Contents - Table Of Contents
- Table Of Contents
- Table Of Contents
- Table Of Contents
- Table Of Contents
- Table Of Contents
- INTRODUCTION
- Organization
- Definitions/Abbreviations
- Units of Measure
- Section 1 1-1 –
- SYSTEM DESCRIPTION
- Figure 2-2, Transponder
- Figure 2-3 GSU-75 ADAHRS with Connector and Mounting Tray
- Figure 2-4, GDL 69A SXM Datalink
- G1000 Optional Interfaces
- G1000 Normal Mode
- Section 2 2-1 –
- SOFTWARE AND CONFIGURATION
- Figure 3-1, SET>ACTV Diagram
- Figure 3-2, Loss of Communication
- G1000 System Software Information
- Figure 3-5, GSU Configuration Settings Storage
- Configuration Mode
- Figure 3-6, Garmin Unit S/N Location
- G1000 Software/Configuration Procedure
- System Software and Configuration Load
- Figure 3-8 – Airframe Group Selection
- Figure 3-9 – Airframe Change Confirmation
- Feature Enablement
- Aircraft Registration Number Entry
- Configuration Manager
- Splash Screen Loading
- Figure 3-10, MFD Aux - Database Page DB Transfer
- Configuration of Navigation Map for Traffic System
- Interface Confirmation
- Section 3 3-1 –
- Servicing Information
- Maintenance Intervals
- Electrical Bonding Test
- GSU 75 Earth Magnetic Field Updates
- Section 4 4-1–
- TROUBLESHOOTING
- System Annunciations
- G1000 Alerting System
- Synthetic Vision and Pathways Troubleshooting
- Backup Communications Path Checks
- GDU 105X Troubleshooting
- GDU 105X Alerts
- GTX Troubleshooting
- GDL69A SXM Troubleshooting (if installed)
- GSU 75 and GMU 44 Troubleshooting
- Figure 5-5, Magnetometer Interference Test
- Table 5-3, Magnetometer Interference Test Sequence
- GSU 75 Troubleshooting
- Software/Configuration Troubleshooting
- Backshell/Backplate Connectors
- Section 5 5-1 –
- EQUIPMENT REMOVAL & INSTALLATION
- GDU 1054B/1050
- GDL 69A SXM (if installed)
- Figure 6-1, Configuration Module Installation
- Figure 6-2, GSU 75 Configuration Module Installation
- Section 6 6-1 –
- GARMIN G1000 LRU REPLACEMENT/CONFIGURATION & TESTING
- Figure 7-1, G1000 Normal Mode Check
- GMA 1347 Audio Panel
- GIA 63W Integrated Avionics Unit
- Figure 7-2, Aux – GPS Status Page (MFD)
- GEA 71 Engine/Airframe Unit
- Figure 7-3, Normal Engine Instrument Markings (MFD)
- GTX 335R, GTX 345R, or GTX 33 Transponder
- Figure 7-4, Aircraft Registration
- GSU 75 ADAHRS (if installed)
- GDC 74A Air Data
- Table 7-1, Altitude Test Points
- Table 7-2, Airspeed Test Points
- GRS 77 and GMU 44 Magnetometer (if installed)
- GMU 44 Magnetometer
- GSU/GRS/GMU Calibration Procedures
- Table 7-4, Required GRS/GMU Calibrations
- Figure 7-5, GRS/GMU Calibration, Pitch/Roll Offset
- Figure 7-6, GRS/GMU Calibration, Engine Run-Up
- Figure 7-7, Normal Mode AHRS Check
- GDL 69A or GDL 69A SXM Data Link (if installed)
- GSA 81 Servos (if installed)
- Garmin Traffic Systems (GTS 800) (if installed)
- Section 7 7-1–
- SUBSYSTEM FUNCTIONAL CHECKS
- ChartView Functional Check
- SafeTaxi Functional Check
- DME Functional Check
- Section 8 8-1 –
- G1000 SYSTEM RETURN TO SERVICE PROCEDURE
- Figure 9-2, PFD Power-up System Annunciations
- Figure 9-3, PFD Normal Operation
- Display Failure Test
- Reversion Mode Check
- GPS Signal Acquisition
- GPS Failure Test
- GIA Failure Test
- GEA Functional Check
- G1000 Backup Path Test
- Appendix A
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G1000 Supplemental Maintenance Manual Page 7-16Textron Nav III Series Revision 3190-02128-042. Set the HSI on the PFD to VOR1 by pressing the CDI softkey until VOR1 is selected.Rotate CRS knob to set VOR1 course pointer to aircraft heading.3. Verify full scale deflection of VOR1 CDI by varying CRS1 selected course at least 10°left and right. Reset course pointer to aircraft heading.4. Engage the autopilot and press the NAV key on the AFCS mode controller. Using theCRS knob alter course by 10° to the right. Verify the flight director and aircraft controlsrespond by flying to the VOR course. Repeat to the left.5. Set CRS course pointer to aircraft heading.6. Simulate a Localizer/Glideslope signal. Tune this signal on NAV 1 and NAV 2 receiver.Set the PFD HSI to LOC1 by pressing CDI softkey until LOC1 is selected. Use the testequipment to center the deviation bars (localizer and glideslope) on the PFD.7. Press the APR key on the AFCS mode controller. Verify that the LOC and PITannunciations are green and ALTS and GS are white on the PFD. Apply right/left andup/down localizer/glideslope signals using the test equipment. Verify that the FlightDirector and flight controls respond appropriately.8. If no other service is to be performed, continue to the return-to-service checks in Section9. |
