Pilot’s Operating Handbook Section 7
EXTRA 500 Description of Airplane and Systems
7.16.g Fuel Quantity Indicating System
The fuel quantity is measured by means of a float sensor
system. Six sensors, three on each side of the wing are installed
at the wing root rib (collector compartment) and on the access
covers of the main and auxiliary compartments. Behind every
sensor stands an analog indicator, directly connected. In
addition, there are two yellow FUEL LOW LEFT and FUEL
LOW RIGHT caution lights located on the annunciator panel,
which will illuminate when the pilot has at least 5 minutes of
fuel on the appropriate tank. In case only one FUEL LOW light
illuminates the pilot has to switch to the other tank.
Note When the collector compartment indication shows zero in
level flight, the remaining 14 l (3.7 U.S. Gallons) unusable
fuel in this compartment cannot be used safely in flight.
7.16.h Fuel Flow Transducer
In addition, a fuel flow transducer is installed upstream of the
fuel inlet of the engine. The relevant indicator is installed on the
instrument panel. It is fully independent of the fuel tank
quantity display.
Note For fuel calculations concerning fuel flow, fuel quantity and
flight endurance, the SHADIN MINIFLO-L computer
system can be applied. For further information refer to
Supplement 905 of this POH.
7.16.i Fuel Pressure/Temperature
Fuel pressure and temperature are displayed by two indicators
located at the instrument panel. The fuel pressure is measured
directly before the engine driven fuel pump and downstream of
the engine fuel filter.
The fuel temperature is measured in the fuel feed line, before
entering the engine compartment. Thus to make sure, that the
temperature measured is always on the low side.
26. January 2011 7-47
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