Airplane Description DA 62 AFM
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 left alternator regulator also measures the power output of both (LH and RH)
alternators via separate current sensors. Based on the current measurements, the LH
alternator regulator controls the output of its associated alternator, providing paralleling
between the alternators.
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.
Storage
Main battery power is stored in a 24 V, 13.6 Ah lead-acid battery mounted on the right-aft
side of the front electric/avionic 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 forward side of the front electric/avionic compartment.
The battery relay is controlled with the ELECT. MASTER switch which is located on the
left-hand side of the instrument panel.
Page 7 - 64 Rev. 0 11-Jan-2019 Doc. No. 11.01.05-E
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