747-400 AMM 飞机维护手册 飞行操纵 FLIGHT CONTROLS 6(52)

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4  BEARING LINER ID OD  1.31251.3115 1.31401.3130 (33.337)(33.312) (33.375)(33.35)  1.3050 1.3205 (33.147) (33.54)  (0.203) 0.008  1 3 
5  BOLT BUSHING ID OD  1.24901.2480 1.25101.2495 (31.724)(31.699) (31.775)(31.737)  1.2420 1.2570 (31.546) (31.927)  (0.203) 0.008  X X  2 2 
6  BOLT BEARING ID OD  1.24901.2480 1.25081.2500 (31.724)(31.699) (31.77)(31.75)  1.2420 1.2570 (31.546) (31.927)  (0.203) 0.008  4  X  2 
7  BUSHING FLANGED BUSHING ID OD  1.49901.4980 1.50101.5000 (38.074)(38.049) (38.125)(38.1)  1.4910 1.5080 (37.871) (38.303)  (0.228) 0.009  3  X  2 
8  BUSHING FLANGED BOLT ID OD  1.24901.2480 1.25101.2500 (31.724)(31.699) (31.775)(31.75)  1.2420 1.2570 (31.546) (31.927)  (0.203) 0.008  3  X  2 
9  BOLT BUSHING ID OD  1.24901.2480 1.25101.2495 (31.724)(31.699) (31.775)(31.737)  1.2420 1.2570 (31.546) (31.927)  (0.203) 0.008  X X  2 2 

Inboard Flight Spoilers Wear Limits
Figure 601 (Sheet 3)

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL

10 INDEX NO.  PART NAME DIM. OD IDBEARING BOLT  1.24901.2480 1.25081.2550 (mm) (mm) INCHES MINIMUM MAXIMUM INCHES DESIGN LIMITS DIAMETER (31.724)(31.699) (31.77)(31.75)  1.2420 1.2570 (mm) PERMITTED DIMENSION INCHES WEAR WEAR LIMITS (31.546) (31.927)  (mm) MAXIMUM DIAMETER CLEARANCE INCHES (0.203) 0.008  PART WORN REPLACE 4  PART WORN REPAIR X  REPAIR INSTR 2 
11  BUSHING FLANGED BUSHING OD ID  1.49901.4980 1.50101.5000 (38.074)(38.049) (38.125)(38.1)  1.4910 1.5080 (38.871) (38.303)  (0.228) 0.009  3  X  2 
12  BUSHING OD ID BOLT  1.12401.1234 1.12501.1245 (28.549)(28.534) (28.575)(28.562)  1.1184 1.1300 (28.407) (28.702)  (0.152) 0.006  X  X  2 
13  BUSHING FLANGED BUSHING OD ID  1.49901.4985 1.49801.4970 (38.074)(38.061) (38.049)(38.023)  1.5040 1.4920 (38.201) (37.896)  (0.177) 0.007  3 X 

REPLACE WHEN THE RADIAL CLEARANCE BETWEEN THE RACES IS MORE THAN 0.005 INCH (0.127 mm).

HARD CHROME PLATE TO A MAXIMUM THICKNESS OF 0.005 INCH (0.127 mm) PER QQ-C-320 AND GRIND
TO THE DESIGN LIMIT.
REPLACEMENT BUSHING CAN HAVE OVERSIZE OD TO +0.03 INCH (+0.762 mm).
REPLACE WHEN THE RADIAL CLEARANCE BETWEEN THE RACES IS MORE THAN 0.006 INCH (0.1523 mm).

Inboard Flight Spoilers Wear Limits
Figure 601 (Sheet 4)

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 ú  Oct 18/00 

BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
 OUTBOARD FLIGHT SPOILERS - REMOVAL/INSTALLATION
_______________________________________________
 1.  General_______
 A.  There are two tasks in this procedure. There is one task for the removal and one task for the installation of an outboard flight spoiler.
 (1)  
The removal procedure has these parts:

 (a)  
The extension of the spoilers

 (b)  
The extension of the trailing edge flaps

 (c)  
The installation of the support equipment

 (d)  
The removal of the spoiler.

 (2)  
The installation procedure has these parts:

 (a)  
A check of the parts that attach the spoiler for worn areas

 (b)  
The installation of the spoiler

 (c)  
The removal of the support equipment

 (d)  
An adjustment of the clearance between the spoilers and the wing surfaces

 (e)  
An adjustment of the seals

 (f)  
An adjustment of the clearance between the spoiler and the flaps.

 TASK 27-61-02-004-001
 2.  Outboard Flight Spoiler Removal (Fig. 401)_______________________________
 A.  Special Tools and Equipment
　
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