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The cantilever wing is a semi-monocoque structure. Each wing has two I-shaped spars with webs made form GFRP/rigid foam sandwich and caps made from CFRP bands. Each wing has top and bottom shells made of CFRP/GFRP/rigid foam sandwich which bond to the spars. GFRP ribs and webs bond to the spars and shells to complete the structure.
The wings attach to the fuselage center section. Each wing has two stump-spars. Four large bolts attach each wing to the fuselage main bulkheads. Standard ailerons and electrically operated flaps attach to the trailing edge of the wing.
The horizontal stabilizer is a semi-monocoque structure. It has top and bottom shells made of GFRP. The shells bond to GFRP spars and ribs. The trailing edge has a conventional elevator and a trim tab.
The one-piece canopy has a large quantity of wrap-around glazing. This gives a good all-round view from the cockpit. A glazed rear passenger door gives access to the rear seats from the left side of the airplane.
A polyurethane paint finish protects the outside skin from ultraviolet rays and humidity.
The fixed tricycle landing gear has fairings attached to each leg. The main legs attach to the fuselage center-section. The nose leg attaches to the forward fuselage. Each main wheel has a disc brake on the inside. Hydraulic pressure operates each disc brake.
The flight control system uses conventional ailerons, elevator and rudder. The DA 40 has 2 control sticks and 2 rudder pedal assemblies to operate the primary flight-controls. Push-pull rods operate the ailerons and elevator. Cables operate the rudder. An electric motor operates the wing flaps. A hand wheel and Bowden cable operate the elevator trim.
% The DA 40 is powered by one of the following engines:
%) Lycoming IO360 - a four cylinder, direct drive, horizontally-opposed engine. The engine has a fuel % injection system and a conventional wet-sump oil system.
%) Thielert Aircraft Engines TAE 125 - a four valve, four cylinder Diesel cycle engine with cylinders % in line. The engine has a turbo-charger and intercooler, a common rail high-pressure direct % injection system, and a wet oil system. It drives the propeller through a reduction gear.
% The DA 40 has a hydraulic constant-speed propeller with 3 blades.
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General Description
AMM

% The airplane has an aluminum fuel tank in each wing. Each tank consists of several chambers. The % fuel tanks are inboard between the spars. The tank assemblies have fuel fillers at or near the outboard % end. Flexible hoses connect the tanks to a fuel selector and shut-off valve under the cockpit floor. An % electrical boost pump (Lycoming version only) and an engine driven pump supply fuel to the engine.
The tanks have fuel quantity probes which operate the cockpit indicating systems.
% The airplane has two sources of electrical power. A 28 Volt (Lycoming version) or 14 Volt (TAE % version) battery supplies power when the engine is not running. An alternator provides power when % the engine is running. Switches and circuit breakers control all electrical devices. A starter key controls % the engine starter motor. It also controls the magnetos (Lycoming version) or serves as electric master % switch (TAE version).
The DA 40 has a full range of flight instruments. These include Pitot/static instruments to show % airspeed and altitude, as well as electrically driven instruments and vacuum driven instruments (TAE % version only) to show attitude. The airplane has all the usual engine instruments, except that the TAE % version has a load indication instead of a manifold pressure indication.
The airplane also has radio and navigation aids installed.
Doc # 6.02.01 Page 3
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AMM

3. Equipment Data
The table below gives you the name and address of the manufacturers who supply systems and/or equipment for the DA 40. This will help you get more data on a system and/or equipment.
　
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