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钻石42飞机飞行手册 DA 42 Airplane Flight Manual(109)

时间:2011-10-28 13:17来源:蓝天飞行翻译 作者:admin
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Both generator power output lines also run through a current sensor for each alternator, which provides an indication of the power being supplied to the electrical system by an alternator including the current for battery charging on the G1000. In the event of a main battery failure the field of each alternator is energized by two 12 V, 1.3 Ah sealed lead acid batteries ('excitation'-battery) connected in series, which are installed in the nose baggage compartment. The 'ENGINE MASTER LH (RH)'-switches connect the 'excitation'
' battery to the alternator field via a 5 Ampère fuse.
' If M.M 42-240 or O.M 42-074 or O.M 42-129 are carried out:
' The 'ENGINE MASTER LH (RH)'-switches connect the 'excitation' battery to the alternator ' field via a 10 Ampère fuse.
Page 7 - 50  Rev. 5  15-Nov-2007  Doc. No. 7.01.05-E 


Alternator control:
Each alternator has an alternator control unit. It measures the alternator output voltage and controls the current through the alternator field coils via a pulse-width modulated signal. To keep the output voltage stable in all load and speed situations, the alternator field signal is modulated accordingly.
The alternator control unit includes a comprehensive set of diagnostic functions that will warn the operator using a caution message (L/R ALTN FAIL) on the G1000 PFD in case of over- or undervoltage as well as a couple of other internal warning levels.
Load Balancing: The alternator control unit supports load balancing across the two alternators via the internal alternator temperature. The temperature is measured and the alternator control unit slightly decreases alternator voltage output at higher internal alternator temperatures. Thus the load is partly shifted to the alternator with the lower internal temperature. This system is able to balance the actual load within a few amps between the two alternators installed.
Storage
'Main'-battery power is stored in a 24 V, 10 Ah lead-acid battery mounted on the right-aft side of the front baggage compartment. The 'main' battery is connected to the 'hot battery bus' and to the 'battery bus' via the 'battery'-relay which is installed in the relay junction box on the center-aft side of the front baggage compartment.
The 'battery'-relay is controlled with the 'ELECTRIC MASTER'-switch which is located on the left-hand side of the instrument panel.
In addition, a non-rechargeable dry battery is installed as a further source of power for the attitude gyro (artificial horizon) and the flood light. When the EMERGENCY switch is set to ON, these two systems are supplied with power for at least 1.5 hours, independent of all other electrical consumers. During each 100 hour inspection, this battery is checked for proper functioning. Every 2 years or after use (broken seal on the switch) the battery package must be replaced.


Distribution
Electrical power is distributed via the 'hot battery bus', the 'battery bus', the 'LH (RH) ECU-bus', the 'LH (RH) main bus', and the 'avionic bus'.
 
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