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the Airplane Flight Manual. Such equipment may be installed in accordance with
the Airplane Maintenance Manual.
Any equipment which is not listed in Section 6.5 of the Airplane Flight Manual is
called "Additional Equipment". The installation of Additional Equipment is a
modification which must be handled in accordance with national regulations or a
Service Bulletin.
AIRCRAFT
Fuel System
DA 40 Series
AMM
Page 2
20 Sep 2007 28-01-00 Doc # 6.02.01
Rev. 5
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M
TAE 125 Engine
TAE
Diesel
Filter
Firewall
Fuel Return Fuel Supply
Gascolator
Drain
Valve
Emergency Fuel Valve
Drain Drain
Finger Filter Finger Filter
Fuel Tank Fuel Tank
Low Fuel
High Fuel Sensor
Sensor
Low Fuel
Sensor
Check Valve
Check
Valve
(Bleed
Type)
Check
Valve
(Bleed
Type)
Fuel Filler Fuel Filler
Fuel Tank Vent Fuel Tank Vent
Relief Valve Restrictor
Wing RH Wing LH
Fuselage
Electric Transfer Pump
Fuel Quantity Probe Fuel Quantity Probe
Cooling Loop
Lightning Protection Hose
Figure 1: Fuel System Schematic Drawing
Check Valve
Check Valve
AIRCRAFT
DA 40 Series
AMM
Fuel System
Doc # 6.02.01
Rev. 5 28-01-00 Page 3
20 Sep 2007
2. Description
Figure 1 shows the fuel system schematic diagram for the DA 40 with the TAE 125 Diesel engine
installed.
A tank located inboard in each wing holds the fuel. Each tank has a fuel filler assembly and a vent
connection at the outboard end. Small diameter flexible hoses connect the top outer corner of the tank
to the top of the fuel filler just below the cap. Two short hoses connect to the fuel filler. One has a bleed
type check valve. The other has a restrictor (RH tank) or a relief valve (LH tank).
Each tank has a fuel drain and a finger-filter at the connection to the main fuel feed pipe. The outlet
from the finger filter in the right tank connects to the emergency fuel valve and the transfer pump. The
outlet from the transfer pump connects to the left tank.
Fuel level sensors and fuel quantity probes are installed in both fuel tanks. The right tank has a
transfer pump shut-off switch (low fuel sensor) located at the bottom inner corner. The left tank has
a transfer pump shut-off switch (high fuel sensor) located at the top outer corner. The left tank also has
a switch for the LOW FUEL caution light (low fuel sensor) located at the bottom inner corner.
The fuel quantity probes go from the bottom inner corner of each tank to the top outer corner. The fuel
level changes the probe electrical properties. The fuel quantity system measures the probe
capacitance. It uses the value as an analogue of fuel quantity. The value for each tank is shown on
the Auxiliary Engine Display (AED) on the right of the instrument panel.
A fuel temperature sensor is installed in each fuel tank. The LH and RH fuel temperatures are
indicated on the Auxiliary Engine Display (AED).
% To cool down the hot return fuel a fuel cooler is installed in the return line from the right tank to the left
% tank direct at the right tank. A winterization kit is provided which has to be removed above hot outside
% air temperatures.
Flexible hoses connect the fuel tanks in the wings to the emergency fuel valve and transfer pump in
the center fuselage. A gascolator attaches to the emergency fuel valve. The gascolator has a filter and
a fuel drain valve. A flexible hose connects the gascolator to the engine fuel filter mounted forward of
the firewall.
Two engine-mounted pumps supply fuel to the engine fuel injection system. A return line from the
engine connects to the right wing tank. A loop of pipe inside the right tank makes a heat exchanger
to cool the return fuel. A flexible hose connects the outlet of the loop to the left tank.
AIRCRAFT
Fuel System
DA 40 Series
AMM
Page 4
20 Sep 2007 28-01-00 Doc # 6.02.01
Rev. 5
3. Operation
A. Normal Operation
The engine pumps take fuel from the left fuel tank. Fuel flows through the finger filter to the
emergency fuel valve. From the valve it flows through the strainer in the gascolator. The gascolator
is also a water separator. The fuel flows to the main filter and the engine fuel system.
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钻石40系列AMM 2(15)
