Electrical System Installation Requirements:
The following requirements have to be observed to ensure a proper performance of the AE 300 in the
installation environment.
Pay attention that the entire electrical system and wiring harness is protected against
chafing at hot parts or sharp edges.
The source of electric power of the aircraft is the main battery as defined in 14.5.5.14. The engine is
equipped with an alternator, which is the electrical power system dedicated to the engine. An
excitation battery as defined in 14.5.2.3 has to be provided for alternator start up. Thereafter the
alternator is self-exciting.
The following basic rules apply for a proper electrical system.
The EECU, alternator and batteries must be wired that in a case of battery failure a voltage supply for
the EECU and fuel feed pumps is still granted.
It must always be possible to separate the engine electrical system (EECU, associated systems and
alternator) from the battery and the rest of the aircraft electrical system.
It must be ensured, that the electric power supply to the EECS is always in compliance with the
requirements defined in RTCA DO160D, Section 16, Cat B.
The required minimum reliability of the EECS electric power supply is depended on the class airplane.
Consult AC 23.1309-1C for determination. If this requires the installation of an EECS backup electric
power system, it must be ensured, that this system is independent and isolated from the airplane bus
system or systems so that electric power from the backup system is supplied to the EECS solely.
An example below gives an overview about a possible installation with isolated supply-Buses showing
the possibility of separating the Alternator from the Main Bus.
G
Main Battery
Excitation & Backup
Source (Battery)
Engine
Alternator
ECU BUS
EECU
MAIN
BUS
Regulator
Excitation
Current
Alternator
Relay
Switch
Signal
Fig. 01 - 19 Power Supply Installation
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