Bombardier CRJ 00-Electrical

7/30/2019 Bombardier CRJ 00-Electrical

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Table of Contents

FlightCrew Operating Manual

CSP A--013

MASTER

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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MASTERFlightCrew Operating Manual

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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--8 Miscellaneous Panels 07--40--13


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MASTER

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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AC Electrical System


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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


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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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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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


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 Indication (Generators)


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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


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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DC Electrical System


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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 Electrical SystemFigure 07---30---2

DC SERVICE

Used to connect the DCservice bus to theAPUbattery direct bus.


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.


26/48

REV 56, J an 31/03




CSP A--013

DC Electrical System EICAS Indications Figure 07---30---3

StatusPage

PrimaryPage


27/48

07--30--7Vol. 1




CSP A--013

MASTER

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


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.


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


28/48

REV 56, J an 31/03




CSP A--013

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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07--30--9Vol. 1




CSP A--013

MASTER

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)


30/48

REV 56, J an 31/03




CSP A--013

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)


31/48

07--30--11Vol. 1




CSP A--013

MASTER

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)


32/48

REV 56, J an 31/03




CSP A--013

F. System Circuit Breakers

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


33/48

07--30--13Vol. 1




CSP A--013

MASTER

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


34/48

REV 56, J an 31/03




CSP A--013

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


35/48

07--40--1Vol. 1


Circuit Breaker Panels


CSP A--013

MASTER

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.


36/48


37/48


38/48

REV 56, J an 31/03




CSP A--013

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.


39/48


40/48


41/48

07--40--7Vol. 1




CSP A--013

MASTER

Circuit Breaker Panel 2 (Sub---Panel) Figure 07---40---4 Sheet 1


-- S 6

-- R 7

-- T 2


42/48

REV 56, J an 31/03




CSP A--013

Circuit Breaker Panel 2 (Sub---Panel) Figure 07---40---4 Sheet 2

Effectivity:

Airplanes 7036 and subsequent,

incorporat ing the following

Service Bulletin:

SB 601 R --2 4--0 17.


SPARE FUSES


43/48

07--40--9Vol. 1




CSP A--013

MASTER

Circuit Breaker Panel 3 Figure 07---40---5

CIRCUIT BREAKER PANEL 3 -- C 4


44/48

REV 56, J an 31/03




CSP A--013

Circuit Breaker Panel 4 Figure 07---40---6

CIRCUIT BREAKER PANEL 4


45/48

07--40--11Vol. 1




CSP A--013

MASTER

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


46/48

REV 56, J an 31/03




CSP A--013

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


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


SB 601R --3 4--04 5.

A 8, A 9 --


47/48

07--40--13Vol. 1




CSP A--013

MASTER

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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Bombardier CRJ 00-Electrical