AFMS
N°
D07
FOR
GARMIN
GFC700
AUTOPILOT
AND
VARIABLE
PITCH
PROPELLER
EQUIPPED
AEROPLANES
9.
ELECT
RI
CAL
SYSTE
M
Primary
DC
power
is
provided
by
an
external alternator with a 28 VDC output, rated
of
70
Amps @ 2700 rpm. During normal operations,
it
recharges the battery.
Secondary
DC
power is provided by a lead type battery (GILL G-247) which provides the
energy necessary for feeding the essential electrical loads
in
the event
of
an
alternator
failure.
The switch between the energy sources
is
automatic and
no
action
is
required
in
order
to
ac-
tivate the alternate energy source.
For ground maintenance and/or starting,
an
external power socket
is
provided.
The alternator and battery are connected to the battery bus
in
order
to
provide energy for
the electric equipment.
Each electrically
fed
instrument
is
connected
to
a dedicated circuit breaker which protects the
cable from the battery bus
to
the associated electric equipment.
If
the Ignition
1s
m the pos1t10n l .
R.
or
BOTH,
an
accidental movement
of
the propeller may start the engine with possible danger
for
bystanders.
In
the following figure is presented the electrical system architecture.
Section
7 -
Airframe
and
Systems
description
ELECTRICAL
SYSTEM
Ed.
2.
Rev.O
To Next Page
Loading...
