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The speedbmke/fuedl ump interlock doesn ot
prevents peedbrakesfm m being deployed if
fuel dump is activated. It only prevents the
dumping of fuel if the speedbrakes are already
extended.
. The FUEL FEEDKHJMF circuit breaker
is on the pilot right-knee circuit breaker
panel.
. Dump operations with either engine in afterburner
should be avoided since the fuel
dump mast discharge will be torched.
. After terminating fuel dump, wait appmximately
1 minute to allow residual fuel in
the fuel dump line to drain before extending
speedbrakeso r lighting afterburners.
Fuel in the wings and external tanks is dumped by
transferring to the fuselage. When the titselage fuel
dump circuit is activated, wing and external tanktmnsfer
to the box-beam tanks is automatically initiated. Fuel
dump is by gravity flow with a nominal discharge rate
of 1,500 pounds per minute. The dump rate is affected
by aircraft pitch attitude and total fuselage titel quantity
with discharge flow inhibited at nosedown conditions.
‘Ihe standpipes in the fuel cells control the minimum
Note
2-55 ORIGINAL
NAVAIR Ol-Fl4AAD-1
Figure 2-35. Fuel Vent and Dump
fuel dump level in the tanks, which, under normal operations
(feed group full), is approximately 4,000
pounds.
2.14.8 internal Tank Pressurization and Vent.
The internal fuel vent system is shown in Figure 2-35.
It is an open-vent-type system, pressurized by ram air
and engine bleed air from the 25-psi external tank pressure
system that is reduced to 1.75 psi by a fuselage
pressure regulator and distributed to all tanks through
the fuselage vent system. This air is automatically supplied
when the landing gear handle is UP or the
WING/EXT TRANS switch is in ORIDE. When the
WING/EXT TRANS switch is in OFF, the low-pressure
bleed air is cut off.
In flight, the vent tank is maintained at a positive
pressure up to 2.5 psi maximum. This pressure is fed by
connecting lines to all internal tanks. These connecting
lines are routed to provide venting to both the forward
and afl end of each fuselage tank so it can function as
both a climb and dive vent. Venting of the box-beam
tanks is controlled by solenoid-operatingv alves, which
when closed, provide suction transfer through the gravity
flow paths in cell Nos. 2 and 5 to the sump tanks.
2.14.9 Fueling and Defueling. Figure 2-36 shows
the refueling system. The aircraft is equipped with a
single-point refueling system, which enables pressure
tilling of all aircraft fuel tanks from a single receptacle.
The receptaclei s at the recessedg round refuel and defuel
station, behind a quick-access door on the lower
right side of the forward fuselage. The maximum retitcling
rate is 450 gallons per minute at a pressureo f 50
psi. Since ground and air refueling connections use a
common manifold, the refueling sequenceis the same.
Standpipes refuel the aft and forward fuselage tanks
by overtlow from the left and right box-beam tanks. A
high-level pilot valve at the high pointofthe forward tank
shuts off the fuselage refueling valve in the right boxbeam
tank when the forward tank group is full. Fuel flows
from the left box-beam tank to cell No. 5, after which it
overtlows to the right side, then the left side. Ahigh-level
pilot valve at the high point ofthe left box-beam tank and
aft tank (cell No. 7) shutso ffthe fuselagere fueling valve
in the let? box-beam tank when the aft tank group is 111.
Individual wing and external tank tilling is accomplished
by flow through a shutoff valve in each tank.
ORIGINAL 2-58
NAVAIR 01.Fl4AAD-1
AFT HIGWLEVEL
“TOFF VALVE
PILOT VALVE
Figure 2-36. Refueling System
mcnt panel. The direct-reading vent pressure indicator
monitors pressure in the vent lines. The gauge consists
of a pointer on a scale having two bands, one green and
one red.
Gravity refueling of the aircraft fuel system
should be accomplished only under emergency
situations. While performing such an
operation, avoid introducing contaminants
into the fnel tanks or damaging the Fuel qnantity
probes and wiring.
The greenb andi ndicatesa safe pressurera nge( 0 to 4
psi), and the red band indicates an unsafe range (4 to 8 psi).
2.14.9.1 Precheck System. Ground retireling con,
trol is by two precheck selector valves and a vent pres,
sum gauge adjacent to the refueling receptacle on the
ground refuel and defuel panel. The precheck valves
functionally test high-level pilot valve operation inci,
dent to ground pressure refueling; the valves separately
　
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本文鏈接地址：F-14D 飛行手冊 Flight Manual 1(87)