535 
Jun 20/89  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-81-12 Page 407 

NOTE:  With flap nose rod disconnected and flap nose link connected and flap nose folded back, clearance between flap nose and operating crank should be
0.01 +0.01 inch.
(c)  
Follow adjustment of link with flap nose rod adjustment to ensure that flap nose contacts pads on flap panel with flap fully extended (actuator bottomed out) and to ensure flap nose will clear fuel boost pump with flap fully retracted. Tighten and lockwire link and rod adjustment nuts.

NOTE:  If adjustment of flap nose link and flap nose rod will not provide proper clearance between flap nose and fuel boost pump, replace or relocate the flap linkage attach fittings, and adjust the linkage.

(d)  
Connect link and rod to operating crank. Tighten nuts 5 to 10 pound-inches and install cotter pins.

(e)  
Recheck clearances and readjust as required.

(5)  
Remove restraint from disconnected outboard flap nose rod and connect to operating crank. Tighten nut 5 to 10 pound-inches and install cotter pin.

(6)  
On outboard flap and outboard flap nose of inboard flap, if flap nose did not clear structure and upstop beam at aft edge of flap cavity on retraction, adjust linkage as follows:

(a)  
Disconnect flap nose links and rods from both operating cranks.

(b)  
Shorten length of flap nose links if quicker retraction of flap nose is required. Lengthen links for slower retraction of flap nose.

(c)  
Follow adjustment of links with adjustment of flap nose rods to ensure that flap nose contacts pads on flap panel with flap fully extended (actuator bottomed out). Tighten and lockwire link and rod adjustment nuts.

(d)  
Connect links and rods to operating cranks. Tighten nuts 5 to 10 pound-inches and install cotter pins.

(e)  
Recheck clearances and readjust as required.

(7)  
Check that a minimum of 0.04 inch clearance exists between retracted flap and any adjacent airplane component in the leading edge flap cavity. This check applies to all flap locations.

W.  Check flap nose clearances with flap retracted hydraulically.
(1)  
Provide system A hydraulic power (Ref 27-81-00 MP).

(2)  
Retract leading edge flap.

(3)  
Check that clearances specified in step V for manual retraction are maintained with flap retracted hydraulically.

(4)  
Remove system A hydraulic power (Ref 27-81-0 MP).

(5)  
If required, readjust flap nose linkages and recheck clearances with flap retracted hydraulically.

504 
27-81-12 Page 408  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Jun 20/91 

X.  On inboard flap, install seal between inboard and outboard flap noses with five screws and retainer. (Seal was removed at beginning of installation.)
Y.  Provide system A hydraulic power (Ref 27-81-0 MP).
Z.  Check that seal depressor contacts entire length of bulb seal on wing structure with flap retracted and clears leading edge structure on flap extension (Section E-E). Adjust seal as required.
AA. Extend leading edge flap fully and remove system A hydraulic power (Ref 27-81-0 MP).
AB. Remove leading edge flap actuator lock.
AC. Provide system A hydraulic power and retract flaps (Ref 27-81-0 MP).
AD. Check flap panel gaps and mismatch as follows:

(1)  
Check gap at flap panel trailing edge and mismatch at leading edge (Section B-B).

(2)  
Check that gap between inboard and outboard flap panels is 0.06 to 0.15 inch except for aft 5 inches of flap which is to be 0.06 to 0.25 inch.

(3)  
If gaps and mismatch are not as required, check wing structure for damage and warpage.

NOTE:  The above checks are made to ensure correct alignment of flap and wing structure. No adjustments can be made.
AE. Remove system A hydraulic power, if no longer required (Ref 27-81-0 MP).
AF. Reinstall landing light lens, if removed.
AG. Install forward wing to body fairing, if removed.

521 
Feb 20/90  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-81-12 Page 409 

LEADING EDGE FLAPS - INSPECTION/CHECK
1.  General
A.  This data consists of illustrations and wear limit charts. This section gives no procedures for gaining access to or removing the components, or for replacing them after inspection for wear. Refer to component removal/installation for this information.
2.  Leading Edge Flaps Wear 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 飛機維護手冊 飛行操縱 FLIGHT CONTROLS 3(160)