[*] AIRPLANES WITH POSITION INDICATION MODULE WITH BUILT-IN-TEST
EQUIMENT
SENSOR - LEADING EDGE FLAP AND 27-88-11
SLAT PROXIMITY
Removal/Installation 401 ALL
Removal/Installation 401
Slat Proximity Sensor 401
Flap Proximity Sensor 412
Adjustment/Test 501 ALL
SWITCH - FLAPS 10-DEGREE 27-88-21
Removal/Installation 401 ALL
27-CONTENTS
BEJ Page 25 Mar 12/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL CHAPTER 27 - FLIGHT CONTROLS TABLE OF CONTENTS
_________________
Chapter
Section
Subject_______ Subject_______ Page____ Effectivity___________
Adjustment/Test 501 ALL
SWITCH - STALL WARNING 27-88-31
Removal/Installation 401 ALL
27-CONTENTS
BEJ Page 26 Mar 12/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
FLIGHT CONTROLS - DESCRIPTION AND OPERATION
___________________________________________
1. General_______
A. The primary flight controls are the ailerons, elevators, and rudder (Fig. 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 null detent 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 (Fig. 2). With hydraulic power on, the control wheel forces are provided by an artifical feel mechanism as all these surfaces are fully hydraulic 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 (Fig. 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 (Fig. 4 and 5). Switches for these valves are on the pilots' overhead panel. The aileron power control units are interchangeable with the elevator power control units and are located in the left wheel well. The aileron power control units drive a bus cable system 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.
B. Lateral (roll) trim is accomplished by the aileron trim control switches (Fig. 2) located on the control stand. An electrical actuator in the left wheel well repositions the artificial feel and centering mechanism null detent. This shift of aileron control system null detent provides trim correction by positioning the ailerons.
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27-00-00
ALL ú ú 01 Page 1 ú Jun 25/84
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
LEADING EDGE FLAPS (SHOWN EXTENDED)
Flight Control Surfaces
Figure 1
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
27-00-00
ALL ú ú 02 Page 2 ú Nov 15/98
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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