GPS Receiver Installation Manual

ManualsBrandsGarmin ManualsGPSGTP 59

190-01115-01 August, 2009 Revision A

G3X

Installation Manual

Summary of content (188 pages)

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G3X Installation Manual 190-01115-01 August, 2009 Revision A
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© Copyright 2009 Garmin Ltd. or its subsidiaries All Rights Reserved Except as expressly provided herein, no part of this manual may be reproduced, copied, transmitted, disseminated, downloaded or stored in any storage medium, for any purpose without the express prior written consent of Garmin.
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WARNING This product, its packaging, and its components contain chemicals known to the State of California to cause cancer, birth defects, or reproductive harm. This Notice is being provided in accordance with California's Proposition 65. If you have any questions or would like additional information, please refer to our web site at www.garmin.com/prop65.
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TABLE OF CONTENTS PARAGRAPH PAGE 1 1.1 1.2 1.3 1.4 1.5 1.6 1.7 G3X Installation Overview ..............................................................................................................1-1 Unpacking Unit ................................................................................................................................1-1 Introduction ......................................................................................................................................
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PARAGRAPH PAGE 5 5.1 5.2 5.3 5.4 5.5 5.6 GTP 59 .............................................................................................................................................5-1 Equipment Description.....................................................................................................................5-1 Installation Requirements.................................................................................................................5-1 TSO/ETSO Compliance.............
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PARAGRAPH PAGE APPENDIX A: G3X Pinouts ................................................................................................................... A-1 A.1 GDU 37X ........................................................................................................................................ A-1 A.2 GMU 44 .......................................................................................................................................... A-5 A.3 GSU 73..................................
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LIST OF ILLUSTRATIONS FIGURE PAGE 1-1 1-2 G3X Interconnect Example..............................................................................................................1-2 Coaxial Cable Installation ................................................................................................................1-7 2-1 2-2 GDU 37X Unit View .......................................................................................................................2-1 GDU 37X Mounting Accessories ......
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FIGURE PAGE 6-26 6-27 6-28 6-29 6-30 6-31 Example Bracket Antenna Mounting Under Glareshield...............................................................6-24 Example Non-structural Antenna Mounting Under Glareshield....................................................6-25 Example Teardrop Antenna Installation in Airframe Under Fabric Skin ......................................6-26 Example ARINC 743 Footprint in Airframe Under Fabric Skin ...................................................
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FIGURE PAGE B-17 B-18 B-19 B-20 B-21 Insulation/Contact Clearance....................................................................................................... B-23 Daisy Chain Shield Termination ................................................................................................. B-24 Quick Term Shield Termination.................................................................................................. B-25 Daisy Chain, Quick-Term Shield Termination..........................
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LIST OF TABLES TABLE PAGE 1-1 1-2 1-3 1-4 1-5 1-6 1-7 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................................
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TABLE PAGE 6-4 6-5 6-6 6-7 XM Satellite Radio Antenna Minimum Requirements ....................................................................6-2 Teardrop Footprint Antenna Doubler Design and Installation.........................................................6-7 ARINC 743 Footprint Antenna Doubler Design and Installation ..................................................6-14 Minimum Distance Required Between Tube Structure and Antenna ............................................
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Limited Warranty for Garmin GMU 44 and GTP 59 Products The Garmin products GMU 44 and GTP 59 are warranted to be free from defects in materials or workmanship for two years from the date of purchase. Within this period, Garmin will at its sole option, repair or replace any components that fail in normal use. Such repairs or replacement will be made at no charge to the customer for parts or labor, provided that the customer shall be responsible for any transportation cost.
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Limited Warranty for GSU 73 and GDU 37X Products The Garmin products GSU 73 and GDU 37X are warranted to be free from defects in materials or workmanship for one year from the date of purchase. Within this period, Garmin will at its sole option, repair or replace any components that fail in normal use. Such repairs or replacement will be made at no charge to the customer for parts or labor, provided that the customer shall be responsible for any transportation cost.
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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.
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1 1.1 G3X Installation Overview Unpacking Unit Carefully unpack the equipment and make a visual inspection of the unit for evidence of damage incurred during shipment. If any component of the G3X system is damaged, notify the carrier and file a claim. To justify a claim, save the original shipping container and all packing materials. Do not return the unit to Garmin until the carrier has authorized the claim. Retain the original shipping containers for storage.
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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).
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1.4 General G3X LRU Specifications 1.4.1 Garmin LRU Part Numbers Table 1-1. G3X LRU Part Numbers LRU Unit Only Part Number Assembly Part Number GDU 370 Americas DB 011-01747-15 010-00667-15 GDU 370 Atlantic DB 011-01747-20 010-00667-20 GDU 370 Pacific DB 011-01747-35 010-00667-35 GDU 375 Americas DB 011-01747-30 010-00667-25 GMU 44 011-00870-10 010-00296-10* GSU 73 011-01817-00 010-00691-00* GTP 59 011-00978-00* NA *Included in G3X LRU Kit (K10-00016-00) Table 1-2.
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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 LRU Width Height Depth (GMU 44 Diameter, including flange*) GDU 370 GDU 375 6.04 inches (153.4 mm) 6.04 inches (153.4 mm) GMU 44 N/A GSU 73 5.50 inches (139.8 mm) 7.83 inches (198.8 mm) 7.83 inches (198.8 mm) 2.10 inches (5.33 cm) 3.96 inches (100.6 mm) 3.41 inches (86.7 mm) 3.41 inches (86.7 mm) *3.35 inches (85.1 mm) 7.
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1.5 Installation Requirements One GDU 37X assembly (listed in Table 1-1) is required, dependent upon customer’s desired database region. Each GDU 37X (010-00667-XX) comes with all equipment needed for installation. 1.5.1 Required Accessories The following kits are required for the installation of the G3X. Table 1-5.
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1.7.1 Wiring Harness Installation Allow adequate space for installation of cables and connectors. Ensure that routing of the wiring does not come in contact with sources of heat, RF or EMI interference. Analog Input wires routed too close to spark plugs, plug wires, or magnetos may result in erratic readings. The installer shall supply and fabricate all of the cables. Required connectors, etc. are provided with the G3X Installation Kit (K10-00017-00).
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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. • Check that there is ample space for the cabling and mating connectors. • Avoid sharp bends in cabling. • Avoid routing near aircraft control cables.
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1.7.4 Backshell Assemblies 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.
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2 GDU 37X Figure 2-1. GDU 37X Unit View 2.1 Equipment Description NOTE There is no TSO/ETSO applicable to the GDU G37X. The GDU 37X provides a central display and user interface for the G3X system. The display is mounted flush to the aircraft instrument panel using four #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. 2.1.
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2.1.2 Interface Summary The GDU 37X uses CAN and RS-232 communications interfaces. The GDU 37X communicates with the following Garmin LRUs: • Other GDU 37X • GSU 73 • SL30 Nav/Comm Transceiver • SL40 Comm Transceiver • GNS 400/500 Series Units • GTX 327/330 Transponder 2.2 Electrical Specifications 2.2.1 Electrical Characteristics Characteristics Power Requirements Table 2-1. GDU 37X Supply Voltages Specifications 14/28 VDC 2.2.2 Power Consumption LRU GDU 370 GDU 375 Table 2-2.
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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. NOTE Only a single GPS antenna is required for installations using more than one GDU 37X unit, as the GDU 37X will “share” the GPS information with all GDU 37X units. Table 2-4.
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2.4 Installation Requirements 2.4.1 Accessories The GDU 37X Connector Kit is provided with the GDU 37X unit and is required to install the unit (Figure 2-2). The GDU 37X Nutplate (115-01054-00) is also supplied with the unit to reinforce the panel cutout in thin panel installations. The contents of the GDU 37X Connector Kit are listed in Table 2-5. One kit is required for each GDU 37X installed. Table 2-5.
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2.5 Installation Considerations Fabrication of a wiring harness is required. Sound mechanical and electrical methods and practices are recommended for installation of the 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.
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2.9 Panel Cutout Template The below drawing can be used as a template when marking the panel for cutout. Dimensions below are to verify accuracy of printout only, see Figure C-1.2 for complete dimensions. GDU 37X PANEL CUTOUT TEMPLATE IMPORTANT! Ensure the Page Scaling setting is set to NONE when printing this page. Verify dimensions of printed template are accurate before cutting panel. Cut out panel to inside line 7.33 in [186.2 mm] 5.57 in [141.
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3. GMU 44 Figure 3-1. GMU 44 Unit View 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. The Garmin ADAHRS and magnetometer replace traditional rotating mass instruments.
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3.3 Environmental Specifications Table 3-2 lists general environmental specifications. Table 3-2. GMU 44 Environmental Specifications Specification Characteristic Regulatory Compliance RTCA/DO-160D Environmental Conditions and EUROCAE/ED-14D Unit Software RTCA/DO-178B Level B Operating Temperature Range -55° C to +70° C Altitude 3.4 55,000 Feet GMU 44 TSO/ETSO Compliance Table 3-3.
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3.5 Installation Requirements 3.5.1 Equipment Available Table 3-5. GMU 44 Part Numbers Model Catalog Part Number GMU 44 010-00296-10* *Included in G3X LRU Kit (K10-00016-00) Unit Part Number Installation Rack 011-00870-10 No Table 3-6.
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Table 3-7. Required Distance from Magnetic Disturbances Disturbance Source Minimum Distance from GMU 44 Electric motors and relays, including servo motors 10 feet (3.0 meters) Ferromagnetic structure greater than 1 kg total (iron, steel, or cobalt materials, especially landing gear structure) 8.2 feet (2.5 meters) Ferromagnetic materials less than 1 kg total, such as control cables 3 feet (1.0 meter) Any electrical device drawing more than 100 mA current 3 feet (1.
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3.6.1 Consideration for Wing Grounded Lighting Fixtures The following installation practices are recommended if the required GMU 44 mounting bracket is located in the wing. 1. The wing tip lights should not have a power ground referenced to the chassis of the light assembly that would then be referenced back to the airframe ground via the light assembly mounting. 2. A dedicated power ground should be used and returned as a twisted pair with the power source back into the fuselage for a wing mounted GMU 44.
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3.8 Mounting Instructions After evaluation of the mounting location has been completed and ensuring that requirements are met, assemble the GMU 44 mounting plate kits according to the dimensions given in Appendix C. Install the unit assemblies. Mount the GMU 44 to its mounting plate, taking care to tighten the mounting screws firmly. Use of nonmagnetic tools (e.g. beryllium copper or titanium) is recommended when installing or servicing the GMU 44.
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4 4.1 GSU 73 Equipment Description NOTE 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. The GSU 73 is intended to be used as a part of the G3X system and it is not suitable for installation in type-certificated aircraft.
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4.1.
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4.3 Environmental Specifications The GSU 73 is a non-TSO’d product, Table 4-2 lists general environmental specifications. NOTE The GSU 73 may require a warm-up period of 15 minutes to reach full accuracy (30 minutes if the environmental temperature is less than 0°C). Table 4-2.
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Table 4-5. Contents of P732 Connector Kit (011-01818-01)** Item Garmin P/N Quantity Sub-Assy,Backshell w/Hdw,Jackscrew 011-01855-04 1 Connector ,Hi Dens, D-Sub, Mil Crimp 78ck 330-00185-78 1 Contact Pin, Mil Crimp, Size 22D 336-00021-00 30 **Included in G3X Installation Kit (K10-00017-00) 4.4.2 Additional Equipment Required 4.5 • • Cables: The installer will fabricate and supply all system cables. Hardware: #10-32 pan or hex head screw (4 ea.
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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. J732 J731 Figure 4-2. GSU 73 Air Hose Fitting Locations Use appropriate air hoses and fittings to connect the pitot and static lines to the unit. Avoid sharp bends and routing near aircraft control cables.
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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. GSU 73 Orientation Calibration The GSU 73 includes an extremely sensitive strap-down inertial measurement unit. It must be mounted rigidly to the aircraft primary structure, preferably to a metallic structure to conduct heat away from the unit.
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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. Avoid areas that are prone to severe vibration.
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4.8 Maintenance Per Part 43 Appendix E, paragraph (b)(2), Garmin specifies a test procedure equivalent to part 43 Appendix E, paragraph (b)(1) with two exceptions. The tests of sub-paragraph (iv)(Friction) and (vi) (Barometric Scale Error) are not applicable because the digital outputs of the GSU 73 are not susceptible to these types of errors.
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5 GTP 59 Figure 5-1. 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). 5.1.1 Available Equipment The GTP 59 is available per the following part number. Table 5-1.
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5.2.1 Additional Equipment Required • 5.3 Cables - The installer will supply all system cables. TSO/ETSO Compliance The following table provides a list of applicable TSO/ETSOs for the GTP 59. Table 5-3. Applicable TSO/ETSOs for the GTP 59 Function TSO/ETSO Applicable LRU SW Part Numbers Applicable CLD Part Numbers Air Data Computer TSO-C106 ETSO-C106 Not Applicable Not Applicable 5.3.1 TSO/ETSO Deviations The following deviations have been requested and granted for the GTP 59. Table 5-4.
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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. true airspeed and delta-ISA). 5.4.2 GTP 59 OAT Probe Installation NOTE The following instructions are general guidance.
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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). 7. Attach the ring terminal (9) to the backshell, using the screw provided in the OAT Probe Kit (10) and one of the tapped holes on the backshell termination area. 8.
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6 Garmin GPS/XM Antennas For non-Garmin antennas, follow the manufacturer’s installation instructions. If using a Garmin GA 26C or GA 26XM, refer to the accompanying installation instructions (190-00082-00 or 190-00522-03). For 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.
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Table 6-4. XM Satellite Radio Antenna Minimum Requirements Characteristics Frequency Range Gain (Typical) Noise Figure Nominal Output Impedance Supply Voltage Supply Current (maximum) Operating Temperature Gain Specifications 2332.5 to 2345 MHz 24 dB* <1.2 dB 50 ohms 3.6 to 5.5 VDC 55 mA -50 to +85°C *For each 1 dB gain over 24 dB, add 1 dB of attenuation into the antenna cable path between the antenna and the GDU 375.
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6.3.2 GPS/XM Antenna Mounting Location The GPS antenna is a key element in the overall system performance and integrity for a GPS navigation system. The mounting location, geometry, and surroundings of the antenna can affect the system performance and/or availability. The following guidance provides information to aid the installer in ensuring that the optimum location is selected for the installation of the GPS antenna. The installation guidelines presented here meet the intent of AC 20-138A section 16.
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Figure 6-1 shows the recommended placement of antennas. 4 Figure 6-1.
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6.3.3 Buried Antenna (below the skin covering or glareshield) Mounting There are potential performance issues related to buried antennas that the kit builder/installer should be aware of prior to electing to install a buried antenna. See also Section 6.6.3, Non-structural Installation to Glareshield. • • • Some gain of the antenna may be lost as the signal needs to penetrate through the skin of the aircraft.
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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.
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6.4 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.
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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. Dimple aircraft skin when the skin thickness is less than 0.051” for installation of flush head rivets.
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6.4.3 Reference Figures Figure 6-4. Doubler Design, Teardrop Footprint Antenna, Skin Thickness 0.032" to 0.049" Figure 6-5. Doubler Design, Teardrop Footprint Antenna, Skin Thickness 0.049" to 0.
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Figure 6-6. Doubler Design, Teardrop Footprint Antenna, Skin Thickness 0.051" to 0.063" Figure 6-7.
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Figure 6-8. Skin Cutout Detail, Teardrop Footprint Antenna, Skin Thickness 0.032" to 0.049" Figure 6-9. Skin Cutout Detail, Teardrop Footprint Antenna, Skin Thickness 0.049" to 0.
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Figure 6-10. Skin Cutout Detail, Teardrop Footprint Antenna, Skin Thickness 0.051" to 0.063" Figure 6-11. Doubler Installation, Teardrop Footprint Antenna, Skin Thickness 0.032" to 0.
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Figure 6-12. Doubler Installation, Teardrop Footprint Antenna, Skin Thickness 0.049" to 0.051" Figure 6-13. Doubler Installation, Teardrop Footprint Antenna, Skin Thickness 0.051" to 0.
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6.5 ARINC 743 Footprint Antenna Installation (GA 55A, GA 57X) This section describes the structural mounting of the ARINC 743 footprint antenna (GA 55A, GA 57X) installation. One acceptable method is to use Garmin P/N: 115-00846-00 doubler plate. Another acceptable method is to fabricate and install one of three doublers, Figure 6-14, Figure 6-15, or Figure 616, depending on the thickness of the skin.
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6.5.2 Antenna Installation Instructions 1. Refer to Table 6-6 (and to Figures 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 6.5.1 for doubler preparation and Table 6-6 for additional guidance on the doubler installation. Dimple aircraft skin when the skin thickness is less than 0.051” for installation of flush head rivets.
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6.5.3 Reference Figures Figure 6-14. Doubler Design, ARINC 743 Footprint Antenna, Skin Thickness 0.032" to 0.
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Figure 6-15. Doubler Design, ARINC 743 Footprint Antenna, Skin Thickness 0.049" to 0.
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Figure 6-16. Doubler Design, ARINC 743 Footprint Antenna, Skin Thickness 0.051" to 0.
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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.
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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.
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Figure 6-21. Doubler Installation, ARINC 743 Footprint Antenna, Skin Thickness 0.032" to 0.049" Figure 6-22. Doubler Installation, ARINC 743 Footprint Antenna, Skin Thickness 0.049" to 0.
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Figure 6-23. Doubler Installation, ARINC 743 Footprint, Skin Thickness 0.051" to 0.063" Figure 6-24.
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6.6 Non-Structural Mount Installation This section provides installation examples and considerations for non-structural mounting of teardrop and ARINC 743 footprint antennas. Typical installations may be below a non-metallic glareshield, under the composite or fabric skin, or on an external, non-structural surface. Other non-structural installations may exist, but are not presented in this manual. 6.6.
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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.
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Figure 6-27.
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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. The doubler plate and mounting hardware described in the generic installation (Section 6.6.1) are used with the bracket as the antenna mounting surface.
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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. The generic installation of the (Section 6.6.
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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 (d) and minimum distance (l) references in the table. Figure 6-31.
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7 7.1 Software, Configuration, Databases, and XM Activation 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. 7.2 Software/Audio Data Identification 7.2.1 LRU Software Version Identification Do the following steps to verify the unit’s current software version(s): 1.
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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. Press the ENT key to display the Database Information page. 5. Use the FMS Joystick to scroll down as needed to display the audio database information.
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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. NOTE It is also acceptable to insert the SD card before powering on the unit. 2. A software update pop-up will appear on the screen, highlight YES and press the ENT key to begin the update.
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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 userselectable options. 1. In configuration mode, use the FMS Joystick to select and view the MAIN Page.
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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. Aircraft Identifier–The aircraft identifier can be entered using the FMS Joystick.
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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).
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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. 1. In configuration mode, use the FMS Joystick to select the UNITS Page. 2.
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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. Press the FMS Joystick to move the cursor to the page selection menu when finished.
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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’ setting. Default Mode: Can be set to Auto or Manual (described above).
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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. Press the FMS Joystick to move the cursor to the page selection menu when finished.
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7.4.7 COMM Configuration Page The COMM Configuration Page allows setting the parameters for the communication ports. 1. In configuration mode, use the FMS Joystick to select the COMM 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. Press the FMS Joystick to move the cursor to the page selection menu when finished.
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7.5 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.
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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. Repeat steps 1-7 for each installed GDU 37X. 7.5.2 Available Databases Jeppesen® Aviation Data (NavData™) The Jeppesen database contains the general aviation data (NavData) used by pilots (Airports, VORs, NDBs, SUAs, etc.) and is updated on a 28-day cycle.
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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. This database is updated on a 56-day cycle, and has no expiration date.
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8. Post-Installation Checkout and Calibration Procedures The checkout procedures in this section are recommended to be performed after installing the G3X. The calibration procedures are required to be performed after installing the G3X. It is assumed that the person performing these checks is familiar with the aircraft, has a working knowledge of typical avionics systems, and has experience using the test equipment defined in this section.
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8.1 Recommended Test Equipment The following test equipment is recommended to conduct and complete all post installation checkout procedures in this section: (All test equipment should have current calibration records) • • • • • 8.
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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.
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8.3 GSU 73/GMU 44 Post-Installation Calibration Procedures After mechanical and electrical installation of the GSU 73 AHRS and GMU 44 magnetometer have been completed, prior to operation, a set of post-installation calibration procedures must be carried out. Table 8-1 describes the necessary calibration procedures: Table 8-1.
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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 Valid Status Required GPS or Air Data GPS or Magnetometer GPS or Air Data. Magnetometer always required. GPS or Air Data GPS or Air Data. Magnetometer always required.
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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. 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.
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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.
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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. 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).
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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.
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8.3.3 Calibration Procedure C: Magnetometer Calibration NOTE Calibration Procedure B must be successfully completed prior to Calibration Procedure C. NOTE 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. The accuracy of the AHRS cannot be guaranteed if this calibration is not performed at a magnetically clean location.
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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. 5. On the GSU Status Page, use the FMS Joystick to select MAGNETOMER. 6. Use the FMS Joystick to highlight the Calibrate button, press the ENT Key.
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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. Upon instruction to turn, taxi the aircraft in a right turn. After approximately 30° of turn from the last heading the PFD instructs the operator to stop the aircraft.
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11. The PFD guides the operator to dwell at multiple headings around a complete circle. NOTE 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. If this is encountered more than once for a given station, the operator should begin turning to the next station (approximately 30°).
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8.3.4 Calibration Procedure D: Heading Offset Compensation NOTE 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. This procedure is required only when the GMU 44 Magnetometer has not been installed facing forward and parallel to within 0.5º of the aircraft longitudinal axis.
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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. 9. The PFD display advises the operator when to turn the aircraft to a cardinal heading, when to stop, and when to turn to another heading.
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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.
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8.3.5 Calibration Procedure E: Engine Run-Up Vibration Test NOTE 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). 2. Use the FMS Joystick to select the GSU Page (if needed). 3. Unlock the GSU Page by pressing softkeys 2, 3, 4 in order (if needed). 4.
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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. NOTE If failures are indicated, the engine run-up test may be repeated up to three times.
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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. NOTE 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.
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8.3.6 Calibration Procedure F: Magnetometer Interference Test NOTE Calibration Procedure F is required for initial installation verification. This test should also be repeated to verify all subsequent electrical changes associated with devices within 10.0 feet of the GMU 44 magnetometer. Such changes include, but are not limited to, wiring, shielding or grounding changes to any light, strobe, beacon or other electrical device located in the same wing as a GMU 44 unit.
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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.
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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. NOTE 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. 10.
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Table 8-4.
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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. NOTE Typically, a compass rose is an acceptable location to perform the magnetometer calibration procedure.
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NOTE 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.
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9 Troubleshooting In this section the term ‘Red-X’ refers to a red “X” that appears on different areas of the display to indicate the failure of that particular function. Refer to the G3X Pilot’s Guide (190-01054-00) for a complete listing of System Status Messages. For additional assistance, contact your G3X Dealer, then for further help (if needed), contact Garmin Aviation Product Support at US Toll Free Number 1-888-606-5482, or US 1-913-397-8200.
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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).
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9.3 GSU 73 GSU 73 ground operation is heavily dependent on GPS data inputs. Be sure to correct any GPS performance problems (i.e. interference caused by some types of cell phones or anything that transmits in the area) before troubleshooting the GSU 73/GMU 44. For GPS data to be considered usable, the receiver must be tracking at least 4 satellites and have a 3D GPS Solution.
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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.
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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 190-01115-01 Page 9-5 Revision A
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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. If this is the case, then the external installation configuration parameters will not be considered calibrated.
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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 Density Altitude Pressure Altitude Static Pressure Differential Pressure If the TAS and/or OAT indications are dashed out as shown in Figure 9-5: 1. Check the GTP 59 OAT probe wiring and connection for faults. 2.
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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. 1. Does cycling power restore operation? 2. Did the operator give it sufficient time to start and initialize? 3.
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Figure 9-7 – Attitude, Heading, Air Data, and Engine/Airframe Failure (Reversionary or Split-Screen PFD) G3X Installation Manual - Troubleshooting 190-01115-01 Page 9-9 Revision A
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9.5 Troubleshooting On-board the Aircraft 1. Review the airframe logbook to verify if any G3X or other avionics or electrical maintenance had been performed recently that may have contributed to the failure. 2. Check for loose wire terminals on the circuit breaker connections on the power wire(s) causing intermittent power connections. Also, check for intermittent circuit breakers. 3. Have ground power put on the aircraft. 4. Turn on the G3X and record the system software level on the GDU start up page. 5.
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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.
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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. Continue to Section 10.2. 10.1.
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10.2.2 New GSU 73 Installed If a new GSU 73 is installed (new serial number), verify the correct software version on the MAIN page in configuration mode. If the correct software version is not installed, load the GSU 73 software contained in the G3X system software loaded to the displays. If the configuration module is operational, no software configuration is required. Continue to Section 10.3. 10.3 GMU 44 NOTE If the GMU 44 is removed, the anti-rotation properties of the mounting screws must be restored.
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APPENDIX A G3X Pinouts A.1 GDU 37X A.1.1 P3701 Connector PIN 17 PIN 1 PIN 18 PIN 34 PIN 33 PIN 50 Figure A-1.
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Connector P3701, continued Pin Pin Name 33 CONFIG MODULE CLOCK 34 SIGNAL GROUND 35 SIGNAL GROUND 36 SIGNAL GROUND 37 SIGNAL GROUND 38 SPARE 39 SPARE 40 SPARE 41 SPARE 42 CDU SYSTEM ID PROGRAM* 4 43 14V LIGHTING BUS HI 44 SIGNAL GROUND 45 CAN BUS LO 46 CAN BUS HI 47 RS-232 IN 1 48 RS-232 OUT 1 49 CONFIG MODULE GROUND 50 CONFIG MODULE DATA * Indicates Active Low A.1.
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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 Connector Pin I/O RS-232 IN 1 P3701 47 In RS-232 OUT 1 P3701 48 Out RS-232 IN 2 P3701 14 In RS-232 OUT 2 P3701 30 Out RS-232 IN 3 P3701 29 In RS-232 OUT 3 P3701 13 Out A.1.4.2 CAN Bus This data bus conforms to the BOSCH standard for Controller Area Network 2.0-B. This bus complies with ISO 11898.
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A.1.6 Audio A.1.6.1 Mono Audio Pin Name MONO AUDIO OUT HI MONO AUDIO OUT LO Connector P3701 P3701 Pin 1 18 I/O Out -- A.1.6.2 Stereo Audio Pin Name Connector Pin I/O STEREO AUDIO OUT LEFT P3701 3 Out STEREO AUDIO OUT LO P3701 20 -STEREO AUDIO OUT RIGHT P3701 19 Out STEREO AUDIO OUT LO P3701 2 -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.
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A.2 GMU 44 A.2.1 P441 Connector Figure A-2. View of J441 Connector Looking at Rear of Unit Pin 1 2 3 4 5 6 7 8 9 A.2.2 Pin Name SIGNAL GROUND RS-485 OUT B SIGNAL GROUND RS-485 OUT A SPARE POWER GROUND SPARE RS-232 IN +12 VDC POWER I/O -Out -Out ---In In Power Function Power-input pins accept 14/28 VDC. AIRCRAFT POWER 2 is for connecting to an alternate power source, such as on aircraft with two electrical buses.
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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. J732 J731 Figure A-3 Rear View of Connector End Plate A.3.2 Pin List A.3.2.1 P731 Connector Figure A-4 Rear Connector J731 Viewed from Connector End of Unit J731 pins are configured as shown in preceding figure.
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Connector P731, continued Pin 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 60 61 62 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 CAN BUS TERMINATION ARINC 429 IN 3 A ARINC 429 IN 3 B ARINC 429 IN 4 A ARINC 429 IN 4 B SIGNAL GROUND SIGNAL GROUND SIGNAL GROU
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A.3.2.
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Connector P732, continued Pin Pin Name 40 ANALOG IN 4 LO 41 ANALOG IN 1 LO 42 ANALOG IN 10 LO 43 ANALOG IN 7 LO 44 ANALOG IN 15 LO 45 ANALOG IN 16 LO 46 ANALOG IN 25 LO 47 ANALOG IN 22 HI 48 ANALOG/CURRENT MONITOR IN 2 HI 49 ANALOG IN 21 LO 50 ANALOG/CURRENT MONITOR IN 1 LO 51 ANALOG IN 18 LO 52 ANALOG IN 13 LO 53 ANALOG IN 5 LO 54 SPARE 55 +12 VDC TRANSDUCER POWER OUT 56 TRANSDUCER POWER OUT LO (GROUND) 57 TRANSDUCER POWER OUT LO (GROUND) 58 +10 VDC TRANSDUCER POWER OUT 59 CONFIG MODULE POWER OUT 60 ANALOG
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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. Pin 47 49 59 61 Connector P731 P731 P731 P731 Pin Name AIRCRAFT POWER 1 AIRCRAFT POWER 2 POWER GROUND POWER GROUND I/O IN IN --- A.3.3.2 Transducer Output Power The GSU 73 supplies output power for engine/airframe sensors that may require supply voltage excitation. The GSU 73 outputs voltage levels of +5, +10, and +12 Vdc.
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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.
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A.3.5.3 RS-485 Input The GSU 73 contains one channel of RS-485 serial data communications. Pin 1 2 Connector P731 P731 Pin Name MAGNETOMETER RS-485 IN B MAGNETOMETER RS-485 IN A I/O IN IN 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.
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A.3.6.2 Discrete Outputs INACTIVE: Floating (can be pulled up to externally sourced Vout in the range 0 ≤ Vout ≤ 33VDC) Leakage current in the INACTIVE state is typically ≤ 10 uA to ground ACTIVE: Vout ≤ 0.5VDC with ≤ 20 mA sink current Sink current must be externally limited to 20 mA max Pin Connector 13 P731 14 P731 * Indicates Active Low A.3.
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NOTE 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.
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Pin 47 67 28 8 27 7 66 46 70 50 48 68 10 9 A.3.
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The following table lists the minimum frequency, maximum frequency, and duty cycles for each of these inputs. Pin Name Minimum Frequency Maximum Frequency Duty Cycle FREQUENCY COUNTER IN* 1 1 Hz 500 Hz/100 KHz* 50% FREQUENCY COUNTER IN* 2 1 Hz 500 Hz/100 KHz* 50% FREQUENCY COUNTER IN* 3 1 Hz 500 Hz/100 KHz* 50% FREQUENCY COUNTER IN* 4 1 Hz 500 Hz/100 KHz* 50% *Each frequency counter channel will be configured for a high or low speed input based on the signal being measured. A.3.
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APPENDIX B Connector Installation Instructions B.1 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). Figure Ref 1 2 3 Table B-1. Thermocouple Kit GPN 011-00981-00 Description Qty.
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Figure B-2.
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B.2 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). Configuration modules are to be installed in the backshells of the P732 connector for the GSU 73, and the P3701 connector for the GDU 37X designated as PFD1. Table B-2.
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NOTES 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. Wire must be visible in the inspection hole after crimping and the insulation must be 1/64 – 1/32 inches from the end of the contact as shown in Figure B-3.
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Figure B-4.
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B.3 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. Table B-4.
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NOTE In Figure B-5, “AR” denotes quantity “As Required” for the particular installation. Figure B-5.
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B.3.2 Shield Termination Technique – Method A.1 (Standard) NOTE 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 Backshell Size 1 2 3 4 5 Number of Pins Std/HD 9/15 15/26 25/44 37/62 50/78 Float Min (inches) 1.25 1.5 1.5 1.5 1.
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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). Make this connection using an approved shield termination technique. NOTE FAA AC 43.
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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. Slide a minimum 0.75 inches of Teflon heat shrinkable tubing (item 3) onto the prepared wire assembly and shrink using a heat gun.
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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). An appropriate amount of excess length without looping should be given to the Flat Braid (item 4) to allow it to freely move with the wire bundle.
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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). All other restrictions and instructions for the shield termination technique set forth for Method A.1 are still applicable. NOTE The maximum length of the combined braids should be approximately 4 inches. Figure B-8. Method A.
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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. NOTE FAA AC 43.13-1B Chapter 11, Section 8 (Wiring Installation Inspection Requirements) may be a helpful reference for termination techniques.
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Table B-7. Shielded Cable Preparations – (Quick Term) Backshell Size Number of Pins Std/HD 1 2 3 4 5 9/15 15/26 25/44 37/62 50/78 Quick Term Min (inches) 1.25 1.5 1.5 1.5 1.5 Quick Term Max (inches) 2.25 2.5 2.5 2.5 2.5 Quick Term Float (inches) 1.75 2.0 2.0 2.0 2.0 B.3.5. Shield Termination-Method B.
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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). All other restrictions and instructions for the shield termination technique set forth for Method A and B are still applicable.
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B.3.7 Double-Shield Termination Technique - Method C.1 In rare situations where double shielding may be necessary, the outer shield should be grounded at both ends, while the inner shield should be grounded only at one end. All other restrictions set forth for in Table B-8 are applicable. NOTE The maximum length of the braids should be approximately 4 inches. Figure B-12. Method C.1 Double-Shield Termination Table B-8.
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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. NOTE The maximum length of the braids should be approximately 4 inches. Figure B-13. Method C.2 Double-Shield Termination B.3.
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B.3.10 Splicing Signal Wires NOTES 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. WARNING Keep the splice out of the backshell for pin extraction, and outside of the strain relief to avoid preloading. Figure B-14 shows a two wire splice, but a maximum of three wires can be spliced. If a third wire is spliced, it is located out front of splice along with signal wire going to pin.
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B.4 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.
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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.
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Table B-11. Shielded Cable Preparations for Garmin Connectors Float (in) Window (in) Backshell Size Insert Arrangement Min Max Ideal Min Max Ideal 14 19 1.35 1.60 1.50 2.10 4.60 3.60 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). Use caution when cutting the jacket to avoid damaging the individual braids of the shield.
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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. Slide a minimum 0.75 inches of Teflon heat shrinkable tubing (item 5) onto the prepared wire assembly and shrink using a heat gun.
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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). An appropriate amount of excess length without looping should be given to the flat braid (item 6) to allow it to freely move with the wire bundle.
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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). All other restrictions and instructions for the shield termination technique set forth for Method A.1 are still applicable. NOTE The maximum length of the combined braids should be approximately 4 inches. Figure B-18.
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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” and “Window Max” from Method A. This technique is depicted in Figure B-19.
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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. The chosen size of solder sleeve must accommodate both the number of conductors present in the cable and the flat braid (item 6) to be attached. NOTE Reference Section B.3.
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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. Do not violate the guidelines presented in step 7 regarding ring terminals. B.4.
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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). All other restrictions and instructions for the shield termination technique set forth for Method A and B are still applicable. NOTE The maximum 4 inches.
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APPENDIX C OUTLINE AND INSTALLATION DRAWINGS 2X 1.72 43.7 .004 0.1 3.89 98.7 FRONT SURFACE OF PANEL #6-32 CAPTIVE SCREW (4 PLCS) 3.41 [86.7] 5.47 139.1 .28 7.2 .93 23.7 .29 7.3 2X 2.34 59.4 4.50 114.4 7.83 198.8 XM CONN. 7.25 184.2 GPS CONN. 2.98 75.8 1.09 27.7 .59 15.0 6.04 153.4 1.08 27.5 1.92 48.7 3.41 86.7 NOTES: 1. DIMENSIONS: INCHES[MM] 2. DIMENSIONS ARE SHOWN FOR REFERENCE ONLY. Figure C-1.
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APPENDIX C OUTLINE & INSTALLATION DRAWINGS Drawing is not to scale! Use for dimensions only. PANEL CUTOUT .19 4.9 TYP. 4X R.39 10.0 TYP. .160 4.1 011-01747-( ) GDU 37x OUTLINE (REF.) 3.67 93.1 2X 3.58 91.1 CL 1.50 38.0 NOTES: 1. DIMENSIONS: INCHES[mm]. 2. DIMENSIONS SHOWN FOR REFERENCE ONLY. 1.24 31.5 0 0.0 CL CONNECTOR KIT 011-01921-00 2X 3.58 91.1 4X 45° 2.78 70.7 2.21 56.2 0 0.0 2X 2.69 68.4 GDU 37x UNIT 011-01747-( ) 2X 2.69 68.4 2.78 70.7 3.67 93.
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APPENDIX C OUTLINE AND INSTALLATION DRAWINGS GMU 44 MOUNTING RACK AIRCRAFT HOLES 3X .213 OPTIONAL CLEARANCE HOLES FOR HOLD-DOWN SCREWS 3.370 85.60 2.520 64.01 120 2.175 55.25 3X .164 4.17 THRU (IN THIN MATERIAL, USING LOCKING NUTS) OR DRILL AND TAP 6-32 UNC IN MATERIAL THICKER THAN 3/16 [4.8] 3 PLCS 120 2X 1.485 37.72 .725 18.42 0 2.51 63.75 2.49 63.25 2.572 65.33 2.511 63.79 1.256 31.90 .061 1.54 0 .795 20.19 NOTE: 1. DIMENSIONS IN INCHES [mm] 2.
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APPENDIX C OUTLINE AND INSTALLATION DRAWINGS GMU 44 INSTALLATION FROM ABOVE (PREFERRED) 6-32 PAN HEAD BRASS SCREWS 0.24 [6.1] MAX THREAD LENGTH WITHOUT CLEARANCE HOLES GMU 44 8.4 214 3.37 85.60 AIRCRAFT MOUNTING RACK 6-32 100 FLAT HEAD BRASS SCREWS REQUIRED .3 8 NOTES: 1. DIMENSIONS IN INCHES [mm] AIRCRAFT MOUNTING SURFACE 2.10 53.34 1.84 46.61 2.38 60.33 Figure C-2.2.
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APPENDIX C OUTLINE AND INSTALLATION DRAWINGS GMU 44 INSTALLATION FROM BELOW (NOT PREFERRED) AIRCRAFT MOUNTING RACK NOTES: 1. DIMENSIONS IN INCHES [mm] 6-32 100 FLAT HEAD BRASS SCREWS REQUIRED AIRCRAFT MOUNTING SURFACE GMU 44 8.4 214 3.370 85.60 6-32 PAN HEAD BRASS SCREWS 0.24 [6.1] MAX THREAD LENGTH WITHOUT CLEARANCE HOLES .3 8 2.23 56.52 2.38 60.33 Figure C-2.
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APPENDIX C OUTLINE AND INSTALLATION DRAWINGS NOTE: 1. BUBBLE NUMBERS IN THIS DRAWING REFER TO REFERENCE NUMBERS LISTED IN TABLES 3-6 AND 3-7. Figure C-2.
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APPENDIX C OUTLINE AND INSTALLATION DRAWINGS 2X .25 6.4 2X 5.00 127.0 .40 10.2 2.8 71 .65 16.6 P732 CONNECTOR KIT 011-01818-01 CONFIGURATION MODULE KIT (NOT SHOWN) 011-00979-20 4.50 114.3 4.25 108.0 THERMOCOUPLE KIT (NOT SHOWN) 011-00981-00 4X .210 5.33 SEE NOTE 3 P731 CONNECTOR KIT 011-01818-00 GSU 73 UNIT 011-01817-00 4.46 113.2 PITOT AIR FITTING 1/8-27 ANPT FEMALE THREAD P732 P731 1.96 49.8 STATIC AIR FITTING 1/8-27 ANPT FEMALE THREAD TYP 3.96 100.6 1.8 46 1.45 36.7 .87 22.1 3.2 81 2X 1.
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APPENDIX C OUTLINE AND INSTALLATION DRAWINGS .03 x 45 CHAMFER .02 x 45 CHAMFER 5/16 - 32 UNEF-2A .563 +.000 -.012 .50 0 .050 SEE NOTE 2 1.57 .57 .255 SEE NOTE 3 SEE NOTE 4 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. SOLDER TERMINAL: MS25036-109 6. SHIELD OF CABLE ELECTRICALLY CONNECTED TO 16 AWG WIRE. 7.
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APPENDIX C OUTLINE AND INSTALLATION DRAWINGS GA 55A FLANGE MOUNT GA 55 STUD MOUNT ARD FORW D AR RW FO 011-00134-00 ANTENNA, AVIATION, GA 55 4X 211-60212-20 #10-32 PHP x 1.00[25.4] TORQUE 20 TO 25 in-lbs 253-00002-00 GASKET, NEOPRENE 011-01153-00 GA 55A XM ANTENNA 253-00138-00 MOLDED GASKET AIRCRAFT SKIN ON TOP OF FUSELAGE AIRCRAFT SKIN 115-00031-00 BACKING PLATE 4X 210-10004-09 #8-32 SELF LOCKING NUT 1.91 48.5 FORWARD .83 [21.1] .60 15.2 FORWARD 4.23 107.
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APPENDIX C OUTLINE AND INSTALLATION DRAWINGS GA 56 STUD MOUNT D AR RW FO 011-00134-00 ANTENNA, AVIATION, GA 56 253-00002-00 GASKET, NEOPRENE AIRCRAFT SKIN ON TOP OF FUSELAGE 115-00031-00 BACKING PLATE .83 [21.1] 4X 210-10004-09 #8-32 SELF LOCKING NUT .60 15.2 FORWARD 4.23 107.4 1.91 48.5 2.59 65.8 .22 5.6 .50 12.7 4X #8-32 STUD BNC CONNECTOR .813 20.64 4X .188 4.78 4.23 107.4 2X .89 22.6 2X 1.625 41.28 FORWARD 1.000 25.40 2X 1.750 44.45 FRONT VIEW 3.00 76.2 5.00 127.0 2X 1.25 31.
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APPENDIX C OUTLINE & INSTALLATION DRAWINGS FORWARD 4.70 119.4 2.90 73.7 2.35 59.7 .80 20.2 .49 12.3 ARD FORW .60 15.2 .25 6.4 XM TNC CONNECTOR GPS BNC CONNECTOR 2X 1.600 40.64 2X .800 20.3 2X 0 .65 16.5 4X 211-60212-20 #10-32 PHP x 1.00[25.4] TORQUE 20 TO 25 in-lbs 011-01032-10 GA 57X GPS/XM ANTENNA .70 17.8 253-00138-00 MOLDED GASKET 2X 0 011-01032-00 ANTENNA OUTLINE FORWARD 1.000 25.40 2X .750 19.05 .625 15.88 AIRCRAFT SKIN 2.350 59.69 2X 3.300 83.82 4X .220 5.
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APPENDIX D INTERCONNECT DRAWING Figure D-1.
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APPENDIX D INTERCONNECT DRAWING Figure D-1.
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APPENDIX E EXTERNAL INTERFACE DRAWING (EXAMPLE ONLY) Figure E-1.
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APPENDIX E EXTERNAL INTERFACE DRAWING (EXAMPLE ONLY) Figure E-1.
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APPENDIX E EXTERNAL INTERFACE DRAWING (EXAMPLE ONLY) Figure E-1.