(25)
Install the rivets (132) (Ref. SRM 514211).
R 1EFF : 106-149, 157-199, 209-299, 301-399, 1 57-41-37Page 875 1401-499, 1Aug 01/05 1 1 1CES 1
(26)
Apply SEALANTS (Material No. 09-001) to the mating faces of the forward angle (86) and the forward sub-spar (81).
(27)
Put the forward angle (86) in position on the forward sub-spar (81). Install the rivets (83) (Ref. SRM 514211).
(28)
Apply SEALANTS (Material No. 09-001) to the mating faces of the landing (71) and the aircraft structure.
(29)
Put the landing (71) in position.
(30)
Install the bolts (85) and the nuts (72) (Ref. SRM 514211).
(31)
Apply SEALANTS (Material No. 09-001) to the mating faces of the landing (73) and the aircraft structure.
(32)
Put the landing (73) in position.
(33)
Install the bolts (74) and (84) (Ref. SRM 514211).
(34)
Apply SEALANTS (Material No. 09-001) to the mating faces of the landing (77) and the aircraft structure.
(35)
Put the landing (77) in position.
(36)
Install the bolts (75) and the nuts (76) (Ref. SRM 514211).
(37)
Apply SEALANTS (Material No. 09-001) to the mating faces of the landing (88) and the aircraft structure.
(38)
Put the landing (88) in position.
(39)
Install the bolts (87) and the nuts (70) (Ref. SRM 514211).
(40)
Examine the seals (140) around the pressure-relief panel (79) 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).
(c)
Cut to length a new seal (140).
(d)
Put the new seal (140) in position on the panel.
R 1EFF : 106-149, 157-199, 209-299, 301-399, 1 57-41-37Page 876 1401-499, 1Aug 01/05 1 1 1CES 1
(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.).
(41)
Make sure that the work area is clean and clear of tool(s) and other items.
(42)
Apply release agent, SPECIAL MATERIALS (Material No. 05-064) to the trailing edge of the pressure-relief panel (79).
(43)
Put the pressure-relief panel (79) in position and install the bolts (80).
(44)
Measure the into/out of wind step tolerances of the pressure-relief panel (79) 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:
-
maximum 0.6 mm (0.0236 in.) below wing surface (into wind)
-
maximum 2.0 mm (0.0787 in.) above wing surface (out of wind).
R **ON A/C 106-149, 157-199, 209-299, 401-499,
(Ref. Fig. 804/TASK 57-41-37-991-016)
**ON A/C 301-399,
(Ref. Fig. 804A/TASK 57-41-37-991-016-A)
R 1EFF : 106-149, 157-199, 209-299, 301-399, 1 57-41-37Page 877 1401-499, 1Aug 01/05 1 1 1CES 1
R **ON A/C 106-149, 157-199, 209-299, 301-399, 401-499,
(45)
Measure the step tolerances of the pressure-relief panel ends across the line of flight. These must be as follows:
(a) For the panel ends:
-
maximum 2.0 mm (0.0787 in.) above or below the adjacent panel end (DIM X)
-
maximum 2.0 mm (0.0787 in.) above or below the adjacent wing surface (DIM Y).
(46)
If an into/out of wind step or an end step is not in tolerance, continue as follows:
(a)
Calculate the necessary thickness of the spacer (123) required to make the step correct.
(b)
Get the correct thickness of spacer (123) (Ref. SRM 574126).
(c)
Remove the bolts (80) and the pressure-relief panel (79).
(d)
Put the spacer (123) in position on the applicable landing.
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(17)
