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
A position transmitter linked to each elevator provides visual indication of the elevator deflection on the FLIGHT CONTROLS synoptic page. If a differential of greater than 5° between each elevator position exists, an ELEVATOR SPLIT caution message will appear.
Within the elevator control mechanism, a stick shaker and stick pusher system can be activated via the stall protection system (SPS). The SPS is covered later in this chapter.
Pitch Disconnect
In the event of a control cable jam or elevator system malfunction, the left and right elevator control circuits can be isolated by pulling the PITCH DISC handle on the center pedestal. This provides reduced pitch authority through the one elevator on the operable circuit. The PITCH DISC handle can be reset at any time, locking the two circuits together again.
Elevator PCU Protection
An elevator PCU jam or failure can be overcome by integrated jam-tolerant input rods. These rods collapse or expand in the event of both PCUs on one side having no hydraulic pressure, and enable operation of the opposite side elevator. If one of the pair of on-side PCU control valves jams, the jam-tolerant input rod will allow operation of the adjacent PCU control valve.
Flutter Damper
Two flutter dampers are installed on each elevator. These are identical in design and function to those installed on the ailerons.
FLIGHT CONTROLS Description Vol. 2 10.10.5
Oct 05/06
Pitch Control . Schematic
Figure 10.10.3
FLIGHT CONTROLS Description Vol. 2 10.10.6
Oct 05/06
Rudder
Yaw control is provided by a hydraulic actuated rudder, hinged on the rear spar of the vertical stabilizer. Two separate mechanical control paths are provided from the rudder pedals to three independent PCUs. Each PCU is powered by a separate hydraulic system. A position transmitter provides visual indication of rudder deflection on the FLIGHT CONTROLS synoptic page.
Both rudder pedal control systems have an anti-jam breakout mechanism. In the event of a jammed rudder control on one side, both pilot and copilot rudder pedals are capable of operating the remaining control system. Additional force on the rudder pedals is required to bypass the inoperative side, allowing rudder operation.
A two-channel yaw damper system is installed, and supplies small rudder corrections in response to reference signals from the IRUs through the FCCs. This is considered a function of the automatic flight control system (AFCS). Refer to Chapter 4, Automatic Flight Control System, for additional information.
FLIGHT CONTROLS Description Vol. 2 10.10.7
Oct 05/06
Yaw Control . Schematic
Figure 10.10.4
SECONDARY FLIGHT CONTROLS
Description
The secondary flight controls include the horizontal stabilizer, inboard and outboard flaps, flight and ground spoilers, and the associated trim systems. The horizontal stabilizer trim is electrically actuated via a jackscrew. Flaps are electrically powered, and are driven by flex cables and ball screw actuators. Spoilers are hydraulically powered. Trim about all three axes is electrically controlled from the cockpit.
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605公务机机组操作手册 CL605-飞行操纵 FLIGHT_CONTROLS(4)
|
