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March 2010
7-36 Information Manual
Section 7 Cirrus Design
Airplane and Systems Description SR22
Engine Lubrication System
The engine is provided with a wet-sump, high-pressure oil system for
engine lubrication and cooling. Oil for engine lubrication is drawn from
an eight-quart capacity sump through an oil suction strainer screen
and directed through the oil filter to the engine-mounted oil cooler by a
positive displacement oil pump. The oil pump is equipped with a
pressure relief valve at the pump output end to bypass oil back to the
pump inlet should the pump exceed limits. The oil cooler is equipped
with a temperature control valve set to bypass oil if the temperature is
below 180°F (82°C). Bypass or cooled oil is then directed through oil
galleries to the engine rotating parts and piston inner domes. Oil is
also directed to the propeller governor to regulate propeller pitch. The
complete oil system is contained in the engine. An oil filler cap and
dipstick are located at the left rear of the engine. The filler cap and
dipstick are accessed through a door on the top left side of the engine
cowling.
Ignition and Starter System
Two engine-driven magnetos and two spark plugs in each cylinder
provide engine fuel ignition. The right magneto fires the lower right and
upper left spark plugs, and the left magneto fires the lower left an
upper right spark plugs. Normal operation is conducted with both
magnetos, as more complete burning of the fuel-air mixture occurs
with dual ignition. A rotary-type key switch, located on the instrument
panel, controls ignition and starter operation. The switch is labeled
OFF-R-L- BOTH-START. In the OFF position, the starter is electrically
isolated, the magnetos are grounded and will not operate. Normally,
the engine is operated on both magnetos (switch in BOTH position)
except for magneto checks and emergency operations. The R and L
positions are used for individual magneto checks and for single
magneto operation when required. When the battery master switch is
ON, rotating the switch to the spring loaded START position energizes
the starter and activates both magnetos. The switch automatically
returns to the BOTH position when released.
28 VDC for Starter operation is supplied through the 2-amp STARTER
circuit breaker on NON-ESSENTIAL BUS.
Air Induction System
Induction air enters the engine compartment through the two inlets in
the forward cowling. The air passes through a dry-foam induction filter,
March 2010
Cirrus Design Section 7
SR22 Airplane and Systems Description
Information Manual 7-37
through the throttle butterfly, into the six-tube engine manifold, and
finally through the cylinder intake ports into the combustion chambers.
Should the dry induction filter become clogged, a pilot controlled
alternate induction air door can be opened, allowing engine operation
to continue as described below. For additional information on the
Alternate Air Control, refer to Engine Controls - Alternate Air Control
description in this section.
Engine Exhaust
Engine exhaust gases are routed through a tuned exhaust system.
After leaving the cylinders, exhaust gases are routed through the
exhaust manifold, through mufflers located on either side of the
engine, then overboard through exhaust pipes exiting through the
lower cowling. A muff type heat exchanger, located around the right
muffler, provides cabin heat.
Engine Fuel Injection
The multi-nozzle, continuous-flow fuel injection system supplies fuel
for engine operation. An engine driven fuel pump draws fuel from the
selected wing tank and passes it to the mixture control valve integral to
the pump. The mixture control valve proportions fuel in response to the
pilot operated mixture control lever position. From the mixture control,
fuel is routed to the fuel-metering valve on the air-induction system
throttle body. The fuel-metering valve adjusts fuel flow in response to
the pilot controlled Power Lever position. From the metering valve, fuel
is directed to the fuel manifold valve (spider) and then to the individual
injector nozzles. The system meters fuel flow in proportion to engine
RPM, mixture setting, and throttle angle. Manual mixture control and
idle cut-off are provided. An electric fuel pump provides fuel boost for
vapor suppression and for priming.
Engine Cooling
Engine cooling is accomplished by discharging heat to the oil and then
to the air passing through the oil cooler, and by discharging heat
directly to the air flowing past the engine. Cooling air enters the engine
compartment through the two inlets in the cowling. Aluminum baffles
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西锐20飞机信息手册 SR22 AIRPLANE INFORMATION MANUAL 2979(63)
