installation manual TSS-4100 Integrated TCAS, Transponder, and ADS-B Traffic Surveillance System Export Control Classification Notice (ECCN) for this document is 6E991. © Copyright 2009 Rockwell Collins, Inc. All rights reserved.
TSS-4100 Integrated TCAS, Transponder, and ADS-B Traffic Surveillance System installation manual Printed in the United States of America © Copyright 2009 Rockwell Collins, Inc. All Rights Reserved. (_TSS-4100_IM_MAY_29/2009_) Rockwell Collins, Inc.
ROCKWELL COLLINS, INC. INSTALLATION MANUAL Export Control Classification Notice (ECCN) for this document is 6E991. PROPRIETARY NOTICE FREEDOM OF INFORMATION ACT (5 USC 552) AND DISCLOSURE OF CONFIDENTIAL INFORMATION GENERALLY (18 USC 1905) This document and the information disclosed herein are proprietary data of Rockwell Collins, Inc. Neither this document nor the information contained herein shall be used, reproduced, or disclosed to others without the written authorization of Rockwell Collins, Inc.
23-0809018 LIST OF EFFECTIVE PAGES INSERT LATEST CHANGED PAGES. DESTROY SUPERSEDED PAGES. NOTE: The portion of the text affected by the changes is indicated by a vertical line in the outer margins of the page. Changes to illustrations are indicated by shaded or screened areas, or by miniature pointing hands. Dates of issue for original and changed pages are: Original 0 . . . . . . . . . . . 29 May 2009 TOTAL NUMBER OF PAGES IN THIS PUBLICATION IS 210 CONSISTING OF THE FOLLOWING: Page No. *Change No.
523-0809018 TABLE OF CONTENTS Chapter/Para Page LIST OF ILLUSTRATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . v LIST OF TABLES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .vi INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . .
523-0809018 Chapter/Para 2.8 2.8.1 2.8.2 2.8.3 2.8.4 2.8.5 2.8.6 2.9 2.9.1 2.10 2.10.1 2.10.2 2.10.3 2.10.4 2.10.5 2.11 2.11.1 2.12 2.12.1 2.12.2 2.12.3 2.12.4 2.12.5 2.13 2.13.1 2.14 2.14.1 2.14.2 2.14.3 2.14.4 2.14.5 2.14.6 2.14.7 TABLE OF CONTENTS MODE S TRANSPONDER, TDR-94D, DATA. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TDR-94D ATC/Mode S Transponder Mounting Considerations. . . . . . . . . . . . . . . . . . . . . . . . . . . . .
523-0809018 Chapter/Para 4.5 4.5.1 4.5.2 4.5.3 4.5.4 4.5.5 4.5.6 4.6 4.6.1 4.7 4.7.1 4.8 4.8.1 4.8.2 4.8.3 4.8.4 4.8.5 4.8.6 4.8.7 4.8.8 4.8.9 4.8.10 4.9 4.9.1 4.9.2 4.10 4.10.1 4.11 4.11.1 4.11.2 4.11.3 TABLE OF CONTENTS Page TSS-4100 MODE S ADDRESS PROGRAMMING TOOL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-6 Programming Tool Support. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
523-0809018 Chapter/Para C.5 C.5.1 C.5.2 C.5.3 C.5.4 C.5.5 C.5.6 TABLE OF CONTENTS Page A429 INPUT BUSES. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . C-10 Control Bus Selection.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . C-10 Control Bus Labels. . . . . . . . . . . . . . . . . .
523-0809018 LIST OF ILLUSTRATIONS Number 1-1 1-2 1-3 2-1 2-2 2-3 2-4 2-5 2-6 2-7 2-8 2-9 2-10 2-11 2-12 2-13 2-14 2-15 2-16 2-17 2-18 2-19 2-20 2-21 2-22 2-23 2-24 2-25 3-1 3-2 3-3 3-4 3-5 3-6 3-7 3-8 3-9 4-1 4-2 4-3 4-4 4-5 4-6 4-7 4-8 4-9 4-10 C-1 C-2 E-1 Title Page Typical Single Traffic Surveillance System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
523-0809018 LIST OF TABLES Number 1-1 1-2 2-1 2-2 2-3 2-4 2-5 2-6 2-7 2-8 2-9 2-10 2-11 2-12 2-13 2-14 2-15 3-1 3-2 3-3 3-4 3-5 4-1 4-2 4-3 B-1 B-2 B-3 B-4 B-5 B-6 B-7 B-8 B-9 B-10 B-11 C-1 C-2 C-3 C-4 C-5 C-6 C-7 C-8 C-9 C-10 C-11 C-12 C-13 C-14 C-15 C-16 D-1 vi Title Page Equipment Covered. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-1 Associated Equipment. . . . . . . .
523-0809018 LIST OF TABLES Number D-2 D-3 D-4 D-5 D-6 D-7 D-8 Title Page Certification Categories.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . D-2 Unit Weight, Power Requirements, and Size.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . D-2 ANT-42 Environmental Qualification Form. . . . . . . . . . .
523-0809018 INTRODUCTION 1. GENERAL. This Installation Manual (IM) provides installation information regarding the TSS-4100 Traffic Surveillance System and its related equipment. 2. HOW TO USE THE MANUAL. This IM is written to Air Transport Association (ATA) Specification 100 standards and contains the chapters outlined below: 2.1. Chapter 1. General Information chapter describes the purpose and technical properties of the Traffic Surveillance System LRUs. 2.2. Chapter 2.
introduction AUTO BITE BNR CDU CPN CRC DCP DCU DPSK ECU EFIS ESDS FMS GPS HAE HDG Hg HIRF HSI HV IAPS IRS LRU MCU MFD ms MSL NA NVRAM PAM PFD PPOS RA RAM REL RIU ROM RTU SDI SLS STBY STC TA TBD TC TCAS TDR TFC TRE TSO TSA TSS TSSA TSM TTC TX x 523-0809018 Automatic Built-In Test Equipment Binary Control Display Unit Collins Part Number Cyclic Redundancy Check Display Control Panel Data Concentrator Unit Differential Phase Shift Keying External Compensation Unit Electronic Flight Instrument System Electr
introduction 523-0809018 To submit comments regarding this manual, please contact: Rockwell Collins, Inc. 400 Collins Rd NE Cedar Rapids, IA 52498-0001 Attn: Technical Operations M/S 153-250 or send email to: techmanuals@rockwellcollins.
523-0809018 SAFETY SUMMARY 1. GENERAL SAFETY INSTRUCTIONS. This manual describes physical and chemical processes which may cause injury or death to personnel or damage to equipment if not properly followed. This safety summary includes general safety precautions and instruction that must be understood and applied during operation and maintenance to make sure personnel safety and protection of equipment.
523-0809018 CHAPTER 1 General Information 1.1. INTRODUCTION. This publication provides all the specifications, principles of operation, and information necessary to install, test, and troubleshoot the TSS-4100 Traffic Surveillance System (TSS). The three major functions of the TSS-4100 follow: • The TSS-4100 is a Mode S transponder that replies to directed and all-call interrogations. • The TSS-4100 is a Traffic Alert Collision Avoidance System (TCAS) II, change 7 unit.
general information 523-0809018 Table 1-2. Associated Equipment. UNIT DESCRIPTION COLLINS PART NUMBER STANDARD QUANTITY OPTIONAL QUANTITY NOTE Information for the TDR-94D and ANT-42 is for reference only. Refer to the Pro Line II Comm/Nav/Pulse System Installation Manual, Collins Part Number (CPN) 523-0772719. TDR-94D Air Traffic Control Radar Beacon System (ATCRBS) Mode S Transponder: -008, -108, -308, -309, -408, or -409. 622-9210-X0X 1 ANT-42 Mode S omnidirectional antenna. Used with TDR-94D.
general information 523-0809018 Figure 1-1.
general information 523-0809018 1.3. SYSTEM OVERVIEW. This section gives an overview of the Traffic Surveillance System. 1.3.1. System Block Diagram. NOTE Most units report maintenance information in a diagnostic word to the built-in diagnostic system. This section does not refer to these diagnostic words. Refer to the maintenance section of this manual for diagnostic information. The system schematics are not intended to replace bench level repair coverage.
general information 523-0809018 Figure 1-2.
general information 523-0809018 Figure 1-3.
general information 523-0809018 1.4. COMPONENT DESCRIPTIONS. The Traffic Surveillance System fully integrates with an airplane transponder and TCAS control system.
523-0809018 CHAPTER 2 System Components 2.1. INTRODUCTION. NOTE The names of some Line Replaceable Unit (LRU) types do not match the initials of the functional name of the equipment. For example, the name TRE-930 does not match the initials of its functional name, the Mode S Omnidirectional Antenna. The information and instructions provided in this section are recommendations and do not necessarily correspond with any actual aircraft installation and wiring.
system components 523-0809018 2.2.3. TRE-930 Mode S Omnidirectional Antenna. The TRE-930 Traffic Alert Collision Avoidance System (TCAS) Antenna is the recommended lower omnidirectional antenna for the Traffic Surveillance System. It is a DC-grounded omnidirectional antenna, and is mounted on the outside of the aircraft fuselage. 2.2.4. TSA-4100 Mode S Directional Antenna. The TSS-4100 requires the upper antenna to be the TSA-4100 directional antenna.
system components 523-0809018 2.3. ANT-42 34-54-00. The sections that follow describe the external theory of operation, and general data of the ANT-42 L-Band antenna. 2.3.1. ANT-42, External Theory of Operation. Refer to Figure 2-7. This sheet shows the external wire signals to and from the ANT-42 and the TDR-94D. The ANT-42 antenna mounts on the top or bottom of an airplane. The antenna connects to the TDR-94D mode S transponder. There are no operator controls or adjustments on this antenna. 2.4.
system components 523-0809018 NOTE The ANT-42 only requires one of the connectors in the table that follows. Table 2-1. ANT-42 Mating Connector Hardware and Tooling.
system components 523-0809018 Figure 2-2.
system components 523-0809018 2.4.4. Installation and Removal. Make sure that the aircraft battery master switch is turned off before installing any equipment, mounts, or interconnect cables. Failure to do so could irradiate the installer. The TDR-94D ATC/Mode S transponder requires two ANT-42 antennas. One ANT-42 L-Band Antenna is mounted on top of the fuselage and the second ANT-42 antenna is mounted on the bottom of the fuselage.
system components 523-0809018 2.5. ECU-3000 34-54-00. The sections that follow describe the external theory of operation, internal theory of operation, and general data of the External Compensation Unit (ECU) in a Traffic Surveillance System. 2.5.1. External Control Unit, External Theory of Operation. The ECU is connected to the TSS through nine wires. Refer to Figure 2-3. This sheet shows a typical TSS External Compensation Unit connection, and the external wire signals to and from the TSS.
system components 523-0809018 • Programmed by the installer • Contains the Mode S address • Either data loaded, or programmed using the TSS-4100 ECU Mode S Address Programming Tool. Table 2-2. ECU Installation Strapping Data.
system components 523-0809018 Table 2-2. ECU Installation Strapping Data. - Continued Description Values Recommend (Function Using Setting) Default Altitude Limit B Range 0 - 127 decimal Recommend: 99 (9,900 ft) (TCAS) Aural Files Used 1 = Aural Files Used 0 = Aural Files Not Used (TCAS) Aural Advisory Discrete Delay 1 = Add delay to Aural Advisory discrete output 0 = No delay (TCAS) In Air Volume 000 = 16 dBm 40 mW 001 = 13 dBm 20 mW 010 = 10 dBm 10 mW 011 = 7 dBm 5 mW 100 = 4 dBm 2.
system components 523-0809018 Table 2-2. ECU Installation Strapping Data. - Continued Description Values Recommend (Function Using Setting) Aircraft Length/Width 0000 = L ≤ 15m, W ≤ 11.5m 0001 = L ≤ 15m, W ≤ 23m 0010 = L ≤ 25m, W ≤ 28.5m 0011 = L ≤ 25m, W ≤ 34m 0100 = L ≤ 35m, W ≤ 33m 0101 = L ≤ 35m, W ≤ 38m 0110 = L ≤ 45m, W ≤ 39.5m 0111 = L ≤ 45m, W ≤ 45m 1000 = L ≤ 55m, W ≤ 45m 1001 = L ≤ 55m, W ≤ 52m 1010 = L ≤ 65m, W ≤ 59.5m 1011 = L ≤ 65m, W ≤ 67m 1100 = L ≤ 75m, W ≤ 72.
system components 523-0809018 Table 2-2. ECU Installation Strapping Data.
system components 523-0809018 Table 2-2. ECU Installation Strapping Data. - Continued Description Values Recommend (Function Using Setting) Bus Speed RMP-7DC (A768 Future Input − Provision) 1 = High Speed 0 = Low Speed Bus Speed LMP-9DC (General Purpose #1 − Provision Output) 1 = High Speed 0 = Low Speed 2.6.4. ECU-3000 Illustration. Refer to Figure 2-4 for an illustration of the ECU-3000. Figure 2-4. ECU-3000 2.6.5. ECU-3000 Mating Connector Data.
system components 523-0809018 Figure 2-5. ECU-3000 Mating Connectors 2.6.6. ECU-3000 Outline and Mounting Dimensions. Refer to Figure 2-6 for an illustration of the ECU outline and mounting dimensions.
system components 523-0809018 Figure 2-6.
system components 523-0809018 2.6.7. Installation and Removal. Make sure that the aircraft battery master switch is turned off before installing any equipment, mounts, or interconnect cables. Failure to do so can damage the equipment. The unit should be mounted on a vertical surface. Other mounting orientations may be acceptable upon confirmation by engineering.
system components 523-0809018 2.7. TDR-94D 34-54-00. The sections that follow describe the external theory of operation, internal theory of operation, and general data of the Mode S transponder in a traffic surveillance system. 2.7.1. Mode S Transponder, External Theory of Operation. NOTE The term CONTROLLER refers to any transponder control unit, such as an Radio Tuning Unit (RTU), a Transponder Control (CTL), or a Control Display Unit (CDU).
system components 523-0809018 Figure 2-7.
system components 523-0809018 2.8. MODE S TRANSPONDER, TDR-94D, DATA. The TDR-94D is a Mode-A, Mode-C, and Mode-S diversity (two antenna) transponder. 2.8.1. TDR-94D ATC/Mode S Transponder Mounting Considerations. The TDR-94D transponder is mounted on the MMT-150 Modular Mounting Tray, CPN 622-9672-XXX. Piggyback mounting brackets are available to mount an MMT-150 Modular Mounting Tray over another MMT-150 Modular Mounting Tray.
system components 523-0809018 Figure 2-9. TDR-94D Mating Connectors 2.8.4. TDR-94D Outline and Mounting Dimensions. Refer to Figure 2-10 for an illustration of the TDR outline and mounting dimensions.
system components 523-0809018 Figure 2-10.
system components 523-0809018 2.8.5. Installation and Removal. Make sure that the aircraft battery master switch is turned off before installing any equipment, mounts, or interconnect cables. The installation and removal instructions for the TDR-94D follow. 2.8.5.1. Installation. The procedure to install the TDR-94D follows: a. Remove electrical power from the aircraft. b.
system components 523-0809018 2.8.6.6. The data bus input through an ARINC 429 high-speed receiver to the third input UART is read from the UART by the microprocessor. 2.8.6.7. The processor reads the discrete inputs through two buffer circuits. The first buffer provides the input port A/B select logic, strut switch logic, source identification logic, maximum airspeed logic, altitude input logic, and TCAS installed logic. 2.8.6.8. Parallel data is output from the microprocessor to the output UARTs.
system components 523-0809018 Figure 2-11.
system components 523-0809018 2.9. TRE-930 34-54-00. The sections that follow describe the external theory of operation, internal theory of operation, and general data of the TRE L-Band Omnidirectional Antenna in the traffic surveillance system. 2.9.1. TRE-930 L-Band Directional Antenna, External Theory of Operation. Refer to the TSS External Simplified Schematic Figure 2-19. This sheet shows the external wire signals to and from the TRE-930 and the TSS-4100.
system components 523-0809018 2.10.2. TRE-930 Mating Connector Data. Table 2-5 shows the mating connector hardware and tooling for the TRE-930. Also refer to the interconnect wiring diagram in the appendix. Table 2-5. TRE-930 Mating Connector Hardware and Tooling.
system components 523-0809018 Figure 2-13.
system components 523-0809018 2.10.4. Omni-Directional Requirements. If a different antenna is used instead of a TRE-930, there are requirements to be compatible with the TSS-4100. There are also requirements to facilitate certification with a TCAS/transponder system. 2.10.4.1. The requirements of an antenna to replace the TRE-930 for use with the TSS-4100 follow: • It must have a DC impedance of 50 Ω. • It must have continuous power at a minimum of 50 W. • It must have peak power at a minimum of 4 kW.
system components 523-0809018 2.11. TSA-4100 34-54-00. The sections that follow describe the external theory and general data of the directional Traffic Surveillance Antenna (TSA) in the Traffic Surveillance System. 2.11.1. Traffic Surveillance Antenna, External Theory of Operation. Refer to Figure 2-18 for a simplified block diagram that includes this antenna. The TSA-4100 Antenna acts both as an omni and a directional antenna at 1030 MHz & 1090 MHz at +/- 3 MHz for the Traffic Surveillance System.
system components 523-0809018 Figure 2-15.
system components 523-0809018 Figure 2-15.
system components 523-0809018 Figure 2-16.
system components 523-0809018 Figure 2-16.
system components 523-0809018 2.12.3. TSA-4100 Mating Connector Data. Table 2-6 shows the mating connector hardware and tooling for the TSA-4100. Also refer to the interconnect wiring diagram in Figure E-1. Table 2-6. TSA-4100 Mating Connector Hardware and Tooling.
system components 523-0809018 2.12.5.1.1. Place the antennas, especially the top antenna, as forward as possible on the aircraft fuselage. Make sure there are as few obstructions as possible between the antenna and the front of the aircraft. 2.12.5.1.2. Make sure that the lateral deviation between the top and bottom antenna is less than 25 feet. This is to make sure that both antennas receive and reply to an interrogation at about the same time. 2.12.5.1.3.
system components 523-0809018 Figure 2-17.
system components 523-0809018 2.12.5.2. Installation. To install a directional antenna, follow the steps below: a. Make sure all interconnect cabling is correct before continuing. b. Inspect the aircraft skin surface at the mounting location for dirt and corrosion. Clean as necessary. c. Install an O-ring, CPN 841-0004-030, in the groove on the bottom of the antenna. d. Connect the appropriate cable to the color-coded J1, J2, J3, and J4 of the antenna, then position the TSA-4100 Antenna.
system components 523-0809018 2.13. TSS-4100 34-43-00. The sections that follow describe the external theory of operation, internal theory of operation, and general data of the Traffic Surveillance System LRU in a traffic surveillance system. 2.13.1. Traffic Surveillance System, External Theory of Operation. Refer to Figure 2-18 and Figure 2-19. A transponder provides air traffic control and other aircraft with appropriate information about its own aircraft.
system components 523-0809018 Figure 2-18.
system components 523-0809018 Figure 2-19. Traffic Surveillance System, TSS-4100 No.
system components 523-0809018 2.14. TRAFFIC SURVEILLANCE SYSTEM, TSS-4100, DATA. The TSS-4100 Traffic Surveillance System is a major component of an aircraft traffic system. The TSS-4100 operates on 28 V dc. It contains all circuits necessary for computing, transmitting, and receiving functions of the TSS and interfacing with a transponder, antennas, and displays.
system components 523-0809018 Figure 2-21. TSM-4100 2.14.3. TSS-4100 Mating Connector Data. Figure 2-22 shows a mating connector pictorial for the TSS-4100. Each connector shows pin locations to aid the troubleshooting effort. Refer to the interconnect wiring diagram in the appendix. Table 2-7 shows the mating connector hardware and tooling for the TSS-4100. Table 2-7. TSS-4100 Mating Connector Hardware and Tooling.
system components 523-0809018 Table 2-7. TSS-4100 Mating Connector Hardware and Tooling.
system components 523-0809018 Figure 2-22. TSS-4100 Mating Connectors 2.14.3.1. TSS-4100 Mating Connector Pins and Functions follow: Table 2-8. TSS-4100 Mating Connector Pins and Functions, Power, Ground, Suppression.
system components 523-0809018 Table 2-8. TSS-4100 Mating Connector Pins and Functions, Power, Ground, Suppression. - Continued Pin Name Connector Pin Chassis Ground RBP 11 Suppression Coax - coaxial insert in the bottom corner of LMP LMP 1T Table 2-9. TSS-4100 Mating Connector Pins and Functions, ARINC 429 Input.
system components 523-0809018 Table 2-10. TSS-4100 Mating Connector Pins and Functions, ARINC 429 Output. - Continued Pin Name Connector Pin A Pin B CMU (Provision) RMP 9E 9F General Purpose #1 (Provision) LMP 9D 9C Table 2-11. TSS-4100 Mating Connector Pins and Functions, GPS Time Mark Input. Pin Name Connector Pin + Pin - GPS Time Mark #1 (On-side) LMP 9J 9K GPS Time Mark #2 (Cross-side) RMP 9J 9K Table 2-12.
system components 523-0809018 Table 2-12. TSS-4100 Mating Connector Pins and Functions, Discrete Input (Gnd = Active).
system components 523-0809018 Table 2-13. TSS-4100 Mating Connector Pins and Functions, Discrete Output (Gnd = Active). - Continued Pin Name Conn Pin Pin Name Conn Pin Aural Advisory C LMP 4A Test Data Address 0 RMP 7G Aural Advisory P LMP 4B Test Data Address 1 RMP 7H Aural Advisory TA LMP 4C Test Read RMP 7J Test Data 0 RMP 6C Test Write RMP 7K Table 2-14. TSS-4100 Mating Connector Pins and Functions, Audio Output.
system components 523-0809018 Figure 2-23.
system components 523-0809018 Figure 2-23.
system components 523-0809018 Figure 2-23.
system components 523-0809018 Figure 2-24.
system components 523-0809018 Figure 2-24.
system components 523-0809018 Figure 2-24.
system components 523-0809018 2.14.5. Cabling Considerations. For the TSS-4100: • Shield wires shall be no greater than 4 inches in length. • The wires from the TSS to the ECU shall be no greater than one meter in length. • The SDI strap shall be no greater than 6 inches in length. • The length of the wires from the TSS to the TSM shall be no greater than 18 inches in length. • The circuit breaker for the TSS should be rated for 7.5 Amps. 2.14.6. Installation and Removal.
system components 523-0809018 parallel antenna ports, four each for the top and bottom antennas on the aircraft. Each port represents a beam heading: fore, aft, port, starboard. The transmit port from the power amplifier is switched to one of these eight antenna ports. The receiver paths on the RF switch include fixed-gain, low-noise amplifiers and band-pass filtering. Each of the eight antenna ports feeds a separate receiver path.
system components 523-0809018 Figure 2-25.
523-0809018 CHAPTER 3 Operation 3.1. INTRODUCTION. NOTE This section is not intended to be a pilot’s guide, but is written to provide a basic knowledge and understanding of operating procedures for this system. For detailed data about the controls and displays of a specific airplane, refer to the Operator's Guide for that airplane. Line Replaceable Units (LRU) with specific controls and displays are described in this section.
operation 523-0809018 Figure 3-1.
operation 523-0809018 Table 3-1. Traffic Display (AFD-3010/3010E), TRAFFIC Page. CONTROL OR DISPLAY FUNCTION/DESCRIPTION Refer to Figure 3-1. TRAFFIC map The TSS traffic symbology is available for display on the display. Push the Traffic (TFC) line select key to show the TSS traffic overlay on the Horizontal Situation Indicator (HSI), arc, or Present Position (PPOS) Map formats. This map is a dynamic, heading-up pictorial that shows nearby transponder-equipped aircraft.
operation 523-0809018 Table 3-1. Traffic Display (AFD-3010/3010E), TRAFFIC Page. - Continued CONTROL OR DISPLAY TRAFFIC MODE DISPLAY FUNCTION/DESCRIPTION The traffic mode display shows the traffic altitude above/below limits selected, the aircraft altitude, and other traffic selected off. This window defines a zone of vertical air space relative to the aircraft. Intruders into this zone are tracked and considered potential threats.
operation 4 4 2 2 1 1 1 1 2 2 4 4 CLIMB PREVENTIVE DESCEND PREVENTIVE 4 4 2 2 1 1 1 1 2 2 4 4 CLIMB CORRECTIVE 523-0809018 DESCEND CORRECTIVE = RED = GREEN TPI4301_02 Figure 3-2.
operation 523-0809018 LNV1 APYD VPATH ALTV 2O 1O 1O 2O = RED = GREEN TPI4301_03 Figure 3-3. Resolution Advisory Display (AFD), Pitch Cues Table 3-2. Resolution Advisory Display (AFD), TCAS II Fly-To Commands and Pitch Cues. CONTROL OR DISPLAY FUNCTION/DESCRIPTION Refer to Figure 3-2 for an illustration of Fly-To Commands on an RA Vertical Speed indicator. RA Fly-To Commands NOTE The message TRAFFIC shows in red below the vertical speed scale on the PFD when the system detects RA traffic.
operation 523-0809018 Table 3-2. Resolution Advisory Display (AFD), TCAS II Fly-To Commands and Pitch Cues. - Continued CONTROL OR DISPLAY RA Pitch Cues, Attitude Indicator FUNCTION/DESCRIPTION The TCAS Resolution Advisory (RA) pitch cues are shown on the PFD attitude indicator. The pitch cues advise the pilot of the pitch attitude that is necessary to satisfy a vertical RA. RA cues are issued by the TSS when aircraft corrective maneuvering is required in order to avoid a potential collision.
operation 523-0809018 Figure 3-4. Top Level Radio Tuning Page, RTU-42XX Radio Tuning Unit Figure 3-5.
operation 523-0809018 Table 3-3. Top Level Radio Tune Page, RTU Radio Tuning Unit or CDU Control Display Unit. CONTROL OR DISPLAY FUNCTION / DESCRIPTION Refer to Figure 3-4 for the top level radio tune page on an RTU. Refer to Figure 3-5 for the top level radio tune page on a CDU. NOTE Some of the controls listed are optional and may or may not be included depending on the installation. LINE SELECT KEYS The RTU and CDU have several panel mounted line select keys.
operation 523-0809018 Figure 3-6. TCAS Page, Radio Tuning Unit (RTU-42XX) Figure 3-7.
operation 523-0809018 Table 3-4. TCAS Page, Radio Tuning Unit or Control Display Unit. CONTROL OR DISPLAY FUNCTION/DESCRIPTION NOTE Some of the controls listed are optional and may or may not be included depending on the installation. Refer to Figure 3-6 for a typical TCAS Page on an RTU. Refer to Figure 3-7 for a typical TCAS Page on a CDU. TCAS CONTROL page Push the TCAS line key on the top level CDU (or RTU) page to select the TCAS CONTROL page.
operation 523-0809018 Table 3-4. TCAS Page, Radio Tuning Unit or Control Display Unit. - Continued CONTROL OR DISPLAY FUNCTION/DESCRIPTION SELECTION ANNUNCIATOR or TRAFFIC DISPLAY SELECT Push the adjacent line select key to set other traffic (non-threat traffic) monitoring ON (all traffic) or OFF (threat traffic only). The active state is shown in cyan and in large letters. RANGE SELECT (RTU only) Turn either tuning knob to set the display range.
operation 523-0809018 Figure 3-8. Transponder Page, RTU-42XX Radio Tuning Unit Figure 3-9. Transponder Page, CDU-62XX Control Display Unit Table 3-5. Transponder Page, RTU Radio Tuning Unit or Control Display Unit. CONTROL OR DISPLAY FUNCTION / DESCRIPTION Figure 3-8 shows the ATC main display page on an RTU. Figure 3-9 shows the ATC controls on a CDU.
operation 523-0809018 Table 3-5. Transponder Page, RTU Radio Tuning Unit or Control Display Unit. - Continued CONTROL OR DISPLAY ATC Page (RTU or CDU) FUNCTION / DESCRIPTION NOTE Identical control selections are presented on both RTUs (or on both CDUs) for the ATC transponder so that either pilot can make transponder control selections. To access the ATC Transponder main display page from the RTU or CDU top level page, push the ATC line select key two times.
523-0809018 CHAPTER 4 Maintenance 4.1. INTRODUCTION. NOTE Use the flight line maintenance procedures as customer acceptance test procedures by interconnecting the equipment on the bench using the equivalent of an aircraft interconnect harness and appropriate sensor data sources. Throughout these procedures the term Traffic Control is intended to apply to any traffic control Line Replaceable Unit (LRU). The term Traffic Surveillance System applies to the entire traffic system.
maintenance 523-0809018 4.2. MAINTENANCE SCHEDULE. The TCAS function of the TSS-4100 does not require any periodic maintenance. However, the transponder function must have an Air Traffic Control (ATC) transponder test and inspection according to FAR part 91 at a minimum of once every two years. 4.2.1. Cleaning and Painting. NOTE Observe all warnings and cautions listed in the advisories paragraph of this manual and the Collins Avionics Standard Shop Practices Manual.
maintenance 523-0809018 4.3. CONVERSION FROM TTR/TDR TO TSS SYSTEM. The Traffic Surveillance System (TSS) is designed to take the place of one TDR-94D and a TTR-920, TTR-921, or TCAS-4000, in an integrated system. 4.3.1. Preparation for Conversion. A list of requirements follows: • The TSS-4100 requires a 7.5 Amp breaker and 28 V input power. • The TSS-4100 requires concentrated input busses. If the existing system has a TDR-94D strapped to Configuration 2, this is already available.
maintenance 523-0809018 4.4. DATA LOADING. Explanations of data loading the ECU and the TSS-4100 follow. 4.4.1. ECU Data. The External Compensation Unit (ECU) attached to the TSS-4100 holds two sets of data. The first set of data, the TSS ECU Media Set Builder, contains the aircraft-configuration strapping for the TSS. These straps are detailed in Table 2-2. These data must be data loaded through the TSS-4100. Refer to Table 4-1 for the data load busses and pins.
maintenance • Set the SDI code of the unit to right or left. OR • Make sure the airspeed and ground speed are each less than 40 kts. • Make sure the Data Load Enable discrete (RMP10K) is grounded. • Make sure one of the air ground discretes is grounded. • Make sure the TSS-4100 receives an ARINC label with a data load request. The TSS uses ARINC label 027 as the data load input label and sends label 226 as the data load output label.
maintenance 523-0809018 Figure 4-1. TSS-4100, Electronic Nameplate 4.4.3.1. The top section of the electronic nameplate (lines 1 - 10) contains information regarding the TSSA-4100 software.
maintenance 523-0809018 • Be logged in with administrator credentials • At least one RJ-45 port on the PC/laptop • A Cross-Over RJ-45 Ethernet Cable. 4.5.3. Programming Tool Installation. NOTE This program requires Microsoft™ .NET 3.5 on the PC. If there is difficulty in installing .NET, uninstall all currently installed versions of Microsoft™ .NET before attempting the new installation. Contact your network administrator or information technology department for further assistance.
maintenance 523-0809018 Figure 4-2. Programming Tool - Select Network Interface Card c. Refer to Figure 4-3. If necessary, change the IP address to be 192.168.111.XXX, where XXX is anything except 110. Change the Subnet mask to 255.255.255.0. Make sure the Default Gateway and DNS server are blank. NOTE In the example below, the second IP address was changed from 192.168.111.120 to 192.168.111.255. This can be seen by looking at the IP Address (1) field in the Current IP Settings window.
maintenance 523-0809018 Figure 4-4. Programming Tool - Unlock the IP Address e. On the Programming Tool, select the System > Settings option. Make sure that the target IP address is 192.168.111.110 and that the port is 3000. Refer to Figure 4-5. Figure 4-5. Programming Tool - Verify the IP Address 4.5.5. Programming Tool Instructions. These instructions assume that the TSS-4100 is installed properly on the aircraft. a. Make sure that the TSS-4100 is off and in the “On Ground” state.
maintenance g. 523-0809018 Enter the Mode S Address. If entering in octal, the entered is eight digits between 0 and 7. If entering in hexadecimal, the entered value is 6 characters, each character being either a single digit (0 – 9), or a letter A thru F. NOTE If there are not enough characters for the selected base, zeroes (0s) will be added to the beginning of the value entered. h. Push the PROGRAM button and wait for up to a minute.
maintenance 9. 523-0809018 Help: Two options are available under Help: an option to view programming tool version information and an option to view these instructions. 10. Match Indicator: After pushing the Query Button, there will be an indication here if the address in the Mode S address box matches the Current Mode S box. If they match it will be green; if they do not match it will be red. Figure 4-6. Programming Tool - Screen Shot 4.6. LED INDICATORS.
maintenance 523-0809018 Figure 4-7. TSS-4100 Front Panel LEDs Table 4-3. LED Descriptions Indicator Color Description LRU STATUS indicator will light green whenever the self-test is successful. The LRU STATUS indicator will light red whenever the self-test fails. LRU STATUS RED/GREEN If this is red, it is probable that the TSS will need to be replaced. See the maintenance words for more information on this.
maintenance 523-0809018 Table 4-3. LED Descriptions - Continued Indicator Color Description ALTITUDE FAULT indicator will light whenever the selected altitude source is failed or missing. ALTITUDE INPUT RED If this is lit, check the transponder control panel to see if it is indicating that it is sending a valid altitude. If the transponder control panel is not sending the altitude, check to verify that the ADC on the PFD which is coupled to the autopilot is sending valid information.
maintenance 523-0809018 4.7. TEST EQUIPMENT AND POWER REQUIREMENTS. Test equipment required to perform the post-installation test procedures is below. Other equipment may be entirely satisfactory if it meets the specifications and is calibrated as necessary. • Combined TCAS/Transponder test set (such as the IFR-6000), or a TCAS test set and a transponder test set • Pitot Static Ramp Tester • Radio Altimeter Ramp Tester. 4.7.1. Power Requirements.
maintenance 523-0809018 4.8. TESTING AND TROUBLESHOOTING. The procedures in this section help isolate LRU failures. The built-in tests present in the Traffic Surveillance System and in the cross-side Mode S transponder system, make diagnostics easy to use on the flight line. For more information on the maintenance reporting of the TSS-4100 and TDR-94D see Appendix B. 4.8.1. Pre-installation Testing.
maintenance 523-0809018 Figure 4-8. TCAS Self Test Standard Output d. Verify that RA vertical guidance is shown on the system. This may be done in the form of pitch cues, path cues, or on a vertical speed tape. e. After the test is completed, the audio system announces, "TCAS SYSTEM TEST OK." If the audio system announces, "TCAS FAIL," instead, repeat self-test by pushing the TEST button on the front of the TSS-4100. The LEDs on the front of the unit show the source of the failure.
maintenance 523-0809018 (3) If this is a dual radio altimeter installation, simulate a radio altimeter system failure by opening both of the radio altimeter circuit breakers. Verify that TCAS FAIL is annunciated. (4) Reset the circuit breaker for the No. 1 radio altimeter. Make sure that the Traffic Surveillance System returns to normal operation. (5) Open the circuit breaker for the No. 1 radio altimeter. Make sure that TCAS FAIL is annunciated. (6) Reset the circuit breaker for the No.
maintenance 523-0809018 (14) Reset the system so that each PFD is using its primary ADC source. Select the off side transponder as the active transponder. Make sure that the system operates normally. 4.8.6. Range and Bearing Test. Perform this test when there is pilot complaint suggesting a problem that is related to bearing accuracy. Run this test with an IFR6000 or other equivalent TCAS test set. a. When testing the top antenna, monitor the TCAS display in the cockpit of the aircraft.
maintenance 523-0809018 Figure 4-9. Bearing Test, Aircraft and TCAS Test Set Orientation 4.8.7. TCAS RA Test. Perform a TCAS RA test when there is pilot complaint suggesting a problem related to TAs or to RAs. Find out which approximate bearing to check, if necessary. Run this test with an IFR-6000, or other equivalent TCAS test set. a. Make sure that the pressure altitude and radio altitude is at or above 1500 ft. b.
maintenance a. 523-0809018 Simulate a 2000 ft pressure altitude (uncorrected). Set the squawk code to 1234. Set the Flight ID to TEST1234. Set the selected altitude to 16000 ft. NOTE Other altitude values can be used to run this test. b. Run a Mode A/C decode and Side Lobe Suppression (SLS) test. Make sure they pass. Make sure that the proper altitude (2000 ft) and squawk code (1234) are reported. c. Run an XPDR A/C Spacing Width Test, which also tests the ATCRBS all-call functionality.
maintenance 523-0809018 at zero-range, and at the same altitude (±200 ft) as own aircraft. The intruder stays at own altitude regardless of evasive vertical maneuver. The problem can also make the display show a cluster of intruder targets at own altitude that move randomly. Check the continuity of the suppression interfaces to show any short-circuits. a. Remove all units connected to the suppression interface, including the TSS-4100, the transponder, and DME units. b.
maintenance 523-0809018 4.9. INITIAL INSTALLATION CHECK OUT PROCEDURE. Follow the procedures that follow to make sure the initial installation of the TSS-4100 performs well. 4.9.1. Initial Transponder Check Out. Follow the procedures described in Paragraph 4.8.8. 4.9.2. Initial TCAS Check Out. Follow the procedures that follow to make sure the initial installation of the TSS-4100 performs TCAS functions correctly. 4.9.2.1. Introduction.
maintenance 523-0809018 4.9.2.3. You should be familiar with how to use the TCAS test set you are using. This procedure does not give detailed instructions on test set operation. These are general instructions for a normal TCAS test set. Change these instructions to apply to your test set if necessary. 4.9.2.4. Equipment Preparation. NOTE Equipment Preparation means running any necessary self-tests, making the necessary connections, and placing the equipment as required for executing the test scenarios.
maintenance 523-0809018 • Scenario 4b: Low Altitude Don't Allow Increase Descent • Scenario 4c: Low Altitude TA Only. NOTE (1) There may be an approximately one second delay between symbol display and the aural advisory. (2) The maximum climb altitude is documented at airplane certification and may be different than the airplane service ceiling. Consult airplane data for applicable altitude. This altitude is programmed in the ECU. 4.9.2.5.1. Scenario 1a: Climb RA.
maintenance Display Range (approx) Display 523-0809018 Aural 12 nmi Other Traffic Symbol None 9 nmi TA Symbol TRAFFIC, TRAFFIC 6 nmi RA Symbol CLIMB, CLIMB 4.9.2.5.3. Scenario 2a: Climb RA just below maximum climb altitude. Scenario 2a and 2b are tests intended to ensure that the maximum climb altitude is properly programmed and read by TCAS. a. Set airplane under test (UUT) simulated altitude to 50 ft below (+/- 10 ft) the maximum climb altitude (NOTE 2).
maintenance 523-0809018 c. Start the scenario. d. Monitor the TCAS display and audio system for correct presentation as follows (NOTE 1): Display Range (approx) Display Aural If the maximum climb altitude is set between 10,000 and 20,000 ft: 12 nmi Other Traffic Symbol None 9 nmi TA Symbol TRAFFIC, TRAFFIC 6 nmi RA Symbol CLIMB, CLIMB If the maximum climb altitude is set to 20,000 ft or more: 12 nmi Other Traffic Symbol None 9.
maintenance Display Range (approx) Display Aural 12 nmi Other Traffic Symbol None 8 nmi TA Symbol TRAFFIC, TRAFFIC 6 nmi RA Symbol CLIMB, CLIMB At a range < 6 nmi 523-0809018 Verify that no increase climb advisory is issued. An RA should be maintained, but which RA being issued can change. This test passes as long as it is not an increase climb advisory. 4.9.2.5.7. Scenario 3c: Climb Inhibit. Scenario 3c can only be run if the "Climb Inhibit" discretes are connected and can be stimulated.
maintenance 523-0809018 Display Range (approx) Display Aural 12 nmi Other Traffic Symbol None 5 nmi TA Symbol TRAFFIC, TRAFFIC 3 nmi RA Symbol DESCEND, DESCEND At a range < 3 nmi RA Symbol INCREASE DESCENT, INCREASE DESCENT 4.9.2.5.9. Scenario 4b: Low Altitude Don't Allow Increase Descent. Scenario 4b shows that within a certain radio altimeter range, a descend advisory will be given, but an increase descent advisories will not be issued. a.
maintenance 523-0809018 d. Start the scenario. e. At a range of 5 nmi (or less) set the altitude rate to -500 fpm. This altitude rate change should occur as close to 5 nmi as possible. f. Monitor the TCAS display and audio system for correct presentation as follows (NOTE 1): Display Range (approx) Display Aural 12 nmi Other Traffic Symbol None 4 nmi TA Symbol TRAFFIC, TRAFFIC 4.10. RETURN TO SERVICE TEST PROCEDURE.
523-0809018 APPENDIX A Faults and Warnings A.1. GENERAL. The faults and warnings generated by the TSS-4100 include Light Emitting Diodes (LED) and maintenance words. The LEDs show on the front panel of the TSS-4100, and are described in Paragraph A.1. The maintenance words are sent by the TSS-4100 to the Maintenance Diagnostic Computer, and are described in Appendix B.
523-0809018 APPENDIX B Maintenance Words B.1. MAINTENANCE DIAGNOSTIC WORDS. Refer to Table B-1 for a list of the diagnostic words from the Traffic Surveillance System (TSS). Table B-2 shows how to interpret a diagnostic word. Use this table to decode the hexadecimal readouts. Refer to Table B-3 for the hexadecimal-to-binary conversion table. Refer to Table B-4 through Paragraph B.1.7 for a bit definition of each diagnostic word. Table B-1.
appendix B 523-0809018 Table B-2. Diagnostic Word Interpretation. These words show on the ADVANCED DIAGNOSTICS pages.
appendix B 523-0809018 Table B-3. Hexadecimal to Binary Conversion Table. HEXADECIMAL DIGIT BINARY VALUE 0 1 2 3 4 5 6 7 8 9 A (10) B (11) C (12) D (13) E (14) F (15) 1 0 1 0 1 0 1 0 1 0 1 0 1 0 1 0 1 2 0 0 1 1 0 0 1 1 0 0 1 1 0 0 1 1 4 0 0 0 0 1 1 1 1 0 0 0 0 1 1 1 1 8 0 0 0 0 0 0 0 0 1 1 1 1 1 1 1 1 1. Turn to the table that shows the Line Replaceable Unit (LRU) diagnostic word to be decoded. 2.
appendix B 523-0809018 B.1.1. Label 350 TDR Maintenance Word. This word is included as an output from the TSS as a way to be backward compatible with installations that previously had the TDR. Many of the controllers use this label as a way to know if the selected transponder is failed. The only field of this word that should be used is the SSM. If the SSM is 11, the TSS is not failed. If the SSM is 00, the TSS is failed. Refer to Paragraph B.2 for a complete definition of this word.
appendix B 523-0809018 B.1.3. Label 352 CDU Diagnostic Word 1. This label is forwarded if it is received through the selected control bus. The only change made to this label is changing the label number from 350 (from the selected control bus) to 352. See the appropriate documentation for the attached controller if a definition of this word is desired. B.1.4. Label 353 TSS-4100 Diagnostic Word 2. Refer to Table B-5 for the definition of this word. Table B-5.
appendix B 523-0809018 Table B-6. LRU Diagnostic Data, Fault Names and Categories.
appendix B 523-0809018 Table B-6. LRU Diagnostic Data, Fault Names and Categories.
appendix B 523-0809018 Table B-6. LRU Diagnostic Data, Fault Names and Categories.
appendix B 523-0809018 Table B-6. LRU Diagnostic Data, Fault Names and Categories.
appendix B 523-0809018 Table B-6. LRU Diagnostic Data, Fault Names and Categories.
appendix B 523-0809018 B.1.5. Label 354 TSS-4100 Diagnostic Word 3. Refer to Table B-7 for the definition of this word and a possible solution to the indicated issue. Table B-7. Label 354 TSS-4100 Diagnostic Word 3 Bit Label 354- TSS-4100 Diagnostics Word 3 9 SDI* 10 SDI* 11 LMP - 1C/D (Control A) (Active = 0 Inactive = 1) Check wiring from appropriate controller to the TSS. Repair wiring or replace the appropriate unit.
appendix B 523-0809018 B.1.6. Label 355 TSS-4100 Diagnostic Word 4. Refer to Table B-8 for the definition of this word. Table B-8.
appendix B 523-0809018 Table B-9. Label 355 Voltage Decode Voltage Index Decode Nominal Upper Limit Lower Limit 1 (VDC) = V * 32.66 31.5 36.3 29.7 2 (VDC) = V * 11.01 12.0 12.60 11.40 3 (VDC) = V 1.5 1.575 1.425 4 (°C) = (V − 0.424) * 160 Ambient temp N/A 5 (°C) = (V − 0.424) * 160 Ambient temp N/A 6 (VDC) = V * 5.71 8.0 8.22 7.54 7 (VDC) = V * -4.21 -8.0 -7.24 -8.34 8 (VDC) = V * 10.53 12.0 12.60 11.40 9 (VDC) = V * 2.00 3.3 3.44 3.16 10 (VDC) = V 1.5 1.
appendix B 523-0809018 B.1.7. Label 350 ACAS Diagnostics. Refer to Table B-10 for the definition of this word and a possible solution to the indicated issue. This label is created to replicate an equivalent word from Rockwell Collins TTR series of TCAS units. This is not sent through the TSS #X output busses. This label should only be used as a supplement to Label 351 and Label 354 on the TSS #X output busses. NOTE This label is sent to the displays on the TA/RA busses. Table B-10.
appendix B 523-0809018 Table B-10.
appendix B 523-0809018 B.2. TDR-94D DIAGNOSTIC CODES. Refer to Table B-11. A traffic control unit such as the CTL-92(), or a maintenance diagnostic system, lists TDR-94D diagnostic codes. Table B-11. TDR-94D Diagnostic Codes. PRIMARY CODE SECONDARY CODE None (refer to Note) DESCRIPTION DIAGNOSTIC DISPLAY T1 F/W No Fault Found NOTE With a No Fault Found condition, a pulsating AL will appear in the upper window and the baro altitude will appear in the lower window.
appendix B 523-0809018 Table B-11. TDR-94D Diagnostic Codes.
appendix B 523-0809018 Table B-11. TDR-94D Diagnostic Codes.
appendix B 523-0809018 Table B-11. TDR-94D Diagnostic Codes. - Continued PRIMARY CODE SECONDARY CODE FF DESCRIPTION Unacceptable Mode S address selected (all address lines identical) DIAGNOSTIC DISPLAY T1 F/W Yes Yes NOTE 1. Transmitter is inhibited (TI) and failure warn (F/W1) output (P1-31) is set only if a diagnostic Code 11 is detected. 2. Transmitter is inhibited and F/W1 discrete is set only if a diagnostic Code 21 is detected. 3.
523-0809018 APPENDIX C Buses and Other Interfaces C.1. INTERFACE TYPES. The various Line Replaceable Unit (LRU) in the Traffic Surveillance System (TSS) interface with each other and other systems using primarily ARINC 429 or discrete interfaces. Each bus has a unique name. The buses are primarily ARINC 429 or discrete format. Refer to Table C-1 for a list of the possible discrete and ARINC bus names. Refer to Table C-2 through Table C-16 for lists of the word labels on each digital bus.
appendix C 523-0809018 Table C-1.
appendix C 523-0809018 Table C-1.
appendix C 523-0809018 C.2. TSS DISCRETE OUTPUTS. Refer to Table C-2 for a list of the discrete outputs for the TSS and their expected destinations. Table C-2.
appendix C 523-0809018 C.3. TSS DISCRETE INPUTS. Refer to Table C-3 for a list of the discrete inputs to the TSS and their expected connections. Table C-3.
appendix C 523-0809018 Table C-3.
appendix C 523-0809018 C.4. TSS A429 OUTPUT BUSES. Refer to Table C-4 for a list of the ARINC 429 output buses and their expected destinations. Table C-4.
appendix C 523-0809018 Table C-5.
appendix C 523-0809018 Table C-7.
appendix C 523-0809018 C.5. A429 INPUT BUSES. Refer to Table C-9 for a list of the A429 Input Buses and their expected source. Table C-9.
appendix C 523-0809018 Table C-11.
appendix C 523-0809018 Table C-12. Concentrated Bus Inputs Bus Source TDR Bus TSS Bus Onside data concentrator FMS/IRS IAPS #1 Cross-side data concentrator AIS/ADS IAPS #2 C.5.3.1. The following figure is of the expected concentrated bus architecture with a right TSS and a left TDR using a single output bus from both the left and the right concentrator. Figure C-1. Bus Architecture, TSS (R) and TDR (L) C.5.3.2. A summary of the data sources that are sorted based on SDI is below.
appendix C Label Parameter Name 523-0809018 Notes 076 GNSS Altitude (MSL) (GPS) May be on GPS bus 101 Selected Heading/Track Required for ADS-B 102 Selected Altitude Either this or label 226 required for enhanced surveillance; 102 used for selected altitude that comes from a source other than the FMS 103 GPS Track Angle (GPS) Required for ADS-B, but may be on GPS bus 110 GNSS Latitude - Coarse (GPS) Required for ADS-B, but may be on GPS bus 111 GNSS Longitude - Coarse (GPS) Required fo
appendix C Label 523-0809018 Parameter Name Notes 302 Aircraft Registry Word 2 (Central Maint) Not required 303 Aircraft Registry Word 3 (Central Maint) Not required 310 Present Position Latitude (FMS) Not required, but desired as backup to GPS position 311 Present Position Longitude (FMS) Not required, but desired as backup to GPS position 312 Ground Speed (FMS) Required 313 Track Angle (True) (FMS) Required 314 True Heading (FMS) Not required 315 Wind Speed (FMS) Not required
appendix C 523-0809018 Table C-13.
appendix C 523-0809018 Table C-14. GPS Data/Time Mark Input Correlation - Continued Unit Time Mark Input GPS Input Concentrated Bus Input TDR GPS Time Tag (P2-37 & 38) GPS #1 FMS/IRS TDR None GPS #2 AIS/ADS C.5.4.4. Single vs Dual GPS Installation. Refer to Figure C-2 for an example block diagram of a GPS installation. In this diagram the Left GPS is standard and the right GPS is optional. NOTE There is an ECU setting for the TSS as to whether there should be one or two GPS inputs expected.
appendix C 523-0809018 C.5.5. XT-2 Input Bus (TDR to TSS). Refer to Table C-15 for a list of the labels received on the XT-2 input bus. NOTE The TSS only supports the DO-185A XT/TX protocol; it does not support the older TSO C119A protocol. Table C-15.
523-0809018 APPENDIX D Equipment Characteristics D.1. EQUIPMENT CHARACTERISTICS. Refer to Table D-1 for the equipment specifications. Refer to Table D-2 for the certification categories. Refer to Table D-3 for the equipment weight, power requirements, and size. Refer to Table D-4 through Table D-8 for the environmental qualifications of each piece of equipment. Table D-1. Equipment Specifications. CHARACTERISTIC SPECIFICATION Certification FAA Technical Standard Order (TSO) Refer to Table D-2.
appendix D 523-0809018 Table D-2. Certification Categories. Unit FAA TSO Environmental Categories ANT-42 C66b,C74c DO-160A E1/B/JLY/XRHXXXXXXXX ECU-3000 TSO-C112 & TSO-C119b (-802 status)+ TSO-C166a Transmit only (-803 status) DO-160E [(F2)(A2)V]ABB[(RBB1)(SCLM)(HR)] EYXXXXZ[AB]AZ[CC] [RR]M[X][X]AAX TDR-94D TSO-C112 Class 3A2 121 011 Level 3es DO-160E [(A2)(E1)-]BBA[SCLM] EXXXFXZZAZZC [RR]M[(A3)(Z3)X]XXAX TRE-930 C66, C74 DO-108 ABAXXXXCL1 NOTE This unit is not tested to DO-160 levels.
appendix D 523-0809018 Table D-4. ANT-42 Environmental Qualification Form. CONDITIONS Temperature and Altitude DO-160A SECTION AND REV 4.0 EQUIPMENT QUALIFICATIONS CATEGORIES OF CONDUCTED TESTS Category E1 - Temperature - Low Operating Temperature –55 °C (+5 °F) - High Operating Temperature +70 °C (+158 °F) - Low Storage Temperature –55 °C (-67 °F) - High Storage Temperature +85 °C (+185 °F) E1 - Altitude Temperature Variation 5.0 B Humidity 6.0 J Shock 7.0 L Vibration 8.
appendix D 523-0809018 Table D-5. ECU-3000 Environmental Qualification Form. CONDITIONS Temperature and Altitude DO-160E SECTION AND REV 4.
appendix D 523-0809018 Table D-5. ECU-3000 Environmental Qualification Form. - Continued CONDITIONS DO-160E SECTION AND REV 26.0 Fire/Flammability EQUIPMENT QUALIFICATIONS CATEGORIES OF CONDUCTED TESTS X NOTE The ECU-3000 Power Input is tested to the worst case of categories A, B, and Z with the exception of the 1 second power interruption test required for category Z.
appendix D 523-0809018 Table D-6. TDR-94D Environmental Qualification Form. CONDITIONS Temperature and Altitude DO-160E SECTION AND REV 4.
appendix D 523-0809018 Table D-6. TDR-94D Environmental Qualification Form. - Continued CONDITIONS DO-160E SECTION AND REV EQUIPMENT QUALIFICATIONS CATEGORIES OF CONDUCTED TESTS 1030 ±0.2 MHz from ATCRBS interrogators 1030 ±0.
appendix D 523-0809018 Table D-7. TSA-4100 Environmental Qualification Form. CONDITIONS DO-160E SECTION AND REV 4.0 Temperature and Altitude EQUIPMENT QUALIFICATIONS CATEGORIES OF CONDUCTED TESTS (D2)(F2)X - Temperature - Low Short Time Operating Temperature D2 - Low Operating Temperature D2 - High Short Time Operating Temperature D2 - High Operating Temperature D2 F2 - Altitude Temperature Variation 5.0 A Humidity 6.0 B Shock 7.0 B Vibration 8.
appendix D 523-0809018 Table D-8. TSS-4100 Environmental Qualification Form. CONDITIONS Temperature and Altitude DO-160E SECTION AND REV 4.0 EQUIPMENT QUALIFICATIONS CATEGORIES OF CONDUCTED TESTS [(F2)(A2)V] - Temperature - Low Temperature Storage F2 - High Temperature Operation F2 - High Temperature Storage F2 - Low Temperature Operation F2 - In-Flight Loss of Cooling V F2 - Altitude - Decompression A2 - Overpressure A2 Temperature Variation 5.0 A Humidity 6.0 B Shock 7.
appendix D 523-0809018 Table D-8. TSS-4100 Environmental Qualification Form. - Continued CONDITIONS DO-160E SECTION AND REV EQUIPMENT QUALIFICATIONS CATEGORIES OF CONDUCTED TESTS Transmit Frequency 1030 ± 0.01 MHz Receive Frequency 1090 ± 3 MHz Sensitivity 75 ± 1 dBm XPDR RF Characteristics NA Receive Frequency (XPDR) 1030 ± 0.
523-0809018 APPENDIX E Interconnect Diagram E.1. INTRODUCTION. This appendix contains the interconnect wiring diagram. Refer to Figure E-1. E.2. CABLING INSTRUCTIONS. Make sure the aircraft battery master switch is turned off before installing any interconnect cabling. NOTE Figure E-1 shows a possible interconnect between the TSS-4100 and various altitude and control sources. Because various part numbers of the TSS-4100 provide different strapping options this information is for reference only.
appendix E 523-0809018 E.4. SYSTEM INTERCONNECT DIAGRAM. Figure E-1 is the TSS interconnect wiring diagram in a consolidated format. The interconnect information for the TSS-4100 is also provided in the individual simplified Line Replaceable Unit (LRU) schematic diagrams in Chapter 2.
appendix E 523-0809018 (992-6037-001B_33) TPJ9606_01 Figure E-1.
appendix E 523-0809018 (992-6037-001B_44) TPJ9606_02 Figure E-1.
appendix E 523-0809018 (992-6037-001B_45) TPJ9606_03 Figure E-1.
523-0809018 © Copyright 2009, Rockwell Collins, Inc.
