AFMS N°D07 FOR GARMIN GFC700 AUTOPILOT AND VARIABLE PITCH PROPELLER EQUIPPED
AEROPLANES
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 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 ac-
tivate 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 equipment.
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.
To Next Page
Loading...
