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CHAPTER 7 --- ELECTRICAL
Page
TABLE OF CONTENTS 07--00Table of Contents 07--00--1
INTRODUCTION 07--10
Introduction 07--10--1
AC ELECTRICAL SYSTEM 07--20
AC Electrical System 07--20--1
Integrated Drive Generator (IDG) 07--20--1APU Generator 07--20--1
AC Distribution 07--20--1
AC Loads Distribution 07--20--11Air Driven Generator (ADG) 07--20--12
Systems Circuit Breakers 07--20--14
DC ELECTRICAL SYSTEM 07--30
DC Electrical System 07--30--1
Transformer Rectifier Units (TRU) 07--30--1Batteries 07--30--1
External DC Power 07--30--5
DC Distribution 07--30--5DC Loads Distribution 07--30--9
Systems Circuit Breakers 07--30--12
CIRCUIT BREAKER PANELS 07--40
Circuit Breaker Panels 07--40--1
LIST OF ILLUSTRATIONS
INTRODUCTIONFigure 07--10--1 Electrical P ower Layout 07--10--3
Figure 07--10--2 Control Panels 07--10--4
AC ELECTRICAL SYSTEMFigure 07--20--1 AC System Distribution 07--20--3
Figure 07--20--2 AC Electrical System 07--20--4
Figure 07--20--3 AC Electrical SystemSynoptic Page 07--20--5
Figure 07--20--4 AC Electrical SystemE ICASIndications (Generators) 07--20--8
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Figure 07--20--5 AC Electrical SystemE ICASIndications (Busses) 07--20--9
Figure 07--20--6 Transformer Rectifier Units 07--20--10
Figure 07--20--7 Air Driven Generator (ADG) 07--20--13
DC ELECTRICAL SYSTEMFigure 07--30--1 DC Distribution System 07--30--3
Figure 07--30--2 DC Electrical System 07--30--4
Figure 07--30--3 DC Electrical System EICAS Indications 07--30--6
Figure 07--30--4 DC Emergency Bus 07--30--7
Figure 07--30--5 External DC Flow Line 07--30--8
CIRCUIT BREAKER PANELSFigure 07--40--1 Circuit Breaker Panel 1 07--40--2
Figure 07--40--2 Circuit Breaker Panel 1 (Sub--Panel) 07--40--4
Figure 07--40--3 Circuit Breaker Panel 2 07--40--5
Figure 07--40--4 Circuit Breaker Panel 2 (Sub--Panel) 07--40--7
Figure 07--40--5 Circuit Breaker Panel 3 07--40--9
Figure 07--40--6 Circuit Breaker Panel 4 07--40--10
Figure 07--40--7 Circuit Breaker Panel 5 07--40--11
Figure 07--40--8 Miscellaneous Panels 07--40--13
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1. INTRODUCTION
The aircraft uses both 115 Volts AC and 28 volts DC power. AC electrical power is providedby two engine-driven generation systems. Each system includes an integrated drivegenerator (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 froman in-flightair-driven generator (ADG). The ADG assembly is stowed in a compartment on the rightside of the nose section.
DC power is supplied by five transformer rectifier units (TRU) which rectifies AC input powerinto DC output power. Another source of DC power is froma main battery and APU battery.The main and APU batteries are connected into the aircraft DC electrical power systemandare charged by their respective battery chargers. Power for starting the APU is provided bythe 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 andcomponents. Power connection is dependent on system configuration and health. Thefollowing is a list of all the aircraft electrical system buses:
AC BUSSES DC BUSSES
DC BUS 1
AC BUS 1DC BUS 2
AC BUS 2DC ESSENTIAL BUS
AC ESSENTIAL BUSDC SERVICE BUS
AC SERVICE BUSADG BUS
DC UTILITY BUS 1AC UTILITY BUS 1
DC UTILITY BUS 2AC 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 onthe forward right side of the fuselage. The aircraft can also receive external DC through areceptacle located on the aft right side of the fuselage.
The electrical power services panel (EP SP ) in the flight compartment, and the externalservice panel on the right forward fuselage, contain the AC and DC systemcontrol switches.The switches are used for manual and automatic control of the electrical power generatingsystem and external power operation.
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Electrical system warnings and cautions are displayed on the EICAS primary page. Statusand advisory messages are displayed on the EICAS status page. General views of theelectrical systems are displayed on the EICAS, AC and DC synoptic pages. The AC and DCsynoptic pages are accessed through the EICAS control panel (ECP). One push of theELEC key on the ECP will display the AC synoptic page. Pushing the ELEC key a second
time will display the DC synoptic page.
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Electrical Power LayoutFigure 07---10---1
IDG 1
IDG 2
APU GENERATOR
EXTERNAL DCCONNECTION
APU BATTERY
MAIN BATTERY
TRANSFORMERRECTIFIER
UNITS
EXTERNAL ACCONNECTION AIR DRIVEN
GENERATOR
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Control PanelsFigure 07---10---2
Electrical PowerPanelOverhead Panel
External Service PanelRightForward Fuselage
Flight Attendant Panel
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1. AC ELECTRICAL SYSTEM
AC power for the aircraft electrical systems is provided by two engine-driven, integrateddrive generators (IDGs) which supply power to all AC buses during normal operations. AnAPU 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, emergencyAC power is provided automatically by a deployable air-driven generator (ADG). The ACdistribution system is controlled by the respective IDG and APU generator control units(GCUs). Each generator is monitored by the GCUs for voltage, frequency and kilovolt amps(KVA) to provide system fault protective shutdowns. An AC power distribution schematicand systemparameters 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 aninternal oil system to hydro--mechanically change the variable input speed from theengine accessory gearbox to a constant output speed to the generator to produce115--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 pressureor 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 thecover--guard and pushing the switchlight will manually disconnect the IDG from theengine gearbox.
The IDG will automatically disconnect if a severe oil overtemperature or overtorquecondition occurs. Once disconnected, either manually or automatically, the IDG cannotbe reconnected in flight. If the IDG was disconnected manually, it can only be reset onthe ground, with the engine shutdown. If the IDG was disconnected automatically, itmust be replaced.
Each generator control unit (GCU) controls and monitors the related AC generatorsystemand provides voltage and frequency regulation and fault protection for itsrespective generator. The GCU also protects the electrical system from overcurrentand differential current faults. In the event of a malfunction, the GCU will automaticallydisconnect the faulty generator from the respective AC buses. The generator may bereset when the malfunction is corrected or no longer exists, by selecting the generatorswitch 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 ACpower and is rated at 30 KVA fromsea level to 37,000 ft. A GCU, identical to the IDGGCU, provides the same regulation and protection functions as the IDG GCUs.
C. AC Distribution
Two different configurations of AC power distribution are available, Full configurationand Service configuration.
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In Full configuration, all the AC buses are powered using either IDG 1, IDG 2, the APUgenerator or external AC. For normal AC distribution, AC power from IDG 1 and IDG 2is distributed to all the AC buses via GCU controlled contactors in junction box 1 (J B1).There is a priority control of AC power distribution. During normal operation, IDG 1powers 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 fromthe failed IDG to the remaining operative IDG. When the APU generator is available, itcan then be used to replace the failed IDG to power the respective AC bus. On theground, if the aircraft is being powered with external AC power and either the APU oran IDG is brought on line, the external power will be automatically disconnected and therespective APU or IDG generator will power all the AC buses. When external power isnot available, the APU generator provides electrical power to all the AC buses. If anIDG is powering its respective AC bus and the APU generator is powering the other ACbus, when the remaining IDG is brought on line the APU generator will be automaticallytaken off line.
In service configuration, either external AC power or the APU generator is used topower 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.
IDG 1 APU GENERATOR IDG 2
Failed Not availableBoth AC Bus 1 and
AC Bus 2
Failed AC Bus 1 AC Bus 2
Both AC Bus 1 andAC Bus 2
Not available Failed
AC Bus 1 AC Bus 2 Failed
FailedBoth AC Bus 1 and
AC Bus 2 Failed
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AC System DistributionFigure 07---20---1
RIGHTENGINE
LEFTENGINE
GCU GEN1
APUGEN
GCU
AC ESS BUS
EXTERNALPOWER
MONITOR
GCU
ADG
APU
EXTERNALAC
CSD
GCU GEN2
CSD
ADG BUS
AC BUS 1
AC UTILBUS 1
AC ESS BUS AC BUS 2
AC SERVBUS
AC UTILBUS 2
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AC Electrical SystemFigure 07---20---2
Electrical PowerPanelOverhead Panel
AUTO XFER
Used to disable automatictransfer of associated IDG.OFF (white) light indicatesautotransfer is selected off.FAIL (amber) light indicates afault preventing autotransfer.
ACUsed to select externalAC power.
AVAIL (green) lightindicates externalpower is connectedand is ready to use.
IN USE (white) lightindicates that theexternal AC power unitis supplying theelectrical system.
External Service PanelRightForward Fuselage
GEN 1, 2 and APU GENAUTO -- Connectsgenerator toassociated bus.OFF/RESET --Disconnects generatorfrom associated busand/or resets the
generator controlcircuit.
EXT AC PUSHUsed to selectexternal AC power.
AVAIL (green) lightindicates externalpower is connected
and is ready to use.IN USE (white) lightindicates that theexternal AC powerunit is supplying theelectrical system.
IDG 1 and 2 DISC(Guarded)Used to disconnectIDG from engine.
DISC (white) lightindicates selecteddisconnect is successful.FAULT (amber) lightindicates a fault withinIDG (low oil pressure orhigh oil temperature).
IDG will automaticallydisconnect, when anovertemperature orovertorque conditionoccurs.
Once disconnected, theIDG cannot be reset withthe engines running.
AC ESS XFERUsed to switch essential bus feedfromAC bus 1 to AC bus 2.
ALTN (white) light indicatesessential bus is fed fromAC bus 2.
Transfer is automatic during anACbus 1 failure.
ON
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AC Electrical System Synoptic PageFigure 07---20---3 Sheet 1
AC Electrical Page
Generator LoadDisplays the load onthe generator.
Generator VoltageDisplays the generatorvoltage level.
Generator FrequencyDisplays the generatorfrequency level.
EICASOUTLINE GREEN AMBER WHITE
HALF INTENSITYMAGENTA
Invalid data_
_
HALF INTENSITYCYAN
Invalid data
Invalid data
GEN Generator onGenerator offwith engine /APU running
Both generatorand engine /APU are off
IDG Constantspeed drive on
Low oil pressureor high oil
temperature
Engine is off orIDG has
disconnected
_ Engine / APU offEngine / APUrunning andready to load
_
APU
EICAS DIGITALREADOUT GREEN AMBER WHITE
HALF INTENSITYMAGENTA
AMBER DASHES
XX KVAGenerator
loadedGenerator
overloadGenerator not
loaded
XXX V Voltage100--125 VAC
Invalid data
Invalid dataXXX HZFrequency
375--425 Hz
Voltage notin range
Frequencynot in range
Invalid data
_
_
UTIL BUS 2 Bus powered Invalid data
UTIL BUS 1 Bus powered Invalid data
SERV BUS Bus powered _Bus inoperative(AC service busfail)
Invalid data
ESS BUS Bus powered _ Invalid data
BUS 2 _ Invalid data
BUS 1Bus powered(generator linecontactor 1)
_ Invalid data
Bus powered(generator linecontactor 2)
Bus not powered(shed)
Bus not powered(shed)
Bus inoperative(essential busfail)
Bus not powered
Bus not powered
_
_
_
_
_
FlowLinesGreen -- Bus energized.Blank -- Bus not energized.
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AC Electrical System Synoptic PageFigure 07---20---3 Sheet 2
EICAS DIGITALREADOUT
EICASOUTLINE
GREEN WHITE
ADG
GREEN WHITE AMBER DASHES
XXX VBetween 108 and
130 voltsInvalid data
Invalid dataXXX HZ
Less than 108 volts ormore than 130 volts
ADG BUS
Between 360 and440 Hz
ADG outline green
Voltage and frequencydigital readouts green
ADG outline white
Voltage or frequencydigital readouts white
Less than 360 Hz ormore than 440 Hz
SHED (white)Indicates thatthe respectiveAC utilitybus has been automatically shed.
DISC (white)Indicates that IDG has been disconnected.
AUTO XFER OFF (white)Indicates that corresponding automatictransfer has been selected off.
AUTO XFER FAIL (amber)Indicates that corresponding automatictransfer has failed.
ADG FeaturesDisplayed when ADG voltage is more than 10 voltsand frequency is more than 300 Hz.
AC Electrical Page
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AC Electrical System Synoptic PageFigure 07---20---3 Sheet 3
External AC Power FeaturesDisplayed when external AC voltage is morethan 10 volts and frequency is more than 50 Hz.
EICASOUTLINE
GREEN WHITE HALF INTENSITYMAGENTA
Invalid dataExternal AC availableor in use
EICAS DIGITALREADOUT
GREEN AMBER WHITEHALF INTENSITY
MAGENTAAMBER DASHES
XX KVA Loaded Overload Not loaded Insufficient data Invalid data
XXX V Between 106and 124 volts
_ Invalid data
Invalid data_
XXX HZBetween 370
and 430 Hz
Less than 106 volts ormore than 124 volts
_
_Less than 370 Hz ormore than 430 Hz
External AC not availableand not in use
SERVICE CONFIGURATION (green)The message is displayed:
When external AC power is available and theAVAIL switchlight on the external service panelhas been selected, orWhenAPU power is available and theAPUSERV BUS switchlight on the forward F/Apanel has been selected.
For either selection, only theAC service bus, ACutility bus 1, AC utility bus 2, and the DC servicebus will be powered.
AC Electrical Page
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AC Electrical System EICAS Indications (Busses) Figure 07---20---5
AC SERV BUS caution (amber)Indicates that AC bus 2 is powered andAC service bus is less than 90 Volts.
AC BUS 1 or 2 caution (amber)Indicates that the associated bus is notpowered.
EMER PWR ONLY warning (red)Indicates that the ADG has deployed.
AC ESS BUS caution (amber)Indicates that AC essential bus isless than 90 Volts.
AC 1 or 2AUTOXFER caution (amber)Indicates that the corresponding automatic
bus transfer has failed.
Primary Page
AC 1 or 2AUTOXFER OFF status (white)Indicates that the corresponding automaticbus transfer has been selected off.
AC ESS ALTN status (white)Indicates that AC essential bus isbeing fed fromAC bus 2.
AC UTIL 1 or 2 OFF status (white)Indicates that corresponding ACutility bus is not powered.
Status Page
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Transformer Rectifier UnitsFigure 07---20---6
TRU Load ReadoutsDisplays, in incrementsof 1 amp, the load onthe rectifier.
EICASOUTLINE
GREEN AMBERWHITEHALF--INTENSITY
MAGENTA
Invalid data
Invalid data
Less than 18 VDCLoad less than
2 amp
Invalid data
18 VDC or greater Invalid data
Invalid data
18 VDC or greaterLoad more than2 amp
Less than 18 VDC
TRU failure
TRU failure18 VDC or greaterLoad more than3 amp
18 VDC or greaterLoad more than3 amp
18 VDC or greater
Less than 18 VDC
Less than 18 VDCLoad less than3 amp
Less than 18 VDCLoad less than3 amp
TRU1
TRU 2
ServiceTRU
EssentialTRU 2
EssentialTRU 1
EssTRU 1
VA
EssTRU 2
VA
SERVTRU 2
V
A
VA
TRU 2
V
A
TRU 1
TRU Voltage ReadoutsDisplays, in incrementsof 1 VDC, the rectifiersvoltage level.
DC ELEC PageEICAS Secondary DisplayCenter InstrumentPanel
EICAS DIGITALREADOUT
GREEN WHITE AMBER DASHES
xx V Between 22 and 29 VDC Invalid data
Invalid dataBetween 3 and 99 amp
Less than 22 VDC or
more than 29 VDC
xxALess than 3 amp ormore than 99 amp
_
_
_
AC BUS to TRU FlowLines
Green -- RespectiveAC bus is powering
TRU.
TRU Output FlowLines
Green -- RespectiveTRU is on--line andoutput is 18 VDC orgreater.
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The AC essential bus is normally powered by AC bus 1. If a fault exists on AC bus 1,the GCU will automatically transfer the power supplied to the AC essential bus, from ACbus 1 to AC bus 2. The crew can also manually transfer theAC essential bus supplypower, from AC bus 1 to AC bus 2, using the AC ESS XFER switchlight on the electricalpanel. In flight, the AC service bus is normally powered fromAC bus 2. On the ground,
it can be powered fromthe APU generator or fromexternal AC power.
The AC service bus supplies power to those circuits necessary for ground--servicingoperations, without having to power the entire electrical system.
The AC utility buses are normally powered (in full configuration) by their respective ACbus. In flight, the AC utility buses are automatically SHED if only one generator isoperational. In service configuration, the AC utility buses are powered from either theAPU generator or from external AC power.
D. AC Loads Distribution
AC BUS 1 AC BUS 2 AC ESSENTIALHydraulic Pumps 2B and 3B
Left Windshield Heater
Probe Heaters (R) (AOA andPitot) and TAT
Left --Navigation, Landing andTaxi Lights
Ground Proximity WarningSystem(GPWS)
Enhanced Ground ProximityWarning System(EGPWS)
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
HSTA (Ch--1)
Hydraulic Pumps 3A and 1B
Right Windshield Heaters
Right Window Heater
Ice Detector 2
Instrument Lights (copilot andoverhead), Landing and TaxiLights (R)
Inertial Reference System (2)
ARINC Display Fan, Galleyand 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 andPitot)
Ice Detector 1
Engine Ignition A
Instrument Lights (P ilots andCenter)
CB Panel Integral Lights
Inertial Reference System (1)
Head--up Guidance System
Traffic Alert and CollisionAvoidance (TCAS)
ARINC Chassis and DisplayCooling Fans (L)
Essential TRU 1
AC UTILITY BUS
1
AC UTILITY BUS
2
AC SERVICE
BUS
ADG Bus
Galley (1) andCoffee Maker
Galley (2) andWater System
Service TRU
Vacuum Cleaner
Hydraulic Pump 3B
Fla sMain BatteryCharger
APU BatteryCharger
ToiletMotor/pump
Power SensingRelay
Power SensingRelay
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E. Air Driven Generator (ADG)
In the event of a complete AC power failure in flight, the ADG will automatically deployand supply 115--volts, 400 Hz AC emergency power to the ADG bus. The ADGgenerator 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 poweressential TRU 1, which will power the DC essential bus.
If the automatic deploy function fails, the ADG can be deployed manually by pulling theADG manual release handle on the ADG CONTROL control panel at the rear of thecenter console.
If either main generator is restored, the crew can override the ADG by pressing thePWR TXFR OVERRIDE button on the ADG control panel. This will reconnect therestored IDG to power AC bus 1, AC bus 2 and the AC essential bus. The ADG willcontinue to power the critical flight controls and the ADG bus. The flaps will move athalf speed when powered fromthe ADG bus.
The ADG generator, voltage, frequency and ADG bus indications on the EICAS, ACELECTRICAL 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 airspeeddecreases below approximately100 kts. At that point, if the APU generator or IDG hasnot 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, bymaintenance personnel.
NOTE
After ADG deployment or APU generator switching,intermittent failure of the pilots and copilots air datasystems may occur. These failures may result inuncommanded changes to the pilots or copilots flightinstruments. The barometric altimetersetting, altitudepreselector, V--speeds andspeedbugsettings shouldbe checked and reset as required.
Automatic deployment of the ADG is inhibited, on the ground, when the parking brakeis set.
The ADG systemcircuits can be checked through a LAMP/UNIT test switch on the ADGcontrol 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:
S Pre--takeoff,When the test switch is set to UNIT the ADG systemcircuits are checked and theTEST light will illuminate within 1 second and remain ON for 2 seconds.
S Inflight,When the test switch is set to UNIT the ADG systemcircuits are checked and theTEST light will illuminate after 5 seconds and remain ON for 2 seconds.
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Air Driven Generator (ADG)Figure 07---20---7
ADG Manual Deploy HandleandAuto--Deploy Panel
Center Pedestal
TEST Light (green)Comes on after successfulcompletion of auto--deploysystemtest.
LAMP/UNIT SwitchUsed to test auto--deploy system.
Test can only be accomplished with
two generators selected ON andboth mainAC busses powered.
ADG Manual Deploy HandleUsed to manually deploy the ADG.
PWR TXFR OVERRIDEUsed to transfer ACessential bus power sourcefromthe ADG bus back to
the main AC bus.
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F. System Circuit Breakers
SYSTEM SUB--SYSTEM
CB NAME BUS BAR CBPANEL
CBLOCATION
NOTES
IDG 1 DISC P9enera orsIDG 2 DISC P10
GCU 1 DC BATTERY 1 Q10Generator GCU 2 Q11
GCU 3 Q12
ADG AUTO APU BATTERY B10ACElectrical
ADG MAN DIRECT BUS B11
PowerADG
ADG DEP LOYAUTO DC BATTERY
2 N6
DeployADG DEP LOYMAN BUS 2 N7
ADG DEP LOYSENS
AC BUS 1 1 C10
STBY PWRCONT
MAIN BATTERYDIRECT BUS
5 A7
AC ESS FEED ADG BUS 3 A8
AC ESS FEED AC BUS 1 1 C2
EssentialBus
ESS PWR CONTAPU BATTERYDIRECT BUS
5 B13
ESS AC XFRCONT
DC BATTERYBUS Q9
AC UTLY BUSFEED AC UTILITY 1 1
E2
ACAC Utility PWR SENS E7
Distribution AC UTLY BUSCONT
DC BUS 2 J 4
AC UTLY BUSFEED
E2
AC UtilityBus 2
AC UTLY BUSSENS
AC UTILITY 2 E7
AC UTLY BUSCONT
DC BUS 1 J 4
AC ServiceBus
AC SERV BUSFEED
AC SERV R2
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1. DC ELECTRICAL SYSTEM
Five transformer rectifier units (TRUs) and two batteries (Main and APU) provide the aircraftwith DC electrical power. DC power is also available through an external DC receptacle onthe right aft fuselage.
A. Transformer Rectifier Units (TRU)
There are five TRUs located in the nose avionics compartment. Each TRU converts115 VAC input power to 28 VDC output power for powering the aircraft DC buses. TheTRUs are rated at 100 amps. Normal distribution of the TRU outputs is shown in thefollowing table:
INPUT BUS TRU OUTPUT BUS
AC Bus 1 TRU 1DC Bus 1 and
DC Utility Bus 1
TRU 2 DC Bus 2 andDC Utility Bus 2
AC Bus 2
Essential TRU 2DC Essential Bus and
Battery Bus
AC Service Bus Service TRU DC Service Bus
AC Essential Bus Essential TRU 1DC Essential Bus and
Battery Bus
B. Batteries
The main and APU nickel-cadmiumbatteries and their battery chargers are located inthe aft equipment compartment. The batteries provide DC power to their respective DCbattery direct buses.
The 17 AMP./HR, 24, volt main battery provides backup power to the attitude headingreference system (AHRS), proximity sensing electronic unit (PSEU), data concentratorunits (DCUs), aircraft clocks, and the APU electronic control unit (ECU). The mainbattery also provides power to the flight compartment lighting system.
The 17 AMP./HR, 24 volt, main battery provides backup power to the inertial referencesystem (IRS), proximity sensing electronic unit (PSEU), data concentrator units(DCUs), aircraft clocks, and the APU electronic control unit (ECU). The main battery
also provides power to the flight compartment lighting system.
The 43 AMP./HR, 24 volt, APU battery provides the cranking power for starting theAPU.
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Battery chargers maintain the batteries at full charge. The main battery charger ispowered fromAC Utility bus 1 and the APU battery charger is powered fromthe ACUtility bus 2. Battery charging is controlled automatically. Each charger monitors thebattery voltage and temperature to control the battery charge rate. If a battery reachesthe overtemperature set point (as sensed by the charger), the charging will stop to
prevent overheating (thermal runaway).
Effectivity:
S Airplanes 7001 to 7220
NOTE
In flight, both chargers will be shed during singlegenerator operations. On the ground, both chargers areshed ifexternal AC poweris connected and the flaps are
out of the 0 detent, and the passenger door is closed.
Effectivity:
S Aircraft 7221 and subsequent
NOTE
In flight, both chargers will be shed during singlegenerator operations. On the ground, both chargers are
shed ifexternal AC poweris connected, theflaps are outofthe0 detent, and thepassengerand service doors areclosed.
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DC Distribution SystemFigure 07---30---1
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DC SERVICE
Used to connect the DCservice bus to theAPUbattery direct bus.
Electrical PowerPanelOverhead Panel
Essential Bus Tie
Switch/LightCLOSED -- Whenpressed in, comeson white to indicatethat ESS Bus hasbeen manually tiedto the service TRUduring a DCessential TRU failure.
BUS TIE 1 or 2Switch/Lights
CLOSED -- Come onwhite to indicate thatthe corresponding DCbus has beenautomatically tied to
the service TRU duringan abnormalcondition, or has beenpressed in, to manuallytie corresponding busto the service TRU.
CLOSED light (white)comes on.
Corresponding utilitybus is shed whenswitch/light indicatesCLOSED.
ESS TIE switch/lightcan only be selectedmanually.
BATTERY MASTERUsed to connect the APUand main battery direct
busses to the battery bus.
NOTE
Battery master shouldalways be in the ONposition in flight.
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C. External DC Power
The aircraft can be connected to 28 volts DC froman external receptacle located on theright aft fuselage below No. 2 engine. External DC is used for ground operations tosave 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 startcontactor. At the same time, the AVAIL lamp in the DC switchlight illuminates. Pressingthe switchlight closes two contactors to connect the external DC to the Main and APUbattery direct buses and the IN USE lamp in the switchlight illuminates.
D. DC Distribution
DC power is distributed to the DC systemby five TRUs. DC bus 1 and DC Utility bus 1are powered fromTRU 1. DC bus 2 and DC Utility bus 2 are powered fromTRU 2.The DC essential bus and battery buses are normally powered fromthe essentialTRUs. The emergency bus is powered fromthe battery bus and the APU battery directbus. The service TRU powers the DC service bus. In the event that an essential TRUfails, the DC essential bus and battery bus will remain powered from the operating
essential TRU. If both essential TRUs fail, the essential DC bus and battery bus maystill be powered from the service TRU by selecting the ES S TIE switchlight on theelectrical panel. In the event that a main TRU fails, the respective DC tie will close tomaintain power to the respective DC bus 1/2 fromthe service TRU. At the same timethe corresponding utility bus will be SHED.
The Main battery direct bus, APU battery direct bus, and the emergency bus are all hotbuses (they are continuously powered at all times from the batteries). When theBATTERY MASTER switch is selected ON, an input signal is supplied to the two powercontrollers (PC). The power controllers monitor for AC power, and if AC power is notavailable then the controllers will connect their respective batteries to the battery bus.When AC power is available, for the TRUs to power the DC system, the power
controllers will disconnect the batteries from the battery bus. Each battery direct buscan power the DC battery bus. Both the battery bus and the APU battery direct buspower the DC emergency bus. The DC service bus is normally powered from theservice TRU. If the DC SERVICE switch on the electrical panel is selected ON, the DCservice bus will be powered fromthe APU battery direct bus.
NOTE
Although there is only one battery bus, it is splitbetween circuit breaker panel 1 and 2 and is referredto 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 closeto connect the battery bus to the DC essential bus. Once the ADG bus is online topower essential TRU 1 and the DC essential bus, the batteries will act as a backuppower source to the DC essential bus.
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StatusPage
PrimaryPage
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DC Emergency Bus Figure 07---30---4
DC ELEC PageEICAS Display
Center Instrument Panel
During normal operation,
when the DC emergencybus is powered by both thebattery bus and the APUbattery direct bus, the DCemergency bus outline andrespective flow lines are notdisplayed.
NOTE
EICAS BUS BAROUTLINE GREEN
AMBER WHITE HALF--INTENSITYMAGENTA
Invalid data
Invalid data
SERVBUS _ Invalid data
ESS BUS
_ Invalid dataBATT BUS
_ Invalid data
Invalid data
Bus not powered
_ Invalid dataBus not powered
Bus powered
Bus powered
Bus powered
Bus powered
Bus powered
_
Bus not powered
Bus not powered
Bus not powered
_
_Battery lessthan 18 VDC
Battery lessthan 18 VDC
Battery 18 VDCor greater
Battery 18 VDCor greater
UTIL BUS 1
UTIL BUS 2
BUS 2
EICAS BUS BAR
OUTLINE GREEN AMBERWHITE
HALF--INTENSITY
MAGENTA
_
Invalid dataExternal dc in use
_
APUBATT
MAINBATT
APU BATTDIR BUS
MAIN BATTDIR BUS
BUS 1
Battery lessthan 18 VDC
Less that 18V orgreater than 32V.
Always displayedbetween 18V & 32V.
Battery 18 VDCor greater
DC Emergency Bus FlowLines
Green -- DC emergencybus is powered throughthe respective flow lineonly, or the respectivefeeder bus is availableto feed the failed DCemergency bus.White -- DC emergencybus is not poweredthrough the respectiveflow line.
DC Emergency BusOutline
Green -- DC emergencybus is powered by onlyone of the following:
Battery bus or,APU battery direct bus.
Amber -- DC emergencybus is not powered
CHARGER (Amber)Indicates that thecorresponding chargeris not charging.
CHARGER (White)
VA
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External DC Flow LineFigure 07---30---5
External DC FlowLine
Displayed when externalDC power is connected.Corresponds to DCAVAIL/IN USEswitch/light.
DC ELEC PageEICAS Secondary Display
Center InstrumentPanel
SERVICE CONFIGURATION (Amber)Indicates that the DC SERVICE switchhas been selected ON. Only the DCservice bus will be powered.
SERVICE BUS(Service Configuration)
Displayed when theDC Service switchis selected ON.
Either the battery masterswitch or external DC mustbe selected ON.
NOTE
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E. DC Loads Distribution
DC BUS 1 (CBP--1)
Spoiler Electronic Unit
Spoiler Electronic ControlSystem(PWR 1)
Heaters, Static (R) and ADSController (R)Cockpit Temperature Control
Left Windshield Heat Controller14th--Stage Bleed Air Isolationand Shutoff Valve (L)10th--Stage Bleed Air Isolationand Shutoff Valve (L)
Anti--ice Automatic NORM (1)Proximity Sensor (Landing GearControl/Door 1)(Weight--on--wheels 1)Lights (cockpit floor, rearanti--collision, wing inspection)
Maintenance Diagnostic
ComputerDME 1
Radio AltimeterFlight Data Recorder ControlWeather Radar (receiver,transmitter and control)EICAS Primary Display
EICAS Secondary DisplayLeft Lamp Driver UnitBright/dim Power supply unit
Data LoaderFlap Control (CH 1)
Nose Landing LightsBrake Temperature MonitorFMS (CDU 1)
DC Tie Control
Bus 1 Feed UtilityBus 1 Feed
DC 1 power SensingTRU 1 Power SensingAC Utility Bus Control
Left Air Conditioning UnitDME (1)
Smoke detectorPassenger signsOverboard shutoff Valve
Pilots Wiper (motor and control)Anti-Skid
GPS (1) Hydraulic System(AC pumpcontrol 2 and 3B, fan control,Indicator 2)
DC BUS 2 (CBP--2)
Horizontal Stabilizer TrimControlUnit (CH 1)Spoiler Electronic Unit (2A)
Spoiler Electronic ControlSystem(PWR 2)Clock 2
Cabin Temperature Controllerand Manual Controller
Right Windshield and WindowHeater Controller14th--Stage Bleed Air Isolationand Shutoff Valve (R)10th--Stage Bleed Air Isolationand Shutoff Valve (R)
Anti--ice Automatic NORM (2)Fuel Pump Control (R)Proximity Sensor (Landing GearControl/Door 2)(Weight--on--wheels 2)
Avionics Cooling (controller 2,cockpit shutoff valve, overboardshutoff valve
IAPS (AFCS) (right fan)EFIS Control Panel 2DCU 3 (CH A,B) .
Audio Control Panel (observers)ADF 2
DME 2VHF Nav radio 2VHF Comm radio 2
P F D 2MFD 2RTU 2
Air Data Computer (2)ATC Transponder 2GPS 2
Brake Pressure IndicatorAnti-SkidCopilots Wiper (motor andcontrol)Hydraulic System(AC pumpcontrol 1 and 3A, Indicator 1)
DC Tie ControlBus 2 Feed Tie and Utility
DC 2 power SensingTRU 1 Power SensingAC Utility Bus Control
Right Air Conditioning UnitFlap Control (CH 2)Nose Wheel Steering
Clock 2Lights (copilot map and winganti--collision)
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DC ESSENTIAL BUS (CBP--4)
Horizontal Stabilizer Trim ControlUnit (CH--2)Spoiler Electronic Unit (1A, 2B)
Spoiler Electronic ControlSystem1--2 (PWR 3)Heater, Static and ADS HeaterControl (L)Cabin Pressure Controllers (1and 2) and Control PanelLeft Window Heater Control10th--stage Bleed air IsolationValveBleed Air Leak TestAnti--ice Manual (L) STBY
Thrust Reverser (Auto, stow, 1and 2)Fuel (Transfer shutoff valve and
control)Oil Pressure (R)Passenger Door Control
Proximity Sensor (Landing GearControl)
Pilots FloodlightsEmergency LightsEFIS, CRT, Dimming Panel 1
Avionic Cooling Controller (1)Stall Protection (CH--R)DCU 1 (CH A, B)
EFIS Panel 1Audio Control Panel (copilots)ADC 1
ADF 1VHF Nav Radio (1)Cockpit Voice Recorder
P F D 1MFD 1
RTU 1Clock 1ATC Transponder 1
Head--up Guidance System
IAPS (AFCS) (left fan)
BATTERY BUS (CBP--1) BATTERY BUS (CBP--2)
Passenger Oxygen (manual deploy and leftpassengers)
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 (pilots)
Air Data Computer(1 and 2) Alternate powersupply
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)
Clock 1
Ram Air Shutoff Valve
CPAM
Crew Oxygen Monitor
Passenger Oxygen (auto deploy and rightpassengers)
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 System3 (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)
Overheat Detector (Main landing gear bay)
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MAIN BATTERY DIRECT BUS(CBP--5)
APU BATTERY DIRECT BUS(CBP--5)
BATTERY BUS (CBP--5)
Main Battery ContactorAPU ECUDCUs 1 and 2
Standby Power ControllerAttitude HeadingClocks 1 and 2
PSEULights (service, boarding andmaintenance)
APU Battery ContactorService Bus FeedOil Bypass Indicator
Engine Oil ReplenishmentSystemADG (auto and manual deploy)
External DC PowerEssential Power Control
Refuel/Defuel PanelEmergency Refuel
Engine Ignition System (B)
DC UTILITY BUS 1 (CBP--1) DC UTILITY BUS 2 (CBP--2) DC SERVICE BUS (CBP--2)
Left Cabin Reading LightsPower sensing
Right Cabin Reading LightsPower sensing
Lights (navigation, toilet andgalley dome)Cabin Lighting, Upward andDownward (L and R)Service Bus Feed from CBP--5Power Sensing (service bus and
TRU)
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SYSTEM SUB--SYSTEM CB NAME BUS BAR CBPANEL
CBLOCATION
NOTES
TRU 1 AC BUS 1 B2FEED E12
DC Bus 1 DC 1 PWRSENS
DC BUS 1 1 E14
TRU 1 PWRSENS
E15
TRU 2 AC BUS 2 B2
FEED E12
DC Bus 2 DC 2 PWRSENS
2 E14
TRU 2 PWRSENS
E15
DC PowerDistribution DC TIE
DC TIECONTROL
DC BUS 1 1 E11
CONTACTSTIE AND UTLY DC BUS 2 2 E11--E13
ESS TRU 1 AC ESS 3 A2
FEED 1 DCESS
DC BATM6
FEED 2 DCESS
2M8
Bus ESS TRU 1PWR SENS
M3
ESS TRU 2PWR SENS
DCESSENTIAL
2 M4
28 VDC ESSSENS
4 B3
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SYSTEM SUB--SYSTEM CB NAME BUS BAR CBPANEL
CBLOCATION
NOTES
FEED 1 BATTBUS
M5
Battery Bus FEED 2 BATTBUS 2 M7
BAT BUS PWRSENS
M9--M10
DC UtilityUTLY BUS 1FEED
DC BUS 11
E13
Bus 1PWR SENS DC UTIL 1 L10
DC UtilityUTLY BUS 2FEED
DC BUS 22
E13
Bus 2PWR SENS DC UTIL 2 L10
DC PowerDistribution
SERVICE BUSFEED
APU BATTDIRECT BUS 5 B3
BUS FEEDDC SERVICEBUS
T5
DC ServiceSERVICE TRU
AC SERVICEBUS
R5
Bus PWRSENS/SERVBUS DC SERVICE 2
T6
PWR BUS
TRU
DCEmergencyBus
APU BATTDIRECT FEED
DC EMERBUS
1 S6
APU BATTCONT
B2
EMER BUSFEED
B4
a n a nAPU Batteries
APU Battery RCCBCONT/APUBATT
BATT &28VDC ESSCONT 2
M12
APUCHARGER AC UTIL 2 E5
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SYSTEM NOTESCBLOCATION
CBPANEL
BUS BARCB NAMESUB--SYSTEM
MAIN BATTCONT
MAINBATTERYDIRECT BUS
5 C5
Main andAPU Batteries
Main BatteryRCCBCONT/MAINBATT
BATT &28VDC ESSCONT
2 M11
MAIN BATTCHARGER
AC UTIL 1 1 E5
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1. CIRCUIT BREAKER PANELS
There are six circuit breaker panels (CBPs) located in the aircraft. Four CBPs (numbered 1to 4) are located in the flight compartment. One CBP is located in the aft equipmentcompartment (number 5) and one CBP is located on the galley control panel.
The circuit breakers are clearly identified. For circuit breaker referencing, each circuitbreaker panel is laid out in an alphanumeric grid with letters running down the side of thepanel and numbers running across each row. For example, the location of a circuit breakeron circuit breaker panel 1, in the 3rd row, column 2, would be identified as CBP1--C2. In thisinstance, C2 is the circuit breaker for the AC ESS FEED.
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Circuit Breaker Panel 1 (Sub---Panel) Figure 07---40---2
CIRCUIT BREAKER PANEL 1(Sub--Panel)
Effectivity:
Airplanes 7003 to 7067, 7069 and
subsequent, incorporat ing
the following Service Bulletin:
SB 601R --2 1--03 9.
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Circuit Breaker Panel 2 (Sub---Panel) Figure 07---40---4 Sheet 1
CIRCUIT BREAKER PANEL 2(Sub--Panel)
-- S 6
-- R 7
-- T 2
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Effectivity:
Airplanes 7036 and subsequent,
incorporat ing the following
Service Bulletin:
SB 601 R --2 4--0 17.
CIRCUIT BREAKER PANEL 2(Sub--Panel)
SPARE FUSES
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Circuit Breaker Panel 3 Figure 07---40---5
CIRCUIT BREAKER PANEL 3 -- C 4
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CIRCUIT BREAKER PANEL 4
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Circuit Breaker Panel 5Figure 07---40---7 Sheet 1
CIRCUIT BREAKER PANEL 5(AFT side of J B--5 inAFT Compartment)
A CB--5 B
ADG
28VDCMAINBATTERY
DIRECTBUS
EICAS
APUBATTERYDIRECT
BUS
BATTBUS
MAIN
BATT
CONT
APU
ECU
STBY
PWR
CONT
CLK1
CLK2
ENGIGNB
APU
BATT
CONT
SERV
BUS
FEED
OIL
BYPS
IND
ENGOIL
PWR
AUTO
MAN
EXT
PWR
ESS
PWR
CONT
EMER
BUS
FEED
1
15
14
13
12
3
11
3
10
9
8
3
7
5
6
5
4
3
71 2
5
2
1
15
14
3
13
12
3
11
3
10
10
9
3
8
7
6
5
20
4
20
3
2
71
2
20
DCU2/3
71
2
FUEL
DEFL
EMRG
REFL
5
3
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Circuit Breaker Panel 5
Figure 07---40---7 Sheet 2
CIRCUIT BREAKER PANEL 5(AFT side of J B--5 inAFT Compartment)
A CB--5 B
ADG
28VDCMAINBATTERYDIRE
CTBUS
EICAS
APUBATTERYDIRECTBUS
BATTBUS
MAIN
BATT
CONT
APU
ECU
STBY
PWR
CONT
ATT
1
CLK1
CLK2
ENGIGNB
APU
BATT
CONT
SERV
BUS
FEED
OIL
BYPS
IND
ENGOIL
PWR
AUTO
MAN
EXT
PWR
ESS
PWR
CONT
HDG
ATT
2HDG
FUEL
DEFL
EMRG
REFL
MAIN
BATT
CHGRO/P
APU
BATT
CHGR
O/P
EMER
BUS
FEED
1
15
14
13
12
3
11
3
10
3
9
3
8
3
7
5
6
5
4
3
71
2
5
2
1
50
15
50
14
3
13
12
3
11
3
10
10
9
3
8
5
7
3
6
5
20
4
20
3
2
71 2
20
DCU2/3
71
2
Effectivity:
Airplanes 7072, 7068, 729 5 and
subsequent, and A irplanes incorporat ing
the following Service Bulletin:
SB 601R --2 4--09 0.
Effectivity:
Airplanes 7036 and subsequent,
and Airplanes incorporat ing
the following Service Bulletin:SB 601R --2 4--01 7.
SPAREFUSES
B 6, B 7
B14, B15 --
Effectivity:
Airplanes 7002, 7068 and
subsequent, incorporat ing
the following Service Bulletin:
SB 601R --3 4--04 5.
A 8, A 9 --
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Miscellaneous PanelsFigure 07---40---8
WaterSystemControl Panel (1)Galley Area
5 5
15
15 10
Galley System CircuitBreakersUsed to protect ovensand coffee maker.
WaterSystemCircuitBreakersUsed to protect thefollowing:
Control logic circuits.Galley and lavatory pumps.Galley and lavatory lineheaters, waste valve, anddrain mast heaters.
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