501 
27-09-400 Page 512  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Sep 20/82 

NOTE:  Shim thickness between leaf spring and midflap must be changed an equal amount when shim thickness between carriage bearing support and midflap is changed (i.e. add same thickness shim under leaf spring as removed from under carriage bearing support). Tapered filler between leaf spring and midflap may be used individually or at both track locations and may be positioned with thick end forward or aft or reversed relative to each other.
4)  Secure leaf spring with bolt at forward attach point.
5)  Secure retainer with radius filler, washer and nut at each aft attach point. Tighten 3/8 nut within 160 to 190 pound-inch torque range and tighten 5/16 nut within 100 to 140 pound-inch torque range. Install cotter pin.
6)  Repeat steps (a) thru (d) to check adjustment.
501 
Jun 20/87  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-09-400 Page 513 

(12a) If shim thickness between midflap carriage bearing support and midflap forging has been changed, adjust flap jackscrew preload cup (Ref 27-51-72 A/T).
CAUTION:  ADJUSTMENT OF SHIM THICKNESS BETWEEN MIDFLAP CARRIAGE BEARING SUPPORT AND MIDFLAP FORGING CHANGES PRELOAD CUP ADJUSTMENT. INCORRECT ADJUSTMENT MAY CAUSE DAMAGE TO PRELOAD CUP.
(13)
Check adjustment of outboard flap track fairing (Ref 27-51-121 A/T).

(14)
Check that clearance between deflection control ramp and roller at outboard end of midflap is per Fig. 502. Adjust, if required (Ref 27-51-72 R/I).

D.  Restore Airplane to Normal
(1)  
Remove system A hydraulic power (Ref 27-51-0 MP).

(2)  
Apply sealant to carriage access panel and midflap faying surface and install access panels on upper surface of midflap.

5.  Adjust Trailing Edge Flaps for 40-Unit Discrepancy
A.  Symmetrical gaps between the mid and aftflaps of outboard flaps are critical at FLAP DOWN (40-unit) position. Shimming of carriage bearing support or torque tube adjustment will have little effect at FLAP DOWN position. If a trim discrepancy is reported, proceed as follows:
(1)  
Provide system A hydraulic power (Ref 27-51-0 MP).

(2)  
Position flap control lever at FLAP DOWN (40-unit) position.

(3)  
Remove system A hydraulic power and depressurize hydraulic system A (Ref 27-51-0 MP).

(4)  
Measure mid-to-aftflap gap at inboard and outboard ends of aftflap on both wings (Fig. 505). Check that inboard gaps on each wing are equal within 0.05 inch and outboard gaps on each wing are equal within 0.05 inch. If gaps are not within limits, adjust gaps as follows:

(a)  
Adjust aftflap bellcrank clevis arm (not aftflap pushrod) at both flap track fairings on one or both wings as necessary to obtain correct gaps. Ensure that dimension B at both flap tracks remains with in limits (Fig. 505).

(b)  
Retract flaps by providing system A hydraulic power (Ref 27-51-0 MP), retracting flaps to FLAPS UP position and removing system A hydraulic power (Ref 27-51-0 MP).

(c)  
Check that aftflap leading edge to midflap trailing edge gap is per Fig. 505. If necessary, adjust aftflap pushrods at both flap track fairings to obtain correct gap.

(d)  
Extend flaps to 40 units and ensure that mid-to-aftflap gaps and dimension B remain unchanged.

(5)  
Retract flaps.

501 
27-09-400 Page 514  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Jun 20/87 

6.  Aileron Tab Adjustment to Equalize Lateral Manual Reversion Forces
A.  General
(1)  If aileron manual reversion asymmetrical flight control forces exceed the allowable 2 to 1 ratio, the following procedure should be used to adjust the aileron tab (AMM 27-11-0/501 Flight Test to Determine and Correct Asymmetrical Flight Control Forces).
B.  Equipment and Materials
(1)  Aileron Tab Alignment protractor - F80222-1 (Ref 27-09-700/201, MP)
C.  Adjust Aileron Tab
(1)  It is essential to verify that a misrigged or out of tolerance condition does not exist prior to determining amount of adjustment required; therefore, do the steps:
(a)  
Make sure the aileron balance tab is correctly adjusted (AMM 27-11-0/501).

(b)  
Make sure the aileron control forces, with power off, are not more than the specified limits (AMM 27-11-0/501, “use a torque wrench and control wheel torque and force test adapter to measure the torque necessary to turn the captain’s control wheel”).
　
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 1(36)