% 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.
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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 O.M 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.
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AIRCRAFT
Check Valve
Capillary Balance Hose
Tank Filler

Balance/Vent Hoses
Vent Hose
Outboard Fuel Chamber
Inboard Fuel Chamber
Flexible Coupling

Finger Filter
Outlet Hose
Outlet Hose from Left Tanks
% Figure 1: Fuel Tank System in the Right Wing, Standard Tanks Installed
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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
from moving quickly from one end of the tank to the other during flight.
% There are two versions of the inboard fuel chamber. They look similar from outside, but can be % identified by the version of the fuel quantity indicating system. Version A of the inboard fuel % chamber is compatible with Version A of the fuel quantity indicating system (factory standard up % to serial number 40.054). Version B of the inboard fuel chamber is compatible with Version B of % the fuel quantity indicating system (factory standard from serial number 40.055 on). Refer to % Section 28-40 for more data on the fuel quantity indication system.
%  Each inboard chamber has a capacity of 52.6 liters (13.9 US gal) and each outboard chamber has a capacity of 26.1 liters (6.9 US gal). The total fuel tank capacity of each wing is 78.7 liters (20.8 US gal).
% A large flexible coupling connects the inboard fuel chamber to the outboard fuel chamber. A worm % drive clamp holds the flexible coupling to the outboard chamber and another worm drive clamp % holds the flexible coupling to the inboard chamber.
%  Smaller diameter flexible hoses connect the inboard and outboard chambers at the top of the
%  chambers. Two vent connections are located at the outboard end of the outboard chamber. A flexible hose connects the aft vent connector to a check valve. Another flexible hose connects the check valve to a vent connector on the outer fuel tank access panel, on the lower surface of the wing.
　
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