The governor must have two mechanical stops which can be detected by the EECU through sensing
pins. If one of these stops is reached, the electric motor will not be actuated into the direction of the
detected stop, only movement into direction of the opposite stop is possible. The EECU also detects
mechanical jamming of electric motor to prevent overheating of the motor because of excessive current
consumption.
EECU E4
H-Bridge
Current
Measurement
Propeller Governor – Actuator Circuit
Input Circuit
M
GND
330R
180R 560R
390R
Left
Stop
Right
Stop
Governor
Stop
Feedback
2K56
Curent
Feedback
Ubatt
Fig. 76 - 8 Electrical Drawing Governor System
EECU Caution Lamp:
Each ECU has its own caution lamp output. The lamp will be supplied with bus voltage via the ECU.
These display lamps are used to inform the flight crew of a detected EECU or Engine failure.
(For particular installation refer to the applicable Aircraft Maintenance Manual)
Power Lever Sensor:
The Power Lever Sensor is a sensor using the Hall-Effect.
Each sensor has two independent outputs with different output characteristics which are verified inside
the EECU.
Each ECU requires its own sensor. E.g. in a twin engine installation, 4 sensors are necessary.
The installation of the two power lever sensors for the EECU shall ensure that the output signals are
within 5% to each other (e.g. Signal A 85%, Signal B 87%).
Engine Self-test Push-button:
The engine is able to perform a self-test. For this, a normally open push-button is installed.
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