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not tell you about the engine fuel system. For more data on the engine fuel system refer to the
Lycoming Maintenance Manual.
The DA 40 has a fuel tank in each wing. Each wing tank is made of the following two or three
chambers:
) the inboard fuel chamber,
) the outboard fuel chamber, and
) the long range chamber (only if the Long Range Tank is installed, see OÄM 40-071).
All individual chambers are interconnected. The total usable fuel capacity of the fuel system is 152
liters (40 US gal) with the Standard Tank and 182 liters (48 US gal) with the optional Long Range Tank
installed. Two pumps supply fuel to the engine and a filter gives protection to sensitive components.
The pilot controls the fuel system with a selector valve and a switch for the electric fuel pump. A fuel
quantity indicator shows the quantity of fuel in the left tanks and in the right tanks. Refer to these
Sections for more data on these systems:
Section 28-10 Fuel storage.
Section 28-20 Fuel distribution.
Section 28-40 Fuel indication.
Note: Equipment which is certified for installation in the DA 40 is listed in Section 6.5 of
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 28-00-00 Doc # 6.02.01
Rev. 5
FP
FF
M
M
Fuel Pump
Overboard
Vent
To Cylinder 4 To Cylinder 3
To Cylinder 2 Cylinder 1
Fuel Flow Divider
Intake
Drain
Drain Valve
Fuel
Pressure
Indicator
Fuel Flow
Indicator
Engine Driven
Fuel Pump
Fuel Injector with Strainer
and Metering Unit
Fire Wall
Engine
Fuselage
Electric
Boost Pump
Overboard Vent
Fuel Selector/Shut-Off Valve
Capillary
Check
Valve
Wing RH
Inboard
Fuel Chamber
Inboard
Fuel Chamber
Outboard
Fuel Chamber
Outboard
Fuel Chamber
Fuel Level Probe Fuel Level Probe
Fuel Drain Fuel Drain
Finger Filter Finger Filter
Wing LH
Capillary
Check
Valve
Fuel Filter/Strainer (Gascolator)
Drain
Fuel Filler Fuel Filler
Fuel Flow Divider
Vent
Low
Fuel
Sens.
Figure 1: Fuel System Schematic Diagram, Standard Tanks Installed
AIRCRAFT
DA 40 Series
AMM
Fuel System
Doc # 6.02.01
Rev. 5 28-00-00 Page 3
20 Sep 2007
2. Description
A. Standard Tanks
Figure 1 shows the fuel system schematic diagram for the DA 40 with the Lycoming engine and the
Standard Tanks installed.
An inboard chamber and an outboard chamber in each wing hold the fuel. A flexible coupling
connects the inboard chamber to the outboard chamber. Each outboard 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 both the
inboard fuel chambers.
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 the inboard chambers and the outboard chambers. The outboard
chambers are vented to atmosphere. Check valves in the vent system prevent fuel from flowing out
of the outboard chamber through the vent system.
The outboard 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 4
20 Sep 2007 28-00-00 Doc # 6.02.01
Rev. 5
Figure 2: Fuel System Schematic Diagram, Long Range Tanks Installed (OÄM 40-071)
AIRCRAFT
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钻石40系列AMM 2(13)
