(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).
(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).
R 1EFF : 001-049, 051-099, 101-105, 151-156, 1 57-41-37Page 817 1201-208, 1May 01/05 1 1 1CES 1
R Leading Edge Pressure-Relief Panels - Seal Location Figure 806/TASK 57-41-37-991-014- 13 (SHEET 1)
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R Leading Edge Pressure-Relief Panels - Seal Location Figure 806/TASK 57-41-37-991-014- 23 (SHEET 2)
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R Leading Edge Pressure-Relief Panels - Seal Location Figure 806/TASK 57-41-37-991-014- 33 (SHEET 3)
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(i) Do again step (41) and step (42).
(44)
Measure the clearance between the D-nose skin and the leading edges of the pressure-relief panels (9) and (30). The clearance must be between 0.5 mm (0.0196 in.) and 4.5 mm (0.1771 in.).
(45)
Measure the clearance at the inboard and outboard edges of the pressure-relief panels (9) and (30). The clearance 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 (9) and (30), measure the clearance between:
-
the wing-skin and the edges of the panel (that are parallel to the panel leading edges), the clearance 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 leading edges), 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 57-41-37-350-051-A
A. Repair of the Leading Edge Pressure-Relief Panel 521AB(621AB) After it has Operated
(1)
Remove the bolts (10).
(2)
Carefully remove the pressure-relief panel 521AB(621AB) (9).
(3)
When you remove the pressure-relief panel (9) a part of the landings (1), (3) and (6) will fall. Make a note of the related position of these landings and keep them for later assembly.
(4)
Remove the bolts (28).
(5)
Carefully remove the pressure-relief panel 521CB(621CB) (30).
(6)
Remove the nuts (2) and the bolts (16) (Ref. SRM 514211).
(7)
Remove the part of the landing (1) that is attached to the aircraft structure.
(8)
Remove the nuts (5) and the bolts (7) (Ref. SRM 514211).
(9)
Remove the part of the landing (6) that is attached to the aircraft structure.
(10)
Remove the nuts (4) and the bolts (8) (Ref. SRM 514211).
(11)
Remove the part of the landing (3) that is attached to the aircraft structure.
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