Garmin G2000, Pilot'S Manual

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Garmin G2000 Pilot’s Guide for the Cessna T240
190-01263-01 Rev. A
SY
STEM
O
VER
VIEW
FLIGHT
INSTRUMENTS
EIS
AUDIO & CNS
FLIGHT
MANA
GEMENT
HAZARD
AV
OID
ANCE
AFCS
ADDITIONAL FEA
TURES
APPENDICES
INDEX
572
Appendix A
Afcs stAtus AnnunciAtions
The following annunciations (listed in order of increasing priority) can appear on the PFD above the Airspeed
and Attitude indicators. Only one annunciation may occur at a time, and messages are prioritized by criticality.
Figure A-7 AFCS Status Annunciation
AFCS Status
Annunciation
condition Annuncia-
tion
description
Pitch Failure Pitch axis control failure. AP is inoperative.
Roll Failure Roll axis 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 annunci-
ated 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 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.
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 DISC 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.
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