turns•Hazardous high terrain ahead situation that can not be cleared by a pull upmaneuver
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--73(2) RWS Operational ModeWhenever wind factors cause aircraft performance to decrease to a predeterminedlevel, an audio warning is sounded, indicating to the crew that the aircraft netperformance capability is deteriorating and rapidly approaching a critical state. Inaddition to the warning, the Windshear Warning algorithm provides a caution whenan increasing--performance Windshear is detected, thus giving advance warning ofdecreasing--performance windshear. Figure 1--25 illustrates reactive windsheardetection.Figure 1--25. Windshear Detection(3) TAWS Display SymbologyThe terrain hazard display function generates an image that provides the followinginformation to the flight crew:•A Terrain Display Background consisting of shaded areas representing terrain atdifferent altitudes relative to the aircraft altitude•An Alert Line depicting the point or points where a CPA caution will occur if theaircraft continues on its current trajectory
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--74•Terrain Alert areas corresponding to the terrain that is causing a CPA caution orwarning.Each of these features is explained in the following sub--sections.(a) Terrain Display BackgroundThe purpose of the Terrain Display Background is to provide overall situationalawareness to the crew about the relative height of the terrain near the aircraft.The terrain is divided into ”slices” based on the elevation of the terrain withrespect to an aircraft reference altitude. Slices above or very near the referencealtitude are typically shown as varying shades of yellow. Slices safely below thereference altitude are typically shown as varying shades of green or even black.The reference altitude is a surface starting at the aircraft and propagatingforward along the aircraft flight path angle for 30 seconds. The reference altitudesurface then extends horizontally at the altitude the aircraft is expected to haveat that time (i.e., 30 seconds in the future).The specific colors and textures used for the various slices, as well as thethreshold altitudes for the slices, are contained in the Aircraft Specific Database(ASDB) and thus can be tailored for specific installations. Figure 1--26 shows atypical color scheme and altitude definitions. (Note: The figure is drawn in color.If this document is printed in black and white, the different yellow and greentextures representing different terrain elevations will appear as different shadesof gray.)Figure 1--26. Terrain Slices
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--75A typical terrain background image is shown in Figure 1--27Figure 1--27. Terrain Display Background(b) Alert Line DisplayThe Terrain Hazard Display can also depict an Alert Line. The Alert Line isdrawn at the points where a CPA caution will occur if the aircraft continues alongit’s current vertical trajectory. When there are no CPA cautions or warningsactive, T2CAS TAWS will determine if an alert line needs to be drawn. Beginningat the current aircraft position, T2CAS TAWS looks ahead of the aircraft todetermine where a CPA caution will occur. T2CAS TAWS will look up to 120seconds into the future and look at all headings within 30 degrees of the currentaircraft heading. If any CPA cautions would be triggered in this area, the alertline will be drawn on the terrain hazard display.Figure 1--28 illustrates the alert line. The alert line is the solid yellow line locatedat about the 5 NM range ring. As the aircraft continued, this line (as well as thebackground terrain) would get closer to the aircraft symbol. When the alert linereached the aircraft symbol, a CPA caution would occur. Thus the alert lineprovides the flight crew an advance indication of when CPA alerts will occur. Thealert line is not displayed when a CPA caution or warning is active.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--76Figure 1--28. Alert Line(c) Display of Terrain AlertsWhen a CPA caution or warning occurs, the terrain that caused the alert will bedisplayed on the Terrain Hazard Display. Solid yellow is used for cautions, solidred is used for pull--up warnings, and black x’s on a solid red background areused for avoid terrain warnings.In Figure 1--29, the caution alarm is generated through the TAWS display byhighlighting the hazardous area ahead of the aircraft in yellow and generating ayellow ”TERRAIN” message on the bottom right of the screen. An aural messageis also played on the flight deck.Figure 1--29. Terrain Hazard Display Upon Caution Alert
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--77In Figure 1--30, the warning alarm is generated through the TAWS display byhighlighting the hazardous area ahead of the aircraft in red and generating a red”TERRAIN” message on the bottom right of the screen. An aural message is alsoplayed on the flight deck.Figure 1--30. Terrain Hazard Display Upon A Pull--up WarningIn Figure 1--31, the warning alarm is generated through the TAWS display byhighlighting the hazardous area ahead of the aircraft in red with black X’s andgenerating a red ”TERRAIN” message on the bottom right of the screen. Anaural message is also played on the flight deck. The ”pull--up” maneuver will notallow for a safe clearance with terrain, and the crew has to immediately initiatean appropriate vertical and/or turning escape maneuver in order to avoid a CFITaccident.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--78Figure 1--31. Terrain Hazard Display Upon An Avoid Terrain Warning(4) TAWS/RWS Aural MessagesAural alerts can be generated for any of the cautions or warnings generated by theTAWS and RWS functions. The specific messages are selectable from a list ofseveral options. Additionally, the T2CAS can be configured to play the voices ineither a male voice or a female voice. The list of selectable aural alerts is shown inTable 1--13.Table 1 -- 13. TAWS/RWS Aural AlertsCondition Selectable Aural AlertsCPA Caution “Terrain Ahead”or“Terrain Caution”CPA Warning -- Pull up “Terrain Ahead, Pull Up”or“Terrain, Terrain, Pull Up, Pull Up”orWhoop Whoop, “Pull Up”CPA Warning -- Avoid Terrain “Avoid Terrain”Mode 1 Caution Whoop Whoop, “Pull Up”or“Pull Up, Pull Up”Mode 1 Warning Whoop, Whoop, “Pull Up”or“Pull Up, Pull Up”
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--79Table 1 -- 13. TAWS/RWS Aural Alerts(cont)Condition Selectable Aural AlertsMode 2 Caution “Terrain, Terrain”Mode 2 Warning Whoop Whoop “Pull Up”or“Pull Up, Pull Up”Mode 3 Caution “Don’t Sink, Don’t Sink”Mode 4 Caution “Too Low Terrain”or“Too Low Flaps”or“Too Low Gear”Mode 5 Caution “Glideslope”Bank Angle Alert “Bank Angle, Bank Angle”Windshear Caution Nothingor“Caution Windshear”
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--80Table 1 -- 13. TAWS/RWS Aural Alerts(cont)Condition Selectable Aural AlertsWindshear Warning “Windshear Windshear Windshear”orsiren “Windshear Windshear Windshear”Callouts “Minimums Minimums”“Minimums”“Decision Height”“Unknown Decision Height”“Approaching Minimums”“Approaching Decision Height”“One thousand”“Five Hundred”500 ft. tone“Four Hundred”“Three Hundred”“Two Hundred”“One Hundred”100 ft tone“Eighty”“Sixty”“Fifty”“Forty”“Thirty Five”35 ft. tone“Thirty”“Twenty”20 ft. tone“Ten”
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--81(5) Operating ProceduresBasic TAWS/RWS operating procedures on the ground include pre--flight test,TAWS/RWS activation before takeoff, and TAWS/RWS deactivation after landing.In--flight procedures are contained in the pilot’s manual.(a) Pre--Flight TestThe Standard Self Test is performed by activating either the CMC self test or theself test discrete input (RTP--10E = GND). The Standard Self Test can occurwhile on the ground or while in the airborne state.Upon activating the Standard Self Test the following will occur:The Standard Self Test will not be initiated if a TAWS alert is present wheneither the CMC self test or the self test discrete input is activated.If the T2CAS unit has the windshear function enabled, the following auralannunciation will occur:”TERRAIN AWARENESS AND WINDSHEAR TEST START”If the T2CAS unit does not have the windshear function enabled, thefollowing aural annunciation will occur:”TERRAIN AWARENESS TEST START”During the Standard Self Test the following will occur:All discrete outputs implemented within a specific aircraft installation will betested for over current and output voltage levels by activating the output for1.5 seconds (±100 milliseconds), then deactivating the output for 1.5seconds (±100 milliseconds), and then re--activating the output for 1.5seconds (±100 milliseconds). Any faults found will be recorded in theT2CAS unit’s non--volatile memory.The T2CAS unit will verify the following functional areas in accordance withFigure 1--32.•Aircraft Personality Module (APM)•Terrain Database CRC•External System Inputs•Internal TAWS Parameters•Internal GPS Parameters (if installed)
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--82Figure 1--32. Standard Self--Test of TAWS/Windshear Functional Areas
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--83ID--8000574TST PTRNHOLD SLF TSTTO VIEW EXTENDEDNN2233445566CCPPAAFigure 1--33. TAWS Display Test PatternThe T2CAS unit will display a multicolor test pattern on both the captain’s andfirst officer’s TAWS displays. Figure 1--33 shows a typical multicolor test pattern.NOTE: Each number in Figure 1--33 represents a texture terrain image slice (2through 6) as well as the Pull Up area texture (P), avoid terrain areatexture (A), and caution area texture (C) as defined in the ASDB SRS,Airplane Personality Module. Slice 1 is black in color therefore it iscamouflaged into the backgroundThe T2CAS unit will interrupt the Standard Self Test when any of the followingalerts occur:•“WINDSHEAR, WINDSHEAR, WINDSHEAR”•“TERRAIN AHEAD, PULL UP”•“TERRAIN TERRAIN, PULL UP PULL UP”•“≈≈ PULL UP”•“TERRAIN AHEAD”•“TERRAIN CAUTION”•“AVOID TERRAIN”•“PULL UP, PULL UP”•“TERRAIN, TERRAIN”•“SINK RATE, SINK RATE”
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--84•“DON’T SINK, DON’T SINK”•“TOO LOW, TERRAIN”•“TOO LOW, GEAR”•“TOO LOW, FLAPS”•“GLIDESLOPE”NOTE: “≈≈” designates a pair of varying tones from 400 to 800 Hz; whereeach tone is 0.3 seconds in duration, separated by 0.1 seconds, and atthe end of the pair there is 0.1 seconds of silence.NOTE: The aural annunciations listed above will depend on the OperatorSelectable Options chosen during installation of the T2CAS unit.Upon completion of the Standard Self Test the following will occur:If the T2CAS unit has the windshear function enabled and the APM andTerrain Database and Internal system and Internal GPS self tests havepassed, the following aural annunciation will occur:”TERRAIN AWARENESS AND WINDSHEAR TEST PASSED”If the T2CAS unit does not have the windshear function enabled and theAPM and Terrain Database and Internal system and Internal GPS self testshave passed, the following aural annunciation will occur:”TERRAIN AWARENESS TEST PASSED”If the T2CAS unit does not have the windshear function enabled and theAPM or Terrain Database or Internal system or Internal GPS self tests havefailed, the following aural annunciation will occur:”TERRAIN AWARENESS AND WINDSHEAR TEST COMPLETE”If the T2CAS unit does not have the windshear function enabled and theAPM or Terrain Database or Internal system or Internal GPS self tests havefailed, the following aural annunciation will occur:”TERRAIN AWARENESS TEST COMPLETE”This information is summarized in the Table 1--14.Table 1--14. Aural AnnunciationTerrain Awarenessand WindshearTest PassedTerrain Awarenessand WindshearTest CompleteTerrain AwarenessTest PassedTerrain AwarenessTest CompleteWindshearEnabled?YES YES NO NOAPM or TerrainDatabase orInternal System orInternal GPS Fail?NO YES NO YES
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--85(b) TAWS/RWS Mode ActivationThe TAWS/RWS is activated upon Aircraft Power Up and becomes availablewhen parameters needed for normal operation of the TAWS/RWS functions areavailable.(c) TAWS/RWS Mode DeactivationThe TAWS/RWS becomes deactivated upon Aircraft Power Down. SpecificTAWS/RWS functions can become unavailable if an Internal or Externalparameter needed for normal operation of the TAWS/RWS functions areunavailable or invalid.The TAWS Predictive CPA Modes may become deactivated upon the selectionof the “Terrain Inhibit” switch. The purpose of the “Terrain Inhibit” switch is toallow the aircraft to operate without nuisance or unwanted warnings at airportsthat are not in the system database. Additionally, there may be some “VFR only”airports where unique terrain features are in close proximity to the runway. The“Terrain Inhibit” switch should NOT be engaged for normal operations.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.1--86Blank Page
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.2--1MECHANICAL INSTALLATION1. GeneralThis section contains information on how and where to mount each component of the T2CASsystem. For new installations, plan installation in two stages. First, determine the location ofthe LRUs in the aircraft. Next, determine the length of RF and electrical interconnections forselected locations.NOTE:The RT--95X CFDS/CMC capability has not been demonstrated as part of aninstalled system. The CFDS/CMC capability must be demonstrated on the aircraft tothe appropriate certification authorities before the CFDS/CMC functionality may beused.2. Equipment and MaterialsFor new T2CAS installations, refer to Table 1--1 for RCZ--852 Transponder Installation Kitinformation and Table 1--2 for mounting tray information. For all other components, refer tothe applicable Outline and Installation drawing in this section for mounting information. TheOutline and Installation drawings show connector and connector contact pin/socket partnumber information, where applicable.3. Mechanical Installation DesignNOTE:To assure proper grounding of the T2CAS system, the aircraft surface to which allmountings or units are attached must be clean bare metal. Mount to the airframewith a resistance of 5 milliohms or less.A. TT--950/951/952 T2CAS Computer Unit ProvisionsMechanical installation data for the TT-- 950/952 T2CAS Computer Unit (6--MCU) isshown in Figure 2--6. Data for the TT--951 T2CAS Computer Unit (4--MCU) is shown inFigure 2--7.The computer unit can be mounted in any convenient location in the aircraft; however, itmust be located so as to maintain an antenna coaxial cable insertion loss of 2.5 ±0.5 dBin accordance with DO--185. This is approximately within 50 feet of the antenna unlesslow loss coaxial cable is used. Top and bottom coaxial delay timing differences can becompensated for by use of the antenna delay program pins.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.2--2The TT--950/952 T2CAS Computer Unit is mounted in an ARINC 600 6--MCU mountingtray. The computer unit requires external cooling air in accordance with ARINC 600 orARINC 404 to maintain the highest possible Mean Time Between Failures (MTBF). Inthose installations where this is not available, a mounting tray with an integral fan isrequired.The TT--951 T2CAS computer unit is mounted in an ARINC 600 4--MCU mounting tray.This unit contains an internal temperature controlled fan, so it does not require anyexternal cooling.The T2CAS computer tray connector is RADIALL part number NSXN3P357X0001 (otherBrands are available, but the RADIALL is preferred). This tray connector does not comewith contacts so approximately 150 each RADIALL part number 620--200, 22 gauge pinswill be needed as well.The required contacts for the LBP insert depend on if the computer is to be powered with+28 Vdc or 115 Vac and if a 115 Vac cooling fan will be connected when the computer ispowered with 115 Vac. Note that there is no output pins to support a +28 Vdc cooling fan.B. Airplane Personality Module ProvisionsReference Figure 2--5 for the mechanical installations of the ACSS T2CAS APM. TheAPM can be mounted to existing aircraft structure or can be mounted to the ACSS APMmounting bracket that is secured to the aft side of the T2CAS computer tray connector,reference Figure 2--5 (Sheet 2). If the Customer specifies the ACSS APM mountingbracket, an APM bracket sub kit will be provided for the Customer’s T2CAS installations.C. Antenna ProvisionsThe T2CAS TCAS top directional antenna should, ideally, be the most forward antenna onthe top of the aircraft and should be located as close to the longitudinal centerline aspossible. See Figure 2--10. A 5--degree tilt angle is allowed laterally, with 2--degreepositive and 5--degree negative tilt angles allowed longitudinally. See Figure 2--11.If a bottom directional antenna is used, it should also be the most forward antenna on thefuselage bottom. Tilt angle allowances are the same as on the top antenna. A bottomomnidirectional antenna need not be the most forward antenna, but it should beseparated by at least 20--inches from any other L--band antenna.Since the bottom antenna may be either a directional (standard) or an omnidirectional(optional) antenna, dual notation is shown in the wiring diagram. Only one coax cable isneeded for an omnidirectional antenna installation.(1) Directional Antenna InstallationThe top directional antenna mounting and installation data is given in Figure 2--12.Figure 2--12 contains the maximum radius dimensions for the various curved antennabase part number units, the number of aircraft mounting holes and the length of theconnector extension for the various part number units. The antenna must beelectrically bonded (less than 5.0 milliohms bonding resistance) to the airframe toprovide a ground plane for the antenna elements.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.2--3The directional antenna must be separated by a least 30--inches from any otherL--band antenna, and 60--inches is preferred. If a bottom directional antenna is used,it should be the most forward antenna on the fuselage bottom with tilt angleallowances the same as for a top mounted antenna.An O--ring (included with the directional antenna) is required to be installed betweenthe directional antenna and the aircraft fuselage. The Navy Aeronautical Standardpart number for the O--ring is NAS 1611--240. The ACSS part number for the O--ringis 4000171--240.NOTE: For directional antennas, ACSS Part No. 7514060--90X, the customer mustprovide an adapter plate for mounting to the aircraft. The antenna baseplate, to which the adapter must mate, is detailed in Figure 2--12.Directional antennas, ACSS Part No. 7514081--9XX, come with apreinstalled adapter plate.(2) Omnidirectional Antenna InstallationThe bottom omnidirectional antenna is a standard ATC type antenna. It should bequalified to TSO C119b and be DC grounded per MIL--A--90941, B--5087B. AllL--band antennas must be separated by at least 20--inches. Only one coax cable isrequired for installation.The omnidirectional antenna is not supplied by ACSS. To install, follow themanufacturer’s installation instructions.D. GPS Antenna and Coax ProvisionsReference Figure 2--4 for the mechanical installations of the ACSS GPS Antenna. TheGPS installation design will consist of an A429 interface to the GPS sensor if the signal isavailable, otherwise the T2CAS internal GPS module will be required. The installationthen consists of the installation of a GPS antenna and the coax cable to the T2CAS unit,LBP pin 13.Where the internal module is required, the T2CAS GPS Installation Data Packageincludes the GPS antenna mounting structures provisions and all of the coax details tosecure the coax to the airframe and connect the T2CAS GPS antenna with the T2CAScomputer’s LBP pin 13.The minimum combined coax and connector insertion loss between the GPS antenna’soutput and the T2CAS computer’s GPS input port is equal to the maximum preamplifiergain minus 29 dB. The maximum coax loss between the GPS antenna’s output and theT2CAS computer’s GPS input port is equal to the minimum preamplifier gain minus 12.5dB.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.2--4This is summarized with several examples in the Table 2--1 below, assuming 4 uniqueinstallations.Table 2--1. Coax Cable/Connector LossAssumedAntennaGain (dB)MinimumCable AndConnectorLoss(dB)Maximum CableAnd ConnectorLoss(dB)CableLength(feet)RecommendedCableType(andloss)(Cable Length (feet)xLoss) + ConnectorLoss= Cable andConnector Loss30 30 -- 29 = 1 30 -- 12.5 = 16.5 10 311601 (0.11 db/ft) (0.11*10)+1=2.130 30 -- 29 = 1 30 -- 12.5 = 16.5 100 311601 (0.11 db/ft) (0.11 * 100) + 1 = 1226 26<29=>0 26 -- 12.5 = 13.5 10 311601 (0.11 db/ft) (0.11*10)+1=2.126 26<29=>0 26 -- 12.5 = 13.5 100 311601 (0.11 db/ft) (0.11 * 100) + 1 = 12In the above examples, the antenna gain and assumed losses effectively stay within thedesired minimum and maximum ranges.High--quality coaxial cables should be used because a mismatch in impedance, possiblewith lower quality cables, produces reflections in the cable that increase signal loss.Losses due to cable mismatch should be considered in the maximum cable loss budget.The coax must meet FAR part 25 specifications for environmental conditions.Recommended antenna mounting location(1) The GPS antenna should be installed close to aircraft centerline with minimumdeviation from the aircraft level horizontal position. The antenna location is on the topside, front half of the aircraft fuselage to minimize the shadowing effect of the verticalstabilizer and wings.(2) The GPS antenna should be installed at least 39 inches (1 meter) away from anyother non L--band or L--band except as mentioned below.(3) If a SATCOM transmitting antenna is installed, the GPS antenna should be located aminimum of 160 inches (4.064 meters) away.(4) For a dual GPS antennae installation, the separation should be a minimum of 12inches.(5) If a TCAS or VHF communication transmitting/receiving antenna is installed, the GPSantenna should be located a minimum of 48 inches (1.219 meters) away.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.2--5E. TCAS Control Panel ProvisionsMechanical installation data for a typical Gables GXXXX Series ATC/TCAS control panelis shown in Figure 2--14.It should be noted that various other types of controllers (Radio Management Units orEFIS Display Controllers) can be used to control the TCAS display. If a controller otherthan a ACSS ATC/TCAS control panel is used, refer to that particular unit’s manual forinstallation data.F. TAWS/RWS Control Panel ProvisionsThe TAWS controls can be mounted on a single control panel or they can be discreteswitches individually mounted at a convenient location in the Flight Deck. The TAWScontrols may be part of the electronic display menu selection in installations where TAWSinformation is displayed on an EFIS or electronic display.Figure 2--1 shows the ACSS King Air C90 TAWS control panel/glareshield switchannunciator installation design. The TERR and WXR select switches shown aremomentary but alternate action switches are also supported. The terrain INHIBIT orOVRD switches are alternate action switches and are typically gaurded.The T2CAS TAWS control/annunciator installation design will vary depending on the Flightdeck configuration and available space.G. VSI/TRA ProvisionsMechanical installation data for the VSI/TRA display is shown in Figure 2--15. TheVSI/TRA is usually used as a direct replacement for the existing 3--ATI form VSI indicatorcurrently mounted in the Flight Deck. Replacement of the installation clamp may benecessary if the previous clamp is less than 2--inches deep. Some older aircraft clampsdo not provide sufficient mechanical support.If a Thales VSI/TRA is used as the TCAS display source, and an Air Data Computer is notavailable to provide vertical speed signals to the display, a static line can be run directlyinto the Thales VSI/TRA from a static pneumatic input.H. TAWS Terrain Hazard Display ProvisionsARINC 708A and ARINC 429 WXR display and EFIS interfaces are supported. T2CAS’dual--independent terrain hazard display I/O supports dual ARINC 708A and dual ARINC429 terrain hazard display systems. Figure 2--2 shows TAWS Dual Terrain hazard displayannunciator switch panels and locations that have been used on B757, B767, andB737--300/400/500 aircraft. Figure 2--3 shows a typical single terrain hazard displayannunciator switch panel.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.2--6NORMCMPSTTERRWXRTERRN/AGPWSN/ATERRTERRCAPTAIN’S AND FIRST OFFICER’S GLARESHIELDSWITCH ANNUNCIATORS. (ANNUNCIATOR TEST ON)CAPTAIN’S AND FIRST OFFICER’S GLARESHIELDSWITCH ANNUNCIATORS. (NORMAL FLIGHT CONDITION)ANNUNCIATOR TEST ON. (WHITE DASHES AREHIDDEN LINES SHOWING EXISTING 3 ATI CUTOUT)ID--8000576FLAPOVRDGSOVRDSTEEPAPPRUPDOWNTERRN/AGPWSN/AON ON ONTERRINHIBITTERRONTERRFigure 2--1. ACSS King Air C90 TAWS Control Panel/Glareshield Switch Annunciators
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.2--7Figure 2--2. Typical Five--Button B737/757/767 Annunciator Switch Panels
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.2--8Figure 2--3. Typical Single Terrain Hazard Display Annunciator Switch PanelI. Transponder ProvisionsThis paragraph contains the mechanical installation data for the ACSS Mode S Data LinkTransponder, Part No. 7517800--XXYYY and ACSS Diversity Mode S Transponder, PartNo. 7510700--850. It also contains provisions for installing the ATC transponderantennas.(1) Mode S Data Link Transponder ProvisionsMechanical installation data for the ACSS Mode S Data Link Transponder, Part No.7517800--XXYYY is shown in Figure 2--8. The transponder can be mounted in anyconvenient location in the aircraft; however, it should be mounted within 30 feet of theantennas unless low loss coaxial cable is used to maintain a worst case loss of 3dBper ARINC 718. Top and bottom antenna coaxial run length differences can becompensated for by use of the antenna delay program pins on the transponder. Theunit can utilize external cooling air in accordance with ARINC 600 or ARINC 404 oroperate in convection--cooled environments. The transponder is mounted in anARINC 600 4--MCU tray assembly.(2) Diversity Mode S Transponder ProvisionsMechanical installation data for the ACSS RCZ--852 Diversity Mode S Transponder,Part No. 7510700--850 is shown in Figure 2--9. The transponder can be mounted inany convenient location in the aircraft that allows the unit to be upright during normalflight. The exact location should allow the cabling between the unit, control panel,and antennas to be as short as possible. The location of the mounting tray (part ofinstallation kit, Part No. 7510707--968) should allow adequate space for installationof the transponder, provide reasonable accessibility for servicing, and allow space ontop, sides, and rear of unit for adequate ventilation. The location must also provide asolid mechanical mount to prevent vibration amplification. The mounting tray shouldbe electrically bonded to the aircraft frame by a low resistance path of less than 2.5milliOhms.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.2--9(3) ATC Transponder Antenna ProvisionsWhen installing transponder antennas, a TSO’d antenna should be selected. Theantenna must be vertically polarized and operate in the frequency range of 960 to1220 MHz. Antenna impedance must be 50 ohms. Selection of a grounded orlightning protected type antenna is required to pass the transponder bite continuitydetection circuitry, if enabled.In dual transponder antenna installations it is important to provide adequate isolationfrom each other to prevent receiver front--end damage. A 20--inch minimumseparation of Mode S antennas from other L--Band antennas, including TCASantennas, must be maintained. The maximum cable length for RG--214/U is 30 feet(9.144 meters). Allow adequate cable length so bends in cable have a minimum3--inch (76 mm) radius. Selection of coax cable assemblies with moisture barrierprotection is highly recommended to minimize the effects of humidity and corrosion.When ATC antennas are installed, the mounting area must provide a solidmechanical base for the antenna as well as clearance for the connector. A doublerplate is usually required when the antenna is mounted on an unsupported largefuselage area. Never weaken aircraft structure for the sake of a good location.Refer to the aircraft manufacturer’s specifications; reinforcements for antennas areoften built into the aircraft structure.Doubler plates or shims, if used, must be metallic and shaped to interface theantenna base with the contour of the aircraft fuselage. ATC antennas are notsupplied by ACSS. All antenna installations should be in accordance withmanufacturer installation instructions.A weather sealant should be applied around the periphery of the antenna base toprevent seepage of water and condensation and preclude corrosion. If a sealant oraerodynamic smoother is used, it should be applied after the antenna has beenbolted down.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.2--10Blank Page
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.2--11/(2--12 blank)Figure 2--4. GPS Antenna Outline and Installation Drawing
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.2--13/(2--14 blank)Figure 2--5 (Sheet 1). APM Outline and Installation Drawings
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.2--15/(2--16 blank)Figure 2--5 (Sheet 2). APM Outline and Installation Drawings
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.2--17/(2--18 blank)Figure 2--6 (Sheet 1). TT--950/952 T2CAS Computer Unit Outline and Installation Drawing
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.2--19/(2--20 blank)Figure 2--6 (Sheet 2). TT--950/952 T2CAS Computer Unit Outline and Installation Drawing
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.2--21/(2--22 blank)Figure 2--6 (Sheet 3). TT--950/952 T2CAS Computer Unit Outline and Installation Drawing
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.2--23/(2--24 blank)Figure 2--6 (Sheet 4). TT--950/952 T2CAS Computer Unit Outline and Installation Drawing
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.2--25/(2--26 blank)Figure 2--7 (Sheet 1). TT--951 T2CAS Computer Unit Outline and Installation Diagram
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.2--27/(2--28 blank)Figure 2--7 (Sheet 2). TT--951 T2CAS Computer Unit Outline and Installation Diagram
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.2--29/(2--30 blank)Figure 2--8 (Sheet 1). XS--950 Data Link Transponder Outline and Installation Diagram
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.2--31/(2--32 blank)Figure 2--8 (Sheet 2). XS--950 Data Link Transponder Outline and Installation Diagram
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.2--33/(2--34 blank)Figure 2--9 (Sheet 1). RCZ--852 Mode S Transponder Outline and Installation Diagram
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.2--35/(2--36 blank)Figure 2--9 (Sheet 2). RCZ--852 Mode S Transponder Outline and Installation Diagram
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.2--37/(2--38 blank)Figure 2--9 (Sheet 3). RCZ--852 Mode S Transponder Outline and Installation Diagram
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.2--39Figure 2--10. TCAS Directional and Omnidirectional Antenna Locations
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.2--40Figure 2--11. Directional Antenna Angular Orientation
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.2--41/(2--42 blank)Figure 2--12 (Sheet 1). Directional Antenna Outline and Installation Diagram
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.2--43/(2--44 blank)Figure 2--12 (Sheet 2). Directional Antenna Outline and Installation Diagram
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.2--45/(2--46 blank)Figure 2--12 (Sheet 3). Directional Antenna Outline and Installation Diagram
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.2--47/(2--48 blank)Figure 2--12 (Sheet 4). Directional Antenna Outline and Installation Diagram
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.2--49/(2--50 blank)Figure 2--12 (Sheet 5). Directional Antenna Outline and Installation Diagram
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.2--51/(2--52 blank)Figure 2--13 (Sheet 1). Directional Antenna Baseplate Outline and Installation Diagram

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