Description and Operation
Flow Limiting Valve
Hydraulic Fuse
Leading Edge Flap Actuator
Leading Edge Flap and Slat Control Valve
Leading Edge Flaps
Leading Edge Slats
Leading Edge Slat Actuator
Leading Edge Standby Drive Shutoff Valve
Trouble Shooting
Maintenance Practices
Application of Hydraulic Power
Adjustment/Test
Leading Edge Flaps ................................................................................................. 27-81-12 Removal/Installation Inspection/Check
Leading Edge Slats.................................................................................................. 27-81-21 Removal/Installation Inspection/Check
Leading Edge Flap Actuator .................................................................................... 27-81-31 Removal/Installation Inspection/Check
Feb 20/84 Contents 27 Page 13 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
Subject Subject No.
Leading Edge Slat Actuator ..................................................................................... 27-81-41 Removal/Installation Inspection/Check
Leading Edge Slat Aerodynamic Seal ..................................................................... 27-81-51 Removal/Installation
Leading Edge Flap and Slat Hydraulic Fuse ........................................................... 27-81-61 Removal/Installation
Leading Edge Flap and Slat Flow Limiting Valve .................................................... 27-81-71 Removal/Installation Adjustment/Test
Leading Edge Flap and Slat Control Valve.............................................................. 27-81-81 Removal/Installation Adjustment/Test
Leading Edge Standby Drive Shutoff Valve............................................................. 27-81-91 Removal/Installation Adjustment/Test
Leading Edge Slat Actuator Switch ......................................................................... 27-81-111 Removal/Installation
LEADING EDGE FLAP AND SLAT POSITION INDICATING SYSTEM .................... 27-88-0
Description and Operation
Leading Edge Devices Annunciator Panel
Leading Edge Flap and Slat Position Indication Module
Leading Edge Flap and Slat Position Indicator
Proximity Sensors
Trouble Shooting
Leading Edge Flap and Slat Proximity Sensors ...................................................... 27-88-11 Removal/Installation Adjustment/Test
Flaps 10-Degree Switch........................................................................................... 27-88-21 Removal/Installation Adjustment/Test
Leading Edge Flap and Slat Position Indication Module ......................................... *[5] 27-88-41 Maintenance Practices
*[1] Airplanes with aluminum/fiberglass rudder *[2] Airplanes with graphite/composite rudder *[3] Airplanes with aluminum/fiberglass elevators *[4] Airplanes with graphite elevators *[5] Airplanes with SB 27-1181 *[6] Airplanes incorporating SB 27A1206
500
Contents 27 Page 14 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. May 01/99
FLIGHT CONTROLS - DESCRIPTION AND OPERATION
1. General
A. The primary flight controls are the ailerons, elevators and rudder. (See figure 1.) These hydraulically-powered control surfaces provide flight control in roll, pitch and yaw. The auxiliary flight controls are the trailing edge flaps, leading edge flaps and slats, the spoilers, and an adjustable horizontal stabilizer.
B. Lateral (roll) trim is provided by repositioning the aileron neutral to deflect the ailerons. Longitudinal (pitch) trim is provided by positioning the adjustable horizontal stabilizer. Directional (yaw) trim is provided by repositioning rudder neutral to deflect the rudder.
2. Roll Control System
A. The roll (lateral) control surfaces consist of the two ailerons and the four flight spoilers. These surfaces are controlled by rotation of the captain's and first officer's control wheels. (See figure 2.) The control wheel forces are sufficient for pilot feel only, as all these surfaces are normally hydraulically-powered. Control signals from the pilots' control wheels are transmitted through the aileron control system to the control valves on the two aileron power control units. (See figure 3.) These power control units are supplied with hydraulic power, one from system A and the other from system B. Aileron hydraulic supplies are controlled by the flight controls shutoff valve in each flight controls hydraulic modular package. (See figures 4 and 5.) Switches for these valves are on the pilots' overhead panel. The aileron power control units, which are interchangeable with the elevator power control units, are located in the left wheel well. They drive a bus cable system which is connected to the ailerons by quadrants and pushrods. Balance tabs and balance panels aerodynamically reduce the forces required for aileron movement. In the event of hydraulic failure, motion of the pilots' control wheels mechanically positions the ailerons.
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