(2)  
Replace sensor with obvious asymmetrical erosion patterns between vane upper and lower surfaces, asymmetrical patterns of nicks, deteriorated index hole, and bent vane shaft.

C.  Check vane for excessive rotational friction.
(1)  Rotate vane slowly and check that only light pressure is required to turn vane. If friction is excessive, replace vane.
D.  Check that sensor drain hole is free of obstructions. Remove any obstruction (drain hole Conrac only).
508 
Jun 20/85  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-32-11 Page 601 

Angle of Airflow Sensor Check  501 
27-32-11  Figure 601  Jun 20/85 
Page 602 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

STALL WARNING MODULE - REMOVAL/INSTALLATION
1. Remove Stall Warning Module
A. Open the STALL WARNING circuit breakers at the P18 circuit breaker panel.
B. Support module and release four fasteners securing module to aft overhead panel.
C. Lower module, disconnect electrical connector and remove module from airplane.
2. Install Stall Warning Module
WARNING:  USE ONLY A STALL WARNING MODULE BOEING PART NO. 69-37339-XX, CONRAC CO. PART NO. 305-2600-XX OR UNITED CONTROLS PART NO. 965-0197-XX AS REPLACEMENT FOR AN EXISTING MODULE, BECAUSE NOT ALL MODULES ARE FUNCTIONALLY INTERCHANGEABLE.
A. Connect electrical connector to receptacle on back of module.
B. Install module in aft overhead panel and secure the four fasteners.
NOTE: Ensure module is installed with STALL WARNING callout located aft.
C. Close STALL WARNING circuit breakers.
D. Perform stall warning system test. Refer to 27-32-0, Stall Warning System - Adjustment/Test.
500 
Feb 15/70  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-32-21 Page 401 

CONTROL COLUMN SHAKER - REMOVAL/INSTALLATION
1.  Remove Control Column Shaker
A.  Open the STALL WARN circuit breakers at the P18 circuit breaker panel.
B.  Disconnect electrical connector from shaker unit (Fig. 401).
C.  Remove two nuts and bolts attaching shaker unit to control column retainer strap.
D.  Remove shaker unit from airplane.
2.  Install Control Column Shaker
A.  Attach shaker unit to control column retainer strap, maintaining 10.90 inches between center of strap and top of clamp at base of control column (Fig. 401).
B.  Tighten bolts within 20 to 25 pound-inches torque range. Add or remove shims as required between shaker unit and retainer strap.
C.  Connect electrical connector to receptacle on underside of shaker unit.
D.  Close STALL WARN circuit breakers.
E.  Depress the toggle switch on the face of the stall warning module to TEST position. Check to ensure control column shaker operates, then return toggle switch to NORMAL position.
500 
Feb 15/69  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-32-31 Page 401 

G10574
Control Column Shaker Installation  500 
27-32-31Page 402   Figure 401 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Feb 15/69 

A HORIZONTAL STABILIZER TRIM CONTROL SYSTEM - DESCRIPTION AND OPERATION
1.  General
A.  The horizontal stabilizer trim control system provides longitudinal trim of the airplane by varying the angle of attack of the horizontal stabilizer. The horizontal stabilizer is moved through 17.0 degrees of travel by means of a jackscrew with ball nut (Fig. 1). Two actuators and a cable drum on the jackscrew gearbox provide for trim control from three separate control systems. The normal control is an electrical system which actuates the jackscrew through the main electric actuator. Autopilot control is provided by the autopilot actuator on the gearbox. A manual control system drives through cables to the cable drum on the jackscrew gearbox. The manual system remains engaged at all times and is therefore back-driven by the main electric actuator or autopilot actuator during normal operation. Manual system operation will disengage both the normal electrical and autopilot actuators if these systems become jammed. A continuous indication of stabilizer position is provided by trim position indicators adjacent to trim wheels on the control stand. The indicator s are positioned by the manual system. A takeoff warning system indicates any unsafe stabilizer position for takeoff (Ref 31-26-0, Description and Operation). A stabilizer trim brake unit, located under the control stand, arrests the motion of stabilizer system during trimming when opposed by the motion of the elevator control.
　
中國航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機(jī)維護(hù)手冊 飛行操縱 FLIGHT CONTROLS 2(135)