A320飞机维护手册 AMM FUSELAGE 机身3(95)_航空信息_民用航空_通用航空

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CES

(23)
Apply SEALANTS (Material No. 09-013) around the edges of the scuff plates, to the anchor nuts (5) and (6) and around the door sill. Let the sealant dry (Ref. TASK 51-76-11-300-001).

(24)
Apply STRUCTURE PAINTS (Material No. 16-003) to the sealant around the door sill, around the edges of the scuff plates and to the anchor nuts (5) and (6) (Ref. TASK 51-75-12-300-003).

5. Close-up
________ Subtask 53-45-15-410-051
A. Close Access
(1)
Make sure that the work area is clean and clear of tool(s) and other items.

(2)
Install the floor panel 162JF at the entrance to the BULK cargo-compartment (Ref. TASK 53-42-17-400-001).

(3)
Close the BULK cargo-compartment door (Ref. TASK 52-30-00-860-008).

(4)
Remove the access platform(s).

(5)
Remove the ground support and maintenance equipment, the special and standard tools and all other items.

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CES FITTINGS - DESCRIPTION AND OPERATION

____________________________________
1. General_______
Fittings are made of forged aluminum alloy, or aluminum alloy sheet. They are riveted to the structure.
2. Component Location__________________ (Ref. Fig. 001)
3. Description___________ Fittings make it possible to connect components to the structure, such as the attachment for the AFT cargo-compartment door.
Fittings are also installed in the main structure to connect the main structures together. The fittings are installed with sealant to prevent corrosion.
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53-46-00Page 1

Fittings
Figure 001 (SHEET 1)
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CES

Fittings
Figure 001 (SHEET 2)
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CES

MISCELLANEOUS (EG : DRAINS) - DESCRIPTION AND OPERATION
_______________________________________________________
1.
General

_______ Drains are installed in the rear 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.
Component Location

__________________ R (Ref. Fig. 001)
3. Description
___________ Drain valves are installed in the rear 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. Drain valves are also installed in the door structure of the aft cargo compartment. In other structures (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.
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53-49-00Page 1

Rear Fuselage Drains
Figure 001
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DRAINS - REAR FUSELAGE - REMOVAL/INSTALLATION
_____________________________________________
TASK 53-49-21-000-001 Removal of the Drain Valves
1. Reason for the Job
__________________
Self Explanatory
2. Job Set-up Information
______________________
A. Fixtures, Tools, Test and Support Equipment
-------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
No specific 1 ACCESS PLATFORM 2M (6 FT) No specific 1 SCRAPER - NON METALLIC
B. Consumable Materials
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
Material No. 11-004 USA MIL-T-81533
1.1.1TRICHLOROETHANE (METHYL CHLOROFORM)
(Ref. 20-31-00)
Material No. 19-003 USA AMS 3819 LINT-FREE COTTON CLOTH (Ref. 20-31-00)
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