0.15 +0.03 inch aft of seal retainer. Determine position and adjust as follows:
(a)  
With aftflap extended, mark a line on lower surface of aftflap 2.00 inches aft of leading edge.

(b)  
Retract aftflap then mark a line on lower surface of midflap 2.15 inches forward of line marked in step (a).

(c)  
Extend aftflap and check that aft face of seal retainer vertically aligns with line marked in step (b).

(d)  
If seal retainer does not align, add or remove shims under seal retainer at each fastener to obtain correct position.

(11)
Check that gap between trailing edge of foreflap and top of midflap is per section A-A between ends of flap. If required, shim between foreflap and foreflap track attach fitting to obtain correct gap (Ref AMM 27-51-41, Removal/Installation).

(12)
Check that gap between trailing edge of midflap and top of aftflap is 0.06 +0.09/-0.05 inch.

NOTE:  Gap between midflap trailing edge and top of aftflap is not considered as adjustable. It may be possible to adjust shim thickness at midflap trailing edge attach point or to make slight adjustment by adjusting pushrods (11 and 14), however, the 16 .00 +0.12 inch dimension must be held. If proper gap cannot be obtained, defective or malformed parts must be replaced.

(13)
Check that phenolic rub strip on nacelle fairing closure door contacts lower surface of hinge flap for its entire surface. If adjustment is necessary loosen nut on pivot bolt and rotate eccentric bushing to obtain contact. If necessary, rotate eccentric one notch to align notch in eccentric with roll pin.

(14)
Install access panels in lower surface of midflap.

(15)
If flap is installed, install inboard flap track fairing (Ref AMM 27-51-141, Inboard Flap Track Fairings).

500 
Aug 01/94  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-51-12 Page 505 

501 
27-51-12 Page 506  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  May 15/78 

INBOARD MIDFLAP CARRIAGES - REMOVAL/INSTALLATION
1. General
A.  Removal of any inboard midflap carriage half requires removal of the applicable flap from the airplane. Removal of the flap requires removal of inboard track fairing and engine nacelle aft fairing.
B.  The flap drive gimbal shaft assembly must be removed from the midflap torque shaft to allow removal of carriage retaining bolts. The gimbal shaft is shimmed to provide proper flap drive screw preload. When any gimbal shaft is removed and replaced, the drive screw preload must be checked as outlined in AMM 27-51-12, Inboard Trailing Edge Flap - Removal/Installation.
2.  Equipment and Materials
A.  Primer - BMS 10-11, Type 1 (Ref 20-30-41)
B.  Grease - MIL-G-21164 (Ref 27-30-21)
C.  Corrosion Preventive Compound - MIL-C-11796, Class 3 (Ref AMM 20-30-21)
3.  Remove Inboard Midflap Carriage
A.  Remove inboard trailing edge flap from airplane (Ref AMM 27-51-12, Removal/Installation).
B.  For removal of inboard carriage: (Fig. 401)
(1)  
Install clamping device on boom cables where they pass through midflap end rib to prevent slack inside midflap when boom cables are loosened.

(2)  
Remove rigging pins from boom, loosen cables at each end of boom, and replace rigging pins; install one rigging pin on each side of boom roller.

(3)  
Dismount pulley bracket (11). Do not remove cable guards or cables from pulley and bracket assembly. Suspend assembly from flap torque shaft (4) during carriage removal and replacement.

505 
Feb 15/78  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-51-21 Page 401 

G43185G43198
Inboard Midflap Carriage Installation  500 
27-51-21  Figure 401 (Sheet 2)  Oct 20/92 
Page 402 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

500  Inboard Midflap Carriage Installation 
Oct 20/92  Figure 401 (Sheet 2)  27-51-21 
Page 403 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

(4)  For removal of inner carriage half (5), dismount pulley and boom roller support (6) with attached boom (1). Suspend assembly from midflap torque shaft.
C.  For removal of outboard carriage:
(1)  
Mark position of index plate (12) to simplify installation and adjustment.

(2)  
Remove crossbeam (17) from underside of carriage.

D.  Remove two gimbal shaft retaining bolts (13).
E.  Pull gimbal shaft (14) from end of torque shaft (4).  Carefully note total thickness of shims (15) under index plate (12) or under bearing retainer (19), as applicable.
　
中國航空網 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(12)