Electrical System - Tecnam P2010 Flight Manual

AFMS N°D03 FOR ALTERNATIVE AVIONICS CONFIGURATION

5. 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.
WARNING
In the following figure is presented the electrical system architecture.
Section 7 – Airframe and Systems description
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.
ELECTRICAL SYSTEM
Page 7G-20
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