SOCATA
MODEL TB 20
SECTION 7
DESCRIPTION
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© 1988, 1991, 1992, 1994 to 1996, 1997, 2000 -
socata
- All rights reserved
June 30, 1988
Revision 8
7.40
STANDARD ELECTRICAL SYSTEM
The airplane is equipped with a 28–volt, direct–current electrical system (see
Figures
A). A belt–driven 70–amp alternator installed on the
engine and, in standard version, a battery located in a compartment under
the baggage compartment floor, supply the system. In optional version, the
battery is located in a compartment over the front table, forward the R.H.
instrument panel.
The alternator is controlled by an alternator control unit providing voltage
regulation, plus overvoltage sensing.
A ”pull–off” type circuit breaker calibrated at 60 amps limits the alternator
electrical load to the battery and the networks.
ALTERNATOR CONTROL UNIT
The alternator control unit located on the firewall, on cabin side provides the
alternator voltage regulation and overvoltage protection.
In the event of overvoltage, the alternator control unit cuts off the alternator
field and the amber (red on UK airplanes) warning light labeled ”ALTr”
illuminates. In this case only the battery powers the airplane mains.
The reset of the alternator control unit is operated by disconnecting and
closing the switch–breaker labelled ”ALT
r
FLD”.
