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122VU ELEC/GCU/2 2XU2 T27 122VU ELEC/GCU/1 2XU1 T26 122VU ANTI ICE/WINDOWS/R 4DG2 W14 122VU ANTI ICE/WINDOWS/L 4DG1 X14 122VU ANTI ICE/PROBES/PHC/3 2DA3 Y16 122VU ANTI ICE/PROBES/2/TAT 1DA2 Y15 122VU ANTI ICE/PROBES/2/PITOT 3DA2 Y14 122VU ANTI ICE/PROBES/2/AOA 4DA2 Y13 122VU ANTI ICE/PROBES/2/PHC 2DA2 Y12 122VU ANTI ICE/PROBES/2/STATIC 5DA2 Y11 122VU ANTI ICE/PROBES/3/PITOT 3DA3 Z16 122VU ANTI ICE/PROBES/3/AOA 4DA3 Z15 122VU ANTI ICE/PROBES/3/STATIC 5DA3 Z14 122VU ANTI ICE/PROBES/1/STATIC 5DA1 Z13 122VU ANTI ICE/PROBES/1/TAT 1DA1 Z12
R **ON A/C 001-049, 051-052, 054-056, 058-059, 061-099, 101-101, 103-149,
R 151-199, 201-299, 301-399, 401-499, Post SB 30-1037 For A/C 001-049,051-052,054-056,
122VU ANTI ICE/RAIN/RPLNT/F/O 1DB2 W11
**ON A/C ALL
Subtask 71-52-43-861-055
D. Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002).
Subtask 71-52-43-869-067
E. Do the EIS start procedure (for the upper and lower display units of the ECAM system) (Ref. TASK 31-60-00-860-001).
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E E Aug 01/05 E E ECES E Subtask 71-52-43-869-068
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F. Aircraft Maintenance Configuration
(1) On the BLEED page of the lower display unit of the ECAM system, make sure that:
- the BLEED PRESSURE REGULATOR VALVE is closed
- the HIGH PRESSURE REGULATOR VALVE is closed.
5. Close-up
________ Subtask 71-52-43-869-069
A. Do the EIS stop procedure (Ref. TASK 31-60-00-860-002). Subtask 71-52-43-862-054
B. De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002).
Subtask 71-52-43-410-058
C. Close Access
(1) Make sure that the work area is clean and clear of tool(s) and other items.
(2) Close the thrust reverser doors (Ref. TASK 78-36-00-410-040). FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
(3) Remove the access platform(s). Subtask 71-52-43-440-054
D. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041).
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E. Close Access
(1) Close the fan cowl doors (Ref. TASK 71-13-00-410-040): FOR 1000EM1 437AL, 438AR FOR 1000EM2 447AL, 448AR
(2) Remove the warning notice(s).
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E E May 01/05 E E ECES E POWER PLANT DRAINS - DESCRIPTION AND OPERATION
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1. General
_______
(Ref. Fig. 001, 002)
A. Drain and Vent System The drain and vent system consists of lines collecting and carrying waste fluids and vapor overboard from the engine and nacelle accessories. Drains are provided to carry fluids from any point where lines and accessories may leak and where fluids may accumulate in a cavity. In addition, some drain lines serve as vents to carry air and vapor from the engine and accessory cavities.
2. System Description
__________________ (Ref. Fig. 001, 002) The drain and vent system is divided into two parts; one which retains drained fluids until expelled during flight (reservoir), and one which discharges fluid directly overboard through the drain mast located in the fan compartment. The reservoir module is mounted on the transfer gearbox. The manifold module is also attached to the transfer gearbox and supports the drain mast, which protrudes through the fan cowl doors into the airstream.
Each accessory pad seal has a separate drain cavity in the reservoir module in which leakage is contained. Manual drain valves in the bottom of these reservoirs aid in tracing the source of excess leakage. Each reservoir is identified with the accessory seal drain to which it is connected. These individual reservoirs overflow into the fuel holding tank or an hydraulic fluid/oil holding tank. This overflow is contained in the holding tank until the aircraft reaches an airspeed of 200 Knots. A pressure valve, which is part of the manifold module assembly, then admits ram air to pressurize the holding tanks and discharge any accumulated fluid overboard through the drain mast.
The fluids that are discharged directly overboard are from:
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