Airplane Description
DV 20 E AFM
Page 7 - 44 Rev. 2 22-Mar-2022 Doc. No. 4.01.25-E
EMS Power Supply
The EMS power supply primarily comprises 2 alternators with permanent magnets. It also
comprises an external rectifier, voltage stabilizer and overvoltage protection, which are
integrated in the FUSE BOX. The two 3-phase A/C current generators (alternators) are
physically separated in the engine integrated power supply units. One is used for the ECU
and the other one is available for the airplane. They are driven by the crankshaft and
require no external supply once the engine has reached its idle speed.
NOTE
Until the idle speed is reached, the EMS requires an external
12 V supply from the onboard system of the airplane.
ECU
The ECU is a digital engine control unit which contains the LANE A and the LANE B in
a single housing. In principle, each LANE represents an independent computer.
In the AUTO (both LANE select switch ON) setting, the ECU decides which LANE takes
control (redundancy management) according to the health level of the EMS.
Any errors or values outside the operating limits are indicated by an EMS lamp for each
LANE.
NOTE
The ECU also contains a databus system (CAN aerospace).
A large number of engine parameters and warnings can be
displayed on a separate display. Usage is up to the airplane
manufacturer.
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