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gallon usable) vented integral fuel tank and a fuel collector/sump in
each wing, a three position selector valve, an electric boost pump, and
an engine-driven fuel pump. Fuel is gravity fed from each tank to the
associated collector sumps where the engine-driven fuel pump draws
fuel through a filter and selector valve to pressure feed the engine fuel
injection system. The electric boost pump is provided for engine
priming and vapor suppression.
Each integral wing fuel tank has a filler cap in the upper surface of
each wing for fuel servicing. Access panels in the lower surface of
each wing allow access to the associated wet compartment (tank) for
inspection and maintenance. Float-type fuel quantity sensors in each
wing tank and each collector tank supply fuel level information to the
fuel quantity indicators. Positive pressure in the tank is maintained
through a vent line from each wing tank. Fuel, from each wing tank,
gravity feeds through strainers and a flapper valve to the associated
collector tank in each wing. Each collector tank/sump incorporates a
flush mounted fuel drain and a vent to the associated fuel tank.
The engine-driven fuel pump pulls filtered fuel from the two collector
tanks through a three-position (LEFT-RIGHT-OFF) selector valve. The
selector valve allows tank selection. From the fuel pump, the fuel is
proportioned to the induction airflow, metered to a flow divider, and
delivered to the individual cylinders. Excess fuel is returned to the
selected tank.
A dual-reading fuel-quantity indicator is located in the center console
next to the fuel selector in plain view of the pilot. Fuel shutoff and tank
selection is positioned nearby for easy access.
Fuel system venting is Essential to system operation. Blockage of the
system will result in decreasing fuel flow and eventual engine fuel
starvation and stoppage. Venting is accomplished independently from
each tank by a vent line leading to a NACA-type vent mounted in an
access panel underneath the wing near each wing tip.
Revision A7
P/N 13772-001 7-55
Cirrus Design Section 7
SR22 Airplane Description
SR22_FM07_1410C
THROTTLE
METERING
VALVE
In Prime mode, relay
allows high-speed pump
operation until 2-4 psi fuel
pressure is reached then
drops to low-speed
operation.
NOTE
In Prime mode, relay
allows high-speed pump
operation until 10 psi oil
pressure is reached then
drops to low-speed
operation.
ELECTRIC
AUXILIARY
PUMP FUEL
PUMP
PRIME
BOOST
FUEL
RELAY
OIL
PRESSURE
SENSOR
(LOW PRESSURE)
STARTING
CIRCUIT / DAU
GASCOLATOR
ELECTRIC
AUXILIARY
PUMP
R. WING
COLLECTOR
FILLER VENT
R. WING TANK
FILLER
OFF
FEED
RETURN
LEFT
RIGHT
FEED
RETURN
FUEL PRESSURE SWITCH
SELECTOR VALVE
OPERATION
FUEL
FLOW
INDICATOR
ANNUNCIATOR
FUEL
FUEL
QUANTITY
INDICATOR
FUEL
PUMP
PRIME
BOOST
DRAIN
(5 PLACES)
INJECTOR
MANIFOLD
FIREWALL
VENT
L. WING TANK
L. WING
COLLECTOR
FUEL
RELAY
ENGINE DRIVEN
FUEL PUMP
MIXTURE CNTL.
TO
SELECTOR
VALVE
TO
GASCOLATOR
Serials 0002 thru 0277 before SB 22-73-01.
Serials 0278 and subs
and 0002 thru 0277 after SB 22-73-01.
FLAPPER
VALVE
FLAPPER
VALVE
SELECTOR
VALVE
Figure 7-10
Fuel System Schematic
Revision A5
7-56 P/N 13772-001
Section 7 Cirrus Design
Airplane Description SR22
The airplane may be serviced to a reduced capacity to permit heavier
cabin loadings. This is accomplished by filling each tank to a tab
visible below the fuel filler, giving a reduced fuel load of 23.5 gallons
usable in each tank (47 gallons total usable in all flight conditions).
Drain valves at the system low points allow draining the system for
maintenance and for examination of fuel in the system for
contamination and grade. The fuel must be sampled prior to each
flight. A sampler cup is provided to drain a small amount of fuel from
the wing tank drains, the collector tank drains, and the gascolator
drain. If takeoff weight limitations for the next flight permit, the fuel
tanks should be filled after each flight to prevent condensation.
• Note •
Serials 0002 and subsequent with optional EMax Engine
Monitoring after factory installation or after Service Bulletin SB
22-77-01: The following fuel system component descriptions
　
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