(39.82 and 44.24 lbf.in).
(3)
For the panel 521EB(621EB):
(a)
Hold the panel (5) in position. Install the four screws (6) and the screws (7).
(d)
Let the sealant go hard then carefully remove the applicable panel (Ref. TASK 57-41-37-000-004).
(e)
Apply talcum powder to the sealant mating surfaces and install the panel (refer to Para. 4B.).
(3)
Make sure that the work area is clean and clear of tool(s) and other items.
(b) TORQUE tighten the screws (6) and (7) to between 0.45 and 0.5 m.daN (39.82 and 44.24 lbf.in).
(4) For the panel 522AB(622AB):
(a) Hold the panel (8) in position. Install the five screws (9) and the screws (10).
(b) TORQUE tighten the screws (9) and (10) to between 0.45 and 0.5 m.daN (39.82 and 44.24 lbf.in).
(5) For the panel 522CB(622CB):
(a) Hold the panel (11) in position. Install the screw (12) and the screws (13).
(b) TORQUE tighten the screws (12) and (13) to between 0.45 and 0.5 m.daN (39.82 and 44.24 lbf.in).
**ON A/C ALL
Subtask 57-41-37-390-055
R B. Sealant
WARNING : OBEY THE MANUFACTURER'S INSTRUCTIONS WHEN YOU USE THE SPECIAL_______ MATERIAL. THIS MATERIAL IS DANGEROUS.
R R (1) Do an inspection of the sealant between the trailing edge of the panel and the forward edge of the wing skin.
(2) If there is damage to the sealant, do the steps that follow:
R (a) Use a non-metallic scraper and a MISCELLANEOUS (Material No. 19-003) made moist with CLEANING AGENTS (Material No. 11-026) to clean: - the trailing edge of the panel - the forward edge of the bottom wing skin.
R R (b) Apply SPECIAL MATERIALS (Material No. 05-013A) to the trailing edge of the panel.
R R (c) Apply SEALANTS (Material No. 09-005) to the interface between the trailing edge of the panel and the forward edge of the wing skin.
R **ON A/C 001-049, 051-099, 101-105, 151-156, 201-208,
Subtask 57-41-37-220-050
C. Dimensional Checks
(1)
Measure the into/out of wind step tolerances of the pressure-relief panels across the line of flight. These must be as follows:
(a)
For the panel leading edge:
-
maximum 0.3 mm (0.0118 in.) above wing surface (into wind)
-
maximum 0.6 mm (0.0236 in.) below wing surface (out of wind).
(b)
For the panel trailing edge:
-
maximum 0.3 mm (0.0118 in.) below wing surface (into wind)
-
maximum 1.0 mm (0.0393 in.) above wing surface (out of wind).
(2)
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).
(3)
Measure the clearance between the D-nose skin and the leading edges of the pressure-relief panels. The clearance must be between 0.5 mm (0.0196 in.) and 2.5 mm (0.0984 in.).
NOTE : A maximum of three clearances can be between 0.5 mm (0.0196
____
in.) and 3.5 mm (0.1377 in.).
(4)
Measure the clearance at the inboard and outboard edges of the pressure-relief panels. The clearance must be between 0.5 mm (0.0196 in.) and 3.5 mm (0.1377 in.).
(5)
Measure the clearance at the trailing edges of the pressure-relief panels between:
-
the wing-skin and the edges of the panels (that are parallel to the panel leading edges), the clearance must be between 0.5 mm (0.0196 in.) and 4.5 mm (0.1771 in.)
-
the wing-skin and the edges of the panel cut-outs (that are not parallel to the panel leading edges), the clearances must be between 0.5 mm (0.0196 in.) and 5.5 mm (0.2165 in.).
R **ON A/C 106-149, 157-199, 209-299, 301-399, 401-499,
Subtask 57-41-37-220-050-A
C. Dimensional Checks
(1)
Measure the into/out of wind step tolerances of the pressure-relief panels 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)
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2(133)
