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时间:2011-04-11 08:58来源:蓝天飞行翻译 作者:航空
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Variable Camber Flaps Clearance and Mismatch Requirements
Figure 402 (Sheet 2)

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.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


E-E
RETAINER

Variable Camber Flaps Gap and Mismatch Requirements
Figure 402 (Sheet 3)

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 ALL  ú ú 01 Page 416 ú Feb 15/99
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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747-400
MAINTENANCE MANUAL

 (3)  
AMM 29-11-00/201, Main Hydraulic Supply System

 (4)  
AMM 36-00-00/201, Pneumatic System

 (5)  
AMM 51-24-03/701, Conductive Coating System for Exterior Fiberglass

 (6)  
SSM 27-81-01, SSM 27-81-02, SSM 27-81-03, SSM 27-81-04,
 SSM 27-81-05, SSM 27-81-06


 (7)  
WDM 27-51-21, WDM 27-51-22, WDM 27-81-11, WDM 27-81-12,
 WDM 27-81-21, WDM 27-81-22, WDM 27-81-31, WDM 27-81-32,
 WDM 27-81-41, WDM 27-81-42, WDM 27-81-81, WDM 27-81-82


 D.
Access

 (1)  
Location Zone
 522 Variable Camber Flap, LH
 523 Variable Camber Flap, LH
 524 Variable Camber Flap, LH
 525 Variable Camber Flap, LH
 526 Variable Camber Flap, LH
 532 Variable Camber Flap, LH
 533 Variable Camber Flap, LH
 534 Variable Camber Flap, LH
 535 Variable Camber Flap, LH
 536 Variable Camber Flap, LH
 537 Variable Camber Flap, LH
 622 Variable Camber Flap, RH
 623 Variable Camber Flap, RH
 624 Variable Camber Flap, RH
 625 Variable Camber Flap, RH
 626 Variable Camber Flap, RH
 632 Variable Camber Flap, RH
 633 Variable Camber Flap, RH
 634 Variable Camber Flap, RH
 635 Variable Camber Flap, RH
 636 Variable Camber Flap, RH
 637 Variable Camber Flap, RH


 E.
Install the Variable Camber Flap


 S 224-011
 (1)  Do this task if you install used bolts or bushings: "Variable Camber Flap Inspection/Check" (AMM 27-81-02/601).
 S 434-012
 CAUTION:  AT PIVOT POINTS B, E, H AND N, MAKE SURE TO KEEP THE INNER AND
_______ OUTER SLEEVES OF THE BUSHING TOGETHER AS AN ASSEMBLY. THIS WILL PREVENT AN INCORRECT INSTALLATION OF THE BUSHING.
 (2)  
Install the linkage on the variable camber flap (Fig. 401).

 (a)  
Install the linkage at each pivot point N: 1) Install the bushing (42) in the flap fitting. 2) Align link MN and link EHN with point N. 3) Install the bolt (40), washer (41) and nut (43).


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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
 4)  Tighten the nuts to 65-90 pound-inches (for LE flap No. 1E-5 and 22-26E) or 130-180 pound-inches (for LE flap No. 6-10 and 17-21).
 (b)  
Install the linkage at each pivot point M: 1) Install two bushings (35). 2) Align two links KM with point M. 3) Install each link with the bolt (32), washers (33) and nut

 (34). 4) Tighten the nuts to 130-180 pound-inches.

 (c)  
Install the linkage at each pivot point L: 1) Install two bushings (50). 2) Align two links JL with point L. 3) Install each link with the bolt (48), washers (49) and nut

 (51). 4) Tighten the nuts to 65-90 pound-inches.

 (d)  
Install the linkage at each pivot point F: 1) Install two bushings (4). 2) Align two links FEBC with point F. 3) Install each link with the bolt (2), washers (3) and nut


 (5). 4) Tighten the nuts to 65-90 pound-inches.
 
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