(n)
Return tank No. 1 FWD boost pump switch to OFF, then return tank No. 1 AFT boost pump switch to OFF.
(o)
Check that respective LOW PRESSURE indicating light comes on as each switch returns to OFF and that MASTER CAUTION and FUEL annunciator lights come on as soon as two boost pumps for same tank are not operating.
(p)
Return tank No. 1 boost pump switches to ON position and repeat steps (l) thru (o) for tank No. 2 fuel boost pumps.
(q)
Return tank No. 2 boost pump switches to ON position and repeat steps (l) thru (o) for center tank fuel boost pumps using the center tank RIGHT and LEFT boost pump circuit breakers on P6 panel to control boost pumps.
(r)
Return all fuel boost pumps remaining ON to OFF position.
(3) Restore Airplane to Normal
(a)
Push engine fire switches on aft electronic panel P8 to open engine fuel shutoff valves.
(b)
Open fuel system circuit breakers on P6 panel: FWD BOOST PUMP TANK 1, FWD BOOST PUMP TANK 2, AFT BOOST PUMP TANK 1, AFT BOOST PUMP TANK 2, BOOST PUMP CTR TANK LEFT, BOOST PUMP CTR TANK RIGHT, ENG 1 SHUT-OFF VALVE, ENG 2 SHUT-OFF VALVE, and MANIF VALVE.
(c)
Open master DIM AND TEST circuit breaker on P6 panel.
(d)
Open INDICATOR LTS MASTER DIMMING BUS and master caution bus FUEL, ANNUNCIATOR NO.1 and BAT circuit breakers on P6 panel, if no longer required.
(e)
Remove external electrical power if no longer required.
527
May 01/03 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 28-22-0 Page 509
D. Fuel Boost Pump Removal Valve, Vent Valve, and Check Valve and Pressure Fueling Line Outlet Check Valve Test
(1)
General
(a) The boost pump removal, vent, and check valves and pressure fueling line outlet check valve are tested by opening the boost pump drain cock and checking for fuel leakage. All three valves will leak through the same drain cock making it difficult to isolate the valve that is malfunctioning. As the fuel boost pump check valve can be isolated to a degree it should be tested first. If the fuel boost pump check valve is eliminated as the source of leakage, the replacement of the boost pump removal valve and/or boost pump vent valve will be a matter of judgment. Fuel leakage from both center boost pump drain cocks indicates failure of pressure fueling line outlet check valve in center tank.
(2)
Prepare for Boost Pump Removal Valve, Vent Valve, and Check Valve and Pressure Fueling Line Check Valve Test
(a)
Connect external electrical power to airplane (Ref Chapter 24).
(b)
Gain access to AFT main and all center tank valves by removing fuel boost pump access panels No. 7201L, 7203L, 7401R, and 7403R (Ref 57-30-11, Removal/Installation).
(c)
Check that each fuel tank contains fuel to cover valves as shown in Table 1.
FUEL TANK BOOST PUMP VALVE MINIMUM FUEL QUANTITY-U.S. GAL.
No. 1, 2 No. 1, 2 No. 1, 2 No. 1, 2 CENTER CENTER CENTER FWD FWD AFT AFT R L L or R VENT REMOVAL VENT REMOVAL FUELING LINE OUTLET CHECK (high point) FUELING LINE OUTLET CHECK REMOVAL 250 100 450 350 2100 1140 900
TABLE 1
28-22-0 Sep 20/82 Page 510
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(d) Extend flaps and install leading edge flap locks (AMM 27-81-0/201).
WARNING: INSTALL THE LOCKS (AMM 27-81-0/201). FLAPS ARE FAST ACTING
AND CAN CAUSE SERIOUS INJURY TO PERSONS.
(e)
Remove small clearance panels from wing lower skin, below main tank FWD boost pump removal valve handles (Fig. 501, View 4).
CAUTION: CLEARANCE PANEL MUST BE REMOVED OR DAMAGE TO REMOVAL VALVE WARNING SIGNAL MAY RESULT WHEN VALVE CLOSING IS ATTEMPTED.
(f)
Check that manual defueling valve is closed.
(g)
Check that APU master switch, on forward overhead panel (P5), is in OFF position.
(h)
Close MANIF VALVE (crossfeed) circuit breaker on P6 panel.
(i)
Put the crossfeed valve switch, on P5 panel in OPEN position.
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