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check the pilot valves in the fuselage tanks and the wing
and external tanks. In addition to this precheck function,
the precheck valves can be used for ground selective
refueling of only the fuselage or all tanks. Since the
precheck valves, which are manually set by the groundcrew,
port pressurized servo fuel to the high-Level pilot
valves and subsequently to the shutoff valves, no
electrical power is necessaryo n the aircraft to perform
ground refueling operations. Additionally, ground refueling
control without engines running is completely
independento f switch positioning on the fuel manage-
During ground refoeling operations, the
direct-reading vent pressure indicator
shall be observed and refueling stopped if
pressure indicates in the red band (above
4 psi).
2.14.10 In-Flight Refueling
Note
See paragraph 9.1 for in-flight refueling
procedures.
The in-flight refueling system permits partial or complete
refueling of the aircraft fuel tanks while in flight.
The retractable refueling probe has an MA-Z-type nozzle,
which is compatible with any drogue-type refueling
2.57 ORIGINAL
NAVAIR 01.F14AAD-1
system. A split refueling system is provided with fuel
routed into the left and right box-beam tanks for initial
replenishment of sump tank fuel. Selectable fuel management
controls dictate the extent of further distribution
to the wing tanks, external tanks, and/or fuselage
tanks. The maximum refueling rate is approximately
475 gpm at a pressure of 57 psi.
(,,,,,,,I
To prevent fuel fumes from entering the
cockpit through the ECS because of possible
tire1 spills during in-flight refueling, select L
ENG air source.
Maximum airspeed for extension or retraction
in flight of the refueling probe is 400
knots (0.8 Mach).
Note
l With the in-flight refueling probe extended,
the pilot and RIO altimeter and
airspeed and Mach indicaton will show
erroneousin dications becauseo f changes
in airflow around the pitot static probes.
l Flight operations with the in-flight refueling
probe door removed are not recommended
because of the effects of water
intrusion, exposure to elements, and structural
fatigue to electrical hydraulic hardware
assemblies. If operational necessity
dictates, the in-flight refueling probe door
may be removed to prevent damage, loss,
or engine FOD.
a The RUDDER AUTH caution light may
illuminate when the in-flight refueling
probe. is extended. Press the MASTER
RESET button to reset the light.
2.14.10.1 in-flight Refueling Probe. The retractable
in-flight refueling probe is in a cavity on the right
side of the forward fuselage section, immediately forward
of the pilot vertical console panel.
Extension of the refueling probe is provided through
redundant circuits by the REFUEL PROBE switch. A
hydraulic actuator within the probe cavity extends and
retracts the probe. The probe actuator is powered by the
combined hydraulic system. It can be extended and IB
tracted by means of the hydraulic handpump in the event
of combined system failure.
Loss of combined pressure may indicate impending
fluid loss. Without fluid in the combined
system return line, the in-flight
refueling probe will not extend with the
handpump. Early extension of the refueling
probe at the first indication of a combined
system malfunction is recommended in a
carrier environment.
Note
To extend or retract the refueling probe
using the hydraulic handpump requires
the refuel probe switch to be placed in
EXT or RET (as appropriate), combined
system fluid in the return line, and essential
dc No. 2 electrical power. With a total
loss of combined hydraulic pressure in
flight, fluid trapped in the return line/
handpump reservoir can be isolated exclusively
for refueling probe extension if the
landing gear handle is in the up position.
Extension of the refueling probe requires
;i;;;imately 25 cycles of the pump
Probe retraction is not available if the
FUEL P/MOTIVE FLOW ISOL V (PPUMP)
circuit breaker (RGl) is pulled.
2.14.10.2 Refueling Probe Transition Light. The
red probe transition light immediately above the REFUEL
PROBE switch illuminates whenever the probe
cavity forward door is not in the closed position. Since
the closed-door position is indicative of both the probe
retracted and extended position, the light serves as a
probe transition indicator as well as a terminal status
indicator. The probe external light illuminates automatically
upon probe extension with the EXT LTS master
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F-14D 飞行手册 Flight Manual 1(88)
