AFMS N°D01 FOR GARMIN GFC700 AUTOPILOT INSTALLATION AND
RNAV/RNP NAVIGATION ELIGIBILITY
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 bat-
tery.
Secondary DC power is provided by a lead type battery (GILL G-247) which
provides 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
energy 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 equip-
ment.
If the Ignition is in the position L, R, or BOTH, an
accidental movement of the propeller may start the
engine with possible danger for bystanders.
In the following figure is presented the electrical system architecture.
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