Garmin GFC 600H Maintenance Manual
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Garmin GFC 600H Maintenance Manual

Garmin GFC 600H Maintenance Manual

Helicopter flight control system
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GFC 600H
Helicopter Flight Control System
Part 27 STC
Maintenance Manual
Contains Instructions for Continued Airworthiness
Rotorcraft Make, Model, Registration Number, and Serial Number and
accompanying STC configuration information in Appendix A must be
completed and retained with rotorcraft permanent records.
190-02081-03
January 2023
Revision 3

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Summary of Contents for Garmin GFC 600H

  • Page 1 GFC 600H Helicopter Flight Control System Part 27 STC Maintenance Manual Contains Instructions for Continued Airworthiness Rotorcraft Make, Model, Registration Number, and Serial Number and accompanying STC configuration information in Appendix A must be completed and retained with rotorcraft 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...
  • Page 3 Software License Agreement (hereinafter the "Agreement") and is subject to the following terms and conditions which are agreed to by 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. Garmin and Licensee may be referred to individually as a "Party"...
  • Page 4 Garmin be liable to licensee for an amount in excess of USD $100, or be liable in any amount for any special, incidental, consequential, punitive or indirect damages, loss of goodwill or profits, liquidated damages, data loss,...
  • Page 5 Assignment. Licensee may not assign this Agreement or any of its rights, interests or obligations hereunder without the prior written consent of Garmin. Any purported assignment in violation of this Section 6.3 shall be null and void. Subject to the foregoing, this Agreement shall be binding upon and shall inure to the benefit of the Parties and their respective successors and permitted assigns and transferees.
  • Page 6 Minor change to update Collective Position Sensor adjustment. Change Description Section Description of Change Updated statement to be compliant with FAA regulations. Updated Figure 6-18 Collective Position Sensor Adjustment with improved rigging instructions. 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page v...
  • Page 7 All information depicted in screen shots, including software file names, versions, and part numbers, is subject to change and may not be up to date. 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page vi...

  • Page 8: Table Of Contents

    GFS 83 Servos ...........................7-3 Collective Position Sensor ......................7-5 GSU 75H ADAHRS ........................7-6 GRS 79H AHRS ........................7-8 GMU 44( ) Magnetometer ......................7-8 Post-Installation Calibration ......................7-9 GFC 600H System Configuration ...................7-21 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page vii...
  • Page 9 Configuration Mode Functional Checkout ................8-2 Normal Mode Functional Checkout ..................8-3 APPENDIX A INSTALLATION-SPECIFIC INFORMATION ............A-1 A.1 General Installation Information ....................A-2 A.2 Interfaced Equipment .......................A-3 A.3 Configuration Log ........................A-5 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page viii...
  • Page 10 Figure 6-16 GTP 59 OAT Probe Installation ..................6-29 Figure 6-17 Collective Position Sensor ....................6-32 Figure 6-18 Collective Position Sensor Adjustment ................6-33 Figure 6-19 GMC 605H Configuration Module Installation ..............6-35 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page ix...
  • Page 11 Figure 6-20 GRS 79H or GSU 75H Configuration Module Installation ..........6-36 Figure 7-1 Rotorcraft Position Example ....................7-15 Figure 8-1 Audio Test Page ........................8-2 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page x...
  • Page 12 Table 7-2 Post-Installation Calibrations ....................7-10 Table 7-3 Magnetic Interference Test Sequence Example ..............7-13 Table 7-4 Heading Verification ......................7-18 Table A-1 Garmin Equipment ........................A-3 Table A-2 Other Equipment ........................A-4 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page xi...
  • Page 13 1 INTRODUCTION Purpose..............................1-2 Scope..............................1-2 Applicability .............................1-2 Revision and Distribution .........................1-2 Terminology............................1-3 Reference Documents ........................1-5 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 1-1...

  • Page 14: Purpose

    1.1 Purpose This document is designed for use by the installing agency of the Garmin GFC 600H Flight Control System (FCS) as a Maintenance Manual (MM) and Instructions for Continued Airworthiness (ICA) to satisfy the requirements for continued airworthiness as defined by 14 CFR Part 27.1529 and 14 CFR Part 27 Appendix A.

  • Page 15: Terminology

    FCS: Flight Control System LOC: Localizer FD: Flight Director LRU: Line Replaceable Unit FPGA: Field Programmable Gate Array LVDT: Linear Variable Differential Transformer FPM: Flight Path Marker LVL: Level Mode 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 1-3...
  • Page 16 VOR: VHF Omni Directional Radio Range RFMS: Rotorcraft Flight Manual Supplement VS: Vertical Speed SAS: Stability Augmentation System WAAS: Wide Area Augmentation System SBAS: Satellite Based Augmentation System 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 1-4...

  • Page 17: Reference Documents

    In addition to this manual, the following documents are recommended for performing maintenance on the GFC 600H FCS. 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 GFC 600H FCS.

  • Page 18: System Description

    Helicopter Electronic Stability and Protection (H-ESP) ............2-4 2.2.3 Flight Director Modes ........................2-5 2.2.4 GMC 605H AFCS Mode Controller ..................2-7 2.2.5 GFS 83 Force Trim Servo ......................2-9 2.2.6 Sensors .............................2-11 Power Requirements ........................2-16 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 2-1...

  • Page 19: Gfc 600H Flight Control System Functions

    2.1 GFC 600H Flight Control System Functions The GFC 600H FCS is a 2-axis flight control system with an optional 3rd axis (Yaw). The GFC 600H utilizes a parallel servo installed in each control axis to provide force trim, attitude hold, and autopilot functions as follows.

  • Page 20: System Overview

    If the pilot pushes on the controls such that the system detects that the pilot is hands-on, an out of detent annunciation is displayed on the GMC 605H and Garmin GDU to indicate that the system is not able to maintain its control objective because the pilot is hands-on.

  • Page 21: Helicopter Electronic Stability And Protection (H-Esp)

    • Level Mode - The GFC 600H system provides an automated leveling function. This H-ESP function differs from others in that it does not require air data for operation, and it is pilot activated. Pressing the dedicated LVL key or optionally installed LVL mode switch on the cyclic will result in engagement of the system to a level attitude.

  • Page 22: Flight Director Modes

    Over-Speed Protection is indicated with aural and visual caution alerts. Yaw Control (Optional) - The yaw axis is an optional installation option for the GFC 600H system. The yaw axis provides a number of benefits in both cruise and hover. In cruise, the yaw control provides yaw damping functionality.

  • Page 23: Figure 2-1 System Function Diagram

    The block diagram shown in Figure 2-1 illustrates the high-level system interconnectivity. The following sections will provide an overview of the system components. Figure 2-1 System Function Diagram 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 2-6...

  • Page 24: Figure 2-2 Gmc 605H Mode Controller

    GMC 605H. The GMC 605H AHRS utilizes the same aiding sources that are provided to the primary AHRS sensor. The GFC 600H system requires a minimum of one GPS, air data, and magnetometer interface to the GMC 605H for improved AHRS performance.

  • Page 25: Figure 2-3 Gmc 605H System Interface Overview

    Alert Audio Output • Twenty-six Discrete Inputs • Four Discrete Outputs • Six Analog Inputs • Three Analog Outputs • Three RS-485 I/O buses • Two CAN I/O buses 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 2-8...

  • Page 26: Gfs 83 Force Trim Servo

    GFS 83 Force Trim Servo The GFC 600H system utilizes two variants of the GFS 83 servo. The pitch and roll servo is a brushless motor with a geared drive and shear fuse mechanism from the output shaft to the arm. With this design, the motor is back-driven while the servo is powered.

  • Page 27: Figure 2-4 Gfs 83 Servo (-11 Variant)

    When the aircraft is in trim, forces are minimized. The GFS 83 also works as an autopilot and provides automated control functions within the GFC 600H system. The GFS 83 contains a brushless DC motor that requires software commutation to operate. The servo runs application software appropriate to the axis that it is installed in.

  • Page 28: Table 2-1 Servo Program Pins And Configuration

    Primary AHRS This STC provides instructions to install either the GRS 79H or GSU 75H sensor. The GFC 600H system requires one of the attitude sensors to be a GRS 79H or GSU 75H. These sensors are interfaced directly to the GFS 83 servos over a CAN bus interface.

  • Page 29: Figure 2-6 Gsu 75H, Gmu 44, Gmu 44B, And Gtp 59 Sensors

    2.2.6.2 Air Data The GFC 600H requires one air data source for AHRS aiding and air data thresholds for various flight control modes. GMC 605H can share a common air data source with the G500 Flight Display system. The following air data sources are approved under this STC: •...

  • Page 30: Figure 2-8 Gtp 59 Oat Probe

    RS-232 AHRS Inputs/Outputs from Garmin GPS source • One CAN Bus • PPS Inputs • Discrete Inputs • Two System ID Program pins • Two Aircraft Power Inputs 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 2-13...

  • Page 31: Figure 2-9 Gmu 44 And Gmu 44B Magnetometers

    FCS will utilize data from the ADC to independently calculate variable V for overspeed and limit cue functionality. When installed with the G500H flight display system, the GFC 600H will provide the variable V to the display and the tape will update accordingly. This functionality requires V and V power off offsets to be configured within the display system.

  • Page 32: Figure 2-10 Collective Position Sensor

    The GFC 600H system uses GPS for AHRS aiding and groundspeed hold functionality. 2.2.6.7 Collective Position Sensor The GFC 600H system includes a string pot for measuring collective position. The sensor aids the system by measuring collective displacement and impacts the following functionality: •...

  • Page 33: Power Requirements

    2.3 Power Requirements The GFC 600H system requires an operational voltage of 28 VDC. Refer to the individual Environmental Qualification Forms for details on surge ratings and minimum/maximum operating voltages. Current draw of each LRU is summarized in Table 2-2.

  • Page 34: Control And Operation

    Refer to GFC 600H Pilot's Guide (P/N 190-02081-04) and Rotorcraft Flight Manual Supplement GFC 600H Helicopter Flight Control System Installed in Airbus Helicopters AS350 B2 / B3 (P/N 190-02081-02) for a full description of the control and operation information of the GFC 600H system in Normal mode.

  • Page 35: Gmc 605H Mode Controller

    Upon selection of the IAS mode, ALTS will automatically arm if there is a valid preselected altitude on the GDU. Indicated airspeed hold is the default pitch mode for the GFC 600H system. If APR is selected, and the vertical deviation indication is beyond the threshold to capture the GP or GS guidance, IAS will become the active mode with GP or GS as the armed mode.

  • Page 36: Figure 3-1 Gmc 605H Normal Mode Operation

    Active vertical modes (with units when available) Armed vertical modes (with units when available) 3-Color LED for Flight Control System engagement, advisory, and failure indication System messages 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 3-3...

  • Page 37: Figure 3-2 Fcs Switches

    3.1.1.3 Pilot Control Switches GFC 600H system utilizes controls located on the cyclic grip to provide inputs to the flight control system. A summary of the switch functions is provided in Table 3-3. Table 3-3 GFC 600H Switch Function Label...

  • Page 38: Figure 3-3 Yaw Switch

    Figure 3-3 Yaw Switch (May be located in alternate location) 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 3-5...

  • Page 39: Garmin Displays (G500H Installations)

    NOTE The following section is only applicable for installations with Garmin displays (G500H). Figure 3-4 depicts visual alerts and annunciations that are seen with a Garmin GDU. Figure 3-4 G500H Alerts and Annunciations Layout Table 3-4 Description of GDU FCS Annunciation Bar...
  • Page 40 Low Speed Protection (flashing)* Active Overspeed Protection (flashing)* Active FCS DATA NNO FCS DATA * Low/Max speed protection alerts will display next to the Vertical Mode Annunciation box. 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 3-7...
  • Page 41 (will display as Active Lat and/ Decoupled, or Vert mode with valid GPS Groundspeed Hold and groundspeed below the Mode hover transition threshold.) 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 3-8...
  • Page 42 XXX represents any valid active vertical mode, or may be blank 8. Second Armed Vertical Mode Not Engaged (Not present) Approach * XXX represents any valid active (green) and armed (white) vertical mode 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 3-9...

  • Page 43: Gmc 605H Configuration Mode

    The VS key is also used to accept the desired selections. • To exit Configuration mode, cycle power to the GFC 600H FCS. Figure 3-5 and Table 3-5 summarizes the configuration mode navigation key functions. Figure 3-5 GMC 605H Configuration Mode Navigation...

  • Page 44: Figure 3-6 Gmc 605H Configuration Mode Layout

    Displays the data for the selected PAGE DATA page Micro-USB port for software loading USB Port and downloading system fault logs. 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 3-11...

  • Page 45: Figure 3-7 Gmc 605H Configuration Mode Map

    *Not used under this STC Figure 3-7 GMC 605H Configuration Mode Map 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 3-12...

  • Page 46: Software Loading

    2. Run the software image executable, loading the software to a USB flash drive. 3. Verify that there is no electrical power to GFC 600H system by pulling the FCS circuit breaker. 4. Connect the USB flash drive to the GMC 605H using a USB adapter cable (P/N 320-00726-01).

  • Page 47: Figure 3-8 Gdu Configuration Mode Home Screen

    STC Equipment List (Garmin P/N 005-01095-01). NOTE A Garmin GDU 620 or GDU TXi can be used to update the necessary configuration and software for the GSU 75H, GRS 79H, and GMU 44( ). This manual includes instructions for completing the configuration using a GDU TXi.

  • Page 48: Figure 3-9 System Management Page

    Only LRUs that are configured in the system and currently online will be selectable for software updates. 6. Select the Update button. 7. Follow the on-screen display instructions. 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 3-15...
  • Page 49 The Duration button selects log entry by duration in minutes. 6. Press Download to SD Card. A dialog box will annunciate that the download is complete and the SD card can be removed. 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 3-16...

  • Page 50: Instructions For Continued Airworthiness

    Magnetic Field Updates ........................4-8 Servo Arm Torque Check .........................4-9 This section provides Instructions for Continued Airworthiness of the GFC 600H FCS as installed under STC SR02647SE and satisfies the requirements for continued airworthiness as defined by 14 CFR Part 27.1529 and Part 27 Appendix A.

  • Page 52: Servicing Information

    4.2 Servicing Information Servicing of the GFC 600H FCS equipment is 'on condition'. In the event of system or LRU failure, troubleshoot the GFC 600H FCS in accordance with Section 1. Refer to Section 1 for equipment removal and installation. No component-level overhaul is required.

  • Page 53: Specialty Tools

    Specialty Tools Required None. Optional Shaft Locking Device, Garmin P/N 117-01307-00 is recommended. The tool is used with the clutchless GFS 83 servo variant to hold the hub when adjusting friction. 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev.

  • Page 54: Maintenance Intervals

    After equipment removal and/or replacement per Section 6.2. Display or FCS status LED Display or status are inoperative, remove and On condition. LED inoperative replace GMC 605H. 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 4-5...

  • Page 55: Visual Inspection

    Garmin for repair if knobs or buttons are missing or damaged. Verify operation and markings of cyclic and collective mounted switches. 6. For every GFS 83 servo, GMC 605H, GRS 79H or GSU 75H, GMU 44( ), and GFC 600H interfaced equipment, inspect wiring, shield terminations, routing, overbraid, and connectors for chafing, deterioration, damage, or wear.
  • Page 56 Magnetic Interference Check in accordance with Section 7.7.2. Perform a GMC 605H and GSU 75H Magnetometer Calibration in accordance with Section 7.7.3 and Section 7.7.4. 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 4-7...

  • Page 57: Electrical Bonding Check

    Aviation Database maintenance. A service bulletin containing the updated magnetic field model and instructions for installation can be obtained from the dealer resource center or by contacting Garmin. 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev.

  • Page 58: Servo Arm Torque Check

    2. Remove the servo output arm shear fuse in accordance with Section 6.2.3. 3. Lock the servo output shaft with the Shaft Locking Device (Garmin P/N 117-01307-00). 4. Select a calibrated torque wrench with ¼ inch drive, and set the torque to 40 in-lbf.

  • Page 59: Figure 4-1 Armature Installation (P/N 011-03367-11)

    Belleville washers must be properly stacked, and torque need not exceed 75 in-lb. This helps cotter pin installation at the end of the procedure. Figure 4-1 Armature Installation (P/N 011-03367-11) 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 4-10...
  • Page 60 The torque is in range if the computed average is between 40 and 44 in-lbf. 11. Align the output hub and armature as shown in Figure 4-2 and install the shear fuse. Garmin P/N 117-01307-00 shaft locking device (optional) or an open ended wrench can be used to help align arm with the hub.

  • Page 61: Figure 4-2 Shear Fuse Installation

    Figure 4-2 Shear Fuse Installation 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 4-12...

  • Page 62: Troubleshooting

    When troubleshooting the GFC 600H FCS, refer to wire routing diagrams, plug and pin descriptions, communication port settings saved in the configuration data, and equipment locations retained in Appendix A of this document.

  • Page 63: General Troubleshooting

    Section 1. If any system messages persist after performing the associated troubleshooting actions, contact Garmin for service. NOTE For cycling power of the GFC 600H system, wait until the display has completely turned off prior to re-energizing the system. Table 5-1 General Troubleshooting Guide...
  • Page 64 • Reload software and ensure there are no software failures. show any status in Normal mode and the system will not • Contact Garmin if issue persists. engage 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 5-3...

  • Page 65: Gmc 605H Mode Controller

    Annunciated Possible Cause Corrective Action Fault • Power cycle the GFC 600H FCS by cycling • FCS DISC and/or FTR switch the FCS circuit breaker. to the GMC 605H and GFS • Ensure the GMC 605H, GFS 83, GSU 75H...
  • Page 66 GMC 605H, GFS 83, and GSU 75H/ GMU 44( ). • Power cycle the GFC 600H FCS by cycling the FCS circuit breaker. • Loss of attitude data • Ensure the GMC 605H, GFS 83, GSU 75H,...
  • Page 67 Annunciated Possible Cause Corrective Action Fault • Power cycle the GFC 600H FCS by cycling the FCS circuit breaker. • Ensure the GMC 605H, GFS 83 (Yaw Servo), GSU 75H and GMU 44( ) connectors are securely mated to the units.

  • Page 68: Table 5-4 Gmc 605H Configuration Mode (Post-Install Procedures) Test Faults

    Table 5-4 GMC 605H Configuration Mode (Post-Install Procedures) Test Faults Annunciated Fault Possible Cause Corrective Action • Power cycle the GFC 600H FCS by cycling the FCS circuit breaker. Data communications failure: GMC TEST FAILED: • Ensure the GMC 605H, GFS 83,...
  • Page 69 • Ensure that the configuration settings MEASUREMENT sensor data. match those retained with the rotorcraft FAILURE records (Appendix A). • Power cycle the GFC 600H FCS by TEST FAILED: GPS The GMC is not receiving GPS cycling the FCS circuit breaker. MEASUREMENT data.
  • Page 70 Refer to TOO LARGE Section 7.7 for required post-install • SITE DOESN’T procedures. HAVE UNIFORM MAGNETIC FIELD • SITE MAG FIELD DIFFERENT FROM IGRF MODEL 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 5-9...

  • Page 71: Grs 79H Or Gsu 75H Adahrs And Gmu 44( ) Magnetometer

    5.3 GRS 79H or GSU 75H ADAHRS and GMU 44( ) Magnetometer For troubleshooting any AHRS/ADC faults in installations with a Garmin G500H system (GDU 620 or TXi), see prior installation data approval for the specific corrective actions. Table 5-5 describes possible symptoms associated with the Garmin Standalone AHRS/ADC Installation Tool and provides corresponding actions for troubleshooting.

  • Page 72: Table 5-7 Post-Install Procedures Troubleshooting

    GPS and Magnetometer Timeout occurred AHRS did not reply complete for (green check). while completing the test/procedure before timeout. <procedure name> • Cycle power to unit and retry procedure. 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 5-11...
  • Page 73 • Sensor measurement not unobstructed clear view of the sky and available the navigator has acquired a valid signal. • Ensure the calibrations are being performed in the order specified. 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 5-12...

  • Page 74: Table 5-8 Upload And Download Troubleshooting

    AHRS AHRS orientation not selected • Ensure configuration settings match the Orientation. Please in AHRS Configuration Settings aircraft permanent records. select valid AHRS orientation and try again. 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 5-13...

  • Page 75: Connectors

    This section contains connector information and description of pin functions for all LRUs that can be installed as part of the GFC 600H STC. Refer to the LRU TSO installation manuals for more detailed signal information on each LRU. All D-Sub connectors follow a similar pin numbering scheme as shown below.

  • Page 76: Table 5-9 P6051 Connector Pinout

    CONFIG DISC IN 18 RS-485 3A CONFIG DISC IN 2 CONFIG DISC IN 4 CONFIG DISC IN 11 CONFIG DISC IN 6 RESERVED RS-485 1A CAN LO 2 RS-485 1B 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 5-15...

  • Page 77: Table 5-10 P6052 Connector Pinout

    LIGHTING BUS LO ANALOG 2 IN X SIGNAL GROUND ANALOG 1 IN Z SIGNAL GROUND ANALOG 1 IN Y ETHERNET OUT 3B ANALOG 1 IN X * Indicates Active-Low 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 5-16...

  • Page 78: Figure 5-3 Gfs 83 P831-P/R/Y Connector

    The GFS 83 reads the states of these lines once, at power-up, to determine the required servo functionality. The servo will not read the strap or pass functional checks until the strapping configuration is saved in configuration. 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 5-17...

  • Page 79: Figure 5-4 Gsu 75H J751 Connector

    Note that the GTP 59 OAT Probe does not have a connector shown since it is pinned directly into the GSU 75H connector. Figure 5-4 GSU 75H J751 Connector (View looking back at GSU 75H) 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 5-18...

  • Page 80: Table 5-12 J751 Connector Pinout

    CAN TERM DISCRETE IN 4 RESERVED DISCRETE IN 2* * Indicates Active-Low ** Both pin numbers are functionally equivalent and are internally connected within the GSU 75. 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 5-19...

  • Page 81: Figure 5-5 Gsu 79H J791 Connector

    Kit P/N Conn, HiDen D-Sub, Mil Crp, Sealed P791 330-00776-78 011-03109-00 w/GND indents, 78 ckt Figure 5-5 GSU 79H J791 Connector (View looking at back of GSU 79H) 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 5-20...

  • Page 82: Table 5-13 J791 Connector Pinout

    DISCRETE IN 3* CAN TERM DISCRETE IN 4 RESERVED DISCRETE IN 2* *Indicates Active-Low ** Both pin numbers are functionally equivalent and are internally connected within the GRS 79H. 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 5-21...

  • Page 83: Figure 5-6 Gmu 44 J441 Pigtail Connector

    Figure 5-6 GMU 44 J441 Pigtail Connector Table 5-14 J441 Connector Pinout Function SIGNAL GROUND RS-485 OUT B SIGNAL GROUND RS-485 OUT A SPARE POWER GROUND SPARE RS-232 IN +12 VDC POWER 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 5-22...

  • Page 84: Figure 5-7 Gmu 44B Connector

    011-04205-00 Figure 5-7 GMU 44B Connector Table 5-15 J442 Connector Pinout Function SHIELD GROUND RS-422 OUT B RS-422 OUT A POWER GROUND RS-232 IN MAG POWER INPUT 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 5-23...

  • Page 85: Figure 5-8 Collective Position Sensor P6053 Connector

    Conn Kit, String Pot, Sub-Assy (FAA-PMA) 011-05126-00 330-01430-01 Figure 5-8 Collective Position Sensor P6053 Connector Table 5-16 P6053 Connector Pinout Function NOT USED V_OUT V_IN SHIELD GROUND NOT USED 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 5-24...

  • Page 86: Equipment Removal And Re-Installation

    Any self-locking nuts are for one time use only and must be replaced if removed. Locations of the servos, LRUs, and sensors in the GFC 600H FCS system as installed in Airbus Helicopters AS 350 B2/B3 are shown in Figure 6-1.

  • Page 87: Figure 6-1 Location Of Gfc 600H System Components

    Figure 6-1 Location of GFC 600H System Components 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 6-2...

  • Page 88: Gmc 605H Mode Controller

    Removal and re-installation of the same GMC 605H (no change to serial number) without moving the mounting rack does not require calibration. Figure 6-2 GMC 605H Installation 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 6-3...
  • Page 89 Removal 1. Remove power from the GFC 600H FCS by pulling the FCS circuit breaker. 2. Insert a 3/32" hex drive tool into the access hole at the bottom of the face of the GMC 605H. 3. Turn the hex drive tool counterclockwise until the hex drive tool stops.

  • Page 90: Gfs 83 Servo

    Two variants of the GFS 83 servo are used in GFC 600H FCS installation in Airbus Helicopters AS 350. Clutched servo is used to control yaw axis and clutchless servos are used to control pitch and roll axis.

  • Page 91: Figure 6-3 Gfs 83 Pitch And Roll Servo Installation

    Figure 6-3 GFS 83 Pitch and Roll Servo Installation 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 6-6...

  • Page 92: Table 6-2 Bom For Yaw Servo Installation

    117-01021-02 SPACER, Ø5/16 ROD END BEARING, 6MM BOLT 117-01021-01 BUSHING, Ø5/16 ROD END BEARING, 6MM BOLT 117-01020-03 ASSEMBLY, ROD, YAW CONTROL, GFC 600H, AIRBUS H125 015-02907-00 BRACKET, YAW SERVO, AIRBUS H125, FAA-PMA 011-03505-04 ATTACHMENT KIT, 2.00 IN ARM, GFS 83...

  • Page 93: Figure 6-4 Gfs 83 Yaw Servo Installation

    Figure 6-4 GFS 83 Yaw Servo Installation 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 6-8...

  • Page 94: Servo Control Push-Rod Linkage

    GFS 83 servos can be removed. NOTE For the GFS 83 Roll-Axis servo arm (1.5 inch servo output arm, Garmin P/N 011-04559-02), there may not be enough clearance between the servo and output arm to remove the bolt connecting the control push-rod to the output arm.
  • Page 95 2. Attach the control push-rod end to the servo output arm. 3. Attach the control push-rod end to the rotorcraft control linkage. 4. Proceed to Figure 7.2 for the GFS 83 configuration and checkout procedures. 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 6-10...

  • Page 96: Figure 6-5 Pitch Control Push-Rod Adjustment

    Figure 6-5 Pitch Control Push-Rod Adjustment 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 6-11...

  • Page 97: Figure 6-6 Roll Control Push-Rod Adjustment

    Figure 6-6 Roll Control Push-Rod Adjustment 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 6-12...

  • Page 98: Figure 6-7 Yaw Control Push-Rod Adjustment

    Figure 6-7 Yaw Control Push-Rod Adjustment 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 6-13...

  • Page 99: Servo

    Removal 1. If necessary, remove power from the GFC 600H FCS by pulling the FCS circuit breaker and gain access to the roll, pitch, or yaw servo. 2. Disconnect the servo connectors J831-P, J831-R, or J831-Y from the servo.

  • Page 100: Shear Fuse

    2. Align fastener holes in the shear fuse with threaded holes in servo arm and the hub. 3. Install retaining screws and torque as specified in Figure 6-8. 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 6-15...

  • Page 101: Figure 6-8 Pitch And Roll Clutchless Servo Output Arm And Shear Fuse Installation

    Figure 6-8 Pitch and Roll Clutchless Servo Output Arm and Shear Fuse Installation 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 6-16...

  • Page 102: Figure 6-9 Yaw Clutched Servo Output Arm And Shear Fuse Installation

    Figure 6-9 Yaw Clutched Servo Output Arm and Shear Fuse Installation 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 6-17...
  • Page 103 3. Ensure the spring washers are stacked as illustrated in Figure 6-8 and/or Figure 6-9 and slide them on the servo shaft. 4. Hand tighten the castellated nut. 5. Lock the servo output shaft with the Shaft Locking Device (Garmin P/N 117-01307-00). 6. Set the arm friction in accordance with Figure 4.7. RESET PROCEDURE...

  • Page 104: Gsu 75H Adahrs

    (re)moved or had the fasteners loosened. Removal and re-installation of the same GSU 75H unit only (same serial number) without disturbing the mounting rack or support shelf, does not require recalibration. Figure 6-10 GSU 75H Installation 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 6-19...
  • Page 105 7. Connect pitot and static lines. Refer to Figure 6-11 for details. 8. Connect the GSU 75H connector (J751). 9. Configure and checkout the GSU 75H following procedures detailed in Figure 7.4. 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 6-20...

  • Page 106: Figure 6-11 Pitot And Static Connections

    Figure 6-11 Pitot and Static Connections 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 6-21...

  • Page 107: Grs 79H Ahrs

    (re)moved or had the fasteners loosened. Removal and re-installation of the same GRS 79H unit only (same serial number) without disturbing the mounting rack or support shelf, does not require recalibration. Figure 6-12 GRS 79H Installation 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 6-22...
  • Page 108 5. Inspect the connector and pins for signs of damage. Repair any damage. 6. Connect the GRS 79H connector (J791). 7. Configure and checkout the GRS 79H following procedures detailed in Section 7.4. 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 6-23...

  • Page 109: Gmu 44( ) Magnetometer

    The GMU 44( ) is installed on frame bearing 5 in the rotorcraft tail boom. It is mounted on top of existing flux valve support or using a universal mount (Garmin P/N 011-01779-01). Figure 6-13 and Figure 6-14 show mounting of the GMU 44. The GMU 44B’s location is identical and its installation details are shown in Figure 6-15.

  • Page 110: Figure 6-13 Gmu 44 Installation On (Existing) Flux Valve Support

    Figure 6-13 GMU 44 Installation on (Existing) Flux Valve Support (GMU 44 shown, GMU 44B similar) 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 6-25...

  • Page 111: Figure 6-14 Gmu 44 Installation With Universal Mount

    Figure 6-14 GMU 44 Installation with Universal Mount (GMU 44 shown, GMU 44B similar) 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 6-26...

  • Page 112: Figure 6-15 Gmu 44B Installation

    Figure 6-15 GMU 44B Installation 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 6-27...
  • Page 113 Removal 1. Remove power from the GFC 600H FCS and GSU 75H by pulling the FCS and ADAHRS circuit breakers. 2. Gain access to the GMU 44( ). 3. Disconnect GMU 44( ) circular connector (J441/J442). 4. Remove the three brass screws attaching the GMU 44( ) to install rack and remove the unit.

  • Page 114: Gtp 59 Oat Probe

    6.6 GTP 59 OAT Probe Figure 6-16 GTP 59 OAT Probe Installation 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 6-29...
  • Page 115 (new equipment) of the GTP 59. 1. Apply power to GSU 75H. 2. Using the Garmin Standalone AHRS/ADC Installation Tool (P/N 006-A0494-00), verify that the correct units (Celsius or Fahrenheit) and temperature reference (SAT, TAT, ISA) are displayed for Air Data following procedures detailed in Figure 7.4.

  • Page 116: Collective Position Sensor

    Likewise, do not pull the steel cable beyond its maximum extension length of 2 inch limit, as it will damage the sensor. Tension must be maintained on the cable at all times. NOTE See the GMC 605 Installation Manual (Garmin P/N 190-01488-01) for the collective position sensor wiring details. NOTE Removal, re-installation, or replacement of the collective position sensor requires sensor calibration (for range of motion).

  • Page 117: Figure 6-17 Collective Position Sensor

    Figure 6-17 Collective Position Sensor 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 6-32...

  • Page 118: Figure 6-18 Collective Position Sensor Adjustment

    Figure 6-18 Collective Position Sensor Adjustment 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 6-33...
  • Page 119 Refer to Figure 6-17 and Figure 6-18 for sensor installation and adjustment details. Removal 1. Remove power from the GFC 600H FCS by pulling the FCS circuit breaker. 2. Gain access to the collective position sensor. 3. Disconnect the sensor connector.

  • Page 120: Configuration Module Replacement

    Figure 6-19 GMC 605H Configuration Module Installation All item numbers in this procedure reference Figure 6-19. 1. Remove power from the GFC 600H FCS by pulling the FCS circuit breaker and remove the GMC 605H per Figure 6-1. 2. Disconnect the J6052 connector from the GMC 605H backplate by removing the two screws.

  • Page 121: Grs 79H Or Gsu 75H Remote Adahrs

    9. Install new configuration module in connector backshell (item 6) and re-install cover (item 7). 10. Reattach to the J7501 connector to the GSU 75H unit. 11. Configure and checkout the GSU 75H following the procedure detailed in Section 1. 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 6-36...

  • Page 122: Configuration And Checkout

    Run-Up Vibration Check (GSU 75H OR GRS 79H Only)............7-20 GFC 600H System Configuration....................7-21 This section details the procedures that must be performed to configure and checkout the GFC 600H equipment after it was re-installed (original equipment) or replaced (repaired/exchanged/new equipment).

  • Page 123: Gmc 605H Mode Controller

    (Appendix A) and the internal AHRS must be recalibrated. Verify the installed software versions match the rotorcraft permanent records. 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 7-2...

  • Page 124: Gfs 83 Servos

    073188 for pitch & roll rigging and pre-mod 076602 for tail rotor rigging in accordance with Airbus AS350 B2/B3 Aircraft Maintenance Manual 67-10-00. Method B uses control axis rigging 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 7-3...
  • Page 125 DO NOT select the START calibration menu selection. This will invalidate the servo's range calibration using this method and the unit must be returned to Garmin for reset. 6. Using the scroll wheel, highlight SAVE STRAP and press the VS key.

  • Page 126: Collective Position Sensor

    Move the collective lever to full up position; the GMC 605H should display “COLL: 100%”. b. Move the collective lever to full down position; the GMC 605H should display “COLL: 00%”. Continue to Section 1 for pre-flight and functional check of the GFC 600H FCS. 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev.

  • Page 127: Gsu 75H Adahrs

    NOT removed or loosened; otherwise, the GSU 75H AHRS must be calibrated in accordance with Section 7.7. Perform engine run-up in accordance with Section 7.7.7. For installations with a Garmin display (GDU), use the software and configuration loading procedures specific to the Garmin GDU.

  • Page 128: Table 7-1 Airspeed Test Points

    Part 43 Appendix E, except 14 CFR Part 43 Appendix E, paragraph (b)(1) (iv) (Friction) and (vi) (Barometric Scale Error) are not applicable to the GDU 700/1060 due to the digital display. 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 7-7...

  • Page 129: Grs 79H Ahrs

    If a new, repaired, or exchanged GMU 44( ) is installed, the software as documented in the rotorcraft permanent records (Appendix A) must be loaded. For installations with a Garmin display (GDU), use the software loading procedures specific to the Garmin GDU.

  • Page 130: Post-Installation Calibration

    7.7 Post-Installation Calibration The following post-installation calibration procedures must be performed prior to operation of the GFC 600H system after the mechanical and electrical installation of the GMC 605H, GSU 75H, and GMU 44. NOTE Mounting rack(s) and support shelves must not be adjusted if GMC 605H, GSU 75H, or GMU 44( ) unit is removed and replaced after it is calibrated;...

  • Page 131: Table 7-2 Post-Installation Calibrations

    [1] If it is determined that a Heading Offset Calibration should be performed, a Heading Accuracy Check (i.e., Compass Swing Test) must be performed in accordance with Section 7.7.4 prior to the Heading Offset Calibration. 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 7-10...

  • Page 132: Pitch / Roll Offset Compensation

    It is best practice to calibrate all sources of AHRS in the cockpit when performing this system alignment calibration. It is required to calibrate all GFC 600H sources of attitude data when performing a Pitch/roll Offset Calibration (i.e. calibrate the GMC 605H and GSU 75H or GRS 79H at the same time).

  • Page 133: Magnetic Interference Test (Performed With Gdu)

    NOTE The second item on the checklist instructs the operator to have the magnetic interference test procedure for the aircraft available. This sequence is listed in Garmin document AHRS/ Magnetometer Installation Considerations (P/N 190-01051-00). 4. Select Test to start the procedure.

  • Page 134: Table 7-3 Magnetic Interference Test Sequence Example

    03:50 End of Test Refer to Section 5.3 for troubleshooting. If issues persist, perform the magnetometer site evaluation check. After the troubleshooting steps have been completed, contact Garmin Support for assistance. 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev.

  • Page 135: Magnetometer Calibration

    To avoid too many stations, turn to the next 30° station when the countdown restarts before completing the previous countdown more than once per heading. 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 7-14...
  • Page 136 While the aircraft is hovering, make a heading change of approximately 30° to the right (i.e., clockwise). b. After turning by approximately 30°, the aircraft should be set back down on the ground. 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 7-15...
  • Page 137 (20) stations is allowed for the entire calibration procedure. If too many countdown restarts are encountered, the calibration will fail with the message “TEST FAILED: TOO MANY STATIONS AROUND COMPASS ROSE”. Refer to Garmin P/N 190-02081-03 for troubleshooting.

  • Page 138: Compass Swing Test

    When looking down at the GMU 44( ), rotate clockwise for positive values and counterclockwise for negative values. 13. After physically correcting the GMU 44( ) installation, repeat the procedures in Section 7.7.3 and Section 7.7.4. 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 7-17...

  • Page 139: Table 7-4 Heading Verification

    Displayed PFD Heading Heading Error GMC 605H Compass (A-B) Heading Heading 360° (North) 30° 60° 90° (East) 120° 150° 180° (South) 210° 240° 270° (West) 300° 330° 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 7-18...

  • Page 140: Grs 79H Or Gsu 75H & Gmu 44( ) Heading Offset Calibration

    “MAG FIELD AT SITE NOT UNIFORM” or “MAG FIELD AT SITE DIFFERS FROM IGRF MODEL” message, then the site contains magnetic disturbances that are too large, and an alternate site should be used for the AHRS magnetic calibration. 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 7-19...

  • Page 141: Run-Up Vibration Check (Gsu 75H Or Grs 79H Only)

    A dynamic component is significantly out of balance After the AHRS calibration is complete, the AHRS attitude and heading information displayed will become valid within 1 minute of power-up in Normal mode. 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 7-20...

  • Page 142: Gfc 600H System Configuration

    7.8 GFC 600H System Configuration Configure the GFC 600H FCS (and all interfaced units) to the original configuration settings that are retained with the rotorcraft permanent records (Appendix A). Each configuration item is saved to the configuration module as it is made. When the configuration item is selected by pressing the VS button to accept the value, the new value is stored in the configuration module at that time.

  • Page 143: Return-To-Service

    All system failure alerts and messages must be resolved prior to returning aircraft to service. The following sections will verify the proper operation of the GFC 600H FCS after maintenance has been performed on the system. Operational information regarding the GFC 600H FCS can be found in GFC 600H Pilot's Guide (P/N 190-02081-04).

  • Page 144: Maintenance Records

    2. Select PLAY to play the autopilot disconnect audio tone. 3. Verify that the autopilot disconnect tone is played through the cockpit speakers and headsets. 4. Select STOP to stop playing the autopilot disconnect audio tone. 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 8-2...

  • Page 145: Normal Mode Functional Checkout

    Perform the following test using ramp test equipment (e.g., DPS450 or similar). Operate the test equipment according to the manufacturer's instructions. NOTE Ensure that the cyclic is in a neutral position before performing the following checks. 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 8-3...
  • Page 146 3. Press the FCS key on the GMC to engage the system after successfully completing the pre-flight test. 4. The GMC 605H FCS status indication light should illuminate green. 5. Hold the collective at approximately 50%. 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 8-4...
  • Page 147 AMM 29-00-00) and ensure that all controls move without undue force as they would under normal operational conditions. CAUTION Ensure the GFC 600H system is powered and operational before attempting this configuration checkout. Moving the controls quickly while the servos are unpowered can lead to damage of the shear fuses.
  • Page 148 6. Move the Selected Altitude Bug to 4500 feet altitude. 7. Engage the GFC 600H system by pressing the FCS key or FTR / FCS ENG switch. 8. Press and release the FCS DISC switch to ensure that no flight director mode is active.
  • Page 149 3. Allow the air data test set to stabilize at the target altitude and airspeed. 4. Lift the collective to approximately 50%. 5. Rotate the heading bug on the HSI to the current rotorcraft heading. 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 8-7...
  • Page 150 “VAPP”, “P”, “R”, and “CPLD” are displayed in green text • CDI is centered 24. Confirm the cyclic is stationary. 25. Press the HDG key on the GMC to return the active roll mode to HDG. 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 8-8...
  • Page 151 “LOC” is displayed on the GMC 605H in the roll field and “GS” is displayed in the pitch field. • “LOC [Roll] and GS [Pitch]”, “P”, “R”, and “CPLD” are displayed in green text on the PFD. 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 8-9...
  • Page 152 12. Verify that the cyclic moves to the right. 13. Restore the OBS heading to the desired track (DTK) displayed on the GPS Navigator. 14. De-select NAV mode on the GMC 605H. 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page 8-10...

  • Page 153: Appendix Ainstallation-Specific Information

    A.2.2 Other Equipment ........................A-4 A.3 Configuration Log..........................A-5 A copy of this appendix must be used to record information for a specific installation of the GFC 600H system and maintained with the rotorcraft permanent records. Include a copy of the aircraft wiring diagrams in the permanent records along with the forms specified in this appendix.

  • Page 154: General Installation Information

    GRS 79H (Note if installed) 011-03732-20 GMU 44 (Note if installed) 011-00870-______ GMU 44B (Note if installed) 011-04201-00 GTP 59 (Note if installed) 011-00978-______ Collective Position Sensor 011-04817-______ 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page A-2...

  • Page 155: Interfaced Equipment

    Use Table A-1 to document GFC 600H FCS system interfaces with other Garmin equipment installed in the rotorcraft. The GFC 600H FCS interfaces to all equipment listed in Table A-1 are covered by this STC. Refer to installation-specific interconnect diagrams retained with the rotorcraft permanent records for detailed equipment interface information.

  • Page 156: Table A-2 Other Equipment

    A.2.2 Other Equipment Use Table A-2 to document GFC 600H FCS interfaces with equipment installed in the rotorcraft that isn’t listed in Table A-1. Refer to GFC 600H FCS Part 27 STC Installation Manual (P/N 190-02081-00) to determine whether interfaces between the GFC 600H FCS and the equipment listed in Table A-2 are approved by this STC.

  • Page 157: Configuration Log

     5 VAC DSP MIN KEY MIN GMC DSP  LIGHTBUS Page SLOPE OFFSET TRANSITION GMC DSP  PHOTOCEL Page SLOPE OFFSET GMC DSP  CONTRAST Page OFFSET Notes: 190-02081-03 GFC 600H HFCS Part 27 STC Maintenance Manual Rev. 3 Page A-5...

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