-
maximum 2.0 mm (0.0787 in.) above wing surface (out of wind). (Ref. Fig. 804/TASK 57-41-37-991-016)
(55)
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).
(56)
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.
R (b) Get the correct thickness of spacer (123) (Ref. ASRM 574126).
(c)
Remove the bolts (52) and (64) and the pressure-relief panel (50).
(d)
Put the spacer (123) in position on the applicable landing.
(e)
Drill the applicable landing and the spacer (123) to a diameter R between 3.27 mm (0.1287 in.) and 3.35 mm (0.1318 in.) (Ref. ASRM R 514411).
(f) Remove the sharp edges from the applicable landing and the spacer (123).
(g)
Put the spacer (123) in position on the applicable landing and R install the rivets (124) (Ref. ASRM 514211).
(h) Install the pressure-relief panel (50) with the bolts (52) and (64).
R 1EFF : 001-049, 051-099, 101-105, 151-156, 1 57-41-37Page 855 1201-208, 1May 01/05 1 1 1CES 1 (i) Do again step (54) and step (55).
(57)
Measure the clearance between the D-nose skin and the leading edge of the pressure-relief panel (50). The clearance must be between 0.5 mm (0.0196 in.) and 4.5 mm (0.1771 in.).
(58)
Measure the clearance at the inboard and outboard edges of the pressure-relief panel (50). The clearance must be between 0.5 mm (0.0196 in.) and 5.5 mm (0.2165 in.).
(59)
At the trailing edge of the pressure-relief panel (50), measure the clearance between:
-
the wing-skin and the edge of the panel (that is parallel to the panel leading edge), the clearance must be between 0.5 mm (0.0196 in.) and 5.5 mm (0.2165 in.)
-
the wing-skin and the edge of the panel cut-outs (that are not parallel to the panel leading edge), the clearance must be between
0.5 mm (0.0196 in.) and 7.0 mm (0.2755 in.).
R **ON A/C 106-149, 157-199, 209-299, 301-399, 401-499,
Subtask 57-41-37-350-053-A
A. Repair of the Leading Edge Pressure-Relief Panel 521EB(621EB) After it has Operated
WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL
_______ MATERIALS ONLY WITH A GOOD SUPPLY OF AIR. OBEY THE MANUFACTURERS INSTRUCTIONS. PUT ON PROTECTIVE CLOTHING. DO NOT GET THEM IN YOUR MOUTH. DO NOT SMOKE. DO NOT BREATHE THE GAS. THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT. GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED.
(1)
Remove the bolts (52) and (64).
(2)
Carefully remove the pressure-relief panel 521EB(621EB) (50).
(3)
When you remove the pressure-relief panel (50), a part of the landings (44) and (58) will fall. Make a note of the related position of these landings and keep them for later assembly.
NOTE : The two parts of the landings (40), (54) and (62) are
____
connected by lanyards.
(4)
Remove the nuts (41) and the bolts (42) (Ref. ASRM 514211).
(5)
Remove the landing (40).
(6)
Remove the nuts (43) and the bolts (45) (Ref. ASRM 514211).
(7)
Remove the part of the landing (44) that is attached to the aircraft structure.
(8)
Remove the nuts (55) and the bolts (56) (Ref. ASRM 514211).
(9)
Remove the landing (54).
(10)
Remove the nuts (57) and the bolts (59) (Ref. ASRM 514211).
(11)
Remove the part of the landing (58) that is attached to the aircraft structure.
(12)
Remove the nuts (61) and the bolts (63) (Ref. ASRM 514211).
(13)
Remove the landing (62).
(14)
Remove and discard the rivets (48) (Ref. ASRM 514211).
(15)
Remove and discard the forward angle (51).
(16)
Remove and discard the rivets (46) (Ref. ASRM 514211).
(17)
Remove and discard the forward angle (47).
(18)
Remove and discard the rivets (60) (Ref. ASRM 514211).
(19)
Remove and discard the forward angle (65).
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：A320飛機維護手冊 AMM WINGS 機翼3(10)
