Raytheon Beech Baron E55 - Page 618

Raynheon
Aircraft
Company
BARON
55
AND
58
SHOP
MANUAL
ALTERNATOR
LOAD
CONTROL UNITS
(SPLIT
VOLTAGE
REGULATORS)
AL
TERNA
TOR
CONTROL
UNITADJUSTMENT
(TC-2457
AND
AFTER;
TE-
1202 AND
AFTER
AND
TH-
1377
AND
AFTER)
Each
alternator
is
individually
controlled
by
an
alternator control unit
which
regulates voltage,
balances
the load and
provides
overvoltage
protection.
T
~-----7
i I ill II I I I
I
fR~
T
ALT/ C I I I III I I I I I I IALT
9
215764
8\ /s
467312
LEFT
REGULATOR
RIGHT
REGULATOR
EXTERNAL
WIRING
DIAGRAM
TERMINAL
IDENTIFICATION:
1.
REGULATOR INPUT
2.
FIELD
3.
N/C
4.
VOLTAGE SENSE
5. CONTROL
(+RELAY
COIL
28VDC,
1 AMP
MAX)
6.
CURRENT
SENSE MINUS
7.
CURRENT SENSE PLUS
8.
EQUALIZATION
9.
GROUND
y351-7
Alternator
Control Unit
Warning
I
Figure
3
The alternator
control
units
are
located in the
nose
baggage
compartment
under
the floor
forward
of
the
battery
I
compartment
on
TH-1377
thru TH-1395
except
TH-1389. On TC-2457
and
After;
TE-1202
and
After;
TH-1389 and
TH-1396
and
After,
the
alternator
control
units
are
located
on
the
forward side of
the
forward
bulkhead
on
both
the
right
and
left
upper
corners.
Load
sharing
depends
on
the alternators
being
adjusted
to
within
0.25
volts
of
each
other.
When
both
altemators
are
turned
on,
the
bus
voltage
will be the
output
of
the
highest
alternator and load
sharing
should be within
10%
of
the
output
of
one
alternator.
NOTE:
During
all
tests
and
adjustments
on
the alternator
control
unit,
make certain
that the
regulation
circuits,
including
any
meter
leads,
are
always
protected
from accidental
grounding
to
the
airplane
structure
and
contact
with other
circuits.
I
The
following
procedures
should be used
to
adjust
the alternator
control unit:
a.
Using
a
portable
precision
voltmeter
(0-50
volt
range,
1%
accuracy),
connect
the
positive
lead
to
the
aircraft
electrical
bus
and
the
negative
lead
to
structural
ground.
Dec
31/03Page
20
SECTION
13
E21