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EJECTOR
PUMP
FLOW-RESTRICTOR
ORIFICE
(TO) (FROM) (FROM) (TO)
L ENGINE FUEL SYSTEM R ENGINE FUEL SYSTEM
TRANSFER
SHUTOFF
VALVE
FIREWALL
SHUTOFF
VALVE
FIREWALL
SHUTOFF
VALVE
LOWPRESSURE
SWITCH
SURGE
VENT LINE
LEGEND
FUEL INSIDE TANK
FROM ENGINE FUEL
SYSTEM
TO ENGINE FUEL
SYSTEM
LOW-PRESSURE,
HIGH-VOLUME FLOW
TRANSFER PRESSURE
VENT LINES
GRAVITY SUCTION
Figure 5-1. Fuel Tank System
CITATION MUSTANG OPERATING MANUAL
510OM-00 5-3
FUEL STORAGE
DESCRIPTION
The left and right tanks each have a fuel capacity
of 192.5 gallons (728.7 liters) for a total combined
fuel capacity per aircraft of 385 gallons
(1,457 liters). Refer to Table 5-1 for approximate
volumes and weights, or refer to the
Airplane Flight Manual (AFM) for current data.
The Citation Mustang fuel system does not require
the use of anti-icing additives.
Each wing tank system (left wing and right
wing) includes:
• Main tank cavity
• Engine feed bay
• Venting system
• Tank filler
• Sump drain valves
• Scavenge pumps
• Fuel probes
• Flapper valves
COMPONENTS
Main Tank Cavity
Each main tank cavity (one in each wing, between
the forward and rear wing spars) is integral
to the wing. Holes in the main spar and
ribs allow fuel flow through the wing (Figure
5-1). Flapper valves, attached to spar and rib
holes, allow fuel flow inboard while inhibiting
flow outboard.
Engine Feed Bay
An engine feed bay is an integral part of each
wing tank. It is the lowest point in the fuel system,
which is the location for fuel pickup (intake)
for the fuel distribution system. Each
feed bay holds approximately 8 gallons and has
four vent openings (ensures the bay maintains
full capacity under all flight conditions).
Venting System
The venting system consists of a tank, vent
lines, flapper, and float-controlled vent valve.
A vent surge tank at the most outboard bay of
the wing fuel tank collects fuel surges from the
main tank and also provides a portion of the
required expansion space. The fuel travels
outboard from the main tank through the surge
vent line.
During climbs and maneuvers, air trapped in
the forward inboard area of the main tank escapes
through the climb vent line to vent into
the surge tank; this allows the main tank area
to fill with fuel.
A float-controlled vent valve is connected to
the vent surge tank. When the fuel level is full
enough to raise the float, the valve closes,
preventing fuel from overflowing into the
surge tank. When the fuel level is low, the
valve opens to provide venting. A flapper
valve permits fuel to drain from the surge tank
back into the main tank. If the vent surge tank
fills, another vent line allows spillage overboard
through the NACA scoop (Figure 5-2)
under the wing. The vent lines normally allow
air to enter or exit through the NACA scoop.
The scoop does not require anti-icing.
Figure 5-2. NACA Scoop Fuel Vent
Table 5-1. FUEL SYSTEM CAPACITY
STANDARD (U.S.) METRIC
Total
Capacity Weight Volume Weight Volume
Each 1,290 192.5 585 728.7
Tank pounds gallons kg liters
Both 2,580 385 1,170 1,457
Tanks pounds gallons kg liters
CITATION MUSTANG OPERATING MANUAL
5-4 510OM-00
Tank Filler
The aircraft has one fuel tank filler assembly
on the upper surface of each wing, between the
main spar and the aileron (Figure 5-3). The
filler assembly consists of a flush-type cap
and a standpipe.
Sump Drain Valves
Sump drain valves (Figure 5-4) are at the low
points in each wing where water can collect.
In each wing, there is a sump drain in each of
the following locations:
• Outboard and inboard of the landing
gear (behind the main spar)
• In the engine feed bay
• Between the feed bay and the main spar
• Between the forward and main spars
(forward of the feed bay)
When draining sumps, do not turn any tool in
the drain. The drain may lock open, resulting
in fuel loss.
CONTROLS AND INDICATIONS
Fuel Quantity Gauging System
The fuel quantity gauging system includes a
signal conditioner and five fuel quantity probes
in each wing. The left and right fuel quantity
signal conditioners gather data from their respective
sides and convert the data into the appropriate
signals for the G1000 engine
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Cessna塞斯纳公务机飞行手册(28)
