Tecnam P2002 JF - Fuel System; Chapter 28; Description and Operation

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Edition – Rev 0
28-10
FUEL SYSTEM – DESCRIPTION AND OPERATION
28-10 FUEL SYSTEM
DESCRIPTION AND OPERATION
Fuel system is designed to supply fuel to the engine with suitable fuel flow rate and pressure for the
whole of certified flight envelope.
The fuel system is equipped with two aluminum fuel tanks integrated within the wing box and
accessible for inspection through dedicated inspection doors.
A multi-position fuel selector valve is located into the cabin. A gascolator with a drainage valve is
located on the firewall. Fuel level indicators, one for each tank and fuel pressure indicator are
located on instrument panel. Fuel feed is through an engine-driven mechanical pump (which is part
of the engine) and also through an electric pump that supplies adequate engine feed in case of main
pump failure.
Only a part of the fuel flow entering the engine-driven mechanical pump is delivered to the
combustion chambers. The return flow is conveyed in the left fuel tank through the return line.
Fuel System is constituted by the following main equipment installed:
 Fuel tanks (two, one for each wing box)
 Emergency electric fuel pump
 Fuel level transducers
 Fuel pressure transducers
 Fuel valves
 Gascolator
 Fuel filters (Located into Gascolator, into fuel pump and on fuel feeding pipe)
In the cockpit are located the following monitoring devices and controls:
 Electric fuel pump switch
 Fuel quantity indicators (two, one for each tank)
 Fuel pressure indicator
 Fuel selector valve (LEFT/RIGHT/OFF)
The fuel system general layout is shown in Figure 1