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The flight control surfaces (ailerons, rudder, and elevators) are ____________ operated from a conventional set of dual
Trim is accomplished through a manually actuated ____________ system for each set of control surfaces. An
electric trim system is incorporated in the elevator trim system and is actuated from either of the control wheels.
The pilot and copilot control wheels are nearly identical except that incorporated switches are in
reverse locations and the pilot control wheel has _________ capability.
A __________________ switch is also located on the outboard grip of the copilot control wheel.
G/A (go around)
Simultaneous movement in the same direction of the dual element thumb switches is required for the electric elevator trim system to operate, and the switches on the _______ control wheel will override the __________ switches.
pilot, copilot
Two pneumatic rudder boosting servos are incorporated into the rudder cable system to aid in compensating for
asymmetrical thrust during an engine failure, or excessive variations in engine power. The system is comprised
of the two pneumatic servos, two solenoid valves, a differential pressure valve, and a differential pressure switch.
The system circuit is energized by a two-position toggle switch on the __________________ placarded RUDDER
BOOST. The differential pressure valve monitors the bleed air pressure of both engines. If the bleed air pressure
varies between engines, a shuttle in the differential valve moves toward the low-pressure side. When the pressure
differential exceeds approximately 60 psi, a switch on the low-pressure side closes, activating the system, and
allowing pressure to actuate the rudder servo. Each rudder servo is attached by cable to the primary rudder control
extended pedestal
A yaw damping system is provided as a function of the autopilot system to aid in maintaining directional stability. The yaw damp system senses changes in heading (from the _________ system) and drives the rudder control cables to deflect the rudder, stabilizing the yaw axis of the aircraft. Yaw damp is automatically engaged when the autopilot is engaged, or it may be engaged independent of the autopilot by pressing the Y/D ENGAGE push switch located on the extended pedestal. Yaw damp may be disengaged by depressing either pilot or copilot red AP/YD disconnect button to first detent or by depressing the Y/D ENGAGE again.
x of y cards