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pilot’s seat base. The extinguisher is approved for use on class B
(liquid, grease) and class C (electrical equipment) fires. The Halon
1211/1301 blend provides the best fire extinguishing capability with
low toxicity. A pin is installed through the discharge mechanism to
prevent inadvertent discharge of extinguishing agent. The fire
extinguisher must be replaced after each use.
To operate the extinguisher:
1. Loosen retaining clamp and remove the extinguisher from its
mounting bracket.
2. Hold the extinguisher upright and pull the pin.
3. Get back from the fire and aim nozzle at base of fire at the nearest
edge.
4. Press red lever and sweep side to side.
June 2007
7-40 Information Manual
Section 7 Cirrus Design
Airplane Description SR22
• WARNING •
Halon gas used in the fire extinguisher can be toxic, especially
in a closed area. After discharging fire extinguisher, ventilate
cabin by opening air vents and unlatching door. Close vents
and door after fumes clear.
The extinguisher must be visually inspected before each flight to
assure that it is available, charged, and operable. The preflight
inspection consists of ensuring that the nozzle is unobstructed, the pin
has not been pulled, and the canister has not been damaged.
Additionally, the unit should weigh approximately 1.5 lb (0.7 kg). For
preflight, charge can be determined by ‘hefting’ the unit.
June 2007
Information Manual 7-41
Cirrus Design Section 7
SR22 Airplane Description
Engine
The SR22 is powered by a Teledyne Continental IO-550-N, sixcylinder,
normally aspirated, fuel-injected engine rated to 310 hp at
2700 RPM. The engine has a 2000-hour Time Between Overhaul
(TBO). Dual, conventional magnetos provide ignition.
Serials 0002 through 0819 before Service Bulletin SB 2X-71-06; The
engine is attached to the firewall by a four-point steel engine mount.
Serials 0002 through 0819 after Service Bulletin SB 2X-71-06 and
airplane serials 0820 and subsequent: The engine is attached to the
firewall by a six-point steel engine mount.
The firewall attach points are structurally reinforced with gusset-type
attachments that transfer thrust and bending loads into the fuselage
shell.
Engine Oil 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.
• Caution •
The engine should not be operated with less than six quarts of
oil. Seven quarts (dipstick indication) is recommended for
extended flights.
June 2007
7-42 Information Manual
Section 7 Cirrus Design
Airplane Description SR22
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
direct the incoming air to the engine and over the engine cylinder
cooling fins where the heat transfer takes place. The heated air exits
the engine compartment through two vents in the aft portion of the
cowling. No movable cowl flaps are used.
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
　
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