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Garmin GI 275 Maintenance Manual
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Garmin GI 275 Maintenance Manual

Garmin GI 275 Maintenance Manual

Part 23 aml stc
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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
May 2024
Revision 9

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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. 9 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 Corrected pin numbers 44 and 45 to “RESERVED” in Table 4-7 GEA 24/GEA 24B 4.2.2 J244/P244 Connector. Updated Figure 5-1 GI 275 Installation (Pan Head Screws) for clarity and added Figure 5-2 GI 275 Installation (Countersunk Screws). Added Figure 5-9 Backup Battery Installation.
  • 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 5.12 TVS and Fuse (Class II & III Composite Aircraft Only) ...........5-37 5.13 Calibration ..........................5-39 5.14 Uploading Software ......................5-53 5.15 System Checks ........................5-54 APPENDIX A INSTALLATION-SPECIFIC INFORMATION ............A-1 General Information ......................A-1 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 9 Page ix...
  • Page 11 Equipment Location ......................A-3 Wire Routing - Single Engine ....................A-4 Wire Routing - Twin Engine ....................A-5 Wire Routing - Jet ........................A-6 Saved Configuration File .....................A-7 Print Configuration Log .......................A-7 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 9 Page x...
  • Page 12 GMU 11 Overbraid Termination ..................3-12 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/GEA 24B Connectors ................... 4-7 Figure 4-5 GEA 24/GEA 24B J241/P241 Connector (Looking at the Connector)......
  • Page 13 Figure 5-23 Fuel Flow Transducer Installation ..................5-36 Figure 5-24 TVS and Fuse Installation ....................5-37 Figure 5-25 Fuel Quantity Calibration Page ..................5-52 Figure 5-26 Fuel Quantity Calculation Procedure................5-52 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 9 Page xii...
  • Page 14 Advanced Airframe Specific Configuration Data – Arc Ranges ........5-58 Table 5-10 Advanced Airframe Specific Configuration Data – Markings ..........5-59 Table 5-11 Textron Aviation Model 525A Altitude Test Points ............5-60 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 9 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. 9 Page 1-1...
  • Page 16 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 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 Extended Squitter Electronic Stability and Protection Federal Aviation Administration Flight Director FIS-B Flight Information Services - Broadcast Garmin Data Link Garmin Engine Adapter Garmin Indicator Garmin Mode Controller 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 9 Page 1-4...
  • Page 19 Omni-Bearing Selector Organization Designation Authorization Personal Electronic Device Part Number Pilot’s Operating Handbook PSIA Pounds per Square Inch - Absolute PSIG Pounds per Square Inch - Gauge 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 9 Page 1-5...
  • Page 20 Universal Serial Bus Coordinated Universal Time Volts Alternating Current Volts Direct Current Visual Flight Rules Very High Bond Very High Frequency VHF Omni-Directional Range WAAS Wide Area Augmentation System 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 9 Page 1-6...
  • Page 21 Integrated ADAHRS ........................2-11 2.4.4 GMU 11 Magnetometer ......................2-12 2.4.5 GMU 44B Magnetometer......................2-12 2.4.6 GTP 59 OAT Probe........................2-12 2.4.7 Backup Battery .........................2-13 2.4.8 GSB 15 .............................2-13 2.4.9 EIS Components........................2-14 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 9 Page 2-1...
  • Page 22 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 23 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 24 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 25 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 26 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 27 2. On the GI 275, touch Pair a Device. 3. Touch Bluetooth Name, select the device, then touch Pair. The GI 275 can store up to 13 paired devices. Once a device is paired, it can be connected to automatically in Normal mode to initiate database uploads.
  • Page 28 USB drive. 5. Touch Back. 6. Insert the USB drive into the USB dongle or optional GSB 15 and wait for the GI 275 to recognize the drive. 7. Once connected, a pop-up will appear to update databases. Touch Yes.
  • Page 29 7. Wait for databases to update. A progress bar is shown for each selected update. If there are other Garmin units in the system that need to receive the new databases, the status of the sync to those units will be displayed as well.
  • Page 30 2. Insert the USB drive containing the configuration files 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 31 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 32 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 33 USB Type-A/single USB Type-C ports. Each variant also has the option to have the connector on the rear or side of the 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 34 2.4.9.2 GEA 110 Engine Adapter The GEA 110 is a remote mount engine interface and monitoring module that gathers sensor input parameters from the engine and processes the signals for the GI 275. The GEA 110 communicates with the GI 275 via RS-485.
  • Page 35 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. 9 Page 2-15...
  • Page 36 Figure 2-17 Pressure Sensors 2.4.9.8 Garmin Restrictor (Optional) The optional Garmin restrictor may be installed on the manifold pressure port to aid erratic pressure indications caused by manifold pressure port locations close to the intake valve. The Garmin restrictor is an aluminum AN3 to 1/8 MNPT fitting with a 0.016-inch orifice, marked with “R.016”.
  • Page 37 GTP 59 OAT Probe........................3-9 3.7.2 GMU 11/44B..........................3-9 3.7.3 Transient Voltage Suppressor (TVS) (If Installed) ..............3-13 Application of Protective Treatments .....................3-13 Data Relative to Structural Fasteners....................3-13 3.10 Additional Instructions ........................3-13 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 9 Page 3-1...
  • Page 39 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 40 CFR §91.411 for system-specific checkout procedure. and 91.413 Test TVS Lightning The GI 275 main power inputs have a TVS/fuse located at the Protection 24 calendar GI 275 connector. Each TVS and fuse must be checked or (Class II & III months replaced in accordance with Section 3.7.
  • Page 41 Contact a Garmin authorized repair station when the backlight lamp requires service. Drain(s) in pitot and static lines added to GI 275 connection with the existing aircraft pitot-static system must be opened and discharged. Drains may not be present in all aircraft. Drains are...
  • Page 42 3.4 Visual Inspection Operation of the GI 275 system is not permitted unless an inspection, as described in this section, has been completed within the preceding 12 calendar months. Conduct the following visual inspection of the GI 275 system LRUs and associated wiring harnesses to ensure installation integrity: 1.
  • Page 43 Rivets used to mechanically attach brackets and shelves provide an inherent electrical bond through the rivets and require no additional bond preparation. The top or bottom side of the Garmin racks or equipment flanges do not need any special bond preparations. Reference the aircraft manufacturer...
  • Page 44 5. Install bonding aluminum tape or equipment at grounding location. 6. After the bond is complete, if any films or coatings were removed from the surface, re-apply a suitable film or coating to the surrounding area. 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 9 Page 3-8...
  • Page 45 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 46 3. Terminate the braid pigtail in an appropriate terminal lug. Method B 1. Comb out a maximum of 2 inches of overbraid pigtail. 2. Twist the pigtail and terminate it in an appropriate terminal lug. 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 9 Page 3-10...
  • Page 47 4. Verify overbraid terminal bonding by checking resistance between the overbraid and the rib with the GMU 11 connector disconnected. Resistance should be less than 2.5 mΩ. Figure 3-1 GMU 11 Overbraid Installation 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 9 Page 3-11...
  • Page 48 Perform the Magnetic Interference Check in accordance with Section 5.13.1.6. The purpose of this check is to ensure the structure around the GMU did not get magnetized by the lightning event to the point of affecting magnetometer performance. 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 9 Page 3-12...
  • Page 49 TVS diodes and fuses. The power line circuit breaker must be opened prior to this check. If the GI 275 is not the only LRU on the corresponding circuit breaker, it must be disconnected from the power bus in order to perform this check.
  • Page 50 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 51 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 52 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 53 Figure 4-2 GI 275 J2751 Connector (Looking at Connector) Table 4-2 GI 275 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*...
  • Page 54 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 55 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. 9 Page 4-6...
  • Page 56 • J244/P244 50-pin male contact HD D-sub GEA 24 UNIT 011-02848-0 J243 J242 J244 J241 Figure 4-4 GEA 24/GEA 24B Connectors GEA 24 Shown, GEA 24B Similar 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 9 Page 4-7...
  • Page 57 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. 9 Page 4-8...
  • Page 58 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. 9 Page 4-9...
  • Page 59 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. 9 Page 4-10...
  • Page 60 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. 9 Page 4-11...
  • Page 61 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. 9 Page 4-12...
  • Page 62 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. 9 Page 4-13...
  • Page 63 J442/P442 6-pin rectangular connector Figure 4-12 J442/P442 Connector Table 4-10 GMU 44B J442/P442 Connector Function SHIELD GROUND RS-485 OUT B RS-485 OUT A POWER GROUND RS-232 IN MAG POWER INPUT 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 9 Page 4-14...
  • Page 64 Table 4-11 GMU 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. 9 Page 4-15...
  • Page 65 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 GEA. Table 4-12 GTP 59 3-Conductor Shielded Cable Conductor Color Name...
  • Page 66 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 67 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. 9 Page 4-18...
  • Page 68 Garmin for service 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. 9 Page 4-19...
  • Page 69 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. 9 Page 4-20...
  • Page 70 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. 9 Page 4-21...
  • Page 71 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. 9 Page 4-22...
  • Page 72 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. 9 Page 4-23...
  • Page 73 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. 9 Page 4-24...
  • Page 74 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. 9 Page 4-25...
  • Page 75 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. 9 Page 4-26...
  • Page 76 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. 9 Page 4-27...
  • Page 77 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. 9 Page 4-28...
  • Page 78 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. 9 Page 4-29...
  • Page 79 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. 9 Page 4-30...
  • Page 80 STC Maintenance reference voltage Manual Verify GI 275 and Clear autopilot Autopilot interface configuration wiring is correct 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. 9 Page 4-31...
  • Page 81 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. 9 Page 4-32...
  • Page 82 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. 9 Page 4-33...
  • Page 83 VFR GPS Antenna Re-installation..................5-27 5.10.3 VFR GPS Antenna Checkout ....................5-27 5.11 EIS Sensors............................5-28 5.11.1 Carburetor/Induction Air Temperature ..................5-29 5.11.2 Oil Temperature Sensor ......................5-30 5.11.3 Pressure Sensors ........................5-31 5.11.4 Fuel Flow..........................5-35 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 9 Page 5-1...
  • Page 84 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 85 5.1 GI 275 Figure 5-1 GI 275 Installation (Pan Head Screws) 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 9 Page 5-3...
  • Page 86 Figure 5-2 GI 275 Installation (Countersunk Screws) 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 9 Page 5-4...
  • Page 87 1. Ensure the current configuration is saved to a USB drive in accordance with the instructions in Section 2.3.4.3. 2. Power off the GI 275 and remove power. If the GI 275 is connected to a GDL 60, remove power from the GDL 60 by opening its circuit breaker.
  • Page 88 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 5-3. If replacing the configuration module on the Master display, the System ID will change and must be updated on the associated flyGarmin.com...
  • Page 89 3. If removed, seal the 1/8-27-NPT male thread fittings with MIL-S-15204 Sealing Compound (Type A or B) and connect the pitot-static lines to the unit. 4. Connect the backshell wiring connector(s) to the back of the GI 275 and tighten the retaining screws.
  • Page 90 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. 9 Page 5-8...
  • Page 91 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. 9 Page 5-9...
  • Page 92 [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 5-6 Example GEA 24/GEA 24B Installation 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 9 Page 5-10...
  • Page 93 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 94 5.4 GEA 110 Figure 5-7 GEA 110 Installation (Mounted Directly to Airframe Example) 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 9 Page 5-12...
  • Page 95 Figure 5-8 GEA 110 Installation (Mounted on a Tray Example) 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 9 Page 5-13...
  • Page 96 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 97 5.5 Backup Battery Figure 5-9 Backup Battery Installation 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 9 Page 5-15...
  • Page 98 For maximum battery longevity, store within a temperature range of -4°F to 68°F (-20°C to 20°C). The GI 275 battery should be kept partially charged when unused for longer periods of time and should not be stored when completely discharged. Charge the battery to 30% within 1 year of receipt and recharge to 30% every 2 years thereafter if the GI 275 is not in use.
  • Page 99 5.6 GSB 15 Figure 5-10 GSB 15 Cutout Installation 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 9 Page 5-17...
  • Page 100 Figure 5-11 GSB 15 Installation with Mounting Kit 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 9 Page 5-18...
  • Page 101 To re-install the GSB 15, perform the removal procedure in reverse. Torque all screws in accordance with Figure 5-10 or Figure 5-11. Torque decorative cover screws in accordance with Figure 5-12. 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 9 Page 5-19...
  • Page 102 [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 5-13 Example GMU 11 Installation 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 9 Page 5-20...
  • Page 103 To remove the GMU 11, perform the following procedure: 1. Remove power from the GI 275 directly connected to the GMU 11. If the GI 275 is connected to a GDL 60, remove power from the GDL 60 by opening its circuit breaker.
  • Page 104 5.8 GMU 44B Figure 5-14 GMU 44B Installation 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 9 Page 5-22...
  • Page 105 To remove the GMU 44B, perform the following procedure: 1. Remove power from the GI 275 directly connected to the GMU 44B. If the GI 275 is connected to a GDL 60, remove power from the GDL 60 by opening its circuit breaker.
  • Page 106 5.9 GTP 59 Figure 5-15 GTP 59 Installation (Aircraft with Metallic Skin Example) 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 9 Page 5-24...
  • Page 107 To remove the GTP 59, perform the following procedure: 1. Remove power from the GI 275 or GEA that is directly interfaced to the GTP 59. If the GI 275 or GEA is connected to a GDL 60, remove power from the GDL 60 by opening its circuit breaker.
  • Page 108 The optimal antenna position is horizontal or as close to horizontal as practical given the shape of the glareshield. Figure 5-16 VFR GPS Antenna Installation (Non-removable Installation Example) 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 9 Page 5-26...
  • Page 109 Use the following procedure to remove the VFR GPS antenna: 1. Remove power from the GI 275 connected to the VFR GPS antenna. If the GI 275 is connected to a GDL 60, remove power from the GDL 60 by opening its circuit breaker.
  • Page 110 (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 111 Figure 5-18 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. 9 Page 5-29...
  • Page 112 Section 7, Safetying, of Chapter 7, Aircraft Hardware, Control Cables and Turnbuckles, of AC 43.13-1B Aircraft Inspection and Repair. Figure 5-19 Oil Temperature Sensor Installation Example 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 9 Page 5-30...
  • Page 113 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 114 Figure 5-20 Brass Sensor Installation (Coupling Mount Example) 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 9 Page 5-32...
  • Page 115 Figure 5-21 Mil-Spec Style Sensor Installation (Housing Mount Example) 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 9 Page 5-33...
  • Page 116 SCREW, MACHINE PAN-HEAD, CROSS-RECESSED, CORROSION RES TING STEEL, MS51958- 0.190-32UNF-2A MS21919WDG9 CLAMP LOOP TYPE, CUSHIONED, SUPPORT, Ø9/16 TUBE 011-05783-XX PRESSURE SENSOR, GPT ITEM PART NUMBER DESCRIPTION Figure 5-22 GPT Sensor Installation 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 9 Page 5-34...
  • Page 117 5.11.3.1 Garmin Restrictor The Garmin restrictor may be removed for inspection and cleaning in the event of erroneous or lagging manifold pressure indications. Removal and Cleaning 1. Disconnect the tubing or hose from the Garmin restrictor fitting. 2. Remove the restrictor from the manifold pressure port.
  • Page 118 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(B)/110. The connection can be made at the magneto or the ignition switch.
  • Page 119 5.12 TVS and Fuse (Class II & III Composite Aircraft Only) This section applies to IFR Class II & III composite aircraft only. Refer to GI 275 Part 23 AML STC Installation Manual for more information. Class II & III composite aircraft require a Transient Voltage Suppressor and fuse at the main power input(s) of the GI 275.
  • Page 120 3. If the fuse does not have continuity, replace with a new fuse and re-check continuity. Then close the fuse holder by screwing the two halves of the fuse holder together. 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 9 Page 5-38...
  • Page 121 Magnetometer Calibration Procedure. An aircraft equipped with a GI 275 can be used to evaluate a candidate site for magnetic disturbances and determine whether it is a suitable location to perform the Magnetometer Calibration Procedure. The Magnetometer Calibration Procedure itself contains the logic to simultaneously survey the location for magnetic cleanliness while it is computing the magnetometer calibration parameters.
  • Page 122 5.13.1.3 Calibrate Pitch/Roll Offset This procedure must be completed on each GI 275 with an integrated ADAHRS. This procedure can be conducted for each AHRS simultaneously on each display. The aircraft must be leveled to within 0.25° of zero pitch and zero roll using the procedures in the aircraft maintenance manual or AFM/POH. The following procedures must be completed with the engine off: 1.
  • Page 123 It is recommended to run the Magnetic Interference Test using the GI 275. Alternatively, the GMU 44 Location Survey Tool and a PC can be used in lieu of the GI 275 display. Refer to AHRS/Magnetometer Installation Considerations (P/N 190-01051-00).
  • Page 124 7. Touch Done when the test sequence is completed. The GI 275 will display a test Pass or Fail, the worst-case percentage of magnetic interference, and the time stamp at which it occurred.
  • Page 125 3:40 AP engaged in a pitch and roll made (to engage servos) 3:50 AP disengaged 4:00 Pitot heat on 4:10 Pitot heat off 4:20 End of test 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 9 Page 5-43...
  • Page 126 360° (Magnetic North), or select a level and magnetically clean location and use a calibrated sight compass. 3. Power on the GI 275(s) in Configuration mode. 4. Touch Calibration/Test → Attitude/Heading → Calibrate Magnetometer.
  • Page 127 360° (Magnetic North) or select a level and magnetically clean location and use a calibrated sight compass. 2. With the GI 275 in Normal mode, press and hold the knob in to open the menu and touchSystem → Units.
  • Page 128 Displayed AHRS Standby Compass Heading (A) Heading Error (A-B) Heading or AHRS #2 Heading (B) 360° (North) 30° 60° 90°(East) 120° 150° 180°(South) 210° 240° 270°(West) 300° 330° 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 9 Page 5-46...
  • Page 129 7. Follow the on-screen commands to complete the calibration. 5.13.2 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). 5.13.3 Analog NAV Calibration If it becomes necessary to re-calibrate the Analog NAV, refer to the calibration procedure contained in Section 6 of the GI 275 installation manuals (refer to Table 1-1).
  • Page 130 The battery rundown test date is reported in UTC. To complete the backup battery test, complete the following steps: 1. Power on each GI 275 with an installed backup battery in Configuration mode. 2. Touch Calibration/Test → Backup Battery Test.
  • Page 131 This procedure is used to calibrate the GI 275 fuel quantity gauges. It begins with drained fuel tanks, then unusable fuel is added, and then fuel is added in specified quantities during the fueling process. Tank calibration takes time and cannot be interrupted once initiated.
  • Page 132 Main L tanks. The available options are dependent Main R on “Main Tank” and “Aux Tank” settings on AUX/Tip L the Fuel page. AUX/Tip R 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 9 Page 5-50...
  • Page 133 19. Fill the indicated tank with the specified amount of usable fuel using a calibrated fueling system. a. The GI 275 will calculate an estimated amount of fuel to be added based on the number of calibration points and the gauge max.
  • Page 134 Figure 5-26 Fuel Quantity Calculation Procedure NOTE It is recommended that the display configuration be saved to a USB drive immediately after the Fuel Quantity Calibration is completed. 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 9 Page 5-52...
  • Page 135 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 136 5.15 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). 5.15.1 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 137 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 5.15.2.1 or Section 5.15.2.2 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 138 Cessna 190/195 with Harpoon-Style Pitot Probe Installations of the GI 275 in a Cessna 190/195 in which the GI 275 replaces the Kollsman airspeed indicator (identifiable by a Harpoon-style pitot probe mounted on the wing) must use the Cessna 190/195 Airspeed Calibration (P/N 006-B4540-01) and must use Table 5-8.
  • Page 139 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 140 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. 9 Page 5-58...
  • Page 141 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 5-10 Advanced Airframe Specific Configuration Data – Markings POH/AFM Marking...
  • Page 142 5.15.2.3 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 5.15.2.4 Textron Aviation Inc.
  • Page 143 (0 feet), 10,000 feet, 20,000 feet, and optionally to 30,000 feet. The calibration is allowed to be finished after the 20,000 feet calibration if the aircraft operational ceiling is below 20,000 feet. CAUTION To avoid damaging the GI 275 pressure sensors, both the pitot and static ports must be connected to the test set. CAUTION Prior to performing the Calibrate Static Pressure procedure, perform a Static System Leak Test in accordance with 14 CFR Part 43 Appendix E.
  • Page 144 This check is required for units configured as a Primary ADI, Standby ADI, HSI, and MFD (with the CDI page) only if the VFR GPS is enabled and the antenna installed. 1. Power on the GI 275 system in Normal mode and verify that the aircraft has an unobstructed view of the sky (or GPS repeater coverage).
  • Page 145 If the manifold pressure appears slow to respond or is reporting an incorrect value during operation, check the Garmin restrictor fitting to ensure no foreign objects are blocking the orifice. Refer to Section 5.11.3.1 for cleaning procedure.
  • Page 146 This check only applies to standalone GI 275 EIS units with an interfaced OAT sensor. NOTE If the GI 275 EIS is interfaced to a PFD, the OAT sensor must be interfaced to that PFD and not to a GEA.
  • Page 147 If the lamp does not illuminate, inspect and/or replace the lamps and repeat the check. 4. If the annunciator(s) do not illuminate, remove power from the aircraft and inspect the wiring. 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 9 Page 5-65...
  • Page 148 MFD/Standby ADI  ADAHRS+AP  Base  ADAHRS  ADI  HSI   MFD  EIS  GI 6  MFD/Standby ADI HSI/Standby ADI  ADAHRS+AP GI 275 Part 23 AML STC Maintenance Manual 190-02246-11 Rev. 9 Page A-1...
  • Page 149 011-00978- VFR GPS Antenna 011-04036- GEA 24(B) #1 011-02848- GEA 24(B) #2 011-02848- GEA 110 #1 011-03454- GEA 110 #2 011-03454- Backup Battery 011-04528- GSB 15 011-04937- 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 9 Page A-2...
  • Page 150 GMU 44B #1 GMU 44B #2 GTP 59 #1 GTP 59 #2 GEA 24(B) #1 GEA 24(B) #2 GEA 110 #1 GEA 110 #2 Restrictor Backup Batt GSB 15 GI 275 Part 23 AML STC Maintenance Manual 190-02246-11 Rev. 9 Page A-3...
  • Page 151 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. 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 9 Page A-4...
  • Page 152 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. 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 9 Page A-5...
  • Page 153 A.6 Wire Routing - Jet The following diagram depicts the wire routing for the GI 275 LRUs throughout the aircraft structure for a jet aircraft. 190-02246-11 GI 275 Part 23 AML STC Maintenance Manual Rev. 9 Page A-6...
  • Page 154 A.7 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 2.3.4.3. It is recommended that the USB drive be taped or otherwise secured to this page in the location marked below.