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field landings with full or partial fuel in the
external tanks is not authorized because of
overloado fthe nacelleb ackups tructureO. nly
minimum descenrta tel andingsa rca uthorized.
14.6.3.3 Wings Do Not Accept Fuel With
Switch in ALL EXTD Position
1. REFUEL PROBE switch - FUS EXTD.
2. WING/EXT TRANS switch - OFF.
14.6.3.4 Wings Accept Fuel With Switch in FUS
EXTD Position
1. WING/EXT TRANS switch - ORIDE.
Note
With AIR SOURCE OFF pushbutton selected,
external fuel tanks will not transfer.
14.6.4 Uncommanded Dump
1. DUMP switch - Check OFF.
2. FUEL FEED/DUMP cb - Pull @El).
NAVAIR Ol-F14AAD-1
14.6.5 Fuel Leak. In the absenceo f actualv isual detection,
a fuel leak resulting from a malfunction or failure
of a fuel system component will usually result in a
split in the fuel quantity tapes or feeds. The flightcrew
must determine from available instruments (tie1 flOW
and total fuil quantity) whether the aircraft is losing
more fuel than the engines indicate they are using. Carrective
steps are based on confirmation ofthe leak. Upon
confirmation of abnormal decreasein fuel quantity:
1. Land as soon as possible.
Use of afterburner wiih fuel leak should be
limited to emergency use only.
2. WING/EXT TRANS switch - OFF.
Ifabnonnal fuel quantity decreasec eases,f uel leak is in
wing/wing pivot or attachment points for auxiliary
tanks:
Note
This cannot be determineduntil the fuel level
hasd ecreasedto below the sourceo fthe leak.
Do not proceed with the below steps prematurely.
If leak is not stopped,i t is in engine/nacellea rea.p roceed
immediately with next step.
3. FUEL FEED/DUMP cb -Pull @El).
Note
Enough time should be allowed for quantity
tapes/feedsto develop split so that leak can
be isolated to left or right feed group. Affected
side will be low side.
4. Throttle (affected side) - OFF.
5. Conditions permitting, allow rpm to decelerateto
windmill ‘pm.
6. FUEL SHUT OFF handle (affected side) - Pull.
7. Refer to Single-Engine Cruise Operations, paragraph
14.5.3.2.
Setting the WING/EXT TRANS switch to OFF stops
motive flow to the wings and inhibits external tank transfer
and fuselage tank pressurization. Pulling the FUEL
NAVAIR Ol-F14AAD-I
FEED/DUMP circuit breaker (REI) isolates the right
and forward system and the left and aft fuel system. This
aids in determining the location of the leak and prevents
loss of fuel from the good side via the fuel system interconnects,
T he circuit breakera lso deactivatest he function
of the FEED switch, the automatic balance
functions, and the fuel dump system. Securing the engine
and, if necessary, pulling the FUEL SHUT OFF
handle should stop most engine leaks.
14.7 ELECTRICAL FAILURE
14.7.1 Generator Failure. Amechanicalgenerator
failure or an overheating automatically causes the CSD
unit of the generator transmission to decouple from the
engine. Once disengaged, the CSD cannot be reconnected
in flight.
Either generatorb y itself is capableo f supplying the
electricalr equirementso f the aircraft. Even doubleg enerator
failure will not cause total loss ofelectrical power;
the 5-kVA emergencyg eneratorw ill automatically pick
up the load for the essential ac and dc buses No. 1 and
No. 2, and the AFCS bus.
If the bidirectional pump is operating and ptessure
drops to bctwcen 2,000 and 1,100p si (dependentu pon
the load placed on the generator), the emergency generator
will automatically shift to the l-kVA mode and
power only the essential ac and dc No. 1 buses. If combined
systemh ydraulic pressures ubsequentlyr ecovers,
the emergencyg enerators witch must be cycled through
OFF/RESET to NORM to regain the essential No. 2 ac
and dc buses. Figure 14-5 lists the equipment available
with only the emergency generator operating.
With both engines inoperative, windmilling engine(
s) provide(s) hydraulic pressure for both the flight
controls and the emergency generator. However, the
flight controls have first priority and may cause the
emergency generator to loiter when low airspeeds reduce
engine windmilling ‘pm. Approximately450 knots
must be maintainedt o ensurea dequatee nginew indmilling
rpm for hydraulic pressure.
14.7.1.1 L or R GEN Light
1. Generator (affected generator switch) - OFF/
RESET, Then NORM.
Note
If the generator fault is corrected, the generator
will be reconnecteda nd the caution light
will go off.
If generatord oes not reset:
2. Generator (affected generator switch) - TEST.
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F-14D 飞行手册 Flight Manual 2(108)
