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 to...
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8.4.7 Updated references to GMC units to include GMC 507 8-40 8-51 8.4.8 Updated references to GMC units to include GMC 507 A-1–A-13 Appendix A Added Appendix A for GMC 507 info 190-02072-01 G5 Installation Manual Rev. 2 Page i...
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• Keep the battery away from children. • Only replace the battery with the approved replacement from Garmin. Using another battery presents a risk of fire or explosion. To purchase a replacement battery, see you Garmin dealer or the Garmin website.
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CAUTION The G5 does not contain any user-serviceable parts. Repairs should only be made by an authorized Garmin service center. Unauthorized repairs or modifications could result in permanent damage to the equipment and void both the warranty and the authority to operate this device under FAA, FCC, and other applicable regulations.
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Software are valuable trade secrets of Garmin and/or its third-party providers and that the Software in source code form remains a valuable trade secret of Garmin and/or its third-party providers. You agree not to reproduce, decompile, disassemble, modify, reverse assemble, reverse engineer, or reduce to human readable form the Software or any part thereof or create any derivative works based on the Software.
This manual is intended to provide mechanical and electrical information for use in the planning and design of an installation of the Garmin G5 into an aircraft. This manual is not a substitute for an approved airframe-specific maintenance manual, installation design drawing, or complete installation data package.
All materials that are required/optional for the installation of the G5 are listed in this section (as such, some of the information in this section is repeated in following sections).
1.5.2 Optional GPS Antenna The G5 includes a built-in GPS receiver with an internal antenna that can be used in many installations. A Garmin or non-Garmin GPS antenna is optional for G5 installations when not using the G5's internal GPS antenna.
Pneumatic Hoses and Connectors Air hoses and fittings are required to connect pitot and static air to the G5. The G5 has a female 1/8-27 ANPT fitting for each pitot and static port. Use appropriate aircraft fittings to connect to pitot and static system lines.
2.1.1 Power Specifications The G5 is capable of operating at either 14 or 28 VDC. Table 2-1 lists the supply voltage and current draw information for the G5. Use this information when determining power supply requirements. All installed electrical appliances must be considered when determining total power requirements.
2.2.2 CAN Bus Considerations The primary digital interface used to exchange data between the G5 and other LRUs is the Controller Area Network, also known as the CAN bus. CAN was developed by Bosch GmbH in the 1980s, and its specifications are currently governed by ISO 11898-2.
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Multiple devices must not connect to the CAN bus backbone at the same point. Rather than splicing two or more stub node connections together, the CAN bus should instead be daisy-chained from one device to the next (Figure 2-3). 190-02072-01 G5 Installation Manual Rev. 2 Page 2-3...
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CAN bus to the other (Figure 2-5). At a minimum, the CAN bus shield should always be grounded to the device connector backshells at the two extreme ends of the bus, but it is recommended to also ground the shield at all other devices on the CAN bus. 190-02072-01 G5 Installation Manual Rev. 2 Page 2-4...
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LRU’s CAN connection. • The GAD 29, GMU 11, GPS 20A, and G5 installation kits each provide a 9-pin termination adapter that provides CAN bus termination when attached between the LRU and the cable assembly.
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TERM INCORRECT - ONE OF THE TERMINATIONS IS NOT AT THE END OF THE BACKBONE INCORRECT - ONLY ONE END OF THE BACKBONE IS TERMINATED Figure 2-9 Incorrect CAN Bus Termination Example 190-02072-01 G5 Installation Manual Rev. 2 Page 2-6...
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The following should be considered when removing an LRU from the ends of the CAN bus. • GAD 29, GMU 11, GPS 20A, G5, or other devices that use the 9-pin CAN termination adapter: The CAN bus will remain terminated as long as the CAN termination adapter is left connected to the cable assembly.
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Figure 2-10 Network Error Rate 8. Power up only the #1 G5 unit and one other CAN device at a time, and verify the connection quality for each device. Sometimes a device will communicate only when it is the only powered device on the CAN bus, if one or more of the above issues is present.
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1. Route the coaxial cable to the unit location. Secure the cable in accordance with good aviation practices. 2. Trim the coaxial cable to the desired length and install the BNC connector. If provided, follow the connector manufacturer’s instructions for cable preparation. 190-02072-01 G5 Installation Manual Rev. 2 Page 2-9...
Cooling Requirements While no forced cooling air is required for the G5, it is highly recommended that the air behind the panel be kept moving (by ventilation or a fan). Units tightly packed in the avionics stack heat each other through radiation, convection, and sometimes by direct conduction.
One installation kit (Section 3-1) is required to install each G5 unit. The G5 Mounting Ring is included in the installation kit to mount the G5 to the aircraft panel and to reinforce the panel cutout in thin panel installations. The installation kit is not included with the G5.
3-4. Air hoses and fittings are required to connect pitot air and static air to the G5. The G5 uses a female 1/8-27 ANPT fitting for each of these ports. Use appropriate aircraft fittings to connect to pitot and static system lines.
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Use appropriate air hoses and fittings to connect the pitot and static lines to the unit. Avoid sharp bends in the tubing and attempt to route hoses away from aircraft control cables. The G5 should not be at the low point of the pneumatic plumbing lines to avoid moisture or debris collecting at or near the unit.
Pneumatic Connections The following steps should be used to aid in the fabrication of pneumatic hose connections and in attaching the aircraft pitot pressure source and aircraft static pressure sources to the G5. NOTE Whenever the aircraft is connected to a pitot-static tester, such as during Part 43 Appendix E altimeter tests, the pitot port must be covered by a pitot adapter that is controlled by the pitot- static tester.
In addition to the mounting requirements listed in Section 3.4.1, it is critical that the G5 be installed with its display bezel perpendicular to the aircraft's longitudinal axis (display bezel parallel to the wing spar) and as close to level in the roll axis as possible. Small roll offsets, and pitch offsets up to 30 , can be corrected for during calibration.
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Unit Installation The G5 is installed by inserting the alignment pin located at the top of the unit into the mating hole in the mounting ring, pushing the unit flush with the instrument panel, and fastening the captive 3/32” hex socket...
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0.150 inch, the captive mounting screw can be replaced with a standard #6-32 hex socket head screw. To replace the screw, remove the two #4-40 flat head Phillips mount plate screws, the G5 screw mount plate, and the captive screw as shown in Figure 3-5.
1.6 41 CENTER OF GRAVITY PITOT R1.52 38.6 TYP. STATIC 1.71 43.4 NOTES: 1-1. DIMENSIONS: INCHES[mm]. METRIC VALUES ARE FOR REFERENCE ONLY. 1-2. DIMENSIONS ARE NOMINAL AND TOLERANCES Figure 3-6 G5 Outline Drawing 190-02072-01 G5 Installation Manual Rev. 2 Page 3-9...
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POINTS ON THE CAN BACKBONE. IF USED WITH THE G3X SYSTEM REFER TO THE G3X INSTALL MANUAL FOR SPECIFIC GUIDANCE ON CAN BUS WIRING. 2-2. ALL RED PLUGS MUST BE REMOVED AND DISCARDED. THEY ARE NOT TO BE USED FOR CAPPING AND SEALING UNUSED PORTS. Figure 3-7 G5 Installation Drawing 190-02072-01 G5 Installation Manual Rev. 2...
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.150±.003 3.81±0.08 2X 1.237±.005 31.4±0.13 1.237±.005 31.4±0.13 Cut out panel to inside line 3.155 80.14 3.125 79.38 Figure 3-8 G5 Panel Cutout Measurements (Not to Scale) 190-02072-01 G5 Installation Manual Rev. 2 Page 3-11...
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For panel cutout, drill out with a 3.125" diameter bimetal hole saw. The outline in this drawing is identical to the outline of the actual bezel. Figure 3-9 G5 Panel Cutout Drawing (Template) 190-02072-01 G5 Installation Manual Rev. 2 Page 3-12...
LRU. Additional GPS antennas may be used for redundancy, but are not required. A GPS 20A (and connected GPS/WAAS antenna) can be used as the sole GPS source for a G5 system, however it is recommended to also install a GPS antenna on a G5 or GDU 37X/4XX for redundancy. If...
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Table 4-2 Supported Garmin Antennas Mounting Model Part Number Install Manual Configuration Flange, Magnetic, or GA 26C (GPS) 011-00149-04 190-00082-00 Suction Cup Mounts (in-cabin) Thru-Mount (tear drop GA 35 (GPS/WAAS) 013-00235-0X 190-00848-00 form factor) Thru-Mount (ARINC GA 36 (GPS/WAAS) 013-00244-0X...
5.1.1 Aircraft Power The G5 can operate using power from one or both inputs (AIRCRAFT POWER 1 and AIRCRAFT POWER 2). The pins are internally connected using diodes to prevent current from flowing between the two power inputs. AIRCRAFT POWER 2 is for connecting to an alternate power source, such as on aircraft with two electrical buses.
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5.1.4 Unit ID The G5 detects its assigned unit type at startup by checking the UNIT ID pin. This pin can be strapped into the following configurations. A maximum of two G5 units may be used in a single installation.
Figure 6-1. The parts listed in Table 6-1 are supplied in the G5 installation kit. The parts listed in Table 6-2 are to be provided by the installer as required. Table 6-1 Garmin Supplied Shield Block Installation Parts for the G5...
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NOTE In Figure 6-1, “AR” denotes quantity “As Required” for the particular installation. Figure 6-1 Example Shield Install onto a Jackscrew Backshell 190-02072-01 G5 Installation Manual Rev. 2 Page 6-2...
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6-2) onto the prepared wire assembly and shrink using a heat gun. The chosen size of heat shrink tubing must accommodate both the number of conductors present in the cable and the flat braid. 190-02072-01 G5 Installation Manual Rev. 2 Page 6-4...
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1/64 – 1/32 of an inch from the end of the contact as shown in Figure 6-3. Figure 6-3 Insulation/Contact Clearance 190-02072-01 G5 Installation Manual Rev. 2 Page 6-5...
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Placing the grooved side of the backshell clamp across the cable bundle may cause damage to the wires. 12. Attach the backshell cover (item 14, Figure 6-1) to the backshell using the provided screws (item 15, Figure 6-1). 190-02072-01 G5 Installation Manual Rev. 2 Page 6-6...
(Figure 6-4). All other restrictions and instructions for the shield termination set forth in Method A.1 are still applicable. NOTE The maximum length of the combined braids should be 4 inches. Figure 6-4 Shield Termination Technique Method A.2 190-02072-01 G5 Installation Manual Rev. 2 Page 6-7...
If Method B.1 is used, care must be taken to ensure that all drain shield terminations can still be inspected. Garmin recommends using Method A.1 on connectors which require a large number of shield drain terminations, as this will allow these terminations to be dispersed across a larger area.
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Teflon heat shrink tubing Reference MIL-SPEC Teflon heat shrink tubing M23053/5-X-Y. 4. Insert the newly crimped pins and wires into the appropriate connector housing location as specified by the installation wiring diagrams. 190-02072-01 G5 Installation Manual Rev. 2 Page 6-9...
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Warning: Placing the grooved side of the backshell clamp across the cable bundle may cause damage to the wires. 11. Attach the backshell cover (item 14, Figure 6-1) to the backshell using the provided screws (item 15, Figure 6-1). 190-02072-01 G5 Installation Manual Rev. 2 Page 6-10...
6-6). All other restrictions and instructions for the shield termination set forth in Method B.1 are still applicable. NOTE The maximum length of the combined braids should be 4 inches. Figure 6-6 Shield Termination Technique Method B.2 190-02072-01 G5 Installation Manual Rev. 2 Page 6-11...
6-7). All other restrictions and instructions for the shield termination set forth in Method A.1 and B.1 are still applicable. NOTE The maximum length of the combined braids should be 4 inches. Figure 6-7 Shield Termination Technique Methods A.1 and B.1 190-02072-01 G5 Installation Manual Rev. 2 Page 6-12...
6.7 Unit ID (Strapping) The Unit ID Program Pin on the G5 provides a ground reference used by the hardware as a means of configuring the unit for system identification. When installing two G5 units, the second unit must have its UNIT ID pin (J51 pin 3) connected to ground.
Raychem D-436-36/37/38 • MIL-SPEC MIL-S-81824/1 WARNING eep the splice out of the backshell for pin extraction, and outside of the strain relief to avoid preloading. Figure 6-8 D-Sub Spliced Signal Wire Example 190-02072-01 G5 Installation Manual Rev. 2 Page 6-14...
The checkout procedures in this section are recommended to be performed after installing the G5. The calibration procedures are required to be performed after installing the G5. 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.
Figure 8-1 Entering Configuration Mode 8.3 Software Loading Procedure G5 software loading can be performed in either normal or configuration mode. Manually loading software to the G5 is not required when the G5 is installed as part of a G3X system. ™ ™...
Figure 8-2 Device Information Page The G5 can be configured as a Standalone Unit or (if connected to a G3X system) it will automatically be configured as G3X Backup Unit. When connected to a G3X system, the G5 will not allow the Installation Type setting to be changed (as long as the G5 is communicating with G3X LRUs).
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Adjusts the scale of the pitch ladder on the PFD. Compact spaces the pitch Pitch Display markings closer together. Normal mimics the spacing of typical mechanical attitude indicators. Expanded spaces the markings further apart. 190-02072-01 G5 Installation Manual Rev. 2 Page 8-4...
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The roll pointer beneath the roll arc moves with the horizon and in the opposite direction to aircraft roll. Section 8.4.6.2 Validates the vibration characteristics of the G5 installation. See Vibration Test for more information. 190-02072-01 G5 Installation Manual Rev.
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Table 8-1 Attitude Configuration Settings Allows for direct manual entry of the present yaw offset when the instrument panel to which the G5 is mounted is not perpendicular to the aircraft centerline. The limit on this setting is +/- 15 degs. Positive is clockwise.
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Configuration Description Setting Select Disabled to disable the G5's internal air data sensors and hide airspeed, altitude, and vertical speed information on the PFD. This option is intended for single standalone G5 installations where the pitot/static inputs are not connected.
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8.4.4 Airspeed Configuration Page This page allows for configuration of the reference speeds. The aircraft Vspeeds can be entered using the knob on the G5. To clear a reference speed setting: 1. Highlight the desired reference speed setting. 2. Rotate the knob counterclockwise until a blank field is displayed.
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Enabled option is intended for single standalone G5 installations that are connected to a GMU 11 Magnetometer. Status Indicates status of communication with GMU 11. Used to inform the G5 of the mounted orientation of a GMU 11 Magnetometer Orientation Section 8.4.6.4 (optional). See for detailed instructions.
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8.4.6 G5 Post-Installation Calibration Procedures After mechanical and electrical installation of the G5 has been completed, prior to operation, a set of post- installation calibration procedures must be carried out. Table 8-4 describes the required and optional calibration procedures. Table 8-4 Post-Installation Calibration Procedure Summary...
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NOTE I n a G3X system, or a non-G3X system with multiple G5 units, if the pitch/roll offset procedure is performed for one unit, it should be performed on all other G3X AHRS units or G5 units before moving the aircraft.
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Engine Run-Up Vibration Test is intended to help discover mounting issues but successful completion of the test does not validate the mounting of the G5, and does not account for all possible vibration profiles that may be encountered during normal aircraft operation 1.
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Vibration or motion of the G5 caused by neighboring equipment and/or supports. c) Mounting of the G5 in a location that is subject to severe vibrations (e.g. close to an engine mount). d) Mounting screws and other hardware for G5 not firmly attached.
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8.4.6.3 Calibration Procedure C: Air Data Static Pressure Calibration The Air Data Configuration page has a selection for static pressure calibration. This procedure is used to perform an altimeter re-calibration. The altitude pressure sensor used in the G5 is very low drift and does not typically require re-calibration.
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3. Select the Orientation of the GMU 11 in the installation using the on-screen instructions as a guide. Figure 8-11 Select Magnetometer Orientation 4. Ensure that the correct orientation is now displayed on the Magnetometer Configuration page. 190-02072-01 G5 Installation Manual Rev. 2 Page 8-16...
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4. Ensure that the aircraft has been properly prepared per the on-screen instructions. See Table 8-5 for a sample test sequence. Select Start to begin the test. Figure 8-13 Magnetometer Interference Test 190-02072-01 G5 Installation Manual Rev. 2 Page 8-17...
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The worst case magnetic deviation value will indicate the test margins. Values less than or equal to 100% constitute a pass and greater than 100% constitute a fail. Figure 8-15 Magnetometer Interference Test Passed 190-02072-01 G5 Installation Manual Rev. 2 Page 8-18...
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5:30 Turn off all wing-tip lights simultaneously 5:40 Beacon on 5:50 Beacon off 6:00 Pitot heat on 6:10 Pitot heat off 6:20 End of test 190-02072-01 G5 Installation Manual Rev. 2 Page 8-19...
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A maximum deviation value greater than 100% of the total limit 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. NOTE Two common reasons for a failed magnetometer interference test are: 1) New equipment is installed in close proximity to the GMU 11 Magnetometer.
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3. Ensure that all on-screen instructions have been complied with, then select Next. Figure 8-17 Magnetometer Calibration Page 4. Ensure that all on-screen instructions have been complied with, then select Next. Figure 8-18 Magnetometer Calibration Page 190-02072-01 G5 Installation Manual Rev. 2 Page 8-21...
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9. If the calibration is successful, a passing status message will be displayed. The calibration will abort if it cannot be successfully completed. Ensure all on-screen instruction are followed and repeat the test (if necessary) to obtain a successful calibration. 190-02072-01 G5 Installation Manual Rev. 2 Page 8-22...
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“wing-leveler”. The roll servo follows roll steering commands from the G5 so the airplane will hold a desired roll angle, follow a desired heading/track, or follow the lateral component of a flight plan.
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Most GSA 28 autopilot systems consist of both a roll and pitch servo allowing for full 2-axis control of the aircraft. The pitch servo follows vertical guidance commands from the G5 so the airplane will hold a desired pitch angle, vertical speed, airspeed, or altitude, or follow the vertical component of a flight plan.
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This is done so the pilot can focus on properly adjusting the performance of the primary autopilot system without having the autotrim functionality interfere. NOTE Ensure basic autopilot functionality is properly adjusted before enabling trim control for any servo. 190-02072-01 G5 Installation Manual Rev. 2 Page 8-25...
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NOTE T he following post installation checkout must be followed after every completed installation. These steps should be followed when using a Garmin mounting kit or non-Garmin mounting parts to install the GSA 28. After mounting the GSA 28, please complete the following steps prior to completing the first flight with the GSA 28.
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Figure 8-25 Device Information Page 5. Select the Autopilot Roll Servo Configuration page and verify the proper trim activity with the servo connected to an auxiliary trim motor. Figure 8-26 Autopilot Roll Servo Configuration Page 190-02072-01 G5 Installation Manual Rev. 2 Page 8-27...
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Verify the pitch servo is properly indicating nose down trim activity. d) If the elevator trim response is reversed, select Reverse for the Trim Motor Direction, then repeat all of step 6. 190-02072-01 G5 Installation Manual Rev. 2 Page 8-28...
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With the Servo Direction set to Reverse, the servo arm should move clockwise to cause a nose up elevator movement and the servo arm should move counterclockwise to cause a nose down elevator movement. 190-02072-01 G5 Installation Manual Rev. 2 Page 8-29...
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The minimum airspeed limit should be set above the stall speed of the aircraft with some margin. b) The maximum airspeed limit should be set below the never exceed speed of the aircraft with some margin. 190-02072-01 G5 Installation Manual Rev. 2 Page 8-30...
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8.4.7.4 On-Ground Autopilot Setup The next phase of setting up the Garmin autopilot system is to verify the proper functionality of the autopilot system on the ground in normal mode. This phase of the checkout requires a valid ground track and pitch output from the G5.
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Push the knob on the G5 to access the menu. d) Select Track from the menu on the G5. e) Push and hold the knob on the G5 to center the HDG bug. f) Rotate the knob on the G5 clockwise to command a right turn.
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8.4.7.5 On-Ground Yaw Damper Setup The next phase of setting up the Garmin autopilot system is to verify the proper functionality of the yaw damper system on the ground in normal mode. This phase of the checkout requires a valid output from the G5.
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Press the AP button on the GMC Mode Controller to engage the AP. ii. Press the YD button on the GMC Mode Controller to disengage the YD. b) Press the knob of the G5 to access the menu. c) Select Setup from the menu.
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Pitch Gain has advanced and expert configurations that can be adjusted to achieve the desired performance. These settings are detailed in Table 8-8 and should only be adjusted after studying the descriptions to properly understand their effect on pitch gain. 190-02072-01 G5 Installation Manual Rev. 2 Page 8-35...
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Yaw Damper Setup The next phase of setting up the Garmin yaw damper system is to verify and tune the proper functionality of the yaw damper system in the air. WARNING This stage of the flight test involves allowing the GSA 28 autopilot servos to manipulate the flight control surfaces of the aircraft.
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The recommended setting for the Trim High Airspeed Threshold is the airspeed typically used to fly the normal aircraft landing pattern. 3. Re-verify proper trim movement described in Section 8.4.7.3. 190-02072-01 G5 Installation Manual Rev. 2 Page 8-37...
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1. Use the Setup page in normal mode to adjust the trim motor speed to get the desired manual electric trim response. a) Press the knob on the G5 to access the menu. b) Select Setup from the menu. c) Note the low and high airspeed threshold settings on this page.
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This should be the higher of the two airspeeds. The recommended setting for the Trim High Airspeed Threshold is the airspeed typically used to fly the normal aircraft landing pattern. 190-02072-01 G5 Installation Manual Rev. 2 Page 8-39...
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GMC Mode Controller AP button. Controls access to the Automatic Flight Control System Setup page in normal AFCS Setup Page mode. Leave this item set to Enabled unless specifically required for the installation. 190-02072-01 G5 Installation Manual Rev. 2 Page 8-40...
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The servo gain setting can be adjusted from 0.00 to 10.00 in steps of 0.05. *Available in normal mode 190-02072-01 G5 Installation Manual Rev. 2 Page 8-41...
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Trim High Airspeed Thresh airspeed. Speed Expressed as a percentage of the maximum auxiliary trim motor speed. The Slowest Trim Motor Speed can be adjusted from 5% to 100% in 5% steps. *Available in normal mode 190-02072-01 G5 Installation Manual Rev. 2 Page 8-42...
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Fine Adjust Time is an expert configuration setting, and should generally be not be changed by the installer. The default value is 0.20. *Available in normal mode 190-02072-01 G5 Installation Manual Rev. 2 Page 8-43...
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After selecting the proper servo direction, the installer should engage the autopilot system in normal mode and verify proper elevator response by rotating the pitch reference up and down from the current pitch. *Available in normal mode 190-02072-01 G5 Installation Manual Rev. 2 Page 8-44...
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If the maximum time is exceeded, the pilot will need to release the Manual Electric Trim (MET) control and then reassert it to continue running trim. *Available in normal mode 190-02072-01 G5 Installation Manual Rev. 2 Page 8-45...
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VS mode. The Vertical Acceleration Gain should be decreased if the aircraft appears to back off from the desired vertical speed target when closing on the bug. *Available in normal mode 190-02072-01 G5 Installation Manual Rev. 2 Page 8-46...
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5 knots. configuration) The Airspeed Tracking Gain should be decreased if the aircraft is overly aggressive while tracking airspeed when the airspeed error is less than 5 knots. *Available in normal mode 190-02072-01 G5 Installation Manual Rev. 2 Page 8-47...
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After selecting the proper servo direction, the installer should engage the yaw damper in normal mode and verify proper rudder response by the tail of the aircraft back and forth. *Available in normal mode 190-02072-01 G5 Installation Manual Rev. 2 Page 8-48...
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If the maximum time is exceeded, the pilot will need to release the Manual Electric Trim (MET) control and then reassert it to continue running trim. *Available in normal mode 190-02072-01 G5 Installation Manual Rev. 2 Page 8-49...
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Filter Constant acceleration. (expert Yaw Acceleration Filter Constant is an expert configuration setting, and should configuration) generally be not be changed by the installer. The default value is 0.16. *Available in normal mode 190-02072-01 G5 Installation Manual Rev. 2 Page 8-50...
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This setting should not be adjusted Angle from the default of 30° except for very high performance aircraft that have bank angle limitations at high speeds. 190-02072-01 G5 Installation Manual Rev. 2 Page 8-51...
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This page allows for configuration of certain options for the ESP (Electronic Stability Protection) function. It will only appear in installations that include an autopilot with Garmin servos. ESP is an optionally enabled feature that is intended to assist the pilot in maintaining the aircraft in a stable flight condition.
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Automatic mode sets the backlight intensity (display brightness) based on the Current Mode photocell (ambient light sensor) input on the G5. Manual mode allows for setting the backlight intensity by changing the Backlight percentage directly. Manual brightness control is available at any time by pressing the power button.
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Enables and disables access to the HSI page in normal mode. Sets the default page (PFD or HSI) displayed at unit power on. The HSI page Powerup Page cannot be configured as the default powerup page on the #1 G5 in a G3X system. 190-02072-01 G5 Installation Manual Rev.
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Lifetime Remaining Table 8-14 Battery Configuration Settings Configuration Description Setting Select When Using Battery to only display the status of the G5 backup battery when the unit is operating from the battery (i.e. aircraft power has been removed). Show Battery Status Select Always to constantly display the status of the G5 backup battery.
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GPS reception and an external GPS antenna is not installed. Internal GPS Receiver When the internal GPS receiver is disabled, the G5 is still able to receive GPS data from an external navigation source such as other Garmin LRUs (e.g. GDU37X/4XX, GPS 20A, or secondary G5).
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NOTE The signal strength bars at the bottom of the GPS Configuration page are a real-time representation of GPS signal strength, which may be useful for troubleshooting a failed COM interference test. 190-02072-01 G5 Installation Manual Rev. 2 Page 8-57...
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Navigation data cannot be hidden when autopilot servos are configured. For a backup unit (part of a G3X system), this setting controls how the G5 selects the navigation data source to display when communicating with a G3X display.
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8.4.13.3 Units Configuration Page This page allows for configuration of the displayed units. The units for each measurement can be selected using the knob on the G5. Figure 8-39 Units Configuration Page The Units Configuration page also allows for the selection of Normal or Alternate Data Field Units Display.
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If the units for airspeed and groundspeed are not the same, the title for the groundspeed field will be moved above the value and updated to include the unit (color-matched to the title). Figure 8-42 Non-Matching Airspeed and Groundspeed Units 190-02072-01 G5 Installation Manual Rev. 2 Page 8-60...
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On the HSI page, all data field titles will be moved above the value and updated to include the unit (color- matched to the title). Figure 8-43 Alternate Data Field Units on HSI Page 190-02072-01 G5 Installation Manual Rev. 2 Page 8-61...
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8.4.13.4 RS-232 Configuration Page This page allows for configuration of the serial communication port on the G5. Both the input and output serial port formats can be configurated independently. Some input/output formats will also allow for a configurable baud rate.
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Supports the input and output of standard NMEA 0183 version 3.01 data at a NMEA configurable baud rate of either 4800 or 9600. The G5 outputs GPS data via NMEA sentences. Outputs attitude, air data, and GPS position/velocity text data as described in Text Section 11.4...
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8.4.13.5 ARINC 429 Configuration Page This page allows for configuration of the 2 ARINC 429 output and 4 ARINC 429 input ports on the G5. Figure 8-45 ARINC 429 Configuration Page Table 8-19 ARINC 429 Outputs Configuration Description Setting Outputs EFIS and air data labels to a GNS 4XX/5XX series unit. The transmitted...
A Garmin Field Service Engineer may ask the technician to email any fault or data logs back to Garmin to help determine if the condition is caused by a G5, a different LRU, or a source elsewhere in the aircraft installation.
(e.g. "Software version mismatch") and a Red-X in configuration mode. More than one G5 strapped as the same unit (i.e. both unit 1 or both unit 2) will be annunciated with a message (e.g. "Communication error" or "Network address conflict") in normal mode and a Red-X in configuration mode.
8. Was there a loss of the GPS position lock? 9.6 Heading Failure Troubleshooting (with GMU 11) If a Red-X (steady or intermittent) is displayed in the heading field on the G5, check the following while the aircraft is on the ground: 1.
No software or calibration is required if the original G5 is reinstalled in its original mounting location. 10.3.2 New G5 is Installed Any time a new G5 is installed, or an existing G5 is moved to a different mounting location, the pitch/roll offset calibration procedure (Section 8.4.6.1) must be performed.
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10.3.3 G5 installations With a GMU 11 For G5 installations that include a GMU 11, verify the heading display is accurate as indicated by the white numbers displaying the magnetic heading. Any time a GMU 11 is moved or reinstalled, a new...
Positional Accuracy < 10 meters 11.2 G5 Environmental Specifications The G5 has an operating temperature range of -20°C to +60°C. The G5 will prevent operation from the battery when the battery is outside of this temperature range. 190-02072-01 G5 Installation Manual Rev.
*Normal dynamic maneuvering is defined as bank angles less than 35° and pitch angles less than 15°. Due to variations in the Earth's magnetic fields, the operational accuracy of the G5's heading (with optional GMU 11) is unknown in the following regions: •...
Carriage return (0x0D hex) • Line feed (0x0A hex) An exception to the above is the GPS Data message, which is backwards compatible with the Garmin Simple Text Output format described at: http://www8.garmin.com/support/text_out.html. The GPS Data message has the following format: •...
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= upward acceleration Unused Vertical speed 10 fpm positive = up -999 +999 Unused Altimeter setting 0.01 inHg offset from 27.50° Checksum ASCII hex sum of prev bytes CR/LF 0x0D/0x0A Total Length 190-02072-01 G5 Installation Manual Rev. 2 Page 11-4...
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'S' = simulated position '_' = invalid position Horizontal position meters error Altitude meters Height above/below MSL -99999 +99999 'E' = east East/west velocity direction 'W' = west East/west velocity 0.1 m/ 0000 9999 magnitude 190-02072-01 G5 Installation Manual Rev. 2 Page 11-5...
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North/south velocity direction 'S' = south North/south velocity 0.1 m/ 0000 9999 magnitude 'U' = up Vertical velocity direction 'D' = down Vertical velocity 0.01 m/ 0000 9999 magnitude CR/LF 0x0D/0x0A Total length 190-02072-01 G5 Installation Manual Rev. 2 Page 11-6...
Figure A-1 GMC 507 Unit View (-00 version) A.1 Equipment Description The GMC 507 is a Garmin Automatic Flight Control System (AFCS) Mode Controller that can be used in a G5 autopilot installation. The GMC 507 provides a user interface for the autopilot function. The...
Figure A-6 for complete cutout dimensions. A .dxf version of the drawing is also available for download at https://support.garmin.com/support/manuals. CAUTION Exercise caution when installing the rack in the instrument panel. Deformation of the rack will make it difficult to install and remove the GMC 507.
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The 15 pin connector, pins, and backshell supplied in the GMC 507 installation kit are used to add wiring for the GMC 507. See Section 7 for interconnect drawings and Section A.4 for pinout information. 190-02072-01 G5 Installation Manual Rev. 2 Page A-3...
CAN LO SONALERT CAN BUS TERM 2 AIRCRAFT POWER 1 CAN BUS TERM 1 AIRCRAFT POWER 2 TO/GA DISCRETE IN LIGHTING BUS HI AP DISCONNECT IN/OUT AUDIO HI AUDIO LO POWER GROUND 190-02072-01 G5 Installation Manual Rev. 2 Page A-4...
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J7001 A.4.2 CAN Bus The G5 CAN bus conforms to the BOSCH standard for Controller Area Network 2.0-B and ISO 11898. Section 2.2.2 for details. To enable the internal CAN terminator when the GMC 507 is installed at one of the two ends of the CAN bus, a wire must be installed to short pin 6 to pin 8.
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Provides an active low discrete input which may optionally be connected to a TO/GA button. Pin Name Connector DISCRETE IN J7001 A.4.7 AP Disconnect In/Out This pin is used for certified installations only. Pin Name Connector AP DISCONNECT IN/OUT J7001 190-02072-01 G5 Installation Manual Rev. 2 Page A-6...
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