cable is exposed. 2) Remove bolt-attaching lower rod end to landing gear torsion link. 3) Install rigging pin SB-3. 4) Loosen checknut and adjust lower rod end so that attaching bolt will fit freely
when installed.
Feb 15/73 27-62-0 Page 508A/508B BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

G39075 G39098
500  Ground Spoiler Control Valve Adjustment 
Feb 15/68  Figure 504  27-62-0 
Page 509 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

Ground spoiler Interlock Valve  543 
27-62-0  Figure 505  Feb 15/73 
Page 510 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

5)  Ensure that threads are visible in inspection hole of rod end.
6)  Install bolt attaching rod end to landing gear torsion link. Secure bolt with washer, nut and cotter pin.
7)  Ensure that both upper and lower rod ends properly align and tighten checknut
on lower rod end.
8)  Position protective boot over rod end and secure with clamp.
9)  Remove rigging pin SB-3.
10)  Remove jacks from airplane.
(5)  Adjust Ground Spoiler Panel to Flap Clearance
(a)  
Connect external electrical power to airplane.

(b)  
Provide system A hydraulic power (Ref 27-62-0 MP).

(c)  
Place speed brake control lever in UP position to raise ground spoilers.

(d)  
With hydraulic power on, retract the flaps to the UP position by placing the flap control lever in the FLAP UP detent.

(e)  
Place speed brake control lever in DOWN position to lower ground spoilers.

(f)  
Check that No. 4 and 5 spoiler to flap clearance is within limits on Fig. 506.

(g)  
Check that No. 1 and 8 spoiler to flap clearance is 0.03 + 0.10/-0.00 inch measured near actuator centerline.

NOTE:  Minimum spoiler panel gap measured along full panel span at trailing edge need only be sufficient to ensure that panel has clearance with flap.
543 
Aug 01/94  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-62-0 Page 511 

A89681
 Ground Spoiler Adjustment  504 
27-62-0  Figure 506  Oct 20/92 
Page 512 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

(h)  If spoiler to flap clearance in steps (f) or (g) is not within limits: 1) Record spoiler to flap clearance. 2) Provide access to spoiler actuator by either lowering flaps and opening
applicable hinged trailing edge panel or by placing speed brake control lever in UP position. Remove systems A and B hydraulic power and depressurize hydraulic system A (Ref 27-62-0, Maintenance Practices).
WARNING:  DO NOT PUT ANY PART OF BODY BETWEEN SPOILER AND WING UNLESS HYDRAULIC POWER IS REMOVED. SERIOUS INJURY CAN RESULT.
3) Break lockwire, loosen checknut and disengage locking key on actuator piston rod end. 4) Turn actuator piston rod to obtain proper spoiler to flap clearance. Each one-sixth turn of the actuator piston rod changes the gap at the trailing edge by
0.093 inch on ground spoilers No. 4 and No. 5 and by 0.05 inch on ground spoilers No. 1 and No. 8.
CAUTION:  TURNING ACTUATOR PISTON ROD WHEN ACTUATOR IS PRESSURIZED WILL DAMAGE ACTUATOR.
5) Coat actuator piston rod end threads with corrosion preventive compound. 6) Engage locking key with actuator piston rod. Tighten checknut to 100 to 200 pound-inches. 7) Provide system A hydraulic power with system B pump (Ref 27-62-0,
Maintenance Practices). 8) Lower spoilers, if applicable. 9) Check that spoiler to flap clearance is within limits. 10) Provide access to actuator. 11) Tighten checknut to 290 to 410 pound-inches and lockwire checknut to locking
key.
12) Apply a bead of sealant to the rod end checknut.

(i)  
Remove system A and B hydraulic power (Ref 27-62-0, Maintenance Practices).

(j)  
Remove electrical power if no longer required.

504 
Feb 01/95  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-62-0 Page 513 

(6)  Test Speed Brake Control System
3.  Speed Brake Control System Test
NOTE:  This test checks operation of ground spoilers No. 1, 4, 5, and 8, and the automatic speed brake operation of flight spoilers No. 2, 3, 6, and 7. Refer to 27-61-0, Test Spoiler Control System, for other tests of flight spoilers No. 2, 3, 6, and 7.
A.  Equipment and Materials
(1)  
Rigging Pins Kit - F70207-3, -52, -61, or -84:
　
中國航空網 m.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 3(122)