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DA 40 Series
AMM
Fuel System
Doc # 6.02.01
Rev. 5 28-00-00 Page 5
20 Sep 2007
B. Long Range Tanks (OÄM 40.071)
Figure 2 shows the fuel system schematic diagram for the DA 40 with the Lycoming engine and the
Long Range Tanks installed.
An inboard chamber, an outboard chamber and a long rang chamber in each wing hold the fuel.
Flexible couplings connect the individual chambers. Each long range chamber has a fuel filler
assembly and a vent connection. Each inboard chamber has a fuel drain and a finger-filter at the
connection to the main fuel feed pipe. Fuel level sensors and probes are installed in each inboard
chamber. Additional fuel probes are installed in each long range fuel chamber.
Flexible hoses connect the fuel tanks in the wings to the fuel selector valve in the center fuselage.
A gascolator attaches to the selector valve. The gascolator has a filter and a fuel drain valve. A
flexible hose connects the gascolator to the electric fuel pump (booster pump). The electric fuel
pump has an internal fuel by-pass should the fuel pump become defective in flight.
A flexible hose connects the booster pump to a bulkhead fitting in the firewall and another flexible
hose connects the bulkhead fitting to the engine driven fuel pump.
Vent pipes connect between each individual fuel chamber. The long range fuel chambers are
vented to atmosphere. Check valves in the vent system prevent fuel from flowing out of the long
range fuel chamber through the vent system.
The long range fuel chambers also have a small capillary tube which connects to atmosphere.
These capillary tubes allow the air pressure within the tanks to equalize with the ambient pressure.
The outlets for both the main vent system and the capillary vent system are on the fuel tank outer
access panel in the lower surface of each wing.
AIRCRAFT
Fuel System
DA 40 Series
AMM
Page 6
20 Sep 2007 28-00-00 Doc # 6.02.01
Rev. 5
3. Operation
With the engine running and the fuel system controls set as follows:
) Electrical fuel pump (booster pump) set to ON.
) Fuel-selector valve set to LEFT or RIGHT.
Fuel flows from the left tank or from the right tank, through finger-filters to the fuel selector valve. The
vents system allows air to flow into the tanks from atmosphere, check valves in the vent system
prevent fuel from flowing out of the tanks through the vents.
The fuel flows from the fuel selector valve through the gascolator filter to the electric fuel pump. Fuel
flows from the pump under pressure to the engine driven fuel pump.
If you set the electric fuel pump to OFF, then an internal by-pass will allow the fuel to flow through the
electric fuel pump to the engine driven fuel pump. The engine can run.
If you set the fuel selector valve to RIGHT then fuel will only flow from the right tank.
If you set the fuel selector valve to LEFT then fuel will only flow from the left tank.
If you set the fuel selector valve to OFF then fuel will not flow from the left tank or the right tank. The
engine will not run.
Both of the inboard fuel chambers and both of the long range fuel chambers (if the Long Range Tanks
are installed) have fuel probes. The signals from the fuel probes are used to set a value on an
indicator. The indicator is located in the instrument panel, right side.
Both of the inboard fuel chambers have additional fuel sensors. The signals from the fuel sensors
operate a low fuel caution light on the annunciator panel.
AIRCRAFT
DA 40 Series
AMM
Fuel System
Doc # 6.02.01
Rev. 5 28-01-00 Page 1
20 Sep 2007
Section 28-01
Fuel System - TAE 125 Diesel Engine
1. General
This Chapter tells you about the DA 40 airplane fuel system with the TAE 125 Diesel engine installed.
It does not tell you about the engine fuel system. For more data on the engine fuel system refer to the
TAE 125 Operation and Maintenance Manual.
The DA 40 has a fuel tank in each wing. The total usable fuel capacity of the fuel system is 28 US gal
(106 liters). Two engine-mounted pumps supply fuel to the engine and a filter gives protection to
sensitive components. An electric transfer pump moves fuel from the right wing to the left wing as
necessary.
The pilot controls the fuel system with a switch for the electric fuel pump. An emergency fuel valve
provides a backup system for fuel transfer. A fuel quantity indicator shows the quantity of fuel in the
tanks. Refer to these Sections for more data on these systems:
Section 28-11 Fuel storage.
Section 28-21 Fuel distribution.
Section 28-41 Fuel indication.
Section 73-01 Engine fuel system.
Note: Equipment which is certified for installation in the DA 40 is listed in Section 6.5 of
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钻石40系列AMM 2(14)
