Tecnam P2006T, Aircraft Flight Manual

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GARMIN G950 IFDS – SMP
FOR DIGITAL CONFIGURATION
Page SMP7-41
Section 7 – Airframe and Systems description
ELECTRICAL SYSTEM
Ed.4, Rev.0
18. E
LECTRICAL SYSTEMS
Primary DC power is provided by two engine-driven alternators which, during
normal operations, operate in parallel.
Each alternator is rated at 14,2-14,8 VDC, 70 Amp, and it is fitted with an exter-
nal voltage regulator, which acts to maintain a constant output voltage, and with
an automatic overvoltage device protecting the circuits and the electric compo-
nents from an excessive voltage caused by alternator failures.
The power rating of the each alternator is such that if one alternator fails the other
one can still supply the airplane equipment to maintain flight safety.
Secondary DC power is provided by a battery (lead type - Gill Teledyne G35, 12
V, 23-Ah in 1h run time) and an external DC power source can be connected to
the aircraft DC distribution system.
On the instruments panel, right side, it is installed a voltmeter/ammeter. The am-
meter section can indicate the current supplied by either left or right alternator
switching a dedicated selector.
There are five different busses (make reference to Figure 11):
• Battery bus
• LH Alternator bus
• RH Alternator bus
• LH Avionic bus
• RH Avionic bus
The distribution system operates as a single bus with power being supplied by the
battery and both alternator but it is possible to separate the left busses from the
right busses when required by means of the Cross Bus switches.
All electrical loads are divided among the five busses on the basis of their im-
portance and required power: equipment with duplicate functions are connected to
separate busses.
The Battery bus, which supplies the most important loads, is energized from three
sources: the battery and both alternator. This allows the bus for remaining active
also in case of two independent faults in the supply paths.