(39)
Put the pressure-relief panel (9) in position and install the bolts (10).
(40)
Put the pressure-relief panel (30) in position and install the bolts (28).
(41)
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). (Ref. Fig. 804/TASK 57-41-37-991-016)
(42)
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).
(43)
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).
R 1EFF : 001-049, 051-099, 101-105, 151-156, 1 57-41-37Page 836 1201-208, 1May 01/05 1 1 1CES 1
(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).
(44)
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.).
(45)
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.).
(46)
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 (that are parallel to the panel leading edges), the gap must be between 0.5 mm (0.0196 in.) and 5.5 mm (0.2165 in.)
-
the wing-skin and the edges of the panel cut-outs (that are not parallel to the panel leading edges), the gap 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 57-41-37-350-052-A
R A. Repair of the Leading Edge Pressure-Relief Panel 521CB(621CB) After it R 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 (10).
(2)
Carefully remove the pressure-relief panel 521AB(621AB) (9).
(3)
Remove the bolts (28).
(4)
Carefully remove the pressure-relief panel 521CB(621CB) (30).
(5)
When you remove the pressure-relief panel (30), a part of the landings (20) and (22) will fall. Make a note of the related position of these landings and keep them for later assembly.
NOTE : The two parts of the landing (25) are connected by lanyards.
____
(6)
Remove the nuts (21) and the bolts (35) (Ref. SRM 514211).
(7)
Remove the part of the landing (20) that is attached to the aircraft structure.
(8)
Remove the nuts (26) and the bolts (27) (Ref. SRM 514211).
(9)
Remove the landing (25).
(10)
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