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where the cabin doors are jammed or inoperable, the hammer may be
used to break through the acrylic windows to provide an escape path
for the cabin occupants.
Fire Extinguisher
A liquefied-gas-type fire extinguisher, containing Halon 1211/1301
extinguishing agent, is mounted on the forward inboard side of the
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.
• WARNING •
Halon gas used in the fire extinguisher can be toxic, especially
in a closed area. After discharging fire extinguisher, ventilate
March 2010
7-42 Information Manual
Section 7 Cirrus Design
Airplane Description SR20
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.
March 2010
Information Manual 7-43
Cirrus Design Section 7
SR20 Airplane Description
Engine
The SR20 is powered by a Teledyne Continental IO-360-ES, sixcylinder,
normally aspirated, fuel-injected engine de-rated to 200 hp at
2,700 RPM. The engine has a 2000-hour Time Between Overhaul
(TBO). Dual, conventional magnetos provide ignition.
The engine is attached to the firewall by a four-point steel mount
structure. 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 to the engine-mounted oil cooler. The oil cooler is
equipped with a pressure relief and temperature control valve set to
bypass oil if the temperature is below 170 F or the pressure drop is
greater than 18 psi. Bypass or cooled oil is then directed through the
one-quart, full-flow oil filter, a pressure relief valve, and then 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.
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
March 2010
7-44 Information Manual
Section 7 Cirrus Design
Airplane Description SR20
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 and automatically provides
altitude compensation to supply the proper full rich mixture at any
altitude. From the mixture control, fuel is routed to the fuel-metering
　
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