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2.  Equipment and Material
A.  Aliphatic Naphtha - TT-N-95
B.  Leading Edge Flap Actuator Locks - F80048-36
3.  Prepare Fuel Scavenge Flow Indicator/Check Valve for Removal (Fig. 401)
A.  Extend leading edge flaps and install actuator locks (Ref 27-81-0 MP)
WARNING:  REFER TO 27-81-0 MP FOR LOCK INSTALLATION PROCEDURE. FLAPS ARE FAST ACTING AND CAN CAUSE SERIOUS INJURY TO PERSONNEL.
B.  Defuel and purge tank No. 1 (Ref 28-23-0, 28-10-0 MP).
WARNING:  DO NOT COMPROMISE THE SAFETY PRECAUTIONS GIVEN FOR PURGING AND FUEL TANK ENTRY.
C.  Remove access panel (Ref 28-11-11 R/I).
4.  Remove Fuel Scavenge Flow Indicator/Check Valve (Fig. 401)
A.  At front spar, remove cap from flow indicator.
B.  Remove nut and washer securing indicator to front spar.
C.  Gain access in tank No. 1.
D.  Disconnect fuel lines and remove indicator. Discard O-ring.
5.  Install Fuel Scavenge Flow Indicator/Check Valve (Fig. 401)
A.  Clean O-ring groove in flow indicator body and tank No. 1 mating surface with naphtha, and wipe dry with lint free cloth.
B.  Install new O-ring, lightly lubricated with fuel, into groove in flow indicator.
C.  Position flow indicator thru hole in front spar and secure with washer and nut. Replace cap on flow indicator.
D.  Connect fuel lines to flow indicator.
6.  Restore Airplane to Normal
A.  Install access panel (Ref 28-11-11 R/I).
B.  Remove actuator locks and retract leading edge flaps (Ref 27-81-0 MP).
WARNING:  LEADING EDGE FLAPS ARE FAST ACTING AND CAN CAUSE SERIOUS INJURY TO PERSONNEL.
C.  Remove electrical power if no longer required (Ref 24-22-0 MP).
5C5
Feb 20/84 28-15-31 Page 401
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

Fuel Scavenge Flow Indicator/Check Valve Installation  500 
28-15-31  Figure 401  Feb 20/89 
Page 402 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

PRESSURE FUELING SYSTEM - DESCRIPTION AND OPERATION
1. General
A.  The pressure fueling system provides a rapid means of filling the fuel tanks on the aircraft. The pressure fueling system distributes fuel under pressure from the fueling station in the right wing to the fuel tanks, through a system of fueling lines and valves (Fig. 1 and 2). The fueling rate is 500 gpm at a delivery pressure of 55 psig.
B.  The fueling station is equipped with a fueling receptacle, a fueling manifold, a fueling power control switch, three fueling station illumination lights, one fueling indicator test switch, three fueling shutoff valves, fueling line check valves, fueling shutoff valve switches, fueling quantity indicator s and indicator lights (Fig. 1). Each tank is equipped with a float switch to provide automatic fueling shutoff when a fuel tank becomes full of fuel.
C.  The fueling operation consists of coupling the fueling hose nozzle to the fueling receptacle, opening the electrical fueling shutoff valves and pumping fuel into the fuel tanks. The fueling quantity indicators allow the servicing personnel to fill the tanks to a predetermined level when a full fuel load is not required.
2.  Fueling Receptacle
A.  A single fueling receptacle mounted on a manifold on the forward face of the wing front spar provides the means of connecting the fueling hose to the pressure fueling system (Fig. 1). The receptacle consists of a fueling hose adapter connected to the fueling receptacle manifold and a cap and a spring-loaded valve. The fueling hose adapter has mating lugs which couple with and secure the fueling hose. When the hose is coupled to the adapter, a plunger in the hose nozzle opens the spring-loaded valve to allow fuel to flow into the tanks.
B.  When not in use, the fueling receptacle is covered and sealed by a receptacle cap. The cap engages the lugs on the fueling hose adapter in the same manner as the fueling hose; when the cap is in position, the seal in the cap is forced against the adapter to seal the inlet to the adapter. To prevent loss, the cap is secured to the adapter with a piece of chain.
526 
May 01/01  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  28-21-0 Page 1 

F94777 F94799 F94807
Pressure Fueling System Component Location  5C8 
28-21-0  Figure 1 (Sheet 1)  Aug 01/96 
Page 2 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

5C8  Pressure Fueling System Component Location 
Aug 01/96  Figure 1 (Sheet 2)  28-21-0 
Page 3 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 
　
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