Thales Communications AHV1600 Radio-altimeter Transceiver User Manual OIM
THALES Communications Radio-altimeter Transceiver OIM
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THALES Communications OPERATION AND INSTALLATION MANUAL AHV1600 Radar Altimeter System ORIGINAL ISSUE REF REVISION No : July 16/09 : 36719226-AA :0 TP Page 1/2 July 16/09 OIM AHV1600-SYSTEM THALES Communications TP Page 2/2 July 16/09 OIM AHV1600-SYSTEM THALES Communications RECORD OF REVISIONS INSERTION REVISION N° REVISION DATE DATE BY INSERTION REVISION N° REVISION DATE DATE BY RR Page 1/2 July 16/09 OIM AHV1600-SYSTEM THALES Communications RR Page 2/2 July 16/09 OIM AHV1600-SYSTEM THALES Communications RECORD OF TEMPORARY REVISIONS TEMPORARY REVISIONS N° PAGE N° INSERTED DATE DELETED BY REVISION N° BY RTR Page 1/2 July 16/09 OIM AHV1600-SYSTEM THALES Communications RTR Page 2/2 July 16/09 OIM AHV1600-SYSTEM THALES Communications SERVICE BULLETIN LIST SERVICE BULLETIN N° REVISION N° REVISION DATE SUBJECT SBL Page 1/2 July 16/09 OIM AHV1600-SYSTEM THALES Communications SBL Page 2/2 July 16/09 OIM AHV1600-SYSTEM THALES COMMUNICATIONS LIST OF EFFECTIVE PAGES SUBJECT PAGE DATE Title Page JULY 16/09 BLANK Record of Revisions JULY 16/09 BLANK Record of Temporary Revisions JULY 16/09 BLANK Service Bulletin List JULY 16/09 BLANK List of Effective Pages JULY 16/09 BLANK Table of Contents JULY 16/09 JULY 16/09 Table of Figures JULY 16/09 BLANK JULY 16/09 JULY 16/09 JULY 16/09 JULY 16/09 JULY 16/09 JULY 16/09 JULY 16/09 JULY 16/09 JULY 16/09 JULY 16/09 101 JULY 16/09 102 103 104 JULY 16/09 JULY 16/09 JULY 16/09 SUBJECT Installation Introduction Identification sheet General Presentation Operation PAGE DATE 105 106 107 108 109 110 111 JULY 16/09 JULY 16/09 JULY 16/09 JULY 16/09 JULY 16/09 JULY 16/09 JULY 16/09 112 113 114 115 116 117 118 119 JULY 16/09 JULY 16/09 JULY 16/09 JULY 16/09 JULY 16/09 JULY 16/09 JULY 16/09 JULY 16/09 120 121 122 123 JULY 16/09 JULY 16/09 JULY 16/09 JULY 16/09 201 202 203 JULY 16/09 JULY 16/09 JULY 16/09 204 205 206 207 208 209 210 211 JULY 16/09 JULY 16/09 JULY 16/09 JULY 16/09 JULY 16/09 JULY 16/09 JULY 16/09 JULY 16/09 301 302 JULY 16/09 JULY 16/09 LEP Page 1/2 July 16/09 OIM AHV1600-SYSTEM THALES Communications LEP Page 2/2 July 16/09 OIM AHV1600-SYSTEM THALES COMMUNICATIONS TABLE OF CONTENTS PAGES INTRODUCTION .................................................................................................................................................1 1. GENERAL INFORMATION ......................................................................................................................1 2. BLOCK PAGE NUMBERS FOR SECTIONS ...........................................................................................1 3. UPDATING ...............................................................................................................................................1 4. ADVISORIES............................................................................................................................................2 A. SAFETY INSTRUCTIONS / ELECTROSTATIC DISCHARGE PRECAUTIONS .................................2 B. SHORT - CIRCUIT PRECAUTIONS ....................................................................................................2 5. UNCOMMON ABBREVIATIONS AND ACRONYMS...............................................................................3 GENERAL ...........................................................................................................................................................1 1. AHV1600 RADAR ALTIMETER MAIN FUNCTION .................................................................................1 2. AHV1600 BASIC PRINCIPLE ..................................................................................................................1 3. BUILT IN TEST FUNCTION .....................................................................................................................3 A. POWER-UP BUILT IN TEST (PBIT).....................................................................................................3 B. INITIATED BUILT IN TEST (IBIT) ........................................................................................................3 C. CONTINUOUS BUILT IN TEST (CBIT) ................................................................................................3 4. AIRCRAFT INTERFACE ..........................................................................................................................3 PRESENTATION.............................................................................................................................................101 1. AHV1600 RADAR ALTIMETER SYSTEM GENERAL DESCRIPTION ...............................................101 2. AHV1600 TRANSCEIVER....................................................................................................................102 A. EXTERNAL CHARACTERISTICS....................................................................................................103 B. INTERNAL SUB-ASSEMBLIES........................................................................................................106 C. FUNCTIONAL CHARACTERISTICS................................................................................................106 3. OPERATIONAL INTERFACES ............................................................................................................117 A. POWER SUPPLY .............................................................................................................................117 B. DIGITAL ARINC429 INTERFACE ....................................................................................................117 C. AID SIGNALS INTERFACE ..............................................................................................................118 D. ENVIRONMENTAL CONDITIONS ...................................................................................................119 E. IN FLIGHT CONDITIONS.................................................................................................................120 4. ANTENNA ANT-140A...........................................................................................................................120 A. GENERALITIES ON ANTENNA ANT-140A .....................................................................................120 B. PHYSICAL CHARACTERISTICS .....................................................................................................120 C. FUNCTIONAL CHARACTERISTICS................................................................................................122 5. COAXIAL CABLES LENGHT ...............................................................................................................122 INSTALLATION ...............................................................................................................................................201 1. GENERAL CONDITIONS.....................................................................................................................201 A. POWER SUPPLY .............................................................................................................................201 B. LOCATION........................................................................................................................................201 C. WATER, SAND, AND DUST TIGHTNESS.......................................................................................201 D. MOUNTING ......................................................................................................................................201 E. INSTALLATION CONDITIONS.........................................................................................................201 2. STEP BY STEP TRANSCEIVER INSTALLATION...............................................................................202 A. CHOICE OF ANTENNAE LOCATION..............................................................................................203 B. ANTENNA MOUNTING ....................................................................................................................204 C. CONNECTION..................................................................................................................................205 3. VERIFICATION ....................................................................................................................................205 A. GROUND TESTS .............................................................................................................................205 TC Page 1/2 July 16/09 OIM AHV1600-SYSTEM THALES Communications PAGES IN FLIGHT TESTS ........................................................................................................................... 205 4. FUNCTIONAL CONNECTIONS WITH RELATED EQUIPMENT........................................................ 205 A. INTERFACES CONNECTIONS....................................................................................................... 205 B. GROUNDING AND BONDING ........................................................................................................ 206 C. COOLING OF THE EQUIPMENT .................................................................................................... 207 D. HANDLING....................................................................................................................................... 207 5. EQUIPMENT INPUTS / OUTPUTS ..................................................................................................... 207 A. MAIN CONNECTOR J1 ................................................................................................................... 207 B. RX/TX ANTENNA............................................................................................................................. 210 B. OPERATION................................................................................................................................................... 301 1. RADAR ALTIMETER ENERGIZATION ............................................................................................... 301 2. FUNCTIONNAL TEST ......................................................................................................................... 301 3. NORMAL OPERATING MODE ........................................................................................................... 301 4. OUT OF RANGE OPERATION ........................................................................................................... 301 5. FAILURE MODE .................................................................................................................................. 301 6. DEFAULT OPERATING INSTRUCTIONS .......................................................................................... 302 7. OPERATIONAL LEVEL MAINTENANCE TASK ................................................................................. 302 A. REMOVING THE TRANSCEIVER................................................................................................... 302 B. INSTALLING THE SPARE TRANSCEIVER .................................................................................... 302 TC Page 2/2 July 16/09 OIM AHV1600-SYSTEM THALES COMMUNICATIONS TABLE OF FIGURES PAGES Figure 1 – AHV1600 TRANSCEIVER SYSTEM ...........................................................................................4 Figure 101 – AHV1600 RADAR ALTIMETER SYSTEM BLOCK DIAGRAM............................................101 Figure 102 – AHV1600 TRANSCEIVER - GENERAL VIEW .............................................................102 Figure 103 – OVERALL DIMENSIONS.....................................................................................................103 Figure 104 – MANUFACTURING SERIAL NUMBER LABEL...................................................................104 Figure 105 – THALES IDENTIFICATION LABEL .....................................................................................104 Figure 106 – AMENDMENT LABEL..........................................................................................................105 Figure 107 – SPECIFIC LABEL ................................................................................................................105 Figure 108 – ORGANIZATION OF HEIGHT DATA WORD LABEL “164” ................................................108 Figure 109 – ORGANIZATION OF STATUS DATA WORD LABEL “271” ...............................................110 Figure 110 – ORGANIZATION OF STATUS DATA WORD LABEL “272" ...............................................112 Figure 111 – ORGANIZATION OF FIRST EQUIPMENT IDENTIFIER DATA WORD LABEL “371” .......112 Figure 112 – ORGANIZATION OF INTERMEDIATE EQUIPMENT IDENTIFIER DATA WORD LABEL “371”....... 113 Figure 113 – ORGANIZATION OF LAST EQUIPMENT IDENTIFIER DATA WORD LABEL “371” .........113 Figure 114 – ORGANIZATION OF STATUS DATA WORD LABEL “377" ...............................................114 Figure 115 – ORGANIZATION OF HEIGHT DATA WORD LABEL “165" ................................................116 Figure 116 – ANT-140A INNER SIDE.......................................................................................................121 Figure 117 – ANT-140A OUTER SIDE .....................................................................................................121 Figure 201 – ANT-140A – ANTENNAE SEPARATION AND ORIENTATION..........................................204 Figure 202 – SURFACES BONDING CONTACT OUTLINES ..................................................................206 Figure 203 – INTERCONNECTIONS........................................................................................................211 TF Page 1/2 July 26/09 OIM AHV1600-SYSTEM THALES Communications TF Page 2/2 July 16/09 OIM AHV1600-SYSTEM THALES COMMUNICATIONS INTRODUCTION 1. GENERAL INFORMATION The manual contains the information for the installation and the operation of the AHV1600 Radar Altimeter P/N: AHV1600-01-01 00 A for Aircraft. 2. BLOCK PAGE NUMBERS FOR SECTIONS Each section has a separate block page number: 1 - 99 : General 101 - 199 Presentation 201 - 299 Installation 301 - 399 Operation All values have been given in the units (or multiples or sub-multiples of these units) of the International System (S.I.). It is possible that the values are given in more usual units. The English equivalents are given into brackets. 3. UPDATING In case of update of the manual, detailed instructions for the insertion and deletion of applicable pages will be given. Revised texts, new texts or deleted texts will be located with a vertical black line in the margin. INTRO Page 1 July 16/09 OIM AHV1600-SYSTEM THALES Communications 4. ADVISORIES A. SAFETY INSTRUCTIONS / ELECTROSTATIC DISCHARGE PRECAUTIONS This graphic symbol showing a hand on a dark background (to IEC 747-1 standard) means that the equipment on which it appears (assembly or subassembly) contains components sensitive to electrostatic discharges. The following rules shall be complied with when carrying out any type of servicing on equipment bearing this symbol: The equipment shall be placed on a conducting or antistatic-working surface grounded through a resistance of between 250 kohm and 1 Mega-ohm. The operator shall wear a cotton smock and shall be linked with the working surface by a conducting wristband through a resistance of 1 Mega-ohm. Soldering iron shall be grounded. The transport and storage of parts removed from the equipment (printed board assemblies, modules, hybrid circuits, etc.) shall be done with conductive or antistatic packaging. B. SHORT - CIRCUIT PRECAUTIONS The inputs/outputs (I/O) are protected from short circuits but, by precautions no servicing shall be performed on any active or passive components while the equipment is energized. INTRO Page 2 July 16/09 OIM AHV1600-SYSTEM THALES COMMUNICATIONS 5. UNCOMMON ABBREVIATIONS AND ACRONYMS The following abbreviations, acronyms, and symbols are used in this manual: Abbreviation/Acronym Identification A/D AGL AID ANT AU BIT CBIT CR CSCI CTZ CW D/A dB dBm DC DMB EMC Fb FM FT Fore HI HIRF IBIT IEC I/O LO LRU LSB MAX MIN MPC NCD NO PBIT PC P/N R/A or RA RET RF RL Rx S.I. Analogical/Digital Above Ground Level Aircraft Installation Delay ANTenna Altimeter Unit Built In Test Continuous Built In Test Carriage Return Computer Software Configuration Item Coastal Transition Zone Continuous Wave Digital/Analogical deciBel deciBel milliwatt Direct Current Digital and Management Board ElectroMagnetic Compatibility Beat Frequency Frequency Modulation Functional Test Forward HIgh High Intensity Radiated Fields (Lightning) Initiated Built-In-Test International Electronical Commission Input /Output Low Line Replaceable Unit Lower Significant Bit MAXimum MINimum Multi Purpose Computer No height Computer Data Normal Operation Power On Built In Test Printed Card Part Number Radar Altimeter RETurn Radio Frequency Return Loss Reception International System INTRO Page 3 July 16/09 OIM AHV1600-SYSTEM THALES Communications Abbreviation/Acronym Identification ST SWR Tx USB VCO Saw Tooth Standing Wave Ratio Transmission Upper Significant Bit Voltage Controlled Oscillator INTRO Page 4 July 16/09 OIM AHV1600-SYSTEM THALES COMMUNICATIONS EQUIPMENT IDENTIFICATION SHEET AHV1600_RADAR ALTIMETER SYSTEM F0057 AHV1600 Transceiver Coaxial Antenna ANT-140A PHYSICAL CHARACTERISTICS MAIN COMPONENTS Qty DIMENSIONS (mm) Length Transceiver: AHV1600 Antenna: ANT140A 190 max WEIGHT P/N Width Height (kg) 90 max 95 max 2 kg AHV1600-01-01 00 A 33 max 0.130 ± 20 g 9599-607-12352 105.41 max 90.17 max Coaxial cables not provided IS Page 1 July 16/09 OIM AHV1600-SYSTEM THALES Communications AHV1600 TRANSCEIVER TECHNICAL CHARACTERISTICS 1- Nominal power supply: 28 Vdc 2- Power consumption: 20 W max (18 W typical) 3- Power input interruption : 2 ms 4- Connection: MIL C 39012 (TNC / RF connectors), MIL C38999 (main connectors) 5- Performance: Transmission : FM/CW. Frequency Range : 4.2 GHz to 4.4 GHz. Frequency Deviation : 123 MHz typical. Transmitted Power : + 18 dBm max typical. Height range accuracy : The maximum error, at every simulated height and within the temperature range - 40°C / + 70°C is : (2 ft + 2 % H) 6- Environmental conditions: DO160E Cat. [(B4)X]BBB[RG]XWFDFSZZAZ[ZC][HF]M[(A4G33)(A3J33)]XXAX AHV1600 TRANSCEIVER FUNCTIONAL CHARACTERISTICS – FUNCTIONS OF THE EQUIPMENT: – IS Page 2 July 16/09 Provide height Above Ground Level (AGL). EQUIPMENT INTERFACE: Transmission antenna. Reception antenna. 28 Vdc supply Main connector OIM AHV1600-SYSTEM THALES COMMUNICATIONS GENERAL 1. AHV1600 RADAR ALTIMETER MAIN FUNCTION The main function of the AHV1600 Radar Altimeter is to provide the height information, via an ARINC 429 digital bus, to the aircraft navigation system, in a range from 0 ft up to 5000 ft. It uses the fact that the electromagnetic waves propagate through the air at a constant speed c, which is the speed of the light. The height information is defined as the shortest distance to the "terrain" (ground or sea). 2. AHV1600 BASIC PRINCIPLE The AHV1600 Transceiver measures altitude above ground as a function of elapsed time from the transmission of the electromagnetic wave to its return after reflection from the ground. The transmission time is directly proportional to the height above ground level. It measures the shortest delay o between the transmitted wave and the received wave, linked to the minimum distance to the terrain o by the formula: o 2.Ho AIRCRAFT t=2 h/c TERRAIN (GROUND/SEA) The AHV1600 Transceiver principle of operation is the FM/CW (Frequency Modulation / Continuous Wave) with variable slope modulation. The basic principle of this technique is to generate a saw tooth waveform with a slope of modulation varying as a function of altitude as shown on the figure below. The transmitted wave is linearly modulated in frequency by the saw tooth. Page 1 July 16/09 OIM AHV1600-SYSTEM THALES Communications The AHV1600 Transceiver performs FM/CW modulation transmissions that are beat against the received reflection. The variable slope modulation allows the beat frequency to be maintained in a given bandwidth (window of 60 kHz to 110 kHz around centre frequency of 80 kHz). The window is then analysed through the equivalent of a 1 kHz bandwidth filter sweeping from 15 kHz to 110 kHz. The evaluation of the aircraft altitude is based on the measurement of the saw tooth duration and the position of the echo frequency in the window. The detection of the beat frequency spectrum is performed by a digital signal processing function. The transmitted wave is linearly modulated in frequency by a saw tooth. A beat signal is then obtained by mixing the transmitted waves F(t) and received waves F(t-i). At every instant, the frequency fbi of this signal is equal to: fbi = F(t) - F(t-i) As the modulation is linear fbi is linked to i and then to Hi by the formulae: fbi i 2. Hi F TST c. TST The fbi frequencies form the beat signal spectrum. This spectrum is constituted of all the frequencies from the ground and the thermal noise as well. To enable a measurement of fbo with a probability of noise detection compatible with the integrity requirements of the Radio Altimeter, a detection level is defined. Only frequencies, which appear in the beat signal with energy above this level are taken into account. As the frequencies fbi and the heights Hi are proportional, the minimum distance to the ground Ho is linked to the minimum frequency fbo of the spectrum. The Radio Altimeter then measures this frequency fbo, the leading edge of the spectrum. In the case of the Radio Altimeter, the frequency excursion F is fixed and TST is made proportional to Ho by a feedback loop that keeps fbo in a constant frequency range. The accurate measurement of the minimum fb Page 2 July 16/09 OIM AHV1600-SYSTEM THALES COMMUNICATIONS in the beat signal spectrum provides an accurate height measurement, and a TST for the feedback loop to keep fbo in its defined frequency range from one measurement to the other. Hence the relationship : Ho K . fbo where K c.TST 2.F 3. BUILT IN TEST FUNCTION The AHV1600 Transceiver implements an operational built-in test (BIT) in the following steps: A. POWER-UP BUILT IN TEST (PBIT) The AHV1600 Transceiver is capable of carrying out a performance test upon completion of the initialization sequence after power up to confirm the serviceability of the assembly. This test is performed in 3 s. B. INITIATED BUILT IN TEST (IBIT) The AHV1600 Transceiver is capable of carrying out a performance test to confirm the serviceability of the Transceiver upon receipt of the discrete input signal “FCT_TST“. This test is performed in 3s. C. CONTINUOUS BUILT IN TEST (CBIT) The AHV1600 Transceiver is carrying out a continuous test of performance of the system as a background task. Continuous BIT provides coverage to the minimum extent possible without interfering with the normal Transceiver operation. The BIT is controlled by the software embedded by the equipment. 4. AIRCRAFT INTERFACE The AHV1600 transceiver interfaces with the following equipment : Airborne navigation computer, Airborne power supply, Two antennae. The figure 1 shows a block diagram of the AHV1600 radar altimeter system: Page 3 July 16/09 OIM AHV1600-SYSTEM THALES Communications AVH1600 TRANSCEIVER Digital/Management Board Mother Board (Including I/O) Radio Module Tx Emission Rx Reception ANT140A 4.2 /4.4 GHz Antenna ANT140A 4.2 /4.4 GHz Antenna Power supply HIRF Stage ARINC 429 lines Discretes RF signals I/O Dedicated information Height and status I/O maintenance Figure 1 – AHV1600 RADAR ALTIMETER SYSTEM Page 4 July 16/09 RS232 lines OIM AHV1600-SYSTEM THALES COMMUNICATIONS PRESENTATION 1. AHV1600 RADAR ALTIMETER SYSTEM GENERAL DESCRIPTION The Radar Altimeter System, named AHV1600, consists of three LRU (Line Replaceable Unit) and is composed of: one AHV1600 transceiver, one antenna ANT-140A to transmit radio frequency (RF) signal, one antenna ANT-140A to receive radio frequency (RF) signal. Two coaxial cables (not provided) are necessary: one transmission cable, to connect the transmission antenna to the transceiver, one reception cable, to connect the reception antenna to the transceiver. AHV1600_RADAR ALTIMETER Transmission antenna ANT140A Reception antenna ANT140A LRU LRU Transceiver AHV1600 Transmission cable Reception cable LRU Figure 101 – AHV1600 RADAR ALTIMETER SYSTEM BLOCK DIAGRAM The AHV1600 is an autonomous system mounted on an aircraft and connected to: 28 Vdc power supply line: “P28V” and “RET28V” signals. Transmit and receive antennae for Radio Frequency (RF) signals through coaxial cables (“TX and RX” signals). Navigation and guidance systems through: Dual differential ARINC429 digital output serial line (“TX429_HI_1, TX429_LO_1 and TX429_HI_2, TX429_LO_2” signals). Page 101 July 16/09 OIM AHV1600-SYSTEM THALES Communications Two discrete inputs (“FCT_TST and TST_INH” signals). Configurable inputs (“AID<2..0>, AID_P and SDI_SEL” signals). 2. AHV1600 TRANSCEIVER The AHV1600 Transceiver is a compact and very light system. It is intended to fit the aircraft. It is fixed on the aircraft structure by means of four M6 screws. The unit is made up of a chassis with a front panel. The front panel is equipped with: one main connector, two coaxial connectors: one reception connector« Rx », one transmission connector« Tx ». Immunity label Transmission connector Reception connector Main connector ESD (Electro Static Discharge) label THALES identification label amendment label Specific label Manufacturing serial number label Figure 102 – AHV1600 TRANSCEIVER - GENERAL VIEW Page 102 July 16/09 OIM AHV1600-SYSTEM THALES COMMUNICATIONS A. EXTERNAL CHARACTERISTICS (1) PHYSICAL CHARACTERISTICS Dimensions (see figure 103): max. 190 x 90 x 95 mm. The weight of the unit is < 2 kg. Figure 103 – OVERALL DIMENSIONS Note: all dimensions are in mm (2) FRONT PANEL The front panel bears the antennae connectors, the main connectors , the specific label, the amendment label, the ESD label and the immunity label. All connectors are equipped with special caps provided electrical shielding as well as mechanical protection. Page 103 July 16/09 OIM AHV1600-SYSTEM THALES Communications (3) IDENTIFICATION (a) Manufacturing Serial Number Label The manufacturing serial number label is stuck on the left side (refer to Figure 102). It is divided into four fields, which provide the following indications: Field Number Field Serial number LRU Description Date of manufacturing Inspection stamp Figure 104 – MANUFACTURING SERIAL NUMBER LABEL (b) THALES Identification Label The THALES identification label is stuck on the left side (refer to Figure 102). One field provides the following indication: Field Number Field THALES commercial part number Figure 105 – THALES IDENTIFICATION LABEL Page 104 July 16/09 OIM AHV1600-SYSTEM THALES COMMUNICATIONS (c) Amendment label Figure 106 – AMENDMENT LABEL (d) Specific label The specific label is stuck on the front panel (refer to Figure 102). It is divided into five fields, which provide the following indications: Field Number Field ETSO certification number TSO certification number FCC ID designation DO designation Weight Figure 107 – SPECIFIC LABEL Page 105 July 16/09 OIM AHV1600-SYSTEM THALES Communications B. INTERNAL SUB-ASSEMBLIES The AHV1600 Transceiver contains the following sub-assemblies: – The Digital chassis: Performs the High Intensity Radiated Field (HIRF) protection, internal module interconnection, digital and management processor capacity and power supply distribution, Provides the helicopter with the mechanical and electrical interfaces, Provides the hardware support of the downloaded software’s. – The radio module: Performs the Radio Frequency (RF) signal emission, the Radio Frequency (RF) signal reception and the Beat Frequency (BF) signal extraction. C. FUNCTIONAL CHARACTERISTICS (1) OPERATION DATA Output signals characteristics : ARINC 429 standard Radar Altimeter height : ARINC word label 164 and 165 (BNR and BCD) Radar Altimeter Status : ARINC word label 272 Timing between both word labels is described hereafter: First ARINC 429 output (serial) Second ARINC 429 output (serial) : IRS2 TX HI (+) / IRS2 TX LO (-) ARINC 429 specification: Exchange: unidirectional asynchronous Word format: 32 bits data transfer with LSB transmitted in first Label format: 8 bits in octal coding from LSB position of the word Parity format: 1 odd parity bit at MSB position of the word Inter word gap: 4 bits minimum : IRS1 TX HI (+) / IRS1 TX LO (-) Note: on each word, the odd parity bit is always computed from the first 31 data bits of the word. Bit duration : 80 µs 2 µs Bit form factor : 40 µs 2 µs Note : the bit duration corresponds to a low speed operation at 12.5 kbps. : 12.5 kbps ARINC signals Transmission speed : AID0, AID1, AID2, AID_P Input signals Page 106 July 16/09 Low level voltage + 3.5 VDC with sink current < 2mA (logic state 1). High level voltage +15.3 VDC with sink current < 1 mA (logic state 0). Maximum level voltage +32.2 VDC. OIM AHV1600-SYSTEM THALES COMMUNICATIONS when measured to the “M_GND” reference signal. Frame structure on IRSx TX HI/LO differential output serial line: six words transmitted in accordance with the following chronological order: 1- Height data word label 164 2- Status data word label 271 3- Status data word label 272 4- Data word label 371 (first equipment identifier data word) 5- Height data word label 377 6- Height data word label 165 Frame rate on IRSx TX HI/LO differential output serial line: 40 ms 1 ms (2) DATA WORD ORGANIZATION (a) height data word label 164 description : Label data field: Bits<8..1> Label value 001 011 10 164OCT Source Destination Identifier (SDI) data field : Bits<10..9> Discrete input “SDI_SEL” 00 Undefined 01 Discrete grounded 10 Discrete open 11 Not used Functional Test Inhibit (FTI) data: Bits<11> Discrete input “TST_INH” Discrete open Discrete grounded Page 107 July 16/09 OIM AHV1600-SYSTEM THALES Communications Height data field: Bits<29..13>Height value Height range from 0 ft up to + 5500 ft LSB value 0.125 ft Height value coded in 2 complement on 17 bits (Sign bit<29> - LSB bit<13>) Status Matrix data field (BNR numeric data word): Failure warning (FW) 01 No Computed Data (NCD) 10 Functional Test (FT) 11 Normal Operation (NO) FTI Spare Height data value in BNR format coded in two’s complement LSB SM SDI Label data field: Page 108 July 16/09 Bits<8..1> Label value 100 111 01 271OCT Label « 164 » Figure 108 – ORGANIZATION OF HEIGHT DATA WORD LABEL “164” (b) Status data word label 271 description MSB 00 LSB Validity 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 Sign Parity 32 Bits<31..30> OIM AHV1600-SYSTEM THALES COMMUNICATIONS Source Destination Identifier (SDI) data field : Bits<10..9> Discrete input “SDI_SEL” 00 Undefined 01 Discrete grounded 10 Discrete open 11 Not used Aircraft Installation delay (AID) data field : Bits<14..11> AID Value (fte) AID_P AID<2..0 111 Reserved 111 Configurable input value not authorized 110 Configurable input value not authorized 110 Reserved 101 Configurable input value not authorized 101 Reserved 100 Reserved 100 Configurable input value not authorized 011 Configurable input value not authorized 011 Reserved 010 Reserved 010 Configurable input value not authorized 001 46.625fte 001 Configurable input value not authorized 000 Reserved 000 Undefined Functional Test data: Bits<17> Discrete input “FCT_TST” Discrete grounded Discrete open Page 109 July 16/09 OIM AHV1600-SYSTEM THALES Communications Test inhibit data: Bits<18> Discrete input “TST_INH” Discrete grounded Discrete open Status Matrix data field (discrete data word): Not used 10 Not used 11 Failure warning (FW) 12 11 10 AID0 AID_P Reserved Reserved FCT_TST TST_INH Reserved Reserved Reserved Spare Reserved Spare Reserved Spare Reserved Spare SM 13 SDI Label data field: Bits<8..1> Label value 010 111 01 272OCT Source Destination Identifier (SDI) data field : Page 110 July 16/09 Bits<10..9> Discrete input “SDI_SEL” 00 Undefined 01 Discrete grounded Label « 271 » Figure 109 – ORGANIZATION OF STATUS DATA WORD LABEL “271” (c) Status data word label 272 description MSB 01 LSB Normal Operation (NO) AID1 00 AID2 Validity 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 Spare Parity 32 Bits<31..30> OIM AHV1600-SYSTEM THALES COMMUNICATIONS 10 Discrete open 11 Not used AHV1600 Transceiver function data field : Bits<18..17> AU Transceiver function” 00 Search 01 Track 10 No function 11 Reserved PBIT / IBIT data : Bits<19> PBIT / IBIT BIT in progress BIT not required AHV1600 Transceiver mode data field: Bits<21..20> AU Transceiver mode 00 Reserved 01 Operational 10 Reserved 11 Reserved Failure data field: Logic state Bit<29..24> Tx antenna Rx antenna PSU Failure No failure Radio failure: I/O CPU Radio Problem detected on radio board CPU failure: Problem detected on CPU board I/O failure: Problem detected on I/O board PSU failure: Problem detected on PSU board Rx antenna failure: Impedance on RX antenna fail (50 ohms not detected) Rx antenna failure: Impedance on TX antenna fail (50 ohms not detected) Page 111 July 16/09 OIM AHV1600-SYSTEM THALES Communications Status Matrix data field (discrete data word): 19 18 17 16 15 14 13 12 11 10 SDI Label « 272 » MSB 20 LSB 21 Spare 22 Reserved 23 Reserved 24 Reserved 25 Reserved 26 AU Transceiver function 27 PBIT / IBIT 28 AU Transceiver mode 29 Reserved Failure warning (FW) Spare 11 Spare Not used Radio failure 10 CPU failure Not used I/O failure 01 PSU failure SM Normal Operation (NO) Rx_ANT failure 30 Validity 00 Tx_ANT failure 31 Parity 32 Bits<31..30> Figure 110 – ORGANIZATION OF STATUS DATA WORD LABEL “272" (d) Status data word label 371 description LSB LSB STX Spare Block Word Count Name> Page 112 July 16/09 Discrete input “SDI_SEL” Label « 371 » Figure 111 – ORGANIZATION OF FIRST EQUIPMENT IDENTIFIER DATA WORD LABEL “371” “Name” data field defined as per three characters: MSB MSB 32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 Parity Several words label “371” are required to transmit the equipment identifier data. These words label “371” are encapsulated by the “STX” and “EOT” words label “371” to form the global transmission of the equipment identifier data. OIM AHV1600-SYSTEM THALES COMMUNICATIONS RA Undefined RA1 Discrete grounded RA2 Discrete open “Part Number” data field defined as per ten characters. e.g. “61778974AC” Label « 371 » MSB Character = 1 LSB MSB Character = 2 Spare LSB MSB Character = 3 Spare LSB MSB Parity 32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 LSB “Serial Number” data field defined as all characters from Part Number plus five number characters. e.g. “61778974AC11111” Figure 112 – ORGANIZATION OF INTERMEDIATE EQUIPMENT IDENTIFIER DATA WORD LABEL “371” The last equipment identifier data word label “371” shall indicate the end of transmission of equipment identifier data by transmitting the “EOT” character. Spare Label « 371 » MSB EOT LSB Parity 32 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 13 12 11 10 Figure 113 – ORGANIZATION OF LAST EQUIPMENT IDENTIFIER DATA WORD LABEL “371” Page 113 July 16/09 OIM AHV1600-SYSTEM THALES Communications (e) Height data word label 377 description Label data field: Bits<8..1> Label value 111 111 11 377OCT Source Destination Identifier (SDI) data field : Bits<10..9> Discrete input “SDI_SEL” 00 Undefined 01 Discrete grounded 10 Discrete open 11 Not used Equipment identification data field: Bits<22..11> Equipement identification 111 111 11 007HEX Status Matrix data field (discrete data word): Normal Operation (NO) 01 Not used 10 Not used 11 Failure warning (FW) No data SM 13 12 11 10 LSB 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 Equipment Identification Code SDI Label « 377 » Figure 114 – ORGANIZATION OF STATUS DATA WORD LABEL “377" Page 114 July 16/09 MSB 00 LSB Validity MSB Parity 32 Bits<31..30> OIM AHV1600-SYSTEM THALES COMMUNICATIONS (f) Height data word label 165 description Label data field: Bits<8..1> Label value 101 011 10 165OCT Source Destination Identifier (SDI) data field : Bits<10..9> Discrete input “SDI_SEL” 00 Undefined 01 Discrete grounded 10 Discrete open 11 Not used Height data field: Bits<29..11>Height value Height range from 0 ft up to + 5500 ft LSB value 0.1 ft Height value in binary coded decimal on 19 bits (MSB bit<29> - LSB bit<11>) Status Matrix data field (BCD numeric data word) : Bits<31..30> Validity” 00 Normal Operation 01 No computer Data (NCD) 10 Functional Test (FT) 11 Not used Page 115 July 16/09 OIM AHV1600-SYSTEM THALES Communications Height data value in BCD format SDI Label « 165 » Figure 115 – ORGANIZATION OF HEIGHT DATA WORD LABEL “165" (3) DISCRETE INPUT SIGNAL (a) Discrete input signal “FCT_TST” The AHV1600 transceiver receives the discrete input signal “FCT_TST” from the navigation and guidance systems to activate its “Built In Test (BIT)” function. The “FCT_TST” discrete input signal shall initiate the following function of the AHV1600 transceiver: Built In Test function initiated when it is set to low level voltage (discrete grounded). Built In Test function not initiated when it is set to high level voltage (discrete open). To initiate the internal Built In Test function of the AHV1600 transceiver, the minimum time duration of “FCT_TST” discrete input signal shall be 200ms when measured at 50% level of the electrical changing voltage. In the AHV1600 transceiver, the “FCT_TST” discrete input signal shall be in accordance with the following electrical characteristics: Low level voltage + 3.5 VDC with sink current < 2mA (discrete grounded). High level voltage +15.3 VDC with sink current < 1 mA. Maximum level voltage +32.2 VDC. when measured to the “M_GND” reference signal. In the AHV1600 transceiver, the discrete input signal ”FCT_TST” shall be protected against the indirect effect of lightning. (b) Discrete input signal “TST_INH” The AHV1600 transceiver receives the discrete input signal “TST_INH” from the navigation and guidance systems to inhibit its “Built In Test (BIT)” function. The “TST_INH” discrete input signal shall inhibit the following function of the AHV1600 transceiver: Page 116 July 16/09 MSB 12 11 10 LSB SM 13 LSB 31 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 15 14 MSB Parity 32 OIM AHV1600-SYSTEM THALES COMMUNICATIONS Initiated Built In Test (IBIT) function inhibited when it is set to low level voltage (discrete grounded). Initiated Built In Test (IBIT) function enabled when it is set to high level voltage (discrete open). In the AHV1600 transceiver, the discrete input signal “TST_INH” shall be in accordance with the following electrical characteristics: Low level voltage + 3.5 VDC with sink current < 2mA (discrete grounded). High level voltage +15.3 VDC with sink current < 1 mA. Maximum level voltage +32.2 VDC. when measured to the “M_GND” reference signal. To inhibit the internal Built In Test function of the AHV1600 transceiver, the minimum time duration of “TST_INH” discrete input signal shall be 200ms when measured at 50% level of the electrical changing voltage. In the AHV1600 transceiver, the discrete input signal ”TST_INH” shall be protected against the indirect effect of lightning. 3. OPERATIONAL INTERFACES A. POWER SUPPLY The Transceiver shall be powered with a 28 Vdc ± 5 %. The voltage transients shall be: range 21 V to 32 V for up to 2 ms, range 21 V to 38 V for up to 1 ms. The Transceiver shall be not damaged in unusual conditions: 50 V during 50 ms. B. DIGITAL ARINC429 INTERFACE This digital interface outputs the altitude information exchanged between the Transceiver and the navigation computer. There is no ARINC 429 input. All information is through the Main receptacle J1. ARINC 429 outputs are differential output signals: first ARINC429 output (IRS1 TX HI / IRS1 TX LO), second ARINC 429 output (IRS2 TX HI / IRS2 TX LO).* (1) ELECTRICAL CHARACTERISTICS (a) When measured to the AID ground reference signal in open circuit differential low level voltage differential high level voltage : - 10 Vdc 1 Vdc : + 10 Vdc 1 Vdc Page 117 July 16/09 OIM AHV1600-SYSTEM THALES Communications differential null level voltage differential output impedance : 0 Vdc 0.5 Vdc : 75 5 (b) When measured to the AID ground reference signal in loaded circuit differential low level voltage differential high level voltage differential null level voltage : between - 11 Vdc and - 7.25 Vdc : between + 7.25 Vdc and + 11 Vdc : between - 0.5 Vdc and + 0.5 Vdc (2) LIGHTNING PROTECTION Both differential output signals are protected against the indirect effect of lightning. (3) TIMING CHARACTERISTICS - Differential rise time : 10 µs 5 µs. - Differential fall time : 10 µs 5 µs. When measured from 10% to 90% level of the differential changing voltage in open circuit. C. AID SIGNALS INTERFACE (1) CONFIGURABLE INPUT SIGNALS The transceiver receives the configurable input signals “AID_P” and “AID 2..0” from the Navigation computer to code the Aircraft Installation Delay. To select the Aircraft Installation Delay, each dedicated “AID_P” and “AID 2..0” configurable input signal must be connected as short as possible to the “AID GROUND” reference signal (or left open). (2) ELECTRICAL CHARACTERISTICS - Low level voltage : + 3.5 Vdc with sink current 2 mA (logic state 1), - High-level voltage : + 15.3 Vdc with sink current 1 mA (logic state 0), - Maximum level voltage + 32.2 Vdc. When measured to the “M_GND” reference signal. (3) LIGHTNING PROTECTION Configurable input signals are protected against the indirect effect of lightning. (4) FUNCTIONAL CHARACTERISTICS Page 118 July 16/09 AID length definition: from TX transceiver output to TX antenna through coaxial cable and from TX antenna to ground through the air and from ground to RX antenna through the air and from RX antenna to RX input transceiver through coaxial cable AID is coded by the “AID_P” and “AID 2..0” configurable input signals. OIM AHV1600-SYSTEM THALES COMMUNICATIONS (5) PERFORMANCE Altitude: 5000 ft Height accuracy: ( 2 ft + 2% of the true height) D. ENVIRONMENTAL CONDITIONS DO160E Cat. [(B4)X]BBB[RG]XWFDFSZZAZ[ZC][HF]M[(A4G33)(A3J33)]XXAX DO160E section Category B4 Temperature variation Category B Humidity Category B Operational shocks and crash safety Category B Vibration Category R curve G Explosive atmosphere Not required Category X Waterproofness 10 Category W Fluids susceptibility 11 Category F Sand and dust 12 Category D Fungus resistance 13 Category F Salt Fog 14 Category S Magnetic effect 15 Power input 16 Voltage spike Audio frequency conducted susceptibility – power inputs Induced signal susceptibility Radio frequency susceptibility (radiated and conducted) Emission of radio frequency energy 17 Category Z Category Z TCF declares that the AHV1600 Transceiver is able to withstand momentary power interruption up to 2ms (Test condition 1 of table 16-3). Category A 18 Category Z 19 Category ZC Category H for Conducted Susceptibility Category F for Radiated Susceptibility Category M Pin Injection Tests : Equipment tested to Category (A4) for power lines and (A3) for interconnecting lines. Cable Bundle Tests : Equipment tested to Category (G33) for power lines and (J33) for interconnecting lines. Environmental Condition DO160E Temperature and altitude 20 21 Description of conducted test Lightning induced transient susceptibility 22 Lightning direct effects 23 Not required Category X Icing 24 Not required Category X Electrostatic discharge 25 Category A Fire, Flammability 26 Not required Category X Page 119 July 16/09 OIM AHV1600-SYSTEM THALES Communications E. IN FLIGHT CONDITIONS In-flight conditions are defined in the following table: Height range domain Horizontal velocity From 0 ft to 5000 ft From 0 ft/s to 500 ft/s up to H = 500 ft From 0 ft/s to 1000 ft/s up to H = 500 ft From 0 ft/s to 20 ft/s up to H = 50 ft Height variation velocity ED-30 height range category B From 0 ft/s to 50 ft/s at 50 ft < H < 500 ft ED-30 in-flight condition category L/P From 0 ft/s to 500 ft/s at 500 ft < H < 800 ft From 0 ft/s to 2000 ft/s above H = 800 ft Pitch angle Range of 0 to ± 25°(at - 3 dB) Roll angle Range of 0 to ± 45°(at - 3 dB) ED-30 in-flight condition category L Radar Altimeter in-flight conditions 4. ANTENNA ANT-140A A. GENERALITIES ON ANTENNA ANT-140A The ANT140A antenna is a flat antenna for AHV1600 Radar Altimeter. The complete installation of the Radar Altimeter requires two identical antennae ANT-140A: one for transmission (Tx) and one for reception (Rx). These two antennae must be suitably located and connected by coaxial cables to the transceiver. The antenna is certified by the DO160B certification. B. PHYSICAL CHARACTERISTICS Dimensions: 105.41 x 90.17 x 33 mm, Weight: 130 ± 20 g, The antenna is fitted with a female TNC 50 ohms coaxial connector. The connector is protected with a special cap that must be removed before connecting the antenna. Two labels equip the antenna: an identification label and an amendment label. A red ink marking indicates antenna orientation into aircraft. Page 120 July 16/09 OIM AHV1600-SYSTEM THALES COMMUNICATIONS Longitudinal Axle Figure 116 – ANT-140A INNER SIDE The outside bears the inscription “DO NOT PAINT”, as well as an antenna-positioning symbol. Figure 117 – ANT-140A OUTER SIDE A: Antenna-positioning symbol Page 121 July 16/09 OIM AHV1600-SYSTEM THALES Communications C. FUNCTIONAL CHARACTERISTICS – Operating frequency band: 4.2 GHz – 4.4 GHz. – Match: The return loss on 50 ohms complies with the following diagram Isotropic gain: ≥ 7 dBi from 4.2 GHz to 4.4 GHz Radiation pattern: Half-power beamwidth (- 3 dB): Roll (E-Plane) : 60° 7° Pitch (H-Plane) : 50° 5° NOTE: The E-plane is perpendicular to the direction of the straight line painted on the external antenna front face. The H-plane is parallel to the direction of the straight line. – Decoupling: The decoupling value for a distance of 0.4 m between antenna centres is ≥ 72 dB. – Grounding: The resistance between connector core and its shielding is < 0.05 ohm. 5. COAXIAL CABLES LENGHT (1) RECOMMENDED CABLE TYPE ( ACCORDING TO MIL.C 17F SPECIFICATION ) Double screened coaxial is essential to avoid RF leakage. Page 122 July 16/09 OIM AHV1600-SYSTEM THALES COMMUNICATIONS (2) AID DEFINITION Installation Delay (AID) is the total electrical length from the transceiver transmitting output port to the aircraft skin, via the transmitting antenna the add to the distance from the antenna to the ground, add to the distance from ground to receive antenna and back to the transceiver receiving output via the receiving antenna. L1+ L2 Electrical length (in feet) of the coaxial cables between the transceiver and transmitting and receiving antennas respectively. L3 + L4 Distance (in feet) between transmitting and receiving antennas to the ground when the aircraft is on the ground ANT1 and ANT2 are the electrical length (in feet) of antennas (1.5 ft per antenna) The formula for cable mechanical length calculation is: Le +Lr Page 123 July 16/09 OIM AHV1600-SYSTEM THALES COMMUNICATIONS INSTALLATION 1. GENERAL CONDITIONS A. POWER SUPPLY A nominal voltage of 28 Vdc powers the equipment. It can nevertheless operate within a DC power supply range of 22 V to 30.3 V. The absorbed power at 28 V is less than 20 W. It is typically 18 W. The primary power supply circuit is isolated from the secondary circuit. B. LOCATION When selecting a location for equipment and working out the details for installation in the platform, the objectives should be easy implementation and replacement of the equipment and radar altimeter as close as possible from the antennae. C. WATER, SAND, AND DUST TIGHTNESS Although the equipment is designed to withstand salt spray and a high degree of humidity, it is not waterproof and precautions should be taken to protect it against trickling or sprayed water (according to its specifications). D. MOUNTING The AHV1600 Transceiver is fixed on the platform by means of four M6 screws, without any preferred orientation. E. INSTALLATION CONDITIONS The AHV1600 Radar altimeter normal installation conditions are described hereafter: Radio Frequency (RF) isolation between the transmission and reception antennae > 75 dB. Adaptation of each antenna 50 ohms, over the frequency range (4.2 GHz to 4.4 GHz). Gain of each antenna at least 7 dBi and 11 dBi maximum, over the frequency range 4.2 GHz to 4.4 GHz. Aperture angles of the antennae are at - 3 dB (with ANT-140A): in pitch ± 25° ± 2.5°. in roll ± 30° ± 3.5°. Page 201 July 16/09 OIM AHV1600-SYSTEM THALES Communications VSWR 3 to 1 of each antenna (return loss of - 6 dB or less) over the frequency range 4.2 GHz to 4.4 GHz. All sides lobes of each antenna must be down 40 dB or better. Coax cable 50 ohms double shielded type RG400 or equivalent. Losses in both the transmission and reception coaxial cables are of 4 dB minimum and 7 dB maximum. Each antenna shall be grounded on the aircraft frame, on a common metallic grounded structure for both antennae. The dimension of this structure being at least 15 cm around each antenna. No conductive features between antennae or within at least 30 cm around each antenna should be accepted. Furthermore no conductive features should be seen in a cone of ± 70° centered on each antenna. Avoid antennae to be fitted close to landing gear doors, landing gear or skids. Antennae should be preferably installed on a flat and horizontal surface. In any cases two antennae of a given system shall have no more than a 5° angle between their planes. Furthermore, users have to take into account the fact that tilting any antenna with respect to the aircraft horizontal plane will affect the system performances in terms of capability to withstand aircraft’s attitudes. The residual resistance between the structure of the aircraft and the structure of each antenna (body of the coaxial connector) shall not exceed 2.5 milliohm. The residual resistance between the structure of the aircraft and the structure of the transceiver (body of the coaxial connector, main connector or specific reference mechanical ground pins in the main connector) shall not exceed 2.5 milliohm. 2. STEP BY STEP TRANSCEIVER INSTALLATION The AHV1600 Transceiver is fitted with a main MIL-C-38999 series III, 37 contacts connector and two female MIL-C-39012/TNC coaxial connectors. Two antennae ANT140A – transmission and reception – are required for the AHV1600 Transceiver. They are connected by means of two coaxial cables to the AHV1600 Transceiver. Recommended installation flowcharts: control the Transceiver visual aspect, secure the Transceiver, connect the Main connector, connect the coaxial cables. Warning: before connecting Main connector, be sure 28 Vdc Transceiver supply is inhibited. Page 202 July 16/09 OIM AHV1600-SYSTEM THALES COMMUNICATIONS A. CHOICE OF ANTENNAE LOCATION Choose the location of the antennae carefully. On it will depend the operation of the Transceiver in all flight configurations. Antennae are generally mounted: Under the fuselage. Such that the H fields are collinear - this configuration corresponds to maximum decoupling between antennae. The antennae centre line should be preferably parallel to the aircraft Fore and AFT axis. Along a plane parallel to the ground for a normal aircraft flight attitude; if it is not possible to mount the antennae horizontally, a maximum angle of 5 degrees may be tolerated. CAUTION: Pitch and roll performances may be degraded for angles exceeding this figure. At a location that is preferably perfectly clear of any obstacles in order to avoid hindrance of the Transceiver by fixed obstacles (landing gear, fuel tanks, other antennae). The distance between antennae should be chosen on the basis of two criteria: Sufficiently large distance to ensure proper decoupling. Sufficiently small distance to ensure proper overlapping of radiation lobes for the minimum height of the antennae above the ground (touchdown or parking position). The distance between antennae should be the following (see Figure 201). Page 203 July 16/09 OIM AHV1600-SYSTEM THALES Communications Figure 201 – ANT-140A – ANTENNAE SEPARATION AND ORIENTATION B. ANTENNA MOUNTING Antennae must be flush-mounted, from below, in the lower part of the aircraft fuselage. Antennae connectors must imperatively face: forwards for the front antenna, rearwards for the rear antenna. Each antenna bears a red ink marking to indicate assembly orientation into aircraft. Page 204 July 16/09 OIM AHV1600-SYSTEM THALES COMMUNICATIONS C. CONNECTION The electrical connection for operational use of each antenna is made by means of a single coaxial connector. Type of connector mounted on antenna: 50 ohm female coaxial type TNC connector conforming to specification MIL-C-39012. 3. VERIFICATION When the AHV1600 Transceiver is installed, a verification of the operation must be done using the PBIT. This verification must be done in operational conditions. A. GROUND TESTS Prior to install the transceiver, check all interfering for continuity and isolation, Install and connect the transceiver, Energise the equipment and check that the ARINC output message contains an altitude close to 0ft. Antenna to ground distance may differ in parked situation from the touch down, so this test altitude may vary slightly around 0 ft, Proceed to Functional Test, the ARINC output message shall contain an altitude of 0 ft exactly, Check that the coupling to other systems is correct. B. IN FLIGHT TESTS Sensitivity versus altitude: check that the “loss track” altitude of the radio altimeter is greater than 5000 ft (No Computed Data indication on ARINC output message), Sensitivity versus attitude: Check that the track is not loss for ROLL and PITCH angles as defined by the half power antennae beamwidth. Immunity from track to landing gear down and the helicopter structure: when flying at an altitude higher than 1000 ft, impose the Functional Test mode. At release of the Functional Test, check that the track mode is recovered and the transceiver outputs a correct altitude different of 0 ft. 0 ft accuracy: at touch down landing, check that the radio altimeter indicates 0 ft. 4. FUNCTIONAL CONNECTIONS WITH RELATED EQUIPMENT A. INTERFACES CONNECTIONS The following table displays the connector labels, the function, and the connector reference for all connectors used for the AHV1600 transceiver. Page 205 July 16/09 OIM AHV1600-SYSTEM THALES Communications CONNECTOR LABEL FUNCTION CONNECTOR REFERENCE MATING CONNECTOR REFERENCE J1 Main connector MIL C- 38999 / MS27468 T 15 B-35 PN (*) MT934-T15B35PM112 J2 To Antenna TX MIL C 39012 34MMBX-TNC-501/1-2-NE J3 To Antenna RX MIL C 39012 34MMBX-TNC-501/1-2-NE (*) Note: The MIL reference designates a connector including the main external characteristics: - 37 pins, - Shell size 15, - Drab olive green finish, - Male contacts, - Normal polarization. B. GROUNDING AND BONDING The bottom part of the chassis is used as mechanical and electrical contact with the aircraft fuselage. Figure 202 shows the surfaces providing bonding contact between the Transceiver chassis and the platform structure. 13.55 35. 492 13 5 45° 16.5 18.992 Nota : All dimensions are in mm. Figure 202 – SURFACES BONDING CONTACT OUTLINES Page 206 July 16/09 R 5. 75 OIM AHV1600-SYSTEM THALES COMMUNICATIONS C. COOLING OF THE EQUIPMENT The AHV1600 on platform installation must take into account that heat dissipation for the Transceiver is partially accomplished through natural convection requiring a minimum space between the Transceiver and the next equipment of 10 mm. The remained part of the heat is dissipated by conduction between the bottom part of the Transceiver chassis and the platform frame. The maximum heat dissipation is 20 watts. D. HANDLING No specific tools or support are required to handle or carry the Transceiver due to its small and prehensile dimensions and its lightweight. The Transceiver is equipped with caps, which are plugged on each I/O connector, and which protect them from ESD, sand and dust. 5. EQUIPMENT INPUTS / OUTPUTS A. MAIN CONNECTOR J1 Input (I) / Output (O) Installation Requirements Socket Contact Contact Gauge 22D Reserved 22D Reserved 22D Reserved 22D Reserved 22D FCT_TST Simple see note 4 Discrete input signal 22D TST_INH Simple see note 4 Discrete input signal 22D Reserved 22D Reserved 22D TX429_HI_1 Twisted/Shielded see note 2&3 Differential output serial line 10 22D TX429_HI_1 Twisted/Shielded see note 2&3 Differential output serial line 11 22D Signal Name Wire Type Reserved Page 207 July 16/09 OIM AHV1600-SYSTEM THALES Communications Contact Gauge 12 22D 13 22D TX429_HI_2 Twisted/Shielded see note 2&3 Differential output serial line 14 22D TX429_HI_2 Twisted/Shielded see note 2&3 Differential output serial line 15 22D 16 22D AID2 Simple (as short as possible) see note 4 Configurable input signal 17 22D P28V_1 Twisted see note 1 Power supply input 1 18 22D P28V_2 Twisted see note 1 Power supply input 2 19 22D RET28V_2 Twisted see note 1 Power supply return 2 20 22D AID_P Simple (as short as possible) see note 4 Configurable input signal 21 22D Reserved 22 22D Reserved 23 22D AID 0 Simple (as short as possible) see note 4 Configurable input signal 24 22D AID 1 Simple (as short as possible) see note 4 Configurable input signal 25 22D Reserved 26 22D Reserved 27 22D Reserved 28 22D Reserved 29 22D Reserved 30 22D Page 208 July 16/09 Input (I) / Output (O) Installation Requirements Socket Contact Signal Name Wire Type Reserved Reserved RET28V_1 Twisted see note 1 Power supply return 1 OIM AHV1600-SYSTEM THALES COMMUNICATIONS Input (I) / Output (O) Installation Requirements Socket Contact Contact Gauge 31 22D Reserved 32 22D Reserved 33 22D E_GND 34 22D SDI_SEL 35 22D Reserved 36 22D Reserved 37 22D Reserved Signal Name Wire Type Electrical reference ground Simple (as short as possible) see note 4 Configurable input signal Note 1 :Twisted wire type Note 2 : Twisted + Shielded wire type (shield shall be terminated at the connector EMI backshell) Note 3 :ARINC data bus A2 (12.5 Khz) Page 209 July 16/09 OIM AHV1600-SYSTEM THALES Communications A2 Note 4 : Simple wire type Note 5: The M_GND reference signal must be connected to the mechanical reference ground of the carrier B. RX/TX ANTENNA Connector Contact Contact Gauge Input (I) / Output (O) Signal Name RX TNC RX TX TNC TX Page 210 July 16/09 Wire Type Installation Requirements Coaxial cable Coaxial cable Length according to AID selection OIM AHV1600-SYSTEM THALES COMMUNICATIONS FCT_TST TST_INH TX429_HI_1 TX429_LO_1 ARINC 429 LINE TX429_HI_2 TX429_LO_2 ARINC 429 LINES AID2 P28V_1 P28V_2 RET28V_2 AID_P AHV1600 TRANSCEIVER INTERNAL DEVICES +28Vdc (first) +28Vdc (second) 28Vdc RETURN (second) AID0 AID1 RET28V_1 28Vdc RETURN (first) E_GND SDI_SEL Figure 203 – INTERCONNECTIONS Page 211 July 16/09 OIM AHV1600-SYSTEM THALES COMMUNICATIONS OPERATION 1. RADAR ALTIMETER ENERGIZATION The AHV1600 radar altimeter is not provided with an “ON-OFF” switch. The equipment starts operating as soon as the + 28 VDC power supply is applied by a circuit breaker or other mean located on the helicopter front panel. 2. FUNCTIONNAL TEST When the functional test is requested, the system shall outputs a 100 ft test height and functional test is indicated in the status matrix of word labels 164 and 165. 3. NORMAL OPERATING MODE When on ground or flying in the system range, the radar altimeter shall output the helicopter height above the ground with the specified accuracy. Alarms shall be out of view. The status matrix of ARINC 429 words shall indicate the Normal Operation status. 4. OUT OF RANGE OPERATION When the helicopter is flying outside the system range (above 5000 ft), the radar altimeter shall enters in the loss of track mode (search mode). The status matrix of ARINC 429 words shall indicate the No Computed Data status. 5. FAILURE MODE When a failure is detected by the radar altimeter monitoring, when the helicopter is either on ground or flying, it is signalled. The status matrix of ARINC 429 words shall indicate the Failure Warning status. Page 301 July 16/09 OIM AHV1600-SYSTEM THALES Communications 6. DEFAULT OPERATING INSTRUCTIONS Default No output data Possible cause - Radar altimeter not powered - Radar altimeter power supply failure - wiring Corrective action - Check circuit breaker - Change power supply module - Check wiring Output data with Failure Warn- - Radar altimeter failure ing status - Change transceiver Output data with No Computed - Loss of system sensitive when heliData indication copter on ground or flying in the equipment operating range - Check antennae installation - Change transceiver 7. OPERATIONAL LEVEL MAINTENANCE TASK The Operational level maintenance task consists in removing and replacing the transceiver (LRU) in case of failure. A. REMOVING THE TRANSCEIVER Recommended removing flowchart: – – – – power-off the transceiver, disconnect the three cables from front panel, remove the four M6 screws which secure the unit onto the aircraft structure, remove the unit. B. INSTALLING THE SPARE TRANSCEIVER Refer to INSTALLATION § 2 Before installing the spare Transceiver, ensure the Transceiver location on aircraft structure is clean. Page 302 July 16/09
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