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R (27) Put the forward angle (51) in position on the forward sub-spar (49). Install the rivets (48) (Ref. ASRM 514211).
R (28) Put the new plate nuts (130) and the new spacers (131) in position on the new forward angle (47) (Ref. ASRM 574118).
R (29) Install the rivets (132) (Ref. ASRM 514211).
(30) Apply SEALANTS (Material No. 09-001) to the mating faces of the forward angle (47) and the forward sub-spar (49).
R (31) Put the forward angle (47) in position on the forward sub-spar (49). Install the rivets (46) (Ref. ASRM 514211).
R (32) Put the new plate nuts (130) and the new spacers (131) in position on the new forward angle (65) (Ref. ASRM 574118).
R (33) Install the rivets (132) (Ref. ASRM 514211).
(34) Apply SEALANTS (Material No. 09-001) to the mating faces of the forward angle (65) and the forward sub-spar (49).
R (35) Put the forward angle (65) in position on the forward sub-spar (49). Install the rivets (60) (Ref. ASRM 514211).
(36) Apply SEALANTS (Material No. 09-001) to the mating faces of the landing (40) and the aircraft structure.
(37) Put the landing (40) in position.
R (38) Install the bolts (42) and the nuts (41) (Ref. ASRM 514211).
(39) Apply SEALANTS (Material No. 09-001) to the mating faces of the landing (44) and the aircraft structure.
(40) Put the landing (44) in position.
R (41) Install the bolts (45) and the nuts (43) (Ref. ASRM 514211).
(42) Apply SEALANTS (Material No. 09-001) to the mating faces of the landing (54) and the aircraft structure.
(43) Put the landing (54) in position.
R (44) Install the bolts (56) and the nuts (55) (Ref. ASRM 514211).
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(45) Apply SEALANTS (Material No. 09-001) to the mating faces of the landing (58) and the aircraft structure.
(46)
Put the landing (58) in position. R (47) Install the bolts (59) and the nuts (57) (Ref. ASRM 514211).
(48) Apply SEALANTS (Material No. 09-001) to the mating faces of the landing (62) and the aircraft structure.
(49)
Put the landing (62) in position. R (50) Install the bolts (63) and the nuts (61) (Ref. ASRM 514211).
(51) Examine the seals (140) around the pressure-relief panel (50) for damage and correct condition. Replace damaged seals as follows:
(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.).
(52)
Make sure that the work area is clean and clear of tool(s) and other items.
(53)
Put the pressure-relief panel (50) in position and install the bolts
(52) and (64).
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(54)
Measure the into/out of wind step tolerances of the pressure-relief panel (50) across the line of flight. These must be as follows:
(a)
For the panel leading edge:
-
maximum 0.6 mm (0.0236 in.) above wing surface (into wind)
-
maximum 1.2 mm (0.0472 in.) below wing surface (out of wind).
(b)
For the panel trailing edge:
- 中国航空网 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：A320飞机维护手册 AMM WINGS 机翼3(9)
