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The engine fuel pumps always supply more fuel than the fuel injection system can use. The
unwanted fuel is hot. It flows back to the right fuel tank and though the cooling loop. Heat transfers
from the return fuel to the cold fuel in the tank. The return fuel flows from the cooling loop to the left
tank. The return fuel mixes with the fuel in the left tank.
This process keeps the Diesel fuel warm in both tanks when the airplane operates in cold
conditions.
As the engine uses fuel, the fuel level in the left tank decreases. Air flows in through the vent
system to fill the space left by the fuel. This prevents the tank pressure from decreasing to less than
atmospheric pressure. It allows the engine pumps to continue to take fuel from the tank.
B. Fuel Transfer
As the engine uses fuel, the fuel level in the left tank decreases. The fuel level in the right tank does
not change. To balance the tank contents, the electric transfer pump moves fuel from the right tank
to the left tank. It is operated through a switch (marked FUEL TRANS ³) on the left of the
instrument panel. A status light (FUEL TRANS) on the annunciator panel is illuminated as long as
the fuel transfer pump is running.
The high fuel sensor in the left tank outer top corner automatically switches off the fuel transfer
pump when the fuel level is high in the left tank. The low fuel sensor in the right tank inner bottom
corner automatically switches off the fuel transfer pump when the fuel level is low in the right tank.
C. Emergency Operation
In an emergency (for example, the transfer pump fails) you can set the emergency fuel valve to
connect the right tank transfer line to the fuel supply line. This is the EMERGENCY setting. The
engine takes fuel from the right tank. However, the return fuel still flows through the cooling loop
to the left tank. As fuel is used from the right tank, the level of fuel in the left tank will slowly
increase.
AIRCRAFT
DA 40 Series
AMM
Fuel System
Doc # 6.02.01
Rev. 5 28-01-00 Page 5
20 Sep 2007
D. Shut-off Valve Function
During the usual operation, the shut-off function of the emergency fuel valve is used only to isolate
the fuel system when the engine is not operating. In an emergency, the shut-off valve function is
used to stop all fuel flow to the engine.
E. Refueling
Add fuel to the system through the fuel fillers on top of each wing. Fuel flows down the large filler
tube to the related tank. Air in the tank can escape back past the fuel. As the tank becomes full, the
air can also escape through the hoses between the tank and the fuel filler.
F. Fuel Drains
You can use the fuel drain valve in each tank and the drain valve in the gascolator to defuel the
airplane. Also use it to drain a small quantity of fuel to test for water or other contamination. Push
the bottom part of the valve up to release fuel. A spring inside the valve closes it automatically.
AIRCRAFT
Fuel System
DA 40 Series
AMM
Page 6
20 Sep 2007 28-01-00 Doc # 6.02.01
Rev. 5
Intentionally left blank
AIRCRAFT
DA 40 Series
AMM
Fuel System
Doc # 6.02.01
Rev. 5 28-10-00 Page 1
20 Sep 2007
Section 28-10
Fuel Storage System - Lycoming Engine
1. General
This Section tells you about the fuel storage system for airplanes with the Lycoming engine installed.
It tells you about these components:
) Inboard fuel chambers.
) Outboard fuel chambers.
) Long range fuel chambers (only if the optional Long Range Tanks are installed, see OÄM 40-071).
) Fuel tank vents.
Refer to Section 28-00 for a general description of the fuel system and a schematic diagram of the fuel
system.
AIRCRAFT
Fuel System
DA 40 Series
AMM
Page 2
20 Sep 2007 28-10-00 Doc # 6.02.01
Rev. 5
Capillary Balance Hose
Check Valve
Tank Filler
Vent Hose
Flexible Coupling
Balance/Vent Hoses
Outboard Fuel Chamber
Inboard Fuel Chamber
Finger Filter
Outlet Hose
Outlet Hose
from Left Tanks
Figure 1: Fuel Tank System in the Right Wing, Standard Tanks Installed
AIRCRAFT
DA 40 Series
AMM
Fuel System
Doc # 6.02.01
Rev. 5 28-10-00 Page 3
20 Sep 2007
2. Description
A. Standard Tanks
Figure 1 shows the fuel tank system in the right wing. The fuel tank system in the left wing is
similar.
The DA 40 has a fuel tank in each wing. Each wing tank is made of two chambers: the inboard fuel
chamber and the outboard fuel chamber. The inboard fuel chamber and the outboard fuel chamber
are interconnected. Aluminum makes the fuel chambers. Baffles in the chambers prevent the fuel
　
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