DV 20 E AFM Airplane Description
Doc. No. 4.01.15-E Rev. 2 22-Mar-2022 Page 7 - 45
Other main functions of the ECU include:
- Ignition control
- Fuel injection control
- Indication of faults and values that are outside operating limits
- Storing faults
- Power supply monitoring
Additional Power Supply (if OÄM 20-245/b is installed):'
In addition to the two in the engine integrated alternators, there is an external alternator'
that supplies power to the aircraft system. It comprises an internal regulator, rectifier and'
an external overvoltage protection. The additional alternator is located on the left-side of'
the engine, short after the propeller. The alternator is driven by a V-belt from the propeller'
drive. The alternator is connected to the electrical system via the ALT circuit breaker. The'
regulator of the alternator is protected by the ALT. CONTROL circuit breaker. A failure'
of the external alternator is indicated by an alternator warning light (AWL), installed on'
top of the instrument panel on the LH side.'
7.10 PITOT-STATIC SYSTEM
The Pitot pressure is measured on the leading edge of a calibrated probe below the left
wing. The static pressure is measured by the same probe. For protection against water
and humidity, water sumps are installed within the line. These water sumps are accessible
beneath the left seat shell.
The error in the static pressure system is negligible. For the error of the airspeed indicating
system refer to Chapter 5.
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