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PAGE
ALPHA Trainer LSA
Pilot Operating Handbook
POH-162-00-40-001
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SECTION 7
AIRPLANE DESCRIPTION
is capable of delivering max. 12A at 14V which feeds the onboard battery
(12V, 11Ah or 12.4Ah for EarthX). In case of emergency, the battery will sup-
ply reduced number of necessary direct-current loads with power for 30
minutes. The electrical system is controlled by means of switch/fuse which
are arranged in one row at the upper half of the switch panel under the in-
strument panel.
The circuit breakers (CB) are located under the switch/fuses of the switch
panel. A voltmeter is integrated in the Engine Management System display
system to monitor electrical system operating. Generator failure is indicated
by a warning red LED light on the Switch panel (labeled GENERATOR FAIL).
7.8.3 POWER DISTRIBUTION
The Master relay connects the battery with main bus. Main bus supplies the
avionics relay which delivers the power to the switch panel and circuit break-
ers. 12V socket is connected via switch/fuse directly to the main battery.
The 22000uF/25V capacitor provides a continuous control voltage for the
regulator/rectifier in the event of momentary interruption of battery voltage.
This is necessary as generator output voltage is variable with RPM and may
increase to as much as 240V AC.
The avionics bus comprises all avionics loads and electrically operated in-
struments. Harnesses of the electrical system from the engine is leading
through the firewall and connected to the electrical board and to other pro-
vided systems.
The electrical system is divided on three main subsystems (engine harness,
main electrical board and switch panel) which are than interconnect to all
equipment and devices.
Electrical supply from generator and battery is distributed to the following :
Equipment
Electrical Consumption
[A] @ 14 V
Kanardia ASI, VSI, ALT, RPM,
Engine Management System display
2.3 A (Total)
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