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Ammeter
The ammeter displays the intensity of current which is supplied to the electrical system by the LH (RH) alternator.
Landing and taxi lights
Landing and taxi lights are built into the wing center section, and are each operated by means of a switch (LANDING, TAXI) located on the row of switches on the instrument panel.
Position and strobe lights
Combined position and strobe lights (anti collision lights) are installed on both wing tips. Each system is operated by a switch (POSITION, STROBE) located on the row of switches on the instrument panel.
Flood light
A two-dimensional light emitter is mounted above the instrument panel. It illuminates the instrument panel as well as all levers, switches, etc. The flood light is switched on and its brightness is adjusted by means of a rotary button (FLOOD) in the LH section of the instrument panel.
Instrument lighting
With a rotary button (INSTRUMENT) in the LH section of the instrument panel the internal lighting of the instruments is switched on and its brightness is adjusted.
Pitot heating
The Pitot probe, which provides measurement for the Pitot-static system, is electrically heated. The heating is activated with a switch (PITOT HEAT) located on the row of switches on the instrument panel. The temperature is automatically kept constant by means of a thermal switch on the Pitot probe, and as an additional safety measure a thermal fuse is built in. If this thermal fuse is activated, the Pitot heating can no longer ' be switched on, and the PITOT HT fail will be displayed. In this case the system should
' be serviced. The PITOT HT OFF is on if the Pitot heating is switched off.
Page 7 - 54 Rev. 5 15-Nov-2007 Doc. No. 7.01.05-E
External power socket
The DA 42 has an external 28 Volt DC power socket located on the lower surface of the fuselage nose section. When external power is connected, the control relay is energized and the external power comes online.
The socket itself has three pins:
.
a large negative pin
.
a large positive pin
.
a small positive pin
A diode protects the system from reverse polarity.
7.10.2 ENGINE CONTROL UNIT / ECU
Engine control and regulation
The ECU monitors, controls and regulates all important parameters for engine operation.
Sensors installed are:
-Oil temperature (lubrication system engine) / OIL TEMP
-Oil pressure (lubrication system engine) / OIL PRES
-Coolant temperature / COOLANT TEMP
-Gearbox temperature / GEARBOX
-Camshaft RPM (twice)
-Crankshaft RPM (twice)
-Fuel pressure in the common rail
-Manifold pressure
-Manifold air temperature
-Ambient air pressure
-Propeller governor / oil pressure
-Power lever position (twice)
-Voltage
-Starter switch signal
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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(30)
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