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headwind.
2. Land on downwind side of the runway.
3. Use the rudder for obstacle avoidance.
• Note •
Rudder effectiveness will decrease with decreasing airspeed.
4. Perform Emergency Engine Shutdown on Ground checklist.
Landing With Flat Tire
If a flat tire or tread separation occurs during takeoff and you cannot
abort, land as soon as conditions permit.
Main Gear
1. Land on the side of the runway corresponding to the good tire.
2. Maintain directional control with the brakes and rudder.
3. Do not taxi. Stop the airplane and perform a normal engine
shutdown.
Nose Gear
1. Land in the center of the runway.
2. Hold the nosewheel off the ground as long as possible.
3. Do not taxi. Stop the airplane and perform a normal engine
shutdown.
June 2007
3A-8 Information Manual
Section 3A Cirrus Design
Abnormal Procedures SR22
ANNUN/ENGINE INST
TURN
COORD. #1
ATTITUDE #1
HSI/PFD #1
STALL
WARNING
BATTERY 2
ALT 2
ESSENTIAL
POWER
AUTOPILOT
AVIONICS
COM 1
GPS 1
STARTER
RELAY
PITOT HEAT/
COOLING FAN
12VDC
OUTLET
STROBE
LIGHTS
NAV LIGHTS
FLAPS
ESSENTIAL
COM 2
ENCODER/
XPONDER
WEATHER/
STORMSCOPE
AUDIO
PANEL
MFD
AVIONICS
FUEL QTY/HOBBS
INST
LIGHTS
PITCH TRIM
ICE PROTECTION
BATT
SR22_FM03_1453C
SKYWATCH/
TAWS
ROLL TRIM
ALT 1 ALT 2
AMMETER
BAT 2
BAT 1
ALT 1 ALT 2
MAIN DISTRIBUTION
BUS
ESSENTIAL
DISTRIBUTION BUS
NON-ESSENTIAL
ESSENTIAL
MAIN BUS 1
ALT 1
CABIN
LIGHTS
HSI/PFD #2
ATTITUDE #2
TURN
COORD. #2
MAIN BUS 2
FUEL PUMP
NON-ESSENTIAL
GPS 2
Figure 3A-1
Electrical Power Distribution (Simplified)
June 2007
Information Manual 3A-9
Cirrus Design Section 3A
SR22 Abnormal Procedures
System Malfunctions
Alternator Failure
Steady illumination of either ALT caution light in the annunciator panel
indicates a failure of the corresponding alternator. The most likely the
cause of the alternator failure is a wiring fault, a malfunctioning
alternator, or a malfunctioning control unit. Usually, electrical power
malfunctions are accompanied by an excessive rate of charge or a
discharge rate shown on the ammeter.
• Caution •
Alternators in this airplane are self-exciting. These alternators
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.
Figure 3-2 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 3-2, Electrical Power Distribution, for details on electrical
busses and what components/systems they power.
(Continued on following page)
June 2007
3A-10 Information Manual
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
　
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