EQUIPMENT INSTALLATION MANUAL. for the GDC66 FUEL QUANTITY ADAPTER UNIT P/N Rev B

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EQUIPMENT INSTALLATION MANUAL for the GDC66 FUEL QUANTITY ADAPTER UNIT P/N 1107-4000-01 Rev B DAC International

1 EQUIPMENT INSTALLATION MANUAL for the GDC66 FUEL QUANTITY ADAPTER UNIT P/N Rev B DAC International 6702 McNeil Drive Austin, TX Copyright 2013, DAC International. All rights reserved. B.doc Rev B Page 1 of 17

2 RECORD OF REVISIONS REV DESCRIPTION DATE APPROVED IR INITIAL RELEASE E /02/2012 BH A ADD SECOND RS422 INPUT PORT E /27/2012 BH B See ECO E /20/2013 BH B.doc Rev B Page 2 of 17

3 Table Of Contents RECORD OF REVISIONS INTRODUCTION: DESCRIPTION: PART NUMBER: GDC REFERENCE DOCUMENTS REGULATORY COMPLIANCE: Software Hardware GDC SUPPLIED EQUIPMENT GDC GDC66 SPECIFICATIONS: Physical: Electrical: RS422 Serial Input Format ARINC 429 Output Format Reliability: OPERATION: INSTALLATION: Aircraft Interconnect Wiring Mounting REMOVAL AND REPLACEMENT Removal Replacement EQUIPMENT CHECKOUT CONTINUED AIRWORTHINESS: ENVIRONMENTAL: CONNECTOR PIN OUT: TYPICAL INTERCONNECT OUTLINE DRAWING...17 B.doc Rev B Page 3 of 17

4 1. INTRODUCTION: This manual contains installation data, specifications and continued airworthiness information for the (FQAU), part number DESCRIPTION: The Model GDC66 FQAU converts two RS422 data streams from the existing fuel quantity sensor found on Piper Meridian and Socata TBM aircraft into an ARINC 429 data set compatible with the Garmin G950 Integrated Flight Deck. The GDC66 has two ARINC 429 data outputs with identical data on each for redundancy. 3. PART NUMBER: 3.1. GDC66 The Model GDC66 FQAU is available under the following part number: ( ) Fuel Quantity Adapter Unit Software part number, where ( ) contains the number zero for initial release, or any letter, A Z to denote a minor change. B.doc Rev B Page 4 of 17

5 4. REFERENCE DOCUMENTS RTCA/DO-160E RTCA/DO-178B ARINC 429 Environmental Conditions and Test Procedures for Airborne Equipment Software Considerations in Airborne Systems and Equipment Certification Mark 33 Digital Information Transfer System B.doc Rev B Page 5 of 17

6 5. REGULATORY COMPLIANCE: 5.1. Software The GDC66 software was developed in accordance with RTCA/DO-178B to criticality level C Hardware GDC66 The GDC66 is approved via PMA for installation on Piper Meridian aircraft. B.doc Rev B Page 6 of 17

7 6. SUPPLIED EQUIPMENT 6.1. GDC66 Each unit is shipped with the following items: Part Number Description Qty ( ) Installation Kit 1 Complete installation kits are available under kit part number Individual pieces are available under the part numbers shown. Contact DAC International sales to place orders. Part Number Description Qty Installation Kit M24308/2-14F Connector, Receptacle, 62 pin D-Sub 1 P10891 Backshell, 62-Pin D-Sub 1 Additional sockets are available under DAC part number M39029/57-354, quantity as required (A/R). M39029/ Socket, Crimp Style, female A/R B.doc Rev B Page 7 of 17

8 7. GDC66 SPECIFICATIONS: 7.1. Physical: The GDC66 attaches to the airframe using four (4) #8 screws. See the paragraph titled Outline Drawing for additional details. Height inches Width (including flanges) inches Depth inches Weight lb Electrical: Input Voltage...28 VDC Nominal (10Vdc 32Vdc operational) Input Current Amp nominal at 28 VDC 7.3. RS422 Serial Input Format RX( )-A...RS422 differential serial stream, 2400 baud, 1 start bit, 8 data bits, one stop bit, odd parity. Expected source is Left side fuel quantity. RX( )-B...RS422 differential serial stream, 2400 baud, 1 start bit, 8 data bits, one stop bit, odd parity. Expected source is Right side fuel quantity ARINC 429 Output Format TX1...ARINC 429 High Speed output data with labels 256 and 257. Label 256 is Tank #1 (Right Side) fuel quantity data, Label 257 contains Tank #2 (Left Side) fuel quantity data. TX2...ARINC 429 High Speed output data with labels 256 and 257. Label 256 is Tank #1 (Right Side) fuel quantity data, Label 257 contains Tank #2 (Left Side) fuel quantity data Reliability: MTBF...Greater than 40,000 hours. B.doc Rev B Page 8 of 17

9 8. OPERATION: The GDC66 contains no operator controls. It accepts two RS422 serial data input data streams from a data acquisition unit converts these to two ARINC 429 high speed data outputs. ARINC 429 labels 256 and 257, left and right quantity, are both output on both data ports. B.doc Rev B Page 9 of 17

10 9. INSTALLATION: This section contains considerations and recommendations for installation of the GDC66 LRU. The interconnect wiring harness and physical mounting must be considered to satisfy all applicable regulations. The environmental conditions and tests required for PMA of these articles are minimum performance standards. If this article is installed in a location that would place it in environmental conditions outside the limitations listed in the manual, it is the responsibility of that installing agency to determine if additional compliance data is required and to present such data to the administrator of the Federal Aviation Administration or other applicable certifying agency. Refer to the Environmental Qualification Forms found later in this document 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/shielded must be installed as shown in order to maintain compliance with the Environmental categories. ARINC 429 outputs are connected using twisted shielded pairs (M SB2T23 or equivalent). Analog inputs are connected using triple twisted shielded pairs (M SB3T23 or equivalent). Power and ground return signals should be connected using M22759/ or equivalent Mounting DESCRIPTION PART NO. 24 AWG M22759/ or equivalent TPL TWSTD SHIELDED M SB3T23 or equivalent DBL TWSTD SHIELDED M SB2T23 or equivalent SHIELD TERMINATION M83519/2-13 or equivalent The GDC66 is intended to mount in the aircraft electronic equipment bay 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. It can be mounted in any orientation. The GDC66 is secured with installer provided hardware; four each 8-32 screws (length as appropriate for aircraft installation), four each #8 flat washers, and four each #8 lock washers are required for proper installation. See section 16 for the location dimensions of the mounting holes. It is recommended that at least 4 inches of clearance be provided on the connector side of the GDC66 to allow room for the mating connector and cable. B.doc Rev B Page 10 of 17

11 10. REMOVAL AND REPLACEMENT Removal 1. Open the circuit breaker powering the GDC Loosen the two jack screws on P1 and remove the connector. 3. Remove four (4) screws securing the unit to the airframe Replacement 1. Open the circuit breaker powering the GDC Attach the unit to the airframe with four (4) screws. 3. Attach connector P1 to the GDC66. Thread the two jack screws on P1 in J1 then tighten. 4. Close circuit breaker. 5. Perform operational test of the GDC66 as prescribed in the aircraft maintenance manual. 11. EQUIPMENT CHECKOUT The GDC66 provides ARINC 429 data compatible with the Garmin G950 Integrated Flight Deck. 1. Apply power to the GDC66 and G950 Integrated Flight Deck system. B.doc Rev B Page 11 of 17

12 12. CONTINUED AIRWORTHINESS: This section provides data intended to assist the installer with establishing Instructions for Continued Airworthiness as required by FAR Maintenance Manual information for the GDC66, 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 article are as specified in the DAC International Installation Manual, (this manual). 8. There are no Airworthiness limitations associated with the installation of this article. B.doc Rev B Page 12 of 17

13 13. ENVIRONMENTAL: NOMENCLATURE: Model PART NO: XXXX MANUFACTURER: DAC International ADDRESS: 6702 McNeil Drive, Austin, TX RTCA/DO-160E Environmental Conditions and Test Procedures for Airborne Equipment Section Category Remarks 4.0 Temperature and Altitude D2 50,000 Ft 5.0 Temperature Variation B Partially controlled temperature 6.0 Humidity A Standard Humidity 7.0 Operational Shock and Crash Safety B Standard Operational Shock 8.0 Vibration SBM Curve B, A/C Type 2, Fixed Wing Turbojet or Turbofan, Reciprocating & Turboprop Engines, Single and Multi Eng, Aircraft Zone 2. Curve M, A/C Type 5, Fixed Wing Reciprocating & Turboprop, Multi Eng, Aircraft Zone 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 B Alternator / Rectifiers with battery 17.0 Voltage Spike A E = 600 volts 18.0 AF Conducted Susceptibility Power B Inputs Alternator / Rectifiers with battery 19.0 Induced Signal Susceptibility AC No interruption of operation 20.0 Radio Frequency Susceptibility QQ 50 volts/meter, amps/meter (Radiated and Conducted) 21.0 Emission of Radio Frequency Energy M At or below acceptable limit per DO- 160E Lightning Induced Transient Susceptibility A3XXX Pin input test, interference controlled to tolerable levels Lightning Direct Effects X Not Tested 24.0 Icing X Not Tested 25.0 ESD A Aircraft mounted equipment B.doc Rev B Page 13 of 17

14 14. CONNECTOR PIN OUT: The GDC66 contains a single 62-pin male connector, J1, DAC part number P The part numbers for mating connector P1, along with crimp pins and backshell are described previously under the section Equipment Supplied. Pin Signal Function 1 A+ 28 Vdc Primary Power 2 Reserved 3 Reserved 4 Reserved 5 429TX2A ARINC Transmitter A 6 429TX2B ARINC Transmitter B 7 RS232 RX1 RS232 RX (connect to pin 36) 8 Reserved 9 Reserved 10 RS232 RX2 RS232 RX (connect to pin 14) 11 n/c Reserved 12 n/c Reserved 13 n/c Reserved 14 RS232 TX1 Out RS232 output of RS422 input data (Connect to pin 10) 15 RS422 RXB-A RS422 Receive Input A (Left Side Fuel) 16 RS422 RXA-A RS422 Receive Input A (Left Side Fuel) TX1A ARINC Transmitter 1A TX1B ARINC Transmitter 1B 19 Reserved 20 Reserved 21 Reserved 22 A+ 28 Vdc Primary Power 23 Reserved 24 Reserved 25 Reserved 26 Reserved 27 Reserved 28 Reserved 29 Reserved 30 COM 1 TX RS232 TX 1 31 n/c Reserved 32 Reserved 33 n/c Reserved B.doc Rev B Page 14 of 17

15 Pin Signal Function 34 n/c 35 Reserved 36 RS 232 TX2 Out RS232 output of RS422 input data (Connect to pin 7move ) 37 RS422 Common Ground 38 RS422 RXB-B RS422 Receive Input B (Right Side Fuel) 39 RS422 RXA-B RS422 Receive Input B (Right Side Fuel) 40 Reserved 41 Reserved 42 Reserved 43 Power Com Ground 44 Reserved 45 Reserved 46 Reserved 47 Reserved 48 Reserved 49 Power Com Ground 50 Reserved 51 Reserved 52 Chassis Gnd Ground 53 Reserved 54 COM2_Common Ground 55 COM1_Common Reserved 56 Chassis Gnd 57 Reserved 58 Reserved 59 Reserved 60 Reserved 61 Reserved 62 Reserved J1 Pin Description NOTE: Do not use pins labeled Reserved. B.doc Rev B Page 15 of 17

16 15. TYPICAL INTERCONNECT GDC66 P1 5A POWER SUPPLY VDC COMMON 52 CHASSIS GARMIN G TX1-A 429TX1-B HI SPD RX-A RX-B GND GARMIN G TX2-A 429TX2-B 5 6 HI SPD RX-A RX-B RS232 RX1 7 GND RS232 TX2 36 RS232 RX2 10 RS232 TX1 14 J1 DAU RS422 GND 37 GND RX TXA+ RX1- TXA- RS422 LEFT RX TXB+ RX2- TXB- RS422 RIGHT ADD JUMPERS AS SHOWN B.doc Rev B Page 16 of 17

17 16. OUTLINE DRAWING Note: Dimensions are in inches. B.doc Rev B Page 17 of 17

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