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Oil Warning Light
The red OIL warning light in the annunciator panel comes on to
indicate either high oil temperature or low oil pressure. The light is
illuminated by a switch in the oil temperature gage if the oil
temperature reaches 240 F or by a switch in the oil pressure gage if
the oil pressure drops to 10 psi or less. If the OIL warning light comes
on in flight, refer to the oil temperature and pressure gages to
determine the cause. Typically, low oil pressure will be accompanied
by a high oil temperature indication. The light is powered by 28 VDC
through the 2-amp ANNUNC circuit breaker on the Essential Bus.
March 2010
7-40 Information Manual
Section 7 Cirrus Design
Airplane Description SR20
Propeller
The airplane is equipped with a constant-speed, aluminum-alloy
propeller with a governor. The airplane is available with the standard
two-blade (76” diameter) propeller or an optional three-blade (74”
diameter) propeller.
The propeller governor automatically adjusts propeller pitch to
regulate propeller and engine RPM. The propeller governor senses
engine speed by means of flyweights and senses throttle setting
through a cable connected to the power (throttle) control lever in the
cockpit. The propeller governor boosts oil pressure in order to regulate
propeller pitch position. Moving the throttle lever forward causes the
governor to meter less high-pressure oil to the propeller hub allowing
centrifugal force acting on the blades to lower the propeller pitch for
higher RPM operation. Reducing the power (throttle) lever position
causes the governor to meter more high-pressure oil to the propeller
hub forcing the blades to a higher pitch, lower RPM, position. During
stabilized flight, the governor automatically adjusts propeller pitch in
order to maintain an RPM setting (throttle position). Any change in
airspeed or load on the propeller results in a change in propeller pitch.
March 2010
Information Manual 7-41
Cirrus Design Section 7
SR20 Airplane Description
Fuel System
A 56-gallon usable wet-wing fuel storage system provides fuel for
engine operation. The system consists of a 30.3-gallon capacity (28-
gallon usable) vented integral fuel tank in each wing, 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. An access panel in the lower surface of
each wing provides access to the associated wet compartment (tank)
for general inspection and maintenance. Float-type fuel quantity
sensors in each wing tank provide 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 check valve to the associated collector
tank/sump 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.
Fuel quantity indicators for each tank are 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.
March 2010
7-42 Information Manual
Section 7 Cirrus Design
Airplane Description SR20
Figure 7-8
SR20_FM07_1016E
Serials 1005 thru 1227 before SB 20-73-02.
Serials 1228 and subs
and 1005 thru 1227 after SB 20-73-02.
THROTTLE
METERING
VALVE
In Prime mode, relay
allows high-speed pump
operation until 2-4 psi fuel
pressure is reached then
　
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本文鏈接地址：西銳20飛機信息手冊 SR22 AIRPLANE INFORMATION MANUAL 1148-126(63)