Pilot’s Operating Handbook Section 7
EXTRA 500 Description of Airplane and Systems
7.18 Electrical System
The electrical system is a 28 VDC system with negative ground.
The primary DC power source is an engine driven 28 V / 200 A
starter-generator. It is backed up by an engine driven 26 V/20 A
standby alternator. In addition a lead acid battery (24 V/28 Ah)
is installed in the engine compartment. Normal battery power is
sufficient to start engine or for ground check operation.
An external 28 V DC power receptacle and its circuit breaker
are installed in a hatch right hand at fixed portion of the
cowling.
A battery charge adapter is installed at the external power
receptacle. The battery may be charged with 29.0 V and 5 A.
The main control switches of the electrical power system are
located on the
MAIN section of the left side panel and are
marked
EXT PWR, BATT, T STBY ALT, GEN and GEN TEST.
Electrical power from the various power sources is supplied to
the “Electrical Heart” installed on the engine side of the
firewall. From there power is distributed partly through
individual fuses to the following buses:
• Hot Bus,
• Emergency Bus,
• Battery Bus,
• Load Bus,
• Avionics Bus.
For further information refer to
Figure 7-15, Electrical System
Schematic.
26. January 2011 7-49
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