Garmin G1000 King Air C90GT - Manual (Page 33)

190-00663-01 Rev. A Garmin G1000 Pilot’s Guide for the Hawker Beechcraft C90A/GT 19
SYSTEM OVERVIEW
SY
STEM
O
VER
VIEW
FLIGHT
INSTRUMENTS
EIS
AUDIO P
ANEL
& CNS
FLIGHT
MANA
GEMENT
HAZARD
AV
OID
ANCE
AFCS
ADDITIONAL
FEA
TURES
APPENDICES
INDEX
AIR DATA INPUT FAILURE
A failure of the air data input has no effect on AHRS output while AHRS is operating in normal mode. A
failure of the air data input while the AHRS is operating in reversionary No-GPS mode results in invalid
attitude and heading information on the PFD (as indicated by red “X” flags).
MAGNETOMETER FAILURE
If the magnetometer input fails, the AHRS transitions to one of the reversionary No-Magnetometer modes
and continues to output valid attitude information. However, if the aircraft is airborne, the heading output
on the PFD does become invalid (as indicated by a red “X”).
G1000 SYSTEM ANNUNCIATIONS
NOTE: For a detailed description of all annunciations and alerts, refer to Appendix A. Refer to the (AFM/
POH) for additional information regarding pilot responses to these annunciations.
When an LRU or an LRU function fails, a large red “X” is typically displayed on windows associated with
the failed data (Figure 1-14 displays all possible flags and responsible LRUs). Upon G1000 power-up, certain
windows remain invalid as equipment begins to initialize. All windows should be operational within one
minute of power-up. If any window remains flagged, the G1000 system should be serviced by a Garmin-
authorized repair facility.
Figure 1-14 G1000 System Failure Annunciations
GDC 74B Air
Data Computer
GTX 33 Transponder
Or
GIA 63W Integrated
Avionics Units GDC 74B Air
Data Computer
GEA 71 Engine
Airframe Unit
Or
GIA 63W
Integrated Avionics
Unit
GIA 63W
Integrated Avionics
Units
GRS 77 AHRS
Or
GMU 44
Magnetometer
GIA 63W
Integrated Avionics
Units
GIA 63W
Integrated
Avionics Units