Garmin GDU 370 Installation Manual
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Garmin GDU 370 Installation Manual

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G3X

Installation Manual

190-01115-01
August, 2009
Revision A

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Summary of Contents for Garmin GDU 370

  • Page 1: Installation Manual

    Installation Manual 190-01115-01 August, 2009 Revision A...
  • Page 2 Garmin. Garmin hereby grants permission to download a single copy of this manual and of any revision to this manual onto a hard drive or other electronic storage medium to be viewed and...
  • Page 3 The Garmin G3X system includes products like the GDU 37X and the GSU 73 that are not TSO-certified products and have received no FAA approval or endorsement. Consequently the G3X system is not suitable for installation in type-certificated aircraft.

  • Page 4: Table Of Contents

    PARAGRAPH G3X Installation Overview ...1-1 Unpacking Unit ...1-1 Introduction ...1-1 System Overview ...1-2 General G3X LRU Specifications...1-3 Installation Requirements...1-5 Mounting ...1-5 Wiring/Cabling Considerations...1-5 GDU 37X ...2-1 Equipment Description...2-1 Electrical Specifications...2-2 Environmental Specifications ...2-3 Installation Requirements...2-4 Installation Considerations...2-5 Mounting Requirements...2-5 Unit Installation...2-5 Maintenance ...2-5 Panel Cutout Template ...2-6 GMU 44 ...3-1...

  • Page 5: Paragraph Page

    Installation Requirements...5-1 TSO/ETSO Compliance...5-2 Installation Considerations...5-3 Unit Installation...5-4 Maintenance ...5-4 Garmin GPS/XM Antennas...6-1 GPS Antennas ...6-1 XM Antennas ...6-1 Antenna Mounting Considerations...6-2 Teardrop Footprint Antenna Installation (GA 55 and GA 56)...6-7 ARINC 743 Footprint Antenna Installation (GA 55A, GA 57X) ...6-14 Non-Structural Mount Installation ...6-23...
  • Page 6 PARAGRAPH PAGE APPENDIX A: G3X Pinouts ... A-1 A.1 GDU 37X ... A-1 A.2 GMU 44 ... A-5 A.3 GSU 73... A-6 APPENDIX B: Connector Installation Instructions... B-1 B.1 Thermocouple Installation into a Backshell... B-1 B.2 Jackscrew Configuration Module Installation into a Jackscrew Backshell... B-3 B.3 Jackscrew Backshell Installation Instructions...
  • Page 7 FIGURE G3X Interconnect Example...1-2 Coaxial Cable Installation ...1-7 GDU 37X Unit View ...2-1 GDU 37X Mounting Accessories ...2-4 GMU 44 Unit View...3-1 GSU 73 Unit View ...4-1 GSU 73 Air Hose Fitting Locations...4-5 GSU 73 Orientation Calibration...4-6 GTP 59 ...5-1 Recommended Antenna Placement...6-4 Carbon/Glass Buried Antenna Area...6-5 Glare Shield Buried Antenna Area...6-6...
  • Page 8 FIGURE 6-26 Example Bracket Antenna Mounting Under Glareshield...6-24 6-27 Example Non-structural Antenna Mounting Under Glareshield...6-25 6-28 Example Teardrop Antenna Installation in Airframe Under Fabric Skin ...6-26 6-29 Example ARINC 743 Footprint in Airframe Under Fabric Skin ...6-26 6-30 Example Non-structural Antenna Mounting on Airframe ...6-27 6-31 Example Teardrop Footprint Antenna Mounting Under Fabric Skin ...6-28 Softkey Positions...8-1 Aircraft Alignment ...8-10...
  • Page 9 FIGURE PAGE B-17 Insulation/Contact Clearance... B-23 B-18 Daisy Chain Shield Termination ... B-24 B-19 Quick Term Shield Termination... B-25 B-20 Daisy Chain, Quick-Term Shield Termination... B-27 B-21 Daisy Chain Shield Termination between Methods A and B... B-28 C-1.1 GDU 37X Outline Drawing... C-1 C-1.2 GDU 37X Panel Cutout Drawing ...
  • Page 10 TABLE G3X LRU Part Numbers ...1-3 Contents of GDU 37X Assembly (010-00667-XX)...1-3 G3X LRU Power Requirements...1-3 G3X LRU Physical Specifications...1-4 Contents of G3X Installation Kit (K10-00017-00) ...1-5 Contents of G3X LRU Kit (K10-00016-00) ...1-5 Pin Contact and Crimp Tools Part Numbers...1-6 GDU 37X Supply Voltages...2-2 GDU 37X Power Requirements...2-2 GDU 37X GPS Specifications ...2-2...
  • Page 11 B-4 Parts supplied for a Shield Block Installation (Figure B-1) ... B-6 B-5 Parts NOT supplied for a Shield Block Installation (Figure B-1)... B-6 B-6 Shielded Cable Preparations for Garmin Connectors... B-8 B-7 Shielded Cable Preparations – (Quick Term) ... B-14 B-8 Shielded Cable Preparations for Garmin Connectors...
  • Page 12 Garmin retains the exclusive right to repair or replace the unit or software or offer a full refund of the purchase price at its sole discretion. SUCH REMEDY SHALL BE YOUR SOLE AND EXCLUSIVE REMEDY FOR ANY BREACH OF WARRANTY.
  • Page 13 Garmin retains the exclusive right to repair or replace the unit or software or offer a full refund of the purchase price at its sole discretion. SUCH REMEDY SHALL BE YOUR SOLE AND EXCLUSIVE REMEDY FOR ANY BREACH OF WARRANTY.
  • Page 14 GSU 73 HARDWARE MOD LEVEL HISTORY The following table identifies hardware modification (Mod) Levels for the GSU 73 LRU. Mod Levels are listed with the associated service bulletin number, service bulletin date, and the purpose of the modification. The table is current at the time of publication of this manual (see date on front cover) and is subject to change without notice.

  • Page 15: G3X Installation Overview

    This manual provides all of the mechanical and electrical information required for the installation of the G3X system. The Garmin G3X system includes products like the GDU 37X and the GSU 73 that are not TSO-certified products and have received no FAA approval or endorsement.

  • Page 16: System Overview

    1.3 System Overview The G3X is an advanced technology avionics suite designed to integrate pilot/aircraft interaction into one central system. The system combines primary flight instrumentation, aircraft systems instrumentation, and navigational information, all displayed on one, two, or three color screens. The G3X system is composed of several sub-units or Line Replaceable Units (LRUs).

  • Page 17: General G3X Lru Specifications

    1.4 General G3X LRU Specifications 1.4.1 Garmin LRU Part Numbers Table 1-1. G3X LRU Part Numbers GDU 370 Americas DB GDU 370 Atlantic DB GDU 370 Pacific DB GDU 375 Americas DB GMU 44 GSU 73 GTP 59 *Included in G3X LRU Kit (K10-00016-00) Table 1-2.
  • Page 18 1.4.3 Physical Specifications All width, height, and depth measurements are taken with unit rack (if applicable) and connectors. Table 1-4. G3X LRU Physical Specifications Width 6.04 inches GDU 370 (153.4 mm) 6.04 inches GDU 375 (153.4 mm) GMU 44 5.50 inches GSU 73 (139.8 mm)

  • Page 19: Installation Requirements

    Do not attempt to combine more than one unit on the same circuit breaker. RG400 or RG142 coaxial cable with 50 Ω nominal impedance and meeting applicable aviation regulations should be used for the installation. G3X Installation Manual – Installation Overview 190-01115-01 Garmin P/N Quantity 011-00871-00 011-00979-20 011-00979-22...
  • Page 20 & Jackscrew kit) 1. Insertion/Extraction tools from ITT Cannon are all plastic; others are plastic with metal tip. 2. Non-Garmin part numbers shown are not maintained by Garmin and consequently are subject to change without notice. Page 1-6 Revision A...

  • Page 21: Coaxial Cable Installation

    1.7.2 Cable Location Considerations Use cable meeting the applicable aviation regulation for the interconnect wiring. Any cable meeting specifications is acceptable for the installation. When routing cables, observe the following precautions: • All cable routing should be kept as short and as direct as possible. •...

  • Page 22: Section 1 1-1 –

    Connector kits include backshell assemblies. The backshell assembly houses the configuration module and a thermocouple reference junction (if applicable, see Appendix D). Garmin’s backshell connectors give the installer the ability to quickly and easily terminate shield grounds at the backshell housing. The instructions needed to install the Jackscrew Backshell, Configuration Module, and Thermocouple are located in Appendix B.

  • Page 23: Gdu 37X

    #6 screws. The GDU 37X is available in two models, GDU 370 and GDU 375. The GDU 370 is a Garmin Display Unit with a VFR WAAS-GPS receiver. The GDU 375 provides these same features plus an XM receiver.

  • Page 24: Electrical Specifications

    15W, 1.10 Amp 15W, 1.10 Amp GDU 375 2.2.3 GPS Specifications The GDU 37X uses a high-sensitivity GPS receiver that continuously tracks and uses up to 12 satellites to compute and update its position. Table 2-3. GDU 37X GPS Specifications Characteristics...

  • Page 25: Environmental Specifications

    2.2.4 Antennas Table 2-4 lists Garmin and non-Garmin antennas currently supported by the GDU 37X. Refer to Section 6 for Garmin antenna installation information. For non-Garmin antennas, follow the manufacturer’s installation instructions. Only a single GPS antenna is required for installations using more than one GDU 37X unit, as the GDU 37X will “share”...

  • Page 26: Gdu 37X Mounting Accessories

    A 3/32” hex drive tool is required to secure the GDU 37X to the panel as described in Section 2.7 Unit Installation. Figure 2-2. GDU 37X Mounting Accessories Page 2-4 Revision A Garmin P/N Quantity 011-01855-04 330-00625-50 336-00094-00 CONNECTOR KIT...

  • Page 27: Installation Considerations

    GDU 37X. Refer to Section 1.6 for wiring considerations and to Appendix A for pinouts. Connector kits include backshell assemblies. Garmin’s backshell connectors give the installer the ability to quickly and easily terminate shield grounds and install a configuration module (PFD1 only) at the backshell housing.

  • Page 28: Section 2 2-1 –

    Verify dimensions printed accurate before cutting panel. For corner holes, center punch and drill (#36) / tap (6/32) to create threaded holes drill out with 25 drill bit and use Garmin nut-plate P/N 115-01054-00 Page 2-6 Revision A template 7.33 in...

  • Page 29: Gmu 44

    3. GMU 44 3.1 Equipment Description The Garmin GMU 44 Magnetometer is a remote mounted device that interfaces with a Garmin GSU 73 to provide flight attitude and heading data for flight instrumentation. An Attitude and Heading Reference System combines the functions of a Vertical Gyro and a Directional Gyro to provide measurement of Roll, Pitch and Heading angles.

  • Page 30: Environmental Specifications

    DO-178A to demonstrate compliance for the verification and validation of the computer software. 3. Garmin was granted a deviation from TSO-C6d to use SAE AS 8013A instead of SAE AS 8013 as the Minimum Performance Standard. 4. Garmin was granted a deviation from TSO-C6d to list this secondary TSO in the Installation Manual rather than on the article itself.

  • Page 31: Installation Requirements

    Considerations document (190-01051-00) available from the Garmin website ( www.garmin.com) The following guidelines describe proper mechanical installation of the Garmin GMU 44 Magnetometer. The guidelines include requirements for proper location selection in the aircraft, requirements for supporting structure and mechanical alignment and restriction on nearby equipment.
  • Page 32 Table 3-7. Required Distance from Magnetic Disturbances Disturbance Source Electric motors and relays, including servo motors Ferromagnetic structure greater than 1 kg total (iron, steel, or cobalt materials, especially landing gear structure) Ferromagnetic materials less than 1 kg total, such as control cables Any electrical device drawing more than 100 mA current...

  • Page 33: Gsu 73/Gmu 44 Interconnect Harness Fabrication Instructions

    Conn,Circular,Female,9 Ckt Backshell,Circular,Kit,SS Cont,Sckt,Mil Crp,Size 20 **Included in G3X Installation Kit (K10-00017-00) G3X Installation Manual – GMU 44 190-01115-01 Qty. Description Included Garmin P/N Quantity 211-60037-08 330-00360-00 330-90005-01 336-00022-00 GPN or MIL Spec Parts used depend on method chosen M22759/16-22...

  • Page 34: Maintenance

    If the GMU 44 is ever removed, the anti-rotation properties of the mounting screws must be restored. This may be done by replacing the screws with new Garmin PN 211-60037-08. If original screws must be re-used, coat screw threads with Loctite 242 (blue) thread-locking compound, Garmin PN 291-00023-02, or equivalent.

  • Page 35: Gsu 73 Unit View

    There is no TSO/ETSO applicable to the GSU 73. The GSU 73 is intended for the LSA (light sport aircraft) and experimental aircraft markets. The Garmin GSU 73 Sensor Unit is not a TSO-certified product and has received no FAA approval or endorsement.

  • Page 36: Electrical Specifications

    4.2 Electrical Specifications Table 4-1. GSU 73 Supply Specifications Characteristic Input Voltage Range Power Input *Garmin recommends using a Mod 1level GSU 73 in aircraft that exclusively use a +28V supply. Page 4-2 Revision A Interfaces CAN (1) RS-232 (2 TX/2 RX)

  • Page 37: Installation Requirements

    190-01115-01 NOTE Specification -1,400 feet to 50,000 Feet -20,000 feet per minute to +20,000 feet per minute 450 Knots <1.00 Mach -85°C to +85°C -40°C to +70°C +73°C Garmin P/N 011-00979-20** 011-00981-00** 011-01817-00* 011-01818-00** 011-01818-01** Garmin P/N 011-01855-03 330-00185-62 336-00021-00...

  • Page 38: Installation Considerations

    Connector kits include backshell assemblies. The backshell assembly houses the configuration module (P732 only) and a thermocouple reference junction (if applicable). Garmin’s backshell connectors give the installer the ability to quickly and easily terminate shield grounds at the backshell housing. The instructions needed to install the Jackscrew Backshell, Configuration Module, and Thermocouple are located in Appendix B.

  • Page 39: Gsu 73 Air Hose Fitting Locations

    4.5.1 Pneumatic Plumbing The GSU 73 has two ports that are connected to the aircraft’s pitot pressure source and static pressure source. The two ports are labeled on the unit (see Figure 4-2). The pressure ports have 1/8-27 ANPT female threads. The mating fitting must have 1/8-27 ANPT male threads. Figure 4-2.

  • Page 40: Mounting Requirements

    4.6 Mounting Requirements Mount the GSU 73 with the connectors aligned within 1.0 deg of either the X or Y axis of the aircraft. The direction of the unit will be accounted for during the calibration procedure as shown in Figure 4-3. Figure 4-3.

  • Page 41: Unit Installation

    Do not use shock mounting to mount the GSU 73. Shock mounts used for other types of inertial systems are not acceptable for the GSU 73 AHRS. The mounting system must have no resonance with the unit installed. Excessive vibration may result in degraded accuracy. The supporting plate must be rigidly connected to the aircraft primary structure through strong structural members capable of supporting substantial loads.

  • Page 42: G3X Lru Part Numbers

    2010, 2015, and every five years thereafter, so long as the GSU 73 remains a Garmin –supported product. The IGRF model can be updated by the end user via the internet, it is not necessary to return the GSU 73 to Garmin for this update. Otherwise maintenance of the GSU 73 is ‘on condition’...

  • Page 43: Gdu 37X Supply Voltages

    GTP 59 5.1 Equipment Description The Garmin GTP 59 is an outside mounted temperature probe that provides raw air temperature data. The temperature input device is a three-wire temperature probe interface. OAT Power Out and OAT High are connected internally at the OAT probe. The GTP 59 is a Resistive Temperature Device (RTD).

  • Page 44: Tso/Etso Compliance

    1, 2, and 3, instead of RTCA DO-160B as the standard for Environmental Conditions and Test Procedures for Airborne Equipment. 2. Garmin was granted a deviation from TSO-C106 to use Society of Automotive Engineers (SAE) AS 8002 Rev A instead of SAE AS 8002 as the Minimum Performance Standard.

  • Page 45: Installation Considerations

    5.4 Installation Considerations 5.4.1 GTP 59 Icing The GTP 59 OAT probe has no icing protection. If ice accumulates on the GTP 59 OAT probe, its accuracy is unknown. Consequently, air temperature measurements may be incorrect if ice accumulates on the probe. Furthermore, computations dependent upon air temperature measurements may be affected (e.g.

  • Page 46: Section 5 5-1 –

    5. Strip back 1/8” (0.125”) of insulation and crimp pins (11) to each of the conductors in the shielded cable. 6. Cut an AWG #16 (8) wire to 3” long. Strip back 0.5” of insulation from this cable. Connect the shield of the OAT Probe cable (3) to the AWG #16 wire (8).

  • Page 47: Garmin Gps/Xm Antennas

    GA 55/55A, or GA 56 or GA 57X antennas, refer to this section and the drawings in Appendix C. Garmin recommends the antennas shown in Tables 6-1 and 6-3. However, any equivalent GPS or XM antenna that meets the specifications listed in Tables 6-2 and 6-4 should work with the G3X.

  • Page 48: Antenna Mounting Considerations

    Locate the GDU 37X as far as possible from all COM antennas. If a COM antenna is found to be the problem, a 1.57542 GHz notch filter (Garmin P/N 330-00067-00) may be installed in the VHF COM coax, as close to the COM as possible.
  • Page 49 VHF COM or the (re-radiating) ELT transmitter. The separation requirement does not apply to GPS and COM combination antennas, provided the antenna has been tested to meet Garmin’s minimum performance standards. The separating requirement includes the combination with an XM antenna element as well.

  • Page 50: Recommended Antenna Placement

    Figure 6-1 shows the recommended placement of antennas. Figure 6-1. Recommended Antenna Placement Page 6-4 G3X Installation Manual – Antennas Revision A 190-01115-01...

  • Page 51: Carbon/Glass Buried Antenna Area

    Modifications of this sort are not recommended or inferred by Garmin or the installation of the G3X, and the installer should seek the guidance of the kit manufacture for such modifications.

  • Page 52: Glare Shield Buried Antenna Area

    Mounting the antenna under the glare shield (Figure 6-3) is a good option for XM – FIS antennas, although it is not typically the best option for a GPS antenna. This location results in the aft fuselage shading the antenna. Figure 6-3.

  • Page 53: Teardrop Footprint Antenna Installation (Ga 55 And Ga 56)

    This section describes the structural mounting of the teardrop footprint antenna installation. An acceptable installation method is to use Garmin P/N: 115-00846-10 doubler plate with the GA 55 or GA 56 stud mount antennas. Another acceptable method is to fabricate and install one of three doublers (Figure 6-4, Figure 6-5, and Figure 6-6), depending on the thickness of the skin.

  • Page 54: Antenna Installation Instructions

    6.4.2 Antenna Installation Instructions 1. Refer to Table 6-5 and the drawings in Appendix C for guidance on selecting the appropriate mounting cutout. Drill or punch the holes to match the mating part (doubler). 2. Install a doubler plate to reinforce the aircraft skin, as required. Refer to Section 6.4.1 for doubler preparation and Table 6-5 for additional guidance on the doubler installation.
  • Page 55 6.4.3 Reference Figures Figure 6-4. Doubler Design, Teardrop Footprint Antenna, Skin Thickness Figure 6-5. Doubler Design, Teardrop Footprint Antenna, Skin Thickness G3X Installation Manual – Antennas 190-01115-01 0.032" to 0.049" 0.049" to 0.051" Page 6-9 Revision A...

  • Page 56: Doubler Design, Teardrop Footprint Antenna, Skin Thickness 0.051" To 0.063"

    Figure 6-6. Doubler Design, Teardrop Footprint Antenna, Skin Thickness 0.051" to 0.063" Figure 6-7. Sample Doubler Location, Teardrop Footprint Antenna, Metal Skin Aircraft Page 6-10 G3X Installation Manual – Antennas Revision A 190-01115-01...
  • Page 57 Figure 6-8. Skin Cutout Detail, Teardrop Footprint Antenna, Skin Thickness Figure 6-9. Skin Cutout Detail, Teardrop Footprint Antenna, Skin Thickness G3X Installation Manual – Antennas 190-01115-01 0.032" to 0.049" 0.049" to 0.051" Page 6-11 Revision A...
  • Page 58 Figure 6-10. Skin Cutout Detail, Teardrop Footprint Antenna, Skin Thickness Figure 6-11. Doubler Installation, Teardrop Footprint Antenna, Skin Thickness Page 6-12 Revision A 0.051" to 0.063" 0.032" to 0.049" G3X Installation Manual – Antennas 190-01115-01...
  • Page 59 Figure 6-12. Doubler Installation, Teardrop Footprint Antenna, Skin Thickness Figure 6-13. Doubler Installation, Teardrop Footprint Antenna, Skin Thickness G3X Installation Manual – Antennas 190-01115-01 0.049" to 0.051" 0.051" to 0.063" Page 6-13 Revision A...

  • Page 60: Arinc 743 Footprint Antenna Installation (Ga 55A, Ga 57X)

    1.5*rivet diameter) 6.5.1 Preparation of Doubler 1. Use Garmin P/N: 115-00846-00, or refer to Table 6-6 for guidance on selecting the appropriate doubler drawing based on the thickness of skin at the antenna location. Make the doubler from 2024-T3 Aluminum (AMS-QQ-A-250/5), 0.063” sheet thickness.
  • Page 61 4. Locking nuts are required to secure the antenna (locking nuts installed on doubler). Torque the four supplied #10-32 stainless steel screws (Garmin P/N: 211-60212-20, MS51958-67, or equivalent) 20-25 in-lbs. Torque should be applied evenly across all mounting studs to avoid deformation of the mounting area.

  • Page 62: Doubler Design, Arinc 743 Footprint Antenna, Skin Thickness 0.032" To 0.049"

    6.5.3 Reference Figures Figure 6-14. Doubler Design, ARINC 743 Footprint Antenna, Skin Thickness 0.032" to 0.049" Page 6-16 G3X Installation Manual – Antennas Revision A 190-01115-01...

  • Page 63: Doubler Design, Arinc 743 Footprint Antenna, Skin Thickness 0.049" To 0.051"

    Figure 6-15. Doubler Design, ARINC 743 Footprint Antenna, Skin Thickness 0.049" to 0.051" G3X Installation Manual – Antennas Page 6-17 190-01115-01 Revision A...

  • Page 64: Doubler Design, Arinc 743 Footprint Antenna, Skin Thickness 0.051" To 0.063"

    Figure 6-16. Doubler Design, ARINC 743 Footprint Antenna, Skin Thickness 0.051" to 0.063" Page 6-18 G3X Installation Manual – Antennas Revision A 190-01115-01...

  • Page 65: Sample Doubler Location, Arinc 743 Antenna, Metal Skin Aircraft

    Figure 6-17. Sample Doubler Location, ARINC 743 Antenna, Metal Skin Aircraft Figure 6-18. Skin Cutout Detail, ARINC 743 Footprint Antenna, Skin Thickness 0.032" to 0.049" G3X Installation Manual – Antennas Page 6-19 190-01115-01 Revision A...
  • Page 66 Figure 6-19. Skin Cutout Detail, ARINC 743 Footprint Antenna, Skin Thickness 0.049" to 0.051" Figure 6-20. Skin Cutout Detail, ARINC 743 Footprint Antenna, Skin Thickness 0.051" to 0.063" Page 6-20 G3X Installation Manual – Antennas Revision A 190-01115-01...
  • Page 67 Figure 6-21. Doubler Installation, ARINC 743 Footprint Antenna, Skin Figure 6-22. Doubler Installation, ARINC 743 Footprint Antenna, Skin G3X Installation Manual – Antennas 190-01115-01 Thickness 0.032" to 0.049" Thickness 0.049" to 0.051" Page 6-21 Revision A...

  • Page 68: Installation Of Arinc 743 Footprint Antenna

    Figure 6-23. Doubler Installation, ARINC 743 Footprint, Skin Thickness 0.051" to 0.063" Figure 6-24. Installation of ARINC 743 Footprint Antenna Page 6-22 G3X Installation Manual – Antennas Revision A 190-01115-01...

  • Page 69: Non-Structural Mount Installation

    Locking nuts are required to secure the ARINC 743 antenna (locking nuts installed on doubler). Torque the four supplied #10-32 stainless steel screws (Garmin P/N: 211-60212-20, MS51958-67, or equivalent) evenly across all mounting screws.

  • Page 70: Example Bracket Antenna Mounting Under Glareshield

    6.6.2 Considerations for Non-Structural Mounting External mounting of the antenna is preferred, although the antenna can be mounted inside the aircraft. When mounted internally, the antenna does not have to be aligned with the aircraft forward direction, but should be equal to the aircraft typical cruise attitude. There should be a solid mechanical base in the mounting area for the antenna, and existing surfaces or brackets may be used with the doubler plate.

  • Page 71: Example Non-Structural Antenna Mounting Under Glareshield

    Figure 6-27. Example Non-structural Antenna Mounting Under Glareshield G3X Installation Manual – Antennas Page 6-25 190-01115-01 Revision A...

  • Page 72: Example Teardrop Antenna Installation In Airframe Under Fabric Skin

    6.6.4 Non-structural Installation to Airframe Internal Non-structural Installation Figure 6-28 and Figure 6-29 show examples of under the fabric skin non-structural mounting of the antenna to the airframe of a tube-and-fabric aircraft. In Figure 6-28, a bracket is made to attach to the airframe, just under the fabric for a teardrop antenna installation.

  • Page 73: Example Non-Structural Antenna Mounting On Airframe

    External Non-structural Installation Figure 6-30 is an example of an external, non-structural mounting of the antenna in a tube-and-fabric aircraft. The antenna support bracket shown should be made of 2024-T3 Aluminum with a minimum material thickness 0.032” and maximum distance between airframe tubes of 36”. The bracket is installed to the airframe under the fabric, and the antenna is mounted externally to the bracket.

  • Page 74: Section 6 6-1 –

    Minimum Distance from Metal Tube Structure Requirements Figure 6-31 shows minimum distance from metal tube structure requirements for internal, non-structural mounting of the antenna. Table 6-7 presents minimum distance requirements between the tube structure and the antenna for cases where the antenna sits underneath the fabric in a metal-tube structure aircraft. Figure 6-31 illustrates the tube diameter ( Figure 6-31.

  • Page 75: Software, Configuration, Databases, And Xm Activation

    Software, Configuration, Databases, and XM Activation 7.1 Configuration Mode Some software loading and all configuration settings are performed in the configuration mode. To enter configuration mode, hold down the left-hand softkey (softkey #1) while powering on the GDU 37X. If more than one GDU 37X is installed, hold down softkey #1 on PFD1.
  • Page 76 7.2.2 Audio Data Identification Do the following steps to view the unit’s current audio data information: 1. Turn on the unit in normal mode. 2. Press the MENU key twice to display the Main Menu 3. Use the FMS Joystick to select Database Information 4.

  • Page 77: Software Loading Procedure

    7.3 Software Loading Procedure Software loading is performed in normal mode. Sections 7.3.1 and 7.3.2 describe the GDU and GSU software load procedure. 7.3.1 GDU Software Loading Procedure 1. Power on the GDU in normal mode, then insert the properly formatted SD card into the SD card slot.

  • Page 78: Configuration

    7.4 Configuration Pages 7.4.1 Main Configuration Page The Main Configuration Page is used to display LRU (device) specific information such as Unit and System ID’s and Database information for the various databases used by the G3X. This page has no user- selectable options.

  • Page 79: Acft Configuration Page

    7.4.2 ACFT Configuration Page The Aircraft Configuration Page allows setting the parameters for Flight Planning, Aircraft Identifier, and Map Symbol. The aircraft’s cruise speed, fuel flow, aircraft identifier, and map symbol can be entered on this page. The flight planning fields let you adjust the default values (cruise speed and fuel flow) used for flight planning calculations.
  • Page 80 7.4.3 W/B (Weight/Balance) Configuration Page The W/B Configuration Page allows setting the weight and balance parameters for the airplane, these parameters are then used on the Main Menu W/B Page in normal mode. Weight/Balance may be used during pre-flight preparations to verify the weight and balance conditions of the aircraft. By entering the weight and arm values into the Aircraft window, the GDU 37X can calculate the total weight, moment, and center of gravity (CG).

  • Page 81: Units Configuration Page

    7.4.4 UNITS Configuration Page The Units Configuration Page allows selection of the desired displayed units for the listed items in the Units Configuration window. The various settings for Location Format, Map Datum, and Heading can be accessed in the Position Configuration window. See the G3X Pilot’s Guide for a description of Location Format and Map Datum.
  • Page 82 7.4.5 DSPL (Display) Configuration Page The DSPL Configuration Page allows setting the parameters for Display and Backlight Control configuration. 1. In configuration mode, use the FMS Joystick to select the DSPL Page. 2. Use the FMS Joystick to select the desired configurable item and make the desired change. Then press the ENT Key or use the FMS Joystick to select the next item.
  • Page 83 7.4.5.1 Display Configuration Window: Backlight Intensity: Can be set to Auto or Manual (this setting is also available in normal mode on the Display Setup page). Auto–Sets the backlight intensity (display brightness) based on the aircraft’s instrument lighting bus voltage. Manual–Allows setting the display brightness by changing the Backlight Intensity (0-9) setting found beside the ‘Manual’...

  • Page 84: Sound Configuration Page

    7.4.6 SOUND Configuration Page The SOUND Configuration Page allows setting the parameters for various alert and message tones. 1. In configuration mode, use the FMS Joystick to select the SOUND Page. 2. Use the FMS Joystick to select the desired configurable item and make the desired change. Then press the ENT Key or use the FMS Joystick to select the next item.

  • Page 85: Comm Configuration Page

    Aviation In - The proprietary format used for input to the G3X (baud rate of 9600) from an FAA certified Garmin panel mount unit. Allows the G3X to display a Go To or route selected on the panel mount unit, which eliminates the need to enter the destination on both units.

  • Page 86: Garmin Database Updates

    The GDU 37X MFD database updates can be obtained by visiting the ‘flyGarmin’ website (www.fly.garmin.com). The ‘flyGarmin’ website requires the unit’s System ID to update databases, this allows the databases to be encrypted with the unit’s unique System ID when copied to the SD Card. The System ID is displayed on the System Setup Menu in normal mode, or on the Main Page in configuration mode.

  • Page 87: Available Databases

    5. When the update process is complete, the screen updates the database status 6. Once the database(s) have been updated, the SD card can be removed from the unit. 7. The unit must be restarted by pressing the Restart softkey. 8.

  • Page 88: Section 7 7-1 –

    all obstacles are necessarily charted and therefore may not be contained in the obstacle database. This database is updated on a 56-day cycle. SafeTaxi The SafeTaxi database contains detailed airport diagrams for selected airports. These diagrams aid in following ground control instructions by accurately displaying the aircraft position on the map in relation to taxiways, ramps, runways, terminals, and services.

  • Page 89: Post-Installation Checkout And Calibration Procedures

    The CONFIG GSU Page must be “unlocked” by pressing the softkeys 2, 3, 4 in order (Figure 8-1) to select a calibration procedure. All procedures in this section require that the GPS receiver is receiving sufficient satellite signal to compute a present position. This requires outdoor line-of-site to GPS satellite...

  • Page 90: Recommended Test Equipment

    Test the GPS Receiver: 1. Power on unit and use the FMS Joystick to select the Info Page. 2. Verify that the GPS receiver is functional and able to calculate its present position. Page 8-2 G3X Installation Manual – Post Installation Checkout and Calibration Procedures...
  • Page 91 Test the XM Receiver (if applicable): 1. Power on unit and use the FMS Joystick to select the XM Page. 2. Verify that the XM receiver is functioning correctly as indicated by the green signal strength bars. See Section 8.6 for XM Activation Instructions if needed. G3X Installation Manual –...

  • Page 92: Gsu 73/Gmu 44 Post-Installation Calibration Procedure

    GMU 44 unit. Garmin recommends this test be performed at least once every 12 months by all aircraft manufacturers on a minimum of one production aircraft for every airframe type or model equipped with the G3X system.

  • Page 93: Data Validity Requirements For Ahrs Calibration Procedures

    For each Calibration Procedure, Table 8-2 lists the LRU’s that require valid calibration data. Table 8-2. Data Validity Requirements for AHRS Calibration Procedures AHRS Calibration Procedure Pitch/Roll Offset Magnetic Calibration Heading Offset Engine Run-Up Magnetometer Interference Test Mounting Orientation Identification Table 8-3 lists the type of valid calibration data required to be output by each LRU for the Calibration Procedures listed in Table 8-2.
  • Page 94 8.3.1 Calibration Procedure A: AHRS ORIENTATION 1. Enter configuration mode by holding down the left-hand softkey while powering on the GDU 37X. 2. Use the FMS Joystick to select the GSU Page. 3. Unlock the GSU Page by pressing softkeys 2, 3, 4 in order. 4.
  • Page 95 9. Use the FMS Joystick to select the direction of the GSU 73 connectors per the on-screen instructions, select OK and press the ENT Key to continue. 10. After a few minutes the calibration will finish and a Done button will appear at the bottom of the display, ensure that a CALIBRATION SUCCESSFUL message appears at the bottom of the display, press the ENT Key to return to the GSU Status Page.
  • Page 96 8.3.2 Calibration Procedure B: Pitch/Roll Offset Compensation by Aircraft Leveling 1. Enter configuration mode by holding down the left-hand softkey while powering on the GDU 37X (if needed). 2. Use the FMS Joystick to select the GSU Page (if needed). 3.
  • Page 97 7. Ensure that the aircraft has been properly leveled per the on-screen instructions. 8. Use the FMS Joystick to highlight the Calibrate button at the bottom of the display, press the ENT Key to begin the calibration. 9. After a few minutes the calibration will finish and a Done button will appear at the bottom of the display, ensure that a CALIBRATION SUCCESSFUL message appears at the bottom of the display, press the ENT Key to return to the GSU Status Page.

  • Page 98: Aircraft Alignment

    8.3.3 Calibration Procedure C: Magnetometer Calibration Calibration Procedure B must be successfully completed prior to Calibration Procedure C. Calibration Procedure C must be carried out at a location that is determined to be free of magnetic disturbances, such as a compass rose. Attempting to carry out this maneuver on a typical ramp area will not yield a successful calibration.
  • Page 99 3. Unlock the GSU Page by pressing softkeys 2, 3, 4 in order (if needed). 4. Ensure that all the required status boxes are checked (Tables 8-2 and 8-3). The GMU 44 and GSU 73 units must be communicating with the GDU 37X, and the GPS antenna must have clear view of the sky or a GPS repeater to produce positive status indications.
  • Page 100 7. Ensure that the aircraft has been properly positioned per the on-screen instructions. 8. Use the FMS Joystick to highlight the Calibrate button at the bottom of the display, press the ENT Key to begin the calibration. 9. The PFD advises the operator when to turn the aircraft, when to stop, and when to turn again. 10.
  • Page 101 11. The PFD guides the operator to dwell at multiple headings around a complete circle. Due to high winds or excessive airframe vibration, the operator may encounter a condition where the PFD restarts the 18-second countdown without full completion of the previous countdown.
  • Page 102 8.3.4 Calibration Procedure D: Heading Offset Compensation Calibration Procedures B and C must have been successfully completed before Calibration Procedure D can be performed. This procedure is optional, and generally not recommended as it is difficult to orient the entire aircraft with an absolute accuracy of less than a few degrees.
  • Page 103 6. Use the FMS Joystick to highlight the Calibrate button, press the ENT Key. 7. Ensure that the aircraft has been properly positioned per the on-screen instructions. 8. Use the FMS Joystick to highlight the Calibrate button at the bottom of the display, press the ENT Key to begin the calibration.
  • Page 104 11. After the complete calibration is finished, a Done button will appear at the bottom of the display, ensure that a CALIBRATION SUCCESSFUL message appears at the bottom of the display, press the ENT Key to return to the GSU Status Page. Page 8-16 G3X Installation Manual –...
  • Page 105 8.3.5 Calibration Procedure E: Engine Run-Up Vibration Test Calibration Procedure E is required for all installations to validate the vibration characteristics of the installation. Calibration Procedures B through D are not required prior to this procedure. 1. Enter configuration mode by holding down the left-hand softkey while powering on the GDU 37X (if needed).
  • Page 106 7. Ensure that the aircraft has been properly positioned per the on-screen instructions. 8. Use the FMS Joystick to highlight the Calibrate button at the bottom of the display, press the ENT Key to begin the calibration. 9. The PFD display instructs the operator to gradually increase power from idle to full throttle and back to idle over the course of a couple of minutes.
  • Page 107 e) Absence of mounting supports recommended by the aircraft manufacturer. f) GSU 73 connector not firmly attached to unit. g) Cabling leading to GSU 73 or GMU 44 not firmly secured to supporting structure. h) An engine/propeller combination that is significantly out of balance. In some aircraft, attempting the engine run-up test on a day with very strong and/or gusty winds may cause the test to occasionally fail.
  • Page 108 GSU 73 AHRS. Calibration Procedures A through E are not required prior to this execution of this procedure. Garmin recommends this test be performed at least once every 12 months by all aircraft manufacturers on a minimum of one production aircraft for every airframe type or model equipped with the G3X system.
  • Page 109 5. Use the FMS Joystick to select MAGNETOMETER INTERFERENCE TEST. 6. Use the FMS Joystick to highlight the Calibrate button, press the ENT Key. 7. Ensure that the aircraft has been properly prepared per the on-screen instructions. See Table 8-2 for a sample test sequence. G3X Installation Manual –...
  • Page 110 8. Use the FMS Joystick to highlight the Calibrate button at the bottom of the display, press the ENT Key to begin the calibration. 9. The operator should carry out the actions called for in the prepared test sequence. It is important that all actions are carried out in the order and at the precise elapsed time as specified in the prepared test sequence.

  • Page 111: Magnetometer Interference Test Sequence Example

    8.0 milligauss in the Z axis indicates a problem that must be resolved. Compare the corresponding timestamps with the prepared test sequence to identify which action produced the problem. Contact Garmin for assistance in resolving the problem. Two common reasons for a failed magnetometer interference test are: 1) New equipment is installed in close proximity to the GMU 44 magnetometer.
  • Page 112 8.3.7 Site Evaluation of Magnetic Disturbances for Magnetometer Calibration Procedure As mentioned in Section 8.3.3, the Magnetometer Calibration Procedure (Calibration Procedure C) must be carried out at a site that is determined to be free of magnetic disturbances. Typically, a compass rose is an acceptable location to perform the magnetometer calibration procedure.
  • Page 113 The Magnetometer Calibration Procedure must consistently report “CALIBRATION SUCCESSFUL / SITE IS CLEAN” in both the clockwise and counter-clockwise directions for the site to be considered acceptable. More than one failure out of ten attempts in a given direction would be sufficient reason to conclude the site is not acceptable.

  • Page 114: Section 8 8-1 –

    This page intentionally left blank Page 8-26 G3X Installation Manual – Post Installation Checkout and Calibration Procedures Revision A 190-01115-01...

  • Page 115: Troubleshooting

    If the labels weren’t the cause, determine what brand of SD card was being used (Garmin recommends using SanDisk® or Toshiba brand cards). 9.1.2 Crosstalk Error (Dual or Three Screen Systems) Crosstalk Error messages occur if there is a mismatch in GDU 37X software versions.

  • Page 116: Gmu 44

    9.2 GMU 44 Figure 9-1 – Heading Failure Indication (Full-Screen PFD) 9.2.1 Red-X Failures If a Red-X (steady or intermittent) is displayed on the heading (Figure 9-1), check the following while the aircraft is on the ground: 1. When taxiing without reliable GPS information, heading performance is susceptible to the presence of magnetic anomalies (metal buildings, underground steel culverts, steel grates in the ramp, rebar).

  • Page 117: Gsu 73

    4 satellites and have a 3D GPS Solution. GSU 73 AHRS operation needs at least two of the three inputs from; the GPS receiver, the GMU 44, and the Air data (also part of the GSU 73) for proper operation. See Table 9-1 below for the attitude and heading outputs the GSU 73 can provide based on the available data inputs.
  • Page 118 9.3.1 Attitude/Heading Failure Troubleshooting Prior to troubleshooting an Attitude Failure on-board the aircraft, gather information from the pilot by asking the following questions. 1. What specifically was the nature of the failure? Was it a Red-X of only heading, only pitch/roll, or both? 2.

  • Page 119: Attitude, Air Data, And Engine/Airframe Failure Indication

    Figure 9-2 – Attitude, Air Data, and Engine/Airframe Failure Indication (Reversionary or Split-Screen PFD) Figure 9-3 – Attitude Fail Indication (PFD) G3X Installation Manual - Troubleshooting Page 9-5 190-01115-01 Revision A...

  • Page 120: Ahrs Align Message (Pfd)

    Figure 9-4 – AHRS Align Message (PFD) 9.3.2 Heading/Pitch/Roll Troubleshooting The GSU 73 may not be able to provide valid heading/pitch/roll data for the following reasons: 1. The GSU 73 external memory module in the harness (that stores the installation configuration parameters) is either not present or not wired properly.

  • Page 121: Gsu 73 -Air Data Troubleshooting

    9.4 GSU 73 –Air Data Troubleshooting Under normal operating conditions, the GSU 73 provides the following air data information: • Total Air Temperature is measured • Outside Air Temperature (OAT) • Indicated Airspeed (IAS) • True Airspeed (TAS) • Barometric Altitude •...
  • Page 122 1. Inspect GSU73 pitot/static plumbing integrity 2. Inspect pitot/static ports and associated equipment 3. If the problem persists replace the GSU 73 with a known good unit 9.4.1 Troubleshooting GSU 73 Engine Indication Failures See Figure 9-7 for example. The following may help to determine to cause of an Engine Indication failure.

  • Page 123: Attitude, Heading, Air Data, And Engine/Airframe Failure

    Figure 9-7 – Attitude, Heading, Air Data, and Engine/Airframe Failure (Reversionary or Split-Screen PFD) G3X Installation Manual - Troubleshooting Page 9-9 190-01115-01 Revision A...

  • Page 124: Troubleshooting On-Board The Aircraft

    A Garmin Field Service Engineer may ask the technician to download the fault logs to a PC (via the USB port on the GSU 73) and email the logs back to Garmin to help determine if the problem is in the GSU 73 or in the aircraft.

  • Page 125: Gsu Page

    9.6 GSU Page All three status boxes on the GSU Page (config mode) must indicate a positive state (green check marks) before performing any calibration procedures (Section 8). The GMU 44 and GSU 73 units must be communicating with the GDU 37X, and the GPS antenna must have clear view of the sky to produce positive status indications.

  • Page 126: Section 9 9-1 –

    This page intentionally left blank Page 9-12 G3X Installation Manual –Troubleshooting Revision A 190-01115-01...

  • Page 127: Return To Service Information

    10 Return to Service Information These return to service procedures are intended to verify the serviceability of the appliance only. These tests alone do not verify or otherwise validate the airworthiness of the installation. 10.1 GDU 37X 10.1.1 Original GDU 37X is Reinstalled No software or configuration loading is required if the original GDU 37X is reinstalled.

  • Page 128: Gmu 44

    If the GMU 44 is removed, the anti-rotation properties of the mounting screws must be restored. This may be done by replacing the screws with new Garmin P/N 211-60037-08. If original screws must be re- used, coat screw threads with Loctite 242 (blue) thread-locking compound, Garmin P/N 291-00023-02, or equivalent.

  • Page 129: Appendix A G3X Pinouts

    APPENDIX A G3X Pinouts A.1 GDU 37X A.1.1 P3701 Connector PIN 1 PIN 34 Figure A-1. View of J3701 Connector from Back of Unit Pin Name MONO AUDIO OUT HI STEREO AUDIO OUT LO STEREO AUDIO OUT LEFT SPARE SPARE SPARE SPARE SPARE...
  • Page 130 Pin Name CONFIG MODULE CLOCK SIGNAL GROUND SIGNAL GROUND SIGNAL GROUND SIGNAL GROUND SPARE SPARE SPARE SPARE CDU SYSTEM ID PROGRAM* 4 14V LIGHTING BUS HI SIGNAL GROUND CAN BUS LO CAN BUS HI RS-232 IN 1 RS-232 OUT 1 CONFIG MODULE GROUND CONFIG MODULE DATA * Indicates Active Low...
  • Page 131 A.1.4 Serial Data A.1.4.1 RS-232 The RS-232 outputs conform to EIA Standard RS-232C with an output voltage swing of 0-5V when driving a standard RS-232 load. Pin Name RS-232 IN 1 RS-232 OUT 1 RS-232 IN 2 RS-232 OUT 2 RS-232 IN 3 RS-232 OUT 3 A.1.4.2 CAN Bus...
  • Page 132 A.1.6 Audio A.1.6.1 Mono Audio Pin Name MONO AUDIO OUT HI MONO AUDIO OUT LO A.1.6.2 Stereo Audio Pin Name STEREO AUDIO OUT LEFT STEREO AUDIO OUT LO STEREO AUDIO OUT RIGHT STEREO AUDIO OUT LO The left and right common pins (pins 2 and 20) may be tied together or only one may be used. It is not necessary to use both common pins.

  • Page 133: Gmu 44

    A.2 GMU 44 A.2.1 P441 Connector Figure A-2. View of J441 Connector Looking at Rear of Unit Pin Name SIGNAL GROUND RS-485 OUT B SIGNAL GROUND RS-485 OUT A SPARE POWER GROUND SPARE RS-232 IN +12 VDC POWER A.2.2 Power Function Power-input pins accept 14/28 VDC.

  • Page 134: Gsu 73

    A.3 GSU 73 A.3.1 Connector Description The GSU 73 has one 62-pin connector (J731) and one 78-pin connector (J732) located on the connector end of the unit, as shown below. J731 and J732 are clearly marked on the connector end plate. Figure A-3 Rear View of Connector End Plate A.3.2 Pin List...
  • Page 135 Pin Name RS-232 IN 2 RS-232 OUT 2 RS-232 IN 3 RS-232 OUT 3 ARINC 429 OUT 1 A ARINC 429 OUT 1 B ARINC 429 OUT 2 A ARINC 429 OUT 2 B SIGNAL GROUND ARINC 429 IN 1 A ARINC 429 IN 1 B ARINC 429 IN 2 A ARINC 429 IN 2 B...
  • Page 136 A.3.2.2 P732 Connector Figure A-5 Rear Connector J732 Viewed from Connector End of Unit Pin Name ANALOG IN 2 LO ANALOG IN 3 HI ANALOG IN 8 LO ANALOG IN 9 LO ANALOG IN 14 LO ANALOG IN 17 LO ANALOG IN 24 LO ANALOG IN 23 LO THERMOCOUPLE REF IN LO...
  • Page 137 Pin Name ANALOG IN 4 LO ANALOG IN 1 LO ANALOG IN 10 LO ANALOG IN 7 LO ANALOG IN 15 LO ANALOG IN 16 LO ANALOG IN 25 LO ANALOG IN 22 HI ANALOG/CURRENT MONITOR IN 2 HI ANALOG IN 21 LO ANALOG/CURRENT MONITOR IN 1 LO ANALOG IN 18 LO ANALOG IN 13 LO...
  • Page 138 A.3.3 Power I/O A.3.3.1 Aircraft Power The GSU 73 has four inputs for aircraft power bus inputs of 14/28Vdc. Connector P731 P731 P731 P731 A.3.3.2 Transducer Output Power The GSU 73 supplies output power for engine/airframe sensors that may require supply voltage excitation.
  • Page 139 A.3.5 Serial Data Electrical Characteristics A.3.5.1 ARINC 429 Input/Output The ARINC 429 outputs conform to ARINC 429 electrical specifications when loaded with up to 5 standard ARINC 429 receivers. Connector P731 P731 P731 P731 P731 P731 P731 P731 P731 P731 P731 P731 A.3.5.2 RS-232 Input/Output...
  • Page 140 A.3.5.3 RS-485 Input The GSU 73 contains one channel of RS-485 serial data communications. Connector P731 P731 A.3.5.4 CAN Bus This data bus conforms to the BOSCH standard for Controller Area Network 2.0-B. This bus complies with ISO 11898. CAN BUS TERMINATION should be connected to CAN BUS LO if GSU is located at the end of the bus.
  • Page 141 A.3.6.2 Discrete Outputs INACTIVE: Floating (can be pulled up to externally sourced Vout in the range 0 ≤  V out ≤  3 3VDC) Leakage current in the INACTIVE state is typically ≤ 10 uA to ground ACTIVE: Vout ≤ 0.5VDC with ≤  2 0 mA sink current Sink current must be externally limited to 20 mA max Connector P731...
  • Page 142 If installing an ungrounded thermocouple to an Analog In input, a DC reference must be added to the LO input. This can be accomplished by adding a resistance of 1 MΩ or less between ground and the Analog In LO input that the ungrounded thermocouple is installed on. Connector P732 P732...
  • Page 143 Connector P732 P732 P732 P732 P732 P732 P732 P732 P732 P732 P732 P732 P732 P732 A.3.8 Temperature Inputs Temperature input is used for Outside Air Temperature (OAT) computations. The temperature input is a three-wire temperature probe interface. OAT Power Out and OAT High are connected internally at the OAT probe.
  • Page 144 The following table lists the minimum frequency, maximum frequency, and duty cycles for each of these inputs. Pin Name FREQUENCY COUNTER IN* 1 FREQUENCY COUNTER IN* 2 FREQUENCY COUNTER IN* 3 FREQUENCY COUNTER IN* 4 *Each frequency counter channel will be configured for a high or low speed input based on the signal being measured.

  • Page 145: Appendix B Connector Installation Instructions

    APPENDIX B Connector Installation Instructions Thermocouple Installation into a Backshell Table B-1 lists parts needed to install a Thermocouple. Parts for this installation are included in the Thermocouple Kit (011-00981-00), which is included in the G3X Installation Kit (K10-00017-00). Table B-1. Thermocouple Kit GPN 011-00981-00 Figure Ref Description 3”...

  • Page 146: B-2 Jackscrew Backshell Thermocouple Installation

    Figure B-2. Jackscrew Backshell Thermocouple Installation Page B-2 G3X Installation Manual – Appendix B Revision A 190-01115-01...

  • Page 147: Jackscrew Configuration Module Installation Into A Jackscrew Backshell

    Jackscrew Configuration Module Installation into a Jackscrew Backshell Tables B-2 & B-3 list parts needed to install a Jackscrew Configuration Module with pins or with sockets. Parts for these installations are included in the 011-00979-20 and 011-00979-22 kits, which are included in the G3X Installation Kit (K10-00017-00).

  • Page 148: B-3 Insulation/Contact Clearance

    For the following steps please refer to Figures B-3 & B-4. 1. Strip back approximately 0.17 inches of insulation from each wire of the four conductor wire harness (item 3) and crimp either a pin (item 4) or a socket (item 9) to each conductor. It is the responsibility of the installer to determine the proper length of insulation to be removed.

  • Page 149: B-4 Jackscrew Backshell Installation

    Figure B-4. Jackscrew Backshell Installation G3X Installation Manual – Appendix B Page B-5 190-01115-01 Revision A...

  • Page 150: Jackscrew Backshell Installation Instructions

    Jackscrew Backshell Installation Instructions B.3.1 Shield Block Installation Parts Tables B-4 and B-5 list the parts needed to install a Shield Block. Parts listed in Table B-4 are supplied in the jackscrew backshell kits (011-01855-03 and 011-01855-04). Parts listed in Table B-5 are to be provided by the installer.

  • Page 151: B-5 Shield Install Onto A Jackscrew Backshell (78 Pin Example)

    NOTE In Figure B-5, “AR” denotes quantity “As Required” for the particular installation. Figure B-5. Shield Install onto a Jackscrew Backshell (78 pin example) G3X Installation Manual – Appendix B Page B-7 190-01115-01 Revision A...

  • Page 152: B-6 Method A.1 For Shield Termination

    For the following steps please refer to the drawings showing the installation of a Jackscrew Backshell. 1. The appropriate number of Jackscrew Backshells will be included in the particular LRU connector kit. Figure B-6. Method A.1 for Shield Termination Table B-6. Shielded Cable Preparations for Garmin Connectors Number Float Backshell of Pins...
  • Page 153 3. Connect a Flat Braid (item 4) to the shield exposed through the window of the prepared cable assembly (item 2) from step 2. The Flat Braid should go out the front of the termination towards the connector. It is not permitted to exit the rear of the termination and loop back towards the connector (Figure B-6).

  • Page 154: B-7 Insulation/Contact Clearance

    Secondary Method: Solder a Flat Braid (item 4) to the shield exposed through the window of the prepared cable assembly (item 2). Ensure a solid electrical connection through the use of acceptable soldering practices. Use care to avoid applying excessive heat that burns through the insulation of the center conductors and shorts the shield to the signal wire.
  • Page 155 6. Insert newly crimped pins and wires into the appropriate connector housing location as specified by the installation wiring diagrams. 7. Cut the Flat Braid (item 4) to a length that, with the addition of a ring terminal, will reach one of the tapped holes of the Jackscrew backshell (item 1) (Figure B-5).

  • Page 156: B-8 Method A.2 (Daisy Chain) For Shield Termination

    B.3.3 Shield Termination Technique - Method A.2 (Daisy Chain) In rare situations where more braids need to be terminated for a connector than three per ring terminal it is allowable to daisy chain a maximum of two shields together before coming to the ring terminal (Figure B-8).

  • Page 157: B-9 Method B.1 (Quick Term) For Shield Termination

    Connect a Flat Braid (item 4) to the folded back shield of the prepared cable assembly. The flat braid should go out the front of the termination towards the connector. It is not permitted to exit the rear of the termination and loop back towards the connector. (Figure B-9). Make this connection using an approved shield termination technique.

  • Page 158: B-10 Method B.2 (Daisy Chain-Quick Term) For Shield Termination

    Table B-7. Shielded Cable Preparations – (Quick Term) Backshell Size B.3.5. Shield Termination-Method B.2 (Daisy Chain-Quick Term) In rare situations where more braids need to be terminated for a connector than three per ring terminal it is allowable to daisy chain a maximum of two shields together before coming to the ring terminal (Figure B-10).

  • Page 159: B-11 Daisy Chain Between Methods A And B

    B.3.6. Daisy Chain between Methods A and B In rare situations where more braids need to be terminated for a connector than three per ring terminal and a mixture of Methods A and B have been used, it is allowable to daisy chain a maximum of two shields together from a Method A termination to a Method B (Figure B-11).

  • Page 160: B-12 Method C.1 Double-Shield Termination

    All other restrictions set forth for in Table B-8 are applicable. The maximum length of the braids should be approximately 4 inches. Figure B-12. Method C.1 Double-Shield Termination Table B-8. Shielded Cable Preparations for Garmin Connectors Number of Backshell Float Min...

  • Page 161: B-13 Method C.2 Double-Shield Termination

    B.3.8 Double-Shield Termination Technique (Quick Term) - Method C.2 In addition to method C.1, described previously, another suitable method for double-shielding wires is presented in Figure B-13. All restrictions set forth for Method C.1 (Table B-8) are still applicable. The maximum length of the braids should be approximately 4 inches. Figure B-13.

  • Page 162: B-14 D-Sub Spliced Signal Wire Illustration

    B.3.10 Splicing Signal Wires Figure B-14 illustrates that a splice must be made within a 3 inch window from outside the edge of clamp to the end of the 3 inch max mark. Keep the splice out of the backshell for pin extraction, and outside of the strain relief to avoid preloading.

  • Page 163: Circular Connector Installation Instructions

    Circular Connector Installation Instructions B.4.1 Pigtail Installation Parts Table B-9 provides a list of parts needed to install a circular connector with backshell. Parts for this installation are included in the pigtail connector kits and some are to be provided by the OEM/installer. Table B-9.

  • Page 164: B-15 Circular Connector Install (19 Contact Example)

    NOTE In Figure B-15, “AR” denotes quantity “As Required” for the particular installation. Figure B-15. Circular Connector Install (19 contact example) B.4.2 Standard Shield Termination Technique – Method A Figure B-16. Standard Shield Termination Page B-20 G3X Installation Manual – Appendix B Revision A 190-01115-01...

  • Page 165: B-11 Shielded Cable Preparations For Garmin Connectors

    Table B-11. Shielded Cable Preparations for Garmin Connectors Backshell Size Insert Arrangement 1. At one end of a shielded cable (item 4) measure a distance between “Window Min” to “Window Max” (Table B-11) and cut a window (max size 0.35”) in the jacket to expose the shield (Figure B-16).
  • Page 166 Secondary Method Solder a flat braid (item 6) to the shield exposed through the window of the prepared cable assembly (item 4). Ensure a solid electrical connection through the use of acceptable soldering practices. Use care to avoid applying excessive heat that burns through the insulation of the center conductors and shorts the shield to the signal wire.

  • Page 167: B-17 Insulation/Contact Clearance

    Figure B-17. Insulation/Contact Clearance 5. Insert newly crimped contacts and wires into the appropriate connector housing location as specified by the installation wiring diagrams. 6. Cut the flat braid (item 6) to a length that, with the addition of a ring terminal, will reach the grounding hole of the circular backshell (item 3) (Figure B-15).

  • Page 168: B-18 Daisy Chain Shield Termination

    B.4.3 Daisy Chain Shield Termination Technique – Method A In rare situations where more braids need to be terminated for a connector than three per ring terminal it is allowable to daisy chain a maximum of two shields together before coming to the ring terminal (Figure B-18).

  • Page 169: B-19 Quick Term Shield Termination

    B.4.4 Quick Term Shield Termination – Method B If desired, the drain wire termination (item 5) and the floating shield termination (item 7) can be effectively combined into a “Quick Term”. This method eliminates the float in the cable insulation and moves the placement of the window which was described by the dimensions “Window Min”...
  • Page 170 Preferred Method Slide a solder sleeve (item 5) onto the prepared cable assembly (item 4) and connect the flat braid (item 6) to the shield using a heat gun approved for use with solder sleeves. It may prove beneficial to use a solder sleeve with a pre-installed flat braid versus having to cut a length of flat braid to be used.

  • Page 171: B-20 Daisy Chain, Quick-Term Shield Termination

    8. Terminate the ring terminals to the circular backshell (item 3) by placing items on the provided pan head screw in the following order: flat washer (provided with circular backshell), first ring terminal, second ring terminal, third ring terminal (if needed) before finally inserting the screw into the grounding hole on the circular backshell and securing with the provided locking nut.

  • Page 172: B-21 Daisy Chain Shield Termination Between Methods A And B

    B.4.6 Daisy Chain Shield Termination Between Methods A and B In rare situations where more braids need to be terminated for a connector than three per ring terminal and a mixture of Methods A and B have been used, it is allowable to daisy chain a maximum of two shields together from a Method A termination to a Method B (Figure B-21).

  • Page 173: Appendix C Outline And Installation Drawings

    APPENDIX C OUTLINE AND INSTALLATION DRAWINGS 2X 1.72 43.7 .004 3.89 98.7 7.83 198.8 2.98 75.8 6.04 153.4 NOTES: DIMENSIONS: INCHES[MM] DIMENSIONS ARE SHOWN FOR REFERENCE ONLY. G3X Installation Manual – Outline & Installation Drawings 190-01115-01 FRONT SURFACE OF PANEL #6-32 CAPTIVE 3.41 SCREW (4 PLCS)

  • Page 174: C-1.2 Gdu 37X Panel Cutout Drawing

    APPENDIX C OUTLINE & INSTALLATION DRAWINGS G3X Installation Manual – Outline & Installation Drawings 190-01115-01 Drawing is not to scale! Use for dimensions only. TYP. 3.67 3.67 93.1 93.1 3.58 3.58 91.1 91.1 CONNECTOR KIT 011-01921-00 3.58 3.58 91.1 91.1 3.67 3.67 93.1...

  • Page 175: C-2.1 Gmu 44 Mounting Rack

    APPENDIX C OUTLINE AND INSTALLATION DRAWINGS GMU 44 MOUNTING RACK 3.370 85.60 NOTE: DIMENSIONS IN INCHES [mm] SEE SECTIONS 3 AND 4 FOR MOUNTING INSTRUCTIONS OF THE GSU 73 AHRS AND GMU 44 MAGNETOMETER UNIT. FOLLOW "FORWARD" AND "TOP" INDICATIONS ON UNIT AND RACK. G3X Installation Manual –...
  • Page 176 APPENDIX C OUTLINE AND INSTALLATION DRAWINGS 8.4 214 3.37 85.60 .3 8 AIRCRAFT MOUNTING SURFACE 2.38 60.33 G3X Installation Manual – Outline & Installation Drawings 190-01115-01 GMU 44 INSTALLATION FROM ABOVE (PREFERRED) GMU 44 AIRCRAFT MOUNTING RACK 2.10 53.34 1.84 46.61 6-32 PAN HEAD BRASS SCREWS 0.24 [6.1] MAX THREAD LENGTH...

  • Page 177: C-2.3 Gmu 44 Bottom Mounted Installation

    APPENDIX C OUTLINE AND INSTALLATION DRAWINGS 8.4 214 3.370 85.60 .3 8 2.38 60.33 G3X Installation Manual – Outline & Installation Drawings 190-01115-01 GMU 44 INSTALLATION FROM BELOW (NOT PREFERRED) AIRCRAFT MOUNTING RACK AIRCRAFT MOUNTING SURFACE GMU 44 6-32 PAN HEAD BRASS SCREWS 0.24 [6.1] MAX THREAD LENGTH WITHOUT CLEARANCE HOLES...

  • Page 178: C-2.4 Gmu 44 Wiring Detail

    APPENDIX C OUTLINE AND INSTALLATION DRAWINGS G3X Installation Manual – Outline & Installation Drawings 190-01115-01 NOTE: 1. BUBBLE NUMBERS IN THIS DRAWING REFER TO REFERENCE NUMBERS LISTED IN TABLES 3-6 AND 3-7. Figure C-2.4 GMU 44 Wiring Detail Page C-11 (Page C-12 blank) Revision A...

  • Page 179: C-3.1 Gsu 73 Outline Drawing

    APPENDIX C OUTLINE AND INSTALLATION DRAWINGS 5.00 .25 6.4 .65 16.6 4.25 108.0 4.46 113.2 PITOT AIR FITTING 1/8-27 ANPT FEMALE THREAD 1.96 49.8 STATIC AIR FITTING 1/8-27 ANPT FEMALE THREAD 22.1 1.17 29.7 5.50 139.7 NOTES: DIMENSIONS: INCHES[mm]. DIMENSIONS ARE SHOWN FOR REFERENCE ONLY. MOUNTING HOLES FOR #10 PAN HEAD OR HEX HEAD FASTENERS.

  • Page 180: C-4.1 Gtp 59 O.a.t. Probe Installation Drawing

    APPENDIX C OUTLINE AND INSTALLATION DRAWINGS .03 x 45 .02 x 45 CHAMFER CHAMFER .255 NOTES: 1. DIMENSIONS: INCHES 2. MAX HEIGHT OF INCOMPLETE THREAD: 0.050 3. CABLE: M27500-22TE3V14. CABLE LENGTH TO BE 10 FEET 6 INCHES 4. 16 AWG WIRE: M22759/16-16. LENGTH OF WIRE OUTSIDE OF CASE TO BE 3.5 INCHES +0.25, -0. 5.

  • Page 181: C-5.1 Ga 55/55A Installation Drawing

    APPENDIX C OUTLINE AND INSTALLATION DRAWINGS GA 55 STUD MOUNT 011-00134-00 ANTENNA, AVIATION, GA 55 FORWARD 4.23 107.4 1.91 48.5 .22 5.6 .50 12.7 4X #8-32 STUD SIDE VIEW 3.00 76.2 BACKING PLATE OUTLINE G3X Installation Manual – Outline & Installation Drawings 190-01115-01 253-00002-00 GASKET, NEOPRENE...

  • Page 182: C-5.2 Ga 56 Installation Drawing

    APPENDIX C OUTLINE AND INSTALLATION DRAWINGS G3X Installation Manual – Outline & Installation Drawings 190-01115-01 GA 56 STUD MOUNT 011-00134-00 ANTENNA, AVIATION, GA 56 253-00002-00 GASKET, NEOPRENE AIRCRAFT SKIN ON TOP OF FUSELAGE 115-00031-00 BACKING PLATE 4X 210-10004-09 #8-32 SELF LOCKING NUT FORWARD 4.23 107.4 2.59 65.8...
  • Page 183 APPENDIX C OUTLINE & INSTALLATION DRAWINGS 2.90 73.7 .80 20.2 .49 12.3 .60 15.2 GPS BNC CONNECTOR .70 17.8 2X 0 1.000 25.40 2.350 59.69 2X 3.300 83.82 MOUNTING CUTOUT NOTES: 1. DIMENSIONS: INCHES[mm] G3X Installation Manual – Outline & Installation Drawings 190-01115-01 FORWARD 4.70 119.4...

  • Page 184: Appendix D Interconnect Drawing

    APPENDIX D INTERCONNECT DRAWING Figure D-1.1 Notes, 14V Power, and Antennas G3X Installation Manual – Interconnect Drawings Page D-1 (Page D-2 blank) 190-01115-01 Revision A...
  • Page 185 APPENDIX D INTERCONNECT DRAWING Figure D-1.2 GDU 37X and GSU 73 G3X Installation Manual – Interconnect Drawings Page D-3 (Page D-4 blank) 190-01115-01 Revision A...

  • Page 186: Appendix E: External Interface Drawing (Example Only

    APPENDIX E EXTERNAL INTERFACE DRAWING (EXAMPLE ONLY) Figure E-1.1 Notes, GDU 37X RS-232 and Audio Examples G3X Installation Manual – External Interface Drawings Page E-1 (Page E-2 blank) 190-01115-01 Revision A...

  • Page 187: E-1.2 Gsu 73 Rs-232 And Arinc 429 Examples

    APPENDIX E EXTERNAL INTERFACE DRAWING (EXAMPLE ONLY) Figure E-1.2 GSU 73 RS-232 and ARINC 429 Examples G3X Installation Manual – External Interface Drawings Page E-3 (Page E-4 blank) 190-01115-01 Revision A...
  • Page 188 APPENDIX E EXTERNAL INTERFACE DRAWING (EXAMPLE ONLY) Figure E-1.3 Tru Trak and Trio Auto Pilot Examples G3X Installation Manual – External Interface Drawings Page E-5 (Page E-6 blank) 190-01115-01 Revision A...

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Gdu 375Gmu 44Gsu 73Gtp 59G3xGdu 37x

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