Pipistrel VIRUS SW 600 D, Руководство по эксплуатации для пилотов

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7-11
Virus SW 600 D
iS engine POH Supplement
SPOH-127-00-41-001
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SECTION 7
AIRPLANE DESCRIPTION
7.8 ELECTRICAL SYSTEM
7.8.1 ELECTRICAL SYSTEM
The airplane is equipped with a double-generator (named generator A and
B, integrated into the engine), single-battery, 12/14-Volt direct current (VDC)
electrical system designed to reduce the risk of electrical system faults. The
system provides uninterrupted power for engine control electronics, avion-
ics, flight instrumentation, lighting, and other electrically operated and con-
trolled systems during normal operation. An additional engine-driven alter-
nator can be installed as option, to power aircraft equipment. A fuse box,
with its two rectifier regulators (from generator A and generator B) is respon-
sible for a constant power supply to all EMS components, fuel pump module
and aircraft systems. The electrical utilities (lights, auxiliary sockets etc.) are
controlled by means of switch/fuses which are arranged in one row on the
switch panel under the instrument panel. The circuit breakers (CB) are locat-
ed under the switch/fuses of the switch panel. An ammeter and a voltmeter
are integrated in the PFD/MFD system and they are displayed on EMS mode
display to monitor electrical system operation.
7.8.2 POWER GENERATION
The electrical system is a 12/14-Volt DC system. Power is normally supplied
to engine management systems by engine generator A (14.2 V/ 16 A), while
engine generator B (14.2 V/ 30 A) supplies aircraft systems and recharges
the on-board battery (Standard Lead-Acid 12V, 11Ah or 12.4Ah for optional
EarthX). Engine Management System manages also the generator backup
functions in case of failure of generator failure (see Section 3 - Emergency
procedures). In case of double generator failure the Engine Management
System can be temporarily powered directly by the on-board battery. An ad-
ditional engine-driven alternator can be installed as option.
7.8.3 POWER DISTRIBUTION
The electrical system itself includes three solenoids, one activated by the
master switch, the second activated by the avionics switch and the starter
engage. All electrical loads that are usually active during operations, are con-
nected to the avionics bus via push-pull circuit breakers. For loads, which are
engaged and disengaged more often, fused rocker switches are used (12 V
socket, NAV/AC lights, LDG light, etc.) All other loads (e.g. avionics) receive
power as soon as the Avionics switch is ON. The avionics switch has no
function when the master switch is OFF. The starter engage switch is also
disabled when the master switch is OFF.