ACSS an L 3 Communications and Thales TT-951 TCAS User Manual Part 2

ACSS an L-3 Communications and Thales Company TCAS Users Manual Part 2

Contents

Users Manual Part 2

T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.2--53/(2--54 blank)Figure 2--13 (Sheet 2). Directional Antenna Baseplate Outline and Installation Diagram
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.2--55/(2--56 blank)Figure 2--14. Gables G130--XX Control Panel Outline and Installation Diagram
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.2--57/(2--58 blank)Figure 2--15. VSI/TRA Outline and Installation Diagram
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.3--1ELECTRICAL INSTALLATION1. GeneralThis section gives electrical installation procedures, power distribution, and interconnectinformation for each component on the T2CAS system.2. Equipment and MaterialsFor new T2CAS installations, refer to Table 1--1 for RCZ--852 Transponder Installation Kitinformation. For all other components, refer to the applicable Outline and Installation Diagramin the MECHANICAL INSTALLATION section for mating connector part numbers.3. Electrical Installation ProcedureThe information necessary to provide the electrical interconnections is contained in thefollowing paragraphs. Refer to Section 4, LOADING/GRADIENT SPECIFICATIONS, for a listof the signal names used in the interconnect diagrams and tables.NOTE:Unless otherwise specified, all wires shall be stranded #22 AWG.NOTE:All ARINC 429 Data Bus wires shall be stranded #22 AWG twisted shield wire. Allouter shields shall be terminated to the airframe ground. Unshielded portions of thecable and shield ground wires should be kept to a minimum length to minimize RFsusceptibility.NOTE:All electrical installations must be in compliance with SFAR--88.4. Electrical InstallationA. TT--950/951/952 T2CAS Computer UnitsFigure 3--1 shows some general types of T2CAS system installations, using variouscombinations of controllers (control panels) and transponders.The various installation options require different electrical connections as described in theparagraphs that follow.The T2CAS Computer Unit uses programming and configuration straps to select ordeselect various TCAS functions. In addition, the T2CAS uses the APM and ASDB toselect or deselect various TAWS/RWS functions.The T2CAS Computer Unit ARINC 600 connector layout is shown in Figure 3--2. Thecontact arrangement for the various connector plugs are shown in Figure 3--3 thruFigure 3--8. Figure 3--9 shows the connector pin layout for the DATA LOADER connectorlocated on the front of the computer unit.B. APMFigure 2--6 shows a typical APM installation. An APM can be mounted to existing aircraftstructure or can be mounted to the ACSS’ APM mounting bracket that is secured to theaftsideoftheT2CAS computer tray connector, reference Figure 3--3. If the Customerspecifies the ACSS APM mounting bracket, the Contractor shall manufacture and providethis APM bracket sub kit for this Customer’s T2CAS installations
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.3--2C. TCAS AntennasThe electrical installation for the TCAS antennas is specified in the LOADING ANDGRADIENT section. Figure 3--3 shows the T2CAS computer contact arrangement for thetop directional antenna and Figure 3--4 shows the T2CAS computer contact arrangementfor the bottom antenna.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.3--3Figure 3--1. Typical TCAS Installation Types
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.3--4D. GPS Antenna and CoaxAll T2CAS installations require a GPS position source (that includes GPS altitude). Theinstallation design will consist of an A429 interface to the GPS sensor if the signal isavailable, or the T2CAS internal GPS module will be required. The installation thenconsists of the installation of a GPS antenna and the coax cable to the T2CAS unit, LBPpin 13. Figure 2--4 shows a typical T2CAS installation with an existing GPS source.Where the internal module is required, the T2CAS GPS Installation Data Packageincludes the GPS antenna mounting structures provisions and all of the coax details tosecure the coax to the airframe and connect the T2CAS GPS antenna with the T2CAScomputer’s LBP pin 13. Figure 2--4 shows a typical T2CAS installation with an internalGPS module (installation includes GPS antenna and coax kit).
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.3--5Figure 3--2. T2CAS Computer Tray Mating Connector
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.3--6Figure 3--3. Contact Arrangement for CU Left Top Plug (LTP) InsertFigure 3--4. Contact Arrangement for CU Left Middle Plug (LMP) Insert
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.3--7Figure 3--5. Contact Arrangement for Left Bottom Plug (LBP) Insert
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.3--8Figure 3--6. Contact Arrangement for Right Top Plug (RTP) Insert
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.3--9Figure 3--7. Contact Arrangement for Right Middle Plug (RMP) Insert
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.3--10Figure 3--8. Contact Arrangement for Right Bottom Plug (RBP) Insert
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.3--11Figure 3--9. TCAS Computer Unit Data Loader Connector (J1) Pin Layout
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.3--12E. Control PanelsTable 3--1 contains the interconnect data for the Gables G7130 series control panels.Table 3--1. Gables G7130--XX ATC/TCAS Control Panel Interconnect DataI/O DescriptionConnectorPin Connects To Notes(I) 5 V ac Pnl Lighting (H) J1--1 (20) Acft Lighting Source(I) 5 V ac Pnl Lighting (L) J1--2 (20) Acft Lighting Source(I) +28 V dc Input Power (H) J1--3 (20) Acft 28 V dc Power(I) +28 V dc Return (L) J1--4 (20) Acft dc Ground(O) Antenna Transfer Discrete J1--5 (22) Antenna Relay 1, 2(I) dc Ground J1--6 (22) Acft dc Ground(O) Standby/On Output Disc J1--7 (22) Transponder No. 1(I) Chassis Ground J1--8 (22) Airframe Ground 3(I) Functional Test J1--9 (22) Remote Test Switch(O) Warning & Caution J1--10 (22) Remote Warn Sys 2Reserved J1--11(I) XPDR Fail Logic No.2 J1--12 (22) Transponder No. 1(I) Ident Input J1--13 (22) Remote IDENT Switch 2(I) XPDR Fail (High Level) J1--14 NC 2, 4(O) Air/Gnd Switched Discrete J1--15 NC(O) Alt Source Select Discrete J1--16 (22) Transponder No.1 2Reserved J1--17(I) Monitor Lamp Power J1--18 (20) Acft 28 V dc PowerReserved J1--19(I) XPDR Configuration J1--20 NC 2(I) Lamp Test J1--21 (22) Rmt Lamp Test SW 2(O) ARINC 429 (A) Out J1--22 (22) S T S||Transponder No.1 5(O) ARINC 429 (B) Out J1--23 (22) S T SGND llGNDTransponder No.1 5(I) Air/Gnd Discrete J1--24 (22) WOW Switch 2Reserved J2--1Reserved J2--2
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.3--13Table 3--1. Gables G7130--XX ATC/TCAS Control Panel Interconnect Data (cont)I/O NotesConnects ToConnectorPinDescription(I) +28V dc Input Power (H) J2--3 (20) Acft 28 V dc Power(I) +28V dc Return (L) J2--4 (20) Acft dc Ground(O) Antenna Transfer Discrete J2--5 (22) Antenna Relay 1, 2(I) dc Ground J2--6 (22) Acft dc Ground(O) Standby/On Discrete J2--7 (22) Transponder No.2(I) Chassis Ground J2--8 (22) Airframe Ground 3(I) Functional Test J2--9 (22) Remote Test SW(O) Warning & Caution J2--10 (22) Remote Warn Sys 2Reserved J2--11(I) XPDR Fail Logic No.2 J2--12 (22) Transponder No.2(I) Ident Input J2--13 (22) Remote Ident SW 2(I) XPDR Fail (High Level) J2--14 NC 2, 4(O) Air/Gnd Switched Discrete J2--15 (22) NC(O) Alt Source Select Discrete J2--16 (22) Transponder No.2 2Reserved J2--17(I) Monitor Lamp Pwr J2--18 (20) Acft 28 V dc Power 2Reserved J2--19(I) XPDR Configuration J2--20 NC Gnd/Open 2(I) Lamp Test J2--21 (22) Rmt Lamp Test SW 2(O) ARINC 429 (A) Out J2--22 (22) S T S||Transponder No.2 5(O) ARINC 429 (B) Out J2--23 (22) S T SGND llGNDTransponder No.2 5(I) Air/Gnd Discrete J2--24 (22) Acft WOW Switch 2NOTES:1. Connect either J1--5 or J2--5 to an antenna switching relay if one set of ATC antennas is used in adual transponder installation.2. Refer to Loading Gradient Specifications in Table 4--2.3. Tie chassis ground to aircraft frame.4. 28 V dc discrete input from Collins TDR--94D transponder.5. Two wire shielded cable. Tie shields to aircraft dc ground.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.3--14F. Thales VSI/TRA DisplayTable 3--2 contains interconnect data for the Thales 41--pin connector units.Figure 3--10 shows the connector pin layouts for the 41--pin VSI/TRA configuration.Table 3--2. 41--Pin VSI/TRA Interconnect DataI/O DescriptionConnectorPin Connects To Notes(I) VS +dc Ref J1--1 (22) ARINC 575 ADC(I) VS dc Rate J1--2 (22) ARINC 575 ADC(I) VS --dc Ref J1--3 (22) ARINC 575 ADC(I) Primary VS (HI) J1--4 (22) S T S||ARINC 565 ADC orIRS1(I) Primary VS (LO) J1--6 (22) S T SGND llGNDARINC 565 ADC orIRS1(I) VS 26 V ac Ref (HI) J1--5 (22) ARINC 565 ADC orIRS(I) Vert. Speed Digital Port (A) J1--7(I) Vert. Speed Digital Port (B) J1--21(I) VS VALID NO.1 J1--8 (22) ARINC 565/575 ADCor IRS(I) 5 V Lamp Dimming (LO) J1--9 (22) Acft Lamp Dim Ckt(I) 5 V Lamp Dimming (HI) J1--10 (22) Acft Lamp Dim Ckt(I) TCAS TA/RAARINC 429 (B)J1--11 (22) S T S||TCAS Computer 1(I) TCAS TA/RAARINC 429 (A)J1--26 (22) S T SGND llGNDTCAS Computer 1(I) VS No.1 ARINC 429 (B) J1--12 (22) S T S||Digital ADC No.1 orIRS No.11(I) VS No.1 ARINC 429 (A) J1--27 (22) S T SGND llGNDDigital ADC No.1 orIRS No.11(O) 26 VAC Bootstrap ref. Out J1--13 Bootstrap instrument
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.3--15Table 3--2. 41--Pin VSI/TRA Interconnect Data (cont)I/O NotesConnects ToConnectorPinDescription(I) VS No.2 ARINC 429 (B) J1--14 (22) STS||Digital ADC No.2 orIRS No.2(I) VS No.2 ARINC 429 (A) J1--30 (22) S T SGND llGNDDigital ADC No.2 orIRS No.2(I) Config Strap Common J1--15 (22) Config Strap LogicGnd5(I) VS 26 V ac Ref (C) J1--16 (22) ARINC 565 ADC orIRS(I) Config Strap No.3 (CS3) J1--17 (22) Gnd/Open(O) Secondary VERT SPEEDValidity input (+ 28 VDC)J1--18 (20) S T S||ARINC 565/575 ADC 2(O) VERT SPEED BootstrapAC Out (HI)J1--19 (20) Bootstrap instrument 2(O) VERT SPEED Boots strapAC Out (LO)J1--20 (20) Bootstrap instrument 2(I) Chassis Ground J1--22 (22) Airframe Ground 3(I) 115 V ac Return (C) J1--23 (20) Acft ac Ground(I) Remote Light Sensor (LO) J1--24 (22) S T S||Acft Rmt Light Sensor 1(I) Remote Light Sensor (HI) J1--25 (22) S T SGND llGNDAcft Rmt Light Sensor 1(I) Configuration strap J1--28 V/S response timeselection(O) RA Valid Out J1--29 (22) TCAS Computer(I) Source Sel Discrete In(SS 1)J1--31 (22) Gnd/Open(I) Config Strap No.0 (CS0) J1--32 (22) Gnd/Open(I) Config Strap No.1 (CS1) J1--33 (22) Gnd/Open(I) Config Strap No.2 (CS2) J1--34 (22) Gnd/Open(I) Config Strap No.4 (CS4) J1--35 (22) Gnd/Open(I) Secondary Analog ACInput (LO)J1--36 (22) ARINC 565 ADC(I) Secondary Source SelectDiscrete Input (SS 2)J1--37 (22) Aircraft Switch
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.3--16Table 3--2. 41--Pin VSI/TRA Interconnect Data (cont)I/O NotesConnects ToConnectorPinDescription(O) VERT SPEED VALIDDiscrete OutputJ1--38 (22)(I) dc Ground J1--39 (22) Acft dc Ground(I) 115 V ac Input Power (H) J1--40 (20) Acft 115 V ac Supply(I) Self--test/Display Test J1--41 (22) Aircraft SwitchNOTES:1. Two wire shielded cable. Tie shields to aircraft dc ground.2. Three wire shielded cable. Tie shields to aircraft dc ground.3. Tie chassis ground to aircraft frame.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.3--17Figure 3--10. VSI/TRA 41--Pin Connector Layout
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.3--18G. TAWS Terrain Hazard DisplayAll T2CAS installations will require at least one TAWS terrain hazard display. ARINC 708and ARINC 429 WXR display and EFIS interfaces are supported. Figure 3--11 shows atypical single ARINC 708 terrain hazard display interface. T2CAS’ dual--independentterrain hazard display I/O supports dual ARINC 708 and dual ARINC 429 terrain hazarddisplay systems. Figure 3--11 shows a typical single ARINC 708 terrain hazard displayand display interface with annunciator switch panels. The TERR and WXR selectswitches shown are momentary but alternate action switches are also supported. Theterrain INHIBIT or OVRD switches are alternate action switches and are typically guarded.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.3--19Figure 3--11. Typical T2CAS Single Terrain Hazard Display Interface
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.3--20H. TranspondersTable 3--3 thru Table 3--6 contain the interface information for the ACSS transponders.The transponders use altimetry data supplied in one of the following formats: ARINC 429(from a digital ADC), ARINC 575, Synchro, or Gillham code. Altimetry data from one ofthese source types must be connected to the transponder. If a single altimetry source isused, it should be wired to both sets of transponder inputs.All Mode S transponders require a unique 24--bit code (Mode S address) assigned toeach aircraft. For aircraft registered in the United States, it is necessary to have aspecific address code assigned. These address codes are presently issued by:Federal Aviation AdministrationFAA Aircraft RegistryP.O. Box 25504Oklahoma City, OK 73125Tel: (405) 954--3116Fax: (405) 954--3548If the aircraft is registered in a country other than the United States, contact the aviationauthority of the country in which the aircraft is registered.The Mode S address is usually issued as an 8--digit octal number. To strap the addresscode correctly, each digit must be converted to a corresponding binary number. (Forexample: 7 octal = 111 binary, 1 octal = 001 binary.)Once the 8--digit octal code is converted to a 24--bit binary number, the straps (addresspins) must be grounded or left open according to this binary number representation.Each binary 0represents an open strap and each binary 1represents a grounded strap.An example of an octal code number being converted to a binary number is shown below:Octal address code = 12345670In binary this number is: (MSB) 001 010 011 100 101 110 111 000 (LSB)(1) XS--950 Data Link TransponderTable 3--3 contains the interconnect data for the XS--950 Data Link Transponder, PartNo. 7517800--XXYYY.If additional XS--950 Data Link Transponder installation or operational information isrequired, refer to Mode S Data Link Transponder System Description and InstallationManual, ACSS Pub. No. A09--3839--001.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.3--21Table 3--3. XS--950 Data Link Transponder Interconnect DataI/O DescriptionConnectorPin Connects To Notes(I) Mode C Pulse A1 #2 P1A--1A (22) Encoding Altm #2(I) Mode C Pulse A2 #2 P1A--1B (22) Encoding Altm #2(I) Mode C Pulse A4 #2 P1A--1C (22) Encoding Altm #2(I) Mode C Pulse B1 #2 P1A--1D (22) Encoding Altm #2(I) Mode C Pulse B2 #2 P1A--1E (22) Encoding Altm #2(I) Mode C Pulse B4 #2 P1A--1F (22) Encoding Altm #2(I) Mode C Pulse C1 #2 P1A--1G (22) Encoding Altm #2(I) Mode C Pulse C2 #2 P1A--1H (22) Encoding Altm #2(I) Mode C Pulse C4 #2 P1A--1J (22) Encoding Altm #2(I) Mode C Pulse D2 #2 P1A--1K (22) Encoding Altm #2(I) ARINC 429 (A) COMM A/BInput from ADLPP1A--2A (22) S T S||Airborne Data LinkProcessor1(I) ARINC 429 (B) COMM A/BInput from ADLPP1A--2B (22) S T SGND llGNDAirborne Data LinkProcessor1(I) ARINC 429 (A) COMM C/DInput from ADLPP1A--2C (22) S T S||Airborne Data LinkProcessor1(I) ARINC 429 (B) Comm C/DInput from ADLPP1A--2D (22) S T SGND llGNDAirborne Data LinkProcessor1(O) ARINC 429 (A) COMM C/DOutput to ADLPP1A--2E (22) S T S||Airborne Data LinkProcessor1(O) ARINC 429 (B) COMM C/DOutput to ADLPP1A--2F (22) S T SGND llGNDAirborne Data LinkProcessor1Reserved P1A--2GReserved P1A--2HReserved P1A--2J(I) Mode C Pulse D4 #2 P1A--2K (22) Encoding Altm #2Reserved P1A--3A(O) XPDR Fail Discrete Out #2 P1A--3B (22) Control Panel(I) Cable Delay Prog Top/Bot P1A--3C (22) Gnd/Open(I) Cable Delay Program B P1A--3D (22) Gnd/Open(I) Cable Delay Program A P1A--3E (22) Gnd/Open(I) Cable Delay Prog Common P1A--3F (22) Program Logic Gnd
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.3--22Table 3--3. XS--950 Data Link Transponder Interconnect Data (cont)I/O NotesConnects ToConnectorPinDescription(I) SDI Program A P1A--3G (22) Gnd/Open(I) SDI Program B P1A--3H (22) Gnd/Open(I) SDI Common P1A--3J (22) Program Logic Gnd(I) Mode C Pulse Common #2 P1A--3K (22) Encoding Altm #2(I) Syn Alt In #1: Coarse X P1A--4A (22) ARINC 565 ADC #1(I) Syn Alt In #1: Coarse Y P1A--4B (22) ARINC 565 ADC #1(I) Syn Alt In #1: Coarse Z P1A--4C (22) ARINC 565 ADC #1(I) Syn Alt In #1: 26 V Ref (H) P1A--4D (22) ARINC 565 ADC #1(I) Syn Alt In #1: 26 V Ref (C) P1A--4E (22) ARINC 565 ADC #1(I) Syn Alt In #1: Fine X P1A--4F (22) ARINC 565 ADC #1(I) Syn Alt In #1: Fine Y P1A--4G (22) ARINC 565 ADC #1(I) Syn Alt In #1: Fine Z P1A--4H (22) ARINC 565 ADC #1(I) Syn Alt In #1: Flag P1A--4J (22) ARINC 565 ADC #1Reserved P1A--4K (22)(I) Max True Airspeed Prog A P1A--5A (22) Gnd/Open(I) Max True Airspeed Prog B P1A--5B (22) Gnd/Open(I) Max True Airspeed Prog C P1A--5C (22) Gnd/Open(I) Max True AS Common P1A--5D (22) Program Logic Gnd(I) ARINC 429 (A) TX Coord P1A--5E (22) S T S||TCAS Computer 1(I) ARINC 429 (B) TX Coord P1A--5F (22) S T SGND llGNDTCAS Computer 1(O) ARINC 429 (A) XT Coord P1A--5G (22) S T S||TCAS Computer 1(O) ARINC 429 (B) XT Coord P1A--5H (22) S T SGND llGNDTCAS Computer 1(I) Air/Gnd Discrete Input #2 P1A--5J (22) Control Panel(I) Air/Gnd Discrete Input #1 P1A--5K (22) Control Panel(I) ARINC 429 (A) Flt ID Input P1A--6A (22) S T S||Flight ID Source 1(I) ARINC 429 (B) Flt ID Input P1A--6B (22) STSGND llGNDFlight ID Source 1
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.3--23Table 3--3. XS--950 Data Link Transponder Interconnect Data (cont)I/O NotesConnects ToConnectorPinDescription(I) ARINC 429 (A) ADL Input P1A--6C (22) S T S||ARINC 615 AirborneData Loader1(I) ARINC 429 (B) ADL Input P1A--6D (22) S T SGND llGNDARINC 615 AirborneData Loader1(O) ARINC 429 (A) ADL Out P1A--6E (22) S T S||ARINC 615 AirborneData Loader1(O) ARINC 429 (B) ADL Out P1A--6F (22) S T SGND llGNDARINC 615 AirborneData Loader1(I) ADL Input Link A P1A--6G (22) ARINC 615 AirborneData Loader(I) ARINC 575 (A) ADC In #1 P1A--6H (22) S T S||ARINC 575 ADC #1 1(I) ARINC 575 (B) ADC In #1 P1A--6J (22) S T SGND llGNDARINC 575 ADC #1 1(I) Single/Dual Antenna Prog P1A--6K (22) Gnd/Open(I) ARINC 429 (A) ControlData Input Port AP1A--7A (22) S T S||Control Panel 1(I) ARINC 429 (B) ControlData Input Port AP1A--7B (22) S T SGND llGNDControl Panel 1Reserved P1A--7C(I) Control Data Port Select In P1A--7D (22) Gnd/Open(I) ARINC 429 (A) ControlData Input Port BP1A--7E (22) S T S||Control Panel(I) ARINC 429 (B) ControlData Input Port BP1A--7F (22) S T SGND llGNDControl Panel(I) STBY/ON Discrete Input P1A--7G (22) Control Panel(I) ARINC 429 (A) ADC #1 In P1A--7H (22) S T S||ARINC 706 ADC #1 1(I) ARINC 429 (B) ADC #1 In P1A--7J (22) S T SGND llGNDARINC 706 ADC #1 1Reserved P1A--7K(I) Top Antenna RF Input P1A--71 coax Top Antenna
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.3--24Table 3--3. XS--950 Data Link Transponder Interconnect Data (cont)I/O NotesConnects ToConnectorPinDescription(I) Mode S Adrs Bit A1 (MSB) P1B--1A (22) Gnd/Open(I) Mode S Address Bit A2 P1B--1B (22) Gnd/Open(I) Mode S Address Bit A3 P1B--1C (22) Gnd/Open(I) Mode S Address Bit A4 P1B--1D (22) Gnd/Open(I) Mode S Address Bit A5 P1B--1E (22) Gnd/Open(I) Mode S Address Bit A6 P1B--1F (22) Gnd/Open(I) Mode S Address Bit A7 P1B--1G (22) Gnd/Open(I) Mode S Address Bit A8 P1B--1H (22) Gnd/Open(I) Mode S Address Bit A9 P1B--1J (22) Gnd/Open(I) Mode S Address Bit A10 P1B--1K (22) Gnd/Open(I) Mode S Address Bit A11 P1B--2A (22) Gnd/Open(I) Mode S Address Bit A12 P1B--2B (22) Gnd/Open(I) Mode S Address Bit A13 P1B--2C (22) Gnd/Open(I) Mode S Address Bit A14 P1B--2D (22) Gnd/Open(I) Mode S Address Bit A15 P1B--2E (22) Gnd/Open(I) Mode S Address Bit A16 P1B--2F (22) Gnd/Open(I) Mode S Address Bit A17 P1B--2G (22) Gnd/Open(I) Mode S Address Bit A18 P1B--2H (22) Gnd/Open(I) Mode S Address Bit A19 P1B--2J (22) Gnd/Open(I) Mode S Address Bit A20 P1B--2K (22) Gnd/Open(I) Mode S Address Bit A21 P1B--3A (22) Gnd/Open(I) Mode S Address Bit A22 P1B--3B (22) Gnd/Open(I) Mode S Address Bit A23 P1B--3C (22) Gnd/Open(I) Mode S Adrs Bit A24 (LSB) P1B--3D (22) Gnd/Open(I) Mode S Adrs Bit Common P1B--3E (22) Address Logic GndReserved P1B--3FReserved P1B--3G(I) Functional Test Discrete In P1B--3H (22) Remote Test Switch(O) Alt Comparison FailDiscrete OutputP1B--3J (22) Control Panel(O) XPDR Fail Discrete Out #1 P1B--3K (22) NC Control Panel
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.3--25Table 3--3. XS--950 Data Link Transponder Interconnect Data (cont)I/O NotesConnects ToConnectorPinDescription(I) Mode C Pulse A1 #1 P1B--4A (22) Encoding Altm #1(I) Mode C Pulse A2 #1 P1B--4B (22) Encoding Altm #1(I) Mode C Pulse A4 #1 P1B--4C (22) Encoding Altm #1(I) Mode C Pulse B1 #1 P1B--4D (22) Encoding Altm #1(I) Mode C Pulse B2 #1 P1B--4E (22) Encoding Altm #1(I) Mode C Pulse B4 #1 P1B--4F (22) Encoding Altm #1(I) Mode C Pulse C1 #1 P1B--4G (22) Encoding Altm #1(I) Mode C Pulse C2 #1 P1B--4H (22) Encoding Altm #1(I) Mode C Pulse C4 #1 P1B--4J (22) Encoding Altm #1(I) Mode C Pulse D2 #1 P1B--4K (22) Encoding Altm #1(I) ARINC 429 (A) ADC #2 In P1B--5A (22) S T S||ARINC 706 ADC #2 1(I) ARINC 429 (B) ADC #2 In P1B--5B (22) S T SGND llGNDARINC 706 ADC #2 1(I) ARINC 575 (A) ADC #2 In P1B--5C (22) S T S||ARINC 575 ADC #2 1(I) ARINC 575 (B) ADC #2 In P1B--5D (22) S T SGND llGNDARINC 575 ADC #2 1(O) ARINC 429 (A) Comm A/BOutput to ADLPP1B--5E (22) S T S||Airborne Data LinkProcessor1(O) ARINC 429 (B) Comm A/BOutput to ADLPP1B--5F (22) S T SGND llGNDAirborne Data LinkProcessor1(I) Alt Comparison On/OffDiscrete InputP1B--5G (22) Control Panel(I) Mode S Data Link Program P1B--5H (22) Gnd/Open(I) Antenna Bite Program P1B--5J (22) Gnd/Open(I) Mode C Pulse D4 #1 P1B--5K (22) Encoding Altm #1(I) ARINC 429 (A)Maintenance Data InputP1B--6A (22) S T S||Onboard MaintComputer System1(I) ARINC 429 (B)Maintenance Data InputP1B--6B (22) STSGND llGNDOnboard MaintComputer System1
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.3--26Table 3--3. XS--950 Data Link Transponder Interconnect Data (cont)I/O NotesConnects ToConnectorPinDescription(O) ARINC 429 (A)Maintenance Data OutputP1B--6C (22) STS||Onboard MaintComputer System1(O) ARINC 429 (B)Maintenance Data OutputP1B--6D (22) S T SGND llGNDOnboard MaintComputer System1(I) Air Data Source SelectDiscrete InputP1B--6E (22) Gnd/Open(I) Alt Type Select Prog B P1B--6F (22) Gnd/Open(I) Alt Type Select Prog A P1B--6G (22) Gnd/Open(I) Alt Type Select Common P1B--6H (22) Program Logic GndReserved P1B--6J(I) Mode C Pulse Common #1 P1B--6K (22) Encoding Altm #1(I) Syn Alt In #2: Coarse X P1B--7A (22) ARINC 565 ADC #2(I) Syn Alt In #2: Coarse Y P1B--7B (22) ARINC 565 ADC #2(I) Syn Alt In #2: Coarse Z P1B--7C (22) ARINC 565 ADC #2(I) Syn Alt In #2: 26 V Ref (H) P1B--7D (22) ARINC 565 ADC #2(I) Syn Alt In #2: 26 V Ref (C) P1B--7E (22) ARINC 565 ADC #2(I) Syn Alt In #2: Fine X P1B--7F (22) ARINC 565 ADC #2(I) Syn Alt In #2: Fine Y P1B--7G (22) ARINC 565 ADC #2(I) Syn Alt In #2: Fine Z P1B--7H (22) ARINC 565 ADC #2(I) Syn Alt In #2: Flag P1B--7J (22) ARINC 565 ADC #2Reserved P1B--7K(I) Bottom Antenna RF Input P1B--71 coax Bottom Antenna(I) 115 V ac Input Power (H) P1C--1 (20) Acft 115 V ac SupSpare P1C--2(I) +28 V dc Return (L) P1C--3 (16) Acft dc Ground(I) XPDR OFF (NO) P1C--4 NCSpare P1C--5(O) Fan +28 V dc P1C--6 (22) Fan +(I) 115 V ac Return (L) P1C--7 (20) Acft ac Ground(I) Signal Ground P1C--8 (16) Acft ac Ground(O) Fan Return (L) P1C--9 Fan --
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.3--27Table 3--3. XS--950 Data Link Transponder Interconnect Data (cont)I/O NotesConnects ToConnectorPinDescription(I) +28 V dc Input Power P1C--10 (16) +28V Acft Power(I) Chassis Ground P1C--11 (16) Airframe Ground 2I/O Suppression Pulse P1C--12 coax L--Band SuppressionBusI/O Suppression Pulse P1C--13 coax L--Band SuppressionBusThe interconnect data that follows is for the ARINC 615 Portable Data Loader (PDL) connector J1 locatedon the front panel of the transponder. The transponder’s operational software can be updated (upload totransponder) through this connector. In addition, the contents of the fault log can be extracted for analysisand troubleshooting (download from transponder).The 53 pin front panel PDL connector contains both an ARINC 429 high speed bus interface for connectionto an ARINC 615 PDL, and an RS--232 bus interface for connection to a personal computer (PC) through astandard serial port. Only the pins used by the transponder are shown.The PDL standard interface cable should be 10 feet in length (3 meters) and be terminated with a connectortype MS27473T--18A--53S at the data loader end and connector type MS27473T--18A--53P at thetransponder end.(I) ARINC 429 (A) PDL Input J1--1 (22) STS ARINC 615 PDL 3(I) ARINC 429 (B) PDL Input J1--2 (22) S T S ARINC 615 PDL 3(I) Bus Shield J1--5 (22) Chassis Ground 3(O) ARINC 429 (A) PDL Out J1--8 (22) S T S ARINC 615 PDL 4(O) ARINC 429 (B) PDL Out J1--9 (22) S T S ARINC 615 PDL 4(O) Bus Shield J1--16 (22) Chassis Ground 4PDL Link A J1--18 (22) ARINC 615 PDLPDL Link B J1--19 (22) ARINC 615 PDL(O) 115 V ac Power Out (H) J1--20 (22) ARINC 615 PDL 5(O) Chassis Ground J1--21 (22) ARINC 615 PDL 5(O) 115 V ac Power Out (C) J1--22 (22) ARINC 615 PDL 5(O) +28 V dc Power Out J1--37 (22) ARINC 615 PDL 6(O) +28 V dc Return J1--38 (22) ARINC 615 PDL 6(I) RS--232 PDL Input J1--40 (22) RS--232 Interface 7(O) RS--232 PDL Output J1--41 (22) RS--232 Interface 7Logic Common (Gnd) J1--48 (22) RS--232 Interface 7Logic Common (Gnd) J1--49 (22) RS--232 Interface 7(I) PDL Function Discrete #1 J1--50 (22) ARINC 615 PDL(I) PDL Function Discrete #2 J1--51 (22) ARINC 615 PDL
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.3--28Table 3--3. XS--950 Data Link Transponder Interconnect Data (cont)I/O NotesConnects ToConnectorPinDescription(I) PDL Function Discrete #3 J1--52 (22) ARINC 615 PDL(I) PDL Function Discrete #4 J1--53 (22) ARINC 615 PDLNOTES:1. Two wire shielded cable. Tie shields to aircraft dc ground.2. Tie chassis ground to aircraft frame.3. Two wire shielded cable. Tie shield to pin 5.4. Two wire shielded cable. Tie shield to pin 16.5. The 115 V ac (H) and 115 V ac (C) should be shielded or twisted and shielded with an insulatingjacket over the shield. The shield should be connected to chassis ground (pin 21).6. There is a +28 V dc output available from the transponder, however most ARINC 615 DataLoaders do not have the capability to operate from 28 Volt power.7. If the RS--232 interface is going to be used, these pins should be connected to a standard serialport (usually a 9--pin D connector).
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.3--29(2) RCZ--852 Diversity Mode S TransponderTable 3--4 contains the interconnect data for the RCZ--852 Diversity Mode STransponder, Part No. 7510700--850.Prior to final installation of the transponder mounting tray, the strap assembly,Figure 3--12, located on the back of each mounting tray must be programmed toincorporate the aircraft Mode S address and the desired options. Information forprogramming the strap assembly is contained in Table 3--5 and Table 3--6.Programming of the strap assembly consists of removing or installing a string ofjumper wires that provide a 48--bit serial data word for encoding the systemconfiguration. In Table 3--6, the output is grounded if the corresponding W* (jumperwire) is installed for a particular bit, and open if the jumper wire is cut out.The strap assembly is shipped with all 48--bit jumpers installed. If a jumper isinadvertently cut out or a parameter change requires a jumper to be reinstalled, asuitable piece of AWG 24 bus wire should be used.Table 3--4. RCZ--852 Diversity Mode S Transponder Interconnect DataI/O DescriptionConnectorPin Connects To Notes(O) XPDR +28 V FAN RTN J1--1 NC(O) XPDR +28 V FAN PWR J1--2 NCI/O MUT SUP (P) J1--3 (24) S SGND llGNDL--Band SuppressionBus1Spare J1--4Spare J1--5Spare J1--6(I) XPDR +28V RTN J1--7 (22) Acft dc Ground(I) XPDR +28V PWR J1--8 (22) Acft 28 V Supply(I) XPDR +28V PWR J1--9 (22) Acft 28 V SupplySpare J1--10(I) PROGRAM ENA (PO) J1--11 NC(O) XPDR TX RS232 J1--12 NCReserved J1--13Reserved J1--14Reserved J1--15Reserved J1--16(I) dc GROUND J1--17 (22) Acft dc Ground(I) dc GROUND J1--18 (22) Acft dc Ground
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.3--30Table 3--4. RCZ--852 Diversity Mode S Transponder Interconnect Data (cont)I/O NotesConnects ToConnectorPinDescription(I) dc GROUND J1--19 (22) Acft dc Ground(I) XPDR +28V RTN J1--20 (22) Acft dc Ground(I) dc GROUND J1--21 (22) Acft dc GroundSpare J1--22(O) XPDR VALID (PO) J1--23 NC(I) XPDR RX RS232 J1--24 NC(O) PROGRAM +15V J1--25 NC(O) XPDR to TCAS 429 (A) J1--26 (22) S T SGND llGND||TCAS Computer 2(O) XPDR to TCAS 429 (B) J1--27 (22) S T SGND llGNDTCAS Computer 2(O) XPDR to DLP A/B 429 (A) J1--28 (22) S T S||Airborne Data LinkProcessor2(O) XPDR to DLP A/B 429 (B) J1--29 (22) S T SGND llGNDAirborne Data LinkProcessor2(O) XPDR to DLP C/D 429 (A) J1--30 (22) S T S||Airborne Data LinkProcessor2(O) XPDR to DLP C/D 429 (B) J1--31 (22) S T SGND llGNDAirborne Data LinkProcessor2(I) ADC1 to XPDR 429/575A J1--32 (22) S T S||ARINC 429 or 575ADC #12(I) ADC1 to XPDR 429/575B J1--33 (22) S T SGND llGNDARINC 429 or 575ADC #12(I) CTL1 to XPDR 429 (A) J1--34 (22) S T S||Control Panel 2(I) CTL1 to XPDR 429 (B) J1--35 (22) S T SGND llGNDControl Panel 2Reserved J1--36Reserved J1--37Reserved J1--38Reserved J1--39
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.3--31Table 3--4. RCZ--852 Diversity Mode S Transponder Interconnect Data (cont)I/O NotesConnects ToConnectorPinDescription(I) TCAS to XPDR 429 (A) J1--40 (22) STS||TCAS Computer 2(I) TCAS to XPDR 429 (B) J1--41 (22) S T SGND llGNDTCAS Computer 2(I) DLP A/B to XPDR 429 (A) J1--42 (22) S T S||Airborne Data LinkProcessor2(I) DLP A/B to XPDR 429 (B) J1--43 (22) S T SGND llGNDAirborne Data LinkProcessor2(I) DLP C/D to XPDR 429 (A) J1--44 (22) S T S||Airborne Data LinkProcessor2(I) DLP C/D to XPDR 429 (B) J1--45 (22) S T SGND llGNDAirborne Data LinkProcessor2(I) ADC2 to XPDR 429/575A J1--46 (22) S T S||ARINC 429/575Digital ADC2(I) ADC2 to XPDR 429/575B J1--47 (22) S T SGND llGNDARINC 429/575Digital ADC2(I) CTL2 to XPDR 429 (A) J1--48 (22) S T S||Control Panel 2(I) CTL2 to XPDR 429 (B) J1--49 (22) S T SGND llGNDControl Panel 2(O) XPDR to CTL 429 (A) J1--50 (22) S T S||Control Panel 2, 3(O) XPDR to CTL 429 (B) J1--51 (22) S T SGND llGNDControl Panel 2, 3Reserved J1--52(I) ENC ALT1 C1 (N) J1--53 (24) Encoding Altm #1(I) ENC ALT1 C2 (N) J1--54 (24) Encoding Altm #1(I) ENC ALT1 C4 (N) J1--55 (24) Encoding Altm #1(I) ENC ALT1 D2 (N) J1--56 (24) Encoding Altm #1(I) ENC ALT1 D4 (N) J1--57 (24) Encoding Altm #1(I) ENC ALT1 A1 (N) J1--58 (24) Encoding Altm #1(I) ALT COMP ENA (NO) J1--59 (24) Gnd/Open 4(I) ALT SRC SEL2 (NO) J1--60 (24) Gnd/Open 4
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.3--32Table 3--4. RCZ--852 Diversity Mode S Transponder Interconnect Data (cont)I/O NotesConnects ToConnectorPinDescription(I) CTL SRC SEL1 (NO) J1--61 (24) Gnd/Open 4Reserved J1--62Reserved J1--63(I) FMS to XPDR 429 (A) J1--64 (22) S T S||Flt Management Sys 2(I) FMS to XPDR 429 (B) J1--65 (22) S T SGND llGNDFlt Management Sys 2Reserved J1--66(I) ENC ALT1 A2 (N) J1--67 (24) Encoding Altm #1(I) ENC ALT1 A4 (N) J1--68 (24) Encoding Altm #1(I) ENC ALT1 B1 (N) J1--69 (24) Encoding Altm #1(I) ENC ALT1 B2 (N) J1--70 (24) Encoding Altm #1(I) ENC ALT1 B4 (N) J1--71 (24) Encoding Altm #1(I) XPDR STANDBY (NO) J1--72 (24) Control Panel(I) SQUAT SWITCH 1 (NO) J1--73 (24) Control Panel or AcftSquat Switch4(I) XPDR OFF (NO) J1--74 NC(I) SQUAT SWITCH 2 (NO) J1--75 (24) Control Panel or AcftSquat Switch4XPDR TX RCB (P) J1--76 NCXPDR TX RCB (N) J1--77 NCXPDR RX RCB (P) J1--78 NCXPDR RX RCB (N) J1--79 NC(I) ENC ALT2 C1 (N) J1--80 (24) Encoding Altm #2(I) ENC ALT2 C2 (N) J1--81 (24) Encoding Altm #2(I) ENC ALT2 C4 (N) J1--82 (24) Encoding Altm #2(I) ENC ALT2 D2 (N) J1--83 (24) Encoding Altm #2(I) ENC ALT2 D4 (N) J1--84 (24) Encoding Altm #2(I) ENC ALT2 A1 (N) J1--85 (24) Encoding Altm #2Reserved J1--86Reserved J1--87Reserved J1--88
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.3--33Table 3--4. RCZ--852 Diversity Mode S Transponder Interconnect Data (cont)I/O NotesConnects ToConnectorPinDescriptionReserved J1--89(O) XPDR STRAP +5V J1--90 (26) Strap Board (Red) 4(O) XPDR STRAP CLK (N) J1--91 (26) Strap Board (Blue) 4(O) XPDR STRAP LOAD (N) J1--92 (26) Strap Board (Orn) 4(I) XPDR STRAP DATA (P) J1--93 (26) StrapBoard(Wht) 4(I) ENC ALT2 A2 (N) J1--94 (24) Encoding Altm #2(I) ENC ALT2 A4 (N) J1--95 (24) Encoding Altm #2(I) ENC ALT2 B1 (N) J1--96 (24) Encoding Altm #2(I) ENC ALT2 B2 (N) J1--97 (24) Encoding Altm #2(I) ENC ALT2 B4 (N) J1--98 (24) Encoding Altm #2(O) XPDR ACTIVE (NO) J1--99 (24) Antenna SwitchingRelay4(O) XPDR VALID (NO) J1--100 (24) Control PanelReserved J1--101(O) ALT VALID (NO) J1--102 (24) Control Panel 5(O) XPDR STRAP GND J1--103 (26) StrapBoard(Blk) 4(O) XPDR STRAP PGM (N) J1--104 (26) Strap Board (Grn) 4(O) XPDR STRAP PGM (P) J1--105 (26) StrapBoard(Yel) 4-- POLARIZATION PIN J1--106 NC(I) Bottom Antenna RF Input J2 coax Bottom Antenna(I) Top Antenna RF Input J3 coax Top AntennaNOTES:1. Use AWG--24 single conductor, shielded wire. Attach shield to ground loop E1 or E2 on back ofmounding tray.2. Two wire shielded cable. Tie shields to ground loop E1 or E2 located on back of mounting tray.3. This ARINC 429 output is required on some Collins Control Panels that require a feedback loop tomake sure the transponder is working properly.4. Refer to interface descriptions in Table 4--5.5. This output is connected only if the control panel has an ALT FAIL input function.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.3--34Table 3--5. Strap Assembly Strap AssignmentsStrapNumber NameStrapNumber NAMEW1 System Position B0 W25 Mode S Address B16W2 System Position B1 W26 Mode S Address B17W3 Parity W27 Mode S Address B18W4 Parity W28 Mode S Address B19W5 Squat Switch Polarity W29 Mode S Address B20W6 Maximum Airspeed B0 W30 Mode S Address B21W7 Maximum Airspeed B1 W31 Mode S Address B22W8 Maximum Airspeed B2 W32 Mode S Address B23W9 Mode S Address B0 W33 Altitude Source B0W10 Mode S Address B1 W34 Altitude Source B1W11 Mode S Address B2 W35 DLP InstalledW12 Mode S Address B3 W36 TCAS II InstalledW13 Mode S Address B4 W37 Antenna Cable Installation B0W14 Mode S Address B5 W38 Antenna Cable Installation B1W15 Mode S Address B6 W39 TCAS TA Display EnableW16 Mode S Address B7 W40 TCAS I InstalledW17 Mode S Address B8 W41 Altitude ResolutionW18 Mode S Address B9 W42 ReservedW19 Mode S Address B10 W43 ReservedW20 Mode S Address B11 W44 ReservedW21 Mode S Address B12 W45 ReservedW22 Mode S Address B13 W46 ReservedW23 Mode S Address B14 W47 ReservedW24 Mode S Address B15 W48 ReservedNOTE: The strap logic levels are as follows:GND = Jumper wire installed (Uncut)OPEN = Jumper wire not installed (Cut)
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.3--35Figure 3--12. Strap AssemblyTable 3--6. Strap Assembly Programming InstructionsStrapNumber Functional DescriptionW1W2SYSTEM (SIDE) POSITION: (B0, B1)The System (Side) Position straps define which system position the transponder islocated at. Normal practice is to designate the captain’s or pilot’s system as Side 1, thecopilot’s system as Side 2, and the engineer’s, center, or backup system as Side 3. Thestraps are defined as follows:Strap NumberW1 W2 DefinitionGnd Gnd Side 1Open Gnd Side 2Gnd Open Side 3Open Open ReservedW3W4PARITYThe Parity straps are used to make sure the strap data is valid. Straps W3 and W4 areparity bits and must be programmed as follows:After all other straps have been programmed, count the number of Gnd (Uncut) straps inpositions W1, W2 and W5 thru W48. If the number of uncut straps is even, cut strap W3.If the number of uncut straps is odd, cut strap W4.NOTES:1. To have correct parity, either jumper W3 or W4 has to be cut, but not both.2. If parity is invalid, the transponder fails the Power--On Self--Test (POST) anddiscontinues operation.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.3--36Table 3--6. Strap Assembly Programming Instructions (cont)StrapNumber Functional DescriptionW5 SQUAT SWITCH POLARITYThe Squat Switch Polarity strap is used to indicate the logic or signal sense of the aircraftsquat switch on ground condition. If the squat switch is closed when the aircraft is on theground, jumper W5 must be installed (Uncut). If the squat switch is closed when theaircraft is airborne, jumper W5 must be Open (Cut).W6W7W8AIRCRAFT MAXIMUM TRUE AIRSPEED RANGE: (B0, B1, B2)The Aircraft Maximum True Airspeed Range straps are used to define the aircraft’smaximum airspeed capability. The straps are defined as follows:Strap NumberW6 W7 W8 DefinitionGnd Gnd Gnd No Data AvailableOpen Gnd Gnd 75 Knots or LessGnd Open Gnd 76 to 150 KnotsOpen Open Gnd 151 to 300 KnotsGnd Gnd Open 301 to 600 KnotsOpen Gnd Open 601 to 1200 KnotsGnd Open Open Over 1200 KnotsOpen Open Open Not AssignedW9 thru W32(LSB -- MSB)MODE S ADDRESS: (B0 THRU B23)The Mode S Address is a unique 24--bit code assigned to each aircraft. Straps W9 thruW32 are used to program this 24--bit binary number. The straps must be set according tothis binary number representation. Each binary 1 represents a Cut strap and each binary0 represents an Uncut strap. Strap W9 represents the least significant digit of the binarynumber and strap W32 represents the most significant digit of the binary number. Theinitial board condition with all jumpers is a 0 address.NOTE: An address of all 0’s or all 1’s is an illegal address, and can cause the aircraft tobe invisible to TCAS II equipped aircraft in flight. Never use an illegal addressfor an installed system.W33W34ALTITUDE SOURCE: (B0, B1)The Altitude Source straps select the type of altitude information used by the transponder.Altitude information can be generated by an encoding altimeter in the form of Gray akaGillham code, or by a digital Air Data Computer. The straps are defined as follows:Strap NumberW33 W34 DefinitionGnd Gnd Gillham Gray Code Altitude SourceOpen Gnd ARINC 429 Altitude SourceGnd Open ARINC 575 Altitude SourceOpen Open RSB Altitude SourceNOTE: The RSB altitude source is a valid selection only when the transponder receivestuning information from an RCB bus.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.3--37Table 3--6. Strap Assembly Programming Instructions (cont)StrapNumber Functional DescriptionW35 DLP INSTALLEDThe DLP Installed strap specifies whether the transponder is connected to an AirborneData Link Processor system. The strap is selected as follows:Gnd = DLP is not installedOpen = DLP is installedW36 TCAS II INSTALLEDThe TCAS II Installed strap specifies whether the transponder is connected to a TCAS IIsystem. The strap is selected as follows:Gnd = TCAS II is not installedOpen = TCAS II is installedNOTE: If both TCAS II and TCAS I (strap W40) are set (Grounded), the transponderwill default to TCAS II operation. Both straps should not be cut.W37W38ANTENNA CABLE INSTALLATION: (B0, B1)The Antenna Cable Install straps are used to set the system for either a single (bottom)antenna installation, or a diversity installation. In the diversity installation, the strapsadjust for the difference in RF propagation times through the upper and lower antennacables which occur because of their dissimilar lengths. The antenna cable delay isselected as follows:Strap NumberW37 W38 DefinitionGnd Gnd Single (bottom) Antenna InstallationOpen Gnd Top > Bottom Cable Length, Differential Delay >40 nanosecondsGnd Open Bottom > Top Cable Length, Differential Delay >40 nanosecondsOpen Open Differential Delay is <40 nanosecondsNOTE: The differential delay is equal to two times the length (in feet) of the differencebetween the top and bottom antenna cable lengths, times the characteristicdelay (nanoseconds / feet) of the cable type in use.W39 TCAS TA DISPLAY ENABLEThe TCAS Display Enable strap allows the TCAS display to be either tunable or fixed.The strap is not processed by the transponder, but is used by a RMU when an RSBtuning source is selected. The strap is not used by ARINC tuning sources. The strapdefinition is as follows:Gnd = TA Display is tunable (ON / OFF / AUTO POP--UP) modes selectableOpen = TA Display is not selectable (AUTO POP--UP mode only)W40 TCAS I INSTALLEDThe TCAS I Installed strap specifies whether the transponder is connected to a TCAS Isystem. The strap is selected as follows:Gnd = TCAS I is not installedOpen = TCAS I is installedNOTE: If both TCAS I and TCAS II (strap W36) are set (Grounded), the transponderwill default to TCAS II operation. Both straps should not be cut.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.3--38Table 3--6. Strap Assembly Programming Instructions (cont)StrapNumber Functional DescriptionW41 ALTITUDE RESOLUTIONThe Altitude Resolution strap allows the transponder output to the TCAS (label 203) to beeither 100 foot resolution or 1 foot resolution. The strap definition is as follows:Gnd = 1 Foot ResolutionOpen = 100 Foot ResolutionNOTE: Most ARINC altitude inputs require 1 foot resolution.W42thruW48 RESERVED FUNCTIONThese straps are not used. The jumpers should be installed (Uncut).W49W50Jumpers W49 and W50 are not part of the 48--bit serial data pulse train and are not usedon RCZ--852 Transponder installations. The jumpers should be installed (Uncut).
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--1LOADING/GRADIENT SPECIFICATIONS1. GeneralThis section contains the loading and gradient specifications for the input and output signalsof each component of the T2CAS system.2. TCAS Interface DescriptionComponent Table No.TT--950/951/952 T2CAS Computer Unit Interface Description Table 4--1Gables Control Panel Interface Description Table 4--241--Pin VSI/TRA Interface Description (Thales) Table 4--3XS--950 Data Link Transponder Interface Description Table 4--4RCZ--852 Diversity Mode S Transponder Interface Description Table 4--5
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--2Table 4--1. TT--950/951/952 T2CAS Computer Unit Interface DescriptionConnector PinDesignation Functional DescriptionT2CAS Computer Unit Right Middle Plug (RMP)RMP--1A,toRMP--1DReserved Discrete Outputs (Standard Ground/Open)RMP--1E TA Display Enable Discrete Output (NO)This output is a ground/open type discrete (Note 3) used by the weather radar display toplace the radar in standby mode. A ground on this pin enables the weather radar display.RMP--1F Corrective Aural Advisory Discrete Output (NO)This aural advisory discrete output is a ground/open type discrete (Note 3) used to controlexternal equipment that generate tones to accompany TCAS advisories. The output isactive whenever a corrective advisory (RA that requires a corrective maneuver) is issued.The output remains active for the duration of the synthesized voice unless it is cancelledby the cancel discrete at RMP--3D. Only one aural advisory is active at a time. Thecorrective discrete and preventative discrete at RMP--1K are mutually exclusive. Theactive state is ground and the inactive state is open.RMP--1G Reserved for GPS use.RMP--1H Reserved for GPS use.RMP--1J Climb Inhibit No. 1 Discrete Input (NO)This input is a ground/open type discrete used to provide information to the T2CAS CUwhether to assume the aircraft cannot achieve a climb rate of 1500 feet per minute(FPM). The climb inhibit discrete inputs are designed in pairs (No. 1 and No. 2 atRMP--13G, or No. 3 at RBP--5J and No. 4 at RBP--5K) but can be wired as a single inputor in conjunction with other aircraft operations to achieve airframe customization of theclimb inhibit feature. The 1500 FPM climb inhibit function is assumed whenever No. 1and No. 2 are ground or No. 3 and No. 4 are ground.See Note 1 for Ground/Open type discrete input definition.RMP--1K Preventive Aural Advisory Discrete Output (NO)Same as RMP--1F, except this discrete is active whenever a preventative advisory (RAthat directs the flight crew to avoid certain maneuvers or maintain flight path) is issued.RMP--2A Traffic Aural Advisory Discrete Output (NO)Same as RMP--1F, except this discrete is active during a traffic advisory when informationis being given to the flight crew regarding other aircraft in the immediate vicinity. Nosuggested maneuver is issued. This output is inhibited if either the corrective orpreventative output is active.RMP--2B Reserved for TAWS/RWS use.RMP--2C Reserved for TAWS/RWS use.RMP--2D Advisory/Announce CommonThis is the return line for the aural and visual advisory discrete outputs.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--3Table 4--1. TT--950/951/952 T2CAS Computer Unit Interface Description (cont)Connector PinDesignation Functional DescriptionRMP--2E Spare PinRMP--2F, 2G 8 Ohm Audio Output: (RMP--2F [HI], RMP--2G [LO])This is a synthesized voice output supplied by the T2CAS computer unit. Its level isprogrammable up to 8 Watts into an 8 Ohm speaker. All aural traffic and resolutionadvisories are announced over this output. See RBP--7A for audio level programming.RMP--2H, 2J Radio Altimeter No. 1 ARINC 552/Analog Input: (RMP--2H [HI], RMP--2J [LO])Normal aircraft configurations include either two digital or two analog radio altimetersources. The T2CAS computer unit attempts to establish which type is present in order toobtain data from one of the two available sources. TCAS first checks the radio altimeterNo. 1 valid flag at RMP--2K. If No. 1 is not valid then No. 2 valid is checked at RBP--3C.If neither are valid then TCAS checks digital source No. 1 for valid data on the ARINC429 bus at RMP--13H and RMP--13J. If none of the above are valid then the TCASchecks the digital source No. 2 for valid data on the ARINC 429 bus at RBP--3D andRBP--3E. This process is repeated until a valid flag or data is detected.Until a valid source is found, the TCAS function inhibits all surveillance, CAS, and TA/RAdisplay functions, records failures in maintenance memory, and sets the TCAS systemstatus discrete output at RMP--13K to invalid. The TCAS function uses radio altitude toinhibit advisories and aural annunciation when in close proximity to the ground. Thisanalog input No. 1, as well as analog input No. 2, can accept data as a dc voltage fromseveral types of radio altimeters. The type of radio altimeter is selected using theprogram pins RMP--12B and RMP--12H thru RMP--12K.RMP--2K Radio Altimeter No. 1 Valid Input (PO)See RMP--2H. A valid condition is greater than +18.5 Vdc. An invalid is open circuit.RMP--3A Corrective Visual Advisory Discrete Output (NO)The visual advisory discrete outputs are ground/open type discretes (Note 3) used tooperate the annunciator lights on the displays. This output is activated whenever acorrective aural advisory is issued. The output remains active for the duration of theadvisory unless cancelled by the cancel discrete at RMP--3D. Only one visual advisory isactive at a time. The active state is ground and the inactive state is open.RMP--3B Preventive Visual Advisory Discrete Output (NO)Same as RMP--3A, except this discrete is activated whenever a preventative auraladvisory is issued.RMP--3C Traffic Visual Advisory Discrete Output (NO)Same as RMP--3A, except this discrete is active during a traffic advisory.RMP--3D Cancel Discrete Input (NO)This input discrete provides a means of canceling aural and visual alerts. It should beconnected to a cancel button (momentary ground type), if used. Groundprox/Windshearhas priority over the cancel button. Open is the inactive state and a momentary ground(less than 50 Ohms) produces the active state, canceling any active aural or visual alert.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--4Table 4--1. TT--950/951/952 T2CAS Computer Unit Interface Description (cont)Connector PinDesignation Functional DescriptionRMP--3E Spare PinRMP--3F, 3G 600 Ohm Audio Output: [RMP--3F (HI), RMP--3G (LO)]This is a synthesized voice output supplied by the T2CAS computer unit. Its level isprogrammable up to 80 milliwatts into a 600 Ohm audio distribution system. All auraltraffic and resolution advisories are annunciated over this output. See RBP--7A for audiolevel programming.RMP--3H Spare PinRMP--3J Reserved for TAWS/RWS use.RMP--3K Reserved for TAWS/RWS use.RMP--4A Reserved for TAWS/RWS use.RMP--4B Reserved for TAWS/RWS use.RMP--4C Reserved for TAWS/RWS use.RMP--4D TCAS Installed Discrete Output (Ground)Indicates to external systems that a TCAS Computer is installed.RMP--4E Reserved for TAWS/RWS use.RMP--4F Reserved for TAWS/RWS use.RMP--4G Reserved for TAWS/RWS use.RMP--4H Reserved for TAWS/RWS use.RMP--4J Reserved for TAWS/RWS use.RMP--4K Reserved for TAWS/RWS use.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--5Table 4--1. TT--950/951/952 T2CAS Computer Unit Interface Description (cont)Connector PinDesignation Functional DescriptionRMP--5A Reserved for TAWS/RWS use.RMP--5B Reserved for TAWS/RWS use.RMP--5C Reserved for TAWS/RWS use.RMP--5D Reserved for TAWS/RWS use.RMP--5E ADS--B Program Input (Intruder File Enable).RMP--5F ADS--B Program Input (GP Bus Enable).RMP--5G ADS--B Program Input (Reserved)RMP--5H Reserved for TAWS/RWS use.RMP--5J Reserved for TAWS/RWS use.RMP--5K Air Ground Discrete Input (NO): (Weight--On--Wheels)This ground/open type discrete input (Note 1) to the T2CAS computer unit indicates thestatus of the Air/Ground or Weight--On--Wheels (WOW) switch. TCAS filters this input tomake sure it remains in a steady state a minimum of 4 seconds before an Air/Groundtransition is recorded. An open indicates the aircraft is airborne and a ground indicatesthe aircraft is on the ground.Inputs should be diode isolated from each other.RMP--6A, 6B ARINC 429 Performance Limit Input: [RMP--6A (A), RMP--6B (B)]This Low Speed ARINC 429 (12.5 Kbits/s) input is provided for future applications toreceive climb rate performance limit information from an external device such as a FlightManagement Computer.RMP--6C Reserved for TAWS/RWS use.RMP--6D Performance Limit Discrete Input (NO)This input provides the T2CAS computer unit with an input from the Flight ManagementComputer (or equivalent) which indicates when the aircraft cannot achieve a 1500 FPMclimb rate. When this input is ground, the climb rate is not limited and no action isneeded by the T2CAS computer unit. When this input is open, the climb rate is limitedwhen the aircraft is above the value set by the altitude limit program pins (RMP--6E thruRMP--6J).
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--6Table 4--1. TT--950/951/952 T2CAS Computer Unit Interface Description (cont)Connector PinDesignation Functional DescriptionRMP--6E 2000 FT Altitude Limit Program Pin (NO)This pin, along with pins RMP--6F thru RMP--6J, select the “can’t climb” altitude in2,000--foot increments up to 62,000 feet. This is the altitude the aircraft is not able toachieve a 0.25 G vertical acceleration to a 1500 FPM climb rate for an altitude gain of 750feet above a certain altitude under all circumstances. The “can’t climb” altitude isselected by connecting jumper wires from altitude limit program pins to the programcommon pin (RMP--6K).RMP--6F 4000 FT Altitude Limit Program Pin (NO)See RMP--6E.RMP--6G 8000 FT Altitude Limit Program Pin (NO)See RMP--6E.RMP--6H 16000 FT Altitude Limit Program Pin (NO)See RMP--6E.RMP--6J 32000 FT Altitude Limit Program Pin (NO)See RMP--6E.RMP--6K Program CommonSee RMP--6E.RMP--7A, 7B ARINC 429 Magnetic Heading/Attitude Input: [RMP--7A (A), RMP--7B (B)]Reserved for future useRMP--7C, 7D ARINC 429 TA/RA Display No. 1 Output: [RMP--7C (A), RMP--7D (B)]This is one of two ARINC 429 high speed (100 kbits/s) bus outputs that supplies data tothe TA/RA display such as a VSI/TRA or EFIS. The other output (TA/RA Display No. 2) isat RMP--7G and --7H. The TA/RA Display No. 1 outputs are also connected to the front(PDL) connector, which is used to supply display information to maintenance displays.See J1--33 and J1--34.RMP--7E TA/RA Display No. 1 Status Discrete Input (NO)Two display status ground/open discrete inputs (Note 1) are provided by the T2CAScomputer unit at RMP--7E (TA/RA Display No. 1) and RMP--7J (TA/RA Display No. 2). Aground on either of these inputs is interpreted by TCAS to mean the display associatedwith that input is operating normally and is capable of displaying the TA/RA information,and that its data bus is active. An open indicates the inability of the display to presentadvisories or indicates its data bus is inactive.RMP--7F Spare PinRMP--7G, 7H ARINC 429 TA/RA Display No. 2 Output: [RMP--7G (A), RMP--7H (B)]See RMP--7C and --7D.RMP--7J TA/RA Display No. 2 Status Discrete Input (NO)See RMP--7E.RMP--7K Spare Pin
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--7Table 4--1. TT--950/951/952 T2CAS Computer Unit Interface Description (cont)Connector PinDesignation Functional DescriptionRMP--8A, 8B ARINC 429 Data Loader Input: [RMP--8A (A), RMP--8B (B)]These pins are used when the T2CAS computer unit is communicating with an ARINC603 or 615 airborne data loader (ADL) through the rear ARINC 600 connector. The dataloader programs the program memory in the T2CAS computer unit per the data loaderfunction specified. The ADL and portable data loader (PDL) Low Speed ARINC 429inputs (12.5 kbits/s) have separate receiver busses to allow for simultaneous connectionof the ADL and PDL.These pins are also connected to the front (PDL) connector on the front of the unit. SeeJ1--1 and J1--2.RMP--8C,8D ARINC 429 ADS--B No. 1 Input: [RMP--8C (A), RMP--8D (B)]TA/RA Display Control A429 Input #1RMP--8E, 8F ARINC 429 Bus Input: [RMP--8E (A), RMP--8F (B)]General Purpose A429 Input #1RMP--8G, 8H ARINC 429 Bus Input: [RMP--8G (A), RMP--8H (B)]TA/RA Display Control A429 Input #2RMP--8J, 8K ARINC 429 ADS--B No. 2 Input: [RMP--8J (A), RMP--8K (B)]TAWS to TCAS A429 Output (A)RMP--9A, 9B ARINC 429 Data Loader Output: [RMP--9A (A), RMP--9B (B)]These pins are used when the T2CAS computer unit is communicating with an ARINC603 or 615 airborne data loader (ADL) through the rear ARINC 600 connector. Thisconnection is used to transmit data to the ADL during data loading operations.These pins are also connected to the front (PDL) connector on the front of the unit. SeeJ1--8 and J1--9.RMP--9C, 9D Reserved for GPS use.RMP--9E, 9F Reserved for TAWS/GPS use.RMP--9G, 9H ARINC 429 Bus Output: [RMP--9G (A), RMP--9H (B)]CD General Purpose A429 Output #1RMP--9J, 9K ARINC 429 ADS--B No. 2 Output: [RMP--9J (A), RMP--9K (B)]CD General Purpose A429 Output #2
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--8Table 4--1. TT--950/951/952 T2CAS Computer Unit Interface Description (cont)Connector PinDesignation Functional DescriptionRMP--10ARMP--10BRMP--10CADS--B Program InputsReserved for future use.RMP--10D Single Mode S Installation Program InputsThis pin allows the T2CAS CU to be configured for single or dual Mode S Transponderoperation. When a single Mode S installation is enabled, the T2CAS CU defaults to theNo. 1 Position Transponder without indicating Failure of the No. 2 Position Transponder.A Ground indicates Single Mode S Transponder Installation and an Open indicates DualMode S Transponder Installation.RMP--10E Reserved for TAWS/RWS use.RMP--10F Reserved for TAWS/RWS use.RMP--10GThruRMP--10KReserved Program InputsReserved for future use.RMP--11A Altitude Alerter Program InputRMP--11B Traffic Display of Flight ID Program InputThis program pin allows traffic display of flight identification information from atransponder to be output on the TA/TA displays. A ground on this pin enables thisfunction and an open disables the function.RMP--11C Male Voice Program InputThis program input is intended to allow audio annunciation to be selectable for either maleor female genders. A ground on this pin selects the male voice and an open selects thefemale voice.RMP--11D Flight Data Recorder ARINC 429 and Extended Maintenance Log Program InputThis program pin is used to specify whether the ARINC 429 Flight Data Recorder (FDR)is to be used. An open on this pin means that the FDR is not utilized. A ground indicatesthat flight data is output as high--speed ARINC 429 (100 kbits/s) data on RA Display No. 1and No. 2 buses. While the FDR is enabled, normal low--speed RA display bus operationis not available. A ground also enables RA/TA events recording in memory.RMP--11EThruRMP--11K Reserved for TAWS/RWS use.RMP--12A Reserved Program InputReserved for future use.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--9Table 4--1. TT--950/951/952 T2CAS Computer Unit Interface Description (cont)RMP--12B Radio Altimeter Type Select Program Input No. 4 (NO)The T2CAS computer unit uses radio altitude to inhibit advisories and aural annunciationwhen in close proximity to the ground. This analog input No. 1, as well as analog inputNo. 2 can accept data as a dc voltage from several types of radio altimeters. Programpin RMP--12B is used, along with program pins RMP--12H, --12J, and --12K, to identify thetype of analog radio altimeter installed.For T2CAS CU ARINC 552, Collins BCA, AHV--6, NR--AS--10A, LPIA, APN--232 CARAand metric type radio altimeters can be selected. The program pin inputs useground/open logic levels. All unassigned program pin combinations are invalid andshould not be selected. Pin RMP--6K can be used to supply a ground.Program PinRMP--12K RMP--12J RMP--12H RMP--12B Altimeter TypeOpen Open Open Open ARINC 552/552AOpen Open Open Ground Collins BCAOpen Open Ground Open Metric Altimeter No. 1Open Open Ground Ground UnassignedOpen Ground Open Open Metric Altimeter No. 2Open Ground Open Ground UnassignedOpen Ground Ground Open Metric Altimeter No. 3Open Ground Ground Ground UnassignedGround Open Open Open Metric Altimeter No. 4Ground Open Open Ground UnassignedGround Open Ground Open Military AHV6 (Linear)Ground Open Ground Ground Military AHV6 (Log)Ground Ground Open Open Military NR--AS--10A (Alternate)Ground Ground Open Ground Military APN--232 CARAGround Ground Ground Open Military LPIAGround Ground Ground Ground Military NR--AS--10A (Curve Fit)The Radio Altitude sources listed are defined by the following:ARINC 552/552A-- 2 0 < H < 480 feet: Voltage = [ 0.02 x (H + 20) ] Vdc480 < H < 2500 feet: Voltage = [ 10 x ( 1 + ln((H + 20)/500)) ] VdcWere H = Radio Altitude in feet.Maximum Voltage output is 26.2 Vdc at any height above 2500 feet.Collins BCA-- 2 0 < H < 500 feet: Voltage = [ 0.02 x (H + 20) ] Vdc500 < H < 2500 feet: Voltage = [ 10.4 + 0.003 x (H -- 500) ] VdcWere H = Radio Altitude in feet.Maximum Voltage output is 26.2 Vdc at any heightabove 2500 feet.AHV 6 Linear0.0 to 25.0 Vdc: H = 200V -- 20Were H = Radio Altitude in feet and V = Voltage in Volts dc.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--10Table 4--1. TT--950/951/952 T2CAS Computer Unit Interface Description (cont)Connector PinDesignation Functional DescriptionRMP--12B(Continued)Radio Altimeter Type Select Program Input No. 4 (NO)AHV 6 Log0.0 to 10.4 Vdc: H = 50V -- 20> 10.4 to 18.09 Vdc: H = EXP(0.1479V + 4.7289)> 18.09 to 25 Vdc: H = 695 + EXP(0.2532V + 2.1111)Were H = Radio Altitude in feet and V = Voltage in Volts dc.APN 2320.0 to 27.0 Vdc: H = 200VWere H = Radio Altitude in feet and V = Voltage in Volts dc.LPIA1.0 to 9.0 Vdc: H = 50V -- 50> 9.0 to 21.0 Vdc: H = 383.14V -- 3048Were H = Radio Altitude in feet and V = Voltage in Volts dc.N R -- A S -- 1 0 A Alternate0.0 to 1.2 Vdc: H = 2105.7VWere H = Radio Altitude in feet and V = Voltage in Volts dc.N R -- A S -- 1 0 A C u r v e Fit0.0 to 18.1 Vdc: H = 0.0833V4-- 1.8887V3+ 15.5169V2-- 21.9374V + 14.8097Were H = Radio Altitude in feet and V = Voltage in Volts dc.Each of the military radio altimeter types provide two outputs that are connected to theT2CAS computer unit input pins. The two altimeter outputs are the Analog Data Outputand Analog Data Reliability Signal. The Data Reliability Signal is connected to RMP--2Kfor source No. 1 and RBP--3C for source No. 2, except for altimeter type LPIA. For radioaltimeter type LPIA, the Analog Data Output must be connected to RMP--2H (HI) andRMP--2J (LO), the Analog Data Reliability Signal must be connected to RBP--3A (HI) andRBP--3B (LO), and the inputs RMP--2K and RMP--3C are set high (greater than 18.5 V).The metric radio altimeters are defined as follows:MetricAltimeter DefinitionNo. 1 Metric unit-- 1000 meter range, 25 mV/M scalingNo. 2 Metric unit-- 1000 meter range, 20 mV/M scalingNo. 3 Metric unit-- 1500 meter range, 20 mV/M scalingNo. 4 Metric unit-- 750 meter range, 50 mV/M scaling
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--11Table 4--1. TT--950/951/952 T2CAS Computer Unit Interface Description (cont)Connector PinDesignation Functional DescriptionRMP--12C RA/TA Block Transfer Program Input (NO)This program input determines the type of block transfer that is made from the T2CAScomputer unit to the TA/RA displays. If this pin is grounded, the T2CAS computer unittransmits in Honeywell BCA EFIS format. If the T2CAS computer unit senses an open atthis pin, it transmits in ARINC 735 format.RMP--12D Aircraft Type 1 Program InputThis program pin is used with pin RMP--12E to designate the aircraft manufacturer (AirTransport customers only) for maintenance support functionality. The aircraftmanufacturer is determined as follows:RMP--12D RMP--12E DescriptionOpen Open All other airframes including BCA aircraftOpen Ground BoeingGround Open McDonnell DouglasGround Ground AirbusRMP--12E Aircraft Type 0 Program InputSee RMP--12D.RMP--12F Reserved Program InputReserved for future use.RMP--12G Option Parity Program InputThe T2CAS computer unit uses nine discrete program input pins to determine whichoptions have been selected by the installer. Eight of these pins are used to determineoption selections. The ninth pin (RMP--12G) is used to determine parity for the eightoption selection pins (RMP--10G, --10H, --10J, --10K, --11A, --11B, --11C, and --11D). Todetermine parity, count the number of option pins that are grounded. If the number ofpins that are grounded is an odd number (1, 3, 5, 7), ground pin RMP--12G. If thenumber of grounded pins in the option group is an even number (0, 2, 4, 6, 8), leave pinRMP--12G open.RMP--12H Analog Radio Altimeter Type Select Program Input No. 3 (NO)See RMP--12B.RMP--12J Analog Radio Altimeter Type Select Program Input No. 2 (NO)See RMP--12B.RMP--12K Analog Radio Altimeter Type Select Program Input No. 1 (NO)See RMP--12B.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--12Table 4--1. TT--950/951/952 T2CAS Computer Unit Interface Description (cont)Connector PinDesignation Functional DescriptionRMP--13A, 13B RA Display No. 1/ARINC 429 Data Recorder Output: [RMP--13A (A), RMP--13B (B)]These ARINC 429 outputs are configured to output either RA information or for use as anARINC 429 data recorder function. The output is configured by program pin RMP--11D.When RMP--11D is open (standard configuration), the bus is configured for low--speed(12.5 kbits/s) ARINC 429 operation and RA information is output according to the formatspecified for the RA display bus in ARINC 735. When RMP--11D is grounded, the bus isconfigured for high--speed (100 kbits/s) ARINC 429 operation and the output supplies TAand RA information to a 429 data recorder.RMP--13C, 13D RA Display No. 2/ARINC 429 Data Recorder Output: [RMP--13C (A), RMP--13D (B)]See RMP--13A.RMP--13E RA Display No. 2 Status Discrete Input (NO)This ground/open discrete input (Note 1) provides the functional status of RA Display No.2. A ground on this pin indicates a valid display. If this discrete is not used by the RADisplay, connect to aircraft ground to prevent RA DISPLAY No. 2 fail message duringself--test.RMP--13F Landing Gear Discrete Input (NO)The T2CAS computer monitors this discrete that indicates the landing gear position.Landing Gear is a Ground/Open type discrete (Note 1) were an open indicates the gear isretracted (gear is up) and a ground indicates the gear is extended (gear is down).RMP--13G Climb Inhibit No. 2 Discrete Input (NO)See RMP--1J.RMP--13H, 13J Radio Altimeter No. 1 Input: [RMP--13H (A), RMP--13J (B)]This input is provided for Low Speed ARINC 429 (12.5 Kbits/s) altitude inputs from anARINC 707 digital radio altimeter. Radio altitude data is used for computation ofsensitivity level, inhibit descend advisories, and inhibit aural annunciation when in closeproximity to the ground. Also see RMP--2H.RMP--13K TCAS System Valid Discrete Output (NO)This ground/open type discrete output (Note 3) indicates the health status of the T2CAScomputer unit to other avionics systems that monitor TCAS system status. This output isused in retrofit installations where instrumentation needs to monitor TCAS status and thestatus is not available across an A429 bus. A ground at this pin indicates normal TCASoperation. An open indicates a TCAS fault.RMP--14A, 14B ARINC 429 TX Coordination Bus No. 2 Output: [RMP--14A (A), RMP--14B (B)]This differential pair output is a high speed ARINC 429 bus (100k bits/second nominal),that transmits data from the TCAS computer unit to the No. 2 Mode S Transponder.The labels on this bus are as follows: 273, 274, 275.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--13Table 4--1. TT--950/951/952 T2CAS Computer Unit Interface Description (cont)Connector PinDesignation Functional DescriptionRMP--14C RA Display No. 1 Status Discrete Input (NO)This ground/open discrete input (Note 1) provides the functional status of RA Display No.1. A ground on this pin indicates a valid display. If this discrete is not used by the RAdisplay, connect to aircraft ground to prevent RA DISPLAY No. 1 fail message duringself--test.RMP--14D, 14E Selected Altitude701/720 ARINC 429 Bus InputReserved for future use.RMP--14F, 14G ARINC 429 XT Coordination No. 1 Input: [RMP--14F (A), RMP--14G (B)]This differential pair input is a high speed ARINC 429 bus (100k bits/second nominal),that receives data from the No. 1 Mode S Transponder.The labels on this bus are as follows: 013, 015, 016, 203, 271, 272, 273, 274, 275, 276,277, 350.RMP--14H, 14J ARINC 429 XT Coordination No. 2 Input: [RMP--14H (A), RMP--14J (B)]This differential pair input is a high speed ARINC 429 bus (100k bits/second nominal),that receives data from the No. 2 Mode S Transponder.The labels on this bus are as follows: 013, 015, 016, 203, 271, 272, 273, 274, 275, 276,277, 350.RMP--14K Reserved for TAWS/RWS use.RMP--15AtoRMP--15HReserved for TAWS/RWS use.RMP--15J, 15K ARINC 429 TX Coordination No. 1 Output: [RMP--15J (A), RMP--15K (B)]This differential pair output is a high speed ARINC 429 bus (100k bits/second nominal),that transmits data from the T2CAS computer unit to the No. 1 Mode S Transponder.The labels on this bus are as follows: 273, 274, 275.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--14Table 4--1. TT--950/951/952 T2CAS Computer Unit Interface Description (cont)Connector PinDesignation Functional DescriptionT2CAS Computer Unit Right Bottom Plug (RBP)RBP--1AThruRBP--1G Reserved for TAWS/RWS use.RBP--1H RA Data Word 270 Bit 18 Discrete OutputThis discrete output provides RA information to the ARINC 573 flight recorder. Theoutput goes to the “ground” state each time its associated bit within the advisory field ofthe RA output words changes from a “zero” condition to a “one” condition. The outputremains in the “ground” state for as long as the associated RA bit remains non--zero.This output is read by the flight recorder as either a series or shunt output.NOTE: The discrete is pulled up to +28 Vdc in the “open” state.RBP--1J RA Data Word 270 Bit 19 Discrete OutputSee RBP--1H.RBP--1K RA Data Word 270 Bit 20 Discrete OutputSee RBP--1H.RBP--2AThruRBP--2G Reserved for TAWS/RWS use.RBP--2H RA Data Word 270 Bit 21 Discrete OutputSee RBP--1H.RBP--2J RA Data Word 270 Bit 22 Discrete OutputSee RBP--1H.RBP--2K RA Data Word 270 Bit 23 Discrete OutputSee RBP--1H.RBP--3A, 3B Radio Altimeter No. 2 ARINC 552/Analog Input: [RBP--3A (HI), RBP--3B (LO)]See RMP--2H and --2J.RBP--3C Radio Altimeter No. 2 Valid Discrete Input (PO)See RMP--2H. Valid condition is greater than +18.5 Vdc. Invalid is open.RBP--3D, 3E Radio Altimeter No. 2 Input: [RBP--3D (A), RBP--3E (B)]See RMP--13H. Also see RMP--2H.RBP--3F,RBP--3GReserved for TAWS/RWS use.RBP--3H RA Data Word 270 Bit 24 Discrete OutputSee RBP--1H.RBP--3J RA Data Word 270 Bit 25 Discrete OutputSee RBP--1H.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--15Table 4--1. TT--950/951/952 T2CAS Computer Unit Interface Description (cont)Connector PinDesignation Functional DescriptionRBP--3K RA Data Word 270 Bit 26 Discrete OutputSee RBP--1H.RBP--4AThruRBP--4FReserved Discrete Inputs (Standard Ground/Open)Reserved for future use.RBP--4G RA Display Test Inhibit Program PinThis program pin is used to determine if RA discrete monitoring will be inhibited duringself--test. If this pin is connected to program common (ground), RA discrete self--testmonitoring is inhibited. An open on this pin indicates RA discretes monitoring duringself--test.RBP--4H RA Data Word 270 Bit 27 Discrete OutputSee RBP--1H.RBP--4J RA Data Word 270 Bit 28 Discrete OutputSee RBP--1H.RBP--4K RA Data Word 270 Bit 29 Discrete OutputSee RBP--1H.RBP--5A Advisory Inhibit Discrete Input No. 1 (NO)Four ground/open type discrete inputs (Note 1) at RBP--5A, --5B, --5C, and --5D providethe capability for the T2CAS computer to defer all advisory (TA), aural alert and visualalert outputs until another, higher priority announcement or alert is completed. An open atall four of these discrete inputs indicates normal advisory/alert operation. These discreteinputs become active by connection to program common (ground) at RBP--7K. No newTA information can be placed on the RA or RA/TA busses during a period of AdvisoryInhibit. If an advisory condition, which occurred during a period of Advisory Inhibit,remains when the T2CAS computer returns to normal operation, it is annunciated. TheAdvisory Inhibit inputs and their effect on the advisory/alert priority system are as follows:Discrete No. Pin No. Mode Priority1 RBP--5A Forced Standby 12 RBP--5B Force TA Only (no voice/tone) 23 RBP--5C Force TA Only (no voice/tone) 24 RBP--5D Force TA Only (no voice/tone) 2Discrete No. 1 (RBP--5A) has priority over No. 2 (RBP--5B), No. 3 (RBP--5C) and No. 4(RBP--5D). Discrete No. 1 forces TCAS into STANDBY mode. Discretes No. 2, No. 3,and No. 4 force TCAS into TA mode with no voice or tone annunciations.See Note 1 for Ground/Open type discrete input definition.RBP--5B Advisory Inhibit Discrete Input No. 2 (NO)See RBP--5A.RBP--5C Advisory Inhibit Discrete Input No. 3 (NO)See RBP--5A.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--16Table 4--1. TT--950/951/952 T2CAS Computer Unit Interface Description (cont)Connector PinDesignation Functional DescriptionRBP--5D Advisory Inhibit Discrete Input No. 4 (NO)See RBP--5A.RBP--5E Increase Climb Inhibit Discrete Input No. 1 (NO)This input is a ground/open type discrete (Note 1) used to provide information to theT2CAS CU whether to assume that the aircraft cannot achieve a climb rate of 2500 feetper minute (FPM). The climb inhibit discrete inputs are designed in pairs (No. 1 and No.2atRBP--5F,or No. 3 at RBP--5G and No. 4 at RBP--5H) but can be wired as a singleinput or in conjunction with other aircraft operations to achieve airframe customization ofthe climb inhibit feature. The 2500 FPM climb inhibit function is assumed whenever No. 1and No. 2 are ground or No. 3 and No. 4 are ground.RBP--5F Increase Climb Inhibit Discrete Input No. 2 (NO)See RBP--5E.RBP--5G Increase Climb Inhibit Discrete Input No. 3 (NO)See RBP--5E.RBP--5H Increase Climb Inhibit Discrete Input No. 4 (NO)See RBP--5E.RBP--5J Climb Inhibit Discrete Input No. 3 (NO)See RMP--1J.RBP--5K Climb Inhibit Discrete Input No. 4 (NO)See RMP--1J.RBP--6A Airborne Data Loader Link A Discrete InputThis discrete input, along with Data Loader Discrete Inputs No. 2, 3, and 4 (pins RBP--6B,RBP--6C, and RBP--6D, respectively), is a ground/open type discrete that specifies whattype of data loader (ARINC 603 or ARINC 615) is attached. The T2CAS computer hasseparate receiver busses and separate data loader enable discrete inputs to supportsimultaneous connections to an ADL and PDL. A ground on pin RBP--6A indicates thatan airborne data loader is connected to the rear connector of the T2CAS computer. Aground on pin J1--18, PDL Link A Discrete Input, indicates that a portable data loader isconnected to the front connector of the T2CAS computer. The data loader discrete inputsat RBP--6B, RBP--6C, and RBP--6D are also connected to the data loader discrete inputson the front connector (pins J1--51, J1--52, and J1--53, respectively). Listed below is anactive discrete (selected) indicated by a ground and an inactive discrete (not selected)indicated by an open.J1--51/ J1--52/ J1--53/RBP--6A J1--18 RBP--6B RBP--6C RBP--6D FunctionGround Open Ground Open Open ARINC 615 ADLGround Open Open Ground Open ARINC 603 ADLOpen Ground Ground Open Open ARINC 615 PDLOpen Ground Open Ground Open ARINC 603 PDL-- -- -- -- -- -- -- -- Ground SW Part Number is output
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--17Table 4--1. TT--950/951/952 T2CAS Computer Unit Interface Description (cont)Connector PinDesignation Functional DescriptionRBP--6B Data Loader Discrete Input No. 2See RBP--6A.RBP--6C Data Loader Discrete Input No. 3See RBP--6A.RBP--6D Data Loader Discrete Input No. 4See RBP--6A.RBP--6E, 6F ARINC 429 CFDS Output: [RBP--6E (A), RBP--6F (B)]This differential pair output is a low speed ARINC 429 bus (12.5k bits/second nominal),that transmits data to an onboard maintenance computer or a central fault display system.RBP--6G, 6H ARINC 429 CFDS Input: [RBP--6G (A), RBP--6H (B)]This differential pair input is a low speed ARINC 429 bus (12.5k bits/second nominal), thatreceives data from an onboard maintenance computer or a central fault display system.RBP--6J Spare PinRBP--6K Spare PinRBP--7A Audio Level Program Pin No. 1 (NO)Two synthesized voice outputs with programmable output levels are provided by theT2CAS computer unit. The output at RMP--2F and --2G supply high level (up to 8 Watts)audio signals to an 8 Ohm speaker. The second output at RMP--3F and --3G supply lowlevel (up to 80 milliwatts) audio signals to a 600 Ohm audio distribution system. All auraltraffic and resolution advisories can be annunciated over these outputs unless cancelledby a Cancel Discrete (RMP--3D).Listed below are the audio level program pin configurations and the resulting outputlevels:Program PinRBP--7A RBP--7B RBP--7C Low Level Output High Level Output(MSB) (LSB) dBm mW dBm WOpen Open Open 16 40 6 4Open Open Ground 13 20 3 2Open Ground Open 10 10 0 1Open Ground Ground 7 5 --3 0.5Ground Open Open 4 2.5 --6 0.25Ground Open Ground 1 1.25 --9 0.125Ground Ground Open --2 0.625 --12 0.0625Ground Ground Ground 19 80 9 8RBP--7B Audio Level Program Pin No. 2 (NO)See RBP--7A.RBP--7C Audio Level Program Pin No. 3 (NO)See RBP--7A.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--18Table 4--1. TT--950/951/952 T2CAS Computer Unit Interface Description (cont)Connector PinDesignation Functional DescriptionRBP--7D Audio Tone Enable Program Pin (NO)If this programming pin is connected to program common, (RBP--7K), all voiceannouncements are delayed by one second and are preceded by a tone. If pin is leftopen, no delays or tones occur.RBP--7E Ground Display Mode Program Pin (NO)The T2CAS computer unit monitors this programming pin to select the TCAS grounddisplay mode while the aircraft is on the ground. If the aircraft is on the ground and thispin is connected to program common (RBP--7K), TCAS goes into standby mode. If thispin is left open and the aircraft is on the ground, TCAS displays traffic only. Aural andvoice annunciations are inhibited while the aircraft is on the ground.NOTE: TCAS does not display any traffic that it locates on the ground. TCAS aircrafthas WOW and intruder aircraft reports the same altitude or a lower altitude.RBP--7F Display All Traffic Program Pin (NO)The T2CAS computer unit monitors this program pin to select either the all traffic displaymode or the TA/RA only mode. If this pin is open, all traffic is displayed. If this pin isconnected to program common (RBP--7K), the TCAS displays only TA/RA type intruders.RBP--7G Cable Delay Signal Program Pin (NO)The cable delay program pins (RBP--7G, RBP--7H, and RBP--7J) convey to the T2CAScomputer unit the amount of delay differential between the top and bottom antennacables. Pin RBP--7G determines whether a time delay is added to the top or bottom. Ifthis pin is open, the time delay is added to the top. If this pin is ground (connected toprogram pin RBP--7K), the time delay is added to the bottom. The cable delay logic isgiven below. Program common for the cable delay program pins is RBP--7K.RBP--7H RBP--7J Differential(MSB) (LSB) Delay AdjustmentOpen Open 0--50 nsec No ChangeOpen Ground 51--150 nsec Add 100 nsec delayGround Open 151--250 nsec Add 200 nsec delayGround Ground 251--350 nsec Add 300 nsec delayRBP--7H Cable Delay MSB Program (NO)See RBP--7G.RBP--7J Cable Delay LSB Program Pin (NO)See RBP--7G.RBP--7K Program CommonThis is the ground source for use with program pins.RBP--8AThruRBP--8DReserved Program Pins
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--19Table 4--1. TT--950/951/952 T2CAS Computer Unit Interface Description (cont)Connector PinDesignation Functional DescriptionRBP--8E Self--Test Test Inhibit Program Pin (NO)This program pin determines if self--test will be inhibited while airborne. If grounded, thispin inhibits self--test while airborne. If open, self--test is enabled while airborne.RBP--8F TA/RA Display Symbol Maximum 16 Program Pin (NO)The T2CAS computer unit establishes the number of intruder symbols to be displayed onthe TA display through the program pins RBP--8F, --8G, --8H, --8J, and --8K. This numbercan vary between 0 and 31, depending on the programming that is a summation of theselected pins (--8F = 16, --8G = 8, --8H = 4, --8J = 2 and --8K = 1). Connecting one ofthese pins to program common (RBP--7K) indicates the associated pin is not selectedand that its value is not included in the summation. Leaving the pin open designates theassociated pin is selected and its value is included in the summation. The encodednumber is placed within the RTS data word (label 357) and sent to the display. Thedisplay should then limit the intruder symbols to this number.RBP--8G TA/RA Display Symbol Maximum 8 Program Pin (NO)See RBP--8F.RBP--8H TA/RA Display Symbol Maximum 4 Program Pin (NO)See RBP--8F.RBP--8J TA/RA Display Symbol Maximum 2 Program Pin (NO)See RBP--8F.RBP--8K TA/RA Display Symbol Maximum 1 Program Pin (NO)See RBP--8F.RBP--9AThruRBP--9JReserved Factory Test PinsLeave these pins unconnected for aircraft installations.RBP--9K Spare PinRBP--10AThruRBP--10GReserved Factory Test PinsLeave these pins unconnected for aircraft installations.RBP--10HThruRBP--10JSpare PinsRBP--10K Reserved Factory Test PinLeave this pin unconnected for aircraft installations.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--20Table 4--1. TT--950/951/952 T2CAS Computer Unit Interface Description (cont)Connector PinDesignation Functional DescriptionT2CAS Computer Unit Left Top Plug (LTP)LTP -- 1 Top Antenna 0 Degree PortJ1 on the antenna is color--coded yellow. This antenna port (Note 2) is called the 0degree port because it produces a transmission pattern in the forward quadrant of theaircraft. J1 is physically located toward the rear of the antenna and to the rear of theaircraft when antenna is properly installed. The T2CAS computer unit checks the built--indc to ground resistance of this antenna port. It must detect approximately 1000 Ohms orTCAS fails its antenna test.LTP -- 2 Top Antenna 270 Degree PortJ2 on the antenna is color--coded black. This antenna port (Note 2) is called the 270degree port because it produces a transmission pattern in the left wing quadrant of theaircraft. J2 is physically located toward the right wing of the aircraft when antenna isproperly installed. The TCAS function checks the built--in dc to ground resistance of thisantenna port. It must detect approximately 8000 Ohms or it reports antenna test failure.LTP -- 3 Top Antenna 180 Degree PortJ3 on the antenna is color--coded blue. This antenna port (Note 2) is called the 180degree port because it produces a transmission pattern in the rear quadrant of theaircraft. J3 is physically located toward the front of the antenna and to the front of theaircraft when antenna is installed properly. The T2CAS computer unit checks the built--indc to ground resistance of this antenna port. It must detect approximately 4000 Ohms orit reports antenna test failure.LTP -- 4 Top Antenna 90 Degree PortJ4 on the antenna is color--coded red. This antenna port (Note 2) is called the 90 degreeport because it produces a transmission pattern in the right wing quadrant of the aircraft.J4 is physically located toward the left wing of the aircraft when antenna is properlyinstalled. The TCAS function checks the built--in dc to ground resistance of this antennaport. It must detect approximately 2000 Ohms or it reports antenna test failure.T2CAS Computer Unit Left Middle Plug (LMP)LMP--1 Bottom Antenna 0 Degree PortJ1 on the antenna is color--coded yellow. Same as top antenna 0 degree port (LTP--1).In addition, this port (Note 2) is used as the omnidirectional antenna connection. TheTCAS function determines that a bottom omnidirectional antenna is installed if it detectsless than 500 Ohms (50 Ohms typical) to ground on this pin and an open circuit (>13kOhms) at LMP-- 2, --3, and --4 or a dc short (<500 Ohms) if unused ports are terminatedat back of mounting tray.LMP--2 Bottom Antenna 90 Degree PortJ2 on the antenna is color--coded black. This antenna port (Note 2) is called the 90degree port because it produces a transmission pattern in the right wing quadrant of theaircraft. J2 is physically located toward the left wing of the aircraft when antenna isproperly installed. The TCAS function checks the built in dc to ground resistance of thisantenna port. It must detect approximately 8000 Ohms or it reports antenna test failure.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--21Table 4--1. TT--950/951/952 T2CAS Computer Unit Interface Description (cont)Connector PinDesignation Functional DescriptionLMP--3 Bottom Antenna 180 Degree PortJ3 on the antenna is color--coded blue. Same as top antenna (Note 2) 180 degree port(LTP--3).LMP--4 Bottom Antenna 270 Degree PortJ4 on the antenna is color--coded red. This antenna port (Note 2) is called the 270degree port because it produces a transmission pattern in the left wing quadrant of theaircraft. J4 is physically located toward the right wing of the aircraft when properlyinstalled. The TCAS function checks the built in dc to ground resistance of this antennaport. It must detect approximately 2000 Ohms or it reports antenna test failure.T2CAS Computer Unit Left Bottom Plug (LBP)LBP--1 115 Vac Power Input (H)This pin along with the 115 Vac Power Input (C) line (pin LBP--7) provides the 115 Vacpower requirements for the TT--950/--952 T2CAS computer units.Wiring requirement is a standard #20 AWG.NOTE: The T2CAS computer unit operates with either 115 Vac, 400 Hz, or +28 Vdcinput power. If 115 Vac is used, the power should be connected through a5 Amp circuit breaker, and the pins for the +28 Vdc input should be leftunconnected.LBP--2 Spare PinLBP--3 +28 Vdc Power Return (LO)See LBP--10.LBP--4 Spare PinLBP--5 Fan 115 Vac Power Output (H)This pin along with the Fan 115 Vac Output Power (C) line (pin LBP--9) provides 115 Vacpower for an external fan.LBP--6 Spare PinLBP--7 115 Vac Power Input (C)See LBP--1.LBP--8 Signal GroundConnect to Aircraft Signal Ground.LBP--9 Fan 115 Vac Power Output (C)See LBP--5.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--22Table 4--1. TT--950/951/952 T2CAS Computer Unit Interface Description (cont)Connector PinDesignation Functional DescriptionLBP--10 +28 Vdc Power Input (HI)This pin along with the T2CAS computer unit +28 Vdc Power Return line (LBP--3) providethe +28 Vdc power requirements for the T2CAS computer unit.Wiring requirement is a standard #18 AWG.NOTE: The T2CAS TT--950/--952 computer operates with either 115 V ac, 400 Hz, or+28 Vdc input power and the TT--951 computer operates on +28 Vdc inputpower only. On the TT--950/--952 computers, if +28 Vdc is used, the powershould be connected through a 10 Amp circuit breaker, and the pins for the 115Vac input should be left unconnected.LBP--11 Chassis GroundConnect to aircraft frame. The T2CAS Chassis and signal ground pins should use thesame AWG as the power connections (See LBP--1 and LBP--10).LBP--12 Mutual Suppression Pulse Bus InputThe T2CAS computer unit joins the mutual suppression bus daisy chained through TCASand other RF transmitting equipment on board the aircraft. The TCAS function receivessuppression pulses from other LRUs on this bus, which is used to suppress the TCASreceivers during such transmissions. This prevents the TCAS function from interpretingthese transmissions as valid replies from an intruder aircraft. When not suppressed, theTCAS function transmits its own suppression pulses on the same bus in order tosuppress the receivers in other L--band systems on the aircraft. The L--Band suppressioncoax must be RG142, RG400, or equivalent coaxial cable which meets the operationalcharacteristics required by ARINC 735A.LBP--13 GPS Antenna Port (Active on TT--952 and reserved for TT--950 and TT--951)T2CAS unit TT--952 uses this pin for the GPS Antenna port -- RF input from the GPSantenna and +12 Vdc output to power the active amplifier GPS antenna.The minimum coax loss between the GPS antenna’s output and the T2CAS computer’sGPS input port is equal to the maximum preamplifier gain minus 29 dB. The maximumcoax loss between the GPS antenna’s output and the T2CAS computer’s GPS input portis equal to the minimum preamplifier gain minus 12.5 dB.The Interface descriptions that follow are for the 53--pin Data Loader connector J1 mounted on thefront panel of the T2CAS computer unit. These descriptions are used to make up the cable that isused to interface between the T2CAS computer unit and an ARINC 615 Portable Data Loader (PDL),a RS--232 PC Serial Port, a RS--422 Flight Data Recorder, or an ARINC 429 Maintenance Display.J1--1, 2 ARINC 429 PDL Bus Input: [J1--1 (A), J1--2 (B)]This differential pair input is a high--speed ARINC 429 bus (100k bits/second nominal)that is used to input data from the data loader to the TCAS computer unit. The standardsfor this interface are defined in ARINC 615 Airborne Computer High Speed Data Loader.These pins should be connected to pins 1 and 2 of the PDL cable interface.J1--3,J1--4Spare Pins
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--23Table 4--1. TT--950/951/952 T2CAS Computer Unit Interface Description (cont)Connector PinDesignation Functional DescriptionJ1--5 Output Bus ShieldsThe shields from the output bus (J1--8, 9) should be connected to this pin.J1--6,J1--7A615A Data Loader Ethernet Output [J1--6 (TD+), J1--7 (TD--)]TAWS Ethernet 10 Base--T.J1--8, 9 ARINC 429 Data Loader/PDL Recorder Bus Output: [J1--8 (A), J1--9 (B)]This differential pair output is a high--speed ARINC 429 bus (100K bits/second nominal)that is used to output data from the T2CAS computer unit to the data loader. Thestandards for this interface are defined in ARINC 615 Airborne Computer High SpeedData Loader.These pins should be connected to pins 8 and 9 of the PDL cable interface.J1--10, 11 RS--422 Recorder External Clock Input: [J1--10 (+), J1--11 (--)]These two pins provide external clocking from an RS--422 Flight Data Recorder forTCAS.J1--12, 13 RS--422 Recorder Reply Input: [J1--12 (+), J1--13 (--)]These two pins provide communication from a RS--422 Flight Data Recorder for TCAS.J1--14 RS--422 Recorder 125 kHz/ External Program PinThis pin is used to designate internal or external recorder clock operation for TCAS. Aground on this pin selects external recorder clock operation. An open selects 125k Hzinternal recorder clock operation.J1--15 RS--422 Recorder Disable Program PinThis program pin is used to enable or disable the RS--422 Data Recorder function forTCAS. The program pin is activated externally by the Flight Data Recorder. Logic is asfollows:Ground = RS--422 Recorder disabled; Open = RS--422 Recorder enabledJ1--16 Input Bus ShieldsThe shields from the input bus (J1--1, 2) should be connected to this pin.J1--17 Spare PinJ1--18 PDL Link A Discrete InputThis is a ground/open discrete (Note 1) from an portable ARINC 615 or ARINC 603 dataloader which indicates, to the T2CAS computer unit, that a data loader is connected. Aground indicates a data loader is connected. This pin is used by the TCAS, TAWS/RWSand GPS.J1--19 PDL Link B CommonConnect this pin to pin 19 of the PDL cable interface.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--24Table 4--1. TT--950/951/952 T2CAS Computer Unit Interface Description (cont)Connector PinDesignation Functional DescriptionJ1--20, 22 115 Vac Power Output: [J1--20 (H), J1--22 (C)]These power output pins provide the 115 Vac operating power for the data loader.The 115 Vac (H) and 115 Vac (C) interconnect wires should be shielded or twisted andshielded with an insulating jacket over the shield. The shield should be connected tochassis ground (J1--21).J1--21 Chassis GroundConnect 115 Vac power shields to this pin.J1--23 A615A Dataloader Ethernet Input (RD+)TAWS Ethernet 10--base--T read inputJ1--24ThruJ1--28Spare PinsJ1--29, 30 RS--422 Recorder Data Output: [J1--29 (+), J1--30 (--)]The RS--422 Flight Data Recorder data is output on these pins.J1--31, 32 RS--422 Recorder Clock Output: [J1--31 (+), J1--32 (--)]The RS--422 Flight Data Recorder internal 125k Hz internal clock is output on these pins.J1--33,34 ARINC 429 TA/RA Display No. 1 Output: [J1--33 (A), J1--34 (B)]This bus can be used to connect to a maintenance display. These pins are alsoconnected to the ARINC 600 connector on the rear of the unit (RMP--7C and --7D).J1--35,J1--36Spare PinsJ1--37, 38 28 V dc Power Output: [J1--37 (HI), J1--38 (LO)]These power output pins provide the +28 Vdc operating power for the data loader. Thesepins are used only if the data loader operates from a +28 Vdc source.J1--39 A615A Dataloader Ethernet Input (RD--)TAWS Ethernet 10--base--T read inputJ1--40 T2CAS RS--232 Data InputThis input is used by the TAWS, TCAS and GPS function to receive RS--232 data from aportable maintenance terminal.J1--41 T2CAS RS--232 Data OutputThis output is used by the TAWS, TCAS and GPS function to transmit RS--232 data to aportable maintenance terminal.J1--42 TCAS RS--232 Data InputThis input is used by the TCAS function to receive RS--232 data from a portablemaintenance terminal.J1--43 TCAS RS--232 Data OutputThis output is used by the TCAS function to transmit RS--232 data to a portablemaintenance terminal.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--25Table 4--1. TT--950/951/952 T2CAS Computer Unit Interface Description (cont)Connector PinDesignation Functional DescriptionJ1--44 GPS RS--232 Data InputThis input is used by the GPS function to receive RS--232 data from a portablemaintenance terminal.J1--45 GPS RS--232 Data OutputThis output is used by the GPS function to transmit RS--232 data to a portablemaintenance terminal.J1--46ThruJ1--47Spare PinsJ1--48,J1--49Logic CommonCommon lines for the RS--232 Data Input/Output lines. These two pins are tied togetherin the T2CAS computer unit.J1--50 Reserved PinJ1--51 Data Loader Link No. 2 Discrete InputPins J1--51 and J1--52 are ground/open discretes from a portable data loader, which areused to specify what type of data loader (ARINC 603 or ARINC 615) is connected to theT2CAS computer unit. These two pins are also connected to the ARINC 600 connectoron the rear of the unit (RBP--6B and --6C respectively).J1--52 Data Loader Link No. 3 Discrete InputSee J1--51.J1--53 Data Loader Link No. 4 Discrete InputThis is a ground/open discrete from a Portable Data Loader (PDL) that is used to transmitthe software part number on the Data Loader output bus when grounded, The landinggear indicates extended, and the air/ground indicates ground. This pin is also connectedto the ARINC 600 connector on the rear of the unit (RBP--6D).NOTE:1: Ground = Voltage of 0.0 Vdc to +3.5 Vdc or Resistance of less than 10 Ohmsapplied to input.Open = Voltage of +18.5 to +36 Vdc or Resistance greater than 100k Ohmsapplied to input.NOTE:2: The Antenna Coax shall be RG225 or equivalent coaxial cable that provides aloss of 2.5 db ±0.5 db or less between the T2CAS computer and each TCASAntenna port. For Directional Antenna Coaxes, each coax cable must be within0.5 db of the other coaxes (e.g. if one port has a 2 db loss, the other 3 ports cannot exceed 2.5 db loss).NOTE:3: Ground = Port capable of sinking at least 20 milli--Amps of current.Open = Voltage of +18.5 to +36 Vdc or Resistance greater than 100k Ohmsapplied to output.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--26Table 4--2. Gables Control Panel Interface DescriptionConnector PinDesignation Functional DescriptionJ1--1, 2 PANEL AND DISPLAY LIGHTING INPUT: (J1--1 HIGH, J1--2 LOW)5 Vac, 2.3 Amp maximum lighting input for front panel and display lighting. Lighting isprovided by incandescent lamps.J1/J2--3, 4 +28 Vdc INPUT POWER: (J1/J2--3 HIGH, J1/J2--4 LOW)The control panel is powered from a +28 Vdc power bus. Two identical but isolatedpower supplies provide the power requirements to each individual electronic module thatindependently control transponder 1 and 2. Maximum current is 2.5 Amps dc.J1/J2--5 ANTENNA TRANSFER DISCRETE OUTPUT: (J1/J2--5)This discrete output is used to provide the ability to switch a RF relay for dual transponderinstallations that have only one set of antennas. These outputs from J1 and J2 are linkedto the XPDR 1--2 switch. The output is OPEN(+12 to +35 Vdc) when the transponder isin standby (inactive) mode, and GROUND(< +3.5 Vdc) when the transponder is in anactive operational mode.J1/J2--6 DC GROUND INPUT: (J1/J2--6)Reference for all discrete inputs/outputs. Tied to aircraft dc ground.J1/J2--7 STANDBY/ON OUTPUT: (J1/J2--7)These discrete outputs (STANDBY/ON) will mimic the XPDR switch position placing onetransponder in Standby and the other in the ON (active) mode. Both transponders willnever be in the ON mode simultaneously. This output is GROUND(< +3.5 Vdc) when inStandby mode and OPEN(+12 to +35 Vdc) when in the ON mode. This output can sink100 mA maximum.Connect pin to transponder STANDBY / ON Discrete Input.J1/J2--8 CHASSIS GROUND INPUT: (J1/J2--8)Tied to airframe. Also used to connect ARINC 429 cable shields to the chassis.J1/J2--9 FUNCTIONAL TEST INPUT: (J1/J2--9)Functional test can also be initiated using this input discrete. When J1/J2--9 is grounded,a functional test similar to pushing the TEST button on the front panel is done.J1/J2--10 WARNING AND CAUTION OUTPUT: (J1/J2--10)This discrete output provides a low signal to a remote master warning system when thecontrol panel receives a Monitor Lamp fault indication from the active transponder.Otherwise it provides 7 to 30 Vdc or a resistance of >100k Ohms to ground. This outputcansink20mAmaximum.J1/J2--12 TRANSPONDER FAIL #2 INPUT: (J1/J2--12)The G7130--XX ATC/TCAS control panel transponder fail annunciator is controlled by thisinput. When the transponder is operating normally this input remains grounded.Otherwise, the transponder opens this input to indicate a transponder failure. The controlpanel turns the annunciator ON to alert the user of a transponder malfunction. Thetransponder fail annunciator turns on only when the failed transponder is selected by theXPDR 1--2 switch.Connect this pin to the transponder XPDR FAIL #2 Discrete Output.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--27Table 4--2. Gables Control Panel Interface Description (cont)Connector PinDesignation Functional DescriptionJ1/J2--13 IDENT INPUT: (J1/J2--13)The IDENT discrete input provides another means of activating the IDENT function. Thisinput allows the control panel to interface with an external IDENT switch located in theFlight Deck. When the input is grounded, the IDENT function is activated; otherwise itshould remain open.J1/J2--14 TRANSPONDER FAIL LOGIC DISCRETE INPUT: (TDR--94D ONLY) (J1/J2--14)This input allows the control panel to use +28 Vdc logic from a Collins TDR--94Dtransponder to control the transponder fail annunciator. This input should not be usedunless a Collins TDR--94D transponder is used with this control panel.J1/J2--15 AIR/GROUND SW DISCRETE OUTPUT: (J1/J2--15)This output is directly connected to the AIR/GND discrete input (J1/J2--24). This outputcan be routed directly to the transponder to disable it (Standby), and terminate ATC codereplies. J1 discrete logic operates independently from J2.J1/J2--16 AIR DATA SOURCE OUTPUT: (J1/J2--16)Ground/Open output that is dependent on the front panel ALT RPTG and XPDR switchpositions. This discrete output is enabled when altitude reporting is selected in the ONmode. When altitude reporting is selected OFF, the J1/J2--16 output remains in theOPEN state.This discrete output is connected to the transponder AIR DATA SOURCE SELECTDiscrete Input.J1/J2--18 MONITOR LAMP POWER INPUT: (J1/J2--18)These inputs are used as the input power source for the transponder fail annunciator onthe front panel of the control panel. The input supply voltage is a dimmable +28 Vdc at200 mA maximum.J1/J2--20 TRANSPONDER STRAPPING CONFIGURATION: (J1/J2--20)This discrete input programs the control panel to operate, and be able to properlyinterface to one of two types of transponder configurations. If this input is left OPEN thenthe control panel operates in accordance with ACSS transponder specifications. If theinput is GROUNDED, it is programmed to operate in accordance with Collins transponderspecifications.J1/J2--21 LAMP TEST INPUT: (J1/J2--21)To initiate a lamp test, J1 or J2 pin 21 must be grounded through an external switch. Allsegments and annunciators in the control panel LCD (except RPLY and decimal points)are ON for as long as this input is grounded. ARINC 429 labels are not affected by theactivation of a lamp test mode.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--28Table 4--2. Gables Control Panel Interface Description (cont)Connector PinDesignation Functional DescriptionJ1/J2--22, 23 ARINC 429 OUTPUTS: (J1/J2--22,23)Communication between the control panel and the transponder is done over a two wirelow speed, odd parity, ARINC 429 compatible bus. Selected ATC code, operating mode,and system parameters are communicated to the transponder over these lines.Transmission of labels 013, 015, 016, and 031 is done every 150 milliseconds.Connect these pins to one of the two transponder ARINC 429 CONTROL DATA InputPorts.J1/J2--24 AIR/GROUND INPUT DISCRETE: (J1/J2--24)The control panel accepts input from two independent Air/Ground (WOW) switches forapplications that require automatic disabling of the transponder upon landing. This inputis wired directly to the AIR/GROUND SW Discrete Output (J1/J2--15).
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--29Table 4--3. 41--Pin VSI/TRA Interface DescriptionConnector PinDesignation Functional DescriptionJ1--1 VERTICAL SPEED +DC REFERENCE INPUT:Pins 1, 2, and 3 are inputs to the VSI/TRA from an ARINC 575 air data computerindicating vertical speed. Pin 1 is a +12 Vdc regulated reference voltage from the ADC.Pin 3 is a --12 Vdc regulated reference voltage from the ADC. Pin 2 receives a +10 to--10 Vdc rate signal from the ADC. Also see pins 31, 32, and 33.J1--2 VERTICAL SPEED DC RATE INPUT:See pin 1.J1--3 VERTICAL SPEED --DC REFERENCE INPUT:See pin 1.J1--4, 6 ARINC 565 VERTICAL SPEED AC INPUT: (J1--4 HIGH, J1--6 LOW)Pins 4, 5, 6, and 16 are inputs to the VSI/TRA from an ARINC 565 air data computer orIRS. A 26 Vac, 400 Hz reference signal is received on pin 5, (HI) and pin 16, (LO). Pin 4,(HI) and pin 6, (LO) provides an amplitude modulated 400 Hz signal with a maximumvoltage of 6.25 volts. The RMS value of this signal is used by the VSI/TRA to computeand display the vertical rate. The phase of this signal is compared with the referencesignal to determine if the rate is positive or negative. An in--phase signal equals apositive rate, an out--of-- phase signal indicates a negative rate. Also see pins 8 and 31.J1--5 VERTICAL SPEED 26 Vac, 400 Hz REFERENCE INPUT (HI):See pins 4 and 16.J1--8 VERTICAL SPEED VALID DISCRETE INPUT:The VSI/TRA receives a +28 Vdc signal from an ARINC 575 or 565 air data computerindicating its valid operation. An “open” at this pin indicates an invalid vertical speedsignal from the ADC. This pin is only used when pins (1, 2, 3) or (4, 5, 6, and 16) areused. Also see pins 1 and 4.J1--9, 10 5 VOLT LAMP DIMMING INPUT: (J1--9 C, J1--10 H)The VSI/TRA monitors the Flight Deck lamp voltage bus at pins 9 and 10. This voltagemay be either ac or dc. The back lighting in the VSI/TRA is adjusted by and tracks thisvoltage from 0.5 Volts to 5 Volts. If this input falls below 0.5 Volts or is absent, theVSI/TRA sets itself to a nominal level to prevent the display from going dark due to lossor failure of the lamp dimming bus.J1--11 ARINC 429 (B) TCAS TA/RA DATA BUS INPUT:Paired with pin 26. These pins connect to a T2CAS computer unit.J1--12 ARINC 429 (B) VERTICAL SPEED NO. 1 INPUT BUS:Paired with pin 27. These pins connect to Digital ADC No. 1 or IRS No 1.J1--14 ARINC 429 (B) VERTICAL SPEED NO. 2 INPUT:Paired with pin 30. These pins connect to Digital ADC No. 2 or IRS No. 2.J1--15 CONFIGURATION STRAP COMMON INPUT:This pin is the return line for the configuration strapping pins J1--17, and J1--32 thru 35.J1--16 VERTICAL SPEED 26 Vac, 400 Hz REFERENCE INPUT (C):See pins 4 and 5.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--30Table 4--3. 41--Pin VSI/TRA Interface Description (cont)Connector PinDesignation Functional DescriptionJ1--17 CONFIGURATION STRAP #3 INPUT (NO):Pin 17 is used in conjunction with pin 35 to select the indicator operating mode as follows:The following applies: O = Open, G = Ground.Pin 35 17 Indicator Operating ModeG G Test (shop level)G O VSI onlyO G RA VSI onlyO O TA/RA VSIJ1--18 SECONDARY VERT SPEED VALIDITY INPUT (+28 Vdc):The VSI/TRA receives a +28 Vdc signal from an ARINC 575 or 565 air data computerindicating its valid operation. An “open” at this pin indicates an invalid vertical speedsignal from the ADC. This pin is only used when pins (1, 2, 3) or (4, 5, 6, and 16) areused.J1--19, 20 VERT SPEED BOOTSTRAP AC OUT: (J1--19 [HIGH], J1--20 [LO])This output repeats the ARINC 565 input signals (26 V 400 Hz reference and signal)available on the primary input when this input has been selected :-- 26 V 400 Hz referenceThe voltage available on the output (26 Vac Bootstrap ref. output) is the same as thatavailable on the 26 Vac 400 Hz reference (hot) of the ARINC 565 primary input, thecommon reference being the cold of the 26 Vac primary ref. input.-- Output signal (vertical speed bootstrap AC output) available on two wires (HI and LO).J1--22 CHASSIS GROUND INPUT:Connected to aircraft frame. Also used to connect ARINC cable shields to the chassis.J1--23 115 Vac, 400 HZ POWER INPUT (COMMON):See pin 40. Connect to aircraft AC ground.J1--24, 25 REMOTE LIGHT SENSOR INPUT: (J1--24 LOW, J1--25 HIGH)This input at pins 24 and 25 provides a means of controlling the VSI/TRA back lighting viaa remote light sensor already present in some aircraft (Douglas and Boeing). TheVSI/TRA has its own built--in sensor and therefore a remote light sensor need not beused in all installations. Program the VSI/TRA for a remote light sensor, as describedunder pin 34.J1--26 ARINC 429 (A) TCAS TA/RA DATA INPUT:Traffic and Resolution Advisory data is supplied to the VSI/TRA from the T2CAScomputer unit via this high speed ARINC 429 data bus. Paired with pin 11.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--31Table 4--3. 41--Pin VSI/TRA Interface Description (cont)Connector PinDesignation Functional DescriptionJ1--27 ARINC 429 (A) VERTICAL SPEED NO. 1 INPUT:This is the primary ARINC 429 input bus to the VSI/TRA. This pin accepts high or lowspeed ARINC 429 vertical speed data (Label 212). Its use is determined by the sourceselect discrete and configuration straps CS0 and CS1 (pins 31, 32, and 33 respectively).Paired with pin 12.J1--28 CONFIGURATION STRAP #2 INPUT (NO):This is the V/S response time selection. A time constant of 3.8 sec with pin 28 open andof 7.6 sec with pin 28 grounded.J1--29 TA/RA VALID DISCRETE OUTPUT (NO):This output discrete indicates the ability of the VSI/TRA to perform as a resolutionadvisory and/or a traffic advisory display. If the VSI/TRA fails, this discrete presents anopen. Normal operation causes a ground. This discrete is monitored by the T2CAScomputer unit.J1--30 ARINC 429 (A) VERTICAL SPEED NO. 2 INPUT:This is the secondary ARINC 429 input bus to the VSI/TRA. This pin accepts high or lowspeed ARINC 429 vertical speed data (Label 212). Its use is determined by the sourceselect discrete and configuration straps CS0 and CS1 (pins 31, 32 and 33 respectively).Paired with pin 14.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--32Table 4--3. 41--Pin VSI/TRA Interface Description (cont)Connector PinDesignation Functional DescriptionJ1--31 SOURCE SELECT DISCRETE INPUT (NO):This discrete input is used in conjunction with configuration straps CS0, CS1 and CS2 toprogram the VSI/TRA to accept and use the vertical speed data being supplied. In someinstallations, this discrete is connected to a switch in the Flight Deck and is used to selectbetween primary and secondary ARINC 429 vertical speed inputs. It is hard wired toconfiguration strap common if ac or dc analog vertical speed inputs are used. Cyclepower to update to the new configuration.The following applies: O = Open, G = Ground.CS0 CS1 CS2Pin SS 32 33 34 DefinitionX G G G ARINC 429 LS (label 212)X O G G ARINC 565 analog ACG G O G ARINC 575 analog DCO G O G PNEUMATICX O O G ARINC 429 HS (label 365)X G G O ARINC 429 LS (Port # 3)X O G O Reserved (ARNICA 575 dig)X G O O User definedG O O O User definedO O O O ”Traffic display only” modeNote: SS is Source Select Pins 31 or 37.In those configurations where digital or analog primary or secondary inputs can beselected, the two source select pins, 31 and 37, are used to select one or other of theseinputs.•pin 31 for the logic OPEN (primary)/GROUND (secondary)•pin 37 for the logic OPEN (primary)/+28 Vdc (secondary) in relation to the dc commonreference pin.Pin 31 37 Input SelectedOO PrimaryG O SecondaryO 28V SecondaryG 28V Not UsedJ1--32 CONFIGURATION STRAP #0 INPUT (NO):See pin 31.J1--33 CONFIGURATION STRAP #1 INPUT (NO):See pin 31.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--33Table 4--3. 41--Pin VSI/TRA Interface Description (cont)Connector PinDesignation Functional DescriptionJ1--34 CONFIGURATION STRAP #2 INPUT (NO):See pin 31.J1--35 CONFIGURATION STRAP #4 INPUT (NO):See pin 17.J1--36 SECONDARY ANALOG AC INPUT (LO):ARINC 565 ADCJ1--37 SECONDARY SOURCE SELECT DISCRETE INPUT (NO):See pin 31.J1--38 VERTICAL SPEED VALID DISCRETE OUTPUT (NO):This validity discrete is representative of the operation of the vertical speed channel.The state of this discrete corresponds to an invalid state (OPEN) if :· the indicator is not energized· the indicator is in the initialization phase on power up· the vertical speed failure warning flag is in view (case of internal or external failures)· the self test/display test pin is activated.Definition of the OPEN state : impedance in relation to the dc common greater than 100kOhms (open collector with an applicable voltage of +14 Vdc to +32 Vdc).A valid state is indicated by either:1) a GROUND state characterized by a voltage of less than 3.5 Vdc in relation to dccommons with a maximum current of 20 mA, when the following types of verticalspeed are selected :-- pneumatic input-- digital inputs (per ARINC 429 HS or LS and digital ARINC 575).or2) a dc output voltage (+ 28 Vdc nominal), the minimum value of which is equal to VIN --(2 + 200 x I), where VIN is the greater of the primary vertical speed and secondaryvertical speed voltages available and I the output current expressed in amps (0.02 Amax.). This type of signal is present on the output when the following types of verticalspeed are selected :-- AC analogue input (ARINC 565)-- DC analogue input (ARINC 575).J1--39 DC GROUND INPUT:To be connected to aircraft dc Ground.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--34Table 4--3. 41--Pin VSI/TRA Interface Description (cont)Connector PinDesignation Functional DescriptionJ1--40 115 Vac, 400 Hz POWER INPUT (HI):This pin, along with its return line (pin 23) supplies power to the VSI/TRA. Connect powerthrougha1Ampcircuitbreaker.J1--41 SELF--TEST/DISPLAY TEST:This input functions on an OPEN/GROUND logic (in relation to dc common) and inparallel with the TEST Push button located on the front face of the indicator (formaintenance purposes only).When this input is activated and maintained in the GROUND state, the indicator performsa self test procedure which results in:-- The display of a representative test pattern within 3 seconds.-- The transmission of an OPEN (invalid) state on the TCAS Display Status DiscreteOutput for the duration of the test.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--35Table 4--4. XS--950 Data Link Transponder Interface DescriptionConnector PinDesignation Functional DescriptionP1A--1A THRUP1A--1K, ANDP1A--2KENCODING ALTIMETER #2 INPUTS:These Mode C pulse discrete inputs allow for altitude inputs from an encoding altimeterthat contains a discrete 11 wire interface. The standards for this interface are defined inARINC Characteristic 572, “Air Traffic Control Transponder”. The inputs use ground/openlogic levels.NOTE: Two encoding altimeters are required if the transponder is used with TCAS.P1A--2A, 2B ARINC 429 ADLP TO COMM A/B BUS INPUT: [P1A--2A (A), P1A--2B (B)]Four high speed ARINC 429 busses (100k bits/second nominal) are provided forinterfacing to a Mode S Airborne Data Link Processor (ADLP). The COMM A/B input andoutput busses are used for the transfer of standard length messages to and from theADLP. The COMM C/D input and output busses are used for the transfer of extendedlength messages (ELM) to and from the ADLP. The standard for this interface is definedin ARINC Characteristic 718, “Air Control Transponder (ATCRBS/Mode S)”.P1A--2C, 2D ARINC 429 ADLP TO COMM C/D BUS INPUT: [P1A--2C (A), P1A--2D (B)]See pins P1A--2A, 2BP1A--2E, 2F ARINC 429 COMM C/D TO ADLP BUS OUTPUT: [P1A--2E (A), P1A--2F (B)]See pins P1A--2A, 2BP1A--3B XPDR FAIL DISCRETE OUTPUT #2:This discrete output is set to annunciate an internal transponder failure or the Mode Saddress is illegal (All 0’s or 1’s). A ground logic threshold (<+3.0 Vdc) is output when thetransponder is operating normally, and an open logic threshold (resistance >100k Ohmsto unit ground) when a failure has occurred. The output is capable of sinking 200 mA ofcurrent. Connect this pin to the Control Panel XPDR FAIL #2 input.P1A--3C,P1A--3D,P1A--3E,P1A--3FCABLE DELAY PROGRAM INPUTS:The Cable Delay Program Inputs are used to compensate for the difference inpropagation delays in the transponder due to antenna transmission line length differencesbetween the top and bottom antennas. The inputs use ground/open logic levels. TheCable Delay Program Common (pin P1A--3F) can be used to supply a ground.Program Pin Differential TransponderP1A--3C P1A--3D P1A--3E Delay AdjustmentOpen Open Open 0--50 nsec No ChangeOpen Open Ground 51--150 nsec Add Delay to Top ChannelOpen Ground Open 151--250 nsec Add Delay to Top ChannelOpen Ground Ground 251--350 nsec Add Delay to Top ChannelGround Open Open 0--50 nsec No ChangeGround Open Ground 51--150 nsec Add Delay to Bottom ChannelGround Ground Open 151--250 nsec Add Delay to Bottom ChannelGround Ground Ground 251--350 nsec Add Delay to Bottom ChannelThe differential delay column is the difference in the round trip cable delay between thetop and bottom antenna cables. The differential delay can be calculated as follows:[Top length in feet -- Bottom length in feet] X [Characteristic Delay (nsec/foot)] X 2.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--36Table 4--4. XS--950 Data Link Transponder Interface Description (cont)Connector PinDesignation Functional DescriptionP1A--3G,P1A--3H,P1A--3JSDI PROGRAM INPUTS:The SDI program inputs are used to identify the system number in the installation. Theinputs use ground/open logic levels. The SDI Common (pin P1A--3J) can be used tosupply a ground.Program PinP1A--3G P1A--3H DefinitionOpen Open Not Applicable (SDI = 00)Open Ground LRU System #1 (SDI = 01)Ground Open LRU System #2 (SDI = 10)Ground Ground LRU System #3 (SDI = 11)P1A--4ATHRUP1A--4JARINC 565 ANALOG AIR DATA COMPUTER #1 INPUTS:These input pins allow for altitude information from an Analog Synchro Altitude Interfaceto be connected to the transponder. The standards for this interface are defined inARINC 565, “Subsonic Air Data System”.P1A--5A,P1A--5B,P1A--5C,P1A--5DMAXIMUM TRUE AIRSPEED PROGRAM INPUTS:The Maximum True Airspeed inputs are used for strapping the maximum cruise airspeedcapability of the aircraft. The inputs use ground/open logic levels. The Max TrueAirspeed Common (pin P1A--5D) can be used to supply a ground.Program PinP1A--5A P1A--5B P1A--5C DefinitionOpen Open Open No Maximum Airspeed AvailableGround Open Open Maximum Airspeed ≤75 KnotsOpen Ground Open Maximum Airspeed >75 and ≤150 KnotsGround Ground Open Maximum Airspeed >150 and ≤300 KnotsOpen Open Ground Maximum Airspeed >300 and ≤600 KnotsGround Open Ground Maximum Airspeed >600 and ≤1200 KnotsOpen Ground Ground Maximum Airspeed >1200 KnotsGround Ground Ground Not AssignedP1A--5E, 5F ARINC 429 TX COORDINATION BUS INPUT: (P1A--5E [A], P1A--5F [B])Two high speed ARINC 429 busses (100k bits/second nominal) are provided to interfacebetween the transponder and a TCAS computer unit. The standards for this interface aredefined in ARINC Characteristic 735A, “Traffic Alert and Collision Avoidance System”.P1A--5G, 5H ARINC 429 XT COORDINATION BUS OUTPUT: (P1A--5G [A], P1A--5H [B])See pins P1A--5E, 5F.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--37Table 4--4. XS--950 Data Link Transponder Interface Description (cont)Connector PinDesignation Functional DescriptionP1A--5J AIR / GROUND #2 DISCRETE INPUT:This pin and AIR / GROUND #1 Discrete Input (pin P1A--5K) provide a method for thetransponder to automatically determine the Air/Ground status of the aircraft. The status isused in replies to Mode S interrogations and to inhibit replies to certain types ofinterrogations. Both inputs use ground/open logic, where a Ground specifies an “On theGround” condition and an Open specifies an “In the Air” condition.When this pin is connected to the Air/Ground Relay (Squat Switch), the transponder willnot reply to ATCRBS, ATCRBS/Mode S All Call, or Mode S All Call when the input is setfor “On the Ground”. This input should be connected to the Air/Ground Relay for normaloperation.P1A--5K AIR / GROUND #1 DISCRETE INPUT:See pin P1A--5J.When this pin is connected to the Air/Ground Relay (Squat Switch), the transponderreplies to all types of interrogations irregardless of the state of the input. This input allowsthe transponder to reply during a ramp test.P1A--6A, 6B ARINC 429 FLIGHT IDENTIFICATION BUS INPUT: (P1A--6A [A], P1A--6B [B])This differential pair input is a low speed ARINC 429 bus (12.5k bits/second nominal) thataccepts a flight identification that is contained within four ARINC 429 data words (labels233, 234, 235 and 236).P1A--6C, 6D ARINC 615 AIRBORNE DATA LOADER BUS INPUT: (P1A--6C [A], P1A--6D [B])The Airborne Data Loader interface consists of two high speed ARINC 429 busses (100kbits/second nominal) and a ground/open logic discrete (pin P1A--6G). The interfaceallows for operational transponder software to be loaded into the unit through an onboarddata loader. The standards for this interface are defined in ARINC 615 “AirborneComputer High Speed Data Loader”.P1A--6E, 6F ARINC 615 AIRBORNE DATA LOADER BUS OUTPUT: (P1A--6E [A], P1A--6F [B])See pins P1A--6C, 6DP1A--6G ADL INPUT LINK A DISCRETE INPUT:See pins P1A--6C, 6DP1A--6H, 6J ARINC 575 AIR DATA COMPUTER #1 INPUT: (P1A--6H [A], P1A--6J [B])This differential pair input is a low speed ARINC 575 bus (12.5k bits/second nominal) thatcan be used to input altitude information from an ARINC 575 Air Data System. Thestandards for this interface are defined in ARINC Characteristic 575, “Subsonic Air DataSystem (Digital) DADS”.P1A--6K SINGLE / DUAL ANTENNA PROGRAM INPUT:This pin allows for installation of the transponder in a system with a single bottommounted antenna or dual top and bottom mounted antennas. The input usesground/open logic as follows:Ground = Single Bottom Mounted Antenna ConfigurationOpen = Diversity Antenna Configuration
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--38Table 4--4. XS--950 Data Link Transponder Interface Description (cont)Connector PinDesignation Functional DescriptionP1A--7A, 7B ARINC 429 CONTROL DATA PORT A BUS INPUT: (P1A--7A [A], P1A--7B [B])The control panel data can be input into the transponder on either of two low speedARINC 429 busses. (Ports A and B). The control data is contained in labels 013, 015,and 016. The port is selected by the CONTROL DATA PORT SELECT Discrete Input(pin PIA--7D).P1A--7D CONTROL DATA PORT SELECT INPUT:See pins P1A--7A, 7B.This discrete input is used to select which port is used to input control data to thetransponder. This input uses a ground/open logic as follows:Ground Specifies Port AOpen Specifies Port BP1A--7E, 7F ARINC 429 CONTROL DATA PORT B BUS INPUT: (P1A--7E [A], P1A--7F [B])See pins P1A--7A, 7B.P1A--7G STANDBY / ON DISCRETE INPUT:This discrete input is connected to the Control Panel STANDBY/ON output. The inputselects the active or standby status of the transponder. A ground causes the transponderto be in standby, and an open causes the transponder to be active.P1A--7H, 7J ARINC 429 ADC #1 BUS INPUT: (P1A--7H [A], P1A--7J [B])The altitude information for the transponder can be obtained from an ARINC 706 Air DataSystem through two low speed ARINC 429 data busses. The standards for this interfaceare defined in ARINC Characteristic 706, “Mark 5 Subsonic Air Data System”.This differential pair input is a low speed ARINC 429 bus that inputs uncorrected pressurealtitude (ARINC label 203) from an altitude source. Also see pins P1B--5A, 5B.P1A--71 TOP ANTENNA RF INPUT:RF input from top antenna.P1B--1ATHRUP1B--3EMODE S ADDRESS INPUTS:The Mode S Address is a unique 24--bit code assigned to each aircraft. Pins P1B--1Athru P1B--3E are used to program this 24--bit binary number. The inputs must be setaccording to this binary number representation. Each binary 1represents a Grounded pinand each binary 0represents an Open pin. Pin P1B--1A represents the most significantbit (MSB) of the binary number and pin P1B--3D represents the least significant bit (LSB)of the binary number.NOTE: An address of all 0’s or all 1’s is an illegal address, and can cause the aircraft tobe invisible to TCAS II equipped aircraft in flight. Never use an illegal addressfor an installed system.P1B--3H FUNCTIONAL TEST DISCRETE INPUT:This discrete input is used to put the transponder in a functional test mode. Thefunctional test that is performed by the transponder is equivalent to a test that is initiatedfrom the control panel. The input uses ground/open logic as follows:Ground = Initiate Functional TestOpen = Normal Operation
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--39Table 4--4. XS--950 Data Link Transponder Interface Description (cont)Connector PinDesignation Functional DescriptionP1B--3J ALTITUDE COMPARISON FAIL DISCRETE OUTPUT:This discrete output annunciates a comparison failure in the altitude data for thetransponder if Gillham altitude data is selected. The output annunciates a failure if thetwo altitude sources are not within 500 feet.The output drives a ground logic threshold (voltage of less than +3.0 Vdc) when thealtitude is valid, and an open logic threshold (resistance is greater than 100k Ohms to unitground) when a failure has occurred. The output is capable of sinking 200 mA of current.P1B--3K XPDR FAIL DISCRETE OUTPUT #1:This discrete output is set to annunciate an internal transponder failure or that the Mode Saddress is illegal (All 0’s or 1’s). The output will source a voltage of greater than +5.0 Vdcat 100 mA of current when a failure has occurred, and an open circuit (resistance ofgreater than 100k Ohms to unit ground) when the transponder is operating normally. Theoutput contains diode isolation. Connect this pin to the Control Panel XPDR FAIL #1input.P1B--4A THRUP1B--4K, ANDP1B--5KENCODING ALTIMETER #1 INPUTS:First of two Encoding Altimeter interfaces. See pins P1A--1A thru 4K and P1A--2K.P1B--5A, 5B ARINC 429 AIR DATA COMPUTER #2 BUS INPUT: (P1B--5A [A], P1B--5B [B])Second ARINC 429 Air Data Computer bus input. See pins P1A--7H, 7J.P1B--5C, 5D ARINC 575 AIR DATA COMPUTER #2 BUS INPUT: (P1B--5C [A], P1B--5D [B])Second ARINC 575 Air Data Computer bus input. See pins P1A--6H, 6J.P1B--5E, 5F ARINC 429 COMM A/B TO ADLP BUS OUTPUT: (P1B--5E [A], P1B--5F [B])See pins P1A--2A, 2B.P1B--5G ALTITUDE COMPARISON ON / OFF DISCRETE INPUT:This discrete input is used to enable/disable the Altitude Comparison function. TheAltitude Comparison function is used only if a Gillham altitude source is selected. This pinuses a ground/open logic as follows:Ground = Altitude Comparison EnabledOpen = Altitude Comparison DisabledNOTE: If an altitude source other than Gillham is selected, the input has no function.P1B--5H MODE S DATA LINK PROGRAM INPUT:This program input specifies if the transponder is connected to an Airborne Data LinkProcessor (ADLP) Unit. The input uses ground/open logic as follows:Ground = ADLP is InstalledOpen = ADLP is not installedP1B--5J ANTENNA BITE PROGRAM INPUT:This program input specifies if the transponder is to perform a built--in test to the antennasubsystem. The transponder performs a continuity check of the antenna to make sure itis not an open circuit. The input uses ground/open logic as follows:Ground = Enables Antenna Subsystem TestOpen = Disables Antenna Subsystem Test
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--40Table 4--4. XS--950 Data Link Transponder Interface Description (cont)Connector PinDesignation Functional DescriptionP1B--6A, 6B ARINC 429 MAINTENANCE DATA BUS INPUT: (P1B--6A [A], P1B--6B [B])Two low speed ARINC 429 busses (12.5k bits/second nominal) are provided to interfacebetween the transponder and an onboard maintenance system. The maintenancecomputer interface is designed to work with all airframe models and types.P1B--6C, 6D ARINC 429 MAINTENANCE DATA BUS OUTPUT: (P1B--6C [A], P1B--6D [B])See pins P1B--6A, 6B.P1B--6E AIR DATA SOURCE SOURCE SELECT DISCRETE INPUT:The transponder contains dual inputs for all types of altitude sources. This discrete inputspecifies which of the two inputs are used to obtain altitude information.Ground = Altitude Source No. 2Open = Altitude Source No. 1P1B--6F,P1B--6G,P1B--6HALTITUDE TYPE SELECT PROGRAM INPUT:The Altitude Type Select program pins are used to configure the transponder for the typeof altitude source that is connected to it. The inputs use ground/open logic. The AltitudeType Select Common (pin P1B--6H) can be used to supply a ground.Program PinP1B--6F P1B--6G DefinitionGround Ground Selects Gillham Altitude SourceGround Open Selects ARINC 575 Altitude SourceOpen Ground Selects ARINC 407 Synchro Altitude SourceOpen Open Selects ARINC 429 Altitude SourceP1B--7ATHRUP1B--7JARINC 565 ANALOG AC AIR DATA COMPUTER #2 INPUTS:Second ARINC 565 Analog AC Air Data Computer Input. See pins P1A--4A Thru 4J.P1B--71 BOTTOM ANTENNA RF INPUT:RF input from bottom antenna.P1C--1 XPDR 115 Vac INPUT POWER: (H)This pin along with the XPDR 115 Vac RETURN line (pin P1C--7) provides the 115 Vacpower requirements for the transponder.NOTE: Only --10XXX thru --54XXX transponders accept 115 Vac, 400 Hz input power.If the 115 Vac version is used, the power should be connected througha5ampcircuit breaker, and the pins for the 28 Vdc input (P1C--10 and P1C--3) shouldbe left unconnected.P1C--3 XPDR +28 Vdc RETURN: (L)See pin P1C--10.P1C--4 XPDR OFF (NO) INPUT:This discrete input is used to turn the transponder power supply OFF. It should not beconnected in aircraft installations.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--41Table 4--4. XS--950 Data Link Transponder Interface Description (cont)Connector PinDesignation Functional DescriptionP1C--6 FAN +28 Vdc OUTPUT: (+)The 28 Vdc version of the transponder can control an externally mounted +28 Vdc fan toprovide cooling air for the transponder. The Fan +28 Vdc output (P1C--6) should beconnected to the positive input of the fan, and the Fan Return (NO) Output (P1C--9)should be connected to the negative input of the fan. The output has the capability todrive a fan that draws up to 200 mA of current. The fan is turned on when the internaltransponder temperature rises above 30 degrees centigrade. In the 115 Vac version ofthe transponder, the outputs are not used.P1C--7 XPDR 115 Vac RETURN: (C)See pin P1C--1.P1C--8 SIGNAL GROUND INPUT:Connect to Aircraft Signal Ground.P1C--9 FAN RETURN (NO): (--)See pin P1C--6.P1C--10 XPDR +28 Vdc INPUT POWER: (H)This pin along with the +28 Vdc RETURN line (P1C--3) provide the 28 Vdc powerrequirements for the transponder.NOTE: Only --55XXX thru --99XXX transponders accept +28 Vdc input power. If the+28 Vdc version is used, the power should be connected through an 8 ampcircuit breaker, and the pins for the 115 Vac input (P1C--1 and P1C--7) shouldbe left unconnected.P1C--11 CHASSIS GROUND INPUT:Connect to aircraft frame.P1C--12,P1C--13MUTUAL SUPPRESSION BUS INPUT/OUTPUT:L--Band suppression coax must be RG--142 or equivalent coaxial cable. P1C--12 andP1C--13 are connected internally. Connection to only one pin is required.The Interface descriptions that follow are for the 53--pin ARINC 615 Portable Data Loader connectorJ1 mounted on the front panel of the transponder. These descriptions are used to make up thecable that is used to interface between the transponder and the ARINC 615 Data Loader or aRS--232 PC Serial Port.J1--1, 2 XPDR ARINC 429 PDL BUS INPUT: (J1--1 [A], J1--2 [B])This differential pair input is a high speed ARINC 429 bus (100k bits/second nominal) isused to input data from the data loader to the transponder. The standards for thisinterface are defined in ARINC 615 “Airborne Computer High Speed Data Loader”.These pins should be connected to pins 1 and 2 of the PDL cable interface.J1--5 INPUT BUS SHIELD:The shields from the input bus (J1--1, 2) should be connected to this pin.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--42Table 4--4. XS--950 Data Link Transponder Interface Description (cont)Connector PinDesignation Functional DescriptionJ1--8, 9 XPDR ARINC 429 PDL BUS OUTPUT: (J1--8 [A], J1--9 [B])This differential pair output is a high speed ARINC 429 bus (100k bits/second nominal)used to output data from the transponder to the data loader. The standards for thisinterface are defined in ARINC 615 “Airborne Computer High Speed Data Loader”.These pins should be connected to pins 8 and 9 of the PDL cable interface.J1--16 OUTPUT BUS SHIELD:The shields from the output bus (J1--8, 9) should be connected to this pin.J1--18 PDL LINK A:Connect this pin to pin 18 of the PDL cable interface.J1--19 PDL LINK B:Connect this pin to pin 19 of the PDL cable interface.J1--20, 22 115VacPOWEROUTPUT: (J1--20[H],J1--22[C])These power output pins provide the 115 Vac operating power for the data loader.NOTE: Only the 115 Vac version transponders provide this output. If a +28 Vdc versiontransponder is installed, either the data loader must be able to operate from +28Vdc or the data loader 115 Vac input power must be connected to a sourceexternal to the transponder.The 115 Vac (H) and 115 Vac (C) should be shielded or twisted and shielded with aninsulating jacket over the shield. The shield should be connected to chassis ground (pin21).J1--21 CHASSIS GROUND:Connect 115 Vac power shields to this pin.J1--37, 38 +28 Vdc POWER OUTPUT: (J1--37 [HI], J1--38 [LO])These power output pins provide the +28 Vdc operating power for the data loader. Thesepins are used only if the data loader operates from +28 Vdc.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--43Table 4--4. XS--950 Data Link Transponder Interface Description (cont)Connector PinDesignation Functional DescriptionJ1--40J1--41J1--48, 49RS--232 PDL INPUT:RS--232 PDL OUTPUTLOGIC COMMON (Gnd)These pins would be connected to an RS--232 Serial Port as follows. Most RS--232Serial Ports use either a 9 pin RS--232 (COM) connector or a 25 pin RS--232 (COM)connector.ARINC 615 PC COM1 OR COM2 PC COM1 OR COM2CONNECTOR PIN 9 PIN CONNECTOR 25 PIN CONNECTOR40 PC TX (pin 3) PC TX (pin 2)41 PC RX (pin 2) PC RX (pin 3)48 or 49 Ground (pin 5) Ground (pin 7)NOTE: When using a RS--232 interface, transponder pin J1--18 (Link A) and pin J1--19(Link B) must be connected (tied together) to do a software upload. The pinsshould be open to verify the software status.J1--50J1--51J1--52J1--53PDL FUNCTION DISCRETE #1 INPUT:PDL FUNCTION DISCRETE #2 INPUT:PDL FUNCTION DISCRETE #3 INPUT:PDL FUNCTION DISCRETE #4 INPUT:These pins are used to receive discrete functional information from the data loader.These pins should be connected to the PDL cable interface.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--44Table 4--5. RCZ--852 Diversity Mode S Transponder Interface DescriptionConnector PinDesignation Functional DescriptionJ1--1, 2 XPDR +28 Vdc FAN PWR and +28Vdc FAN RTN: (J1--1 LOW, J1--2 HIGH)The fan discrete outputs supply a switched, filtered +28 Vdc for a dc fan. The RCZ--852Transponder has an internal fan built into the unit, so external cooling is not required.Pins J1--1 and J1--2 should not be connected.J1--3 MUTUAL SUPPRESSION BUS I/O:This bus is a single conductor, shielded bidirectional line that connects to all aircraftL--Band equipment. It is used to desensitize the associated receiver inputs whiletransmitting.J1--7 XPDR +28 Vdc RTN:See pins 8, 9.J1--8J1--9XPDR +28 Vdc PWR:These pins along with there return lines (J1--7 and J1--20) provide the +28 Volt powerrequirements for the transponder.J1--11 PROGRAM ENABLE INPUT:Bench test function. Do not connect this pin in aircraft installations.J1--12 XPDR RS232 TX OUTPUT:Bench test function. Do not connect this pin in aircraft installations.J1--17, J1--18J1--19, J1--21DC GROUND INPUT:To be connected to aircraft dc ground.J1--23 XPDR VALID (PO) OUTPUT:This discrete outputs the status of the transponder continuous monitor tests. It is thesame as the XPDR VALID (NO) output (J1--100) except the discrete is a positive/openlogic. A +28 Vdc (200 mA maximum) is provided when the transponder is operationaland an active transponder mode is selected. An Open (>100k Ohms resistance toground) output is provided when the transponder has failed or the standby mode isselected.J1--24 XPDR RS232 RX INPUT:Bench test function. Do not connect this pin in aircraft installations.J1--25 PROGRAM +15 Vdc OUTPUT:Bench test function. Do not connect this pin in aircraft installations.J1--26, 27 XPDR TO TCAS ARINC 429 BUS OUTPUT: (J1--26 [A], J1--27 [B])This differential pair output is a high speed ARINC 429 bus (100k bits/second nominal)that sends data to the TCAS computer unit. The data bus conforms to the ARINC 718and ARINC 735A standards for TCAS to transponder interface.J1--28, 29 XPDR TO DLP A/B ARINC 429 BUS OUTPUT: (J1--28 [A], J1--29[B])This differential pair output is a high speed ARINC 429 bus (100k bits/second nominal)that sends data to an airborne data link processor (ADLP) system. The data bus is usedto transfer COMM--A and COMM--B messages between the two systems and conforms tothe ARINC 718 standard for ADLP to transponder interface.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--45Table 4--5. RCZ--852 Diversity Mode S Transponder Interface Description (cont)Connector PinDesignation Functional DescriptionJ1--30, 31 XPDR TO DLP C/D ARINC 429 BUS OUTPUT: (J1--30 [A], J1--31 [B])This differential pair output is a high speed ARINC 429 bus (100k bits/second nominal)that sends data to an airborne data link processor (ADLP) system. The data bus is usedto transfer COMM--C and COMM--D messages between the two systems and conformsto the ARINC 718 standard for ADLP to transponder interface.J1--32, 33 ADC1 TO XPDR ARINC 429/575 BUS INPUT: (J1--32 [A], J1--33 [B])This differential pair input is a low speed ARINC 429 or 575 bus that inputs uncorrectedpressure altitude (ARINC label 203) from an altitude source. The input accepts eitherARINC 429 or 575 data format, which is selected by the altitude source straps (W33,W34) on the Strap Assembly. The ALT SRC SEL2 (NO) discrete, pin 60, selects eitherADC1 or ADC2.J1--34, 35 CTL1 TO XPDR ARINC 429 BUS INPUT: (J1--34 [A], J1--35 [B])The transponder can receive data from the control panel(s) on the CTL1 TO XPDR andCTL2 TO XPDR data busses. The bus used, is selected by the CTL SRC SEL1 (NO)DISCRETE. See pin 61. The data bus not selected will not be processed. Thesedifferential pair inputs are low speed ARINC 429 busses (12.5k bits/second nominal) thattransmits tuning information from the control panel to the transponder. The transponderexpects to receive ARINC labels 016 and 031 at an update rate of 100 to 200milliseconds. Also see CTL2 TO XPDR ARINC 429 bus input (pins 48 and 49).J1--40, 41 TCAS TO XPDR ARINC 429 BUS INPUT: (J1--40 [A], J1--41 [B])This differential pair input is a high speed ARINC 429 bus (100k bit/second nominal) thatreceives data from a T2CAS computer unit. The data bus conforms to the ARINC 718and ARINC 735A standards for TCAS to transponder interface.J1--42, 43 DLP A/B TO XPDR ARINC 429 BUS INPUT: (J1--42 [A], J1--43 [B])This differential pair input is a high speed ARINC 429 bus (100k bits/second nominal) thatreceives data from an airborne data link processor (ADLP) system. The data bus is usedto transfer COMM--A and COMM--B messages between the two systems and conforms tothe ARINC 718 standard for ADLP to transponder interface.J1--44, 45 DLP C/D TO XPDR ARINC 429 BUS INPUT: (J1--44 [A], J1--45 [B])This differential pair input is a high speed ARINC 429 bus (100K bits/second nominal) thatreceives data from an airborne data link processor (ADLP) system. The data bus is usedto transfer COMM--C and COMM--D messages between the two systems and conformsto the ARINC 718 standard for ADLP to transponder interface.J1--46, 47 ADC2 TO XPDR ARINC 429/575 BUS INPUT: (J1--46 [A], J1--47 [B])See pins J1--32, 33J1--48, 49 CTL2 TO XPDR ARINC 429 BUS INPUT: (J1--48 [A], J1--49 [B])See pins J1--34, 35J1--50, 51 XPDR TO CTL ARINC 429 BUS OUTPUT: (J1--50 [A], J1--51 [B])This differential pair output is a low speed ARINC 429 bus (12.5k bits/second) thattransmits control panel input data back to the control panel for verification purposes.These output pins are connected only on some Collins control panels that requirefeedback from the transponder to make sure it is operating properly.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--46Table 4--5. RCZ--852 Diversity Mode S Transponder Interface Description (cont)Connector PinDesignation Functional DescriptionJ1--53 thru 58,J1--67 thru 71ENCODING ALTIMETER NO.1 ELEVEN BIT INPUT:Transponder input from Encoding Altimeter No. 1. These eleven lines from the altitudeencoder comprise an 11--bit word representative of the aircraft’s uncorrected pressurealtitude.J1--59 ALT COMP ENA (NO) DISCRETE INPUT:This discrete input enables or disables altitude comparison when dual Gillham altitudesources are selected via the ALTITUDE SOURCE strap. If comparison is enabled (J1--59Grounded), the two altitude sources (ENC ALT1 and ENC ALT2) are compared, and areconsidered valid if they are within 500 feet. If the altitude comparison is enabled and itfails, the altitude data is considered invalid in Mode S replies and altitude data sent toTCAS. If comparison is disabled (J1--59 Open), only the selected altitude source is used.This discrete has no effect if ARINC 429 or 575 altitude sources are used.NOTE: For installations with TCAS that use Gillham encoding altimeter sources, twoencoding altimeter sources must be used, and pin J1--59 must be enabled(Grounded).J1--60 ALT SRC SEL2 (NO) DISCRETE INPUT:This discrete input allows selection of one of two altitude sources. An Open causes thetransponder to use altitude source No.1, and a Ground causes the transponder to usealtitude source No.2. The altitude data sent to TCAS and used for transponder replies isderived from the selected source.J1--61 CTL SRC SEL1 (NO) DISCRETE INPUT:This discrete input is used to select one of two ARINC 429 control tuning ports. AGround on this pin causes the transponder to use CTL1 TO XPDR bus for tuning data,and an Open causes the transponder to use CTL2 TO XPDR bus for tuning data. Theinput is used only when the transponder tuning source is an ARINC 429 source in astand--alone transponder system. When an RSB tuning source is used, the input isignored.J1--64, 65 FMS TO XPDR ARINC 429 BUS INPUT: (J1--64 [A], J1--65 [B])This differential pair input is a low speed ARINC 429 bus (12.5k bits/second nominal) thatreceives basic transponder control data (label 031) and AIS flight ID (labels 233, 234,235, and 236) from a Flight Management System (FMS).J1--72 XPDR STANDBY (NO) INPUT:This discrete input is connected to the Control Panel STANDBY/ON output. The inputselects the active or standby status of the transponder. A ground causes the transponderto be in Standby, and an Open causes the transponder to be active. The input is usedonly when the transponder tuning source is an ARINC 429 source in a stand--alonetransponder system. When an RCB tuning source is used, the input is ignored.NOTE: If using a Collins CTL--92 Controller, this pin is not used.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--47Table 4--5. RCZ--852 Diversity Mode S Transponder Interface Description (cont)Connector PinDesignation Functional DescriptionJ1--73 SQUAT SWITCH 1 (NO) DISCRETE INPUT:This discrete input is used in conjunction with SQUAT SWITCH 2 discrete input (pin 75).The squat switch inputs tell the transponder if the aircraft is on the ground or in the air.The two inputs have different affects on transponder operation, and the status of the twoare combined. SQUAT SWITCH 1 (NO) causes the transponder to indicate the in the air/on the ground condition in replies to interrogations. SQUAT SWITCH 2 (NO) in additionto performing the function of SQUAT SWITCH 1 (NO), also inhibits replies to ATCRBS,ATCRBS/Mode S All--Call, and Mode S All--Call interrogations when the aircraft is “on theground”. The air/ground polarity is set by the SQUAT SWITCH POLARITY strap. Thematrix that follows, shows how the discretes affect the transponder operation:Squat Sw Transponder OperationPolarity Squat Switch Inputs Air/Ground ATCRBS/All--CallStrap 1 (NO) 2 (NO) Status RepliesGnd Gnd Gnd On Ground DisabledGnd Gnd Open On Ground EnabledGnd Open Gnd On Ground DisabledGnd Open Open In Air EnabledOpen Gnd Gnd In Air EnabledOpen Gnd Open On Ground DisabledOpen Open Gnd On Ground EnabledOpen Open Open On Ground DisabledJ1--74 XPDR OFF (NO) INPUT:This discrete input is used to turn the transponder power supply OFF. It should not beconnected in aircraft installations.J1--75 SQUAT SWITCH 2 (NO) DISCRETE INPUT:See pin 73.J1--80 thru 85J1--94 thru 98ENCODING ALTIMETER NO. 2 ELEVEN BIT INPUT:Transponder input from Encoding Altimeter No. 2. These eleven (11) lines from thealtitude encoder comprise an 11--bit word representative of the aircraft altitude.J1--90 XPDR STRAP +5 Vdc OUTPUT:Connect Strap Board connector pin W1P1--3 (red wire) to J1--90. This output pinprovides the +5 Vdc input power required by the Strap Assembly.J1--91 XPDR STRAP CLOCK (N) OUTPUT:Connect Strap Board connector pin W1P1--6 (blue wire) to J1--91. This output consists of48 clock pulses that serially shift the system options data out of the Strap Assembly shiftregisters.J1--92 XPDR STRAP LOAD (N) OUTPUT:Connect Strap Board connector pin W1P1--2 (orange wire) to J1--92. This output is usedto load the system options status into the Strap Assembly shift registers during initialsystem power--up.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--48Table 4--5. RCZ--852 Diversity Mode S Transponder Interface Description (cont)Connector PinDesignation Functional DescriptionJ1--93 XPDR STRAP DATA (P) INPUT:Connect Strap Board connector pin W1P1--7 (white wire) to J1--93. This input receivesthe serial data from the Strap Assembly that is used to program the desired systemoptions and Mode S address.J1--99 XPDR ACTIVE (NO) OUTPUT:This discrete output can be connected to an RF relay for systems that use a singleantenna connected to two transponders for the purpose of switching the antenna to theactive transponder. A Ground (200 mA maximum) output is provided when an Activetransponder mode is selected. An Open (>100k Ohms to ground) output is providedwhen Standby mode is selected.J1--100 XPDR VALID (NO) OUTPUT:This discrete outputs the status of the transponder continuous monitor tests. A Ground(200 mA maximum) output is provided when the transponder is operational and an activetransponder mode is selected. An Open (>100k Ohms resistance to ground) output isprovided when the transponder has failed or the Standby mode is selected.This pin should be connected to the Control Panel XPDR FAIL input.J1--102 ALT VALID (NO) OUTPUT:This discrete outputs the status of the altitude source when the transponder is in an activemode and altitude reporting is enabled. A Ground (200 mA maximum) is output when theselected altitude source is valid and the transponder is in an altitude reporting mode. AnOpen (>100k Ohms resistance to ground) output is provided when the selected altitudesource is invalid or the transponder is in Standby or not in an altitude reporting mode.This pin should be connected to the Control Panel ALT FAIL input if applicable.J1--103 XPDR STRAP GROUND OUTPUT:Connect Strap Board connector pin W1P1--4 (black wire) to J1--103. This output is thereturn line for the +5 Vdc output. See pin 90.J1--104 RESERVED FUNCTION:Connect Strap Board connector pin W1P1--1 (green wire) to J1--104.J1--105 RESERVED FUNCTION:Connect Strap Board connector pin W1P1--8 (yellow wire) to J1--105.J2 BOTTOM ANTENNA RF INPUT:RF input signal from bottom antenna.J3 TOP ANTENNA RF INPUT:RF input signal from top antenna.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--49TAWS/RWS PINOUTS AND PIN DEFINITIONS3. TAWS/RWS SpecificationsThe Ground Collision Avoidance Module (GCAM) function performs the core TAWS andreactive windshear detection processing. Inputs to the GCAM are aircraft state variables,aircraft performance models, the combined terrain and airport database, aircraft discretes, andARINC label busses. The outputs from the GCAM are the TAWS alerts, reactive windshear(RWS) alerts, and the terrain display buffers.The TAWS/RWS input data is attained from a variety of aircraft LRUs depending on theconfiguration of the specific aircraft. Since the source of the TAWS/RWS input data isprimarily unknown until a Customer Worksheet (Appendix A) and aircraft survey has beencompleted, most of the ARINC 600 connector pins are configurable. Once the origin of theTAWS/RWS input data has been determined an Aircraft Specific Data Base (ASDB) isgenerated by ACSS that defines the pin assignments for that specific aircraft. At installationtime, the ASDB is loaded into the aircraft’s Aircraft Personality Module (APM) which thenremains with the aircraft throughout any T2CAS LRU removal/replacements to retain theaircraft configuration data.In addition to the configurable pins, the TAWS/RWS also contains some permanent ornon--configurable pin assignments as well as some pin assignments that are shared with theTCAS functionality.This section is organized in a generic format to accommodate the dynamic, aircraft dependantpin assignments. The flow for configurable pin assignments is as follows:•An aircraft configuration type is determined based on the equipment installed.•Using the aircraft configuration data, the pin assignments are engineered, assigned anddocumented in the ASDB system requirements.•An Aircraft Configuration Table is then generated in Appendix B of this document thatdetails the specifics of the equipment installed on the new aircraft (columns) and assignsan Aircraft Installation Number to the newly identified aircraft installation type (rows).•The Aircraft Installation Number then references a Table that assigns the TAWS/RWSsignals to an Analog, Discrete or Digital Input/Output number. For example, FMS #1 (Left)could be assigned Digital Input #2. Table 4--13 of this section would then be referenced toobtain the specifics (pin numbers, usage, tolerances, etc.) of Digital Input #2.•If any new aircraft installation data and pinouts match a previously identified aircraftinstallation type, then that specific aircraft (identified at a minimum by Customer and aircrafttype) is added to the existing Aircraft Configuration Table.In addition to providing configurable and non--configurable pinouts, this section also providesthe following:•Characteristics and tolerances for the generic analog, discrete and digital inputs/outputs.For example, analog Input #1 must be a 3W or 2W Synchro, be within thevoltage/impedance tolerances defined in Table 4--10 and Table 4--11, and have the signalcharacteristics defined in the applicable subsection of the “Programmable Analog InputPins” section.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--50•A listing of the TAWS/RWS Input Data Signals, LRUs providing those signals, their datadefinitions (i.e. Analog signal type, A429 Label, etc.) and the minimum requirements thatmust be met by that specific input signal in order for TAWS/RWS to function withinspecification.A. TAWS/RWS Pinout and Pin Descriptions (Non--Configurable)This section contains the non--configurable pin assignments for the GCAM functionality(Table 4--6).Table 4--6. TAWS/RWS Non--Configurable PinoutPinDesignation Signal Functional DescriptionRightTopPlug(RTP)RTP--1A, --1B ARINC 453 Terrain Display Output No. 1:(RTP--1A [A], RTP--1B [B])A453 OutputRTP--1E, --1F ARINC 453 Terrain Display Output No. 2:(RTP--1E [A], RTP--1F [B])A453 OutputRTP--8G, --8H Glide Slope Low Level Deviation No. 1:(RTP--8G [+], RTP--8H [--])Analog ILS InputRTP--8J, --8K Localizer Low Level Deviation No. 1:(RTP--8J [+], RTP--8K [--])Analog ILS InputRTP--9C, --9D Glide Slope Low Level Deviation No. 2:(RTP--9C [+], RTP--9D [--])Analog ILS InputRTP--9E, --9F Localizer Low Level Deviation No. 2:(RTP--9E [+], RTP--9F [--])Analog ILS InputRTP--14E dc Total Air Temperature Return Analog dc TAT ReturnRTP--14F,--14G, --14Hdc Altitude Rate A575/595:(RTP--14F [Signal], --14G [Ref+], --14H [Ref--])Analog dc A575/595RTP--14J dc Output Reference +5 Vdc: The T2CAS provides a +5 Vdcprecision reference output as areference voltage for analogsensors which provide aratio--metric output. In mostinstallations the referencevoltage and the signal voltageare monitored so that thetolerance of the reference outputis not critical. This is thepreferred method and eliminatesissues such as grounddifferentials in aircraftinstallations.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--51Table 4--6. TAWS/RWS Non--Configurable Pinout(cont)PinDesignation Functional DescriptionSignalRTP--14K dc Output Reference Return: This is the Analog ReferenceReturn for the +5 Vdc OutputReference voltage on pinRTP--14J. Hence, the outputvoltage is measured between theAnalog Reference +5 Vdc outputand Analog Reference Returnoutput.RTP--15A Audio Output -- 8Ω(H) The 8Ωanalog outputs are usedto drive a speaker in the aircraftfor the annunciation of auralalerts. The TCAS has it’s ownaudio output, and TAWS andRWS functions share an audiooutput. The TCAS andTAWS/RWS outputs areindependent and separatelycontrolled.RTP--15B Audio Output -- 600Ω(H)The 600Ωanalog outputs areused to drive an intercom orheadset in the aircraft for theannunciation of aural alerts. TheTCAS has it’s own audio output,and TAWS and RWS functionsshare an audio output. TheTCAS and TAWS/RWS outputsare independent and separatelycontrolled.RTP--15C Audio Output -- 8Ω(L) / 600Ω(L)This is the Ground return forboth the 8Ωand 600ΩAudiooutputs (RTP--15A and --15Brespectfully).RTP--15D APM Power This is the +12 Vdc powersource for the AirplanePersonality Module.RTP--15E APM Return This is the Ground return for+12 Vdc APM power source.See pin RTP--15DRTP--15F APM Clock This the APM Clock Outputwhich is used to synchronizeserial output to the APM. TheClock output frequency is 2.0MHz + 1% when the APM isbeing accessed and is set to alogic 0 (not toggling) when theAPM is not being accessed.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--52Table 4--6. TAWS/RWS Non--Configurable Pinout(cont)PinDesignation Functional DescriptionSignalRTP--15G APM Serial Data Input: This is the Serial Data Outputfrom T2CAS to the APM SerialData Input. APM Enable(RTP--15J) and APM WriteEnable (RTP--15K) must beenabled before data can bewrittentotheAPM.RTP--15H APM Serial Data Output This is the Serial Data Input toT2CAS from the APM SerialData Output. APM Enable(RTP--15J) must be enabledbefore data can be read from theAPM.RTP--15J APM Enable No. 1 This pin is used to EnableRead/Write access to the APM.An APM Enable Output logic of 1disables Read/Write access tothe APM and a logic 0 enablesAPM Read/Write access. Thispin is used in conjunction withpins RTP--15G (APM serialoutput) and RTP--15H (APMserial input).RTP--15K APM Write Enable No. 1 This pin is used to Enable Writeaccess to the APM. An APMWrite Enable Output logic of 1disables Write access to theAPM and a logic 0 enables APMWrite access. This pin is used inconjunction with pin RTP--15G(APM serial output).Right Middle Plug (RMP)RMP--2H, --2J Radio Altitude ARINC 552/552A #1(RMP--2H [+], RMP--2J [--])Analog Rad Alt InputRMP--2K Radio Altitude Valid Discrete Input #1 +28 Vdc Disc Input. Used withAnalog Rad Alt Input #1(RMP--2H, --2J).
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--53Table 4--6. TAWS/RWS Non--Configurable Pinout(cont)PinDesignation Functional DescriptionSignalRMP--5K Air Ground Discrete Input(Weight--On--Wheels)This discrete input to the T2CAScomputer unit indicates thestatus of the Air/Ground orWeight--On--Wheels (WOW)switch. TCAS filters this input tomake sure it remains in a steadystate a minimum of 4 secondsbefore an Air/Ground transitionis recorded. An open indicatesthe aircraft is airborne and aground indicates the aircraft ison the ground.Inputs should be diode isolatedfrom each other.RMP--9C,RMP--9DGPS Data A429 Output(RMP--9C [A], RMP--9D [B])A429 Output H/L. Signal isreserved on TT--950 andTT--951 models (units withoutGPS).RMP--9E, --9F GPS Time Mark RS--422 Input/Output(RMP--9E [A], RMP--9F [B])Signals are GPS Time MarkInputs on TT--950 and TT--951models (units without GPS).Signals are GPS Time MarkOutputs on TT--952 (unit withGPS).RMP--9G,-- 9 HCD General Purpose A429 Output #1(RMP--9G [A], RMP--9H [B])A429 Output H/L. Signals arereserved for TCAS functions,however the ARINC 429 outputbusses are internally connectedand generated by the A6 TAWSCCA.RMP--9J, --9K CD General Purpose A429 Output #2(RMP--9J [A], RMP--9K [B])A429 Output H/L. Signals arereserved for TCAS functions,however the ARINC 429 outputbusses are internally connectedand generated by the A6 TAWSCCA.RMP--13F Landing Gear Discrete Input GND Disc InputRMP--13H,RMP--13JRadio Altitude A429 Input #1(RMP--13H [A], RMP--13J [B])A429 Input H/L. Signals areused by TCAS and TAWS/RWSfunctionsRMP--14K Accelerometer Self Test Output Accelerometer Test OutputRMP--15G Pitch Limit Indicator Output #1 (Reserved) Pitch Limit OutputRMP--15H Pitch Limit Indicator Output #2 (Reserved) Pitch Limit Output
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--54Table 4--6. TAWS/RWS Non--Configurable Pinout(cont)PinDesignation Functional DescriptionSignalRight Bottom Plug (RBP)RBP--1E, --1F Computer Power Output(RMP--1E [+], RMP--1F [--])Power Output (+24V)RBP--1G Radio Altitude Valid Discrete Input #3 + 28 Vdc Disc Input. Used withAnalog Rad Alt Input #3(RBP--3F, --3G).RBP--3A, --3B Radio Altitude ARINC 552/552A #2(RBP--3A [+], RBP--3B [--])Analog Rad Alt Input.RBP--3C Radio Altitude Valid Discrete Input #2 +28 Vdc Disc Input. Used withAnalog Rad Alt Input #2(RBP--3A, --3B).RBP--3D, --3E Radio Altitude A429 Input #2(RBP--3D [A], RBP--3E [B])A429 Input H/L. Signals areused by TCAS and TAWSfunctions.RBP--3F, 3G Radio Altitude ARINC 552/552A #3(RBP--3F [+], RBP--3G [--])Analog Rad Alt Input.RBP--10A JTAG Test Bus -- TCK Input Test JTAG Bus.RBP--10D JTAG Test Bus -- TDI Input Test JTAG Bus.RBP--10E JTAG Test Bus -- TDO Output Test JTAG Bus.RBP--10F JTAG Test Bus -- TMS Output Test JTAG Bus.RBP--10G Reserved JTAG Test Bus -- TRST Output Test JTAG Bus.B. TAWS/RWS Data Configuration(1) ASDBThe ASDB is a field loadable database that customizes the T2CAS operation for aspecific aircraft. The ASDB defines the Input/Output definition for the specific aircrafttype, the aircraft climb performance data to support of the TAWS functionality, andthe windshear algorithm coefficient data. The ASDB file is produced with a uniquepart number and can be uploaded to the APM via the RS--232 port or from aCompact Flash card.The ASDB I/O Database contains specific information needed to perform the I/Ofunctionality for the specific aircraft type. The I/O tables define the following types ofinformation for processing system inputs and outputs:•Physical mapping between external systems and T2CAS inputs and outputs.Example, GPS #1 is connected to ARINC 429 Input Bus #5.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--55•Types of data or information which is processed by the input or generated by theoutput. Example: GPS#1 has the following ARINC 429 labels: 100, 101, etc..•Input or output timing characteristics such as time--out periods or output rates.Example: Label 100 must be received every 2 seconds for it to be valid.•Data processing characteristics which define specific types of processing whichmay be performed on each input or output. This includes an example of thefollowing types of options:-- Method of storage (single or ping--pong buffer)-- Digital filter option (low--pass filter received data with a specified cut--offfrequency based on parameters in the tables)-- Extrapolation option (extrapolate data at a given interval based on previoussamples received)-- Sequence number option (example, process 310 Latitude and 311 Longitudeas a pair)-- Push--button option (look for a transition from 0 to 1 in the data)•Conversion code and parameters which specify how to process the data.Examples: 1) Decode Label 310 as a BNR (binary) number with a MSB of 90degrees. 2) Multiply analog radio altitude voltage by a parameter (scale factor) toget feet.•Non--standard conversion parameters. The conversion code in 5) provides astandard set of conversion operations which can handle many types of inputs andoutputs. However for more complex types of conversions, the non--standardconversion allows for a number of operations to be performed on the data.Operations which may be performed include mathematical, comparison andbranching.•A parameter which is used to determine the location in RAM where the input datais stored after processing, or data is read prior to output. This allows I/O data tobe mapped into the correct memory locations where GCAM can access it.(2) APMThe T2CAS uses an Airplane Personality Module (APM) to hold aircraft specificconfiguration data for TAWS and RWS functions. The APM is used in place ofprogram pin inputs to provide system configuration. The APM is in an ARINC 607Type II form factor, and is mounted to the aircraft as part of the installation. It retainsconfiguration data if a T2CAS LRU is removed and replaced with a new LRU serialnumber.The APM contains two types of data:•Aircraft Type Data•Installation Option Data
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--56The aircraft type data is produced by ACSS, and contains data that is specific toeach particular aircraft type. It contains performance data for that aircraft which isused by TAWS and Windshear functions. It also contains I/O configuration data forthe aircraft that defines and configures the interfaces to the aircraft system. For eachaircraft type, a unique Aircraft Type Data file is produced by ACSS that has a uniquepart number.The Installation Option data replaces the function of program pin (strap) inputs, andallows the installer to customize the operation of the unit at the time of installation.Types of functions that can be configured include display options, discrete outputoptions, altitude callout options, aural annunciation volume control, and other options.A complete list of Operator Selectable Options is contained in Table 4--7 andTable 4--8.The programming of the APM includes the Aircraft Type Data and Installation OptionData, and is accomplished through the RS--232 port on the PDL connector through aLaptop PC, or a Compact Flash Card. The APM data file that contains both types ofdata is generated on a PC with the EDDIT software tool and allows the selection ofthe aircraft type and installation options for that aircraft type. The EDDIT tool builds afile that contains a cyclical redundancy check (CRC) field around the APM data. Witha blank APM installed in the aircraft, the file can be uploaded to the T2CAS unit overthe RS--232 port or through a Compact Flash card. The T2CAS will then program theAPM.Verification of the correct APM contents may be accomplished by the RS--232 port oron the TAWS display. After the APM is programmed, the T2CAS, will output theAircraft Type Data part number and the installation option settings to the RS--232port. Additionally, it will display the APM configuration information on the TAWSdisplay. The data contained in the APM is recorded as part of the aircraftconfiguration data. The software in the T2CAS unit checks the CRC of the data toinsure the file is not corrupted.Table 4--7. Callout Configuration ItemsConfiguration Option ACD Setting OptionCallout Enable Flag [1] Enable/Disable CalloutsBank Angle Callout Enable Flag Enable/Disable Bank AngleCalloutDH/MDA Switch Available Flag Enable/DisableDecision Height Callout Enable Flag Enable/Disable DH CalloutMinimums Callout Enable Flag Enable/Disable Minimums CalloutMinimums--Minimums Callout Enable Flag Enable/Disable CalloutApproaching Decision Height Callout Enable Flag Enable/Disable Approaching DHCalloutApproaching Minimums Callout Enable Flag Enable/Disable ApproachingMinimums Callout
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--57Table 4--7. Callout Configuration Items(cont)Configuration Option ACD Setting Option1000 ft. Callout Enable Flag Enable/Disable Callout500 ft. Callout Enable Flag Enable/Disable Callout500 ft. (Tone) Callout Enable Flag Enable/Disable Callout Tone400 ft. Callout Enable Flag Enable/Disable Callout300 ft. Callout Enable Flag Enable/Disable Callout200 ft. Callout Enable Flag Enable/Disable Callout100 ft. Callout Enable Flag Enable/Disable Callout100 ft. (Tone) Callout Enable Flag Enable/Disable Callout Tone80 ft. Callout Enable Flag Enable/Disable Callout60 ft. Callout Enable Flag Enable/Disable Callout50 ft. Callout Enable Flag Enable/Disable Callout40 ft. Callout Enable Flag Enable/Disable Callout35 ft. Callout Enable Flag Enable/Disable Callout35 ft. (Tone) Callout Enable Flag Enable/Disable Callout Tone30 ft. Callout Enable Flag Enable/Disable Callout20 ft. Callout Enable Flag Enable/Disable Callout20 ft. (Tone) Callout Enable Flag Enable/Disable Callout Tone10 ft. Callout Enable Flag Enable/Disable CalloutTable 4--8. Operator Selectable Options -- Default SettingsOperator SelectableOptions Data Parameter Selectable OptionAircraft Configuration DataPart NumberACD_PART_NUMBER up to 23 ASCII charactersAircraft Registration Number(Tail Number)AIRCRAFT_REGISTRATION_NUMBERup to 23 ASCII charactersAlert High ImpedanceVolume LevelHIGH_IMPEDANCE_VOLUME_LEVELinteger in the range 0 .. 255( min = 0, max = 255)Alert Low ImpedanceVolume LevelLOW_IMPEDANCE_VOLUME_LEVELinteger in the range 0 .. 255( min = 0, max = 255)
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--58Table 4--8. Operator Selectable Options -- Default Settings(cont)Operator SelectableOptions Selectable OptionData ParameterBank Angle Repetition BANK_ANGLE_REPETITION 1, 2, 3, 4, Infinity -- T2CASwill repeat the Bank AngleWarning based on the BankAngle Repetition input.CPA Caution Alert CPA_MODE_CAUTION 1 = “TERRAIN AHEAD”,2 = “TERRAIN CAUTION“CPA Mode A Warning Alert CPA_MODE_A_WARNING 1 = “TERRAIN AHEADPULL--UP”,2 = “TERRAIN TERRAINPULL--UP PULL--UP” or3 = “Whoop, Whoop--PULLUP”CPA Mode B Warning Alert CPA_MODE_B_WARNING 1 = “AVOID TERRAIN”GPWS Caution FlashEnableGPWS_CAUTION_FLASH_ENABLEEnable -- Caution lampflashing for the duration ofthe GPWS Caution Event.Disable -- Caution lampsolid for the duration of theGPWS Caution Event.GPWS Warning FlashEnableGPWS_WARNING_FLASH_ENABLEEnable -- Warning lampflashing for the duration ofthe GPWS Warning Event.Disable -- Warning lampsolid for the duration of theGPWS Warning Event.Male Voice Enable MALE_VOICE_ENABLE Enable -- enables the malealerting voiceDisable -- alerting voice is afemale voice.Mode 1 Caution Alert MODE_1_CAUTION 1 = “Whoop, Whoop, PULLUP” or2=“PULLUP,PULLUP”Mode 1 Warning Alert MODE_1_WARNING 1 = “Whoop, Whoop, PULLUP” or2=“PULLUP,PULLUP”Mode 2 Caution Alert MODE_2_CAUTION 1 = “TERRAIN, TERRAIN”Mode 2 Warning Alert MODE_2_WARNING 1 = “Whoop, Whoop, PULLUP” or2=“PULLUP,PULLUP”
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--59Table 4--8. Operator Selectable Options -- Default Settings(cont)Operator SelectableOptions Selectable OptionData ParameterMode 3 Caution Alert MODE_3_CAUTION 1 = “DON’T SINK, DON’TSINK”Mode 4A Caution Alert MODE_4A_CAUTION 1 = “TOO LOW TERRAIN”or2 = “TOO LOW FLAPS”Mode 4B Caution Alert MODE_4B_CAUTION 1 = “TOO LOW TERRAIN”or2 = “TOO LOW GEAR”Mode 5 Caution Alert MODE_5_CAUTION 1 = “GLIDESLOPE”Mode 6 High ImpedanceVolume LevelMODE_6_HIGH_IMPEDANCE_VOLUME_LEVELinteger in the range 0 .. 255( min = 0, max = 255)Mode 6 Low ImpedanceVolume LevelMODE_6_LOW_IMPEDANCE_VOLUME_LEVELinteger in the range 0 .. 255( min = 0, max = 255)Mode 6 Volume LevelEnable -- Altitude CalloutsMODE_6_VOLUME_LEVEL_ENABLE_ALTITUDE_CALLOUTSEnable -- Altitude Calloutsannunciated at the Mode 6Volume Level.Disable -- Altitude Calloutsannunciated at the HighImpedance or LowImpedance Normal VolumeLevels.Mode 6 Volume LevelEnable -- Bank AngleCalloutsMODE_6_VOLUME_LEVEL_ENABLE_BANK_ANGLE_CALLOUTSEnable -- Bank AngleCallouts annunciated at theMode 6 Volume Level.Disable -- Bank AngleCallouts annunciated at theHigh Impedance or LowImpedance Normal VolumeLevels.Mode 6 Volume LevelEnable -- Minimum CalloutsMODE_6_VOLUME_LEVEL_ENABLE_MINIMUM_CALLOUTSEnable -- MinimumsCallouts annunciated at theMode 6 Volume Level.Disable -- MinimumsCallouts annunciated at theHigh Impedance or LowImpedance Normal VolumeLevels.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--60Table 4--8. Operator Selectable Options -- Default Settings(cont)Operator SelectableOptions Selectable OptionData ParameterMode 6 Volume LevelEnable -- Mode 5 CalloutMODE_6_VOLUME_LEVEL_ENABLE_MODE_5_CALLOUTEnable -- Mode 5 Calloutsannunciated at the Mode 6Volume Level.Disable -- Mode 5 Calloutsannunciated at the HighImpedance or LowImpedance Normal VolumeLevels.QFE Enable QFE_ENABLE Enable -- Indicates QFEaltitude correction isenabled.Disable -- QNH altitudecorrection is used.Store GCAM ParametersEnableSTORE_GCAM_PARAMETERSEnable -- Records additionalGCAM parameters when anEvent occurs, for addeddiagnostic ability of GCAMparameters.Disable -- Records standardsetofGCAMData.GCAM Event data is storedfor every event,independent of this setting.Store GFM ParametersEnableSTORE_GFM_PARAMETERS Enable -- Records additionalGFM parameters when anEvent occurs, for addeddiagnostic ability of Platformparameters.Disable -- Records standardsetofGFMData.TAWS Caution Flash Enable TAWS_CAUTION_FLASH_ENABLEEnable -- Caution lampflashing for the duration ofthe TAWS Caution Event.Disable -- Caution lampsolid for the duration of theTAWS Caution Event.TAWS Warning FlashEnableTAWS_WARNING_FLASH_ENABLEEnable -- Warning lampflashing for the duration ofthe TAWS Warning Event.Disable -- Warning lampsolid for the duration of theTAWS Warning Event
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--61Table 4--8. Operator Selectable Options -- Default Settings(cont)Operator SelectableOptions Selectable OptionData ParameterTerrain Alert AudioSuppression EnableTERRAIN_ALERT_AUDIO_SUPPRESSION_ENABLEEnable -- Allows TerrainAlert (CPA or GPWS) audioalerts to be suppressed bythe flight crew after onecycle.Disable -- Prohibits flightcrew from suppressingTerrain audio alerts.Windshear Caution FlashEnableWINDSHEAR_CAUTION_FLASH_ENABLEEnable -- Caution lampflashing for the duration ofthe Windshear CautionEvent.Disable -- Caution lampsolid for the duration of theWindshear Caution EventWindshear Warning Alert WINDSHEAR_WARNING_AURAL1 = “WINDSHEAR,WINDSHEAR,WINDSHEAR”2 = “Siren, WINDSHEAR,WINDSHEAR,WINDSHEAR”Windshear Warning AudioSuppression EnableWINDSHEAR_WARNING_AUDIO_SUPPRESSION_ENABLEEnable -- Allows WindshearAlert audio alerts to besuppressed by the flightcrew after one cycle.Disable -- Prohibits flightcrew from suppressingWindshear audio alerts.Windshear Warning FlashEnableWINDSHEAR_WARNING_FLASH_ENABLEEnable -- Warning lampflashing for the duration ofthe Windshear WarningEvent.Disable -- Warning lampsolid for the duration of theWindshear Warning EventAural Alert PrioritizationInput 1 EnableAURAL_ALERT_PRIORITIZATION_INPUT_1_ENABLEEnable -- Inhibits Auralalerts that are of lesserpriority than Aural AlertPriority 1.Disable -- Lesser priorityaural alerts Not inhibited.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--62Table 4--8. Operator Selectable Options -- Default Settings(cont)Operator SelectableOptions Selectable OptionData ParameterVisual Alert PrioritizationInput 1 EnableVISUAL_ALERT_PRIORITIZATION_INPUT_1_ENABLEEnable -- Inhibits Visualalerts that are of lesserpriority than Visual AlertPriority 1.Disable -- Lesser priorityVisual alerts Not inhibited.Aural Alert PrioritizationInput 2 EnableAURAL_ALERT_PRIORITIZATION_INPUT_2_ENABLEEnable -- Inhibits Auralalerts that are of lesserpriority than Aural AlertPriority 2.Disable -- Lesser priorityaural alerts Not inhibited.Visual Alert PrioritizationInput 2 EnableVISUAL_ALERT_PRIORITIZATION_INPUT_2_ENABLEEnable -- Inhibits Visualalerts that are of lesserpriority than Visual AlertPriority 2.Disable -- Lesser priorityVisual alerts Not inhibited.Aural Alert PrioritizationInput 3 EnableAURAL_ALERT_PRIORITIZATION_INPUT_3_ENABLEEnable -- Inhibits Auralalerts that are of lesserpriority than Aural AlertPriority 3.Disable -- Lesser priorityaural alerts Not inhibited.Visual Alert PrioritizationInput 3 EnableVISUAL_ALERT_PRIORITIZATION_INPUT_3_ENABLEEnable -- Inhibits Visualalerts that are of lesserpriority than Visual AlertPriority 3.Disable -- Lesser priorityVisual alerts Not inhibited.Aural Alert PrioritizationInput 4 EnableAURAL_ALERT_PRIORITIZATION_INPUT_4_ENABLEEnable -- Inhibits Auralalerts that are of lesserpriority than Aural AlertPriority 4.Disable -- Lesser priorityaural alerts Not inhibited.Visual Alert PrioritizationInput 4 EnableVISUAL_ALERT_PRIORITIZATION_INPUT_4_ENABLEEnable -- Inhibits Visualalerts that are of lesserpriority than Visual AlertPriority 4.Disable -- Lesser priorityVisual alerts Not inhibited.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--63C. APM/ASDB Configurable Pinout and Pin Description(1) Programmable Analog Input PinsT2CAS contains generic analog inputs which are used to input a variety ofdynamically assigned analog signals. Most inputs channels can accept a number ofdifferent signal types and are individually selectable by the APM through the ASDBdatabase.The analog signals addressed in this section are APM/ASDB programmable inputsas shown in Table 4--9. As new Aircraft configurations/ASDBs are defined, theanalog signals will be assigned to a particular input per Appendix n (’n’ denotes anAppendix assigned as new Aircraft Configurations are defined).The statically assigned analog signal definitions are addressed in the “TAWS/RWSPinout and Pin Descriptions (Non--Configurable)” Section.Table 4--9. APM/ASDB Programmable Analog InputsAnalog Signal Definition Pin # Notes3W Synchro(X) #1 RTP--3J 3W Syncro Input, multiplexed withA429 receivers3W Synchro(Y) or 2W(+) #1 RTP--4K 2/3W Syncro Input, multiplexed withA429 receivers3W Synchro(Z) or 2W(--) #1 RTP--3K 2/3W Syncro Input, multiplexed withA429 receivers3W Synchro(X) #2 RTP--4A 3W Syncro Input, multiplexed withA429 receivers3W Synchro(Y) or 2W(+) #2 RTP--4C 2/3W Syncro Input3W Synchro(Z) or 2W(--) #2 RTP--4B 2/3W Syncro Input, multiplexed withA429 receivers3W Synchro(X) #3 RTP--4D 3W Syncro Input, multiplexed withA429 receivers3W Synchro(Y) or 2W(+) #3 RTP--4F 2/3W Syncro Input3W Synchro(Z) or 2W(--) #3 RTP--4E 2/3W Syncro Input, multiplexed withA429 receivers3W Synchro(X) #4 RTP--4G 3W Syncro Input, multiplexed withA429 receivers3W Synchro(Y) or 2W(+) #4 RTP--4J 2/3W Syncro Input3W Synchro(Z) or 2W(--) #4 RTP--4H 2/3W Syncro Input, multiplexed withA429 receivers3W Synchro(X) #5 RTP--5A 3W Syncro Input, multiplexed withA429 receivers3W Synchro(Y) or 2W(+) #5 RTP--5C 2/3W Syncro Input3W Synchro(Z) or 2W(--) #5 RTP--5B 2/3W Syncro Input, multiplexed withA429 receivers
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--64Table 4--9. APM/ASDB Programmable Analog Inputs(cont)Analog Signal Definition NotesPin #3W Synchro(X) #6 RTP--5D 3W Syncro Input, multiplexed withA429 receivers3W Synchro(Y) or 2W(+) #6 RTP--5F 2/3W Syncro Input3W Synchro(Z) or 2W(--) #6 RTP--5E 2/3W Syncro Input, multiplexed withA429 receivers3W Synchro(X) #7 RTP--5G 3W Syncro Input, multiplexed withA429 receivers3W Synchro(Y) or 2W(+) #7 RTP--5J 2/3W Syncro Input3W Synchro(Z) or 2W(--) #7 RTP--5H 2/3W Syncro Input, multiplexed withA429 receivers3W Synchro(X) #8 RTP--6A 3W Syncro Input, multiplexed withA429 receivers3W Synchro(Y) or 2W(+) #8 RTP--6C 2/3W Syncro Input3W Synchro(Z) or 2W(--) #8 RTP--6B 2/3W Syncro Input, multiplexed withA429 receivers3W Synchro(X) #9 RTP--6D 3W Syncro Input3W Synchro(Y) or 2W(+) #9 RTP--6F 2/3W Syncro Input3W Synchro(Z) or 2W(--) #9 RTP--6E 2/3W Syncro Input3W Synchro(X) #10 RTP--6G 3W Syncro Input3W Synchro(Y) or 2W(+) #10 RTP--6J 2/3W Syncro Input3W Synchro(Z) or 2W(--) #10 RTP--6H 2/3W Syncro Input3W Synchro(X) #11 RTP--7A 3W Syncro Input3W Synchro(Y) or 2W(+) #11 RTP--7C 2/3W Syncro Input3W Synchro(Z) or 2W(--) #11 RTP--7B 2/3W Syncro Input3W Synchro(X) #12 RTP--7D 3W Syncro Input3W Synchro(Y) or 2W(+) #12 RTP--7F 2/3W Syncro Input3W Synchro(Z) or 2W(--) #12 RTP--7E 2/3W Syncro Input3W Synchro(X) #13 RTP--7G 2W Syncro Input3W Synchro(Y) or 2W(+) #13 RTP--7J 2/3W Syncro Input3W Synchro(Z) or 2W(--) #13 RTP--7H 2/3W Syncro Input3W Synchro(X) #14 RTP--5K 3W Syncro Input3W Synchro(Y) or 2W(+) #14 RTP--7K 2/3W Syncro Input3W Synchro(Z) or 2W(--) #14 RTP--6K 2/3W Syncro Input
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--65Table 4--9. APM/ASDB Programmable Analog Inputs(cont)Analog Signal Definition NotesPin #2W dc Input #1 (+) RTP--9A 2W dc Input2W dc Input #1 (--) RTP--9B 2W dc Input2W dc Input #2 (+) RTP--9G 2W dc Input2W dc Input #2 (--) RTP--9H 2W dc Input2W dc Input #3 (+) RMP--2B 2W dc Input2W dc Input #3 (--) RMP--2C 2W dc Input2W dc Input #4 (+) RMP--3J 2W dc Input2W dc Input #4 (--) RMP--3K 2W dc Input2W dc Input #5 (+) RMP--4A 2W dc Input2W dc Input #5 (--) RMP--4B 2W dc Input2W dc Input #6 (+) RMP--4C 2W dc Input2W dc Input #6 (--) RMP--4E 2W dc Input2W dc Input #7 (+) RMP--4F 2W dc Input2W dc Input #7 (--) RMP--4G 2W dc Input2W ac/dc Input #8 (+) RMP--5A 2W ac/dc Input2W ac/dc Input #8 (--) RMP--5B 2W ac/dc Input2W ac/dc Input #9 (+) RMP--5C 2W ac/dc Input2W ac/dc Input #9 (--) RMP--5D 2W ac/dc Input2W dc Input #10 (+) RMP--10E 2W dc Input2W dc Input #10 (--) RMP--10F 2W dc Input2W dc Input #11 (+) RMP--11E 2W dc Input2W dc Input #11 (--) RMP--11F 2W dc Input2W dc Input #12 (+) RMP--11G 2W dc Input2W dc Input #12 (--) RMP--11H 2W dc Input2W dc / ac Reference Input #13 (+) RMP--11J 2W dc / ac reference Input2W dc / ac Reference Input #13 (--) RMP--11K 2W dc / ac reference Input2W dc / ac Reference Input #14 (+) RMP--15A 2W dc / ac reference Input2W dc / ac Reference Input #14 (--) RMP--15B 2W dc / ac reference Input2W dc / ac Reference Input #15 (+) RMP--15C 2W dc / ac reference Input2W dc / ac Reference Input #15 (--) RMP--15D 2W dc / ac reference Input
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--66Table 4--9. APM/ASDB Programmable Analog Inputs(cont)Analog Signal Definition NotesPin #2W dc / ac Reference Input #16 (+) RMP--15E 2W dc / ac reference Input2W dc / ac Reference Input #16 (--) RMP--15F 2W dc / ac reference Input2W ac / dc / ac Ref Input #17 (+) RBP--1A 2W ac/dc / ac reference Input2W ac / dc / ac Ref Input #17 (--) RBP--1B 2W ac/dc / ac reference Input2W ac / dc / ac Ref Input #18 (+) RBP--1C 2W ac/dc / ac reference Input2W ac / dc / ac Ref Input #18 (--) RBP--1D 2W ac/dc / ac reference Inputac 400Hz Reference #1 (H) RMP--4H 2W ac reference Inputac 400Hz Reference #1 (C) RMP--4J 2W ac reference Inputac 400Hz Reference #2 (H) RMP--5H 2W ac reference Inputac 400Hz Reference #2 (C) RMP--5J 2W ac reference Input(a) Analog Input Type Definitions/TolerancesThe analog input types accept signals with input voltage ranges as defined inTable 4--10. Table 4--11 list the input impedance ranges for the accepted analoginput types.Table 4--10. Analog Input Voltage RangesAnalog Input TypeCommon modevoltage on each pin(Volts, peak)Differential voltagebetween 2 pins(Volts, peak) (NOTE)Analog 3W/2W multiplexed with A429receivers--22.0V to +22.0 V --22.0V to +22.0 VAnalog 3W/2W non--multiplexed --50.0V to +50.0 V --50.0V to +50.0 VAnalog 2W ac/dc --50.0V to +50.0 V --50.0V to +50.0 VAnalog 2W dc --50.0V to +50.0 V --50.0V to +50.0 VAnalog 2W dc/Ref --50.0V to +50.0 V --50.0V to +50.0 VAnalog 2W ac/dc/Ref --50.0V to +50.0 V --50.0V to +50.0 VNOTE: For 3 Wire inputs, the differential voltage requirement applies to thevoltage between the XZ and YZ legs.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--67Table 4--11. Analog Input ImpedanceAnalog Input Type Impedance relativeto groundImpedance between2pins(NOTE)Analog 3W/2W multiplexed with A429receivers>9k Ohms >9k OhmsAnalog 3W/2W non--multiplexed >95k Ohms (X, Y)>47k Ohms (Z)>500k OhmsAnalog 2W ac/dc >95k Ohms >500k OhmsAnalog 2W dc >95k Ohms >500k OhmsAnalog 2W dc/Ref >95K Ohms >500K OhmsAnalog 2W ac/dc/Ref >95K Ohms >500K OhmsNOTE: For 3 Wire inputs, the differential impedance requirement applies to theimpedance between the XZ and YZ legs.(b) 3W AC Synchro Signal Type ProcessingThe 3W ac synchro input signal consists of a 3 wire synchro which is excited bya 400 Hz (nominal) AC reference input. The amplitude of the X, Y and Z inputsand the phase relative to the AC reference determines the angle. The 3W acsynchro inputs accept ARINC 407 syncro signals.T2CAS accepts the 400 Hz ac reference signals on the specified programmablepins as defined in Table 4--12.NOTE: The reference is used to synchronously detect 400 Hz ac signals.Table 4--12. 3W Synchro AC References400Hz AC Reference Signal Type Pin Assignmenta. Internal self--generated ac reference N/Ab. ac synchro Reference #1 RMP--4H (H), RMP--4J (C)c. ac synchro Reference #2 RMP--5H (H), RMP--5J (C)d. Analog 2W dc / ac Reference Input #13 RMP--11J (+), RMP--11K (--)e. Analog 2W dc / ac Reference Input #14 RMP--15A (+), RMP--15B (--)f. Analog 2W dc / ac Reference Input #15 RMP--15C (+), RMP--15D (--)g. Analog 2W dc / ac Reference Input #16 RMP--15E (+), RMP--15F (--)h. Analog 2W ac / dc / ac Reference Input #17 RBP--1A (+), RBP--1B (--)j. Analog 2W ac / dc / ac Reference Input #18 RBP--1C (+), RBP--1D (--)
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--68(c) 2W DC Signal ProcessingThe 2W dc Inputs input signal consists of a 2 Wire dc input signal that isconnected to the Y and Z leg of the input circuit. The X leg is not connected toexternal circuitry in this configuration.(2) Programmable Digital Input/Output PinsThis section defines the physical characteristics of each Digital signal type supportedby the T2CAS TAWS/RWS function. The T2CAS supports the following Digitalsignals: ARINC 429, ARINC 453, Ethernet 10 Base--T and RS--422.The Digital signals addressed in this section are APM/ASDB programmable input andoutput signals as shown in Table 4--13 and Table 4--14 respectfully. As new Aircraftconfigurations/ASDBs are defined, the Digital signals will be assigned to a particularinput/output per Appendix n (’n’ denotes Appendix’ that are created as new AircraftConfigurations are defined).The statically assigned Digital signal definitions are addressed in the “TAWS/RWSPinout and Pin Descriptions (Non--Configurable)” Section.Table 4--13. APM/ASDB Programmable Digital InputsDigital Signal Definition Pin # NotesARINC 429 Input #1 (A) RTP--1C A429 Input H/LARINC 429 Input #1 (B) RTP--1D A429 Input H/LARINC 429 Input #2 (A) RTP--1G A429 Input H/LARINC 429 Input #2 (B) RTP--1H A429 Input H/LARINC 429 Input #3 (A) RTP--1J A429 Input H/LARINC 429 Input #3 (B) RTP--1K A429 Input H/LARINC 429 Input #4 (A) RTP--2E A429 Input H/LARINC 429 Input #4 (B) RTP--2F A429 Input H/LARINC 429 Input #5 (A) RTP--3A A429 Input H/LARINC 429 Input #5 (B) RTP--3B A429 Input H/LARINC 429 Input #6 (A) RTP--3C A429 Input H/LARINC 429 Input #6 (B) RTP--3D A429 Input H/LARINC 429 Input #7 (A) RTP--3E A429 Input H/LARINC 429 Input #7 (B) RTP--3F A429 Input H/LARINC 429 Input #8 (A) RTP--3G multiplexed with RS--422 and GPS Time MarkInputsARINC 429 Input #8 (B) RTP--3H multiplexed with RS--422 and GPS Time MarkInputs
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--69Table 4--13. APM/ASDB Programmable Digital Inputs(cont)Digital Signal Definition NotesPin #ARINC 429 Input #9 (A) RTP--3J multiplexed with Analog 3W Synchro(X)ARINC 429 Input #9 (B) RTP--3K multiplexed with Analog 3W Synchro(Z) or 2W(--)ARINC 429 Input #10 (A) RTP--4A multiplexed with Analog 3W Synchro(X)ARINC 429 Input #10 (B) RTP--4B multiplexed with Analog 3W Synchro(Z) or 2W(--)ARINC 429 Input #11 (A) RTP--4D multiplexed with Analog 3W Synchro(X)ARINC 429 Input #11 (B) RTP--4E multiplexed with Analog 3W Synchro(Z) or 2W(--)ARINC 429 Input #12 (A) RTP--4G multiplexed with Analog 3W Synchro(X)ARINC 429 Input #12 (B) RTP--4H multiplexed with Analog 3W Synchro(Z) or 2W(--)ARINC 429 Input #13 (A) RTP--5A multiplexed with Analog 3W Synchro(X)ARINC 429 Input #13 (B) RTP--5B multiplexed with Analog 3W Synchro(Z) or 2W(--)ARINC 429 Input #14 (A) RTP--5D multiplexed with Analog 3W Synchro(X)ARINC 429 Input #14 (B) RTP--5E multiplexed with Analog 3W Synchro(Z) or 2W(--)ARINC 429 Input #15 (A) RTP--5G multiplexed with Analog 3W Synchro(X)ARINC 429 Input #15 (B) RTP--5H multiplexed with Analog 3W Synchro(Z) or 2W(--)ARINC 429 Input #16 (A) RTP--6A multiplexed with Analog 3W Synchro(X)ARINC 429 Input #16 (B) RTP--6B multiplexed with Analog 3W Synchro(Z) or 2W(--)RS--422 Input (H) RTP--3G multiplexed with A429 and GPS Time Mark InputsRS--422 Input (L) RTP--3H multiplexed with A429 and GPS Time Mark InputsEthernet LAN #1 RX (+) RTP--2C Ethernet 10 Base--TEthernet LAN #1 RX (--) RTP--2D Ethernet 10 Base--TEthernet LAN #2 RX (+) RTP--2J Ethernet 10 Base--TEthernet LAN #2 RX (--) RTP--2K Ethernet 10 Base--TTable 4--14. APM/ASDB Programmable Digital OutputsDigital Signal Definition Pin # NotesARINC 429 Output #1 (A) RTP--8A A429 Output H/LARINC 429 Output #1 (B) RTP--8B A429 Output H/LARINC 429 Output #2 (A) RTP--8E A429 Output H/LARINC 429 Output #2 (B) RTP--8F A429 Output H/L
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--70Table 4--14. APM/ASDB Programmable Digital Outputs(cont)Digital Signal Definition NotesPin #RS--422 Output (H) RTP--8C RS--422 OutputRS--422 Output (L) RTP--8D RS--422 OutputEthernet LAN #1 TX (+) RTP--2A Ethernet 10 Base--TEthernet LAN #1 TX (--) RTP--2B Ethernet 10 Base--TEthernet LAN #2 TX (+) RTP--2G Ethernet 10 Base--TEthernet LAN #2 TX (--) RTP--2H Ethernet 10 Base--T(a) ARINC 429 SignalsThe T2CAS TAWS/RWS Circuit Card supports up to 18 ARINC 429 receivers, 16of which are APM/ASDB programmable (as shown in Table 4--13). Additionally,4 ARINC 429 transmitters are supported, 2 of which are APM/ASDBprogrammable (as shown in Table 4--14).The ARINC 429 definition for the Source Destination Identifier Bits are shown inTable 4--15.Table 4--15. Source Destination Identifier (SDI)BITS Meaning10 90 0 All--Call0 1 Installation #11 0 Installation #21 1 Installation #3The ARINC 429 Sign Status Matrix Bit definitions for Binary data and BinaryCoded Decimal data are shown in Table 4--16 and Table 4--17 respectfully.Table 4--16. Sign Status Matrix (SSM) [BNR]BITS Meaning30 310 0 Failure Warning0 1 No Computed Data1 0 Functional Test1 1 Normal Operation
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--71Table 4--17. Sign Status Matrix (SSM) [BCD]BITS Meaning30 310 0 North/Plus0 1 No Computed Data1 0 Functional Test1 1 UndefinedARINC 429 inputs are classified as one of the following: high speed (H), lowspeed (L) or either (H/L). The A429 receivers are capable of receiving high orlow speed data through APM configuration. The ports are designated H or L ifthey are designated for a function with a known bus speed, otherwise H/L isassigned (there is no hardware difference between the H, L or H/L ports).ARINC 429 outputs are also classified as either high speed (H), low speed (L) orselectable (H/L). A429 outputs designated as H/L speed are capable ofoperating in either high or low speed modes, selectable by the APM through theASDB database.(b) Ethernet 10 Base--T SignalsEthernet 10 Base--T is specified in IEEE Standard 802.3 Ethernet 10 Base--Tprovides communication at a data rate of 10 MBPS over two pairs of wires,where one twisted pair is used to receive data and the other twisted pair is usedto transmit data. Segments of approximately 100 meters in length can beconstructed when twisted pair wire that meets the EIA/TIA Category 3 wirespecifications is used.(c) RS--422 SignalsThe TAWS/RWS card has an RS--422 Input bus which is multiplexed on thesame pins as an ARINC 429 Input bus. The RS--422 Input Bus meets theelectrical requirements in EIA/TIA--422--B.The RS--422 Input Bus has an input impedance on each pin relative to ground of≥9k Ohms and a differential input impedance between + and -- pins of ≥9kOhms.NOTE: This is due to the fact the input is multiplexed with an ARINC 429Receiver.The RS--422 Output Bus has an output impedance of 75 ±5 Ohms distributedequally between the + and -- outputs.(d) GPS Time MarkThe GPS Time Mark Input accepts RS--422 GPS Time Mark signals from anARINC--743A GPS.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--72The GPS Time Mark Output is used to provide an accurate timing reference forGPS signals. The output has a differential RS--422 signal format.(3) Programmable Discrete Input/Output PinsThe Discrete signals addressed in this section are APM/ASDB programmable inputand output signals as shown in Table 4--18 and Table 4--19 respectfully. As newAircraft configurations/ASDBs are defined, the Discrete signals will be assigned to aparticular input/output per Appendix n (’n’ denotes Appendix’ that are created as newAircraft Configurations are defined).Table 4--18. APM/ASDB Programmable Discrete InputsDigital Signal Definition Pin # NotesGround Discrete Input #1 RTP--9J GND Disc InputGround Discrete Input #2 RTP--9K GND Disc InputGround Discrete Input #3 RTP--10A GND Disc InputGround Discrete Input #4 RTP--10B GND Disc InputGround Discrete Input #5 RTP--10C GND Disc InputGround Discrete Input #6 RTP--10D GND Disc InputGround Discrete Input #7 RTP--10E GND Disc InputGround Discrete Input #8 RTP--10F GND Disc InputGround Discrete Input #9 RTP--10G GND Disc InputGround Discrete Input #10 RTP--10H GND Disc InputGround Discrete Input #11 RTP--10J GND Disc InputGround Discrete Input #12 RTP--10K GND Disc InputGround Discrete Input #13 RTP--11A GND Disc InputGround Discrete Input #14 RTP--11B GND Disc InputGround Discrete Input #15 RTP--11C GND Disc InputGround Discrete Input #16 RTP--11D GND Disc InputGround Discrete Input #17 RTP--11E GND Disc InputGround Discrete Input #18 RTP--11F GND Disc InputGround Discrete Input #19 RTP--11G GND Disc InputGround Discrete Input #20 RTP--11H GND Disc InputGround Discrete Input #21 RTP--11J GND Disc InputGround Discrete Input #22 RTP--11K GND Disc Input+28 Vdc Discrete Input #1 RTP--12A +28 Vdc Disc Input
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--73Table 4--18. APM/ASDB Programmable Discrete Inputs(cont)Digital Signal Definition NotesPin #+28 Vdc Discrete Input #2 RTP--12B +28 Vdc Disc Input+28 Vdc Discrete Input #3 RTP--12C +28 Vdc Disc Input+28 Vdc Discrete Input #4 RTP--12D +28 Vdc Disc Input+28 Vdc Discrete Input #5 RTP--12E +28 Vdc Disc Input+28 Vdc Discrete Input #6 RTP--12F +28 Vdc Disc Input+28 Vdc Discrete Input #7 RTP--12G +28 Vdc Disc Input+28 Vdc Discrete Input #8 RTP--12H +28 Vdc Disc Input+28 Vdc Discrete Input #9 RTP--12J +28 Vdc Disc Input+28 Vdc Discrete Input #10 RTP--12K +28 Vdc Disc Input+28 Vdc Discrete Input #11 RTP--13A +28 Vdc Disc Input+28 Vdc Discrete Input #12 RMP--4K +28 Vdc Disc Input+28 Vdc Discrete Input #13 RMP--6C +28 Vdc Disc Input+28 Vdc Discrete Input #14 RBP--2A +28 Vdc Disc Input+28 Vdc Discrete Input #15 RBP--2B +28 Vdc Disc Input+28 Vdc Discrete Input #16 RBP--2C +28 Vdc Disc Input+28 Vdc Discrete Input #17 RBP--2D +28 Vdc Disc Input+28 Vdc Discrete Input #18 RBP--2E +28 Vdc Disc Input+28 Vdc Discrete Input #19 RBP--2F +28 Vdc Disc Input+28 Vdc Discrete Input #20 RBP--2G +28 Vdc Disc InputTable 4--19. APM/ASDB Programmable Discrete OutputsDigital Signal Definition Pin # NotesGround Discrete Output #1 RTP--13B GND Disc Output 500mAGround Discrete Output #2 RTP--13C GND Disc Output 500mAGround Discrete Output #3 RTP--13D GND Disc Output 500mAGround Discrete Output #4 RTP--13E GND Disc Output 500mAGround Discrete Output #5 RTP--13F GND Disc Output 500mAGround Discrete Output #6 RTP--13G GND Disc Output 500mAGround Discrete Output #7 RTP--13H GND Disc Output 500mA
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--74Table 4--19. APM/ASDB Programmable Discrete Outputs(cont)Digital Signal Definition NotesPin #Ground Discrete Output #8 RTP--13J GND Disc Output 500mAGround Discrete Output #9 RTP--13K GND Disc Output 500mAGround Discrete Output #10 RTP--14A GND Disc Output 500mAGround Discrete Monitor Output #1 RTP--14B GND Disc Monitor 500mAGround Discrete Monitor Output #2 RTP--14C GND Disc Monitor 250mAGround Discrete Monitor Output #3 RTP--14D GND Disc Monitor 250mA(a) Discrete Input Ground/OpenT2CAS provides ground/open discrete inputs for aircraft level discrete interfaces.The GROUND and OPEN logic states are determined as follows:GROUND ≤3.5 Vdc at the input OR a resistance of less than 10 Ohms toground.OPEN ≥14.0 Vdc at the input OR a resistance of greater than 100k Ohms toground.The discrete inputs source 1.0 ±0.25 ma of current when the input is groundedand has diode isolation circuitry to prevent the inputs from being loaded toground when power is removed from the T2CAS.NOTE: When an input goes to a discrete on both TCAS and TAWS/RWS, theinput current is twice the specification for a single discrete.(b) Discrete Input +28 Vdc/OpenT2CAS provides +28 Vdc/open discrete inputs for aircraft level discreteinterfaces. The +28 Vdc and OPEN logic states are determined per thefollowing:+28 Vdc ≥14.0 Vdc at the input.OPEN ≤3.5 Vdc at the input OR a resistance of greater than 100k Ohms tothe positive voltage source.The discrete inputs sink 1.0 ±0.25 mA of current when a +27.5 Vdc input andhas diode isolation circuitry is applied to prevent the inputs from being loaded toground when power is removed from the T2CAS.NOTE: When an input goes to a discrete on both TCAS and TAWS/RWS, theinput current is twice the specification for a single discrete.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--75(c) Discrete Output Ground/Open 500 mAThe discrete outputs listed in this section pertain to ground/open discrete outputsfor the TAWS/RWS function.The discrete output in the GROUND logic state has an output voltage of ≤3.0Vdc when sinking 500 mA of current and an output voltage of ≤1.5 Vdc whensinking 100 mA of current.The discrete output in the OPEN logic state has an output impedance of ≥2.4MOhms to ground for voltages applied to the output of 0.0 to +33.0 Vdc and ≥100kOhms to ground for voltages applied to the output of +33.0 to +36.0 Vdc.The discrete output circuitry contains a monitor which detects if an over--currentcondition has occurred and is able to withstand a direct short to +28 Vdc for anindefinite period of time.Additionally, the discrete output circuitry contains a monitor which detects if theoutput voltage is incorrect for the driven state of the discrete output.D. TAWS/RWS Input Data SignalsThe T2CAS TAWS/RWS functions requires a minimum set of data that is needed toperform within the standard specifications (detailed in RTCA DO--161A [GPWS],TSO--C151a [TAWS] and TSO--C117a [RWS] ). This section contains the minimum set ofTAWS/RWS data signals and the information/guidelines that is needed by the installer toobtain the correct analog or digital signal on a specific aircraft. Since the TAWS/RWS I/Ofunction is very flexible, the installer must keep in mind that the data signal sources listedin this section are typical for the specified signal and that the I/O function can be modifiedvia the ASDB to accommodate other non--typical signal sources.The information in this section will include External Sensor Input accuracies for specificinputs to T2CAS GCAM function. These External Sensor accuracies must be met for thespecified inputs in order for the T2CAS to perform the TAWS/RWS functions. Inputs toT2CAS GCAM function consists of errors due to the external system sensor plusmeasurement errors within the T2CAS LRU. In addition, for analog inputs the internalT2CAS errors due to the hardware circuit are also considered.(1) Vertical Speed (Digital/Analog)The TAWS/RWS Vertical Speed parameter is updated from an Inertial, GPS or AirData Computer source. The IRS/GPS source can be any one of the following :ADIRS, GPIRS, IRS, AHRS, GPS and ADC.NOTE: When Vertical Speed is unavailable from an IRS or GPS source, thealternate variable Baro Altitude Rate will be used from an ADC source.The minimum External Sensor input accuracy accepted is 68 ft/min when GPS is thesource or 30 ft/min when IRS, ADIRS, AHRS or ADC (alternate Baro Altitude Ratevariable) is the source.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--76(a) Digital InputT2CAS accepts ARINC 429 Vertical Speed inputs from Inertial Systems, GPSSystems and Digital Air Data Systems (DADC).IRS systems supported: ARINC 705 Attitude Reference and Heading System(AHRS), ARINC 738 Air Data Inertial Reference System (ADIRS), and othernon--ARINC standard interfaces.GPS systems supported: ARINC 743 or ARINC 743A.DADC systems supported: ARINC 706 Air Data Computer (ADC), ARINC 738 AirData Inertial Reference System (ADIRS) and other non--ARINC standardinterfaces.(b) Analog InputThe electrical pin connection for the analog Altitude Rate is listed underTable 4--6 of the TAWS/RWS Non--Conigurable Pinout and Pin Descriptionsection.T2CAS can also process ARINC 575/595 analog DC Altitude Rate inputs. TheDC altitude rate input consists of a positive and negative reference voltage(nominally +12.0 Vdc) and a signal input which can range between the positiveand negative reference input.(2) Ground SpeedThe T2CAS Digital Ground Speed input parameter is updated from a GPS, FlightManagement Systems or Inertial source. GPS/FMS would be the primary source, anInertial source would only be used in the short--term during GPS drop--outs.GPS system supported: ARINC 743/743A.FMC system supported: ARINC 702 Flight Management System and othernon--ARINC standard interface.Inertial systems supported: ARINC 704 Inertial Reference System (IRS), ARINC 705Attitude Reference and Heading System (AHRS), ARINC 738 Air Data InertialReference System (ADIRS), ARINC 743A GPS and other non--ARINC standardinterfaces.The minimum External Sensor input accuracy accepted for Ground Speed is 2 Ktsfrom a primary source (GPS/FMS) and 12 Kts from a secondary (Inertial) source.(3) True Track AngleThe T2CAS Digital True Track Angle input parameter is updated from a GPS, FlightManagement Systems or Inertial source. GPS/FMS would be the primary source, anInertial source would only be used in the short--term during GPS drop--outs.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--77Inertial systems supported: ARINC 704 IRS, ARINC 705 AHRS, ARINC 738 ADIRS,and other non--ARINC standard interface.GPS system supported: ARINC 743/743A.FMC system supported: ARINC 702 Flight Management System and othernon--ARINC standard interface.The minimum External Sensor input accuracy accepted for True Track Angle is 1Degree from a primary source (GPS/FMS) and 5 Degrees from a secondary (Inertial)source.(4) Radio Altitude (Digital/Analog)T2CAS accepts up to 3 analog Radio Altitude inputs or 3 Digital ARINC 429 RadioAltitude inputs. Digital Radio Altitude Inputs 1 and 2 are shared with the TCASfunction.The external LRUs/External Sensors providing the data parameters must provide aninput to the T2CAS that is within the range of ±3 ft. or 4% from 0 to 500 ft. and 5%when above 500 ft.The electrical pin connections for the Digital/Analog Radio Altitude is listed underTable 4--6 of the TAWS/RWS Non--Configurable Pinout and Pin Description section.(a) Digital InputThe Table below shows the ARINC 429 digital interface characteristics for theARINC 707 radio altimeter system. Two of the ARINC 429 input busses(RADIO_ALTITUDE_1 and RADIO_ALTITUDE_2) are shared with the TCASARINC 429 Radio Altitude Inputs. The TAWS input circuitry is independent fromTCAS.Radio Altitude429 Label: 164 (Octal) Units: Feet Max Range: ±8,192 FeetAppox. LSB: 0.125 Data Bits: 1613(lsb) -- 28(msb)Sign Bit: 290=Up,1=DownPad Bits: 11, 12 Transmit Interval:25--50msData Type: Two’s ComplementBinary(b) Analog InputThe Analog Radio Altitude inputs are compatible with an ARINC 552 RadioAltimeter system and may have a number of different input formats as defined forspecific aircraft requirements. The external connector pins for Analog RadioAltitude Inputs #1 and #2 are shared by TCAS and TAWS/RWS, both haveindependent circuitry.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--78The following common mode and differential mode inputs signals are acceptedby the T2CAS with the voltage ranges defined:•(+) input common mode range --5.0 to +40.0 Vdc•(--) input common mode range --2.5 to +2.5 Vdc•Differential (+ to --) range --2.5 to +37.5 VdcNOTE: The maximum radio altitude input currently used in TCAS is +37.5 Vdcfor a metric system. The common mode ranges allow for a ±2.5 Vdcground voltage differential.The minimum input impedance on each pin is 95k Ohms relative to ground. Theminimum input impedance for inputs which are connected to both TCAS andTAWS/RWS will be one half the minimum number listed.(5) Flight Path AngleThe T2CAS Digital Flight Path Angle input parameter is updated from an Inertial,Flight Management or GPS source.Inertial systems supported: ARINC 704 IRS, ARINC 705 AHRS, ARINC 738 ADIRS,and other non--ARINC standard interface.FMC system supported: ARINC 702 Flight Management System and othernon--ARINC standard interface.GPS system supported: ARINC 743/743A.The minimum External Sensor input accuracy accepted for Flight Path Angle is 0.3Degrees.(6) Current Aircraft WeightThe T2CAS updates the Current Aircraft Weight from either an FMS or a Weight andBalance System source.FMC system supported: ARINC 702 Flight Management System and othernon--ARINC standard interface.The minimum External Sensor input accuracy accepted for Current Aircraft Weight is220 lbs. with 95% confidence.(7) Aircraft Position Latitude/LongitudeThe T2CAS Aircraft Position input parameter is updated from a GPS or FMS source.The GPS source can be any one of the following: GPIRS or GPS. In addition, an IRSsource can be used, but only for short periods of time during GPS or FMS drop--outsGPS system supported: ARINC 743/743A.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--79FMC system supported: ARINC 702 Flight Management System and othernon--ARINC standard interface.The minimum External Sensor input accuracies accepted for Aircraft Position are:•Phase I (Take Off) 1 nmi•Phase II (Outside Terminal or final area) 2 nmi•Phase III (Terminal area) 1 nmi•Phase IV (Final area) 0.5 nmi(8) Aircraft AltitudeThe T2CAS Aircraft Altitude input parameter is updated from an ADC or GPS source.The T2CAS uses (but is not limited to) the following altitude types: CorrectedBarometric Altitude, GPS Altitude -- MSL and Uncorrected Barometric Altitude.The minimum External Sensor input accuracy accepted for Aircraft Altitude is 95 feetwith 95% confidence.(9) Navigation AccuracyWhen using GPS or FMS data for aircraft position determination, the T2CAS usesthe available GPS or FMS signals to determine accuracy of the Position information..(a) GPSFor a GPS source, the minimum External Sensor input accuracy accepted is100m (333 feet) for an HDOP (Horizontal Dilution of Position) of 1.5 with S/A on.(b) FMSThe T2CAS determines the Navigation Accuracy parameter by using the RNPdata value if a valid RNP data is received AND a valid FMS Discrete Word isreceived with the Nav Mode set to ”High Accuracy”.For FMS Discrete Word -- Type 2, bit 15 indicates high or low navigationaccuracy and is set independently of the navigation mode, bits 16 -- 18. TheFMS sets bit 15 (high accuracy) if the estimated error of the FMS position is lessthan the phase of flight position accuracy tolerance listed in Table 4--20.Otherwise the FMS resets bit 15 (low accuracy).Table 4--20. Navigation AccuracyPhase of Flight Accuracy ToleranceApproach 0.5 nmTerminal 0.5 nmEnroute FMS not in DegradeOceanic FMS not in Degrade
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--80(10) Static Air TemperatureThe T2CAS Static Air Temperature parameter is updated from a Digital ADC or FMSsource.The minimum External Sensor input accuracy accepted for Static Air Temperature is4.5 Degrees C, with 95% confidence.(11) Roll AngleThe T2CAS Roll Angle parameter is updated from an Inertial Reference source(GPIRS, ADIRS, IRS and AHRS).For a T2CAS TAWS only system, the minimum External Sensor input accuracy forRoll Angle is 2 Degrees with 95% confidence.For T2CAS equipped with Windshear, the minimum External Sensor input accuracyRoll Angle is 0.5 Degrees with 95% confidence.(12) Computed AirspeedThe T2CAS Computed Airspeed input parameter is updated from an Air DataComputer source.The minimum External Sensor input accuracy accepted for Computed Airspeed is asfollows (with 95% confidence):•5kts@60kts•2 kts @ 100 kts•2 kts @ 200 kts•4 kts @ 450 kts(13) Selected Runway HeadingThe T2CAS Selected Runway Heading input parameter is updated using eitherSelected Runway Heading data OR Selected Course from one of the following LRUdata sources: ILS, MCP or FMS.The minimum External Sensor input accuracy accepted for Selected RunwayHeading is 2 Degrees.(14) Glideslope Deviation (Digital/Analog)The T2CAS Glideslope Deviation input parameter is updated using either GlideslopeDeviation data or MLS Elevation Deviation from one of the following LRU datasources: ILS, FMS, DFS, MLS or GPS.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--81The minimum External Sensor input accuracies accepted for Glideslope Deviationare as follows:•0.00455 for ddm < 0.0455•10% for ddm < 0.175•non--decreasing for ddm < 0.800(a) Analog ILS InputThe glideslope deviation input signal is defined in ARINC 547 and ARINC 578--4.This input accepts signals which have a common mode voltages of --5.0 V to+5.0 V, a differential voltages between pins of --2.5 V to +2.5 V and an inputimpedance relative to ground of greater than 1M Ohm on each pin.NOTE: The common mode ranges allow for a ±2.5 V ground voltage differential.NOTE: ARINC 547 ILS receivers have current mode outputs which drive 5meter movements in parallel, each with 1k Ohm impedance. The ILS iscalibrated to output the correct current into 5 -- 1k Ohm loads in parallel.Any additional impedance added to the circuit will cause an error in theoutput. A 1M Ohm input impedance will induce a 0.02% error. NewerARINC 578 ILS receivers have voltage mode outputs which are immuneto load variations.(15) Localizer Deviation (Digital/Analog)The T2CAS Localizer Deviation input parameter is updated using either LocalizerDeviation data OR MLS Azimuth Deviation from the following LRU data sources: ILS,FMS, DFS and MLS.The minimum External Sensor input accuracies accepted for Localizer Deviation areas follows:•0.00465 for ddm < 0.0465•10% for ddm < 0.155•20% for ddm < 0.310•non--decreasing for ddm < 0.400(a) Analog ILS InputSee Glideslope Deviation Analog ILS Input(16) Selected Decision HeightThe T2CAS Selected Decision Height input parameter is updated using one of thefollowing LRU data sources: EFIS, MCP or FMS.If the Decision Height is not available from one of the above LRU sources, theDecision Height will not be annunciated.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--82The minimum External Sensor input accuracy accepted for Selected Decision Heightis 1 foot.(17) Minimum Descent AltitudeThe T2CAS Minimum Descent Altitude input parameter is updated using one of thefollowing LRU data sources: EFIS, MCP or FMS.The minimum External Sensor input accuracy accepted for Minimum Descent Altitudeis 1 foot.(18) Body Longitudinal Acceleration (Digital/Analog)The Body Longitudinal Acceleration input parameter is only used on installationswhere T2CAS is performing the RWS function.The T2CAS Body Longitudinal Acceleration input parameter is updated from one ofthe following Inertial Reference sources: ADIRS, IRS or AHRS.The minimum External Sensor input accuracy accepted for Body LongitudinalAcceleration is 0.01 G with 95% confidence.(19) Body Normal Acceleration (Digital/Analog)The Body Normal Acceleration input parameter is only used on installations whereT2CAS is performing the RWS function.The T2CAS Body Normal Acceleration input parameter is updated from one of thefollowing Inertial Reference sources: ADIRS, IRS or AHRS.The minimum External Sensor input accuracy accepted is 0.01 G with 95%confidence.(20) Pitch AngleThe T2CAS Pitch Angle input parameter is updated from one of the following InertialReference sources: GPIRS, ADIRS, IRS or AHRS.For T2CAS equipped with Windshear, the minimum External Sensor input accuracyaccepted for Pitch Angle is 0.5 Degrees with 95% confidence.(21) Flap AngleThe T2CAS Flap Angle input parameter is updated with valid Flap Angle data fromone of the following LRUs: Flap Slat Electronic/Control Unit, Digital Stall WarningComputer (DSWC), Analog or Discrete.The minimum External Sensor input accuracy accepted for Flap Angle is 2.0 Degreeswith 95% confidence or the Discrete value setting.NOTE: Most aircraft types have discrete flap settings, where a range of angles orvoltages map into discrete flap settings. For example, 747--1/2/3 has 7 flapsettings with 40--50 degrees range per setting.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--83(22) Slat AngleThe Slat Angle input parameter is only used on installations where T2CAS isperforming the RWS function. Slat Angle data is updated from one of following LRUsources: Flap Slat Electronic/Control Unit, Digital Stall Warning Computer (DSWC),Analog or Discrete.The minimum External Sensor input accuracy accepted for Slat Angle is 2.0 Degreeswith 95% confidence or the Discrete value setting.NOTE: Most aircraft types have discrete Slat settings, where a range of angles orvoltages map into discrete Slat settings. For example, 747--1/2/3 has 7 slatsettings with 40--50 degrees range per setting.(23) True AirspeedThe True Airspeed input parameter is only used on installations where T2CAS isperforming the RWS function.The T2CAS True Air Speed input parameter is updated from one of the following AirData sources: ADIRS or ADC.The minimum External Sensor input accuracy accepted for True Airspeed is 4.0 ktswith 95% confidence.(24) Angle of Attack (AOA) Left/RightThe AOA input parameter is only used on installations where T2CAS is performingthe RWS function.The T2CAS AOA input parameter is updated from a Digital Stall Warning Computer ora Analog Left/Right Angle of Attack Vane source.The minimum External Sensor input accuracy accepted for AOA is 0.6 degrees with95% confidence.(25) Magnetic HeadingThe T2CAS Magnetic Heading input parameter is updated from one of the followingInertial Reference sources: ADIRS or IRS.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--84(26) True Display Orientation LeftThe T2CAS updates the True Display Orientation Left data based on Table 4--21.The minimum External Sensor input accuracy accepted for True Display OrientationLeft is the same as what is accepted for True Track Angle, True Heading or MagneticHeading.Table 4--21. True Display Orientation LeftIf Map Mode Orientation Left indicates: Then True Display Orientation Left =Track Up True Track AngleHeading Up True Heading OR (Magnetic Heading --Magnetic Variation)NorthUpOROther INVALID(27) True Display Orientation RightThe T2CAS updates the True Display Orientation Right data based on Table 4--22.The minimum External Sensor input accuracy accepted for True Display OrientationLeft is the same as what is accepted for True Track Angle, True Heading or MagneticHeading.Table 4--22. True Display Orientation RightIf Map Mode Orientation Right indicates: Then True Display Orientation Right =Track Up True Track AngleHeading Up True Heading OR (Magnetic Heading --Magnetic Variation)NorthUpOROther INVALID(28) Display Range Left/RightThe T2CAS Display Range input parameter is updated from the EFIS Control Panel.The range selections are dependant on the type of Display installed.The minimum External Sensor input accuracy accepted is 1.0 nmi.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--85E. TAWS/RWS Discrete InputsThe specifics of the following discrete (e.g. ground/open, +28 Vdc/open, definition ofopen/ground states, etc.) are aircraft dependant and will be defined in the ASDB.(1) Landing Gear DownThe Landing Gear Down input Discrete is used on installations where T2CAS isperforming both the TAWS and RWS functions.This Discrete input is shared between the TCAS and TAWS functions with separateinternal wiring. The T2CAS computer unit monitors this discrete to update the landinggear position.(2) Landing FlapThe Landing Flap Discrete input is used for GPWS Mode 2, GPWS Mode 4 andWindshear Caution/Warning Calculations.This discrete indicates whether or not the Flaps are in the correct position for aircraftlanding.(3) Terrain InhibitWhen the Terrain Inhibit switch is engaged, all TAWS aural and visual alerts areinhibited. The Auto Pop--up feature, being based on these alerts, is suppressed aswell. The terrain image, if selected for display, is removed and a ”TERRAININHIBITED” message is displayed. This inhibit feature is typically used to avoidnuisance alerts during operation around airports that are not in the terrain database,or during approach under VFR conditions at airports in close proximity to terrainfeatures. The Terrain Inhibit must be manually de--selected.(4) Steep ApproachThe Steep Approach Discrete input enables Mode 1 Steep Approach alert biasing.This discrete is typically enabled by an Autopilot Flight Deck switch and is used toreduce nuisance alerts during aircraft steep approach landings.(5) Glideslope InhibitThe Glideslope Inhibit Discrete input is used to inhibit Mode 5 Glideslope alerting.This discrete would typically be enabled by a Flight Deck switch during back--courseapproaches (see ILS Back--Course).(6) Glideslope CancelThe Glideslope Cancel Discrete input is typically a Flight Deck switch that is used tocancel Glideslope alerting when an unreliable Glideslope is expected or whenmaneuvering is required during ILS final approach.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--86(7) Decision Height /Minimum Descent Altitude Selection (DH/MDA)The DH/MDA Discrete input is used select either the Decision Height or MinimumDescent Altitude input. The selected DH or MDA is used to determine AltitudeCall--Outs.(8) Below Decision HeightThe Below Decision Height Discrete input is to trigger Altitude Call--Outs.(9) Aircraft On GroundThe Aircraft On Ground Discrete input is shared between the TCAS and TAWSfunctions with separate internal wiring.(10) ILS Back CourseThe ILS Back Course Discrete input is used to indicate that a back--course landingapproach has been selected/detected.A back--course approach is a landing approach in which the localizer signal lobeshave been reversed. Typically the back--course switch is selected on the Auto--Pilotcontrol panel and will compensate for the reversal of the localizer radio beams.Additionally, when Back--Course is selected, the Glideslope radio beams becomeinvalid )resulting in the Glideslope Inhibit discrete being set).(11) Altitude Callout DisableThe Altitude Callout Disable Discrete input is used to disable all altitude call--outs.(12) Engine OutWhen set, the Engine Out discrete indicates that one or more aircraft engines isinoperative. The Engine Out data is used as part of the aircraft performancecalculations during a TAWS or Windshear event.F. TAWS/RWS Digital Output Data(1) GCAM Event DataThe T2CAS TAWS/Windshear events are caused by terrain and weather conditions.An event begins when a terrain or weather condition causes the T2CAS to declare aTAWS/Windshear caution or warning alert or when the aircraft telemetry causes aBank Angle Callout. This data is set at each apparition of alert (caution or warning)and contains information about the triggering event. The T2CAS then transmits theGCAM Event Data over one of the programmable ARINC 429 output Buses inTable 4--14.Table 4--23 shows the GCAM Event Data Labels transmitted on the A429 output Bus.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--87Table 4--23. A429 Output Bus GCAM Event Data LabelsLabel Number Data Name100 Vertical speed101 Ground speed102 True Track Angle103 Radio Altitude104 Flight Path Angle105 Current aircraft weight106 Latitude107 Longitude110 Altitude111 Navigation accuracy112 Static Air temperature113 Roll Angle114 Computed Air Speed115 Selected Runway Heading116 Glide slope deviation117 Localizer deviation120 Body axis longitudinal acceleration121 Body axis normal acceleration122 Pitch angle123 Flap angle124 Slat angle125 Baro Altitude Rate126 True airspeed127 Body Angle of attack left130 Body Angle of attack right131 True Display Orientation #1132 True Display Orientation #2133 Display Range #1134 Display Range #2
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--88Table 4--23. A429 Output Bus GCAM Event Data Labels(cont)Label Number Data Name270 Gear in Landing(Discrete Data) Flaps in LandingTerrain InhibitGPWS InhibitSteep approachGlideslope InhibitGlideslope cancelDH/MDA SelectionBelow Decision HeightILS BackcourseEngine outCallout disableAircraft on groundWarm StartFlight Phase read at warm startGCAM flight Phase(2) GCAM DataThe GCAM Data output relays information about the GCAM, which is set at eachcomputation cycle.(3) GCAM General PurposeThe GCAM General Purpose output relays information about the GCAM as set in theAPM.(4) Terrain Awareness Display OutputTerrain Awareness Display Images are transmitted to the display using the ARINC708A format.NOTE: Although Draft characteristic ARINC 453 is engrained in industryterminology, ARINC 453 was never adopted as a characteristic. ARINC 453has been superceded and included into the ARINC 708A characteristic.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--89The ARINC 708A formatted terrain display is transmitted as a series of 1600--bitwords, each word containing color information along a specific angle radial. Therefresh rate of the entire image is based on the number of radials transmitted. Atransmission interval of 5.00 milliseconds per radial with a total of 513 radials perimage results in an image refresh interval of 2.565 seconds with an acceptable levelof image clarity.(5) OMS Fault Summary WordThe T2CAS transmits the OMS information (overall fault bit, status of all ARINC 429digital input buses, and status of all BITE tests) listed in Table 4--24, Table 4--25 andTable 4--26, OMS Fault Summary Words.OMS Fault Summary Discrete Word429 Label: 350, 351, and352 (Octal)Units: N/A Max Range: N/AAppox. LSB: N/A Data Bits: 1911 -- 29Sign Bit: NonePad Bits: None Transmit Interval: 100ms Data Type: DiscreteTable 4--24. OMS Label 350 DiscretesBit FUNCTION DESCRIPTION11 TAWS Fail (overall fault bit) 0 = Normal, 1 = Fail12 ARINC 429 Input #1 Fail 0 = Normal, 1 = Fail13 ARINC 429 Input #2 Fail 0 = Normal, 1 = Fail14 ARINC 429 Input #3 Fail 0 = Normal, 1 = Fail15 ARINC 429 Input #4 Fail 0 = Normal, 1 = Fail16 ARINC 429 Input #5 Fail 0 = Normal, 1 = Fail17 ARINC 429 Input #6 Fail 0 = Normal, 1 = Fail18 ARINC 429 Input #7 Fail 0 = Normal, 1 = Fail19 ARINC 429 Input #8 Fail 0 = Normal, 1 = Fail20 ARINC 429 Input #9 Fail 0 = Normal, 1 = Fail21 ARINC 429 Input #10 Fail 0 = Normal, 1 = Fail22 ARINC 429 Input #11 Fail 0 = Normal, 1 = Fail23 ARINC 429 Input #12 Fail 0 = Normal, 1 = Fail24 ARINC 429 Input #13 Fail 0 = Normal, 1 = Fail25 ARINC 429 Input #14 Fail 0 = Normal, 1 = Fail
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--90Table 4--24. OMS Label 350 Discretes(cont)Bit DESCRIPTIONFUNCTION26 ARINC 429 Input #15 Fail 0 = Normal, 1 = Fail27 ARINC 429 Input #16 Fail 0 = Normal, 1 = Fail28 ARINC 429 Input #17 Fail 0 = Normal, 1 = Fail29 ARINC 429 Input #18 Fail 0 = Normal, 1 = FailTable 4--25. OMS Label 351 DiscretesBit FUNCTION DESCRIPTION11 A/D Converter and AnalogMultiplexer Monitor0 = Normal, 1 = Fail12 Analog LRU Input Monitor 0 = Normal, 1 = Fail13 APM Test 0 = Normal, 1 = Fail14 APM Monitor 0 = Normal, 1 = Fail15 ARINC 429 Input Bus Monitor 0 = Normal, 1 = Fail16 ARINC 429 Receiver Loop Back Test 0 = Normal, 1 = Fail17 ARINC 429 Transmitter Monitor 0 = Normal, 1 = Fail18 ARINC 453 Transmitter Monitor 0 = Normal, 1 = Fail19 Compact Flash Data Loader Test 0 = Normal, 1 = Fail20 CPLD Register Test 0 = Normal, 1 = Fail21 Discrete Outputs Monitor 0 = Normal, 1 = Fail22 EDC Monitor 0 = Normal, 1 = Fail23 EEPROM Monitor 0 = Normal, 1 = Fail24 Exception Interrupt Monitor 0 = Normal, 1 = Fail25 External Interrupt Controller Test 0 = Normal, 1 = Fail26 Flash EPROM Test/Monitor 0 = Normal, 1 = Fail27 FPGA Program Test 0 = Normal, 1 = Fail28 HBM Test 0 = Normal, 1 = Fail29 HBM Monitor 0 = Normal, 1 = Fail
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--91Table 4--26. OMS Label 352 DiscretesBit FUNCTION DESCRIPTION11 MMU Partition Test 0 = Normal, 1 = Fail12 Over--Temperature Monitor 0 = Normal, 1 = Fail13 PCI Bus Monitor 0 = Normal, 1 = Fail14 PCI Bus Configuration Test 0 = Normal, 1 = Fail15 Power Fail Monitor 0 = Normal, 1 = Fail16 Power Supply Monitor 0 = Normal, 1 = Fail17 SDRAM Flash Copy Monitor 0 = Normal, 1 = Fail18 SDRAM/EDC Test 0 = Normal, 1 = Fail19 Software Event Log 0 = Normal, 1 = Fail20 Software Heartbeat Monitor 0 = Normal, 1 = Fail21--29 Spare 0 = Normal, 1 = FailG. TAWS/RWS Discrete Output Data(1) Ground Discrete ParametersThis section describes the T2CAS TAWS/RWS ground discrete outputs. The grounddiscrete outputs are used to drive alert lamps and are not activated when power isremoved from the LRU. All Ground discretes in this section are dependant on theaircraft Flight Deck configuration and subsequent ASDB settings.(a) Alert Prioritization Output 1 -- 4These discretes exist to inform external LRUs that T2CAS has a higher priorityalert. For example, on the input side, if the Alert Prioritization Input 2 Value was’5’ and the Alert Prioritization Input 2 Discrete became active because anengine--out condition was detected, the T2CAS would suppress all of its alerts oflower priority but still allow output alerts of priority 1 through 4. On the outputside, the T2CAS would set only the Alert Prioritization Output # discretes toactive whose corresponding values are of lower priority than the alert. OtherLRUs capable of sensing the states of these discretes would suppress their ownalerts of lower priority.(b) Audio OnThe Audio On output discrete is used to inhibit other audio systems (e.g., TCAS)during GPWS warnings. In addition, it can be used to drive the audio key lineinput provided on some aircraft audio systems.The Audio On discrete is activated whenever any aural message is beingannunciated and it remains activated until the aural message is completed.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--92(c) Glideslope Cancel IndicatorThe Glideslope Cancel Indicator output discrete is activated when the T2CASdetects the Glideslope Cancel input discrete is active AND the aircraft is at a lowaltitude (below 2000 ft. radio altitude).(d) Ground Proximity Caution AlertUsed to activate the GPWS Caution Alert lamp.(e) Ground Proximity Warning AlertUsed to activate the GPWS Warning Alert lamp.(f) TAWS Caution AlertUsed to activate the TAWS Caution Alert lamp.(g) TAWS Warning AlertUsed to activate the TAWS Warning Alert lamp.(h) Terrain Mode Display #1/Terrain Mode Display #2The Terrain Display Switch output discretes are used to activate external relaysthat make the switch between Weather and Terrain. When the relay is activated(IO_TERRAIN_DISPLAY_SWITCH_# is Active), Terrain is displayed. When therelay is de--activated (IO_TERRAIN_DISPLAY_SWITCH_# is Not Active),Weather is displayed.This output discrete can be activated/de--activated by one of two methods: Pilotselection via a control panel pushbutton, or as a result of the auto pop--upfeature. In the event that the TAWS function generates an alert, terrain isautomatically selected for display.(i) Windshear Caution AlertUsed to activate the Windshear Caution Alert lamp.(j) Windshear Warning AlertUsed to activate the Windshear Warning Alert lamp.(2) Ground Discrete Monitor ParametersThis section describes the T2CAS TAWS/RWS ground discrete monitor outputs. Theground discrete monitor outputs are used to signal failure conditions and areactivated (grounded) when power is removed from the LRU.(a) GCAM Fail IndicatorUsed to activate the GCAM Fail lamp.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--93(b) GCAM Inop IndicatorUsed to activate the GCAM Inop lamp.(c) GPWS Fail IndicatorUsed to activate the GPWS Fail lamp.(d) GPWS Inop IndicatorUsed to activate the GPWS Inop lamp.(e) Terrain Fail IndicatorUsed to activate the Terrain Fail lamp.(f) Terrain Inop IndicatorUsed to activate the Terrain Inop lamp.(g) Windshear Fail IndicatorUsed to activate the Windshear Fail lamp.(h) Windshear Inop IndicatorUsed to activate the Windshear Inop lamp.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.4--94Blank Page
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.5--1ADJUSTMENT/TEST1. GeneralThe procedures that follow are designed to check for proper operation and satisfactoryinstallation of the T2CAS Traffic and Terrain Collision Avoidance System components.Should any failures occur while performing the check out procedures, refer to FAULTISOLATION as required.2. EquipmentSee Table 5--1 for equipment required to test the unit.Table 5--1. EquipmentName Description SourceDigital Multimeter Fluke Model 29 DigitalMultimeterJohn Fluke Mfg Co Inc.,Everett, WATCAS Ramp Tester TCAS--201 Reply GeneratorTraffic Alert and CollisionAvoidance System Test SetIFR Systems, Inc.Wichita, KSNOTE: Equivalent alternatives are permitted for equipment in this list.3. Initial Harness Checkout (New Installations Only)A. T2CAS Computer Unit Harness CheckoutCheck the T2CAS computer unit’s mounting tray connector pins referenced in Table 5--2,to make sure they are not connected or shorted to ground. A ground on these pins cancause damage or degrade system performance.Table 5--2. Computer Unit Harness CheckoutConnector Pin No. Pin FunctionP1C--1 (LBP) 115 V AC (H) T2CASP1C--5 (LBP) 115 V AC (H) External FanP1C--10 (LBP) 28 V AC T2CAS PowerB. T2CAS Controller and Display Unit Harness CheckoutRefer to the applicable controller and display unit interconnect diagrams to do continuitymeasurements and to ensure confidence in wiring for these units.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.5--2C. LRU Preinstallation Power CheckoutBefore you do any operational tests, a power--on check is recommended to reduce thepossibility of damage to newly installed system components due to miswired power leads.(1) Make sure all T2CAS system components are removed from their mounting trays orthat their aircraft mating connector(s) are disconnected.(2) Connect external power to aircraft.(3) Close all T2CAS system 115 V, 400 Hz circuit breakers, if applicable, and check for115 V ac at the appropriate LRU mating connector pins. Refer to the applicableinterconnect diagrams for LRU pin numbers.(4) Close all T2CAS system 28 V dc circuit breakers, if applicable, and check for 28 V dcat the appropriate LRU mating connector pins. Refer to the applicable interconnectdiagrams for LRU pin numbers.(5) If power is misapplied on any connector pin, open the circuit breaker and reworkmiswired harness.(6) Remove aircraft power.D. Initial System Installation Operational TestThe initial checkout of a newly installed system should start with a system self--test andthen be followed by a ramp test. The system self--test procedures are referenced inparagraph 4.A. The ramp tests should include a Scenario Test and a Power andFrequency Test. Refer to the applicable TCAS Ramp Tester Operation Manual forprocedures to do these tests.If an ACSS VSI/TRA is used as the display instrument, it contains a feature that displayssome typical installation errors. See Figure 5--1. If an error is detected during initialinstallation checkout, the VSI/TRA displays the error as follows:(1) Removes all symbology from the display.(2) Displays a red Xthat covers the entire screen.(3) Displays a two digit error code as follows:•00 = Invalid discrete setting at power--up•01 = Invalid light curve setting specified at power--up•03 = Bad checksum detected at power--up•04 = Illegal op--code test failed•05 = Unsupported test failed.(4) Strobes the watchdog timer to keep the red Xand status displayed.NOTE: If the VSI/TRA displays error code 10, 11, 12, 29, 30, 31, or 40, an internalVSI/TRA failure has been detected.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.5--3Figure 5--1. VSI/TRA Fault Warning Display4. System Self--TestsA. TCAS Flight Deck Display Test ModesThe T2CAS TCAS System provides two types of test modes; a short functional test modeand an extended maintenance test. Both test modes can be activated by the TESTbutton or switch on the ATC/TCAS Control Panel. The short test mode can also beactivated by a central maintenance computer (CMC) or a central fault display interfaceunit (CFDIU). The extended test mode can only be initiated at the end of the short test.The short test mode is inhibited in the air if the Self--Test Inhibit programming pin(RBP--8E) is grounded.(1) Short Test ModeThe short test mode provides a flight deck initiated functional test of the TCAS RAand TA displays and associated TCAS interfaces. It also provides an auralannunciation of the TCAS system status.The short test mode is available in all TCAS operational modes (Standby, TA Only, orTA/RA) when on the ground. If a TA or RA occurs while airborne, the test isterminated and normal operating status is resumed. The test mode is alsoterminated if any of the Advisory Inhibit discrete inputs (grounds) are received on pinsRBP--5A, RBP--5B, RBP--5C, or RBP--5D.Push and hold the TEST button/switch on the ATC/TCAS controller for a few secondsto start the test. When the test mode becomes active, the words “TCAS Test” aretransmitted once aurally. In addition to the TCAS test pattern, RA indications and ared TCAS TEST annunciation are displayed on the applicable display(s). Refer toFigure 1--18 for a typical test pattern display on the VSI/TRA.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.5--4At the completion of the test (8--seconds), the words “TCAS Test Pass” should betransmitted once aurally. In addition, the test pattern is removed from the display(s)and a TCAS PASS annunciation is displayed. If the test fails, the words “TCAS TestFail” are transmitted once aurally and a TCAS FAIL annunciation is displayed on theapplicable display(s).If the TCAS short test fails, do the TCAS Computer Unit Self--Test proceduresreferenced in paragraph 4.C. to determine which LRU or subsystem is not functioningproperly. To troubleshoot the system, refer to the procedures in the FAULTISOLATION section.(2) Extended Test ModeThe extended test mode provides a flight deck initiated test that displays variouspages of text information that is selected by the ATC Mode S control panel 4096code switches. This test mode is accessible only when on the ground and cannot beinitiated while airborne.The extended test mode is used for maintenance purposes only. It displays variouspages of text information containing the TCAS software part number, fault messages,status of program pins, analog and digital inputs, and other aircraft parameters.To start the test, push and hold the TEST button/switch on the ATC/TCAS controllerfor a minimum of 9 seconds. In addition the conditions that follow must occur:•TCAS is in Standby•The selected transponder is in Standby•Aircraft is on the ground (The AIR/GND discrete [RMP--5K] is grounded)•Landing gear is extended (Landing Gear discrete [RMP--13F] is grounded).Once the extended test mode is established, the 4096 code switches on theATC/TCAS controller are used to select the desired maintenance page for display.Table 5--3 lists the extended mode page names and numbers and the corresponding4096 Ident Code number.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.5--5Table 5--3. Extended Test Menu Selections4096 Ident Code Number Page Page Name0000 0System Status0001 1Display Status0002 2Rad/Alt Status0003 3Xpdr Status0004 4Program Pins 1/30005 5Program Pins 2/30006 6Program Pins 3/30007 7Help Reference0011 11 Antenna Port Status0012 12 Option Pins StatusAll Other Codes Blank TCAS Test MenuTo view the TCAS test menu and system status pages along with the troubleshootingmessages, refer to the FAULT ISOLATION section.To exit the extended test mode, set the ATC/TCAS mode selector switch to Mode SON.B. TAWS/RWS Flight Deck Display Test ModesThe T2CAS TAWS/RWS System provides two types of test modes; a standard functionaltest mode and an extended maintenance test. Both test modes can be activated by theTAWS/RWS/GPS TEST button or switch on the Flight Deck. The short test mode canalso be activated by a central maintenance computer (CMC) or a central fault displayinterface unit (CFDIU). The extended test mode can only be initiated at the end of theshort test.(1) Standard Test ModeThe standard test mode provides a flight deck initiated functional test of the auralannunciations, lamp tests, and display activity.The Standard Self--Test is performed by activating either the CMC self--test or theself--test discrete input (RTP--10E = GND). The Standard Self--Test can occur whileon the ground or while in the airborne state.Upon activating the Standard Self--Test the following will occur:The Standard Self--Test will not be initiated if a TAWS alert is present when eitherthe CMC self test or the self test discrete input is activated.If the T2CAS unit has the windshear function enabled, the following auralannunciation will occur:
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.5--6”TERRAIN AWARENESS AND WINDSHEAR TEST START”If the T2CAS unit does not have the windshear function enabled, the followingaural annunciation will occur:”TERRAIN AWARENESS TEST START”During the Standard Self--Test the following will occur:All discrete outputs implemented within a specific aircraft installation will betested for over current and output voltage levels by activating the output for 1.5seconds (±100 milliseconds), then deactivating the output for 1.5 seconds (±100milliseconds), and then reactivating the output for 1.5 seconds (±100milliseconds). Any faults found will be recorded in the T2CAS unit’s nonvolatilememory.The T2CAS unit will verify the following functional areas in accordance withFigure 1--32.•Aircraft Personality Module (APM)•Terrain Database CRC•External System Inputs•Internal TAWS Parameters•Internal GPS Parameters (if installed)The T2CAS unit will display a multicolor test pattern on both the captain’s and firstofficer’s TAWS displays. Figure 1--33 shows a typical multicolor test pattern.The T2CAS unit will interrupt the Standard Self--Test when any of the following alertsoccur:•“WINDSHEAR, WINDSHEAR, WINDSHEAR”•“TERRAIN AHEAD, PULL UP”•“TERRAIN TERRAIN, PULL UP PULL UP”•“≈≈ PULL UP”•“TERRAIN AHEAD”•“TERRAIN CAUTION”•“AVOID TERRAIN”•“PULL UP, PULL UP”•“TERRAIN, TERRAIN”•“SINK RATE, SINK RATE”•“DON’T SINK, DON’T SINK”•“TOO LOW, TERRAIN”
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.5--7•“TOO LOW, GEAR”•“TOO LOW, FLAPS”•“GLIDESLOPE”NOTE: “≈≈” designates a pair of varying tones from 400 to 800 Hz; where eachtone is 0.3 seconds in duration, separated by 0.1 seconds, and at the end ofthe pair there is 0.1 seconds of silence.NOTE: The aural annunciations listed above will depend on the Operator SelectableOptions chosen during installation of the T2CAS unit.Upon completion of the Standard Self--Test the following will occur:If the T2CAS unit has the windshear function enabled and the APM and TerrainDatabase and Internal system and Internal GPS self--tests have passed, thefollowing aural annunciation will occur:”TERRAIN AWARENESS AND WINDSHEAR TEST PASSED”If the T2CAS unit does not have the windshear function enabled and the APMand Terrain Database and Internal system and Internal GPS self--tests havepassed, the following aural annunciation will occur:”TERRAIN AWARENESS TEST PASSED”If the T2CAS unit does not have the windshear function enabled and the APM orTerrain Database or Internal system or Internal GPS self--tests have failed, thefollowing aural annunciation will occur:”TERRAIN AWARENESS AND WINDSHEAR TEST COMPLETE”If the T2CAS unit does not have the windshear function enabled and the APM orTerrain Database or Internal system or Internal GPS self--tests have failed, thefollowing aural annunciation will occur:”TERRAIN AWARENESS TEST COMPLETE”If the TAWS/RWS standard test fails, do the T2CAS Computer Unit Self--Testprocedures referenced in paragraph 4.C. to determine which LRU or subsystem isnot functioning properly. To troubleshoot the system, refer to the procedures in theFAULT ISOLATION section.(2) Extended Test ModeThe Extended Self--Test can only be entered at the completion of the StandardSelf--Test. The Extended Self--Test can only be entered while on the ground(RMP--5K = GND). The Extended Self--Test is activated at the end of the StandardSelf--Test by activating the self--test discrete input (RTP--10E = GND) for a minimumof 3 seconds within 3 seconds after the initial aural annunciation (”TERRAINAWARENESS AND WINDSHEAR TEST COMPLETE” or ”TERRAIN AWARENESSTEST COMPLETE ” or ”TERRAIN AWARENESS AND WINDSHEAR TEST PASSED”or ”TERRAIN AWARENESS TEST PASSED”) occurs. This activation sequence issummarizedinFigure5--2.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.5--8Figure 5--2. Extended Self--Test of TAWS/Windshear Functional Areas
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.5--9Upon activating the Extended Self--Test the T2CAS unit will display the ExtendedSelf--Test Introduction page on both the captain’s and first officer’s TAWS displays.While in the Extended Self--Test:(a) The T2CAS unit will display the next Extended Self--Test page when the self--testdiscrete input (RTP--10E) is active for less than or equal to three seconds.(b) Each subsequent activation of the self--test discrete input will result in the T2CASunit displaying the next Extended Self--Test page.(c) The following is a listing of Extended Self--Test information pages available fordisplay:Information Displayed PagesIntroduction 0, 1Part Numbers 2, 3, 4, 5, 6The T2CAS unit will exit the Extended Self--Test when the self--test discrete input(RTP--10E) is active for greater than three seconds or the aircraft transitions fromground to air (RMP--5K = OPEN).C. T2CAS Computer Unit Self--TestThe Front Panel has a test switch to initiate testing of T2CAS as well as LED indicatorswhich are used for the annunciation of internal LRU or external system faults for T2CAS.There are two sets of LED indicators, one set pertains to the TCAS function and TCASexternal I/O; the other set pertains to the TAWS/RWS and internal GPS functions.The testing for T2CAS is initiated through the test switch on the front of the LRU. TCASand TAWS/RWS functions both monitor the switch and initiate a test sequence when theswitch is pressed. The test results for both functions are annunciated on their respectiveLED displays.(1) With all power off, reinstall the T2CAS computer unit in its mounting tray. Make surethe TCAS control panel and display(s) are also installed.(2) Apply aircraft power and close all applicable T2CAS system circuit breakers.(3) On the TCAS control panel, set the ATC/TCAS controller mode switch to Mode S ON.(4) Push the PUSH TO TEST button on the T2CAS computer unit front panel. TheTCAS and TAWS/RWS test sequence that follows should occur:•All TCAS computer unit front panel annunciators come on for a 3--second lamptest.•If the TCAS is operational, the TCAS PASS green annunciator comes on for a10--second display period and then goes off.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.5--10•If the TCAS is not operational, one or more of the red fault annunciators comes onfor a 10--second display period.•For TAWS/RWS, an LED test will occur where all LEDs, on the T2CAS unit, will belit for a minimum of 1.5 seconds in the following colors:-- TAWS P/F STATUS: Red-- TAWS I/O FAIL: Amber-- TAWS APM FAIL: Amber-- XFER IN PROCESS: Green-- C/F LOAD STATUS: Red•For TAWS/RWS, an LED test will occur where all LEDs, on the T2CAS unit, willthen be lit for a minimum of 1.5 seconds in the following colors:-- TAWS P/F STATUS: Green-- TAWS I/O FAIL: Amber-- TAWS APM FAIL: Amber-- XFER IN PROCESS: Green-- C/F LOAD STATUS: Green•During the TAWS/RWS LED test, the last 10 flight legs will be reviewed for faults.After the LEDs are illuminated, as described above, if a fault has occurred duringthe last 10 flight legs then the LED associated with that fault will be lit for 11seconds ±1 second in the following colors:-- TAWS P/F STATUS: Red-- TAWS I/O FAIL: Amber-- TAWS APM FAIL: Amber-- XFER IN PROCESS: ---- C/F LOAD STATUS: Red•During the TAWS/RWS LED test, all discrete outputs implemented within a specificaircraft installation will be tested for over current and output voltage levels byactivating the output for 1.5 seconds (±100 milliseconds), then deactivating theoutput for 1.5 seconds (±100 milliseconds), and then reactivating the output for 1.5seconds (±100 milliseconds). Any faults found will be recorded in the T2CASunit’s nonvolatile memory. At the end of this test the XFER IN PROCESS LED willbe extinguished.During the TAWS/RWS LED test, each time the push to test button (on the T2CASunit) is reactivated, the following will occur in the order presented:(a) All front TAWS/Windshear LEDs will be lit for 1 second (±0.5 seconds) in thefollowing colors:•TAWS P/F STATUS: Red•TAWS I/O FAIL: Amber
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.5--11•TAWS APM FAIL: Amber•XFER IN PROCESS: Green•C/F LOAD STATUS: Red(b) The XFER IN PROCESS LED and C/F LOAD STATUS LED will be extinguished.(c) The TAWS P/F STATUS, TAWS IO FAIL, TAWS APM FAIL and C/F LOADSTATUS LEDs will be set for the fault information of the current and previousflight legs for a period of 11 seconds ( ±1 second). The first time the push to testbutton, on the T2CAS unit, is depressed the current flight leg information isdisplayed. Subsequent activations of the push to test button, on the T2CAS unit,will display faults from previous flight legs in order from most recent to leastrecent.(d) If the push to test button, on the T2CAS unit, is reactivated during the display ofthe tenth previous flight leg fault information (or during the display of the oldestflight leg stored in the BITE log), then the LEDs, on the T2CAS unit, will flash at 2Hz for 3 seconds and then extinguish, terminating the display mode.(5) If a TCAS or TAWS/RWS fault is detected, refer to the Fault Isolation section fortroubleshooting information.5. Return to Service TestAnytimeaT2CAS LRU is removed and replaced following repair or maintenance, a return toservice test is required. The System Self--Test procedures referenced in paragraph 4.A. and4.B. are sufficient to check all system parameters.NOTE:Anytime the T2CAS APM is removed and replaced, the APM must be reconfiguredusing the procedures in section 6.C. or 6.D.6. Operational Software Loading Using an ARINC Portable Data Loader,RS232 Port or Compact Flash CardWhen updating the TT--950/951/952 Computer Unit with an ARINC portable data loader PDLor Compact flash card, verify the current TT--950/951/952 Computer Unit software partnumber prior to continuing for Flight Deck system only.NOTE:The TCAS operational software can ONLY be loaded using a conventional ADL/PDLdataloader and the TAWS/RWS operational software and Database can ONLY beloaded using the Compact flash card. Additionally, the TAWS/RWS APMConfiguration Data (referred to as ACD) and APM Application Data (referred to asAircraft Specific Database or ASDB) can be dataloaded using either a Compact Flashcard or through the RS232 interface.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.5--12A. Current Software VerificationNOTE: Software verification using Flight Deck systems ONLY.(1) TCAS Software VerificationVerify the current software part number according to the extended maintenancecapabilities on status page code 0000 in the FAULT ISOLATION section of thismanual or the individual aircraft maintenance manual (refer to the onboardmaintenance system program).(2) TAWS/RWS Software VerificationVerify the current software part number according to the extended maintenancecapabilities Part Number Page.B. Portable Data Loader -- TCAS Operational Software Loading (While Installed onAircraft)(1) Verify that the system inputs for AIR/GROUND (RMP--5K) and GEAR UP/DOWN(RMP--13F) are grounded.(2) Obtain an ARINC PDL and the appropriate interface cable for connecting the dataloader to the J1 (front) connector of the TT--950/951/952 Computer Unit.The following PDLs have been tested and found to be satisfactory for performing thistask:•DEMO Systems -- Part No. 30100 (Revision A and later versions)•Teledyne -- Part No. 2230915--01--D•SFIM -- Part No. YV68A110.Other part numbers from these suppliers and ARINC 615 data loaders from othermanufacturers may perform the task successfully. However, ACSS can not verifytheir usability.(3) Shut off the PDL and remove power from the TT--950/951/952 Computer Unit.Connect the cable between the PDL and the J1 front connector on theTT--950/951/952 Computer Unit.(4) Apply power to the TT--950/951/952 Computer Unit.(5) Turn on the PDL.(6) Obtain the operational software. Insert disk No. 1 of the operational software into thePDL for program uploading (or follow the applicable instructions for the PDL).(7) After the PDL indicates that the disk upload was successful, repeat step (6) formultiple disks, if necessary.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.5--13(8) Wait at least 20 seconds after the last disk has finished uploading. Then turn off thePDL, remove power from the TT--950/951/952 Computer Unit, and disconnect theinterface cable.(9) Apply power to the TT--950/951/952 Computer Unit and ensure the TCAS system isfully operational. Push the PUSH TO TEST button located on the front panel. Thegreen LED indicator on the front of the panel lights at the end of the test cycle(approximately 8 seconds) to show the TCAS system is functional.C. Compact Flash Card -- TAWS/RWS Operational Software/ACD/ASDB Loading(While Installed on Aircraft)Due to the size of the TAWS/RWS operational software and database (in excess of 60megabytes), the use of an ARINC 615 data loader is not feasible for TAWS/RWSdataloading. As such, a high speed data loading method is provided using a CompactPC Flash Card. The unit’s front panel has an access plate that allows a Compact PCFlash Card to be inserted.(1) Verify that the system inputs for AIR/GROUND (RMP--5K) and GEAR UP/DOWN(RMP--13F) are grounded.(2) Obtain the operational software and/or applicable TAWS/ACD/ASDB Database(3) Apply power to the TT--950/951/952 Computer Unit.(4) Insert the Compact Flash CardNOTE: When a Compact Flash Card is inserted the T2CAS will blink the front panel”XFER IN PROCESS” LED to indicate that a Compact Flash Card isdetected, but uploading or downloading has not begun.(5) Once Software Upload has started the Dataload status will be indicated by the LEDson the front of the T2CAS Computer Unit. The LED correlations expected for thevarious upload events are shown in Table 5--4.(6) After Uploading has completed (Green CF Status LED), remove the Compact FlashCard and the T2CAS will automatically restart.Table 5--4. Compact Flash Upload / LED correlationTriggering Event CF Status LEDXFER INPROCESS LEDFault TypeLogged Ending EventCF Card Inserted Blink CF UPLOADREQUESTCRC 1 completedCorrupt CF header Red CF FILE ERROR CF Card removedUpload CardInserted whileAirborneRed CF FILE ERROR CF Card removedIncorrectConfiguration ErrorRed CF FILE ERROR CF Card removed
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.5--14Table 5--4. Compact Flash Upload / LED correlation(cont)Triggering Event Ending EventFault TypeLoggedXFER INPROCESS LEDCF Status LEDMajor/MinorIncompatibilityRed CF FILE ERROR CF Card removedFile Header CRCerrorRed CF FILE ERROR CF Card removedFile does not existerrorRed CF FILE ERROR CF Card removedMultiple file error Red CF FILE ERROR CF Card removedFile Image CRCerror (CRC 1)Red CF FILE ERROR CF Card removedCRC 1 completed Green CF LOAD CF Card error isdetected or uploadcompleted or restartAborted Upload Red CF WRITE ERROR 10 seconds aftercard removalAirborne Upload Red CF FILE ERROR CF Card removedGround--to--airtransition duringuploadGreen (per normaluploadingsequence)CF FILE ERROR CF Card error isdetected or uploadcompleted or restartFlash Copy CRCfails to match CFFile CRC (CRC 2)Red CF WRITE ERROR Card removalFlash Copy 2 failsto match CRC atCopy 1 locationRed FLASH EPROMERRORCard removalAPM CalculatedCRC doesn’t matchCF File CRC.Red APM WRITEERROR -- CFUploadCard removalAPM CalculatedCRC doesn’t matchAPM embeddedCRC.Red APM DATA FAULT-- CF UploadCard removalAPM write to FlashunsuccessfulRed APM COPY WRITE-- CF UploadCard removalAPM CalculatedCRC doesn’t matchAPM embeddedCRCRed APM Copy CRC --CF UploadCard removalAll files loadedsuccessfulGreen CF UPLOAD SETCOMPLETECard removal
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.5--15D. RS232 -- TAWS/RWS APM Configuration Data and APM Application Data LoadingThe T2CAS is capable of uploading the ACD or ASDB while in the air or on the ground,while using the RS--232 interface with the APM_LOAD XXXX command.(1) Obtain PC software tool EDDIT (Engineering Diagnostic & Data Interface Transfer)Part No. 9000286--001.(2) Obtain or build an RS--232 cable. (Refer to Figure 5--3.)(3) Turn PC power off.(4) Remove power from the TT--950/951/952 Computer Unit.(5) Connect the RS--232 cable from the PC (9--pin connector) to the J1 front connectoron the TT--950/951/952 Computer Unit.(6) Apply power to the TT--950/951/952 Computer Unit.(7) Power on the PC to Microsoft Windows operation.(8) On the PC, follow the Online instructions provided with the EDDIT tool to load theASDB file and/or the ACD file.(9) Shut down the PC and remove power.(10) Remove power from the TT--950/951/952 Computer Unit.(11) Disconnect the RS--232 cable from the J1 front connector on the TT--950/951/952Computer Unit.E. Updated Software Verification(1) Software Verification Using Flight Deck Systems ONLY(a) TCASVerify the updated software part number according to the T2CAS TCASextended maintenance capabilities on status page code 0000 in the FAULTISOLATION section of this manual or the individual aircraft maintenance manual(refer to the onboard maintenance system program).(b) TAWS/RWSVerify the current software part number according to the extended maintenancecapabilities Part Number Page.(2) TCAS Software Verification Using a Stand--Alone PC ONLYVerify the updated TCAS software part number using a stand--alone PC according tothe following procedure.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.5--16(a) Obtain PC software Part No. PS4088035--101.(b) Obtain or build an RS--232 cable. (Refer to Figure 5--3.)(c) Shut down and power off the PC.(d) Remove power from the TT--950/951/952 Computer Unit.(e) Connect the RS--232 cable from the PC (9--pin connector) to the J1 frontconnector on the TT--950/951/952 Computer Unit.(f) Apply power to the TT--950/951/952 Computer Unit.(g) Power on the PC to Microsoft Windows operation.(h) On the PC, go to START => PROGRAMS => HONEYWELL TOOLS and doubleclick “TCAS Part Number”.(i) Verify the updated TCAS software part number.(j) Shut down and power off the PC.(k) Remove power from the TT--950/951/952 Computer Unit.(l) Disconnect the RS--232 cable from the J1 front connector on theTT--950/951/952 Computer Unit.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.5--17Figure 5--3. RS--232 PC to TCAS Interface Cable(3) TAWS/RWS Software Verification Using a Stand--Alone PC ONLYVerify the updated TAWS/RWS software/Database part numbers using a stand--alonePC according to the following procedure.(a) Obtain PC software tool EDDIT, Part No. PS4088035--101.(b) Obtain or build an RS--232 cable. (Refer to Figure 5--3.)(c) Shut down and power off the PC.(d) Remove power from the TT--950/951/952 Computer Unit.(e) Connect the RS--232 cable from the PC (9--pin connector) to the J1 frontconnector on the TT--950/951/952 Computer Unit.(f) Apply power to the TT--950/951/952 Computer Unit.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.5--18(g) Power on the PC to Microsoft Windows operation.(h) On the PC, follow the Online instructions provided with the EDDIT tool todownload the TAWS/RWS operational software/Database part numbers.(i) Shut down the PC and remove power.(j) Remove power from the TT--950/951/952 Computer Unit.(k) Disconnect the RS--232 cable from the J1 front connector on theTT--950/951/952 Computer Unit.(4) TCAS Software Verification Using a Software Verification Fixture ONLY(a) Obtain Software Verification Fixture (Part No. T326948--901) with associatedadapter cable (Part No. 200F--00084).(b) Remove power to the TT--950/951/952 Computer Unit.(c) Connect the adapter cable (Part No. 200F--00084) to the TT--950/951/952Computer Unit and the software verification fixture.(d) Apply power to the TT--950/951/952 Computer Unit.(e) Enable the software verification fixture and verify the appropriate software partnumber is displayed in the 15--digit display.(f) Perform a TCAS system self--test and verify that TCAS TEST PASS isannunciated.NOTE: The TCAS TEST FAIL message may be annunciated if an LRU thatsupplies input to the TT--950/951/952 Computer Unit is not powered on.(g) If the software part number is not displayed, repeat step (a) thru step (f).(5) TCAS Software Verification Using a Remote Connected VSI/TRA ONLYOn some aircraft configurations, software verification may be performed using aremote connected VSI/TRA (Part No. 4067241--861, --862, or --863) display attachedthrough adapter cable (Part No. 200F--00083) to the J1 front connector of theTT--950/951/952 Computer Unit during the extended test mode.Verify the particular aircraft configuration can support a Flight Deck initiated self--testand be recognized at the 8--second time period after activation.NOTE: CMC/CFDS activated self--test will not be recognized at the 8--second timeperiod, only an approved TCAS control panel.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.6--1FAULT ISOLATION1. GeneralThe T2CAS Traffic and Terrain Collision Avoidance System has three optional procedures forfault detection and isolation to the LRU level. The first option uses the aircraft CMC or centralfault display system (CFDS) if the aircraft is equipped with an onboard maintenance system.The second option uses a digital interface between the T2CAS Computer Unit and the displaysystem (Weather Radar, EFIS, or multifunction display for TAWS/RWS and VSI/TRA flat paneldisplay or EFIS for TCAS). The third option uses the annunciators located on the front panelof the computer unit. The annunciators are activated by a self--test function within the T2CASComputer Unit. Select the procedural option for fault isolation from Fault Isolation paragraph3 (Procedure), which is applicable to the type of aircraft and the equipment installed.2. Equipment and MaterialsNOTE:Equivalent alternatives are permitted for equipment in this list.Digital Multimeter -- Fluke Model 29, John Fluke Mfg Co. Inc., Everett, WA3. ProcedureA. CMC or CFDSFault information can be displayed from an onboard maintenance system when theaircraft is so equipped. Fault data is accessible only when the aircraft is on the ground.Faults that occur at any time, on the ground or while airborne, are stored in fault memoryand reported to the CMC or CFDS. All displayed information is in the English languagewith abbreviated terms used only as necessary. Refer to the appropriate CMC or CFDSsupport manual for fault retrieval procedures.B. Flight Deck Initiated Self--Test/Fault Display Systems(1) TCASThe TCAS display system can be used to display system status and fail messages inthe Flight Deck, making it more convenient to use than the computer unit front panelannunciators for a quick checkout of the TCAS system. In contrast with the computerunit self--test, which records and stores faults from previous flights, the displaysystem test shows only current status and failure data.To access the Flight Deck display test modes, perform the following procedures:NOTES:1. Fault detection with diagnostics can only be done on the ground. The pilothas the option to do a pass/fail test while airborne if this feature is notinhibited.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.6--22. This procedure is valid when used with either a single or dual control panel.(a) Make sure the aircraft configuration indicates Aircraft On Ground and GearExtended.(b) Set the Mode Select switch on the ATC/TCAS control panel to STBY.(c) Push and hold the TCAS TEST button for a minimum of 9 seconds.(d) Set the transponder 4096 Ident Code Number to any code except 0000 thru0007, 0011, or 0012.NOTE: Do not use codes 7500, 7600, or 7700; these code are reserved foremergency operation.(e) Make sure the TCAS TEST MENU is being displayed on the TCAS display. Itshould match the screen shown in Figure 6--1.(f) Set the transponder 4096 Ident Code Number to 0000.(g) If the system passes, a maintenance page similar to that shown in Figure 6--2 isdisplayed. A failure results in a referral to one or more specific ident codes. Setthe indicated code on the ATC/TCAS Control Panel and follow the instructionsgiven.(h) If the system passes, set the mode switch on the ATC/TCAS Control Panel toMODE S ON. This allows you to exit the expanded test mode. If a failure isindicated, set the transponder 4096 Ident Code to the codes indicated by theautomatic referral system. The remaining screens shown in Figure 6--3 thruFigure 6--13 are examples of the other maintenance pages.(i) Set system power to OFF and correct faults by replacing indicated LRUs or byrepairing faulty wiring harness.(j) Test system as required after repair.(2) TAWS/RWSThe TAWS display system (EFIS or weather Radar) can be used to display systemstatus and fail messages in the Flight Deck, making it more convenient to use thanthe computer unit front panel annunciators for a quick checkout of the TAWS system.In contrast with the computer unit self--test, which records and stores faults fromprevious flights, the display system test shows only current status and failure data.Toaccess the Flight Deck display test modes, do the procedures that follow:NOTE: The TAWS/RWS/GPS Fault detection with diagnostics can only be done onthe ground. The pilot has the option to do a pass/fail test while airborne ifthis feature is not inhibited.(a) Make sure the aircraft configuration indicates Aircraft On Ground and GearExtended.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.6--3(b) Push and hold the TAWS/RWS/GPS TEST button/switch on the Flight Deck for afew seconds to start the standard self test.(c) The extended self--test is then initiated by pushing and holding theTAWS/RWS/GPS TEST button/switch on the Flight Deck for more than threeseconds, with the initiation beginning between the end of the standard self--testaural annunciation of one of the following messages and three seconds later:•“TERRAIN AWARENESS AND WINDSHEAR TEST COMPLETE”.•“TERRAIN AWARENESS TEST COMPLETE”.•“TERRAIN AWARENESS AND WINDSHEAR TEST PASSED”.•“TERRAIN AWARENESS TEST PASSED”.(d) Once on Extended Self--Test Page One as shown in Figure 6--14, the T2CASExtended Self--Test display can be indexed to the next Extended Self--Test pageby pressing the TAWS/RWS/GPS TEST button/switch for three seconds or less.NOTE: If the CMC Self--Test Input initiates a standard self--test during the extendedself--test, the T2CAS will replace the extended self--test page with themulticolor test pattern and begin standard self--test.(e) After system fault isolation test is completed, the Extended Self--Test pages canbe exited by pressing the TAWS/RWS/GPS TEST button/switch for more thanthree seconds.(f) Set system power to OFF and correct faults by replacing indicated LRUs or byrepairing faulty wiring harness.(g) Test system as required after repair.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.6--4C. T2CAS Aural and Visual Annunciations(1) TCAS Aural and VSI/TRA AnnunciationsTCAS aural and VSI/TRA annunciations are given in Table 6--1.Table 6--1. TCAS Aural and VSI/TRA AnnunciationsVSI/TRA AnnunciationCondition AuralUpperLeftUpperRight Center Color NotesTRAFFIC DisplayControl ON ModeNormal Range ring and ownaircraft in view at all times,along with qualifyingtraffic.TRAFFIC DisplayControl AUTOModeNormal Range ring and ownaircraft come up withtraffic when a TA or RAexists.Transponder OnlyModeNone TCASOFFWhite TCAS is not operational.STANDBY Mode None TCASOFFWhite TCAS is not operational,transponder is in standby.Vertical SpeedInput Failure toSingle VSI (DualVSI Aircraft)Normal RA FAILon failedsideVSI FAILon failedsideYellow Vertical speed needleremoved from display withfailed data. No RAsposted on failed side.TCAS is operational onremaining side.VSI Input Failureto Both (Dual VSIAircraft) or SingleVSI (Single VSIAircraft)None VSI FAILon bothsidesTCASFAIL onboth sidesYellow Vertical speed needleremoved from both VSIs(dual VSI aircraft) or onlyVSI (single VSI aircraft).No RA information posted.TCAS is not operational.TA Only Mode Traffic --TrafficonlyTA ONLY WhiteorYellowTraffic alerts are the onlyinformation displayed. NoRAs.(The color changes fromwhite to yellow when a TAactually occurs.)Transponder orAltitude SourceFailNone TCASFAILYellow TCAS is not operational.Altitude ReportingOFFTCASOFFWhite TCAS is not operational.ATCRBSTransponderSelectedNone TCASOFFWhite TCAS is not operational.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.6--5Table 6--1. TCAS Aural and VSI/TRA Annunciations (cont)Condition NotesVSI/TRA AnnunciationAuralCondition NotesColorCenterUpperRightUpperLeftAuralRA Only(TA DisplayControl to OFF)RA ONLY White VSI/TRA displaysresolution advisories only.RA Fail RA FAIL VSI FAIL Yellow No resolution advisoriesdisplayed.Traffic DisplayFailureTD FAIL Yellow No traffic advisoriesdisplayed.Single VSI/TRAFailure (Dual VSIAircraft)Normal X acrossfaileddisplayRed On failed side, allsymbology removed andreplaced with a large redXand hex--coded failurenumber. TCASoperational on good side.Dual VSI/TRAFailure (or Singleon Single VSIAircraft)None X acrossbothdisplaysRed All symbology removedfrom both displays andreplaced with a large redXand failure code. TCASis not operational.Flight Deck LampTestNormal Display fullwhiteDuring Flight Deck lamptest, display goes fullwhite and displays nosymbology.TCAS SELF--TEST (Note 1.)TCAS Test Mode(First Second)TCASTESTTCASTESTWhite TCAS system self--test.TCAS Test Mode(2 to 8 Seconds)TCASTESTWhite TCAS test pattern shown.TCAS Test Mode(at 8 Seconds)TCASTESTPASS/FAILTCASTESTTCAS test patternremoved and TCASreturns to normaloperation unless the testswitch is held, the aircraftis on the ground, andTCAS is in STBY.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.6--6Table 6--1. TCAS Aural and VSI/TRA Annunciations (cont)Condition NotesVSI/TRA AnnunciationAuralCondition NotesColorCenterUpperRightUpperLeftAuralTCAS EXTENDED SELF TEST (MAINTENANCE ONLY) (Note 2.)TCAS ExtendedTest Mode (TestSwitch Held at 7Seconds for 2Seconds andAircraft on theGround Only)SysteminformationpagesWhite Current status of theTCAS system,transponder, antennas,radio altimeters.barometric altitude, etc. ispresented in a series ofpages called by selectionof 4096 code.NOTES:1. Self--Test should only be run in STANDBY mode in flight or on the ground.2. Extended Self--Test provides maintenance information on seven screens selected using 4096code. This mode is available only on the ground and in STANDBY. Extended Self--Test endsautomatically with a TCAS/Transponder mode change or if the aircraft becomes airborne.(2) TAWS/RWS Aural and Visual Annunciations
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.6--7D. T2CAS Test Menu and System Status Pages(1) TCAS Test Menu and System Status PagesThe extended test mode provides maintenance information on the TCAS display.Pages are selected by 4096 codes on the transponder control panel. The extendedtest mode is accessible only on the ground, with the transponder in standby.To start the extended test mode, select STBY and push the transponder controlpanel TCAS TEST switch for 8 seconds. To exit the extended test mode, move thetransponder mode control out of STBY.(a) TCAS Test MenuThe TCAS Menu Page, Figure 6--1, can be displayed whenever a TCASsuppression bus failure is not indicated and the 4096 Ident Code is any codeother than 0000 thru 0007, 0011 or 0012. If a TCAS suppression bus failure isindicated, all 4096 Ident Codes other than 0000 thru 0007, 0010 thru 0012 and0510 can be used to select the TCAS Test Menu.Figure 6--1. TCAS Test Menu Page(b) System Status PageSelection of code 0000 displays the System Status page, Figure 6--2. This pagedisplays the PASS or FAIL status of the TCAS system and the current version ofthe operating software loaded into the T2CAS computer.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.6--8Figure 6--2. Typical System Status PageIn the event of a detected system failure, one or more of the messages inTable 6--2 are displayed. Lines 6 thru 10 of the display screen are used todisplay the five highest priority faults within the TCAS system. A maximum offive messages can be displayed.Table 6--2. System Status Page Fault MessagesPriority Message Description1SUPP FAULT GOTO 0010 Suppression bus failure. Select page 0010 for moreinformation.2TCAS CU FAIL T2CAS TCAS function has failed BITE test.3ANT FAIL TOP Antenna failure. Message field will display TOP, BOTor BOTH to indicate which antenna failed.4DISP FAIL GOTO 0001 TCAS has lost valid signal from display. Select page0001 for more information.5RALT INACT GOTO 0002 TCAS has lost valid signal from radio altimeter.Select page 0002 for more information.6XPDR FAIL GOTO 0003 TCAS has lost valid signal from Mode S transponder.Select page 0003 for more information.7ANT FAIL GOTO 0011 One of the antenna ports connected to the T2CAS CUhas failed. Select page 0011 for more information.8OPT FAIL GOTO 0012 Parity for the option selections has failed. Selectpage 0012 for more information.(c) Display Status PageSelection of code 0001 displays the Display Status page, Figure 6--3. This pagedisplays the current status of the Resolution Advisory and Traffic Advisorydisplays.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.6--9Figure 6--3. Typical Display Status PageThe message contents for the Display Status page are determined as follows:RA DISPLAY #1 PASS Indicates valid signal (ground/low) is present at T2CAS CUpin RMP--14C. Fail is displayed if this signal is an open/high.TA DISPLAY #1 PASS Indicates valid signal (ground/low) is present at T2CAS CUpin RMP--7E. FAIL is displayed if this signal is an open/high.RA DISPLAY #2 PASS Indicates valid signal (ground/low) is present at T2CAS CUpin RMP--13E. FAIL is displayed if this signal is anopen/high.TA DISPLAY #2 PASS Indicates valid signal (ground/low) is present at T2CAS CUpin RMP--7J. FAIL is displayed if this signal is an open/high.RNG SELECT 6NM Indicates current range selection for the traffic display. Forinstallations using control panels without range selectswitches, range defaults to 6NM.ALT SELECT NORM Indicates current selection of vertical display limits for trafficdisplay -- NORM, BELOW, or ABOVE. For installations thatuse control panels without ABV--NORM--BLW switch, limitsdefault to NORM.ALT TAG RELATIVE Indicates current selection on control panel for type of trafficsymbol altitude indication, RELATIVE or FLT LVL. Default isRELATIVE if no switch is available on control panel.(d) RAD/ALT Status PageSelection of code 0002 displays the RAD/ALT Status page, Figure 6--4. Thispage displays the status of the selected radio altimeter interface to the T2CAS.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.6--10Figure 6--4. Typical RAD/ALT Status PageThe first information line (line 3) of the RAD/ALT STATUS page indicates whichof the two radio altimeter ports is being used by the T2CAS computer. TheT2CAS computer attempts to use radio altimeter No. 1 first. If it determines thisinput is invalid, it automatically switches to radio altimeter No. 2.The current status of the two radio altimeter ports is displayed on lines 5 and 6.If a signal is valid, the radio altitude value is displayed in either “FT” for Englishtype altimeters, or “M” for Metric type altimeters.If one of the radio altitude signals is determined to be invalid, the altitude value isreplaced by INACT. Radio altitude INACT indicates the radio altimeter has failed,is not powered, or is not connected.The radio altimeter input is determined to be invalid if, for an analog radioaltimeter input, +28 Vdc valid is not present at T2CAS CU pin RMP--2K for RadioAlt #1 or pin RMP--3C for Radio Alt #2, or for a digital radio altimeter input, thesign status matrix (SSM) of the radio altimeter output indicates not valid or nodata is present on the digital bus.If the radio altimeter output is greater than 2200 feet (source is valid, but data isinvalid), the radio altitude value is replaced by OVR RNG.When both radio altitude sources are invalid, line 3 is blank.(e) Transponder (XPDR) Status PageSelection of code 0003 displays the XPDR Status page, Figure 6--5. This pagedisplays data for the transponder selected at the time the extended test modewas entered.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.6--11Figure 6--5. Typical Transponder (XPDR) Status PageThe message contents for the XPDR Status page are determined as follows:XPDR #1 PASS Indicates PASS or FAIL status of the selected transponder(XPDR #1 or XPDR #2) as indicated by the digitaltransmission from that transponder. FAIL is displayed if nodata is received on the bus.MODE S ADDR: 8E78A0H Indicates the Mode S address (in hexadecimal format) of theselected transponder as determined by program pins at therear connector of the transponder. (See Note 1.)PRESS. ALT 1133FT Indicates the last pressure altitude being reported by theselected Mode S transponder before the TCAS system wasplaced into STBY. This value is not updated while in extendedtest mode.ALTREPORTINGON Indicates current position of altitude reporting switch on ModeS/TCAS control panel -- ON or OFF.S/W PN PS7021601--903 (See Note 2.)NOTES:1. If the transponder detects either all 1s or all 0s, the following message will appear --ILLEGAL ADDRESS --. In addition, a fail message will appear on the front of thetransponder and on Extended Test. The message reads CHECK DISCRETEADDR WIRING ON XPDR PINS MP1A THROUGH MP3D.2. The S/W PN information, line 8 of the display screen, displays general text suppliedby the ACSS ATDL transponder via label 356 (block transfer), which is equipped tosupply the text to the display. If a transponder is installed that does not have thisfeature, line 8 is blank.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.6--12(f) Programming Pins Status PagesThe following three displays indicate the status of various option programmingpins located in the rear connector of the T2CAS computer. The 1s and 0sfollowing a programming option indicate the GROUND or OPEN status for thoseprogramming pins. Each 1 and 0 is associated with a program pin. A one (1)indicates the pin is grounded by connecting to a program common pin on theT2CAS connector or to an aircraft ground. A zero (0) indicates the pin is leftopen.Selection of code 0004 displays the first of three pages that define program pinstatus. See Figure 6--6.Figure 6--6. Typical Program Pins 1/3 PageProgramming pins on the T2CAS computer associated with each of the functionsdefined on the page 1 display are listed below. Where more than one programpin is indicated, the listed connector pins correspond to the display digits readfrom left to right. A one (1) indicates the associated pin is grounded. A zero (0)indicates open.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.6--13CLIMB INH 0000 Climb Inhibit inputs:RMP--1J, RMP--13G, RBP--5J, RBP--5K.INC CLIMB INH 0000 Increase Climb Inhibit inputs:RBP--5E, RBP--5F, RBP--5G, RBP--5HADVISORY INH 0000 Advisory Inhibit inputs:RBP--5A, RBP--5B, RBP--5C, RBP--5DRADIO ALT TYPE 10000 Analog Radio Altimeter Type: RMP--12BARINC 552/552A (0), Collins BCA (1)VOICE DELAYENABLE0 Voice Delay option: RBP--7DEnabled = (1), Disabled = (0)AUDIO PROG PINS 000 Audio output level selection inputs:RBP--7A, RBP--7B, RBP--7CCANCEL DISCRETE 20Advisory Cancel Discrete option: RMP--3D(0) allows advisories to be cancelled. A (1) does not allowadvisories to be cancelled.Selection of code 0005 displays the second of three pages that define theProgram Pins status. See Figure 6--7.Figure 6--7. Typical Program Pins 2/3 PageProgramming pins on the T2CAS computer associated with each of the functionsdefined on the Program Pins 2/3 page are listed below. Where more than oneprogram pin is indicated, the listed connector pins correspond to the displaydigits read from left to right. A one (1) indicates the associated pin is grounded.Azero(0) indicates open.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.6--14BCA EFIS 0RA/TA block transfer program that determines the type ofdata transfer from the T2CAS CU to the TA/RA displays:A(1) indicates Honeywell BCA EFIS format. A (0) indicatesARINC 735 format: RMP--12C.CABLE DELAYPROG000 RF delay compensation program for antenna cable lengthdifference (top versus bottom): RBP--7G, RBP--7H, RBP--7JTEST MODE 0000 Shop test function (all 0s for flight mode):RBP--9D, RBP--9E, RBP--9F, RBP--9GFUNCT TEST INH 0 Inhibits Flight Deck self--test when airborne (0for no inhibit):RBP--8ESIM SOFT ENABLE 0 Simulator Software Enable input: RBP--10KShould always be (0) for flight mode.MAX # INTRUDER 00000 Select maximum number of traffic symbols displayed on VSI.Value for each digit, from left to right, is 16, 8, 4, 2, 1. Themaximum number is the sum of not selected values (0s):RBP--8F, RBP--8G, RBP--8H, RBP--8J, RBP--8K.DISP THREATSONLY0 Selects display of traffic only when TAs or RAs occur:(0indicates display of any traffic): RBP--7F.GND DISPLAYMODE0Selects TCAS OFF automatically with aircraft ON GROUND(0indicates TCAS active ON GROUND): RBP--7E.Selection of code 0006 displays the third of three pages that define the ProgramPins status. See Figure 6--8.Figure 6--8. Typical Program Pins 3/3 Page
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.6--15Programming pins on the T2CAS computer associated with each of the functionsdefined on the Program Pins 3/3 page are listed below. Where more than oneprogram pin is indicated, the listed connector pins correspond to the displaydigits read from left to right. A one (1) indicates the associated pin is groundedandazero(0) indicates open, except for RCZ--852 MAX TAS where a one (1)indicates an open and a zero (0) indicates a ground.ALT LIMIT 00000 Shows selected altitude above which TCAS will not give CLIMBcommands. Value for each digit, from left to right, is 32000, 16000,8000, 4000, and 2000 feet. Altitude is the sum of selected values(1s): RMP--6J, RMP--6H, RMP--6G, RMP--6F, RMP--6E.PERF LIMIT 0 Selects CLIMB command altitude limit control from externalperformance computer: A ground (1) indicates performance/climbrate is not limited. An open (0) indicates performance/climb rate islimited: RMP--6D.METRIC TYPE 000 Shows the status of the metric selection program pins #1, #2, and#3: RMP--12K, RMP--12J, and RMP--12H. The metric type willappear only with TCAS computer unit part number7517900--XX001 and --XX002. On TCAS computer unit partnumber 7517900--XX003 and --XX004, the message “METRICTYPE 0000” is replaced with “SINGLE TRANSPONDER 0”.MAX TAS 000 Shows the selected maximum airspeed operating range of aircraft.This data is obtained from ARINC label 276 of the selectedtransponder. Refer to the appropriate Mode S transponderinstallation manual.NOTE: Line 8 of the Program Pins 3/3 display indicates which transponder is currentlyselected.Help Reference PageSelection of code 0007 displays the Help Reference page, Figure 6--9. Thispage serves as a reference to assist aircraft maintenance personnel in checkingthe functionality of dual transponders.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.6--16Figure 6--9. Help Reference PageIn addition to the recommended procedure, the number 2 transponder must beselected on the Mode S/TCAS control panel and the mode select switch placedin TA only or TA/RA mode momentarily prior to restarting self-test to enterextended maintenance mode.(g) Suppression Bus Fail PageThe Suppression Bus Fail page, Figure 6--10, is displayed only when a TCASsuppression bus failure is indicated and the 4096 Ident Code is 0010. Thispage displays information about detected suppression bus failures. It brieflydescribes the problem and instructs maintenance personnel to change the 4096Ident Code to display the Suppression Bus Clear page for clearing instructions.If there is no suppression bus failure, the main menu (0000) is displayed.Figure 6--10. Suppression Bus Fail Page
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.6--17The flight crew may report a unique problem of an intruder displayed whichappears to be co--altitude, located on the own aircraft symbol. In many of thesecases, TCAS may issue a TA followed by an RA. After the flightcrew hasinitiated the advisory, the intruder may not appear to change relative to the ownaircraft symbol.In this type of report, a failure in the mutual suppression bus, which connects theown aircraft transponder to the T2CAS CU, could result in the T2CAS CUdeveloping an intruder track file on its own associated transponder. Simplyperforming a DC continuity test of the connection between the T2CAS CU andthe transponders may not identify the problem. In many cases, a connectortermination or pushed back pin may be the cause.That is why it is very important to be monitoring the suppression signal from theactive source, on both ends. The following is one method to monitor the signal.Remove the T2CAS CU and the non--selected transponder. With anoscilloscope, monitor the signal at the T2CAS CU rack rear connector for theMode S transponder suppression signal related to the squitter message sentevery second by the selected operational transponder.Repeat the same test with the second transponder after removing the firsttransponder. To test the T2CAS CU suppression pulse, install the TCAS CU,remove the No. 1 transponder and monitor the TCAS suppression pulse duringthe time of the UF16 broadcast or the WSS while in the air (if possible). ThisTCAS suppression signal should also be present on the No. 2 transponder.(h) Suppression Bus Clear PageThe Suppression Bus Clear page, Figure 6--11, is displayed only when a TCASsuppression bus failure is indicated and the 4096 Ident Code is 0510. This pagebriefly describes how to clear suppression bus failures from the fault record byexiting the extended test mode with this page displayed. When the TCASextended test is exited, the failure indication is cleared and a Suppression BusClear code is recorded in the current flight leg.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.6--18Figure 6--11. Suppression Bus Clear Page(i) Antenna Port Status PageSelection of code 0011 displays the Antenna Port Status page, Figure 6--12.This page displays the current operational status of the top and bottom TCASantennas. The status of each port is indicated as PASS when valid and FAILwhen invalid. Information lines 8, 9, and 10 are not displayed when anomnidirectional bottom antenna is installed.Figure 6--12. Typical Antenna Port Status Page(j) Option Pins Status PageSelection of code 0012 displays a page that defines the T2CAS computer optionpins. See Figure 6--13.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.6--19Figure 6--13. Typical Option Pins Status PageOption pins on the T2CAS computer associated with each of the functionsdefined on the Option Pins Status page are listed below. Where more than oneoption pin is indicated, the listed connector pins correspond to the display digitsread from left to right.There are eight option pins available on the T2CAS computer for selection ofvarious options. The OPT PINS are as follows: RMP--10G, --10H, --10J, --10K,-- 11 A , -- 1 1 B , -- 11 C , a n d -- 11 D .NOTE: OPT PINS RMP--10G, --10H, --10J, and --10K are reserved for futureenhancements and are used for parity check only.The PARITY line (line 4) displays the status of the parity program pin(RMP--12G). Pin RMP--12G must be grounded (1) when the number of OPTPINS grounded is an odd number (1, 3, 5, 7). If number of OPT PINS groundedis an even number (0, 2, 4, 6, 8), then pin RMP--12G should be open (0).The STATUS line (line 5) displays FAIL if the option pins parity is incorrect orPASS if parity is correct.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.6--20The ENHANCEMENTS line (line 6) displays the status of the Flight DataRecorder ARINC 429 and Extended Maintenance Log Program input status (PinRMP--11D). This option enables the use of the Flight Data Recorder and thedown loading of the extended maintenance log through a PDL connected toconnector J1 located on the front of the TCAS computer. If pin RMP--11D isopen, the Flight Data Recorder is not used and normal RA display bus operationoccurs. If pin RMP--11D is grounded, high speed ARINC 429 flight data is outputon the RA Display #1 and #2 buses and maintenance log data can bedownloaded through a portable data loader.NOTE: The three options that follow have been defined, but the functions havenot been implemented in --XX001 and --XX002 TCAS computersoftware. These options should always indicate OFF in these versions.The three options are activated with --XX003 and --XX004 TCAScomputer software.The MALE VOICE line (line 7) displays the Male Voice Program input status (PinRMP--11C). This option allows audio annunciation to be selectable for eithermale or female gender. If pin RMP--11C is grounded, the male voice option isenabled (ON). If pin RMP--11C is open, the female voice option is enabled(OFF).The DISPLAY FLT ID line (line 8) displays the Flight ID Program input status (PinRMP--11B). This program allows flight identification from the transponder to beoutput on traffic display buses. If pin RMP--11B is grounded, Flight ID Display isenabled (ON). If pin RMP--11B is open, Flight ID Display is disabled (OFF).The ALTITUDE ALERTER line (line 9) displays the Altitude Alerter Program inputstatus (Pin RMP--11A). This program prevents the weakening of an RA basedon selected altitude. If pin RMP--11A is grounded, the Altitude Alerter option isenabled (ON). If pin RMP--11A is open, the Altitude Alerter option is disabled(OFF).(2) TAWS/RWS Test Menu and System Status PagesThe extended test mode provides maintenance information on the TAWSEFIS/Weather Radar display. Pages are indexed by pressing and holding theTAWS/RWS/GPS TEST button/switch on the Flight Deck for three seconds or less.The extended test mode is accessible only on the ground, and only after thestandard short test has completed as outlined in section 3.B.2 of this (Fault Isolation)section.NOTE: The Extended Self--Test pages can be exited at any time by pressing theTAWS/RWS/GPS TEST button/switch for more than three seconds.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.6--21(a) Extended Self--Test PageThe Extended Self--Test Display page layout is dependent on the selection ofdisplay formats made in the ASDB. Some types have more viewable area thanothers thus the font size and formatting will differ, but the actual text displayedwill remain the same. As such, all of the Extended Self--Test pages shown in thissection are typical WXR display formats, the actual displays will vary according tothe usable display area.The T2CAS TAWS Extended Self--Test page is the first page displayed. TheExtended Self--Test page is divided into two pages, Figure 6--14 shows page 1,the Instructions Page and Figure 6--15 shows Page 2, the Table of ContentsPage.NOTE: The gray shaded area represents the anticipated viewable area of thedisplay. The viewable area will vary with the display types as defined inthe ASDB.ID--8000637Figure 6--14. Extended Self--Test Page (Page 1)
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.6--22ID--8000638PART NUMBERSPAGE 2 -- 6TABLE OFCONTENTSFigure 6--15. Extended Self--Test Page (Page 1 of 6)(b) Part Numbers PageThe Part Numbers Page is divided into five pages. Figure 6--16 shows page 1,which displays the Aircraft Type and OMS Type.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.6--23ID--8000639Figure6--16. PartNumbersPage1(Page2of6)Pages 2 and 3, shown in Figure 6--17 and Figure 6--18 respectfully, display theAircraft Identifier, LRU Part Number, Software Modification Number and TAWSDatabase Part Number.ID--8000640Figure6--17. PartNumbersPage2(Page3of6)
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.6--24ID--8000641Figure6--18. PartNumbersPage3(Page4of6)Part Number Pages 4 (Figure 6--19) and 5 (Figure 6--20) contain APMinformation including Hardware Part Number, ACD Part Number and ASDB PartNumber. Page 5 also includes a Internal System PASS/FAIL indication.ID--8000642Figure 6--19. Part Numbers Page 4 (Page 5 of 6)
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.6--25ID--8000643Figure6--20. PartNumbersPage5(Page6of6)E. T2CAS Computer Unit Self--TestThe T2CAS computer unit detects system faults and displays them on its front panelannunciators. Its flight leg memory stores system status and fault information for 10consecutive flight legs. A flight leg is the interval between weight--off--wheels and weight--on--wheels during which T2CAS is operative. By recalling the stored data, groundmaintenance personnel can evaluate in--flight performance on the ground and faultisolate a current or previous failure to a specific LRU or LRU interface.Table 6--3 summarizes how the T2CAS computer unit self--test is activated at power--up,during operation, and during commanded self--test. The computer unit can activate thecommanded self--test only when the aircraft is on the ground.Table 6--4 lists the functions of the computer unit’s status annunciators and thecorresponding troubleshooting actions. If the annunciators indicate an antenna problem,the antenna connections should be checked by measuring the antenna resistance valuesat the computer unit mounting tray. The resistance values listed in Table 6--5 aremeasured between the center conductor and shield on each LTP and LMP antennaconnector.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.6--26Table 6--3. Computer Unit Self--Test ExecutionTest Sequence Activation Test IndicationsPower On Self--Test Self--Test is activated witheach application of systempowerNo indication unless a fault is detected.System status/fault data is stored in memoryfor 10 consecutive flight legs. Data can berecalled by doing the commanded self--test onthe ground.Continuous Self--Test Executed automatically aspart of normal TCAS inflightoperationNo indication unless a fault is detected.System status/fault data is stored in memoryfor 10 consecutive flight legs. Data can berecalled by doing the commanded self--test onthe ground.CommandedSelf--TestPush the front panel PUSHTO TEST button•All T2CAS TCAS front panel lamps comeon during a 3--second lamp test.•If the TCAS is operational, the TCAS PASSgreen lamp comes on for a 10--seconddisplay period and then goes off.•If the TCAS is not operational, one or morered fault lamps come on for a 10--seconddisplay period. Refer to Table 6--4 forcorrective action.•The T2CAS TAWS/RWS front panel lampscycle as defined in Section 5Adjustments/Test.•If the TAWS/RWS is operational XFER INPROCESS LED will be extinguished andthe TAWS P/F STATUS green lamp comeson for approximately 11 seconds.•If the TAWS/RWS is not operational, TAWSP/F STATUS, TAWS I/O FAIL, TAWS APMFAIL, and CF LOAD STATUS LEDs will beset for approximately 11 seconds.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.6--27Table 6--3. Computer Unit Self--Test Execution (cont)Test Sequence Test IndicationsActivationPush the PUSH TO TESTbutton again before theprevious 10--second displayperiod has elapsed•Previous fault display is aborted•All T2CAS TCAS lamps come on during a1--second lamp test•All front T2CAS TAWS/RWS LEDs will be litfor 1 second (+/-- 0.5 seconds) in thefollowing colors:-- TAWS P/F STATUS: Red-- TAWS I/O FAIL: Red-- TAWS APM FAIL: Red-- XFER IN PROCESS: Green-- C/F LOAD STATUS: Red•The TAWS/RWS XFER IN PROCESS LEDwill be extinguished.•The TCAS Status/fault data recordedduring the preceding flight leg is displayedfor 10--seconds.•The TAWS/RWS Status/fault data recordedduring the preceding flight leg is displayedfor approximately 11 seconds.Push the PUSH TO TESTbutton before the end of eachsucceeding display period•TCAS and TAWS/RWS Status/fault datarecorded during a total of 10 flight legs(maximum) is displayed•When data from the earliest recorded flightleg has been displayed, all lamps flash atapproximately a 2.5--Hz rate for 3--secondsif the PUSH TO TEST button is pushed.This indicates the end of recorded testdata.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.6--28Table 6--4. TCAS Fault Reporting and Corrective ActionsStatusAnnunciator Failure Possible corrective ActionTCASPASSThe T2CAS TCAS functionpasses its own internal BITEtestT2CAS TCAS function is operational. If otherannunciators are on, the problem is in the indicatedsubsystem or aircraft wiring.TCASFAILThe T2CAS TCAS functionhas failed its own internalBITE testReplace the T2CAS computer unit.TOPANTThe top antenna DCresistance test indicates afailureRemove the T2CAS computer unit. Use a multimeterto measure the DC resistances indicated in Table 6--5for the top antenna. Repair antenna cables or replacethe antenna as required.BOTANTThe bottom antenna DCresistance test indicates afailureRemove the T2CAS computer unit. Use a multimeterto measure the DC resistance indicated in Table 6--5for the bottom antenna. Repair antenna cable(s) orreplace the antenna as required.HDG Heading input function notusedNot applicableTADISPTraffic advisory displaydiscrete signals No.1 or No. 2indicate a failureCheck wiring and power to TA display. (On both sidesof the Flight Deck, if two are installed.) Make surethat RA/TA valid discrete 1 and 2 (RMP--7E andRMP--7J) are <3.5 V dc to ground. Repair wiring orreplace display as required.RADISPResolution advisory displaydiscrete signals No.1 or No. 2indicate a failureCheck wiring and power to RA displays. Make surethat RA valid discrete 1 and 2 (RMP--14C andRMP--13E) are <3.5 V dc to ground. Repair wiring orreplace display as required.RADALTRadio altitude source No.1 orNo. 2 is invalid or has failedCheck wiring and power to the radio altimeters. Foranalog radio altimeters, make sure the RAD ALT No.1and No.2 valid discrete (RMP--2K and RBP--3C) are>18.5 V dc. Repair wiring or replace radio altimeteras required.XPDRBUSMode S Transponder No.1 orNo. 2 is invalid or has failed.Check wiring and power to the transponders. Checkfor data on XT 429 bus No.1 and No.2 (RMP--14F/Gand RMP--14H/J). Repair wiring or replacetransponder as required. If the Single Mode STransponder program pin (RMP--10D) is not groundedin installations using --XX003, --XX004 TCASComputer Units, a XPDR Bus Fault may bedisplayed.ATT Attitude input function notused.Not applicable
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.6--29F. Directional Antenna Test / Fault Isolation ProcedureNOTE: These procedures are recommended only if a T2CAS TCAS function bite orextended test failure of the top or bottom directional antenna has occurred.(1) Review extended maintenance or flight leg BITE data to determine which antennahas failed.(2) Remove T2CAS computer unit from mounting tray. Visually examine all antenna coaxcable connectors at the mounting tray side as well as the LRU connectors. Removeany foreign material discovered and reinstall the LRU.(3) Do a system self--test to determine if the fault has cleared. If the failure continues,remove the T2CAS computer unit and proceed.(4) Do a continuity test at the LRU end of each antenna cable. The resistance valuesshould be as specified in Table 6--5.(5) If an open circuit, short circuit, or unacceptable resistance measurement is detectedon the directional antenna path, a failure has occurred in the connector, coax cable,or directional antenna.(6) Locate the directional antenna that has a suspected failure. Remove the coax cablefrom the antenna port that is suspected to have failed. Isolate which section of theantenna system is at fault by a process of elimination. The resistance values of theantenna ports should be as specified in Table 6--5.(7) Remove and replace the appropriate failed component in accordance with approvedAircraft Maintenance Manual procedures.Table 6--5. Antenna Wiring ResistanceAntennaConnectorSection Pin DC ResistanceTop Directional Antenna LTP 12341000 ±100 Ohms8060 ±800 Ohms4020 ±400 Ohms2000 ±200 OhmsBottom Directional Antenna LMP 12341000 ±100 Ohms8060 ±800 Ohms4020 ±400 Ohms2000 ±200 OhmsOptional BottomOmnidirectional AntennaLMP 12340 to 50 Ohms (50 Ohms maximum)Infinite (>50K Ohms)Infinite (>50K Ohms)Infinite (>50K Ohms)
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.6--30NOTE: The procedures that follow are recommended for intermittent antenna systemfailures or if the continuity tests have not identified a failed component in theantenna system or if the flight crew detects an unacceptable visual discrepancybetween an intruder aircraft and its displayed location.(8) If the displayed location of an intruder aircraft is believed to be in error, appropriateramp test equipment can be used to simulate intruder aircraft to check the suspecteddiscrepancy while on the ground.(9) Remove the suspected TCAS directional antenna and terminate the antenna side ofthe cable with a 50 ohm termination (Omni--Spectra Part Number 3102--6100--00 orequivalent TNC jack with VSWR ≤1.15 : 1).(10) Perform a thorough inspection for moisture or contamination of all coax cableassemblies.(11) Remove the T2CAS LRU and do a VSWR check on the coax cable from the T2CAScomputer tray side. Use approved VSWR test equipment and operating procedures.The measured VSWR should be less than 2.0 : 1.(12) If the VSWR test fails, isolate failed antenna coax section. Remove/repairappropriate cable and/or connector.(13) An additional procedure for troubleshooting TCAS antenna system failures is todetermine the RF insertion loss in the TCAS antenna coaxial cables. RF insertionloss is equivalent to RF IxR (voltage) drop through the coax and is measured in dBrather than volts. Each coax cable is required to have is 2.5 dB ( ±0.5 dB) of insertionloss and the loss in all the coax cables must be within 0.5 dB of each other. ManyVSWR meters have a fixed RF source and can be used to measure RF insertion loss.In this test, the VSWR meter is used to measure the loss up one cable and down theother. The total loss should not exceed 6 dB.NOTE: The VSWR/insertion loss meter should be set up for L--band frequencies(approximately 1.0 GHz).To perform an RF insertion loss test, do the following:(a) Connect two of the TCAS antenna coax cables to each other at the antenna endwith a DC shorted coupler.(b) Before any measurements are taken on the antenna system, the meter and anyconnectors/cables that are used to connect the meter to the TCAS antennasystem must be zeroed out. This is typically done with a calibration adjustmenton the VSWR meter.(c) After the VSWR meter (and associated connectors/cables) have been calibratedfor 0 dB, connect the VSWR meter to the TCAS antenna coaxes under test (atthe LRU end). Measure and record the RF loss.(d) Test different combinations of the TCAS antenna coax cables by connecting thecoupler (at the antenna end) to different coax cables. By process of elimination, itcan be determined if one of the TCAS antenna coax cables has excessive RFinsertion loss.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.6--31(e) As an example, suppose the following insertion losses have been measured:Antenna Port Antenna Port Measured Loss090 8.5 dB0180 5.5 dB90 180 8.0 dBIt can be seen that when the coax connected to the 90 degree port is included inthe measurement, there is excessive loss. Simple algebra can be used todetermine that this coax has 5.5 dB of insertion loss.NOTE: 1 dB of excessive loss in one cable can result in about 3.5 degrees ofintruder bearing error.(14) If the VSWR tests and RF insertion loss test comply, return the directional antenna tothe manufacturer for further testing. Install a new directional antenna in accordancewith Aircraft Maintenance Manual procedures.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.6--32Blank Page
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.7--1MAINTENANCE PRACTICES1. GeneralThis section provides instructions for removing, reinstalling, and adjusting each LRU of theT2CAS that has been previously installed by the aircraft manufacturer or completion center.Where applicable, instructions for replacing lamps, knobs, and set screws are included.Adjustment information is called out as required.CAUTION: SHOULD ANY INSTALLATION CRITICAL CASES ARISE WITH THEREINSTALLATION OF ANY UNIT, YOU MUST COMPLY 100 PERCENT WITH THEINSTRUCTION.CAUTION: TO PREVENT DAMAGE TO EQUIPMENT, TURN AIRCRAFT POWER OFF WHENREMOVING OR INSTALLING LRUS.When removing or installing any T2CAS LRU, prepare the aircraft for safe groundmaintenance. Open and tag all applicable system circuit breakers.2. Equipment and MaterialsCAUTION: BEFORE YOU USE A MATERIAL, REFER TO THE MANUFACTURERS’ MATERIALSAFETY DATA SHEETS FOR SAFETY INFORMATION. SOME MATERIALS CAN BEDANGEROUS.Maintenance materials identified with a Honeywell Material Number (HMN) are given inTable 7-- 1.Table 7-- 1. MaterialsName Description SourceHMN 9722878 Sealing compound,temperature--resistant,high--adhesion, two component,polysulfide synthetic rubber(MIL--S--8802, Type I --dichromate cured sealingmaterials, Class B1/2 --spreadable) — PR--1422 (baseand accelerator)Courtaulds Aerospace,Glendale, CANOTES:1. Equivalent alternatives are permitted for materials in this list.2. The HMN codes in the list of materials identify the HMN given to each material.No additional special equipment or materials, other than those commonly used in the shop,are required to install the units in existing trays and clamps, and to adjust the system. Do notover tighten mounting screws. Where torque values are not given, it is acceptable to fingertighten the mounting screws.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.7--23. Procedure for the TT--950/951/952 T2CAS Computer UnitA. Removal and Installation Procedure(1) Remove the T2CAS computer unit.(a) Loosen mounting tray hold--down knobs.(b) Slowly pull forward on the computer unit handle to separate computer unit andmounting tray connectors. The computer unit is now free to be removed from themounting tray.(c) Place electrostatic protective covers on the computer unit and the mounting trayelectrical connectors.(2) Reinstall the T2CAS computer unit.(a) Remove protective plastic covers from aircraft connectors. Remove electrostaticprotective covers from computer unit electrical connectors.(b) Slide computer unit into mounting tray.CAUTION: DO NOT FORCE FIT. IF MATING IS DIFFICULT, REMOVE THE COMPUTERUNIT AND EXAMINE THE CONNECTOR FOR PINS THAT ARE BENT OROUT OF ALIGNMENT. ALSO CHECK THE ALIGNMENT OF THERECEPTACLE IN THE MOUNTING TRAY.(c) Carefully apply firm pressure until the computer unit connectors mate with theconnector receptacles on the mounting tray.(d) Tighten mounting tray hold--down knobs to make sure all connectors are fullyengaged.B. Adjustment ProcedureNot Applicable.C. Repair ProcedureNot Applicable.D. Return to Service ProceduresDo the Return to Service Test Procedures referenced in the ADJUSTMENT/TEST sectionof this manual.4. Procedure for the APMA. Removal and Installation Procedure(1) Remove the APM.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.7--3(a) If APM is attached to the T2CAS mounting tray, remove the screws that attachthe APM to the T2CAS mounting tray.(b) Loosen the screws that attach the APM to the APM Mating Connector.(c) Carefully disconnect the APM from the APM Mating Connector.(2) Reinstall the APM.(a) Carefully insert the APM connector plug into the APM Mating Connector.(b) Tighten the screws that attach the APM to the APM Mating Connector.(c) If APM is to be attached to the T2CAS mounting tray, reattach the APM to theT2CAS mounting tray using the provided mounting screws.NOTE: If a new APM (blank or previously programmed for a different aircraft) is installed,the APM must be reprogrammed as specified in Adjustments/Test, section 6--D.B. Adjustment ProcedureNot Applicable.C. Repair ProcedureThe ACSS APM is a non--repairable item. If the APM is damaged or determined to befaulty, it must be replaced with a new APM.D. Return to Service ProceduresDo the Return to Service Test Procedures referenced in the ADJUSTMENT/TEST sectionof this manual.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.7--45. Procedure for the Directional AntennaA. Removal and Installation Procedure(1) Remove the directional antenna.(a) If applicable, use a phenolic scraper to remove aerodynamic sealant aroundperiphery of antenna.(b) Remove four or eight (quantity depends on dash number of antenna) non--Torxdrive screws used to attach antenna to fuselage. See Figure 2--9 for locationand number of mounting holes for each dash number antenna.(c) Carefully lift antenna from fuselage avoiding any damage to the coaxial cables.(d) Disconnect coaxial cables from antenna connectors J1, J2, J3, and J4.(e) Put protective covers on the aircraft coaxial cable connectors and the antennacoax connectors.(2) Reinstall the directional antenna.(a) If applicable, remove any existing aerodynamic sealant from antenna and cleanantenna mounting area.(b) Put supplied o--ring in antenna o--ring groove. If antenna is supplied with aTeflon gasket, install gasket between antenna and fuselage.(c) Remove protective covers from antenna and aircraft coaxial mating connectors.(d) Examine antenna and coaxial mating connectors to make sure they are cleanand secure.(e) Orient antenna with respect to airframe (arrow painted on radome must pointforward). Connect four aircraft coaxial cables to antenna. Refer to Figure 2--12for wiring information. Note the color bands on the antenna connectors andcables: yellow = J1, black = J2, blue = J3, and red = J4.NOTE: Do not apply a sealant between antenna base and fuselage.Application of a sealant will reduce lightning protection.(f) Align antenna mounting holes with holes in fuselage (note the non--symmetrichole pattern).(g) Attach antenna to fuselage with four or eight (quantity depends on dash numberof antenna) non--Torx drive screws and flat washers. See tables 3 and 4 ofFigure 2--12 for dash number mounting information. Apply a sealant to the screwthreads before installing them. Torque mounting screws to 22 ±3 inch--pounds(2.5 ±0.2 Newton--Meters).(h) Apply an aerodynamic sealant around periphery of the antenna base to preventseepage of water and condensation and to preclude corrosion.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.7--5B. Adjustment ProcedureNot Applicable.C. Repair ProcedureThe ACSS TCAS Directional Antenna is a non--repairable item. If the antenna isdamaged or determined to be faulty, it must be replaced with a new antenna.D. Return to Service ProceduresDo the Return to Service Test Procedures referenced in the ADJUSTMENT/TEST sectionof this manual.6. Procedure for the Omnidirectional AntennaA. Removal and Installation Procedure(1) Remove the Omnidirectional Antenna.(a) If applicable, use a phenolic scraper to remove aerodynamic sealant aroundperiphery of antenna baseplate.(b) If applicable, remove sealant from antenna mounting screw holes.(c) Remove retaining screws used to attach antenna to aircraft fuselage.(d) Carefully pull antenna from fuselage.(e) Disconnect coaxial cable from antenna connector.(f) Put protective covers on the aircraft coaxial cable connector and the antennaconnector.(2) Reinstall the Omnidirectional Antenna.(a) If applicable, remove any existing aerodynamic sealant from antenna mountingsurface and clean antenna mounting area.(b) Remove and clean sealant from baseplate and baseplate cutout.(c) Remove protective covers from antenna and coaxial cable connectors.(d) Examine antenna and coaxial cable connectors to make sure they are clean andsecure.(e) Connect aircraft coaxial cable to antenna connector.(f) Apply a coating of sealant under heads of antenna mounting screws and positionantenna on fuselage mounting surface. Attach antenna to fuselage withmounting screws.(g) Apply an aerodynamic sealant around the periphery of the antenna baseplate.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.7--6B. Adjustment ProcedureNot Applicable.C. Repair ProcedureMost omnidirectional antennas are non--repairable. If the antenna is damaged ordetermined to be faulty, it must be replaced with a new antenna.D. Return to Service ProceduresDo the Return to Service Test Procedures referenced in the ADJUSTMENT/TEST sectionof this manual.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.7--77. Procedure for the GPS AntennaA. Removal and Installation ProcedureTBDB. Adjustment ProcedureNot Applicable.C. Repair ProcedureTBDD. Return to Service Procedures8. Procedure for the Control PanelA. Removal and Installation Procedure(1) Remove the Control Panel.(a) Disengage Dzus fasteners on control panel.(b) Pull control panel out of aircraft mounting location and disconnect aircraft cableconnectors. Control panel is now free to be removed from aircraft.(c) Put electrostatic protective covers on control panel and aircraft mating electricalconnectors.(2) Reinstall the Control Panel.(a) Remove protective covers from control panel and aircraft mating connectors.(b) Connect aircraft cables to control panel connectors J1 and J2.(c) Insert control panel into mounting location.(d) Engage Dzus fasteners on the control panel to attach it to aircraft structure.B. Adjustment ProcedureNot Applicable.C. Repair ProcedureAny repair procedures should be in accordance with the manufacturer’s repairinstructions.D. Return to Service ProceduresDo the Return to Service Test Procedures referenced in the ADJUSTMENT/TEST sectionof this manual.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.7--89. Procedure for the VSI/TRA DisplayA. Removal and Installation Procedure(1) Remove the VSI/TRA Display.(a) Loosen screws of instrument panel mounting clamp.NOTE: Most installation clamps require the top screws be loosened to removethe instrument. Other clamps require the diagonal screws be loosened.Refer to the aircraft maintenance manual (AMM) for specific application.(b) Pull the VSI/TRA out of the instrument panel and disconnect J1 matingconnector.(c) Put electrostatic protective covers on display and aircraft mating electricalconnectors.(2) Reinstall the VSI/TRA Display.(a) Remove protective covers from display and aircraft mating connectors.(b) Connect aircraft cable to VSI/TRA connector J1.(c) Insert the display into the instrument panel and push all the way back againstpanel.(d) Tighten the four instrument mounting clamp screws.B. Adjustment ProcedureNot Applicable.C. Repair ProcedureNot Applicable.D. Return to Service ProceduresDo the Return to Service Test Procedures referenced in the ADJUSTMENT/TEST sectionof this manual.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.7--910. Procedure for the TransponderA. Removal and Installation Procedure(1) Remove Transponder(a) Loosen mounting tray hold--down knobs.(b) Slowly pull forward on the unit handle to separate transponder and mounting trayconnectors. The transponder is now free to be removed from the mounting tray.(c) Place electrostatic protective covers on the transponder and the mounting trayelectrical connectors.(2) Reinstall Transponder(a) Remove protective plastic covers from mounting tray connectors andtransponder electrical connectors.(b) Slide transponder into mounting tray.CAUTION: DO NOT FORCE FIT. IF MATING IS DIFFICULT, REMOVE THE UNIT ANDEXAMINE THE CONNECTORS FOR PINS THAT ARE BENT OR OUT OFALIGNMENT. ALSO CHECK THE ALIGNMENT OF THE RECEPTACLE INTHE MOUNTING TRAY.(c) Carefully apply firm pressure until the transponder connectors mate with theconnector receptacles on the mounting tray.(d) Tighten mounting tray hold--down knobs making sure all connectors are fullyengaged.B. Adjustment ProcedureNot Applicable.C. Repair ProcedureNot Applicable.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.7--10D. Return to Service Procedures(1) For installations using serial data bus (ARINC 429) altitude data:(a) The POST (automatic on power on) and PAST self--test (initiated from the controlpanel) are the only required Return to Service tests for the transponder.(b) After the transponder passes these tests, the appropriate logbook entries maybe made and the unit is ready for use.(2) For installations using parallel (Gillham code) altitude data:(a) The POST (automatic on power on) and PAST self--test (initiated from the controlpanel) must be passed.(b) Connect an air data tester to the aircraft pitot/static system and set up atransponder ramp tester.(c) Setup the air data tester to output the following altitudes. The transponder’sencoded altitude must correspond.•11,700 feet•24,400 feet•30,800 feet.NOTE: These three altitudes check the operation of all parallel altitude wires.(d) After the transponder passes these tests, the appropriate logbook entries maybe made and the unit is ready for use.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.7--1111. Instructions for Continued Airworthiness, FAR Part 25.1529Maintenance requirements and instructions for Continued Airworthiness of the T2CAS TrafficTerrain and Collision Avoidance System components are contained in the paragraphs thatfollow:Installation of the T2CAS on an aircraft by Supplemental Type Certificate or Form 337obligates the aircraft operator to include the maintenance information provided by this manualin the operator’s AMMl and the operator’s Aircraft Scheduled Maintenance Program.A. Maintenance information for the T2CAS (system description, removal, installation, testing,etc.) is contained in this manual.B. LRU part numbers and other necessary part numbers contained in this manual should beplaced into the aircraft operator’s appropriate aircraft illustrated parts catalog (IPC).C. Wiring diagram information contained in this manual should be placed into the aircraftoperator’s appropriate aircraft Wiring Diagram Manuals.D. The T2CAS components are considered on--condition units and no additionalmaintenance is required other than a check for security and operation at normalinspection intervals.E. If a system component is inoperative, remove unit, secure cables and wiring, collarapplicable switches and circuit breakers, and placard them inoperative. Reviseequipment list and weight and balance as applicable prior to flight and make a log bookentry that unit was removed (refer to FAR Part 91.213 or the aircraft’s MinimumEquipment List [MEL]).F. The T2CAS components can be repaired only at a factory authorized repair center or anappropriately rated FAA Part 145 repair station.G. Once repaired, reinstall the LRU in the aircraft in accordance with the original Form 337approved data or instructions in this manual. Do a Return to Service test of the systemand approve it for return to service with a log book entry in accordance with therequirements specified in FAR Part 43.9.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.7--12H. Scheduled maintenance program tasks to be added to the aircraft operator’s appropriateaircraft maintenance program are as follows:(1) Recommended periodic scheduled servicing tasks: None required.(2) Recommended periodic inspections are as follows:•The TCAS directional antennas used with the T2CAS should be removed and theunderlying structure inspected for deterioration and corrosion during zonalinspections usually performed in conjunction with heavy maintenance D checks.•The ATC transponder(s) used with this system have test and inspections that arerequired by FAR 91.413 to be completed every 24 months.(3) Recommended periodic scheduled preventative maintenance tests (Tests todetermine system condition and/or latent failures):•The ACSS T2CAS Computer Unit is designed to detect its own failures as well asfailures external to the computer unit. This BITE is continuously being executedon a periodic basis. No formal periodic maintenance is required for the T2CAScomputer unit or the VSI/TRA display.•The ACSS RCZ--852 Diversity Mode S Transponder is designed to detect its ownfailures. This BITE is continuously being executed on a periodic basis. No formalperiodic maintenance is required for the transponder other than the 24 monthrecertification test required by FAR 91.413.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.8--1INSPECTION/CHECK1. GeneralThe visual check procedures that follow are recommended for the T2CAS Traffic and TerrainCollision Avoidance System components after they have been installed in the aircraft.2. Equipment and MaterialsNone3. ProcedureCAUTION: BEFORE YOU DO ANY OF THE PROCEDURES THAT FOLLOW, MAKE SURE ALL T2CASSYSTEM CIRCUIT BREAKERS ARE PULLED.A. Check T2CAS Computer Unit(1) Visually examine all external surfaces for possible damage. Check dust cover andexternal connectors for dust, corrosion, or damage.(2) Check external parts for loose or damaged hardware.(3) Make visual check of wiring and connectors for damage.B. Check Antennas(1) Visually examine all external surfaces for possible damage.(2) Check cabling for breaks, burned areas, and damaged insulation.C. Check Control Panel(1) Visually examine all external surfaces for possible damage.(2) Check external parts (connectors, control knobs, annunciators) for looseness ordamage.(3) Check that controller is securely mounted (Dzus fasteners properly engaged).(4) Check controls for smooth, positive action.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.8--2D. Check VSI/TRA Display(1) Visually examine all external surfaces for possible damage. Check dust cover andexternal connector for dust or damage.(2) Check that display is securely mounted (locking mechanism is properly engaged).(3) Check that LCD glass is not scratched or cracked.E. Check Transponders(1) Visually examine all external surfaces for possible damage. Check dust cover andexternal connectors for dust, corrosion, or damage.(2) Check external parts for loose or damaged hardware.(3) Make visual check of wiring and connectors for damage.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.9--1CLEANING/PAINTING1. GeneralWhile the T2CAS Traffic and Terrain Collision Avoidance System is installed in the aircraft,cleaning is limited to the procedures given below. Painting and more extensive cleaningshould be done during shop maintenance when the LRUs can be disassembled. Detailedinstructions are given in each applicable component--level maintenance manual.2. Equipment and MaterialsWARNING: BEFORE YOU USE A MATERIAL, REFER TO THE MANUFACTURERS’ MATERIALSAFETY DATA SHEETS FOR SAFETY INFORMATION. SOME MATERIALS CAN BEDANGEROUS.Table 9--1 gives the equipment and materials required for cleaning and painting.Table 9--1. Equipment and MaterialsName Description SourceAbrasive paper No. 600, nonconductive abrasive Optional sourceAir supply Air ionizing nozzle gunattachment for compressed air(20 psi)Optional sourceCleaning brush Soft, natural--bristle(camel hair)Optional sourceGlass cleaner Ammoniated Optional sourceLens tissue Lint Free Optional sourceSandpaper Grit sizes 220 and 400 Optional sourceHMN 110C878 Catalyst, polyurethane — No.V66V44(--4)Sherwin--Williams Co,Cleveland, OHHMN 110C978 Reducer, polyurethane — No.R7K84Sherwin--Williams Co,Cleveland, OHHMN 1130778 Solvent — Isopropyl alcohol(99%), semigradeOptional sourceHMN 6008676 Lint free cloth — Bluewipes, No.TX512Texwipe Co,Upper Saddle River, NJ
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.9--2Table 9--1. Equipment and Materials (cont)Name SourceDescriptionHMN 94C2178 Coating, Prolane 2.8TPLUSpolyurethane, semigloss WHT,FED--STD--595, Color No. 27925— No. F63EXW968--4380Sherwin--Williams Co,Cleveland, OHHMN 9460078 Primer, coating, epoxy, low VOC(MIL--P--23377, Type I, Class 2)Optional sourceNOTES:1. Equivalent alternatives are permitted for equipment and materials in this list.2. The HMN codes in the list of materials identify the Honeywell Material Number (HMN) givento each material.3. CleaningCAUTION: IF YOU CLEAN ELECTROSTATIC SENSITIVE COMPONENTS WITH PRESSURIZED AIR,MAKE SURE THE HOSE HAS AN AIR IONIZING NOZZLE OR GUN. AN ELECTROSTATICCHARGE CAN CAUSE DAMAGE TO THE LRU COMPONENT PARTS IF THE NOZZLE ORGUN ATTACHMENT IS NOT USED.A. Clean T2CAS Computer Unit and Mounting Tray(1) Loosen mounting tray hold--down clamps and pull T2CAS computer unit out ofmounting tray.(2) Clean mounting tray with cloth or brush dampened with solvent, then dry with cloth orcompressed air.(3) Clean all dust and foreign matter from front panel and cover air vents with a cleancloth or brush dampened with solvent or clean with compressed air.B. Clean AntennasClean antennas with a cloth dampened with solvent. Dry with a clean cloth or usecompressed air.C. Clean Control Panel(1) Clean dust and foreign matter from cover and connectors with a brush dampenedwith solvent, then dry with a clean cloth or compressed air.(2) Clean front of control panel with a mild glass cleaner and soft cotton cloth.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.9--3D. Clean VSI/TRA Display(1) Clean front panel of display with a mild glass cleaner and soft cotton cloth.(2) Clean the glass face with a mild glass cleaner and lens tissue.E. Clean TranspondersClean transponders with a cloth dampened with solvent. Dry with a clean cloth or usecompressed air.4. PaintingA. TCAS Directional Antennas(1) ScopeThis procedure covers the removal and reapplication of coating to the TCASdirectional antenna. Localized touch--up is allowable and preferred using airbrushtechniques to ensure minimal paint thickness. The touch--up may be applied eitherwith the antenna on the aircraft or removed from the aircraft.(2) ProcedureWARNING: SOLVENTS AND COATINGS ARE COMBUSTIBLE. KEEP AWAY FROMHEAT AND OPEN FLAME.(a) CleanScrape away all filleting and adhesive material from area to be coated. Removesurface contamination using isopropyl alcohol or reducer.(b) Scuff SandIf the entire antenna is to be recoated, sand to primer with 220 grit sandpaper.An orbital sander is preferred. For localized touch--up, feather sand areas ofexposed radome material to provide a smooth transition to the painted surface.(c) Final SandIf the entire antenna is to be recoated, sand primer and through--holes using 400grit sandpaper or Scotch--Brite so the primer is removed except in swirlswherever possible.(d) Final CleanClean the surface to be coated with isopropyl alcohol or reducer.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.9--4(e) PrimeNOTE: The pot life of the primer after mixing components is 8 hours.1Cover each Torx screw head with an adhesive dot to prevent paint frombeing applied to the screw heads.2Mix components in a 1:1 ratio under slow agitation.3Allow 15 minutes before spraying.4Spray one light coat -- wet film thickness of 1.5 mils.•Viscosity -- 18 to 20 seconds No. 2 Zahn test•Gun orifice -- 363--A needle or equivalent•Fluid pressure -- 5 to 10 psi recommended•Air pressure -- 50 psi recommended.(f) Primer CureAllow the primer to air dry for a minimum of one hour and a maximum of 4 hoursbefore applying the top coat.(g) Paint1Mix paint in a base to catalyst ratio of 6:1 under slow agitation.NOTE: The percentage of reducer used can vary to meet the applicable colorstandard.2Spray one light tack coat and allow to dry 15 minutes.•Viscosity -- 20 to 22 seconds No. 2 Zahn test•Gun orifice -- 363--A needle or equivalent•Fluid pressure -- 5 to 10 psi recommended•Air pressure -- 50 psi recommended.3Apply final top coat -- total wet film thickness of 3.5 to 4.0 mils.(h) Drying CycleThe antenna must air dry overnight or be baked at 85 degrees Celsius for 30minutes minimum before flying. Remove the adhesive dots from the heads ofthe Torx screws.(3) Performance Verification TestingPerform a ramp test per approved aircraft maintenance procedure on the T2CASsystem to ensure the bearing accuracy is within specification after the coatingapplication.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.9--5B. Other T2CAS System LRUsExcept for minor touch up, painting should only be done after the LRU has been removedfrom the aircraft or during shop maintenance. Painting procedures and materials aregiven in the applicable LRU component maintenance manual (CMM).
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T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.10--1REPAIRS1. GeneralMajor repairs to the T2CAS system components are made only during shop maintenancewhen the equipment is removed from the aircraft. Detailed instructions for repair andadjustment of each of the repairable LRUs are presented in the applicable componentmaintenance manuals given in Table 10--1.Table 10--1. LRU Maintenance ManualLRUACSS ComponentMaintenance Manual (CMM) ATA NumberTT--950 T2CAS Computer UnitPart No. 9000000--10001TBD 34--43--11TT--951 T2CAS Computer UnitPart No. 9000000--55001TBD 34--43--11TT--952 T2CAS Computer UnitPart No. 9000000--20001TBD 34--43--11Control PanelPart No. 4052190--902, --904, --906, --90815--3841--01 34--43--01Control PanelPart No. 4052190--903, --905, --907, --90915--3841--03 34--43--05VSI/TRA IndicatorPart No. 4067241--8XX15--2254--01 22--54--01XS--950 Mode S Data Link TransponderPart No. 7517800--XXYYYA09--3839--002 34--52--08XS--950 S/I Mode S/IFF Data Link TransponderPart No. 7519350--XXYYYA09--3839--003 34--52--09RCZ--852 Diversity Mode S TransponderPart No. 7510700--850A09--3800--15 23--81--01
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T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.A--1APPENDIX A
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.A--2T2CAS AIRCRAFT CONFIGURATION WORK SHEETPlease fill out a T2CAStCustomer Worksheet for each aircraft type.Aircraft Operator Current GPWS Altitude Callout MenuAircraft Type (Ex. B747--200) Aircraft Quantity Configuration Variants (i.e., different displaytypes)Aircraft Serial Number(s) / Registration Number(s)Installation Approval InformationPlease provide the following as applicable.Installation Approval Method (i.e., ACSS FAA STC,customer local, OEM TC, etc.)Installer (include contact and phone number)Are the Aircraft FAA Type Certified? Installation Design and Kit Provider (customer, ACSS,etc.)Target Date for Initial Installation Plan for Fleet InstallationAircraft Systems InformationPlease provide the following information as applicable.Existing TCAS ll Manufacturer Model / Part NumberExistingModeSManufacturer Model / Part NumberExistingModeSTransponder(s) Number of Sources Available forT2CAStUseExistingModeSManufacturer Model / Part NumberExistingModeSControl Panel Number of Sources Available forT2CAStUse
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.A--3ExistingGPWSManufacturer Model / Part NumberExistingGPWSWindshear Detection Enabled?-Yes -NoNumber of Sources Available forT2CAStUseManufacturer Model / Part NumberRadio Altimeter *FormatofData Number of Sources Available forT2CAStUseManufacturer Model / Part NumberAir Data Computer *FormatofData Number of Sources Available forT2CAStUseManufacturer Part Number and Software VersionFMS *FormatofData Number of Sources Available forT2CAStUseIRS/INS/VGManufacturer Model / Part NumberIRS/INS/VG(Select Correct Input) *FormatofData Number of Sources Available forT2CAStUseDirectionalGyroManufacturer Model / Part NumberDirectionalGyro(If Applicable) *FormatofData Number of Sources Available forT2CAStUseManufacturer Model / Part NumberGPS *FormatofData Number of Sources Available forT2CAStUse
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.A--4Manufacturer Model / Part NumberILS Receiver *FormatofData Number of Sources Available forT2CAStUseStallWarningManufacturer Model / Part NumberStallWarningComputer *FormatofData Number of Sources Available forT2CAStUseManufacturer Model / Part NumberAngle of Attack (AOA) *FormatofData Number of Sources Available forT2CAStUseA. Aircraft Flight Deck Architecture for EFIS Equipped AircraftPlease provide the following information as applicable.EFIS Display Manufacturer Model / Part NumberEHSI Manufacturer Model / Part NumberMFD Manufacturer Model / Part NumberEICAS Manufacturer Model / Part NumberEFIS SymbolGenerator(s)Manufacturer Model / Part Number and SoftwareVersionEFIS Control Panel Manufacturer Model / Part Number
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.A--5B. Aircraft Flight Deck Architecture for Non--EFIS Equipped AircraftPlease provide the following information as applicable.Weather RadarManufacturer Model / Part NumberWeatherRadarDisplay Single or Dual Display ConfigurationWeatherRadarManufacturer Model / Part NumberWeatherRadarSingle or Dual Display ConfigurationDisplay RangeSource WXR Ranges (Ex. 10, 20, 40nm,etc.)pygSelection (WXRControl Panel) WXR Indicator or WXR ControlPanel Format of DataC. Aircraft Flap and Landing Gear DataLanding Gear Down jGnd / OpenLanding Flaps jGnd / Open j+28 VDC / Open j3WireSynchroFlap Angle jGnd / Open jDigital j3WireSynchroT2CAStSystem Integration WorksheetThe following checklist allows the user to define the level of system integration services required ofACSS’ Certification and Applications Engineering. Please mark/select the integration servicesdesired by the ACSS Certification and Applications Engineering:Option CheckServiceRequiredACSS AircraftApprovalOptionsDepartment of Services / Products Provided to Customer1Equipment Only No Systems Integration or Certification Services Requested ofACSS2Installation DataPackage (IDP)ACSS Coordinates the Development of the Aircraft InstallationData Package Sufficient to Obtain Airworthiness Approval
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.A--63Aircraft InstallationKitACSS Coordinates the Fabrication of Aircraft Installation KitsBased on The Installation Data Package4AirworthinessApprovalACSS Supports Customer’s Effort to Obtain a Local ApprovalNo Direct Approval Coordination by ACSS is Requested5AirworthinessApprovalACSS Coordinates the Airworthiness Approval(FAA STC, CAA Approval, Etc.)6InstallationSupportACSS Provides On--Site Installation Support for the FirstAircraft (Additional Aircraft as Mutually Agreed)7PhysicalInstallationACSS Coordinates the Touch Labor for the Physical Installationof the T2CAStSystemNote: This option involves many variables and will need tobe negotiated on a case--by--case basis.Aircraft Installation Kit WorksheetFor programs where installation kit services are requested of ACSS, the following table allows theCustomer to provide a general description of the type of kit required for its particular aircraft. It isanticipated that one aircraft installation kit worksheet will be completed for each aircraft type and/orof each aircraft configuration type.Review of the previous sections provides the user with a general understanding of the variousaspects of the T2CAStinstallation, and provides a basis for the kit installation options.Initial Aircraft Configuration1Mode STransponder(s) GPSTAWS SwitchAnnunicators2ExistingGPSPositionSourceExistingTCAS llExistingGPWS Number to Add2Source Desired20No No No 0 1 2 T2CAStOther31No No Yes 0 1 2 T2CAStOther3Discrete(cube)LRU(s) withEdge2No Yes No 0 1 2 T2CAStOther3(cube)UnitsEdgeLighted3No Yes Yes 0 1 2 T2CAStOther3UnitsInstalled inhLightedPanels4Yes No No 0 1 2 theInstrument5Yes No Yes 0 1 2InstrumentPanel or6Yes Yes No 0 1 2PanelorGlareshield7Yes Yes Yes 0 1 21. Select the row that best represents the current configuration of aircraft.2. Indicate selection by blackening the appropriate cells.3. If other compatible GPS source will be installed, please specify the manufacturer, model and part number of the unit.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.B--1APPENDIX B
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-2015 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.B--2Blank Page
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.B--3/(B--4 blank)APPENDIX BAIRCRAFT CONFIGURATION MATRIXTable B--1. Aircraft ConfigurationFigureNumber Aircraft TypeICDDocumentNo.RadioAltimeterAir DataComputerInertialSystem FMC GPS/GNSS ILS/ MLSAngle ofAttackDecisionHeightFlap/SlatSettingsOnboardMaintenanceSystemTerrain HazardDisplayB--1 King Air C90Configuration 18000119--002Note 1 RockwellCollins Alt--55BISS ADDU--80130--16 (AirData DisplayUnit)Dir Gyro:Sperry C--14AVert Gyro:Bendix--KingKVG--350Not InstalledHoneywell/TrimbleHT9100Garmin GNS530 Not InstalledBendix--KingEFS 40 Not Installed Not InstalledBendix RDR2000NOTES:1. The King Air Configuration 1 is internal to ACSS. As such, no ICD was created for this configuration. The document number given is for the ASDB SRS.
T2CAS / Part No. 9000000SYSTEM DESCRIPTION AND INSTALLATION MANUAL34-43-20 15 Feb 2003Use or disclosure of information on this page is subject to the restrictions in the proprietary notice of this document.B--5/(B--6 blank)Figure B--1. T2CAS King Air C90 Interface Block Diagram

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