737 AMM 飞机维护手册 飞行操纵 FLIGHT CONTROLS 3(49)

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DIAMETER  MAX WEAR DIM.  MAX DIAM CLEAR ANCE 
MIN  MAX 
3 3  TRACK  ID  0.5000  0.5210  0.0100  X 
BOLT  OD  0.4365  0.4370  X 
4  BUSHING  ID  0.4995  0.5005  0.5025  0.0030  X 
BOLT  OD  0.4990  0.4995  0.4965  X 
5  BUSHING  ID  0.5010  0.5050  0.5070  0.0090  X 
BOLT  OD  0.4990  0.4995  0.4965  X 
6  BUSHING  ID  0.7690  0.7710  0.7750  0.0290  X 4 
BUSHING  OD  0.7500  0.7510  0.7430  X 
7  BUSHING  ID  0.4370  0.4420  0.4470  0.0100  X 
BOLT  OD  0.4365  0.4370  0.4270  X 
8  BUSHING  ID  0.4370  0.4420  0.4470  0.0100  X 
BOLT  OD  0.4365  0.4370  0.4270  X 
9  BUSHING  ID  0.7690  0.7710  0.7750  0.0290  X 4 
BUSHING  OD  0.7500  0.7510  0.7430  X 
10  BUSHING  ID  0.4370  0.4420  0.4470  0.0100  X 
BOLT  OD  0.4365  0.4370  0.4270  X 
11  BUSHING  ID  0.4370  0.4420  0.4470  0.0100  X 
BOLT  OD  0.4365  0.4370  0.4270  X 

LOOSE FIT BUSHING PROVIDES FOR 0.062 INCH NOMINAL CLEARANCE BETWEEN BUSHING
AND FITTING.
NO BUSHING BETWEEN BOLT AND TRACK PROVIDES FOR 0.074 INCH NOMINAL CLEARANCE
BETWEEN BOLT AND TRACK.
IF PRESS FIT BUSHINGS IN FORWARD SUPPORT FITTING HAVE BEEN REPLACED, REAM
BUSHINGS TO DESIGN LIMITS.

502  Outboard Flap Track Wear Limits 
May 01/03  Figure 601 (Sheet 3)  27-51-151 
Page 603 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

INBOARD FLAP TRACKS - REMOVAL/INSTALLATION
1. General
A.  The flap track installation requires use of solid tapered aluminum shim and rub strip at point where track attaches to wing rear spar and landing gear trunnion support beam. Maximum design thickness of shim is determined at jig assembly of wing and flap track during manufacture. Some airplanes were delivered with phenolic rub strip, laminated shims, and aluminum fillers and other airplanes were delivered with aluminum rub strip and solid tapered aluminum shim. If shim replacement is necessary, the solid tapered shim with aluminum rub strip is the preferred replacement.
B.  During track replacement it is extremely important to maintain thickness of shims as originally manufactured. Instructions are provided for replacing damaged or lost tapered shim and rub strip. Failure to follow instructions will result in incorrect track alignment after installation. If a tapered aluminum shim and aluminum rub strip are being fabricated to replace a tapered aluminum shim and phenolic rub strip, the thickness of the new shim and rub strip should be equal to the thickness of the original shim and rub strip.
2.  Inboard Flap Outboard Track - Removal/Installation
A.  Equipment and Materials
(1)  
Primer - BMS 10-11, Type I (Ref 20-30-41)

(2)  
Corrosion Preventive Compound - MIL-C-11796, Class 3 (Ref 20-30-21)

(3)  
Grease - MIL-G-23827 (Ref 20-30-21)

(4)  
Sealant - BMS 5-95 (Ref 20-30-11)

(5)  
Inboard Flap Rigging Tools:

(a)
Inboard Flap Rigging Beam - F80209-3 (Preferred)(Ref 27-09-700)

NOTE:  Rigging Beam is a part of F80209-1.

(b)  
Inboard Flap Rigging Tool - 2TE65-73720-1 and -2 (Optional)

 

B.  Prepare Inboard Flap Outboard Track for Removal
(1)  
Remove trailing edge flaps (Ref 27-51-12, R/I).

(2)  
Remove flap transmission (Ref 27-51-281, R/I).

(3)  
Remove power plant (Ref Chapter 71, Power Plant).

(4)  
Remove fixed fairing (Ref Chapter 71, Fixed Fairing).

(5)  
Remove engine-to-wing mid fairing (Ref Chapter 54, Engine-to-Wing Mid Fairing).

(6)  
Remove aft vibration isolator (Ref Chapter 71, Aft Vibration Isolator).

C.  Remove Inboard Flap Outboard Track
(1)  Remove track aft attach bolts (Fig. 401).
NOTE:  Be careful not to damage rub strip or tapered shim when flap track is removed to simplify reinstallation.
Rub strip is bonded to wing lower surface. Tapered shim is bonded to the flap track upper surface.
505 
Oct 20/84  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-51-161 Page 401 
　
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