P/N ( )

Transcription

1 EQUIPMENT INSTALLATION MANUAL for the P/N ( ) DAC International 6702 McNeil Drive Austin, TX Copyright 2007, DAC International. All rights reserved. A.doc Rev A Page 1 of 19

2 Record of Revisions REV DESCRIPTION DATE APPROVED IR Initial Release E742 7/13/07 LW A Moved SEL ALT to RS232 IN 1. Updated test matrix to reflect DO-160E categories (changed sect 18 to Cat B, sect 19 to Cat ZC). Changed label 212 rate to 62.5ms. Modified 2/22/08 BH connection diagram. E821 A.doc Rev A Page 2 of 19

3 Table Of Contents Record of Revisions Introduction: Description: Part Numbers: Reference documents Specifications: Other Publications: Regulatory Compliance: Software Hardware Required Equipment: ADLP-2 Specifications: Physical: Electrical: MADC Input: INU CHA and CHB input: Selected Altitude Input: ARINC 706 Output: ARINC 718A Input: ARINC 718A Output: Reliability: Operation: Installation: Aircraft Interconnect Wiring Mounting Removal and replacement ADLP-2 Removal ADLP-2 Replacement Equipment Checkout Continued Airworthiness: Environmental: Connector Pin Out: Typical Interconnect: Outline Drawing:...19 A.doc Rev A Page 3 of 19

4 1. Introduction: This manual contains installation data, specifications and Instructions for Continued Airworthiness for the DAC International Model ADLP-2, Airborne Data Link Processor. 2. Description: The ADLP-2 compiles airborne data from multiple input sources and communicates this data to the APX-119 digital transponder in both ARINC 718A and ARINC 706 format. The ADLP-2 integrates with the digital transponder to enable the Polish Air Force C-130E aircraft fleet to comply with European Enhanced Mode S requirements. The Micro Air Data Computer (MADC) input accepts an ARINC 429 data stream. The selected data source is translated into an ARINC 706 format to independently supply the APX-119 transponder with airdata. In addition, certain air data parameters are also converted to ARINC 718A along with 1553 data from the INU bus, and pre-selected altitude from the autopilot. MADC ARINC 429 ADLP APX-119 A/P SEL ALT ARINC 706 Digital 1553 CHA 1553 CHB INU INU ARINC 718 Digital ARINC 718 Digital Figure 2.1: Model ADLP-2 Block Diagram A.doc Rev A Page 4 of 19

5 3. Part Numbers: The ADLP-2 is available under the following part number: ( ) Software part number, where ( ) contains the number zero for initial release, or any letter, A Z to denote a minor change. 4. Reference documents 4.1 Specifications: ARINC Air Transport Avionics Equipment Interfaces, Mar 30, 2001 ARINC 429 Mark 33 Digital Information Transfer Systems (DITS), Sep 27, 2001 ARINC 718A Mark 4 Air Traffic Control Transponder (ATCRBS/MODE S), Feb 15, 2002 ARINC Mark 5 Subsonic Air Data System, Jan 11, 1988 MIL-STD-1553B Aircraft Internal Time Division Command/Response Multiplex Data Bus, June 28, 1978 MIL-STD-810F Environmental Engineering Considerations and Laboratory Tests, January, 1, Other Publications: RTCA/DO-178B RTCA/DO-160E Software Considerations in Airborne Systems and Equipment Certification Environmental Conditions and Test Procedures for Airborne Equipment Doc No Transponder Set, Digital AN/APX-119, Raytheon Electronic Combat Systems Hardware Interface Control Document, October 25, 2005 Doc No Transponder Set, Digital AN/APX-119 Raytheon Electronic Combat Systems Document Software Interface Control Document, June 20, 2005 ICAO Volume IV, Annex 10, Amendment 77 - Aeronautical Telecommunications (Surveillance Radar and Collision Avoidance Systems), July, 2002 A.doc Rev A Page 5 of 19

6 ICAO Volume III, Part 1, Annex 10, Appendix to Chapter 5, Amendment 77 - Aeronautical Telecommunications (Digital Data Communication Systems), Nov 11, Regulatory Compliance: 5.1 Software The model ADLP-2 software was developed in accordance with RTCA/DO-178B to criticality level C. 5.2 Hardware The Model ADLP-2 is tested to the environmental conditions found in section Required Equipment: Each ADLP-2 System is shipped with the following items: DAC Part Number Description Qty ( ) ADLP-2 1 Equipment Installation Manual for the ADLP-2 1 Equipment not supplied (but required for most installations): DAC Part Number Description Qty P10319 ARINC 600 Connector 1 P10320 Equipment Tray, Long/ Short 2 MCU, Size 1 1 MS Screw, Pan HD 6-32 x AN960-6L Washer, Flat, #6 4 A.doc Rev A Page 6 of 19

7 7. ADLP-2 Specifications: 7.1 Physical: The ADLP-2 attaches to the equipment rack via a 2 MCU tray with ARINC 600 size 1 connector. Height Width Length Weight lb. 7.2 Electrical: Input Voltage...28 VDC Nominal (10Vdc 32Vdc operational) Input Current Amp max at 28 VDC 7.3 MADC Input: Bus Name:...MADC Bus Type:...Digital Bus Source...MADC Destination:...ADLP-2 Applicable Standard:...ARINC 429 Clock Speed/Frequency:...11 ± 1 khz Source Impedance:...75 Ohms line-to-line Voltage Range:...Logic 1 = +10 ± 1 V (A to B) Logic 0 = -10 ± 1 V (A to B) Null = 0 ± 1 V (A to B) Labels processed (Mach #), 206 (CAS), and 212 (Vert. Rate) 7.4 INU CHA and CHB input: Bus Name:...INU 1553B Bus Bus Type:...Digital Bus Source...INU Destination:...ADLP-2 Applicable Standard:...MIL-STD-1553B A.doc Rev A Page 7 of 19

8 Clock speed/frequency:...1 MHz Messages Processed...RT6, SA25, W13: Mag HDG RT6, SA16, W10: Roll Angle RT6, SA27, W23: True Track Angle RT6, SA27, W22: Groundspeed RT5, SA20, W7 & 8: TAS 7.5 Selected Altitude Input: Bus Name:...Selected Altitude Bus Type:...Digital Bus (RS-232) Source:...IS&S Altitude Pre-Selector Destination:...ADLP-2 Applicable Standard:...N/A Clock Speed/Frequency Baud Source Impedance:...single-ended outputs to drive lines with characteristic impedance of 50 to 500 Ohms Voltage Range:...Logic 0 = +3.0 V, +12 / - 0 V Logic 1 = -3.0V, -12 / + 0V Data Processed...Selected Altitude Note 1:...The Data line consists of 8-bit words with a terminating checksum. 7.6 ARINC 706 Output: The input ARINC 429 labels from the MADC are redirected to the ARINC 706 output. Table: MADC ARINC 429 Format Label Description Rate (Octal) 205 Mach Number 125mS 206 Indicated Airspeed 125mS 212 Barometric Altitude Rate 62.5mS Bus Name:...ARINC 706 TX Bus Type:...Digital Bus A.doc Rev A Page 8 of 19

9 Source...ADLP-2 Destination:...Transponder Applicable Standard:...ARINC 429 Clock Speed/Frequency:...High Speed 7.7 ARINC 718A Input: Bus Name:...ARINC 718A RX Bus Type:...Digital Bus Source...Transponder Destination:...ADLP-2 Applicable Standard:...ARINC 429 Clock Speed/Frequency:...High Speed 7.8 ARINC 718A Output: Bus Name:...ARINC 718A TX Bus Type:...Digital Bus Source...ADLP-2 Destination:...Transponder Applicable Standard:...ARINC 429 Clock Speed/Frequency...High Speed 7.9 Reliability: MTBF...Greater than 10,000 hours. A.doc Rev A Page 9 of 19

10 8. Operation: The model ADLP-2 is comprised of a single 2MCU LRU. The ADLP-2 accepts inputs from a MADC, a 1553 bus, and selected altitude from the autopilot control panel. The ADLP-2 performs these major operations: Monitoring/receiving and converting the following inputs into an ARINC 718A data stream sent to the transponder. INU MIL-STD-1553B High Speed Data Bus input MADC ARINC 429 data bus input ARINC 429 Air Data Computer Output Altitude Pre-select Digital Data Bus The ADLP-2 loads these Mode-S Registers: 0,B* Air/air state info #1 0,C* Air/air state info #2 Vert. vel., roll angle, & level off alt. 4,0 Aircraft intention sel. Alt. only 5,0 Track and turn report Roll angle, true track, GS, & TAS 5,3* Air referenced state vector Mag HDG, IAS, MACH, & TAS only 6,0 Heading and speed report Mag HDG, IAS, MACH, & Vert. Vel. only * Preliminary register assignments. Subject to change Receiving ARINC 718A data from the transponder to maintain link validity. At the present time, the ADLP-2 is only required to process handshake data received from the transponder. A.doc Rev A Page 10 of 19

11 9. Installation: This section contains considerations and recommendations for installation of the ADLP-2 LRU. The interconnect wiring harness and physical mounting must be considered to satisfy all applicable equipment specifications. 9.1 Aircraft Interconnect Wiring The typical interconnect diagram and connector pin listings are provided to assist the installation agency in preparation of the interconnect wiring cables. Wiring shown as twisted and/or shielded must be installed as shown in order to maintain compliance with the Environmental categories. 9.2 Mounting The ADLP-2 is intended to mount in the aircraft electronic equipment bay, on the specified mounting tray, but may mount in either a pressurized or non-pressurized section of the aircraft so long as consideration is given to the appropriate environmental categories. The ADLP-2 requires +28VDC power to operate along with connections to the aircraft's APX-119 transponder and other equipment supplying data. A.doc Rev A Page 11 of 19

12 10. Removal and replacement 10.1 ADLP-2 Removal 1. Open the circuit breaker powering the ADLP Remove the unit by disengaging the front latch then pulling the unit free ADLP-2 Replacement 1. Open the circuit breaker powering the ADLP Seat the unit on its tray then engage the front latch to secure. 3. Close circuit breaker. 4. Perform operational test of the ADLP-2 as prescribed in the aircraft maintenance manual. 11. Equipment Checkout The ADLP-2 provides conversion of various navigation and air data parameters for use by the APX-119 transponder system. The MADC, INU, 1553 Bus Controller, and APX-119 must all be operational in order to perform this functional checkout. 1. Apply power to the MADC, INU, Bus Controller, autopilot, and APX-119 transponder. 2. Perform the functional test of the APX-119 system according to existing, approved maintenance data A.doc Rev A Page 12 of 19

13 12. Continued Airworthiness: This section provides data intended to assist the installer with establishing Instructions for Continued Airworthiness as required by FARs , , and Maintenance Manual information for the ADLP-2, which includes system description, removal instructions, installation instructions and functional testing is contained in DAC International Installation Manual, (this document). 2. Line Replaceable Unit (LRU) part numbers and other parts contained in the installation data package should be placed in the aircraft operator s appropriate airplane illustrated Parts Catalog (IPC). 3. Wiring diagram information contained in the installation data package should be placed in the aircraft operator s appropriate airplane Wiring Diagram Manual. 4. Scheduled Maintenance Program tasks are as follows: a. Recommended Periodic Scheduled Servicing:...None required b. Recommended Periodic Scheduled Preventive Maintenance Tests...None Required c. Recommended Periodic Inspections:...None Required d. Recommended Periodic Overhaul Period...None Required e. Special Inspection Requirements...None Required 5. Application of Protective Treatments...None Required 6. Special Tools...None Required 7. Electrical Loads for this appliance are as specified in the DAC International Installation Manual, (this manual). 8. There are no Airworthiness limitations associated with the installation of this appliance. A.doc Rev A Page 13 of 19

14 13. Environmental: The ADLP-2 units meets the environmental test categories detailed on the following page in accordance with RTCA/DO-160E, Environmental Conditions and Test Procedures for Airborne Equipment and MIL-STD-810F as noted. NOMENCLATURE: Model ADLP-2 PART NO: XXXX MANUFACTURER: DAC International ADDRESS: 6702 McNeil Drive, Austin, TX Section Category Remarks Temperature and Altitude (MIL-STD-810F) C non-operating, -15 C operating Temperature Variation B 5 C degrees per minute 6.0 Humidity A Standard humidity Operational Shock and Crash Safety (MIL- Standard op shock and crash safety STD-810F) Vibration (MIL-STD-810F) Multi-engine, turboprop, fixed wing 9.0 Explosion Proofness X Not tested 10.0 Waterproofness X Not tested 11.0 Fluids Susceptibility X Not tested 12.0 Sand and Dust X Not tested 13.0 Fungus Resistance X Not tested 14.0 Salt Spray X Not tested 15.0 Magnetic Effect Z Less than 0.3 meter 16.0 Power Input A Constant frequency AC, Trans/Rectifier DC 17.0 Voltage Spike B 56 volts 18.0 AF Conducted Susceptibility Power Inputs B Alternator / Rectifiers 19.0 Induced Signal Susceptibility ZC 20.0 Radio Frequency Susceptibility (Radiated and Conducted) T 5 volts/meter 21.0 Emission of Radio Frequency Energy L 22.0 Lightning Induced Transient Susceptibility XXC3X 23.0 Lightning Direct Effects X Not tested 24.0 Icing X Not tested 25.0 ESD A A.doc Rev A Page 14 of 19

15 14. Connector Pin Out: The ADLP-2 contains a single 120-pin connector, J1, per ARINC 600 size 1, DAC part number P The mating connector, P1, is described previously under the section Equipment Required. Pin Signal Function TP A1 +28VDC PRIMARY POWER TP A2 PWR COM POWER GROUND TP A3 RESERVED LED OUT TP A CHAhi 1553 data input (CHA+) TP A CHAlo 1553 data input (CHA-) TP A8 RESERVED DISC 0 TP A9 RESERVED DISC 1 TP A CHBhi 1553 data input (CHB+) TP A CHBlo 1553 data input (CHB-) TP A12 RESERVED RS232 IN 2 TP A13 RESERVED RS232 OUT 2 TP A14 UNUSED TP A15 RESERVED /PGM 2 TP B1 RESERVED DISC 2 TP B2 RESERVED DISC 3 TP B3 RESERVED DISC 4 TP B A SHIELD 1553 CHA shield TP B7 UNUSED TP B8 UNUSED TP B B SHIELD 1553 CHB shield TP B10 ADLP-2 OUT A 718A DATA TO APX-119 TP B11 ADLP-2 OUT B 718A DATA TO APX-119 TP B12 ADLP-2 IN A 718A DATA FROM APX-119 TP B13 ADLP-2 IN B 718A DATA FROM APX-119 TP B14 ADPL-2/ADC OUTA 706 DATA TO APX-119 TP B15 ADPL-2/ADC OUTB 706 DATA TO APX-119 TP C1 UNUSED TP C2 UNUSED TP C3 UNUSED TP C4 UNUSED TP C5 UNUSED TP C6 UNUSED TP C7 UNUSED TP C8 UNUSED TP C9 CHASSIS GROUND A.doc Rev A Page 15 of 19

16 Pin Signal Function TP C10 SELECTED ALT. COM RS232 COM TP C11 ADLP-2 OUT SHIELD TP C12 ADLP-2 IN SHIELD TP C13 ADC OUT SHIELD TP C14 RESERVED TP C15 RESERVED TP D5 RESERVED TP D6 RESERVED TP D7 UNUSED TP D8 RESERVED RS232 IN 3 TP D9 RESERVED RS232 OUT 3 TP D10 UNUSED TP D11 RESERVED /PGM 3 TP D12 SELECTED ALT. RS232 IN 1 TP D13 RESERVED RS232 OUT 1 TP D14 UNUSED TP D15 RESERVED /PGM 1 MP A1 RESERVED MP A2 RESERVED MP A3 RESERVED MP A4 RESERVED RTAGND MPA5 RESERVED RTA0 MPA6 RESERVED RTA1 MP A7 RESERVED RTA2 MP A8 RESERVED RTA3 MP A9 RESERVED RTA4 MP A10 RESERVED RTAP MP A11 IN ARINC A DATA FROM MADC MP A12 IN ARINC B DATA FROM MADC MP A13 RESERVED SPARE IN ARINC A MP A14 RESERVED SPARE IN ARINC B MP A15 RESERVED MP B1 RESERVED MP B2 RESERVED MP B3 RESERVED DISC 5 MP B4 RESERVED DISC 6 MP B5 RESERVED MP B6 RESERVED MP B7 RESERVED MP B11 ARINC SHIELD A.doc Rev A Page 16 of 19

17 Pin Signal Function MP B12 ARINC SHIELD MP C1 RESERVED GND MP C2 RESERVED GND MP C3 RESERVED GND MP C4 RESERVED GND MP D5 RESERVED SPARE 429 IN 2A MP D6 RESERVED SPARE 429 IN 2B TP/ MP Description NOTE: Do not use pins labeled Reserved. These are for factory test and In-Circuit-Programming A.doc Rev A Page 17 of 19

18 15. Typical Interconnect: A.doc Rev A Page 18 of 19

19 16. Outline Drawing: Note: Dimensions are in inches. A.doc Rev A Page 19 of 19