-to the mating area of the scuff plates on the fuselage skin and - on the rough area of the scuff plates.
(8)
Put the scuff plates (3), (5) and (9) in position on the fuselage skin.
(9)
Install the screws (2), (8) and (1) with SEALANTS (Material No. 09-016), the washers (7) and (6) and the nuts (4).
(10)
Tighten the nuts (4) and the screws (1), (2) and (8).
(11)
Remove unwanted sealant around the scuff plates (3), (5) and (9).
(12)
Apply SEALANTS (Material No. 09-030) around and approximately 30 mm (1.1811 in.) from the edges of the scuff plates (3), (5) and (9).
(13)
Cover the scuff plates (3), (5) and (9) with a sheet of porous material.
(14)
Attach the porous material with BONDING AND ADHESIVE COMPOUNDS (Material No. 08-065) to the scuff plates (3), (5) and (9).
(15)
Connect the vacuum valve to the SPECIAL MATERIALS (Material No. 05-068).
(16)
Cover the scuff plates (3), (5) and (9) and SEALANTS (Material No. 09-030) with SPECIAL MATERIALS (Material No. 05-068). You must make an overlap of 30 mm (1.2 in.) from the edge of SEALANTS (Material No. 09-030).
(17)
Connect the vacuum pump to the vacuum valve.
(18)
Operate the vacuum pump to extract the air from the scuff plates (3),
(5) and (9).
Refer to the temperature given in the table: -------------------------------------------------------------------------------TEMPERATURE TIME -------------------------------------------------------------------------------
18 deg.C (64.40 deg.F) for 48 hours 20 deg.C (68.00 deg.F) for 30 hours 23 deg.C (73.40 deg.F) for 24 hours
(19)
Disconnect the vacuum pump.
(20)
Remove the SPECIAL MATERIALS (Material No. 05-068).
(21)
Remove the vacuum valve from the SPECIAL MATERIALS (Material No. 05-068), the porous material, and SEALANTS (Material No. 09-030).
EFF : 301-399, 53-25-41Page 407
Nov 01/04
R
CES
Scuff Plates - Installation Procedure
Figure 402/TASK 53-25-41-991-002- 12 (SHEET 1)
CES
Scuff Plates - Installation Procedure
Figure 402/TASK 53-25-41-991-002- 22 (SHEET 2)
CES
(22)
Apply SEALANTS (Material No. 09-016) on the external joints of the scuff plates (3), (5) and (9) and around the scuff plates.
(23)
Remove unwanted sealant with CLEANING AGENTS (Material No. 11-003) AND MISCELLANEOUS (Material No. 19-003).
5. Close-up
________ Subtask 53-25-41-942-050
A. Close Access
(1)
Make sure that the work area is clean and clear of tool(s) and other items.
(2)
Close the applicable emergency exit (Ref. TASK 52-22-00-410-002).
(3)
Remove the access platform(s).
EFF : 301-399, 53-25-41Page 410
Nov 01/04
R
CES MISCELLANEOUS (EG : DRAINS) - DESCRIPTION AND OPERATION
_______________________________________________________
1. General
_______
Drains are installed in the forward fuselage structure of the aircraft at or
near to the lowest points in an area. The drains let water and condensation
drain out so that they do not cause corrosion.
2. Description
___________
**ON A/C 001-049, 051-099, 101-149, 201-299, 301-399,
(Ref. Fig. 001)
R **ON A/C 151-199, 401-499,
(Ref. Fig. 001A)
**ON A/C ALL
Drain valves are installed in the forward fuselage shell. When the cabin pressurizes, the valves, preset to operate when cabin pressurization reaches 2 psi (0.1378 bar) , close to prevent loss of cabin pressure. As the cabin pressure decreases below the preset value (normally after the aircraft has landed), the valves open (under spring tension) to allow any water that has collected to drain away. You can remove the drain valves, for inspection or replacement, with an allen key from outside the aircraft. In other structural components (doors, door frames, stringers, brackets and fittings) holes are drilled at the lowest points to make sure that water and condensation drain to the drain valves.
EFF : ALL
53-29-00Page 1
Forward Fuselage - Drains Figure 001
R EFF : 001-049, 051-099, 101-149, 201-299, 301-399, 53-29-00 Page 2 May 01/05
CES
Forward Fuselage - Drains Figure 001A
R EFF : 151-199, 401-499, 53-29-00 Page 3 Aug 01/05
CES
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