Garmin GI 275 Maintenance Manual
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Garmin GI 275 Maintenance Manual

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GI 275 Part 23 AML STC
Maintenance Manual
Contains Instructions for Continued Airworthiness
for STC SA02658SE
Aircraft make, model, registration number, and serial
number, along with the applicable STC configuration
information, must be completed in Appendix A and
saved with aircraft permanent records.
190-02246-11
January 2020
Revision 1

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Summary of Contents for Garmin GI 275

  • Page 1 GI 275 Part 23 AML STC Maintenance Manual Contains Instructions for Continued Airworthiness for STC SA02658SE Aircraft make, model, registration number, and serial number, along with the applicable STC configuration information, must be completed in Appendix A and saved with aircraft permanent records.
  • Page 2 Garmin. Garmin hereby grants permission to download a single copy of this manual and of any revision to this manual onto a hard drive or other electronic storage medium to be viewed and to print one copy of this manual or of any revision...
  • Page 3 The AES file encryption software is provided “as is” with no explicit or implied warranties in respect of its properties, including, but not limited to, correctness and/or fitness for purpose. 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page ii...
  • Page 4 End User (“Licensee”, “you” or “your”), on the one hand, and Garmin and its licensors and affiliated companies of Garmin and its licensors, on the other hand. The Licensed Software is licensed, not sold, to you.
  • Page 5 Section 4. b. Termination by Garmin. Garmin may immediately terminate this Agreement upon written notice to Licensee if Licensee commits a material breach of this Agreement or breaches a material term of this Agreement.
  • Page 6 Garmin or its affiliated companies in connection with: (a) any use or misuse of the Licensed Software or Documentation by Licensee or any third party in Licensee's reasonable control;...
  • Page 7 Entire Agreement. This Agreement shall constitute the entire agreement between Garmin and you with respect to the subject matter hereof and will supersede all prior negotiations, agreements and understandings of Garmin and you of any nature, whether oral or written, with respect to such subject matter.
  • Page 8 RECORD OF REVISIONS Revision Revision Date Description 1/13/20 Initial release. 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page vii...
  • Page 9 Battery replacement and removal must be performed by a licensed A&P technician. CAUTION To avoid damage to the GI 275, take precautions to prevent electrostatic discharge (ESD) when handling the unit, connectors, and associated wiring. ESD damage can be prevented by touching an object of the same electrical potential as the unit before handling the unit itself.

  • Page 10: Table Of Contents

    5.11 EIS Sensors .........................5-26 5.12 Calibration ..........................5-34 5.13 Uploading Software ......................5-36 5.14 System Checks ........................5-37 APPENDIX A INSTALLATION-SPECIFIC INFORMATION ............A-1 General Information ......................A-1 LRU Information .........................A-2 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page ix...
  • Page 11 Equipment Location ......................A-3 Wire Routing - Single Engine ....................A-4 Wire Routing - Twin Engine ....................A-5 Saved Configuration File .....................A-6 Print Configuration Log .......................A-6 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page x...
  • Page 12 Figure 2-18 Stainless Steel Pressure Sensor..................2-13 Figure 4-1 GI 275 Connectors......................4-3 Figure 4-2 GI 275 J2751 Connector (Looking at Connector) .............. 4-4 Figure 4-3 GI 275 J2752 Connector (Looking at Connector) .............. 4-5 Figure 4-4 GEA 24 Connectors......................4-7 Figure 4-5 GEA 24 J241/P241 Connector (Looking at the Connector) ..........
  • Page 13 Figure 5-18 Brass Sensor Installation (Coupling Mount Example) ............. 5-30 Figure 5-19 Stainless Steel Sensor Installation (Housing Mount Example) ........5-31 Figure 5-20 Fuel Flow Transducer Installation ..................5-33 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page xii...
  • Page 14 Table 5-3 Airspeed Test Points ......................5-39 Table 5-4 Advanced Airframe Specific Configuration Data – Arc Ranges ........5-40 Table 5-5 Advanced Airframe Specific Configuration Data – Markings ..........5-41 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page xiii...
  • Page 15 1 INTRODUCTION Purpose..............................1-2 Scope..............................1-2 Organization............................1-2 Applicability .............................1-2 Publications............................1-3 Revision and Distribution .........................1-3 Terminology and Acronyms ......................1-3 1.7.1 Terminology ..........................1-3 1.7.2 Acronyms ...........................1-4 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 1-1...

  • Page 16: Purpose

    Provides a template to record aircraft-specific installation and configuration data for the GI 275 system. 1.4 Applicability This document applies to all aircraft with the GI 275 system installed in accordance with AML STC SA02658SE. Modification of an aircraft by this STC obligates the aircraft operator to include the maintenance information provided by this document in the operator’s Aircraft Maintenance Manual and...

  • Page 17: Publications

    In addition to this manual, the following documents are recommended for performing maintenance on the GI 275 system. It is the responsibility of the owner/operator to ensure the latest applicable versions of these documents are used during operation, servicing, or maintenance of the GI 275 system.

  • Page 18: Acronyms

    Coordinated Universal Time Global Positioning System Very High Frequency Garmin Reference System VHF Omni-Directional Range WAAS Garmin Temperature Probe Wide Area Augmentation System Horizontal Situation Indicator Weather Radar 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 1-4...

  • Page 19: System Description

    Integrated ADAHRS ........................2-8 2.4.4 GMU 11 Magnetometer ......................2-9 2.4.5 GMU 44B Magnetometer......................2-9 2.4.6 GTP 59 OAT Probe........................2-9 2.4.7 Backup Battery .........................2-10 2.4.8 GSB 15 .............................2-10 2.4.9 EIS Components........................2-11 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 2-1...

  • Page 20: System Overview

    The HSI can provide course error and deviations to an autopilot if the GI 275 ADAHRS+AP is used. The required HSI installation consists of: • GI 275 display (the GI 275 Base can be used if it receives AHRS from a GI 275 ADAHRS or ADAHRS+AP) •...

  • Page 21: Table 2-1 Aml Stc Installed Sensors

    Configurable EIS gauges include optional gauges and those required by the aircraft POH and manufacturer. This manual only provides information for the EIS sensors installed per the GI 275 AML STC. Table 2-1 lists the sensors that are maintained in this manual. Refer to the applicable maintenance data and/or TSO manual for other sensors that are interfaced to the EIS.

  • Page 22: Table 2-2 Gi 275 Lru Electrical Load

    2.1.7 Electrical Load Information Electrical load information for the GI 275 system LRUs is provided below. Appendix A of this document contains details specific to the load changes for the specific aircraft installation. Table 2-2 GI 275 LRU Electrical Load...

  • Page 23: Normal Mode Operation

    The Normal mode home page differs depending on the configuration and purpose of the GI 275 unit. The menu can be accessed on any page by swiping up from the bottom of the screen or by pressing and holding the inner knob for 2 seconds.

  • Page 24: Configuration Mode Operation

    Entering Configuration Mode The Configuration mode of the GI 275 can be accessed by holding down the inner knob located at the bottom-left of the unit upon initial power-up. The knob must be pressed until the splash screen shown in Figure 2-2 appears.

  • Page 25: Export Configuration

    2. Insert a USB drive into the USB dongle or GSB 15 (if installed). A USB icon should appear on the left of the display once the GI 275 has recognized the device. If the icon doesn’t appear after 1 minute, remove the drive and re-insert it.

  • Page 26: Lru Description, Control, And Operation

    VFR GPS Antenna The GI 275 has an internal VFR GPS that may be used as a primary GPS source for VFR navigation only or as a backup GPS. The internal VFR GPS is not approved as an IFR navigation source. If the VFR GPS antenna is installed, the internal VFR GPS is automatically used when the primary GPS source is unavailable.

  • Page 27: Figure 2-5 Gmu 11 Magnetometer

    The GMU 11 Magnetometer senses the magnetic field and sends the data to the internal ADAHRS to determine aircraft magnetic heading. This unit receives power directly from the GI 275 and communicates with the AHRS board via RS-232. The GMU 11 is applicable to Class I & II aircraft only.

  • Page 28: Figure 2-8 Backup Battery

    The GSB 15 is an optional LRU that mounts into the instrument panel and provides two USB ports for charging and data transfer to a GI 275 unit. The USB ports can be used in place of a USB dongle to update the software on the GI 275 system and to charge devices while in-flight.

  • Page 29: Figure 2-10 Gea 24 Engine Adapter

    The GEA 24 is a remotely mounted engine interface and monitoring module that gathers sensor input parameters from the engine and processes the signals for the GI 275. The GEA 24 communicates with the GI 275 via RS-232. The GEA 24 is applicable to Class I & II aircraft only.

  • Page 30: Figure 2-12 Engine Annunciator (Single)

    The carburetor temperature probe is a Type-K thermocouple (Chromel and Alumel) probe. Figure 2-14 Carburetor Temperature Probe 2.4.9.5 Oil Temperature Probe The oil temperature probe is a Type-K thermocouple (Chromel and Alumel) probe. Figure 2-15 Oil Temperature Probe 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 2-12...

  • Page 31: Figure 2-16 Fuel Flow Sensor Ft-60 (Left) And Ft-90 (Right)

    2.4.9.9 P-Lead RPM Pickup A wire with two parallel resistors in-line connects from each P-lead, at the Magneto or the ignition switch, to the GEA 24/110 to sense RPM. 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 2-13...

  • Page 32: Instructions For Continued Airworthiness

    Aluminum Foil Tape (Non-metallic Aircraft Only)..............3-6 Electrical Bonding Maintenance Check ...................3-6 Overhaul Period ..........................3-7 Special Inspection Requirements......................3-7 Application of Protective Treatments ....................3-7 Data Relative to Structural Fasteners....................3-7 3.10 Additional Instructions ........................3-7 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 3-1...

  • Page 34: Servicing Information

    3.2 Servicing Information There are no servicing requirements for the GI 275 system. In the event of a system or LRU failure, troubleshoot the GI 275 system in accordance with Section 4. 3.2.1 Periodic Maintenance Instructions GI 275 system LRUs are designed to detect internal failures. A thorough self-test is executed automatically upon application of power to the units, and built-in tests are continuously executed while the LRUs are operating.

  • Page 35: Maintenance Intervals

    Section 5.5. If an EIS annunciator(s) is installed, perform a check of the annunciator lamps using the following procedure: 1. Power on the GI 275 directly interfaced to the annunciator in Configuration mode. 2. Navigate to Diagnostics → Discrete Outputs.
  • Page 36 The user must Display Backlight determine by observation when the display brightness is not On Condition suitable for its intended use. Contact a Garmin authorized repair station when the backlight lamp requires service. 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev.

  • Page 37: Visual Inspection

    Aluminum Foil Tape (Non-metallic Aircraft Only) Any aluminum foil tape used in the GI 275 installation for grounding of a GEA 24 or GEA 110 (refer to Appendix A of this document) must be inspected every 12 calendar months. The inspection must verify that the foil tape is not torn, damaged, or showing signs of corrosion.

  • Page 38: Overhaul Period

    The system does not require overhaul at a specific time period. Power on self-test and continuous BIT will monitor the health of the GI 275 system. If any LRU indicates an internal failure, the unit may be removed and replaced. Refer to Section 4 of this document for fault corrective actions.

  • Page 39: Troubleshooting

    GSB 15 .............................4-16 Troubleshooting Flow Charts ......................4-17 This section provides information to assist troubleshooting if fault codes are displayed on the GI 275 or problems occur after completing system maintenance. Refer to Appendix A of this document retained in the aircraft permanent records for a list of the interfaced equipment and system configuration data. When troubleshooting the GI 275 system, refer to wire routing drawings and interconnect diagrams retained in Appendix A of this document or with the aircraft’s permanent records.

  • Page 40: General System Troubleshooting

    Section 4.3. 4.1.1 System Maintenance Log The GI 275 system has a maintenance and error log that can be accessed or printed to assist with system maintenance and troubleshooting. The maintenance and error log can be printed using the following procedure: 1.

  • Page 41: Connector Information

    GI 275 displays have up to three connectors: • J2751/P2751 - 78 pin female contact HD D-sub • J2752/P2752 - 78 pin female contact HD D-sub (GI 275 ADAHRS and ADAHRS+AP units only) • BNC, Male Figure 4-1 GI 275 Connectors...

  • Page 42: Figure 4-2 Gi 275 J2751 Connector (Looking At Connector)

    Figure 4-2 GI 275 J2751 Connector (Looking at Connector) Table 4-2 J2751/P2751 Connector Function Function CONFIG MODULE GROUND CONFIG MODULE DATA AIRCRAFT POWER 1 AIRCRAFT GROUND AIRCRAFT POWER 2 LIGHTING BUS LO DISCRETE OUT 1 LO DISCRETE OUT 2* VOR/LOC COMPOSITE LO...

  • Page 43: Figure 4-3 Gi 275 J2752 Connector (Looking At Connector)

    Figure 4-3 GI 275 J2752 Connector (Looking at Connector) CAUTION Pins highlighted in gray are not present in GI 275 ADAHRS units (P/Ns 011-04489-10 and 011-04489-30) and should be treated as Not Connected. All pins listed in Table 4-3 are present in GI 275 ADAHRS+AP units (P/Ns 011-04489-20 and 011-04489-40).
  • Page 44 TIME MARK A TIME MARK B The Active-Low discrete outputs shall provide a connection to ground with a resistance of no more than 25Ω when in the active state. 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 4-6...

  • Page 45: Figure 4-4 Gea 24 Connectors

    • J243/P243 37-pin male contact HD D-sub • J244/P244 50-pin male contact HD D-sub GEA 24 UNIT 011-02848-00 J243 J242 J244 J241 Figure 4-4 GEA 24 Connectors 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 4-7...

  • Page 46: Figure 4-5 Gea 24 J241/P241 Connector (Looking At The Connector)

    EGT 3 LO CHT 2 HI CHT 2 LO EGT 2 HI EGT 2 LO CHT 1 HI CHT 1 LO EGT 1 HI EGT 1 LO 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 4-8...

  • Page 47: Figure 4-7 Gea 24 J243/P243 Connector (Looking At Connector)

    SHUNT 2 HI (shared w/Pin 46, OIL PRESS GROUND J244 connector) OIL PRESS HI SHUNT 1 LO OIL PRESS XDCR +12V SHUNT 1 HI OIL PRESS XDCR +5V 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 4-9...

  • Page 48: Figure 4-8 Gea 24 J244/P244 Connector (Looking At The Connector)

    GP2 LO / GOURND RESERVED / SPARE 1 GP +5V_2 RESERVED / SPARE 2 VOLTS 1 GP +12V *Indicates Active-Low **Can be configured as Active-High or Active-Low 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 4-10...

  • Page 49: Figure 4-9 Gea 110 Connectors

    RS 485 2A RS 485 1A AV PWR IN 2 RESERVED DISCRETE OUT 2 RS 485 2B RS 485 1B DISCRETE IN 5 SYS ID #1 SYS ID #2 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 4-11...

  • Page 50: Figure 4-11 Gea 110 J1102/P1102 Connector Looking At Unit

    GENERAL PURPOSE 3 (-) FUEL QUANTITY 3 / FUEL QUANTITY 2 / GENERAL PURPOSE 5 (-) GENERAL PURPOSE 4 (-) FUEL QUANTITY 4 / GENERAL PURPOSE 6 (-) 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 4-12...
  • Page 51 SHUNT 1 (+) SHUNT 2 (+) SPARE RPM IN 1 (-) +5 VDC RPM IN 2 (-) BUS 3 CONFIG MOD DATA CONFIG MOD GND 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 4-13...

  • Page 52: Figure 4-12 J442/P442 Connector

    J442/P442 6-pin rectangular connector Figure 4-12 J442/P442 Connector Table 4-10 J442/P442 Connector Function SHIELD GROUND RS-422 OUT B RS-422 OUT A POWER GROUND RS-232 IN MAG POWER INPUT 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 4-14...

  • Page 53: Figure 4-13 Gmu 11 Connector

    Table 4-11 J111/P111 Connector Function CAN BUS HI CAN BUS LO UNIT ID 1 RS-232 IN RS-232 OUT SIGNAL GROUND AIRCRAFT PWR 1 AIRCRAFT PWR 2 POWER GROUND 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 4-15...

  • Page 54: Figure 4-14 Gsb 15 Connectors

    4.2.6 GTP 59 The GTP 59 Temperature Probe does not have a connector. Rather, a 3-conductor shielded cable extends from the sensor for interface with a GI 275 or GDC unit. Table 4-12 GTP 59 3-Conductor Shielded Cable Conductor Color...

  • Page 55: Troubleshooting Flow Charts

    If a specific alert or fault condition is not listed, or the fault still exists after completing the given corrective action, contact Garmin Aviation Technical Support at the number listed for your specific region on the “Support” tab of the flyGarmin.com...

  • Page 56: Figure 4-15 Gi 275 Alert Message Troubleshooting

    Free display knob from the configuration mode pushed position If fault persists, contact Garmin. Figure 4-15 GI 275 Alert Message Troubleshooting Sheet 1 of 2 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 4-18...
  • Page 57 Shut down GI 275 reconfigure Garmin for service for at least 30 min Replace configuration module If fault persists,  contact Garmin. Figure 4-15 GI 275 Alert Message Troubleshooting Sheet 2 of 2 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 4-19...

  • Page 58: Figure 4-16 Battery Alert Message Troubleshooting

    Run battery Ensure battery is Replace battery with capacity test properly installed authentic Garmin battery If fault persists,  contact Garmin. Figure 4-16 Battery Alert Message Troubleshooting Sheet 1 of 4 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 4-20...
  • Page 59 Return GI 275 to Return GI 275 to Garmin for service Garmin for service Garmin for service If fault persists,  contact Garmin. Figure 4-16 Battery Alert Message Troubleshooting Sheet 2 of 4 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 4-21...
  • Page 60 Return GI 275 to Garmin for service Replace battery Replace battery Replace battery Replace battery If fault persists,  contact Garmin. Figure 4-16 Battery Alert Message Troubleshooting Sheet 3 of 4 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 4-22...
  • Page 61 Return GI 275 to Garmin for test; recharge fully service Replace battery Return GI 275 to Garmin for service If fault persists,  contact Garmin. Figure 4-16 Battery Alert Message Troubleshooting Sheet 4 of 4 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 4-23...

  • Page 62: Figure 4-17 Ahrs Alert Message Troubleshooting

    Verify connections Verify wiring is and wiring heading sources configured sources and wiring correct If fault persists,  contact Garmin. Figure 4-17 AHRS Alert Message Troubleshooting 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 4-24...

  • Page 63: Figure 4-18 Adc Alert Message Troubleshooting

    ADCs ADC configuration is correct Ensure there are no Verify wiring is leaks in the pitot correct static system If fault persists,  contact Garmin. Figure 4-18 ADC Alert Message Troubleshooting 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 4-25...

  • Page 64: Figure 4-19 Terrain/Taws Alert Message Troubleshooting

    TAWS and enablement GI 275 have the same aircraft type Inspect GPS antenna configured and wiring If fault persists,  contact Garmin Figure 4-19 Terrain/TAWS Alert Message Troubleshooting 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 4-26...

  • Page 65: Figure 4-20 Traffic Alert Message Troubleshooting

    ADS-B LRU UAT LRU ADS-B LRU ADS-B LRU maintenance maintenance maintenance maintenance manual manual manual manual If fault persists,  contact Garmin Figure 4-20 Traffic Alert Message Troubleshooting Sheet 1 of 2 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 4-27...
  • Page 66 TAS/TCAS LRU TIS-A LRU LRU maintenance maintenance maintenance manual manual manual If fault persists,  contact Garmin Figure 4-20 Traffic Alert Message Troubleshooting Sheet 2 of 2 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 4-28...

  • Page 67: Figure 4-21 Audio And Weather Alert Message Troubleshooting

    Inspect GDL 69/69A accordance with accordance with wiring and audio device audio device connectors maintenance maintenance manual manual If fault persists,  contact Garmin Figure 4-21 Audio and Weather Alert Message Troubleshooting 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 4-29...

  • Page 68: Figure 4-22 Nav Alert Message Troubleshooting

    Inspect GPS antenna, wiring Verify configuration settings and connections settings Inspect NAV wiring Inspect NAV wiring and connections and connections If fault persists,  contact Garmin. Figure 4-22 NAV Alert Message Troubleshooting 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 4-30...

  • Page 69: Figure 4-23 Autopilot Alert Message Troubleshooting

    AFCS Part 23 AML required autopilot STC Maintenance reference voltage Manual Clear autopilot configuration settings and reconfigure If fault persists,  contact Garmin. Figure 4-23 Autopilot Alert Message Troubleshooting 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 4-31...

  • Page 70: Figure 4-24 Miscellaneous Gi 275 Alert Messages

    Corrective Corrective Action Action Update database to Activate databases: the current version follow system prompts If fault persists,  contact Garmin. Figure 4-24 Miscellaneous GI 275 Alert Messages 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 4-32...

  • Page 71: Figure 4-25 External Lru Alert Message Troubleshooting

    GTX 3X5 the same maintenance Verify configuration settings manual Replace configuration module Verify proper software version Verify wiring If fault persists,  contact Garmin. Figure 4-25 External LRU Alert Message Troubleshooting 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 4-33...

  • Page 72: Equipment Maintenance And Checkout Procedures

    5.11 EIS Sensors............................5-26 5.11.1 Carburetor/Induction Air Temperature ..................5-27 5.11.2 Oil Temperature Sensor ......................5-28 5.11.3 Pressure Sensors ........................5-29 5.11.4 Fuel Flow..........................5-32 5.11.5 Engine RPM ...........................5-33 5.12 Calibration .............................5-34 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 5-1...
  • Page 73 This section provides the procedures to remove, replace, and re-install required and optional LRUs that are part of the GI 275 system. Refer to Section 4.2 for the definition of connectors and pin functions for GI 275 system LRUs. Before performing any maintenance on the GI 275 system, all information in Appendix A must be filled out.

  • Page 74: Figure 5-1 Gi 275 Installation

    2. Power off the GI 275 and remove power. 3. Remove the three screws retaining the GI 275 in the instrument panel. 4. Remove the backshell connectors (one or two) from the back of the GI 275. 5. Remove the BNC connector, if installed.

  • Page 75: Figure 5-2 Configuration Module Installation

    5.1.2 GI 275 Configuration Module Replacement To replace a GI 275 configuration module, perform the following procedure. All item numbers in this procedure refer to Figure 5-2. If replacing the configuration module on the Master display, the System ID will change and must be updated on the associated flyGarmin.com...

  • Page 76: Gi 275 Re-Installation

    2. Install the three screws. Torque to specifications in Figure 5-1. 3. Connect the pitot-static connections. 4. Connect the wiring connector(s) and any installed antenna wires to the back of the GI 275 and tighten the retaining screws. 5. Perform the Configuration mode ground checks in Section 5.14.1.

  • Page 77: Eis Annunciator

    3. Tighten the mounting screws until the module is fully seated in the housing. 4. Rotate the cap back into position on the module and gently press until secured. 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 5-6...

  • Page 78: Figure 5-4 Separate Eis Annunciator Installation

    1. Insert the MS25041 assembly without lens holder from the forward side of the panel and secure. 2. Install lamp on the lens holder. 3. Install and secure lens holder on the indicator. 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 5-7...

  • Page 79: Gea 24

    [2] Torque 0.190-32 UNF-2A screws 13.5 ± 1.0 in-lbf. [3] Nut can be substituted by any suitable aerospace steel self-locking nuts or nutplates. Figure 5-5 Example GEA 24 Installation 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 5-8...

  • Page 80: Gea 24 Removal

    2. Insert the USB drive containing the saved configuration into the USB dongle or GSB 15. A USB icon should appear in the bottom-left of the display once the GI 275 has recognized the device. If the icon doesn’t appear after 1 minute, remove the drive and re-insert it.

  • Page 81: Gea 110

    5.4 GEA 110 Figure 5-6 GEA 110 Installation (Mounted Directly to Airframe Example) 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 5-10...

  • Page 82: Figure 5-7 Gea 110 Installation (Mounted On A Tray Example)

    Figure 5-7 GEA 110 Installation (Mounted on a Tray Example) 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 5-11...

  • Page 83: Gea 110

    2. Insert the USB drive containing the saved configuration into the USB dongle or GSB 15. A USB icon should appear in the bottom-left of the display once the GI 275 has recognized the device. If the icon doesn’t appear after 1 minute, remove the drive and re-insert it.

  • Page 84: Backup Battery

    Backup Battery Removal 1. Remove the GI 275 in accordance with Section 5.1.1. 2. Remove the four screws securing the battery access panel to the top of the GI 275 and remove the panel. 3. Remove the battery by pulling the battery pack straight up until it is unseated from the connector.

  • Page 85: Gsb 15

    [1] Screws can be substituted by any other suitable pan head or countersink #4-40 UNC-2A aerospace steel screws. [2] Torque 0.112-40 UNC-2A screws to 5.0 ± 1.0 in-lbf. Figure 5-8 GSB 15 Cutout Installation 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 5-14...

  • Page 86: Figure 5-9 Gsb 15 Installation With Mounting Kit (2.25-Inch Cutout)

    [2] Torque 0.112-40 UNC-2A screws to 5.0 ± 1.0 in-lbf. [3] Torque 0.138-32 UNC-2A screws to 8.0 ± 1.0 in-lbf. Figure 5-9 GSB 15 Installation with Mounting Kit (2.25-Inch Cutout) 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 5-15...

  • Page 87: Figure 5-10 Gsb 15 Installation With Mounting Kit (3.125-Inch Cutout)

    [2] Torque 0.112-40 UNC-2A screws to 5.0 ± 1.0 in-lbf. [3] Torque 0.138-32 UNC-2A screws to 8.0 ± 1.0 in-lbf. Figure 5-10 GSB 15 Installation with Mounting Kit (3.125-Inch Cutout) 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 5-16...

  • Page 88: Gsb 15 Removal

    GSB 15 Re-installation To re-install the GSB 15, perform the removal procedure in reverse. Torque all screws in accordance with Figure 5-8, Figure 5-9, or Figure 5-10. 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 5-17...

  • Page 89: Gmu 11

    [2] Torque 0.138-32 UNC-2A screws 8.0 ± 1.0 in-lbf. [3] Nuts can be substituted by any other equivalent aerospace steel nutplates. Figure 5-11 Example GMU 11 Installation 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 5-18...

  • Page 90: Gmu 11 Removal

    Perform the checkout procedure in Section 5.7.3. 5.7.3 GMU 11 Checkout Perform the following AHRS ground checks found in Section 6 of GI 275 Part 23 AML STC Installation Manual (P/N 190-02246-10) to return the aircraft to service: • Magnetometer Calibration •...

  • Page 91: Gmu 44B

    5.8 GMU 44B Figure 5-12 GMU 44B Installation 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 5-20...

  • Page 92: Gmu 44B Removal

    5. Perform the checkout procedure in Section 5.8.3. 5.8.3 GMU 44B Checkout Perform the following AHRS ground checks found in Section 6 of GI 275 Part 23 AML STC Installation Manual (P/N 190-02246-10) to return the aircraft to service: •...

  • Page 93: Figure 5-13 Gtp 59 Installation (Aircraft With Metallic Skin Example)

    5.9 GTP 59 Figure 5-13 GTP 59 Installation (Aircraft with Metallic Skin Example) 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 5-22...

  • Page 94: Gtp 59

    2. Install washer and nut and torque to specifications in Figure 5-13. 5.9.3 GTP 59 Checkout Perform the Primary ADI checkout procedures in Section 6 of GI 275 Part 23 AML STC Installation Manual (P/N 190-02246-10). 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev.

  • Page 95: Vfr Gps Antenna

    The optimal antenna position is horizontal or as close to horizontal as practical given the shape of the glareshield. Figure 5-14 VFR GPS Antenna Installation (Non-removable Installation Example) 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 5-24...

  • Page 96: Vfr Gps Antenna Removal

    Install the VFR GPS antenna in the reverse order of the removal procedure. 5.10.3 VFR GPS Antenna Checkout Perform the Backup GPS Signal Check as described in Section 6 of GI 275 Part 23 AML STC Installation Manual (P/N 190-02246-10) or GI 275 EIS & MFD Installation Manual (P/N 190-02246-14).

  • Page 97: Eis Sensors

    (AN/MS). After removing or replacing any EIS sensor, perform the EIS ground checkout procedure in Section 6 of the GI 275 installation manuals (refer to Table 1-1) for the sensor that was affected. CAUTION Check hose routing for sharp bends. Check sensors and fittings for leaks during engine run-up and correct prior to flight.

  • Page 98: Figure 5-16 Carburetor Temperature Sensor Installation Example

    Figure 5-16 Carburetor Temperature Sensor Installation Example CAUTION Fuel and air passages must remain free of contaminants during work near and around the carburetor. 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 5-27...

  • Page 99: Figure 5-17 Oil Temperature Sensor Installation Example

    Section 7, Safetying, of Chapter 7, Aircraft Hardware, Control Cables and Turnbuckles, of AC 43.13-1B Aircraft Inspection and Repair. Figure 5-17 Oil Temperature Sensor Installation Example 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 5-28...

  • Page 100: Table 5-1 Pressure Sensor Equipment List

    Manifold pressure, oil pressure, and fuel pressure sensor installations are similar. Garmin pressure sensors with a brass housing are limited to aircraft with operational ceilings up to 32,000 feet. Garmin pressure sensors with a stainless steel housing may be used on all aircraft on the AML.

  • Page 101: Figure 5-18 Brass Sensor Installation (Coupling Mount Example)

    Figure 5-18 Brass Sensor Installation (Coupling Mount Example) 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 5-30...

  • Page 102: Figure 5-19 Stainless Steel Sensor Installation (Housing Mount Example)

    Figure 5-19 Stainless Steel Sensor Installation (Housing Mount Example) 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 5-31...

  • Page 103: Fuel Flow

    19 gauge minimum (0.044 inches) and installed as provisioned by the aircraft structural repair manual or standard practices manual. Methods, techniques, and practices defined in Chapter 4, Metal Structure, Welding and Brazing, of AC 43.13-1B Aircraft Inspection and Repair are acceptable. 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 5-32...

  • Page 104: Figure 5-20 Fuel Flow Transducer Installation

    5.11.5 Engine RPM The GI 275 system can use the electrical signal generated by the primary magneto coils or “P-Lead” to display RPM. When used, the left and right magneto P-Lead signals must both be connected to the GEA 24/110. The connection can be made at the magneto or the ignition switch.

  • Page 105: Calibration

    Section 5 and Section 6 of GI 275 Part 23 AML STC Installation Manual (P/N 190-02246-10). 5.12.2 Autopilot Calibration If it becomes necessary to re-calibrate the autopilot, refer to the calibration procedure contained in GI 275 Part 23 AML STC Installation Manual (P/N 190-02246-10). 5.12.3...
  • Page 106 30 minutes is required to be considered a PASS. 12. If the test results were not a PASS as described in the previous step, the battery must be replaced using the procedure in Section 5.5. 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 5-35...

  • Page 107: Uploading Software

    Uploading Software The SW/Config page is used to update the software for the GI 275 and any LRUs directly interfaced to the GI 275. The approved software version and part numbers can be found in the most recent revision of GI 275 Part 23 AML STC Equipment List (P/N 005-01208-42).

  • Page 108: System Checks

    5.14 System Checks Periodic system checks that do not require a Garmin dealer to perform are contained in this section. For complete system checkout procedures, refer to Section 6 of the GI 275 installation manuals (refer to Table 1-1). 5.14.1 Configuration Ground Check The configuration ground check procedures are intended to verify that each LRU and interface in the GI 275 system has been properly configured.

  • Page 109: Pitot-Static And Airspeed Tape Settings Checks

    30 minutes may be required if the environmental temperature is below 0º C. The GI 275 airspeed tape display and settings must be verified using the procedures in Section 5.14.2.1 or Section 5.14.2.2 depending on the airspeed tape configuration (Basic or Advanced, respectively). The airspeeds referenced in the following steps must match those shown in the printed configuration log.

  • Page 110: Table 5-3 Airspeed Test Points

    1. Power on the GI 275 system in Normal mode. 2. Using a pitot-static test set, increase the airspeed until the ADI airspeed tape pointer is at the bottom of the white band (Vs0).

  • Page 111: Table 5-4 Advanced Airframe Specific Configuration Data - Arc Ranges

    If the YELLOW arc is defined, set to the Min of the YELLOW arc (Vno). If the YELLOW arc is not defined, set Max value to Vno/Vne. 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 1 Page 5-40...

  • Page 112: Table 5-5 Advanced Airframe Specific Configuration Data - Markings

    2 - Limitations If variable with altitude, set to Variable, and max operating mach set overspeeds in accordance with number Appendix E in GI 275 Part 23 AML STC Installation Manual. Table 5-5 Advanced Airframe Specific Configuration Data – Markings POH/AFM Marking...
  • Page 113 5.14.2.3 Altimeter Check The GI 275 standby altitude displays must be verified per Title 14 of the CFR 91.411 and Part 43 Appendix E, with the following exception to 14 CFR Part 43 Appendix E, paragraph (b)(1): • The tests of sub-paragraphs (iv) (Friction) and (vi) (Barometric Scale Error) are not applicable to the GI 275 due to the internal ADAHRS interface and instrument display being digital 5.14.2.4...

  • Page 114: Appendix A Installation-Specific Information

    MFD/Standby ADI  ADAHRS+AP  Base  ADAHRS  ADI  HSI   MFD  EIS  GI 6  HSI/Standby ADI MFD/Standby ADI  ADAHRS+AP GI 275 Part 23 AML STC Maintenance Manual 190-02246-11 Page A-1 Rev. 1...

  • Page 115: Lru Information

    011-00978- VFR GPS Antenna 011-04036- GEA 24 #1 011-02848- GEA 24 #2 011-02848- GEA 110 #1 011-03454- GEA 110 #2 011-03454- Backup Battery 011-04528- GSB 15 011-04937- GI 275 Part 23 AML STC Maintenance Manual 190-02246-11 Page A-2 Rev. 1...

  • Page 116: Equipment Location

    GMU 44B #1 GMU 44B #2 GTP 59 #1 GTP 59 #2 GEA 24 #1 GEA 24 #2 GEA 110 #1 GEA 110 #2 Backup Batt GSB 15 GI 275 Part 23 AML STC Maintenance Manual 190-02246-11 Page A-3 Rev. 1...

  • Page 117: Wire Routing - Single Engine

    A.4 Wire Routing – Single-Engine The following diagram depicts the wire routing for the GI 275 LRUs throughout the aircraft structure for a single-engine aircraft: GI 275 Part 23 AML STC Maintenance Manual 190-02246-11 Page A-4 Rev. 1...

  • Page 118: Wire Routing - Twin Engine

    A.5 Wire Routing – Twin-Engine The following diagram depicts the wire routing for the GI 275 LRUs throughout the aircraft structure for a twin-engine aircraft: GI 275 Part 23 AML STC Maintenance Manual 190-02246-11 Page A-5 Rev. 1...

  • Page 119: Saved Configuration File

    A.6 Saved Configuration File The GI 275 system configuration must be saved to a USB drive and placed with the permanent aircraft maintenance records. For instructions on saving the aircraft configuration file to a USB drive, refer to Section 2.1.10. It is recommended that the USB drive be taped or otherwise secured to this page in the location marked below.

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