(2)  
Pull inboard on WFFA cable in wheel well until jackscrew stops contact.

500 
27-61-51 Page 404  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Feb 01/95 

N.  Remove systems A and B hydraulic power (Ref 27-61-0 MP).
O.  Place speed brake control lever in DOWN position.
P.  Using hand pressure on upper surface of spoiler panel push down until actuator piston bottoms.
Q.  Check that spoiler to flap clearance for flight spoilers is 0.03 (+ 0.10/-0.00) inch. Measure at point of minimum clearance (Fig. 402).
R.  If spoiler to flap clearance is not within limits:
(1)  
Provide systems A and B hydraulic power (Ref 27-61-0 MP).

(2)  
Provide access to spoiler actuator by either lowering flaps or opening applicable trailing edge panel or by placing speed brake control lever in UP position to raise spoilers. Depressurize hydraulic systems A and B (Ref 27-61-0 MP).

WARNING:  DO NOT PUT ANY PART OF BODY BETWEEN SPOILER AND WING UNLESS HYDRAULIC POWER IS REMOVED. SERIOUS INJURY CAN RESULT.

(3)  
Break lockwire and loosen checknut on actuator rod end.

(4)  
Disengage locking key from piston rod.

(5)  
Turn actuator piston rod to obtain proper spoiler to flap clearance. Each quarter turn will change spoiler to flap clearance by approximately 0.12 inch.

CAUTION:  TURNING PISTON ROD WHEN ACTUATOR IS PRESSURIZED WILL DAMAGE ACTUATOR.

(6)  
Engage locking key with piston rod.

(7)  
Coat rod end threads with corrosion preventive compound.

(8)  
Tighten rod end checknut to 350-400 pound-inches.

(9)  
Lockwire checknut to locking key.

S.  Check spoiler to flap clearance with hydraulic power on.
(1)  
Provide systems A and B hydraulic power (Ref 27-61-0 MP).

(2)  
Lower spoilers or raise flaps, if applicable.

500 
Jun 20/89  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-61-51 Page 405 

A89650
 Flight Spoiler Adjustment  500 
27-61-51  Figure 402  Oct 20/92 
Page 406 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

(3)  
Rotate captain's control wheel clockwise to ensure that flight spoilers No. 2 and 3 are full down, or counterclockwise to ensure that flight spoilers No. 6 and 7 are full down.

(4)  
Check that spoiler to flap clearance is 0.03 + 0.10/-0.00 inch.

(5)  
If spoiler to flap clearance is not within limits, adjust per step R.

T.  Adjust spoiler actuator input arm.
NOTE:  Adjustment of all flight spoiler actuator input arms is presented in this procedure. However, only actuator which has been changed need be checked.
(1)  
Install protractor mount and bubble protractor on captain's aileron control wheel.

(2)  
Place straightedge across both aileron control wheels and set bubble protractor to zero with control wheels in this position. Remove straightedge.

(3)  
Provide systems A and B hydraulic power (Ref. 27-61-0).

(4)  
Set control surface protractor to zero as follows:

(a)  
Turn captain's control wheel clockwise from neutral to ensure that flight spoilers No. 2 and 3 are fully retracted.

(b)  
Position protractor and stand on flight spoiler and set protractor to zero.

NOTE: Protractor may be hand-held on spoiler instead of using stand.
(5)  
Rotate captain's control wheel counterclockwise 50 + 5 degrees and return toward neutral.

(6)  
Check that flight spoilers No. 2 and 3 are fully retracted when the captain's control wheel is 4 + 2 degrees counterclockwise from neutral. Check that spoiler-to-flap clearance remains at 0.03 (+ 0.10/-0.00) inch.

(7)  
If check in step (6) is not within limits:

(a)  
Lower trailing edge flaps by placing flap control lever in FLAP DOWN detent.

(b)  
Hold captain's control wheel at 9 +1 degrees counterclockwise from neutral.

(c)  
Break lockwire on input lever adjusting screw and loosen checknut (Fig. 401).

(d)  
Using adjusting screw set No. 2 and 3 actuators so that spoiler panels begin to rise from the zero (fully retracted) position.

(e)  
Raise trailing edge flaps by placing flap control lever in FLAP UP detent.

(f)  
Release captain's control wheel and perform steps (5) and (6). Spoilers must operate within these limits.
　
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(cè) 飛行操縱 FLIGHT CONTROLS 3(108)