7-44 P/N 13772-003
Section 7 Cirrus Design
Airplane and Systems Description SR22T
Fuel Quantity Gage
A dual reading 2¼” fuel quantity gage is installed on the console
immediately forward of the fuel selector valve. The LEFT pointer
indicates left tank fuel quantity and sweeps a scale marked from 0 to
46 U.S. gallons in 5-gallon increments. The RIGHT pointer sweeps an
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 and are internally lighted.
The fuel quantity gage provides output signals to the Engine Airframe
Unit based on the float sensor positions in the fuel tanks. The output
signals are processed and transmitted to the CAS window for display.
• An white Advisory message is generated when either fuel tank
goes below 14 gallons.
• A amber Caution message is generated when both fuel tanks go
below 14 gallons.
• A red Warning message is generated when the fuel totalizer
amount goes below 9 gallons. Note that the Warning message is
generated based on the fuel totalizer which is dependent on
correct input by the pilot.
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 gage and as a digital value. The gage pointer
sweeps a scale range from 0 to 45 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.
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