Diamond DA 62, Flight Manual

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DA 62 AFM Airplane Description
Main Fuel Tanks
Each tank consists of three aluminum chambers which are connected by a flexible hose.
The tank is filled through a filler in the outboard fuel chamber. Only four liters (1 US gal)
of fuel in each wing are unusable, so that a total quantity of 96 liters (25.4 US gal) in each
wing is usable.
There are two tank vents. One includes a check valve with a capillary, and one includes
a pressure relief valve (bleed type), which operates at 150 mbar (2 PSI) and allows fuel
and air to flow to the outside with higher internal pressure. The pressure relief valve
protects the tank against high pressure, if the tank was overfilled, in case of an auxiliary
fuel transfer failure. The check valve with capillary allows air to enter the tank but prevents
flow of fuel to the outside. The capillary equalizes the air pressure during climb. The hose
terminals are located on the underside of the wing, approximately 2 meters (7 ft) from
the wing tip.
In each tank a coarse filter (finger filter) is fitted before the outlet. To allow draining of
the tank, a drain valve is located at the lowest point of the fuel tank.
At the lowest point on each side of the fuel system, a fuel filter with a drain valve is
installed. This drain valve can be used to remove water and sediment which has collected
in the fuel system. The drain valves are fitted in each nacelle behind the firewall,
approximately 15 cm (0.56 ft) backward of the wing leading edge.
Fuel Quantity Indication
Two capacity probes measure the fuel quantity in each main tank. The indication is
provided by the G1000 flight display. Information about fuel consumption can be found
in Chapter 5 - PERFORMANCE.
Doc. No. 11.01.05-E Rev. 0 11-Jan-2019 Page 7 - 47