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Figure A-1 Sensor Comparator WindowComparatorWindow
Comparator Window Text
Condition
ALT MISCOMP
Difference in altitude sensors is > 200 ft.
IAS MISCOMP
If both airspeed sensors detect < 35 kts, this is inhibited.
If either airspeed sensor detects > 35 kts, and the difference in sensors is > 10 kts.
If either airspeed sensor detects > 80 kts, and the difference in sensors is > 7 kts.
HDG MISCOMP
Difference in heading sensors is > 6º.
PIT MISCOMP
Difference in pitch sensors is > 5º.
ROL MISCOMP
Difference in roll sensors is > 6º.
ALT NO COMP
No data from one or both altitude sensors.
IAS NO COMP
No data from one or both airspeed sensors.
HDG NO COMP
No data from one or both heading sensors.
PIT NO COMP
No data from one or both pitch sensors.
ROL NO COMP
No data from one or both roll sensors..
190-00494-02 Rev. B Garmin G1000 Pilot’s Guide for the Cessna Citation Mustang
SYSTEM
OVERVIEW
FLIGHT
INSTRUMENTS EICAS AUDIO PANEL
& CNS
FLIGHT
MANAGEMENT
HAZARD
AVOIDANCE AFCS ADDITIONAL
FEATURES APPENDICES INDEX
491
Appendix A
Reversionaryeversionary Sensor Annunciationsnnunciations
Reversionary sensor selection is annunciated in the Reversionary Sensor Window, as shown in Figure A-2. These annunciations reflect reversionary sensors selected on one or both PFDs. Pressing the SENSOR Softkey gives access to ADC1, ADC2, AHRS1, and AHRS2 Softkeys. These softkeys allow manual switching of sensors. In the case of certain types of sensor failures, the G1000 may make some sensor selections automatically. The GPS sensor cannot be switched manually.
Figure A-2 Reversionary Sensor WindowsReversionarySensorWindow
Reversionary Sensor Window Text
Condition
BOTH ON ADC1
Both PFDs are displaying data from the #1 Air Data Computer.
BOTH ON ADC2
Both PFDs are displaying data from the #2 Air Data Computer.
BOTH ON AHRS1
Both PFDs are displaying data from the #1 AHRS.
BOTH ON AHRS2
Both PFDs are displaying data from the #2 AHRS.
BOTH ON GPS1
Both PFDs are displaying data from the #1 GPS receiver.
BOTH ON GPS2
Both PFDs are displaying data from the #2 GPS receiver.
USING ADC1
PFD2 is displaying data from the #1 Air Data Computer.
USING ADC2
PFD1 is displaying data from the #2 Air Data Computer.
USING AHRS1
PFD2 is displaying data from the #1 AHRS.
USING AHRS2
PFD1 is displaying data from the #2 AHRS.
USING GPS1
PFD2 is displaying data from the #1 GPS.
USING GPS2
PFD1 is displaying data from the #2 GPS.
G1000 Systemystem Annunciationsnnunciations
When a new message is issued, the MSG Softkey will flash to alert the flight crew of a new message. It will continue to flash until acknowledged by pressing the softkey. Active messages are displayed in white text. Messages that have become inactive will change to gray text. The MSG Softkey will flash if the state of a displayed message changes or a new message is displayed. The inactive messages can be removed from the Message Window by pressing the flashing MSG Softkey.
The G1000 System Messages conveys messages to the flight crew regarding problems with the G1000 system. Typically, a large red “X” appears in a window when a related LRU fails or detects invalid data.
When an LRU or an LRU function fails, a large red “X” is typically displayed on windows associated with the failed data. The following section describes various system annunciations. Refer to the AFM for additional information regarding pilot responses to these annunciations.
Garmin G1000 Pilot’s Guide for the Cessna Citation Mustang 190-00494-02 Rev. B
SYSTEM
OVERVIEW
FLIGHT
AUDIO PANEL EICAS INSTRUMENTS
& CNS
FLIGHT
MANAGEMENT
HAZARD
ADDITIONAL AFCS AVOIDANCE
INDEX APPENDICES FEATURES 492
Appendix A
NOTE: Upon power-up of the G1000 system, certain windows remain invalid as G1000 equipment begins to initialize. All windows should be operational within one minute of power-up. Should any window continue to remain flagged, the G1000 system should be serviced by a Garmin-authorized repair facility.
Figure A-3 G1000 System MessagesMessages WindowMessage Softkey AnnunciationSystem Annunciation Red ‘X’
Figure A-4 G1000 System Failure AnnunciationsGDC 74B Air Data ComputerGTX 33/D TransponderOrGIA 63W Integrated Avionics UnitsGDC 74B Air Data ComputerGEA 71 Engine Airframe UnitOrGIA 63W Integrated Avionics UnitGIA 63W Integrated Avionics UnitsGRS 77 AHRSOrGMU 44 MagnetometerGIA 63W Integrated Avionics UnitsGIA 63W Integrated Avionics UnitsFADECFuel Qty. Signal ConditionerKAPSIIPressure ControllerGEA 71 Engine Airframe UnitGEA 71 Engine Airframe Unit
　
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