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1. AVIONICS FAN 1 Circuit Breaker .......................................CYCLE
If annunciation does not extinguish:
a. High cabin temperatures .... LAND AS SOON AS PRACTICAL
b. Low cabin temperatures ..................... CONTINUE, MONITOR
MFD FAN FAIL
March 2010
3A-10 Information Manual
Section 3A Cirrus Design
Abnormal Procedures SR22
Pitot Static System
Pitot Static Malfunction
Static Source Blocked
If erroneous readings of the static source instruments (airspeed,
altimeter and vertical speed) are suspected, the alternate static source
valve, on side of console near pilot’s right ankle, should be opened to
supply static pressure from the cabin to these instruments. With the
alternate static source on, adjust indicated airspeed slightly during
climb or approach according to the Airspeed Calibration (Alternate
Static Source) table in Section 5 as appropriate for vent/ heater
configuration.
1. Pitot Heat .................................................................................. ON
2. Alternate Static Source .........................................................OPEN
Pitot Tube Blocked
If only the airspeed indicator is providing erroneous information, and in
icing conditions, the most probable cause is Pitot ice. If setting Pitot
Heat ON does not correct the problem, descend to warmer air. If an
approach must be made with a blocked Pitot tube, use known pitch
and power settings and the GPS groundspeed indicator, taking
surface winds into account.
1. Pitot Heat .................................................................................. ON
Pitot Heat Current Sensor Annunciation
PITOT HEAT Caution
Pitot heat failure. Displayed when Pitot heat switch is ON and Pitot
heat current is not detected.
1. Pitot Circuit Breaker ............................................................CYCLE
2. Pitot Heat .............................................................CYCLE OFF, ON
If inadvertent icing encountered, perform Inadvertent Icing
Encounter Emergency Checklist and:
a. Airspeed .......................EXPECT NO RELIABLE INDICATION
b. Exit icing conditions using attitude, altitude, and power
instruments.
PITOT HEAT
March 2010
Cirrus Design Section 3A
SR22 Abnormal Procedures
Information Manual 3A-11
Pitot Heat Required Annunciation
PITOT HEAT REQUIRED Caution
Displayed 20 seconds after system detects OAT is less than 41°F
(5°C) and Pitot Heat Switch is OFF.
1. Pitot Heat ...................................................................................ON
Pitot Heat Required Annunciation
PITOT HEAT OFF Caution
Displayed when system detects OAT is above 41°F (5°C) and Pitot
Heat Switch is OFF.
1. Pitot Heat ...................................................................................ON
PITOT HT RQD
PITOT HT OFF
March 2010
3A-12 Information Manual
Section 3A Cirrus Design
Abnormal Procedures SR22
Flight Control System
Electric Trim/Autopilot Failure
Any failure or malfunction of the electric trim or autopilot can be overridden
by use of the control yoke. If runaway trim is the problem, deenergize
the circuit by pulling the appropriate circuit breakers and land
as soon as conditions permit.
1. Airplane Control ......................................... MAINTAIN MANUALLY
2. Autopilot (if engaged) .................................................DISENGAGE
If Problem Is Not Corrected:
3. Circuit Breakers............................................ PULL AS REQUIRED
• PITCH TRIM
• ROLL TRIM
• YAW SERVO
• AP SERVOS
4. Power Lever ........................................................... AS REQUIRED
5. Control Yoke................................. MANUALLY HOLD PRESSURE
6. Land as soon as practical.
Flap System Exceedance
FLAPS Caution
Flaps are extended beyond airspeed limitations.
Flaps at 100%, airspeed greater than 109 KIAS for 5 seconds or more,
OR
Flaps at 50%, airspeed greater than 124 KIAS for 5 seconds or more.
1. Airspeed...........................................................................REDUCE
or
1. Flaps ..............................................................................RETRACT
FLAPS
March 2010
Cirrus Design Section 3A
SR22 Abnormal Procedures
Information Manual 3A-13
Landing Gear System
Brake Failure During Taxi
Ground steering is accomplished by differential braking. However,
increasing power may allow some rudder control due to increased
groundspeed and airflow over the rudder.
　
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