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require battery power for alternator starting; however, once
started, the alternators will provide self-generated field power
to continue operation in case of a battery failure. To assure
alternator restart power is available if the alternators fail, the
batteries should not be turned off during flight.
Serials 0002 thru 1643 and 1645 thru 1666: A flashing ALT 1 light
indicates an excessive charging rate. This could occur with a very low
BAT 1 and heavy equipment loads. Since the loads on ALT 2 are much
lower, it is unlikely that a flashing ALT 2 light could occur, even with a
very low BAT 2.
The Power Distribution Schematic shows the electrical system power
distribution. Individual loads on each circuit breaker panel bus are
shown in the same order as they are on the panel. Note that items on
the circuit breaker panel Essential buses are powered from ALT 1, ALT
2, BAT 1, and BAT 2. The circuit breaker panel Main buses and Non-
Essential buses are powered from ALT 1 and BAT 1 only.
• Note •
If it is necessary to reduce electrical loads due to an alternator
malfunction, switch off electrical components and/or systems
that are not essential for the current flight conditions rather
than pulling circuit breakers. Load shedding in this manner will
prevent accidental circuit breaker disconnection and loss of
power to flight-critical systems. See Figure Electrical Power
Distribution, for details on electrical busses and what
components/systems they power.
Revision A8
3A-10 P/N 13772-001
Section 3A Cirrus Design
Abnormal Procedures SR22
ALT 1 Light Steady
Steady illumination indicates a failure of ALT 1. Attempt to bring
alternator back on line. If alternator cannot be brought back, reduce
loads and use Main Bus or Non-Essential loads only as necessary for
flight conditions.
1. ALT 1 Master Switch ................................................................OFF
2. Alternator 1 Circuit Breaker............................ CHECK and RESET
3. ALT 1 Master Switch ................................................................. ON
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
Revision A5
P/N 13772-001 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.
　
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