Section 7 – Airframe and Systems description
FUEL SYSTEM
8. FUEL SYSTEM
Fuel system consists of two integrated tanks inside the wing torque boxes and fit-
ted with inspection doors.
Each fuel tank has a capacity of 100 litres and is equipped with a vent valve (its
outlet is located on the lower wing skin) and a sump fitted with a drain valve for
water/moisture drainage purposes.
An electric fuel pump feeds the pertinent engine in case of engine-driven pump
failure. The fuel Gascolator (a sediment-filter bowl) is located beneath the engine
nacelle, between the fuel tank and the electrical pump, in correspondence of the
fuel system lowest point. It is fitted with a drain valve which allows for the overall
fuel line drainage.
Fuel quantity indicators and fuel pressure indicators for each engine are located on
the RH instrument panel.
In normal conditions, to supply fuel to engines, each engine pump sucks fuel from
the related tank; crossfeed is allowed by fuel valves located on the front spar and
controlled by Bowden cables from the fuel selectors located on the cabin over-
head panel.
Left fuel selector manages the left engine feeding, allowing fuel supply from the
left fuel tank or from the right one (crossfeed).
Right fuel selector manages the right engine feeding, allowing fuel supply from
the right fuel tank or from the left one (crossfeed).
Each selector can be set in OFF position only pulling and simultaneously rotating
the lever: this avoids an unintentional operation.
Use of Aviation Fuel Avgas 100LL results in greater wear of
valve seats and greater combustion deposits inside cylinders
due to higher lead content. Make reference to Rotax Mainte-
nance Manual who provides dedicated checks due to the pro-
longed use of Avgas.
System schematic is shown on the following Figure.
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