Cessna 182 1978 - Electrical Power Supply System; Master Switch; Split Bus Bar; Split Bus Power Relay

MODEL
182
&
T182
SERIES
SERVICE
MANUAL
Description
. .
.
......
2K17
16-55
Removal
Installation
of
Removal
Installation
.
...
.
2K17
16-55
Lithium
Four
Cell
Stall
Warning
System
.
..... 2K17
16-55
Battery
Pack
.
...
.
2K24
16-62
Description
.
.......
. 2K17
16-55
Trouble
Shooting
. ...
2K24
16-62
Pitot
Stall
Warning
Heaters
..
. 2K17
16-55
Emergency
Locator
Transmitter
Description
.
........
2K17
16-55
(Beginning
with
18265361)
....
2L2
16-64
Cigar
Lighter
. . . . .
. ... 2K17 16-55
Description.
.
. . . . . .
. 2L2. 16-64
Description
. . . ...
2K17 16-55
Operation .
.........
2L2 16-64
Removal Installation
. . . . . 2K17
16-55 Checkout
Interval . .
. . . 2L2 16-64
Emergency
Locator Transmitter
Removal Installation
of
(Thru 18265360)
.......
. 2K22,16-60
Transmitter
.........
2L6
16-68
Description
. . . . .
. . 2K2216-60
Removal/Installation
of
Operation ........
. 2K22/16-60 Anten .
. ........ 2L6 16-68
Checkout
Interval
.. . .
... 2K2216-60
Removal/Installation
of
Removal/Installation of
Battery Pack ....
. ... 2L7 16-69
Transmitter
.......
.. 2K22/16-60
Trouble Shooting
....
. .. 2L7
16-69
Removal/Installation
of
Electrical
Load Analysis
Antenna
..........
2K24/16-2
Chart ............
2L8 16-70
16-1.
ELECTRICAL
SYSTEMS.
tronic
installation.
(See figure
16-2.)
16-2. GENERAL.
This section
contains
service
in-
16-9.
MASTER
SWITCH.
formation
necessary
to
maintain
the
Aircraft
Electri-
cal
Power Supply
System, Battery
and
External Pow-
16-10.
DESCRIPTION.
The
operation
of the battery
er
Supply System,
Aircraft Lighting
System, Pitot
and
alternator system
is controlled
by a master
Heater,
Cigar
Lighter
and Electrical
Load
Analysis.
switch.
The switch,
when
operated,
connects
the
battery
contactor
coil
to ground
and
the
alternator
16-3.
ELECTRICAL
POWER
SUPPLY
SYSTEM.
field
circuit
to the battery,
activating
the power
sys-
tems.
The switch
is a inter-locking,
split
rocker
16-4.
DESCRIPTION.
Electrical
energy
for
the air-
with
battery
mode
on the
right
hand side
and the
craft
is
supplied
by
a 14-volt.
direct
current,
single-
alternator
mode
on
the left
hand
side.
This
arrange-
wire,
negative
ground
electrical
system.
A single
ment
allows
the battery
to
be on the
line without
the
12-volt
battery
supplies
power
for
starting
and
fur-
alternator,
however,
operation
of
the alternator
nishes
a reserve
source
of power
in
the event
of
alter-
without
the
battery
on
the line
is not
possible.
The
nator
failure
thru
1977
models.
Beginning
with
1978
switch
is
labeled
BAT
and
ALT
above
the
switch
and
models
the
electrical
system
is
28-volt
and a 24-volt
is
located
on the left
hand
side of
the switch
panel.
battery
is utilized.
An
engine-driven
alternator
is
the
normal
source
of
power
during
flight
and
maintains
a
16-11.
AMMETER.
battery
charge
controlled
by a
voltage
regulator.
An
external
power receptacle
is offered
as
optional
equip-
16-12.
DESCRIPTION.
The
ammeter
is
connected
ment
to supplement
the battery
system
for
starting
between
the battery
and
the aircraft
bus.
The
meter
and ground
operation.
indicates
the
amount
of current
flowing
either
to or
from
the battery.
With
a low
battery
and
the engine
16-5.
SPLIT
BUS BAR.
operating
at
cruise
speed,
the
ammeter
will
show
the
full alternator
output.
When
the
battery
is fully
16-6.
DESCRIPTION.
Electrical
power
is supplied
charged
and
cruise is
maintained
with
all electrical
through
a
split bus
bar.
One
side of
the bus
bar
sup-
equipment
off, the
ammeter
will show
a minimum
plies
power
to
the electrical
equipment
while
the other
charging
rate.
side
supplies
the electronic
installations.
When
the
master
switch
is closed,
the battery
contactor
en-
16-13.
BATTERY
POWER
SYSTEM.
gages
and
the
battery
power
is
supplied
to
the electri-
cal
side
of the
split
bus
bar.
The
electrical
bus
feeds
16-14.
BATTERY.
battery
power
thru
a relay,
thru 1977
models
and
an
avionics
master
switch beginning
with 1978
models,
16-15.
DESCRIPTION.
Thru 1977
models
the battery
to the
electronics
bus. On
the T182 the
electronic
furnished
as
standard equipment,
is
12-volt and
is
bus
is mounted
on the left
hand cabin
sidewall for-
approximately
25 ampere-hour
capacity.
A larger
ward
of the
doorpost.
heavy duty
battery
is offered
as optional
equipment.
The
heavy duty
battery
is
also 12-volt
but
is approx-
16-7.
SPLIT
BUS
POWER
RELAY.
(THRU
1977
imately
33
ampere
hour
capacity.
The
battery
is
MODELS).
mounted
in the
tailcone
and
is equipped
with
non-spill
filler
caps.
Since
the same
battery
box
is used
for
16-8.
DESCRIPTION.
A
power relay
is
installed
both batteries,
a spacer
is utilized
to
fill the
unused
behind
the instrument
panel
on all aircraft
utilizing
portion
of the battery
box
when
the smaller
standard
a split
bus bar.
The
relay
is a normally
closed
type.
battery
is installed.
Beginning
with
1978
models
a
opening
when
external
power
is connected
or when
24-volt
battery
is installed.
This
battery
has
an
the starter
is
engaged.
thus removing
battery
power
approximate
12. 75
ampere
hour
capactiy
on the
stan-
from
the electronic
side of
the split
bus bar
and pre-
dard battery
and
15. 5
ampere
hour capacity
on the
venting
transient
voltages
from
damaging
the elec-
optional
battery.
16-2