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is selected OFF. This may occur with only a trace of ice accumulation visible on the airplane.
If both Engine Anti-Ice circuit breakers are pulled, the engine inlets will both be heated, but an
amber ENG A/I COLD CAS message will display due to the loss of nacelle temperature
monitoring. No additional action is required to address the amber ENG A/I COLD CAS message,
and the message will clear when either circuit breaker is reset.
1. Engine Sync . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
2. ENGINE ANTI-ICE Switch (affected engine) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
3. RAT Indication on PFD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . VERIFY decrease
4. Exit icing conditions as soon as practical.
5. Monitor for ice accumulation.
• IF ICING INTENSITY IS TRACE OR LESS
Go to Step 8 prior to descent.
• IF ICING INTENSITY IS GREATER THAN TRACE
6. Engine Anti-Ice Circuit Breaker (affected engine). . . . . . . . . . . . . . . . . . . . . . . . . PULL
7. Exit icing conditions as soon as possible.
PRIOR TO DESCENT
8. Engine Anti-Ice Circuit Breaker. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RESET
9. ENGINE ANTI-ICE Switches . . . . . . . . . . . . . ON until RAT indications are normal and
icing conditions are exited.
NOTE
No maintenance corrective action as required after flight. Verify all Engine Anti-Ice
circuit breakers are reset and the affected T2 probes are clear of ice or other
contamination.
PROCEDURE COMPLETED
510FM-07 AA 3-91/3-92

MODEL 510 SECTION III - OPERATING PROCEDURES
ABNORMAL PROCEDURES
FAA APPROVED
Configuration U.S.
AVIONICS / AUTOPILOT
 AILERON MISTRIM (AIL OR AIL ANNUNCIATION PFD)
1. Control Wheel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GRIP
2. Autopilot . . . . . . . . . . . . . . . . . . . . . . . DISCONNECT (high aileron control forces possible)
NOTE
The yaw damper does not need to be disconnected for this procedure. Therefore it is
permissible to use the LEFT half of either Manual Electric Trim switch or 1 press of
the AP button on the Autopilot Mode Control panel to disconnect the autopilot.
3. AILERON TRIM Switch. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED
4. Autopilot . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ENGAGE as desired
PROCEDURE COMPLETED
 ELEVATOR MISTRIM (ELE OR ELE ANNUNCIATION PFD)
Indicates a mistrim of the elevator while the autopilot is engaged. The autopilot will normally trim
automatically as required. However, during rapid acceleration, deceleration, or configuration
changes, momentary illumination of this message may occur accompanied by minor fluctuations
in the flight path. If the autopilot is disconnected while this message is displayed, high elevator
control forces are possible. In the event of a sustained illumination, the following procedure
should be followed:
1. Control Wheel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GRIP
2. Autopilot . . . . . . . . . . . . . . . . . . . . . . DISCONNECT (high elevator control forces possible)
NOTE
The yaw damper does not need to be disconnected for this procedure. Therefore it is
permissible to use the LEFT half of either Manual Electric Trim switch or one press of
the AP button on the Autopilot Mode Control panel to disconnect the autopilot.
3. Elevator Trim. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED
4. Autopilot . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ENGAGE as desired
PROCEDURE COMPLETED
 RUDDER MISTRIM (RUD OR RUD ANNUNCIATION PFD)
1. Rudder Pedals . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HOLD FIRMLY
2. AP/TRIM DISC Button . . . . . . . . . . . . . . . . . . PRESS (high rudder control forces possible)
3. RUDDER TRIM Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED
4. Autopilot and Yaw Damper . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ENGAGE as desired
PROCEDURE COMPLETED
510FM-07 AA 3-93
SECTION III - OPERATING PROCEDURES MODEL 510
ABNORMAL PROCEDURES
FAA APPROVED
U.S. Configuration
 ALT MISCOMP (ALTITUDE MISCOMPARE)
This message is displayed when the G1000 detects a difference of 200 feet or greater between
　
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