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(1) Move the tank assembly into position in the wing. Make sure that the tank assembly is
correctly located.
(2) Install the fuel filler assembly:
S Install a new O-ring seal on the fuel filler
flange.
S Make sure that the mounting in the fuel filler
assembly is correctly aligned with the hole in
the top surface of the wing.
S Install a new O-ring seal in position on the top
surface of the wing.
S Apply a thin layer of sealant to the contact
area between the fuel filler flange and the ring
for the filler cap.
S Put the ring for the filler cap in position over
the filler flange.
S Install the 8 screws which attach the fuel filler
and the ring for the filler cap to the wing.
S When all of the screws are installed, then
tighten the screws.
If necessary, move the tank assembly to
give correct alignment.
Make sure that the O-ring is correctly
positioned.
Use DP 300 or equivalent.
Finger tight only.
Tighten opposite screws.
AIRCRAFT
Fuel System
DA 40 Series
AMM
Detail Steps/Work Items Key Items/References
Page 208
20 Sep 2007 28-11-00 Doc # 6.02.01
Rev. 5
(3) Connect two the vent hoses to the adapters on
the access panel:
S Push the vent hoses onto the adapters on the
access panel.
S Install the clamps which hold the vent hoses
to the adapters on the access panel.
Near the outboard end of the fuel filler
assembly.
(4) Connect the bonding cable to the fuel filler
assembly.
(5) Install the access panel on the bottom surface of
the wing.
Refer to Section 52-40.
(6) Attach the bonding strip to the inboard end of the
tank:
S Put the bolt up through the bonding tag on
the inboard tank.
S Move the bonding cable into position on the
bolt.
S Install the washer and nut onto the bolt.
S Tighten the bolt.
(7) Connect these electrical connectors:
S Fuel quantity probe.
S Low fuel sensor.
S High fuel sensor (left wing only).
S Fuel temperature sensor.
At the inboard end of the tank.
At the in-line connector.
(8) Install the access panel at the wing root rib:
S Put the access panel into position on the
studs.
% S If access panel is made from aluminium
% (DA4-5741-26-00_2) install bonding cable.
S Install the 11 washers and nuts.
S Tighten the nuts.
%
% Install on 3rd bolt from bottom aft corner.
AIRCRAFT
DA 40 Series
AMM
Fuel System
Detail Steps/Work Items Key Items/References
Doc # 6.02.01
Rev. 5 28-11-00 Page 209
20 Sep 2007
(9) Install the drain valve:
S Install a new O-ring onto the drain valve
assembly.
S Install the drain valve assembly into the
mounting at the bottom of the inboard tank.
S Secure the drain valve assembly with lockwire.
S Install the access panel. Refer to Section 52-40.
(10) Install the wing onto the airplane. Refer to Section 57-10.
(11) Refuel the airplane. Refer to Section 12-10. Look specially
for fuel leaks from the tanks assembly
which you have installed.
(12) Do an engine ground test. Refer to Section 71-01.
AIRCRAFT
Fuel System
DA 40 Series
AMM
Page 210
20 Sep 2007 28-11-00 Doc # 6.02.01
Rev. 5
Intentionally left blank
AIRCRAFT
DA 40 Series
AMM
Fuel System
Doc # 6.02.01
Rev. 5 28-20-00 Page 1
20 Sep 2007
Section 28-20
Fuel Distribution System - Lycoming Engine
1. General
This Section tells you about the fuel distribution system for airplanes with the Lycoming engine
installed. The fuel distribution system supplies fuel from the fuel tanks to the engine. This Section tells
you about the components and equipment which make the fuel distribution system. These are the
components of the fuel distribution system:
) Flexible fuel hoses.
) Fuel selector/shut-off valve.
) Fuel gascolator and filter.
) Electric fuel pump (booster pump).
Refer to Section 28-00 for a general description of the fuel system and for the schematic diagram of
the fuel system.
AIRCRAFT
Fuel System
DA 40 Series
AMM
Page 2
20 Sep 2007 28-20-00 Doc # 6.02.01
Rev. 5
Fuel Selector Control Lever
Safety Lock
Connecting Shaft
Fuel Selector Valve
Selector Valve Operating Head
Flexible Hose from Left Wing
Electric Fuel Pump
Gascolator
Flexible Hose from Right Wing
Figure 1: Fuel Distribution System Main Components
AIRCRAFT
DA 40 Series
AMM
Fuel System
Doc # 6.02.01
Rev. 5 28-20-00 Page 3
　
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