Specifications

7-44 P/N 11934-004
Section 7 Cirrus Design
Airplane and Systems Description SR20
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 7 gallons indicated.
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 20 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.
Original Issue