Cessna R182 - Brake System; Electrical System

CESSNA
MODEIL
R182
SECTION
7
AIRPLANE
&
SYSTEMS
DESCN,IPTIONS
BRAKE
SYSTEM
The
airplane has
a single-disc, hydraulically-actuated
brake on
each
/
main landing
gear
wheel. Each
brake
is
connected,
by a hydraulic
line, to a
\
master cylinder attached
to each of the
pilot's
rudder
pedals.
The
brakes
are operated
by applyin,g
pressure
to the top of either the left
(pilot's)
or
right
(copilot's)
set of
rudder
pedals,
which are interconnected.
When the
airplane is
parked,
both
main wheel
brakes
may
be set by utilizing the
parking
brake which
is operated by a
handle under the left side of the
instrument
panel.
To
qppty
the
parking
brake, set the brakes with the
rudder
pedals, pull
the handle a,ft, and rota,te
it 90o
down.
For
maximum
brake life,
keep the brake system
properly
maintained,
and minimize
brake
usa,ge during
taxi operations and
landings.
Some
of
the symptoms
of
impending brake failure
are:
gradual
decrease in braking
action
after brake application,
noisy
or dragging
brakes, soft or spongy
pedals,
and excessive
travel and weak
braking
action.
If
any
of
these sjrmptoms
appea,r, the brake system is
in need of
immediate
attention.
If, during
taxi or
landing roll,
braking
action
decreases,
let up on
tbe
pedals
and then re-apply the brakes with
heavy
pressure.
If the brakes
bebome spongy
or
pedal
travel
increases,
pumping
the
pedals
should
build:braking
p.ressure.
If one brake becomes weak or
(
fails, use ttre other
brake
sparingly
while using opposite rudder, as
\
required,
to offset
the
good
brake.
ELECTRICAL
SYSTEM
Electrical
energy
(see
figure
7-8) is
supplied by
a 28-volt,
direct-
current
system
powered
by an engine-driven,60-amp
alternator. A24-volt,
14-amp
hour
battery
(or
17-amp hour battery,
if installed) is located on
the
right forward
portion
of
the firewall. Power
is
supplied to most
general
electrical
and all aviouics
circuits through
the
primary
bus bar and
the
avionics bus
bar, which are
interconnected by
an
avionics
power
switch.
The
primary
bus
is on anytime the
master switch is turned
on,
and
is not
affected by
starter
or external
power
usage. Both
bus
bars are on anytime
the
master and
avionics
power
switches
are turned on.
CAUTION
Prior to
turning the
master
switch
on or off,
starting
the
engine,
or appl5ring an external
power
source,
the avionics
power
switch,
labeled AVN
PWR,,
should
be turned
off to
prevent
any
harmful transient voltage
from
damaging the
avionics
equipment.
7-29