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identical scale for the right tank. Each scale is marked with a yellow
arc from 0 to 14 U.S. gallons. The indicators are calibrated to read 0
gallons when no usable fuel remains.
March 2010
Cirrus Design Section 7
SR22 Airplane and Systems Description
Information Manual 7-43
Figure 7-9
Fuel System Controls and Indicating
8
1
2 4 5 6 7
9
Fuel System Indication
Fuel System Controls
3
LEGEND
1. Fuel Flow
2. Fuel At Destination (Totalizer)
3. Fuel Used (Totalizer)
4. Fuel Remaining (Totalizer)
5. Time Remaining (Totalizer)
6. Fuel Range (Totalizer)
7. Nautical Miles Per Gallon (Totalizer)
8. Fuel Pump Switch
9. Fuel Quantity Gage (Float Sensor)
10. Fuel Selector Valve
SR22_FM07_2803
10
Density Alt 8000 Ft
Oat 31°F -1°C (ISA +0°C)
March 2010
7-44 Information Manual
Section 7 Cirrus Design
Airplane and Systems Description SR22
Each indicator also provides an output signal to the Engine Airframe
Unit that is processed and transmitted to the CAS window for display
when the fuel quantity goes below approximately 9 gallons indicated
and remains less than this level for more than 60 seconds. The
indicator is internally lighted.
28 VDC for fuel quantity system operation is supplied through the 3-
amp FUEL QTY circuit breaker on MAIN BUS 1.
• Note •
When the fuel tanks are 1/4 full or less, prolonged
uncoordinated flight such as slips or skids can uncover the
fuel tank outlets. Therefore, if operating with one fuel tank dry
or if operating on LEFT or RIGHT tank when 1/4 full or less, do
not allow the airplane to remain in uncoordinated flight for
periods in excess of 30 seconds.
Fuel Flow
Fuel Flow is shown in the upper mid right corner of the ENGINE page
as both a simulated pressure gage and as a digital value. The gage
pointer sweeps a scale range from 0 to 30 Gallons Per Hour (GPH).
The fuel flow value is displayed in white numerals below the gage.
Fuel flow is measured by a transducer on the right side of the engine
in the fuel line between the engine driven fuel pump and distribution
block. The fuel flow signal is sent to the Engine Airframe Unit,
processed, and transmitted to the Engine Indicating System for
display.
March 2010
Cirrus Design Section 7
SR22 Airplane and Systems Description
Information Manual 7-45
Fuel Totalizer and Calculated Information
Fuel totalizer calculations are located in the lower right section of the
ENGINE page and are separate and independent of the fuel quantity
gage and float sensor system. The fuel totalizer monitors fuel flow and
calculates fuel-to-destination, fuel used, fuel remaining, time
remaining, fuel range, and nautical miles per gallon. Upon system
startup, the fuel totalizer initial fuel screen appears and prompts the
user to enter the total fuel on board at start. The option to enter the
number of gallons added since last fuel fill and the ability to set fuel to
“Full” or to “Tabs” buttons is also available.
March 2010
7-46 Information Manual
Section 7 Cirrus Design
Airplane and Systems Description SR22
Electrical System
The airplane is equipped with a two-alternator, two-battery, 28-volt
direct current (VDC) electrical system designed to reduce the risk of
electrical system faults. The system provides uninterrupted power for
avionics, flight instrumentation, lighting, and other electrically operated
and controlled systems during normal operation.
Power Generation
Primary power for the aircraft is supplied by a 28-VDC, negativeground
electrical system. The electrical power generation system
consists of two alternators controlled by a Master Control Unit (MCU)
mounted on the left side of the firewall and two batteries for starting
and electrical power storage.
Alternator 1 (ALT 1) is a gear-driven, internally rectified, 100-amp
alternator mounted on the right front of the engine. Alternator 2 (ALT 2)
is a belt-driven, internally rectified, 70-amp alternator mounted on the
front left of the engine. ALT 1 is regulated to 28 volts and ALT 2 is
regulated to 28.75 volts. Both alternators are self-exciting and require
battery voltage for field excitation in order to start up - for this reason,
the batteries should not be turned off in flight.
Storage
Battery 1 (BAT 1) is an aviation grade 12-cell, lead-acid, 24-volt, 10-
amp-hour battery mounted on the right firewall. BAT 1 is charged from
the Main Distribution Bus 1 in the MCU.
Battery 2 (BAT 2) is composed of two 12-volt, 7-amp-hour, sealed,
　
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