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7.9.7 OIL SYSTEMS
Each engine has two separate oil systems.
Lubrication system (engine and turbo-charger)
The engine lubrication is a wet sump lubrication system. The oil is cooled by a separate cooler on the underside of the engine.
A dip-stick is provided to check the oil quantity through an inspection hole in the upper cowling. If required, oil can also be filled in there (for approved oil grades refer to Section
2.4 - POWER-PLANT LIMITATIONS).
Gearbox and propeller governor system
The second oil circuit lubricates the gearbox and serves the governor system and the regulation of the propeller.
The gearbox oil quantity can be checked with the help of an inspection glass which can be reached through an inspection hole on the front side of the lower cowling.
CAUTION
If the gearbox oil quantity is too low, an unscheduled maintenance is necessary (for approved oil grades refer to Section 2.4 - POWER-PLANT LIMITATIONS).
7.9.8 TURBO-CHARGER SYSTEM
The exhaust system contains a manifold which collects exhaust gases from the outlets of the cylinders and feeds them to the turbine of the turbo charger. Behind the turbine the exhaust gases are guided through the lower cowling to the exterior of the airplane. Excess exhaust gases bypass the turbine. The bypass is controlled by the ECU through the waste gate valve. A manifold pressure sensor behind the compressor allows the ECU to calculate the correct position of the waste gate valve. This prevents excessive manifold pressures at low density altitudes. The intake air is compressed in the compressor which is driven by the turbine, and is subsequently cooled down in the intercooler to increase power. Cooling the air increases efficiency through the higher density of the cooler air.
7.9.9 FIRE DETECTION SYSTEM
The fire detection system in the DA 42 consists of an overheat detector in the hot area of each engine. In case of an increase of the engine compartment temperature above 250 °C (480 °F) the overheat detector closes the electric circuit and a warning message appears in the annunciation window of the G1000 PFD.
To test the fire detectors (refer to Section 4A.6.1 - PREFLIGHT INSPECTION) push the test button located next to the gear selector switch. An aural alert and the fire warning message for the LH and RH engine should appear in the annunciation window of the G1000 PFD.
CAUTION
If the aural alert or the warning does not appear, an unscheduled maintenance is necessary.
Page 7 - 48 Rev. 5 15-Nov-2007 Doc. No. 7.01.05-E
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Doc. No. 7.01.05-E Rev. 5 15-Nov-2007 Page 7 - 49
7.10.1 GENERAL
The DA 42 has 28 Volt DC system, which can be sub-divided into:
-Power generation
-Storage
-Distribution
-Consumers
Power generation
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本文链接地址：钻石40系列飞机维护手册 DA 40 SERIES AIRPLANE MAINTENANCE MANUAL 4(27)
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