Canadair Regional Jet 100/200 - Electrical
1.
INTRODUCTION
The aircraft uses both 115 Volts AC and 28 volts DC power. AC electrical power is provided
by two engine-driven generation systems. Each system includes an integrated drive
generator (IDG) and a generator control unit (GCU). An auxiliary power unit (APU)
generator is also available as a back AC power source to replace either or both IDGs.
In the event of total AC power loss, emergency AC power is available from an in-flight
air-driven generator (ADG). The ADG assembly is stowed in a compartment on the right
side of the nose section.
DC power is supplied by five transformer rectifier units (TRU) which rectifies AC input power
into DC output power. Another source of DC power is from a main battery and APU battery.
The main and APU batteries are connected into the aircraft DC electrical power system and
are charged by their respective battery chargers. Power for starting the APU is provided by
the APU battery.
Electrical contactors, switches and relays located throughout 13 junction boxes in the
aircraft, are used for connecting AC and DC power to the appropriate buses and
components. Power connection is dependent on system configuration and health. The
following is a list of all the aircraft electrical system buses:
DC BUSSES
DC BUS 1
AC BUSSES
DC BUS 2
AC BUS 1
DC ESSENTIAL BUS
DC SERVICE BUS
AC BUS 2
AC ESSENTIAL BUS
LEFT AND RIGHT BATTERY BUS
AC SERVICE BUS
ADG BUS
DC EMERGENCY BUS
DC UTILITY BUS 1
DC UTILITY BUS 2
AC UTILITY BUS 1
AC UTILITY BUS 2
MAIN BATTERY DIRECT BUS
APU BATTERY DIRECT BUS
On the ground, the aircraft can receive external AC power through a receptacle located on
the forward right side of the fuselage. The aircraft can also receive external DC through a
receptacle located on the aft right side of the fuselage.
The electrical power services panel (EPSP) in the flight compartment, and the external
service panel on the right forward fuselage, contain the AC and DC system control switches.
The switches are used for manual and automatic control of the electrical power generating
system and external power operation.
Page 1
Canadair Regional Jet 100/200 - Electrical
Electrical system warnings and cautions are displayed on the EICAS primary page. Status
and advisory messages are displayed on the EICAS status page. General views of the
electrical systems are displayed on the EICAS, AC and DC synoptic pages. The AC and DC
synoptic pages are accessed through the EICAS control panel (ECP). One push of the
ELEC key on the ECP will display the AC synoptic page. Pushing the ELEC key a second
time will display the DC synoptic page.
Page 2
Canadair Regional Jet 100/200 - Electrical
MAIN BATTERY
APU BATTERY
IDG 1
APU GENERATOR
IDG 2
EXTERNAL DC
CONNECTION
TRANSFORMER
RECTIFIER
UNITS
EXTERNAL AC
CONNECTION
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AIR DRIVEN
GENERATOR
Canadair Regional Jet 100/200 - Electrical
External Service Panel
Right Forward Fuselage
Electrical Power Panel
Overhead Panel
Flight Attendant Panel
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Canadair Regional Jet 100/200 - Electrical
1.
AC ELECTRICAL SYSTEM
AC power for the aircraft electrical systems is provided by two engine-driven, integrated
drive generators (IDGs) which supply power to all AC buses during normal operations. An
APU generator provides a backup AC power source in flight if an IDG is inoperative or when
the aircraft is on the ground with the engines off. If all AC power is lost in flight, emergency
AC power is provided automatically by a deployable air-driven generator (ADG). The AC
distribution system is controlled by the respective IDG and APU generator control units
(GCUs). Each generator is monitored by the GCU’s for voltage, frequency and kilovolt amps
(KVA) to provide system fault protective shutdowns. An AC power distribution schematic
and system parameters are displayed on the EICAS AC synoptic page.
A.
Integrated Drive Generator (IDG)
Each IDG consists of a constant speed drive (CSD) and a generator. The CSD uses an
internal oil system to hydro--mechanically change the variable input speed from the
engine accessory gearbox to a constant output speed to the generator to produce
115--volts AC and to maintain a constant frequency of 400 Hz. Each generator is rated
at 30 kilovoltamperes (KVA) up to an altitude of 35,000 ft., then 25 KVA to 41,000 ft.
An oil cooler cools the oil used by the IDG. Each IDG is monitored for low oil pressure
or high oil temperature. In the event of low oil pressure or high oil temperature, an
(amber) FAULT light (cover--guarded) on the EPSP will illuminate. Lifting the
cover--guard and pushing the switchlight will manually disconnect the IDG from the
engine gearbox.
The IDG will automatically disconnect if a severe oil overtemperature or overtorque
condition occurs. Once disconnected, either manually or automatically, the IDG cannot
be reconnected in flight. If the IDG was disconnected manually, it can only be reset on
the ground, with the engine shutdown. If the IDG was disconnected automatically, it
must be replaced.
Each generator control unit (GCU) controls and monitors the related AC generator
system and provides voltage and frequency regulation and fault protection for its
respective generator. The GCU also protects the electrical system from overcurrent
and differential current faults. In the event of a malfunction, the GCU will automatically
disconnect the faulty generator from the respective AC buses. The generator may be
reset when the malfunction is corrected or no longer exists, by selecting the generator
switch to the OFF/RESET position then back to ON.
B.
APU Generator
The APU generator is driven, directly by the APU gearbox, at a constant speed to
maintain a constant frequency output. The generator provides 115--volts, 400 Hz AC
power and is rated at 30 KVA from sea level to 37,000 ft. A GCU, identical to the IDG
GCU, provides the same regulation and protection functions as the IDG GCUs.
C.
AC Distribution
Two different configurations of AC power distribution are available, Full configuration
and Service configuration.
Page 5
Canadair Regional Jet 100/200 - Electrical
In Full configuration, all the AC buses are powered using either IDG 1, IDG 2, the APU
generator or external AC. For normal AC distribution, AC power from IDG 1 and IDG 2
is distributed to all the AC buses via GCU controlled contactors in junction box 1 (JB1).
There is a priority control of AC power distribution. During normal operation, IDG 1
powers AC bus 1 and IDG 2 powers AC bus 2. The failure of a generator, for any
reason other than a fault on its associated bus, will automatically transfer the load from
the failed IDG to the remaining operative IDG. When the APU generator is available, it
can then be used to replace the failed IDG to power the respective AC bus. On the
ground, if the aircraft is being powered with external AC power and either the APU or
an IDG is brought on line, the external power will be automatically disconnected and the
respective APU or IDG generator will power all the AC buses. When external power is
not available, the APU generator provides electrical power to all the AC buses. If an
IDG is powering its respective AC bus and the APU generator is powering the other AC
bus, when the remaining IDG is brought on line the APU generator will be automatically
taken off line.
In service configuration, either external AC power or the APU generator is used to
power specific buses for general servicing of the aircraft on the ground. Only AC Utility
bus 1, AC Utility bus 2, the AC service bus and the DC service bus are powered.
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,'* Canadair Regional Jet 100/200 - Electrical
GCU
LEFT
ENGINE
RIGHT
ENGINE
APU
CSD
CSD
APU
GEN
GEN
1
GCU
GCU
GCU
GEN
2
EXTERNAL
POWER
MONITOR
AC BUS 1
ADG
AC ESS BUS
AC BUS 2
AC UTIL
BUS 1
AC UTIL
BUS 2
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EXTERNAL
AC
AC SERV
BUS
ADG BUS
Canadair Regional Jet 100/200 - Electrical
AC ESS XFER
Used to switch essential bus feed
from AC bus 1 to AC bus 2.
ALTN (white) light indicates
essential bus is fed from AC bus 2.
Transfer is automatic during an AC
bus 1 failure.
IDG 1 and 2 DISC
(Guarded)
Used to disconnect
IDG from engine.
DISC (white) light
indicates selected
disconnect is successful.
FAULT (amber) light
indicates a fault within
IDG (low oil pressure or
high oil temperature).
AC
Used to select external
AC power.
AVAIL (green) light
indicates external
power is connected
and is ready to use.
IN USE (white) light
indicates that the
external AC power unit
is supplying the
electrical system.
ON
IDG will automatically
disconnect, when an
overtemperature or
overtorque condition
occurs.
Once disconnected, the
IDG cannot be reset with
the engines running.
Electrical Power Panel
Overhead Panel
AUTO XFER
Used to disable automatic
transfer of associated IDG.
OFF (white) light indicates
autotransfer is selected off.
FAIL (amber) light indicates a
fault preventing autotransfer.
EXT AC PUSH
Used to select
external AC power.
AVAIL (green) light
indicates external
power is connected
and is ready to use.
IN USE (white) light
indicates that the
external AC power
unit is supplying the
electrical system.
External Service Panel
Right Forward Fuselage
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GEN 1, 2 and APU GEN
AUTO -- Connects
generator to
associated bus.
OFF/RESET -Disconnects generator
from associated bus
and/or resets the
generator control
circuit.
Canadair Regional Jet 100/200 - Electrical
Flow Lines
Green -- Bus energized.
Blank -- Bus not energized.
Generator Load
Displays the load on
the generator.
Generator Voltage
Displays the generator
voltage level.
Generator Frequency
Displays the generator
frequency level.
AC Electrical Page
EICAS DIGITAL
READOUT
XX KVA
XXX V
XXX HZ
GREEN
AMBER
WHITE
Generator
loaded
Voltage
100--125 VAC
Frequency
375--425 Hz
Generator
overload
_
Generator not
loaded
Voltage not
in range
Frequency
not in range
_
HALF INTENSITY
AMBER DASHES
MAGENTA
Invalid data
_
_
Invalid data
_
Invalid data
EICAS
OUTLINE
GREEN
AMBER
GEN
Generator on
Generator off
with engine /
APU running
Both generator
and engine /
APU are off
Invalid data
IDG
Constant
speed drive on
Low oil pressure
or high oil
temperature
Engine is off or
IDG has
disconnected
Invalid data
_
_
Engine / APU off
Invalid data
Bus not powered
_
Invalid data
Bus not powered
_
Invalid data
_
Invalid data
_
Invalid data
APU
BUS 1
BUS 2
Bus powered
(generator line
contactor 1)
Bus powered
(generator line
contactor 2)
ESS BUS
Bus powered
SERV BUS
Bus powered
UTIL BUS 1
Bus powered
UTIL BUS 2
Bus powered
Bus inoperative
(essential bus
fail)
Bus inoperative
(AC service bus
fail)
_
_
WHITE
Bus not powered
(shed)
Bus not powered
(shed)
HALF INTENSITY HALF INTENSITY
MAGENTA
CYAN
Invalid data
Invalid data
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_
_
Engine / APU
running and
ready to load
Canadair Regional Jet 100/200 - Electrical
ADG Features
Displayed when ADG voltage is more than 10 volts
and frequency is more than 300 Hz.
SHED (white)
Indicates that the respective AC utility
bus has been automatically shed.
AUTO XFER OFF (white)
Indicates that corresponding automatic
transfer has been selected off.
AUTO XFER FAIL (amber)
Indicates that corresponding automatic
transfer has failed.
AC Electrical Page
DISC (white)
Indicates that IDG has been disconnected.
EICAS DIGITAL
READOUT
Less than 108 volts or
more than 130 volts
Less than 360 Hz or
more than 440 Hz
Between 108 and
130 volts
Between 360 and
440 Hz
XXX V
XXX HZ
EICAS
OUTLINE
AMBER DASHES
WHITE
GREEN
GREEN
Invalid data
Invalid data
WHITE
ADG BUS
ADG outline green
ADG outline white
ADG
Voltage and frequency
digital readouts green
Voltage or frequency
digital readouts white
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Canadair Regional Jet 100/200 - Electrical
SERVICE CONFIGURATION (green)
The message is displayed:
When external AC power is available and the
AVAIL switchlight on the external service panel
has been selected, or
When APU power is available and the APU
SERV BUS switchlight on the forward F/A
panel has been selected.
For either selection, only the AC service bus, AC
utility bus 1, AC utility bus 2, and the DC service
bus will be powered.
External AC Power Features
Displayed when external AC voltage is more
than 10 volts and frequency is more than 50 Hz.
AC Electrical Page
EICAS DIGITAL
READOUT
GREEN
AMBER
WHITE
XX KVA
Loaded
Overload
Not loaded
Insufficient data
Between 106
and 124 volts
Between 370
and 430 Hz
_
Less than 106 volts or
more than 124 volts
Less than 370 Hz or
more than 430 Hz
_
XXX V
XXX HZ
EICAS
OUTLINE
_
GREEN
HALF INTENSITY AMBER DASHES
MAGENTA
WHITE
External AC available External AC not available
or in use
and not in use
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Invalid data
Invalid data
_
Invalid data
HALF INTENSITY
MAGENTA
Invalid data
Canadair Regional Jet 100/200 - Electrical
<0006>
<0039>
IDG 1 or 2 caution (amber)
Indicates that IDG has low oil pressure
or high oil temperature.
GEN 1 or 2 OFF caution (amber)
Indicates that generator is off.
(Indications are inhibited during start)
GEN 1 or 2 OVLD caution (amber)
Indicates that generator control unit has
detected a load of greater than 40 kVA.
APU GEN OFF caution (amber)
Indicates that APU generator is off and
APU is ready to load.
APU GEN OVLD caution (amber)
Indicates that generator control unit has
detected a load of greater than 40 kVA.
Primary Page
IDG 1 or 2 DISC status (white)
Indicates that IDG has been disconnected,
either automatically or manually.
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Status Page
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Canadair Regional Jet 100/200 - Electrical
<0006>
<0039>
EMER PWR ONLY warning (red)
Indicates that the ADG has deployed.
AC BUS 1 or 2 caution (amber)
Indicates that the associated bus is not
powered.
AC ESS BUS caution (amber)
Indicates that AC essential bus is
less than 90 Volts.
AC SERV BUS caution (amber)
Indicates that AC bus 2 is powered and
AC service bus is less than 90 Volts.
AC 1 or 2 AUTOXFER caution (amber)
Indicates that the corresponding automatic
bus transfer has failed.
Primary Page
AC 1 or 2 AUTOXFER OFF status (white)
Indicates that the corresponding automatic
bus transfer has been selected off.
<0039>
AC ESS ALTN status (white)
Indicates that AC essential bus is
being fed from AC bus 2.
<0039>
AC UTIL 1 or 2 OFF status (white)
Indicates that corresponding AC
utility bus is not powered.
Status Page
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Canadair Regional Jet 100/200 - Electrical
AC BUS to TRU Flow
Lines
Green -- Respective
AC bus is powering
TRU.
TRU Voltage Readouts
Displays, in increments
of 1 VDC, the rectifier’s
voltage level.
TRU Output Flow
Lines
Green -- Respective
TRU is on--line and
output is 18 VDC or
greater.
TRU Load Readouts
Displays, in increments
of 1 amp, the load on
the rectifier.
DC ELEC Page
EICAS Secondary Display
Center Instrument Panel
EICAS DIGITAL
READOUT
GREEN
xx V
Between 22 and 29 VDC
xx A
Between 3 and 99 amp
EICAS
OUTLINE
TRU 1
AMBER DASHES
Less than 22 VDC or
more than 29 VDC
Less than 3 amp or
more than 99 amp
Invalid data
HALF--INTENSITY
MAGENTA
WHITE
TRU
1
18 VDC or greater
Less than 18 VDC
_
Invalid data
TRU 2
18 VDC or greater
Less than 18 VDC
_
Invalid data
V
A
Service
TRU
18 VDC or greater
Load more than
2 amp
_
V
A
Essential
TRU 2
V
A
Essential
TRU 1
Less than 18 VDC
Load less than
2 amp
Less than 18 VDC
Load less than
3 amp
Less than 18 VDC
Load less than
3 amp
V
V
AMBER
Invalid data
GREEN
A
TRU 2
WHITE
A
SERV
TRU 2
Ess
TRU 2
Ess
TRU 1
18 VDC or greater
Load more than
3 amp
18 VDC or greater
Load more than
3 amp
TRU failure
Invalid data
TRU failure
Invalid data
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Invalid data
Canadair Regional Jet 100/200 - Electrical
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SDQHO. In flight, the AC service bus is normally powered from AC bus 2. On the ground,
it can be powered from the APU generator or from external AC power.
The AC service bus supplies power to those circuits necessary for ground--servicing
operations, without having to power the entire electrical system.
The AC utility buses are normally powered (in full configuration) by their respective AC
bus. In flight, the AC utility buses are automatically SHED if only one generator is
operational. In service configuration, the AC utility buses are powered from either the
APU generator or from external AC power.
D.
AC Loads Distribution
AC BUS 1
AC BUS 2
AC ESSENTIAL
Hydraulic Pumps 2B and 3B
Left Windshield Heater
Probe Heaters (R) (AOA and
Pitot) and TAT
Left --Navigation, Landing and
Taxi Lights
Ground Proximity Warning
System (GPWS)
Enhanced Ground Proximity
Warning System (EGPWS)
HSTA (Ch--1)
Hydraulic Pumps 3A and 1B
Right Windshield Heaters
Right Window Heater
Ice Detector 2
Instrument Lights (copilot and
overhead), Landing and Taxi
Lights (R)
Inertial Reference System (2)
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ARINC Display Fan, Galley
and Cabin Fan
Flap Power Drive Unit (2)
ADG Deploy Sensor
TRU 2, DC Essential bus
HSTA (Ch--2)
Bleed Leak Controllers (L / R)
Left Window Heater
Probe Heaters (L) (AOA and
Pitot)
Ice Detector 1
Engine Ignition A
Instrument Lights (Pilot’s and
Center)
CB Panel Integral Lights
Inertial Reference System (1)
Flight Recorder Power
Hydraulic System Fan
Display Cooling Fan (R)
Exhaust and Cockpit Fan
Flap Power Drive Unit (1)
Engine Vibration Monitor
ADG Deploy Sensor
TRU 1, DC essential bus
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Traffic Alert and Collision
Avoidance (TCAS)
ARINC Chassis and Display
Cooling Fans (L)
Essential TRU 1
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Canadair Regional Jet 100/200 - Electrical
E.
Air Driven Generator (ADG)
In the event of a complete AC power failure in flight, the ADG will automatically deploy
and supply 115--volts, 400 Hz AC emergency power to the ADG bus. The ADG
generator is rated at 15 KVA. The ADG bus will then supply emergency power to the
AC essential bus and the 3B hydraulic pump. The AC essential bus will then power
essential TRU 1, which will power the DC essential bus.
If the automatic deploy function fails, the ADG can be deployed manually by pulling the
ADG manual release handle on the ADG CONTROL control panel at the rear of the
center console.
If either main generator is restored, the crew can override the ADG by pressing the
PWR TXFR OVERRIDE button on the ADG control panel. This will reconnect the
restored IDG to power AC bus 1, AC bus 2 and the AC essential bus. The ADG will
continue to power the critical flight controls and the ADG bus. The flaps will move at
half speed when powered from the ADG bus.
The ADG generator, voltage, frequency and ADG bus indications on the EICAS, AC
ELECTRICAL synoptic page are only displayed when the ADG bus is powered.
The ADG will continue to operate and supply power to the ADG bus until the airspeed
decreases below approximately100 kts. At that point, if the APU generator or IDG has
not been restored, the only power available will be from the batteries.
The ADG cannot be restowed in flight. It is restowed manually, on the ground, by
maintenance personnel.
NOTE
After ADG deployment or APU generator switching,
intermittent failure of the pilot’s and copilot’s air data
systems may occur. These failures may result in
uncommanded changes to the pilot’s or copilot’s flight
instruments. The barometric altimeter setting, altitude
preselector, V--speeds and speed bug settings should
be checked and reset as required.
Automatic deployment of the ADG is inhibited, on the ground, when the parking brake
is set.
The ADG system circuits can be checked through a LAMP/UNIT test switch on the ADG
control panel. When the switch is set to LAMP, a ground is supplied to check that the
green TEST light illuminates. The UNIT test has two modes, Pre--takeoff and Inflight:
: Pre--takeoff,
When the test switch is set to UNIT the ADG system circuits are checked and the
TEST light will illuminate within 1 second and remain ON for 2 seconds.
: Inflight,
When the test switch is set to UNIT the ADG system circuits are checked and the
TEST light will illuminate after 5 seconds and remain ON for 2 seconds.
Page 16
Canadair Regional Jet 100/200 - Electrical
LAMP/UNIT Switch
Used to test auto--deploy system.
Test can only be accomplished with
two generators selected ON and
both main AC busses powered.
ADG Manual Deploy Handle
Used to manually deploy the ADG.
TEST Light (green)
Comes on after successful
completion of auto--deploy
system test.
ADG Manual Deploy Handle
and Auto--Deploy Panel
Center Pedestal
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PWR TXFR OVERRIDE
Used to transfer AC
essential bus power source
from the ADG bus back to
the main AC bus.
Canadair Regional Jet 100/200 - Electrical
F.
System Circuit Breakers
SYSTEM
SUB--SYST
EM
Generators
CB NAME
GCU 2
ADG
D l
Deploy
AC
Essential
Bus
AC Utilit
Utility
AC
Bus 1
Distribution
AC Utility
Bus 2
AC Service
Bus
P10
DC BATTERY
BUS
1
ADG DEPLOY
AUTO
ADG DEPLOY
MAN
ADG DEPLOY
SENS
STBY PWR
CONT
AC ESS FEED
AC ESS FEED
ESS PWR CONT
ESS AC XFR
CONT
AC UTLY BUS
FEED
PWR SENS
AC UTLY BUS
CONT
AC UTLY BUS
FEED
AC UTLY BUS
SENS
AC UTLY BUS
CONT
AC SERV BUS
FEED
Q10
Q11
GCU 3
ADG MAN
CB
LOCATION
P9
IDG 2 DISC
ADG AUTO
AC
Electrical
Power
CB
PANEL
IDG 1 DISC
GCU 1
Generator
G
t
Control
BUS BAR
Q12
APU BATTERY
DIRECT BUS
DC BATTERY
BUS
AC BUS 1
MAIN BATTERY
DIRECT BUS
ADG BUS
AC BUS 1
APU BATTERY
DIRECT BUS
DC BATTERY
BUS
AC UTILITY 1
5
B10
B11
2
N6
2
N7
1
C10
5
A7
3
A8
1
C2
5
B13
Q9
1
E2
E7
DC BUS 2
J4
E2
AC UTILITY 2
E7
2
DC BUS 1
J4
AC SERV
R2
Page 18
NOTES
Canadair Regional Jet 100/200 - Electrical
1.
DC ELECTRICAL SYSTEM
Five transformer rectifier units (TRU’s) and two batteries (Main and APU) provide the aircraft
with DC electrical power. DC power is also available through an external DC receptacle on
the right aft fuselage.
A.
Transformer Rectifier Units (TRU)
There are five TRU’s located in the nose avionics compartment. Each TRU converts
115 VAC input power to 28 VDC output power for powering the aircraft DC buses. The
TRU’s are rated at 100 amps. Normal distribution of the TRU outputs is shown in the
following table:
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Batteries
The main and APU nickel-cadmium batteries and their battery chargers are located in
the aft equipment compartment. The batteries provide DC power to their respective DC
battery direct buses.
The 17 AMP./HR, 24, volt main battery provides backup power to the attitude heading
reference system (AHRS), proximity sensing electronic unit (PSEU), data concentrator
units (DCU’s), aircraft clocks, and the APU electronic control unit (ECU). The main
battery also provides power to the flight compartment lighting system.
The 17 AMP./HR, 24 volt, main battery provides backup power to the inertial reference
system (IRS), proximity sensing electronic unit (PSEU), data concentrator units
(DCU’s), aircraft clocks, and the APU electronic control unit (ECU). The main battery
also provides power to the flight compartment lighting system. <0025>
The 43 AMP./HR, 24 volt, APU battery provides the cranking power for starting the
APU.
Page 19
Canadair Regional Jet 100/200 - Electrical
Battery chargers maintain the batteries at full charge. The main battery charger is
powered from AC Utility bus 1 and the APU battery charger is powered from the AC
Utility bus 2. Battery charging is controlled automatically. Each charger monitors the
battery voltage and temperature to control the battery charge rate. If a battery reaches
the overtemperature set point (as sensed by the charger), the charging will stop to
prevent overheating (thermal runaway).
Effectivity:
: Airplanes 7001 to 7220
NOTE
In flight, both chargers will be shed during single
generator operations. On the ground, both chargers are
shed if external AC power is connected and the flaps are
out of the 0 detent, and the passenger door is closed.
Effectivity:
:
Aircraft 7221 and subsequent
NOTE
In flight, both chargers will be shed during single
generator operations. On the ground, both chargers are
shed if external AC power is connected, the flaps are out
of the 0 detent, and the passenger and service doors are
closed.
Page 20
Canadair Regional Jet 100/200 - Electrical
'& 'LVWULEXWLRQ 6\VWHP
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Canadair Regional Jet 100/200 - Electrical
BATTERY MASTER
Used to connect the APU
and main battery direct
busses to the battery bus.
DC SERVICE
Used to connect the DC
service bus to the APU
battery direct bus.
NOTE
Battery master should
always be in the ON
position in flight.
BUS TIE 1 or 2
Switch/Lights
CLOSED -- Come on
white to indicate that
the corresponding DC
bus has been
automatically tied to
the service TRU during
an abnormal
condition, or has been
pressed in, to manually
tie corresponding bus
to the service TRU.
Essential Bus Tie
Switch/Light
CLOSED -- When
pressed in, comes
on white to indicate
that ESS Bus has
been manually tied
to the service TRU
during a DC
essential TRU failure.
CLOSED light (white)
comes on.
Corresponding utility
bus is shed when
switch/light indicates
CLOSED.
ESS TIE switch/light
can only be selected
manually.
Electrical Power Panel
Overhead Panel
'& (OHFWULFDO 6\VWHP
)LJXUH Page 22
Canadair Regional Jet 100/200 - Electrical
C.
([WHUQDO '& 3RZHU
The aircraft can be connected to 28 volts DC from an external receptacle located on the
right aft fuselage below No. 2 engine. External DC is used for ground operations to
save battery power and can be used to start the APU. When external DC is connected
to the aircraft, an external DC contactor is energized to provide power to the APU start
contactor. At the same time, the AVAIL lamp in the DC switchlight illuminates. Pressing
the switchlight closes two contactors to connect the external DC to the Main and APU
battery direct buses and the IN USE lamp in the switchlight illuminates.
D.
DC Distribution
DC power is distributed to the DC system by five TRU’s. DC bus 1 and DC Utility bus 1
are powered from TRU 1. DC bus 2 and DC Utility bus 2 are powered from TRU 2.
The DC essential bus and battery buses are normally powered from the essential
TRUs. The emergency bus is powered from the battery bus and the APU battery direct
bus. The service TRU powers the DC service bus. In the event that an essential TRU
fails, the DC essential bus and battery bus will remain powered from the operating
essential TRU. If both essential TRU’s fail, the essential DC bus and battery bus may
still be powered from the service TRU by selecting the ESS TIE switchlight on the
electrical panel. In the event that a main TRU fails, the respective DC tie will close to
maintain power to the respective DC bus 1/2 from the service TRU. At the same time
the corresponding utility bus will be SHED.
The Main battery direct bus, APU battery direct bus, and the emergency bus are all hot
buses (they are continuously powered at all times from the batteries). When the
BATTERY MASTER switch is selected ON, an input signal is supplied to the two power
controllers (PC). The power controllers monitor for AC power, and if AC power is not
available then the controllers will connect their respective batteries to the battery bus.
When AC power is available, for the TRU’s to power the DC system, the power
controllers will disconnect the batteries from the battery bus. Each battery direct bus
can power the DC battery bus. Both the battery bus and the APU battery direct bus
power the DC emergency bus. The DC service bus is normally powered from the
service TRU. If the DC SERVICE switch on the electrical panel is selected ON, the DC
service bus will be powered from the APU battery direct bus.
NOTE
Although there is only one battery bus, it is split
between circuit breaker panel 1 and 2 and is referred
to as the left and right battery bus.
In flight, if the power controllers sense a complete loss of AC power, they will reconnect
the batteries to the battery bus and at the same time the DC emergency ties will close
to connect the battery bus to the DC essential bus. Once the ADG bus is online to
power essential TRU 1 and the DC essential bus, the batteries will act as a backup
power source to the DC essential bus.
Page 23
Canadair Regional Jet 100/200 - Electrical
<0006>
<0039>
Primary Page
<0039>
<0039>
Status Page
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Canadair Regional Jet 100/200 - Electrical
DC Emergency Bus Flow
Lines
Green -- DC emergency
bus is powered through
the respective flow line
only, or the respective
feeder bus is available
to feed the failed DC
emergency bus.
White -- DC emergency
bus is not powered
through the respective
flow line.
CHARGER (White) <0039>
CHARGER (Amber)
Indicates that the
corresponding charger
is not charging.
NOTE
During normal operation,
when the DC emergency
bus is powered by both the
battery bus and the APU
battery direct bus, the DC
emergency bus outline and
respective flow lines are not
displayed.
EICAS BUS BAR
OUTLINE
BUS 1
BUS 2
UTIL BUS 1
UTIL BUS 2
DC ELEC Page
EICAS Display
Center Instrument Panel
GREEN
AMBER
Bus powered
Bus not powered
_
Bus powered
Invalid data
Invalid data
Bus not powered
_
Invalid data
Battery 18 VDC
or greater
Battery less
than 18 VDC
_
Battery 18 VDC
or greater
Battery less
than 18 VDC
_
BATT BUS
Bus powered
Bus not powered
SERV BUS
Bus powered
APU BATT
DIR BUS
MAIN BATT
DIR BUS
V
A
Bus not powered
Invalid data
_
Bus not powered
MAIN
BATT
_
HALF--INTENSITY
MAGENTA
Invalid data
Bus powered
APU
BATT
WHITE
_
ESS BUS
EICAS BUS BAR
OUTLINE
DC Emergency Bus
Outline
Green -- DC emergency
bus is powered by only
one of the following:
Battery bus or,
APU battery direct bus.
Amber -- DC emergency
bus is not powered
WHITE
GREEN
Battery 18 VDC
or greater
External dc in use
Always displayed
between 18V & 32V.
Less that 18V or
greater than 32V.
AMBER
Battery less
than 18 VDC
'& (PHUJHQF\ %XV <MST>
)LJXUH Page 25
_
Invalid data
Invalid data
HALF--INTENSITY
MAGENTA
Invalid data
_
Canadair Regional Jet 100/200 - Electrical
SERVICE CONFIGURATION (Amber)
Indicates that the DC SERVICE switch
has been selected ON. Only the DC
service bus will be powered.
SERVICE BUS
(Service Configuration)
Displayed when the
DC Service switch
is selected ON.
External DC Flow Line
Displayed when external
DC power is connected.
Corresponds to DC
AVAIL/IN USE
switch/light.
NOTE
Either the battery master
switch or external DC must
be selected ON.
DC ELEC Page
EICAS Secondary Display
Center Instrument Panel
([WHUQDO '& )ORZ /LQH
)LJXUH Page 26
Canadair Regional Jet 100/200 - Electrical
E.
DC Loads Distribution
DC BUS 1 (CBP--1)
Spoiler Electronic Unit
Spoiler Electronic Control
System (PWR 1)
Heaters, Static (R) and ADS
Controller (R)
Cockpit Temperature Control
Left Windshield Heat Controller
14th--Stage Bleed Air Isolation
and Shutoff Valve (L)
10th--Stage Bleed Air Isolation
and Shutoff Valve (L)
Anti--ice Automatic NORM (1)
Proximity Sensor (Landing Gear
Control/Door 1)
(Weight--on--wheels 1)
Lights (cockpit floor, rear
anti--collision, wing inspection)
Maintenance Diagnostic
Computer
DME 1
Radio Altimeter
Flight Data Recorder Control
Weather Radar (receiver,
transmitter and control)
EICAS Primary Display
EICAS Secondary Display
Left Lamp Driver Unit
Bright/dim Power supply unit
Data Loader
Flap Control (CH 1)
Nose Landing Lights
Brake Temperature Monitor
FMS (CDU 1) <0024><0050>
DC Tie Control
Bus 1 Feed Utility
Bus 1 Feed
DC 1 power Sensing
TRU 1 Power Sensing
AC Utility Bus Control
Left Air Conditioning Unit
DME (1)
Smoke detector
Passenger signs
Overboard shutoff Valve
Pilots Wiper (motor and control)
Anti-Skid
GPS (1) <0027><0047>
Hydraulic System (AC pump
control 2 and 3B, fan control,
Indicator 2)
DC BUS 2 (CBP--2)
Horizontal Stabilizer Trim Control
Unit (CH 1)
Spoiler Electronic Unit (2A)
Spoiler Electronic Control
System (PWR 2)
Clock 2
Cabin Temperature Controller
and Manual Controller
Right Windshield and Window
Heater Controller
14th--Stage Bleed Air Isolation
and Shutoff Valve (R)
10th--Stage Bleed Air Isolation
and Shutoff Valve (R)
Anti--ice Automatic NORM (2)
Fuel Pump Control (R)
Proximity Sensor (Landing Gear
Control/Door 2)
(Weight--on--wheels 2)
Avionics Cooling (controller 2,
cockpit shutoff valve, overboard
shutoff valve
IAPS (AFCS) (right fan)
EFIS Control Panel 2
DCU 3 (CH A,B) <0019>.
Audio Control Panel (observers)
ADF 2
DME 2
VHF Nav radio 2
VHF Comm radio 2
PFD 2
MFD 2
RTU 2
Air Data Computer (2)
ATC Transponder 2
GPS 2 <0027>
Page 27
Brake Pressure Indicator
Anti-Skid
Copilots Wiper (motor and
control)
Hydraulic System (AC pump
control 1 and 3A, Indicator 1)
DC Tie Control
Bus 2 Feed Tie and Utility
DC 2 power Sensing
TRU 1 Power Sensing
AC Utility Bus Control
Right Air Conditioning Unit
Flap Control (CH 2)
Nose Wheel Steering
Clock 2
Lights (copilot map and wing
anti--collision)
Canadair Regional Jet 100/200 - Electrical
DC ESSENTIAL BUS (CBP--4)
Horizontal Stabilizer Trim Control
Unit (CH--2)
Spoiler Electronic Unit (1A, 2B)
Spoiler Electronic Control
System 1--2 (PWR 3)
Heater, Static and ADS Heater
Control (L)
Cabin Pressure Controllers (1
and 2) and Control Panel
Left Window Heater Control
10th--stage Bleed air Isolation
Valve
Bleed Air Leak Test
Anti--ice Manual (L) STBY
Thrust Reverser (Auto, stow, 1
and 2)
Fuel (Transfer shutoff valve and
control)
Oil Pressure (R)
Passenger Door Control
Proximity Sensor (Landing Gear
Control)
Pilot’s Floodlights
Emergency Lights
EFIS, CRT, Dimming Panel 1
Avionic Cooling Controller (1)
Stall Protection (CH--R)
DCU 1 (CH A, B)
BATTERY BUS (CBP--1)
Passenger Oxygen (manual deploy and left
passengers)
Fuel System Control
Left Fuel Pump (Control and Power)
Fuel X--Feed Control
Left Engine oil Pressure
Passenger Address
Lights (Standby instrument and compass, map
dome,chart holder,overhead and copilot flood)
Fire Detector (A, B, Test)
Passenger Signs
EICAS/RTU Dimming
Stall Protection (stick pusher CH 1)
Audio Control Panel (pilot’s)
Air Data Computer(1 and 2) Alternate power
supply
VHF Comm Radio 1
Emergency Tuning Unit
IDG Disconnect (1 and 2)
Essential AC Transfer Control
GCU (1, 2 and 3)
DC Emergency bus Feed
Engine Ignition (A & B) Control
Engine Start (L and R)
Transfer/APU (manual x--flow, fuel pump,
controller, ECU)
EFIS Panel 1
Audio Control Panel (copilot’s)
ADC 1
ADF 1
VHF Nav Radio (1)
Cockpit Voice Recorder
PFD 1
MFD 1
RTU 1
Clock 1
ATC Transponder 1
Head--up Guidance System
<0026>
IAPS (AFCS) (left fan)
BATTERY BUS (CBP--2)
Clock 1
Ram Air Shutoff Valve
CPAM
Crew Oxygen Monitor
Passenger Oxygen (auto deploy and right
passengers)
Anti--ice Valves (L and R manual 2)
Proximity Sensor (Landing Gear Control/Door 1
and 2) (Weight--on--wheels 1 and 2)
EICAS Control Panel
DCU 1 and 2 (CH A and B)
Standby Horizon Indicator
EICAS Display 1 (ED1)
EICAS Display 2 (ED2)
Lamp Driver Unit
Bright/Dim Power Supply Unit
Hyd System 3 (Gauges)
ADG Controller (auto and manual)
Essential TRU (power 1 and 2 sensing)
Feed 1 (battery and DC essential)
Feed 2 (battery and DC essential)
Battery Bus (power sensing)
RCCB Control (Main and APU battery)
FMS (CDU 2) <0024>
Overheat Detector (Main landing gear bay)
Page 28
Canadair Regional Jet 100/200 - Electrical
MAIN BATTERY DIRECT BUS
(CBP--5)
Main Battery Contactor
APU ECU
DCU’s 1 and 2
Standby Power Controller
Attitude Heading
Clocks 1 and 2
PSEU
Lights (service, boarding and
maintenance)
DC UTILITY BUS 1 (CBP--1)
Left Cabin Reading Lights
Power sensing
APU BATTERY DIRECT BUS
(CBP--5)
APU Battery Contactor
Service Bus Feed
Oil Bypass Indicator
Engine Oil Replenishment
System
ADG (auto and manual deploy)
External DC Power
Essential Power Control
Refuel/Defuel Panel
Emergency Refuel
DC UTILITY BUS 2 (CBP--2)
Right Cabin Reading Lights
Power sensing
Page 29
BATTERY BUS (CBP--5)
Engine Ignition System (B)
DC SERVICE BUS (CBP--2)
Lights (navigation, toilet and
galley dome)
Cabin Lighting, Upward and
Downward (L and R)
Service Bus Feed from CBP--5
Power Sensing (service bus and
TRU)
Canadair Regional Jet 100/200 - Electrical
F.
System Circuit Breakers
SYSTEM
SUB--SYSTEM
CB NAME
TRU 1
BUS BAR
CB
CB
PANEL LOCATION
AC BUS 1
B2
FEED
DC Bus 1
DC 1 PWR
SENS
TRU 1 PWR
SENS
TRU 2
E12
DC BUS 1
1
E15
AC BUS 2
B2
FEED
DC Bus 2
DC Power
Distribution
DC TIE
CONTACTS
DC Essential
Bus
E12
DC 2 PWR
SENS
DC BUS 2
TRU 2 PWR
SENS
DC TIE
DC BUS 1
CONTROL
TIE AND UTLY DC BUS 2
2
ESS TRU 1
FEED 1 DC
ESS
FEED 2 DC
ESS
ESS TRU 1
PWR SENS
ESS TRU 2
PWR SENS
28 VDC ESS
SENS
E14
AC ESS
DC BAT
E14
E15
1
E11
2
E11--E13
3
A2
M6
2
M8
M3
DC
ESSENTIAL
Page 30
2
M4
4
B3
NOTES
Canadair Regional Jet 100/200 - Electrical
SYSTEM
SUB--SYSTEM
Battery Bus
DC Utility
B 1
Bus
DC Utility
B 2
Bus
DC Power
Distribution
DC Service
Bus
DC
Emergency
Bus
Main and
APU Battery
APU Batteries
CB NAME
BUS BAR
FEED 1 BATT
BUS
DC BAT
FEED 2 BATT
BUS
BAT BUS PWR
SENS
UTLY BUS 1
DC BUS 1
FEED
PWR SENS
DC UTIL 1
UTLY BUS 2
FEED
PWR SENS
DC BUS 2
APU BATT
DC EMER
DIRECT FEED BUS
APU
CHARGER
M5
2
M7
M9--M10
1
E13
L10
2
DC UTIL 2
SERVICE BUS APU BATT
FEED
DIRECT BUS
DC SERVICE
BUS FEED
BUS
AC SERVICE
SERVICE TRU
BUS
PWR
SENS/SERV
BUS
DC SERVICE
BUS
PWR
SENS/SERV
TRU
APU BATT
CONT
EMER BUS
FEED
RCCB
CONT/APU
BATT
CB
CB
PANEL LOCATION
E13
L10
5
B3
T5
1
R5
T6
2
T7
1
S6
B2
APU BAT DIR
5
B4
BATT &
28VDC ESS
CONT
AC UTIL 2
Page 31
M12
2
E5
NOTES
Canadair Regional Jet 100/200 - Electrical
SYSTEM
SUB--SYSTEM
Main and
Main Battery
APU Batteries
CB NAME
BUS BAR
CB
CB
PANEL LOCATION
MAIN BATT
CONT
MAIN
BATTERY
DIRECT BUS
5
C5
RCCB
CONT/MAIN
BATT
BATT &
28VDC ESS
CONT
2
M11
MAIN BATT
CHARGER
AC UTIL 1
1
E5
Page 32
NOTES
Canadair Regional Jet 100/200 - Electrical
1.
&,5&8,7 %5($.(5 3$1(/6
There are six circuit breaker panels (CBP’s) located in the aircraft. Four CBP’s (numbered 1
to 4) are located in the flight compartment. One CBP is located in the aft equipment
compartment (number 5) and one CBP is located on the galley control panel.
The circuit breakers are clearly identified. For circuit breaker referencing, each circuit
breaker panel is laid out in an alphanumeric grid with letters running down the side of the
panel and numbers running across each row. For example, the location of a circuit breaker
on circuit breaker panel 1, in the 3rd row, column 2, would be identified as CBP1--C2. In this
instance, C2 is the circuit breaker for the AC ESS FEED.
Page 33
Page 34
&LUFXLW %UHDNHU 3DQHO <MST>
)LJXUH 6KHHW H
G
F
E
D
C
B
A
2
20
AC ESS
FEED
2
10
TRU
1
2
25
3
2
3
1
IAPS
LEFT
FMS/MDC
2
PULSE
LTS
3
A/ICE
AUTO
1
CARGO
FIREX
2
1
2
3
3
IND
1
DOOR
2
25
AC
UTLY BUS
FEED
2
3
15
ACT
1
1
AVIONICS COOLING
DISPLAY
FAN 2
1
1
1
3B
3
10
PRIM
DISPL
3
3
BRAKE
TEMP
MON
3
7
1
2
SECS
PWR 1
3
5
15
FLAPS
FDU 1
5
25
2
4
4
4
10
SEC
DISPL
4
3
ANTI
SKID
4
3
5
3
EICAS
LDU
L
5
15
6
7
7
7
2
8
7
1
2
1
1
2
28 VDC BUS 1
8
5
9
9
3
9
3
SEL
CAL
9
5
WING
INSP
9
3
ISOL
9
10
20
10
10
3
11
10
3
DME
1
10
5
MAINT
10
3
SOV L
10
3
CPLR
10
11
3
DATA
LOAD
11
3
AC PUMP
CONT 3B
11
3
10 ST
B/AIR
SOV L
11
3
DC TIE
CONTROL
11
10
COFFEE
MAKER
13
13
3
NAV
LTS
13
13
3
AOA
R
3
13
3
12
3
CDU
1
12
3
13
3
GPS
1
13
15
15
14
14
5
L
NOSE
3
14
3
14
14
3
AC PUMP
CONT 2
14
3
GND
PROX
WARN
15
3
TRU 1
PWR
SENS
15
15
5
L
WING
LDG/TAXI LTG
14
14
7
1
2
PITOT
R
HEATERS
ADS
STATIC
CONT 2
R
13
20
HYD SYST
FAN
IND
CONT
2
12
3
HTR
CONT L
WSHLD
12
20
NOTE
2
3
FLIGHT
REC
CONT
2
5
2
3
STBY
INSTR
LT/VIB
2
5
FIRE DET
LOOP B
2
3
1
7
1
2
2
7
1
2
2
3
7
1
2
VHF
COMM
1
3
3
PLT
MAP
3
3
TEST
3
3
B
3
3
BAGG
COMP
CONT
ENG IGN
A
2
5
STALL PROT
STICK
LH
PUSHER
CHAN
1
5
CARGO
FIREX
1
1
5
LOOP A
1
3
L ENG
OIL PRESS
1
5
1
3
7
4
3
AC UTLY
BUS
CONT
J
1
2
4
3
EMER
TUNING
4
3
C/PLT OBS
MAP
4
4
7
7
3
6
5
MIDFWD
1
2
7
5
MIDAFT
6
20
6
3
7
7
3
6
3
5
7
1
2
PASS
ADDR
6
5
PILOT
7
3
7
5
AUDIO
C / PLT
28 VDC BATTERY BUS
5
3
28 VDC BATTERY BUS
LIGHTS
O/H
EICAS / RTU
DOME
PNL
DIMMING
5
28 VDC BATTERY BUS
ENG
OIL
LEVEL
5
7
K
1
2
8
5
OBS
8
3
ADC
STBY
8
7
1
2
SECU
1
8
7
X/FLOW
SOV
8
5
AFT
28 VDC UTILITY BUS 1
LEFT CABIN READING LTS
6
RAD
ALT
28 VDC BATTERY BUS
L
L FUEL
FUEL
PUMP
PUMP
CONT
5
5
FWD
5
3
ENG START
R
L
4
3
O/B
SOV
4
3
WEATHER RDR
CONT 2
CONT 1
28 VDC BUS 1
R/T
3
5
28 VDC BUS 1
CKPT TEMP
MAN
CONT
CONT
28 VDC BUS 1
PASS
PASS
DOOR
SIGNS
ACT
1
3
SMOKE
DET
1
5
L AIR
COND
UNIT
For single HF installation <0011>,
circuit breakers E--8 to E--10 are
deactivated (collared) and labeled
as inoperative.
28 VDC BUS 1 CONTROL
UTLY
DC 1
BUS 1
PWR
FEED
SENS
FEED
12
12
12
12
3
TAT
HEATERS
115 VAC UTILITY BUS 1
10
11
11
20
CBP--1
LEFT
WSHLD
ADG
DEPLOY
SENS
14 ST
B/AIR
28 VDC BUS 1
HF 1
28 VDC BUS 1
LIGHTS
REAR
A / COLL
8
3
NOSE
STEER
9
9
FLIGHT
REC
PWR
RX/TX
28 VDC BUS 1
8
10
8
15
OVEN
1
8
7
3
7
3
CKPT
FLOOR
7
3
WOW 1
7
3
PWR
SENS
7
7
3
1
2
CKPT
FAN
115VAC BUS 1
8
5
115VAC BUS 1
BAGG
COMPT
HEATER
8
3
HYD SYST
FAN
115 VAC BUS 1
BRT / DIM PWR SUP
1
2
6
5
CONT
6
7
1
2
7
7
ENG
VIB
MON
PROX SENS
6
6
6
6
6
LGC/DI
WIPER
MOTOR
5
3
PITCH
FEEL
CH 1
FLAPS
CONT
CH 1
1
2
5
4
7
MAIN BATT
CHARGER
5
3
BAGG
COMPT
FAN
5
7
1
2
AVIONICS COOLING
EXHAUST
FAN
4
4
115 VAC UTILITY BUS 1
3
115 VAC BUS 1
3
3
3
HYD PUMP
POWER MUST BE OFF BEFORE OPENING PANEL
CIRCUIT BREAKER PANEL 1
(Behind Pilot’s Seat)
1
2
9
3
ESS AC
XFR
CONT
9
5
IDG 1
DISC
9
5
XFER
SOV
9
7
VHF
COMM
3
9
11
5
PASS
SIGNS
L
10
7
1
2
1
10
5
IDG 2
DISC
10
20
12
10
APU
ECU
12
3
FUEL
SYST
CONT
1
2
11
7
GCU
2
11
3
1
11
7
3
12
5
2
PASS OXYGEN
LEFT
MANUAL
DEPLOY
PASS
11
3
XFER/APU
FUEL
PUMP
CONT
10
20
EMER
BUS
FEED
10
3
PWR
SENS
Q
P
N
M
<0060> -- E 8, E 9, E 10
<0055> -- G 10
<0047> -- H 13
<0031> -- H 1
<0027> -- H 13
<0014> -- M 9
<0011> -- E 8, E 9, E 10
<0010> -- H 9
<0008> -- M 9
Canadair Regional Jet 100/200 - Electrical
Page 35
H
G
F
E
D
C
B
A
2
20
AC ESS
FEED
2
10
TRU
1
2
25
1
2
2
3
IAPS
LEFT
FMS/MDC
3
A/ICE
AUTO
1
CARGO
FIREX
2
1
2
3
3
IND
1
DOOR
2
25
AC
UTLY BUS
FEED
2
3
15
ACT
1
1
AVIONICS COOLING
DISPLAY
FAN 2
1
1
1
3B
3
10
PRIM
DISPL
3
3
BRAKE
TEMP
MON
3
7
1
2
SECS
PWR 1
3
5
15
FLAPS
FDU 1
5
25
2
4
4
1
2
4
10
SEC
DISPL
4
3
ANTI
SKID
4
3
5
3
EICAS
LDU
L
5
15
1
2
6
7
7
7
2
8
7
1
2
1
1
2
28 VDC BUS 1
8
5
9
9
3
9
9
5
WING
INSP
9
3
ISOL
9
20
10
10
3
11
11
3
DATA
LOAD
11
3
AC PUMP
CONT 3B
11
3
10 ST
B/AIR
SOV L
11
3
DC TIE
CONTROL
11
10
GUARD
10
3
DME
1
10
10
3
SOV L
10
CPLR
10
COFFEE
MAKER
13
13
2
NAV
LTS
13
13
3
AOA
R
1
2
14
14
5
L
NOSE
3
12
3
CDU
1
12
3
14
13
3
3
13
13
14
14
3
AC PUMP
CONT 2
14
3
HEATERS
ADS
STATIC
CONT 2
R
13
20
HYD SYST
FAN
IND
CONT
2
12
3
HTR
CONT L
WSHLD
12
20
15
15
3
GND
PROX
WARN
15
3
TRU 1
PWR
SENS
15
15
5
L
WING
LDG/TAXI LTG
14
14
7
PITOT
R
28 VDC BUS 1 CONTROL
UTLY
DC 1
BUS 1
PWR
FEED
FEED
SENS
12
12
12
12
3
TAT
HEATERS
115 VAC UTILITY BUS 1
10
11
11
20
CBP--1
LEFT
WSHLD
ADG
DEPLOY
SENS
14 ST
B/AIR
28 VDC BUS 1
HF 1
28 VDC BUS 1
LIGHTS
REAR
A / COLL
8
3
NOSE
STEER
9
9
FLIGHT
REC
PWR
RX/TX
28 VDC BUS 1
8
8
15
OVEN
1
8
7
3
7
3
CKPT
FLOOR
7
3
WOW 1
7
3
PWR
SENS
7
7
3
CKPT
FAN
115VAC BUS 1
8
5
115VAC BUS 1
BAGG
COMPT
HEATER
8
3
HYD SYST
FAN
115 VAC BUS 1
BRT / DIM PWR SUP
1
2
6
5
CONT
6
7
1
2
7
7
ENG
VIB
MON
PROX SENS
6
6
6
6
6
LGC/DI
WIPER
MOTOR
5
3
PITCH
FEEL
CH 1
FLAPS
CONT
CH 1
1
2
5
4
7
MAIN BATT
CHARGER
5
3
BAGG
COMPT
FAN
5
7
AVIONICS COOLING
EXHAUST
FAN
4
4
115 VAC UTILITY BUS 1
3
115 VAC BUS 1
3
3
3
HYD PUMP
POWER MUST BE OFF BEFORE OPENING PANEL
CIRCUIT BREAKER PANEL 1
(Behind Pilot’s Seat)
2
3
FLIGHT
REC
CONT
2
5
2
3
STBY
INSTR
LT/VIB
2
5
FIRE DET
LOOP B
2
3
1
7
1
2
2
7
1
2
2
3
7
1
2
VHF
COMM
1
3
3
PLT
MAP
3
3
TEST
3
3
B
3
3
BAGG
COMP
CONT
ENG IGN
A
2
5
STALL PROT
STICK
LH
PUSHER
CHAN
1
5
CARGO
FIREX
1
1
5
LOOP A
1
3
L ENG
OIL PRESS
1
5
1
3
7
4
3
AC UTLY
BUS
CONT
J
1
2
4
3
EMER
TUNING
4
3
C/PLT OBS
MAP
4
4
7
6
5
MIDFWD
1
2
7
5
MIDAFT
6
20
6
3
7
7
3
6
3
5
7
1
2
PASS
ADDR
6
5
PILOT
7
3
7
5
AUDIO
C / PLT
28 VDC BATTERY BUS
5
3
28 VDC BATTERY BUS
LIGHTS
O/H
EICAS / RTU
DOME
PNL
DIMMING
5
28 VDC BATTERY BUS
ENG
OIL
LEVEL
5
7
K
1
2
8
5
OBS
8
3
ADC
STBY
8
7
1
2
SECU
1
8
7
X/FLOW
SOV
8
5
AFT
28 VDC UTILITY BUS 1
7
3
LEFT CABIN READING LTS
6
RAD
ALT
28 VDC BATTERY BUS
L
L FUEL
FUEL
PUMP
PUMP
CONT
5
5
FWD
5
3
ENG START
R
L
4
3
O/B
SOV
4
3
WEATHER RDR
CONT 1
CONT 2
28 VDC BUS 1
R/T
3
5
28 VDC BUS 1
CKPT TEMP
MAN
CONT
CONT
28 VDC BUS 1
PASS
PASS
DOOR
SIGNS
ACT
1
3
SMOKE
DET
1
5
L AIR
COND
UNIT
9
3
ESS AC
XFR
CONT
9
5
IDG 1
DISC
9
5
LEFT
FUEL
SOV
9
9
10
7
1
2
1
10
5
IDG 2
DISC
10
20
FUEL
PUMP
L
12
10
APU
ECU
12
3
FUEL
SYST
CONT
1
2
11
7
GCU
2
11
3
1
11
7
3
12
5
2
PASS OXYGEN
LEFT
MANUAL
DEPLOY
PASS
11
3
CONT
11
5
PASS
SIGNS
XFER/APU
10
20
EMER
BUS
FEED
10
3
PWR
SENS
Q
P
N
M
Effectivity:
Airplanes 7452 and subsequent,
Circuit Breaker Guard Installation.
C 13 -- Effectivity:
Airplanes 7300 and subsequent, C 13 is 2 AMPS.
F 1, F 2 -- Effectivity:
Airplanes 7390 and subsequent, equipped
with Phase III or Phase IV Passenger Door.
L 2 -- Effectivity:
Airplanes 70722 and subsequent,
and Airplanes incorporating
the following Service Bulletin:
SB 601R--28--022.
Canadair Regional Jet 100/200 - Electrical
&LUFXLW %UHDNHU 3DQHO <7072 & subs, SB601R--28--022><7300 & subs><7390 & subs><7452 & subs>
)LJXUH 6KHHW Canadair Regional Jet 100/200 - Electrical
Effectivity:
Airplanes 7003 to 7067, 7069 and
subsequent, incorporating
the following Service Bulletin:
SB 601R--21--039.
CIRCUIT BREAKER PANEL 1
(Sub--Panel)
&LUFXLW %UHDNHU 3DQHO 6XE3DQHO <Aircraft 7003 to 7067, 7069 & subs,SB601R--21--039>
)LJXUH Page 36
Page 37
&LUFXLW %UHDNHU 3DQHO <MST>
)LJXUH 6KHHW Q
P
N
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2
2
3
CH A
1
2
3
7
3
3
3
VALVE
L END
DCU 1
LGC/DI
2
1
2
3
3
CH B
3
5
4
3
CH A
4
4
3
DCU 2
A/ICE
VALVE
R END
4
3
ESS TRU
PWR 1
PWR 2
SENS
SENS
3
CONT
2
1
3
K
2
5
3
CH B
5
3
RAM
AIR
SOV
5
3
MAN
2
5
50
BATT
BUS
3
3
4
3
I/B
SOV
5
5
FWD
6
5
MIDFWD
7
50
8
50
1
2
7
3
1
2
8
7
1
7
7
2
8
10
6
10
7
10
8
3
28 VDC BATTERY BUS
EICAS
PRIM
SEC
CONT
DISPL
DISPL
PNL
6
3
28 VDC BATTERY BUS
CABIN
IAPS
IAPS
PRESS
LEFT
LEFT
MOD
AFCS
FAN
6
7
28 VDC BATTERY BUS
ADG DEPLOY
CONT
SECU
AUTO
MAN
2
6
50
BATT & 28 VDC ESS CONTROL
FEED 1
FEED 2
DC
DC
BATT
ESS
BUS
ESS
CKPT
SOV
3
3
EFIS
CONT
PNL 2
J
5
2
5
8
5
AFT
9
3
LDU
R
9
9
3
MLG BAY
OVHT
DET
9
3
1
2
10
7
10
3
PWR
SENS
7
3
DCU 3
CH B
4
3
AC UTLY
BUS
CONT
1
2
1
2
12
3
HYD
SYST
IND 3
12
7
11
3
1
2
11
7
2
20
AC ESS
FEED
2
10
TRU
2
1
12
7
1
1
2
2
7
IAPS
RIGHT
FMS
2
3
3
A/ICE
AUTO
2
2
2
25
AC
UTLY BUS
FEED
2
3
5
1
1
1
1
4
4
4
4
1
2
3
10
IAPS
RIGHT
AFCS
3
3
BRAKE
PRESS
IND
3
7
SECS
PWD 2
3
4
5
AUDIO
OBS
4
3
ANTI
SKID
4
3
FLAPS
CONT
CH2
4
5
5
1
2
5
3
CLOCK
2
5
15
6
6
6
6
6
6
3
ADC
2
6
3
CONT
6
3
RUDDER
TRIM
WIPER 2
MOTOR
5
3
STAB CH 1
HSTCU
7
APU
CHARGER
5
5
5
15
FLAPS
FDU 2
115 VAC UTILITY BUS 2
3
115 VAC BUS 2
3
3
3
25
2
25
AVIONICS COOLING
ARINC
FAN 2
1
1
1
1
HYD PUMP
2
NOSE
STEER
28 VDC BUS 2
8
3
7
3
ADF
2
7
3
8
3
XPDR
2
28 VDC BUS 2
8
5
9
9
9
9
9
3
VHF
NAV
2
9
9
3
PROX
SENS
WOW 2
9
10
28 VDC BUS 2
HF 1
RX/TX
28 VDC BUS 2
8
10
8
15
OVEN
2
8
3
CABIN
FAN
115VAC BUS 2
8
7
1
STAB CH 1
HEATER
115VAC BUS 2
8
10
LIGHTS
WING
C/PLT
MAP
A / COLL
7
3
AIL
TRIM
7
3
PWR
SENS
7
7
3
ICE
DET 2
7
7
115 VAC BUS 2
ESS
TRU
2
11
3
ACARS
11
7
1
2
GALLEY
HTRS
11
20
10
3
DME
2
10
20
R
FUEL
PUMP
10
3
14 ST
B/AIR
SOV R
10
3
CPL
10
1
2
11
7
VHF
COMM
2
11
3
R FUEL
PUMP
CONT
11
3
10 ST
B/AIR
SOV R
11
3
DC TIE
CONTROL
11
10
COFFEE
MAKER 2
115 VAC UTILITY BUS 2
10
3
ADG
DEPLOY
SENS
10
10
20
13
3
5
14
14
10
LAV
12
3
CDU
2
12
3
GALLEY
HTRS
CONT
12
3
R
WSHLD
13
3
GPS
2
13
3
IND
1
13
3
R
WIND
13
20
HTR CONT
12
20
14
3
AHRS
2
14
3
HYD SYST
AC PUMP
CONT 1
14
3
PITCH
FEEL
CH 2
14
3
15
5
R
WING
15
15
15
3
AHRS
FAN
2
15
3
PUMP
CONT 3A
15
10
IAPS
RIGHT
FAN
15
3
TRU 2
PWR
SENS
15
10
TANKS
HTRS
L/T LTS
R
NOSE
14
WATER SYSTEM
GALLEY
10
14
IRU
1
LINES HTRS
13
3
O/H
PNL
13
13
28 VDC BUS 2 CONTROL
DC 2
TIE &
PWR
FEED
UTLY
SENS
12
12
3
C/PLT
PNL
INST LTG
12
12
15
RIGHT
WING
CBP--2
HEATERS
RIGHT
WSHLD
POWER MUST BE OFF BEFORE OPENING PANEL
3A
12
2
PASS OXYGEN
AUTO
RIGHT
DEPLOY
PASS
11
3
CLOCK
1
11
7
RCCB CONT
MAIN
APU
BATT
BATT
9
NOTE
For single HF installation <0011>,
circuit breakers E--8 to E--10 are
deactivated (collared) and labeled
as inoperative.
BRT / DIM PWD SUP
1
2
10
3
CREW
OXYGEN
MONITOR
10
3
STBY
INSTR
10
3
BAT BUS
PWR
PWR
SENS
SENS
7
5
MIDAFT
6
3
EICAS
CH A
3
5
28 VDC BUS 2
CABIN TEMP
CONT
CONT
MAN
28 VDC UTILITY BUS 2
4
3
RTU
2
28 VDC BUS 2
1
5
R AIR
COND
UNIT
RIGHT CABIN READING LTS
10
1
MFD
2
10
PFD
2
AVIONIC COOLING
28 VDC BUS 2
3
RAD
ALT 2
PROX SENS
LGC/D2
WOW 1 + 2
2
1
1
ESS TRU 1
SHUNT FUSES
F7PA
F8PA
1
ESS TRU 2
SHUNT FUSES
F5PA
F6PA
L
<0082> -- C 11
<0060> -- E 8, E 9, E 10
<0047> -- H 13
<0045> -- L 1
<0027> -- H 13
<0019> -- K 6, K 7
<0011> -- E 8, E 9, E 10
CIRCUIT BREAKER PANEL 2
(Behind Copilot’s Seat)
H
G
F
E
D
C
B
A
Canadair Regional Jet 100/200 - Electrical
Page 38
subs><7676, 7686, 7784 and 7807>
)LJXUH 6KHHW Q
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2
2
3
CH A
3
1
2
7
1
2
LGC/DI
2
3
CONT
2
3
3
VALVE
L END
3
3
DCU 1
3
3
CH B
3
5
4
3
CH A
4
4
3
DCU 2
A/ICE
VALVE
R END
4
3
ESS TRU
PWR 1
PWR 2
SENS
SENS
1
PROX SENS
LGC/D2
WOW 1 + 2
2
1
1
ESS TRU 1
SHUNT FUSES
F7PA
F8PA
1
ESS TRU 2
SHUNT FUSES
F5PA
F6PA
L
2
4
3
I/B
SOV
5
5
FWD
6
5
MIDFWD
5
3
CH B
5
3
RAM
AIR
SOV
5
3
MAN
2
5
50
7
50
8
50
1
2
7
3
1
2
8
7
7
7
8
10
6
10
PRIM
DISPL
7
10
8
3
28 VDC BATTERY BUS
EICAS
SEC
CONT
DISPL
PNL
6
3
1
2
28 VDC BATTERY BUS
CABIN
IAPS
IAPS
PRESS
LEFT
LEFT
MOD
AFCS
FAN
6
7
AUTO
28 VDC BATTERY BUS
ADG DEPLOY
CONT
SECU
MAN
2
6
50
BATT & 28 VDC ESS CONTROL
FEED 1
FEED 2
BATT
DC
DC
BATT
BUS
ESS
BUS
ESS
3
3
CKPT
SOV
3
3
EFIS
CONT
PNL 2
1
5
8
5
AFT
3
9
3
LDU
R
9
1
10
7
2
3
10
1
2
1
2
12
3
HYD
SYST
IND 3
12
7
11
3
1
2
11
7
2
20
AC ESS
FEED
2
10
1
2
12
7
1
1
2
2
7
IAPS
RIGHT
FMS
2
3
3
A/ICE
AUTO
2
2
2
25
AC
UTLY BUS
FEED
2
3
5
1
1
1
1
AVIONICS COOLING
ARINC
FAN 2
1
1
TRU
2
4
4
4
4
1
2
3
10
IAPS
RIGHT
AFCS
3
3
BRAKE
PRESS
IND
3
7
SECS
PWD 2
3
4
5
AUDIO
OBS
4
3
ANTI
SKID
4
3
FLAPS
CONT
CH2
4
5
5
1
2
5
3
CLOCK
2
5
15
6
6
6
6
6
6
3
ADC
2
6
3
CONT
6
3
RUDDER
TRIM
WIPER 2
MOTOR
5
3
STAB CH 1
HSTCU
7
APU
CHARGER
5
5
3
GALLEY &
LAVATORY
FAN
5
15
FLAPS
FDU 2
115 VAC UTILITY BUS 2
3
115 VAC BUS 2
3
3
3
25
2
25
12
PASS OXYGEN
AUTO
RIGHT
DEPLOY
PASS
11
3
CLOCK
1
11
7
RCCB CONT
MAIN
APU
BATT
BATT
9
PWR
SENS
7
4
3
AC UTLY
BUS
CONT
BRT / DIM PWD SUP
1
2
10
3
CREW
OXYGEN
MONITOR
RIGHT
FUEL
XFER
SOV
5
10
3
STBY
INSTR
10
9
3
MLG BAY
OVHT
DET
9
3
BAT BUS
PWR
PWR
SENS
SENS
7
5
MIDAFT
6
3
2
5
5
5
28 VDC BUS 2
CABIN TEMP
CONT
MAN
CONT
28 VDC UTILITY BUS 2
4
3
RTU
2
28 VDC BUS 2
RIGHT CABIN READING LTS
10
1
MFD
2
J
R AIR
COND
UNIT
1
1
HYD PUMP
3A
RX/TX
NOSE
STEER
8
3
7
3
ADF
2
7
3
8
3
XPDR
2
9
3
VHF
NAV
2
9
9
3
PROX
SENS
WOW 2
9
11
11
7
1
2
GALLEY
HTRS
11
20
10
3
DME
2
10
20
R
FUEL
PUMP
10
3
14 ST
B/AIR
SOV R
10
CPL
10
1
2
11
7
VHF
COMM
2
11
3
R FUEL
PUMP
CONT
11
3
10 ST
B/AIR
SOV R
11
3
DC TIE
CONTROL
11
10
COFFEE
MAKER 2
115 VAC UTILITY BUS 2
10
3
ADG
DEPLOY
SENS
10
10
20
HEATERS
RIGHT
WSHLD
GUARD
28 VDC BUS 2
8
5
9
9
9
9
28 VDC BUS 2
HF 1
28 VDC BUS 2
8
8
15
OVEN
2
8
3
CABIN
FAN
115VAC BUS 2
8
7
1
2
STAB CH 1
HEATER
115VAC BUS 2
8
10
28 VDC BUS 2
LIGHTS
WING
C/PLT
MAP
A / COLL
7
3
AIL
TRIM
7
3
PWR
SENS
7
7
3
ICE
DET 2
7
7
115 VAC BUS 2
ESS
TRU
2
WATER SYSTEM
GALLEY
13
10
5
14
14
10
LAV
12
3
CDU
2
12
3
GALLEY
HTRS
CONT
12
3
R
WSHLD
13
13
3
IND
1
13
3
R
WIND
13
20
HTR CONT
12
20
14
3
AHRS
2
14
3
HYD SYST
AC PUMP
CONT 1
14
3
PITCH
FEEL
CH 2
14
3
15
5
R
WING
15
15
15
3
AHRS
FAN
2
15
3
PUMP
CONT 3A
15
10
IAPS
RIGHT
FAN
15
3
TRU 2
PWR
SENS
15
10
TANKS
HTRS
L/T LTS
R
NOSE
LINES HTRS
13
3
O/H
PNL
14
3
IRU
1
14
28 VDC BUS 2 CONTROL
DC 2
TIE &
PWR
FEED
UTLY
SENS
12
12
3
C/PLT
PNL
13
13
3
ACARS
PRINTER
INST LTG
12
12
15
RIGHT
WING
CBP--2
H
G
F
E
D
C
B
A
Airplanes 7002, 7076 and subsequent,
and Airplanes incorporating
the following Service Bulletin:
SB 601R--24--036.
P 9 -- Effectivity:
Airplanes 7072 and subsequent,
and Airplanes incorporating
the following Service Bulletin:
SB 601R--28--022.
C 5 -- Effectivity:
POWER MUST BE OFF BEFORE OPENING PANEL
Effectivity:
Airplanes 7452 and subsequent,
Circuit Breaker Guard Installation.
A 13 -- Effectivity:
Airplanes 7676, 7686, 7784 and 7807,
incorporating
the following Customer Request:
CR 601R--23--372.
10
AVIONIC COOLING
28 VDC BUS 2
K
PFD
2
CIRCUIT BREAKER PANEL 2
(Behind Copilot’s Seat)
Canadair Regional Jet 100/200 - Electrical
&LUFXLW %UHDNHU 3DQHO <7002, 7076 & subs, SB601R--24--036><7072 & subs, SB601R--28--022><7452 &
Canadair Regional Jet 100/200 - Electrical
<0009> -- S 6
CIRCUIT BREAKER PANEL 2
(Sub--Panel)
<0020> -- R 7
<0035> -- T 2
&LUFXLW %UHDNHU 3DQHO 6XE3DQHO <MST>
)LJXUH 6KHHW Page 39
Canadair Regional Jet 100/200 - Electrical
Effectivity:
Airplanes 7036 and subsequent,
incorporating the following
Service Bulletin:
SB 601R--24--017.
CIRCUIT BREAKER PANEL 2
(Sub--Panel)
SPARE FUSES
&LUFXLW %UHDNHU 3DQHO 6XE3DQHO <7036 & subs, SB601R--24--017>
)LJXUH 6KHHW Page 40
Canadair Regional Jet 100/200 - Electrical
<0026> -- C 4
CIRCUIT BREAKER PANEL 3
&LUFXLW %UHDNHU 3DQHO <MST>
)LJXUH Page 41
Canadair Regional Jet 100/200 - Electrical
CIRCUIT BREAKER PANEL 4
&LUFXLW %UHDNHU 3DQHO <MST>
)LJXUH Page 42
10
11
12
13
14
15
Page 43
3
3
3
20
20
7
1
2
APU
BATT
CONT
1
6
7
8
APU BATTERY DIRECT BUS
10
6
1
2
4
7
EMER SERV
BUS
BUS
FEED FEED
2
3
9
OIL
BYPS
IND
5
ENG
IGN
B
20
7
1
2
APU
ECU
CB--5
3
8
ENG
OIL
PWR
7
ADG
AUTO
MAN
EICAS
MAIN
BATT
CONT
A
5
EXT
PWR
5
5
ESS
PWR
CONT
3
28 VDC MAIN BATTERY DIRECT BUS
STBY
DCU
PWR
CONT
2/3
3
FUEL
DEFL
3
CLK
1
1
EMRG
REFL
3
CLK
2
Canadair Regional Jet 100/200 - Electrical
CIRCUIT BREAKER PANEL 5
(AFT side of JB--5 in
AFT Compartment)
B
BATT
BUS
2
3
4
5
9
10
11
12
13
14
15
&LUFXLW %UHDNHU 3DQHO )LJXUH 6KHHW Canadair Regional Jet 100/200 - Electrical
A 8, A 9 -- Effectivity:
CIRCUIT BREAKER PANEL 5
(AFT side of JB--5 in
AFT Compartment)
Airplanes 7002, 7068 and
subsequent, incorporating
the following Service Bulletin:
SB 601R--34--045.
EICAS
15
20
20
APU BATTERY DIRECT BUS
3
5
10
3
9
3
10
1
2
7
12
3
ESS
PWR
CONT
EXT
PWR
14
SPARE
FUSES
11
APU MAIN
BATT BATT
CHGR CHGR
O/P
O/P
13
3
FUEL
DEFL
OIL
BYPS EMRG
IND
REFL
ENG
OIL
PWR
8
11
12
7
13
50
3
CLK
2
10
6
14
50
3
CLK
1
9
3
5
ADG
MAN
AUTO
5
3
3
3
28 VDC MAIN BATTERY DIRECT BUS
ATT
ATT
STBY
HDG HDG
DCU
PWR
2/3
2
1
CONT
8
Airplanes 7072, 7068, 7295 and
subsequent, and Airplanes incorporating
the following Service Bulletin:
SB 601R--24--090.
Effectivity:
Airplanes 7036 and subsequent,
and Airplanes incorporating
the following Service Bulletin:
SB 601R--24--017.
4
4
7
20
ENG
IGN
B
APU
BATT
CONT
EMER SERV
BUS
BUS
FEED FEED
3
6
BATT
BUS
2
2
5
1
1
2
1
2
1
B
7
CB--5
7
A
5
MAIN
BATT
CONT
APU
ECU
B 6, B 7
B14, B15 -- Effectivity:
15
&LUFXLW %UHDNHU 3DQHO <7072, 7068 & subs, SB601R--34--045><7072, 7068, 7295 & subs,
SB601R--24--090><7036 & subs, SB601R--24--017>
)LJXUH 6KHHW Page 44
Canadair Regional Jet 100/200 - Electrical
Water System Circuit
Breakers
Used to protect the
following:
Control logic circuits.
Galley and lavatory pumps.
Galley and lavatory line
heaters, waste valve, and
drain mast heaters.
15
15
5
10
5
Water System Control Panel (1)
Galley Area
Galley System Circuit
Breakers
Used to protect ovens
and coffee maker.
0LVFHOODQHRXV 3DQHOV
)LJXUH Page 45