Initial issue
Page 7-37
7.18
Electric System
The aircraft has 12 V DC system. Installation is dual-wire type.
Board network is supplied by maintenance free accumulator 12 V / 17 Ah that is installed on firewall in the engine
compartment. Network is supplied with AC generator with external rectifier regulator (12 V DC).
Circuit breakers are installed at the lower edge of
instrument panel’s right side.
Dual contactless ignition of the engine is a separate part of electrical installation. Each ignition circuit can be switched
ON/OFF independently using corresponding switches labelled
IGNITION
.
Ignition box is connected to the accumulator through the master switch labelled
MASTER SWITCH
. It has positions
OFF
-
INST.
-
CHARGE
-
START
. In the
OFF
position, the starter is electrically isolated. In the
INST.
position are
energized single value instruments (RPM indicator, engine hours, flight hours) and fuel pump. In the
CHARGE
position
also a warn light
CHARGE
is energized and indicates the charging status. In the
START
position, the starter is energized
and will automatically return to the position
CHARGE
when released. Before repeated engine starting, it is necessary
to turn the ignition box to
OFF
position first, and then to position
START
.
Dynon SkyView SV-D1000 displays are connected through a circuit breaker to the
MASTER SWITCH
.
Avionics (RDST, XPDR, intercom) are activated by a separate switch labelled
AVIONICS
and are connected through a
circuit breaker to the
MASTER SWITCH
.
Autopilot is activated by a separate switch labelled
AP
and is connected through a circuit breaker to the
MASTER
SWITCH
.
Navigation and anti-collision lights are activated by a switch labelled
NAV/ACL
and are connected through a circuit
breaker to the
MASTER SWITCH
. Landing lights are activated by a switch labelled
LAND
and are connected through a
circuit breaker to the
MASTER SWITCH
.
Fuel pump is activated by a separate switch labelled
FUEL PUMP
and is connected through a circuit breaker to the
INST.
position of ignition box.
Stall warning system consists of a buzzer and warning light that are activated by ACI Stall Warner (AoA flap). Stall
warning system is connected through a circuit breaker to the
MASTER SWITCH
.
Function of warning and control lights and stall warning horn can be verified by pressing the test button labelled
TEST
.
12 V / 10 A sockets of an automotive type are installed in both lower corners of the instrument panel and are
connected through a circuit breaker to the
MASTER SWITCH
.
Engine hours and flight hours are power supplied through a circuit breaker from the
INST.
position of ignition box.
Содержание WT9 Dynamic LSA / Club
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