Electrical Power Supply System; Split Bus Bar; Split Bus Power Relay; Master Switch - Cessna T182 Series Service Manual

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