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CESSNA
SECTION 7
MODEL 152
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 knob on the lower left side of the instrument panel. 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 off set the good brake.
ELECTRICAL SYSTEM
The airplane is equipped with a 28-volt, direct-current electrical system (see figure 7-7). This
system uses a 24-volt battery mounted on the right forward side of the firewall as the source of
electrical energy and an engine-driven 60-amp alternator to maintain the battery's state of
charge. Power is supplied to a bus bar, and a master switch controls this power to all circuits,
except the engine ignition system, clock, and flight hour recorder (if installed). The flight hour
recorder receives power through activation of an oil pressure switch whenever the engine is
operating, and the clock is supplied with current at all times. All avionics equipment should be
turned off prior to starting the engine or using an external power source to prevent harmful
transient voltages from damaging the transistors in this 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 all electrical
power to the airplane. The left half, labeled ALT, controls the alternator.
1 July 1978
7-22
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