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S 414-044-N00
(2) Close the right core cowl panel (AMM 71-11-06/201).
S 414-045-N00
(3) Close the right fan cowl panel (AMM 71-11-04/201).
S 444-046-N00
(4) Do the activation procedure for the thrust reversers (AMM 78-31-00/201).
S 864-028-N00
(5) For the applicable engine, remove the DO-NOT-CLOSE tag and close this circuit breaker as follows:
(a) P6 Main Power Distribution Panel 1) 6L10 FUEL CONT VALVE ENG 1 2) 6L11 FUEL CONT VALVE ENG 2 3) 6L12 FUEL CONT VALVE ENG 3 4) 6L13 FUEL CONT VALVE ENG 4
S 864-029-N00
(6) For the applicable engine, remove these DO-NOT-CLOSE tags and close these circuit breakers as follows:
(a) P6 Main Power Distribution Panel 1) 6F1 IGN 1 ENG 1 2) 6F2 IGN 1 ENG 2 3) 6F3 IGN 1 ENG 3 4) 6F4 IGN 1 ENG 4 5) 6K19 IGN 2 ENG 1 6) 6K20 IGN 2 ENG 2 7) 6K21 IGN 2 ENG 3 8) 6K22 IGN 2 ENG 4 9) 6G19 STBY IGN ENG 1 10) 6G20 STBY IGN ENG 2
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES/MAINTENANCE MANUAL ////////////////////////
11) 6G21 STBY IGN ENG 3 12) 6G22 STBY IGN ENG 4
(7) S 864-030-N00Remove the DO-NOT-OPERATE tag from the FUEL CONTROL switch.
(8) S 714-031-N00Do the test of the fuel flow transmitter that is shown in the Power Plant Test Reference Table (AMM 71-00-00/501). (a) Monitor the fuel flow indication.
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FUEL FILTER BYPASS WARNING SYSTEM - DESCRIPTION AND OPERATION
_____________________________________________________________
1. General
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A. The fuel filter bypass warning system provides a status message, in the flight compartment, in the event of an impending fuel filter bypass.
B. The fuel filter bypass warning system consists of the fuel filter differential pressure switch and uses the auxiliary EICAS status page for display.
C. The fuel filter differential pressure switch closes to provide a signal to the EFIS/EICAS interface units (EIU's) when the fuel filter inlet and outlet pressure differential increases to a predetermined value.
2. Fuel Filter Differential Pressure Switch (Fig. 1)
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A. The fuel filter differential pressure switch is mounted on top of the fuel filter housing on the fuel pump. The fuel pump is mounted on the forward face of the main gearbox at the 5 o'clock position.
B. The fuel filter differential pressure switch is a snap-action, pressure sensitive switch. The switch consists of a diaphragm, exposed to filter inlet pressure on one side and filter outlet pressure on the other side, a pressure plate, negative rate disc spring, wobble shaft, a single pole double throw electrical switch, and housing.
C. The switch closes at an increasing differential pressure of 5.0-6.0 psid (34.5-41.4 kPad) and opens at a decreasing differential pressure of 3.0-4.0 psid (20.7-27.6 kPad).
3. Fuel Filter Bypass Warning Indication
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A. The EIU's interpret the signal from the fuel filter differential pressure switch and provide a status message which can be called up on the auxiliary EICAS status page.
B. In the event of an impending fuel filter bypass, with the engine(s) operating, ENG (1, 2, 3, or 4) FUEL FILT will be displayed on the EICAS status page.
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本文链接地址：747-400 AMM 飞机维护手册 发动机燃油和控制 2(94)
