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CESSNA
MODELT210M
SECTION 7
AIRPLANE
&
SYSTEMS DESCRIPTIONS
parking brake which is operated by a handle under the left side of the
instrument panel. To apply the parking brake, set the brakes with the
rudder pedals, pull the handle aft, and rotate it 90°
down.
For maximum brake life, keep
the
brake system properly maintained,
and minimize brake usage
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 symptoms
appear,
the brake system is in need of
immediate attention.
If,
during taxi or landing roll, braking action
decreases, let up on the pedals and then re-apply the brakes with heavy
pressure.
If
the brakes become spongy or pedal travel increases, pumping
the pedals should build braking pressure.
If
one brake becomes weak or
fails,
use the other brake spai:ingly while using opposite rudder, as
required, to offset the good brake.
ELECTRICAL SYSTEM
,,~
Electrical energy (see figure 7-9) is supplied by
a
28-volt, direct-
current system powered by an engine-driven, 60-amp
(95-amp,
if
installed)
alternator.
A 24-volt, 14-amp hour battery
(or
17-amp hour
battery,
if
installed)
is located on the upper left forward portion of the firewall. Power
is supplied to most general electrical and all avionics circuits through the
primary ous 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 applying an external source, the avionics power
switch labeled A VN PWR should be turned off to prevent
any harmful transient voltage from damaging the avio-
nics equipment.
MASTER SWITCH
,,.,,...-.,,,,,. .
The master switch is a split-rocker type switch labeled MASTER, and
is on in the up position and off in the down position. The right half of the
switch, labeled BAT, controls electrical power to the airplane through the
primary bus
bar.
The left half, labeled ALT, controls the alternator.
Normally, both sides of the master switch should be used simultane-
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