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71. Electrical power is supplied by a 28-volt direct current system with the following
characteristics:
a. power is generated by an engine driven 28 Volt 60 amp alternator;
b. power for starting and for emergency situations is provided by a sealed 11 amp-hr
battery located in the tail, aft of the baggage compartment;
c. power is supplied to all electrical circuits through a split bus bar, one side serving
electronic circuits and components and the other side serving general electrical
system components;
d. electrical circuits and equipment are protected by push-to-reset type circuit
breakers;
e. a split rocker style Master Switch is used to connect the alternator and the battery
to the electrical system;
f. a Radio Master Switch is used to isolate the electronic circuits from transient
voltage spikes during start-up and shutdown; and
g. battery voltage, electrical loads, alternator output and associated limit alerts are
displayed on the EDM-930.
72. A basic schematic of the aircraft electrical system is provided on the following page.
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