Honeywell CAS-100 Maintenance Manual Download Page 161

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1 Dec 2003

34-45-4

MAINTENANCE MANUAL

CAS-100 COLLISION AVOIDANCE SYSTEM

Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.

Table 1006. Active Unit, System and Input Faults, and Display Status Indication

Active Unit

Faults

Active System

Faults

Active Input

Faults

Unit (Status)

System/Input

(Status)

Unit OK

System OK

Yes

Unit OK

*Inputs Faulted

Yes

Unit OK

*System Failed

Yes

Unit OK

*System Failed

Yes

*Unit Failed

*System Failed

Yes

*Unit Failed

*System Failed

Yes

*Unit Failed

*System Failed

Yes

*Unit Failed

*System Failed

Summary of Contents for CAS-100

Page 1: ...shington 98073 9701 U S A Maintenance Manual CAS 100 Collision Avoidance System This document contains technical data and is subject to U S export regulations These commodities technology or software were exported from the United States in accordance with the export administration regulations Diversion contrary to U S law is prohibited ...

Page 2: ... others without the written authorization of Honeywell except to the extent required for installation or mainte nance of the recipient s equipment NOTICE FREEDOM OF INFORMATION ACT 5 USC 552 AND DISCLOSURE OF CONFIDENTIAL INFORMATION GENERALLY 18 USC 1905 This document is being furnished in confidence by Honeywell The information disclosed herein fall within exemption b 4 of 5 usc 552 and the proh...

Page 3: ...47 RECORD OF REVISIONS For each revision put the revised pages in your manual and discard the superseded pages Write the revision number and date date put in manual and the incorporator s initials in the applicable columns on the Record of Revisions The initial H shows Honeywell is the incorporator Revision Number Revision Date Date Put In Manual By Revision Number Revision Date Date Put In Manual...

Page 4: ... Dec 2003 MAINTENANCE MANUAL CAS 100 COLLISION AVOIDANCE SYSTEM Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document 34 45 47 THIS PAGE LEFT BLANK ...

Page 5: ...uctions on each page of a temporary revision tell you where to put the pages in your manual Remove temporary revision pages only when discard instructions are given For each temporary revision put the applicable data in the record columns on this page The initial H is this column shows Honeywell has done this task Temporary Revision Number Temporary Revision Date Temporary Revision Status Date Put...

Page 6: ... Dec 2003 MAINTENANCE MANUAL CAS 100 COLLISION AVOIDANCE SYSTEM Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document 34 45 47 THIS PAGE LEFT BLANK ...

Page 7: ...COLLISION AVOIDANCE SYSTEM SERVICE BULLETIN LIST Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document 34 45 47 Service Bulletin Identified Mod Date Included in this Manual Description ...

Page 8: ... Dec 2003 MAINTENANCE MANUAL CAS 100 COLLISION AVOIDANCE SYSTEM Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document 34 45 47 THIS PAGE LEFT BLANK ...

Page 9: ...03 LEP 3 1 Dec 2003 LEP 4 1 Dec 2003 LEP 5 1 Dec 2003 LEP 6 1 Dec 2003 Table of Contents TC 1 1 Dec 2003 TC 2 1 Dec 2003 TC 3 1 Dec 2003 TC 4 1 Dec 2003 TC 5 1 Dec 2003 TC 6 1 Dec 2003 TC 7 1 Dec 2003 TC 8 1 Dec 2003 TC 9 1 Dec 2003 TC 10 1 Dec 2003 Introduction INTRO 1 1 Dec 2003 INTRO 2 1 Dec 2003 INTRO 3 1 Dec 2003 INTRO 4 1 Dec 2003 INTRO 5 1 Dec 2003 INTRO 6 1 Dec 2003 INTRO 7 1 Dec 2003 INTR...

Page 10: ... 37 1 Dec 2003 38 1 Dec 2003 39 1 Dec 2003 40 1 Dec 2003 F 41 42 1 Dec 2003 43 1 Dec 2003 44 1 Dec 2003 45 1 Dec 2003 46 1 Dec 2003 47 1 Dec 2003 48 1 Dec 2003 49 1 Dec 2003 50 1 Dec 2003 51 1 Dec 2003 52 1 Dec 2003 53 1 Dec 2003 54 1 Dec 2003 55 1 Dec 2003 56 1 Dec 2003 57 1 Dec 2003 58 1 Dec 2003 59 1 Dec 2003 60 1 Dec 2003 F 61 62 1 Dec 2003 F 63 64 1 Dec 2003 F 65 66 1 Dec 2003 67 1 Dec 2003 6...

Page 11: ... 108 1 Dec 2003 109 1 Dec 2003 110 1 Dec 2003 F 111 112 1 Dec 2003 F 113 114 1 Dec 2003 Testing and Fault Isolation 1001 1 Dec 2003 1002 1 Dec 2003 1003 1 Dec 2003 1004 1 Dec 2003 1005 1 Dec 2003 1006 1 Dec 2003 1007 1 Dec 2003 1008 1 Dec 2003 1009 1 Dec 2003 1010 1 Dec 2003 1011 1 Dec 2003 1012 1 Dec 2003 1013 1 Dec 2003 1014 1 Dec 2003 1015 1 Dec 2003 1016 1 Dec 2003 1017 1 Dec 2003 1018 1 Dec 2...

Page 12: ...03 2021 1 Dec 2003 2022 1 Dec 2003 2023 1 Dec 2003 2024 1 Dec 2003 2025 1 Dec 2003 2026 1 Dec 2003 2027 1 Dec 2003 2028 1 Dec 2003 2029 1 Dec 2003 2030 1 Dec 2003 2031 1 Dec 2003 2032 1 Dec 2003 2033 1 Dec 2003 2034 1 Dec 2003 2035 1 Dec 2003 2036 1 Dec 2003 2037 1 Dec 2003 2038 1 Dec 2003 2039 1 Dec 2003 2040 1 Dec 2003 2041 1 Dec 2003 2042 1 Dec 2003 2043 1 Dec 2003 2044 1 Dec 2003 2045 1 Dec 20...

Page 13: ...2086 1 Dec 2003 F 2087 2088 1 Dec 2003 F 2089 2090 1 Dec 2003 F 2091 2092 1 Dec 2003 F 2093 2094 1 Dec 2003 2095 1 Dec 2003 2096 1 Dec 2003 F 2097 2098 1 Dec 2003 F 2099 2100 1 Dec 2003 F 2101 2102 1 Dec 2003 F 2103 2104 1 Dec 2003 2105 1 Dec 2003 2106 1 Dec 2003 2107 1 Dec 2003 2108 1 Dec 2003 2109 1 Dec 2003 2110 1 Dec 2003 2111 1 Dec 2003 2112 1 Dec 2003 2113 1 Dec 2003 2114 1 Dec 2003 2115 1 D...

Page 14: ...CE MANUAL CAS 100 COLLISION AVOIDANCE SYSTEM LEP 6 1 Dec 2003 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document 34 45 47 THIS PAGE LEFT BLANK ...

Page 15: ... 5 D Weights and Measurements INTRO 5 E Acronyms and Abbreviations INTRO 6 DESCRIPTION AND OPERATION 1 1 General 1 A Purpose of Equipment 1 B Equipment Part Numbers 3 C TCAS Accessories 14 D Aircraft Equipment Required But Not Supplied By Honeywell 15 E Aircraft Optional Non Essential Equipment 17 F Related Publications 18 2 System Configurations 18 A System 18 B TPA 100A TCAS Processor 19 3 Syste...

Page 16: ...ination Function 39 8 Data Recording Function 39 9 Data Loader Function 39 5 System Component Description and Functions 39 A TCAS Processor 39 1 General 39 2 TCAS Processor Description and Basic Functions 39 3 Real Time TCAS Functions Controlled by Processor 44 4 Power Requirements 50 5 Rear Connector 51 6 Leading Particulars 51 B Directional Antenna 51 1 General 51 2 TCAS Directional Antenna Desc...

Page 17: ...it 82 E TA VSI 104 1 Resolution Advisories 104 2 Traffic Display 104 F RA VSI 107 G Dedicated TCAS Traffic Display 107 H PPI Radar TCAS Display 109 I Optional Aural Lamp Advisory Outputs 109 J Audio Message Alerts 109 K TCAS Processor and Mode S Transponder Front Panel Indicators and TEST Switch 109 L Optional Advisory Cancel Switch 109 M Range Selection and Range Rings 110 TESTING AND FAULT ISOLA...

Page 18: ...lanning 2002 A General 2002 B Location of Equipment 2002 1 TCAS Processor Location 2002 2 TCAS Antenna Location 2002 3 Display Units TA VSI RA VSI and Dedicated Display 2003 C Interwiring and Cable Fabrication 2003 1 General 2003 2 Interface Capability and Requirements 2004 3 Primary Power and Circuit Breaker Requirements 2004 4 Suppression Pulse Requirements and Wiring 2004 5 Antenna Cable Type S...

Page 19: ...Component Installation 2035 7 Inspection System Checkout and Flight Test Procedures 2036 A Inspection 2036 1 Individual Unit Inspection 2036 B System Checkout 2037 1 General 2037 2 System Interwiring Check 2037 3 Visual Inspection 2038 4 Post Installation Test Using Self Test Function 2038 5 Ramp Test Optional 2040 6 Antenna Test 2051 7 ARINC 429 Installation Checkout Data Words 2051 C Flight Test...

Page 20: ... document 34 45 47 E TRA 67 ATC Mode S Transponder System Component 2055 1 Removal and Reinstall 2055 F Omni Antenna 2055 1 Removal and Reinstall 2055 9 Maintenance Procedures 2056 A In Aircraft Adjustments 2056 B System Protection 2056 C Lubrication 2056 D Cleaning 2056 10 Aircraft Maintenance Programs 2057 A General 2057 B Honeywell TCAS Maintenance Recommendations 2057 Subject Page ...

Page 21: ...ck Diagram 77 Figure 10 CTA 81A Control Unit Typical 83 Figure 11 CTA 81B Control Unit Typical 90 Figure 12 CTA 100A Controllers 98 Figure 13 TA VSI Controls and Indicators 105 Figure 14 RA VSI Controls and Indicators 108 Figure 15 ITA 81A Traffic Display Controls and Indicators 111 Figure 16 PPI Radar TCAS Display Controls and Indicators 113 Figure 1001 Test Pattern 1003 Figure 1002 TCAS Processo...

Page 22: ...Connector 2026 Figure 2005 Adapter and Moldable Shim Assembled on the Airframe 2034 Figure 2006 TPA 100A TCAS Processor Outline Drawing 2059 Figure 2007 ANT 81A Directional Antenna Four Element Array Curved Base Outline Drawing 2063 Figure 2008 ANT 81A Directional Antenna Four Element Array Flat Base Four Mounting Screws Outline Drawing 2065 Figure 2009 ANT 81A Directional Antenna Four Element Arr...

Page 23: ...60D Environmental Certification Categories 36 Table 15 TPA 100A TCAS Processor Inputs and Outputs 67 Table 16 IVA 81A D TA VSI and IVA 81B RA VSI Inputs and Outputs 79 Table 17 ITA 81A Traffic Display Inputs and Outputs 81 Table 18 CTA 81A Control Unit Controls and Indicators 84 Table 19 CTA 81B Control Unit Controls and Indicators 91 Table 20 CTA 100A Control Unit Controls and Indicators 99 Table...

Page 24: ... 81A Configuration Matrix Software Version 01 and 03 2111 Table 2009 IVA 81A Configuration Matrix Software Version 02 2113 Table 2010 IVA 81A Configuration Matrix Software Version 04 2115 Table 2011 IVA 81A Configuration Matrix Software Version 05 2117 Table 2012 IVA 81A Configuration Matrix Software Version 06 2119 Table 2013 IVA 81D Configuration Matrix Software Version 02 and 04 2121 Table 2014...

Page 25: ...ntains unrestricted technical data and is being exported under license exception TSUOTS in accordance with EAR Section 740 13 a 2 These commodities technology or software were exported from the United States in accordance with the export administration regulation Diversion contrary to U S law is prohibited ECCN 7E994 Schedule B 4901 99 0050 C Special Precautions 1 Warnings cautions and notes in th...

Page 26: ...efer to the table of contents to see which subheadings are included in this manual The table of contents identifies those subheadings that are not applicable or require no special instructions 3 We recommend that the tests in TESTING AND FAULT ISOLATION be done before the unit is disassembled These tests can tell the condition of the CAS 100 or most probable cause of any malfunction Should any mal...

Page 27: ...Component Maintenance Manual I B 1181E 34 45 25 CTA 81B Control Unit Part No 071 01480 XXXX 071 01492 XXXX Component Maintenance Manual I B 1181F 34 45 11 ITA 81A Traffic Display Part No 066 50003 XXXX Component Maintenance Manual I B 1181G 34 45 30 CTA 81C Control Unit Part No 071 01515 XXXX Component Maintenance Manual I B 1181J 34 45 12 TRA 67 Mode S Transponder System Maintenance Manual I B 11...

Page 28: ...cation for this manual is shown in the list that follows PUBLICATION PUBLICATION No ATA No Standard Repair Procedures for Honeywell Avionics Equipment Instruction Manual A09 1100 004 Abbreviations for Use on Drawings and in Text ASME Y14 38 1999 Formerly ASME Y1 1 1989 Graphic Symbols for Electrical and Electronics Diagrams ANSI Y32 2 1974 Standard Letter Symbols for Units of Measurement ANSI IEEE...

Page 29: ...of this document 34 45 47 C Symbols 1 The symbols in Figure Intro 1 may be used to identify static sensitive ESDS and moisture sensitive devices Figure Intro 1 Symbols D Weights and Measurements 1 All weights and measurements are in U S values and S I metric values 2 The letter symbols for units of measurement are the same as shown in the GPO Style Manual and in ANSI IEEE Std 260 ...

Page 30: ...ines Electronic Engineering Committee AGL above ground level AHRS attitude heading reference system ANSI American National Standards Institute ARINC Aeronautical Radio Incorporated ASME American Society of Mechanical Engineers ATC Air Traffic Control ATCRBS Air Traffic Control Radar Beacon System ATE automatic test equipment BITE built in test equipment CAS Collision Avoidance System CFDS centrali...

Page 31: ... LED light emitting diode LMP left middle plug LRU line replaceable unit LTP left top plug MSL mean sea level MTL minimum trigger level NAR non altitude reporting NM nautical mile No number PC personal computer PPI plane position indicator RA resolution advisory RBP right bottom plug RF radio frequency RMP right middle plug RTCA Radio Technical Commission for Aeronautics RTP right top plug S I Int...

Page 32: ...re of information on this page is subject to the restrictions in the proprietary notice of this document 34 45 47 TCAS Traffic Alert and Collision Avoidance System TNC threaded N connector TSO Technical Standing Order VSI vertical speed indicator VSWR voltage standing wave ratio Term Definition ...

Page 33: ...ION AVOIDANCE SYSTEM 012 0680 001 Page 0 1 Dec 2003 34 45 47 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document CAS 100 Collision Avoidance System Components Figure 1 ...

Page 34: ...L CAS 100 COLLISION AVOIDANCE SYSTEM 012 0680 001 Page 00 1 Dec 2003 34 45 47 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document THIS PAGE LEFT BLANK ...

Page 35: ...that report altitude data in their transponder messages Traffic advisories are given for nonaltitude reporting NAR aircraft only A traffic advisory display warns the flight crew to the position of nearby aircraft threats and possible threats This warning improves the ability of the flight crew to see the intruder aircraft before answering the resolution advisory The resolution advisories are shown...

Page 36: ...dvisory display The symbol position on the display shows relative range and bearing of the intruder The symbol shape and color identifies if the aircraft is categorized as a nonthreat proximity traffic advisory or resolution advisory threat If the intruder is reporting altitude intruder relative altitude is shown on the display NOTE TCAS only categorizes and displays an intruder aircraft as an RA ...

Page 37: ...e in Mode A However an aircraft equipped with a minimal transponder that replies to Mode A interrogations will reply to Mode C interrogations with no altitude encoded data present in the reply TCAS tracks such aircraft in bearing and range and will display the aircraft a nonthreat intruder proximity intruder or traffic advisory However a resolution advisory will not be generated since the correcti...

Page 38: ...S transponder and its control units directional antenna TA VSI RA VSI and dedicated TCAS traffic display are examined in detail in separate manuals recorded in Table Intro 1 Table 1 TCAS System Components Honeywell Supplied Equipment Type Honeywell Part Number Description TCAS Processor TPA 100A 940 0300 001 940 0400 001 The TCAS processor is a tray mounted ARINC 735A assembly The processor contai...

Page 39: ...raps discrete advisory inhibit inputs from ground proximity and wind shear warning systems discrete input from an advisory cancel switch The TCAS processor outputs a suppression pulse to on board L band rf equipment and receives suppression pulses from the same L band equipment Voice audio advisory outputs are provided to a cockpit speaker and headphones and discrete advisory alert outputs are pro...

Page 40: ...iquid crystal display LCD has two controls to give the maintenance personnel the ability to check the equipment The processor contains a front panel Personal Computer PC card slot where internal signal data can be recorded on a PC card or data from the PC card can be loaded into the processor The TCAS processor receives 115 V 360 to 800 Hz or 28 V dc primary power and 26 V ac synchro reference pow...

Page 41: ...een the TCAS processor and directional antenna The ANT 81A is a passive device and does not require input power TCAS Omni Antenna One TCAS Omnidirectional Antenna NOTE 2 Customer Supplied The antenna is installed directly to bottom of the aircraft The antenna is an L band blade type dipole antenna The antenna connects to the TCAS processor through an rf cable The antenna must have a dc ground for ...

Page 42: ...mode data on a high speed ARINC 429 bus through the TPA 100A TCAS processor RA command data is shown around the edge of the vertical speed scale Built in test continuously monitors for a loss of primary power internal IVA 81A D failures altitude rate input failures and gives a discrete display valid status signal to the TCAS processor The strap inputs are supplied to set the vertical speed input s...

Page 43: ...sories RAs with curved lamp segments around the edge of the vertical speed scale does not give a display of adjacent intruder traffic The vertical speed display operates from pneumatic or air data electrical input The display receives RA and TCAS mode data on a high speed ARINC 429 bus from the TPA 100A TCAS processor Built in test continuously monitors for missing primary power internal IVA 81B f...

Page 44: ...t power sources TRA 67 Transponder Subsystem TRA 67A Mode S Transponder NOTE 5 066 01127 The TRA 67A transponder is a tray attached ARINC 718A assembly The transponder contains a microprocessor based Mode S ATCRBS transponder control and processing unit The unit also contains an L band rf transmitter receiver and various synchro discrete and digital interface networks A Mode S transponder transmit...

Page 45: ...processor with a two direction ARINC 429 data link Many data link communications between the TCAS processor and Mode S transponder are continuously interchanged The CTA 81 Control Unit gives on board control for manually selecting Mode S transponder and TCAS operating modes Mode control data from the control unit is connected into the Mode S transponder and moved to the TCAS processor through ARIN...

Page 46: ...or through the ARINC 429 data link that a broadcast message was received The ARINC 429 data link is also used to move the maximum airspeed pressure altitude aircraft address identification and TCAS coordination message data from the transponder to the TCAS processor The TCAS processor also moves housekeeping and coordination update data to the transponder Built in test equipment software continuou...

Page 47: ...unit also contains a transponder failure indicator and ATC IDENT code display The Mode S transponder TCAS control unit moves the control data and failure status data to the Mode S transponder The control unit FAIL annunciator receives the failure status from the Mode S transponder through a discrete monitor signal line The Mode S transponder TCAS control unit receives 115 V 400 Hz and lighting pow...

Page 48: ...ed if pointer traffic resolution displays are given on another display unit i e PPI or TCAS dedicated traffic display unit and user does not require RA and TA displays on the same unit 5 The fundamentals of TRA 67 Mode S Transponder System operation in the CAS 100 system are shown in this manual For more Mode S transponder and Mode S transponder control unit details refer to TRA 67 ATC Mode S Tran...

Page 49: ...tude pitch and roll and heading gyros 5 V ac or dc or 28 V dc Lighting Bus Panel lighting power source for TA VSI RA VSI and dedicated TCAS traffic display 5 V ac or 28 V dc Power Source separate Fault lamp power for Mode S transponder TCAS control unit ARINC 429 Attitude Heading Reference System digital Supplies the aircraft pitch roll and heading on an ARINC 429 digital input to the TCAS process...

Page 50: ...ipment on the aircraft including the TCAS processor bi directional bus Static Input Source pneumatic Supplies the aircraft static pressure source input to the TA VSI or RA VSI OR Altitude Rate Source electrical Supplies the aircraft altitude rate on an electrical ARINC 429 ARINC 565 or ARINC 575 input to the TA VSI or RA VSI Pressure Altimeter Source Supplies the aircraft pressure altitude input t...

Page 51: ...CAS Processor Advisory Cancel Switch Lets flight crew to cancel verbal advisory alerts on the cockpit speaker cockpit headphones tone generators and alert lamps PPI Modified to Provide TCAS Traffic Displays NOTE Supplies isolated or total displays of weather map data and TCAS traffic data The display modes are selectable from the changed PPI control panel ARINC 429 Digital or ARINC 573 Non Digital...

Page 52: ... Related Publications Table Intro 1 Optional Aircraft Equipment Description Performance Management Computer Supplies the aircraft climb rate performance limit discrete input to the TPA 100A TCAS Processor Wind Shear System and or Ground Proximity System Supplies the TCAS advisory inhibit discrete input to the TPA 100A TCAS Processor during wind shear or ground proximity alarm conditions ARINC 615 ...

Page 53: ...rcraft with Mode S or ATCRBS transponders that are tracked by own aircraft TCAS 1 Range Tracking Volumes The shape and size of the range tracking volume depends on If Mode S or ATCRBS transponders are being interrogated If tracking is occurring on a directional or OMNI antenna The attenuation levels applied to the transmitted pulses from the TCAS processor s transmitter NOTE The TCAS processor dec...

Page 54: ...Modes TCAS logic separates the adjacent airspace into the altitude layers as shown in Figure 2 A different sensitivity limit level for issuing RAs and TAs is applied to each altitude layer Lower altitudes have less sensitive RA and TA limit levels to prevent unwanted advisories in the higher traffic densities anticipated at lower flight levels i e terminal areas The following TCAS sensitivity leve...

Page 55: ...47 MAINTENANCE MANUAL CAS 100 COLLISION AVOIDANCE SYSTEM Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document CAS 100 Sensitivity Level Altitude Layers Figure 2 ...

Page 56: ...functions Sensitivity Level 1 TCAS stops all surveillance tracking and resolution advisory functions in sensitivity level 1 The traffic advisory display is blanked but for a STANDBY mode annunciation The conditions for sensitivity level 1 are any one of the following 1 CTA 100A or KFS 578A Control Unit function switch is set to TEST STBY ALT OFF or ALT ON 2 CTA 100A Control Unit function switch is...

Page 57: ...ls NOTE The conditions for sensitivity level 3 through 7 are from own aircraft altitude as follows 1 Sensitivity level 3 Own aircraft altitude is between 1 000 and 2 350 feet AGL radio altitude 2 Sensitivity level 4 Own aircraft altitude is between 2 350 feet AGL and 5 000 feet mean sea level MSL pressure altitude 3 Sensitivity level 5 Own aircraft altitude is not higher than 10 000 feet MSL 4 Sen...

Page 58: ...100 COLLISION AVOIDANCE SYSTEM Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document Typical Resolution Advisory and Traffic Advisory Volumes for Sensitivity Levels Figure 3 Sheet 1 of 2 ...

Page 59: ...minimum TA Protection Volume These two conditions cause Resolution Advisories RAs to be issued 1 TCAS calculates that at the current closure rate and distance the time separating own aircraft and intruder aircraft is less than RA Alarm Time AND the altitude difference between own aircraft and intruder aircraft is less than the RA Relative Altitude Threshold 2 The separation in slant range between ...

Page 60: ...onents are given in TRA 67 Mode S ATC Transponder System Maintenance Manual I B 1167 Table 8 TPA 100A TCAS Processor Leading Particulars Characteristic Description TSO C 119b Form Factor 4 or 6 MCU ARINC Specification 600 Weight Approximate 14 lb 6 3 kg Overall Dimensions See Outline Drawing Figure 2006 in the MAINTENANCE PRACTICES section of this manual Power Requirements 115 V 400 Hz 110 watts a...

Page 61: ... being interrogated tracking is occurring on a directional or omni antenna attenuation levels applied to the transmitted pulses from the TCAS processor transmitter NOTE Altitude Tracking Volumes TCAS II tracks other transponder equipped aircraft that are in a relative range of 10 000 feet Surveillance Capacity Minimum of 60 tracks The 30 closest intruders go to Collision Avoidance Algorithms Proce...

Page 62: ...all Dimensions See Outline Drawings Figures 2007 thru 2009 Antenna Mounting Footprint See Figure 2010 Antenna Mounting Mounts directly to aircraft using mounting screws defined in Figures 2007 thru 2009 An antenna adapter Figure 2010 is available for mounting flat base antenna on a curved surface Exterior Material High strength composite Number of Antenna Array Elements Four Polarization Vertical ...

Page 63: ...itions 360 Beam Null Compared to Main Beam at each elevation from 15 to 20 9 dB Input Port VSWR 1 5 1 maximum Antenna Cable Loss Requirement 2 5 0 5 dB at 1030 MHz for each coaxial cable including connectors Antenna Cable Differential Phase Delay One half wavelength maximum approximately 5 inches Maximum Peak Input Power 1000W pulsed Maximum Average Input Power 10W continuous ARINC Characteristic ...

Page 64: ...e power if altitude rate source input is ARINC 575 analog 26 V ac reference power if altitude rate source input is ARINC 565 analog 5 V ac or dc or 28 V dc lighting power Operating Temperature Range 15C to 70C Number of Intruder Aircraft Displayed Determined by TCAS processor TA RA display symbols maximum program strap configuration Display High resolution full color dot matrix LCD Combination ver...

Page 65: ...ctions in the proprietary notice of this document Table 10 IVA 81A TA VSI Leading Particulars cont Characteristic Description Pneumatic Connector located on indicator rear panel See Outline Drawing Figure 2011 Electrical Connector located on indicator rear panel See Outline Drawing Figure 2011 TSO C119a C8c Environmental Certification Refer to Table 14 ...

Page 66: ... primary power 12 V dc reference power if altitude rate source input is ARINC 575 analog 26 V ac reference power if altitude rate source is ARINC 565 analog 5 V ac or dc lighting power Operating Temperature Range 15C to 70C Display Lamps around the periphery of a fixed vertical speed scale and electro mechanical needle Combination vertical speed and RA display Vertical Speed Input The IVA 81B meet...

Page 67: ... V 400 Hz or 28 V dc primary power Maximum power dissipation of 40 Watts short term at cold temperature at full brightness including display warm up at low temperature Lighting 5 V ac or dc or 28 V dc Reference 12 V dc if altitude rate source input is ARINC 575 analog 26 V ac if altitude rate source is ARINC 565 analog Operating Temperature Range 20C to 70C Number of Intruder Aircraft Displayed Ma...

Page 68: ...1D TA VSI Leading Particulars cont Characteristic Description Data Input High speed ARINC 429 Front mounted Range Control Optional Front mounted TA SEL Switch and BRT Con trol Optional Pneumatic Connector located on indicator rear panel See Outline Drawing Figure 2013 Electrical Connector located on indicator rear panel See Outline Drawing Figure 2013 TSO C118 C119b C8d Environmental Certification...

Page 69: ...imensions See Outline Drawing Figure 2014 Mounting Dzus Mounting Power Input Requirements 115 V 400 Hz 35 W nominal Operating Temperature Range 15C to 55C Cooling Convection forced air cooling not required Type of Display Rectangular CRT X Y scan Scan Rate 65 Hz Inputs from TCAS High speed ARINC 429 Display Enable grounded input enables unit s power supply Output to TCAS Display Valid ground valid...

Page 70: ...al Certification Categories Certification Category A2F2Y B B B H2U E X X X X X Z BZ A Z C WWW M A3C3 X A A Category Interpretation DO 160D Section Number Category Description 4 A2F2Y Temperature and Altitude Y 300 Min without forced air cooling 5 B Temperature Variation 6 B Humidity 7 B Shock 8 H2 Vibration 9 E Explosion Proofness 10 X Waterproofness X Not Applicable 11 X Fluids Susceptibility 12 ...

Page 71: ...anual Other TCAS equipment is examined to a level necessary for understanding total TCAS operation Mode S Transponder System components are included in separate manuals recorded in Table Intro 1 B CAS 100 Functional Overview The basic CAS 100 system does traffic alert and collision avoidance functions to give safe separation between own aircraft and other aircraft equipped with Mode S transponders...

Page 72: ...mines the threat potential of intruder aircraft based on results using tracking data Categorizes intruders as RAs TAs proximities or nonthreats 4 Collision Avoidance Computation and Resolution Advisory Display Function When an RA threat aircraft is present TCAS finds the applicable vertical maneuvering for own aircraft to get or keep a safe miss distance between own aircraft and intruder aircraft ...

Page 73: ...eral The TPA 100A TCAS processor is the primary control unit in the CAS 100 system The processor has a combined computerized control system and L band receiver transmitter The operation of the TCAS system is controlled by TCAS software in the computer control memory 2 TCAS Processor Description and Basic Functions See Figure 4 The TCAS processor routinely reads and keeps the following own aircraft...

Page 74: ...ons The performance limit inputs include 1 Performance limit discrete input or ARINC 429 input from performance management computer 2 Five discrete altitude limit program strap inputs 2000 4000 8000 16000 and 32000 3 Four discrete 1500 fpm Climb Inhibit inputs which are configured by the user to limit the RAs to performance functions of the aircraft Example Wing flap retracted extended switch can ...

Page 75: ...SION AVOIDANCE SYSTEM 1 Dec 2003 34 45 47 Collision Avoidance System Simplified Block Diagram Figure 4 Page 41 42 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document ...

Page 76: ...is found on any of the following input TCAS supplies the failure annunciation data to the resolution advisory and traffic displays 1 Discrete failure status input from the TA VSI units RA VSI units or other optional display units NOTE In the event of a display unit failure the display sets its display valid output discrete to invalid and tries to show status of the fault found The fault is shown i...

Page 77: ...processor formats and transmits the messages and listens for broadcasts Messages are transmitted at 1030 MHz by each TCAS system to tell other TCAS equipped aircraft that own TCAS equipped aircraft is present The messages are transmitted on the TCAS directional and omni antennas Each TCAS including own TCAS keeps track of the number of broadcast messages received by its Mode S transponder This sup...

Page 78: ...n ATCRBS equipped aircraft is in TCAS ATCRBS tracking range and altitude ATCRBS search track initialization and track update operations include the TCAS processor formatting and then transmitting 1030 MHz ATCRBS interrogations and receiving 1090 MHz ATCRBS replies on the directional antenna and or the omni antenna The TCAS processor sets one directional antenna beam to use for ATCRBS directional m...

Page 79: ...MAINTENANCE MANUAL CAS 100 COLLISION AVOIDANCE SYSTEM Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document ATCRBS Mode C and Mode S Interrogation Formats Figure 5 ...

Page 80: ...MAINTENANCE MANUAL CAS 100 COLLISION AVOIDANCE SYSTEM Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document ATCRBS Mode S Transponder Reply Message Formats Figure 6 ...

Page 81: ...rocessor establishes a coordination data link with the threat category aircraft that are also TCAS equipped The TCAS processor transmits coordination messages and receives coordination messages from the threat aircraft transponders through own TCAS antennas Once the TCAS equipped threat aircraft has sensed own aircraft as a threat the same procedure is started through own Mode S transponder A full...

Page 82: ...ircraft position 0 6 own surface position and 0 9 own velocity o When the ADS B program pin is strapped the TPA 100A will 1 Output on both high speed display output busses 2 Request own aircraft position and velocity data from own transponder p The following is a brief summary about the Display Traffic Information File DTIF 1 The TPA 100A implements the definition of ARINC 735A supplement 1 Attach...

Page 83: ...of the TCAS processor are calibrated automatically during power up initiated functional test and periodically The calibration adjusts for phase shifts added by the cables relative phase error in the receiver circuitry and temperature effects t TCAS processors contain an Antenna System Built In Test Equipment BITE test that operates when power is applied to the TCAS processor The first function of ...

Page 84: ...s on one of four antenna beams By selecting the beam the TCAS processor electronically points the antenna in a surveillance direction during TCAS transmit and receive operations 2 TCAS Directional Antenna Description and Basic Functions The directional antenna is an electronically steerable phased array that has four top loaded monopole elements Different from mechanically steered antennas the ant...

Page 85: ... main beam to be transmitted one of four beams The resultant 1030 MHz signals radiated from the four elements of the antenna mix and cancel in a procedure that makes a main beam directional pattern for pulses transmitted In a TCAS ATCRBS interrogation transmission the TCAS message is transmitted from the directional main beam with the exception of the ATCRBS suppression pulse P2 which is designed ...

Page 86: ...the rf energy is received These signals are received on the same four cables that connect transmit signals between the TCAS processor and directional antenna Many filters are used in the TCAS processor for noise suppression and pulse shaping of the received signals Phase detectors in the TCAS processor then examine the relative phasing of the four signals from the antenna and make an analog voltag...

Page 87: ...nput validity The display intensity level is controlled by a group of bezel and remote light sensors and by the lighting bus input An optional bezel attached intensity control is also available Traffic display range control can be supplied at a distance from a Control Unit or locally through an optional bezel attached range control An optional traffic select TA SEL switch lets deselection of traff...

Page 88: ...ditions resolution advisory conditions and show the TCAS operational modes and failure conditions The selected traffic display functions as a self sufficient auxiliary device controlled by the TPA 100A TCAS processor through one high speed ARINC 429 data bus The traffic displays are secondary displays in the total CAS 100 system Resolution advisories on the TA VSI and RA VSI are the primary TCAS d...

Page 89: ...des LEDs An electro mechanical TCAS flag To show normal and fail conditions and RA mode OFF conditions Vertical speed failure flag The resolution advisory LEDs are installed below a coated surface which makes them not seen when unlighted The VSI face is matte black with a matte white vertical speed scale The vertical speed pointer is controlled by a two phase motor The position is controlled by th...

Page 90: ...plays the pilot can monitor traffic while avoiding weather The PPI receives traffic display data from the TCAS processor through a high speed ARINC 429 data bus The PPI does not show resolution advisories G Mode S Transponder The Mode S Transponder does the following functions in the CAS 100 system Automatically transmits 1090 MHz Mode S squitter messages each second These squitter messages tell o...

Page 91: ...el and TCAS coordination update data from the TCAS processor through the ARINC 429 data link and inserts this data into 1090 MHz coordination messages H CTA 100 Control Unit The CTA 100 Control Units are examined in this manual to a depth necessary to know total TCAS operation For more data refer to TRA 67 Mode S Transponder System Maintenance Manual I B 1167 The microprocessor based CTA 100 Contr...

Page 92: ...100 operation that includes 1 Complete Block Diagrams and Description of Input Output Signals 2 TCAS Failure Monitoring NOTE All data in this manual is superseded by the latest engineering software and hardware documentation B Detailed Block Diagrams and Description of Input Output Signals The Figure 8 is a block diagram of the CAS 100 system unit connects to the TPA 100A TCAS Processor The Table ...

Page 93: ...ormation on this page is subject to the restrictions in the proprietary notice of this document Refer to Table 15 for the TPA 100A TCAS Processor input and output The IVA 81A D TA VSI and IVA 81B RA VSI input and output are shown in Table 16 Table 17 shows the input and output of the ITA 81A Traffic Display ...

Page 94: ...AVOIDANCE SYSTEM 34 45 47 TCAS Processor System Interconnect Block Diagram Figure 8 Sheet 1 of 3 Page 61 62 1 Dec 2003 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document ...

Page 95: ...AVOIDANCE SYSTEM 34 45 47 TCAS Processor System Interconnect Block Diagram Figure 8 Sheet 2 of 3 Page 63 64 1 Dec 2003 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document ...

Page 96: ...AVOIDANCE SYSTEM 34 45 47 TCAS Processor System Interconnect Block Diagram Figure 8 Sheet 3 of 3 Page 65 66 1 Dec 2003 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document ...

Page 97: ...t messages from TCAS processor to omni antenna and 1090 MHz received messages from the omni antenna to TCAS processor Three Strapped Pins on Processor Rear Connector Antenna Delay Straps Three discretes Supply calibration data base inputs to TCAS processor to adjust for the difference in the cable lengths between top and bottom antenna MODE S TRANSPONDER RELATED I O Mode S Transponder No 1 and No ...

Page 98: ...te Heading Valid Synchro heading system failure status to TCAS processor 26 V ac Reference Input Heading synchro reference voltage to TCAS processor Pitch and Roll Gyros Pitch Synchro X Y Z Own synchro pitch attitude data to TCAS processor from pitch gyro Discrete Pitch Roll Valid Own pitch gyro and roll gyro failure status to TCAS processor Roll Synchro X Y Z Own synchro roll attitude data to TCA...

Page 99: ...gital radio altimeter No 1 to TCAS processor ARINC 429 Digital Radio Altimeter No 2 ARINC 429 Digital Radio Altitude No 2 ARINC 429 data from digital radio altimeter No 2 to TCAS processor Three Strapped Pins on Processor Rear Connector Three discretes from Analog Radio Altimeter Select Straps Specify the type of analog radio altimeter that is connected to the Analog Radio Altitude No 1 and No 2 i...

Page 100: ...tended Optional Aircraft Equipment that Monitor the Aircraft Factors Relating to 1500 Feet For Each Minute Climb Rate Performance Climb Inhibit 1 2 3 and 4 Four discrete inputs Tell the TCAS processor that conditions exist to prevent or not prevent an own aircraft climb rate of 1500 feet for each minute Optional Aircraft Equipment that Monitor the Aircraft Factors Relating to 2500 Feet For Each Mi...

Page 101: ...ffic display operating mode and failure status data from TCAS processor to TA VSI No 2 or RA VSI No 2 a PPI or a dedicated display Display Status No 2 Discrete TA VSI No 2 or RA VSI No 2 failure status output to TCAS processor Display Status No 4 Discrete Optional for maintenance reporting Failure status output of PPI or dedicated display connected to TA RA Display No 2 high speed ARINC 429 bus RA...

Page 102: ...ound TCAS goes to STANDBY on the ground One Strapped Pin on Processor Rear Connector RA TA Display Mode Strap Discrete Shows either all traffic or TA RA and near traffic only for example nonthreat traffic not shown Optional Ground Proximity System Ground Proximity GPWS Advisory Delay Discrete Puts TCAS into the TA only mode sensitivity level 2 and prevents all audio and aural advisories Optional W...

Page 103: ...utputs for Corrective RA Tone Preventive RA Tone and TA Tone alerts 1 second ground 20 milliamp maximum Supply TA and RA alert output that start optional tone generators found externally in the aircraft Strapped Pin on Processor Rear Connector Audio tone Enable Program Strap Discrete Input When strapped supplies interval of voice output 1 second to aural advisory output When open drives aural advi...

Page 104: ...ed receive bus Maintenance digital 429 data from maintenance computer or CFDS to TCAS processor and maintenance digital 429 data from TCAS processor to maintenance computer or CFDS Automatic Test Equipment ATE ATE Test Pins Twenty discrete output TCAS processor status output to ATE monitors Not necessary for the aircraft installation Data Loader Data loader high or low speed ARINC 429 transmit bus...

Page 105: ...put pulse suppresses the TCAS receiver An output suppression pulse suppresses other L band equipment in the aircraft POWER RELATED I O Own Aircraft Power Supplies Fan On TCAS Processor Assembly Tray 115 V 400 Hz or 28 V dc and 26 V ac reference power input 115 V 400 Hz output or from 28 V dc source Provide power to the TCAS processor from own aircraft power sources Supplies energizing power from t...

Page 106: ...Dec 2003 34 45 47 MAINTENANCE MANUAL CAS 100 COLLISION AVOIDANCE SYSTEM Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document THIS PAGE LEFT BLANK ...

Page 107: ...AVOIDANCE SYSTEM 34 45 47 IVA 81A D and IVA 81B RA VSI System Interconnect Block Diagram Figure 9 Page 77 78 1 Dec 2003 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document ...

Page 108: ...ssor VERTICAL RATE SOURCE RELATED I O One of the following input can be selected Aircraft Static Pressure Source Static Pressure Source Pneumatic Input Pressure altitude from an aircraft static pressure port Aircraft ARINC 565 ac Analog Rate Source and Reference Voltage Altitude Rate AC Analog with 26 V ac High and Low Reference Analog altitude rate which is converted by the TA VSI or RA VSI into ...

Page 109: ...r than the maximum of 67 milli seconds Vertical Speed Source Vertical Speed Valid Discrete Supplies failure status from set analog vertical rate source unit to the VSI ALTITUDE RATE OUTPUT IVA 81A D or IVA 81B Digital Altitude Rate Output Buffered altitude rate output for use by remote indicators CONFIGURATION AND SOURCE SELECT STRAPPING RELATED I O Nine Configuration Straps and Two Source Select ...

Page 110: ...annunciated When the display is set to TCAS mode the specified LRU failure s is shown BITE monitors the internal operation of the system components and I O data links When a TCAS FAIL condition is found TCAS stops all surveillance and tracking functions NOTE A complete description of BITE monitoring operations and their failure annunciations and indicators is contained in the TESTING AND FAULT ISO...

Page 111: ...ackground panel lighting power are applied to TCAS by closing aircraft circuit breakers TCAS does not contain a power on off switch or fuses C CTA 81 Control Unit See Figures 10 and 11 The CTA 81 Control Unit is the primary control for both TCAS and the transponder The CTA 81A Control Unit is used in the installations containing two TRA 67A Mode S transponders The CTA 81B is used in the installati...

Page 112: ...COLLISION AVOIDANCE SYSTEM Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document CTA 81A Control Unit Typical Figure 10 Refer to Table 18 for the CTA 81A Control Unit controls and indicators ...

Page 113: ... If the TCAS processor Functional Test Inhibit program pin is strapped the TCAS functional test is prevented while the aircraft is airborne The TCAS flag shows TCAS on the RA VSI display during the functional test approximately 12 seconds The traffic display shows TEST A test pattern shown on the traffic display allows verification of each type of intruder symbol During the first three seconds a l...

Page 114: ...ns are made unserviceable The traffic display screen is erased but for a TCAS STBY mode annunciation On the Ground Mode S transponder squitters and replies to Mode S interrogations Depending on Mode S transponder strapping the transponder replies or not to ATCRBS Mode C and Mode A interrogations The transponder reply to ATCRBS and Mode S interrogations does not contain an altitude report The trans...

Page 115: ...or exception TCAS does not categorize or display one aircraft as a RA threat symbol TCAS gives the traffic advisory alerts but does not give resolution advisory alerts for example voice RA alerts or RA indications on the traffic display are not supplied A TA ONLY annunciation comes into the view on the traffic display On the Ground Mode S transponder squitters and replies to Mode S interrogations ...

Page 116: ...e S interrogations Depending on transponder strapping transponder replies fully or does not reply to ATCRBS Mode C and Mode A interrogations or Mode S interrogations TCAS defaults to TA ONLY mode TCAS sensitivity level No 2 and functions as shown for the TA position on the ground of the Function Selector Switch in this table FL Pushbutton Switch Spring loaded pushbutton switch When pushed and rele...

Page 117: ...isplay of nonthreat aircraft maximum 8700 feet above own aircraft and down to 2700 feet below own aircraft ABOVE is annunciated on the traffic display NORM Position Sets display of nonthreat aircraft maximum 2700 feet above own aircraft and down to 2700 feet below own aircraft on the traffic display BELOW Position Sets display of nonthreat aircraft down to 8700 feet below own aircraft and maximum ...

Page 118: ...TA RA mode request from the panel 2 TCAS can be strapped to show all traffic all the time or when a TA or RA is present 3 If own aircraft is below 500 feet AGL TCAS defaults to TA ONLY mode 4 Holding the FL switch pushed for longer than 15 seconds will not show flight level altitudes for longer than 15 seconds 5 The range at which resolution or traffic advisories are generated by TCAS is unaffecte...

Page 119: ... or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document CTA 81B Control Unit Typical Used With One Mode S Transponder and One ATCRBS Transponder Figure 11 Refer to Table 19 for the CTA 81B Control Unit controls and indicators ...

Page 120: ...borne The TCAS flag shows TCAS on the RA VSI display during the functional test approximately 12 seconds The traffic display shows TEST A test pattern shown on the traffic display lets verification of each type of intruder symbol During the first three seconds of the functional test a lamp test is done on all segments of the RA VSI If a failure is found during functional test the TCAS flag continu...

Page 121: ...rrogations contains the ATC transponder code normal Mode A reply All the TCAS broadcast surveillance and tracking functions are made unserviceable The traffic display screen is erased but for a TCAS STBY annunciation On the Ground Power is not applied to ATCRBS transponder The Mode S transponder squitters and replies fully to the Mode S interrogations Depending on the Mode S transponder strapping ...

Page 122: ...esolution advisory alerts for example voice RA alerts or RA indications on the traffic display are not given A TA ONLY mode annunciation comes into view on the traffic display On the Ground Power is not applied to ATCRBS transponder The Mode S transponder squitters and replies fully to the Mode S interrogations Depending on the Mode S transponder strapping the transponder replies fully or does not...

Page 123: ...n advisories on the TA VSI or RA VSI NOTE 4 On the Ground The Mode S transponder squitters and replies fully to Mode S interrogations Depending on the Mode S transponder strapping the transponder replies fully or does not reply to the Mode S ATCRBS Mode C and Mode A interrogations The power is removed from ATCRBS transponder The TCAS defaults to TA ONLY mode TCAS sensitivity level No 2 and functio...

Page 124: ...flight level altitude also comes into view on the traffic display After 15 seconds own aircraft flight level altitude goes out of view from the display and the intruder aircraft altitude annunciations change to relative altitude annunciations NOTE 5 If a new RA or TA category aircraft is detected by the TCAS during the 15 second period the 15 second flight level display is made unserviceable and r...

Page 125: ... 21 Mode S replies to the interrogations from ground stations The SPI is shown for 18 seconds If the switch is held pushed longer than 18 seconds the SPI bit is transmitted while the switch is pushed plus an additional 18 seconds after the switch is released The SPI pulse is not used by the TCAS Code Select Knobs Lets selection of transponder identification code The transponder inserts this code i...

Page 126: ...mode The TCAS functions as shown for the ATC 1 TA position in flight of the Function Selector Switch in this table 5 Holding the FL switch pushed for longer than 15 seconds will not show flight level altitudes for longer than 15 seconds 6 The range at which RAs or TAs are generated by the TCAS is unaffected by the TCAS RANGE switch 7 The presence of the intruder aircraft that are categorized as RA...

Page 127: ...003 34 45 47 MAINTENANCE MANUAL CAS 100 COLLISION AVOIDANCE SYSTEM Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document CTA 100A Controllers Figure 12 ...

Page 128: ...sory or TA RA Traffic Advisory Resolution Advisory modes for the TCAS processor The position of the mode selector switch finds the correct ARINC 429 control data to transmit to the Mode S transponders and the TCAS processor The switch supplies a momentary TEST position which lets the personnel start a TCAS system test NOTE 1 TEST Position The TEST mode is to start the TCAS system test The TEST mod...

Page 129: ...threat symbol The TCAS gives the traffic advisory alerts but does not give resolution advisory alerts for example voice RA alerts or RA indications on the traffic display are not given A TA ONLY annunciation comes into view on the traffic display On the Ground The Mode S transponder squitters and replies fully to Mode S interrogations Depending on transponder strapping transponder replies fully or...

Page 130: ...DENT command and default to the ATC code display mode ATC SELECT Pushbutton The ATC SELECT pushbutton is used to set either Transponder No 1 or Transponder No 2 in the TCAS system Each operation of the ATC SELECT pushbutton alternately sets the Transponder No 1 or Transponder No 2 The indication of the set transponder is given by annunciators indicating either a 1 or 2 The CTA 100A controls the an...

Page 131: ...A will toggle to the subsequent highest range value NOTE 4 FCN Pushbutton The function of the FCN pushbutton is to set the function modes that use the CTA 100A display When the FCN pushbutton is pushed the CTA 100A sets and shows the subsequent available function mode RIGHT Pushbutton The RIGHT pushbutton shows current Flight identification when Flight ID mode is set on the display The pushbutton ...

Page 132: ...me on when the set transponder and related TRANSPONDER FAIL No 1 or No 2 discrete input is in operation The annunciator color will be amber ROTARY CONTROL Knob Rotary control CTA 100A version only The data entry of the ATC code will use the dual concentric rotary control The data is recorded one digit at a time using the outer knob to forward to the subsequent digit An underline is used to identif...

Page 133: ...ied from TCAS The green arc will be immediately adjacent to the red arc and have a width of approximately equal to the space between 1500 ft min and 2000 ft min It is possible to show two red arcs at the same time with an RA for example do not climb more than 1000 feet and do not descend more than 2000 feet Since one procedure can be corrective the green arc will be immediately adjacent to the red...

Page 134: ...4 45 47 MAINTENANCE MANUAL CAS 100 COLLISION AVOIDANCE SYSTEM Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document TA VSI Controls and Indicators Figure 13 ...

Page 135: ...RESTRICTED CLIMBING OR DESCENDING Adjust Vertical Speed Adjust ANY WEAKENING OR SOFTENING OF AN RA Adjust Vertical Speed PREVENTATIVE ADVISORY Monitor Vertical Speed MAINTAIN EXISTING VERTICAL SPEED Maintain Vertical Speed Maintain MAINTAIN EXISTING VERTICAL SPEED WHILE CROSSING THREAT S ALTITUDE Maintain Vertical Speed Crossing Maintain THE FOLLOWING RESOLUTION ADVISORIES REQUIRE 2 5 SECONDS RESP...

Page 136: ...TCAS applications has flags that show the TCAS operating conditions The Honeywell made RA VSI receives resolution advisory and flag control data from the TPA 100A TCAS processor through a high speed ARINC 429 data link RA VSI display units are used as the resolution advisory display when TCAS traffic displays are given on a different display for example a PPI Radar TCAS display or dedicated TCAS t...

Page 137: ...on which is due to a loss of essential aircraft data or TCAS data indicator power OFF TCAS in STBY mode or TCAS in TA mode Also appears when VSI appears NORMAL Black Shows normal operation of TCAS functions TCAS Black TCAS on Amber Shows a loss of or invalid digital TCAS data or SSM set to Failure Warning VS Flag NORMAL Black Shows normal operation of VSI functions VSI Black VSI on Amber Shows a l...

Page 138: ...ntive and traffic advisories given by the TCAS processor The started aural advisory discrete output is given for a 1 0 0 2 second period When the aural advisory discrete output is for an installation the Audio Tone Enable Program pin must be strapped This strap supplies a 1 0 0 2 second interval of the synthesized voice output to be properly phased with the aural advisories The lamp advisory outpu...

Page 139: ...c display The Range rings shown are a function of range set if the range selection is made at a distance or locally Table 22 summarizes range ring distances for each possible range that can be selected on the different types of traffic displays available NOTE The Range selections more than 34 nautical miles are only possible on PPI weather traffic displays For these displays the range ring data in...

Page 140: ...ISION AVOIDANCE SYSTEM 34 45 47 ITA 81A Traffic Display Controls and Indicators Figure 15 Page 111 112 1 Dec 2003 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document ...

Page 141: ...ISION AVOIDANCE SYSTEM 34 45 47 PPI Radar TCAS Display Controls and Indicators Figure 16 Page 113 114 1 Dec 2003 Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document ...

Page 142: ...S Built In Test Equipment that monitors and because of manually started TCAS Functional Self Test monitoring Fault isolation is usually done on the ground as a result of failures shown during post installation preflight testing or malfunctions that were seen during the flight operation 2 Fault Isolation A General The TCAS processor can find the malfunctions of the TCAS components that decrease or ...

Page 143: ...adar TCAS display is used as the traffic display and has a TCAS mode on the selector switch it must be turned to the TCAS position for the test If not the selector switch must turn to the OFF position to let the traffic display set discrete from the TCAS processor and turn the display ON It takes approximately 5 seconds for the display to get warm after the test is started 1 Dual Mode S Equipped A...

Page 144: ... flag to come into the view on the RA VSI If a TA VSI is used the legend VSI comes into the view on the display A TCAS processor failure causes the TCAS flag to come into the view on the RA VSI and the TCAS to come into the view on the TA VSI c For the aircraft that have TA VSI The TA VSI shows a set Resolution Advisory and the traffic symbol test pattern A TEST message is shown d For the aircraft...

Page 145: ...2 XPNDR CONTROL DATA No 1 XPNDR DATA BUS No 1 XPNDR ALT DATA No 2 XPNDR DATA BUS No 2 XPNDR ALT DATA TRAFFIC DISPLAY ATTITUDE RA DISPLAY No 1 RA DISPLAY No 2 HEADING RA DISPLAY No 1 and No 2 NO TCAS NO DATA on some versions TCAS FAIL 4 Test Results Not to Specification If self test results are not to specification do these a If PPI or dedicated display is used check and record the fault annunciati...

Page 146: ...y b On the control unit letter R comes on in the TEST The letter R comes on in the ATC 2 position for the aircraft that have a non Mode S transponder The letter R does not come on during usual Mode S operation in ATC 1 or ATC 2 c The TCAS will not operate when the ATC FAIL lamp comes on The TCAS system must have a serviceable Mode S transponder selected to function correctly CAUTION REMOVE THE POW...

Page 147: ...Coax cable Coax Switches Coax switch circuit defective Transponder antenna No 1 XPNDR ALT DATA No 2 XPNDR ALT DATA XPNDR ALT DATA No 1 and No 2 Check Altitude source Associated wiring SELECTED XPNDR XPNDR CONTROL DATA Check Mode S transponder control unit Denotes loss incorrect data not covered by other fault codes XPNDR TCAS DATA No 1 XPNDR DATA BUS No 2 XPNDR DATA BUS Check Max airspeed program ...

Page 148: ...SSOR UPPER ANTENNA LOWER ANTENNA ATTITUDE HEADING Do the TCAS processor self test paragraph 2 C for specifics TCAS FAIL NO TCAS TRAFFIC DISPLAY PPI or dedicated display failure RA DISPLAY No 1 One RA DISPLAY or RADIO ALT FAULT will not show in a two system display unless other faults are shown RA DISPLAY No 2 RA DISPLAY No 1 and No 2 Check ADCs VSIs wiring power RADIO ALT No 1 and No 2 TD FAIL Che...

Page 149: ...cal Main Menu The first line of each display contains a title and the page number is shown with the number of pages that comprise that display Any line that has an asterisk in the first column shows that the line is selectable The caret shows the location of a selectable item if the Select pushbutton is pushed When an item is chosen a different menu is shown Any line that does not have an asterisk...

Page 150: ...MAINTENANCE MANUAL CAS 100 COLLISION AVOIDANCE SYSTEM Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document TCAS Processor Front Panel LCD and Pushbuttons Figure 1002 ...

Page 151: ...ay lists the text of all the unit faults that have occurred Refer to Table 1003 for a list of possible unit faults 3 System OK Failed Display Screen When SYSTEM FAILED is the active selectable item the system faults are active and the input faults can be active at the same time When the Select button is pushed the text for all active system and input faults are shown The display title will be INPU...

Page 152: ...U MCE PCI 429 Fault CPU3 DM CPU MCE PCI Unknown Fault CPU4 DM CPU Processor Transaction Fault CPU5 DM CPU Memory Refresh Overflow Fault CPU6 DM CPU Memory Select Fault CPU7 DM CPU ECC Multi bit Fault CPU8 DM CPU Processor Unknown Fault CPU9 SW Execution Error SWn where n A to Z and identifies task DM BIT ADC Fault BADC DM ref 2 5 VREF Synthesizer Initialization SYN1 DM SDRAM Data RAMD DM SDRAM Pro...

Page 153: ...25 TTM 6 PT6 TTM 3 3 PT3 TTM 6v Bias PT6B DM IO A D Slow Conversion DA1 DM IO A D Invalid Ground DA2 DM IO A D Invalid 2 5 V ref DA3 DM Invalid Voice Program CRC DV2 DM Invalid Voice Program Version DV3 DM Invalid Configuration Data DCFG DM Voice Synthesizer Initialization DV1 DM TA RA 1 Loop Around Missing DL1 DM TA RA 1 Loop Around Bad Data DL2 DM TA RA 2 Loop Around Missing DL3 DM TA RA 2 Loop ...

Page 154: ... 1 Immediate Reg Error DF4 DM 429 TX 2 Immediate Reg Error DF5 DM ATCRBS Loop Around DSP1 DM Mode S Loop Around DSP2 DM SP Reply Data FIFO DSP3 DM SP Reply Bearing FIFO DSP4 DM SP Squitter Data FIFO DSP5 DM SP Squitter Bearing FIFO DSP6 DM SP DPSK Loop Around Fail DSP7 DM SP Mode Decode Mode S DSP8 DM SP Mode Decode Mode C DSPA DM SP Missing EOI DSP9 Bias Ctl Offset Voltage TB00 Bias Ctl Chan 1 Lo...

Page 155: ...003 Unit Internal Faults cont Internal Faults Fault Identification TX Output Power Low Channel 3 T3PW TX Output Power Low Channel 4 T4PW 1030 TX Frequency 1030 TTM Power Leveling TLVL TTM Power Attenuation Monotonicity TATT Cal PS1 Fault TPS1 Cal PS3 Fault TPS3 Cal PS4 Fault TPS4 RX Cal Fault Top 1090 RCT0 RX Cal Fault Bot 1090 RCB0 TX Cal Top Fault TCT TX Cal Bot Fault TCB Top Bottom Antenna Phas...

Page 156: ...nna Element 1 failed Bott Ant E2 2 2 Bottom Antenna Element 2 failed Bott Ant E3 2 3 Bottom Antenna Element 3 failed Bott Ant E4 2 4 Bottom Antenna Element 4 failed Radio Alt 1 3 Radio Altitude 1 for A330 A340 and Boeing Radio Alt 2 4 Radio Altitude 2 for A330 A340 and Boeing Radio Alt 1 3a Radio Altitude 1 for A320 Radio Alt 2 4a Radio Altitude 2 for A320 Transponder 1 5 Mode S Transponder 1 Tran...

Page 157: ...trictions in the proprietary notice of this document Table 1004 System and Input Faults cont Front Panel Text Fault Description FMC 16 FMC for aircraft type not A330 and not A340 FMC 16 1 FMC for A340 and A330 Suppression Line 17 Suppression Line TCAS Unit Failed 18 TCAS Unit Fault Power Interrupt 19 Power Supply Interrupted Program Pin 20 Program Pin ...

Page 158: ...dio Tone Enable Program RBP 7D PP RBP 7E Ground Display Mode RBP 7E PP RBP 7F Display All Traffic Program RBP 7F PP RBP 7G Cable Delay Program Sign RBP 7G PP RBP 7H Cable Delay Program MSB RBP 7H PP RBP 7J Cable Delay Program LSB RBP 7J PP RBP 8F TA RA Display Symbols Max Prgm RBP 8F PP RBP 8G TA RA Display Symbols Max Prgm RBP 8G PP RBP 8H TA RA Display Symbols Max Prgm RBP 8H PP RBP 8J TA RA Dis...

Page 159: ...aret is adjacent to the Start Test selectable item causes the Test In Progress screen to come into the view and the test to start Front Panel Text Fault Description PP RMP 6E Altitude Limit Prgm RMP 6E PP RMP 6F Altitude Limit Prgm RMP 6F PP RMP 6G Altitude Limit Prgm RMP 6G PP RMP 6H Altitude Limit Prgm RMP 6H PP RMP 6J Altitude Limit Prgm RMP 6J PP TARA 3 Intrd TA RA Display Limit Program Pins s...

Page 160: ...iled To push the Select button with the caret at SYSTEM FAILED or UNIT FAILED causes a display screen with the entries that include the applicable found faults When faults are found START TEST is selectable and a retest is possible The selection of GO BACK causes the previous screen with a selectable item to be shown That previous screen is the same as it was when previously visited A GO BACK is p...

Page 161: ...Unit System and Input Faults and Display Status Indication Active Unit Faults Active System Faults Active Input Faults Unit Status System Input Status No No No Unit OK System OK No No Yes Unit OK Inputs Faulted No Yes No Unit OK System Failed No Yes Yes Unit OK System Failed Yes No No Unit Failed System Failed Yes No Yes Unit Failed System Failed Yes Yes No Unit Failed System Failed Yes Yes Yes Un...

Page 162: ...MAINTENANCE MANUAL CAS 100 COLLISION AVOIDANCE SYSTEM Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document Start Test Test Inhibited Sample Flow Diagram Figure 1004 ...

Page 163: ...the Stored Fault Display shows in which leg the stored fault is found The title shows the current leg minus the number of legs to where the fault is kept For example LEG 2 shows the fault is found two legs back from the present leg If the current leg equals the leg with the fault then the title is INBOUND The date and time the first fault of the flight leg occurred is shown in the screen title PHA...

Page 164: ... 45 47 MAINTENANCE MANUAL CAS 100 COLLISION AVOIDANCE SYSTEM Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document Stored Faults LCD Screen Example Figure 1006 ...

Page 165: ...ration Screen to come into the view A representation of a two page Configuration screen is shown in Figure 1007 The screen title is CONFIG The lines two three and four of page 1 2 contain the software part number s To push the Scroll button causes page 2 2 of the CONFIG screen to come into the view The hardware part number and the unit serial number are shown on the screen The Active Selectable It...

Page 166: ...ietary notice of this document 7 Inputs Display Screen To push the Select button when Input is the Active Selectable Item on the Menu Screen causes the Input select screen page 1 3 to come into the view See Figure 1008 Refer to Table 1007 for Program Pin displayed text and fault descriptions a Program Pins Display Screen Typical Input Display Screens Pages 1 3 Figure 1008 ...

Page 167: ...e Airborne Audio Level Program Pins to Program Pin Common RBP7K See NOTE PP RBP 7B Airborne Audio Level 2 PP RBP 7C Airborne Audio Level 3 PP RBP 7D Audio Advisory Discrete Audio Advisory Discrete Program Pins show if there is an interval in the Synthesizer Voice output when an advisory is given O No Delay 1 1 0 2 second delay an audio tone is output prior to the issuance of a voice command PP RBP...

Page 168: ...borne O Functional Test In Air Permitted 1 Functional Test In Air Prevented PP RBP 8F Disp Intruder Limit 16 TA RA Display Intruder Limit Program Pins limit the number of intruders that can be shown all pins maximum traffic can be displayed 31 There are five straps to limit the number of intruders that are shown 0 31 The pins connected to RBP7K are not shown PP RBP 8G Disp Intruder Limit 8 PP RBP ...

Page 169: ... Display Screen Figure 1009 is an example of a Discrete screen The line 1 contains the screen title the line 2 shows the pin number followed by Open or Ground The lines 3 and 4 are reserved for the name of the discrete On the last Discrete page the Active Selectable Item GO BACK is shown Table 1008 lists the discrete pins the text shown and a short description of the discrete Example of Discrete S...

Page 170: ...Inhibit 3 AND Increase Climb Inhibit 4 Cannot climb at 2500 feet for each minute RBP5H Increase Climb Inhibit 4 The low is the in operation condition RMP1J Climb Inhibit 1 TCAS is Climb Inhibited when the logic is as follows Climb Inhibit 1 AND Climb Inhibit 2 OR Climb Inhibit 3 AND Climb Inhibit 4 The low is the in operation condition RMP13G Climb Inhibit 2 RBP5J Climb Inhibit 3 RBP5K Climb Inhib...

Page 171: ...n no longer get a 1500 feet per minute climb When the input is GROUND the performance is not limited When the input is OPEN the climb is limited if the altitude of the aircraft is above the value set by the Altitude Limit Program See below Limit Input RMP6D Relative Altitude Climb Limited Yes Open Below No Yes Open Above Yes No Gnd Below No No Gnd Above No RMP7E TA Display No 1 Status The TA Displ...

Page 172: ...auses the TCAS Data screen 1 8 to be shown The TCAS Data screen shows the validity and the value of input data for the following input used by TCAS Digital Radio Altitude Analog Radio Altitude The priority of Radio Altitude sources is 1 Digital Radio Altitude No 1 3 Analog Radio Altitude No 1 2 Digital Radio Altitude No 2 4 Analog Radio Altitude No 2 Pressure Altitude Roll Pitch Heading Climb Inhi...

Page 173: ...be shown on the line two The line 3 shows the Altitude No 2 data in the same procedure that line 2 shows the Altitude No 1 data Digital Radio Altitude Display Screen Example Figure 1010 2 Analog Radio Altitude The Figure 1011 shows an example of an Analog Radio Altitude screen The line two shows that analog radio altitude No 1 data is incorrect If the analog altitude No 1 data were correct then th...

Page 174: ...is example the data source is correct altitude 2400 ft and the plus sign shows that the XPDR No 1 is the active source If that data were correct then line two can show INVALID The line three indications are almost the same except that they are for XPDR No 2 Pressure Altitude Display Screen Example Figure 1012 4 Roll An example of a Roll display is shown in Figure 1013 The line two shows the data f...

Page 175: ...ynchro In this case the data is correct Pitch Display Screen Example Figure 1014 6 Heading There are two types of heading data one is ARINC 429 and the other is synchro There are two types of ARINC 429 heading data true and magnetic An example of a Heading display is shown in Figure 1015 The second line shows the true heading data from ARINC 429 label 314 The indicated that data source is the acti...

Page 176: ...f climb is inhibited or not yes or no The line three shows if increased climb is inhibited yes or no Climb Inhibit Display Screen Example Figure 1016 8 Air Ground and Landing Gear An example of an Air Ground and Landing Gear display screen is shown in Figure 1017 The second line shows if Air Ground Input Discretes show Ground Air or invalid The line three shows if Landing Gear Discrete Input shows...

Page 177: ...ination No 1 pins RMP 14F and RMP 14G ARINC 429 data bus labels 275 and 276 If the data words are not received no address will be shown and that area of the screen will stay blank Typical Mode S Transponder Display Screen Figure 1018 e Continuous Wave Interference To push the Select button when the Continuous Wave CW Interference is the Active Selectable Item on the Input Screen causes the CW Inte...

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