Tecnam P2010 - Fuel System

Page 7 - 18
2
nd
Edition, Rev 0
Section 7 – Airframe and Systems description
FUEL SYSTEM
8. FUEL SYSTEM
The fuel system is designed to supply the reciprocating engine (Lycoming IO-
360-M1A) with the suitable flow rate and pressure according to engine limitations
required by Lycoming operator manual.
Following figure shows a schematic of the fuel system assy for P2010 airplane.
OFF
RH
LH
LH Fuel qty indicator
RH Fuel qty indicator
RH Fuel vent
LH Fuel vent
LH Fuel tank
RH Fuel tank
RH Fuel sump
LH Fuel sump
Firewall
Gascolator
Electric
fuel pump
Mechanical
fuel pump
Vent
Vent
Injector
Nozzle pressure
connection
Fuel pressure
sensor
Fuel flow
sensor
Fuel pressure
indicator
Fuel flow
indicator
Fig. 7-14. FUEL SYSTEM SCHEME
Each fuel tank is integrated within the wing box. The capacity of each tank is 120
liters (31,7 gal.), total capacity is thus 240 liters (63.4 gal.).
The internal side of fuel tank is accessible for inspection through 4 upper dedicat-
ed caps.
Two bottom inspection panels allow the inspection of vent line and tank structure.
An anti-sloshing movable wall is located within each fuel tank, this prevents fuel
centrifugation which is a possible cause of undesired engine shut down.
The fuel tank filler cap is located on the top of the wing, in the area outside of the
tank and it is easily accessible from the leading edge of the aircraft. At the lowest
point of the tank it is positioned a drain sump.
The engine is equipped with an engine gear pumps, mechanical (primary). An ad-
ditional auxiliary electrical fuel pump is provided (auxiliary).
The fuel selector is operated by a fuel selector control knob located in the cabin on
the central panel. The fuel selector control and the fuel valve are connected via a
rigid control rod.