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ECU TEST
There are two ECU TEST buttons, one for each engine. Depending on the position of the power lever and the engine speed, the ECU TEST button has two different functions.
Power lever at IDLE and RPM below approximately 900:
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 as well as during flight, but only if the power lever is in the IDLE position. Otherwise the test will not start. During the procedure the ECU performs a switch from ECU A to ECU B 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 from ECU B to ECU A. After that both caution lights must extinguish and the engine must run without a change.
Power lever above IDLE, or RPM above approximately 900:
If an ECU A or ECU B caution message is displayed, the ECU TEST button can be pressed for more than 2 seconds to reset the message. The reset is possible only once, and only in case of system faults of minor criticality.
Alternate Air
In the event of power loss because of icing or blocking of the air filter, there is the possibility of drawing air from the engine compartment. The ALTERNATE AIR operating lever which serves both engines simultaneously is located under the instrument panel to the right of the center console. To open the alternate air source the lever is pulled to the rear. Normally, the alternate air source is closed with the lever 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
ON
7.9.4 ENGINE INSTRUMENTS
The engine instruments are displayed on the Garmin G1000 MFD. Also refer to Section
7.13.3 - MULTI FUNCTION DISPLAY (MFD). Indications for the LH engine are on the left side, indications for the RH engine are on the right side.
Default page Display when pushing Display when pushing
Engine the SYSTEM button the FUEL button
NOTE
The figure on previous page is a general demonstration of a typical G1000 MFD to show the different display modes. The pictured engine instrument markings may not stringently agree with the current engine limitations of the DA 42.
NOTE
The fuel calculations on the FUEL CALC portion do not use the airplane*s fuel quantity indicators. The values shown are numbers which are calculated from the last fuel quantity update done by the pilot and actual fuel flow data. Therefore, the endurance and range data is for information only, and must not be used for flight planning.
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Designation Indication Unit
LOAD % Available power %
RPM Propeller RPM 1/min
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