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SECTION 7 CESSNA
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AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B (675 SHP)
ELECTRICAL
SYSTEM
(Continued)
AVIONICS BUS TIE SWITCH
The avionics bus tie switch is a two-position guarded toggle-type switch
located on the
left sidewall switch and circuit breaker panel. The switch
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connects the number 1 and number 2 avionics buses together in the
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event of failure of either bus feeder circuit. Because power for each
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avionics bus is supplied from a separate current limiter on the power
distribution bus, failure of a current limiter can cause failure of the
affected bus. Placing the bus tie switch to the ON position will restore
power to the failed bus. Operation without both bus feeder circuits may
require an avionics load reduction, depending on equipment installed.
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INVERTER SELECTOR SWITCH (Airplanes With KFC-250
Autopilot Only)
Two inverters, a main (inverter I) and a spare (inverter 2), are located
beneath the front passenger's floor. The inverters operate from DC
power supplied through two circuit breakers on the main bus. Each
inverter supplies 26-volt AC and 115-volt AC to the 26-volt AC bus bar
and 115-volt AC bus, respectively. The inverters are controlled by an
inverter selector switch located on the instrument panel below the
avionics stack. The selector switch had INVERTER 1, INVERTER 2
positions with a center unmarked off position. AC power is available
when the battery switch is on and the inverter selector switch is placed
in either INVERTER 1 or INVERTER 2 position.
(Continued Next Page)
1
7-88 U.S.
Revision
23
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