Sennheiser SI 234 - ANNEXE 802 Operations Instructions download pdf (Page 388)

Airplane Description DA 42 NG AFM

Page 7 - 40 Rev. 3 01-Apr-2014 Doc. No. 7.01.16-E

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.

1 2 ... 383 384 385 386 387 388 389 390 391 392 393 ... 439 440

No comments

Sennheiser SI 234 - ANNEXE 802 Operations Instructions Page 388