747-400 AMM 飞机维护手册 飞行操纵 FLIGHT CONTROLS 7(82)

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6  BUSHING  ID  0.6870  0.6880  0.6920  1 0.0060  X 
BUSHING  OD  0.6850  0.6860  0.6810  X 
7  BEARING  ID  0.2495  0.2500  0.2545  0.0050  X 
BOLT  OD  0.2485  0.2495  0.2445  X 
8  BUSHING  ID  0.2495  0.2505  0.2454  0.0050  X 
BOLT  OD  0.2485  0.2495  0.2445  X 
9  BUSHING  ID  0.2495  0.2505  0.2545  0.0050  X 
BOLT  OD  0.2485  0.2495  0.2445  X 
10  BUSHING  ID  0.2495  0.2510  0.2545  1 0.0050  X 
BOLT  OD  0.2485  0.2495  0.2445  X 

PERMITTED TOTAL MAXIMUM CLEARANCE IN THIS JOINT 0.008 INCH.
Krueger Flaps Wear Limits
Figure 601 (Sheet 4)

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747-400
MAINTENANCE MANUAL

INDEX NO.  PART NAME  DIM.  DESIGN LIMITS  WEAR LIMITS  REPLACE PART WORN  REPAIR WORN PART  REPAIR INSTR 
DIAMETER  PER-WEAR DIM. MITTED  MAX CLEAR-ANCE DIA 
MIN  MAX 
11  BUSHING  ID  0.4370  0.4380  0.4410  1 0.0050  X 
BUSHING  OD  0.4350  0.4360  0.4310  X 
2 12  BEARING  ID  0.3745  0.3750  0.3795  0.0050  X 
BOLT  OD  0.3735  0.3745  0.3695  X 
3 12  BEARING  ID  0.2495  0.2500  0.2545  X 
BOLT  OD  0.2485  0.2495  0.2445  X 
2 13  BUSHING  ID  0.3745  0.3755  0.3795  0.0050  X 
BOLT  OD  0.3735  0.3745  0.3695  X 
3 13  BUSHING  ID  0.2495  0.2505  0.2545  0.0050  X 
BOLT  OD  0.2485  0.2495  0.2445  X 
14  BEARING  ID  0.2495  0.2505  0.2545  X 
BOLT  OD  0.2485  0.2495  0.2445  X 
15  BUSHING  ID  0.2495  0.2505  0.2545  X 
BOLT  OD  0.2485  0.2495  0.2445  X 
16  BEARING  ID  0.2495  0.2500  0.2545  0.0050  X 
BOLT  OD  0.2485  0.2495  0.2445  X 

PERMITTED TOTAL MAXIMUM CLEARANCE IN JOINT 0.008 INCH. FLAPS NO. 11 AND 16 FLAPS NO. 12,13,14,15
Krueger Flaps Wear Limits
Figure 601 (Sheet 5)

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747-400 MAINTENANCE MANUAL
 VARIABLE CAMBER FLAPS - 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 the variable camber flaps in the leading edge flap system. The procedure has these parts:
 (1)  
The installation of the safety locks

 (2)  
The removal of the folding nose

 (3)  
The removal of the variable camber flap

 (4)  
The installation of the linkage on the variable camber flap

 (5)  
The installation of the folding nose

 (6)  
The installation of the variable camber flap.

 B.  
The eleven outboard and midwing flaps in each wing are the variable camber flaps. The area of each flap is increased by a folding nose.

 C.  
The removal and installation procedure is the same for all the variable camber flaps.

 D.  
In this procedure the pivot points of the flap linkage are identified by the letters shown in Fig. 401. Each link is identified by the letter of its pivot points.
　
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