SECTION II
MODEL 560 AIRPLANE AND SYSTEMS
ELECTRICAL
GENERAL
Electrical power is normally supplied by two 28.5-volt direct current (DC), 300-ampere, engine-driven
starter/generators. A 24-volt, 40 or 44 ampere-hour, nickel-cadmium battery is located in the tailcone
compartment to supply power for starting and emergency requirements. A receptacle below the left engine
pylon is provided for connection of an external power unit.
ALTERNATING CURRENT (AC) POWER
Alternating current (AC) is provided by two 250 VA static inverters that convert 28 volt DC into 115
volts, 400 hertz AC and 26 volts, 400 hertz, single phase, single wave AC power. The AC system is a dual
split bus system in which the number one 115 and 26 volt AC buses, and the number two 115 and 26 volt
buses are powered by the number one and number two inverters respectively. If an inverter fails, the
respective INVTR FAIL, AC FAIL, and MASTER CAUTION lights will alert the crew to then manually select
the remaining inverter.
The AC power distribution system consists of a 2-position AVIONIC POWER switch, a 3-position INV
1/NORM/INV 2 switch, two 26 VAC/115 VAC, 400 Hz static inverters, four AC buses (two 26-volt and two
115-volt) and 2 annunciator panel lights (AC FAIL and INVERTER FAIL 1 and 2). Each inverter converts 28
volts DC into AC power, with a maximum output of 250 VA each.
Each inverter normally supplies AC power to its respective 115-volt and 26-volt buses; however, in the
event of an inverter failure, the pilot must select the remaining inverter with the INV 1/NORM/INV 2 switch
to connect the remaining good inverter to the 26-volt and 115-volt buses of the failed inverter. Inverter
failure is annunciated by illumination of the INVERTER FAIL 1 or 2 light, the AC FAIL light and the MASTER
CAUTION light. One inverter provides adequate power for the AC system; however, both inverters must be
operational for takeoff.
The AC system powers avionics and navigation equipment. The number two 26-volt AC (VAC) bus
provides reference voltage to the traffic collision avoidance system (TCAS). The number one 115 VAC bus
powers the pilot's vertical gyro. The number one 26 VAC bus provides reference voltage to the standby
horizontal situation indicator (HSI). The number two 115 VAC bus provides power for the copilot's vertical
gyro. When the battery switch is placed in the EMER position, AC power for the standby HSI is provided
by an internal static inverter in the pilot’s directional gyro.
Power to the AC system is controlled by two switches labeled AVIONIC POWER on the left instrument
panel. The right switch controls DC power to the system including DC power to the two 250 volt-ampere
inverters. The left avionics switch (INV 1/NORM/INV 2) controls AC power from each (or both) inverter(s)
to their respective 26 VAC and 115 VAC buses. The AC system is required to function normally prior to
flight.
I
56OMB-01 Configuration AA 2-35
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