Garmin G1000 King Air C90GT - Manual (Page 553)

190-00663-01 Rev. A Garmin G1000 Pilot’s Guide for the Hawker Beechcraft C90A/GT
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
539
APPENDIX A
AFCS ALERTS
Figure A-8 AFCS System Status Field
System Status Field
The following alert annunciations appear in the AFCS System Status field on the PFD.
Condition Annunciation Description
Pitch Failure Pitch axis control failure. AP and YD are inoperative.
Roll Failure Roll axis control failure. AP and YD are inoperative.
Yaw Damper Failure YD control failure; AP is inoperative
MET Switch Stuck,
or Pitch Trim Axis
Control Failure If annunciated when AP is engaged, take control of the aircraft and disengage the
autopilot. If annunciated when AP is not engaged, move each half of the MET
switch separately to check if a stuck switch is causing the annunciation.
System Failure AP, YD, and MET are unavailable. FD may still be available.
Elevator Mistrim Up A condition has developed causing the pitch servo to provide a sustained force. Be
prepared to apply nose up control wheel force upon autopilot disconnect.
Elevator Mistrim
Down A condition has developed causing the pitch servo to provide a sustained force. Be
prepared to apply nose down control wheel force upon autopilot disconnect.
Aileron Mistrim Left A condition has developed causing the roll servo to provide a sustained left force.
Ensure the slip/skid indicator is centered and observe any maximum fuel imbalance
limits.
Aileron Mistrim
Right A condition has developed causing the roll servo to provide a sustained right force.
Ensure the slip/skid indicator is centered and observe any maximum fuel imbalance limits.
Rudder Mistrim Left A condition has developed causing the yaw servo to provide a sustained force. Ensure
the slip/skid indicator is centered and observe any maximum fuel imbalance limits.
Rudder Mistrim
Right A condition has developed causing the yaw servo to provide a sustained force.
Ensure the slip/skid indicator is centered and observe any maximum fuel imbalance
limits.
Preflight Test Performing preflight system test. Upon completion of the test, the aural alert is
heard.
Preflight system test has failed.
NOTE: Do not press the AP/YD DISC TRIM INTRPT switch during servo power-up and preflight system tests
as this may cause the preflight system test to fail or never to start (if servos fail their power-up tests). Power
must be cycled to the servos to remedy the situation.