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If you set the electric fuel pump to OFF, then an internal by-pass will allow the fuel to flow through the electric fuel pump to the engine driven fuel pump. The engine can run.
%  If you set the fuel selector valve to RIGHT then fuel will only flow from the right tank.
%  If you set the fuel selector valve to LEFT then fuel will only flow from the left tank.
%  If you set the fuel selector valve to OFF then fuel will not flow from the left tank or the right tank. The engine will not run.
% Both of the inboard fuel chambers and both of the long range fuel chambers (if the Long Range Tanks % are installed) have fuel probes. The signals from the fuel probes are used to set a value on an indicator. The indicator is located in the instrument panel, right side.
%  Both of the inboard fuel chambers have additional fuel sensors. The signals from the fuel sensors operate a low fuel caution light on the annunciator panel.
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Fuel System
AMM

% Section 28-01 % Fuel System - TAE 125 Diesel Engine % 1. General
% This Chapter tells you about the DA 40 airplane fuel system with the TAE 125 Diesel engine installed. % It does not tell you about the engine fuel system. For more data on the engine fuel system refer to the % TAE 125 Operation and Maintenance Manual.
% The DA 40 has a fuel tank in each wing. The total usable fuel capacity of the fuel system is 28 US gal % (106 liters). Two engine-mounted pumps supply fuel to the engine and a filter gives protection to % sensitive components. An electric transfer pump moves fuel from the right wing to the left wing as % necessary.
% The pilot controls the fuel system with a switch for the electric fuel pump. An emergency fuel valve % provides a backup system for fuel transfer. A fuel quantity indicator shows the quantity of fuel in the % tanks. Refer to these Sections for more data on these systems:
% Section 28-11 Fuel storage.
% Section 28-21 Fuel distribution.
% Section 28-41 Fuel indication.
% Section 73-01 Engine fuel system.
% 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.
%

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Check Valve Restrictor
Lightning Protection Hose(BleedType)

Emergency Fuel Valve

Check Valve
Figure 1: Fuel System Schematic Drawing

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Fuel System
AMM

% 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.
　
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