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A gascolator sits at the lowest point in the fuel system. A drain valve is fitted to the gascolator, which can be used to remove water and sediment which has collected in the fuel system. This valve is fitted centrally on the underside of the fuselage, approximately 30 cm (1 ft) forward of the wing leading edge.
A capacity probe measures the fuel quantity in each tank. The AED shows only counts. The indication is non-linear, therefore proportional calculations to determine the remaining fuel quantity or direct calculations of fuel consumption are not possible. Information about the fuel consumption can be found in Chapter 5 (PERFORMANCE).
Long Range Tank
If the Long Range Tank is installed, the filler tube of the main and the auxiliary tank is replaced by another tank chamber. This tank chamber has a capacity of approx. 5 US gal (19 liters). The ventilation system of the main and the auxiliary tank remains unchanged.
A capacity probe ascertains fuel quantity in the Long Range Tank. When the fuel quantity indicator reads zero, only the unusable fuel remains in the tank. The useable capacity of each tank is 19.5 US gal, the maximum quantity that can be indicated is 15 US gal. Up to an actual quantity of 15 US gal the indication is correct. At an actual quantity above 15 US gal the indication remains at 15 US gal.
NOTE
When the fuel quantity indicator reads 15 US gal, the correct fuel quantity must be determined with the alternate mean for fuel quantity indication. If this measurement is not carried out, the fuel quantity available for flight planning is 15 US gal.
Doc. No. 6.01.05-E Revision 3 26-May-2003 Page 7 - 33
Alternate mean for fuel quantity indication for the Standard Tank
The alternate mean for fuel quantity indication allows the fuel quantity in the tank to be determined during the pre-flight inspection. It functions according to the principle of communicating containers. The fuel quantity measuring device has a recess which fits the airfoil of the wing. With this recess the device is held against the stall strip at the leading edge of the wing. The exact position is marked by a bore in the stall strip. Then the metal connector is pressed against the drain of the tank. The amount of fuel in the tank can now be read off from the vertical ascending pipe.
For an exact indication the airplane must stand on a horizontal ground.
The designated place for the fuel quantity measuring device is the bag on the rear side of the pilot seat.
Doc. No. 6.01.05-E Revision 3 26-May-2003 Page 7 - 34
DA 40 D AFM Airplane Description
Alternate Mean for fuel quantity indication for Long Range Tank
Doc. No. 6.01.05-E
Revision 3 26-May-2003
Page 7 - 35
7.9.6 COOLING SYSTEM
The water cooling systemconsists of a radiator and a bypass to this radiator. The bypass cooler is in operation when coolant temperatures are low. It therefore allows a warm-up of the engine. Upon reaching a certain temperature (approximately 80 °C) the radiator is activated by a thermostat valve. Additionally a coolant to air heat exchanger is provided for the cabin heat system. The flow through the heat exchanger is independent of the coolant temperature. An expansion tank helps to adjust the pressure in the system. The system is protected against overpressure by means of a pressure relief valve.
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