(f)  
Check that fuel flow increases and engine operates normally at 93% N2 position.

NOTE: At first indication of power loss, shut down engine (AMM 71-09-100/201).

(g)  
Return thrust lever to idle position and check that engine runs normally.

(h)  
Put the L CTR tank and tank No. 1 boost pump switches to ON position.

1)  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.
a)  Immediately put the applicable fuel boost pump switch(es) to OFF if the LOW PRESSURE light comes on and stays on.
NOTE:  When defueling or transferring fuel with minimum backpressure to the pumps, it is possible for the low pressure light(s) to be on.  In this case, monitor the tank quantity and put the pump switch(es) to OFF if the tank quantity is not changing.
(i)  
Stop the engine (AMM Chapter 71, Power Plant).

(j)  
If engine had to be shut down due to lack of fuel, do the bypass valve test per par. E.

(k)  
Repeat steps (a) thru (j) for tank No. 2 boost pump bypass valve, except substitute: 1) Engine No. 2 for engine No. 1 2) R CTR tank boost pump switch for L CTR tank boost pump switch. 3) Tank No. 2 boost pump switches for tank No. 1 boost pump switches.

(l)  
Results of test of tank No. 2 boost pump bypass valve shall be the same as the tank No. 1 boost pump bypass valve test.

May 01/03  28-22-0
Page 515
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

G.  Fuel Feed System Leak Test
(1)  
Prepare Fuel Feed System for Leak Test

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

(b)  
Check that each fuel tank has a minimum of 700 pounds (350 kilograms) of fuel.

(c)  
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.

(d)  
Check that all fuel boost pump switches, on the forward overhead panel (P5), are in OFF position.

(e)  
Check that APU master switch on P5 panel is in OFF position.

(f)  
Check that manual defueling valve is closed.

(g)  
Make sure that engine ignition circuit breakers on P6 panel are open.

(h)  
Close fuel system circuit breakers on aft overhead panel (P6): FWD BOOST PUMP TANK 1, SHUTOFF VALVE ENG 1, SHUTOFF VALVE ENG 2, and MANIF VALVE.

(i)  
Put both engine start levers in IDLE position to open engine fuel shutoff valves.

(j)  
Put the crossfeed valve switch on P5 panel in open position.

(k)  
Manually open the APU fuel valve.

(2)  
Test the fuel feed system for leaks.

(a)  Put the tank No. 1 FWD boost pump switch in ON position.
1)  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.
a)  Immediately put the applicable fuel boost pump switch(es) to OFF if the LOW PRESSURE light comes on and stays on.
NOTE:  When defueling or transferring fuel with minimum backpressure to the pumps, it is possible for the low pressure light(s) to be on.  In this case, monitor the tank quantity and put the pump switch(es) to OFF if the tank quantity is not changing.
(b)  When boost pump low pressure indicating light goes off, check the following points for fuel leaks.
NOTE:  If light does not go off, refer to the fuel boost pump reprime procedure  (AMM 28-22-41/401).
527 
28-22-0 Page 516  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  May 01/03 

1) Engine fuel shutoff valve on left wing front spar 2) Crossfeed valve on left wing front spar 3) Engine fuel shutoff valve on right wing front spar 4) Manual defueling valve on right wing front spar 5) Center tank cavity drain/APU fuel line shroud drain at left wing-body fillet fairing
drain mast.
NOTE:  If leakage is indicated at the drain mast, a check of all the upstream branches of the drain manifold must be made to pinpoint source. The APU shrouded fuel feed line drain mast maximum allowable leakage is 5 drops/minute.
　
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