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regulation, the MCU also provides external power reverse polarity
protection, alternator overvoltage protection, as well as alternator fail
June 2007
7-66 Information Manual
Section 7 Cirrus Design
Airplane Description SR22
and overcurrent annunciations. Power is distributed to the airplane
circuit panel buses through Main and Essential buses in the MCU.
During normal operation, the alternators feed their respective
Distribution Bus independently (ALT 1 feeds Main Distribution Bus and
ALT 2 feeds the Essential Distribution Bus). The distribution busses
are interconnected by two 50-amp fuses and a diode. The diode
prevents ALT 2 from feeding the Main Distribution Bus. Additionally,
since ALT 2 / Essential Distribution Bus voltage is slightly higher than
ALT 1 / Main Distribution Bus voltage, ALT 1 will not feed the Essential
Distribution Bus unless ALT 2 fails.
Power Distribution
The power distribution system for the SR22 consists of the Main
Distribution Bus and the Essential Distribution Bus in the MCU and
associated buses in the Circuit Breaker panel. The circuit breaker
panel is located on the left side of the console next to the pilots right
knee.
For normal operation, the Essential Buses in the circuit breaker panel
are powered from the Essential Distribution Bus in the MCU through
25-amp circuit breakers. BAT 2 is connected directly to the Essential
Bus in the circuit breaker panel and will power the bus should the
voltage coming from the MCU distribution buses drop below the
battery voltage. Additionally, in the event of an ALT 2 failure, the circuit
breaker panel Essential Bus will be powered from ALT 1 through the
Main distribution and Essential distribution buses in the MCU. Main
Bus 1, Main Bus 2, and the equipment Non-Essential Bus in the circuit
breaker panel are powered from ALT 1 through the Main Distribution
Bus in the MCU. The Avionics Non-Essential Bus in the circuit breaker
panel is powered from Main Bus 1.
June 2007
Information Manual 7-67
Cirrus Design Section 7
SR22 Airplane Description
Serials 0002 thru 1601, 1603 thru 1643 and 1645 thru 1662: 80A fuse.
NOTE
Serials 0002 thru 1601, 1603 thru 1643 and 1645 thru 1662: 100A fuse.
Serials 1602, 1821, 1840, 1863 & subs with optional Air Conditioning
system installed.
25A
25A
STARTER
50A
50A
125A
EXTERNAL
POWER
A/C 1
CONDENSER
A/C 2
FAN
COMPRESSOR/
CONTROL
BAT 1
SWITCH
LANDING
LIGHT
LANDING LIGHT
SWITCH
15A
30A
ALT 2
SWITCH
BAT 2 SWITCH
AVIONICS
ESSENTIAL RELAY
AVIONICS
NON-ESSENTIAL
RELAY AVIONICS
SWITCH
BAT 1
ALT 1
RELAY
FUEL OIL
ALT 1 ALT 2 PITOT
HEAT
ESSENTIAL
DIST
MAIN DIST
25A
25A
25A
25A
25A
VOLT REG
F ALT 2
B
F ALT 1
B
100A
40A
VOLT REG
GPS 2
ANNUN/ENGINE INST
MASTER CONTROL UNIT
CIRCUIT BREAKER PANEL
TURN COORD. #1
AVIONICS
ESSENTIAL
BAT 2
ALT 1
SWITCH
LOW
VOLTS
ATTITUDE #1
HSI /PFD #1
STALL WARNING
BATTERY 2
ALT 2
ESSENTIAL POWER
ESSENTIAL
AUTOPILOT
AVIONICS
COM 1
GPS 1
FUEL PUMP
TURN COORD. #2
MAIN BUS 2
ATTITUDE #2
HSI /PFD #2
CABIN LIGHTS
ALT 1
STARTER RELAY
NON-ESSENTIAL
MAIN BUS 1 AVIONICS NON-ESSENTIAL
PITOT HEAT/
COOLING FAN
12VDC OUTLET
STROBE LIGHTS
NAV LIGHTS
FLAPS
SKYWATCH/
TAWS
COM 2
ENCODER/XPONDER
WEATHER/
STORMSCOPE
AUDIO PANEL
MFD
AVIONICS
FUEL QTY/HOBBS
INST LIGHTS
PITCH TRIM
ROLL TRIM
ICE PROTECTION
SR22_FM07_1458F
Figure 7-13
Electrical System Schematic
June 2007
7-68 Information Manual
Section 7 Cirrus Design
Airplane Description SR22
BAT & ALT Master Switches
The rocker type electrical system MASTER switches are ON in the up
position and OFF in the down position. The switches, labeled BAT 2,
BAT 1, ALT 1, ALT 2 are located in the bolster switch panel
immediately below the instrument panel. These switches, along with
the AVIONICS power switch, control all electrical power to the
airplane.
Battery Switches
The BAT 1 and BAT 2 switches control the respective battery. Setting
the BAT 1 switch 'on' energizes a relay connecting BAT 1 to the MCU
Distribution Buses (also energizing the circuit breaker panel buses)
　
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