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A320飞机维护手册 AMM WINGS 机翼3(3)

时间:2011-03-27 12:43来源:蓝天飞行翻译 作者:航空 点击:
  

 (14)
 Remove and discard the rivets (11) (Ref. SRM 514211).

 (15)
 Remove and discard the rivets (34) (Ref. SRM 514211).

 (16)
 Remove and discard the forward angle (33). NOTE : The forward angle (33) and the forward angle (12) is the same


____ item. The forward angle (33) or (12) attaches the two pressure relief panels 521CB(621CB) and 521AB(621AB) to the aircraft structure.
R 1EFF : 001-049, 051-099, 101-105, 151-156, 1 57-41-37Page 833 1201-208, 1May 01/05 1 1 1CES 1


 (17)
 Clean these items with a lint-free cloth made moist with CLEANING AGENTS (Material No. 11-026):

 -
the forward sub-spar (13) and (32)

 -
the landings (20), (22) and (25)

 -
the landing (20), (22) and (25) interfaces and the adjacent areas.

 

 (18)
 Examine the two parts of the landings (20), (22) and (25) for damage, discard those that are damaged.

 (19)
 Assemble the landings (20), (22) and (25) as follows:

 (a)
 Put the two parts of the applicable landing together.

 (b)
 Install the spacers (122) and the washers (121).

 (c)
 Install the shear rivets (120) (Ref. SRM 514211).

 (d)
 Make sure that the two parts of the landings can move on the spacers (122).

 

 (20)
 Examine the pressure-relief panels (9) and (30) for damage. Discard those that are damaged.

 (21)
 Put the new plate nuts (130) and the new spacers (131) in position on the new forward angle (31) (Ref. SRM 574118).

 (22)
 Install the rivets (132) (Ref. SRM 514211).

 (23)
 Apply SEALANTS (Material No. 09-001) to the mating faces of the forward angle (31) and the forward sub-spar (32).

 (24)
 Put the forward angle (31) in position on the forward sub-spar (32). Install the rivets (29) (Ref. SRM 514211).

 (25)
 Put the new plate nuts (130) and the new spacers (131) in position on the new forward angle (33) (Ref. SRM 574118).


 NOTE : The forward angle (33) and the forward angle (12) is the same
____ item. The forward angle (33) or (12) attaches the two pressure relief panels 521CB(621CB) and 521AB(621AB) to the aircraft structure.
 (26)
 Install the rivets (132) (Ref. SRM 514211).

 (27)
 Apply SEALANTS (Material No. 09-001) to the mating faces of the forward angle (33) and the forward sub-spar (13) and (32).


R 1EFF : 001-049, 051-099, 101-105, 151-156, 1 57-41-37Page 834 1201-208, 1May 01/05 1 1 1CES 1


 (28)
 Put the forward angle (33) in position on the forward sub-spar (13) and (32). Install the rivets (11) and (34) (Ref. SRM 514211).

 (29)
 Apply SEALANTS (Material No. 09-001) to the mating faces of the landing (20) and the aircraft structure.

 (30)
 Put the landing (20) in position.

 (31)
 Install the bolts (35) and the nuts (21) (Ref. SRM 514211).

 (32)
 Apply SEALANTS (Material No. 09-001) to the mating faces of the landing (22) and the aircraft structure.

 (33)
 Put the landing (22) in position and install the bolts (24) and the nuts (23) (Ref. SRM 514211).

 (34)
 Apply SEALANTS (Material No. 09-001) to the mating faces of the landing (25) and the aircraft structure.

 (35)
 Put the landing (25) in position.

 (36)
 Install the bolts (27) and the nuts (26) (Ref. SRM 514211).

 (37)
 Examine the seals (140) around the pressure-relief panels (9) and

 (30)
 for damage and correct condition. Replace damaged seals as
 follows:
 (Ref. Fig. 806/TASK 57-41-37-991-014)


 (a)
 Remove the damaged length of seal (140) with a non-metallic scraper.

 (b)
 Clean the applicable area of the panel with a lint-free cloth made moist with CLEANING AGENTS (Material No. 11-026).

 


R (c) Cut to length a new seal (140).
 (d)
 Put the new seal (140) in position on the panel.

 (e)
 Cut the corners of the new seal (140) to make a continuous surface at the corner joints.

 (f)
 Remove the protective back from the new seal (140) and install the seal on the panel.

 (g)
 Use a suitable cutting tool to remove the seal from the holes X. The diameter of the hole X is between 5.75 mm (0.2263 in.) and


 6.25 mm (0.2460 in.).


 (38)
 Make sure that the work area is clean and clear of tool(s) and other items.
 
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