7-40
P/N 13772-005
Section 7
Cirrus Design
Systems Description
SR22T
Fuel System
An 92-gallon usable wet-wing fuel storage system provides fuel for
engine operation. The system consists of a 47.25-gallon capacity (46-
gallon usable) vented integral fuel tank and a fuel collector/sump in
each wing, a three position selector valve, an electric fuel 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 fuel 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 supply fuel level information to the fuel quantity gages.
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
metered to a flow divider, and delivered to the individual cylinders.
Excess fuel is returned to the selected tank.
A simulated fuel quantity gage is located on the Engine Strip along the
left edge of the MFD and in the Fuel Qty block on the MFD’s Engine
page.
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.
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 30.0 gallons
usable in each tank (60 gallons total usable in all flight conditions).
Original Issue
