Airplane

DA 40 NG AFM

Description

7.9 POWER PLANT

7.9.1 ENGINE, GENERAL

The installed Austro Engine E4-A engine has the following specifications:

-Liquid-cooled four-cylinder four-stroke engine with wet sump lubrication

-Inline construction

-Common rail direct injection

-Propeller speed reducing gear 1:1.69

-Digital engine control with integrated propeller governor (using the gearbox oil system)

-Turbo charger with intercooler

Max. continuous power: 114.0 kW (152.8 DIN-HP) at 2100 RPM at sea level and ISA

The indications for monitoring important engine parameters during operation are integrated

'within the Garmin G1000 display (if installed) or on the MED and SED (if installed). The engine can only be operated with the ENGINE MASTER switch ON. The engine has an

EECU (Electrical Engine Control Unit) which receives its electrical power from the generator when the engine is running. When the engine is not running, the ECU receives its electrical power from the battery.

DA 40 NG AFM

Airplane

Description

7.9.2 OPERATING CONTROLS

POWER lever

The engine performance is controlled by the power lever, situated on the large center console. 'Front' and 'rear' are defined in relation to the direction of flight.

This lever is used to set the desired engine power LOAD (%)

Lever forward (MAX) = Full power

Lever to rear (IDLE) = Idle

The ECU controls manifold pressure, injected fuel quantity and propeller speed according to the desired engine power preselected with the power lever.

The propeller governor is attached to the top rear side of the gearbox and uses gearbox oil for propeller pitch regulation. Following a loss of oil pressure the propeller blades go to the low pitch stop (maximum RPM), thus allowing continuation of the flight according to 3.3.6 - DEFECTIVE RPM REGULATING SYSTEM.

Airplane

DA 40 NG AFM

Description

ELECTRIC MASTER

The key can be switched into three positions:

ENGINE MASTER

The engine can only be cranked with the ENGINE MASTER switched to ON. To shut down the engine the ENGINE MASTER is switched to OFF.

ECU VOTER

For normal operation the switch is set to AUTO. The engine is controlled by either ECU A or ECU B. In case of a failure of the active electrical engine control unit (ECU) there is an automatic switch-over to the other ECU. If the automatic switch over fails, switch over can be done manually by switching to ECU A or ECU B. This procedure should only be applied in an emergency.

DA 40 NG AFM

Airplane

Description

ECU TEST

POWER lever at IDLE:

By pushing and holding the button until the end of the procedure, the self-test of each engine control unit is started. The procedure is possible on the ground only. Otherwise the test will not start. During the procedure the ECU performs a switch from ECU A to ECU B or ECU B to ECU A, whichever is active at the moment, with the propeller cycling. The propeller RPM is monitored automatically by the ECU. When switching from one ECU to the other, a slight shake of the engine may occur. Finally the ECU switches back. After that both caution lights must extinguish and the engine must run without a change.

Alternate Air

In the event of power loss because of icing or blockage of the air filter, there is the possibility of drawing air from the engine compartment. The ALTERNATE AIR operating lever is located under the instrument panel on the left side of the center console. To open the alternate air source the lever is pulled to the rear. The alternate air source is closed, with the lever being in the forward position.

Placard on the lever, forward position:

ALTERNATE AIR

Placard on the lever, visible when lever is in the rearward position (alternate air open):

ALTERNATE AIR

ON