G02372G02376 G02403G07757
Flight Control Surfaces 500
27-00 Figure 1 Nov 15/67
Page 2
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
500 Pilot's Controls
Jun 15/66 Figure 2 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-00 Page 3
Roll Control System Schematic 501
27-00 Figure 3 May 01/99
Page 4
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
500 Flight Controls Hydraulic Modular Package
Feb 15/67 Figure 4 27-00
Page 5
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
C. Flight spoilers and ground spoilers are located on the upper surface of the wing. Two flight spoilers are outboard of each nacelle. One ground spoiler is outboard of the flight spoilers, and one ground spoiler is inboard of each nacelle. The flight spoilers are hydraulically actuated in response to inputs from the aileron control system. They rise on the wing with up aileron and remain faired on the wing with down aileron. Flight spoiler motion is in proportion to aileron movement. One spoiler actuator hydraulically positions each flight spoiler panel. Hydraulic system A provides power for spoilers 3 and 6. Hydraulic system B provides power for spoilers 2 and 7. The flight spoilers may be deactivated by the spoiler shutoff valves, in the flight controls hydraulic modular packages. (See figure 4.) These valves are controlled by spoiler system A and B switches on the pilots' overhead panel. (See figure 5.) All flight spoilers may also be used as speed brakes by aft movement of the speed brake control lever. (See figure 2.) The speed brake control lever actuates the spoiler control system to cause all the flight spoiler panels to rise in unison. The flight spoilers will still respond to aileron inputs when being used as speed brakes. With speed brakes on and the airplane on the ground, hydraulic system A will power the ground spoilers to full up position.
3. Pitch Control System
A. The elevators provide primary response of the airplane in pitch control. Fore and aft movement of the captain's and first officer's control columns (figure 2) is transmitted through the elevator control system to the control valves of the two elevator power control units. These power control units are supplied with hydraulic power, one from system A and the other from system
B. Elevator hydraulic supplies are controlled by the flight controls shutoff valve in each flight controls hydraulic modular package. (See figure 4.) Switches for these valves are located on the pilots' overhead panel. (See figure 5.) The power control units, which are interchangeable with the aileron power control units, are located in the empennage aft of the stabilizer rear spar. These power control units drive the elevator through pushrods and a torque tube. Balance panels aerodynamically reduce the forces required for elevator movement. In the event of hydraulic failure, motion of the pilots' control column mechanically positions the elevators. Also, the elevator balance tabs, which are hydraulically locked in a fixed position during powered elevator operation, are released to operate. These balance tabs further reduce the forces required to operate the elevator.
500
27-00 Page 6 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Nov 15/67
B. The adjustable horizontal stabilizer provides pitch (longitudinal) trim. The stabilizer is controlled by stabilizer trim control switches (figure 2) located on the outboard horn of both the captain's and first officer's control wheels. Manual operation of the stabilizer is accomplished by rotating the stabilizer trim control wheels which are located on the control stand. The stabilizer trim control wheels operate a forward mechanism which drives the stabilizer trim indicator and is connected to the stabilizer trim actuator by cables. The trim actuator is a gearbox, jackscrew and ballnut assembly which drives the stabilizer front spar to provide stabilizer motion. The gearbox is driven by an electric actuator, an autopilot actuator, and a cable drum. The autopilot actuator is a two speed reversible electric motor. Stabilizer trim cutout switches, which electrically isolate either of the drive motors, are located on the control stand.
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機維護手冊 飛行操縱 FLIGHT CONTROLS 1(14)
