FAA Approved Airplane Flight Manual Supplement

Hawker Beechcraft C90A, C90GT and C90GTi King Air 190-00682-02 Rev. F
Page 66 of 124 FAA APPROVED
WARNING
• Pilot’s Trim Override .................................................................................................... CHECK
Activate the copilot’s Pitch Trim Switches nose down. Verify elevator tab wheel is
moving nose down. While the tab wheel is moving in the DN direction, activate the
pilot’s Pitch Trim Switches nose up. Verify the elevator tab wheel begins to move in the
UP direction. Release both pilot’s and copilot’s Pitch Trim switches and reset elevator
tab as required.
• Manually Operate Elevator Tab Wheel ..................... VERIFY Pitch Trim Servo is Not Engaged
3. Press GA Button on Left Power lever ............... VERIFY FD Command Bars show Takeoff Attitude
‘TO / / TO’ is Annunciated in Mode Window on Both PFDs
BEFORE TAKEOFF (FINAL ITEMS)
These procedures should be conducted after completing the airplane’s AFM BEFORE TAKEOFF
(FINAL ITEMS) checklist.
1. PFD Attitude and Heading .................................................................................................. NORMAL
2. GPS Position .................................................................. VALID, ‘LOI’ NOT ANNUNCIATED on HSI
3. Standby Attitude Indicator .......................................... ERECT and NORMAL, Fail Flag not in view
ON TAKEOFF ROLL
This procedure should be conducted after brake release during the takeoff roll but before
becoming airborne.
1. Verify correspondence of PFD airspeed display and standby airspeed
CLIMB, CRUISE, AND DESCENT
Disengage autopilot and yaw damper and retrim the airplane in roll and yaw following a power
change, change in airspeed, or if a slight wing rocking is observed. Re-engage the autopilot and
yaw damper after trimming the airplane.
ICING CONDITIONS
DUE TO DISTORTION OF THE WING AIRFOIL, ICE ACCUMULATION ON THE LEADING EDGES
CAN CAUSE A SIGNIFICANT LOSS IN RATE OF CLIMB AND IN SPEED PERFORMANCE, AS
WELL AS INCREASES IN STALL SPEED. EVEN AFTER CYCLING THE DEICE BOOTS, THE
ICE ACCUMULATION REMAINING ON THE BOOTS AND UNPROTECTED AREAS OF THE
AIRPLANE CAN CAUSE LARGE PERFORMANCE LOSSES. FOR THE SAME REASON, THE
AURAL STALL WARNING SYSTEM MAY NOT BE ACCURATE AND SHOULD NOT BE RELIED
UPON. UNDER THESE CONDITIONS, ESP AND AUTOPILOT UNDERSPEED PROTECTION
MAY ALSO NOT BE ACCURATE AND SHOULD NOT BE RELIED UPON.