Installation Manual
Table Of Contents
- REVISION RECORD
- TABLE OF CONTENTS
- CHAPTER 1 – INTRODUCTION 7
- 1. PURPOSE 7
- 2. SCOPE 8
- 3. STYLE AND DEFINITION 8
- 4. UNPACKING THE GDR 8
- 5. SPECIAL TOOLS 9
- 6. FUNCTIONAL DESCRIPTION 10
- 7. SYSTEM COMPONENTS 14
- 8. ELECTRICAL SPECIFICATIONS 17
- A. Power Inputs 17
- B. System Antenna Specifications 17
- C. Antenna Inputs 17
- D. Microphone Inputs (DO-214, § 1.5.2) 17
- E. Audio Outputs and Levels 17
- 9. ENVIRONMENTAL SPECIFICATIONS 18
- 10. TSO APPLICABILITY 20
- 11. TSO DEVIATIONS 20
- 12. ACRONYMS AND ABBREVIATIONS 21
- CHAPTER 2 – SYSTEM INSTALLATION 23
- 1. LIMITATIONS AND NOTES 23
- A. Notes and Warnings 23
- 2. PRE-INSTALLATION INFORMATION 23
- 3. CABLING TERMINATION 24
- A. General 24
- B. Solder Sleeve Assembly 24
- C. Optional Shield Pull-Out Method 26
- D. Back Shell Termination 28
- E. Right Angle BNC Connector Assembly 28
- 4. MOUNTING 29
- A. Tray Installation 29
- B. Tray Assembly 30
- 5. ANTENNA LOCATION 31
- A. COM Antenna 31
- B. NAV Antenna 32
- C. MB Antenna 33
- 6. SIGNAL DESCRIPTION 34
- A. Power and Ground 34
- B. RS-232 Interface 34
- C. ARINC 429 Interface 34
- D. MIC Audio 35
- E. COM Audio and SIDETONE 35
- F. PTT and TX INTERLOCK 36
- G. NAV and MB AUDIO 36
- H. SDI, Power, and Discrete 37
- CHAPTER 3 – SYSTEM DRAWINGS 39
- 1. MECHANICAL DRAWING 39
- A. GDR-XXXX 39
- B. GDR TRAY 40
- 2. GDR-XXXX CONNECTOR DRAWINGS 41
- A. P1 Connector 41
- B. P2 Connector 42
- 3. WIRING DIAGRAMS 43
- CHAPTER 4 – GROUND FUNCTIONAL TESTS 46
- CHAPTER 5 – TROUBLESHOOTING 49
- 1. TOOLS 49
- 2. SETUP 49
- 3. FAULT INDICATIONS 49
- 4. FAILURES 49
- 5. COM PORT INSPECTOR 49
- 6. GDR-XXXX MAINTENANCE UTILITY 49
- APPENDIX A – ARINC 429 SPECIFICATIONS 50
- 1. ARINC Labels 030 and 047, VHF COM 51
- 2. ARINC Label 034, VOR/ILS Frequency 52
- 3. ARINC Label 035, DME Frequency 53
- 4. ARINC Label 040, UHF COM 54
- 5. ARINC Label 173, LOC Deviation 56
- 6. ARINC Label 174, G/S Deviation 57
- 7. ARINC Label 222, VOR Bearing and Marker Beacon Tones 58
- 8. ARINC Label 242 & 244, VOR Ground Station ID 59
- 9. ARINC Label 263 & 264, ILS Ground Station ID 60
- 10. ARINC Label 350 LRU Maintenance Status 61
- 11. ARINC 429 Update Rate (ARINC 429-18, Attachment 2) 62
- LIST OF FIGURES
- Figure 1: GDR-XXXX 10
- Figure 2: GDR Block Diagram 13
- Figure 3: Solder Sleeve Assembly 24
- Figure 4: Wire Termination 25
- Figure 5: Shield Pull-Out Method 27
- Figure 6: Shield Pull-Out Method (Continued) 27
- Figure 7: Right Angle BNC Connector 28
- Figure 8: Tray Assembly 30
- LIST OF TABLES
- Table 1: Installation Guide Style Conventions 8
- Table 2: Special Tools Required 9
- Table 3: List of Specifications and Major Components 14
- Table 4: GDR-XXXX Configuration 14
- Table 5: GDR Installation Kit P/N 42-033100-0001 15
- Table 6: List of Possible Antennas 16
- Table 7: List of VHF COM Antennas 31
- Table 8: List of Extended VHF COM Antennas 32
- Table 9: List of VHF & UHF COM Antennas 32
- Table 10: List of NAV Antennas 32
- Table 11: List of MB Antennas 33
- Table 12: VHF COM 118 MHz Frequency with 25 kHz or 8.33 kHz channel bandwidth 51
- Table 13: Sign Status Matrix definition and SDI bit definition 51
- Table 14: NAV Frequency Selection Format for 109.3 MHz, ARINC Label 034 52
- Table 15: Definition of Bits 11 to 13 for Label 034 52
- Table 16: Sign Status Matrix definition 52
- Table 17: ARINC SDI bit definition 52
- Table 18: DME Frequency Format for 109.3 MHz, ARINC Label 035 53
- Table 19: ARINC Label 035, Bits 11-13 53
- Table 20: Sign Status Matrix definition 53
- Table 21: Navigation source bit definition 53
- Table 22: ARINC Label 035 SDI bit definition 53
- Table 23: UHF COM Data Format Label 040 54
- Table 24: Modulation Bits 54
- Table 25: Bit 13 54
- Table 26: SDI bit definition 54
- Table 27: Sign Status Matrix definition 54
- Table 28: LOC Deviation Specification, ARINC Label 173 56
- Table 29: LOC Deviation Format, ARINC Label 173 56
- Table 30: Status Matrix definition 56
- Table 31: Sign Bit definition 56
- Table 32: Glideslope Deviation Specification, ARINC Label 174 57
- Table 33: Glideslope Deviation Format, ARINC Label 174 57
- Table 34: Status Matrix definition 57
- Table 35: Sign Bit definition 57
- Table 36: VOR Bearing Specification, ARINC Label 222 58
- Table 37: VOR Bearing Format, ARINC Label 222 58
- Table 38: Status Matrix definition 58
- Table 39: Sign Bit definition 58
- Table 40: Marker Beacon Tone Bit definition 58
- Table 41: Morse code first word format, ARINC Label 263 59
- Table 42: Morse code second word format, ARINC Label 264 59
- Table 43: Status Matrix definition 59
- Table 44: Morse code first word format, ARINC Label 263 60
- Table 45: Morse code second word format, ARINC Label 264 60
- Table 46: Status Matrix definition 60
- Table 47: Sign Bit definition 60
- Table 48: Maintenance Status 61
- Table 49: Label 350 maintenance bit definition 61
- Table 50: Status Matrix definition 62
- CHAPTER 1 – INTRODUCTION
- 1. PURPOSE
- This manual provides a description of the Genesys Aerosystems (Genesys) Digital Radio (GDR) series installation in an aircraft. The GDR can be used for new or retrofit installations. The most recent version of this installation manual is always loca...
- NOTE: “The conditions and tests required for TSO approval of this article are minimum performance standards. It is the responsibility of those desiring to install this article either on or within a specific type or class of aircraft to determine tha...
- CAUTION: These instructions are intended for use by installers familiar with standard aircraft avionics practices and methods of installation. If you do not have prior experience with or knowledge of avionics installations, do not attempt the followi...
- 2. SCOPE
- This manual includes installation and checkout procedures for the GDR.
- Chapter 1: Provides an introduction to the GDR.
- Chapter 2: Includes system installation instructions.
- Chapter 3: Includes unit drawings, both mechanical and electrical.
- Chapter 4: Includes ground maintenance procedures.
- Chapter 5: Includes ground functional test procedures.
- Chapter 6: Includes troubleshooting procedures.
- Appendix A: Includes ARINC 429 specifications.
- 3. STYLE AND DEFINITION
- 4. Special Considerations
- WARNING:
- A. Changes or modifications to the equipment not expressly approved by the Genesys Aerosystem could void the user's authority to operate the equipment.
- B. It is the responsibility of the operator of this equipment to obtain any necessary FCC licenses for transmitting with this equipment and transmit only on authorized channels.
- 5. UNPACKING THE GDR
- A. System components are shipped in packaging designed to protect the components during transit. Carefully unpack and identify each component using the list in Table 3. Check the contents of the package against the packing list in the box. Visually...
- B. Keep all shipping containers and packaging in case they are needed for returning items. Contact Genesys immediately if there are missing or damaged components. Before returning any items, please contact Genesys by one of the means below.
- Phone: (800) 872-7832
- Fax: (940) 325-3904
- E-mail: genesys-support@genesys-aerosystems.com
- 6. SPECIAL TOOLS
- 7. FUNCTIONAL DESCRIPTION
- A. The GDR is a remotely mounted Very High Frequency (VHF) Navigation (NAV) receiver, a VHF Communications (COM) receiver, an Ultra High Frequency (UHF) Communications receiver and Marker receiver contained in a single rack-mounted enclosure. A singl...
- Figure 1: GDR-XXXX
- B. COM RX: Four (4) communications receivers are included in the GDR unit; two (2) for VHF (Main and Guard) and two (2) for UHF (Main and Guard). Each band has a separate audio output for audio panel interfacing. Guard and Main audio are combined on...
- C. COM TX: The GDR shares a single transmitter for VHF and UHF frequencies. The VHF and UHF receivers have a separate microphone (MIC) inputs, Push-To-Talk (PTT), and audio output for interface with the aircraft’s audio system. The transmit frequenc...
- D. COM Classes: TX class, 3 and 5. RX class, C, D, and E.
- E. Sidetone: A separate Sidetone audio output is available. Sidetone can be configured to be on the receiver’ audio output or obtained from the independent Sidetone audio output. When Sidetone is combined with the audio, only the transmit band’s aud...
- F. COM TX Power: The transmitter is configured for either 16 Watts or 25 Watts as determined by the part number. This is identified by the number “16” or “25” respectively as the first two digits in the model number.
- G. VHF frequency range: Depending on the model number, the VHF receiver operates in the 118 MHz to 136.991 MHz, or the extended 118 MHz to 155.975 MHz range with either 8.33 KHz or 25 KHz spacing. This is identified with the number “36” or “56” respe...
- H. UHF frequency range: Units with UHF transceivers operate from 225 MHz to 399.975 MHz with either 12.5 KHz or 25 KHz spacing. The letter “U” at the end of the model number designates that the UHF option has been enabled. The UHF transceiver can op...
- I. COM guard receivers: Guard receivers are factory configured with the standard emergency frequencies of the 121.5 MHz and/or 243 MHz. The receivers may be disabled or configured for other channels as desired.
- J. TX interlock: A TX interlock input is available when needed for multiple transmitter installations.
- K. NAV ILS/VOR receiver: The GDR has a combined VHF Omnidirectional Radio (VOR) and Localizer (LOC) receiver. The VOR covers 160 channels and the LOC covers 40 channels in the 108.00 to 117.95 MHz range.
- L. NAV audio: The GDR provides a separate audio outputs for the VOR/LOC. Audio volume control is available in the radio for single pilot operation when an audio panel is not available.
- M. Glideslope receiver: The GS channels are automatically paired by the radio to provide Instrument Landing System (ILS) guidance on Localizer channels. The GS covers 40 channels in the 330.95 MHz to 334.70 MHz range.
- N. NAV antenna: The Glideslope and NAV receivers share a common antenna input through an internal RF diplexer. The GDR is intended to be connected to a combined VOR/LOC/GS antenna to be supplied by the installer. If two GDRs are installed, an exter...
- O. Marker beacon receiver: The GDR has a MB receiver, which uses a separate BNC connector mounted on the front of the chassis. If two GDRs are installed, an external MB splitter, supplied by the installer, may be used to route the MB signal to both G...
- P. Marker audio: The GDR has a separate MB audio output for connection to the aircraft’s audio system. Audio volume control is available in the radio for single pilot operation when an audio panel is not available.
- Q. Marker thresholds: The MB receiver has a HI and LO threshold factory set for -67 dBm and -53 dBm respectively. When am external splitter is installed, the installer may wish to compensate the MB thresholds for the loss. On installation, the thres...
- R. Control buses: The GDR radio has four (4) tuning buses, two RS-232, two RX ARINC 429 and one TX ARINC 429. The last bus tuned controls the radio, which is compatible with burst mode tuning.
- Figure 2: GDR System Block Diagram
- 8. SYSTEM COMPONENTS
- The table below provides a list of specifications and major components (by part number) that make up the equipment system complying with the standards prescribed in all TSOs listed in Chapter 1, Section 10.
- Table 3: List of Specifications and Major Components
- Table 4 provides a part number breakdown for the currently defined radio configurations.
- Table 4: GDR-XXXX Configuration
- NOTE: Small parts and electrical components required for installation that are not specifically called out in the parts list, shall meet the requirements for aerospace use as “acceptable parts” or “standard parts. Selection of these parts shall be in...
- Table 5: GDR Installation Kit P/N 42-033100-0001
- Table 6: List of Possible Antennas
- NOTE: This is list is provided as a reference only. It is up to the installer to determine suitability of each antenna for its intended purpose. The GDR radio should operate properly with any antenna meeting the appropriate TSO.
- 9. ELECTRICAL SPECIFICATIONS
- A. Power Inputs
- Receiver (NORM) 22 to 33 VDC, 1.0 Amps @ 22 VDC
- 27.5 VDC, 0.8 Amps typical
- (EMER) 18.0 VDC, 1.2 Amps typical
- Transmit (NORM) 22 to 33 VDC, 6.0 Amps @ 22 VDC
- 27.5 VDC, 5.7 Amps typical
- (EMER) 18.0 VDC, 6 Amps typical
- B. System Antenna Specifications
- COM Ant: 50 Ohm, 3:1 VSWR max., recommended ≤ 2.5:1 max.
- Marker Ant: 50 Ohm, 1.5:1 VSWR max.
- G/S Ant: 50 Ohm, 5.0:1 VSWR max., recommended ≤ 3.0:1 VSWR
- NAV Ant: 50 Ohm, 5.0:1 VSWR max., recommended ≤ 3.0:1 VSWR
- C. Antenna Inputs
- COM 50 Ohm BNC
- Marker Ant 50 Ohm BNC
- G/S RX 50 Ohm BNC
- NAV RX 50 Ohm BNC
- D. Microphone Inputs (DO-214, § 1.5.2)
- Impedance: 150 Ohm
- Bias: 12 VDC, on MIC HI input
- Input voltage range: 0.25 to 2.5 VRMS for specified AM modulation
- 0.27 VRMS recommended typical audio panel input level
- Input type: Differential, MIC HI to MIC LO
- E. Audio Outputs and Levels
- 10. ENVIRONMENTAL SPECIFICATIONS
- 11. TSO APPLICABILITY
- 12. TSO DEVIATIONS
- 13. ACRONYMS AND ABBREVIATIONS
- The following acronyms may appear in this document.
- AC Advisory Circular, Alternating Current
- A/C Aircraft
- AD Airworthiness Directive
- ADF Automatic Direction Finding
- AFM Aircraft Flight Manual
- ANSI American National Standards
- Institute
- ARINC Aeronautical Radio, Inc.
- ARP SAE Aerospace Recommended
- Practice
- AS SAE Aerospace Standard
- C Centigrade
- CAR Civil Air regulations
- COM Communication
- CPU Central Processing Unit
- D-A Digital to Analog (converter)
- dB Decibel
- DC Direct Current
- DME Distance Measuring Equipment
- DO RTCA Document
- EFIS Electronic Flight Instrument System
- EIA Electronics Industry Association
- EMI Electromagnetic Interference
- FAA Federal Aviation Administration
- FAR Federal Aviation Regulation
- FMS Flight Management System
- FSD Full Scale Deflection
- GDR Genesys Digital Radio
- GND Ground (potential)
- GS Glideslope
- IC Integrated Circuit
- ICAO International Civil Aviation Organization
- ID Identity or Identification
- IDU Integrated Display Unit
- ILS Instrument Landing System
- JTAG Joint Test Action Group (IEEE 1149.1 Standard)
- K Kilo=1000
- KB Kilobyte
- KHz Kilo-Hertz
- LOC Localizer
- LRU Line Replaceable Unit
- LSB Least Significant Bit or Byte
- M Meters
- MB Marker Beacon
- MFD Multifunction Display (an IDU with
- software for showing multiple display
- screens)
- MIC Microphone
- MIL Military
- MHz Mega-Hertz
- MOPS Minimum Operational Performance
- Standard
- MSB Most Significant Bit or Byte
- MSL Mean Sea Level
- MTBF Mean Time Between Failures
- NAS U.S. National Airspace System
- NAV Navigation
- Nm Nautical Mile
- OBS Omni-bearing Selector
- PN Part Number
- PTT Push-To-Talk
- RS EIA Recommended Standard
- RTCA Radio Telephone Commission for Aeronautics
- RX Receive
- SAE Society of Automotive Engineers
- SDI Source/Destination Identifier
- SN Serial Number
- SNI Serial Number Information
- STC Supplemental Type Certificate
- TSO Technical Standard Order
- TX Transmit
- UHF Ultra High Frequency
- UTC Universal Time Coordinated
- VFR Visual Flight Rules
- VHF Very High Frequency
- VOR Very High Frequency Omnidirectional Radio
- THIS PAGE IS BLANK
- 1. PURPOSE
- CHAPTER 2 – SYSTEM INSTALLATION
- CAUTION: It is critically important that this installation manual be read and understood completely and thoroughly before starting component installation and wiring.
- A successful installation should begin with careful consideration and planning of mounting locations, cable routing and any associated airframe modifications that may be required.
- The conditions and tests required for TSO approval of this article are minimum performance standards. Those installing this article, on or in a specific type of class of aircraft, must determine that the aircraft installation conditions are within th...
- 14. LIMITATIONS AND NOTES
- 15. PRE-INSTALLATION INFORMATION
- A. Always follow good avionics installation practices per FAA Advisory Circulars 43.13-1B, 43.13-2A, and AC 23-1311-1A or later FAA approved revisions of these documents.
- B. Follow the installation procedures in this chapter as it is presented for a successful installation. Read and understand the entire chapter before beginning the installation procedures. Perform the post installation checkout before closing the wo...
- C. Complete an electrical load analysis on the aircraft prior to starting modification to ensure the aircraft electrical system has the ability to carry the GDR electrical load per AC 43.13-1B, Chapter 11. Refer to Chapter 1, Table 3 for the power co...
- 16. CABLING TERMINATION
- A. General
- (1) Terminate all individual cable shields which are not “dead ended” using a solder sleeve and braided pigtail (equivalent in cross section to shield braid with center conductors removed) or optionally the braid pull-out method. Use the smallest sol...
- (2) The shield pigtail may be either a wire segment (of sufficient diameter equivalent to shield braid with center conductors removed) or another small braid segment. Wire segments are used when the cable shield is terminated to a connector contact o...
- (3) For back shell shield terminations, the individual cable shield shall be terminated at the end of the cable maintaining the minimum length of unshielded conductors with the shield pigtail installed at the back end. The solder sleeve may end up ins...
- Figure 3: Solder Sleeve Assembly
- B. Solder Sleeve Assembly
- (a) When using a suitable tool other than a thermal stripper to remove jacket, score jacket lightly and bend cable to complete jacket separation. Do not cut completely through cable jacket.
- CAUTION: Cutting through the cable jacket may result in damage to shield.
- (2) Push the solder sleeve over the exposed shield braid so solder sleeve shall be approximately centered over the exposed shield braid.
- (a) To avoid heat concentration which might split or otherwise damage the solder sleeve, the end of the shield ground wire insulation, if not preinstalled, should be positioned approximately even with the inner edge of the seal ring.
- (b) Maintain the relative position of the solder sleeve, shield ground wire and shield braid during assembly.
- Figure 4: Wire Termination
- (c) Use tinned copper braid Alpha P/N 1223 (3/64 inch) or equivalent for pigtail. Lap pigtail braid or wire segment with wire shield and place solder sleeve over assembly.
- (d) Shrink the solder sleeve in accordance using infrared or hot air heaters. Apply the heat uniformly, periodically rotating the solder sleeve during the heating process. Do not allow the infrared or hot air heater to touch the solder sleeve or wir...
- (e) Inspect for conformance to criteria for installed solder sleeves per the following:
- (i) No appearance of the solder perform ring will remain.
- (ii) In the case of solder sleeves with indicator rings the following also applies: It is necessary that the indicator ring has completely disappeared or melted.
- NOTE: If the process continually results in less than 100 percent melting of the indicator ring there may be a problem with the process which should be corrected before further processing.
- – If infrared heating is used, the problem is usually caused by a dirty reflector.
- – If hot air is used, the sleeve may not be centered in the hot air reflector.
- (iii) The shield ground wire shall be approximately centered in the melted area.
- (iv) Preformed solder ring inserts are to melt and flow along the shield ground wire leads and shield.
- (v) A minimum 0.125 inch fillet length is visible under a maximum power of 4X magnification along the shield ground wire lead and shield junction on at least one side of the shield ground wire. This requirement also applies to each shield ground wire...
- (vi) Browning or darkening of the sleeve is acceptable unless this condition inhibits visibility of the solder termination.
- (vii) The materials must not be split, charred, or otherwise damaged to any extent that that would compromise the insulating integrity of the sleeve.
- (viii) Inserts are to melt and flow around the circumference of the cable between the cable jacket and the insulation sleeve to prevent solder from flowing out of the work area.
- (ix) The melted insert rings must not obstruct visual inspection of the solder joint.
- (x) A maximum of 1/2 inch wicking up the shield ground wire (measured from the shield ground wire end of the sleeve) is allowed.
- C. Optional Shield Pull-Out Method
- (1) Do not use this procedure for a shield that has flat conductor braid strands.
- (2) Remove the cable outer jacket to the point of breakout.
- (3) Using a non–metallic awl or similar tool, start a small hole in the shield braid approximately 0.5 inch from end of outer jacket by spreading the shield carriers slightly.
- (4) Push the shield braid back on the wire(s) to cause it to bunch.
- (5) Widen the hole in the shielding by alternately pushing shield carriers back in each direction.
- (6) As the hole enlarges, start bending the wire(s) slightly to allow shield carriers to be worked down over the bent wire(s) until the wire(s) can be pulled through the opening. During this operation, avoid damage to braid and conductor insulation.
- (i) Do not overstress individual shield strands causing breakage.
- (ii) Do not subject the conductors to a bend radius less than 3 times the insulation diameter.
- (7) Work the bunched shielding back down the wire and straighten the shield ground wire to its full length.
- (8) Cut the shield ground wire to a maximum length of 2.0 inches.
- (9) Protect shield breakout area using M23053/5 sleeving.
- Figure 5: Shield Pull-Out Method
- Figure 6: Shield Pull-Out Method (Continued)
- D. Back Shell Termination
- E. Right Angle BNC Connector Assembly
- The NAV and COM coaxial cables terminate in a right-angled BNC connector that is mounted on the tray assembly.
- Figure 7: Right Angle BNC Connector
- 17. MOUNTING
- A. Tray Installation
- Use the following guidelines in locating and mounting the tray assembly in the aircraft. See Chapter 3 for tray mechanical dimensions.
- For normal operation, it is preferred the GDR be mounted in a temperature controlled environment between -20 C and +55 C.
- The GDR may be mounted in the pressure vessel. The GDR contains no batteries or potentially explosive components.
- The tray assembly may be mounted in the normal (mounting screws down), inverted, or on its side.
- The GDR should be located within 20 feet of the NAV display system (EFIS or HSI) and audio control system.
- Burnish and apply an electrical bonding agent to the mounting surface area that will be contacting the mounting tabs of the tray assembly.
- Install the tray assembly using four (4) 8-32 screws (MS27039-0807) and four (4) #8 washers (NAS1149F0832P) or equivalent with installer supplied AN, MS, or NAS nuts, nut clips, or nut plates as required.
- Use four (4) self-locking nuts (AN365) or equivalent, nut plates, or #8 threaded inserts to secure the tray assembly to the airframe.
- Verify resistance between the tray assembly chassis and airframe ground is less than 2.5 milliohms.
- Upon determination of a suitable existing shelf, or completion of a new equipment shelf, a static load test must be performed per AC 43.13-2A, Chapter1, §2 and §3 to determine proper load bearing and security of the equipment. A typical aircraft oper...
- The installer will make a simple test jig that will be used to measure the static test loads as shown in the table above. Perform the tests at the center of gravity of the GDR-XXXX and record the completion of the test in the Ground Maintenance secti...
- B. Tray Assembly
- The tray assembly provides the mounting for the electrical connectors and coax cable connectors. Hardware to mount the connectors is contained in the Installation Kit.
- Install
- Group wires to P1 together and secure to
- Figure 8: Tray Assembly
- 18. ANTENNA LOCATION
- A. COM Antenna
- The GDR requires a 50 Ohm vertically polarized COM antenna compliant with TSO-C169. The COM antenna should cover the COM frequencies appropriate for your model number. Some possible antennas are listed in Table 7, Table 8, and Table 9.
- Use RG-400 or equivalent, not to exceed 2 dB of signal loss.
- The COM antenna should be mounted on the centerline of the airframe, at least 3 feet from other antennas.
- In multiple GDR installations, one antenna should be mounted on the bottom centerline of the airframe and the other antenna should be mounted on the top centerline of the airframe.
- Avoid sharp bends of the coax.
- Do not route the COM coax near ADF antenna cables.
- Maintain at least a 2 foot distance between COM and NAV coaxial cables when routed parallel to each other.
- CAUTION:
- The installer must ensure that the antenna is placed such that radiation exposure to aircraft personnel is limited to 0.2 mWatt/cm2 to conform to the FCC safe exposure limit. This may be measured or calculated. For direct line of sight spacing the...
- ,𝑃𝑜𝑤𝑒𝑟 -𝐸𝑥𝑝𝑜𝑠𝑢𝑟𝑒.=,,𝑃𝑜𝑤𝑒𝑟-𝑒𝑓𝑓𝑒𝑐𝑡𝑖𝑣𝑒.-4𝜋,𝑅-2.. 𝑚𝑊/,𝑐𝑚-2.
- In this formula, R is the distance from the antenna. The effective transmit power is found by adjusting the transmitter power for the antenna gain in milli-Watts. For a 25 Watt radio with an antenna gain of 3 dBi, the corrected transmit power is 49,...
- Table 7: List of VHF COM Antennas
- Table 8: List of Extended Range VHF COM Antennas
- Table 9: List of Combined VHF & UHF COM Antennas
- B. NAV Antenna
- The GDR requires a 50 Ohm horizontally polarized navigation VOR/LOC/GS antenna meeting TSOs TSO-C34e, TSO-C36e, and TSO-C40c. Some possible antennas are listed in Table 10.
- An external diplexer for VOR/LOC and GS signals is not required for a combined NAV and GS antenna. The GDR contains an internal diplexer to split the GS signal from the VOR/LOC signal.
- Use RG-400 or equivalent, not to exceed 2 dB of signal loss.
- The antenna must be mounted symmetrically with the centerline of the airframe and should have a clear line of sight in front of the aircraft.
- In multiple GDR installations, a splitter may be used for the VOR/LOC and GS signals to route signals to both GDR inputs. A Sensor Systems P/N SSPD-113-10, or equivalent is recommended for this splitter.
- When using a splitter, the coax from the antenna will be routed to the “REC” port of the splitter and the coax from each GDR will be routed to one of the “ANT” ports of the splitter.
- Avoid sharp bends of the coax.
- Maintain at least a 2 foot distance between NAV and COM coaxial cables when routed parallel to each other.
- Table 10: List of NAV Antennas
- C. MB Antenna
- The GDR requires a 50 Ohm horizontally polarized Marker Beacon antenna meeting TSO-C36e. Some possible antennas are listed in Table 11.
- Use RG-400 or equivalent, not to exceed 2dB of signal loss.
- Antenna should be mounted on the bottom of the aircraft, along the centerline of the airframe at least 3 feet from other antennas.
- In multiple GDR installations, a Comant CI 165 dual Marker Beacon antenna (or equivalent) may be used.
- Avoid sharp bends of the coax.
- Maintain at least a 2 foot distance between MB and NAV or COM coaxial cables when routed parallel to each other.
- Table 11: List of MB Antennas
- 19. SIGNAL DESCRIPTION
- Use of the following signals will be determined by the avionics and audio panel interface.
- A. Power and Ground
- In receive mode, maximum current draw is 1.0 A. When one COM channel is transmitting, maximum current draw is 8.0 A.
- B. RS-232 Interface
- The GDR contains two RS-232 communications ports. Both ports can be connected to an EFIS or Radio Management Unit to set frequencies, volumes, and other modes of the COM, NAV, and MB. The GDR will use the last valid data from any tuning port. The d...
- C. ARINC 429 Interface
- The GDR contains two ARINC 429 receive ports and one ARINC 429 transmit port. Either ARINC429 receive port may be used to control the VHF, UHF, NAV, and MB receivers. The GDR will use the last valid data from either port. Burst mode operation is re...
- The ARINC 429 transmit port is used to send COM, VOR/LOC, GS, and MB data and/or status. The following ARINC 429 labels are accepted and/or transmitted by the GDR. Please refer to APPENDIX A – ARINC 429 SPECIFICATIONS for bit definition and other de...
- D. MIC Audio
- There are two microphone audio inputs to the GDR. In dual radio mode, the VHF MIC is used for VHF transmission and the UHF MIC is used for UHF transmission. In single radio mode, only the UHF mic input is used for both bands.
- The MIC input has a 150 Ohm impedance, biased at 12 VDC on MIC+, and has an input range of 0.25 to 2.50 Vrms for full modulation. A typical input setting of 0.27 Vrms is recommended, which minimizes cabin noise.
- E. COM Audio and SIDETONE
- The UHF and VHF bands have separate RX audio outputs and are configurable to combined Sidetone on these outputs. Both bands have a shared Sidetone output, when Sidetone level control by the audio panel is desired. The GDR must be configured to provi...
- All audio outputs are floating differential, but may be installed single-ended with the negative output grounded if required. Differential connection to the audio panel is recommended for noise immunity.
- Each COM audio output can generate up to 100 mW into a 600 Ohm load or 7.75 ± 0.5 Vrms. Normal production setting is for 100 mW into 150 Ohm load at 3.87 ± 0.5 Vrms. Desired audio levels depend on the audio panel and headset impedance used in the ai...
- F. PTT and TX INTERLOCK
- The VHF and UHF transceivers have separate Push-To-Talk (PTT) inputs, except when configured for single radio mode. Each PTT input has an impedance of 7.9k Ohms and requires a voltage below 2.0 VDC to be active.
- The Transmit Interlock discrete input is available in installations where a co-located transmitter’s noise floor opens the receiver’s squelch during transmit. This can occur when COM to COM antenna separation is limited. If this occurs, all receiver...
- When the Transmit Interlock input is pulled low, this inserts a 10 dB pad at the input of the COM receivers and enables the TX Squelch level settings. This reduces the sensitivity of the receiver during transmit and allows an alternate squelch settin...
- CAUTION: The TX Interlock pin of all radios cannot sink any current otherwise TX Interlock will be permanently active unless an external pull up resistor is installed.
- G. NAV and MB AUDIO
- The NAV (VOR/LOC) and MB receivers each have separate balanced audio outputs. Each output can generate 100 mW into a 600 Ohm load at 7.75 ± 0.5 Vrms. Normal production setting is for 100 mW into 150 Ohm load at 3.87 ± 0.5 Vrms.
- H. SDI, Power, and Discrete
- Two pins on the P2 connector are used to set the ARINC 429 Source/Destination Identifier (SDI), one pin is used to remotely turn on the radio, and one pin to tune to the Emergency frequency.
- An open condition is valid when the input is above 12VDC. A ground condition is valid when the input is below 2VDC.
- The two SDI pins are used to identify the identification of the radio for the ARINC 429 words. The combination of SDI1 and SDI2 will determine NAV/COM1 through NAV/COM3 as noted below.
- The PS ENABLE pin enables the power supply of the radio on when grounded. This pin may be wired to a control head power switch or permanently wired to ground. When permanently wired to ground, the unit will activate when 28 Volt power is applied.
- The EMERGENCY pin will tune the VHF and UHF transceivers to the emergency frequency of 121.5MHz (VHF) and 243.00MHz (UHF) when grounded.
- CHAPTER 3 – SYSTEM DRAWINGS
- This section contains the drawings of the GDR-XXXX and electrical connectors.
- 20. MECHANICAL DRAWING
- 21. GDR-XXXX CONNECTOR DRAWINGS
- 22. WIRING DIAGRAMS
- This section will provide generic diagrams for installation of auxiliary equipment to the GDR-XXXX. Refer to the aircraft wiring diagrams for actual connections.
- NOTE: Wiring codes in the diagrams are for reference and may not reflect the actual wire codes on the aircraft. Refer to the aircraft installation drawings for correct codes and connections.
- WIRING NOTES:
- 1. Unless noted otherwise, all new wire to meet MIL-W-22759/16 or later revision. All shielded wire to be MIL-C-27500E with shields type (T) and jackets type (14). For additional routing, bonding, and grounding details, reference AC43-13-1B Chapter ...
- 2. Grounds to be as short as possible unless otherwise indicated. Grounds under 6 inches in length do not require a wire number. Shield preparation should not exceed 3 inches from connector. Shield grounds may not be accomplished by daisy-chaining....
- 3. All wires 22AWG unless otherwise specified.
- 4. Small parts and electrical components required for installation that are not specifically called out in the parts lists shall meet the requirement for aerospace use as “Accepted Parts” or “Standard Parts”. Selection of these parts shall be in acco...
- 5. Due to the many different configuration possibilities and options, the drawings are divided into function groups (Power, Communications, etc.) to allow flexibility in the installation.
- CHAPTER 4 – GROUND FUNCTIONAL TESTS
- CHAPTER 5 – TROUBLESHOOTING
- APPENDIX A – ARINC 429 SPECIFICATIONS
- 29. ARINC Labels 030 and 047, VHF COM
- 30. ARINC Label 034, VOR/ILS Frequency
- 31. ARINC Label 035, DME Frequency
- Table 18: DME Frequency Format for 109.3 MHz, ARINC Label 035
- Note: 1) The frequency in this label is the frequency to which the NAV radio is tuned plus 100 MHz.
- 2) The DME does the translation to the required DME frequency.
- 3) The SDI bits of the NAV radio are used to determine the DME number as shown in Table 22 .
- 4) The SDI bits for Label 035 should always be set to “All Call”, if a scanning DME is used.
- 5) The Sign Status Matrix is always set to Verified.
- 5) Table 21 defines the bit definitions for the navigational source, which will be set to ILS or VOR mode as determined by the NAV frequency received.
- Table 19: ARINC Label 035, Bits 11-13
- Table 20: Sign Status Matrix definition
- Table 21: Navigation source bit definition
- Table 22: ARINC Label 035 SDI bit definition
- 32. ARINC Label 040, UHF COM
- 33. ARINC Label 173, LOC Deviation
- Table 28: LOC Deviation Specification, ARINC Label 173
- Table 29: LOC Deviation Format, ARINC Label 173
- Note: 1) “P” denotes a pad with a “0” value.
- 2) Negative values are encoded as the two’s complements of positive values and the negative sign is annunciated in bit 29.
- 3) The transmitted binary value is found as (ddm)/0.4 * 4096, encoded as two’s complement.
- 4) The two's complement of an N-bit number is the result of subtracting the number from 2N.
- Table 30: Status Matrix definition
- Table 31: Sign Bit definition
- 34. ARINC Label 174, G/S Deviation
- Table 32: Glideslope Deviation Specification, ARINC Label 174
- Table 33: Glideslope Deviation Format, ARINC Label 174
- Note: 1) “P” denotes a pad with a “0” value.
- 2) Negative values are encoded as the two’s complements of positive values and the negative sign is annunciated in bit 29.
- 3) The transmitted binary value is found as ddm/0.8 * 4096, encoded as two’s complement.
- 4) The two's complement of an N-bit number is the result of subtracting the number from 2N.
- Table 34: Status Matrix definition
- Table 35: Sign Bit definition
- 35. ARINC Label 222, VOR Bearing and Marker Beacon Tones
- Table 36: VOR Bearing Specification, ARINC Label 222
- Table 37: VOR Bearing Format, ARINC Label 222
- Note: (1) ‘P’ denotes a pad set for a ‘0’ value.
- (2) Negative values are encoded as the two’s complements of positive values and the negative sign is annunciated in the sign/status matrix.
- (3) Angles in the range 0 to 180˚are encoded as positive numbers. Angles in the range >180˚ to <360˚ are subtracted from 360˚ and the resulting number encoded as a negative value per note 2.
- (4) Bits 11 to 13 are set as per Table 40 when valid Marker Beacon Tones are present. The presence of these tones does not affect the SSM matrix. Only one tone is allowed to be present and shall have a dominance of > 20 dB over the other tones.
- (5) Bit 14 designates ILS mode and indicates only the Marker Tones are functional and the Data field is parked at all zeros.
- Table 38: Status Matrix definition
- Table 39: Sign Bit definition
- Table 40: Marker Beacon Tone Bit definition
- 36. ARINC Label 242 & 244, VOR Ground Station ID
- 37. ARINC Label 263 & 264, ILS Ground Station ID
- 38. ARINC Label 350 LRU Maintenance Status
- 39. ARINC 429 Update Rate (ARINC 429-18, Attachment 2)
64-000109 Page 1 of 62
GDR-XXXX NAV/COM Installation Manual
REVISION HISTORY FOLLOWS ON PAGE 2.
WARNING:
A printed copy of this document may not be the latest revision.
It is the responsibility
of the user to ensure that the latest revision is used.
The latest revision of this document may be
printed from the Genesys Aerosystems electronic document repository.
THIS DOCUMENT CONTAINS PROPRIETARY INFORMATION OF GENESYS AEROSYSTEMS. NEITHER RECEIPT, NOR
POSSESSION THEREOF, CONFERS ANY RIGHT TO REPRODUCE OR USE, OR DISCLOSE, IN WHOLE OR IN PART, ANY SUCH
INFORMATION WITHOUT WRITTEN AUTHORIZATION FROM GENESYS AEROSYSTEMS.
APPROVAL NAME
PURPOSE:
This document is the Installation Manual for
the GDR-XXXX series Navigation and
Communication radio.
AUTHOR R DuRall
CHECK
D Boston
QUALITY
S Conn
COGNIZANT
B DeLong
COGNIZANT
COGNIZANT
RELEASE DATE:
DOCUMENT NUMBER
64-000109
REV
A
Status
Draft
Typed signatures indicate approval. Handwritten,
or electronic signature approval of this document is
on file at Genesys Aerosystems, Anchorage,
Alaska.