Rockwell Collins 8222132 Rockwell Collins TSS-4100 Integrated Surveillance System User Manual Manual 2

Rockwell Collins Inc Rockwell Collins TSS-4100 Integrated Surveillance System Manual 2

Contents

Manual 2

installationmanualTSS-4100 Integrated TCAS,Transponder, and ADS-B TrafficSurveillance SystemExport Control Classification Notice (ECCN) for this document is 6E991.©Copyright 2009 Rockwell Collins, Inc. All rights reserved.
TSS-4100 Integrated TCAS,Transponder, and ADS-B TrafficSurveillance Systeminstallation manualPrinted in the United States of America Rockwell Collins, Inc.© Copyright 2009 Rockwell Collins, Inc. All Rights Reserved. Cedar Rapids, Iowa 52498(_TSS-4100_IM_MAY_29/2009_) 523-0809018-0021161st Edition, 20 July 20072nd Edition, 29 May 2009T-1
ROCKWELL COLLINS, INC.INSTALLATION MANUALExport Control Classification Notice (ECCN) for this document is 6E991.PROPRIETARY NOTICEFREEDOM OF INFORMATION ACT (5 USC 552) AND DISCLOSURE OF CONFIDENTIAL INFORMATIONGENERALLY (18 USC 1905)This document and the information disclosed herein are proprietary data of Rockwell Collins, Inc. Neither thisdocument nor the information contained herein shall be used, reproduced, or disclosed to others without the writtenauthorization of Rockwell Collins, Inc., except to the extent required for installation or maintenance of recipient’sequipment. This document is being furnished in confidence by Rockwell Collins, Inc. The information disclosedherein falls within the exemption (b) (4) of 5 USC 552 and the prohibitions of 18 USC 1905.SOFTWARE COPYRIGHT NOTICE© COPYRIGHT 2007-2009 ROCKWELL COLLINS, INC. ALL RIGHTS RESERVEDAll software resident in this equipment is protected by copyright.We welcome your comments concerning this manual. Although every effort has been made to keep it free oferrors, some may occur. When reporting a specific problem, please describe it briefly and include the manual partnumber, the paragraph or figure number, and the page number.Send your comments to: Rockwell Collins, Inc.400 Collins Road NE, M/S 153-250Cedar Rapids, IA 52498-0001EMAIL: techmanuals@rockwellcollins.comFor product orders or inquiries, please contact: Rockwell Collins, Inc.Customer Response Center400 Collins Road NE, M/S 133-100Cedar Rapids, IA 52498-0001TELEPHONE: 1.888.265.5467INTERNATIONAL: 1.319.265.5467FAX NO: 319.295.4941EMAIL: response@rockwellcollins.com.T-2
523-0809018INSERT LATEST CHANGED PAGES. DESTROY SUPERSEDED PAGES.LIST OF EFFECTIVE PAGESNOTE: The portion of the text affected by the changes is indicated by a vertical linein the outer margins of the page. Changes to illustrations are indicated byshaded or screened areas, or by miniature pointing hands.Dates of issue for original and changed pages are:Original0 ........... 29May2009TOTAL NUMBER OF PAGES IN THIS PUBLICATION IS 210 CONSISTING OF THE FOLLOWING:Page *Change Page *Change Page *ChangeNo. No. No. No. No. No.T-1-T-2 .......................0A .............................0BBlank........................0i-vii ..........................0viiiBlank.......................0ix-xi..........................0xiiBlank .......................0xiii ............................0xivBlank.......................01-1-1-5 .......................01-6Blank.......................01-7 ............................01-8Blank.......................01-9 ............................01-10Blank......................02-1-2-5 .......................02-6Blank.......................02-7 ............................02-8Blank.......................02-9-2-15 ......................02-16Blank......................02-17 ...........................02-18Blank......................02-19 ...........................02-20Blank......................02-21 ...........................02-22Blank......................02-23 ...........................02-24Blank......................02-25-2-27 .....................02-28Blank......................02-29-2-31 .....................02-32Blank......................02-33-2-35 .....................02-36Blank......................02-37 ...........................02-38Blank......................02-39 ...........................02-40Blank......................02-41 ...........................02-42Blank......................02-43 ...........................02-44Blank......................02-45 ...........................02-46Blank......................02-47 ...........................02-48Blank......................02-49-2-55 .....................02-56Blank......................02-57-2-65 .....................02-66Blank......................02-67 ...........................02-68Blank......................02-69 ...........................02-70Blank......................02-71 ...........................02-72Blank......................02-73 ...........................02-74Blank......................02-75 ...........................02-76Blank......................02-77-2-79 .....................02-80Blank......................03-1-3-14 ......................04-1-4-29 ......................04-30Blank......................0A-1 ...........................0A-2Blank ......................0B-1-B-19 .....................0B-20Blank .....................0C-1-C-17 .....................0C-18Blank .....................0D-1-D-10 .....................0E-1-E-3 .......................0E-4Blank ......................0E-5 ............................0E-6Blank ......................0E-7 ............................0E-8Blank ......................0*Zero in this column indicates an original page.A/(B Blank)
523-0809018TABLE OF CONTENTSChapter/Para PageLISTOFILLUSTRATIONS .................................................................................... vLISTOFTABLES.............................................................................................viINTRODUCTION .............................................................................................ixSAFETYSUMMARY........................................................................................ xiii1 GeneralInformation.......................................................................................... 1-11.1 INTRODUCTION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-11.2 EQUIPMENT........................................................................................ 1-11.2.1 EquipmentCovered. ................................................................................. 1-11.3 SYSTEMOVERVIEW. .............................................................................. 1-41.3.1 SystemBlockDiagram................................................................................ 1-41.4 COMPONENTDESCRIPTIONS. ..................................................................... 1-91.4.1 TSS-4100 Traffic Surveillance System. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-91.4.2 ECU-3000ExternalCompensationUnit................................................................. 1-91.4.3 TDR-94DATC/ModeSTransponder. .................................................................. 1-91.4.4 TSA-4100DirectionalAntenna. ....................................................................... 1-91.4.5 TRE-930OmnidirectionalAntenna..................................................................... 1-91.4.6 ANT-42OmnidirectionalAntenna...................................................................... 1-91.4.7 TSM-4100 Traffic Surveillance Mount. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-92 SystemComponents.......................................................................................... 2-12.1 INTRODUCTION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-12.1.1 LRUSystemSection.................................................................................. 2-12.1.2 LRUDataSection.................................................................................... 2-12.2 COMPONENTDESCRIPTIONS. ..................................................................... 2-12.2.1 ANT-42ModeSL-BandAntenna...................................................................... 2-12.2.2 TDR-94DATC/ModeSTransponder. .................................................................. 2-12.2.3 TRE-930ModeSOmnidirectionalAntenna. ............................................................ 2-22.2.4 TSA-4100ModeSDirectionalAntenna................................................................. 2-22.2.5 TSS-4100 Traffic Surveillance System. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-22.3 ANT-4234-54-00.................................................................................... 2-32.3.1 ANT-42,ExternalTheoryofOperation. ................................................................ 2-32.4 L-BANDANTENNA,ANT-42,DATA................................................................. 2-32.4.1 ANT-42Illustration. ................................................................................. 2-32.4.2 ANT-42MatingConnectorData. ...................................................................... 2-32.4.3 ANT-42OutlineandMountingDimensions. ............................................................ 2-42.4.4 InstallationandRemoval.............................................................................. 2-72.5 ECU-300034-54-00.................................................................................. 2-92.5.1 ExternalControlUnit,ExternalTheoryofOperation. .................................................... 2-92.6 EXTERNALCONTROLUNIT,ECU-3000,DATA. .................................................... 2-92.6.1 ECUTopHalf. ...................................................................................... 2-92.6.2 ECUBottomHalf,FirstPartition....................................................................... 2-92.6.3 ECU Bottom Half, Second Partition. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-92.6.4 ECU-3000Illustration. .............................................................................. 2-142.6.5 ECU-3000MatingConnectorData.................................................................... 2-142.6.6 ECU-3000OutlineandMountingDimensions.......................................................... 2-152.6.7 InstallationandRemoval............................................................................. 2-192.6.8 InternalTheoryofOperation.......................................................................... 2-192.7 TDR-94D34-54-00.................................................................................. 2-212.7.1 ModeSTransponder,ExternalTheoryofOperation. .................................................... 2-21i
523-0809018TABLE OF CONTENTSChapter/Para Page2.8 MODE S TRANSPONDER, TDR-94D, DATA. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-252.8.1 TDR-94DATC/ModeSTransponderMountingConsiderations........................................... 2-252.8.2 TDR-94DIllustration................................................................................ 2-252.8.3 TDR-94DMatingConnectorData..................................................................... 2-252.8.4 TDR-94DOutlineandMountingDimensions........................................................... 2-262.8.5 InstallationandRemoval............................................................................. 2-292.8.6 InternalTheoryofOperation.......................................................................... 2-292.9 TRE-93034-54-00. ................................................................................. 2-332.9.1 TRE-930L-BandDirectionalAntenna,ExternalTheoryofOperation...................................... 2-332.10 ANTENNA, TRE-930, DATA. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-332.10.1 TRE-930Illustration................................................................................. 2-332.10.2 TRE-930MatingConnectorData. .................................................................... 2-342.10.3 TRE-930 Outline and Mounting Dimensions.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-342.10.4 Omni-DirectionalRequirements....................................................................... 2-372.10.5 InstallationandRemoval............................................................................. 2-372.11 TSA-410034-54-00. ................................................................................ 2-392.11.1 Traffic Surveillance Antenna, External Theory of Operation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-392.12 ANTENNA, TSA-4100, DATA. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-392.12.1 TSA-4100Illustration................................................................................ 2-392.12.2 TSA-4100OutlineandMountingDiagram. ............................................................ 2-392.12.3 TSA-4100MatingConnectorData. ................................................................... 2-492.12.4 CablingConsiderations. ............................................................................. 2-492.12.5 InstallationandRemoval............................................................................. 2-492.13 TSS-410034-43-00.................................................................................. 2-532.13.1 Traffic Surveillance System, External Theory of Operation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-532.14 TRAFFICSURVEILLANCESYSTEM,TSS-4100,DATA............................................... 2-572.14.1 TSS-4100AntennaRequirements. .................................................................... 2-572.14.2 TSS-4100andTSM-4100Illustration.................................................................. 2-572.14.3 TSS-4100MatingConnectorData..................................................................... 2-582.14.4 TSS-4100OutlineandMountingDimensions........................................................... 2-642.14.5 CablingConsiderations. ............................................................................. 2-772.14.6 InstallationandRemoval............................................................................. 2-772.14.7 InternalTheoryofOperation.......................................................................... 2-773 Operation ................................................................................................... 3-13.1 INTRODUCTION. .................................................................................. 3-13.2 GENERAL.......................................................................................... 3-14 Maintenance................................................................................................. 4-14.1 INTRODUCTION. .................................................................................. 4-14.1.1 FlightLineMaintenance. ............................................................................. 4-14.1.2 AutomaticTesting.................................................................................... 4-14.2 MAINTENANCE SCHEDULE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-24.2.1 CleaningandPainting................................................................................. 4-24.2.2 CleaningIndicators................................................................................... 4-24.2.3 CleaningAntennas. .................................................................................. 4-24.2.4 ApprovedRepairs.................................................................................... 4-24.3 CONVERSIONFROMTTR/TDRTOTSSSYSTEM.................................................... 4-34.3.1 PreparationforConversion............................................................................ 4-34.3.2 DifferencesbetweenTTR/TDRandTSS................................................................ 4-34.4 DATALOADING.................................................................................... 4-44.4.1 ECUData........................................................................................... 4-44.4.2 TSSDataLoading.................................................................................... 4-44.4.3 TSSElectronicNameplate............................................................................. 4-5ii
523-0809018TABLE OF CONTENTSChapter/Para Page4.5 TSS-4100 MODE S ADDRESS PROGRAMMING TOOL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-64.5.1 ProgrammingToolSupport............................................................................ 4-64.5.2 ProgrammingToolSystemRequirements. .............................................................. 4-64.5.3 ProgrammingToolInstallation......................................................................... 4-74.5.4 ProgrammingToolSetup.............................................................................. 4-74.5.5 ProgrammingToolInstructions. ....................................................................... 4-94.5.6 ProgrammingToolOverview. ........................................................................ 4-104.6 LEDINDICATORS. ................................................................................ 4-114.6.1 LEDDescriptions. .................................................................................. 4-114.7 TESTEQUIPMENTANDPOWERREQUIREMENTS................................................. 4-144.7.1 PowerRequirements................................................................................. 4-144.8 TESTINGANDTROUBLESHOOTING. ............................................................. 4-154.8.1 Pre-installationTesting............................................................................... 4-154.8.2 TCASSelfTest. .................................................................................... 4-154.8.3 EquipmentSetup.................................................................................... 4-164.8.4 Radio Altitude System Failure Tests. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-164.8.5 Pressure Altitude System Failure Tests. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-174.8.6 RangeandBearingTest.............................................................................. 4-184.8.7 TCASRATest...................................................................................... 4-194.8.8 TransponderTests................................................................................... 4-194.8.9 ADS-BTransmitGroundTest......................................................................... 4-204.8.10 Transponder/TCASSuppressionBusIssues. ........................................................... 4-204.9 INITIALINSTALLATIONCHECKOUTPROCEDURE................................................ 4-224.9.1 Initial Transponder Check Out. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-224.9.2 Initial TCAS Check Out.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-224.10 RETURNTOSERVICETESTPROCEDURE.......................................................... 4-294.10.1 ReturntoServiceTest. .............................................................................. 4-294.11 INSPECTION/CHECK. ............................................................................. 4-294.11.1 Antennas........................................................................................... 4-294.11.2 TSS-4100 Traffic Surveillance System. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-294.11.3 TDR-94DATC/ModeSTransponder. ................................................................. 4-29AppendixAFaultsandWarnings...................................................................................A-1A.1 GENERAL...........................................................................................A-1AppendixBMaintenanceWords....................................................................................B-1B.1 MAINTENANCEDIAGNOSTICWORDS..............................................................B-1B.1.1 Label350TDRMaintenanceWord.....................................................................B-4B.1.2 Label351TSS-4100DiagnosticWord1. ...............................................................B-4B.1.3 Label352CDUDiagnosticWord1.....................................................................B-5B.1.4 Label353TSS-4100DiagnosticWord2. ...............................................................B-5B.1.5 Label354TSS-4100DiagnosticWord3. ..............................................................B-11B.1.6 Label355TSS-4100DiagnosticWord4. ..............................................................B-12B.1.7 Label350ACASDiagnostics.........................................................................B-14B.2 TDR-94DDIAGNOSTICCODES.....................................................................B-16Appendix C Buses and Other Interfaces. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . C-1C.1 INTERFACETYPES..................................................................................C-1C.2 TSSDISCRETEOUTPUTS. ..........................................................................C-4C.3 TSSDISCRETEINPUTS..............................................................................C-5C.4 TSSA429OUTPUTBUSES...........................................................................C-7C.4.1 TSS-1andTSS-2OutputBusLabels. ..................................................................C-7C.4.2 TSS-3OutputBusLabels. ............................................................................C-8C.4.3 TA/RA-1andTA/RA-2OutputBusLabels..............................................................C-8C.4.4 TX-2OutputBusLabels. .............................................................................C-9iii
523-0809018TABLE OF CONTENTSChapter/Para PageC.5 A429INPUTBUSES. ...............................................................................C-10C.5.1 ControlBusSelection................................................................................C-10C.5.2 ControlBusLabels..................................................................................C-10C.5.3 ConcentratedBusInputs. ............................................................................C-11C.5.4 GPSInputData. ....................................................................................C-14C.5.5 XT-2InputBus(TDRtoTSS)........................................................................C-17C.5.6 TSSDataLoadBus..................................................................................C-17AppendixDEquipmentCharacteristics..............................................................................D-1D.1 EQUIPMENTCHARACTERISTICS. ..................................................................D-1AppendixEInterconnectDiagram .................................................................................. E-1E.1 INTRODUCTION....................................................................................E-1E.2 CABLINGINSTRUCTIONS. .........................................................................E-1E.3 GROUNDING AND HIRF GUIDELINES.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-1E.4 SYSTEMINTERCONNECTDIAGRAM. .............................................................. E-2iv
523-0809018LIST OF ILLUSTRATIONSNumber Title Page1-1 Typical Single TrafficSurveillanceSystem ................................................................... 1-31-2 Typical TrafficSurveillanceSystemwithRIUs,BlockDiagram................................................. 1-51-3 Typical TrafficSurveillanceSystemwithoutRIUs,BlockDiagram .............................................. 1-72-1 ANT-42.................................................................................................. 2-32-2 ANT-42L-BandAntenna,OutlineandMountingDimensions .................................................. 2-52-3 External Compensation Unit, ECU-3000, External SimplifiedSchematic......................................... 2-92-4 ECU-3000............................................................................................... 2-142-5 ECU-3000MatingConnectors............................................................................. 2-152-6 ECU-3000 Outline and Mounting Dimensions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-172-7 ModeSTransponder,TDR-94D,ExternalTheoryofOperation ................................................ 2-232-8 TDR-94D ............................................................................................... 2-252-9 TDR-94DMatingConnectors.............................................................................. 2-262-10 TDR-94D Outline and Mounting Dimensions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-272-11 ModeSTransponder,TDR-94D,InternalTheoryofOperation................................................. 2-312-12 TRE-930................................................................................................ 2-332-13 TRE-930L-BandAntenna,OutlineandMountingDimensions................................................. 2-352-14 TSA-4100,ShortandLongConnectors ..................................................................... 2-392-15 TSA-4100 Outline and Mounting Diagram, Long Connector Version . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-412-16 TSA-4100 Outline and Mounting Diagram, Short Connector Version . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-452-17 TCASDirectionalAntenna,MountingDiagram.............................................................. 2-512-18 Traffic Surveillance System, External Block Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-542-19 Traffic Surveillance System, TSS-4100 No. 1, External SimplifiedSchematic.................................... 2-552-20 TSS-4100 ............................................................................................... 2-572-21 TSM-4100............................................................................................... 2-582-22 TSS-4100MatingConnectors.............................................................................. 2-602-23 TSS-4100 Traffic Surveillance System, Outline and Mounting Dimensions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-652-24 TSM-4100 TrafficSurveillanceMount,Outline .............................................................. 2-712-25 Traffic Surveillance System, TSS-4100, Internal Block Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-793-1 TrafficDisplay(AFD-3010/3010E),TRAFFICPage........................................................... 3-23-2 ResolutionAdvisoryDisplay(AFD),TCASIIFly-ToCommands............................................... 3-53-3 ResolutionAdvisoryDisplay(AFD),PitchCues .............................................................. 3-63-4 TopLevelRadioTuningPage,RTU-42XXRadioTuningUnit.................................................. 3-83-5 TopLevelRadioTunePage,CDU-62XXControlDisplayUnit ................................................. 3-83-6 TCASPage,RadioTuningUnit(RTU-42XX) ............................................................... 3-103-7 TCASPage,ControlDisplayUnit(CDU-62XX)............................................................. 3-103-8 TransponderPage,RTU-42XXRadioTuningUnit ........................................................... 3-133-9 TransponderPage,CDU-62XXControlDisplayUnit......................................................... 3-134-1 TSS-4100,ElectronicNameplate............................................................................ 4-64-2 ProgrammingTool-SelectNetworkInterfaceCard............................................................ 4-84-3 ProgrammingTool-ChangetheIPAddress .................................................................. 4-84-4 ProgrammingTool-UnlocktheIPAddress................................................................... 4-94-5 ProgrammingTool-VerifytheIPAddress.................................................................... 4-94-6 ProgrammingTool-ScreenShot........................................................................... 4-114-7 TSS-4100FrontPanelLEDs............................................................................... 4-124-8 TCASSelfTestStandardOutput........................................................................... 4-164-9 BearingTest,AircraftandTCASTestSetOrientation......................................................... 4-194-10 SimplifiedFlightScenarioandParameters................................................................... 4-22C-1 BusArchitecture,TSS(R)andTDR(L).....................................................................C-12C-2 DualGPSInstallation.....................................................................................C-16E-1 Traffic Surveillance System, Interconnect Wiring Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . E-3v
523-0809018LIST OF TABLESNumber Title Page1-1 EquipmentCovered........................................................................................ 1-11-2 AssociatedEquipment...................................................................................... 1-22-1 ANT-42MatingConnectorHardwareandTooling............................................................. 2-42-2 ECUInstallationStrappingData............................................................................ 2-102-3 ECU-3000MatingConnectorHardwareandTooling.......................................................... 2-142-4 TDR-94DMatingConnectorHardwareandTooling........................................................... 2-252-5 TRE-930MatingConnectorHardwareandTooling. .......................................................... 2-342-6 TSA-4100MatingConnectorHardwareandTooling.......................................................... 2-492-7 TSS-4100MatingConnectorHardwareandTooling........................................................... 2-582-8 TSS-4100MatingConnectorPinsandFunctions,Power,Ground,Suppression................................... 2-602-9 TSS-4100MatingConnectorPinsandFunctions,ARINC429Input. ........................................... 2-612-10 TSS-4100MatingConnectorPinsandFunctions,ARINC429Output........................................... 2-612-11 TSS-4100MatingConnectorPinsandFunctions,GPSTimeMarkInput......................................... 2-622-12 TSS-4100MatingConnectorPinsandFunctions,DiscreteInput(Gnd=Active).................................. 2-622-13 TSS-4100MatingConnectorPinsandFunctions,DiscreteOutput(Gnd=Active)................................ 2-632-14 TSS-4100MatingConnectorPinsandFunctions,AudioOutput................................................ 2-642-15 TSS-4100 Mating Connector Pins and Functions, ECU Interface.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-643-1 TrafficDisplay(AFD-3010/3010E),TRAFFICPage. .......................................................... 3-33-2 ResolutionAdvisoryDisplay(AFD),TCASIIFly-ToCommandsandPitchCues. ................................ 3-63-3 TopLevelRadioTunePage,RTURadioTuningUnitorCDUControlDisplayUnit. .............................. 3-93-4 TCASPage,RadioTuningUnitorControlDisplayUnit....................................................... 3-113-5 TransponderPage,RTURadioTuningUnitorControlDisplayUnit. ........................................... 3-134-1 DataLoadBusesAndPins ................................................................................. 4-44-2 ARINC615DataLoaders................................................................................... 4-54-3 LEDDescriptions ........................................................................................ 4-12B-1 LRUDiagnosticData,ReportingLRUs......................................................................B-1B-2 DiagnosticWordInterpretation..............................................................................B-2B-3 HexadecimaltoBinaryConversionTable.....................................................................B-3B-4 Label351TSS-4100DiagnosticWord1......................................................................B-4B-5 Label353TSS-4100DiagnosticWord2......................................................................B-5B-6 LRUDiagnosticData,FaultNamesandCategories. ...........................................................B-6B-7 Label354TSS-4100DiagnosticWord3.....................................................................B-11B-8 Label355TSS-4100DiagnosticWord4.....................................................................B-12B-9 Label355VoltageDecode.................................................................................B-13B-10 Label350ACASDiagnosticsWord ........................................................................B-14B-11 TDR-94DDiagnosticCodes................................................................................B-16C-1 BusesandDiscretes .......................................................................................C-1C-2 TSSDiscreteOutputs......................................................................................C-4C-3 TSSDiscreteInputs .......................................................................................C-5C-4 TSSA429OutputBuses ...................................................................................C-7C-5 TSS-1andTSS-2OutputBusLabels ........................................................................C-7C-6 TSS-3OutputBusLabels ..................................................................................C-8C-7 TA/RA-1andTA/RA-2OutputBusLabels...................................................................C-9C-8 TX-2OutputBusLabels ...................................................................................C-9C-9 A429InputBuses ........................................................................................C-10C-10 ControlBusSelection.....................................................................................C-10C-11 ControlBusLabels.......................................................................................C-11C-12 ConcentratedBusInputs ..................................................................................C-12C-13 GPSBusLabels..........................................................................................C-14C-14 GPSData/TimeMarkInputCorrelation.....................................................................C-15C-15 XT-2InputBus(TDRtoTSS).............................................................................C-17C-16 TSSDataLoadBus.......................................................................................C-17D-1 Equipment Specifications...................................................................................D-1vi
523-0809018LIST OF TABLESNumber Title PageD-2 CertificationCategories.....................................................................................D-2D-3 UnitWeight,PowerRequirements,andSize...................................................................D-2D-4 ANT-42 Environmental QualificationForm...................................................................D-3D-5 ECU-3000 Environmental QualificationForm.................................................................D-4D-6 TDR-94D Environmental QualificationForm..................................................................D-6D-7 TSA-4100 Environmental QualificationForm. ................................................................D-8D-8 TSS-4100 Environmental QualificationForm..................................................................D-9vii/(viii Blank)
523-0809018INTRODUCTION1. GENERAL.This Installation Manual (IM) provides installation information regarding the TSS-4100 Traffic Surveillance System and its relatedequipment.2. HOW TO USE THE MANUAL.This IM is written to Air Transport Association (ATA) Specification 100 standards and contains the chapters outlined below:2.1. Chapter 1.General Information chapter describes the purpose and technical properties of the Traffic Surveillance System LRUs.2.2. Chapter 2.System Components chapter describes each LRU separately and in detail. First the LRU is described as it relates to the rest of theTraffic Surveillance System. Then the LRU is described as a stand alone piece of avionics equipment.2.3. Chapter 3.Operation chapter provides a description of the operating controls and displays that are available in the Traffic Surveillance System.2.4. Chapter 4.Maintenance chapter provides flight line maintenance instructions for the Traffic Surveillance System. This includes theory of op-eration.2.5. APPENDICES .Appendices describe very detailed information about the avionics system.1. APPENDIX A Faults and Warnings2. APPENDIX B Maintenance Words3. APPENDIX C Buses and Other Interfaces4. APPENDIX D Equipment Characteristics5. APPENDIX E Interconnect Diagram3. ACRONYMS, ABBREVIATIONS, AND MNEMONICS.The list that follows shows the abbreviations, acronyms, and mnemonics that are used in this publication to describe the avionicssystem.TERM MEANINGABS AbsoluteACAS Airborne Collision Avoidance SystemADC Air Data ComputerADLP Aircraft Data Link Processor (MODE-S)ADS Air Data SystemADS-B Automatic Dependent Surveillance-BroadcastAFD Adaptive Flight DisplayAHC Attitude Heading ComputerALT AltitudeANT AntennaARINC Digital Database ProtocolsAT C A i r Tr a fficControlATCRBS Air Traffic Control Radar Beacon Systemix
introduction 523-0809018AUTO AutomaticBITE Built-In Test EquipmentBNR BinaryCDU Control Display UnitCPN Collins Part NumberCRC Cyclic Redundancy CheckDCP Display Control PanelDCU Data Concentrator UnitDPSK Differential Phase Shift KeyingECU External Compensation UnitEFIS Electronic Flight Instrument SystemESDS Electrostatic Discharge SensitiveFMS Flight Management SystemGPS Global Positioning SystemHAE Height Above EllipsoidHDG HeadingHg Millimeters of MercuryHIRF High Intensity Radiated FieldHSI Horizontal Situation IndicatorHV High-VoltageIAPS Integrated Avionics Processor SystemIRS Inertial Reference SystemLRU Line Replaceable UnitMCU Modular Concept UnitMFD Multifunction Displayms MillisecondMSL Mean Sea LevelNA Not ApplicableNVRAM Non-Volatile RAMPAM Pulse Amplitude ModulationPFD Primary Flight DisplayPPOS Present PositionRA TCAS Resolution AdvisoryRAM Random Access MemoryREL RelativeRIU Radio Interface UnitROM Read Only MemoryRTU Radio Tuning UnitSDI Source Destination IdentifierSLS Side-Lobe-SuppressionSTBY StandbySTC Supplemental Type CertificateTA Traffic AdvisoryTBD To Be DeterminedTC Type CertificateTCAS Traffic Alert Collision Avoidance SystemTDR TransponderTFC TrafficTRE TCAS II Directional AntennaTSO Technical Standard OrderTSA Traffic Surveillance AntennaTSS Traffic Surveillance SystemTSSA Traffic Surveillance System ApplicationTSM Traffic Surveillance MountTTC TCAS Transponder ControlTX Transmitx
introduction 523-0809018To submit comments regarding this manual, please contact:Rockwell Collins, Inc.400 Collins Rd NECedar Rapids, IA 52498-0001Attn: Technical Operations M/S 153-250or send email to: techmanuals@rockwellcollins.comxi/(xii Blank)
523-0809018SAFETY SUMMARY1. GENERAL SAFETY INSTRUCTIONS.This manual describes physical and chemical processes which may cause injury or death to personnel or damage to equipment ifnot properly followed. This safety summary includes general safety precautions and instruction that must be understood and appliedduring operation and maintenance to make sure personnel safety and protection of equipment. Prior to performing any task, theWARNING, CAUTIONS, and NOTES included in that task shall be reviewed and understood.2. WARNING, CAUTIONS AND NOTES.WARNINGS and CAUTIONS are used in this manual to highlight operating or maintenance procedures, practices, conditions orstatements which are considered essential to protection of personnel (WARNING) or equipment (CAUTION). WARNINGS andCAUTIONS immediately precede the step or procedure to which they apply. WARNINGS and CAUTIONS consist of four parts:heading (WARNINGS, CAUTIONS or Icon [HAZARDOUS MATERIALS WARNING ]), a statement of the hazard, minimumprecautions, and possible result if disregarded. NOTES are used in this manual to highlight operating or maintenance procedures,practices, conditions or statements which are not essential to protection of personnel or equipment. NOTES may precede or followthe step or procedure, depending upon the information to be highlighted. The headings used and definitions are as follows.Highlights an essential operating or maintenance procedure, practice, condition, or statement, etc. which if notstrictly observed, could result in injury to, or death of, personnel or long term health hazards.Highlights an essential operating or maintenance procedure, practice, condition, or statement, etc. which if notstrictly observed, could result in damage to, or destruction of, equipment or loss of mission effectiveness.NOTEHighlights an essential operating or maintenance procedure, condition, or statement.xiii/(xiv Blank)
523-0809018CHAPTER 1General Information1.1. INTRODUCTION.This publication provides all the specifications, principles of operation, and information necessary to install, test, and troubleshootthe TSS-4100 Traffic Surveillance System (TSS). The three major functions of the TSS-4100 follow:• The TSS-4100 is a Mode S transponder that replies to directed and all-call interrogations.• The TSS-4100 is a Traffic Alert Collision Avoidance System (TCAS) II, change 7 unit. It monitors the area around the aircraftfor potential airspace conflicts.• When enabled, the TSS-4100 is also an Automatic Dependent Surveillance-Broadcast (ADS-B) transmitter/receiver unit. It trans-mits the aircraft position, velocity, and identification. It also processes the transmissions of other ADS-B equipped aircraft.1.2. EQUIPMENT.The Equipment Covered table shows the system avionics, mount, and avionics software. Associated equipment shows closely relatedavionics. Refer to Figure 1-1 for the hardware of a typical single Traffic Surveillance System.1.2.1. Equipment Covered.Refer to Table 1-1 for a complete list of the Rockwell Collins avionics equipment covered in this manual.Table 1-1. Equipment Covered.UNIT DESCRIPTION COLLINS PARTNUMBERSTANDARDQUANTITYOPTIONALQUANTITYTSS-4100 Traffic Surveillance System 822-2132-001 1TSSA-4100 Traffic Surveillance System Application 810-0052-001 1TSM-4100 Traffic Surveillance Mount 866-0128-020 1ECU-3000 External Compensation Unit-802: TCAS II, EHS Mode S Transponder-803: TCAS II, EHS Mode S Transponder, ADS-BOut822-1200-80X 1TSA-4100 Traffic Surveillance Antenna-101: Baseline antenna; short connectors-001: Optional replacement; long connectors866-0016-X01 1 +1TRE-930 Omnidirectional Antenna 866-5019-010 1 -11-1
general information 523-0809018Table 1-2. Associated Equipment.UNIT DESCRIPTION COLLINS PARTNUMBERSTANDARDQUANTITYOPTIONALQUANTITYNOTEInformation for the TDR-94D and ANT-42 is for reference only. Refer to the Pro Line II Comm/Nav/Pulse System Instal-lation Manual, Collins Part Number (CPN) 523-0772719.TDR-94D Air Traffic Control Radar Beacon System (ATCRBS)Mode S Transponder: -008, -108, -308, -309, -408,or -409.622-9210-X0X 1ANT-42 Mode S omnidirectional antenna. Used withTDR-94D.622-6591-001 21.2.1.1. In addition to the Avionics, the TSS-4100 Mode S Address Programming Tool, CPN 811-3937-002, is covered in chapter4 of this installation manual. This is used to program the Mode S Address for use by the TSS-4100.1-2
general information 523-0809018Figure 1-1. Typical Single Traffic Surveillance System1-3
general information 523-08090181.3. SYSTEM OVERVIEW.This section gives an overview of the Traffic Surveillance System.1.3.1. System Block Diagram.NOTEMost units report maintenance information in a diagnostic word to the built-in diagnostic system. This section doesnot refer to these diagnostic words. Refer to the maintenance section of this manual for diagnostic information.The system schematics are not intended to replace bench level repair coverage. Component level coverage isprovided in the applicable repair manual.Refer to Figure 1-2 for a block diagram of a typical Traffic Surveillance System with Radio Interface Unit (RIU). Refer to Figure1-3 for a block diagram of a typical Traffic Surveillance System without RIUs. Heavy solid-black borders identify all system units.The slashed border outlines identify the interfacing units.1-4
general information 523-0809018Figure 1-2. Typical Traffic Surveillance System with RIUs, Block Diagram1-5/(1-6 Blank)
general information 523-0809018Figure 1-3. Typical Traffic Surveillance System without RIUs, Block Diagram1-7/(1-8 Blank)
general information 523-08090181.4. COMPONENT DESCRIPTIONS.The Traffic Surveillance System fully integrates with an airplane transponder and TCAS control system. The Traffic SurveillanceSystem includes the Line Replaceable Units (LRU) that follow:• One TSS-4100 Traffic Surveillance System LRU• TSSA-4100 Traffic Surveillance System Application (TSSA) software• One ECU-3000 External Compensation Unit (ECU)• One upper TSA-4100 Traffic Surveillance Antenna (TSA)• One lower TRE-930 L-Band Omnidirectional TCAS Antenna (TRE)• One TSM-4100 Traffic Surveillance Mount (TSM) with monitored cooling fan•OneAirTraffic Control (ATC) Mode-S Transponder (TDR)• Two ANT-42 L-Band Transponder Omnidirectional Antennas (ANT)• A transponder/TCAS control unit•Atrafficdisplay• An aural alert system.The LRU overviews below describe each unit in the Traffic Surveillance System.1.4.1. TSS-4100 Traffic Surveillance System.The TSS-4100 is the main component of the Traffic Surveillance System. The TSS-4100 operates on 28-V dc. It contains all circuitsnecessary for computing, transmitting, and receiving functions of the Traffic Surveillance System and interfacing with a stand-alonetransponder, other aircraft sensors (for example, Air Data Computer (ADC), Inertial Reference System (IRS), Global PositioningSystem (GPS), etc.), antennas, controls, and displays.1.4.1.1. The TSSA-4100 Traffic Surveillance System Application is necessary software for the TSS-4100. The TSSA-4100 filesare field loadable.1.4.2. ECU-3000 External Compensation Unit.The ECU is used to hold all of the aircraft and unit configuration data necessary for the TSS-4100 to operate properly. This simplifiesthe wiring for the Traffic Surveillance System. For example, instead of program pins for the Mode S address, maximum aircraftaltitude, and bus speeds that must be wired and tested for every aircraft, a simple file is dataloaded through the TSS and stored inthe ECU.1.4.3. TDR-94D ATC/Mode S Transponder.The TDR-94D Duplex ATC/Mode S Transponder operates on 28-V dc. The TDR-94D has the capability of operating with Mode Sinterrogators. The Mode S capability permits sending and receiving messages via the interrogation/reply data link.1.4.4. TSA-4100 Directional Antenna.The TSA-4100 directional antenna is the top antenna for the TSS. It is also optionally used as the lower antenna for the TSS. It hasfour passive antenna elements for directionality and is mounted on the outside of the aircraft fuselage.1.4.5. TRE-930 Omnidirectional Antenna.The TRE-930 omnidirectional antenna is an optional lower antenna for the TSS.1.4.6. ANT-42 Omnidirectional Antenna.Two ANT-42 omnidirectional antennas, one upper and one lower antenna, connect to the TDR-94D mode S transponder.1.4.7. TSM-4100 Traffic Surveillance Mount.The TSM-4100, or Traffic Surveillance Mount, is a standard 4 Modular Concept Unit (MCU) mount with a fan that can be controlledand monitored.1-9/(1-10 Blank)
523-0809018CHAPTER 2System Components2.1. INTRODUCTION.NOTEThe names of some Line Replaceable Unit (LRU) types do not match the initials of the functional name of theequipment. For example, the name TRE-930 does not match the initials of its functional name, the Mode S Om-nidirectional Antenna.The information and instructions provided in this section are recommendations and do not necessarily correspondwith any actual aircraft installation and wiring. This section cannot be used in place of a Supplemental TypeCertificate (STC) or Type Certificate (TC).2.1.1. LRU System Section.The first section under a tab shows the LRU-type name (for example, TDR-94D), and the external theory of operation for each LRUof that LRU-type. This includes all the sources of all the input signals to the LRU, and all the output signals from the LRU. Then asimplified diagram shows what pins are used for each signal to and from the LRU.2.1.2. LRU Data Section.The next section contains blocks of data that describe, where applicable, general details about the same LRU. These data include,for example:•LRUpurpose• LRU graphic• LRU connector graphic• LRU connector data• LRU installation control drawing• LRU install and removal instructions• LRU internal theory• LRU internal block diagram.2.2. COMPONENT DESCRIPTIONS.This section describes the necessary and some optional LRU components of the Traffic Surveillance System (TSS).2.2.1. ANT-42 Mode S L-Band Antenna.The TDR-94D Mode S Transponder requires two Antenna (ANT), one L-Band antenna (upper) and one L-Band antenna (lower).The ANT-42 is an ac (capacitive) coupled antenna and does not meet the requirements for being an antenna for the TSS-4100.2.2.2. TDR-94D ATC/Mode S Transponder.The TDR-94D Air Traffic Control (ATC)/Mode S Transponder operates on 28 V dc. The TDR-94D has the capability of operatingwith Mode S interrogators as well as the standard 4096 interrogators. The Mode S capability permits sending and receiving messagesvia the interrogation/reply data link.2-1
system components 523-08090182.2.3. TRE-930 Mode S Omnidirectional Antenna.The TRE-930 Traffic Alert Collision Avoidance System (TCAS) Antenna is the recommended lower omnidirectional antenna forthe Traffic Surveillance System. It is a DC-grounded omnidirectional antenna, and is mounted on the outside of the aircraft fuselage.2.2.4. TSA-4100 Mode S Directional Antenna.The TSS-4100 requires the upper antenna to be the TSA-4100 directional antenna. The lower antenna can be another TSA-4100directional antenna or it can be an omnidirectional antenna like the TRE-930.2.2.5. TSS-4100 Traffic Surveillance System.The TSS-4100 (hardware) and TSSA-4100 (software) work together to provide TCAS, Mode S transponder, and Automatic Depen-dent Surveillance-Broadcast (ADS-B) capability in one LRU.2-2
system components 523-08090182.3. ANT-42 34-54-00.The sections that follow describe the external theory of operation, and general data of the ANT-42 L-Band antenna.2.3.1. ANT-42, External Theory of Operation.Refer to Figure 2-7. This sheet shows the external wire signals to and from the ANT-42 and the TDR-94D. The ANT-42 antennamounts on the top or bottom of an airplane. The antenna connects to the TDR-94D mode S transponder. There are no operatorcontrols or adjustments on this antenna.2.4. L-BAND ANTENNA, ANT-42, DATA.The ANT-42 is an L-Band antenna. The ANT-42 antenna mounts on the top or bottom of an aircraft. There are no operator controlsor adjustments on this antenna.2.4.1. ANT-42 Illustration.Refer to Figure 2-1 for an illustration of the ANT-42.Figure 2-1. ANT-422.4.2. ANT-42 Mating Connector Data.Table 2-1 shows the mating connector hardware and tooling for the ANT-42. Also refer to Figure 2-7 for the interconnect wiringdiagram.2-3
system components 523-0809018NOTEThe ANT-42 only requires one of the connectors in the table that follows.Table 2-1. ANT-42 Mating Connector Hardware and Tooling.ANT-42 HARDWARE/TOOLINGRF connector 90° TNC for ECS cable 311201: Collins Part Number (CPN) 857-1502-020 (CTS122), Vendor Ref VC-8,RF connector straight, TNC for ECS cable 311201: CPN 857-1502-010 (CTR122), Vendor Ref VC-8RF connector, straight, TNC for RG-142: CPN 357-9666-000RF connector, 90°, TNC for RG-142: CPN 357-9664-000RF grounding gasket: CPN 018-1394-1102.4.3. ANT-42 Outline and Mounting Dimensions.Refer to Figure 2-2 for an illustration of the ANT-42 Outline and Mounting Dimensions.2-4
system components 523-0809018Figure 2-2. ANT-42 L-Band Antenna, Outline and Mounting Dimensions2-5/(2-6 Blank)
system components 523-08090182.4.4. Installation and Removal.Make sure that the aircraft battery master switch is turned off before installing any equipment, mounts, or inter-connect cables. Failure to do so could irradiate the installer.The TDR-94D ATC/Mode S transponder requires two ANT-42 antennas. One ANT-42 L-Band Antenna is mounted on top of thefuselage and the second ANT-42 antenna is mounted on the bottom of the fuselage. All antennas should be mounted in a locationthat keeps the interconnecting coaxial cables as short as practicable.2.4.4.1. Installation. The procedure to install the ANT-42 follows (Refer to Paragraph 2.12.5.1.3 for instructions on antennaplacement relative to other antennas):a. Verify interconnect cabling before proceeding.b. Connect the connector to the ANT-42 antenna and position the Antenna on the fuselage.c. Secure with three mounting screws. No. 8 Stainless steel flat head screws are recommended. Zinc, cadmium plated, or alu-minum alloy screws are not recommended.d. Apply any weather/aerodynamic fillet of sealant to the periphery of the antenna and shape as necessary. The height of the beadshould not exceed 2.5 mm (0.1 in).2.4.4.2. Removal. The procedure to remove the ANT-42 follows:a. Remove sealant around periphery of the ANT-42 antenna.Do not allow the antenna to hang from cable. Allowing the antenna to hang from the cable could damage theconnector.b. Remove three screws from antenna.c. Disconnect connector from antenna.2-7/(2-8 Blank)
system components 523-08090182.5. ECU-3000 34-54-00.The sections that follow describe the external theory of operation, internal theory of operation, and general data of the ExternalCompensation Unit (ECU) in a Traffic Surveillance System.2.5.1. External Control Unit, External Theory of Operation.The ECU is connected to the TSS through nine wires. Refer to Figure 2-3. This sheet shows a typical TSS External CompensationUnit connection, and the external wire signals to and from the TSS.NOTEThere should be three twisted-shielded pairs and one twisted-shielded triple when wiring the ECU to the TSS. Thewires that are bracketed together should be within the same shield.Figure 2-3. External Compensation Unit, ECU-3000, External Simplified Schematic2.6. EXTERNAL CONTROL UNIT , ECU-3000, DATA.The ECU-3000 holds Rockwell Collins programmed data, aircraft-specificconfiguration data, and Mode S address. The ECU hastwo halves.2.6.1. ECU Top Half.Pre-programmed data for the TSS LRU is in the top half.2.6.2. ECU Bottom Half, First Partition.Refer to Table 2-2 for a list of the parameters that need to be set and their possible values. The first partition of the bottom half hasthe characteristics that follow:.• Programmed by the installer• Contains installation strapping, including number of GPSs, ARINC 429 bus speeds, airplane height and length, etc.• Must be data loaded.2.6.3. ECU Bottom Half, Second Partition.The second partition of the bottom half is used to store the Mode S address, and has the characteristics that follow:2-9
system components 523-0809018• Programmed by the installer• Contains the Mode S address• Either data loaded, or programmed using the TSS-4100 ECU Mode S Address Programming Tool.Table 2-2. ECU Installation Strapping Data.Description Values Recommend (Function Using Setting)Installation Part Number Up to 16 alpha-numeric charactersAircraft Installation 0000 0000 = Default0000 0001 = BRSRecommend: 0000 0001 (BRS)Antenna Monitoring 1 = Enable Antenna Monitoring0 = Disable Antenna MonitoringRecommend: 1 (Enable)Antenna Coaxial Cable Loss Upper 00 = Not used01 = 0 to 1 db10 = 1 to 2 db11 = 2 to 3 dbAntenna Coaxial Cable Loss Lower 00 = Not used01 = 0 to 1 db10 = 1 to 2 db11 = 2 to 3 dbAntenna Coaxial Cable Delay 00 = 0 to 50 nsec01 = 51 to 150 nsec10 =151 to 250 nsec11 = 251 to 300 nsecCable Delay Sign Bit 1 = Add Cable Delay to Bottom Antenna0=AddCableDelaytoTopAntennaShare Antennas 1 = Enable (share antennas)0 = Disable (independent antennas)Recommend: 0 (Disable)Bearing Lookup Configuration 0 = Standard1 = EnhancedRecommend: 1 (Enhanced)Fan Speed 0 = 0 (Fan monitor not connected)1..255 = 500..127500 (X times 500)(In Pulses Per Minute)Recommend: 42 (21000 pulses perminute) if have TSM; 0 otherwiseRA Valid Discrete Disable 1 = Disable RA Display Status DiscreteMonitor0 = Enable RA Display Status DiscreteMonitorRecommend: 0 (Enable) (TCAS)Display All Traffic/Threat Traffic 1 = Display all intruders0 = Display only TA and RA intrudersRecommend: 1 (Display all) (TCAS)Ground Display Mode 1 = TCAS in Standby mode on ground0 = TCAS in to TA Only mode on groundRecommend: 0 (TA Only mode) (TCAS)TA Display Intruder Limit Range 0 - 31 decimal Recommend: 31 (TCAS)Default Altitude Limit A Range 0 - 127 decimal Recommend: 27 (2,700 ft) (TCAS)2-10
system components 523-0809018Table 2-2. ECU Installation Strapping Data. - ContinuedDescription Values Recommend (Function Using Setting)Default Altitude Limit B Range 0 - 127 decimal Recommend: 99 (9,900 ft) (TCAS)Aural Files Used 1 = Aural Files Used0 = Aural Files Not Used(TCAS)Aural Advisory Discrete Delay 1 = Add delay to Aural Advisory discreteoutput0=Nodelay(TCAS)In Air Volume 000 = 16 dBm 40 mW001 = 13 dBm 20 mW010 = 10 dBm 10 mW011=7dBm5mW100 = 4 dBm 2.5 mW101 = 1 dBm 1.25 mW110 = -2 dBm 0.625 mW111 = 19 dBm 80 mWNOTEThis value is only applicable ifusing the TSS’s 600 ohm output.Audio power output tolerance is+35%/-25% of power outputs showin Watts (TCAS)On Ground Volume 000 = Match “In Air Volume”001 = 13 dBm 20 mW010 = 10 dBm 10 mW011=7dBm5mW100 = 4 dBm 2.5 mW101 = 1 dBm 1.25 mW110 = -2 dBm 0.625 mW111 = 19 dBm 80 mWNOTEThis value is only applicable ifusing the TSS’s 600 ohm output.Audio power output tolerance is+35%/-25% of power outputs showin Watts (TCAS)Maximum Climb Altitude Range 0 - 31 decimal (TCAS)Aircraft Category (maximum takeoffweight)0000 = Not available0001 = < 15,500 lbs0010 = 15,500 to 75,0000011 = 75,000 to 300,0000100 = High Vortex Large0101 = > 300,0000110 = High Performance0111 = Rotorcraft1000 through 1111 = Reserved for Set“B”(ADS-B)Maximum Cruising Airspeed 000 = Not available001 = 0 to 75 knots010 = 75 to 150 knots011 = 150 to 300 knots100 = 300 to 600 knots101 = 600 to 1200 knots110 = more than 1200 knots111 = not used(ADS-B)2-11
system components 523-0809018Table 2-2. ECU Installation Strapping Data. - ContinuedDescription Values Recommend (Function Using Setting)Aircraft Length/Width 0000 = L 15m, W 11.5m0001 = L 15m, W 23m0010 = L 25m, W 28.5m0011 = L 25m, W 34m0100 = L 35m, W 33m0101 = L 35m, W 38m0110 = L 45m, W 39.5m0111 = L 45m, W 45m1000 = L 55m, W 45m1001 = L 55m, W 52m1010 = L 65m, W 59.5m1011 = L 65m, W 67m1100 = L 75m, W 72.5m1101 = L 75m, W 80m1110 = L 85m, W 80m1111=L>85m,W>80m(ADS-B)FMS Surveillance Integrity Limit 00 = Unknown01 = e-310 = e-511 = e-7Recommend: 00 (Unknown) (ADS-B)GPS Surveillance Integrity Limit 00 = Unknown01 = e-310 = e-511 = e-7Recommend: 10 (e-5) (ADS-B)GPS Time Mark Source 00 = No GPS Time Mark01 = Single GPS Time Mark Only10 = Dual GPS Time Mark11 = Not Used(ADS-B)Position Offset Applied 1 = Position Offset applied0 = No offset appliedRecommend: 0 (No offset) (ADS-B)Allow/Disallow Use of GPS fromConcentrator1 = Disallow use of GPS data from IAPSbus0 = Allow use of GPS data from IAPSbussesCross-side XPDR Installed 1 = Installed 0 = Not Installed (TCAS)Dual or Triple AHRS 1 = Triple 0 = DualADLP Installed 1 = ADLP Installed0 = ADLP Not InstalledRecommend: 0 (Not Installed) (XPDR)Bus Speed LMP-1DC (Control A Input) 1 = High Speed0 = Low SpeedBus Speed LMP-7DC (Control B Input) 1 = High Speed0 = Low SpeedBus Speed RMP-1DC (Control C Input) 1 = High Speed0 = Low Speed2-12
system components 523-0809018Table 2-2. ECU Installation Strapping Data. - ContinuedDescription Values Recommend (Function Using Setting)Bus Speed LMP-8HG (IAPS #1 Input) 1 = High Speed0 = Low SpeedBus Speed RMP-8HG (IAPS #2 Input) 1 = High Speed0 = Low SpeedBus Speed RMP-8AB (XT2 (XPDR toTSS) or ADLP Input)1 = High Speed0 = Low SpeedBus Speed RMP-8DC (TX2 (TSS toXPDR) or ADLP Output)1 = High Speed0 = Low SpeedBus Speed LMP-1EF (TA/RA-1 Output) 1 = High Speed0 = Low SpeedBus Speed RMP-1EF (TA/RA-2 Output) 1 = High Speed0 = Low SpeedBus Speed LMP-7AB (TSS-1 Output) 1 = High Speed0 = Low SpeedBus Speed LMP-1AB (TSS-2 Output) 1 = High Speed0 = Low SpeedBus Speed RMP-1AB (TSS-3; DataLoad Output)1 = High Speed0 = Low SpeedBus Speed LMP-7JK (Data Load Input) 1 = High Speed0 = Low SpeedBus Speed LMP-6HG (GPS #1 Input) 1 = High Speed0 = Low SpeedBus Speed RMP-2HG (GPS #2 Input) 1 = High Speed0 = Low SpeedBus Speed LMP-7EF (ADS-B #1 InputProvision)1 = High Speed0 = Low SpeedBus Speed LMP-7HG (ADS-B #2 InputProvision)1 = High Speed0 = Low SpeedBus Speed LMP-9EF (ADS-B #1 OutputProvision)1 = High Speed0 = Low SpeedBus Speed LMP-8JK (CMU #1 Input Provision)1 = High Speed0 = Low SpeedBus Speed RMP-8JK (CMU #2 Input Provision)1 = High Speed0 = Low SpeedBus Speed RMP-9EF (CMU Output Provision)1 = High Speed0 = Low Speed2-13
system components 523-0809018Table 2-2. ECU Installation Strapping Data. - ContinuedDescription Values Recommend (Function Using Setting)Bus Speed RMP-7DC (A768 FutureInput Provision)1 = High Speed0 = Low SpeedBus Speed LMP-9DC (General Purpose#1 Provision Output)1 = High Speed0 = Low Speed2.6.4. ECU-3000 Illustration.Refer to Figure 2-4 for an illustration of the ECU-3000.Figure 2-4. ECU-30002.6.5. ECU-3000 Mating Connector Data.NOTEThe wiring to the ECU should be done with three twisted shield pairs and one twisted shield triple.Figure 2-5 shows a mating connector pictorial for the ECU-3000. Each connector shows pin locations to aid the troubleshootingeffort. Also refer to the interconnect wiring diagram in the appendix.2.6.5.1. Table 2-3 shows the mating connector hardware and tooling for the ECU-3000.Table 2-3. ECU-3000 Mating Connector Hardware and Tooling.ECU-3000 HARDWARE/TOOLINGMating connector: MIL MS27484T10F35S, Collins 359-0645-020Contacts: MIL M39029/57-354, Collins 359-0608-110Strain relief: MIL M85049/49-2-10N, Collins 859-6604-110Insertion/extraction tool: MIL M81969/14-01, Collins 359-8032-010Crimp tool: MIL M22520/2-01, Collins 359-8102-010Crimp tool positioner: MIL M22520/2-06, Collins 359-8102-0602-14
system components 523-0809018Figure 2-5. ECU-3000 Mating Connectors2.6.6. ECU-3000 Outline and Mounting Dimensions.Refer to Figure 2-6 for an illustration of the ECU outline and mounting dimensions.2-15/(2-16 Blank)
system components 523-0809018Figure 2-6. ECU-3000 Outline and Mounting Dimensions2-17/(2-18 Blank)
system components 523-08090182.6.7. Installation and Removal.Make sure that the aircraft battery master switch is turned off before installing any equipment, mounts, or inter-connect cables. Failure to do so can damage the equipment.The unit should be mounted on a vertical surface. Other mounting orientations may be acceptable upon confir-mation by engineering. Mounting on a horizontal surface with the connector facing up is not acceptable, and cancause operational failure or damage to the ECU due to water that does not drain out.For installations with a TSS, the maximum length of each wire between the TSS and the ECU should be one meterto avoid potentially damaging currents.NOTERefer to the ECU-3000 outline and mounting diagram Figure 2-6 for further instructions. Refer to Table 2-3 forspecific mating connector and contact information.The installation and removal instructions for the ECU-3000 follow.2.6.7.1. Installation. The ECU-3000 is designed to stay with the aircraft during a TSS-4100 removal. The ECU-3000 is designedto be secured to a vertical surface of the aircraft frame. Instructions for installing the unit are as follows:a. Remove aircraft power.b. Secure the ECU to the mounting surface with two mounting screws.c. Connect the mating connector cable assembly to the unit connector.2.6.7.2. Removal. The procedure to remove the ECU-3000 follows:a. Remove aircraft power.b. Disconnect the mating connector cable assembly from the unit connector.c. Remove the two mounting screws that secure the ECU to the mounting surface.2.6.8. Internal Theory of Operation.The ECU-3000 is used to store aircraft specificconfiguration data. The ECU has two halves in which it stores data. The top halfis programmed by Rockwell Collins to enable basic functionality of the TSS. The bottom half is programmed by the aircraft manu-facturer. There are two partitions of this bottom half. The first partition contains all of the aircraft specific transponder, TCAS, andADS-B strapping information. The second partition contains the aircraft Mode S address.2-19/(2-20 Blank)
system components 523-08090182.7. TDR-94D 34-54-00.The sections that follow describe the external theory of operation, internal theory of operation, and general data of the Mode Stransponder in a traffic surveillance system.2.7.1. Mode S Transponder, External Theory of Operation.NOTEThe term CONTROLLER refers to any transponder control unit, such as an Radio Tuning Unit (RTU), a Transpon-der Control (CTL), or a Control Display Unit (CDU). Buses and discretes are followed in parentheses by the spe-cific bus name shown in the example illustration, Figure 2-7.Refer to Figure 2-7. This sheet shows a typical transponder system, and the external signals to and from the Transponder (TDR).Operating power is derived from the +28 V dc avionics triple-fed bus supply.2.7.1.1. The TDR is controlled by an ARINC standard transponder controller such as an RTU or a CDU. A controller provides thetransponder state (STANDBY, ALTITUDE REPORTING OFF, ALTITUDE REPORTING ON), the flight ID, the squawk code, theselected altitude, and TCAS control data.2.7.1.2. Either two or three ARINC 429 low-speed control busses may be routed to the TDR containing control and altitude data.The on-side data comes to Control Port B. The cross side data comes to Control Port A. An optional back up third controller comesto Control Port C. The microprocessor reads the discrete (RTU PORT A/B SELECT, P2-57) and selects the active port. Normally,port B is selected and the TDR is tuned by the on-side controller (RTU). When the reversion switch (RTU1 INHB) is set to inhibit, aground is applied to pin P2-57, which selects port A of the right side controller (RTU) tune data. When the reversion switch (RTU2INHB) is also set to inhibit, a ground (BURST TUNE ENABLE) is applied to pin P2-59, which selects port C (IAPS) burst tunedata.2.7.1.3. The TCAS/transponder cross talk busses (TSS-TX and TDR-XT busses) are used for coordination between the TCASfunction of the TSS and the TDR.2.7.1.4. The Mode S address is set by rear connector strapping (P1-33 through P1-56) and is unique for each aircraft.2.7.1.5. The main transponder output bus (TDR-1) outputs maintenance data and echoes selected control data.2.7.1.6. The TDR-94D operates with two antennas to provide traffic air-to-air capability. The 1030 Hz interrogation input isreceived on either or both L-band antennas, low-pass filtered, and applied through diversity and transmit/receive switches to thefront-end receiver. The diversity switch is not used in receive mode. The transmit/receive switch connects the antennas to the re-ceiver (not the transmitter) in receive mode.2.7.1.7. The TDR responds to Air Traffic Control Radar Beacon System (ATCRBS) and Mode S All-Call interrogations.2.7.1.8. The TDR also responds to selective Mode S interrogations. These interrogations use the transponder Mode S address.This mode allows the air traffic controller to identify each aircraft by tail number. It is also used by the traffic surveillance systemfor air-to-air communication with a cooperating aircraft.2.7.1.9. A suppression pulse (P1-29) is generated while the TDR is transmitting a response to an interrogation. This pulse isintended to inhibit the receivers in other L-band radios, such as the TSS and the DME. These other radios also generate a suppressionpulse while they are transmitting. While this is active the TDR will inhibit its replies.2-21/(2-22 Blank)
system components 523-0809018Figure 2-7. Mode S Transponder, TDR-94D, External Theory of Operation2-23/(2-24 Blank)
system components 523-08090182.8. MODE S TRANSPONDER, TDR-94D, DATA.The TDR-94D is a Mode-A, Mode-C, and Mode-S diversity (two antenna) transponder.2.8.1. TDR-94D ATC/Mode S Transponder Mounting Considerations.The TDR-94D transponder is mounted on the MMT-150 Modular Mounting Tray, CPN 622-9672-XXX. Piggyback mounting brack-ets are available to mount an MMT-150 Modular Mounting Tray over another MMT-150 Modular Mounting Tray. Refer to the ProLine II Installation Manual (CPN 523-0772719) for additional information.2.8.2. TDR-94D Illustration.Refer to Figure 2-8 for an illustration of the TDR-94D.Figure 2-8. TDR-94D2.8.3. TDR-94D Mating Connector Data.Figure 2-9 shows a mating connector pictorial for the TDR-94D. Each connector shows pin locations to aid the troubleshootingeffort. Refer to Figure 2-11 for internal signals for the TDR-94D. Also refer to the interconnect wiring diagram in the appendix.Table 2-4 shows the mating connector hardware and tooling for the TDR-94D.Table 2-4. TDR-94D Mating Connector Hardware and Tooling.TDR-94D HARDWARE/TOOLINGMating connector kit: CPN 628-8661-001 (qty 2)Connector: 60-pin Thinline II, CPN 634-1112-001Contacts: CPN 372-2514-110 (insulation up to 1.27 mm (0.050 in) diameter)Contacts: CPN 372-2514-180 (insulation from 1.27 mm (0.050 in) to 2.03 mm (0.080 in) diameter)TNC connector: Automatic 301-T2100N, CPN 357-7351-010 (qty 2)Tooling **Thinline II Connector Tooling:Insertion tool: Daniels DAK-188, CPN 359-0697-050Extraction tool: Daniels DRK-188, CPN 359-0697-060Crimp tool: Daniels GMT-221, CPN 359-0697-010Coax extraction tool: Cannon CET-C6B, CPN 370-8040-030Coax crimp tool: MIL M22520/5-01, CPN 359-8103-010Crimp tool positioner: Daniels Y142, CPN 359-8103-0502-25
system components 523-0809018Figure 2-9. TDR-94D Mating Connectors2.8.4. TDR-94D Outline and Mounting Dimensions.Refer to Figure 2-10 for an illustration of the TDR outline and mounting dimensions.2-26
system components 523-0809018Figure 2-10. TDR-94D Outline and Mounting Dimensions2-27/(2-28 Blank)
system components 523-08090182.8.5. Installation and Removal.Make sure that the aircraft battery master switch is turned off before installing any equipment, mounts, or inter-connect cables.The installation and removal instructions for the TDR-94D follow.2.8.5.1. Installation. The procedure to install the TDR-94D follows:a. Remove electrical power from the aircraft.b. Install the MMT-150 Modular Mounting Tray and connector kit according to the procedures printed in the Pro Line II Installa-tion Manual (CPN 523-0772719).c. Install and orient the mating connector keyway pins, (part of the mating connector kits). If installing systems on multipleaircraft, similar orientation of the keyways is advisable for quick maintenance removal and replacement.d. Verify all interconnect wiring before proceeding. Verify input power is applied to appropriate pins only.e. Remove aircraft power and slide TDR-94D ATC/Mode S Transponder into mount until mating connector is fully engaged.f. Position knurled knobs on front of mount to engage unit-mounting projections and tighten knurled knobs.g. Push on the front panel to make sure that the unit is fully seated in the mount. Retighten the knurled knobs until the unit issecure in mount.h. Make sure a good electrical bond exists between the unit and mount.i. Install safety wire.2.8.5.2. Removal. The procedure to remove the TDR-94D follows:a. Remove electrical power from the aircraft.b. Remove the safety wire.c. Loosen the knurled knobs that secure the unit to the mount.d. Pull TDR-94D ATC/Mode S Transponder from mount.2.8.6. Internal Theory of Operation.Refer to Figure 2-11. When active, the TDR responds to valid ATCRBS radar interrogations with a coded identificationinMode-Aor reporting altitude in Mode-C reply. The response code is selected on the controller.2.8.6.1. The TDR consists of a main microprocessor, serial and discrete I/O interfaces, a 1030 MHz receiver, an interrogationprocessor, and a 1090 MHz transmitter. Operating power is derived from the +28 V dc avionics triple-fed bus supply. This input isfiltered and applied through an internal breaker to the low-voltage power supply. This supply generates internally required low-levelvoltages, and feeds the high-voltage power supply. A voltage monitor reports power supply integrity to the microprocessor.2.8.6.2. Refer to Figure 2-11. The main microprocessor uses a 16-bit bidirectional data bus to control unit operation. An addresslatch and a data transceiver provide the interface between the processor and internal circuits. This processor controls all I/O datatransfer, monitors key internal power levels, programs the frequency synthesizer, generates high-voltage supply disable logic, andshares data with the dedicated video processor through a dual-port Random Access Memory (RAM). The processor also directlymonitors the temperature of the transmit modulator. If temperature becomes excessive, data is latched that toggles a discrete toinhibit the high-voltage power supply.2.8.6.3. The I/O interface circuits consist of three input UARTs, two discrete input buffers, and two output UARTs. The mainmicroprocessor accesses each circuit using the bidirectional data bus (DB0-DB15).2.8.6.4. ARINC 429 low-speed data buses are received and applied to the RTU multiplexer. The microprocessor reads the PORTA/B select discrete and selects the active port. The RTU multiplexer supplies control data from the selected port, A or B, throughan input UART to the microprocessor.2.8.6.5. The second input UART is reserved for two Air Data Computer (ADC) air data input buses.2-29
system components 523-08090182.8.6.6. The data bus input through an ARINC 429 high-speed receiver to the third input UART is read from the UART by themicroprocessor.2.8.6.7. The processor reads the discrete inputs through two buffer circuits. The first buffer provides the input port A/B selectlogic, strut switch logic, source identification logic, maximum airspeed logic, altitude input logic, and TCAS installed logic.2.8.6.8. Parallel data is output from the microprocessor to the output UARTs. Both UARTs are enabled by the processor to decodeand transmit serial data.2.8.6.9. The TDR is interrogated by the 3-pulse Side-Lobe-Suppression (SLS) method. The TDR-94D operates with one antennato provide TCAS air-to-air capability. The 1030-MHz interrogation input is received on the L-band antenna, low-pass filtered,and applied through the transmit/receive switch to the front end receiver. The transmit/receive switch connects the antennas to thereceiver, but not the transmitter, in receive mode.2.8.6.10. The front end receiver is a dual 1030-MHz bandpass filter that rejects images and spurious responses. The two filteredrf inputs are then independently mixed with a 1090-MHz injection frequency from the synthesizer. This local oscillator frequency isprogrammed by the microprocessor using latched data, clock, and enable logic. The two resultant 60-MHz if signals are amplifiedand applied to the Differential Phase Shift Keying (DPSK) detector and the video processor.2.8.6.11. The DPSK detector is a part of the receiver circuit that senses phase reversals present in mode-S interrogations. TheDPSK detector outputs are applied to the Pulse Amplitude Modulation (PAM) decoder. The video processor monitors the receivedsignal strengths and generates video signals to the PAM decoder.2.8.6.12. The PAM decoder and a dedicated video microprocessor function together as an interrogation processor. This circuitprocesses the video inputs to determine if the received interrogation is a valid ATCRBS or Mode-S interrogation. If a responseis required, the processor determines if the top or the bottom antenna should be used for the reply. The processor then enables thetransmit mode and generates the proper response. The TCAS generated collision avoidance transmit data is input to the interrogationprocessor through the dual port RAM.2.8.6.13. When transmit mode is enabled by the interrogation processor, INT SUPRN logic activates the suppression amplifier andXMT ENBL logic activates the transmit enable driver. During transmit mode, the suppression amplifier momentarily inhibits otherL-band units, described in a later paragraph. During transmit mode, the enable driver closes the transmit/receive switch. This isolatesthe receiver and connects the transmitter to the selected antenna. The interrogation processor generates the ATCRBS or Mode-Sreply output and top/bottom antenna select logic. This response is applied through a multiplexer to the rf transmit modulator.2.8.6.14. The 1090-MHz transmitter circuit consists of an rf modulator and a power amplifier. The rf modulator receives operatingpower from the high-voltage power supply. This power supply provides the voltage levels required for L-band transmission. Acurrent monitor disables both the rf modulator and the High-Voltage (HV) supply if the current draw or power output becomesexcessive. An HV power monitor provides a high-power monitor output through a buffer to the main microprocessor.2.8.6.15. The reply output from the interrogation processor controls the modulator bias applied to the power amplifier. The poweramplifier is driven by a 1090-MHz CW signal generated by the synthesizer. The ON/OFF BIAS from the modulator causes thepower amplifier to generate a corresponding pulse train output, at the 1090-MHz drive frequency. This rf reply output is a series ofpulses, the number and spacing of which is determined by the ATC code plus a trailing IDENT pulse, if selected, and the operatingmode. The pulse transmission is applied through the closed transmit/receive switch and radiated out the antenna. The transmit signalis sampled by a forward power monitor, which provides a low-power monitor output through a buffer to the processor.2.8.6.16. A suppression amplifier generates a blanking pulse output when the interrogation processor selects transmit mode.2-30
system components 523-0809018Figure 2-11. Mode S Transponder, TDR-94D, Internal Theory of Operation2-31/(2-32 Blank)
system components 523-08090182.9. TRE-930 34-54-00.The sections that follow describe the external theory of operation, internal theory of operation, and general data of the TRE L-BandOmnidirectional Antenna in the traffic surveillance system.2.9.1. TRE-930 L-Band Directional Antenna, External Theory of Operation.Refer to the TSS External Simplified Schematic Figure 2-19. This sheet shows the external wire signals to and from the TRE-930and the TSS-4100. The TRE-930 antenna is a single, non-repairable unit. When used with the TSS-4100, the TRE-930 antennamounts only on the bottom of the aircraft. There are no operator controls or adjustments on this antenna.2.10. ANTENNA, TRE-930, DATA.NOTEIf the TRE-930 or any other omni-directional antenna is used, the option for antenna monitoring in the aircraftconfiguration portion of the ECU must be enabled. The TSS uses antenna monitoring to determine that there isonly a single connection on the bottom of the aircraft. If antenna monitoring is off, the TSS will assume thatthere is a directional antenna on the bottom of the aircraft. If antenna monitoring is off, any TSS antenna port notconnected to an antenna may cause a failure of the TSS transmitter or receiver.The TRE is an L-band omnidirectional antenna. The TRE radiates and receives L-band signals in an omnidirectional pattern.2.10.1. TRE-930 Illustration.Refer to Figure 2-12 for an illustration of the TRE-930.Figure 2-12. TRE-9302-33
system components 523-08090182.10.2. TRE-930 Mating Connector Data.Table 2-5 shows the mating connector hardware and tooling for the TRE-930. Also refer to the interconnect wiring diagram in theappendix.Table 2-5. TRE-930 Mating Connector Hardware and Tooling.TRE-930 HARDWARE/TOOLINGRF connector 90° TNC for ECS cable 311201: CPN 857-1502-020 (CTS122), Vendor Ref VC-8,RF connector straight, TNC for ECS cable 311201: CPN 857-1502-010 (CTR122), Vendor Ref VC-8RF connector, straight, TNC for RG-142: CPN 357-9666-000RF connector, 90°, TNC for RG-142: CPN 357-9664-000RF grounding gasket: CPN 018-1394-1102.10.3. TRE-930 Outline and Mounting Dimensions.Refer to Figure 2-13 for an illustration of the TRE-930 Outline and Mounting Dimensions.2-34
system components 523-0809018Figure 2-13. TRE-930 L-Band Antenna, Outline and Mounting Dimensions2-35/(2-36 Blank)
system components 523-08090182.10.4. Omni-Directional Requirements.If a different antenna is used instead of a TRE-930, there are requirements to be compatible with the TSS-4100. There are alsorequirements to facilitate certification with a TCAS/transponder system.2.10.4.1. The requirements of an antenna to replace the TRE-930 for use with the TSS-4100 follow:• It must have a DC impedance of 50 .• It must have continuous power at a minimum of 50 W.• It must have peak power at a minimum of 4 kW.• Itmustbecertified to work at a minimum of the maximum altitude of the aircraft.2.10.4.2. The recommended requirements to facilitate the certification of the TCAS, transponder, and related antenna system onan aircraft are below:• It is recommended that the system be certified as operational, at a minimum, between -55 and 80 ºC.• It is recommended that the system have a Voltage-Standing Wave Ratio (VSWR) of 1.5 to 1 or less, for 1000 to 1100 MHz.• It is recommended that the system be compliant with TSO-C119. Specifically, it is recommended that the antenna comply withthe requirement in Section 2.2.4.7.2.1 of DO-185A. This requires that the gain of an omnidirectional wave pattern not be lessthan the gain of a matched quarter-wave stub, minus one dB, over 90% of a coverage volume from 0 to 360 degrees in azimuth,and -15 to +20 degrees in elevation.2.10.5. Installation and Removal.Make sure that the aircraft battery master switch is turned off before installing any equipment, mounts, or inter-connect cables.The installation and removal instructions for the TRE-930 follow.2.10.5.1. Installation. The procedure to install the TRE-930 follows:a. Make sure that the cabling to the TSS-4100 is correct before proceeding.b. Connect the connector to the TRE-930 antenna and position the antenna on the fuselage.c. Secure with four mounting screws.d. Apply any weather or aerodynamic strip of sealant to the periphery of the antenna and shape as necessary.2.10.5.2. Removal. The procedure to remove the TRE-930 follows:a. Remove sealant around periphery of the TRE-930 antenna.b. Remove the four screws from the antenna and do not allow the antenna to hang from the cable.c. Disconnect the connector from the antenna.2-37/(2-38 Blank)
system components 523-08090182.11. TSA-4100 34-54-00.The sections that follow describe the external theory and general data of the directional Traffic Surveillance Antenna (TSA) in theTraffic Surveillance System.2.11.1. Traffic Surveillance Antenna, External Theory of Operation.Refer to Figure 2-18 for a simplified block diagram that includes this antenna. The TSA-4100 Antenna acts both as an omni and adirectional antenna at 1030 MHz & 1090 MHz at +/- 3 MHz for the Traffic Surveillance System. It has four passive antenna elementsfor directionality and is mounted on the outside of the aircraft fuselage. The upper antenna must be the TSA-4100 directional antenna.The lower antenna can be another TSA-4100 directional antenna or it can be an omnidirectional antenna. The return loss for eachconnector is less than or equal to -12.5 dB. Meeting the MOPS requirements for TSO-C112 and TSO-C119b, the antenna is verticallypolarized. The TSA-4100 meets all lightning protection requirements for Zone 1A on an aluminum ground plane.2.12. ANTENNA, TSA-4100, DATA.The TSA is Mode S directional antenna. The number 1 TSA is mounted on the top of the aircraft. The optional number 2 TSAis mounted on the bottom of the aircraft. For the TCAS function of the TSS, the TSA is directional, which allows the system tocompute bearing to a target aircraft. For the transponder function of the TSS, the TSA acts as an omnidirectional antenna.2.12.1. TSA-4100 Illustration.Refer to Figure 2-14 for an illustration of the TSA-4100.Figure 2-14. TSA-4100, Short and Long Connectors2.12.2. TSA-4100 Outline and Mounting Diagram.NOTEThere are two versions of connectors on the TSA. One version of TSA has longer connectors, the other versionhas shorter connectors. Refer to Figure 2-15 for connector lengths.Refer to Figure 2-15 for outline and mounting diagrams of the TSA-4100 with long connectors. Refer to Figure 2-16 for outline andmounting diagrams of the TSA-4100 with short connectors.2-39/(2-40 Blank)
system components 523-0809018Figure 2-15. TSA-4100 Outline and Mounting Diagram, Long Connector Version (Sheet 1 of 2)2-41/(2-42 Blank)
system components 523-0809018Figure 2-15. TSA-4100 Outline and Mounting Diagram, Long Connector Version (Sheet 2 of 2)2-43/(2-44 Blank)
system components 523-0809018Figure 2-16. TSA-4100 Outline and Mounting Diagram, Short Connector Version (Sheet 1 of 2)2-45/(2-46 Blank)
system components 523-0809018Figure 2-16. TSA-4100 Outline and Mounting Diagram, Short Connector Version (Sheet 2 of 2)2-47/(2-48 Blank)
system components 523-08090182.12.3. TSA-4100 Mating Connector Data.Table 2-6 shows the mating connector hardware and tooling for the TSA-4100. Also refer to the interconnect wiring diagram inFigure E-1.Table 2-6. TSA-4100 Mating Connector Hardware and Tooling.TSA-4100 HARDWARE/TOOLINGRF connector, TNC for RG-142, qty 4 required: CPN 357-9664-000, Mil M39012/30/0101RF connector, straight, low loss for ECS cable: CPN 857-1502-010RF connector 90 degrees low-loss for ECS cable: CPN 857-1502-020Silicon rubber plug (qty 4): CPN 676-3291-002O-ring: CPN 841-0004-0302.12.4. Cabling Considerations.The recommended cable for use between the TSS-4100 and the TSA-4100 is ECS 311201. Information for RG-142/U has also beenprovided in the following table, but no testing has been done with the TSS using this cable. The maximum allowable loss betweenthe TSS and its antennas is 3.0 dB. Refer to the values below. The maximum length of the cables is calculated by dividing 3.0 dBby the Loss Factor.Cable Type Collins P/N Delay Loss Factor Max LengthECS 311201 858-5804-010 1.26 ns/ft 0.0589 dB/ft 15.5 m (51 ft)RG-142/U Not Available 4.6 ns/ft 0.13 dB/ft 7.0 m (23 ft )2.12.4.1. The ECU contains settings based on the type and length of cable used (refer to Table 2-2). The antenna coaxial-cableloss is calculated by multiplying the loss factor of the cable used by the length of the cable. The coaxial cable delay is calculated bysubtracting the amount of delay from the antenna that is closer to the TSS from the amount of delay from the antenna that is furtheraway from the TSS. The cable delay sign bit is simply a way to determine which antenna is further away from the TSS. Adding thedelay to the bottom antenna means that the bottom antenna is closer to the TSS.2.12.4.2. The TSA-4100 directional antenna requires four antenna cables. Unlike other TCAS antennas, the TSA-4100/TSS-4100combination does not require the four cables to be in phase. The requirements for the four cables are:• They are of the same type.• They are within .3 m (12 in) of length of each other (so cable delay difference between the cables is minimized).• They are within 0.5 dB of loss of each other (including loss due to the connectors. This is so the Coaxial Cable Loss is the samefor all of the cables to the same antenna).2.12.5. Installation and Removal.Make sure that the aircraft battery master switch is turned off before installing any equipment, mounts, or inter-connect cables.One TSA-4100 Traffic Surveillance Antenna is mounted on top of the fuselage and the second antenna, either another TSA-4100 oran omnidirectional antenna, is mounted on the bottom of the fuselage. All antennas should be mounted in a location that keeps theinterconnecting coaxial cables as short as practicable.2.12.5.1. Antenna Placement. One TSA-4100 is mounted on top of the aircraft fuselage. Another TSA-4100 or an omnidirec-tional antenna is mounted on the bottom.2-49
system components 523-08090182.12.5.1.1. Place the antennas, especially the top antenna, as forward as possible on the aircraft fuselage. Make sure there are asfew obstructions as possible between the antenna and the front of the aircraft.2.12.5.1.2. Make sure that the lateral deviation between the top and bottom antenna is less than 25 feet. This is to make sure thatboth antennas receive and reply to an interrogation at about the same time.2.12.5.1.3. Separate the antennas as much as possible from other antennas. The minimum distances from a TSS or TDR antenna,to another type of antenna, are specified below:• To an ADF antenna, 2 feet• To a VHF antenna, 5 feet• ToanL-bandantenna,30inches(approximately20dBisolation).NOTEOther L-band antennas include the DME, TDR, and TSS antennas.2.12.5.1.4. Make sure that the tilt angle both in the longitudinal and in the latitudinal directions are as close to parallel to thehorizon as possible. Refer to Figure 2-17 for limitations on mounting the antenna.2-50
system components 523-0809018Figure 2-17. TCAS Directional Antenna, Mounting Diagram2-51
system components 523-08090182.12.5.2. Installation. To install a directional antenna, follow the steps below:a. Make sure all interconnect cabling is correct before continuing.b. Inspect the aircraft skin surface at the mounting location for dirt and corrosion. Clean as necessary.c. Install an O-ring, CPN 841-0004-030, in the groove on the bottom of the antenna.d. Connect the appropriate cable to the color-coded J1, J2, J3, and J4 of the antenna, then position the TSA-4100 Antenna.• J1–Yellow• J2–Black•J3–Blue•J4–Red.e. Use four mounting screws to secure the antenna. Stainless-steel socket head-cap screws are recommended. Zinc, cadmium-plated, or aluminum-alloy screws are not recommended.f. Tighten the screws to almost contact with the bearing surface, and then torque to 25 ±5 lb in.g. Apply any weather/aerodynamic fillet of sealant to the periphery of the antenna, and shape it as necessary. The height of thebead should not exceed 2.5 mm (0.1 in).h. Install the four foam-rubber plugs, CPN 676-3291-002, in the antenna mounting holes. Push them down below the antennasurface. Cover the plugs with a layer of Dow Corning gray RTV-3145 (CPN 005-1531-010, or three 3 oz collapsible tubes, orCPN 005-2531-030 for one 11 oz cartridge), or equivalent sealant. Feather sealant over mounting holes and remove any excesssealant.2.12.5.3. Removal. To remove a directional antenna, follow the steps below:a. Remove the sealant from mounting holes and around periphery of the TSA-4100 Antenna.b. Remove the foam plugs from the antenna mounting holes.c. Remove the four mounting screws from the antenna. Do not allow the antenna to hang from cables.d. Disconnect connectors P1, P2, P3, or P4 from the antenna.2-52
system components 523-08090182.13. TSS-4100 34-43-00.The sections that follow describe the external theory of operation, internal theory of operation, and general data of the Traffic Surveil-lance System LRU in a traffic surveillance system.2.13.1. Traffic Surveillance System, External Theory of Operation.Refer to Figure 2-18 and Figure 2-19. A transponder provides air traffic control and other aircraft with appropriate information aboutits own aircraft. When interrogated, the transponder may provide an aircraft’s current altitude, squawk code (4096 code), or otherinformation that is requested. The TSS receives this information through ARINC 429 messages that are routed through the aircraftswiring. Other A429 signals that are received by the TSS are used to control the transponder and TCAS functions.2.13.1.1. A pilot may put his own aircraft’s transponder into one of three modes: standby, on with altitude reporting off, or onwith altitude reporting on. TCAS may also be put into one of three modes: standby, TA Only, or TA/RA. TCAS interrogates thetransponders of other aircraft to gather the altitude, range, relative speed, and bearing of those aircraft. The altitude, range, andbearing information is then passed along to a display so that it can be shown to the pilots.2.13.1.2. If TCAS determines that one of those other aircraft is going to be a potential threat, then it issues a TA (Traffic Advisory).This is noted by a TRAFFIC, TRAFFIC aural and a visual annunciation on the display. The icon representing the offending aircraftis changed as well.2.13.1.3. If TCAS believes that a collision is possible, it will issue an RA (Resolution Advisory). This resolution advisory willadvise the pilot to climb, descend, or maintain the current vertical rate. This information will be related aurally and via a visualannunciation on the display. Again, the icon representing the offending aircraft is changed. If an RA is issued and both aircraft areTCAS equipped, then the TCAS and transponder of both aircraft coordinate which aircraft goes up and which goes down. The TSSmay use either its internal transponder or an external TDR-94D in order to perform this coordination.2.13.1.4. Automatic Dependant Surveillance - Broadcast (ADS-B) allows for traffic information to be made available withoutinterrogations. If enabled, the transponder function of the TSS takes own aircraft position, velocity, track, and flight ID informationand makes it available at a periodic basis for anyone to receive. Either a ground station or another aircraft may read this informationand use it for one of many defined applications. If enabled, a TSS will merge the ADS-B messages it receives with TCAS targetsand send them to a display as one data block.2.13.1.5. The TSM-4100 is a standard 4 Modular Concept Unit (MCU) mount with a fan that can be controlled and monitored.The Traffic Surveillance Mount (TSM) has a discrete line in that turns on and off the fan. The TSM also has a line out which containsa signal wave form that indicates the speed of the fan. The TSS uses this output to determine if the fan has failed by checking thespeed against a predetermined threshold.2-53
system components 523-0809018Figure 2-18. Traffic Surveillance System, External Block Diagram2-54
system components 523-0809018Figure 2-19. Traffic Surveillance System, TSS-4100 No. 1, External Simplified Schematic2-55/(2-56 Blank)
system components 523-08090182.14. TRAFFIC SURVEILLANCE SYSTEM, TSS-4100, DATA.The TSS-4100 Traffic Surveillance System is a major component of an aircraft traffic system. The TSS-4100 operates on 28 V dc.It contains all circuits necessary for computing, transmitting, and receiving functions of the TSS and interfacing with a transponder,antennas, and displays. The TSS LRU and Traffic Surveillance System Application (TSSA) work together to provide TCAS, ModeS transponder, and ADS-B capability in one LRU. The TSS, TSSA, and Traffic Surveillance Mount (TSM) are described in thissection.2.14.1. TSS-4100 Antenna Requirements.The TSS-4100 requires two antennas. One antenna is mounted on the fuselage on top of the aircraft. The other antenna is mountedon the fuselage on the bottom of the aircraft. The top antenna is a TSA-4100 directional antenna. The bottom antenna can either bea second TSA-4100 antenna, or it can be an omnidirectional antenna such as the TRE-930.2.14.2. TSS-4100 and TSM-4100 Illustration.Refer to Figure 2-20 for an illustration of the TSS-4100. Refer to Figure 2-21 for an illustration of the TSM-4100.Figure 2-20. TSS-41002-57
system components 523-0809018Figure 2-21. TSM-41002.14.3. TSS-4100 Mating Connector Data.Figure 2-22 shows a mating connector pictorial for the TSS-4100. Each connector shows pin locations to aid the troubleshootingeffort. Refer to the interconnect wiring diagram in the appendix. Table 2-7 shows the mating connector hardware and tooling forthe TSS-4100.Table 2-7. TSS-4100 Mating Connector Hardware and Tooling.TSS-4100 HARDWARE/TOOLINGMating connector kit: CPN 628-8661-001 (qty 2)Connector: 60-pin Thinline II, CPN 859-3477-510Contacts: Standard Size 22 pins (RADIALL 620200)Contacts: CPN 372-2514-180 (insulation from 1.27 mm (0.050 in) to 2.03 mm (0.080 in) diameter)TNC connector: Automatic 301-T2100N, CPN 357-7351-010 (qty 2)Mating connector: ARINC 600, Cannon BKAD3-67404-55, CPN 370-0501-050Contacts (size 12): Cannon 031-1308-000, CPN 370-0066-090Insertion/extraction tool: Cannon CET 12-4, CPN not assignedCrimp tool: MIL M22520/1-01, CPN 359-8101-010Crimp tool positioner: MIL M22520/1-11, CPN 359-8101-120Contacts (size 16): Cannon 031-1303-000, CPN 370-0066-080Insertion/extraction tool: Cannon CET 16-9, CPN 371-8445-0802-58
system components 523-0809018Table 2-7. TSS-4100 Mating Connector Hardware and Tooling. - ContinuedTSS-4100 HARDWARE/TOOLINGCrimp tool: MIL M22520/1-01, CPN 359-8101-010Crimp tool positioner: MIL M22520/1-02, CPN 359-8101-020Contacts (size 20): Cannon 031-1302-000, CPN 370-0066-070Insertion/extraction tool: Cannon CIET 20HDL, CPN 371-8445-040Crimp tool: MIL M22520/2-01, CPN 359-8102-010Crimp tool positioner: MIL M22520/2-08, CPN 359-8101-080Contacts (size 22): Cannon 030-2259-000, CPN 370-0066-060Insertion/extraction tool: Cannon CIET 22, CPN 371-8445-020Crimp tool: MIL M22520/2-01, CPN 359-8102-010Crimp tool positioner: MIL M22520/2-23, CPN 359-8102-130TNC connector (qty 8): Cannon 349-1046-000, CPN 370-0066-220Contact, coaxial RG-178 (qty 2): Cannon 249-2080-000, CPN 370-0055-1002-59
system components 523-0809018Figure 2-22. TSS-4100 Mating Connectors2.14.3.1. TSS-4100 Mating Connector Pins and Functions follow:Table 2-8. TSS-4100 Mating Connector Pins and Functions, Power, Ground, Suppression.Pin Name Connector Pin+ 28 VDC Power In RBP 2Power Return RBP 32-60
system components 523-0809018Table 2-8. TSS-4100 Mating Connector Pins and Functions, Power, Ground, Suppression. - ContinuedPin Name Connector PinChassis Ground RBP 11Suppression Coax - coaxial insert in thebottom corner of LMPLMP 1TTable 2-9. TSS-4100 Mating Connector Pins and Functions, ARINC 429 Input.Pin Name Connector Pin A Pin BControl A LMP 1D 1CControl B LMP 7D 7CControl C RMP 1D 1CIAPS #1 (on-side) LMP 8H 8GIAPS #2 (cross-side) RMP 8H 8GGPS #1 LMP 6H 6GGPS #2 RMP 2H 2GXT2 (TDR to TSS) (or ADLP) RMP 8A 8BData Load LMP 7J 7KCMU #1 (Provision) LMP 8J 8KCMU #2 (Provision) RMP 8J 8KADS-B #1 (Provision) LMP 7E 7FADS-B #2 (Provision) LMP 7H 7GA768 Future (Provision) RMP 7D 7CTable 2-10. TSS-4100 Mating Connector Pins and Functions, ARINC 429 Output.Pin Name Connector Pin A Pin BTSS-1 LMP 7A 7BTSS-2 LMP 1A 1BTSS-3 (Data Load) RMP 1A 1BTA/RA-1 LMP 1E 1FTA/RA-2 RMP 1E 1FTX2 (TSS to TDR) (or ADLP) RMP 8D 8CADS-B #1 (Provision) LMP 9E 9F2-61
system components 523-0809018Table 2-10. TSS-4100 Mating Connector Pins and Functions, ARINC 429 Output. - ContinuedPin Name Connector Pin A Pin BCMU (Provision) RMP 9E 9FGeneral Purpose #1(Provision)LMP 9D 9CTable 2-11. TSS-4100 Mating Connector Pins and Functions, GPS Time Mark Input.Pin Name Connector Pin + Pin -GPSTimeMark#1(On-side) LMP 9J 9KGPS Time Mark #2(Cross-side)RMP 9J 9KTable 2-12. TSS-4100 Mating Connector Pins and Functions, Discrete Input (Gnd = Active).Pin Name Conn Pin Pin Name Conn PinSpare LMP 2H AdvisoryInhibit #3LMP 11JXTDR Active(from XTDR)LMP 2J AdvisoryInhibit #4LMP 11KExtendedSquitter DisableLMP 2K AdvisoryInhibit #1LMP 10JPerf Limit LMP 3E AdvisoryInhibit #2LMP 10KSimulatorEnableLMP 3F Shop ModeEnableRMP 6AAir/Gnd(F) #1 LMP 3G ATE Discrete In(Spare)RMP 6BSpare LMP 3H TA DisplayVa l i d # 1RMP 10ASpare LMP 3J TA DisplayVa l i d # 2RMP 10BFan Monitor LMP 3K RA DisplayVa l i d # 1RMP 10CSpare LMP 4F RA DisplayVa l i d # 2RMP 10DAir/Gnd(F) #2 LMP 4H Burst TuneSelectRMP 10ESpare LMP 4J Control PortSelect 0RMP 10F2-62
system components 523-0809018Table 2-12. TSS-4100 Mating Connector Pins and Functions, Discrete Input (Gnd = Active). - ContinuedPin Name Conn Pin Pin Name Conn PinClimb Inhibit#1LMP 11A Control PortSelect 1RMP 10GClimb Inhibit#2LMP 11B AdvisoryAnnun CancelRMP 10HClimb Inhibit#3LMP 11C Spare RMP 10JClimb Inhibit#4LMP 11D Data LoadEnableRMP 10KIncrease ClimbInh #1LMP 11E Program PinCommonRMP 11HIncrease ClimbInh #2LMP 11F SourceDestinationIdentifier (SDI)Position 1RMP 11JIncrease ClimbInh #3LMP 11G SDI Position 2 RMP 11KIncrease ClimbInh #4LMP 11HCtrl Port:CtrlPortSel 0CtrlPortSel 1 SDI code:SDIPos 1SDIPos 2Gnd Open Ctrl Bus A Gnd Open Side 1 - LeftOpen Open Ctrl Bus B Open Gnd Side 2 - RightX Gnd Ctrl Bus C Open Open Not UsedGnd Gnd Not UsedTable 2-13. TSS-4100 Mating Connector Pins and Functions, Discrete Output (Gnd = Active).Pin Name Conn Pin Pin Name Conn PinTSS Active (toXTDR)LMP 2E Test Data 1 RMP 6DSpare +28/Open LMP 2F Test Data 2 RMP 6ESpare LMP 2G Test Data 3 RMP 6FVisual Annun C LMP 3A Test Data 4 RMP 6GVisual Annun P LMP 3B Test Data 5 RMP 6HVisual AnnunTALMP 3C Test Data 6 RMP 6JFan Off(100ma)LMP 3D Test Data 7 RMP 6K2-63
system components 523-0809018Table 2-13. TSS-4100 Mating Connector Pins and Functions, Discrete Output (Gnd = Active). - ContinuedPin Name Conn Pin Pin Name Conn PinAural AdvisoryCLMP 4A Test DataAddress 0RMP 7GAural AdvisoryPLMP 4B Test DataAddress 1RMP 7HAural AdvisoryTALMP 4C Test Read RMP 7JTest Data 0 RMP 6C Test Write RMP 7KTable 2-14. TSS-4100 Mating Connector Pins and Functions, Audio Output.Pin Name Connector Pin Hi Pin LoAudio #1 LMP 1J 1KAudio #2 RMP 1J 1KTable 2-15. TSS-4100 Mating Connector Pins and Functions, ECU Interface.Pin Name Connector PinClock Out to ECU LMP 9GPower Out to ECU LMP 10APower Return from ECU LMP 10BSerial Data In from ECU LMP 10CSerial Data Out to ECU LMP 10DWrite Enable #1 Out to ECU LMP 10EEnable #1 Out to ECU LMP 10FWrite Enable #2 Out to ECU LMP 10GEnable #2 Out to ECU LMP 10H2.14.4. TSS-4100 Outline and Mounting Dimensions.Refer to Figure 2-23 for an illustration of the TSS-4100 Outline and Mounting Dimensions. Refer to Figure 2-24 for an illustrationof the TSM-4100 Outline.2-64
system components 523-0809018Figure 2-23. TSS-4100 Traffic Surveillance System, Outline and Mounting Dimensions (Sheet 1 of 3)2-65/(2-66 Blank)
system components 523-0809018Figure 2-23. TSS-4100 Traffic Surveillance System, Outline and Mounting Dimensions (Sheet 2 of 3)2-67/(2-68 Blank)
system components 523-0809018Figure 2-23. TSS-4100 Traffic Surveillance System, Outline and Mounting Dimensions (Sheet 3 of 3)2-69/(2-70 Blank)
system components 523-0809018Figure 2-24. TSM-4100 Traffic Surveillance Mount, Outline (Sheet 1 of 3)2-71/(2-72 Blank)
system components 523-0809018Figure 2-24. TSM-4100 Traffic Surveillance Mount, Outline (Sheet 2 of 3)2-73/(2-74 Blank)
system components 523-0809018Figure 2-24. TSM-4100 Traffic Surveillance Mount, Outline (Sheet 3 of 3)2-75/(2-76 Blank)
system components 523-08090182.14.5. Cabling Considerations.For the TSS-4100:• Shield wires shall be no greater than 4 inches in length.• The wires from the TSS to the ECU shall be no greater than one meter in length.• The SDI strap shall be no greater than 6 inches in length.• The length of the wires from the TSS to the TSM shall be no greater than 18 inches in length.• The circuit breaker for the TSS should be rated for 7.5 Amps.2.14.6. Installation and Removal.Make sure that the aircraft battery master switch is turned off before installing any equipment, mounts, or inter-connect cables.NOTEThe resistance between the TSS-4100 and the rear contact shell and mounting surfaces must not be greater than2.5 milliohms.The TSS-4100 is rack mounted in the TSM-4100.2.14.6.1. Installation. The procedure to install the TSS-4100 follows:a. Remove electrical power from the aircraft.b. Slide the unit into the mount until the mating connectors are fully engaged.c. Position the knurled knobs (on the front of mount) to engage the unit holddown hooks. Tighten the knurled knobs to secure theunit to the mount. Safety-wire the knurled knobs.2.14.6.2. Removal. The procedure to remove the TSS-4100 follows:a. Remove electrical power from the aircraft.b. Remove the safety wire and loosen the knurled knobs that secure the unit to the mount.c. Slide the unit straight out to disconnect it from the mount connectors.2.14.7. Internal Theory of Operation.The TSS-4100 Processing unit provides the main processing, system I/O, and traffic RF functions for the system in an ARINC 600 4MCU Line Replaceable Unit (LRU). The paragraphs that follow outline the functions of the main assemblies. Refer to Figure 2-25for an internal block diagram of the TSS-4100.2.14.7.1. Power Supply Assembly. Power supply assembly develops the primary 12 V dc bus voltage from the 28 V dc aircraftpower. The power supply assembly consists of a power supply circuit card and a storage capacitor assembly which enables theTSS-4100 to continue operating through momentary power interruptions. The power supply assembly supplies +31.6 V dc to thetransmitter module and +12 V dc to the other circuit cards and sub-assemblies of the TSS-4100.2.14.7.2. System Processor Input / Output Assembly. The System I/O Circuit Card (SysIO) controls almost all of the inputand output between the TCAS/transponder function and other aircraft systems. SysIO outputs display data, aural messages, faultinformation, aircraft system discretes, and data logging outputs. SysIO receives data used by the TCAS/transponder card and per-forms most of the source selection logic. SysIO manages the data loading of the unit and of the attached ECU. SysIO is responsiblefor communications with the ECU and for monitoring of an external fan.2.14.7.3. Traffic Receiver Assembly. The traffic receiver assembly consists of three circuit card assemblies, the RF switch,receiver circuits and digital signal processing circuits for the ACAS/transponder function. The RF switch circuit controls the selec-tion function for the top and bottom antennas, antenna element selection and the transmit/receive switch function. There are eight2-77
system components 523-0809018parallel antenna ports, four each for the top and bottom antennas on the aircraft. Each port represents a beam heading: fore, aft,port, starboard. The transmit port from the power amplifier is switched to one of these eight antenna ports. The receiver paths on theRF switch include fixed-gain, low-noise amplifiers and band-pass filtering. Each of the eight antenna ports feeds a separate receiverpath. The receiver circuits down-convert the band-pass filtered L-band frequencies provided through the switch card to intermediatefrequencies, provide additional filtering and provide receiver gain. There are 16 parallel transponder receiver paths; eight each highand low gain. There are four parallel TCAS receiver channels, with switchable high/low gain. These 16 Transponder and four TCASsignals become 20 parallel high speed Analog to Digital Converter channels to the signal processor circuit card. The TSS designalso supports a 5 antenna port installation where top ports one thru four are connected to a directional antenna and bottom port 1 isconnected to an omni-directional antenna. Bottom ports two thru four would not be used in this configuration. The signal processingcircuits correlate and track the replies of Mode S and Mode C transponders for the TSS-4100 TCAS function. The signal processingcircuits use these replies to calculate intruder aircraft range, altitude and bearing. From this calculation, the signal processing circuitsalso develop resolution and traffic advisory data. Resolution Advisories (RA) and Traffic Advisories (TA) are sent to the aural andvisual displays. The signal processing circuits also receive and prepare responses to ATCRBS and Mode S interrogations for theTSS-4100 transponder function.2.14.7.4. Traffic Transmitter Assembly. The traffic transmitter module consists of a modulator circuit card and a power am-plifier circuit card. The Traffic Transmitter Module receives serial frequency tuning data and a set of digital commands from thedigital signal processor that specify the desired pulses to be sent. The modulator circuit card then generates the appropriate ACASDifferential Phase Shift Keying (DPSK) modulation, Mode-C whisper shout, or transponder interrogation output that will be sent tothe ATC/ACAS antenna. The modulator card implements a power control loop so that the drive to the power amplifier is varied toachieve the desired output power. Modulation is produced in a quadrature modulator, allowing amplitude only (pulse), PPM, andthe PSK waveform to be produced. The modulator drive level changes on a 16.667 nsec (60.000 MHz) clock, allowing tight controlof the rise and fall times of the pulse. The power amplifier circuit amplifies the transmit signals before the signals are sent throughthe RF switch to the antenna.2.14.7.5. TSS-4100 Cooling Considerations. Because the TSS-4100 was tested without the TSM-4100 for the loss of coolingtest, the TSS-4100 must be installed with cooling. If the TSM-4100 is not used, equivalent cooling must be supplied or a thermalanalysis of the installation must be done to show that the TSS-4100 will remain within its operating temperature range (-55 to +80degrees C).2.14.7.5.1. If the traffic module of the TSS detects that the transmitter is getting too hot, the TSS-4100 will put itself into standbyand declare itself failed.2-78
system components 523-0809018Figure 2-25. Traffic Surveillance System, TSS-4100, Internal Block Diagram2-79/(2-80 Blank)
523-0809018CHAPTER 3Operation3.1. INTRODUCTION.NOTEThis section is not intended to be a pilot’s guide, but is written to provide a basic knowledge and understanding ofoperating procedures for this system. For detailed data about the controls and displays of a specific airplane, referto the Operator's Guide for that airplane.Line Replaceable Units (LRU) with specific controls and displays are described in this section. However, theTraffic Surveillance System (TSS) can be controlled by any Transponder (TDR) / Traffic Alert Collision Avoid-ance System (TCAS) control unit, and TCAS traffic. Also, Traffic Advisory (TA) / Resolution Advisory (RA)information can be shown by any ARINC 735A standard display.Only basic controls and indicators, plus those related to TRAFFIC operation, are discussed in this manual.This section shows the typical operating controls and displays of a Traffic Surveillance System. Tables describe each control ordisplayinsufficient detail so that the flight-line technician can operate the equipment and troubleshoot the complete system.3.2. GENERAL.This chapter of the Traffic Surveillance System installation manual contains examples and a description of the controls and indicatorslisted below:•Traffic Display on an Adaptive Flight Display (AFD)•RADisplaysonanAFD• Top Level Radio Page on a Radio Tuning Unit (RTU) or a Control Display Unit (CDU)• TCAS Control Page on an RTU or CDU• Transponder Control Page on a CDU or an RTU.3-1
operation 523-0809018Figure 3-1. Traffic Display (AFD-3010/3010E), TRAFFIC Page3-2
operation 523-0809018Table 3-1. Tra ffic Display (AFD-3010/3010E), TRAFFIC Page.CONTROL ORDISPLAY FUNCTION/DESCRIPTIONRefer to Figure 3-1.TRAFFIC map The TSS traffic symbology is available for display on the display. Push the Traffic (TFC) lineselect key to show the TSS traffic overlay on the Horizontal Situation Indicator (HSI), arc,or Present Position (PPOS) Map formats. This map is a dynamic, heading-up pictorial thatshows nearby transponder-equipped aircraft. This screen shows traffic symbols that alert thecrew to potential and predicted collision threats. A traffic only format, along with the standardtraffic overlay option, is available from the PPOS Map using either a LOWER FORMAT orthe TFC line select key. The traffic only format erases all non-trafficsymbols.TRAFFIC RANGERINGSThree range rings provide a distance measuring scale. These rings show distance from theaircraft. Turn the RANGE knob on the Display Control Panel (DCP) to select the desiredfull-scale display range. The outer ring is a full-intensity circle with a tic mark every 30degrees. This ring represents the selected full-scale range. A numeric distance label showsby the outer range ring. The middle ring is a half-intensity circle with a tic mark every 30degrees. This ring marks the half-scale range (not shown when full-scale range is 5 miles).The inner ring consists of (only) tic marks every 30 degrees. This ring normally marks a rangeof 3 miles, but blanks when the full-scale range is more than 25 miles.INTRUDER AIRCRAFT INTRUDER AIRCRAFT are shown with an INTRUDER SYMBOL, Altitude (ALT) DATA,and a VS ARROW.INTRUDER SYMBOL Four kinds of intruder aircraft symbols may show.NOTEIf a Traffic Advisory (TA) or TCAS Resolution Advisory (RA) intruder is detected thatis beyond the selected display range, (only) half of the TA or RA traffic symbol shows.This half-symbol appears on the outer ring at the appropriate bearing.• The cyan open-diamond symbol shows an aircraft that is in the protected air space volume,but is not considered to be a collision threat.• The cyan solid-diamond symbol is a proximate traffic symbol. This symbol shows an aircraftthat is nearby (<1200 feet relative altitude), but not close enough to be considered advisorytraffic.• The yellow solid-circle is a TA traffic symbol. This is a traffic advisory that means the in-truder aircraft is a potential threat.• The red solid-square is an RA traffic symbol. This is a resolution advisory that means theintruder aircraft is an immediate threat. Take corrective or preventive action to maintainminimum air space separation. RA traffic symbols are shown only with traffic.VS ARROW If the vertical trend rate of the intruder is greater than 500 feet per minute, the VS arrowshows. The arrow points up if the intruder is climbing, and down if descending.3-3
operation 523-0809018Table 3-1. Tra ffic Display (AFD-3010/3010E), TRAFFIC Page. - ContinuedCONTROL ORDISPLAY FUNCTION/DESCRIPTIONTRAFFIC MODEDISPLAYThe traffic mode display shows the traffic altitude above/below limits selected, the aircraftaltitude, and other traffic selected off. This window defines a zone of vertical air space relativeto the aircraft. Intruders into this zone are tracked and considered potential threats. Fourselections are possible, and the selected option on the CDU is enlarged.• NORM: The protection window is 2700 feet above and 2700 feet below the aircraft.• ABOVE: The protection window is 9900 feet above and 2700 feet below the aircraft.• BELOW: The protection window is 2700 feet above and 9900 feet below the aircraft.• ABOVE/BELOW: The protection window is 9900 feet above and 9900 feet below the air-craft.When Absolute (ABS) altitude is selected, the airplane absolute altitude shows in hundreds offeet. This field is blank when Relative (REL) altitude is selected.AIRPLANE SYMBOL This symbol is a reference that represents the airplane. This symbol is used to visualize therelative positions of intruder aircraft. The airplane symbol is stationary and always shows inthe center of the screen. Intruder traffic symbols show and move about the screen as longas valid bearing information is received, and the aircraft is within the selected range andrelative altitude window.TRAFFICANNUNCIATORPush the TFC line select key to add or remove the traffic overlay from the arc or presentposition map formats. The selected traffic operating mode annunciates below the TFCannunciator. Select the traffic mode from the TRAFFIC CONTROL page on the CDU orRadio Tuning Unit (RTU). When TA/RA mode is selected, the TFC annunciator field is blank.TA and RA symbols may show. TA/RA mode is inhibited when the aircraft is on the ground.When Standby (STBY) mode is selected, TRAFFIC OFF (or TCAS OFF) annunciates inwhite. When TA mode is selected, TA ONLY annunciates in white (no intruders) or flashesyellow (TA intruder detected). RA symbols are not shown in this mode. TRAFFIC FAIL (orTCAS FAIL) annunciates if the display is not receiving the TRAFFIC bus. TRAFFIC TEST(or TCAS TEST) annunciates when the TSS is in test mode.No bearing table This two line table, shown below the TRAFFIC operating mode, automatically shows whenthe TSS detects an RA or TA intruder, but does not receive valid bearing information. Thistable shows data for the first two TA/RA intruders for which bearing information is notavailable. Each line lists the RA/TA advisory type, distance/altitude, and a VS trend arrow (iftrend is more than 500 feet/minute). The lines are red (RA) or yellow (TA).3-4
operation 523-0809018TPI4301_02222222221111111144444444CLIMBPREVENTIVEDESCENDCORRECTIVEDESCENDPREVENTIVECLIMBCORRECTIVE= RED= GREENFigure 3-2. Resolution Advisory Display (AFD), TCAS II Fly-To Commands3-5
operation 523-0809018TPI4301_032O1O1O2OALTVLNV1APYD VPATH= RED= GREENFigure 3-3. Resolution Advisory Display (AFD), Pitch CuesTable 3-2. Resolution Advisory Display (AFD), TCAS II Fly-To Commands and Pitch Cues.CONTROL ORDISPLAY FUNCTION/DESCRIPTIONRefertoFigure3-2foranillustrationofFly-ToCommandsonanRAVerticalSpeedindicator.RA Fly-To Commands NOTEThe message TRAFFIC shows in red below the vertical speed scale on the PFD when thesystem detects RA traffic. The message shows in yellow below the vertical speed scalewhen the system detects TA traffic.RA vertical speed fly-to commands show on the PFD vertical speed scale when in TA/RAmode and a trafficconflict exists. The fly-to commands show as red and green bands. Tocomply with an RA, avoid flying vertical speeds within the red-banded areas and do flythevertical speeds within the green-banded areas.There are two types of RAs that show on the PFD, preventive and corrective. These aredescribed below:• Preventive RAs are issued for threat traffic for which the TSS has determined current verticalspeed will resolve the threat situation. The vertical speed range to avoid shows in red on thePFD vertical speed scale.• Corrective RAs are issued for threat traffic for which the TSS has determined that correctiveaction needs to be taken to avoid the traffic. The vertical speed range to seek (green) andavoid (red) shows on the PFD vertical speed scale. Aural commands are issued over thecockpit audio system.Refer to Figure 3-3 for an illustration of RA pitch cues on an attitude indicator.3-6
operation 523-0809018Table 3-2. Resolution Advisory Display (AFD), TCAS II Fly-To Commands and Pitch Cues. - ContinuedCONTROL ORDISPLAY FUNCTION/DESCRIPTIONRA Pitch Cues, AttitudeIndicatorThe TCAS Resolution Advisory (RA) pitch cues are shown on the PFD attitude indicator. Thepitch cues advise the pilot of the pitch attitude that is necessary to satisfy a vertical RA.RA cues are issued by the TSS when aircraft corrective maneuvering is required in order toavoid a potential collision. The pitch cues are shown as red avoidance zones and green flytozones. A yellow NO ATT RA message is shown in the TCAS data fieldwhenRApitchcuescannot be computed or if pitch data is not in view on the PFD. The pitch cues are disabledwhen an excessive attitude condition exists. When any data required to compute pitch cues isinvalid, the pitch cues are removed.The two types of RA cues that can be issued by the TSS are preventative and corrective.These are described above.3-7
operation 523-0809018Figure 3-4. Top Level Radio Tuning Page, RTU-42XX Radio Tuning UnitFigure 3-5. Top Level Radio Tune Page, CDU-62XX Control Display Unit3-8
operation 523-0809018Table 3-3. Top Level Radio Tune Page, RTU Radio Tuning Unit or CDU Control Display Unit.CONTROL OR DISPLAY FUNCTION / DESCRIPTIONRefertoFigure3-4forthetoplevelradiotunepageonanRTU.Refer to Figure 3-5 for the top level radio tune page on a CDU.NOTESome of the controls listed are optional and may or may not be included depending onthe installation.LINE SELECT KEYS The RTU and CDU have several panel mounted line select keys. These are used to selectcontrol of individual radio frequencies, presets, codes, and modes.TCAS SUBDISPLAY (RTU) orTCAS MODE DISPLAY(CDU)Displays various TCAS operating modes and selections.TCAS CONTROL PAGEACCESS(CDU only)Push the TCAS line key to view the ATC/TCAS CONTROL page. Refer to Figure 3-7. Theselected TCAS altitude display format ABS (Absolute) or REL (Relative) also shows abovethe TCAS legend.ATC DISPLAY(CDU only)Set the active ATC beacon code by keying the desired beacon code onto the scratch pad line.Then push the ATC line key to transfer this code to the selected field. If the beacon codeis valid, it shows in the data field, and the active transponder immediately responds to thenew beacon code. ALT OFF is shown to the right of the ATC legend when reply Mode A isselected. STBY shows when standby is selected. REPLY shows when the active TDR repliesto an interrogation. IDENT shows when the IDENT line key on the ATC/TCAS CONTROLpage is pushed and the active TDR transmits. The digit to the right of the ATC legend showswhich transponder is active.TUNE WINDOW(RTU only)The tune window surrounds the item selected for control.TUNING KNOBS(RTU only)The tuning knobs are used to set the value shown in the tune window. When a frequency, code,or mode is shown in the tune window, the large tuning knob controls the most significant digits,and the small tuning knob controls the least significant digits.VOLUME KNOB(RTU only)If present, the volume knob is the third (smallest diameter) knob on the knob cluster. As thevolume knob is rotated, a volume scale is displayed adjacent to the selected radio.IDENT KEY(RTU only)Push the IDENT function key to transmit an Air Traffic Control (ATC) identification pulse.When the ident feature is active, ID is shown in cyan on the ATC sub-display and on the ATCmain display page.3-9
operation 523-0809018Figure 3-6. TCAS Page, Radio Tuning Unit (RTU-42XX)Figure 3-7. TCAS Page, Control Display Unit (CDU-62XX)3-10
operation 523-0809018Table 3-4. TCAS Page, Radio Tuning Unit or Control Display Unit.CONTROL ORDISPLAY FUNCTION/DESCRIPTIONNOTESome of the controls listed are optional and may or may not be included depending on theinstallation.Refer to Figure 3-6 for a typical TCAS Page on an RTU.Refer to Figure 3-7 for a typical TCAS Page on a CDU.TCAS CONTROL page Push the TCAS line key on the top level CDU (or RTU) page to select the TCAS CONTROLpage.MODE ANNUNCIATORor MODE SELECT linekeyPush the MODE line key to to toggle through the TCAS modes:•TA/RA(Traffic and Resolution Advisories)• STBY (Standby)• TA ONLY (Traffic Advisories Only).The active mode is shown in cyan and in large letters. Open-diamond traffic is other traffic. RAtraffic, TA traffic, and proximate traffic may still show.ALTITUDE TAGANNUNCIATOR orALTITUDE MODESELECT line keyPush this line select key to toggle between the altitude modes. The available modes are Rela-tive (REL) and Absolute (ABS).TEST ANNUNCIATORand line keyPush the TEST line key to initiate the TSS self-test routines. When self test is active, TEST isannunciated in cyan and in large letters for approximately 10 seconds. When TSS self test isinitiated, the ATC self test is also initiated.NOTEIf an extended test is an option, push and hold the TEST line select key to initiate theextended self test.ALTITUDE LIMITSSELECT line keys andOT WINDOW DISPLAYPush the ABOVE, NORM, or BELOW line key to select the altitude range of the trafficpro-tection window. The active altitude volume limit of Other Traffic (OT) is shown in cyan and inlarge letters.NOTEIf there is no NORM line key between the ABOVE and BELOW line keys (for example,on the RTU shown), then NORM is selected when neither ABOVE nor BELOW are se-lected.The altitude limit defines a volume of vertical air space relative to the aircraft. Intruders into thisvolume are tracked and considered potential threats. When NORM is selected, the protectionvolume is 2700 feet above and 2700 feet below the aircraft. When ABOVE is selected, the pro-tection volume is 9900 feet above and 2700 feet below the aircraft. When BELOW is selected,the protection volume is 2700 feet above and 9900 feet below the aircraft. When ABOVE andBELOW are both selected, the protection volume is 9900 feet above and 9900 feet below theaircraft.3-11
operation 523-0809018Table 3-4. TCAS Page, Radio Tuning Unit or Control Display Unit. - ContinuedCONTROL ORDISPLAY FUNCTION/DESCRIPTIONSELECTIONANNUNCIATOR orTRAFFIC DISPLAYSELECTPush the adjacent line select key to set other traffic (non-threat traffic) monitoring ON (all traffic)or OFF (threat traffic only). The active state is shown in cyan and in large letters.RANGE SELECT (RTUonly)Turn either tuning knob to set the display range. Clockwise rotation selects increasing rangesand counterclockwise rotation selects decreasing ranges. Available range depends on the instal-lation and may be either 6/12, 6/12/20/40, 3/5/10/20/40, or 5/10/20/40 (nmi).3-12
operation 523-0809018Figure 3-8. Transponder Page, RTU-42XX Radio Tuning UnitFigure 3-9. Transponder Page, CDU-62XX Control Display UnitTable 3-5. Transponder Page, RTU Radio Tuning Unit or Control Display Unit.CONTROL OR DISPLAY FUNCTION / DESCRIPTIONFigure 3-8 shows the ATC main display page on an RTU.Figure 3-9 shows the ATC controls on a CDU.3-13
operation 523-0809018Table 3-5. Transponder Page, RTU Radio Tuning Unit or Control Display Unit. - ContinuedCONTROL OR DISPLAY FUNCTION / DESCRIPTIONAT C P ag e ( RT U or C D U ) NOTEIdentical control selections are presented on both RTUs (or on both CDUs) for the ATCtransponder so that either pilot can make transponder control selections.To access the ATC Transponder main display page from the RTU or CDU top level page, pushthe ATC line select key two times. The first push positions the tune window around the ATCcode, and the second push shows the ATC main display page.ACTIVE ATC BEACONCODE ANNUNCIATORTo enter the ATC Ident code from the TUNE page or ATC CONTROL page, enter the desiredcode in the scratchpad.The conditions that follow define a valid beacon code entry:• One to four digits have been entered (i.e., 1 = 0001).• Each digit entered is between 0 and 7 (i.e., 2753, 7367, 377, etc.).IDENT ANNUNCIATOR Push the IDENT ANNUNCIATOR ident line key to transfer the contents of the scratchpad tothe ATC fieldonaCDU.ALTITUDE REPORTINGMODEThe ALTITUDE REPORTING MODE is set from the ATC main display page. The line selectkey adjacent to the ALT legend is used to select altitude reporting mode (push-on/push-off).NOTETCAS operation requires altitude data, so if the ATC transponder is not set to ALT re-porting mode, the TCAS system automatically selects STBY mode.REPORTING ALTITUDEANNUNCIATOR3-14
523-0809018CHAPTER 4Maintenance4.1. INTRODUCTION.NOTEUse the flight line maintenance procedures as customer acceptance test procedures by interconnecting the equip-ment on the bench using the equivalent of an aircraft interconnect harness and appropriate sensor data sources.Throughout these procedures the term Traffic Control is intended to apply to any traffic control Line ReplaceableUnit (LRU).The term Traffic Surveillance System applies to the entire traffic system. The abbreviation TSS-4100 applies tothe LRU.Throughout these procedures, the term Traffic Display refers to whatever traffic display device is present in theinstallation. This can be a single or dual VSI/Resolution Advisory (RA)/TA display like the TVI-920D, an Elec-tronic Flight Instrument System (EFIS) display like an MFD-3010E, or a combination of these or other trafficdisplays.This section contains the procedures necessary to assure proper post-installation system operation.4.1.1. Flight Line Maintenance.The flight line maintenance procedures assist the flight line technician in isolating a reported failure to a given LRU. Therefore, theinstructions in this series favor a higher probability of traffic surveillance system equipment failure. Faulty units then can be testedand repaired with the bench procedures given in the associated unit repair manual.4.1.2. Automatic Testing.The traffic surveillance system incorporates automatic testing routines (Built-In Test Equipment (BITE)) in the TSS-4100 Trans-mitter/Receiver to check the operational integrity of the system. Monitoring of system functions is continuous during operation.Testing may be initiated manually via the traffic control LRU, or by pushing the TEST switch on the front panel of the TSS-4100.If a system failure is detected during operation or after initiating test, an indicator illuminates on the TSS-4100 front panel and a redTraffic Alert Collision Avoidance System (TCAS) System flag displays on the TCAS display. Refer to the Operation chapter of thismanual for a description of front panel control and indicators.4-1
maintenance 523-08090184.2. MAINTENANCE SCHEDULE.The TCAS function of the TSS-4100 does not require any periodic maintenance. However, the transponder function must have anAir Traffic Control (ATC) transponder test and inspection according to FAR part 91 at a minimum of once every two years.4.2.1. Cleaning and Painting.NOTEObserve all warnings and cautions listed in the advisories paragraph of this manual and the Collins Avionics Stan-dard Shop Practices Manual.This section presents the special instructions necessary for cleaning the traffic surveillance system equipment. For standard cleaninginstructions, the technician should follow the instructions outlined in the Collins Avionics Standard Shop Practices Manual, CollinsPart Number (CPN) 523-0768039.4.2.2. Cleaning Indicators.There are no indicators coming from any part of the Traffic Surveillance System to indicate necessary cleaning.4.2.3. Cleaning Antennas.Do not paint the antenna surface. Do not attempt to touch up the silk screening with paint.Do not use cleaning solvents on the antennas.NOTERefer to TRE-920 Service Information Letter 1-95, Radome Paint Peeling, for cleaning the TSA-4100 or TRE-930.Methods of cleaning antennas follow.a. Clean the exposed antenna surface using a soft cloth moistened with soap and water.b. Rinse the surface with clean water and allow to air dry.4.2.4. Approved Repairs.No repairs should be attempted on any component of the traffic surveillance system while the equipment is installed in the aircraft.4-2
maintenance 523-08090184.3. CONVERSION FROM TTR/TDR TO TSS SYSTEM.The Traffic Surveillance System (TSS) is designed to take the place of one TDR-94D and a TTR-920, TTR-921, or TCAS-4000, inan integrated system.4.3.1. Preparation for Conversion.A list of requirements follows:• The TSS-4100 requires a 7.5 Amp breaker and 28 V input power.• The TSS-4100 requires concentrated input busses. If the existing system has a TDR-94D strapped to Configuration 2, this isalready available. If the TDR-94D is strapped to any other configuration more changes will be necessary to the architecture ofthe aircraft to accommodate the TSS-4100.• The TSS-4100 requires radio altitude on the concentrated input bus for the TCAS function. This may require a change to theinput/output concentrator routing in order to route this data to the TSS-4100. This is already true for most Configuration 2 TDR-94D installations.• The TSS-4100 requires the following interfaces from the TDR it is replacing: Concentrated bus inputs, Control bus inputs, Con-trol bus control discretes, All GPS inputs, X-side transponder standby input and output discretes, TDR No. 1 output bus (usedfor TSS No. 1 output bus), and Air/Gnd input.• The TSS-4100 requires the following interfaces from the TTR it is replacing: TA/RA output busses, RA Display and TA Displayinput discretes, XT and TX busses to stand alone transponder, 600 output, (Climb Inhibit, Increase Climb Inhibit, Perf Limit,and Advisory Inhibit) discrete inputs), and Visual Annunciation and Aural Annunciation output discretes.• The TSS-4100 requires ARINC 615-3/4 data load capability. This is required to load aircraft configuration data.• The TSS-4100 requires a couple of changes to the maintenance system. The maintenance labels being sent through the TSS No.1 output bus are different. In addition there must be an option to show the TSS-4100 electronic nameplate.• A change to the input/output concentrator tables to route the maintenance and electronic nameplate labels to the maintenancesystem is necessary.• The TSA-4100 replaces the TRE-920 directional antenna. The connectors for the TSA-4100 are rotated 45 degrees from theplacement of the connectors for the TRE-920. This is not an issue if there is only one hole in the skin of the aircraft for all of theconnectors to go through.4.3.2. Differences between TTR/TDR and TSS.Differences between the TTR/TDR and TSS systems follows:• It is recommended that the TDR is on the left and the TSS-4100 is on the right. This is because a transponder is required to be onthe emergency battery bus. Typically, the left transponder is on this bus. A stand alone TDR uses less power than the TSS-4100.• The TSS-4100 only supports A429 input busses. CSDB inputs, Gillham altitude, and analog inputs (for example, an analog radioaltitude input) are not supported.• The TSS-4100 does not support an 8 audio output.• The TSS-4100 supports a Time Mark input from both GPS sources. The TDR only supports an input from one GPS.• Aircraft configuration data is maintained electronically in a file loaded through the TSS-4100 into an attached ECU. In aTDR/TTR, this aircraft configuration data is maintained through hard straps on the back of the unit.• The Mode S address for the TSS-4100 is maintained electronically within the attached ECU. TDR has 24 discrete inputs to settheModeSAddress.• The TSS-4100 requires cooling. It is highly recommended that the TSM is used as the fan. This mount can be monitored by theTSS-4100.NOTEThe TSS-4100 (hardware only) and TSSA-4100 (software only) are separate top level part numbers. Both mustbe maintained as part numbers on the aircraft.The TDR and TTR top level part numbers are different. Each includes both software, and hardware, components.4-3
maintenance 523-08090184.4. DATA LOADING.Explanations of data loading the ECU and the TSS-4100 follow.4.4.1. ECU Data.The External Compensation Unit (ECU) attached to the TSS-4100 holds two sets of data. The first set of data, the TSS ECU MediaSet Builder, contains the aircraft-configuration strapping for the TSS. These straps are detailed in Table 2-2. These data must be dataloaded through the TSS-4100. Refer to Table 4-1 for the data load busses and pins. The TSS-4100 will recognize the format of thedata set and store the data appropriately. The second set of data contains the aircraft Mode S Address. The TSS Mode S AddressProgramming Tool loads just the Mode S address onto the ECU, refer to Paragraph 4.5 for details. Verification of a proper load ofthese sets of data will be accomplished by reviewing the TSS-4100 Electronic Nameplate on the aircraft maintenance system. SeeParagraph 4.4.3 for more information on the TSS electronic nameplate.Table 4-1. Data Load Buses And PinsBus Name Pin Numbers (Hi & Low) Bus SpeedControl B Input Bus LMP-7D & 7C LowDataload Input Bus LMP-7J & 7K HighTSS-1 Output Bus LMP-7A & 7B LowTSS-2 Output Bus LMP-1A & 1B HighTSS-3 Output Bus RMP-1A & 1B High4.4.1.1. If the bus speeds are configured differently in the ECU than what is listed in Table 4-1, follow the following steps in orderto load data.a. Disconnect the cable from the ECU.b. Power cycle the TSS-4100. This forces the TSS to use the default speeds listed in Table 4-1.c. Reconnect the cable to the ECU.d. Start the data load process as normal. The data load software always uses the default bus speeds. The bus speeds in the ECUare ignored once the data load process has begun.4.4.2. TSS Data Loading.The TSSA-4100 and the ECU files are field loadable. Rockwell Collins has tested the TSS data load procedure using the ARINC615-3 data loaders shown in Table 4-2. It is recommended that one of these data loaders, or an upgraded version of one of these dataloaders, is used to load the Traffic Surveillance System Application (TSSA) or the ECU.4.4.2.1. The TSS may be data loaded using one of two input buses and one of three output buses. Loading must be done using thedefault speed of the bus. Refer to Table 4-1 for bus names, pin numbers, and bus speeds. Refer to Table 4-2 for a list of the dataloaders that the TSS-4100 has been tested with. Most standard ARINC 615-3/4 compatible data loaders should be able to interface tothe TSS-4100. No special adaptor is called out for the TSS-4100. See the specifications of the applicable data loader for informationon the mating connector to be used.4.4.2.2. The TSS-4100 needs one of the following sets of requirements in order to enter data load mode:4-4
maintenance 523-0809018• Set the SDI code of the unit to right or left.• Make sure the airspeed and ground speed are eachless than 40 kts.• Make sure the Data Load Enable discrete (RMP-10K) is grounded.• Make sure one of the air ground discretes isgrounded.• Make sure the TSS-4100 receives an ARINC labelwith a data load request. The TSS uses ARINC label027 as the data load input label and sends label 226as the data load output label.OR • Set the SDI code of the unit is set to indeterminate(neither of the SDI pins are grounded).• Make sure the Data Load Enable discrete (RMP-10K) is grounded.• Make sure the Shop Mode Enable discrete (RMP-6A) is grounded.• Make sure the TSS-4100 receives an ARINC labelwith a data load request.4.4.2.3. Refer to Figure 4-1. To make sure that the TSSA has been loaded correctly, look at the electronic nameplate being sentto the maintenance system. Refer to Paragraph 4.4.3 for data about the TSS electronic nameplate, and for what needs to be verifiedafter a TSSA or ECU media set data load.Table 4-2. ARINC 615 Data Loaders.Company Product Part NumberHoneywell (AlliedSignal)PDL 964-0400-024USB429win USB/ ARINC 429 Adapter 650-0200AvionicaUSB429win 615 Data Loader SW for PC 700-0300; (version040903)Demo Systems PMAT-2000Demo Systems PDL-615/MSD4.4.3. TSS Electronic Nameplate.Refer to Figure 4-1. Through the aircraft maintenance system it is necessary to access the TSS Electronic Nameplate. There arethree sections of the electronic nameplate.4-5
maintenance 523-0809018Figure 4-1. TSS-4100, Electronic Nameplate4.4.3.1. The top section of the electronic nameplate (lines 1 - 10) contains information regarding the TSSA-4100 software. Whenthe software is updated, make sure the items that follow:• CPN – this is the top level software part number for the TSSA loaded• CRC32-SysIO – this is a Cyclic Redundancy Check (CRC) on the first of two load sets that are part of the TSSA-4100• CRC32-SysIO – this is a CRC on the second of two load sets that are part of the TSSA-4100.4.4.3.2. The second section of the electronic nameplate (lines 12 - 15) contains data about the ECU connected to the TSS-4100.4.4.3.2.1. When the ECU is properly connected to the TSS-4100, the hardware part number of the ECU is shown. If the ECU isincorrectly formatted for the TSS or is not properly connected, the hardware part number will be shown as INVALID.4.4.3.2.2. The second and third lines of the ECU portion of the electronic nameplate show the aircraft configuration that is loadedinto the ECU. If there is not an aircraft configuration loaded, or if the load is invalid, both the LOADED CONFIG PN and CRC32-AIRCRAFT CONFIG line of the aircraft configuration are INVALID. When a valid aircraft configuration file is loaded into the ECU,the part number and the CRC must be compared against the part number and CRC provided with the configuration file.4.4.3.2.3. The last line of the ECU portion of the electronic nameplate shows the Mode S address stored within the ECU. TheMode S address is shown in octal. Do not use this display of the Mode S address to verify a changed Mode S address. Instead, usea transponder test set such as the IFR-6000 to verify a changed Mode S address.4.4.3.3. The third section of the electronic nameplate (lines 17+) contains some information about the TSS-4100 hardware. Thisis reported as a convenience only and is not to be used for official record keeping. The official part number, serial number, and listof installed service bulletins are on the physical TSS-4100 nameplates.4.5. TSS-4100 MODE S ADDRESS PROGRAMMING TOOL.Rockwell Collins provides the TSS-4100 Mode S Address Programming Tool (Mode S tool). This tool changes the Mode S address,and does not require data loading. The Mode S tool is provided to allow an update to the Mode S address of the TSS-4100 withoutrequiring a data load and without removing the TSS-4100 or the ECU from the aircraft.4.5.1. Programming Tool Support.Support for the TSS-4100 Mode S Programming Tool is provided by Rockwell Collins Product Support Representatives.4.5.2. Programming Tool System Requirements.The system requirements for using the TSS-4100 Mode S Address Programming Tool are as follows:• A PC or laptop with Microsoft Windows™ XP or later4-6
maintenance 523-0809018• Be logged in with administrator credentials• At least one RJ-45 port on the PC/laptop• A Cross-Over RJ-45 Ethernet Cable.4.5.3. Programming Tool Installation.NOTEThis program requires Microsoft™ .NET 3.5 on the PC. If there is difficulty in installing .NET, uninstall all cur-rently installed versions of Microsoft™ .NET before attempting the new installation. Contact your network ad-ministrator or information technology department for further assistance.Do the steps that follow to install the Mode S Programming Tool:a. Obtain the TSS-4100 Mode S Address Programming Tool (CPN 811-2989-001).NOTEThis is available through a CD-ROM. It may also be available through a digital download. Contact a RockwellCollins Product Support Representative for more information regarding this option.b. Open the directory with the TSS-4100 Mode S Address Programming Tool setup files.c. If .NET is not already installed, run Install .NET 3.5 Offline.exe. If unsure whether or not .NET is installed,proceed to the next step. This setup program is provided by Microsoft™. This setup program will indicate that it is downloadingfiles from the internet, and will say, "Download Complete. You can now disconnect from the Internet." These statements arenormal. All necessary files are contained within the executable.d. Run the Mode S Tool Installation Package.msi program. Follow the prompts to install the TSS-4100 Mode SAddress Programming Tool.NOTEIf .NET is not installed, a prompt to download the applicable files from the Internet will show. It is recommendedto decline this download, and to perform Step 4.5.3.c. This is because the .NET framework is very large, anddownloading the files will take a significant amount of time.4.5.4. Programming Tool Setup.Make sure the IP address of the PC or laptop is within the proper address space. If the Mode S Programming Tool is expected to beused often, then configure an IP port, on the PC or laptop, to not get an IP address from a DNS server at start-up.NOTEIf there are problems setting up the IP address of the PC or laptop, contact your network administrator or informa-tion technology department for assistance.a. On the TSS-4100 Mode S Address Programming Tool, select the System > IP Addresses option.b. Select the appropriate Network Interface Card (NIC). Refer to Figure 4-2.NOTEIn the example below, the second NIC card is being selected.4-7
maintenance 523-0809018Figure 4-2. Programming Tool - Select Network Interface Cardc. Refer to Figure 4-3. If necessary, change the IP address to be 192.168.111.XXX, where XXX is anything except 110. Changethe Subnet mask to 255.255.255.0. Make sure the Default Gateway and DNS server are blank.NOTEIn the example below, the second IP address was changed from 192.168.111.120 to 192.168.111.255. This can beseen by looking at the IP Address (1) field in the Current IP Settings window.Also, the status now indicates IP Address Updated.Figure 4-3. Programming Tool - Change the IP Addressd. Refer to Figure 4-4. If the IP address is locked by the program, it is possible to unlock the IP address and make changes. Thisis not recommended, and if this is done it is recommended that these settings are changed back after use of the tool.NOTEIn the example below, the first NIC card is selected, and there is a Default Gateway and DNS server. In order forthis NIC card to be used to communicate with the TSS-4100, these values would need to be cleared, and the IPaddress would need to be set to the proper address space.4-8
maintenance 523-0809018Figure 4-4. Programming Tool - Unlock the IP Addresse. On the Programming Tool, select the System > Settings option. Make sure that the target IP address is 192.168.111.110and that the port is 3000. Refer to Figure 4-5.Figure 4-5. Programming Tool - Verify the IP Address4.5.5. Programming Tool Instructions.These instructions assume that the TSS-4100 is installed properly on the aircraft.a. Make sure that the TSS-4100 is off and in the “On Ground” state.Do not attempt to remove the front panel screws from the TSS-4100. This will likely result in either a shearedscrew or the screw not being able to be screwed back in. If this happens, please return the TSS-4100 to a RockwellCollins Service Center. These screws are designed to stay on the TSS-4100.b. Loosen, but do not remove, the screws located on the front panel of the TSS-4100. Slide the access panel up and rotate it sothat the TSS-4100 RJ-45 maintenance ports are accessible.c. Connect the cross-over cable from the PC to the TSS-4100 SYSP port.NOTEIf a cross-over cable is not used, there will be no connection between the PC and the TSS-4100.d. Turn the TSS-4100 on. Allow the unit up to 30 seconds to complete its power up sequence.e. Run the TSS-4100 Mode S Address Programming Tool. If a default installation is done, the program may be accessed througha shortcut on the desktop, or in the START menu under > Rockwell Collins > Mode S Programmer > TSS-4100 Mode S Tool.f. Select the appropriate base for programming the Mode S address – either octal or hexadecimal.4-9
maintenance 523-0809018g. Enter the Mode S Address. If entering in octal, the entered is eight digits between 0 and 7. If entering in hexadecimal, theentered value is 6 characters, each character being either a single digit (0 – 9), or a letter A thru F.NOTEIf there are not enough characters for the selected base, zeroes (0s) will be added to the beginning of the valueentered.h. Push the PROGRAM button and wait for up to a minute. The system will attempt to send the new Mode S address to theTSS-4100. If the process completes incorrectly, an error message will appear in the Display Log. If the process completescorrectly, the TSS-4100 will reset itself. Allow the TSS-4100 to complete its power up sequence.i. Push the QUERY button. Make sure that the Mode S address displayed is the newly programmed address.NOTEThis is not an approved way to officially verify the current Mode S address setting.j. Select the TSS-4100 as the active transponder. Make sure that there is no annunciation of a transponder failure. Interrogate theTSS-4100 using a test set (such as the IFR-6000), and verify the Mode S Address.k. Turn off the power to the TSS-4100.l. Remove the cross-over cable from the TSS-4100.m. Slide the cover back onto the front panel of the TSS-4100 and tighten the screws.4.5.6. Programming Tool Overview.Figure 4-6 shows a screen shot of the TSS-4100 Mode S Address Programming Tool. The description of the screen shot follows:1. Octal / Hexadecimal: Radio buttons used to change between Octal and Hex just by clicking on the radio button with theappropriate base for ease of readability. This affects both the input and the output.2. Mode S Address: Text box in which to enter a Mode S address. If octal is selected, only the characters 0 – 7 are accepted.If hexadecimal is selected, only the characters 0 – 9 and A – F are accepted.3. Current Mode S: Text field that shows the Mode S address currently being used by the TSS-4100. This is only populatedafter the Query button is pushed. This output is either in octal or in hexadecimal based on the current setting.NOTEThe Current Mode S field is for informational use only. This is not an approved way to officially verify thecurrent Mode S Address setting. Checking the reported Mode S Address from the reply to an interrogationof the TSS-4100 (using a test set such as the IFR-6000) is the appropriate way to verify the Mode S address.4. Program Button: This button makes the programming tool attempt to program a new Mode S address into the TSS-4100.5. Query Button: Button that causes the Programming Tool to obtain and display the Mode S address currently being used bythe TSS-4100. Pushing this button populates the Current Mode S text field. Pushing this button also causes a comparisonbetween the value in the Mode S address text field and the value in the Current Mode S text field.6. Display Log: Log of communications between the TSS-4100 and the programming tool.7. File: Three options are available under File: an option that replicates the functionality of the Program Button, an option thatreplicates the functionality of the Query Button, and an option to exit the programming tool.8. System: Two options are available under System: an option to view and change the target port and IP address, and anoption to view and change the IP address of the PC or laptop in use. These options are described in the Setup section ofthese instructions.4-10
maintenance 523-08090189. Help: Two options are available under Help: an option to view programming tool version information and an optionto view these instructions.10. Match Indicator: After pushing the Query Button, there will be an indication here if the address in the Mode S address boxmatches the Current Mode S box. If they match it will be green; if they do not match it will be red.Figure 4-6. Programming Tool - Screen Shot4.6. LED INDICATORS.This section contains descriptions of the Traffic Surveillance System (TSS) Light Emitting Diodes (LED) that show on the frontpanel of the TSS-4100.NOTERefer to the system pilot guide or the operation section of the system installation manual for displays indicatorsand data.4.6.1. LED Descriptions.There are nine LED indicators on the front panel of the TSS-4100 to show the internal status and some external faults. Refer toFigure 4-7. And, refer to Table 4-3 for a description of what each LED represents. The LED indicators show the results of thepower-up self-test and the results when the front panel TEST push button is pushed. The LED indicators also show the results ofany continuous monitoring errors detected during normal operation.4-11
maintenance 523-0809018Figure 4-7. TSS-4100 Front Panel LEDsTable 4-3. LED DescriptionsIndicator Color DescriptionLRU STATUS indicator will light green whenever the self-test is successful. The LRUSTATUS indicator will light red whenever the self-test fails.LRU STATUS RED/GREENIf this is red, it is probable that the TSS will need to be replaced. See the maintenancewords for more information on this.UPPER ANT FAIL indicator will light red whenever the impedance of the upperantenna does not meet specification.UPPER ANT FAIL REDIf this is lit the cabling from the TSS to the upper antenna needs to be checked.LOWER ANT FAIL indicator will light red whenever the impedance of the lowerantenna does not meet specification.LOWER ANTFAILREDIf this is lit the cabling from the TSS to the lower antenna needs to be checked.CONTROL INPUT indicator will light whenever a fault with the control panel isdetected.CONTROL INPUT REDIf this is lit the connection between the TSS and the selected control panel needs tobe checked. Alternately, check the control panel selection discretes and verify theyare correctly being set.4-12
maintenance 523-0809018Table 4-3. LED Descriptions - ContinuedIndicator Color DescriptionALTITUDE FAULT indicator will light whenever the selected altitude source isfailed or missing.ALTITUDEINPUTREDIf this is lit, check the transponder control panel to see if it is indicating that it issending a valid altitude. If the transponder control panel is not sending the altitude,check to verify that the ADC on the PFD which is coupled to the autopilot is sendingvalid information.The RAD ALT INPUT indicator will light whenever the selected radio altitude inputsare missing, or when there are two radio altitude inputs and they are not in agreement.RAD ALT INPUT REDIf this is lit and there are two radio altimeters, try turning off one at a time to see ifthe failure goes away. If the failure persists or if there is only one radio altimeter,check the wiring from the radio altimeter.The HEADING INPUT indicator will light whenever one of the following is missing:selected heading, pitch angle, roll angle, or true heading.HEADING INPUT REDThese are optional parameters for the TCAS function. If these parameters are notavailable, the Traffic Surveillance System will work properly.The R/A DISPLAY indicator will light whenever either R/A display discrete input isnot grounded.R/A DISPLAY REDIf this is lit, check that both the left and right displays are active and can display TCAStraffic. Push the TCAS test button, if the targets do not appear on one of the displays –check the TA/RA port to that display. If the targets are shown on all displays, checkthe RA discrete connection from the display to the TSS.The T/A DISPLAY indicator will light whenever either T/A display discrete input isnot grounded.T/A DISPLAY REDThis is a legacy TCAS discrete input and is not generally used any more. If this islit check to make sure that the straps setting the two T/A discrete inputs are correctlystrapped to ground.4-13
maintenance 523-08090184.7. TEST EQUIPMENT AND POWER REQUIREMENTS.Test equipment required to perform the post-installation test procedures is below. Other equipment may be entirely satisfactory if itmeets the specifications and is calibrated as necessary.• Combined TCAS/Transponder test set (such as the IFR-6000), or a TCAS test set and a transponder test set• Pitot Static Ramp Tester• Radio Altimeter Ramp Tester.4.7.1. Power Requirements.All power required to perform the system tests and trouble shooting is provided by the aircraft in which the system is installed.4-14
maintenance 523-08090184.8. TESTING AND TROUBLESHOOTING.The procedures in this section help isolate LRU failures. The built-in tests present in the Traffic Surveillance System and in thecross-side Mode S transponder system, make diagnostics easy to use on the flight line. For more information on the maintenancereporting of the TSS-4100 and TDR-94D see Appendix B.4.8.1. Pre-installation Testing.To make sure that equipment works before installing the equipment in an aircraft, perform one of the tests that follow:•Thefinal performance test• The customer acceptance test• Connect the unit to a system mock-up.4.8.2. TCAS Self Test.NOTERun this test as a Return to Service Test, and as part of the pilot pre-flight check.The TCAS System Test shows that the Traffic Surveillance System is working properly. Run this test first whenever there is anproblem with the TCAS function. To initiate a TCAS self-test, perform the steps that follow:a. Push the TEST button on the TCAS control, or push any other remote TCAS self-test button.NOTEThe TSS will only go into test while on the ground.b. Make sure that TEST is shown on the TrafficDisplay.c. Make sure that the test intruder set of traffic symbols are as shown in Figure 4-8 and are as follows:• An RA symbol (solid red square) at 2 nmi, at 200 feet relative altitude, above (+02), with no VS arrow, at a relative bearingof +90 degrees.• A TA symbol (solid yellow circle) at 2 nmi, at 200 feet relative altitude, below (–02), with ascending arrow, and a relativebearing of –90 degrees.• An PT symbol (solid cyan or white diamond) at 3.625 nmi, at 1000 feet relative altitude, below (–10), with descendingarrow, at a relative bearing of +33.75 degrees.• An OT symbol (open cyan or white diamond) at 3.625 nmi, at 1000 feet relative altitude, above (+10), with no arrow, at arelative bearing of –33.75 degrees.4-15
maintenance 523-0809018Figure 4-8. TCAS Self Test Standard Outputd. Verify that RA vertical guidance is shown on the system. This may be done in the form of pitch cues, path cues, or on a verticalspeed tape.e. After the test is completed, the audio system announces, "TCAS SYSTEM TEST OK." If the audio system announces, "TCASFAIL," instead, repeat self-test by pushing the TEST button on the front of the TSS-4100. The LEDs on the front of the unitshow the source of the failure. See section XXXX for a description of the meaning of the LEDs.4.8.3. Equipment Setup.Perform the steps that follow to setup the TCAS test equipment, only if a ramp-tester is used:a. Position the TCAS test set according to the instructions supplied with the test set.b. Make sure that the electrical power is applied to all of the aircraft systems that are required for Traffic Surveillance Systemoperation.c. Turn off any Traffic Surveillance System ground operation controls that may be present in the installation under test. Thisincludes the WOW automatic-standby, and landing gear and flaps extended switching features.d. Perform the test set self-test procedure to be sure the set is operating properly.4.8.4. Radio Altitude System Failure Tests.Perform this test when a pilot complaint suggests a problem related to the TCAS/Radio Altitude interface. A failure of all radioaltitude sources will fail the TCAS function. Do the steps that follow to perform a radio altitude system failure test:a. Set the aircraft simulated altitude to 2,000 feet, both radio and barometric altimeters, and simulate WOW in air.b. Select Traffic Advisory (TA)/RA or Automatic (AUTO) and verify that Traffic Surveillance System operation is normal.c. Select the TSS-4100 as the active transponder.d. Make sure no transponder failure annunciates.e. Make sure that the single and dual radio altitude source operation is normal.(1) If this is a single radio altimeter installation, simulate a radio altimeter system failure by opening the circuit breaker forthe radio altimeter. Make sure that TCAS FAIL is annunciated.(2) Reset the circuit breaker opened in the previous step. Make sure that the Traffic Surveillance System returns to normaloperation.4-16
maintenance 523-0809018(3) If this is a dual radio altimeter installation, simulate a radio altimeter system failure by opening both of the radio altimetercircuit breakers. Verify that TCAS FAIL is annunciated.(4) Reset the circuit breaker for the No. 1 radio altimeter. Make sure that the Traffic Surveillance System returns to normaloperation.(5) Open the circuit breaker for the No. 1 radio altimeter. Make sure that TCAS FAIL is annunciated.(6) Reset the circuit breaker for the No. 2 radio altimeter. Make sure that the Traffic Surveillance System returns to normaloperation.(7) Reset the circuit breaker for the No. 1 radio altimeter.4.8.5. Pressure Altitude System Failure Tests.Perform this test when there is pilot complaint suggesting a problem related to both the pressure altitude, and either the TCAS or thetransponder systems. A failure of the pressure altitude source makes the TCAS function fail. To perform a pressure altitude systemfailure test, do the steps that follow:a. If this is a single ADC installation, make sure that the source operation is normal.(1) Select the left transponder. Select No. 1 or single altitude source.(2) MakesurethattheTraffic Surveillance System operation is normal.(3) Open the circuit breaker for the No. 1 altitude source. Make sure that the TCAS FAIL annunciates.(4) Reset the circuit breaker for the No. 1 altitude source. Make sure that the Traffic Surveillance System returns to normaloperation.(5) Select the right transponder and repeat this procedure.b. If this is a multiple ADC installation, make sure that the source operation is normal.(1) Make sure that all of the ADCs are on and are working. Make sure that the TSS-4100 is the selected transponder.(2) Select the pilot PFD as the side that is driving the auto pilot (couple the auto pilot to the pilot side PFD). Have the pilotside PFD use the No. 1 ADC. Make sure that the Traffic Surveillance System operation is normal.(3) Open the circuit breaker for the ADC No. 1. Make sure that TCAS FAIL annunciates.(4) If possible, select the ADC No. 2 on the pilot PFD. If this is not possible, then skip to Step 4.8.5.b.(6). Make sure that thesystem returns to normal operation.(5) Reset the circuit breaker for the No. 1 ADC and open the circuit breaker for the No. 2 ADC. Make sure that TCAS FAILannunciates.(6) Reset the circuit breaker for the No. 2 ADC. If possible, select the No. 3 ADC on the pilot PFD. If this is not possible,then skip to Step 4.8.5.b.(8). Make sure that the system returns to normal operation.(7) Open the circuit breaker for the No. 3 ADC. Make sure that TCAS FAIL annunciates. Reset the circuit breaker for theNo. 3 ADC.(8) Select the copilot PFD as the side driving the auto pilot (couple the auto pilot to the pilot PFD). Have the copilot PFD usethe No. 2 ADC. Make sure that the Traffic Surveillance System operates normally.(9) Open the circuit breaker for the No. 2 ADC. Make sure that a TCAS FAIL is annunciated.(10) If possible, select the No. 1 ADC on the copilot PFD. If this is not possible, then skip to Step 4.8.5.b.(12). Make sure thatthe system returns to normal operation.(11) Reset the circuit breaker for the No. 2 ADC and open the circuit breaker for the No. 1 ADC. Make sure that TCAS FAILannunciates.(12) Reset the circuit breaker for the No. 1 ADC. If possible, select the No. 3 ADC on the pilot PFD. If this is not possible,then skip to Step 4.8.5.b.(14). Make sure that the system returns to normal operation.(13) Open the circuit breaker for the No. 3 ADC. Make sure that TCAS FAIL annunciates. Reset the circuit breaker for theNo. 3 ADC.4-17
maintenance 523-0809018(14) Reset the system so that each PFD is using its primary ADC source. Select the off side transponder as the active transpon-der. Make sure that the system operates normally.4.8.6. Range and Bearing Test.Perform this test when there is pilot complaint suggesting a problem that is related to bearing accuracy. Run this test with an IFR-6000 or other equivalent TCAS test set.a. When testing the top antenna, monitor the TCAS display in the cockpit of the aircraft. Set the viewed range to 10 NM.b. Set the Traffic Surveillance System aircraft simulated altitude below 400 ft agl. This automatically disables Mode C interroga-tions (Mode S is still enabled) from the bottom antenna.c. Set the test set parameters as follows:(1) Altitude: Same as Traffic Surveillance System aircraft altitude(2) Range: 8 nmi. Make sure a stationary PT symbol shows on the display. Make sure the PT symbol is at a relative bearingthat is equivalent to the bearing to the test set.(3) VS: 0(4) Rate: 0.d. If a tarmac clock pattern (as shown in Figure 4-9) or a compass rose is available, use it as a reference to position the test set. Ifnot, position the TCAS test set at 45° intervals around the airplane and make sure that the displayed PT-symbol bearing agreeswith the bearing to the test set. Use two technicians if possible: one moves the test set around the aircraft, the other one watchesthe display. The symbol moves about the aircraft symbol with no dropouts and no deviations in bearing that are more than 15degrees. The center of the rose should be the TCAS antenna, not the center of the airplane. It is not required to test behind theaircraft.NOTEWatch for large and constant bearing errors. An occasional bearing drift can be caused by signal reflections, andis not an equipment failure. But if the symbol shifts to an adjacent or opposite quadrant, and remains there whenthe test set moves into a test quadrant, then suspect a problem with the installation. Make sure this is a problemby rotating the aircraft 90 degrees, then repeating the test. If the problem quadrant remains in the same positionrelative to the aircraft, suspect an equipment failure (the TSS-4100, the TSA-4100, or the cabling). If the problemquadrant stays fixed in space, suspect signal reflections or other outside interference.4-18
maintenance 523-0809018Figure 4-9. Bearing Test, Aircraft and TCAS Test Set Orientation4.8.7. TCAS RA Test.Perform a TCAS RA test when there is pilot complaint suggesting a problem related to TAs or to RAs. Find out which approximatebearing to check, if necessary. Run this test with an IFR-6000, or other equivalent TCAS test set.a. Make sure that the pressure altitude and radio altitude is at or above 1500 ft.b. Set the TCAS test set to make a collision course starting from 10 nmi away at 200 ft below the aircraft. Choose an appropriatebearing from which this target should approach.c. Make sure that initially on the TCAS display, an open cyan diamond is shown, then a filled-in cyan diamond is shown, then ayellow circle is shown, then a red square is shown.d. Make sure that when the yellow circle shows, a "Traffic, Traffic" aural is also heard.e. Make sure that when the red square shows, that a "Climb, Climb" aural is also heard. Also make sure that a vertical advisoryshows on the Primary Flight Display (PFD). This indicates that a climb is commanded.4.8.8. Transponder Tests.Verify that the TSS transponder is functioning properly. This test should be performed whenever there is pilot complaint suggestinga transponder issue. This may be run with an IFR-6000 or other equivalent transponder test set. It is recommended that all of thetransponder tests on the test set are run, but provided is a minimum subset that should be run.NOTEFor a transponder to reply to Mode A, Mode C, or Mode S interrogations, it will be necessary to simulate theaircraft being in the air. At a minimum this includes ensuring that the weight on wheels discrete is open and thatthe radio altimeter reads above 50 feet. If possible it would be best to also simulate an airspeed of greater than100 knots.4-19
maintenance 523-0809018a. Simulate a 2000 ft pressure altitude (uncorrected). Set the squawk code to 1234. Set the Flight ID to TEST1234. Set theselected altitude to 16000 ft.NOTEOther altitude values can be used to run this test.b. Run a Mode A/C decode and Side Lobe Suppression (SLS) test. Make sure they pass. Make sure that the proper altitude (2000ft) and squawk code (1234) are reported.c. Run an XPDR A/C Spacing Width Test, which also tests the ATCRBS all-call functionality. Make sure it passes.d. Run the power and frequency tests. This also tests receiver sensitivity. Make sure they pass.e. Run a Mode S All Call test. Make sure it passes. Make sure the Mode S address is correct.f. Run a Mode S Reply test that includes a test of diversity. Make sure it passes.g. Run a Mode S UF0 test. Make sure it passes. Make sure that the maximum airspeed range is what should be programmed forthat aircraft.NOTEThe maximum airspeed range is programmed in the ECU as part of the aircraft configuration. If necessary, readthe documentation that comes with the aircraft configuration media set to see what this value should be.h. Run a Mode S UF4 test. Make sure it passes. Make sure that the reported altitude is 2000 ft.i. Run a Mode S UF5 test. Make sure it passes. Make sure that the reported squawk code is 1234.j. Run a Mode S UF11 test. Make sure it passes.k. Run Elementary Surveillance tests. Retrieve, at a minimum, registers 1,0, 1,7 and 2,0. Make sure that the tests pass and thatthe retrieved value of register 2,0 is TEST1234.l. Run Enhanced Surveillance tests. Retrieve, at a minimum, registers 4,0, 5,0, and 6,0. Make sure that the tests pass and that theselected altitude reported in Register 4,0 is 16000 ft.4.8.9. ADS-B Transmit Ground Test.Run this test only if the ADS-B Out option is available. Perform this test when there is pilot complaint that there is an issue with theADS-B position transmissions from the aircraft.NOTEFlight testing, or GPS simulation of a flying aircraft, is required to do more testing than specified here.a. Set the TSS-4100 as the selected transponder, and have it set to reporting altitude. Turn on the primary GPS and turn off anysecondary GPS. Allow the GPS to obtain a good position fix.b. Use the IFR-6000, or any other ADS-B capable test set. Use it to monitor for Register 0.6, the surface position squitter. Makesure that the decoded position is correct. Make sure that the position is synced to the time mark. On the IFR-6000, this isindicated by the annunciation UTC. The indication that the position is not synced to the time mark is N/UTC.c. If there is a secondary GPS, then turn off the primary GPS and turn on the secondary GPS. Let the secondary GPS to obtain agood position fix.d. Use the IFR-6000, or any other ADS-B capable test set, and use it to monitor for Register 0.6, the surface position squitter.Make sure that the decoded position is correct. Make sure that the position is synced to the time mark.4.8.10. Transponder/TCAS Suppression Bus Issues.If the pilot report describes a Tracking Own Aircraft TCAS error when the non-TSS transponder is selected, then the transpondersuppression interface should be examined for open/short circuits. The suppression interface connects each TDR-94D connector,TSS-4100 connector, and DME radio. When there is a suppression interface problem, the traffic display shows an intruder aircraft4-20
maintenance 523-0809018at zero-range, and at the same altitude (±200 ft) as own aircraft. The intruder stays at own altitude regardless of evasive verticalmaneuver. The problem can also make the display show a cluster of intruder targets at own altitude that move randomly. Check thecontinuity of the suppression interfaces to show any short-circuits.a. Remove all units connected to the suppression interface, including the TSS-4100, the transponder, and DME units.b. Make sure that the continuity is less than 1to each contact in the interface. Make sure an open is greater than 100 kbetweenthe center conductor and the shield/barrel of the coaxial connector.c. Make sure that all coaxial pin contacts are positioned correctly.d. When each unit is inserted back into the system but not powered, make sure that the connections to that unit are open.4-21
maintenance 523-08090184.9. INITIAL INSTALLATION CHECK OUT PROCEDURE.Follow the procedures that follow to make sure the initial installation of the TSS-4100 performs well.4.9.1. Initial Transponder Check Out.Follow the procedures described in Paragraph 4.8.8.4.9.2. Initial TCAS Check Out.Follow the procedures that follow to make sure the initial installation of the TSS-4100 performs TCAS functions correctly.4.9.2.1. Introduction.NOTEThese tests simulate TCAS-equipped aircraft at different altitudes with altimeter test equipment, but simulate theaircraft as stationary in space.The instructions in this section use the TCAS test set to simulate certain flight scenarios. The activity of intruder aircraft is simulatedby the TCAS test set. That activity simulates the combined relative horizontal and vertical movements of both aircraft in an actualflight situation. For example, in an actual flight situation in which a TCAS equipped aircraft and an intruder are approaching atthe same altitude both with a speed of 360 kts, the relative approach speed is 720 kts. This situation can be simulated by givingthe intruder a speed of 720 kts. Refer to Figure 4-10 for the parameters involved in the flight scenarios (CPA = Closest Point ofApproach).Figure 4-10. Simplified Flight Scenario and Parameters4.9.2.2. The altitude of the TCAS aircraft is simulated by means of radio and barometric altimeter system test equipment. TheTCAS test set allows entry of intruder-simulated altitude and vertical speed. A change in relative vertical speed can be simulated bychanging the intruder vertical speed while the test runs.4-22
maintenance 523-08090184.9.2.3. You should be familiar with how to use the TCAS test set you are using. This procedure does not give detailed instructionson test set operation. These are general instructions for a normal TCAS test set. Change these instructions to apply to your test setif necessary.4.9.2.4. Equipment Preparation.NOTEEquipment Preparation means running any necessary self-tests, making the necessary connections, and placingthe equipment as required for executing the test scenarios.Follow the instructions supplied with the test equipment.a. Prepare the TCAS test set, pitot-static ramp tester, and radio altimeter ramp tester for the tests that follow.b. Prepare aircraft to simulate an in-flight condition. If necessary:• Defeat the strut switch automatic standby feature.• Apply electrical power.c. Set the TCAS control to the STBY (standby) position.d. If the TCAS system has an altitude volume selector switch (ABOVE-NORM-BELOW), then select NORM.e. If the TCAS system has an altitude reference selector switch (REL-ABS), then select REL (relative).f. Make sure the TCAS display shows no RA (resolution advisory), TA (Traffic Advisory), or PT (proximity traffic) symbols.g. Make sure the TCAS display shows that the TCAS system is in standby mode.h. Select TA/RA mode on the TCAS control.NOTEThe TCAS controls may have a position labeled AUTO. If so, use AUTO instead of TA/RA.i. Make sure the TCAS display shows that TCAS is no longer in standby.j. Make sure the TCAS display is set for full-time traffic display. If it is not, then select traffic mode. Set the TCAS DisplayRange to 15 nmi or greater.NOTEIf airborne aircraft are near (i.e. within approximately 15 nmi), the display can show an other traffic(OT)orPTsymbol.4.9.2.5. Test Scenarios. Refer to Figure 4-10 for the Test Scenario setups. If using the IFR-6000 Test Set, pre-program the unitfor the desired scenarios. This can save time on the flight line. In all test scenarios, the bearing to the intruder symbol on the TCASdisplay will always be in the direction of the test set with respect to the airplane. That is, if the test set is situated off the right wing,all intruder symbols will appear at or very near, the 3:00 o’clock position on the TCAS display. Here is a summary of the scenarios:• Scenario 1a: Climb RA• Scenario 1b: Descend RA• Scenario 2a: Climb RA just below maximum climb altitude• Scenario 2b: Descend RA just above the maximum climb altitude• Scenario 3a: Increase Climb RA• Scenario 3b: Increase Climb Inhibit (not applicable to all installations)• Scenario 3c: Climb Inhibit (not applicable to all installations)• Scenario 4a: Low Altitude Allow Increase Descent4-23
maintenance 523-0809018• Scenario 4b: Low Altitude Don't Allow Increase Descent• Scenario 4c: Low Altitude TA Only.NOTE(1) There may be an approximately one second delay between symbol display and the aural advisory.(2) The maximum climb altitude is documented at airplane certification and may be different than the airplaneservice ceiling. Consult airplane data for applicable altitude. This altitude is programmed in the ECU.4.9.2.5.1. Scenario 1a: Climb RA. In Scenario 1a, the intruder is placed below own airplane to induce a CLIMB RA command.a. Set the airplane under test (UUT) simulated altitude to 12,000 ft and the radio altimeter to maximum setting.b. Set the following values as necessary:•TCASType:TCASII• Intruder Type: Mode S• Range at Start: 15.00 nmi• Range Rate: +720 kts• Altitude at Start: 11900 ft (if entering as an absolute altitude) or -100 ft (if entering relative altitude)• Altitude Rate: 0.c. Start the scenario.d. Monitor the TCAS display and audio system for correct presentation as follows (NOTE 1):Display Range (approx) Display Aural12 nmi Other Traffic Symbol None9 nmi TA Symbol TRAFFIC, TRAFFIC6 nmi RA Symbol CLIMB, CLIMB4.9.2.5.2. Scenario 1b: Descend RA. In Scenario 1b, the intruder is placed above own airplane to induce a DESCEND RAcommand.a. Set the airplane under test (UUT) simulated altitude to 12,000 ft and the radio altimeter to the maximum setting.b. Set the following values as necessary.•TCASType:TCASII• Intruder Type: Mode S• Range at Start: 15.00 nmi• Range Rate: +720 kts• Altitude at Start: 12,100 ft (if entering as an absolute altitude) or +100 ft (if entering relative altitude)• Altitude Rate: 0.c. Start the scenario.d. Monitor the TCAS display and audio system for correct presentation as follows (NOTE 1):4-24
maintenance 523-0809018Display Range (approx) Display Aural12 nmi Other Traffic Symbol None9 nmi TA Symbol TRAFFIC, TRAFFIC6 nmi RA Symbol CLIMB, CLIMB4.9.2.5.3. Scenario 2a: Climb RA just below maximum climb altitude. Scenario 2a and 2b are tests intended to ensure thatthe maximum climb altitude is properly programmed and read by TCAS.a. Set airplane under test (UUT) simulated altitude to 50 ft below (+/- 10 ft) the maximum climb altitude (NOTE 2). Set the radioaltimeter to the maximum setting.b. Set the following values as necessary:• TCAS Type: TCAS II• Intruder Type: Mode S• Range at Start: 15.00 nmi• Range Rate: +720 kts• Altitude at Start: Set to 50 ft below the UUT altitude (or equal to 100 ft below the maximum climb altitude)• Altitude Rate: 0.c. Start the scenario.d. Monitor the TCAS display and audio system for correct presentation as follows (NOTE 1):Display Range (approx) Display AuralIf the maximum climb altitude is set between 10,000 and 20,000 ft:12 nmi Other Traffic Symbol None9 nmi TA Symbol TRAFFIC, TRAFFIC6 nmi RA Symbol CLIMB, CLIMBIf the maximum climb altitude is set to 20,000 ft or more:12 nmi Other Traffic Symbol None9.6 nmi TA Symbol TRAFFIC, TRAFFIC7 nmi RA Symbol CLIMB, CLIMB4.9.2.5.4. Scenario 2b: Descend RA just above the maximum climb altitude. Scenario 2a and 2b are tests intended toensure that the maximum climb altitude is properly programmed and read by TCAS.a. Set airplane under test (UUT) simulated altitude to 50 ft above (+/- 10 ft) the maximum climb altitude (NOTE 2). Set the radioaltimeter to the maximum setting.b. Set the following values as necessary:• TCAS Type: TCAS II• Intruder Type: Mode S• Range at Start: 15.00 nmi• Range Rate: +720 kts• Altitude at Start: Set to 50 ft below the UUT altitude (or equal to the maximum climb altitude)• Altitude Rate: 0.4-25
maintenance 523-0809018c. Start the scenario.d. Monitor the TCAS display and audio system for correct presentation as follows (NOTE 1):Display Range (approx) Display AuralIf the maximum climb altitude is set between 10,000 and 20,000 ft:12 nmi Other Traffic Symbol None9 nmi TA Symbol TRAFFIC, TRAFFIC6 nmi RA Symbol CLIMB, CLIMBIf the maximum climb altitude is set to 20,000 ft or more:12 nmi Other Traffic Symbol None9.6 nmi TA Symbol TRAFFIC, TRAFFIC7 nmi RA Symbol CLIMB, CLIMB4.9.2.5.5. Scenario 3a: Increase Climb RA. Scenario 3a can always be run.a. Set airplane under test (UUT) simulated altitude to 11990 ft and set the radio altimeter to the maximum setting.b. Set the following values as necessary.•TCASType:TCASII• Intruder Type: Mode S• Range at Start: 15.00 nmi• Range Rate: +720 kts• Altitude at Start: 11,500 ft (if entering as an absolute altitude) or -490 ft (if entering relative altitude)• Altitude Rate: 0.c. Start the scenario.d. Monitor the TCAS display and audio system for correct presentation as follows (NOTE 1):Display Range (approx) Display Aural12 nmi Other Traffic Symbol None8 nmi TA Symbol TRAFFIC, TRAFFIC6 nmi RA Symbol CLIMB, CLIMB1.3 RA Symbol INCREASE CLIMB,INCREASE CLIMB4.9.2.5.6. Scenario 3b: Increase Climb Inhibit. Scenario 3b can only be run if the "Increase Climb Inhibit" discretes areconnected and can be stimulated. This test is intended to ensure TCAS properly recognizes the increase climb inhibit input (2500ft/min climb inhibit). Follow the same steps as SCENARIO 3a except as follows:a. Configure the airplane as needed to enable the 2500 ft/min climb inhibit condition. This may require a change to both thealtitude of the own aircraft and the altitude of the target aircraft. If the altitude of this test is greater than 20,000 ft, then theranges in the following step will be off. Also, the TA and the RA will occur sooner than indicated.b. Monitor the TCAS display and audio system for correct presentation as follows (NOTE 1):4-26
maintenance 523-0809018Display Range (approx) Display Aural12 nmi Other Traffic Symbol None8 nmi TA Symbol TRAFFIC, TRAFFIC6 nmi RA Symbol CLIMB, CLIMBAt a range < 6 nmi Verify that no increase climb advisory is issued. An RA should bemaintained, but which RA being issued can change. This test passes aslong as it is not an increase climb advisory.4.9.2.5.7. Scenario 3c: Climb Inhibit. Scenario 3c can only be run if the "Climb Inhibit" discretes are connected and can bestimulated. This test is intended to ensure TCAS properly recognizes the climb inhibit input (1500 ft/min climb inhibit). Follow thesame steps as SCENARIO 3a except as follows:a. Configure the airplane as needed to enable the 1500 ft/min climb inhibit condition. This may require a change to both thealtitude of the own aircraft, and the altitude of the target aircraft. If the altitude of this test is greater than 20000 ft, the rangesin the following step will be off. Also, the TA and the RA will occur sooner than indicated.b. Monitor the TCAS display and audio system for correct presentation as follows (NOTE 1):Display Range (approx) Display Aural12 nmi Other Traffic Symbol None8 nmi TA Symbol TRAFFIC, TRAFFICAt a range < 8 nmi RA Symbol See BelowVerify no climb or increase climb advisory issued.NOTEAn RA should be issued at about 6 nmi, and that it is possible that there is a change in which RA is being issuedinside of 6 nmi. This test passes as long as there is not a climb or an increase climb advisory.4.9.2.5.8. Scenario 4a: Low Altitude Allow Increase Descent. Scenario 4a shows that a descend and increase descent advi-sories will be given at low altitudes above a certain radio altimeter threshold.a. Set airplane under test (UUT) simulated altitude to 1390 ft and set the radio altimeter to 1700 ft agl.b. Set the following values as necessary.• TCAS Type: TCAS II• Intruder Type: Mode S• Range at Start: 15.00 nmi• Range Rate: +720 kts• Altitude at Start: 1600 ft (if entering as an absolute altitude) or +210 ft (if entering relative altitude)• Altitude Rate: 0.c. Start the scenario.d. At a range of 5 nmi set the altitude rate to -500 fpm. This altitude rate change must occur as close to 5 nmi as possible. Thetiming of the alert is tight. Changing the value too soon or too late may cause other alerts to be annunciated.e. Monitor the TCAS display and audio system for correct presentation as follows (NOTE 1):4-27
maintenance 523-0809018Display Range (approx) Display Aural12 nmi Other Traffic Symbol None5 nmi TA Symbol TRAFFIC, TRAFFIC3 nmi RA Symbol DESCEND, DESCENDAt a range < 3 nmi RA Symbol INCREASE DESCENT,INCREASE DESCENT4.9.2.5.9. Scenario 4b: Low Altitude Don't Allow Increase Descent. Scenario 4b shows that within a certain radio altimeterrange, a descend advisory will be given, but an increase descent advisories will not be issued.a. Set airplane under test (UUT) simulated altitude to 1390 ft and set the radio altimeter to 1400 ft agl.b. Set the following values as necessary.•TCASType:TCASII• Intruder Type: Mode S• Range at Start: 15.00 nmi• Range Rate: +720 kts• Altitude at Start: 1600 ft (if entering as an absolute altitude) or +210 ft (if entering relative altitude)• Altitude Rate: 0.c. Start the scenario.d. At a range of 5 nmi set the altitude rate to -500 fpm. This altitude rate change must occur as close to 5 nmi as possible. Thetiming of the alert is tight. Changing the value too soon or too late may cause other alerts to be annunciated.e. Monitor the TCAS display and audio system for correct presentation as follows (NOTE 1):Display Range (approx) Display Aural12 nmi Other Traffic Symbol None5 nmi TA Symbol TRAFFIC, TRAFFIC3 nmi RA Symbol DESCEND, DESCENDAt a range < 3 nmi RA Symbol Make sure that there is no IncreaseDescent RA, but that the RA continues.4.9.2.5.10. Scenario 4c: Low Altitude TA Only. Scenario 4c shows that below a certain radio altimeter threshold, TCAS willbe in TA ONLY mode.a. Set airplane under test (UUT) simulated altitude to 1390 ft and set the radio altimeter to 850 ft agl.b. Set the following values as necessary.•TCASType:TCASII• Intruder Type: Mode S• Range at Start: 15.00 nmi• Range Rate: +720 kts• Altitude at Start: 1600 ft (if entering as an absolute altitude) or +210 ft (if entering relative altitude)• Altitude Rate: 0.c. Verify that the TCAS display shows that TCAS is in TA ONLY mode.4-28
maintenance 523-0809018d. Start the scenario.e. At a range of 5 nmi (or less) set the altitude rate to -500 fpm. This altitude rate change should occur as close to 5 nmi as possible.f. Monitor the TCAS display and audio system for correct presentation as follows (NOTE 1):Display Range (approx) Display Aural12 nmi Other Traffic Symbol None4 nmi TA Symbol TRAFFIC, TRAFFIC4.10. RETURN TO SERVICE TEST PROCEDURE.Use the procedures that follow to make sure that the Traffic Surveillance System equipment that has been removed for maintenance,repair, or bench testing and is now being reinstalled in an aircraft, operates normally. If the equipment fails these tests, use the faultisolation procedures to determine which LRUs should be removed for shop maintenance.4.10.1. Return to Service Test.Perform the test steps that follow to return TSS equipment to service:a. Perform the procedures in the TCAS self-test, described in Paragraph 4.8.2.b. Perform the procedures in Transponder Tests, described in Paragraph 4.8.8.4.11. INSPECTION/CHECK.This section presents the unique instructions necessary to verify that the conditions of the Traffic Surveillance System are normal inthe airplane. Refer to the applicable component maintenance manual if any repair to the equipment is required.4.11.1. Antennas.Do not paint any antenna. Paint can affect the performance of the antenna.Perform the items that follow:• Make sure that the antenna is free of dents, cracks, punctures, and dirt.• Make sure that the plugs are installed and sealed correctly.4.11.2. TSS-4100 Traffic Surveillance System.Perform the inspections that follow:• Make sure that the transmitter/receiver and mount connectors are properly mated and that the transmitter/receiver is securelyfastened to the rack mounting position.• Make sure that the knurled hold-down knobs on the rack are secured to the transmitter/receiver and are properly safety-wired.• Make sure that the front RJ-45 access panel is properly fastened with both screws.4.11.3. TDR-94D ATC/Mode S Transponder.Perform the inspections that follow:• Make sure that the transponder and mount connectors are properly mated and that the transponder is securely fastened to the rackmounting position.• Make sure that the knurled hold-down knobs on the rack are secured to the transponder and are properly safety-wired.4-29/(4-30 Blank)
523-0809018APPENDIX AFaults and WarningsA.1. GENERAL.The faults and warnings generated by the TSS-4100 include Light Emitting Diodes (LED) and maintenance words. The LEDs showon the front panel of the TSS-4100, and are described in Paragraph A.1. The maintenance words are sent by the TSS-4100 to theMaintenance Diagnostic Computer, and are described in Appendix B.A-1/(A-2 Blank)
523-0809018APPENDIX BMaintenance WordsB.1. MAINTENANCE DIAGNOSTIC WORDS.Refer to Table B-1 for a list of the diagnostic words from the Traffic Surveillance System (TSS). Table B-2 shows how to interpreta diagnostic word. Use this table to decode the hexadecimal readouts. Refer to Table B-3 for the hexadecimal-to-binary conversiontable. Refer to Table B-4 through Paragraph B.1.7 for a bit definition of each diagnostic word.Table B-1. LRU Diagnostic Data, Reporting LRUsBus Label Number Label NameTSS #1, #2, #3 Output Bus 350 TDR Maintenance WordTSS #1, #2, #3 Output Bus 351 TSS-4100 Diagnostic Word 1TSS #1, #2, #3 Output Bus 352 CDU Diagnostic Word 1TSS #1, #2, #3 Output Bus 353 TSS-4100 Diagnostic Word 2TSS #1, #2, #3 Output Bus 354 TSS-4100 Diagnostic Word 3TSS #1, #2, #3 Output Bus 355 TSS-4100 Diagnostic Word 4TA/RA #1, #2 Output Bus 350 ACAS DiagnosticsB-1
appendix B 523-0809018Table B-2. Diagnostic Word Interpretation.These words show on the ADVANCED DIAGNOSTICS pages.SAMPLE 6-DIGIT HEXADECIMAL DISPLAY: 2 0 5 7 A EBINARY VALUE BIT NUMBER HEX VALUE19 0210 1411 1812E1113 0214 1415 0816A1117 1218 1419 182070121 1222 0423 182450125 0226 0427 082800129 0230 1Bits 10–12, 14, 16–19, 21, 23, and 30 are set.431 083220B-2
appendix B 523-0809018Table B-3. Hexadecimal to Binary Conversion Table.HEXADECIMAL DIGITBINARYVALUE 0 1234 5 6 7 8 9 A(10) B(11) C(12) D(13) E(14) F(15)1 0 1010 1 0 1 0 1 0 1 0 1 0 12 0 0110 0 1 1 0 0 1 1 0 0 1 14 0 0001 1 1 1 0 0 0 0 1 1 1 18 0 0000 0 0 0 1 1 1 1 1 1 1 11. Turn to the table that shows the Line Replaceable Unit (LRU) diagnostic word to be decoded.2. Convert each of the 6 hexadecimal digits shown on Multifunction Display (MFD) to a binary value.3. Mark a 1 or a 0 by each bit number in the left column of the table.4. The description of each line marked with a 1 is true.B-3
appendix B 523-0809018B.1.1. Label 350 TDR Maintenance Word.This word is included as an output from the TSS as a way to be backward compatible with installations that previously had the TDR.Many of the controllers use this label as a way to know if the selected transponder is failed. The only field of this word that shouldbe used is the SSM. If the SSM is 11, the TSS is not failed. If the SSM is 00, the TSS is failed. Refer to Paragraph B.2 for a completedefinition of this word. There has been no attempt to replicate TDR fault ID's by the TSS. This field will always be 0.B.1.2. Label 351 TSS-4100 Diagnostic Word 1.Refer to Table B-4 for the definition of this word and a possible solution to the indicated issue.Table B-4. Label 351 TSS-4100 Diagnostic Word 1Bit Label 351- TSS-4100 Diagnostics Word 1 Possible Solution9SDI*10 SDI*11 TSS-4100 Unit Failure (Normal = 0 Fail = 1) Replace the unit12 ACAS Function Summary (Normal = 0 Fail = 1) Replace the unit13 XPDR Function Summary (Normal = 0 Fail = 1) Replace the unit14 SysIO Function Summary (Normal = 0 Fail = 1) Replace the unit15 ACAS System Summary (Normal = 0 Fail = 1) Check for other faults.16 XPDR System Summary (Normal = 0 Fail = 1) Check for other faults.17 ECU Unit Failure (Normal = 0 Fail = 1) Reprogram the ECU with the appropriate configurationdata. If this does not work replace the ECU.18 Fan Unit Failure (Normal = 0 Fail = 1) Replace mount with integral fan19 Upper Antenna Unit Failure (Normal = 0 Fail = 1) If no TSS unit failure, check wiring to the top antenna;replace antenna if there is no wiring problem.20 Lower Antenna Unit Failure (Normal = 0 Fail = 1) If no TSS unit failure, check wiring to the bottom antenna;replace antenna if there is no wiring problem.21 to 29 Pad30 SSM**31 SSM**32 Odd Parity*SDI Code: Bit 10 Bit 9 LRU Number **SSM Code: Bit 31 Bit 30 LRU Status00NotUsed 00Normal01Left 01NotUsed10Right 10Test1 1 Not Used 1 1 Not UsedB-4
appendix B 523-0809018B.1.3. Label 352 CDU Diagnostic Word 1.This label is forwarded if it is received through the selected control bus. The only change made to this label is changing the labelnumber from 350 (from the selected control bus) to 352. See the appropriate documentation for the attached controller if a definitionof this word is desired.B.1.4. Label 353 TSS-4100 Diagnostic Word 2.Refer to Table B-5 for the definition of this word.Table B-5. Label 353 TSS-4100 Diagnostic Word 2Bit Label 353- TSS-4100 Diagnostics Word 2 Note9SDI*10 SDI*11 Pad12 ACAS Function Fault (Normal = 0 Failed = 1) Indicated fault sets bit 12 in Label 35113 XPDR Function Fault (Normal = 0 Failed = 1) Indicated fault sets bit 13 in Label 35114 SysIO/ECU/Fan Function Fault (Normal = 0 Failed=1)Indicated fault sets bit 14, 17, or 18 in Label 35115 ACAS System Fault (Normal = 0 Failed = 1) Indicated fault sets bit 15 in Label 35116 XPDR System Fault (Normal = 0 Failed = 1) Indicated fault sets bit 16 in Label 35128 to 17 12-bit Monitor IDRange 0 4095 Refer to Table B-4 for Monitor IDs29 Start of Reporting Cycle (True = 1 False = 0)30 SSM**31 SSM**32 Odd Parity*SDI Code: Bit 10 Bit 9 LRU Number **SSM Code: Bit 31 Bit 30 LRU Status00NotUsed 00Normal01Left 01NotUsed10Right 10Test1 1 Not Used 1 1 Not UsedB.1.4.1. TSS-4100 Monitor IDs. Label 353 cycles through all active faults detected by the TSS-4100. If there is more than oneactive fault, every 500 ms a different Monitor ID will be transmitted. The "Start of Reporting Cycle" bit is implemented so that it ispossible to know that all currently active faults are recorded. For example, if there are four active faults corresponding to MonitorID 2150, 2151, 2152, and 2153, then label 353 will output Monitor ID 2150 with the Start of Reporting Cycle bit set to 1. The otherMonitor IDs will be output one at a time with the "Start of Reporting Cycle" bit set to 0. Once all of the Monitor IDs have beenoutput, the TSS will start with Monitor ID 2150 again. Refer to Table B-6 for a list of all the possible Monitor IDs and the associatedfaults.B-5
appendix B 523-0809018Table B-6. LRU Diagnostic Data, Fault Names and Categories.Moni-tor IDFault Name TSS-4100 FaultCategoryMonitor Name Internal /External Fault259 SysIO Failure SysIO Function SysIO PPC Program CRC Test Internal260 SysIO Failuree SysIO Function SysIO Program RAM Monitor Internal263 ModuleSynchronization FaultSysIO Function Traffic Synchronization Monitor Internal264 SysIO Failure SysIO Function DSP Init Monitor Internal265 SysIO Failure SysIO Function DSP Program CRC Test Internal267 Dataload InhibitedRequest Fault ReportSysIO Function Dataload – Dataload Enable Monitor External269 Dataload InhibitedRequest Fault ReportSysIO Function Dataload – Air Ground Monitor External273 SysIO To TFC IMCTransmit FaultSysIO Function Intermodule Communication SysIO toTFC Transmit MonitorInternal278 SysIO – TFC CommFaultSysIO Function Traffic Receive Monitor Internal279 SysIO Health Fault SysIO Function Internal Power Supply Monitor Internal280 SysIO Health Fault SysIO Function Temperature Sensor Monitor Internal281 SysIO Health Fault SysIO Function Boot Config ROM Monitor Internal282 SysIO Health Fault SysIO Function NVRAM Monitor Internal299 SysIO Load ListCheck FaultSysIO Function SysIO Load List Check Test Internal303 TFC Load List CheckFaultSysIO Function TFC OPS Load List Check Test Internal304 SysIO Part NumberComp FaultSysIO Function SysIO Part Number Compatibility Test Internal305 TrafficPartNumberComp FaultSysIO Function Traffic Part Number Compatibility Test Internal310 Test Inhibited RequestFault ReportSysIO Function Initiated Test – Air Speed Monitor External311 Test Inhibited RequestFault ReportSysIO Function Initiated Test – Air Ground Monitor External339 ECU Fault ECU Function ECU Data Fault Monitor External340 Fan Fault Fan Function Fan Fault External343 SysIO – TFC CommFaultSysIO Function Traffic PTT Time-out Fault Internal346 SysIO – TFC CommFaultSysIO Function Traffic UIT Time-out Fault Internal360 ACAS Aural File Fault ACAS Function ACAS Aural File Load List Check Test InternalB-6
appendix B 523-0809018Table B-6. LRU Diagnostic Data, Fault Names and Categories. - ContinuedMoni-tor IDFault Name TSS-4100 FaultCategoryMonitor Name Internal /External Fault361 ECU Fault ECU Function ECU Write Protection Fault Monitor External362 ECU Fault ECU Function ECU Installation Part Number Fault Monitor External363 SysIO Part NumberComp FaultSysIO Function Top Level Load Set Mismatch Monitor Internal2048 Traffic Unit Failure ACAS & XPDRFunctionPPC Program Memory CRC Monitor Internal2049 Traffic Input Failure XPDR System Mode S Discrete Address Continuous Monitor External2050 Traffic Unit Failure ACAS & XPDRFunctionMode S Discrete Address Continuous Monitor Internal2053 Traffic Unit Failure ACAS & XPDRFunctionRadio Altitude Right Activity External2069 Traffic Unit Failure ACAS & XPDRFunctionReceiver Monitor Internal2071 Traffic Unit Failure ACAS & XPDRFunctionReceiver Frequency Lock Monitor Internal2072 Traffic Unit Failure ACAS & XPDRFunctionTransmitter Frequency Lock Monitor Internal2073 Traffic Unit Failure ACAS & XPDRFunctionTransmitter Power Monitor Internal2074 Traffic Unit Failure ACAS & XPDRFunctionTransmitter Calibration Pulse Power Monitor Internal2075 Traffic Unit Failure ACAS & XPDRFunctionTransmitter DAC Monitor Internal2076 Traffic Unit Failure ACAS & XPDRFunctionSwitch Card Monitor (Diode Monitor) Internal2077 Traffic Unit Failure ACAS & XPDRFunctionResolution Message Queue Full DSP-XPDR Mon Internal2078 Traffic Unit Failure ACAS & XPDRFunctionLink DSP Initialization Monitor Internal2079 Traffic Unit Failure ACAS & XPDRFunctionNVRAM Monitor Internal2080 XPDR Input Failure XPDR System Mode S Discrete Address Monitor External2083 Traffic Unit Failure ACAS & XPDRFunctionHardware Init Status Monitor Internal2084 Traffic Unit Failure ACAS & XPDRFunctionWatch Dog Timer Test Monitor Internal2085 Traffic Unit Failure ACAS & XPDRFunctionPower Supply Monitors InternalB-7
appendix B 523-0809018Table B-6. LRU Diagnostic Data, Fault Names and Categories. - ContinuedMoni-tor IDFault Name TSS-4100 FaultCategoryMonitor Name Internal /External Fault2086 Traffic Unit Failure ACAS & XPDRFunctionIOSM - FPGA Initialization Monitor Internal2087 Traffic Unit Failure ACAS & XPDRFunctionFPGA Health Status Monitor Internal2088 Traffic Unit Failure ACAS & XPDRFunctionTransponder/ACAS Interface Monitor Internal2089 Traffic Unit Failure ACAS & XPDRFunctionMode S DSP Initialization Monitor Internal2090 Traffic Unit Failure ACAS & XPDRFunctionMode S DSP heart Beat Monitor Internal2091 XPDR Input Failure XPDR System On Side GPS Time Mark Fault External2092 Bottom AntennaConnector FailureACAS & XPDRFunctionBottom Antenna Connector Monitor External2094 Top AntennaConnector FailureACAS & XPDRFunctionTop Antenna Connector Monitor External2096 Traffic Input Failure ACAS System Barometric Altitude Monitor External2097 Barometric AltitudeParametric FailureACAS System Barometric Altitude CRED Monitor External2098 XPDR Input Failure XPDR System Cross Side GPS Time Mark Fault External2100 ACAS Function Intruder Buffer Monitor Internal2102 Receiver CalibrationBottom AntennaFailureACAS Function Receiver Calibration Bottom Antenna Monitor Internal2103 Receiver CalibrationTop Antenna FailureACAS Function Receiver Calibration Top Antenna Monitor Internal2104 ACAS Failure ACAS Function Resolution Message Queue Full XPDR-ACASMonitorInternal2105 Traffic Input Failure ACAS System Resolution Advisory (RA) Display 1 BITE External2106 Traffic Input Failure ACAS System Resolution Advisory (RA) Display 2 BITE External2107 Traffic Input Failure ACAS System RA Display 1 Status Discrete External2108 Traffic Input Failure ACAS System RA Display 2 Status Discrete External2109 Traffic Advisory (TA)Display 1 StatusDiscrete FailureACAS System Traffic Advisory (TA) Display 1 Status Discrete Internal2110 Traffic Advisory (TA)Display 2 StatusDiscrete FailureACAS System Traffic Advisory (TA) Display 2 Status Discrete Internal2112 XPDR Failure XPDR Function Acquisition Squitter Monitor InternalB-8
appendix B 523-0809018Table B-6. LRU Diagnostic Data, Fault Names and Categories. - ContinuedMoni-tor IDFault Name TSS-4100 FaultCategoryMonitor Name Internal /External Fault2113 ACAS / XPDR ControlPanel Validity FailureACAS & XPDRSystemAcquisition Squitter Monitor External2114 ACAS / XPDR ControlPanel Validity FailureACAS & XPDRSystemACAS Control Panel Validity Monitor External2135 Traffic Unit Failure ACAS & XPDRFunctionACAS 1Hz Producer IOSM Monitor Internal2136 Traffic Unit Failure ACAS & XPDRFunctionXPDR 100 Hz Producer Monitor Internal2138 Traffic Unit Failure ACAS & XPDRFunctionXPDR 10 Hz Producer IOSM Monitor Internal2139 Traffic Unit Failure ACAS & XPDRFunctionCDTI 10 Hz Producer IOSM Monitor Internal2140 Traffic Unit Failure ACAS & XPDRFunctionADSB 10 Hz Producer Monitor Internal2145 Traffic Unit Failure ACAS & XPDRFunctionCDTI to IOSM Display Data Monitor Internal2146 Traffic Unit Failure ACAS & XPDRFunctionACAS 1 Hz Producer CDTI Monitor Internal2149 Traffic Unit Failure ACAS & XPDRFunctionLink DSP CRC Monitor InternalB-9
appendix B 523-0809018Table B-6. LRU Diagnostic Data, Fault Names and Categories. - ContinuedMoni-tor IDFault Name TSS-4100 FaultCategoryMonitor Name Internal /External Fault2150 Traffic Unit Failure ACAS & XPDRFunctionLink DSP CRC Monitor Internal2151 Traffic Unit Failure ACAS & XPDRFunctionMode S DSP CRC Monitor Internal2152 Traffic Unit Failure ACAS & XPDRFunctionConfiguration Monitor Internal2157 Traffic Input Failure ACAS System Pitch Angle Input Monitor External2158 Traffic Input Failure ACAS System Roll Angle Input Monitor External2160 Traffic Input Failure ACAS System Mag Heading Input Monitor External2168 Traffic Input Failure ACAS System Radio Altitude Left Activity External2177 Traffic Unit Failure ACAS & XPDRFunctionACAS Null Pointer Monitor Internal2178 Radio AltitudeParametric FailureACAS System Radio Altitude Parametric Failure External2180 XPDR Failure XPDR Function Extended Squitter Monitor Internal2190 Bottom AntennaFailureACAS & XPDRSystemBottom Forward Monitor External2191 Bottom AntennaFailureACAS & XPDRSystemBottom Right Monitor External2192 Bottom AntennaFailureACAS & XPDRSystemBottom Left Monitor External2193 Bottom AntennaFailureACAS & XPDRSystemBottom Aft Monitor External2194 Top Antenna Failure ACAS & XPDRSystemTop Forward Monitor External2195 Top Antenna Failure ACAS & XPDRSystemTop Right Monitor External2196 Top Antenna Failure ACAS & XPDRSystemTop Left Monitor External2197 Top Antenna Failure ACAS & XPDRSystemTop Aft Monitor ExternalB-10
appendix B 523-0809018B.1.5. Label 354 TSS-4100 Diagnostic Word 3.Refer to Table B-7 for the definition of this word and a possible solution to the indicated issue.Table B-7. Label 354 TSS-4100 Diagnostic Word 3Bit Label 354- TSS-4100 Diagnostics Word 3 Possible Solution9SDI*10 SDI*11 LMP - 1C/D (Control A) (Active = 0 Inactive = 1) Check wiring from appropriate controller to the TSS.Repair wiring or replace the appropriate unit.12 LMP - 6G/H (GPS #1) (Active = 0 Inactive = 1) (Optional connection) Check wiring from the onside GPS.Repair wiring or replace the GPS.13 LMP - 7C/D (Control B) (Active = 0 Inactive = 1) Check wiring from appropriate controller to the TSS.Repair wiring or replace the appropriate unit.14 LMP - 7E/F (ADS-B #1) (Active = 0 Inactive = 1)15 LMP - 7G/H (ADS-B #2) (Active = 0 Inactive = 1)16 LMP - 7J/K (Data Load) (Active = 0 Inactive = 1)17 LMP - 8G/H (IAPS #1) (Active = 0 Inactive = 1) Check wiring from the onside I/O Concentrator. Repairwiring or replace the concentrator.18 LMP - 8J/K (CMU #1) (Active = 0 Inactive = 1)19 RMP - 1C/D (Control C) (Active = 0 Inactive = 1) (Optional connection) Check wiring from appropriatecontroller to the TSS. Repair wiring or replace theappropriate unit.20 RMP - 2G/H (GPS #2) (Active = 0 Inactive = 1) (Optional connection) Check wiring from the cross-sideGPS. Repair wiring or replace the GPS.21 RMP - 7C/D (A768) (Active = 0 Inactive = 1)22 RMP - 8G/H (IAPS #2) (Active = 0 Inactive = 1) Check wiring from the cross-side I/O Concentrator.Repair wiring or replace the concentrator.23 RMP - 8J/K (CMU #2) (Active = 0 Inactive = 1)24 RMP - 8A/B (XT #2) (Active = 0 Inactive = 1) Check both the XT and TX bus wiring; check to see if offside TDR is working properly.25 to 29 Pad30 SSM**31 SSM**32 Odd Parity*SDI Code: Bit 10 Bit 9 LRU Number **SSM Code: Bit 31 Bit 30 LRU Status00NotUsed 00Normal01Left 01NotUsed10Right 10Test1 1 Not Used 1 1 Not UsedB-11
appendix B 523-0809018B.1.6. Label 355 TSS-4100 Diagnostic Word 4.Refer to Table B-8 for the definition of this word.Table B-8. Label 355 TSS-4100 Diagnostic Word 4Bit Label 355 −TSS Diagnostic Word 49SDI*10 SDI*14 to 11 Voltage Index (Range: 1 - 12)1) Traffic reported 33VDC (LVDS message from Traffic)2) Power Supply Side A 12 VDC (ADC Channel 12)3) SysIO GAIN_REF (ADC Channel 10)4) SysIO Top Temp (ADC Channel 15)5) SysIO Bottom Temp (ADC Channel 14)6) SysIO +8 VDC (ADC Channel 6)7) SysIO - 8 VDC (ADC Channel 7)8) SysIO Post Switch 12 VDC (ADC Channel 8)9) SysIO 3.3 VDC (ADC Channel 4)10) SysIO 1.5 VDC (ADC Channel 2)11) SysIO DSP Core Voltage (ADC Channel 0)12) SysIO RAM Voltage (ADC Channel 9)15 Pad16 Pad28 to 17 12-bit Voltage Value (Range: 0 - 0xFFF)NOTE0xBAD means no voltage present to report (1011 1010 1101)29 Pad30 SSM**31 SSM**32 Odd Parity*SDI Code: Bit 10 Bit 9 LRU Number **SSM Code: Bit 31 Bit 30 LRU Status00NotUsed 00Normal01Left 01NotUsed10Right 10Test1 1 Not Used 1 1 Not UsedB.1.6.1. TSS-4100 Label 355 Voltage Decode. Refer to Table B-7 to determine what the reading is and whether or not thereading is within the specified range for the TSS-4100. In the Decode column,V = (2.5 / 4096) Xwhere X is the raw decimal value encoded in bits 28 to 17.B-12
appendix B 523-0809018Table B-9. Label 355 Voltage DecodeVoltage Index Decode Nominal Upper Limit Lower Limit1 (VDC) = V * 32.66 31.5 36.3 29.72 (VDC) = V * 11.01 12.0 12.60 11.403 (VDC) = V 1.5 1.575 1.4254(°C)=(V0.424) *160Ambient temp N/A5(°C)=(V0.424) *160Ambient temp N/A6 (VDC) = V * 5.71 8.0 8.22 7.547 (VDC) = V * -4.21 -8.0 -7.24 -8.348 (VDC) = V * 10.53 12.0 12.60 11.409 (VDC) = V * 2.00 3.3 3.44 3.1610 (VDC) = V 1.5 1.57 1.4311 (VDC) = V 1.26 1.32 1.2012 (VDC) = V 1.25 1.35 1.15B-13
appendix B 523-0809018B.1.7. Label 350 ACAS Diagnostics.Refer to Table B-10 for the definition of this word and a possible solution to the indicated issue. This label is created to replicate anequivalent word from Rockwell Collins TTR series of TCAS units. This is not sent through the TSS #X output busses. This labelshould only be used as a supplement to Label 351 and Label 354 on the TSS #X output busses.NOTEThis label is sent to the displays on the TA/RA busses.Table B-10. Label 350 ACAS Diagnostics WordBit Label 350 −ACAS Diagnostics Possible Solution9Pad10 Pad11 TSS ACAS Fail (Normal = 0 Failure = 1) Check for other faults.12 Upper Antenna (Normal = 0 Failure = 1) Check wiring to the top antenna; replace antenna if thereis no wiring problem or a TSS unit fault.13 Lower Antenna (Normal = 0 Failure = 1) Check wiring to the bottom antenna; replace antenna ifthere is no wiring problem or a TSS unit fault.14 Radio Altimeter Input Bus #1 (Normal = 0 Inactive=1)Check the units and the wiring path from radio altimeter#1 to the I/O Concentrator to the TSS.15 Radio Altimeter Input Bus #2 (Normal = 0 Inactive=1)Check the units and the wiring path from radio altimeter#2 to the I/O Concentrator to the TSS.16 TSS Transponder (Active or Stby = 0 Fail = 1) Check for other faults.17 X-Side Transponder (Active or Stby = 0 Fail = 1) Check wiring to the Cross side TDR; replace TDR ifnecessary.18 Attitude Input Bus (Normal = 0 Inactive = 1) Check the units and the wiring path from the selectedAHRS/IRS to the I/O Concentrator to the TSS.19 Magnetic Heading Input Bus (Normal = 0 Inactive=1)Check the units and the wiring path from the selectedAHRS/IRS to the I/O Concentrator to the TSS.20 TCAS System Status (Normal = 0 Failure = 1) Check for other faults.21 Pad22 Pad23 TA 1 Display System Status (Normal = 0 Failure = 1) Check the ground strap to the TA #1 discrete.24 TA 2 Display System Status (Normal = 0 Failure = 1) Check the ground strap to the TA #2 discrete.25 RA 1 Display System Status (Normal = 0 Failure = 1) Check the discrete wire from the displays to the TSS;check the RA/TA bus to the appropriate displays. Ifthe wiring is OK AND there is no TSS unit fault, thenReplace Display.26 RA 2 Display System Status (Normal = 0 Failure = 1) Check the discrete wire from the displays to the TSS;check the RA/TA bus to the appropriate displays. Ifthe wiring is OK AND there is no TSS unit fault, thenReplace Display.B-14
appendix B 523-0809018Table B-10. Label 350 ACAS Diagnostics Word - ContinuedBit Label 350 −ACAS Diagnostics Possible Solution27 Not Used28 Not Used29 Not Used30 SSM*31 SSM*32 Odd Parity*SSM Code: Bit 31 Bit 30 LRU Status00Normal01NotUsed10Test11NotUsedB-15
appendix B 523-0809018B.2. TDR-94D DIAGNOSTIC CODES.Refer to Table B-11. A traffic control unit such as the CTL-92(), or a maintenance diagnostic system, lists TDR-94D diagnosticcodes.Table B-11. TDR-94D Diagnostic Codes.DIAGNOSTIC DISPLAYPRIMARYCODESECONDARYCODE DESCRIPTION T1 F/WNone(refer to Note)No Fault FoundNOTEWith a No Fault Found condition, a pulsating AL will appear in the upper window and the baro altitudewill appear in the lower window.10 Power Supply Diagnostics (Note 1) (Note 1)11 +5-V dc Yes Yes12 + 70-V dc No No13 +35-V dc No No14 LVPS No No20 Transmitter / Modulator diagnostics (Note 2) (Note 2)21 Final stage over current Yes Yes22 Top antenna low-power output No No23 Bottom antenna low-power output No No24 Transmitter over temperature No No30 Synthesizer diagnostics No No31 Synthesizer lock detect No No32 Synthesizer low-power detect No No40 Receiver / IF diagnostics No No41 Top receiver channel No No42 Bottom receiver channel No No43 Top Differential Phase Shift Keying (DPSK)demodulatorNo No44 Bottom DPSK demodulator No No50 Program memory (ROM) diagnostics Yes Yes51 High-byte ROM Yes Yes52 Low-byte ROM Yes Yes53 Both ROM chips Yes Yes60 Volatile memory (RAM) diagnostics Yes Yes61 High-byte RAM Yes YesB-16
appendix B 523-0809018Table B-11. TDR-94D Diagnostic Codes. - ContinuedDIAGNOSTIC DISPLAYPRIMARYCODESECONDARYCODE DESCRIPTION T1 F/W62 Low-byte RAM Yes Yes63 Both RAM chips Yes Yes64 Cache RAM Yes Yes65 Cache RAM and high-byte RAM Yes Yes66 Cache RAM and low-byte RAM Yes Yes67 Cache RAM and both RAM chips Yes Yes68 Dual Port RAM Yes Yes70 Non-Volatile RAM (NVRAM) diagnostics No No80 Serial input control bus diagnostics (Note 4) No81 ARINC 429 control UART (Note 4) No82 ARINC 429 control Port A inactive (Note 4) No83 ARINC 429 control Port B inactive (Note 4) No84 ARINC 429 control Port C inactive (Note 4) No85 CSDB control input Port A inactive (Note 4) No87(-004 TDR-94D only)AIS/Air Data System (ADS) UART failure No No88(-004 TDR-94D only)GPS UART failure No No89(-004 TDR-94D only)IRS UART failure No No90 Serial altitude input diagnostics No No91 ARINC 429/575 altitude UART No No92 ARINC 429/575 input Port A inactive No No93 ARINC 429/575 input Port B inactive No No94 CSDB altitude input Port A inactive No No95 CSDB altitude input Port B inactive No No99 No data received — —A0 ADLP communication diagnostics No NoA1 ADLP com A/B UART No NoA2 ADLP com A/B bus inactive No NoA3 ADLP com C/D UART No NoA4 ADLP com C/D bus inactive No NoB0 TCAS communication diagnostics No NoB1 TCAS UART No NoB-17
appendix B 523-0809018Table B-11. TDR-94D Diagnostic Codes. - ContinuedDIAGNOSTIC DISPLAYPRIMARYCODESECONDARYCODE DESCRIPTION T1 F/WB2 TCAS unit — —B3 TCAS bus inactive No NoB4 TCAS protocol error No NoC0 Squitter diagnostics No YesC1(TDR-94D only)Top channel squitter No YesC2(TDR-94D only)Bottom channel squitter No YesD0 (TDR-94D only) Diversity diagnostic No YesE0 Message processor diagnostics No NoE1(TDR-94D only)Top channel message processor, soft failure No NoE2 Bottom channel message processor, soft failure No NoE3 Top channel message processor, hard failure Yes YesE4 Bottom channel message processor, hard failure Yes YesF0 Configuration diagnostics No NoF1 Mode S discrete address changed No NoF2 TCAS selection changed No NoF3 Altitude units selection changed No NoF4 Max airspeed program selects changed No NoF5 Port selects changed No NoF6 SDI selects changed No NoF7 Single antenna selection changed No NoF8 ADLP selection changed No NoF9-FE Not assigned No NoB-18
appendix B 523-0809018Table B-11. TDR-94D Diagnostic Codes. - ContinuedDIAGNOSTIC DISPLAYPRIMARYCODESECONDARYCODE DESCRIPTION T1 F/WFF Unacceptable Mode S address selected (all addresslines identical)Yes YesNOTE1. Transmitter is inhibited (TI) and failure warn (F/W1) output (P1-31) is set only if a diagnostic Code 11 is detected.2. Transmitter is inhibited and F/W1 discrete is set only if a diagnostic Code 21 is detected.3. Transmitter is inhibited and TDR-94/TDR-94D is set to standby only if all selected control inputs are nonfunctional.4. Transmitter is inhibited and TDR-94/TDR-94D is set to standby only if the control bus failure is detected on the selectedcontrol bus.5. Transmitter is inhibited and TDR-94/TDR-94D is set to standby only if serial control is selected and all serial inputs arenonfunctional.6. Except for 00, 70, and D0, primary diagnostics are not displayed.7. F/W SET refers to:• TDR-94D fault monitor discrete output, P1-31, set to high level• TDR-94D CSDB data word Label 1F, Byte-1, Bit-7, set to logic 0• TDR-94D ARINC 429 SSM and other data bits related to diagnostics set to the appropriate fault level.B-19/(B-20 Blank)
523-0809018APPENDIX CBuses and Other InterfacesC.1. INTERFACE TYPES.The various Line Replaceable Unit (LRU) in the Traffic Surveillance System (TSS) interface with each other and other systemsusing primarily ARINC 429 or discrete interfaces. Each bus has a unique name. The buses are primarily ARINC 429 or discreteformat. Refer to Table C-1 for a list of the possible discrete and ARINC bus names. Refer to Table C-2 through Table C-16 for listsof the word labels on each digital bus. Interfaces to the ECU, audio systems, and test equipment are not described here.Table C-1. Buses and DiscretesName of Bus or Discrete Type of Bus or DiscreteTSS Active (to XTDR) Discrete OutputVisual Annun C Discrete OutputVisual Annun P Discrete OutputVisual Annun TA Discrete OutputFan Off (100ma) Discrete OutputAural Advisory C Discrete OutputAural Advisory P Discrete OutputAural Advisory TA Discrete OutputXTDR Active (from XTDR) Discrete InputExtended Squitter Disable Discrete InputPerf Limit Discrete InputSimulator Enable Discrete InputAir/Gnd(F) #1 Discrete InputFan Monitor Discrete InputAir/Gnd(F) #2 Discrete InputClimb Inhibit #1 Discrete InputClimb Inhibit #2 Discrete InputClimb Inhibit #3 Discrete InputClimb Inhibit #4 Discrete InputIncrease Climb Inh #1 Discrete InputIncrease Climb Inh #2 Discrete InputIncrease Climb Inh #3 Discrete InputIncrease Climb Inh #4 Discrete InputAdvisory Inhibit #1 Discrete InputAdvisory Inhibit #2 Discrete InputC-1
appendix C 523-0809018Table C-1. Buses and Discretes - ContinuedName of Bus or Discrete Type of Bus or DiscreteAdvisory Inhibit #3 Discrete InputAdvisory Inhibit #4 Discrete InputTA Display Valid #1 Discrete InputTA Display Valid #2 Discrete InputRA Display Valid #1 Discrete InputRA Display Valid #2 Discrete InputBurst Tune Select Discrete InputControl Port Select 0 Discrete InputControl Port Select 1 Discrete InputAdvisory Annun Cancel Discrete InputData Load Enable Discrete InputSDI Position 1 Discrete InputSDI Position 2 Discrete InputTSS-1 Output BusTSS-2 Output BusTSS-3 (Data Load) Output BusTA/RA-1 Output BusTA/RA-2 Output BusTX2 (TSS to TDR) (or ADLP) Output BusADS-B #1 (Provision) Output BusCMU (Provision) Output BusGeneral Purpose #1 (Provision) Output BusControl A Input BusControl B Input BusControl C Input BusIAPS #1 Input BusIAPS #2 Input BusGPS #1 Input BusGPS #2 Input BusXT2 (TDR to TSS) (or ADLP) Input BusData Load Input BusCMU #1 (Provision) Input BusCMU #2 (Provision) Input BusADS-B #1 (Provision) Input BusC-2
appendix C 523-0809018Table C-1. Buses and Discretes - ContinuedName of Bus or Discrete Type of Bus or DiscreteADS-B #2 (Provision) Input BusA768 Future (Provision) Input BusC-3
appendix C 523-0809018C.2. TSS DISCRETE OUTPUTS.Refer to Table C-2 for a list of the discrete outputs for the TSS and their expected destinations.Table C-2. TSS Discrete OutputsPin Name Conn Pin Expected Connection/NotesTSS Active (to XTDR) LMP 2E Cross side transponder, even if it is another TSSVisual Annun C LMP 3A Not normally connectedVisual Annun P LMP 3B Not normally connectedVisual Annun TA LMP 3C Not normally connectedFan Off (100ma) LMP 3D Connect to TSM to control the fanAural Advisory C LMP 4A May be connected as a push-to-talk for audio outputsAural Advisory P LMP 4B May be connected as a push-to-talk for audio outputsAural Advisory TA LMP 4C May be connected as a push-to-talk for audio outputsC-4
appendix C 523-0809018C.3. TSS DISCRETE INPUTS.Refer to Table C-3 for a list of the discrete inputs to the TSS and their expected connections.Table C-3. TSS Discrete InputsPin Name Conn Pin Expected Connection/NotesXTDR Active (from XTDR) LMP 2J Cross side transponderExtended Squitter Disable LMP 2K This will only be connected if there is a switch to turn offextended squittersPerf Limit LMP 3E This is an ARINC 735 (TCAS) pin that is not usually usedSimulator Enable LMP 3F Not normally connectedAir/Gnd(F) #1 LMP 3G Not normally connected use Air/Gnd #2Fan Monitor LMP 3K Connect to TSM to monitor fan speedAir/Gnd(F) #2 LMP 4H Connect to Weight on Wheels indicatorClimb Inhibit #1 LMP 11A This is an ARINC 735 (TCAS) pin that is not usually usedClimb Inhibit #2 LMP 11B This is an ARINC 735 (TCAS) pin that is not usually usedClimb Inhibit #3 LMP 11C This is an ARINC 735 (TCAS) pin that is not usually usedClimb Inhibit #4 LMP 11D This is an ARINC 735 (TCAS) pin that is not usually usedIncrease Climb Inh #1 LMP 11E This is an ARINC 735 (TCAS) pin that is not usually used; insome installations connected to ADC to inhibit increase climbsat some altitudeIncrease Climb Inh #2 LMP 11F This is an ARINC 735 (TCAS) pin that is not usually used; insome installations connected to ADC to inhibit increase climbsat some altitudeIncrease Climb Inh #3 LMP 11G This is an ARINC 735 (TCAS) pin that is not usually used; insome installations connected to ADC to inhibit increase climbsat some altitudeIncrease Climb Inh #4 LMP 11H This is an ARINC 735 (TCAS) pin that is not usually used; insome installations connected to ADC to inhibit increase climbsat some altitudeAdvisory Inhibit #1 LMP 10J Not usually used; puts TCAS into standbyAdvisory Inhibit #2 LMP 10K Connect to TAWS or CAS system; puts TCAS into TA onlymode and inhibits all auralsAdvisory Inhibit #3 LMP 11J Connect to TAWS or CAS system; puts TCAS into TA onlymode and inhibits all auralsAdvisory Inhibit #4 LMP 11K Connect to TAWS or CAS system; puts TCAS into TA onlymode and inhibits all auralsTA Display Valid #1 RMP 10A Usually strapped to ground; for use on TA only displayTA Display Valid #2 RMP 10B Usually strapped to ground; for use on TA only displayRA Display Valid #1 RMP 10C Connect to pilot side displaysRA Display Valid #2 RMP 10D Connect to co-pilot side displaysC-5
appendix C 523-0809018Table C-3. TSS Discrete Inputs - ContinuedPin Name Conn Pin Expected Connection/NotesBurst Tune Select RMP 10E If control port C is a burst tuner, connect to same source asControl Port Select 1 pin (RMP 10G)Control Port Select 0 RMP 10F See control bus section in this appendixControl Port Select 1 RMP 10G See control bus section in this appendixAdvisory Annun Cancel RMP 10H Not usually connected; cancels aurals, but RA info still senton TA/RA busData Load Enable RMP 10K Connect to data load enable switchSDI Position 1 RMP 11J *Refer to NoteSDI Position 2 RMP 11K *Refer to NoteNOTETSSSDIstrapencodingisasfollows:SDI Coding Side 1 - Left Side 2 - Right Not Used Not UsedSDI Position 1 (RMP11J)Gnd Open Open GndSDI Position 2 (RMP11K)OpenGndOpenGndC-6
appendix C 523-0809018C.4. TSS A429 OUTPUT BUSES.Refer to Table C-4 for a list of the ARINC 429 output buses and their expected destinations.Table C-4. TSS A429 Output BusesPin Name Con-nectorPin A Pin B DestinationTSS-1 LMP 7A 7B Onside controller or concentratorTSS-2 LMP 1A 1B Offside controller or concentratorTSS-3 (Data Load) RMP 1A 1B Data loader or maintenance systemTA/RA-1 LMP 1E 1F Pilot side displaysTA/RA-2 RMP 1E 1F Copilot side displaysTX2 (TSS to TDR) (or ADLP) RMP 8D 8C Cross-side TDRADS-B #1 (Provision) LMP 9E 9F Not connectedCMU (Provision) RMP 9E 9F Not connectedGeneral Purpose #1 (Provision) LMP 9D 9C Not connectedC.4.1. TSS-1 and TSS-2 Output Bus Labels.Refer to Table C-5 for a list of the labels output on the TSS-1 and the TSS-2 output buses and their expected output rate.Table C-5. TSS-1 and TSS-2 Output Bus LabelsLabel Parameter Name Rate (ms)011 TSS Configuration Data 100013 TCAS Control Word 100015 Altitude Select Limits 100016 TCAS/Mode-S Transponder 100031 ATC Transponder 200203 Pressure Altitude 200204 Baro-Corrected Altitude 200226 Data Load Output On Demand233 Aircraft Ident Word 1 1000234 Aircraft Ident Word 2 1000235 Aircraft Ident Word 3 1000236 Aircraft Ident Word 4 1000237 Aircraft Ident Word 5 1000243 Aural Annunciation 50275 Mode S Address Part 1 1000276 Mode S Address Part 2 1000C-7
appendix C 523-0809018Table C-5. TSS-1 and TSS-2 Output Bus Labels - ContinuedLabel Parameter Name Rate (ms)301 Aircraft Registry Word 1 1000302 Aircraft Registry Word 2 1000303 Aircraft Registry Word 3 1000350 TDR Maintenance Word 500351 TSS-4100 Diagnostic Word 1 500352 CDU Diagnostic Word 1 500353 TSS-4100 Diagnostic Word 2 500354 TSS-4100 Diagnostic Word 3 500355 TSS-4100 Diagnostic Word 4 500356 ARINC 604 to CMS On Demand357 TSS-4100 Diagnostic Word 5 (Reserved) 500377 TSS-4100 Equipment Identification 1000C.4.2. TSS-3 Output Bus Labels.Refer to Table C-6 for a list of the labels output on the TSS-3 output bus and their expected output rate.Table C-6. TSS-3 Output Bus LabelsLabel Parameter Name Rate (ms)011 TSS Configuration Data 100226 Data Load Output On Demand350 TDR Maintenance Word 500351 TSS-4100 Diagnostic Word 1 500352 CDU Diagnostic Word 1 500353 TSS-4100 Diagnostic Word 2 500354 TSS-4100 Diagnostic Word 3 500355 TSS-4100 Diagnostic Word 4 500356 ARINC 604 to CMS On Demand357 TSS-4100 Diagnostic Word 5 (Reserved) 500361 NVRAM Download Header Words (Shop Mode) On Demand362 NVRAM Download Data Words (Shop Mode) On Demand377 TSS-4100 Equipment Identification 1000C.4.3. TA/RA-1 and TA/RA-2 Output Bus Labels.Refer to Table C-7 for a list of the labels output on the TA/RA-1 and TA/RA-2 output buses and their expected output rate.C-8
appendix C 523-0809018Table C-7. TA/RA-1 and TA/RA-2 Output Bus LabelsLabel Parameter Name Rate (ms)013 TCAS Control Word 100015 Altitude Select Limits 100016 TCAS/Mode-S Transponder 100130 Intruder Range Block131 Intruder Altitude Block132 Intruder Bearing Block203 Pressure Altitude 500204 Baro-Corrected Altitude 500270 Vertical Resolution Advisory 500274 TX Word 2 500320 Magnetic Heading 500350 ACAS Diagnostics 500357 Intruder File, Block Protocol Block377 ACAS Equipment ID 500C.4.4. TX-2 Output Bus Labels.Refer to Table C-8for a list of the labels output on the TX-2 output bus and their expected output rate.NOTEThe TSS only supports the DO-185A XT/TX protocol. It does not support the older TSO C119A protocol.Table C-8. TX-2 Output Bus LabelsLabel Parameter Name Rate (ms)270 TGD Protocol On Demand274 TX Word 2 200275 TX Word 3 On DemandC-9
appendix C 523-0809018C.5. A429 INPUT BUSES.Refer to Table C-9 for a list of the A429 Input Buses and their expected source.Table C-9. A429 Input BusesPin Name Con-nectorPin A Pin B SourceControl A LMP 1D 1C Offside controller, directly or via RIUControl B LMP 7D 7C Onside controller, directly or via RIUControl C RMP 1D 1C Third control sourceIAPS #1 LMP 8H 8G On side data concentratorIAPS #2 RMP 8H 8G Cross-side data concentratorGPS #1 LMP 6H 6G On side GPSGPS #2 RMP 2H 2G Cross-side GPSXT2 (TDR to TSS) (or ADLP) RMP 8A 8B Cross-side TDRData Load LMP 7J 7K Data loaderCMU #1 (Provision) LMP 8J 8K Not connectedCMU #2 (Provision) RMP 8J 8K Not connectedADS-B #1 (Provision) LMP 7E 7F Not connectedADS-B #2 (Provision) LMP 7H 7G Not connectedA768 Future (Provision) RMP 7D 7C Not connectedC.5.1. Control Bus Selection.The control port is selected using the control-port select discretes as encoded in Table C-10.Table C-10. Control Bus SelectionControl Port Select Coding Ctrl Bus A Ctrl Bus B Ctrl Bus C Not UsedControl Port Select 0 (RMP 10F) Gnd Open Open GndControl Port Select 1 (RMP 10G) Open Open Gnd GndNOTEIf both the control-port select 0 and control-port select 1 pins are grounded, then the control bus selection is invalid.If the installation will cause this to happen, it is recommended that the source of the discrete for selecting controlbus C is connected to the burst tuning discrete.C.5.2. Control Bus Labels.Refer to Table C-11 for a list of the labels expected to be received on the control buses and notes regarding their use.C-10
appendix C 523-0809018Table C-11. Control Bus LabelsLabel Parameter Name Notes006 Mode-S Address Set Word 1 Not required; only received when controller is attemptingto set the Mode S address007 Mode-S Address Set Word 2 Not required; only received when controller is attemptingto set the Mode S address013 TCAS Control Word Not used by TSS; passed through to display015 TCAS Altitude Select Limits Not used by TSS; passed through to display016 TCAS/Mode-S Transponder Required; TCAS control word027 TSS Data Load Receive (Dataloader) TSS Control B port only; may data load through this port031 Mode-S ATC Control Required; transponder control word203 Pressure Altitude (ADC) Required, but may be passed through concentrated busesinstead of through controller204 Baro-Corrected Altitude (ADC) May be passed through concentrated buses instead ofthrough controller227 ARINC 604 from CMS TSS Control B port only; maintenance system may requestECU data through this port233 Aircraft Ident Word 1 Required, but may be passed through concentrated busesinstead of through controller234 Aircraft Ident Word 2 Required, but may be passed through concentrated busesinstead of through controller235 Aircraft Ident Word 3 Required, but may be passed through concentrated busesinstead of through controller236 Aircraft Ident Word 4 Required, but may be passed through concentrated busesinstead of through controller237 Aircraft Ident Word 5 May be passed through concentrated buses instead ofthrough controller; this label is not present from allsources of flight ID will usually only have labels 233236 available350 CDU Diagnostics Word 1 (CDU) Not required; only needed if the controller does not haveits own interface to the maintenance system360 Download NVRAM Request (Shop Mode) TSS Control B port only while in shop mode; response toa request to download NVRAMC.5.3. Concentrated Bus Inputs.It is expected that the left and right transponders, whether the transponder is a TSS or a TDR, will receive exactly the same infor-mation. This may be done either through separate or through shared concentrated buses. The only difference is that data will comein from a different side. Table C-12lists the TDR concentrated bus inputs and the TSS bus inputs and how they correspond.C-11
appendix C 523-0809018Table C-12. Concentrated Bus InputsBus Source TDR Bus TSS BusOnside data concentrator FMS/IRS IAPS #1Cross-side data concentrator AIS/ADS IAPS #2C.5.3.1. The following figure is of the expected concentrated bus architecture with a right TSS and a left TDR using a single outputbus from both the left and the right concentrator.Figure C-1. Bus Architecture, TSS (R) and TDR (L)C.5.3.2. A summary of the data sources that are sorted based on SDI is below. Data from all other sources are sorted by the busthat the data is received.• Radio Altimeter• PFD• ADC• AHC/IRS.C.5.3.3. Here is a list of the labels that can be received on the concentrated buses, the ultimate expected source of the data, andnotes regarding their use. Not Required does not mean that it is not desired or will not be used – it means that at this time it is nota required parameter.C-12
appendix C 523-0809018Label Parameter Name Notes076 GNSS Altitude (MSL) (GPS) May be on GPS bus101 Selected Heading/Track Required for ADS-B102 Selected Altitude Either this or label 226 required for enhanced surveillance;102 used for selected altitude that comes from a sourceother than the FMS103 GPS Track Angle (GPS) Required for ADS-B, but may be on GPS bus110 GNSS Latitude - Coarse (GPS) Required for ADS-B, but may be on GPS bus111 GNSS Longitude - Coarse (GPS) Required for ADS-B, but may be on GPS bus112 GNSS Ground Speed (GPS) Required for ADS-B, but may be on GPS bus120 GNSS Latitude - Fine (GPS) Required for ADS-B, but may be on GPS bus121 GNSS Longitude - Fine (GPS) Required for ADS-B, but may be on GPS bus130 Horizontal Integrity Limit (GPS) Required for ADS-B, but may be on GPS bus133 Vertical Integrity Limit (GPS) Required for ADS-B, but may be on GPS bus136 Vertical Figure of Merit (GPS) Required for ADS-B, but may be on GPS bus151 GNSS UTC (Time) (GPS) Required for ADS-B, but may be on GPS bus164 Radio Height (RALT) Required165 Vertical Velocity (GPS) Required for ADS-B, but may be on GPS bus166 GNSS N/S Velocity (GPS) Required for ADS-B, but may be on GPS bus174 GNSS E/W Velocity (GPS) Required for ADS-B, but may be on GPS bus175 PFD Mode Select Word (PFD) Required; use bits 11, 12, 13, 15, & 25-28203 Pressure Altitude (ADC) Required, but may be received on selected control bus204 Baro-Corrected Altitude (ADC) May be on selected control bus205 Mach (ADC) Required206 Computed Airspeed (ADC) Required210 True Airspeed (BNR) (ADC) Required212 Altitude Rate (ADC) Required213 Static Air Temperature (BNR) (ADC) Not required217 Static Pressure (Hg) SSE Corrected (ADC) Not required226 Target Altitude (From FMS) Either this or label 102 required for enhanced surveillance;226 used for target altitude that comes from the FMS240 Barometric Correction (ADC) Required247 Horizontal Figure of Merit (GPS) Required for ADS-B, but may be on GPS bus253 FGC Mode Word 2 (FGC) Required; only use bit 19261 GNSSDate(GPS) MaybeonGPSbus273 GNSS Sensor Status (GPS) Required for ADS-B, but may be on GPS bus301 Aircraft Registry Word 1 (Central Maint) Not requiredC-13
appendix C 523-0809018Label Parameter Name Notes302 Aircraft Registry Word 2 (Central Maint) Not required303 Aircraft Registry Word 3 (Central Maint) Not required310 Present Position Latitude (FMS) Not required, but desired as backup to GPS position311 Present Position Longitude (FMS) Not required, but desired as backup to GPS position312 Ground Speed (FMS) Required313 Track Angle (True) (FMS) Required314 True Heading (FMS) Not required315 Wind Speed (FMS) Not required316 Wind Direction (FMS) (Reserved) Not required317 Track Angle, Magnetic (IRS) Not required320 Magnetic Heading (AHC) Required must be magnetic heading, not displayedheading324 Pitch Angle (IRS) Not required325 Roll Angle (IRS) Required335 Track Angle Rate (IRS) Required, but known that it is not available on an AHRSsystem; for new AHRS installations it is expected that theFMS will calculate this value and it will be received aslabel 336336 Track Angle Rate (FMS) Required see above365 Inertial Vertical Speed (IRS) Required, may be from FMS instead of IRS366 North/South Velocity (FMS) Not required, but desired as backup to GPS velocity367 East/West Velocity (FMS) Not required, but desired as backup to GPS position370 GNSS Altitude (HAE) (GPS) Required for ADS-B, but may be on GPS bus376 PFD Discrete Wd 2 (PFD) Required; using bits 27-28C.5.4. GPS Input Data.GPS Input Data section includes information about:• GPS Bus Labels•GPSDataLatency• GPS Data/Time Mark Input Correlation• Single vs Dual GPS Installation.C.5.4.1. GPS Bus Labels. Refer to Table C-13 for a listing of the data used from the ARINC 429 data block coming from aGPS.Table C-13. GPS Bus LabelsLabel Parameter Name076 GNSS Altitude (MSL)103 GPS Track Angle TrueC-14
appendix C 523-0809018Table C-13. GPS Bus Labels - ContinuedLabel Parameter Name110 GNSS Latitude Coarse111 GNSS Longitude Coarse112 GNSS Ground Speed120 GNSS Latitude Fine121 GNSS Longitude Fine130 Horizontal Integrity Limit133 Vertical Integrity Limit136 Vertical Figure of Merit150 GNSS UTC Time165 GPS Vertical Velocity166 GNSS N/S Velocity174 GNSS E/W Velocity247 Horizontal Figure of Merit260 GNSS Date273 GNSS Sensor Status370 GNSS Altitude (HAE)C.5.4.2. GPS Data Latency. It is important that the GPS time mark (which comes out once a second) and the ARINC 429 datablock associated with it have less than a 200 ms lag between them. Typically, a high speed data block associated with the timemark comes out about 150 ms after the time mark. A low speed data block comes out just under 200 ms. If there is not a directconnection between the GPS and the TSS or TDR transponder, the latency through the rest of the system must be minimized. AGPS may transmit data at either a 1 Hz rate or at a 5 Hz rate. Either input rate is acceptable for the transponders. GPS data may notbe down-sampled (for example, to one every 5 data blocks) as the block that corresponds to the time mark must be received by thetransponder.C.5.4.3. GPS Data/Time Mark Input Correlation. GPS data may either come in through the dedicated GPS bus or through theconcentrated bus. It is not allowable to have the data come in through both. When received on the concentrated bus, GPS data issorted by the bus it comes in, so the data from the left GPS must come from the left concentrator and the data from the right GPSmust come from the right concentrator. In addition, the GPS Time Mark input being used must match the input of the ARINC 429data. Refer to Table C-14 for which time mark matches which input port.NOTEFor the TDR there is only one time mark input. Data received either from the cross-side GPS or the cross-sideconcentrator will not have an associated time mark.Table C-14. GPS Data/Time Mark Input CorrelationUnit Time Mark Input GPS Input Concentrated Bus InputTSS GPS Time Mark #1 (LMP 9J & 9K) GPS #1 IAPS #1TSS GPS Time Mark #2 (RMP 9J & 9K) GPS #2 IAPS #2C-15
appendix C 523-0809018Table C-14. GPS Data/Time Mark Input Correlation - ContinuedUnit Time Mark Input GPS Input Concentrated Bus InputTDR GPS Time Tag (P2-37 & 38) GPS #1 FMS/IRSTDR None GPS #2 AIS/ADSC.5.4.4. Single vs Dual GPS Installation. Refer to Figure C-2 for an example block diagram of a GPS installation. In thisdiagram the Left GPS is standard and the right GPS is optional.NOTEThere is an ECU setting for the TSS as to whether there should be one or two GPS inputs expected.In a single GPS installation, a right TSS expects that the single GPS input to come in from the cross side – to comein on the #2 input.Figure C-2. Dual GPS InstallationC-16
appendix C 523-0809018C.5.5. XT-2 Input Bus (TDR to TSS).Refer to Table C-15 for a list of the labels received on the XT-2 input bus.NOTEThe TSS only supports the DO-185A XT/TX protocol; it does not support the older TSO C119A protocol.Table C-15. XT-2 Input Bus (TDR to TSS)Label Parameter Name013 TCAS Control Word015 TCAS Altitude Select Limits016 TCAS/Mode-S Transponder203 Pressure Altitude (XT Word 4)204 Baro-Corrected Altitude (XT Word 9)270 XGD Protocol (XT Word 10) (Reserved)271 XT Word 1272 XT Word 2273 XT Word 3274 XT Word 8275 XT Word 5276 XT Word 6277 XT Word 7C.5.6. TSS Data Load Bus.Refer to Table C-16 for a list of the labels received on the data load input bus.Table C-16. TSS Data Load BusLabel Parameter Name027 TSS Data Load Receive (Dataloader)227 ARINC 604 from CMSC-17/(C-18 Blank)
523-0809018APPENDIX DEquipment CharacteristicsD.1. EQUIPMENT CHARACTERISTICS.Refer to Table D-1 for the equipment specifications. Refer to Table D-2 for the certification categories. Refer to Table D-3 for theequipment weight, power requirements, and size. Refer to Table D-4 through Table D-8 for the environmental qualifications of eachpiece of equipment.Table D-1. Equipment Specifications.CHARACTERISTIC SPECIFICATIONCertificationFAA Technical StandardOrder (TSO)Refer to Table D-2.Environmental Refer to Table D-2 and to the environmental qualification forms provided in Table D-4through Table D-8.Size Refer to Table D-3.Weight Refer to Table D-3.Power requirements Refer to Table D-3 (typical values).Maintenance requirements The TCAS function of the TSS-4100 does not require any periodic maintenance -- it is oncondition. The exception follows:TSS-4100 and TDR-94D: The transponder function must have an Air TrafficControl (ATC) transponder test and inspection according to FAR part 91 at a minimumof once every two years.D-1
appendix D 523-0809018Table D-2. Certification Categories.Unit FAA TSO Environmental CategoriesANT-42 C66b,C74c DO-160A E1/B/JLY/XRHXXXXXXXXECU-3000 TSO-C112 & TSO-C119b (-802status)+ TSO-C166a Transmit only(-803 status)DO-160E [(F2)(A2)V]ABB[(RBB1)(SCLM)(HR)]EYXXXXZ[AB]AZ[CC] [RR]M[X][X]AAXTDR-94D TSO-C112 Class 3A2 121 011 Level3esDO-160E [(A2)(E1)-]BBA[SCLM] EXXXFXZZAZZC[RR]M[(A3)(Z3)X]XXAXTRE-930 C66, C74 DO-108 ABAXXXXCL1NOTEThis unit is not tested to DO-160 levels.TSA-4100 TSO-C112, TSO-C119b &TSO-C166a Transmit only.DO-160E [(D2)(F2)X]ABB[(RCC1)(HR)(SLM)]XSFDFSZ[X]XX[CW] [RR]H[(XX)(K4)4][1A]AAXTSS-4100 TSO-C112 Class 2A1 121 011 Level2es, TSO-C119b & TSO-C166aTransmit OnlyDO-160E [(F2)(A2)V]ABB[(RBB1)(SCLM)(HR)]EYXXXXZ[AB]AZ[CC] [RR]M[(B3)(K3)3]XAAXTable D-3. Unit Weight, Power Requirements, and Size.UNIT WEIGHTkg (lb)POWER(Nominal)POWER(Max) SIZE(H×W×L)mm(in)ANT-42 96 (0.2) NotApplicable (NA)84.1 x 44.5 x 115.3 (3.31 x 1.75 x 4.45)TSA-4100 1.0 (2.2) NA 33.0 x 160 x 284.5 (1.30 x 6.30 x 11.20)NOTEHeight does not include length of connector. The-101 connector is 20 mm long. The -001 connec-tor is 39 mm long.ECU-3000 0.08 (0.17) Powered byTSS-410036x51x70(1.4x2.0x2.8)TDR-94/94D 3.86 (8.5) 28.0 W 85.0 x 124 x 353 (3.31 x 4.87 x 14.0) (1/2 ATR,short-low)TRE-930 0.17 (0.38) NA 84 x 44 x 133 (3.3 x 1.7 x 5.24)TSS-4100 7.55 (16.6) 85 W 120 W 194 x 129 x 382 (7.64 x 5.08 x 15.0)D-2
appendix D 523-0809018Table D-4. ANT-42 Environmental Qualification Form.CONDITIONS DO-160A SECTIONAND REVEQUIPMENT QUALIFICATIONSCATEGORIES OF CONDUCTED TESTSTemperature and Altitude 4.0 Category E1-Temperature- Low Operating Temperature –55 °C (+5 °F)- High Operating Temperature +70 °C (+158 °F)- Low Storage Temperature –55 °C (-67 °F)- High Storage Temperature +85 °C (+185 °F)- Altitude E1Temperature Variation 5.0 BHumidity 6.0 JShock 7.0 L- Operational- Crash SafetyVibration 8.0 YExplosion 9.0 XWaterproofness 10.0 RFluids Susceptibility 11.0 HSand and Dust 12.0 XFungus 13.0 XSalt Spray 14.0 XMagnetic Effect 15.0 XPower Input 16.0 XVoltage Spike Conducted 17.0 XAudio Frequency Conducted Susceptibility 18.0 XInduced Signal Susceptibility 19.0 XRadio Frequency Susceptibility 20.0 XD-3
appendix D 523-0809018Table D-5. ECU-3000 Environmental Qualification Form.CONDITIONS DO-160E SECTIONAND REVEQUIPMENT QUALIFICATIONSCATEGORIES OF CONDUCTED TESTSTemperature and Altitude 4.0 (F2)(A2)V- Temperature- Low Operating Temperature F2 –55 °C (–67 °F)- High Operating Temperature F2 +70 °C (+158 °F)- Low Storage Temperature F2 –55 °C (–67 °F)- High Storage Temperature F2 +85 °C (+185 °F)- High (Short Time) Operating Temperature F2 +70 °C (+158 °F)- Altitude F2 16 800 m (55 000 ft)- In-Flight Loss of Cooling V- Decompression A2- Over pressure A2Temperature Variation 5.0 AHumidity 6.0 BShock 7.0 B- Operational Tested at 6 g peak- Crash Safety Tested at 20 g peakVibration 8.0 Equipment Tested to Cat R curves BB1, Cat Scurves CLM and Cat H curve RExplosion Proofness 9.0 EWaterproofness10.0YFluids Susceptibility 11.0 XSand and Dust 12.0 XFungus Resistance 13.0 XSalt Spray 14.0 XMagnetic Effect 15.0 ZPower Input 16.0 ABVoltage Spike 17.0 AAudio Frequency Conducted Susceptibility 18.0 ZInduced Signal Susceptibility 19.0 CCRadio Frequency Susceptibility 20.0 RREmission of Radio Frequency Energy 21.0 MLightning Induced Transient Susceptibility 22.0 XLightning Direct Effects 23.0 XIcing 24.0 AElectrostatic Discharge 25.0 AD-4
appendix D 523-0809018Table D-5. ECU-3000 Environmental Qualification Form. - ContinuedCONDITIONS DO-160E SECTIONAND REVEQUIPMENT QUALIFICATIONSCATEGORIES OF CONDUCTED TESTSFire/Flammability 26.0 XNOTEThe ECU-3000 Power Input is tested to the worst case of categories A, B, and Z with the exception of the 1 second power interruptiontest required for category Z.D-5
appendix D 523-0809018Table D-6. TDR-94D Environmental Qualification Form.CONDITIONS DO-160E SECTIONAND REVEQUIPMENT QUALIFICATIONSCATEGORIES OF CONDUCTED TESTSTemperature and Altitude 4.0 A2 and E1-Temperature- Low Operating Temperature –55 °C (–67 °F)- High Operating Temperature +70 °C (+158 °F)- Low Storage Temperature –55 °C (–67 °F)- High Storage Temperature +85 °C (+185 °F)- Altitude 21 300 m (70 000 ft)- In-Flight Loss of Cooling - (Not applicable)Temperature Variation 5.0 BHumidity 6.0 BShock 7.0 A- Operational Tested at 6 g peak- Crash Safety Tested at 15 g (11 ms duration)Vibration 8.0 Equipment Tested to Cat S, curves CLMExplosion 9.0 EWaterproofness 10.0 XFluids Susceptibility 11.0 XSand and Dust 12.0 XFungus 13.0 FSalt Spray 14.0 XMagnetic Effect 15.0 ZPower Input 16.0 ZVoltage Spike Conducted 17.0 AAudio Frequency Conducted Susceptibility 18.0 ZInduced Signal Susceptibility 19.0 ZCRadio Frequency Susceptibility 20.0 RRRadio Frequency Emission 21.0 MLightning Induced Transient Susceptibility 22.0 A3Z3XLightning Direct Effects 23.0 XIcing 24.0 XElectrostatic Discharge 25.0 AFlammability 26.0 XElectrical NAPrimary Power 28 V DC, 28 W nominal, 100WmaxReceive Frequency NAD-6
appendix D 523-0809018Table D-6. TDR-94D Environmental Qualification Form. - ContinuedCONDITIONS DO-160E SECTIONAND REVEQUIPMENT QUALIFICATIONSCATEGORIES OF CONDUCTED TESTS1030 ±0.2 MHz from ATCRBS interrogators1030 ±0.01 MHz from Mode-S interrogatorsTransmit Frequency NA1090 ± 1 MHzTransmit Peak Power NAmin250W,max625WD-7
appendix D 523-0809018Table D-7. TSA-4100 Environmental Qualification Form.CONDITIONS DO-160E SECTIONAND REVEQUIPMENT QUALIFICATIONSCATEGORIES OF CONDUCTED TESTSTemperature and Altitude 4.0 (D2)(F2)X- Temperature- Low Short Time Operating Temperature D2- Low Operating Temperature D2- High Short Time Operating Temperature D2- High Operating Temperature D2- Altitude F2Temperature Variation 5.0 AHumidity 6.0 BShock 7.0 BVibration 8.0 Equipment Tested to Cat R curves CC1, Cat Hcurve R and Cat S curves LM (RCC1)(HR)(SLM)Explosion 9.0 XWaterproofness 10.0 SFluids Susceptibility 11.0 FSand and Dust 12.0 DFungus 13.0 FSalt Spray 14.0 SMagnetic Effect 15.0 ZPower Input 16.0 XVoltage Spike Conducted 17.0 XAudio Frequency Conducted Susceptibility 18.0 XInduced Signal Susceptibility 19.0 CWRadio Frequency Susceptibility 20.0 RRRadio Frequency Emission 21.0 HLightning Induced Transient Susceptibility 22.0 (XX)(K4)4Lightning Direct Effects 23.0 1AIcing 24.0 AElectrostatic Discharge 25.0 AFire/Flammability 26.0 XDC Input Resistance: NAJ1 to ground - 1.2 MJ2 to ground - 680 kJ3 to ground - 390 kNOTEThese values are used by the TSS-4100 during initializa-tion to verify proper antenna connections J4 to ground - 220 kD-8
appendix D 523-0809018Table D-8. TSS-4100 Environmental Qualification Form.CONDITIONS DO-160E SECTIONAND REVEQUIPMENT QUALIFICATIONSCATEGORIES OF CONDUCTED TESTSTemperature and Altitude 4.0 [(F2)(A2)V]- Temperature- Low Temperature Storage F2- High Temperature Operation F2- High Temperature Storage F2- Low Temperature Operation F2- In-Flight Loss of Cooling V- Altitude F2- Decompression A2- Overpressure A2Temperature Variation 5.0 AHumidity 6.0 BShock 7.0 B- Operational- Crash SafetyVibration 8.0 Equipment Tested to Cat R curves BB1, Cat Scurves CLM andCatHcurveRExplosion 9.0 EWaterproofness 10.0 YFluids Susceptibility 11.0 XSand and Dust 12.0 XFungus 13.0 XSalt Spray 14.0 XMagnetic Effect 15.0 ZPower Input 16.0 ABVoltage Spike Conducted 17.0 AAudio Frequency Conducted Susceptibility 18.0 ZInduced Signal Susceptibility 19.0 CCRadio Frequency Susceptibility 20.0 RRRadio Frequency Emission 21.0 MLightning Induced Transient Susceptibility 22.0 (B3)(K3)3Lightning Direct Effects 23.0 XIcing 24.0 AElectrostatic Discharge 25.0 AFire/Flammability 26.0 XTCAS RF Characteristics NAD-9
appendix D 523-0809018Table D-8. TSS-4100 Environmental Qualification Form. - ContinuedCONDITIONS DO-160E SECTIONAND REVEQUIPMENT QUALIFICATIONSCATEGORIES OF CONDUCTED TESTSTransmit Frequency 1030 ± 0.01 MHzReceive Frequency 1090 ± 3 MHzSensitivity 75 ± 1 dBmXPDR RF Characteristics NAReceive Frequency (XPDR) 1030 ± 0.2 MHzTransmit Frequency 1090 ± 1 MHzTransmit Peak Power min 125 W, max 500 WSensitivity 74 ± 3 dBmElectrical NAPrimary Power 28 V DC, 85 W nominal, 120WmaxInrush current – 40 amps max1.875 microhenry inductorNOTEThe TSS-4100 has been tested to the highest level of power input testing of Category A, B, and Z – with the exception of a one secondpower interrupt test required for Category Z.The TSS-4100 has undergone flammability testing/ analysis that meets Rockwell Collins standard CS-ENG-M-122: Flammability, Toxi-city, and Smoke Density Analysis Method.D-10
523-0809018APPENDIX EInterconnect DiagramE.1. INTRODUCTION.This appendix contains the interconnect wiring diagram. Refer to Figure E-1.E.2. CABLING INSTRUCTIONS.Make sure the aircraft battery master switch is turned off before installing any interconnect cabling.NOTEFigure E-1 shows a possible interconnect between the TSS-4100 and various altitude and control sources. Becausevarious part numbers of the TSS-4100 provide different strapping options this information is for reference only.The Traffic Surveillance System (TSS) interconnect diagram is shown in Figure E-1. All installations follow this general configu-ration pattern. Various options offer the installer a wide choice of configurations for new and retrofit installations. Use the genericinterconnect diagram to help locate specific interconnect data. Each functional area, shown in bold type, is complete only withrespect to TSS interface data for that particular function. That is, for peripheral systems, for example the air data system or radioaltimeter system, interconnect data to non-TSS related equipment is not provided here. In those cases, you must refer to other appro-priate documentation. Most of the application groupings are also shown in bold type. Subordinate application groupings are shownin normal type.During preparation of the interconnect cables, observe the precautions that follow:a. Read all notes on drawings and interconnect diagrams prior to fabricating interconnect wiring cables.b. Bond and shield all parts of the aircraft electrical system, such as generator and ignition systems.c. Keep the interconnect cables away from circuits carrying heavy current, pulse transmitting equipment, and other sources ofinformation.d. Make all external connections of the equipment through the designated connectors listed on the outline and mounting diagrams.e. For balanced connections, use twisted-pair shielded wiring for minimum pickup of electrostatic and magnetic fields. Avoidlong runs of wire and keep input and output circuits separated as much as possible.f. All interconnect wires and cables should be marked in accordance with the Aircraft Electronics Association Wire MarkingStandard.g. Avoid excessive cable lengths, but allow sufficient slack for movements due to vibration.h. After installation of the cables in the aircraft, and before installation of the equipment, check to make sure that aircraft poweris applied to the pins specified on the interconnect diagrams and that all other wires and shields are properly terminated.E.3. GROUNDING AND HIRF GUIDELINES.The notes on the system interconnect wiring diagram (refer to Figure E-1, sheet 1) describe the recommended methods and tech-niques for reducing the hazards of High Intensity Radiated Field (HIRF). These are general recommendations that apply to wiringmodification/repair as well as to new installations. It shows the preferred method for grounding the shields of shielded wires.E-1
appendix E 523-0809018E.4. SYSTEM INTERCONNECT DIAGRAM.Figure E-1 is the TSS interconnect wiring diagram in a consolidated format. The interconnect information for the TSS-4100 is alsoprovided in the individual simplified Line Replaceable Unit (LRU) schematic diagrams in Chapter 2.E-2
appendix E 523-0809018(992-6037-001B_33)TPJ9606_01Figure E-1. Traffic Surveillance System, Interconnect Wiring Diagram (Sheet 1 of 3)E-3/(E-4 Blank)
appendix E 523-0809018(992-6037-001B_44)TPJ9606_02Figure E-1. Traffic Surveillance System, Interconnect Wiring Diagram (Sheet 2 of 3)E-5/(E-6 Blank)
appendix E 523-0809018(992-6037-001B_45)TPJ9606_03Figure E-1. Traffic Surveillance System, Interconnect Wiring Diagram (Sheet 3 of 3)E-7/(E-8 Blank)
523-0809018© Copyright 2009, Rockwell Collins, Inc.,All Rights Reserved, Printed in USA

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