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provided for the fuel caps.
Windshield and Windows
The windshield and side windows are manufactured of acrylic. Use
only clean soft cloths and mild detergent to clean acrylic surfaces.
Refer to Section 8 for detailed cleaning instructions.
March 2010
7-30 Information Manual
Section 7 Cirrus Design
Airplane and Systems Description SR22
Engine
The aircraft 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.
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 Controls
Engine controls are easily accessible to the pilot on a center console.
They consist of a single-lever power (throttle) control and a mixture
control lever. A friction control wheel, labeled FRICTION, on the right
side of the console is used to adjust control lever resistance to rotation
for feel and control setting stability.
Power (Throttle) Lever
The single-lever throttle control, labeled MAX-POWER-IDLE, on the
console adjusts the engine throttle setting in addition to automatically
adjusting propeller speed. The lever is mechanically linked by cables
to the air throttle body/fuel-metering valve and to the propeller
governor. Moving the lever towards MAX opens the air throttle butterfly
and meters more fuel to the fuel manifold. A separate cable to the
propeller governor adjusts the governor oil pressure to increase
propeller pitch to maintain engine RPM. The system is set to maintain
approximately 2500 RPM throughout the cruise power settings and
2700 RPM at full power.
March 2010
Cirrus Design Section 7
SR22 Airplane and Systems Description
Information Manual 7-31
Mixture Control
The mixture control lever, labeled RICH-MIXTURE-CUTOFF, on the
console adjusts the proportion of fuel to air for combustion. The
Mixture Control Lever is mechanically linked to the mixture control
valve in the engine-driven fuel pump. Moving the lever forward
(towards RICH) repositions the valve allowing greater proportions of
fuel and moving the lever aft (towards CUTOFF) reduces (leans) the
proportion of fuel. The full aft position (CUTOFF) closes the control
valve.
Alternate Air Control
An Alternate Induction Air Control knob, labeled ALT AIR – PULL, is
installed on the left console near the pilot’s right knee.To operate the
control, depress the center lock button, pull the knob to the open
position, and then release the lock button. Pulling the knob opens the
alternate air induction door on the engine induction air manifold,
bypasses the air filter, and allows warm unfiltered air to enter the
engine. Alternate induction air should be used if blocking of the normal
air source is suspected. Operation using alternate induction air should
be minimized and the cause of filter blocking corrected as soon as
practical.
March 2010
7-32 Information Manual
Section 7 Cirrus Design
Airplane and Systems Description SR22
Engine Indicating
Engine information is displayed as analog-style gages, bar graphs,
and text on the MFD’s ENGINE page. When the ENGINE page is not
active or in the case of an electronic display failure (backup mode), all
essential engine information is displayed along the LH edge of the
display. Engine data is acquired by the Engine Airframe Unit which
transmits the data to the Engine Indicating System for display as
described in the following pages.
• Note •
A “Red X” through any electronic display field indicates that
the display field is not receiving valid data and should be
considered inoperative.
Engine System Annunciations
Engine system health, caution, and warning messages are displayed
in color-coded text in the Crew Alerting System (CAS) window located
to the right of the Altimeter and Vertical Speed Indicator. In
combination with a CAS alert, the affected engine parameter displayed
on the ENGINE page changes to the corresponding color of CAS alert
and the annuncation system issues an audio alert.
For specific pilot actions in response to Engine System
Annunciations, refer to the Engine System procedures
contained in Section 3 - Emergency Procedures, and Section
3A - Abnormal Procedures.
For additional information on Engine Instrument Markings and
Annunciations, refer to Section 2 - Limitations.
　
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