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 4-5Textron Nav III Series Revision 3190-02128-044.4 Electrical Bonding TestThe following bonding tests are provided for G1000-equipped Nav III Series aircraft as arequirement beyond what is given in the 172, 182, or 206 Series Maintenance Manual.RequirementsAll G1000 equipment must be installed. Gain access for the procedure listed below in Section4.4.3 as required and in accordance with the Cessna Nav III Series Maintenance Manuals.Test EquipmentA milliohm meter and Kelvin probes are recommended for this test. However, an alternatemethod may be used to provide equivalent results by using the following procedure and astandard voltmeter, power supply with adjustable current limit, and ammeter. The test set up forthis alternate method is described below.All test equipment used for the bond checks must be calibrated.1. Connect the positive lead of the power supply to airframe ground. Connect/touch thepositive lead of the voltmeter to the same point.NOTEEnsure that the voltmeter and power supply probes do not touch, so as not toinduce contact resistance.2. Touch negative lead of power supply to each of the test points listed while performingStep 3. At each required point, configure the power supply to produce 1 amp beforemeasuring voltage. (Use an ammeter to ensure current is within minimum of 1 amp±100 milliamp at each point). Do not allow the reference current to exceed 1.5 amps forsafety.3. With the current set to 1A, the voltage reading will be the value of the bondingresistance. Set the voltmeter to measure millivolts and null the reading. Measure thevoltage from airframe ground (step 1) to each required test points and record thevoltage. (Perform Step 2 at each required point and ensure that minimum of 1 amp±100 milliamp is present when measuring the voltage.)TIP: When a 1A current is used all the millivolt readings are the same as milliohms, andrequired no further calculation of bond resistance. If 1 amp reference current cannot bemaintained and is higher divide the measured voltage by current to get the resistancevalue. Alternatively, calculate the percentage increase in current and then reduce themeasured voltage reading by the same percentage. Example: If the measured current is1.2 amps, (20% high from the desired 1 amp current) and the measured voltage is 3.0millivolts, then the value recorded will be 3 millivolts reduced by 20% which is 2.4millivolts which is the same as 2.4 milliohms. |
