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Section 7 – Airframe and Systems description
ELECTRICAL SYSTEM
9. ELECTRICAL SYSTEM
Primary DC power is provided by an external alternator with a 28 VDC output,
rated of 70 Amps @ 2700 rpm. During normal operations, it recharges the battery.
Secondary DC power is provided by a lead type battery (GILL G-247) which pro-
vides the energy necessary for feeding the essential electrical loads in the event of
an alternator failure.
The switch between the energy sources is automatic and no action is required in
order to activate the alternate energy source.
For ground maintenance and/or starting, an external power socket is provided.
The alternator and battery are connected to the battery bus in order to provide en-
ergy for the electric equipment.
Each electrically fed instrument is connected to a dedicated circuit breaker which
protects the cable from the battery bus to the associated electric equipment.
If the Ignition is in the position L, R, or BOTH, an accidental
movement of the propeller may start the engine with possible dan-
ger for bystanders.
In the following figure is presented the electrical system architecture.
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