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Supplements SR20
Fuel System
A 56-gallon usable wet-wing fuel storage system provides fuel for
engine operation. The system consists of a 29.3-gallon capacity (28
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 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
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.
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 13.0 gallons
usable in each tank (26 gallons total usable in all flight conditions).
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Cirrus Design Section 9
SR20 Supplements
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.
Exterior Lighting
The airplane is equipped with wing tip navigation lights with integral
anti-collision strobe lights and recognition Lights. The landing light is
located in the lower cowl.
Recognition Lights
The airplane is equipped with recognition lights on the leading edge of
the wing tips. The lights are controlled through the landing light switch
on the instrument panel bolster. 28 VDC for recognition light operation
is supplied through the 5-amp REC/INST LTS circuit breaker on Main
Bus 1.
Revision 01: 08-26-09
52 of 56 11934-S37
Section 9 Cirrus Design
Supplements SR20
Environmental System
Cabin heating and ventilation is accomplished by supplying
conditioned air for heating and windshield defrost and fresh air for
ventilation. The environmental system consists of a fresh air inlet in
the lower RH cowl, a heat exchanger around the RH engine exhaust
muffler, an air mixing chamber, air ducting for distribution, a distribution
manifold, a windshield diffuser, and crew and passenger air vents. An
optional 3-speed blower fan is available to supplement airflow when
ram air may be inadequate such as during ground operation.
Fresh air enters the cabin air distribution system through a NACA vent
on the RH lower cowl and is ducted to the air mixing chamber mounted
to the forward side of the firewall. Fresh air also enters the upper RH
cowl inlet, flows through the upper cowl, and is ducted to a heat
exchanger surrounding the RH engine exhaust muffler. The heated air
is then routed to the air mixing chamber to be mixed with the fresh air.
The mixed air is then distributed by either ram air or by optional blower
　
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