(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.

 (39)
 Apply release agent, SPECIAL MATERIALS (Material No. 05-064) to the trailing edge of the pressure-relief panel (9).

R 1EFF : 106-149, 157-199, 209-299, 301-399, 1 57-41-37Page 840 1401-499, 1Aug 01/05 1 1 1CES 1

 (40)
 Put the pressure-relief panel (9) in position and install the bolts (10).

 (41)
 Apply release agent, SPECIAL MATERIALS (Material No. 05-064) to the trailing edge of the pressure-relief panel (30).

 (42)
 Put the pressure-relief panel (30) in position and install the bolts (28).

 (43)
 Measure the into/out of wind step tolerances of the pressure-relief panels (9) and (30) 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 **ON A/C 106-149, 157-199, 209-299, 301-399, 401-499,
 (44) 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).

R 1EFF : 106-149, 157-199, 209-299, 301-399, 1 57-41-37Page 841 1401-499, 1Aug 01/05 1 1 1CES 1

 (45)
 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 applicable bolts (10) and/or (28) and the applicable pressure-relief panel (9) and/or (30).

 (d)
 Put the spacer (123) in position on the applicable landing.

 (e)
 Drill the applicable landing and the spacer (123) to a diameter between 3.27 mm (0.1287 in.) and 3.35 mm (0.1318 in.) (Ref. SRM 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 install the rivets (124) (Ref. SRM 514211).

 (h)
 Install the applicable pressure-relief panel (9) and/or (30) with the bolts (10) and/or (28).

 (i)
 Do again step (41) and step (42).

 (46)
 Measure the gap between the D-nose skin and the leading edges of the pressure-relief panels (9) and (30). The gap must be between 0.5 mm (0.0196 in.) and 4.5 mm (0.1771 in.).

 (47)
 Measure the gap at the inboard and outboard edges of the pressure-relief panels (9) and (30). The gap must be between 0.5 mm (0.0196 in.) and 5.5 mm (0.2165 in.).

 (48)
 At the trailing edges of the pressure-relief panels (9) and (30), measure:

 -the gap between the wing-skin and the edges of the panels. The gap must not be less than 0.5 mm (0.0196 in.).
R 1EFF : 106-149, 157-199, 209-299, 301-399, 1 57-41-37Page 842 1401-499, 1Aug 01/05 1 1 1CES 1 Subtask 57-41-37-390-051

 B. Seal Installation
 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.
 (Ref. Fig. 805/TASK 57-41-37-991-017)
 NOTE : Seal only the gap between the trailing edge of the pressure-relief
____
 panels and the wing skin.

 (1)
 Degrease the area to be filled fully with a MISCELLANEOUS (Material No. 19-003), made moist with CLEANING AGENTS (Material No. 11-026).

 (2)
 Apply masking tape around the edges of the gap to be filled.
　
中國航空網 m.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(6)