Electrical System
Schematic Symbols
ON
RELAY COIL
OFF
SWITCH
SHUNT WITH
METER
CURRENT
LIMITER
GROUND
DIODE
PUSH-PULL
CIRCUIT
BREAKER
SWITCH
BREAKER
FUSE
CHECK
VALVES
NORMALLY
OPEN
(NO)
NORMALLY
CLOSED
(NC)
King Air 200
October 1998
Developed for Training Purposes
4B-1
CAE SimuFlite
DC Electrical System
King Air 200
RIGHT GEN
CONTROL
RIGHT
STARTER
GEN
40
15A
REVERSE
CURRENT
PROTECTION
80
0
10
20
100
30
60A
DC LOAD
15A
+
-
SHUNT
EXT PWR
RIGHT GENERATOR BUS
60
20
0
RIGHT START RELAY
ISOLATION
LIMITER
325A
EXTERNAL POWER
PLUG-ENGAGED
SENSOR
BATTERY
BATTERY
RELAY FUSE
5A
RIGHT STANDBY
FUEL PUMP
5A
5A
LEFT STANDBY
FUEL PUMP
5A
5A
THRESHOLD LT
5A
LEFT FIREWALL
SHUTOFF VALVE
5A
RIGHT FIREWALL
SHUTOFF VALVE
H
O
T
BATTERY
RELAY
EXT POWER
RELAY
+
-
5A
RIGHT FIRE EXT
5A
+
-
LEFT
STARTER
GEN
4B-2
SHUNT
+
15A
LEFT GEN
CONTROL
B
A
T
T
E
R
Y
L FUEL FLOW
BB225 AND AFTER
BB364
AND
AFTER
+
LEFT START RELAY
-
15A
40
I
S
O
L
A
T
I
O
N
B
U
S
LEFT ENGINE FUEL
CONTROL HEAT
LEFT OIL TEMP
INDICATOR
FIRE DETECTION
LEFT ICE VANE
PROP
SYNCHROPHASER
CABIN PRESSURE
CONTROL
FLIGHT
INSTRUMENT LIGHTS
OVERHEAD AND
SIDE PANEL LIGHTS
PILOT'S TURN AND
SLIP INDICATOR
NO. 1 INVERTER
CONTROL
FUEL DRAIN
COLLECTER PUMPS
LEFT BLEED
AIR CONTROL
N
O
LOGO LIGHT
1
INSTRUMENT
DIRECT LIGHT
D
U
A
L
STALL WARNING
SYSTEM
F
E
D
B
U
S
LANDING GEAR
WARNING HORN
LEFT FUEL
VENT HEATER
OPTIONAL
ALTIMETER
TRIM TAB
LEFT GEN
CONTROL
YAW
DAMP
RIGHT PITOT
HEAT SW
LEFT MANUAL
PROP DEICE
ICE LIGHT SW
FLAP MOTOR
LANDING GEAR
CONTROL
FLAP CONTROL
& INDICATOR
STALL WARNING
HEAT
LEFT IGNITOR
POWER
R FUEL FLOW
BB225 AND AFTER
RIGHT ENGINE FUEL
CONTROL HEAT
RIGHT OIL TEMP
INDICATOR
RADIO & ENGINE
INSTRUMENT LIGHTS
CABIN FASTEN SEAT
BELT & NO SMOKING
SIGN AND CHIMES
LANDING GEAR
POSITION INDICATOR
RIGHT FUEL
VENT HEATER
COPILOT'S TURN &
SLIP INDICATOR
RUDDER BOOST
SYSTEM
N
O
RIGHT ICE VANE
2
AUTOFEATHER
CABIN TEMP
CONTROL
D
U
A
L
SUBPANEL AND
CONSOLE LIGHTS
F
E
D
ANNUNCIATOR
INDICATOR
B
U
S
RIGHTBLEED
AIR WARNING
50A
MANUAL PROP
DEICE CONTROL
RIGHT LANDING
LIGHT SW
RIGHT OIL
PRESSURE
INDICATOR
RIGHT BLEED
AIR CONTROL
60A
RECOGNITION
LIGHT SW
NAV LIGHT SW
CHIP DETECTOR
50A
RIGHT MANUAL
PROP DEICE
PROPELLER
GOVERNOR
RIGHT IGNITOR
POWER
RIGHT STARTER
CONTROL
LEFT STARTER
CONTROL
LEFT FUEL
PRESSURE
WARNING
LEFT AUX FUEL
QUANTITY
WARNING AND
TRANSFER
LEFT STANDBY
FUEL PUMP
WINDSHIELD WIPER
LEFT FIREWALL
VALVE
VACUUM DAMPER
SYSTEM
LEFT FUEL
QUANTITY
N
O
N
O
3
RIGHT FIREWALL
VALVE
D
U
A
L
RIGHT STANDBY
FUEL PUMP
F
E
D
RIGHT AUX FUEL
QUANTITY
WARNING AND
TRANSFER
B
U
S
RIGHT FUEL
PRESSURE
WARNING
FUEL
CROSSFEED
NO. 2 INVERTER
CONTROL
4
D
U
A
L
F
E
D
B
U
S
RIGHT FUEL
QUANTITY
RIGHT GEN
CONTROL
ISOLATION
LIMITER 325A
60A
50A
60A
50A
60A
50A
60A
50A
60
80
20
0
LEFT OIL PRESSURE
INDICATOR
AVIONICS
MASTER CONTROL
PNEUMATIC
SURFACE DEICE
EXT POWER CONNECTION
REVERSE
CURRENT
PROTECTION
STROBE
LIGHTS
ANNUNCIATOR
POWER
OVER
VOLT
PROT
50A
60A
PROP DEICE
AUTO HEAT SW
LEFT BLEED
AIR WARNING
B
U
S
5A
LEFT FIRE EXT
M
A
I
N
B
U
S
B
A
T
T
E
R
Y
LEFT LANDING
LIGHT SW
LEFT PITOT
HEAT SW
BEACON
LIGHTS SW
BATTERY
5A
SW
BB364 AND AFTER
60A
TAXI LIGHT SW
SHUNT
BATTERY
CHARGE
SENSOR
50A
0
10
20
30
DC LOAD
100
LEFT GENERATOR BUS
Developed for Training Purposes
King Air 200
October 1998
Electrical System
RIGHT GENERATOR BUS
FROM NO. 2
DUAL FED BUS
MOD OPTIONAL
EQUIPMENT
5A
LDG GEAR CONTROL
VENT BLOWER
POWER
60A
50A
AFT EVAPORATOR
BLOWER POWER 30A
LANDING GEAR
MOTOR CONTROLLER
AND DYNAMIC BRAKE
AIR CONDITIONER
CLUTCH
50A
COPILOT'S
WINDSHIELD
ANTI-ICE
20A
RIGHT RADIANT
HEAT
7.5A
15A
LANDING
GEAR
MOTOR
40A
60A
50A
TO AC
POWER
DC TEST JACK
AVIONICS BUS NO. 2
30A
AVIONICS NO. 2
POWER RELAY
AVIONICS BUS NO. 3
FROM NO. 1
DUAL FED BUS
AVIONICS NO. 3
POWER RELAY
AVIONICS
SWITCH
ON
AVIONICS BUS NO. 1
5A
AVIONICS OFF
MASTER
CONTROL
AVIONICS NO. 1
POWER RELAY
30A
50A
PILOT'S
WINDSHIELD
ANTI-ICE
20A
LEFT RADIANT
HEAT
CONDENSER
BLOWER
60A
30A
TO AC
POWER
40A
40A
50A
CURRENT
LIMITER
LEFT GENERATOR BUS
King Air 200
October 1998
Developed for Training Purposes
4B-3
CAE SimuFlite
DC Electrical System
King Air B200
RIGHT GEN
CONTROL
RIGHT
STARTER
GEN
40
80
0
15A
+
-
SHUNT
EXT PWR
10
20
100
30
60A
DC LOAD
15A
REVERSE
CURRENT
PROTECTION
RIGHT GENERATOR BUS
60
20
0
ISOLATION
LIMITER
325A
RIGHT START RELAY
BEACON LIGHTS
SWITCH
STROBE LIGHTS
SWITCH
M
A
I
N
BATTERY SW
5A
R NAV
MEMORY (OPT)
STEREO (OPT.)
5A
ENTRY LTS &
CLOCK LTS &
EXT PWR SENSE
5A
RIGHT STANDBY
FUEL PUMP
5A
LEFT STANDBY
FUEL PUMP
5A
5A
2
2
5A
5A
THRESHOLD LT
LEFT FIREWALL
SHUTOFF VALVE
RIGHT FIREWALL
SHUTOFF VALVE
LEFT FIRE EXT
RIGHT FIRE EXT
5A
5A
H
O
T
BATTERY
RELAY
B
A
T
T
E
R
Y
+
-
B
U
S
5A
4B-4
B
U
S
+
-
ISOLATION
LIMITER
325A
SHUNT
+
15A
LEFT START RELAY
-
15A
40
PROP
SYNCHROPHASER
N
O
FLIGHT & GYRO
INSTRUMENT LIGHTS
1
OVERHEAD AND
SIDE PANEL LIGHTS
D
U
A
L
LEFT BLEED
AIR WARNING
PITCH TRIM
LEFT GEN CONTROL
60A
50A
F
E
D
B
U
S
FIRE DETECTION
LEFT CHIP
DETECTOR
INSTRUMENT
INDIRECT LIGHTS
STALL WARNING
SYSTEM
RECOGNITION
LIGHTS
LANDING GEAR
CONTROL
RIGHT PITOT HEAT
STALL WARNING
HEAT
RIGHT OIL TEMP
TEMPERATURE
RIGHT ENGINE FUEL
CONTROL HEAT
R ICE VANE CONT
RIGHT CHIP
DETECTOR
CABIN READING
LIGHTS
RIGHT BLEED AIR
WARNING
NO. 1 INVERTER
CONTROL
LEFT OIL
TEMPERATURE
CABIN PRESS
CONTROL
ANNUNCIATOR
INDICATOR
WINDSHIELD WIPER
CABIN TEMP
CONTROL
N
O
RIGHT GEN
OVERHEAT (OPT.)
AUTOFEATHER
2
AVIONICS & ENGINE
INSTRUMENT LTS
D
U
A
L
COPILOT'S TURN
& SLIP
F
E
D
B
U
S
FLOURESCENT LTS
NO SMK, FSB, AND
CABIN
RIGHT FUEL
VENT HEAT
FURNISHINGS
MASTER CONTROL
RUDDER BOOST
CONTROL
60A
RIGHT MANUAL
PROP DEICE
FLAP MOTOR
PROPELLER
GOVERNOR
FLAP CONTROL
& INDICATOR
RIGHT IGNITOR
POWER
LEFT IGNITOR
POWER
RIGHT STARTER
CONTROL
N
O
LEFT FUEL
PRESSURE
WARNING
LEFT FUEL
QUANTITY
LEFT AUX FUEL
QUANTITY
WARNING AND
TRANSFER
LEFT STANDBY
FUEL PUMP
N
O
3
4
D
U
A
L
RIGHT FIREWALL
VALVE
F
E
D
RIGHT STANDBY
FUEL PUMP
RIGHT AUX FUEL
QUANTITY
WARNING AND
TRANSFER
B
U
S
RIGHT FUEL
QUANTITY
LEFT FIREWALL
VALVE
RIGHT GENERATOR
CONTROL
CIGARETTE
LIGHTER
60A
50A
D
U
A
L
F
E
D
B
U
S
RIGHT FUEL
PRESSURE
WARNING
FUEL
CROSSFEED
CABIN PRESSURE
LOSS (OPT.)
RIGHT BLEED AIR
CONTROL
50A
MANUAL PROP
DEICE CONTROL
LANDING GEAR
POSITION IND
NO. 2 INVERTER
CONTROL
50A
60A
LEFT MANUAL
PROP DEICE
RIGHT OIL PRESS
INDICATOR
RIGHT OIL PRESS
WARNING (OPT.)
RIGHT FIRE
DETECTION
50A
LEFT STARTER
CONTROL
RIGHT FUEL
FLOW INDICATOR
LEFT FUEL
VENT HEATER
PILOT'S TURN
& SLIP
ICE LIGHTS
NAV LIGHTS
LANDING GEAR
WARNING HORN
YAW DAMPER
TAXI LIGHT
SWITCH
RIGHT LANDING
LIGHT SWITCH
OVERHEAD,
SUBPANEL AND
CONSOLE LTS
BRAKE DEICE
(OPTIONAL)
60A
60
60A
50A
80
20
0
LEFT ENGINE FUEL
CONT HEAT
LEFT GEN
OVERHEAT (OPT.)
ENCODER
ALTIMETER (OPT.)
+
LEFT OIL PRESSURE
WARNING (OPT.)
LEFT ICE VANE
CONT
LEFT BLEED AIR
CONTROL
EXT POWER
CONNECTION
LEFT GEN
CONTROL
I
S
O
L
A
T
I
O
N
AUTOMATIC
OXYGEN CONTROL
5A
LEFT FUEL FLOW
LEFT OIL PRESSURE
ANNUNCIATOR
POWER
OVER
VOLT
PROT
TAIL FLOOD
LIGHTS SWITCH
AVIONICS
MASTER CONTROL
PNEUMATIC
SURFACE DEICE
5A
REVERSE
CURRENT
PROTECTION
B
U
S
EXT POWER
RELAY
1
LEFT
STARTER
GEN
B
A
T
T
E
R
Y
5A
BAT RELAY
LEFT PITOT
HEAT
PROP AUTOMATIC
HEAT SWITCH
SHUNT
50A
60A
L EFT LANDING
LIGHT
EXTERNAL POWER
PLUG-ENGAGED
SENSOR
BATTERY
BATTERY
CHARGE SENSOR
50A
0
10
20
30
100
DC LOAD
LEFT GENERATOR BUS
1
ON BB-1096, BB-1098 AND SUBSEQUENT
CIRCUIT BREAKERS REPLACE FUSES
2
ON BB-1097, BB-1095 AND PRIOR
Developed for Training Purposes
King Air 200
October 1998
Electrical System
RIGHT GENERATOR BUS
FROM NO. 2
DUAL FED BUS
MOD OPTIONAL
EQUIPMENT
5A
LDG GEAR CONTROL
VENT BLOWER
POWER
60A
AFT EVAPORATOR
BLOWER POWER
LANDING GEAR
MOTOR CONTROLLER
AND DYNAMIC BRAKE
AIR CONDITIONER
CLUTCH
50A
30A
50A
COPILOT'S
WINDSHIELD
ANTI-ICE
20A
RIGHT RADIANT
HEAT
7.5A
15A
50A
40A
60A
TO AC
POWER
DC TEST JACK
LANDING
GEAR
MOTOR
30A
AVIONICS BUS NO. 2
AVIONICS NO. 2
POWER RELAY
AVIONICS BUS NO. 3
FROM NO. 1
DUAL FED BUS
AVIONICS NO. 3
POWER RELAY
AVIONICS
SWITCH
ON
AVIONICS BUS NO. 1
5A
AVIONICS
MASTER OFF
CONTROL
AVIONICS NO. 1
POWER RELAY
30A
50A
20A
PILOT'S
WINDSHIELD
ANTI-ICE
LEFT RADIANT
HEAT
CONDENSER
BLOWER
30A
TO AC
POWER
40A
60A
40A
50A
LEFT GENERATOR BUS
King Air 200
October 1998
Developed for Training Purposes
4B-5
CAE SimuFlite
4B-6
Developed for Training Purposes
King Air 200
October 1998
Electrical System
Electrical System
DC System
DC electrical sources include:
■
a 24V, 34 amp-hour nickel-cadmium battery
■
two 250A 30V DC starter/generators
■
an external DC power system.
These power sources supply the dual-fed bus system that distributes power to the aircraft through circuit breakers:
■
Battery
The battery powers starting and emergency operation of essential equipment powered from the Hot Battery bus. With the BATT
switch in ON, power flows from the battery through the battery
relay to the Main Battery bus. The Main Battery bus then feeds
the Isolation bus that, in turn, provides power to the Left and
Right Generator buses. Once the Generator buses are powered, the four Dual-Fed buses are powered.
The Main Battery bus also supplies two starter circuits controlled
by the engine starter switches and starter relays.
For nicad batteries, a battery charge current detector continuously monitors battery charging rate. If charging rate exceeds 7
amps for six seconds or more, the monitoring system illuminates
the BATTERY CHARGE annunciator and triggers the flashing
MASTER CAUTION annunciators. After a battery engine start,
the BATTERY CHARGE annunciator normally illuminates after
the operating engine generator is turned on.
King Air 200
October 1998
Developed for Training Purposes
4B-7
CAE SimuFlite
Generators
The generators function as starters during engine starts. Once
an engine is running, the generators provide DC power to the
aircraft. GEN 1 and GEN 2 switches control the generators. The
MASTER SWITCH gang bar turns off the battery and generator
switches simultaneously.
Reverse-current protection prevents the generators from
absorbing power from the Generator buses if the generators are
not operating, or if generator voltage is less than bus voltage.
Voltage Regulation
On aircraft BB-2 to 88, a voltage regulation system consists of
transistorized regulators, overvoltage relays, paralleling relays,
and reverse current relays. These components provide:
■
generator load paralleling
■
reverse current cutout
■
voltage regulation to 28.25 ±0.25V DC
■
overvoltage protection
■
under voltage protection
■
starter/generator priority
The voltage regulators (one for each generator) maintain a constant level voltage output. The paralleling circuit functions when
both generators are on-line. The circuit depresses the voltage of
the high- output generator and increases that of the low-output
generator until both are equal.
If generator output exceeds 32 to 34V, the overvoltage relay
trips to take the generator off-line. Actuation of the overvoltage
relay also removes voltage from the SW terminal of the reversecurrent relay so it opens and removes the generator from the bus.
If the overvoltage condition is the result of a voltage regulator malfunction, the overvoltage relays stops the condition. If generator
output voltage drops below bus voltage, the reverse current relay
isolates the generator from the bus to protect the generator.
4B-8
Developed for Training Purposes
King Air 200
September 2002
Electrical System
On aircraft BB-89 and subsequent; BL-1 and subsequent,
generator control units (GCUs) and line contactor relays regulate voltage to provide:
■
voltage regulation
■
line contactor relay control
■
generator load paralleling
■
differential voltage and reverse current sensing and control
■
overvoltage and overexcitation control
■
start/generator priority.
Once the engine is running, the GCU uses residual voltage to
build generator voltage to the point where it can actually regulate
output voltage. Once generator output reaches this point, the
GCU increases generator output until it reaches 28.25 ±0.25V
DC. At this point, generator output can be connected to the associated Generator bus.
After the GEN switch is in ON, the GCU compares bus voltage
to generator output voltage. When these voltages are nearly the
same, the GCU closes the line contactor relay. Generator output
is then connected to the respective Generator bus. With both
generators on-line, the GCU equalizer relay energizes to enable
load paralleling circuits. Both GCUs compare their respective
generator’s output voltage to the opposite generator. The GCUs
then adjusts generator output voltage so both generators equally share the load within approximately 10%.
If a generator begins drawing current from the electrical system
(i.e., reverse current condition), the GCU opens the line contactor relay to remove the generator from its Generator bus. Once
the reverse current condition clears, the GCU automatically
resets and the generator comes back on-line.
An overvoltage condition can occur when generator output
voltage increases to 32V DC. If this occurs, the GCU will deenergize the generator and trip the line contactor. Once the
overvoltage condition clears, the generator must be manually
brought back on-line.
King Air 200
September 2002
Developed for Training Purposes
4B-9
CAE SimuFlite
External Power
An appropriately rated ground power unit (GPU) can supply the
aircraft electrical system through an external power receptacle
on the right wing. The ground power unit (GPU) should be capable of providing a continuous load of 300A at 24 to 30V DC and
1,000A for 0.1 seconds during engine start. Use of an inadequate GPU will cause a voltage drop below the start relay’s
drop-out voltage. This may result in relay chatter and welded
contacts. Similarly, a GPU that provides more than 350A continuous load will damage the external power relay and airplane
power cables. Connecting a GPU illuminates the EXT PWR
annunciator. With external power connected, the generators will
not come on-line.
CAUTION: The output setting must not exceed 1,000A on
external power sources with a higher current-carrying
capability. Any current in excess of 1,000A may overtorque
the starter-generator driveshaft or produce heat sufficient
to shorten starter-generator life.
4B-10
Developed for Training Purposes
King Air 200
September 2002
Electrical System
DC Power Distribution
The DC power distribution system includes:
■
Hot Battery bus
■
Main Battery bus
■
Isolation bus
■
Left and Right Generator buses
■
Nos. 1, 2, 3, and 4 Dual-Fed buses
■
Nos. 1 and 2 Avionics buses
■
optional No. 3 Avionics bus.
The battery directly powers the Hot Battery bus. This bus is unswitched (i.e., always powered) and supplies power to items that
may be operating with the battery switch OFF. With the battery
switch ON, the closed battery contacts connect the battery to
the Main Battery bus.
The primary load of the Main Battery bus is the left and right
starter/generators during engine start. It also powers the
Isolation bus. With a GPU connected to the aircraft, the Main
Battery bus is powered through the closed external power relay.
The Isolation bus serves as a connection between the Left and
Right Generator buses. High amperage current limiters between
the Isolation bus and the Generator buses isolate the battery
from a Generator bus fault.
Each of the four Dual-Fed buses receive power simultaneously
from the Left and Right Generator buses. These buses are
always powered from a combination of three sources. Typically,
these sources are both generators or a generator and/or battery.
The left and right generators power, respectively, the Nos. 1 and
2 DC Avionics buses. The AVIONICS MASTER switch and
avionics master power relays control this power. With the switch
in ON, the relays de-energize to the normally closed position to
ensure that if the switch fails, the relays provide continued
power to the avionics equipment.
King Air 200
September 2002
Developed for Training Purposes
4B-11
CAE SimuFlite
AC Electrical System
KING AIR 200
RIGHT GEN BUS
YAW RATE
(BB113 AND AFTER)
50 A
26V
AC
NO. 2
INV
2
6
V
RIGHT ENGINE
TORQUEMETER
A
C
RIGHT ENGINE FUEL FLOW
(PRIOR TO BB225)
B
U
S
LEFT ENGINE
TORQUEMETER
LEFT ENGINE FUEL FLOW
(PRIOR TO BB225)
115V AC
5A
INV
CONTROL
RELAY
FROM NO. 2
DUAL-FED BUS
KING AIR B200
2
6
V
10A
INV
SELECT
SWITCH
NO. 2 INV
CONTROL
AC
AVIONICS
AND
RADAR
5A
5A
YAW RATE
A
C
RIGHT ENGINE
TORQUEMETER
B
U
S
LEFT ENGINE
TORQUEMETER
1
1
5A
5A
NO. 1 INV
CONTROL
FROM NO. 1
DUAL-FED BUS
10A
INV
SELECT
RELAY
INV
CONTROL
RELAY
5A
INVERTER
115V AC
NO. 1
INV
26 V
AC
380
4B-12
400
110
100
5A
410
120
130
420
AC VOLTS
LEFT GEN BUS
1
INST INV
TEST JACK
390
50A
MODEL VARIATION
ANNUNCIATOR
KING AIR B200 KING AIR 200
VOLTS/FREQUENCY METER
BB-1097, BB-1095 AND PRIOR
FROM NO. 2
DUAL-FED BUS
Developed for Training Purposes
King Air 200
October 1998
Electrical System
AC Power
Two 250VA or 750VA, 400 Hz static inverters supply 115V and
26V AC power. Each inverter operates on 28V DC. The Left
Generator bus powers the No. 1 inverter while the Right
Generator bus powers the No. 2 inverter.
Placing the INVERTER switch in the No. 1 or No. 2 position
energizes the respective inverter’s control relay. The relay closes so that Generator bus powers the inverter. The INVERTER
switch also controls the inverter select relay to connect the 26V
AC buses to the selected inverter and 115V AC to the
voltage/frequency meter and inverter fail relay.
THE INVERTER or INST INV annunciator illuminates when
115V is lost at the annunciator relay.
MODEL
King Air 200
September 2002
PC-250
PC-17A
250VA
750VA
115V ±3%
115V +5% or -7%
400 Hz ±1%
400 Hz ±1%
Developed for Training Purposes
4B-13
CAE SimuFlite
Electrical Systems
DC Electrical System
Power Source
Battery
Starter/Generators (2) 250A (STD)
External power unit
Distribution
Hot Battery bus
Battery relay
Main Battery bus
Start Relays (left and right)
Isolation bus
Generator buses (left and right)
Dual-Fed buses (No. 1 through 4)
Avionic buses (No. 1, No. 2, and optional No. 3)
Control
Switches
BATT
IGNITION AND ENGINE START (L/R)
Two-position GEN (1/2) – BB-088 and prior
Three-position GEN (1/2) – BB-089 and sub.
Monitor
DC volt/loadmeter (L/R)
GEN annunciators (L/R)
EXT POWER annunciator
Battery Charge annunciator
Protection
Voltage regulator
Generator paralleling
Reverse current sensing and control
Over-voltage protection
Over-excitation protection
Under-excitation protection
GPU Reverse polarity sensing
Generator buses
Isolation limiters (325A)
Current limiters
Circuit breakers
Dual-fed buses
Current limiters (60A)
Circuit breakers (50A)
Diodes (70A)
Hot Battery bus
Fuses or circuit breakers
4B-14
Developed for Training Purposes
King Air 200
September 2002
Electrical System
AC Electrical System
Power Source
Inverters (250VA – 750VA)
Distribution
Generator buses (L/R)
Inverters Nos 1 and 2
26V AC bus
115V AC avionics
Control
INVERTER switch
Monitor
INVERTER annunciator
Volt/Frequency meter
Protection
DC to inverter: 50A current limiter
Inverter output: fuses and circuit breakers
King Air 200
September 2002
Developed for Training Purposes
4B-15
CAE SimuFlite
4B-16
Developed for Training Purposes
King Air 200
October 1998