Garmin G1000 NXi Supplemental Maintenance Manual
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Garmin G1000 NXi Supplemental Maintenance Manual

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Supplemental Maintenance
Manual
Textron Aviation Inc.
NAV III Aircraft
Includes Instructions for Continued Airworthiness
for STC SA01830WI
190-02128-04
2017
Revision 3

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  • Page 1 Supplemental Maintenance Manual Textron Aviation Inc. NAV III Aircraft Includes Instructions for Continued Airworthiness for STC SA01830WI 190-02128-04 2017 Revision 3...
  • 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...
  • Page 3 California to cause cancer, birth defects, or reproductive harm. This Notice is being provided in accordance with California's Proposition 65. If you have any questions or would like additional information, please refer to our web site at www.garmin.com/prop65. CAUTION The GDU lens is coated with a special anti-reflective coating that is very sensitive to skin oils, waxes and abrasive cleaners.

  • Page 4: Table Of Contents

    TABLE OF CONTENTS PARAGRAPH PAGE 1. INTRODUCTION ......................... 1-1 Content, Scope, Purpose ....................1-1 Organization ........................1-2 Definitions/Abbreviations ....................1-3 Units of Measure ......................1-4 Publications........................1-4 Revision and Distribution ....................1-5 2. SYSTEM DESCRIPTION ....................2-1 Equipment Descriptions ....................2-1 G1000 Optional Interfaces ....................
  • Page 5 GSU 75 ADAHRS (if installed) ..................6-2 GDL 69A SXM (if installed) ................... 6-3 Configuration Modules ....................6-3 7. GARMIN G1000 LRU REPLACEMENT/CONFIGURATION & TESTING ......7-1 GDU 1054B/1050 PFD & MFD ..................7-1 GMA 1347 Audio Panel ....................7-4 GIA 63W Integrated Avionics Unit ................
  • Page 6 7.11 GDL 69A or GDL 69A SXM Data Link (if installed) ............. 7-42 7.12 GSA 81 Servos (if installed) ..................7-44 7.13 Garmin Traffic Systems (GTS 800) (if installed) ............7-46 8. SUBSYSTEM FUNCTIONAL CHECKS ................8-1 Stormscope Functional Check (if installed) ..............8-1 TAWS Functional Check ....................
  • Page 7 Figure 3-3, Configuration Status ....................3-3 Figure 3-4, Data Transmission Indicators .................. 3-3 Figure 3-5, GSU Configuration Settings Storage ..............3-13 Figure 3-6, Garmin Unit S/N Location ..................3-15 Figure 3-7, Software/Configuration Overview ................3-16 Figure 3-8 – Airframe Group Selection ..................3-18 Figure 3-9 –...
  • Page 8 TABLE ..........................PAGE Table 1-1, Required Documents ....................1-4 Table 1-2, Reference Publications .................... 1-5 Table 3-1, Garmin Unit S/N Prefixes ..................3-15 Table 4-1, Maintenance Intervals ....................4-4 Table 5-1, SVS Troubleshooting ....................5-13 Table 5-2, SVS-Related Alert Messages ................5-14 Table 5-3, Magnetometer Interference Test Sequence ............

  • Page 9: Introduction

    T206H models. Items in this document that are aircraft model(s) specific will identify the model(s) instead of “NAV III”. This document is a supplement to the existing G1000 Nav III Line Maintenance Manual, Garmin part number 190-00352-00. Except where noted, refer to the G1000 Nav III Line Maintenance Manual for servicing instructions.

  • Page 10: Organization

    Section 6: Equipment Removal & Replacement Gives instructions for the removal and replacement of G1000 equipment. Section 7: Garmin G1000 LRU Replacement/Configuration & Testing Gives instructions for loading software, configuring, and testing of G1000 equipment. Section 8: Subsystem Functional Checks Gives instructions for testing G1000 subsystems.

  • Page 11: Definitions/Abbreviations

    Definitions/Abbreviations ADAHRS: Air Data and Attitude Heading Reference System ADC: Air Data Computer ADF: Automatic Direction Finder ADS-B: Automatic Dependent Surveillance – Broadcast ADTS: Air Data Test Set AFCS: Automatic Flight Control System AFM: Airplane Flight Manual AFMS: Airplane Flight Manual Supplement AHRS: Attitude Heading Reference System AML: Approved Model List...

  • Page 12: Units Of Measure

    / operator to ensure latest versions of these documents are used during operation, servicing or maintenance of the airplane. Table 1-1, Required Documents Part Number Garmin Document 005-00620-21 Master Drawing List, G1000 Avionics Updates, Part 23 AML STC 005-00620-22...

  • Page 13: Revision And Distribution

    This document is required for maintaining the continued airworthiness of the aircraft. When this document is revised, every page will be revised to indicate current revision level. Garmin Dealers may obtain the latest revision of this document on the Garmin Dealer Resource Center website.

  • Page 14: System Description

    GDU 1054B OR GDU 1050 PFD & MFD Two Garmin GDU 1054B or GDU 1050 displays are installed in the Nav III instrument panel. The GDU 1054B displays are standard equipment on all Nav III models, while the GDU 1050 displays are installed on Model 172 aircraft that are not equipped with the Garmin GFC700 autopilot.

  • Page 15: Figure 2-2, Transponder

    Transponder The Garmin GTX 33, GTX 345R, or GTX 335R transponders communicate with the GIA 63Ws through RS-232 digital interface. The GTX 345R also communicates with the G1000 Avionics through an HSDB interface connected to the PFD. When installed, the GTX 345R communicates and controls the GTS Processor through the HSDB interface for all TAS operations.

  • Page 16: Figure 2-3 Gsu-75 Adahrs With Connector And Mounting Tray

    GSU 75 ADAHRS The GSU 75 ADAHRS is a combined Air Data and AHRS system. The unit is mounted in the tail avionics area. It contains advanced tilt sensors, accelerometers, rate sensors, static pressure sensors, and pitot pressure sensors. The GSU 75 receive GPS data from the GIA 63Ws, and magnetic heading from the GMU 44 Magnetometer.

  • Page 17: Figure 2-4, Gdl 69A Sxm Datalink

    GDL 69A SXM Datalink The GDL 69A SXM provides SiriusXM Radio weather and music entertainment through means of a dedicated satellite data link. The GDL 69A SXM is mounted behind the instrument panel in the 182 and 206 models and in the aft avionics area for 172 models. Power to the GDL 69A SXM is received from the Avionics No.

  • Page 18: G1000 Optional Interfaces

    G1000 Optional Interfaces There are no new optional interfaces approved as part of this STC. Refer to the G1000 Nav III Line Maintenance Manual for optional interfaces. Electrical Power Distribution The electrical power distribution has not changed as a result of this STC. Refer to the G1000 Nav III Line Maintenance Manual for power distribution.

  • Page 19: G1000 Normal Mode

    To cancel a selection, press the small FMS knob in again, deactivating the cursor. The CLR key may also be used to cancel a selection or deactivate the cursor. G1000 Normal Mode To start the G1000 system in Normal Mode: 1.

  • Page 20: Reversionary Mode

    Reversionary Mode Reversionary mode allows for display of information related to safe flight in the event of a display communication or hardware failure. The PFD automatically goes into reversionary mode when communication to the MFD is lost. Manual reversionary mode allows the operator to force the PFD and MFD into reversionary mode by pressing the large red button labeled ‘DISPLAY BACKUP’...

  • Page 21: Software And Configuration

    3. Software and Configuration Configuration Mode Overview Throughout this document, references are made to the PFD and/or MFD being in configuration mode. The configuration mode exists to provide the avionics technician with a means of configuring, checking, and calibrating various G1000 sub-systems. Troubleshooting and diagnostics information can also be viewed in this mode.

  • Page 22: Figure 3-1, Set>Actv Diagram

    • ACTV>SET (read ‘Active to Set’) softkey: Causes the LRUs current settings to be copied to the master configuration module as SET items. CAUTION: The ACTV>SET softkey must be used with caution! If an improperly configured unit is installed, this softkey causes the wrong configuration to replace the correct aircraft configuration.

  • Page 23: Figure 3-2, Loss Of Communication

    A blank active column, as shown in Figure 3-2, represents loss of communication between the display and the particular unit. See Section 5 for more details on troubleshooting. Figure 3-2, Loss of Communication Configuration Prompts When configuration settings are changed, the technician receives on-screen prompts and/or confirmations such as those shown in Figure 3-3.
  • Page 24 Configuration Mode Navigation Using the FMS knob as described in Section 2.7, a user can navigate through different pages and page groups in the Configuration Mode. For complete description and breakdown of each page, refer to the G1000 System Maintenance Manual listed in Table 1-2. System Page Group 1.
  • Page 25 GDL Page Group 1. GDL 69 Configuration GTS Page Group ***** 1. GTS Configuration OTHER Page Group ***** 1. Stormscope CAL Page Group 1. Fuel Tank Calibration 3. HSCM Calibration 2. Flaps & Trim Calibration 4. DAT Calibration * Appears only if GTX 33 w/ ES is installed. ** Appears only if loader card is in top slot of PFD and if GTX 335 or GTX 345 are installed.

  • Page 26: G1000 System Software Information

    G1000 Software Image All software and configuration files were certified by Garmin and are considered part of FAA- approved Type Design data. Approved software and hardware definitions for each STC Configuration are defined on the appropriate General Arrangement drawing listed in Table 1-1.
  • Page 27 NOTE In order to create a Textron Nav III system loader card, the installer completing these procedures must be an authorized Garmin Service Center to gain access to the necessary data via the Garmin website. 1. Go to www.garmin.com and click on the...
  • Page 28 5. Click on the Select Action button for the appropriate software image part number as shown on the Garmin General Arrangement drawing 005-00620-22 and choose Download to save the software file to the local hard drive. 6. After the file is downloaded, close the web browser.
  • Page 29 9. Follow the on screen prompts to continue. G1000 Supplemental Maintenance Manual Page 3-9 Textron Nav III Series Revision 3 190-02128-04...
  • Page 30 10. Select the SD card reader drive and click Next>. 11. Follow the on screen prompts to continue. G1000 Supplemental Maintenance Manual Page 3-10 Textron Nav III Series Revision 3 190-02128-04...
  • Page 31 12. The program will make the SD loader card and prompt you when it’s done. 13. Once successfully completed, the following window will display. Click Finish to close the program. The SD card can then be removed from the computer and is ready for use in the aircraft.
  • Page 32 Software Files Software files are defined by part number and version number on the General Arrangement drawing. Each G1000 system LRU reports the software version it currently contains to the user in two places. • Normal System Mode: The Aux – System Status page lists each LRU and the reported software version.

  • Page 33: Figure 3-5, Gsu Configuration Settings Storage

    Configuration File Storage The storage of G1000 system configuration files is unchanged from that depicted in the G1000 Nav III Line Maintenance Manual, except as noted in Figure 3-5 for the GSU 75. The GSU 75 ADAHRS air data configuration file is loaded directly to GSU 75 internal memory. A copy of the file is stored in the GSU 75 configuration module.

  • Page 34: Configuration Mode

    Loading the incorrect files could lead to longer down time and unplanned removal of equipment. • Garmin optional equipment (i.e. GDC 74 ADC, GRS 77 AHRS or GSU 75 ADAHRS, GTX 33 or GTX 3X5 transponder, etc.). Section 3.5.1 helps find which units are installed without a physical inspection.

  • Page 35: Figure 3-6, Garmin Unit S/N Location

    • Third party avionics equipment interfaced to G1000 (ADF, DME, non-Garmin traffic systems, WX-500, etc.). To determine if the third party equipment is installed, check the circuit breaker panel for circuit breakers for the units, and check for G1000 controls for the third party devices.

  • Page 36: G1000 Software/Configuration Procedure

    G1000 Software/Configuration Procedure This section summarizes the procedures required to load software and configuration files to the G1000. It is intended to work as a central guide for technicians to use while performing maintenance on the aircraft. In sections of this manual where software is required to be reloaded, these sections will make reference back to this section for instructions.

  • Page 37: System Software And Configuration Load

    1. Open the MFD, PFD (ESS BUS) and PFD (AVN BUS 1) circuit breakers. 2. Remove Garmin SD/MMC/FS510 cards from bottom slots of PFD and MFD if present. 3. Insert the software loader card into the MFD top card slot.

  • Page 38: Figure 3-8 - Airframe Group Selection

    Baseline Software and Configuration Load IMPORTANT If the aircraft being modified has incorporated any modifications beyond factory configuration that effect engine or airspeed limitations, your configuration may not be supported at this time. It is the responsibility of the installer to ensure compatibility with existing modifications.

  • Page 39: Figure 3-9 - Airframe Change Confirmation

    Figure 3-9 – Airframe Change Confirmation 5. Once the appropriate airframe option is selected, the cursor moves to the ITEM window. Rotate the small FMS knob to activate the drop-down menu. Highlight “Cessna XXX – Baseline Configuration” (where XXX is the airframe type selected above) and press the ENT key to select it.
  • Page 40 GSU 75 Software/Configuration Loading (if installed) Follow this procedure to configure the GSU 75 ADAHRS. Do not follow the procedures in this section if a GSU 75 is not installed in the aircraft. Move the cursor to the Item window and rotate FMS inner knob to display drop down menu.
  • Page 41 GTX 345 without GTS 800 Transponder Software/Configuration Loading (if installed) Follow this procedure to configure the GTX 345 transponder in the aircraft in aircraft without a GTS 800. Do not follow the procedures in this section if a GTX 345 is not installed in the aircraft or if the GTX 345 is installed with a GTS 800.
  • Page 42 GDL 69A SXM Software/Configuration Loading (if installed) Follow this procedure to configure the GDL 69A SXM Receiver. Do not follow the procedures in this section if a GDL69A SXM unit is not installed. Rotate the large FMS knob until the Item field is highlighted, rotate the small FMS knob to activate the drop down menu.
  • Page 43 CAN Bus Fuel Level Sensors (if installed) Follow this procedure to configure the system to use CAN Bus Fuel Level Sensors. Do not follow the procedures in this section if the aircraft is not equipped with CAN Bus Fuel Level Sensors.
  • Page 44 GTS 800 with GTX 345 Software/Configuration Loading (if installed) Follow this procedure to configure the GTS 800 Traffic System. Do not follow the procedures in this section if the aircraft is not equipped with GTS 800 or if it is equipped with a GTS 800 and without a GTX 345.
  • Page 45 KN63 DME Configuration Loading (if installed) Follow this procedure to configure the system to use the KN 63 DME. Do not follow the procedures in this section if the aircraft is not equipped with a KN 63. Rotate the large FMS knob until the Item field is highlighted, rotate the small FMS knob to activate the drop down menu.
  • Page 46 GRS 77 and GDC 74 Software/Configuration Loading (if installed) Follow this procedure to configure the system for GRS 77 and GDC 74. Do not follow the procedures in this section if the aircraft is not equipped with the GRS 77 and GDC 74. Rotate the large FMS knob until the Item field is highlighted, rotate the small FMS knob to activate the drop down menu.
  • Page 47 GDL 69 Software/Configuration Loading (if installed) Follow this procedure to configure the GDL 69 Receiver. Do not follow the procedures in this section if a GDL69 unit is not installed or if a GDL 69A SXM unit is installed. Rotate the large FMS knob until the Item field is highlighted, rotate the small FMS knob to activate the drop down menu.
  • Page 48 KTA 870 Configuration Loading (if installed) Follow this procedure to configure the system to use a KTA 870 Traffic System. Do not follow the procedures in this section if the aircraft is not equipped with a KTA 870. Rotate the large FMS knob until the Item field is highlighted, rotate the small FMS knob to activate the drop down menu.
  • Page 49 Pre BP 2007 CI 2480-400 Antenna Configuration Loading (if installed) Follow this procedure to configure the system to use a CI 2480-400 Antenna (Pre BP 2007 aircraft). Do not follow the procedures in this section if the aircraft is not a Pre-BP 2007 Aircraft with CI 2480-400 Antenna installed.
  • Page 50 Initialize Fuel Cal Data (Only for CAN Bus Fuel sensors before fuel cal) Follow this procedure to initialize fuel cal data. This section is only for aircraft with CAN Bus Fuel Sensor and only before the fuel calibration is completed. Rotate the large FMS knob until the Item field is highlighted, rotate the small FMS knob to activate the drop down menu.

  • Page 51: Feature Enablement

    NOTES The required ChartView databases are subscription-based and need to be procured by the installing agency from the Garmin or Jeppesen website. The ChartView database is not present in a new display. Insert the ChartView Enablement card in the top slot of the PFD and power on the PFD in configuration mode.
  • Page 52 Synthetic Vision System Enablement Follow this procedure to enable the Synthetic Vision feature. Insert the SVS Enablement card in the top slot of the PFD and power on the PFD in configuration mode. If a message appears on the PFD stating an “arfrm_imgs.zip” file is not present, follow the on screen instructions to continue.
  • Page 53 TAWS-B Enablement Follow this procedure to enable the TAWS-B feature. Insert the TAWS-B Enablement card in the top slot of the PFD, power on the PFD in configuration mode. If a message appears on the PFD stating an “arfrm_imgs.zip” file is not present, follow the on screen instructions to continue.

  • Page 54: Aircraft Registration Number Entry

    Search and Rescue Enablement (not required if enhanced SAR is enabled) Follow this procedure to enable the Search and Rescue (SAR) feature. Insert the SAR Enablement card in the top slot of the PFD, power on PFD in configuration mode. If a message appears on the PFD stating an “arfrm_imgs.zip”...

  • Page 55: Configuration Manager

    Press the SET GTS softkey (if present) and acknowledge the PFD prompt by pressing the ENT key. After completing transponder configuration, deactivate the cursor. Equipped with GTX 335 or GTX 345 Insert the software loader card into the top slot of the PFD. Place the PFD in configuration mode.

  • Page 56: Splash Screen Loading

    3.12 Database Loading Follow this procedure to load the databases. Obtain the following databases from fly.garmin.com and install on a blank 16GB or larger card or by obtaining Garmin SD Card p/n 010-00474-50. Databases with an asterisk are not included on the p/n 010-00474-50 SD card. When obtaining the databases from fly.garmin.com and using SD cards smaller than 16GB, you may need to use multiple...

  • Page 57: Figure 3-10, Mfd Aux - Database Page Db Transfer

    databases are synchronized, the system will verify them for use by showing “Verifying” in the Standby column. After the databases are verified, a cyan double arrow symbol will appear between the Standby and Active columns to show which databases will be transferred to Active use on the next power cycle or restart.

  • Page 58: Configuration Of Navigation Map For Traffic System

    b. Turn the FMS knob to highlight the database to transfer to the Active column. c. Press the ENT key on the MFD and a cyan double arrow will appear between the Standby and Active columns. d. Restart the displays. e.

  • Page 59: Interface Confirmation

    3.15 Interface Confirmation Lightning Detection System Configuration Load Confirmation Coordinate the StormScope configuration with Section 8.1 “Stormscope Functional Check”. 1. With PFD in configuration mode, use the PFD large FMS knob to select OTHER and the Stormscope configuration page. Figure 3-11, Stormscope Configuration Page 2.

  • Page 60: Section 3 3-1 –

    3. Verify that the DATA window shows the following: Hdg: None: J3-1 Open J3-2 Open Hdg Valid Flag Flag Sense J3-4 Open Hdg Value Inhibit Line Antenna Mount Bottom J3-3 Open 4. Deactivate the cursor. NOTE The DATA window is only updated once every five seconds. G1000 Supplemental Maintenance Manual Page 3-40 Textron Nav III Series...

  • Page 62: Servicing Information

    Servicing Information G1000 LRU maintenance is ‘on condition’ only. No component-level overhaul is required for this type design change. On Condition Servicing ‘On Condition’ replacement and/or servicing should occur when an item exhibits conditions, symptoms, and/or abnormalities defined in Section 5 of this manual. Replacement and/or servicing should be made only after the technician troubleshoots the system to the extent determined necessary by using the guidance in this manual along with common avionics maintenance practices.
  • Page 63 Required Tools The following tools are needed to perform maintenance tasks on G1000 equipment: • Calibrated Milliohm meter, OR o Agilent 34410A Ammeter or equivalent o Fluke 187 Voltmeter or equivalent o Variable DC Power Supply capable of providing 1 amp current •...

  • Page 64: Maintenance Intervals

    The tolerance for inspection times is the same as that stated in 5-10-00 of the Cessna Maintenance Manual applicable to the airframe. The intention of Garmin is to align this maintenance program as best as possible with the existing Cessna Nav III inspection program. For a complete description of the Cessna inspection program, refer to the Cessna Maintenance Manuals listed in Table 1-1.

  • Page 65: Electrical Bonding Test

    Electrical Bonding Test The following bonding tests are provided for G1000-equipped Nav III Series aircraft as a requirement beyond what is given in the 172, 182, or 206 Series Maintenance Manual. Requirements All G1000 equipment must be installed. Gain access for the procedure listed below in Section 4.4.3 as required and in accordance with the Cessna Nav III Series Maintenance Manuals.

  • Page 66: Gsu 75 Earth Magnetic Field Updates

    GSU 75 Earth Magnetic Field Updates The GSU 75, utilizes an Earth magnetic field model which is updated once every five years. The update is expected to be available from Garmin every five years, as long as the GSU 75, remain Garmin-supported products.
  • Page 67 3. With the G1000 system in normal mode, pull the following circuit breakers on the circuit breaker panel: • PFD (ESS BUS) • ADC/AHRS (ESS BUS) • NAV 1/ENG (ESS BUS) 4. Wait at least 5 seconds, then verify the data on the PFD remains valid and the following alert messages are not present: •...

  • Page 68: Section 4 4-1–

    6. In the GDU page group, go to the GIA RS-232/ARINC 429 CONFIG page. 7. With PFD1 selected in the SELECT UNIT window, verify the following indicators are green checks: • ARINC 429 IN1 (GSU75 #1) • ARINC 429 IN2 (GDC72 #1) (Ref.

  • Page 69: Troubleshooting

    5. TROUBLESHOOTING This section provides instructions and guidance for G1000 system troubleshooting as installed in the Cessna Nav III Series. IMPORTANT! Sections 6, 7 and 9 provide detailed instructions on equipment removal, replacement, configuration, and return-to-service testing. Anytime a G1000 component or LRU is removed, swapped, or replaced, the technician must follow the procedures given in Sections 6, 7 and 9 to ensure proper operation of the system.

  • Page 70: System Annunciations

    The Aux – System Status page displays the following information for each LRU and sub- function: • Status: A green check is displayed for properly operating LRUs. A red ‘x’ appears when an internal LRU fault is detected and it has taken itself offline, or if the MFD cannot communicate with the LRU.
  • Page 71 The FAILED PATH message is triggered by a timeout of any one digital channel. IMPORTANT! Once the FAILED PATH message has been triggered, it will remain on the list of messages until the next power cycle. This latching was implemented so that for intermittent failures, the message would remain at the end of the flight (to alert maintenance crew).
  • Page 72 GDU ARINC 429 CONFIG Page PFD and MFD ARINC 429 Channel Indicator Status Green PFD/GSU 75 data path is functioning correctly. PFD/GSU 75 data path is not functioning correctly. • Verify GSU 75 status is “OK” using the Aux – System Status page on the MFD.
  • Page 73 GIA RS-232 / ARINC 429 CONFIG Page GIA1 RS-232 Channel Indicator Status Green GIA1/GSU 75 (ADC) data path is functioning correctly. GIA1/GSU 75 (ADC) data path is not functioning correctly. • Load GIA1 and GSU configuration files. • Swap GIA1 and GIA2, reconfigure both GIA’s to their new locations to confirm if the problem is in the original GDC 72 #1 GIA1.
  • Page 74 GIA1 RS-232 (continued) Channel Indicator Status Green GIA1/GSU 75 (AHRS) data path is functioning correctly. GIA1/GSU 75 (AHRS) data path is not functioning correctly. • Load GIA1 configuration files. • Swap GIA1 and GIA2, reconfigure both GIA’s to their new locations to confirm if the problem is in the original GRS 79 #1 GIA1.
  • Page 75 GIA2 RS-232 Channel Indicator Status GIA2/GSU 75 (AHRS) data path is functioning Green correctly. GIA2/GSU 75 (AHRS) data path is not functioning correctly. • Load GIA2 and GSU configuration files. • Swap GIA2 and GIA1, reconfigure both GIA’s to their new locations to confirm if the problem GRS 79 #1 (if GSU 75 is in the original GIA1.
  • Page 76 GIA2 ARINC 429 Channel Indicator Status Green GIA2/GSU 75 data path is functioning correctly. GIA2/GSU 75 data path is not functioning correctly. • Load GIA2 and GSU 75 configuration files. • Swap GIA2 and GIA1, reconfigure both GIA’s to their new locations to confirm if the problem is in the original GSU 75 #1 GIA2.
  • Page 77 System Failure Troubleshooting The following table provides basic troubleshooting guidance for LRU failures. Refer to G1000 Wiring Diagram, listed in Table 1-1, as needed to verify interconnects. NOTE: For troubleshooting of data fields and units not listed here, refer to the Cessna Nav III Line Maintenance Manual.
  • Page 78 Replace GSU 75. ✓ If problem persists replace GSU 75 configuration module. ✓ Contact Garmin Aviation Product Support if condition continues after replacing the GSU 75 and config module for additional assistance G1000 Supplemental Maintenance Manual Page 5-10 Textron Nav III Series...
  • Page 79 Associate Invalid Data Field Solution d LRU(s) • Ensure metal objects (tool boxes, power carts, etc.) are not interfering with the magnetometer and aircraft is not in hangar, near other buildings, parked over metal drainage culverts or on hard surfaces that may contain steel reinforcements •...

  • Page 80: G1000 Alerting System

    G1000 Alerting System Figure 5-3, Alerts & Annunciations The G1000 Alert System conveys alerts to the pilot using combinations of the following features: Alert Window: The Alert window displays alert text messages. Pressing the Alerts softkey displays the Alerts window. Pressing the ALERTS softkey again removes the Alerts window from the display. Softkey Annunciation: When the G1000 Alerting System issues an alert, the Alerts softkey is used as a flashing annunciation to accompany the alert.

  • Page 81: Synthetic Vision And Pathways Troubleshooting

    Synthetic Vision and Pathways Troubleshooting The SVS/Pathways software feature requires the following G1000 sensors/data to be valid: • AHRS • Heading • GPS Position • 9 Arc-Second (or less) Terrain Data In the event that one the above items fails or is unavailable, the SVS/Pathways feature is automatically removed from the PFD.

  • Page 82: Backup Communications Path Checks

    Table 5-2, SVS-Related Alert Messages Failure Message Cause Solution Geographical operation limitations are SVS is disabled because the SVS – SVS DISABLED: Out of defined in the AFMS listed in Table 1-1. aircraft exceeded the boundaries available terrain region. Ensure that operations are within this of the loaded terrain database.

  • Page 83: Gdu 105X Troubleshooting

    Data Path Failures Failure Message Cause Solutions Determine which data path has failed: See Section 5.1.1. A communications data path FAILED PATH – A data path has status is not being received by the Check wiring continuity for the failed failed.
  • Page 84 Symptom Recommended Action • Go to the GDU TEST page in configuration mode and verify button, knob, or joystick operates correctly by observing a change in color from red to green in the button/knob/joystick icon when the button/knob/joystick is pressed. If a A button/knob/joystick does not button is stuck, the button icon will be green without pressing the button as appear to function...

  • Page 85: Gdu 105X Alerts

    GDU 105X Alerts Software/Configuration Alerts Failure Message Cause Solution The system has found the PFD SW MISMATCH – GDU software and MFD software versions do not version mismatch. Xtalk is off. match. • MANIFEST – PFD 1 software Load correct software version. mismatch.
  • Page 86 Failure Message Cause Solution • Reload the display configuration files from SD Loader Card. • Reload system configuration files by pressing the UPDT CFG MFD1 CONFIG – MFD1 softkey on the Configuration configuration error. Config service Upload Page in the PFD System req’d.
  • Page 87 Key Alerts Failure Message Cause Solution • Go to the GDU TEST page in configuration mode and verify key MFD “key” KEYSTK – key is The SYSTEM has determined a is stuck (if key is stuck the stuck. key is stuck on MFD. corresponding indicator will be green).
  • Page 88 Failure Message Cause Solution • Ensure the MFD connector is fully seated and locked. MFD SERVICE – needs service. The G1000 has determined MFD • Replace the MFD. Return unit for repair. needs service. • Return faulty unit to an Authorized Repair Facility.

  • Page 89: Gtx Troubleshooting

    GTX Troubleshooting GTX Alerts Failure Message Cause Solutions MANIFEST – GTX software The system has detected an • mismatch. Communication incorrect software version loaded Reload software. halted. in the GTX unit. • Perform a SET>ACTV configuration reset on the GTX Config page and verify the aircraft registration is present.

  • Page 90: Gdl69A Sxm Troubleshooting (If Installed)

    GDL69A SXM Troubleshooting (if installed) For GDL69A SXM Troubleshooting, refer to the GDL 69A Troubleshooting section in the G1000 Nav III Line Maintenance Manual. G1000 Supplemental Maintenance Manual Page 5-22 Textron Nav III Series Revision 3 190-02128-04...

  • Page 91: Gsu 75 And Gmu 44 Troubleshooting

    • Remove the GSU 75 connector and verify there are no bent pins. • Replace the GSU 75. • Contact Garmin for further troubleshooting if required. G1000 Supplemental Maintenance Manual Page 5-23 Textron Nav III Series Revision 3 190-02128-04...
  • Page 92 GSU Alerts Failure Message Cause Solutions MANIFEST – GRS software The system has detected an • mismatch. Communication incorrect software version loaded Load correct software version. halted. in the specified GRS unit. The AHRS magnetic field model AHRS SERVICE – AHRS •...

  • Page 93: Figure 5-5, Magnetometer Interference Test

    Calibration Procedure E: Magnetometer Interference Test A magnetometer interference test is available for troubleshooting and/or verifying a magnetically ‘clean’ installation of the GMU 44. This test exercises various devices on the aircraft that could potentially affect the magnetic field as measured by the GMU 44. NOTE This test is used to validate that no electronic device or magnetized components produce a magnetic field sufficient to interfere with the operation of the GMU 44...

  • Page 94: Table 5-3, Magnetometer Interference Test Sequence

    NOTE item on the checklist instructs the operator to “prepare a detailed test The 3 sequence with precise start and stop times for exercising all electronic devices”. The list of relevant electronic devices is given in Table 5-3. Begin test with flaps retracted, flight controls in a neutral position, all lights selected OFF.

  • Page 95: Gsu 75 Troubleshooting

    01639-00 for acceptable magnetic interference limits. Compare the corresponding timestamps with the prepared test sequence to identify which action produced the problem. Contact Garmin for assistance in resolving the problem. NOTE Two common reasons for a failed magnetometer interference test are: 1)

  • Page 96: Software/Configuration Troubleshooting

    5.11 Software/Configuration Troubleshooting Problem Solutions • Ensure that the criteria listed in Section 5.11.1 are MFD or PFD displays do not power up: fulfilled for the applicable situation. • Ensure power is present at display backshell connector. • Troubleshoot per the “Blank Display” GDU section. •...
  • Page 97 System Communication Hierarchy The following criteria must be satisfied to be able to perform the desired operation: Desired Operation Criteria for Success • Load Software to MFD or PFD Displays SW Loader Card must be inserted in top slot for each display to be loaded.

  • Page 98: Backshell/Backplate Connectors

    5.12 Backshell/Backplate Connectors The following figures depict the backplate connectors as viewed with the LRU removed. For units not shown here, refer to the G1000 Nav III Line Maintenance Manual. Figure 5-6, GTX 335R/345R Looking at Front of Connector (P3251) Figure 5-7, GTX 345R (Only) Looking at Front of Connector (P3252) G1000 Supplemental Maintenance Manual Page 5-30...

  • Page 99: Figure 5-8, Gdu 1054B/1050 Backshell Connector (P10401)

    Figure 5-8, GDU 1054B/1050 Backshell Connector (P10401) Figure 5-9, GSU 75 Connector View from Front (P751) Figure 5-10, GDL 69A SXM Backplate Connector (P69A1) G1000 Supplemental Maintenance Manual Page 5-31 Textron Nav III Series Revision 3 190-02128-04...

  • Page 100: Equipment Removal & Installation

    Software Manifest page may also be used to check part numbers and versions. The General Arrangement drawing allows alternate part number units to be installed with certain hardware/software combination restrictions. Refer to the applicable “Garmin Equipment/Software List” contained in the General Arrangement drawing for details.

  • Page 101: Gdu 1054B/1050

    GDU 1054B/1050 Removal: 1. Using a 3/32” hex tool, rotate all four ¼-turn fasteners counter-clockwise until they reach their stops. 2. Carefully remove the display from the panel. 3. While supporting the display, disconnect the connector. Reinstallation: 1. Visually inspect the connector and pins for signs of damage. Repair any damage. 2.

  • Page 102: Gdl 69A Sxm (If Installed)

    2. Disconnect the ADAHRS connector. 3. Disconnect the pitot and static lines. 4. Turn each retention screw counterclockwise until they disconnect from the remote rack. 5. Gently slide the unit from the remote rack. Do NOT loosen the remote rack hardware fastening it to the avionics shelf or the GSU 75 must be re-calibrated per Section 7.10) GSU 75 Installation: 1.

  • Page 103: Figure 6-1, Configuration Module Installation

    Refer to the Master Drawing List, listed in Table 1-1, for specific installation drawings. Figure 6-1, Configuration Module Installation Table 6-1, Configuration Module Kit – 011-00979-00 Garmin Part Item Description Qty Needed Number Configuration Module PCB Board Assembly w/EEPROM & Temp...

  • Page 104: Figure 6-2, Gsu 75 Configuration Module Installation

    GSU 75 Configuration Module Removal & Replacement CONFIGURATION MODULE Figure 6-2, GSU 75 Configuration Module Installation Table 6-2, GSU 75 Configuration Module Kit – 011-00979-20 Garmin Part Item Description Qty Needed Number Sub-Assy,Potted,Config Mdl,w/EEPROM,Jackscrew 011-02179-00 Cable, 4-Conductor Harness 325-00122-00 Pins, #22 AWG (HD)

  • Page 105: Section 6 6-1 –

    Configuration Module Checkout If a GSU 75 Configuration Module is replaced: Configuration settings must be reloaded to the GSU 75 per Section 7.6, then proceed to Section 7.7.3. Additionally, GSU 75 and GMU 44 calibration procedures must be performed. Proceed to Section 7.10.

  • Page 106: Garmin G1000 Lru Replacement/Configuration & Testing

    7. Garmin G1000 LRU Replacement/Configuration & Testing This section provides procedures to be followed after a piece of G1000 equipment is replaced. At the beginning of each LRU section, instructions are given to guide the technician for various removal/replacement scenarios. These instructions define necessary procedures to be followed for situations where original equipment was reinstalled as well as for situations where new equipment (new serial number) is installed.
  • Page 107 LRU Replacement Procedure PFD 1. Open the MFD, PFD (ESS BUS), and PFD (AVN BUS 1) circuit breakers. 2. Remove SD cards from top and bottom slots of the MFD and PFD if present. 3. Apply power to the G1000 system by connecting external power to the aircraft to energize the aircraft and avionics electrical busses.

  • Page 108: Figure 7-1, G1000 Normal Mode Check

    8. Press the CHK All softkey. 9. Press the Load softkey. 10. Press ENT to acknowledge the process was complete. 11. Deactivate the cursor. 12. Scroll to the Configuration Manager page. 13. Press the CNFM CFG softkey. 14. Select ok when prompted to “Confirm configuration as expected configuration” 15.

  • Page 109: Gma 1347 Audio Panel

    LRU Replacement Procedure GMA 1. Open the MFD, PFD (ESS BUS), and PFD (AVN BUS 1) circuit breakers. 2. Remove Garmin SD/MMC/FS 510 cards from bottom slots of the MFD and PFD if present. 3. Apply power to the G1000 system by connecting external power to the aircraft to energize the aircraft and avionics electrical busses.
  • Page 110 17. If there are no red-Xs or system alerts, continue to Section 7.2.3. Legacy Replacement Procedure GMA (Alternate Method) To load the GMA complete the following subsections in order as they apply to the aircraft. Cessna XXX – Baseline Configuration (where XXX is the airframe type) 1.
  • Page 111 Option – KN63 DME Installation (For GMA replacement and aircraft equipped with a DME only) 1. Scroll the cursor to the ITEM window highlight “Option – KN63 DME Installation” and press the ENT key on the PFD. 2. Press the CLR ALL softkey. 3.
  • Page 112 9. Initiate passenger address using pilot’s headset boom mic by keying the pilot’s PTT. Verify the following: • Clear PA audio can be heard over cabin speaker and headsets • PA selected annunciator on GMA flashes ~ once per second during PA address. 10.

  • Page 113: Gia 63W Integrated Avionics Unit

    LRU Replacement Procedure GIA1 or GIA2 1. Open the MFD, PFD (ESS BUS), and PFD (AVN BUS 1) circuit breakers. 2. Remove Garmin SD/MMC/FS 510 cards from bottom slots of the MFD and PFD if present. 3. Apply power to the G1000 system by connecting external power to the aircraft to energize the aircraft.
  • Page 114 23. Deactivate the cursor. 24. Scroll to the Configuration Manager page. 25. Press the CNFM CFG softkey. 26. Select ok when prompted to “Confirm configuration as expected configuration” 27. Power cycle the system verify there are no red-Xs or system alerts. 28.
  • Page 115 19. Highlight the software box and press the ENT key to check the box 20. Use the large FMS knob to scroll to GIA 1 – GPS or GIA 2 – GPS, whichever was replaced. 21. Highlight the software box and press the ENT key to check the box. 22.
  • Page 116 2. Press the CLR ALL softkey. 3. Scroll the cursor to GIA CERT software box, and press the ENT key to check the box. 4. Press “Load” softkey. 5. Monitor load progress. Verify software load completes without errors as indicated by the following: •...
  • Page 117 1. In the ITEM window highlight “Option – KR87 ADF Installation” and press the ENT key on the PFD. 2. Press the CLR ALL softkey. 3. Scroll the cursor to GIA 2 configuration box, and press the ENT key to check the box. 4.
  • Page 118 Stormscope GIA Configuration (For GIA 2 replacement and aircraft equipped with a WX500 system only) 1. Scroll the cursor to the ITEM window highlight “Option – WX500 Installation” and press the ENT key on the PFD. 2. Press the CHK ALL softkey. 3.

  • Page 119: Figure 7-2, Aux - Gps Status Page (Mfd)

    GIA 63W Test GPS Signal Acquisition Figure 7-2, Aux – GPS Status Page (MFD) The GIA 63W units should normally acquire a GPS navigation solution within 5 to 10 minutes of startup, provided the aircraft is outside (or indoors with a GPS repeater). Select the Aux – GPS Status page on the MFD.
  • Page 120 7. Repeat steps 5 and 6 and re-transmit while monitoring GPS 2 signal levels on the MFD. 8. Repeat steps 4 through 7 for each of the following frequencies: • 121.175 MHz • 121.200 MHz • 131.250 MHz • 131.275 MHz •...
  • Page 121 2. Set the HSI on the PFD to VOR1 by pressing the CDI softkey until VOR1 is selected. Rotate CRS knob to set VOR1 course pointer to aircraft heading. 3. Verify full scale deflection of VOR1 CDI by varying CRS1 selected course at least 10° left and right.

  • Page 122: Gea 71 Engine/Airframe Unit

    LRU Replacement Procedure GEA 1. Open the MFD, PFD (ESS BUS), and PFD (AVN BUS 1) circuit breakers. 2. Remove Garmin SD/MMC/FS 510 cards from bottom slots of the MFD and PFD if present. 3. Apply power to the G1000 system by connecting external power to the aircraft to energize the aircraft and avionics electrical busses.
  • Page 123 Legacy Replacement Procedure GEA (Alternate Method) To load the GEA complete the following subsections in order as they apply to the aircraft. GEA Configuration (For GEA replacement) 1. Insert the software loader card in the top slot of the PFD. 2.
  • Page 124 Configuration Manager Update 1. With the system still in configuration mode, scroll to the Configuration Manager page on the PFD. 2. Press the CNFM CFG softkey. 3. Select ok when prompted to “Confirm configuration as expected configuration” 4. Power cycle the system verify there are no red-Xs or system alerts. 5.

  • Page 125: Figure 7-3, Normal Engine Instrument Markings (Mfd)

    GEA 71 Test On the MFD (normal mode), check the indication for each of the sensor or monitor inputs with the aircraft engines off. In general, verify all engine and system instruments show valid static normal values and markings, with no red Xs or erratic indications. Reference Figure 7-3 for normal engine instrument markings (figure may not reflect actual aircraft installation).

  • Page 126: Gtx 335R, Gtx 345R, Or Gtx 33 Transponder

    LRU Replacement Procedure GTX1 1. Open the MFD, PFD (ESS BUS), and PFD (AVN BUS) circuit breakers. 2. Remove Garmin SD/MMC/FS 510 cards from bottom slots of the MFD and PFD if present. 3. Apply power to the G1000 system by connecting external power to the aircraft to energize the aircraft and avionics electrical busses.
  • Page 127 5. Activate cursor and rotate the small FMS knob to display the drop down menu. Rotate the large FMS knob to highlight “0X - XXX” (where 0X is the menu position and XXX is the airframe type) and press ENT key on the PFD. 6.

  • Page 128: Figure 7-4, Aircraft Registration

    Figure 7-4, Aircraft Registration GTX 335R, GTX 345R, or GTX 33 Test Operation of the GTX 335R, GTX 345R, or GTX 33 Mode-S transponder is accomplished using the PFD or the MFD. Refer to G1000 Cessna Nav III Cockpit Reference Guide, listed in Table 1-1, for basic operation.

  • Page 129: Gsu 75 Adahrs (If Installed)

    LRU Replacement Procedure GSU 1. Open the MFD PFD (ESS BUS), and PFD (AVN BUS 1) circuit breakers. 2. Remove Garmin SD/MMC/FS 510 cards from bottom slots of the MFD and PFD if present. 3. Apply power to the G1000 system by connecting external power to the aircraft to energize the aircraft and avionics electrical busses.
  • Page 130 Legacy Replacement Procedure GSU (Alternate Method) (if installed) 1. Insert the software loader card in the top slot of the PFD. 2. Power on the MFD and PFD in configuration mode. 3. Select no when “Do you want to update system files” is displayed on the screen of PFD. 4.

  • Page 131: Gdc 74A Air Data

    LRU Replacement Procedure GDC 74A (if installed) 1. Open the MFD, PFD (ESS BUS), and PFD (AVN BUS 1) circuit breakers. 2. Remove Garmin SD/MMC/FS 510 cards from bottom slots of the MFD and PFD if present. 3. Apply power to the G1000 system by connecting external power to the aircraft to energize the aircraft and avionics electrical busses.
  • Page 132 Legacy Replacement Procedure GDC 74A (Alternate Method) (if installed) 1. Insert the software loader card in the top slot of the PFD. 2. Power on the MFD and PFD in configuration mode. 3. Select no when “Do you want to update system files” is displayed on the screen of the PFD.

  • Page 133: Table 7-1, Altitude Test Points

    1. For GSU 75 installations, gain access to the aft avionics compartment in the tail of the aircraft. Locate the tee fittings in the pitot and static lines just forward of the GSU 75 and remove the capped nuts. Drain any condensation from the lines and tees. Reinstall the capped nuts onto the tees and tighten, ensuring caps are facing downward.

  • Page 134: Table 7-2, Airspeed Test Points

    Table 7-2, Airspeed Test Points PFD Airspeed Reading Test Set Airspeed Allowed Tolerance (from IAS field) +/- 5.0 +/- 3.0 +/- 2.0 +/- 2.0 +/- 2.0 +/- 2.0 Static Port Vertical Speed (Rate of Climb) Test 1. Command ADTS to change the altitude at the rates shown in the table below. 2.

  • Page 135: Grs 77 And Gmu 44 Magnetometer (If Installed)

    LRU Replacement Procedure GRS 77 (if installed) 1. Open the MFD, PFD (ESS BUS), and PFD (AVN BUS 1) circuit breakers. 2. Remove Garmin SD/MMC/FS 510 cards from bottom slots of the MFD and PFD if present. 3. Apply power to the G1000 system by connecting external power to the aircraft to energize the aircraft and avionics electrical busses.
  • Page 136 Legacy Replacement Procedure GRS 77 (Alternate Method) (if installed) 1. Insert the software loader card in the top slot of the PFD. 2. Power on the MFD and PFD in configuration mode. 3. Select no when “Do you want to update system files” is displayed on the screen of the PFD.

  • Page 137: Gmu 44 Magnetometer

    LRU Replacement Procedure GMU 1. Open the MFD, PFD (ESS BUS), and PFD (AVN BUS 1) circuit breakers. 2. Remove Garmin SD/MMC/FS 510 cards from bottom slots of the MFD and PFD if present. 3. Apply power to the G1000 system by connecting external power to the aircraft to energize the aircraft and avionics electrical busses.

  • Page 138: Gsu/Grs/Gmu Calibration Procedures

    6. Rotate the small FMS knob to display the drop down menu. Rotate the large FMS knob to highlight either “Baseline Option – GSU75 Installation” or “Baseline Option – Legacy – GRS77 and GDC74 Installation” as applicable. Press ENT key on the PFD. 7.

  • Page 139: Table 7-4, Required Grs/Gmu Calibrations

    Table 7-4, Required GRS/GMU Calibrations Calibrations Required Procedure A1: Procedure B: Procedure D: GSU 75 GSU/GRS/GMU Engine Run-up Condition or GRS 77 Magnetic Vibration Pitch/Roll Calibration Test Offset GMU 44 was removed and reinstalled. (no None Required. change in serial number) Continue to GSU/GRS/GMU Test Section.

  • Page 140: Figure 7-5, Grs/Gmu Calibration, Pitch/Roll Offset

    Figure 7-5, GRS/GMU Calibration, Pitch/Roll Offset NOTE On the calibration pages, “GRS” includes GRS and GSU units. 4. Ensure that the GRS 1 is selected in the SELECT GRS UNIT window on the PFD. 5. Activate the cursor and highlight the SELECT PROCEDURE window and select PITCH / ROLL OFFSET.
  • Page 141 Compass Rose Evaluation of Magnetic Disturbances for Magnetometer Calibration Procedure (Optional) NOTE The Magnetometer Calibration Procedure that follows in Section 7.10.3 (Calibration Procedure B) must be carried out at a site that is determined to be free of magnetic disturbances. If it is unsure whether the site is ‘clean’, the technician should verify that the site is ‘clean’...
  • Page 142 Procedure B: GSU 75 or GRS 77 and GMU 44 Magnetic Calibration NOTES Procedure A-1 (Section 7.10.1) must first be successfully accomplished before performing Procedure B, only for situations where the GSU/GRS was replaced with a new unit. On the calibration pages, “GRS” refers to whichever GRS or GSU unit is installed.
  • Page 143 completion of a 30 turn. If this scenario is encountered, it is best for the operator to ignore the “HOLD POSITION” command and instead use outside references to complete the approximate 30 turn. Instead of using the PFD instruction to turn as a real-time indication of when to turn, simply judge the 30° (±5°) turn increments of the aircraft by using the compass rose radials.

  • Page 144: Figure 7-6, Grs/Gmu Calibration, Engine Run-Up

    Procedure D: Engine Run-Up Vibration Procedure NOTES On the calibration pages, “GRS” refers to whatever GRS or GSU unit is installed. Calibration Procedure D is performed in order to guarantee that the ADAHRS/AHRS mounting is sufficiently rigid and insensitive to vibration. This procedure must be performed for both GSU/GRS units installed in the aircraft.
  • Page 145 6. The PFD informs the operator if the installation has passed or failed the vibration test. If the test fails, the specific measurements causing the failure are identified and associated numeric values are displayed on the PFD. NOTE Should a failure occur, the technician may perform the Engine Run-up test up to 3 times successively before corrective action must be taken.

  • Page 146: Figure 7-7, Normal Mode Ahrs Check

    Figure 7-7, Normal Mode AHRS Check If no other service is to be performed, continue to the return-to-service checks in Section 9. This area intentionally blank. G1000 Supplemental Maintenance Manual Page 7-41 Textron Nav III Series Revision 3 190-02128-04...

  • Page 147: Gdl 69A Or Gdl 69A Sxm Data Link (If Installed)

    LRU Replacement Procedure 1. Open the MFD, PFD (ESS BUS), and PFD (AVN BUS 1) circuit breakers. 2. Remove Garmin SD/MMC/FS 510 cards from bottom slots of the MFD and PFD if present. 3. Apply power to the G1000 system by connecting external power to the aircraft to energize the aircraft and avionics electrical busses.
  • Page 148 5. Activate cursor and rotate the small FMS knob to display the drop down menu. Rotate the large FMS knob to highlight “0X – XXX” (where 0X is the menu position and XXX is the airframe type) and press ENT key on the PFD. 6.

  • Page 149: Gsa 81 Servos (If Installed)

    LRU Replacement Procedure GSA81 Servos 1. Open the MFD, PFD (ESS BUS), and PFD (AVN BUS 1) circuit breakers. 2. Remove Garmin SD/MMC/FS 510 cards from bottom slots of the MFD and PFD if present. 3. Apply power to the G1000 system by connecting external power to the aircraft to energize the aircraft and avionics electrical busses.
  • Page 150 Legacy Replacement Procedure GSA81 Servos (Alternate Method) 1. Insert the software loader card in the top slot of the PFD. 2. Power on the MFD and PFD in configuration mode. 3. Select no when “Do you want to update system files” is displayed on the screen of the PFD.

  • Page 151: Garmin Traffic Systems (Gts 800) (If Installed)

    LRU Replacement Procedure GTS 1. Open the MFD, PFD (ESS BUS), and PFD (AVN BUS 1) circuit breakers. 2. Remove Garmin SD/MMC/FS 510 cards from bottom slots of the MFD and PFD if present. 3. Apply power to the G1000 system by connecting external power to the aircraft to energize the aircraft and avionics electrical busses.
  • Page 152 5. Activate cursor and rotate the small FMS knob to display the drop down menu. Rotate the large FMS knob to highlight “0X – XXX” (where 0X is the menu position and XXX is the airframe type) and press ENT key on the PFD. 6.
  • Page 153 3. Set up a stationary intruder by selecting the following on the ramp tester: • Intruder type: ATCRBS. • Intruder Start Distance: 2 nm • Intruder Start Altitude: 600 feet above field elevation • Vertical Speed: 0 fpm • Velocity: 0 kts (on some ramp testers, a velocity greater than 0 kts is required and a stationary intruder is created by not starting the scenario.) 4.

  • Page 154: Section 7 7-1–

    • Intruder Start Distance: 10 nm • Intruder Start Altitude : 600 ft above field altitude • Vertical Speed: 0 fpm • Velocity:600 kts 4. Initiate the intruder scenario and observe the following: • Traffic should be acquired at approximately 10 NM at 90 degree bearing and co- altitude.

  • Page 155: Subsystem Functional Checks

    8. Subsystem Functional Checks Stormscope Functional Check (if installed) Refer to the G1000 Nav III Line Maintenance Manual for Stormscope Functional Checks. If no other service is to be performed, continue to the return-to-service checks in Section 9. TAWS Functional Check For Functional Check of the TAWS-B system, refer to the G1000 Nav III Line Maintenance Manual.

  • Page 156: Chartview Functional Check

    9. If no other service is to be performed, continue to the return-to-service checks in Section ChartView Functional Check ChartView must be enabled using a ChartView Enable Card. Reference Section 3.8.1 for enabling procedures. NOTE The required ChartView databases are subscription-based and are to be procured by the aircraft owner directly from Jeppesen.

  • Page 157: Safetaxi Functional Check

    SafeTaxi Functional Check The maximum map ranges for enhanced detail are configurable by the flight crew. When zoomed in close enough to show the airport detail, the map reveals runways with numbers, taxiways with identifying letters/numbers, and airport landmarks including ramps, buildings, control towers, and other prominent features.

  • Page 158: Dme Functional Check

    DME Functional Check For DME Functional Check, refer to the G1000 Nav III Line Maintenance Manual. ADF Functional Check For ADF Functional Check, refer to the G1000 Nav III Line Maintenance Manual. GTS Traffic System Functional Check This section is applicable to the GTS 800 (TAS) traffic systems. Perform the following tests to verify GTS 800 operational and surveillance functions.
  • Page 159 Antenna Verification The following test assures the antennas and coaxial cables are properly connected. The GTS 800 must be in Ground Test mode. 1. On the Map – Traffic Map page of the MFD, press the TAS OPER softkey. A self-test of the antenna circuit is initialized.

  • Page 160: Search And Rescue Functional Check (If Installed)

    Ramp Test The following test provides a scenario that will converge and intercept the GTS 800 to assure proper operational and surveillance functions. 1. On the Map – Traffic Map page of the MFD, press the TAS OPER softkey. 2. Position ramp tester at 90 degrees. 3.

  • Page 161: G1000 System Return To Service Procedure

    9. G1000 System Return to Service Procedure If a G1000 LRU was replaced, verify the correct LRU software part numbers and versions against the numbers listed on the General Arrangement drawing listed in Table 1-1. Perform the following subsection tests to confirm the G1000 system is operating correctly. Display Test Apply aircraft power.

  • Page 162: Figure 9-2, Pfd Power-Up System Annunciations

    Figure 9-2, PFD Power-up System Annunciations Allow the displays to initialize for approximately one minute. During normal operation, this causes the airspeed, altitude, vertical speed, and OAT fields to be invalid during the first ~40-60 seconds of PFD power-up. After two minutes, verify no Red-X’s are present on the PFD and the MFD.

  • Page 163: Figure 9-3, Pfd Normal Operation

    (Without SVS enabled) (With SVS enabled) Figure 9-3, PFD Normal Operation G1000 Supplemental Maintenance Manual Page 9-3 Textron Nav III Series Revision 3 190-02128-04...

  • Page 164: Display Failure Test

    NOTE Outputs from the GRS 77 or GSU 75 (AHRS portion) and GMU 44 are not valid until the units have been calibrated. Check that all COM/NAV fields are valid in the top corners of the PFD. Check that altitude, airspeed, vertical speed, GS, TAS, and OAT fields are valid on PFD. Press the PFD Opt softkey on each PFD.

  • Page 165: Reversion Mode Check

    Reversion Mode Check Push the red DISPLAY BACKUP button on the GMA 1347. Verify that the PFD and MFD displays enter reversion mode (See Figure 9-4). MFD should have valid altitude, airspeed, vertical speed, COM1, COM2, NAV1, NAV2 and engine instruments. Figure 9-4, GDU Reversionary Mode De-activate reversion mode by pushing the DISPLAY BACKUP button.

  • Page 166: Gps Signal Acquisition

    GPS Signal Acquisition This test requires the aircraft to be outside to see the GPS satellites or indoors with a GPS repeater. Figure 9-5, AUX-GPS Status Page Select the AUX - GPS Status page on the MFD. After the G1000 system has been on for a minimum of two minutes, toggle between GPS 1 and GPS 2 using the two softkeys on the bottom of the display.

  • Page 167: Gps Failure Test

    GPS Failure Test Before starting this test, create a simple Direct-To flight plan to an airport or other waypoint that is greater than 31 NM from the present aircraft position. Verify that the phase of flight displayed on the GPS CDI is ENR. Step Desired Result For each of the single GPS failure conditions, the following...

  • Page 168: Gia Failure Test

    GIA Failure Test Step Desired Result GIA 1 Failure Condition: For a GIA 1 failure condition, the following shall occur: • Ensure GPS satellites are acquired. NAV 1 and COMM1 tuning fields on PFD are invalid (red X). Open NAV1/ENG (ESS BUS) and NAV1/ENG •...

  • Page 169: Gea Functional Check

    GEA Functional Check Verify the MFD engine instruments are displayed and indicate valid readings. Reference figure below for normal EIS Display. Note: 182T model EIS strip is shown. Other models are similar. On GMA, select DISPLAY BACKUP button. Observe MFD in reversion mode and verify all engine instruments are displayed and indicate valid readings.

  • Page 170: G1000 Backup Path Test

    G1000 Backup Path Test With both displays in normal mode and the entire avionics system turned on, verify on PFD there is not a system alert message stating “Failed Data Path". If this message is present, troubleshoot per Section 5.1.1 and resolve the issue before continuing. Maintenance Records Record the following information: •...

  • Page 171: Appendix A

    APPENDIX A - Garmin Unit Part and Serial Number Cross Reference This table allows shows the unit part number and serial number prefix combinations. SERIAL NUMBER FIRST PART NUMBER THREE DIGITS GIA 63W 011-01105-20 GDU 1054B (PFD & MFD) 011-03470-70 GDU 1050 (PFD &...

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