Page 1 Uncontrolled if Printed G1000 NXi Integrated Avionics System Line Maintenance Manual Kodiak 100 System Software Version 2633.00 or later 2634.00 or later 190-02102-00 August 2021 Revision 4...
Page 2 Uncontrolled if Printed BLANK PAGE...
Page 3 Wi-Fi Alliance. Sirius, XM, and all related marks and logos are trademarks of Sirius XM Radio, Inc. and its subsidiaries. The Bluetooth® word mark and logos are owned by the Bluetooth SIG, Inc. and any use of such marks by Garmin is under license.
Page 4 CANCER, BIRTH DEFECTS, OR REPRODUCTIVE HARM. THIS NOTICE IS BEING PROVIDED IN ACCORDANCE WITH CALIFORNIA PROPOSI- TION 65. FOR ANY QUESTIONS, OR FOR ADDITIONAL INFORMATION, REFER TO THE GARMIN WEB SITE AT WWW.GARMIN.COM/PROP65. CAUTION The GDU lens is coated with a special anti-reflective coating which is very sensitive to skin oils, waxes and abrasive cleaners.
Page 5 NOTE To protect against any SEUs, many Garmin LRUs incorporate hardware with Error Checking and Correcting (ECC) functionality. This hardware can detect an SEU and repair the changed memory state caused by the SEU.
Page 6 AND CONDITIONS OF THE FOLLOWING SOFTWARE LICENSE AGREEMENT. PLEASE READ THIS AGREEMENT CAREFULLY. Garmin Ltd. and its subsidiaries (“Garmin”) grants you a limited license to use the software embedded in the Garmin Product (the “Software”) in binary executable form in the normal operation of the Garmin Product.
Page 7: Table Of Contents
G1000 NXi System Controls ........
Page 8 Uncontrolled if Printed ______________________________________________________________________________ TABLE OF CONTENTS Section Page CONFIGURATION FILE STORAGE ......2-31 LOADER CARDS .
Page 9 Uncontrolled if Printed ______________________________________________________________________________ TABLE OF CONTENTS Section Page 4.3.13 OAT (Number 13) ..........4-8 4.3.14 GS (Number 14) .
Page 10 Uncontrolled if Printed ______________________________________________________________________________ TABLE OF CONTENTS Section Page 5.2.11 GTX 345R Transponder Replacement ......5-11 5.2.12 GTP 59 Outside Air Temperature Probe Replacement .
Page 11 Uncontrolled if Printed ______________________________________________________________________________ TABLE OF CONTENTS Section Page 7.6.2 Calibration Procedure A-2: Zero Pitch/Roll Offsets by Manual Entry ..7-15 7.6.3 Calibration Procedure B: Magnetometer Calibration ....7-16 7.6.4 Calibration Procedure C: Heading Offset Compensation .
Page 12 Uncontrolled if Printed ______________________________________________________________________________ TABLE OF CONTENTS Section Page 8.14.1 GSA 80/81 Greasing Procedure ........8-2 8.15 GSM 86 Servo Gearbox .
Page 13: Introduction
G1000 NXi system operation. 1.1 Line Maintenance Performing line maintenance on the G1000 NXi system consists of the following tasks: • Loading and Configuring System Software • Troubleshooting • LRU Replacement •...
Page 14: Supplemental Documents
______________________________________________________________________________ 1.8 Supplemental Documents The following documents supplement the information contained in this manual: • Kodiak 100 Pilot’s Guides, Garmin part numbers 190-02100-00 and 190-02534-01 • SN21-01 Kodiak 100 G1000 Software Configurations and Updates. • Kodiak 100 Aircraft Maintenance Manual •...
Page 15: Manual Distribution
The latest revision of this manual can be accessed in the Dealer Resource Center at dealers.garmin.com. 1.11 Activation of Garmin Connext Satellite Services Activation of a GSR 56 or GDL 69A SXM unit for Garmin Connext Satellite Services can be done at flyGarmin.com. NOTE In addition to Garmin Connext Satellite Services activation, refer to ‘GDL69...
Page 16 Uncontrolled if Printed ______________________________________________________________________________ BLANK PAGE ____________________________________________________________________________ Page 1-4 LMM for the Kodiak 100 190-02102-00 Rev.4...
Page 17: System Description And Operation
2.1 G1000 NXi Integrated Avionics System Description This section provides an overview of the G1000 NXi Integrated Avionics System as installed in the Kodiak 100. The G1000 NXi system is an integrated flight control system that presents flight instrumentation, position, navigation, communication, and identification information to the pilot through large-format displays.
Page 18 Uncontrolled if Printed ______________________________________________________________________________ Table 2-1. Kodiak 100 G1000 NXi System LRUs Part Number Type 011-01768-20 GWX 70R Airborne Weather Radar Optional 011-03997-00 GWX 75 Airborne Weather Radar Optional 011-03177-10 GDL 69A SXM Satellite Radio Receiver Optional 011-03177-15 GDL 69A SXM Satellite Radio Receiver...
Page 19 Uncontrolled if Printed ______________________________________________________________________________ Figure 2-1. Kodiak 100 Block Diagram-1 ____________________________________________________________________________ LMM for the Kodiak 100 Page 2-3 190-02102-00 Rev.4...
Page 20 Uncontrolled if Printed ______________________________________________________________________________ Figure 2-2. Kodiak 100 Block Diagram-2 ____________________________________________________________________________ Page 2-4 LMM for the Kodiak 100 190-02102-00 Rev.4...
Page 21: Lru Descriptions
Connecting through Wi-Fi requires a pilot-configurable Wi-Fi Protected Access WPA2 security password. By updating databases wirelessly, new databases can be transferred to the G1000 NXi system without taking the data card out of the aircraft. 2.2.3 GMA 1347 Audio Panel The GMA 1347 is a vertically oriented panel mounted audio control and marker beacon system.
Page 22: Gma 1360D Audio Panel
The GMC 710 Autopilot Mode Controller provides pitch and roll commands and displays them on the PFDs. The mode logic and flight director calculations are performed by the Garmin GIA 64W Integrated Avionics Unit (IAU) and are displayed on the pilot's and copilot's GDU 1050 primary flight displays.
Page 23: Gia 63W/Gia 64W Integrated Avionics Unit
ATCRBS Mode A, Mode C and Mode S All-Call interrogation. It also includes ADS-B In which provides TISB and FIS-B data via UAT and 1090 MHz. The transponder offers an optional Garmin altitude encoder to meet the required barometric pressure altitude source and an optional internal GPS/SBAS source to meet the required GNSS position source integrity for ADS-B Out.
Page 24: Grs 79 Altitude And Heading Reference System
(relative to aircraft structure), and placement position (relative to aircraft structure), and magnetic disturbances must be observed. Refer to the GRS 79 AHRS Installation Manual, Garmin P/N 190-01852-00, for details. 2.2.12 GTP 59 Outside Air Temperature Probe Each of the GTP 59 OAT probes provides outside air temperature data for use by the associated GDC 72 Air Data Computer.
Page 25: Gts 800 Traffic System
Uncontrolled if Printed ______________________________________________________________________________ 2.2.13 GTS 800 Traffic System The GTS 800 is a microprocessor-based Line Replaceable Unit (LRU) that uses active interrogations of Mode C transponders to provide Traffic Advisories to the pilot. When installed with a 1090 MHz ADS-B transmit class of equipment, the GTS 800 also utilizes passive surveillance.
Page 26: Gsa 80/81 Servo Actuator
Uncontrolled if Printed ______________________________________________________________________________ 2.2.17 GSA 80/81 Servo Actuator The GSA 80/81 Servo Actuators are electromechanical units that provide automatic control of a single flight axis (pitch, roll, or yaw) and/or their associated trims. The units contain a motor-control and monitor circuit board, as well as a solenoid and a brushless DC motor, all enclosed in an extruded aluminum housing.
Page 27: System Operation
2.3 System Operation 2.3.1 G1000 NXi System Controls Control and operation of G1000 NXi equipment as normally used in flight occurs through the PFD and MFD bezel controls, the GMA 1360D Audio Panel faceplate buttons, and the GMC 710 AFCS Controller.
Page 28 Uncontrolled if Printed ______________________________________________________________________________ Table 2-2. GDU Control Functions NAV VOL/ID • Controls NAV audio volume level. Knob • Press to toggle the Morse code identifier audio ON and OFF. NAV Frequency • Toggles the standby and active NAV frequencies. Transfer Key Dual NAV Knob •...
Page 29 Uncontrolled if Printed ______________________________________________________________________________ Table 2-2. GDU Control Functions (Continued) Dual FMS Knob • Press to turn the selection cursor On/Off. • Data Entry: With cursor on, turn to enter data in the highlighted field (large knob moves cursor location, small knob selects character for highlighted cursor location).
Page 30 Uncontrolled if Printed ______________________________________________________________________________ 2.3.1.3 GMA 1347 Audio Panel Controls Figure 2-5. GMA 1347 Controls ____________________________________________________________________________ Page 2-14 LMM for the Kodiak 100 190-02102-00 Rev.4...
Page 31 Uncontrolled if Printed ______________________________________________________________________________ Table 2-3. GMA 1347 Control Functions COM1 MIC Selects the #1 COM for transmitting. The COM1 receiver is simultaneously selected when this key is pressed, allowing received audio from the COM1 receiver to be heard. COM2 receiver audio can be added by pressing the COM2 Key.
Page 32 Uncontrolled if Printed ______________________________________________________________________________ Table 2-3. GMA 1347 Control Functions (Continued) 19 PLAY Press once to play the last recorded audio. Pressing the PLAY Key during play begins playing the previously recorded memory block. Each subsequent press of the PLAY Key begins playing the next previously recorded block.
Page 33 Uncontrolled if Printed ______________________________________________________________________________ 2.3.1.4 GMA 1360D Audio Panel Controls Figure 2-6. Audio Panel Controls ____________________________________________________________________________ LMM for the Kodiak 100 Page 2-17 190-02102-00 Rev.4...
Page 34 Uncontrolled if Printed ______________________________________________________________________________ Table 2-4. GMA 1360D Control Functions COM1 MIC Selects the #1 COM for transmitting. The COM1 receiver is simultaneously selected when this key is pressed, allowing received audio from the COM1 receiver to be heard. COM2 receiver audio can be added by pressing the COM2 Key.
Page 35 Uncontrolled if Printed ______________________________________________________________________________ Table 2-4. GMA 1360D Control Functions (Continued) 14 MUS1 Selects/deselects the MUS1 audio source and assigns the Bluetooth device to the MUS1 audio. Press the MUS1 button until the annunciator turns blue. The annunciator will cycle from OFF to WHITE to BLUE.
Page 36 Uncontrolled if Printed ______________________________________________________________________________ Table 2-4. GMA 1360D Control Functions (Continued) 23 Cursor (CRSR) Turn to move the cursor (flashing white or blue annunciator) Control Knob to the desired source. 24 Volume/Squelch Turn the smaller knob to control volume or squelch of the (VOL/SQ) selected source (indicated by the flashing white or blue Control Knob...
Page 37 ______________________________________________________________________________ 2.3.1.5 GMC 710 AFCS Controller Figure 2-7 shows the GMC 710 faceplate controls. The Garmin AFCS is mainly controlled through the GMC 710 AFCS Control Unit. The AFCS Control Unit consists controls listed below. Figure 2-7. GMC 710 Controls...
Page 38 Uncontrolled if Printed ______________________________________________________________________________ Table 2-5. AFCS Control Unit (GMC 710) CRS2 Knob Sets the copilot-selected course on the HSI of PFD2 when the VOR1, VOR2, or OBS/SUSP mode is selected. Pressing this knob centers the CDI on the currently selected VOR. The copilot-selected course provides course reference to the copilot-side flight director when operating in Navigation and Approach modes.
Page 39: Apply System Power
Uncontrolled if Printed ______________________________________________________________________________ 2.3.2 Apply System Power The system is integrated with the aircraft electrical system and receives power directly from electrical busses. The PFDs, MFD and supporting sub-systems include both power on and continuous built-in test features that exercise the processor, system memory, external inputs and outputs to provide safe operation.
Page 40 Uncontrolled if Printed ______________________________________________________________________________ Figure 2-8. PFD Initialization (both PFDs) Figure 2-9. MFD Start Page ____________________________________________________________________________ Page 2-24 LMM for the Kodiak 100 190-02102-00 Rev.4...
Page 41: Normal Operation
Uncontrolled if Printed ______________________________________________________________________________ 2.3.3 Normal Operation In normal operating mode, the PFD presents graphical flight instrumentation (attitude, heading, airspeed, altitude, vertical speed), replacing the traditional flight instrument cluster. The MFD displays a full-color moving map with navigation information, while the left portion of the MFD is dedicated to the Engine Indication System (see Figure 2-10).
Page 42: Configuration Mode
Reversionary Mode. 2.3.5 Configuration Mode Configuration mode enables configuring, checking, and calibrating the various G1000 NXi subsystems. Troubleshooting and diagnostics information can also be derived from the configuration pages when the system is in this mode.
Page 43: Set>Actv Configuration
Uncontrolled if Printed ______________________________________________________________________________ Figure 2-13. System Upload Page The FMS knob is the primary control for the G1000 NXi system when in configuration mode. It is located near the lower right corner of each display. FMS Control Functions: • To change page groups, turn the large FMS knob.
Page 44: Data Transmission
Uncontrolled if Printed ______________________________________________________________________________ NOTE 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. In the first example shown in Figure 2-14 the SET columns do not match the ACTIVE columns.
Page 45: Configuration Mode Navigation
2.5 SOFTWARE FILES Software files are defined by part number and version number in SN21-01 Kodiak 100 G1000 Software Configurations and Updates. Each 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 46: Configuration File Descriptions
Uncontrolled if Printed ______________________________________________________________________________ 2.6 CONFIGURATION FILE DESCRIPTIONS There are configuration files for baseline settings and various options. Configuration files contain preset selections for input/output channels, aircraft-specific settings, and LRU specific settings. CAUTION Certain software and configuration files are REQUIRED to be reloaded during maintenance that involves removal and replacement of system equipment.
Page 47: Configuration File Storage
Uncontrolled if Printed ______________________________________________________________________________ 2.7 CONFIGURATION FILE STORAGE The G1000 NXi is designed to store all configuration settings in various places so the configuration of the system is retained in the aircraft during maintenance. Figure 2-15 Figure 2-16 show a block diagram of how a typical G1000 NXi stores configuration settings.
Page 48: Loader Cards
Each loader card's part number defines all files found on the card for a specific installation. Approved loader card part numbers are found in SN21-01 Kodiak 100 G1000 Software Configurations and Updates. The display data card slots are located on the right side of the display bezels (Figure 2- 17).
Page 49: Sd Card Replacement
2.8.1 SD Card Replacement In the event a card(s) is lost or damaged, and requires replacement contact Garmin Aviation Support to order the replacement card(s). The authorized OEM service center or installing technician is required to give proof of the successful initial installation to the OEM and/or Garmin Aviation Support.
Page 50: Spare Supplemental Data Cards
______________________________________________________________________________ 2.8.2 Spare Supplemental Data Cards To ensure availability of data cards that are both compatible and authorized, Garmin offers blank replacement cards. These blank cards do not contain any preloaded aviation databases and are intended for operators who have already purchased databases from the flyGarmin website.
Page 51: Loading System Software And Configuration
______________________________________________________________________________ 3 LOADING SYSTEM SOFTWARE AND CONFIGURATION The G1000 NXi system does not contain the correct software or configuration settings for the Kodiak 100 when it is shipped from the factory. Those must be loaded when the system is initially installed.
Page 52: Readyboost
4. Click OK. 3.2.1 Display Digital Signature Check If loader card 006-B2634-0(X) is going to be installed, first determine if the G1000 NXi has had loader card 006-B2633-0(X) previously installed by checking the PFD1 MANIFEST config page or the MFD start-up page in the upper right corner. Alternately, check PFD1, MFD, and PFD2 displays if any were replaced if they have unit software versions 20.00 through 20.12 installed using configuration mode and the SYSTEM...
Page 53 1. Download the digital signature update executable program Garmin P/N 006- B3071-01 from the Garmin Dealer Resource center. Run the program to make an SD card for use in the aircraft. 2. Open the PFD1, MFD, and PFD2 circuit breakers.
Page 54: Pfd/Mfd Software Loading
Software is loaded to the displays first. To load the display software: 1. Pull the PFD and MFD circuit breakers. 2. Insert the correct G1000 NXi Daher Kodiak 100 Loader Card into the card slot of the display requiring the update. See Required Equipment List for correct Loader Card part number.
Page 55: System Upload For Software Versions 2633.00+ And 2634.00 To 2634.04
Uncontrolled if Printed ______________________________________________________________________________ 7. The following screen is displayed. Figure 3-4. File Update Verification 8. Software is loaded to the display. When complete, the display starts in configuration mode. 9. Repeat steps 1-8 for all displays that require the update. 10.
Page 56 Uncontrolled if Printed ______________________________________________________________________________ 5. An UPDATED xx FILES SUCCESSFULLY! screen is displayed. New software is loaded to PFD2. 6. When complete, PFD2 starts in configuration mode. 7. Remove power to PFD2 by pulling the PFD2 circuit breaker. 8. Remove the Software/Configuration card loader from PFD2 and insert it into the top card slot on the MFD.
Page 57 Uncontrolled if Printed ______________________________________________________________________________ Figure 3-5. 006-B2633-0(X) Loader Card Example Figure 3-6. 006-B2634-0(X) Loader Card Example 4. Once the Group choice is selected, the cursor moves to the ITEM window. Turn the small FMS knob to activate the drop-down menu. Highlight the appropriate baseline configuration, then press the ENT key to select it.
Page 58 Figure 3-10. Options Selection 5. Press the CHK All softkey. 6. For aircraft that do not have Garmin GMA 1347/1360 audio panels installed, manually uncheck the GMA 1347/1360 software and configuration files by using the small FMS knob to scroll down and highlight the software or configuration.
Page 59 Uncontrolled if Printed ______________________________________________________________________________ box, then press the ENT key to uncheck the selection. Do this for all GMA 1347/ 1360 files. 7. If a CARD COPY item is present, manually uncheck the configuration box by using the small FMS knob to scroll down and highlight the configuration box, then press the ENT key to uncheck the selection.
Page 60 Uncontrolled if Printed ______________________________________________________________________________ Figure 3-12. Update Complete 16. After all option files are loaded, go to the Optional Features Enablement section next. Table 3-1. Version 2633+ Options Configuration Options Action Quest Kodiak - F/W Installation Option Load this option only for Fish and Wildlife aircraft.
Page 61 Quest Kodiak - AFCS Option Load this option only if Garmin GFC 700 Autopilot System is installed on the aircraft. Quest Kodiak - FS 510 Installation Option Load this option only if a Flight Stream 510 is going being used.
Page 62 Uncontrolled if Printed ______________________________________________________________________________ Table 3-2. Version 2634.00 to 2634.04 Options Configuration Options Action Quest Kodiak - F/W Installation Option Load this option only for Fish and Wildlife aircraft. Quest Kodiak - Aerocet 6650 Float Load this option only if Aerocet 6650 Option floats are installed.
Page 63 Quest Kodiak - AFCS Option Load this option only if Garmin GFC 700 Autopilot System is installed on the aircraft. Quest Kodiak - FS 510 Installation Load this option only if a Flight Stream Option 510 is going being used.
Page 64: System Upload For Software Version 2634.05 And Later
A review of the Kodiak aircraft equipment list or maintenance records should provide the actual equipment installed. If the current Garmin system functions, a review of the Aux System Status Page or Transaction Log will indicate what hardware that is actually or was installed on the aircraft.
Page 65: Baseline Software And Configuration Loading
Uncontrolled if Printed ______________________________________________________________________________ 8. Remove the Software/Configuration card loader from PFD2 and insert it into the top card slot on the MFD. Repeat Steps 2 through 5 for the MFD, using the MFD to hold Softkey #12 (far right) down. 9.
Page 66 GRS79 AHRS and GMU 44B Magnetometers. 04 - Autopilot GFC 700 Load when equipped with the GFC700 Autopilot System. 05 - GEA GEA 71B Load when equipped with the GEA 71B Garmin Engine Airframe. ____________________________________________________________________________ Page 3-16 LMM for the Kodiak 100 190-02102-00 Rev.4...
Page 67 Uncontrolled if Printed ______________________________________________________________________________ Table 3-3. Loader Card Folder Structure Kodiak Series - SW2634.05 and Later Group Item Details 06 - Transponder • GTX 345R-00 • Load when equipped with the • GTX 345R-01 GTX345R PN 011-03303-00 transponder. • Load when equipped with the GTX345R PN 011-03303-01 transponder.
Page 68 Uncontrolled if Printed ______________________________________________________________________________ Table 3-3. Loader Card Folder Structure Kodiak Series - SW2634.05 and Later Group Item Details 013 - ELT GPS Position - RS232 • Load when equipped with the ELT 1000. This option configures GIA 1 RS-232 Channel 2 to output GPS position data.
Page 69: Loading Optional Equipment Software And Configuration
Following this, the configuration for the optional systems must be repeated. 1. Insert the correct G1000 NXi Kodiak 100 Loader Card into the PFD1 top card slot, if it is not already in the PFD. 2. Start both the PFDs and the MFD in configuration mode.
Page 70 • Part Number 010-00330-HH, CVDR 1. Remove power from the PFDs and the MFD by opening the PFD1, PFD2 and MFD circuit breakers. 2. A special enablement card is required to enable some optional G1000 NXi features. This example refers to TAWS enablement. NOTE An enablement card can only enable the applicable feature on one system (one aircraft).
Page 71: Crossfill Monitoring System
Uncontrolled if Printed ______________________________________________________________________________ Figure 3-14. Upload Complete Confirmation 13. View the SUMMARY field and ensure the loaded items are COMPLETED. 14. Repeat Step 1 through Step 13 to load any other desired options requiring an enable card. 15. De-activate the cursor. 16.
Page 72 Uncontrolled if Printed ______________________________________________________________________________ Figure 3-15. Crossfill Monitor The Crossfill Monitor immediately fails if it detects that a configured LRU (PFD, MFD) is not online. This is because an offline device could cause the problem the monitoring system was meant to prevent if it did not receive the configuration, or if it received only partial configuration.
Page 73 Uncontrolled if Printed ______________________________________________________________________________ Figure 3-17. Crossfill Failed In this case, the summary window displays the configured LRU or LRUs it detects as being offline. Figure 3-18. Crossfill Summary The Crossfill Monitor waits indefinitely for crossfill to complete, but after 10 minutes it displays a message advising the technician that something may be wrong.
Page 74 Uncontrolled if Printed ______________________________________________________________________________ Figure 3-20. Unsynced Summary The listed LRUs would be the ones to check for the problems mentioned in the troubleshooting section. The crossfill will still be ongoing even after the user cancels, though it will no longer be monitored. Figure 3-21.
Page 75: Crossfill Troubleshooting
Uncontrolled if Printed ______________________________________________________________________________ 3.8.1 Crossfill Troubleshooting 1. Possible causes of a failure for this include the following: a) An LRU is not online or is not connected to the uploading LRU. b) An LRU is configured and should not be. 2.
Page 76: Software And Configuration Load Troubleshooting
Uncontrolled if Printed ______________________________________________________________________________ d) The Crossfill Monitoring system is advisory (it doesn't perform cross-filling, it monitors) and cross-filling proceeds normally, so waiting 10 minutes (which is the crossfill timeout time) still applies. 3.9 Software and Configuration Load Troubleshooting Table 3-4. Software/Config Troubleshooting Problem Solution GDU 1050 MFD or PFD display...
Page 77: System Communication Hierarchy
Manual, the aircraft may be returned to service. Record the following information in appropriate aircraft maintenance logs: • Part number of the G1000 NXi Kodiak 100 Loader Card used to perform software loading or software updates. • Part numbers and versions of LRU software files reported after maintenance is complete (found at the System Status page in configuration mode).
Page 78: Aviation Database Loading
Uncontrolled if Printed ______________________________________________________________________________ 3.11 Aviation Database Loading 1. With the system OFF, remove an SD Card from the top SD card slot of the MFD. 2. Download and install the databases on an SD card. 3. Put the SD Card in the top SD card slot of the MFD. 4.
Page 79 Uncontrolled if Printed ______________________________________________________________________________ 10. Remove the SD card from the bottom slot of the MFD if desired. 11. Remove and reapply power to the system. 12. Press the ENT Key or the right-most softkey on MFD display to acknowledge the startup screen.
Page 80: Final Configuration Items
Uncontrolled if Printed ______________________________________________________________________________ e) Press the ENT Key or the right-most softkey on MFD display to acknowledge the startup screen. f) Turn the large FMS Knob and select Aux. g) Turn the small FMS Knob and select Databases. h) Make sure the standby databases transferred and are now in the Active col- umn.
Page 81: Fuel Flow Configuration
Uncontrolled if Printed ______________________________________________________________________________ 8. Press the Set GTS softkey (if present) and acknowledge the PFD1 prompt by pressing the ENT key 9. Deactivate the cursor. 10. Turn large FMS knob to select GTX 3X5 configuration page group. 11. Turn the small FMS knob to select Transponder Airframe Config page. 12.
Page 82: Engine Serial Number
Uncontrolled if Printed ______________________________________________________________________________ Configure K Factor 1. Select the FUEL TANK CALIBRATION Page in the CAL Page Group. 2. Using the softkeys along the bottom of the screen, enter the following pass code: 12, 11, 10, 9. The cursor should now appear on the screen. NOTE Softkeys are numbered 1 to 12, left to right.
Page 83: Date And Time Setting (Optional)
Uncontrolled if Printed ______________________________________________________________________________ 3.12.4 Date and Time Setting (Optional) NOTE This setting may allow the GPS to acquire satellites more rapidly. 1. Select the System Setup Page. 2. Press the FMS knob. 3. Use the large and small FMS knob to enter the current UTC date and time. 4.
Page 84 Uncontrolled if Printed ______________________________________________________________________________ BLANK PAGE ____________________________________________________________________________ Page 3-34 LMM for the Kodiak 100 190-02102-00 Rev.4...
Page 85: Troubleshooting
In addition to the troubleshooting information presented in this section, it should be noted that Garmin LRUs carry out Built-In Test (BIT) and performance checks on a full time basis. They do not require a special request to run the BIT cycle. All LRUs report health and diagnostic information to the display in real time.
Page 86: System Annunciations
______________________________________________________________________________ 4.3 System Annunciations NOTE Operating the G1000 NXi in the vicinity of metal buildings, metal structures, or electromagnetic fields can cause sensor differences that may result in nuisance annunciations during start up, shut down, or while taxiing. If one or both sensed values are unavailable, it will be annunciated as a NO COMP (no compare).
Page 87: Nav1 Or Com1 (Numbers 1 & 4)
Uncontrolled if Printed ______________________________________________________________________________ Figure 4-1. Failure Annunciations (PFD) 4.3.1 NAV1 or COM1 (Numbers 1 & 4) 1. Check for GIA1 configuration, software, or failed data path error messages. Correct any errors before proceeding. 2. Switch GIA1 and GIA2 to verify the location of the problem. If the problem follows GIA1, replace GIA1.
Page 88: Nav2 Or Com2 (Numbers 1 & 4)
Uncontrolled if Printed ______________________________________________________________________________ 4.3.2 NAV2 or COM2 (Numbers 1 & 4) 1. Check for GIA2 configuration, software, or failed data path error messages. Correct any errors before proceeding. 2. Switch GIA2 and GIA1 to verify the location of the problem. If the problem follows GIA2, replace GIA2.
Page 89: Altitude (Number 5)
Uncontrolled if Printed ______________________________________________________________________________ 3. Check that no related alert messages are present on PFD1 (press the ALERTS softkey). 4. Isolate the fault to an LRU. Replace this LRU and confirm the resolution of the annunciation. 5. Isolate the fault to an LRU. Replace this LRU and confirm the resolution of the annunciation.
Page 90: Hdg (Number 10)
Uncontrolled if Printed ______________________________________________________________________________ 4. Make sure a cell phone or Wi-Fi/Bluetooth technology is not turned on in the cabin (even in a monitoring state). 5. Check the GPS strength bars on both GPS receivers on the GPS 1 or GPS 2 Status Display on the MFD.
Page 91: No Traffic Data (Number 11)
NOTE Option and enablement cards will need to be replaced if the master configuration module is changed. The G1000 NXi System ID number will change to a new number when installing a new master config module. 4. Load the correct GTS 800 software.
Page 92: Oat (Number 13)
Uncontrolled if Printed ______________________________________________________________________________ 4.3.13 OAT (Number 13) 1. Check the GTP 59 wiring and connectors for faults or damage. 2. Check the GDC 72 config module wiring for damage and replace if any is found. 3. Replace the GDC 72 config module. 4.
Page 93: Flaps (Number 16)
Uncontrolled if Printed ______________________________________________________________________________ Figure 4-2. Failure Annunciations (MFD) 4.3.16 FLAPS (Number 16) 1. Check the flap position - GEA 71/GEA 71B wiring. 2. Replace the GEA 71/GEA 71B. 4.3.17 ELEV (Number 17) 1. Check the elevator trim - GEA 71/GEA 71B wiring. 2.
Page 94: Ail (Number 19)
Uncontrolled if Printed ______________________________________________________________________________ 4.3.19 AIL (Number 19) 1. Check the GEA 71/GEA 71B wiring. 2. Replace the GEA 71/GEA 71B. 4.3.20 Assorted Engine/Airframe Sensors (Number 20) 1. 1.Check the PFD Alert Window for GIA1/2 or GEA configuration, software or failed data path error messages.
Page 95: System Messages
Uncontrolled if Printed ______________________________________________________________________________ 4.4 System Messages NOTE New Terrain/Obstacle cards, Jeppesen Aviation Database and other optional features (i.e. TAWS unlock card) will need to be replaced if the master configuration module is changed. The System ID number will change to a new number when installing a new master configuration mod- ule.
Page 96 Uncontrolled if Printed ______________________________________________________________________________ Table 4-1. Troubleshooting System Messages (Continued) Possibly Faulty System Message Description LRU / Subsystem AHRS1 SRVC The AHRS1 magnetic-field model • GRS 79 is out of date. AHRS1 TAS AHRS1 is not receiving valid true • GRS 79 airspeed.
Page 97 Uncontrolled if Printed ______________________________________________________________________________ Table 4-1. Troubleshooting System Messages (Continued) Possibly Faulty System Message Description LRU / Subsystem COM2 CONFIG COM2 configuration error. • GIA 64W • Master Config Module COM2 INOP - CRNT GIA COM current. • Aircraft supply voltage to the GIA 64W •...
Page 98 Uncontrolled if Printed ______________________________________________________________________________ Table 4-1. Troubleshooting System Messages (Continued) Possibly Faulty System Message Description LRU / Subsystem G/S1 FAIL A failure has been detected in the • GIA 64W Glideslope subsystem of GIA1. G/S1 SERVICE A failure has been detected in the •...
Page 99 Uncontrolled if Printed ______________________________________________________________________________ Table 4-1. Troubleshooting System Messages (Continued) Possibly Faulty System Message Description LRU / Subsystem GIA 1 INOP - CRNT Check GIA1 Current. • Aircraft supply voltage to the GIA 64W • Wiring GIA 1 INOP - SERL (COM) Internal GIA Serial •...
Page 100 Uncontrolled if Printed ______________________________________________________________________________ Table 4-1. Troubleshooting System Messages (Continued) Possibly Faulty System Message Description LRU / Subsystem GIA 2 INOP - SERL (COM) Internal GIA Serial • Aircraft supply Communication Fault (COM voltage to the Transceiver). GIA 64W • GIA 64W GIA 2 INOP - SERL (GPS) Internal GIA Serial •...
Page 101 Uncontrolled if Printed ______________________________________________________________________________ Table 4-1. Troubleshooting System Messages (Continued) Possibly Faulty System Message Description LRU / Subsystem PILOT PTT STUCK GMA 1 Pilot Push-to-Talk is Stuck. • Pilot Push-to- Talk Switch • GMA 1360D COPILOT PTT STUCK GMA 1 Copilot Push-to-Talk is •...
Page 102 Uncontrolled if Printed ______________________________________________________________________________ Table 4-1. Troubleshooting System Messages (Continued) Possibly Faulty System Message Description LRU / Subsystem HDG FAULT AHRS1 magnetometer fault has • GMU 44/44B occurred. HW MISMATCH GIA HW mismatch. Only one GIA • GIA 64W is SBAS capable. GPS information loss of integrity •...
Page 103 Uncontrolled if Printed ______________________________________________________________________________ Table 4-1. Troubleshooting System Messages (Continued) Possibly Faulty System Message Description LRU / Subsystem NAV 2 INOP - CONFIG A NAV software or configuration • GIA 64W fault. NAV 2 INOP - INTRL A NAV internal fault. •...
Page 104: System Status Page
Uncontrolled if Printed ______________________________________________________________________________ 4.5 System Status Page The System Status Page on the MFD provides LRU health status by means of a green check mark or red X indication (see Figure 4-3). Software versions are listed for installed LRUs, along with other database versions and dates. If a red X is shown for an LRU, refer to the associated troubleshooting information in Section 4.7.
Page 105: Lru Visual Inspections
4.6.1.1 Shield Block Grounds G1000 NXi connectors may employ a Shield Block grounding system to provide necessary ground reference to shielding and/or transducers. The shield block termination method allows multiple grounds to be terminated directly to a block mounted to the backshell assembly.
Page 106 Uncontrolled if Printed ______________________________________________________________________________ 4.6.1.8 GRS 79 Inspect the GRS 79 unit, rack, and connector for corrosion or other defects. Check the integrity of the SHIELD BLOCK ground attachments to the harness connector assembly as well as the integrity of the individual shields and their attachment. Inspect wiring harness for chaffing.
Page 107 Uncontrolled if Printed ______________________________________________________________________________ Contact Garmin Aviation support before disassembly or removal of roll servo cable(s). 4.6.1.12 GMU 44/44B Visually inspect the GMU 44/44B and rack. Inspect the mounting hardware and GMU 44/ 44B for corrosion or other damage. Inspect the mounting hardware and GMU 44/44B for corrosion or other damage.
Page 108: Lru Troubleshooting
4.7 LRU Troubleshooting This section contains troubleshooting information and procedures for the various components of the G1000 NXi system. Check the servo control cable to ensure no fraying, corrosion, or other damage exists. If the condition of the cable is questionable, replace it with a new one.
Page 109 Uncontrolled if Printed ______________________________________________________________________________ Table 4-2. GDU 1050 System Messages (Continued) System Message Cause Recommended Actions DB MISMATCH Terrain database • Load the correct database mismatch. type and version in both displays. FAILED PATH A data path connected to • Determine which data path a GDU and/or GIA has has failed and check wiring failed.
Page 110 Uncontrolled if Printed ______________________________________________________________________________ Table 4-2. GDU 1050 System Messages (Continued) System Message Cause Recommended Actions MFD1 VOLTAGE MFD1 has low voltage. • Check input voltage to the GDU. • If the input voltage is correct, replace the GDU. PFD1 BACKLIGHT CAL PFD1 backlight calibration •...
Page 111 Uncontrolled if Printed ______________________________________________________________________________ Table 4-2. GDU 1050 System Messages (Continued) System Message Cause Recommended Actions XTALK ERROR A flight display crosstalk • Check the PFD Alerts error has occurred. A PFD window for database errors and an MFD are not and correct all faults before communicating with each proceeding.
Page 112 8. Ensure the SD card is from SanDisk. Use of other SD cards is not approved. 9. If the card was inserted with the label facing to the right, do not attempt to remove. Return the unit to Garmin for repair. ____________________________________________________________________________...
Page 113 2. If the problem is verified, replace the GDU. 4.7.1.3 Garmin SVT™ (Synthetic Vision Technology) Troubleshooting The optional Synthetic Vision Technology (SVT) is a visual enhancement to the G1000 NXi. SVT depicts a forward-looking attitude display of the topography immediately in front of the aircraft.
Page 114 Uncontrolled if Printed ______________________________________________________________________________ SVT is intended to be used with traditional attitude, heading, obstacle, terrain, and traffic inputs. SVT is disabled when valid attitude or heading data is not available for the display. In case of invalid SVT data, the PFD display reverts to the standard blue-over- brown attitude display.
Page 115: Gma 1360D Audio Panel Troubleshooting
Uncontrolled if Printed ______________________________________________________________________________ 4.7.2 GMA 1360D Audio Panel Troubleshooting 4.7.2.1 GMA 1360D System Messages Table 4-4 lists GMA 1360D related system messages, possible causes, and recommended actions. Table 4-4. GMA 1360D System Messages System Message Cause Recommended Actions PILOT PTT STUCK GMA The Pilot push-to-talk •...
Page 116 Uncontrolled if Printed ______________________________________________________________________________ Table 4-4. GMA 1360D System Messages (Continued) System Message Cause Recommended Actions GMA 1 PANEL STUCK The Front Panel key for • Cycle power to the unit. KEY Front Panel Key is the GMA is stuck. •...
Page 117 Uncontrolled if Printed ______________________________________________________________________________ Table 4-4. GMA 1360D System Messages (Continued) System Message Cause Recommended Actions GMA 1 CONFIG The audio panel • Reload configuration to the configuration settings do GMA. not match backup • If the problem persists, configuration memory. replace the GMA.
Page 118 Uncontrolled if Printed ______________________________________________________________________________ 4. Turn all electrical equipment On and Off (strobes, other radios, etc.) and check for noise. 5. If the noise is identified as coming from one electrical system or component, refer to the OEM approved Aircraft Maintenance Manual for information about eliminating the noise source.
Page 119 Uncontrolled if Printed ______________________________________________________________________________ Figure 4-5. GMA Configuration Page/Disable Split Com ____________________________________________________________________________ LMM for the Kodiak 100 Page 4-35 190-02102-00 Rev.4...
Page 120: Gia 64W Integrated Avionics Unit Troubleshooting
GIA 64W related system messages, possible causes, and recommended actions. NOTE If necessary, retrieve log from CMC Diagnostic Folder and provide it to the OEM or Garmin for assistance with further troubleshooting Table 4-5. GIA 64W System Messages System Message Cause...
Page 121 Uncontrolled if Printed ______________________________________________________________________________ Table 4-5. GIA 64W System Messages (Continued) System Message Cause Recommended Actions AHRS1 GPS AHRS1 not receiving any • Check AFMS limitations. GPS information. • Ensure no device using cell phone, Wi-Fi, or Bluetooth technology is turned on (even in a monitoring state) in the aircraft cabin.
Page 122 Uncontrolled if Printed ______________________________________________________________________________ Table 4-5. GIA 64W System Messages (Continued) System Message Cause Recommended Actions AHRS1 GPS AHRS1 is operating • Ensure no device using cell exclusively in no-GPS phone, Wi-Fi, or Bluetooth mode. technology is turned on (even in a monitoring state) in the aircraft cabin.
Page 123 Uncontrolled if Printed ______________________________________________________________________________ Table 4-5. GIA 64W System Messages (Continued) System Message Cause Recommended Actions COM1 INOP - CRNT The COM subsystem of • Check the aircraft supply GIA1 is inoperative due voltage. to a current fault. • Check input voltage to the GIA.
Page 124 Uncontrolled if Printed ______________________________________________________________________________ Table 4-5. GIA 64W System Messages (Continued) System Message Cause Recommended Actions COM1 REDUCED TX The COM sub-system of • Check input voltage to the POWER the GIA is operating in a GIA while transmitting. reduced power transmit •...
Page 125 Uncontrolled if Printed ______________________________________________________________________________ Table 4-5. GIA 64W System Messages (Continued) System Message Cause Recommended Actions COM1 TEMP The system has detected • Check the fan, wiring, and an over temperature air tubing for proper condition in COM1. The ventilation (if applicable). transmitter is operating at •...
Page 126 Uncontrolled if Printed ______________________________________________________________________________ Table 4-5. GIA 64W System Messages (Continued) System Message Cause Recommended Actions COM2 MANIFEST COM2 has incorrect • Load the correct software. software installed and communication has halted. COM2 PTT The COM2 push-to-talk • Press the PTT switch to (PTT) key line is stuck in cycle its operation.
Page 127 Uncontrolled if Printed ______________________________________________________________________________ Table 4-5. GIA 64W System Messages (Continued) System Message Cause Recommended Actions G/S1 FAIL A failure has been • Replace the GIA. detected in Glideslope subsystem of GIA1. G/S1 SERVICE A failure has been • Cycle power to the GIA. detected in the Glideslope •...
Page 128 • If the problem persists, replace the GIA. • If the problem persists, contact Garmin Aviation Support for assistance. GIA 1 INOP - CRNT Check GIA1 Current. • Aircraft supply voltage to the GIA 64W.
Page 129 • Replace the cooling fan if not sure it is operating properly. • If the problem persists, replace the GIA. • If the problem persists, contact Garmin Aviation Support for assistance. ____________________________________________________________________________ LMM for the Kodiak 100 Page 4-45 190-02102-00 Rev.4...
Page 130 Uncontrolled if Printed ______________________________________________________________________________ Table 4-5. GIA 64W System Messages (Continued) System Message Cause Recommended Actions GIA2 MANIFEST GIA2 software mismatch. • Load correct software. GIA2 SERVICE The GIA1 self-test has • Cycle power to the GIA. detected a problem in the •...
Page 131 Uncontrolled if Printed ______________________________________________________________________________ Table 4-5. GIA 64W System Messages (Continued) System Message Cause Recommended Actions GPS1 SERVICE A fault has been detected • If the message persists in the GPS1 receiver. The through a normal power receiver may still be cycle, replace the GIA.
Page 132 Uncontrolled if Printed ______________________________________________________________________________ Table 4-5. GIA 64W System Messages (Continued) System Message Cause Recommended Actions NAV1 INOP - INTRL NAV internal fault. • Cycle power to the GIA. • Replace the GIA. NAV1 INOP - SERL An internal NAV serial •...
Page 133 Uncontrolled if Printed ______________________________________________________________________________ Table 4-5. GIA 64W System Messages (Continued) System Message Cause Recommended Actions NAV2 INOP - SERL An internal NAV serial • Check data bus wiring. communication fault. • Check status of the other LRU. • Retrieve log from CMC fault folder.
Page 134 • Locate the GIA as far as possible from all COM antennas. • If a COM antenna is found to be the problem, a 1.57542 GHz notch filter (Garmin P/ N 330-00067-00) can be installed in the VHF COM coax, as close to the COM as possible.
Page 135 Uncontrolled if Printed ______________________________________________________________________________ 3. A window showing the SIDETONE setting is displayed (see Figure 4-6). 4. Check the sidetone setting and adjust as necessary. The range is -100 to +100. Figure 4-6. COM Setup Page Sidetone Adjustment 5. If the problem continues; switch GIA1 and GIA2, and reconfigure both GIAs at their new locations, to verify if the unit or the aircraft wiring is the problem.
Page 136 Uncontrolled if Printed ______________________________________________________________________________ 4. Turn off the PFD and MFD by pulling the associated circuit breakers. Restart the PFD and MFD in configuration mode. 5. Select the COM SETUP page on the PFD. 6. Select GIA1 or GIA2 in the COM Setup window. This forces an update of the calibration data values and must be accomplished before making any changes.
Page 137 Uncontrolled if Printed ______________________________________________________________________________ 4.7.3.7 GPS Troubleshooting 4.7.3.7.1 GPS Receiver Operation Each GIA contains a GPS receiver. Information collected by the specified receiver (GPS1 for GIA1 or GPS2 for GIA2) can be viewed on the GPS1 or GPS2 Status pane (see Figure 4-9).
Page 138 Uncontrolled if Printed ______________________________________________________________________________ 2. Touch the GPS1 button to select the GIA1 GPS receiver. The button annunciator is green when enabled and subdued when disabled. The system displays the GPS1 STATUS pane. 3. Touch the GPS2 button to select the GIA2 GPS receiver. The button annunciator will be green when selected.
Page 139 Uncontrolled if Printed ______________________________________________________________________________ 4.7.3.7.5 GPS Satellite Signal Strengths The GPS1 and GPS2 Status Panes can be helpful in troubleshooting weak (or missing) signal levels due to poor satellite coverage or installation problems. As the GPS receiver locks onto satellites, a signal strength bar is displayed for each satellite in view, with the appropriate satellite PRN number (01-32 or 120-138 for WAAS) below each bar.
Page 140 Uncontrolled if Printed ______________________________________________________________________________ Figure 4-10. Date / Time Setup Page 4. Switch GIA1 and GIA2 to verify the location of the problem. If the problem follows the unit, clear the GPS almanac by performing the following steps. a) Select the GIA Serial (RS-232 / ARINC 429) Configuration Page (see Figure 4-11).
Page 141 Uncontrolled if Printed ______________________________________________________________________________ Figure 4-11. GIA RS-232 / ARINC 429 Configuration Page 5. If clearing nonvolatile memory is unsuccessful and the GPS still cannot acquire a position, Reload the GIA audio and configuration files. Also, reload the configuration files for any optional equipment which is installed on the aircraft that require the GIA configuration to be updated.
Page 142 GIA1 and COM2 circuit breakers. If problem is resolved, the GPS1 antenna has failed. 3. Contact Garmin Aviation Product Support for a replacement antenna. Return the failed antenna to Garmin for engineering evaluation.
Page 143: Gea 71B Engine And Airframe Unit Interface Troubleshooting
GEA 71 related system messages, possible causes, and recommended actions. NOTE If necessary, retrieve log from CMC Diagnostic Folder and provide it to the OEM or Garmin for assistance with further troubleshooting Table 4-6. GEA 71B System Messages System Message Cause...
Page 144 Uncontrolled if Printed ______________________________________________________________________________ Table 4-6. GEA 71B System Messages (Continued) System Message Cause Recommended Actions GEA 1 INOP EXCIT - The GEA is inoperative • Cycle power to the unit. Check GEA Transducer due to an excitation • Check the input voltage to Power Outputs voltage fault.
Page 145 Uncontrolled if Printed ______________________________________________________________________________ Table 4-6. GEA 71B System Messages (Continued) System Message Cause Recommended Actions GEA 1 CM INOP - The GEA Config Module • Cycle the power to the unit. COMM: Check GEA is inoperative due to loss •...
Page 146: Gtx 345R Transponder Troubleshooting
Figure 4-12 provides a general troubleshooting flowchart. Refer to the Garmin GTX 33x and GTX 3x5 ADS-B Maintenance Manual (190-00734-11) for further troubleshooting information and additional flowcharts.
Page 147 Uncontrolled if Printed ______________________________________________________________________________ Figure 4-12. GTX 3x5R General Troubleshooting Flowchart ____________________________________________________________________________ LMM for the Kodiak 100 Page 4-63 190-02102-00 Rev.4...
Page 148: Gts Troubleshooting
GTS and volume is not set too low. Calibration Fault Factory calibration • If the unit fails to go into invalid. operate mode then return to Garmin for service. ____________________________________________________________________________ Page 4-64 LMM for the Kodiak 100 190-02102-00 Rev.4...
Page 149 Ensure that power and ground connections to the GPA 65 are connected in their proper place. Verify input voltage and if it continues return to Garmin for service. 1030 MHz Fault • Internal Fault. • Replace the unit. 1090 MHz Fault PA/LNA Fault •...
Page 150 Uncontrolled if Printed ______________________________________________________________________________ Table 4-8. GTS Troubleshooting (Continued) Problem Cause Solution TCAS Equipage Fault Broken wire, improper • Verify configuration settings configuration. on the transponder and the GTS. Ensure proper wiring between the transponder and the GTS. Radio Altitude Fault •...
Page 151: Gwx Processor Troubleshooting
Uncontrolled if Printed ______________________________________________________________________________ 4.7.7 GWX Processor Troubleshooting Figure 4-13. WARNING SAFE DISTANCE DETERMINATION - THE FOLLOWING INFORMATION ESTABLISHES A MINIMUM SAFE DISTANCE FROM THE ANTENNA FOR PERSONNEL NEAR AN OPERATING AIRBORNE WEATHER RADAR. THE MINIMUM SAFE DISTANCE IS BASED UPON THE FCC EXPOSURE LIMIT AT 9.3 TO 9.5 GHZ FOR GENERAL POPULATION/ UNCONTROLLED ENVIRONMENTS WHICH IS 10 MW/CM2.
Page 152 Uncontrolled if Printed ______________________________________________________________________________ WARNING MAXIMUM PERMISSIBLE EXPOSURE LEVEL (MPEL)- THE ZONE IN WHICH THE RADIATION LEVEL EXCEEDS THE 1 MW/CM2, IS THE SEMI-CIRCULAR AREA WITHIN A RADIUS OF 7.4 FT FROM THE 10" ANTENNA, 9.6 FT FROM THE 12" ANTENNA, AND 14 FT FROM THE 18" ANTENNA AS INDICATED IN THE ILLUSTRATION BELOW.
Page 153 Uncontrolled if Printed ______________________________________________________________________________ WARNING AIRBORNE WEATHER RADAR SHOULD BE OPERATED ON THE GROUND ONLY BY QUALIFIED PERSONNEL. INSTALLED AIRBORNE RADAR SHOULD NOT BE OPERATED WHILE THE AIRCRAFT IS IN A HANGER OR OTHER ENCLOSURE UNLESS THE RADAR TRANSMIT- TER IS NOT OPERATING, OR THE ENERGY IS DIRECTED TOWARD AN ABSORPTION SHIELD WHICH DISSIPATES THE RADIO FRE- QUENCY ENERGY.
Page 154 Uncontrolled if Printed ______________________________________________________________________________ 4.7.7.1 GWX 75 Troubleshooting Table Table 4-10 lists the various GWX Processor fault indication descriptions and corrective actions. NOTE The fault indications are reset if PFD1 is transitioned from normal mode to configuration mode. It will return if the fault is persistent. It may not return if the fault is intermittent.
Page 155 Uncontrolled if Printed ______________________________________________________________________________ Table 4-10. GWX Processor Troubleshooting (Continued) Fault Indication Cause Solution AFC Status Indicator • Radar receiver signal • Replace the GWX if strength below condition remains. minimum threshold. • Not viewable in config mode. Temp Status Indicator •...
Page 156 Uncontrolled if Printed ______________________________________________________________________________ Table 4-10. GWX Processor Troubleshooting (Continued) Fault Indication Cause Solution RAM Status Indicator • Internal SW execution • Ensure the software, failure or RAM including FPGA, is up to component failure. date. • Replace the GWX 80. •...
Page 157 Uncontrolled if Printed ______________________________________________________________________________ 4.7.7.2 Miscellaneous Radar Faults Table 4-11. Possible Radar Faults Symptom Possible Cause Recommended Action Radar audibly noisy Excessive gear train • Remove radome. during ground operation. noise or radome • Inspect interior surfaces of interference. the radome for contact with the radar dish.
Page 158 Uncontrolled if Printed ______________________________________________________________________________ Table 4-11. Possible Radar Faults (Continued) Symptom Possible Cause Recommended Action Radar fails to make a full Radome Interference or • Remove the radome and vertical or horizontal GWX 80 failure inspect interior surfaces for sweep on the screen. contact with the radar dish.
Page 159: Grs 79 / Gmu 44B (Ahrs) Troubleshooting
Uncontrolled if Printed ______________________________________________________________________________ 4.7.8 GRS 79 / GMU 44B (AHRS) Troubleshooting 4.7.8.1 AHRS Description In addition to using internal sensors, the GRS 79 AHRS uses GPS information, magnetic field data and air data to assist in attitude/heading calculations. In normal mode, the AHRS relies upon GPS and magnetic field measurements.
Page 160 GRS 79 related system messages, possible causes, and recommended actions. NOTE If necessary, retrieve log from CMC Diagnostic Folder and provide it to the OEM or Garmin for assistance with further troubleshooting. Table 4-12. GRS 79 System Messages System Message Cause...
Page 161 Uncontrolled if Printed ______________________________________________________________________________ Table 4-12. GRS 79 System Messages (Continued) System Message Cause Recommended Actions AHRS1 GPS AHRS1 not receiving • Ensure no device using cell any, or any useful, GPS phone, Wi-Fi, or Bluetooth information. technology is turned on (even in a monitoring state) in the aircraft cabin.
Page 162 Uncontrolled if Printed ______________________________________________________________________________ Table 4-12. GRS 79 System Messages (Continued) System Message Cause Recommended Actions AHRS1 SERVICE A failure has been • Replace the GRS. detected in ADHARS1. AHRS1 SRVC The ADHARS1 • Update the magnetic-field magnetic-field model is model.
Page 163 Uncontrolled if Printed ______________________________________________________________________________ Table 4-12. GRS 79 System Messages (Continued) System Message Cause Recommended Actions AHRS2 GPS AHRS2 not receiving • Ensure no device using cell any, or any useful, GPS phone, Wi-Fi, or Bluetooth information. technology is turned on (even in a monitoring state) in the aircraft cabin.
Page 164 Uncontrolled if Printed ______________________________________________________________________________ Table 4-12. GRS 79 System Messages (Continued) System Message Cause Recommended Actions AHRS2 SERVICE A failure has been • Replace the GRS. detected in AHRS2. AHRS2 SRVC The AHRS2 magnetic- • Update the magnetic-field field model is out of model.
Page 165 Uncontrolled if Printed ______________________________________________________________________________ 4.7.8.4 GPS Input Failure Two GPS inputs are provided to the AHRS. If GPS information from one of the inputs fails, the AHRS uses the operating GPS input and a System Message is issued to inform the flight crew.
Page 166 Uncontrolled if Printed ______________________________________________________________________________ Table 4-14. AHRS Troubleshooting Symptom Recommended Action The attitude appears to be • Make sure no cell phone or device using cell phone unstable. technology is turned on in the cabin, even in a monitoring state. •...
Page 167 Uncontrolled if Printed ______________________________________________________________________________ Table 4-15 lists attitude and heading outputs the GRS can provide based on the available data inputs. Table 4-15. GRS 79 Inputs and Outputs GRS 79 Input GRS 79 Output GRS 79 Mode Heading Pitch Roll Data Data Data...
Page 168 Uncontrolled if Printed ______________________________________________________________________________ 4.7.8.9 GRS 79 Troubleshooting Questions If possible, ask the operator the following questions to help gather the information to accurately troubleshoot the GRS 79: 1. What specifically was the nature of the failure? Was it a red X of only heading, only pitch/roll, or both? 2.
Page 169 ______________________________________________________________________________ 3. Apply ground power to the aircraft. Energize the system and record the system software level. This will be needed if assistance from Garmin Aviation Support is required. 4. After the system has initialized (about one minute from applying power), note any red X or system messages.
Page 170 15. Replace the GRS. 16. If the problem persists, replace the GRS configuration module. 17. Contact Garmin Aviation Support for additional assistance if the condition is not resolved. 4.7.8.11 Heading Red X For heading issues, a heading red X (steady or intermittent) is the typical fault indication.
Page 171 Uncontrolled if Printed ______________________________________________________________________________ When taxiing without reliable GPS information, heading performance is susceptible to the presence of magnetic anomalies (metal buildings, underground steel culverts, steel grates in the ramp). Localized sources of interference on the ground might consistently red X the heading in the same spot while taxiing, this is not caused by a failure of the GMU 44 or its calibration.
Page 172: Gdc 72 Air Data Computer Troubleshooting
GDC 72 related system messages, possible causes, and recommended actions. NOTE If necessary, retrieve log from CMC Diagnostic Folder and provide it to the OEM or Garmin for assistance with further troubleshooting. Table 4-17. GDC 72 System Messages System Message Cause...
Page 173: Gtp 59 Outside Air Temperature Probe Troubleshooting
2. Determine which instrument is outside limits and recalibrate or replace. Both units might individually meet specifications but show a difference in altitude. Do not return a unit to Garmin for service if it meets specifications. 3. Recalibrate the unit if it does not meet the specifications.
Page 174: Gdl 69A Sxm Satellite Radio Receiver Troubleshooting
• the label on the back of the GDL 69A SXM Datalink Receiver Contact Garmin Aviation Support if the Audio and Data Radio IDs cannot be located. SiriusXM uses the coded IDs to send an activation signal to enable the system to receive weather data and/or audio entertainment programming.
Page 175 Uncontrolled if Printed ______________________________________________________________________________ NOTE Complete instructions for activating the SiriusXM satellite radio can be found in document 190-00355-04 ‘GDL 69 Series SiriusXM® Satellite Radio Activation Instructions’. 4.7.11.3 GDL 69A SXM General Troubleshooting Table 4-19. GDL 69A Troubleshooting Guide Problem Probable Cause Corrective Action No communication...
Page 176: Afcs Troubleshooting
4.7.12 AFCS Troubleshooting The Garmin AFCS is a digital Automatic Flight Control System (AFCS) which is inte- grated into various components of the G1000 NXi System. This section covers upon key items to note while troubleshooting the AFCS. Should a problem be encountered during the operation of the AFCS, the pilot and main- tenance personnel should first evaluate the overall status and condition of the G1000 NXi System.
Page 177 • Review the fault and assert logs for the GIAs and servos. • Isolate the fault to an LRU, airframe switch, or wiring using the information in the fault log. Contact Garmin Aviation Support for assistance, if needed. ____________________________________________________________________________ LMM for the Kodiak 100 Page 4-93 190-02102-00 Rev.4...
Page 178 Uncontrolled if Printed ______________________________________________________________________________ Table 4-20. AFCS Annunciations (Continued) Annunciation Condition Recommended Actions Pitch Failure - Pitch • Check the Avionics Status page to see if the axis control failure. servo is online (green check mark). AP is inoperative. • Ensure the affected servo is receiving power. •...
Page 179 Uncontrolled if Printed ______________________________________________________________________________ Table 4-20. AFCS Annunciations (Continued) Annunciation Condition Recommended Actions Aileron Mistrim • Roll servo providing sustained force in the Right. indicated direction. • Check for possible fuel imbalance. Aileron Mistrim • Check the aileron control adjustments. Left.
Page 180 To access the GIA and GSA Maintenance Logs, perform the following steps: 1. Start the G1000 NXi system in configuration mode. 2. Use the FMS knob on the PFD to go to the Diagnosis Terminal page in the PFD configuration pages System group.
Page 181 Uncontrolled if Printed ______________________________________________________________________________ Table 4-21. (Continued)GIA Maintenance Log Faults Fault Description PFT FAIL: Timeout, Preflight test has failed because the specified step has <STEP> not passed in the allotted time. See the GIA preflight steps for a description of the possible values for <STEP> on the failed GIA and corrective actions.
Page 182 Uncontrolled if Printed ______________________________________________________________________________ Table 4-21. (Continued)GIA Maintenance Log Faults Fault Description PRMTR: • The mode specified by <MODE> has been disengaged <PARAMETER> MODE: because the parameter specified by <PARAMETER> <MODE> Parameter lost has become invalid. The following is a list of some of the possible values for <PARAMETER>: •...
Page 183 Uncontrolled if Printed ______________________________________________________________________________ 4.7.12.3.5 PFT Step 4: System Initializing, Verify AHRS Monitor This step checks to verify the AHRS monitor is valid and not reporting and AHRS failure. NOTE AHRS monitor will be assumed valid if on the ground. •...
Page 184 Uncontrolled if Printed ______________________________________________________________________________ 4.7.12.3.13 PFT Step 12: Verify Servo PFT Status This test checks to verify all servos have passed their own preflight test. 4.7.12.3.14 PFT Step 13: Verify AP Disconnect Enabled This steps checks to verify GIA1, GIA2, and all servos are connected to the 28-volt autopilot disconnect.
Page 185 Uncontrolled if Printed ______________________________________________________________________________ The monitor processor contains the logs that are found in these processors: 2 – Pitch Servo 4 – Roll Servo 6 - Yaw 8 – Pitch Trim Servo There are two main groupings of faults that can occur in the monitor processor. The first grouping of faults can occur during the GSA unit pre-flight test (PFT).
Page 186 Uncontrolled if Printed ______________________________________________________________________________ Table 4-23. Normal Mode Faults Monitor Fault Notes GIA DIS FAULT Check the AP Disconnect power to the unit. HOST DATA DIF Check the AHRS wiring to the system. HOST DATA INV Check the AHRS wiring to the system. SVO PWER INV Check unit power and AP Disconnect power.
Page 187 Uncontrolled if Printed ______________________________________________________________________________ Table 4-24. PFT Faults Monitor PFT Step Notes INTERNAL COMM This can sometimes be the result of a failure on the TESTFAIL other board. Check faults on the other processor. CTL MOT PWR ON FAIL Check unit power and AP Disconnect power. MON SOL PWR ON FAIL Check unit power and AP Disconnect power.
Page 188: Downloading Gia And Gsa Maintenance Logs
Continue to scroll through all the OUTPUT data until you see the text End of Fault Log. 9. If you need to download Servo fault logs (usually done at the request of Garmin Product Support), perform the following steps. Otherwise, skip to step 10.
Page 189: Downloading Assert (Diagnostic) Logs
4.7.14 Downloading Assert (Diagnostic) Logs If additional assistance is needed in troubleshooting LRU faults, assert logs for selected LRUs can be downloaded to an SD card as encrypted files and emailed to Garmin Aviation Product Support for evaluation. Contact Garmin Aviation Product Support before sending a log to prevent any delay in response.
Page 190 7. Repeat steps 4-7 for any additional LRUs which require data. 8. Power down the system and remove the SD card. 9. Insert the assert log as an attachment to an email and include the LRU download order. Send to Garmin Aviation Product Support at avionics@Garmin.com. ____________________________________________________________________________ Page 4-106 LMM for the Kodiak 100 190-02102-00 Rev.4...
Page 191: Additional Troubleshooting
4.8 Additional Troubleshooting This section contains additional information that can aid in the troubleshooting process. 4.8.1 Aircraft Report An Aircraft Report is a human readable report generated by the G1000 NXi system to publish pertinent information about the system (see Figure 4-21).
Page 192 MFD units. This file is available in a human readable csv format. An equivalent file in encrypted zip format is also generated. This is a tamper proof means of manually send- ing the file to Garmin. (through email/web portal upload). Manual: The report file can also be generated manually, using the configuration mode System Status page on the GDU.
Page 193: Aircraft Copy / Fleet Copy
4.8.1.2 Auto Export Through Garmin GFDS Server Using GSAF Protocol The G1000 NXi system is capable of being set up to auto transmit the aircraft report file upon landing. This uses the Garmin Send Any File (GSAF) format for export through Iridium (RUDICS) or Wi-Fi.
Page 194 There are two cases to be considered for system import. Import into the same system: When the source and target G1000 NXi system has the same system ID, system import is supported without requiring special permissions or an enablement card.
Page 195: Cmc Maintenance Log Exporting
8. Restart the system in normal mode after the upload is completed. NOTE If the import side G1000 NXi system has an additional or missing LRU, the software/configuration/option associated with that unit will not get automat- ically imported. These items can get loaded using manual selection using the System Upload page.
Page 196 Uncontrolled if Printed ______________________________________________________________________________ Figure 4-22. MFD Aux-Maintenance Logs page 3. Select the folder for export. Figure 4-23. File Selected for Export ____________________________________________________________________________ Page 4-112 LMM for the Kodiak 100 190-02102-00 Rev.4...
Page 197 Uncontrolled if Printed ______________________________________________________________________________ 4. Press the Export Button, and then press OK. Figure 4-24. Selected File Exporting 5. Once the Status indicates ‘Exported’, the file will be on the SD card in a folder with the same name as the log folder (in this case, FOLDER_0). Figure 4-25.
Page 198 Uncontrolled if Printed ______________________________________________________________________________ BLANK PAGE ____________________________________________________________________________ Page 4-114 LMM for the Kodiak 100 190-02102-00 Rev.4...
Page 199: Lru Replacement
Disconnect any auxiliary power supplies when performing LRU replacement. NOTE This section lists reference documents which contain additional information for installing Garmin LRUs. The technician should read all of this relevant reference material before removing and reinstalling an LRU. NOTE Software and configuration must be loaded to an LRU after it has been replaced.
Page 200: Gdu 1050 Display Unit Replacement
Uncontrolled if Printed ______________________________________________________________________________ 5.2.1 GDU 1050 Display Unit Replacement Unit Part Number: 011-03470-10 Garmin Reference Documents: • Captive Screw Hardware Replacement Instructions: 190-00313-65. • SPIDER Installation Instructions: 190-00313-03. • Shield Block Installation Instructions: 190-00313-09. • Installation Manual: 190-00303-92. The GDU 1050 is installed by holding the unit flush with the instrument panel. The locking studs should be oriented with the alignment marks in the vertical position for installation.
Page 201: Gma1360D/Gma1347 Audio Panel Replacement
Uncontrolled if Printed ______________________________________________________________________________ 5.2.2 GMA1360D/GMA1347 Audio Panel Replacement Unit Part Number: 011-03568-20 or 011-00809-00 Installation Manual Part Number: 190-03813-00 or 190-00303-20 CAUTION Switch off No. 2 GMA when No. 2 GIA is being replaced. If No. 2 GMA was not switched off, then reload the config for No.
Page 202: Gia 64W/63W Integrated Avionics Unit Replacement
• 190-00355-02 GDL 69/69A Installation Manual • 190-00522-01 GA 55A, GA 56A, GA 57 Installation Instructions • 190-00483-01 GA 56W Antenna Installation Instructions • 004-00287-00 Antenna Minimum Performance Specification for the Garmin GPS/ WAAS Receiver System 1. To Remove: a) Loosen the Phillips screw (or pull on the D-Ring and twist counter-clockwise 90°, for units with a D-Ring).
Page 203: Gmc 710 Afcs Control Unit
______________________________________________________________________________ 5.2.4 GMC 710 AFCS Control Unit Unit Part Number: 011-01020-10 Garmin Installation Manual: 190-00303-70 1. To Remove: a) Use a 3/32" hex drive tool to turn each of the four locking sockets ¼ turn counterclockwise until they reach their stops.
Page 204: Gmu 44/44B Magnetometer Replacement
If the GMU 44/44B is removed, the anti-rotation properties of the mounting screws must be restored. This may be done by replacing the screws with new Garmin P/N 211-60037-08. If original screws must be re-used, coat screw threads with Loctite 242 (blue) thread-locking compound, Garmin P/ N 291-00023-02, or equivalent.
Page 205 Uncontrolled if Printed ______________________________________________________________________________ b) Slide the GDC 72 forward to remove from the remote rack. 2. To Reinstall: a) Place the GDC 72 (with endplate mount assembly installed) on the remote rack. b) Slide the GDC 72 back (with endplate mount assembly facing forward) until the feet are fully engaged with the remote rack.
Page 206: Gea 71/71B Engine And Airframe Interface Unit Replacement
The application of torque exceeding 14 in-lbs. to the screw may result in damage to the LRU case and/or retaining hardware. If the retaining hard- ware is damaged during installation, a replacement hardware kit, Garmin part number K00-00652-00, is available. Reference Garmin part number 190-00313-65 for instructions on replacing the retaining hardware.
Page 207: Gdl 69A Sxm Satellite Radio Receiver Replacement
Uncontrolled if Printed ______________________________________________________________________________ 5.2.9 GDL 69A SXM Satellite Radio Receiver Replacement Installation Manual: 190-00355-07 GDL 69 Series SiriusXM Activation Instructions: 190-00355-04 CAUTION Carefully start the handle screw into the hole to avoid cross-threading. Damage to the LRU case and/or hardware will occur if a torque value of 14 in-lbs.
Page 208: Gts Traffic System
Uncontrolled if Printed ______________________________________________________________________________ 5.2.10 GTS Traffic System Unit Part Number: 011-01356-00 GTS 8XX Installation Manual: 190-00587-00 GTS 8XX Maintenance Manual: 190-00587-01 1. To remove: a) If a cooling hose is attached to the unit, remove it from the air fitting and set aside.
Page 209: Gtx 345R Transponder Replacement
Uncontrolled if Printed ______________________________________________________________________________ 5.2.11 GTX 345R Transponder Replacement Unit Part Number: GTX 345R 011-03303-01 Installation Manual Part Number: 190-01499-02 WARNING TURN OFF AIRCRAFT POWER BEFORE REMOVAL OR REINSTALLA- TION OF THE TRANSPONDER. UNPLUG ANY AUXILIARY POWER SUPPLY 1. To Remove: a) Insert a 3/32”...
Page 210 Uncontrolled if Printed ______________________________________________________________________________ 2. To Reinstall: a) Place the ring terminal over the end of the sensor. b) Insert the sensor and ring terminal into the hole in the aircraft skin. c) Slide the washer onto the sensor. d) Thread the washer onto the sensor. e) Tighten the nut to 100 ±20 in-lbs using the deep well socket and open end wrench.
Page 211: Gwx 70R/75 Weather Radar
Uncontrolled if Printed ______________________________________________________________________________ 5.2.13 GWX 70R/75 Weather Radar Unit Part Number: 011-03997-00 or 011-01768-20 Garmin Installation Manual: 190-02009-00 NOTE Take care to avoid any contact between tools that can become magnetized and the magnetron. Even momentary contact of a potentially magnetic object with the magnetron case will cause serious weakening of the mag- netic field.
Page 212: Gsa 80/81 Servo Actuators
Uncontrolled if Printed ______________________________________________________________________________ 5.2.14 GSA 80/81 Servo Actuators Unit Part Numbers: GSA 80: 011-00877-20, GSA 81: 011-00878-20 Installation Manuals: 190-00303-72 and 190-00303-83 NOTE The technician should be familiar with information contained in the GSA 8X/GSM 85(A) and the GSM 86 Servo Gear Box Installation Manuals (part numbers 190-00303-72 and 190-00303-83 respectively) before performing maintenance on the autopilot servo equipment.
Page 213: Gsm 86 Servo Gearbox
If foreign object/debris contamination of either the servo actuator or servo mount is suspected, immediately return the contaminated unit(s) to Garmin for repair. CAUTION Do not disassemble the servo actuator or servo mount. There is no require- ment or provision for routine maintenance, lubrication, or field repair of the servo actuator or servo mount.
Page 214: Configuration Module Replacement
Uncontrolled if Printed ______________________________________________________________________________ 5.2.16 Configuration Module Replacement Figure 5-1. Configuration Module Installation Figure 5-2. Configuration Module Kit - 011-00979-03 1. To Remove: a) Disconnect the connector (1) from the LRU. b) Remove the two screws (5) from the cover (4) and remove the cover. c) Unplug the connector from the configuration module (3).
Page 215 Press the UPDT CFG softkey. 4. If both the PFD and the Master Configuration Module are replaced, configuration must be reloaded to all LRUs in the G1000 NXi system except the GRS 79, GMU 44B, and GDC 72. Refer to...
Page 216: Gea 71B Backshell Thermocouple Removal And Replacement
Uncontrolled if Printed ______________________________________________________________________________ 5.2.17 GEA 71B Backshell Thermocouple Removal and Replacement The GEA 71B has a K-Type thermocouple (Item 1 shown below) installed in its back- shell, in addition to the configuration module. The thermocouple is used in conjunction with the configuration module temperature sensor to compensate for temperature probe errors resulting from the dissimilar metals at the pin contacts.
Page 217 Uncontrolled if Printed ______________________________________________________________________________ 1. To Remove: a) Remove the GEA 71B. b) Remove the GEA 71B connector backplate. c) Remove connector assembly J711 from the backplate. d) Remove screws, item 7, and cover, item 6, from the backshell, item 5. e) Unscrew thermocouple from boss on backshell.
Page 218 Uncontrolled if Printed ______________________________________________________________________________ BLANK PAGE ____________________________________________________________________________ Page 5-20 LMM for the Kodiak 100 190-02102-00 Rev.4...
Page 219: Reloading Software And Configuration
Uncontrolled if Printed ______________________________________________________________________________ 6 RELOADING SOFTWARE AND CONFIGURATION This section provides procedures to be followed after equipment is replaced. 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 220: Transaction Log Page
Section NOTE Garmin recommends the use of SanDisk brand SD cards to reload soft- ware and configuration. If another brand of card is used, and software load- ing problems occur, replace the card with a SanDisk brand card and reattempt loading.
Page 221: Reloading Procedures
Uncontrolled if Printed ______________________________________________________________________________ 6.3 Reloading Procedures NOTE If the technician skips the reloading of a replaced LRU, an ‘LRU replace- ment detected’ message is shown on the GDU in normal mode. This mes- sage persists until the LRU software reloading procedure is performed. The ‘LRU replacement detected’...
Page 222: Lrus With Unique Loading Procedures
Uncontrolled if Printed ______________________________________________________________________________ 6.3.1 LRUs with Unique Loading Procedures When LRUs contain multiple subassemblies (i.e., GIA contains the following subassemblies: GIA, COM, NAV, and GPS), each subassembly must go through the replacement process. It is not sufficient just to load the LRU only. 1.
Page 223: Card Copy Management
Uncontrolled if Printed ______________________________________________________________________________ 3. Blank - This indicates the GDU to LRU synchronization status information is not available for that LRU. Any configuration mismatches will be reported elsewhere on the system. 4. Gray Not Supported - This indicates the GDU to LRU synchronization status information is not supported for that LRU.
Page 224: Alternate Loading Procedures
Uncontrolled if Printed ______________________________________________________________________________ 6.5 Alternate Loading Procedures In the case of any unresolved faults encountered during the reloading of LRU software and configuration described in Section 6.3, perform the reloading of software and configuration according to the following: 1. Load Baseline software and configuration per Section 2.
Page 225: Grs 79 Ahrs / Gmu 44(B) Magnetometer
The GDL 69A will also have to be activated. Follow the instructions in Section 3 to load the GDL software and configuration files. Activation of the GDL 69A unit for Garmin Connext Satellite Services can be done at flygarmin.com. ____________________________________________________________________________ LMM for the Kodiak 100 Page 6-7...
Page 226 Uncontrolled if Printed ______________________________________________________________________________ BLANK PAGE ____________________________________________________________________________ Page 6-8 LMM for the Kodiak 100 190-02102-00 Rev.4...
Page 227: Lru Testing And Calibration
7 LRU TESTING AND CALIBRATION This section contains LRU testing and calibration procedures to ensure proper operation of the G1000 NXi system after maintenance has been performed and software has been reloaded to the affected unit(s). Throughout this section, reference is made to softkey numbers.
Page 228 Uncontrolled if Printed ______________________________________________________________________________ NOTE The following steps are for two GMA1360D's installed; if one GMA is installed, push the red display reversion button on the GMA 1360D. Verify both displays enter reversionary mode (both should have valid altitude, air- speed, vertical speed, and engine instruments).
Page 229: Gia 64W/63W Testing
Uncontrolled if Printed ______________________________________________________________________________ 7.2 GIA 64W/63W Testing 7.2.1 GPS Signal Acquisition Figure 7-2. Aux - GPS Status Page (MFD) The GIA 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 230: Vhf Com Interference Test
Uncontrolled if Printed ______________________________________________________________________________ 7.2.2 VHF COM Interference Test NOTE Conduct this test outside. A GPS repeater operating inside a hangar may result in a failed test. This procedure assumes the system is currently set to 25 kHz COM channel spacing. 1.
Page 231: Vor/Loc/Gs Test
Uncontrolled if Printed ______________________________________________________________________________ 16. Repeat Step 14 and Step 15, and re-transmit while monitoring GPS2 signal levels on the MFD. 17. Repeat Step 14 through 16 for each of the following frequencies: • 121.190 MHz • 130.285 MHz • 131.290 MHz 18.
Page 232: Transceiver Operational Check
Uncontrolled if Printed ______________________________________________________________________________ 7. Select PA and verify the PA select annunciator is illuminated. Make sure the COM1 active frequency is displayed white. 8. Initiate passenger address using pilot's headset boom mic by keying the pilot's PTT. Check the following: •...
Page 233: Marker Beacon Test
Uncontrolled if Printed ______________________________________________________________________________ 7.3.4 Marker Beacon Test 1. Using a ramp tester, simulate the outer marker, middle marker and inner marker signals by following the test equipment manufacturer instructions. Make sure that each marker audio signal is present over the headphones and speaker. 2.
Page 234: Gea 71/71B Engine And Airframe Interface Unit
Uncontrolled if Printed ______________________________________________________________________________ 7.4 GEA 71/71B Engine and Airframe Interface Unit If the unit is removed or replaced, the following tests are recommended: 1. The system Engine Indication System (EIS) displays critical engine, electrical, fuel, and other system parameters on the left side of the Multi Function Display (MFD) during normal operations.
Page 235: Gtx 345R Transponder
Uncontrolled if Printed ______________________________________________________________________________ 4. To test the GEA 71/71B, start the system in normal mode. The Engine Indicator System gauges should become valid within two minutes of system power being supplied. 7.5 GTX 345R Transponder The transponder system must be verified in accordance with Title 14 of the Code of Federal Regulations (14 CFR) §§...
Page 236: Ads-B Out Test
Uncontrolled if Printed ______________________________________________________________________________ 7.5.2 ADS-B Out Test The ADS-B Out test procedure requires the use of a Mode S transponder ramp tester, such as an Aeroflex IFR-6000 or TIC TR-220. Specific instructions for operating the ramp tester are contained in the applicable operator's manual. To perform the test, do the following: 1.
Page 237: Gdc 72 Testing
GPS source. 7.5.3 GDC 72 Testing Per Part 43 Appendix E, paragraph (b)(2), Garmin specifies a test procedure equivalent to Part 43 Appendix E, paragraph (b)(1) with two exceptions. The tests of sub-para- graphs (iv) (Friction) and (vi) (Barometric Scale Error) are not applicable because the digital outputs of the GDC 72 are not susceptible to these types of errors.
Page 238 Uncontrolled if Printed ______________________________________________________________________________ Table 7-1. Post-Installation Calibration Procedure Summary Calibration Procedure Procedure Installations Requiring Procedure Procedure Name Description Pitch/Roll Offset Level Aircraft Either procedure A-1 or A-2 is Compensation required for all installations. Pro- cedure A-1 is recommended. Zero Pitch/Roll Manually enter This procedure should be used Offsets by Man-...
Page 239 GMU 44 unit. Garmin recom- mends this test be performed at least once every 12 months by all aircraft manufacturers on a mini-...
Page 240: Calibration Procedure A-1: Pitch
Uncontrolled if Printed ______________________________________________________________________________ Any degaussing of the area near the GMU 44(B) mounting location requires repeating the magnetometer calibration procedure (Procedure B), and if recommended initially, the heading offset compensation procedure (Procedure C). A repeat of the pitch/roll offset procedure (either Procedure A-1 or A-2) requires a repeat of the magnetometer calibration procedure (Procedure B), and also (if previously recommended) a repeat of the heading offset compensation procedure (Procedure C).
Page 241: Calibration Procedure A-2: Zero Pitch/Roll Offsets By Manual Entry
4. Select PITCH/ROLL OFFSET, then press the ENTER key. If the PITCH/ROLL OFFSET selection is still flashing, press the ENTER key again. Contact Garmin for the passcode. 5. Follow the checklist items displayed on the PFD and press the ENTER key as each one is completed or confirmed.
Page 242: Calibration Procedure B: Magnetometer Calibration
Uncontrolled if Printed ______________________________________________________________________________ 13. When the RECORD OFFSETS field is flashing, press the ENTER key to complete data entry. 14. The result of the pitch/roll offset compensation is displayed on the PFD. If successful, the AHRS records the required pitch and roll offsets, informs the operator of a successful conclusion and then returns to normal operation.
Page 243 Uncontrolled if Printed ______________________________________________________________________________ Figure 7-5. Fixed Wing Aircraft Position Example With the aircraft stationary, initiate the magnetometer calibration procedure as follows: 1. Enter configuration mode (refer to Section 2.3.5 as needed). 2. Select the GRS/GMU Calibration page on the PFD. The GRS/GMU Calibration page is protected and requires a keystroke password to perform the calibration.
Page 244: Calibration Procedure C: Heading Offset Compensation
Uncontrolled if Printed ______________________________________________________________________________ NOTE Due to high winds or excessive airframe vibration, the operator might encounter a condition where the PFD restarts the 18-second countdown without full completion of the previous countdown. If this is encountered more than once for a given station, the operator should begin turning to the next station (approximately 30 degress).
Page 245: Calibration Procedure D: Engine Run-Up Vibration Test
Uncontrolled if Printed ______________________________________________________________________________ 3. Follow the checklist items displayed on the PFD and press the ENTER key as each one is completed or confirmed. When the CALIBRATE field is flashing press the ENTER key to begin the procedure. 4. The PFD display advises the operator when to turn the aircraft to a cardinal heading, when to stop, and when to turn to another heading.
Page 246 Uncontrolled if Printed ______________________________________________________________________________ and numeric values are displayed on the PFD. Use the FMS small knob to scroll through and view the entire list of failed measurements. 7. If failures are indicated, the engine run-up test can be repeated up to three times. If the test does not pass after three attempts, the installation should be considered unreliable until the source of the vibration problem is identified and remedied.
Page 247: Calibration Procedure E: Magnetometer Interference Test
Procedure E should be performed once every 12 months on at least one production aircraft for every airframe type or model equipped with the G1000 system. This procedure validates that no electronic device is inter- fering with the operation of the GMU 44 magnetometer which directly impacts the determination of attitude and heading by the GRS 79 AHRS.
Page 248 Uncontrolled if Printed ______________________________________________________________________________ d) Select MAG INTERFERENCE TEST and press the ENT key. e) Follow the checklist items displayed on the PFD and press the ENT key as each one is completed or confirmed. NOTE The third item on the checklist instructs the operator to prepare a detailed test sequence list with precise start and stop times for exercising all elec- tronic devices.
Page 249 Uncontrolled if Printed ______________________________________________________________________________ Table 7-2. Magnetometer Interference Test Sequence Example (Continued) Elapsed Time Since Start of Test Action (min:sec) Pulse Lights On Pulse Lights Off Landing + Taxi Lights On Landing + Taxi Lights Off Turn on all wing-tip lights simultaneously (Strobe and Nav) Turn off all wing-tip lights simultaneously Pitot Heat On, Left and Right...
Page 250: Site Evaluation Of Magnetic Disturbances For Magnetometer Calibration
Magnetometer Calibration Procedure. A G1000 NXi system equipped airplane can be used to evaluate a candidate site for magnetic disturbances and determine whether it is a suitable location to perform the magnetometer calibration procedure.
Page 251 Uncontrolled if Printed ______________________________________________________________________________ NOTE Although Section 7.6.3 indicates the Magnetometer Calibration Procedure should be performed by making a series of clockwise turns around the site, the procedure can also be performed by making counter-clockwise turns for the purpose of evaluating the site for magnetic disturbances. If, upon completion of the Magnetometer Calibration Procedure in both the clockwise and counter- clockwise directions, the PFD displays the CALIBRATION SUCCESSFUL / SITE IS CLEAN message, the candidate site is sufficiently free of magnetic disturbances...
Page 252: Gea 71 High-Side Current Monitor Calibration Procedure (Gea 71 Only)
Uncontrolled if Printed ______________________________________________________________________________ 7.6.8 GEA 71 High-Side Current Monitor Calibration Procedure (GEA 71 only) 1. In the aircraft a) Make sure the sensor (shunt) in question has been energized at operating voltage, but is isolated from current flow (both high and low inputs to GEA should be at the same high voltage).
Page 253 Press the ENT Key to accept the CALIBRATION OFFSET value, the instantaneous CALIBRATION OFFSET value will be stored as the CURRENT OFFSET. f) The G1000 NXi will now recheck the GEA configuration (this may take several minutes). During this time the box shown in Figure 7-9 will be displayed.
Page 254: Gdc 72 Air Data Computer
Uncontrolled if Printed ______________________________________________________________________________ Figure 7-10. Configured Confirmation Box h) Once verification is complete, the CURRENT CORRECTED VALUE should be zero, within a range of fluctuation that is equal to or less than noted before calibration. If this is the case the calibration has been successfully completed. 7.7 GDC 72 Air Data Computer After software and configuration have been loaded to a replacement GDC, test per the procedures in the OEM approved Aircraft Maintenance Manual.
Page 255: Audio Entertainment Testing
Complete instructions for activating the XM data link can be found in Garmin document 190-00355-04 or by calling XM at 1- 800-985-9200. XM service is currently only available in the U.S. and select Canadian areas.
Page 256 Uncontrolled if Printed ______________________________________________________________________________ 1. Select the AUX - XM RADIO page on the MFD. 2. Using the channel control located in the cabin, make sure you can increment and decrement the channels (the white arrow to the left of the channel list indicates the currently selected channel).
Page 257: Sirius Xm Weather
Uncontrolled if Printed ______________________________________________________________________________ 7.8.2 SIRIUS XM Weather Make sure weather data is being displayed on the Navigation Map Page. If not, begin troubleshooting. 7.8.2.1 Displaying SiriusXM Weather on the Navigation Map Page 1. Press the MAP Softkey. 2. Press the NEXRAD or XM LTNG Softkey to display the desired weather. 3.
Page 258: Gts Ground Test Procedure
Uncontrolled if Printed ______________________________________________________________________________ 7.9.2 GTS Ground Test Procedure Use a ramp tester such as a TIC TR220 or equivalent to make the following setup and measurements. 1. The Ground Test mode can be set by starting PFD1 in configuration mode, and the MFD and PFD2 in normal mode.
Page 259: Gts 800 Antenna Functional Check
Uncontrolled if Printed ______________________________________________________________________________ NOTE The air/on-ground mode logic mutes the aural TA while GSL altitude is below 400 ft. 7.9.3 GTS 800 Antenna Functional Check NOTE The GTS 800 must be in Ground Test mode to perform antenna verification testing.
Page 260 Uncontrolled if Printed ______________________________________________________________________________ 9. Connect the directional antenna to the ramp test set. 10. Set the multifunction test set to perform TCAS testing. Press the TAS OPER softkey on the MFD. 11. Program a static intruder per the following scenario: NOTE Refer to the ramp test set operators manual to set the following parameters:...
Page 261: Gwx Processor Testing
Uncontrolled if Printed ______________________________________________________________________________ 27. If the bearing is not as anticipated, recheck the antenna coaxial connections by verifying the following: • QMA connectors are 'snapped' firmly in place. • Connections are made to the proper channels and color-coded heat shrink is the same color on both ends of cable QMA connectors are correctly installed on cables.
Page 262: Gwx Processor Pitch And Roll Trim Adjustments
Uncontrolled if Printed ______________________________________________________________________________ 7.10.1 GWX Processor Pitch and Roll Trim Adjustments NOTE Whenever any configuration is changed in this manual, confirm the configuration so the system does not display configuration error messages. The following procedure assumes the correct configuration files have been loaded to the GWX.
Page 263: Gfc 700 Testing
The following procedure will make sure the proper operation of the GFC 700 AFCS. The technician performing these checks must be thoroughly familiar with the GFC 700, refer to the Garmin G1000 Kodiak 100 Pilot's Guide. 7.11.1 Preflight Test 1. If selected ON, select the MASTER and AVIONICS MASTER PWR switches to OFF.
Page 264: Afcs Switch Checks
Uncontrolled if Printed ______________________________________________________________________________ NOTE A momentarily red AFCS annunciation displayed before PFT starts is acceptable 3. Upon successful completion of the test, an aural alert will sound, and the annun- ciation will clear. The aural alert is generated by either GIA1 or GIA2, alternately, with each system start.
Page 265 Uncontrolled if Printed ______________________________________________________________________________ 6. Release the CWS switch and press the AP/YD DISC TRIM INTRPT switch on the pilots control wheel. Verify the autopilot disengages with a flashing amber 'AP' and YD annunciation on PFD1 and PFD2, accompanied by an aural alert. Verify the control wheel is free in pitch and roll and the rudder pedals also move freely.
Page 266: Autopilot Clutch Overpower Check
Uncontrolled if Printed ______________________________________________________________________________ 14. Press the FD key and verify the mode annunciations and command bars are removed from both PFDs. 7.11.3 Autopilot Clutch Overpower Check NOTE The GFC 700 uses electronic torque limiting as well as mechanical slip clutches to limit the maximum servo effort.
Page 267: Hdg, Cws And Nose Up/Dn Wheel Check
Uncontrolled if Printed ______________________________________________________________________________ 7.11.5 HDG, CWS and NOSE UP/DN Wheel Check 1. Engage the Autopilot by pressing the AP key on the AFCS mode controller. Push the HDG knob to synchronize the heading bug to the current aircraft heading. Select HDG mode by pressing the HDG key on the AFCS mode controller.
Page 268: Esp Functional Check
7.11.6 ESP Functional Check 1. Apply power to the aircraft and avionics systems by placing the aircraft MASTER and AVIONICS MASTER switches to ON. Ensure the G1000 NXi and components are powered and operating normally. 2. Verify the DISPLAY BACKUP buttons on the audio panels are pushed in so the GDUs will not operate in reversionary mode.
Page 269 Uncontrolled if Printed ______________________________________________________________________________ 12. Make sure the status on the MFD SETUP 2 page Stability & Protection window is DISABLED. 13. Make sure on PFD 1 and PFD 2 the ESP Roll Indexes are not displayed at 45° on the roll indicator on the Attitude Display.
Page 270: Calibration Procedures
Uncontrolled if Printed ______________________________________________________________________________ NOTE On system start the coupled side will default to the left side. Each time power is reapplied couple back to the right side and continue test steps. 20. Repeat step 1 thru 19 while coupled to right side. 21.
Page 271: Fuel Level Indication System Calibration
Uncontrolled if Printed ______________________________________________________________________________ c) Aileron Trim Press RESET (softkey 12). Press ENT. ii) Move trim all the way left until it hits the stop. iii) Press the right-most LEFT softkey. iv) Move trim all the way right until it hits the stop. v) Press the right-most RIGHT softkey.
Page 272 Uncontrolled if Printed ______________________________________________________________________________ Figure 7-19. G1000NXi Fuel Calibration 7.12.2.1 Fuel Temperature Configuration The fuel temperature sensor is integrated into the Right-Wing fuel sensor. The Fuel Temp L Offset must be set for the fuel quantity to display on the EICAS. Although the fuel temperature sensor is in the right wing the left fuel temp offset must be set to zero.
Page 273 OFF position. Fill each wing tank with 3.25 gallons (21.8 lb.) of Jet A fuel. NOTE If the G1000 NXi is shut down during fuel handling, the system should be allowed to stabilize for AT LEAST three minutes before proceeding.
Page 274 Uncontrolled if Printed ______________________________________________________________________________ 12. Press ENT. If a previous CALIBRATION VALUE exists, a prompt will appear requesting overwrite acknowledgment. If prompted, select YES and press ENT. An ACTUAL QUANTITY of 0.00 lb. and a CALIBRATED VALUE will appear in the CALIBRATION TABLE.
Page 275 Uncontrolled if Printed ______________________________________________________________________________ 10. Press the TNK SEL softkey and turn the inner FMS knob to select RIGHT. Press ENT. 11. Press the FULL softkey. The cursor will highlight the CALIBRATE? option. 12. Press ENT. If a previous CALIBRATION VALUE exists, a prompt appears requesting overwrite acknowledgment.
Page 276 Uncontrolled if Printed ______________________________________________________________________________ BLANK PAGE ____________________________________________________________________________ Page 7-50 LMM for the Kodiak 100 190-02102-00 Rev.4...
Page 277: Periodic Maintenance
Maintenance of the GTS 800 is on-condition only. 8.4 GDC 72 Air Data Computer Periodic Maintenance Per Part 43 Appendix E, paragraph (b)(2), Garmin specifies a test procedure equivalent to Part 43 Appendix E, paragraph (b)(1) with two exceptions. The tests of sub-para- graphs (iv) (Friction) and (vi) (Barometric Scale Error) are not applicable because the digital outputs of the GDC 72 are not susceptible to these types of errors.
Page 278: Grs 79 Altitude And Heading Reference System Periodic Maintenance
______________________________________________________________________________ 8.10 GRS 79 Altitude and Heading Reference System Periodic Maintenance Per Part 43 Appendix E, paragraph (b)(2), Garmin specifies a test procedure equivalent to Part 43 Appendix E, paragraph (b)(1) with two exceptions. The tests of sub-para- graphs (iv) (Friction) and (vi) (Barometric Scale Error) are not applicable because the digital outputs of the GRS 79 are not susceptible to these types of errors.
Page 279: Gsm 86 Servo Gearbox
To perform the Automatic Slip Clutch Test Procedure that follows, all G1000 NXi and GFC 700 equipment must be installed and operational. Start the G1000 NXi in Configuration Mode and select the GFC STATUS Configuration Page. Perform the following checks:...
Page 280 Uncontrolled if Printed ______________________________________________________________________________ Figure 8-1. GFC Status Page NOTE The displayed test results on the PFD are not stored in G1000NXi memory. If power is cycled, these values will be lost. However, these test values are not lost by changing configuration mode pages. NOTE Perform the following test at temperatures between 50°...
Page 281 Uncontrolled if Printed ______________________________________________________________________________ 6. Position the control surface in the neutral position (full aft position if the PITCH SERVO is selected). Press the DIS CLCH softkey 7. Press the TEST SVO softkey. Highlight YES and press the ENT key. NOTE Once the test starts the servo will begin to move the aircraft controls.
Page 282 Uncontrolled if Printed ______________________________________________________________________________ a) Up pitch minimum allowed torque is 97.026 in-lbs and maximum is 115.360 in- lbs. b) Down pitch minimum allowed torque is 97.026 in-lbs and maximum is 115.630 in-lbs. c) Roll left minimum allowed torque is 57.462 in-lbs and maximum is 68.320 in- lbs.
Page 283 Uncontrolled if Printed ______________________________________________________________________________ Table 8-1. (Continued)Troubleshooting Table Message Prompt Probable Cause Action SERVO TORQUE TOO The servo detected an • Engage the autopilot for HIGH average torque value the axis which reported which exceeded 130% torque to high. Manually of the established operate the controls and mechanical torque limit.
Page 284 An out-of-calibration load cell may be the cause. AIRBORNE STATUS The G1000 NXi has • Verify the ADC is online. detected airborne status, • Check pitot/static system (determined by true air- is free of obstructions and speed) and has can- plumbing kink.
Page 285: Gsm Slip Clutch Checking And Adjustment Procedure
1. On the ground, with the autopilot off, check for freedom of control movement in the roll, yaw, pitch and pitch trim control axes. 2. Apply system power and start the G1000 NXi in configuration mode. Turn on AP power.
Page 286: Gfc 700 Visual Inspection Procedure
Uncontrolled if Printed ______________________________________________________________________________ NOTE This procedure will only work correctly if both are selected. False readings may be given otherwise. During the next two steps, the softkeys DIS CLCH and STP SRVO should be showing - do not select them yet. 7.
Page 287 Uncontrolled if Printed ______________________________________________________________________________ BLANK PAGE ____________________________________________________________________________ LMM for the Kodiak 100 Page 8-11 190-02102-00 Rev.4...
Page 288 Uncontrolled if Printed...

Garmin G1000 Line Maintenance Manual

Quick Links

Troubleshooting

Related Manuals for Garmin G1000

Summary of Contents for Garmin G1000

Table of Contents