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A leak of less than 400 pph can, however, be discovered during the post-flight switching valve checks.
Following engine shutdown, the SDC opens the cross cooling valve and the heat exchanger bypass valve
on the non-operating side for 20 seconds. If ground crew observe fuel exiting from the fuel/air heat
exchanger drainage ports (bottom, inboard edge of the inlet), a leak exists.
2.2.5 Refueling System. The aircraft can be refueled on deck through a single point refueling
receptacle or inflight through a hydraulically actuated inflight refueling probe. The refueling
receptacle is located behind door 8R on the forward right fuselage. The refueling probe is located on
the upper right side of the fuselage forward of the windscreen. A fuel pressure regulator/surge
suppressor is installed downstream of the refueling probe in order to control pressure spikes associated
with inflight refueling. Fuel from the single point receptacle or the refueling probe enters the
refuel/defuel line and is routed to all internal and external tanks. During refueling, the SDC opens all
refuel valves, allowing fuel to transfer into all internal tanks. External tank pressurization is
terminated when the probe is extended, allowing the refuel/defuel line to fill all installed external tanks
(EXT TANKS switch(es) not in STOP).
2.2.5.1 PROBE Switch. The guarded PROBE switch, located on the FUEL panel on the left console,
is used to extend and retract the inflight refueling probe.
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I-2-17 ORIGINAL
EXTEND Extends the inflight refueling probe using HYD 2A pressure, energizes the probe
light (external lights master switch in NORM), and depressurizes all internal and
external tanks.
RETRACT Retracts the inflight refueling probe using HYD 2A pressure, deenergizes the probe
light, and repressurizes the internal and external tanks. The probe cannot be
retracted if HYD 2A pressure is not available.
EMERG
EXTD
Emergency extends the inflight refueling probe using either HYD 2B or APU accumulator
pressure, energizes the probe light (external lights master switch in NORM),
and depressurizes all internal and external tanks.
2.2.6 Fuel Dump System. The fuel dump system allows all fuel except feed tank fuel to be dumped
overboard. The dump valve, controlled by the DUMP switch, is located in the Tank 1 and 4 transfer
line. With the dump valve open, the Tank 1 and 4 transfer pumps (high-speed setting) force fuel out
the dump outlet, located on the trailing edge of each vertical tail. Wing tank fuel is dumped by
transferring to Tank 4 with the INTR WING switch in NORM. External fuel is dumped by
transferring to Tanks 1 and 4 only with the EXT TANKS switch(es) in NORM or ORIDE.
Dump rate is typically in excess of two engine MAX power fuel flow, approximately 1,300 lb per
minute (78,000 pph). Fuel dumping continues until:
a. The DUMP switch is placed to OFF
b. The BINGO caution comes on
c. Tanks 1 and 4 are empty and all available fuel from internal wing and external tanks has been
depleted.
d. The FUEL LO caution comes on.
Simultaneous selection of fuel dump and afterburner during high AOA
maneuvering may ignite fuel and cause fuselage damage.
2.2.6.1 Fuel DUMP Switch. The lever locked fuel DUMP switch, located on the FUEL panel on the
left console, is spring loaded to the OFF position and electrically held in the ON position.
ON Opens the dump valve, allowing transfer tank and external tank fuel to be dumped.
The switch reverts to OFF with a BINGO or FUEL LO caution. With either caution,
holding the switch in the ON position with Tank 1 and/or 4 fuel available reinitiates
fuel dump.
OFF Dump valve closed
2.2.7 Fuel Quantity Indicating System. The fuel quantity indicating system measures the individual
fuel quantities in all internal and external fuel tanks and provides cockpit readouts for individual
tanks, total internal fuel, and total fuel onboard. Quantities are displayed on the EFD and the FUEL
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I-2-18 ORIGINAL
display, rounded to the nearest 10 pounds (figure 2-5). Actual fuel tank probe readings are displayed
on the FUEL QTY display selected from the SUPT MENU/BIT/STATUS MONITOR display.
While the volume of fuel with full tanks does not change, the fuel quantities listed in pounds vary
with changes in temperature and fuel density. Full internal fuel quantity can vary from 13,250 to 15,960
lb for the F/A-18E or from 12,410 to 14,940 lb for the F/A-18F at fuel temperatures of 100° and -40°F,
respectively. Figure 2-5 lists standard day fuel quantities for JP-5, JP-8, and JP-4.
2.2.7.1 EFD - Engine Fuel Display, Fuel Parameters. The EFD displays fuel, maintenance code, and
consumables information in green digits on a black background (figure 2-6). The top level EFD format
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NATOPS Flight Manual 飞行手册 1(39)
