ROBINSON
MODEL R44
SECTION 7
SYSTEMS DESCRIPTION
REVISED: 21 FEB 2014 7-11
ELECTRICAL SYSTEM
A 14-volt DC electrical system which includes an alternator
and a sealed lead-acid battery is standard. A 28-volt
electrical system is optional. The battery is located either
in the engine compartment, under the left front seat, or
beneath the instrument console.
The circuit breaker panel is on the ledge just forward of the
left front seat. Breakers are marked to indicate function
and amperage and are of the push-to-reset type.
The battery switch controls the battery relay which
disconnects the battery from the electrical system. A wire
protected by a fuse near the battery bypasses the battery
relay to allow both tachometers and the clock to continue
to receive battery power with the battery switch off.
The alternator control unit protects the electrical system
from overvoltage conditions. The ammeter indicates
current to the battery (“—” indicates discharge). An ALT
caution light or ammeter discharge indication in flight
indicates low voltage and possible alternator failure. Turn
off nonessential electrical equipment and switch alternator
off then back on after one second to reset alternator
control unit. If ALT light stays on or ammeter still indicates
discharge, land as soon as practical.
CAUTION
Continued flight without functioning alterna
-
tor can result in loss of power to tachom-
eters, producing a hazardous flight condition.
NOTE
Except for emergency procedures, do not
operate alternator with battery switched off.
The battery helps protect electrical equip
-
ment from voltage spikes.
Later aircraft have an avionics master switch which controls
power to the avionics bus. This allows all avionics to be
switched on and off by a single switch.
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