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If alternator does not reset:
4. Switch off unnecessary equipment on Main Bus 1, Main Bus 2,
and the Non-Essential Buses to reduce loads. Monitor voltage.
5. ALT 1 Master Switch ................................................................OFF
6. Land as soon as practical.
ALT 1 Light Flashing
Serials 0002 thru 1643 and 1645 thru 1666: The most likely cause is a
severely discharged battery along with heavy equipment loads. In this
event, reduce loads on Main and Non-Essential buses and monitor
amperage until charging rate is within normal limits. Then loads can be
added as required.
1. Ammeter Switch..................................................................... BATT
2. If charging rate is greater than 30 amps, reduce load on Main Bus
1, Main Bus 2, and Non-Essential buses.
3. Monitor ammeter until battery charge rate is less than 15 amps.
4. When battery charge rate is within limits, add loads as necessary
for flight conditions.
ALT 2 Light Steady
Except during low RPM operations, steady illumination indicates a
failure of ALT 2. If alternator cannot be brought back, Essential bus
loads will be powered from ALT 1, BAT 1, and BAT 2.
• Note •
ALT 2 light will illuminate steady and ALT 2 will not come on
line until 1700 - 2200 RPM.
1. ALT 2 Master Switch ................................................................OFF
June 2007
Information Manual 3A-11
Cirrus Design Section 3A
SR22 Abnormal Procedures
2. Alternator 2 Circuit Breaker ........................... CHECK and RESET
3. ALT 2 Master Switch ..................................................................ON
If alternator does not reset:
4. Switch off unnecessary equipment on Main Bus 1, Main Bus 2,
and Non-Essential Buses to reduce loads.
5. ALT 2 Master Switch ................................................................OFF
6. Land as soon as practical.
Engine Indicating System Failure
Serials 1644, 1663 and Subsequent: In the event of an Data
Acquisition Unit (DAU) failure, the engine indications displayed on the
MFD and PFD will be disabled. Numeric readouts will display as three
white dashes, the CHT and EGT bar graphs will be removed, and
indicator needles displayed on the simulated gages will be removed.
In the event of DAU failure, pull and reset the ANNUN / ENGINE INST
circuit breaker. If the engine indicating system fails to reset, land as
soon as practical.
1. ANNUN / ENGINE INST Circuit Breaker ...............................Cycle
2. Land as soon as practical.
LOW VOLTS Warning Light Illuminated
Illumination of the LOW VOLTS light indicates that the voltage
measured at the Essential Bus is 24.5 volts or less. Typically, this
indicates that the airplane is operating on battery power only and both
alternators have failed or are off. If both alternators have failed:
1. Land as soon as practical.
June 2007
3A-12 Information Manual
Section 3A Cirrus Design
Abnormal Procedures SR22
Communications Failure
Communications failure can occur for a variety of reasons. If, after
following the checklist procedure, communication is not restored,
proceed with FAR/AIM lost communications procedures.
• Note •
In the event of an audio panel power failure the audio panel
connects COM 1 to the pilot’s headset and speakers. Setting
the audio panel ‘Off’ will also connect COM 1 to the pilot’s
headsets and speakers.
1. Switches, Controls ............................................................. CHECK
2. Frequency ....................................................................... CHANGE
3. Circuit Breakers.................................................................. CHECK
4. Headset........................................................................... CHANGE
5. Hand Held Microphone .................................................CONNECT
June 2007
Information Manual 3A-13
Cirrus Design Section 3A
SR22 Abnormal Procedures
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.
• Note •
If selecting the alternate static source does not work, in an
emergency, cabin pressure can be supplied to the static
pressure instruments by breaking the glass in the face of the
vertical speed indicator. When static pressure is supplied
through the vertical speed indicator, the vertical speed UPDOWN
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AIRPLANE INFORMATION MANUAL for the CIRRUS DESIGN SR22(23)
