CESSNA SECTION 7
MODEL T182T NAV III AIRPLANE AND SYSTEM DESCRIPTION
GFC 700 AFCS
U.S.
ELECTRICAL SYSTEM
The airplane is equipped with a 28-volt direct current (DC) electrical
system (Refer to Figure 7-8). A belt-driven 95-ampere alternator
powers the system. A 24-volt main storage battery is located in the
tailcone of the airplane. The alternator and main battery are controlled
through the MASTER switch found near the top of the pilot's switch
panel.
Power is supplied to most electrical circuits through two primary buses
(ELECTRICAL BUS 1 and ELECTRICAL BUS 2), with an essential bus
and a crossfeed bus connected between the two primary buses to
support essential equipment.
The system is equipped with a secondary or standby battery located
between the firewall and the instrument panel. The STBY BATT switch
controls power to or from the standby battery. The standby battery is
available to supply power to the essential bus in the event that
alternator and main battery power sources have both failed.
The primary buses are supplied with power whenever the MASTER
switch is turned on, and are not affected by starter or external power
usage. Each primary bus is also connected to an avionics bus through
a circuit breaker and the AVIONICS BUS 1 and BUS 2 switches. Each
avionics bus is powered when the MASTER switch and the
corresponding AVIONICS switch are in the ON position.
BOTH BUS 1 AND BUS 2 AVIONICS SWITCHES
SHOULD BE TURNED OFF TO PREVENT ANY
HARMFUL TRANSIENT VOLTAGE FROM DAMAGING
THE AVIONICS EQUIPMENT PRIOR TO TURNING THE
MASTER SWITCH ON OR OFF, STARTING THE ENGINE
OR APPLYING AN EXTERNAL POWER SOURCE.
The airplane includes a power distribution module, located on the left
forward side of the firewall, to house all the relays used in the airplane
electrical system. The Alternator Control Unit (ACU), main battery
current sensor, and the external power connector are also housed
within the module.
(Continued Next Page)
T182TPHBUS-00
7-57
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