Brake System; Electrical System - Cessna TR182 1979 Pilot Operating Handbook

CESSNA
MODELTR182
SECTION 7
AIRPLANE
&
SYSTEMS DESCRIPTIONS
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 applying 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 below the switch and control
panel in front of the pilot. 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 sparingly while using opposite rudder, as
required, to offset the good brake.
ELECTRICAL SYSTEM
The airplane is equipped with a 28-volt, direct-current electrical
system (see figure 7-9). The system is powered by an engine-driven 50-amp
alternator and a 24-volt battery located in the tailcone aft of the baggage
compartment wall. Power is supplied to most general electrical and all
avionics 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 switch and
avionics power switches are turned on.
CAUTION
Prior to turning the master switch on or off, starting the
engine, or applying 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.
1 October 1978 7-33