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However, the BAT 1 and BAT 2 switches can be turned 'on' separately
to check equipment while on the ground. Setting only the BAT 2 switch
'on' will energize those systems connected to the circuit breaker
panel’s ESS BUS 1 and ESS BUS 2. If any system on the other buses
is energized, a failure of the Distribution Bus interconnect isolation
diode is indicated. When the BAT 1 switch is set to 'on,' the remaining
systems will be energized. To check or use non-essential avionics
equipment or radios while on the ground, the AVIONICS power switch
must also be turned on.
Alternator Switches
The ALT 1 and ALT 2 switches control field power to the respective
alternator. For ALT 1 to start, the BAT 1 switch must be 'on'. Setting the
ALT 1 switch 'on' energizes a relay allowing 28 VDC from the 5 amp
ALT 1 circuit breaker on A/C BUS 1 to be applied to a voltage regulator
for ALT 1. For ALT 2 to start, either the BAT 1 switch or the BAT 2
switch must be 'on.' Setting the ALT 2 switch 'on' energizes a relay
allowing 28 VDC from the 5 amp ALT 2 circuit breaker on ESS BUS 2
to be applied to voltage regulator for ALT 2. Positioning either ALT
switch to the OFF position removes the affected alternator from the
electrical system.
• Caution •
Continued operation with the alternators switched off will
reduce battery power enough to open the battery relay,
remove power from the alternator field, and prevent alternator
restart.
March 2010
7-52 Information Manual
Section 7 Cirrus Design
Airplane and Systems Description SR22
Avionics Power Switch
A rocker switch, labeled AVIONICS, controls electrical power from the
circuit breaker panel (MAIN BUS 1) to the Avionics Bus. The switch is
located next to the ALT and BAT Master switches. Typically, the switch
is used to energize or de-energize all non-essential avionics on the
AVIONICS bus simultaneously. With the switch in the OFF position, no
electrical power will be applied to the non-essential avionics
equipment, regardless of the position of the MASTER switch or the
individual equipment switches. For normal operations, the AVIONICS
switch should be placed in the OFF position prior to activating the
MASTER switches, starting the engine, or applying an external power
source.
Ground Service Receptacle
A ground service receptacle is located just aft of the cowl on the left
side of the airplane. This receptacle is installed to permit the use of an
external power source for cold weather starting and maintenance
procedures requiring reliable power for an extended period. The
external power source must be regulated to 28 VDC. The external
power control contactor is wired through the BAT 1 MASTER switch so
that the BAT 1 switch must be 'on' to apply external power.
Refer to Section 8, Ground Handling, Servicing, and Maintenance, for
use of external power and special precautions to be followed.
March 2010
Cirrus Design Section 7
SR22 Airplane and Systems Description
Information Manual 7-53
Electrical Indicating
Electrical system information is displayed as bar graphs and text on
the MFD’s ENGINE page. When the ENGINE page is not active or in
the case of an electronic display failure (backup mode), Battery 1
ampere output and Essential Bus voltage output are displayed along
the LH edge of the display. Electrical data is acquired by the Engine
Airframe Unit which transmits the data to the Engine Indicating System
for display as described in the following pages.
• Note •
A “Red X” through any electronic display field indicates that
the display field is not receiving valid data and should be
considered inoperative.
Electrical System Annunciations
Electrical system health, caution, and warning messages are
displayed in color-coded text in the Crew Alerting System (CAS)
window located to the right of the Altimeter and Vertical Speed
Indicator. In combination with a CAS alert, the affected electrical
parameter displayed on the ENGINE page changes to the
corresponding color of CAS alert and the annuncation system issues
an audio alert.
• Note •
For specific pilot actions in response to Electrical System
Annunciations, refer to the Electrical System procedures
contained in Section 3 - Emergency Procedures, and Section
3A - Abnormal Procedures.
For additional information on Engine Instrument Markings and
Annunciations, refer to Section 2 - Limitations.
For additional information on the System Annunciations And
Alerts, refer to the Perspective Integrated Avionics System
description in this section.
　
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