G17883

G11817
535  Trailing Edge Flap System Adjustment 
May 15/72  Figure 501 (Sheet 2)  27-51-01 
Page 503 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

B.  Equipment and Materials
(1)  
Rigging Pin F-1 - 0.311 +0.000/-0.002 inch diameter, 2.35 +0.06-inches long (MS20392-4)

NOTE:  Rigging pin is a part of kit F70207-61, or -84.

(2)  
Flap Drive Adapter - F70300-1

(3)  
Control Column Protractor Assembly 4MIT65B80307-1 (Preferred) or F52485-500 (Optional)

(4)  
Protractor Stand Assembly - F71292-17

C.  Adjust Trailing Edge Flap System
(1)  Retract trailing edge flaps and depressurize hydraulic system.
CAUTION:  IF MAINTENANCE HAS BEEN PERFORMED ON FLAP CONTROL OR FLAP DRIVE SYSTEM, FLAP RETRACTION SHOULD BE CLOSELY MONITORED TO PREVENT DAMAGE DUE TO IMPROPERLY ADJUSTED COMPONENTS.
(a)  
Connect electrical power to airplane.

(b)  
Provide system A hydraulic power (Ref 27-51-0 MP).

(c)  
Set flap control lever in FLAP UP detent.

NOTE:  If asymmetry shutoff mechanism is not properly adjusted, flaps may not operate. Manually positioning asymmetry shutoff valve will allow flap operation.

(d)  
After flaps are fully retracted, wait 2 minutes then depressurize hydraulic system A (Ref 27-51-0 MP).

(2)  Adjust flap control cables WFA and WFB.
(a)  
Lift flap control lever and clamp so that index dog is disengaged from detent plate.

(b)  
Place shims between flap control lever riveted on drum and telescoping handle to prevent relative fore and aft movement of handle. Shims should be placed in aft gap between lever and handle.

NOTE: Shims are used to compensate for wear between lever and handle.

(c)  
Position flap control lever all the way forward and then release lever.

(d)  
Check that lever springs back to rigging position (Fig. 502).

(e)  
Open lower nose compartment access door 1103.

(f)  
Check that tension in WFA and WFB cables is within limits of that specified in temperature-tension chart (Fig. 501).

(g)  
If conditions in steps (d) and (f) are not within limits: 1) Remove forward right ceiling panel in aft cargo compartment (Ref Chapter 25,

587 
27-51-01 Page 504  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  May 01/99 

Cargo Compartment Ceiling Lining). 2) Clamp flap control quadrants against quadrant stop (Fig. 503).
NOTE:  Ensure that no foreign matter is on contacting surface of quadrant stop.
3)  Remove turnbuckle locking clips from WFA and WFB turnbuckles in lower nose compartment.
4)  Adjust turnbuckles so that flap control lever springs back to rigging position  (Fig. 502). Adjust so that cable tension is within limits of that specified in temperature-tension chart (Fig. 501).
5) Install turnbuckle locking clips.
6) Remove clamp from flap control quadrant.
7) Install aft cargo compartment ceiling panel (Ref Chapter 25, Cargo

Compartment Ceiling Lining).
(h)  
Remove clamp and shims from flap control lever.

(i)  
Position flap control lever in FLAP UP detent.

(3)  Adjust flap follow-up cables WFFA and WFFB.
(a)  Check that index mark on drum and matching mark on flap power unit housing align within + 0.03 inch (Fig. 504). If index marks do not align: 1) If flap transmission upstops are not in contact, position flap bypass valve to
BYPASS (position 2) and manually rotate flap torque tubes. Rotate torque tubes until index mark on drum aligns with index mark on housing within + 0.03 inch.
535 
Sep 20/82  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-51-01 Page 505 

G11927G11935 G11974
Flap Control Lever Rigging Position  535 
27-51-01  Figure 502  Aug 15/80 
Page 506 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

535  Flap Control Unit Adjustment 
Oct 20/85  Figure 503 (Sheet 1)  27-51-01 
Page 507 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

Flap Control Unit Adjustment  535 
27-51-01  Figure 503 (Sheet 2)  May 15/72 
Page 508 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

2)  If flap transmission upstop contact prevents rotation of torque tubes; disconnect both torque tubes from flap power unit, position flap bypass valve to BYPASS (position 2) and manually rotate power unit output shaft. Rotate output shaft until index mark on drum aligns with index mark on housing within + 0.03 inch. Connect torque tubes and lockwire heads of coupling screws together.
　
中國(guó)航空網(wǎng) m.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 2(181)