|
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
Controls and Indications......................................................................................................10-02-16
Flap Control Lever .....................................................................................................10-02-16
EICAS Trim Status Display ........................................................................................ 10-02-16
Flight Control Synoptic Page .....................................................................................10-02-17
EICAS Messages................................................................................................................10-02-18
Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6
10-00-01
INTRODUCTION
The primary flight controls are the elevators, rudder, ailerons and roll spoilers. The ailerons are cable operated. The spoilers are electrically actuated and hydraulically operated. Cables connect the control column and rudder pedals to the hydraulic power control units for the elevators and rudder. The elevators and rudder have a mechanical reversion capability in the event of a dual hydraulic system failure.
The secondary flight controls consist of horizontal stabilizer, aileron, and rudder trims, flaps, and spoilers when operated symmetrically (flight and ground spoilers).
DESCRIPTION
The primary flight controls are arranged conventionally with rudder pedals and a control wheel and column for both the pilot and copilot. The roll spoilers, ailerons, elevators, and rudder are operated by means of conventional dual control wheels, dual control columns, and dual rudder pedal assemblies. The aileron system is a reversible mechanical cable sys-tem. The spoilers are controlled through an electronic/hydraulic fly-by-wire system. The elevator and rudder are mechan-ically controlled and hydraulically powered systems. The elevator and rudder has a manual reversion capability in the event of a dual hydraulic failure.
CFO1001002_013
Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6
10-01-01 PRIMARY FLIGHT CONTROLS
COMPONENTS AND OPERATION AILERONS AND MULTIFUNCTION SPOILERS
The aileron control cable runs to both control wheels and both ailerons. The roll disconnect mechanism disconnects the pilots control wheel from the aileron circuit. When disconnected, the pilot controls the roll spoilers and the copilot controls both ailerons. Normally the aileron and roll spoilers are interconnected and there is a simultaneous and coordinated move-ment of all lateral control surfaces from either pilot station.
Moving the control wheels also generates a signal that is sent to the spoiler electronic control units (SECU 1 and SECU 2). Dual redundant modules within the SECU control the extension/retraction of the multifunction spoilers (MFS). The SECUs combine the control wheel signals with other information to determine the required multifunction spoiler panel deflection for any given airplane configuration. There are four spoiler panels on each wing. The two outboard panels are the multi-function spoilers that operate asymmetrically in a roll, symmetrically for flight spoilers, and on the ground as ground spoil-ers. The two inboard spoilers only operate on the ground. A single power control unit is used on each spoiler. The MFS operate on the down-going wing only to assist the ailerons in roll control. In order to reduce roll control forces, an aileron balance geared tab is mounted on each aileron. The balance tabs have a maximum ±15 degrees of travel each side of the aileron chord line. It consists of a constant length push rod hinged at both ends on brackets rigidly mounted on the wing at one end and on the balance tab at the other end. The mechanism acts as a linkage with the aileron surface being the driving link and the geared balance tab being the driven link. The aileron balance tab is geared to move in the opposite direction of its corresponding ailerons movement. A roll damper is mounted on the pilot control column. Under normal operation, the roll damper acts like a quadrant and transmits all of the crew member’s inputs. In case of any one aileron cable failure, the roll damper limits the rate the control wheel deflects (driving the roll spoilers) to a recoverable level. To prevent damage to the aileron surfaces from wind gusts when the aircraft is parked, a gust lock mechanism is incorporated to lock the left drive quadrant in the neutral position. The mechanism is actuated by the crew, via a telescoping gust lock lever mounted in the throttle quadrant. The lever moves a cable, that engages a spring loaded pawl into a quadrant mounted cam recess. When the gust lock is engaged, the throttles are physically prevented from being moved above idle. Aileron position is dis-played on the EICAS FLIGHT CONTROL synoptic page. A full-scale deflection of the AIL position indicator corresponds to maximum aileron deflection.
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(3)
|
