|
曝光台 注意防骗 网曝天猫店富美金盛家居专营店坑蒙拐骗欺诈消费者
Volume 2 Flight Crew Operating Manual Sep 14/2005 CSP 100-6 REV 4
10-01-02 PRIMARY FLIGHT CONTROLS (Cont)
ROLL DISCONNECT
The roll disconnect allows the flight crew to isolate the left control wheel from the aileron control system. The roll discon-nect mechanism is mounted on the left control wheel. It is comprised of a lever, a shaft, a stud roller, a cam, and two torsion springs. The lever and the shaft are held in axial alignment by two bushings.
During normal operation, the roller position is held into the cam detent by the torsion springs, allowing the pilot control wheel and the input quadrant to rotate as one single unit.
In the event of a jam in the mechanical circuit, the pilot can disconnect from the aileron circuit and retain roll control through the multifunction spoilers. However, if a jam occurs in the pilot control wheel, the pilot can disconnect from the circuit thus permitting the copilot to retain control of the ailerons.
A pull of the roll disconnect mechanism lever retracts the roller which is held in the disconnect position by a spring-loaded hook. This action uncouples the pilot control wheel and the pilot input quadrant and allows the control wheel to rotate freely. This disconnect feature allows in-flight reset once the roller and the cam are realigned and the disconnect lever is released. A microswitch senses the retraction of the roller and sends a signal of the disconnect status and a ROLL DISCONNECT (W) CAS message will be illuminated.
RUDDER
RUDDER CONTROL SYSTEM
The rudder provides directional control about the yaw axis. The system is mechanically controlled and hydraulically pow-ered. The mechanical part of the system has control pedals, levers, pulleys and cables which connect to two hydraulic power control units (PCUs) in the vertical stabilizer. The PCUs cause the rudder to move in proportion to the flight-crew’s control pedal input. A rudder-control feel unit supplies a simulated pedal load to the flight crew.
The pilot and copilot rudder pedal assemblies are both connected to the forward quadrant assembly, with no means to dis-connect one from the other. Two cable systems beginning at the forward quadrants follow the same path in the fuselage until they reach the engine rotor burst zone, where they are routed separately towards the rear fuselage. In the event of a severed single cable in the rotor burst zone, the aft quadrant still receives input from the unaffected cables, thus retaining rudder system functionality. On the ground, trapped hydraulic fluid provides rudder control surface gust lock damping when the hydraulic systems are depressurized.
Rudder position is displayed on the EICAS FLIGHT CONTROL synoptic page. A full-scale deflection of the rudder posi-tion indicator corresponds to maximum rudder travel.
Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6
10-01-03 PRIMARY FLIGHT CONTROLS (Cont)
RUDDER POWER CONTROL UNIT (PCU)
There are two hydraulic rudder PCUs attached to the rear spar of the vertical stabilizer. The left hydraulic system energizes the upper rudder PCU and the right hydraulic system energizes the lower rudder PCU. If the right hydraulic system loses pressure, the lower rudder PCU is powered by the auxiliary hydraulic system.
中国公务机网 www.gongwuji.com
公务机翻译 www.aviation.cn
本文链接地址：庞巴迪挑战者300公务机机组操作手册 Bombardier Challenger-飞行操纵(4)
|
