(c)  Place tank NO. 1 FWD boost pump switch in OFF position.
(3)  Restore airplane to normal.
(a)  
Return both engine start levers to CUTOFF position to close engine fuel shutoff valves.

(b)  
Place crossfeed valve switch on P5 panel in closed position.

(c)  
Open fuel system circuit breakers on P6 panel: FWD BOOST PUMP TANK 1, SHUTOFF VALVE ENG 1, SHUTOFF VALVE ENG 2, and MANIF VALVE.

(d)
Manually close APU fuel valve.

(e)  
Remove leading edge flap locks (Ref 27-81-0 MP).

WARNING:  LEADING EDGE FLAPS ARE FAST ACTING AND CAN CAUSE SERIOUS INJURY TO PERSONNEL.

(f)  
Remove external electrical power, if no longer needed.

538 
Feb 20/93  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  28-22-0 Page 517 

H.  Center Wing Tank Boost Pump Override Test
(1)  
Fill center tank to a minimum of 2000 lbs (900 kgs) and wing tanks to approximately 80% full.

(2)  
Start both engines (AMM 71-09-100/201).

(3)  
Make sure that all boost pumps are operating.

(a)  To operate any of the fuel boost pumps, you must be in the flight compartment to continuously monitor the fuel quantity and the low pressure indication in the fuel tank.
WARNING:  DO NOT OPERATE ANY FUEL BOOST PUMP IF THE LOW PRESSURE LIGHT COMES ON AND STAYS ON. FUEL VAPORS IN THE TANK MAY IGNITE AND CAUSE A FIRE OR EXPLOSION.
1)  Immediately put the applicable fuel boost pump switch(es) to OFF if the LOW PRESSURE light comes on and stays on.
(4)  
Make sure that crossfeed valve is in CLOSE position.

(5)  
Position airplane for engine run, set engines to IDLE.

(6)  
Record fuel quantity indicator readings for all tanks, and start 10-minute engine run at IDLE.

(7)  
At end of 10-minute engine run, record fuel quantity readings.

(8)  
Shut down engines (AMM 71-09-100/201).

(9)  
Compare before and after fuel quantities.

(a)  
Readings for tanks No. 1 and 2 should be within + 50 lbs (+ 25 kgs) (reading repeatability tolerance).

(b)  
Center tank difference should be approximately 220 +50 lbs (100 +25 kgs) (fuel consumed).

I.  Test APU Fuel Shutoff Valve
(1)  
Prepare for APU fuel shutoff valve test.

(a)  
Connect external electrical power to airplane (AMM 24-22-0/201).

(b)  
Extend flaps and install leading edge flap locks (AMM 27-81-0/201).

WARNING:  REFER TO AMM 27-81-0/201 FOR LOCK INSTALLATION PROCEDURE. FLAPS ARE FAST ACTING AND CAN CAUSE SERIOUS INJURY TO PERSONS.

(c)  
Open APU FIRE EXT BOTTLE circuit breaker on P6 panel and attach DO-NOT-CLOSE identifier.

CAUTION:  ACCIDENTAL DISCHARGE OF APU FIRE BOTTLE CAN OCCUR IF CIRCUIT BREAKER IS NOT OPENED.

(d)  
Close APU CONT circuit breaker on P6 panel.

(e)  
Close INDICATOR LTS MASTER DIMMING control cabin lighting circuit breaker on P6 panel.

(f)  
Position BAT switch, on forward overhead panel (P5), to ON.

(2)  
Test APU fuel shutoff valve.

(a)  
Place APU master switch to ON position.

(b)  
Verify that valve override handle moves to OPEN position.

(c)  
Pull APU fire handle on engine and APU fire control module on P8 panel.

(d)  
Verify valve override handle moves to CLOSE position.

(e)  
Push fire handle in to the stowed position.

(f)  
Verify that valve override handle moves to OPEN position.

(g)  
Pull APU remote fire handle on the APU remote fire control panel P28 in the right wheel well.

(h)  
Verify that valve override handle moves to CLOSE position.

(i)  
Push APU remote fire handle to stowed position.

(j)  
Verify that valve override handle moves to OPEN position.

(k)  
Place APU master switch in OFF position.

(l)  
Verify that valve override handle moves to CLOSE position.

(3)  
Restore airplane to normal.

(a)  
Remove DO-NOT-CLOSE identifier and close P6 panel APU FIRE EXT BOTTLE circuit breaker.

CAUTION:  CIRCUIT BREAKER MUST BE CLOSED FOR APU FIRE EXTINGUISHING SYSTEM TO BE OPERATIONAL.

(b)  
Open INDICATOR LTS MASTER DIMMING control cabin lighting circuit breaker on P6 panel.

(c)  
Position BAT switch, on forward overhead panel (P5), to OFF.
　
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