R 29-10-00-864-001 Depressurize the Green Hydraulic System
R 29-10-00-864-002 Depressurize the Yellow Hydraulic System
R 29-10-00-864-003 Depressurize the Blue Hydraulic System
R 32-12-00-410-001 Close the Main Gear Doors after Access
R 53-35-13-991-011 Fig. 408
R 3. Job Set-up__________
R Subtask 53-35-13-860-055
R A. Aircraft Maintenance Configuration
R (1) Make sure that the aircraft is in the same configuration as for the
R removal task.
R (2) Depressurize the Green, Yellow and Blue hydraulic systems (Ref. TASK
R 29-10-00-864-001), (Ref. TASK 29-10-00-864-002) and (Ref. TASK 29-10-
R 00-864-003).
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Nov 01/04
4. Procedure_________
(Ref. Fig. 408/TASK 53-35-13-991-011)
Subtask 53-35-13-560-054
A. Preparation for Installation
(1) Clean the component interface and/or the adjacent area.
(2) Do an inspection of the component interface and/or the adjacent area.
Subtask 53-35-13-420-055
R B. Installation of the Louver Panel
R R R CAUTION : BE CAREFUL WHEN YOU INSTALL THE LOUVER PANEL. IF YOU INSTALL IT_______ INCORRECTLY, THE BELLY FAIRING WILL PRESSURIZE AND CAUSE DAMAGE TO THE STRUCTURE.
R
(1) Put the louver panel (4) in its correct installation position. Make sure that the openings of the vanes point to the rear of the aircraft.
(2) Install the screws (3), the washers (2) and the nuts (1).
5. Close-up________
Subtask 53-35-13-410-054
A. Close Access
(1) Make sure that the work area is clean and clear of tool(s) and other items.
(2) Remove the access platform(s).
(3) Close the MLG doors (Ref. TASK 32-12-00-410-001).
(4) Remove the ground support and maintenance equipment, the special and standard tools and all other items.
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53-35-13Page 451
FITTINGS - DESCRIPTION AND OPERATION
____________________________________
1.
General
_______ Fittings make possible the connection of structural parts directly to the fuselage, or to those components that are attached to the fuselage.
2.
Description
___________ The fittings are made of aluminum alloy. They are machined from forgings or sheet.
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53-36-00Page 1
MISCELLANEOUS (EG : DRAINS) - DESCRIPTION AND OPERATION
_______________________________________________________
1. General
_______
A. Drain Assemblies
(1) Small quantities of water collect in the cabin because of condensation. Drains are installed in the fuselage structure to let the water out and to give more protection to the structure from corrosion. The center fuselage drains are located at the lowest point of the cabin, below the cabin floor. They are installed in the rear diaphragm structure and any water is let out through the main gear bay. As the cabin is a pressurized area, the drains are sensitive to cabin pressure and close during normal cabin pressurization.
B. Overpressure Valves
(1) Although the belly fairing is not a pressurized structure, differential pressures can build up between the internal sections. Equal pressures in the sections is maintained by the overpressure valves, located at FR36, left and right, in the structure. The valves open, against spring tension, to release any overpressure build-up in the belly fairing FWD sections. When the valves open, they remain open until the pressure again equalizes between the FWD and AFT sections of the structure.
2.
Component Location
__________________
(Ref. Fig. 001)
3.
Description
___________ Fuselage Drains: The center fuselage drain assemblies have a rubber seal and an upper plate. The rubber seal is sensitive to cabin pressure and will move to close or open a water drain hole. The upper plate limits the movement of the rubber seal when it moves up. As the cabin pressurizes, the pressure sensitive rubber seal will move down to close the drain hole. When the hole is closed, loss of cabin pressure through the drain hole is prevented. When the cabin pressure decreases the rubber seal will move up to its usual position and open the drain hole. Any water that has collected will drain away through the main gear bay. Overpressure Valves:
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53-39-00Page 1
Center Fuselage Drains - Component Location
Figure 001
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