Brake System; Electrical System - Cessna 1980 182Q Pilot's Operating Handbook And Flight Manual

CESSNA
MODEL 182Q
SECTION 7
AIRPLANE
&
SYSTEMS DESCRIPTIONS
each refueling, by using the sampler cup provided tp drain fuel from the
wing tank sumps, and by utilizing the fuel strainer drain under an access
panel on the left side of the engine cowling. The fuel tanks should b~ filled
after each flight to prevent condensation.
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. Wh!3.n the
airplane is parked, both main wheel brakes may be set by utilizing the
parking brake which is operated by a handle below the left side of the
switch and control 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 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 7-7). The system is powered by a belt-driven, 60-amp
alternator and a 24-volt battery (a heavy duty battery is available) 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 any time the master switch and avionics power switches are turned on.
1 October 1979 7-25