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(1) Make sure that there is fuel in both wing tanks.
(2) Disconnect the fuel hose from the emergency
fuel valve to the fuel filter.
% Cut the lock wire at the fuel filter, 'tank'
port.
Put a cap on the open fuel filter port.
(3) Connect an external fuel pump to the open
hose.
(4) Make sure that the emergency fuel valve is in
the NORMAL position.
(5) Switch the external fuel pump ON. The external fuel pump must draw fuel
from the left tank (main tank).
Catch fuel in a suitable container.
(6) Set the emergency fuel valve to EMERG.
TRANSFER.
Break the seal.
The external fuel pump must draw fuel
from the right tank (auxiliary tank).
(7) Set the emergency fuel valve to OFF. The external fuel pump must NOT draw
any fuel.
(8) Switch the external fuel pump OFF.
(9) Disconnect the hose from the external fuel
pump.
(10) Re-connect hose from emergency fuel valve to
fuel filter.
% (11) Secure the fuel hose with new lock wire.
(12) Set the emergency fuel valve to NORMAL.
(13) Replace the seal on the emergency fuel valve
handle.
Use two strands of locking wire. Use
tinned annealed copper, RS components
P/N 390-555 or equivalent.
(14) Bleed the fuel distribution system. Refer to Paragraph 8.
AIRCRAFT
Fuel System
DA 40 Series
AMM
Page 212
20 Sep 2007 28-21-00 Doc # 6.02.01
Rev. 5
8. Test the Check Valve in the Fuel Return Line
CAUTION: YOU MUST REPLACE THE CHECK VALVE IF THE TEST FAILS.
Detail Steps/Work Items Key Items/References
(1) Make sure that the left fuel tank (main tank) is
full. (Refer to Section 12-10).
% (2) Disconnect the fuel return line from the fuel filter. Cut the lock wire at the fuel filter.
(3) Connect an external fuel pump to the open hose.
(4) Switch the external fuel pump ON. The external fuel pump must NOT draw
any fuel.
(5) Switch the external fuel pump OFF.
(6) Disconnect the hose from the external fuel pump.
% (7) Secure the fuel hose with new lock wire.
(8) Re-connect return line to fuel filter.
(9) Bleed the fuel distribution system Refer to Paragraph 8.
AIRCRAFT
DA 40 Series
AMM
Fuel System
Doc # 6.02.01
Rev. 5 28-21-00 Page 213
20 Sep 2007
9. Bleed the Fuel Distribution System
Detail Steps/Work Items Key Items/References
(1) Disconnect the fuel hose from the intake side of
the low-pressure fuel pump.
At the upper right side of the engine.
% Cut the lock wire.
Put a cap on the pump intake.
(2) Connect the open fuel hose to an external fuel
pump.
% Use a transparent hose in between fuel
% system and pump.
(3) Switch the external fuel pump ON until fuel with
no air is pumped.
Collect the fuel in a suitable container.
% Check for air in the transparent hose.
(4) Disconnect the fuel hose from the external fuel
pump.
(5) Connect the fuel hose to the intake side of the
low-pressure fuel pump.
At the upper right side of the engine.
Torque: 17 - 22 Nm (12.5 - 16.2 ftlb)
% CAUTION: MAKE SURE TO TIGHTEN THE FUEL HOSE TO THE LOW%
PRESSURE FUEL PUMP WITH THE CORRECT TORQUE. SINCE THE
% PRESSURE IN THE FUEL HOSE IS LOWER THAN THE AMBIENT AIR
% PRESSURE, A LEAK WILL ALLOW AIR TO ENTER THE FUEL
% SYSTEM. THIS LEADS TO A REDUCTION OF ENGINE POWER AND
% MAY CAUSE AN ENGINE FAILURE.
% NOTE: DUE TO THE DIFFERENTIAL PRESSURE A POSSIBLE LEAK IS NOT
% DETECTABLE THROUGH FUEL LEAKAGE NEXT TO THE
% CONNECTOR.
% (6) Secure the fuel hose with new lock wire.
AIRCRAFT
Fuel System
DA 40 Series
AMM
Page 214
20 Sep 2007 28-21-00 Doc # 6.02.01
Rev. 5
Intentionally left blank
AIRCRAFT
DA 40 Series
AMM
Fuel System
Doc # 6.02.01
Rev. 5 28-40-00 Page 1
20 Sep 2007
Section 28-40
Fuel Quantity Indicating - Lycoming Engine
1. General
This Section tells you about the fuel quantity indicating system of the DA 40 with the Lycoming engine
installed. Refer to Section 28-00 for the general data on the fuel system and refer to Section 31-10 for
data on replacing the fuel quantity indicator.
2. Description
A. Standard Tanks
Figure 1 shows the fuel quantity indication system main components for the Standard Tanks. The
fuel quantity indicator is part of the integrated engine indicating system. The inboard fuel tank in each
wing has a fuel probe and a fuel sensor. The fuel quantity indicating system cannot be calibrated in
service.
Electric cables connect the fuel probes to the I/O board of the integrated engine indicating system.
The system displays the fuel quantity on an indicator located in the instrument panel, below the
　
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