Garmin G1000 Quest Kodiak - Manual (Page 26)

Garmin G1000 Pilot’s Guide for the Quest Kodiak 100 190-00590-02 Rev. A
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
14
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
Garmin G1000 Pilot’s Guide for the Quest Kodiak 100
Figure 1-9 G1000 Reversionary Mode (Failed PFD #1)
Primary Flight Display #1 Multi-Function Display Primary Flight Display #2
Figure 1-10 DISPLAY BACKUP Button
Pressing the DISPLAY BACKUP
Button activates/deactivates
reversionary mode for both the
on-side PFD and the MFD.
Each display can be configured to operate in reversionary mode, as follows:
• PFD1 – By pressing the DISPLAY BACKUP Button on the left audio panel.
• MFD – By pressing the DISPLAY BACKUP Button on the left or the right audio panel.
• PFD2 – By pressing the DISPLAY BACKUP Button on the right audio panel.
Should the connection between a PFD and the on-side GIA 63W become inoperative, the on-side GIA 63W
can no longer communicate with the remaining PFD (refer to Figure 1-1). As a result, the NAV and COM
functions provided to the failed PFD by the on-side GIA 63W are flagged as invalid (red “X”) on the remaining
PFD (see Figure 1-12).
Figure 1-11 Inoperative Input (NAV1 Shown)
AHRS OPERATION
NOTE: Refer to Appendix A for specific AHRS alert information.
NOTE: Aggressive maneuvering while AHRS is not operating normally may degrade AHRS accuracy.
The Attitude and Heading Reference System (AHRS) performs attitude, heading, and vertical acceleration
calculations for the G1000 System, utilizing GPS, magnetometer, and air data in addition to information
from its internal sensors. Attitude and heading information are updated on the PFD while the AHRS receives
appropriate combinations of information from the external sensor inputs.
Loss of GPS, magnetometer, or air data inputs is communicated to the pilot by message advisory alerts. Any
failure of the internal AHRS inertial sensors results in loss of attitude and heading information (indicated by red
‘X’ flags over the corresponding flight instruments).