SOLOY TURBINE PAC
SECTION 7
POHS CESSNA T206H/206H
AIRPLANE & SYSTEMS
DESCRIPTION
7-14
F.A.A. Approved
May 23, 2003
FUEL SYSTEM
The fuel system, see Figure 7-2, consists of left and right vented fuel
tanks, two fuel reservoir tanks, a fuel selector valve, airframe mounted
fuel filter, engine driven fuel pump, fuel system quantity and flow
instrumentation.
Existing Warning, Note and Figure 7-6 Fuel Quantity Data in U.S.
Gallons” are still applicable.
FUEL DISTRIBUTION
Fuel flows by gravity from the two wing tanks to two reservoir
tanks to a four position selector valve. From the selector valve,
fuel flows through the fuel temperature transducer fitting, the
airframe fuel filter and to the engine driven fuel pump. The fuel
then enters the fuel control unit (FCU) then through the fuel flow
transducer to the burner can fuel nozzle.
FUEL INDICATING SYSTEM
The fuel indicating system remains unchanged except the
replacement of the fuel flow measurement system with the
following information.
A fuel totalizer system is also installed. The totalizer displays a
continuous readout of total fuel flow in pounds per hours, time
remaining in hours and minutes and fuel temperature in degrees
fahrenheit. Other features of the system include fuel remaining in
pounds, fuel used in pounds, fuel temperature in degrees C, and
a low fuel warning system that flashes when there are less than
45 minutes of fuel remaining.
FUEL FLOW INSTRUMENT OPERATING DETAILS
NOTE
The accuracy of the fuel totalizer system is totally
dependent upon the accurate entry of data by the
pilot, the following procedure should be followed.
LIMITATIONS
All computations are based on Jet A fuel with a density of 6.71
lb./gal. at 80
F. If JP-5, JP-4, Jet B or AVGAS/JET A mixture is
used, the following procedures should be followed.
1. The time remaining function is considered inaccurate.
UNCONTROLLED
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