Cessna 402C Pilot Operating Handbook page 228

SECTION 7
AIRPLANE & SYSTEMS DESCRIPTIONS
BRAKE SYSTEM
~""'402C
Moon
The a i rp 1ane is pravi ded wi th an independent hyd raul i ca 11y actuated
brake system for each main wheel. A hydraul ic master cyl inder is attached
to each pilot ' s rudder pedal. Hydraulic lines and hoses are routed from
each master cyl inder to the wheel cyl inder on each brake assembly. No ...-.
manual adjustment is necessary on these brakes. The brakes can be operated
from either pilot's or copilot's pedals. The parking brake system consists
of a manually operated handle assembly, see Figure 7-1, connected to the
parking brake valves located in each main brake line. When pressure is
applied to the brake system and the parking brake handle is pulled, the
valve holds pressure on the brake assemblies until released. To release
the parking brakes, push the parking brake handle in. It is not necessary
to depress the rudder pedals when releasing the parking brake.
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ELECTRICAL SYSTEM
Electrical energy, see Figure 7-17, ;s supplied by a 28-volt, negative-
ground, direct current system powered by an alternator on each engine. The
el ect ri ca1 sy stem ha s independent ci rcu
i
ts for each side with each alter-
nator having its own regulator and overvoltage protection relay. The volt-
age regulators are connected to provide proper load sharing. The standard
location for the 24-volt battery is in the left stub wing. The optional
location for the 24-volt battery is in the nose area. Immediate detection
of low system voltage is provided by a LOW VOLT light on the annunciator
panel, see Figure 7-3. The light will illuminate when the airplane bus
voltage decreases below approximately 25 volts .
. - - - - - - - - - N O T E - - - - - - - - . ,
I Ensure all circuit breakers are engaged and ser-
viceable fuses are installed before all f1 ights.
Never operate wi th any blown fuses or di sengaged
circuit breakers without a thorough knowledge of the
consequences.
A hot battery bus is prOVided to supply power to essential circuits
regardless of the position of the battery switch (see Figure 7-17). This
bus is energized any time the battery or external power is connected to the
airplane. The circuits connected to the bus are protected from the battery
by a circuit breaker located in the wing near the battery and by individual
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circuit breakers. If the battery is located in the nose, the emergency
power and cabin lights circuit breakers are located near the battery in the
nose.
BATTERY AND ALTERNATOR SWITCHES
Separate battery and alternator switches, see Figure 7-18, are provided
as a means of checking for a malfunctioning alternator circuit and to
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permit such a ci rcuit to be turned off. If an alternator ci rcuit fail s or
malfunctions, or when one engine is not running, the switch for that al-
ternator should be turned off. Operation should be continued on the func-
tioning alternator, using only necessary electrical equipment. If both
alternator circuits should malfunction, equipment can be operated at short
intervals on the battery alone. In either case, a landing should be made
as soon as practical to check and repair the circuits.
7-24
1 November 1979
Revision 4 - 1 December 1983