table of contents 07--00 introduction 07--10 ac … · 2012-06-27 · rev56,jan31/03 vol. 1...

07--00--1Vol. 1

REV 56, Jan 31/03ELECTRICAL

Table of Contents

Flight Crew Operating ManualCSP A--013

MASTER

CHAPTER 7 --- ELECTRICAL

Page

TABLE OF CONTENTS 07--00Table of Contents 07--00--1

INTRODUCTION 07--10Introduction 07--10--1

AC ELECTRICAL SYSTEM 07--20AC Electrical System 07--20--1

Integrated Drive Generator (IDG) 07--20--1APU Generator 07--20--1AC Distribution 07--20--1AC Loads Distribution 07--20--11Air Driven Generator (ADG) 07--20--12Systems Circuit Breakers 07--20--14

DC ELECTRICAL SYSTEM 07--30DC Electrical System 07--30--1

Transformer Rectifier Units (TRU) 07--30--1Batteries 07--30--1External DC Power 07--30--5DC Distribution 07--30--5DC Loads Distribution 07--30--9Systems Circuit Breakers 07--30--12

CIRCUIT BREAKER PANELS 07--40Circuit Breaker Panels 07--40--1

LIST OF ILLUSTRATIONS

INTRODUCTIONFigure 07--10--1 Electrical Power Layout 07--10--3Figure 07--10--2 Control Panels 07--10--4

AC ELECTRICAL SYSTEMFigure 07--20--1 AC System Distribution 07--20--3Figure 07--20--2 AC Electrical System 07--20--4Figure 07--20--3 AC Electrical System Synoptic Page 07--20--5Figure 07--20--4 AC Electrical System EICAS

Indications (Generators) 07--20--8

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Table of Contents

MASTERFlight Crew Operating ManualCSP A--013

Figure 07--20--5 AC Electrical System EICASIndications (Busses) 07--20--9

Figure 07--20--6 Transformer Rectifier Units 07--20--10Figure 07--20--7 Air Driven Generator (ADG) 07--20--13

DC ELECTRICAL SYSTEMFigure 07--30--1 DC Distribution System 07--30--3Figure 07--30--2 DC Electrical System 07--30--4Figure 07--30--3 DC Electrical System EICAS Indications 07--30--6Figure 07--30--4 DC Emergency Bus 07--30--7Figure 07--30--5 External DC Flow Line 07--30--8

CIRCUIT BREAKER PANELSFigure 07--40--1 Circuit Breaker Panel 1 07--40--2Figure 07--40--2 Circuit Breaker Panel 1 (Sub--Panel) 07--40--4Figure 07--40--3 Circuit Breaker Panel 2 07--40--5Figure 07--40--4 Circuit Breaker Panel 2 (Sub--Panel) 07--40--7Figure 07--40--5 Circuit Breaker Panel 3 07--40--9Figure 07--40--6 Circuit Breaker Panel 4 07--40--10Figure 07--40--7 Circuit Breaker Panel 5 07--40--11Figure 07--40--8 Miscellaneous Panels 07--40--13

07--10--1Vol. 1

REV 56, Jan 31/03ELECTRICALIntroduction


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 from an 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 from a main battery and APU battery.The main and APU batteries are connected into the aircraft DC electrical power system andare 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 theaircraft, 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 BUSSESDC BUS 1

AC BUS 1DC BUS 2

DC ESSENTIAL BUSAC BUS 1AC BUS 2

DC ESSENTIAL BUSDC SERVICE BUS

AC BUS 2AC ESSENTIAL BUS

DC SERVICE BUSLEFT AND RIGHT BATTERY BUS

AC SERVICE BUSLEFT AND RIGHT BATTERY BUS

DC EMERGENCY BUSADG BUS

DC EMERGENCY BUSDC UTILITY BUS 1

AC UTILITY BUS 1DC UTILITY BUS 1DC UTILITY BUS 2

AC UTILITY BUS 2DC UTILITY BUS 2

MAIN BATTERY DIRECT BUSMAIN BATTERY DIRECT BUSAPU 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 (EPSP) in the flight compartment, and the externalservice 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 generatingsystem and external power operation.

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Vol. 1 07--10--2ELECTRICALIntroduction


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 secondtime will display the DC synoptic page.

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REV 56, Jan 31/03ELECTRICALIntroduction


MASTER

Electrical Power LayoutFigure 07---10---1

IDG 1

IDG 2

APU GENERATOR

EXTERNAL DCCONNECTION

APU BATTERY

MAIN BATTERY

TRANSFORMERRECTIFIERUNITS

EXTERNALACCONNECTION AIR DRIVEN

GENERATOR

REV 56, Jan 31/03

Vol. 1 07--10--4ELECTRICALIntroduction


Control PanelsFigure 07---10---2

Electrical Power PanelOverhead Panel

External Service PanelRight Forward Fuselage

Flight Attendant Panel

07--20--1Vol. 1


AC Electrical System


MASTER

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 whenthe 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 GCU’s for voltage, frequency and kilovolt amps(KVA) to provide system fault protective shutdowns. An AC power distribution schematicand 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 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 ratedat 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 generatorsystem and 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 tomaintain a constant frequency output. The generator provides 115--volts, 400 Hz ACpower and is rated at 30 KVA from sea 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.

REV 56, Jan 31/03




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 (JB1).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 anyreason 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 Utilitybus 1, AC Utility bus 2, the AC service bus and the DC service bus are powered.

IDG 1 APU GENERATOR IDG 2

Failed Not available Both AC Bus 1 andAC Bus 2

Failed AC Bus 1 AC Bus 2Both AC Bus 1 and

AC Bus 2 Not available Failed

AC Bus 1 AC Bus 2 Failed

Failed Both AC Bus 1 andAC Bus 2 Failed

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MASTER

AC System DistributionFigure 07---20---1

RIGHTENGINE

LEFTENGINE

GCU GEN1

APUGEN GCU

AC ESS BUS

EXTERNALPOWERMONITOR

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

REV 56, Jan 31/03




AC Electrical SystemFigure 07---20---2


AUTO XFERUsed 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 PanelRight Forward Fuselage

GEN 1, 2 and APU GENAUTO -- Connectsgenerator toassociated bus.OFF/RESET --Disconnects generatorfrom associated busand/or resets thegenerator controlcircuit.

EXT AC PUSHUsed to selectexternal AC power.AVAIL (green) lightindicates externalpower is connectedand 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 feedfrom AC bus 1 to AC bus 2.ALTN (white) light indicatesessential bus is fed from AC bus 2.

Transfer is automatic during an ACbus 1 failure.

ON

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MASTER

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 oiltemperature

Engine is off orIDG has

disconnected

_ Engine / APU offEngine / APUrunning andready to load

_

APU

EICAS DIGITALREADOUT GREEN AMBER WHITE

HALF INTENSITYMAGENTA AMBER DASHES

XX KVA Generatorloaded

Generatoroverload

Generator notloaded

XXX V Voltage100--125 VAC

Invalid data

Invalid dataXXX HZ Frequency375--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

_

_

_

_

_

Flow LinesGreen -- Bus energized.Blank -- Bus not energized.

REV 56, Jan 31/03





EICAS DIGITALREADOUT

EICASOUTLINE GREEN WHITE

ADG

GREEN WHITE AMBER DASHES

XXX V Between 108 and130 volts Invalid 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 that the respective AC 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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MASTER


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 WHITE HALF INTENSITY

MAGENTAAMBER DASHES

XX KVA Loaded Overload Not loaded Insufficient data Invalid data

XXX VBetween 106and 124 volts

_ Invalid data

Invalid data_XXX HZ Between 370and 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, orWhen APU power is available and the APUSERV BUS switchlight on the forward F/Apanel has been selected.

For either selection, only the AC service bus, ACutility bus 1, AC utility bus 2, and the DC servicebus will be powered.

AC Electrical Page

REV 56, Jan 31/03




AC Electrical System EICAS Indication (Generators) <MSTFigure 07---20---4

<0039> <0006>

IDG 1 or 2 caution (amber)Indicates that IDG has low oil pressureor high oil temperature.

GEN 1 or 2 OVLD caution (amber)Indicates that generator control unit hasdetected a load of greater than 40 kVA.

GEN 1 or 2 OFF caution (amber)Indicates that generator is off.(Indications are inhibited during start)

APU GEN OVLD caution (amber)Indicates that generator control unit hasdetected a load of greater than 40 kVA.

APU GEN OFF caution (amber)Indicates that APU generator is off andAPU is ready to load.

Primary Page

<0039>

<0039>

IDG 1 or 2 DISC status (white)Indicates that IDG has been disconnected,either automatically or manually.

Status Page

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MASTER

AC Electrical System EICAS Indications (Busses) <MST>Figure 07---20---5

<0039> <0006>

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 2 AUTOXFER caution (amber)Indicates that the corresponding automaticbus transfer has failed.

Primary Page

<0039>

<0039>

AC 1 or 2 AUTOXFER 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 from AC bus 2.

AC UTIL 1 or 2 OFF status (white)Indicates that corresponding ACutility bus is not powered.

Status Page

REV 56, Jan 31/03




Transformer Rectifier UnitsFigure 07---20---6

TRU Load ReadoutsDisplays, in incrementsof 1 amp, the load onthe rectifier.

EICASOUTLINE

GREEN AMBERWHITE HALF--INTENSITYMAGENTA

Invalid data

Invalid data

Less than 18 VDCLoad less than2 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 amp18 VDC or greaterLoad more than3 amp

18 VDC or greater

Less than 18 VDC

Less than 18 VDCLoad less than3 ampLess 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 rectifier’svoltage level.

DC ELEC PageEICAS Secondary DisplayCenter Instrument Panel

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 ormore than 29 VDC

xx A Less than 3 amp ormore than 99 amp

_

_

_

AC BUS to TRU FlowLinesGreen -- RespectiveAC bus is poweringTRU.

TRU Output FlowLinesGreen -- RespectiveTRU is on--line andoutput is 18 VDC orgreater.

07--20--11Vol. 1




MASTER

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 the AC 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 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--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 ESSENTIAL

Hydraulic Pumps 2B and 3BLeft Windshield HeaterProbe Heaters (R) (AOA andPitot) and TATLeft --Navigation, Landing andTaxi LightsGround Proximity WarningSystem (GPWS)Enhanced Ground ProximityWarning System (EGPWS)<0040>

Flight Recorder PowerHydraulic System FanDisplay Cooling Fan (R)Exhaust and Cockpit FanFlap Power Drive Unit (1)Engine Vibration MonitorADG Deploy SensorTRU 1, DC essential bus

HSTA (Ch--1)Hydraulic Pumps 3A and 1BRight Windshield HeatersRight Window HeaterIce Detector 2Instrument Lights (copilot andoverhead), Landing and TaxiLights (R)Inertial Reference System (2)<0025>

ARINC Display Fan, Galleyand Cabin FanFlap Power Drive Unit (2)ADG Deploy SensorTRU 2, DC Essential bus

HSTA (Ch--2)Bleed Leak Controllers (L / R)Left Window HeaterProbe Heaters (L) (AOA andPitot)Ice Detector 1Engine Ignition AInstrument Lights (Pilot’s andCenter)CB Panel Integral LightsInertial Reference System (1)<0025>

Head--up Guidance System<0026>

Traffic Alert and CollisionAvoidance (TCAS)ARINC Chassis and DisplayCooling Fans (L)Essential TRU 1

AC UTILITY BUS1

AC UTILITY BUS2

AC SERVICEBUS

ADG Bus

Galley (1) andCoffee Maker

Galley (2) andWater System

Service TRUVacuum Cleaner

Hydraulic Pump 3BFlapsCo ee a e

Main BatteryCharger

ate SysteAPU BatteryCharger

Vacuum CleanerToiletMotor/pump

Flaps

gPower SensingRelay

gPower SensingRelay

Motor/pump

REV 56, Jan 31/03




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 theAC 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 from the 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 pilot’s and copilot’s air datasystems may occur. These failures may result inuncommanded changes to the pilot’s or copilot’s flightinstruments. The barometric altimeter setting, altitudepreselector, V--speeds and speed bug settings shouldbe checked and reset as required.

Automatic deployment of the ADG is inhibited, on the ground, when the parking brakeis set.

The ADG system circuits 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 thegreen 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 system circuits 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 system circuits are checked and theTEST light will illuminate after 5 seconds and remain ON for 2 seconds.

07--20--13Vol. 1




MASTER

Air Driven Generator (ADG)Figure 07---20---7

ADG Manual Deploy Handleand Auto--Deploy Panel

Center Pedestal

TEST Light (green)Comes on after successfulcompletion of auto--deploysystem test.

LAMP/UNIT SwitchUsed to test auto--deploy system.Test can only be accomplished withtwo generators selected ON andboth main AC busses powered.

ADG Manual Deploy HandleUsed to manually deploy the ADG.

PWR TXFR OVERRIDEUsed to transfer ACessential bus power sourcefrom the ADG bus back tothe main AC bus.

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F. System Circuit Breakers

SYSTEM SUB--SYSTEM

CB NAME BUS BAR CBPANEL

CBLOCATION

NOTES

GeneratorsIDG 1 DISC P9

GeneratorsIDG 2 DISC

DC BATTERYP10

G tGCU 1 DC BATTERY

BUS 1 Q10GeneratorControl

GCU 2BUS

Q11Control

GCU 3 Q12

ACADG AUTO APU BATTERY 5

B10ACElectrical

ADG MANAPU BATTERYDIRECT BUS 5

B11ElectricalPower

ADGD l

ADG DEPLOYAUTO DC BATTERY

2 N6

Deploy ADG DEPLOYMAN

DC BATTERYBUS

2 N7

ADG DEPLOYSENS AC BUS 1 1 C10

STBY PWRCONT

MAIN BATTERYDIRECT BUS 5 A7

AC ESS FEED ADG BUS 3 A8

ACAC ESS FEED AC BUS 1 1 C2

ACEssentialBus

ESS PWR CONT APU BATTERYDIRECT BUS 5 B13

BusESS AC XFRCONT

DC BATTERYBUS Q9

AC Utilit

AC UTLY BUSFEED AC UTILITY 1 1

E2

ACAC UtilityBus 1

PWR SENSAC UTILITY 1 1

E7ACDistribution

Bus 1AC UTLY BUSCONT DC BUS 2 J4

AC UTLY BUSFEED E2

AC UtilityBus 2

AC UTLY BUSSENS AC UTILITY 2

2E7

AC UTLY BUSCONT DC BUS 1

2J4

AC ServiceBus

AC SERV BUSFEED AC SERV R2

07--30--1Vol. 1


DC Electrical System


MASTER

1. DC ELECTRICAL SYSTEM

Five transformer rectifier units (TRU’s) 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 TRU’s located in the nose avionics compartment. Each TRU converts115 VAC input power to 28 VDC output power for powering the aircraft DC buses. TheTRU’s 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 1 DC Bus 1 andDC Utility Bus 1

AC B 2

TRU 2 DC Bus 2 andDC Utility Bus 2

AC Bus 2Essential TRU 2 DC Essential Bus and

Battery Bus

AC Service Bus Service TRU DC Service Bus

AC Essential Bus Essential TRU 1 DC Essential Bus andBattery Bus

B. Batteries

The main and APU nickel-cadmium batteries 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 (DCU’s), 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(DCU’s), aircraft clocks, and the APU electronic control unit (ECU). The main batteryalso provides power to the flight compartment lighting system. <0025>

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 from AC Utility bus 1 and the APU battery charger is powered from the 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 toprevent 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 if external AC power is connected and the flaps areout 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 areshed if external AC power is connected, the flaps are outof the 0 detent, and the passenger and service doors areclosed.

07--30--3Vol. 1




MASTER

DC Distribution SystemFigure 07---30---1

REV 56, Jan 31/03




DC Electrical SystemFigure 07---30---2

DC SERVICEUsed to connect the DCservice bus to the APUbattery direct bus.


Essential Bus TieSwitch/LightCLOSED -- Whenpressed in, comeson white to indicatethat ESS Bus hasbeen manually tiedto the service TRUduring a DCessential TRU failure.

BUS TIE 1 or 2Switch/LightsCLOSED -- Come onwhite to indicate thatthe corresponding DCbus has beenautomatically tied tothe 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 directbusses to the battery bus.

NOTEBattery master shouldalways be in the ONposition in flight.

07--30--5Vol. 1




MASTER

C. External DC Power

The aircraft can be connected to 28 volts DC from an 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 connectedto 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 system by five TRU’s. DC bus 1 and DC Utility bus 1are 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 essentialTRUs. The emergency bus is powered from the 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 operatingessential TRU. If both essential TRU’s fail, the essential DC bus and battery bus maystill be powered from the service TRU by selecting the ESS 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 from the 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 TRU’s to power the DC system, the powercontrollers 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 from the 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 reconnectthe 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.

REV 56, Jan 31/03




DC Electrical System EICAS Indications <MST>Figure 07---30---3

Status Page

<0039> <0006>

<0039>

<0039>

Primary Page

07--30--7Vol. 1




MASTER

DC Emergency Bus <MST>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--INTENSITY

MAGENTA

Invalid data

Invalid data

SERV BUS _ 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 BAROUTLINE 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 FlowLinesGreen -- 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 BusOutlineGreen -- 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.

<0039>CHARGER (White)

VA

REV 56, Jan 31/03




External DC Flow LineFigure 07---30---5

External DC Flow LineDisplayed when externalDC power is connected.Corresponds to DCAVAIL/IN USEswitch/light.

DC ELEC PageEICAS Secondary DisplayCenter Instrument Panel

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

07--30--9Vol. 1




MASTER

E. DC Loads Distribution

DC BUS 1 (CBP--1)

Spoiler Electronic UnitSpoiler Electronic ControlSystem (PWR 1)Heaters, Static (R) and ADSController (R)Cockpit Temperature ControlLeft 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 DiagnosticComputerDME 1Radio AltimeterFlight Data Recorder ControlWeather Radar (receiver,transmitter and control)EICAS Primary DisplayEICAS Secondary DisplayLeft Lamp Driver UnitBright/dim Power supply unitData LoaderFlap Control (CH 1)Nose Landing LightsBrake Temperature MonitorFMS (CDU 1) <0024><0050>

DC Tie ControlBus 1 Feed UtilityBus 1 FeedDC 1 power SensingTRU 1 Power SensingAC Utility Bus ControlLeft Air Conditioning UnitDME (1)Smoke detectorPassenger signsOverboard shutoff ValvePilots Wiper (motor and control)Anti-SkidGPS (1) <0027><0047>Hydraulic System (AC pumpcontrol 2 and 3B, fan control,Indicator 2)

DC BUS 2 (CBP--2)

Horizontal Stabilizer Trim ControlUnit (CH 1)Spoiler Electronic Unit (2A)Spoiler Electronic ControlSystem (PWR 2)Clock 2Cabin Temperature Controllerand Manual ControllerRight 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 valveIAPS (AFCS) (right fan)EFIS Control Panel 2DCU 3 (CH A,B) <0019>.Audio Control Panel (observers)ADF 2DME 2VHF Nav radio 2VHF Comm radio 2PFD 2MFD 2RTU 2Air Data Computer (2)ATC Transponder 2GPS 2 <0027>

Brake Pressure IndicatorAnti-SkidCopilots Wiper (motor andcontrol)Hydraulic System (AC pumpcontrol 1 and 3A, Indicator 1)DC Tie ControlBus 2 Feed Tie and UtilityDC 2 power SensingTRU 1 Power SensingAC Utility Bus ControlRight Air Conditioning UnitFlap Control (CH 2)Nose Wheel SteeringClock 2Lights (copilot map and winganti--collision)

REV 56, Jan 31/03




DC ESSENTIAL BUS (CBP--4)

Horizontal Stabilizer Trim ControlUnit (CH--2)Spoiler Electronic Unit (1A, 2B)Spoiler Electronic ControlSystem 1--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 andcontrol)Oil Pressure (R)Passenger Door ControlProximity Sensor (Landing GearControl)Pilot’s FloodlightsEmergency LightsEFIS, CRT, Dimming Panel 1Avionic Cooling Controller (1)Stall Protection (CH--R)DCU 1 (CH A, B)

EFIS Panel 1Audio Control Panel (copilot’s)ADC 1ADF 1VHF Nav Radio (1)Cockpit Voice RecorderPFD 1MFD 1RTU 1Clock 1ATC Transponder 1Head--up Guidance System<0026>IAPS (AFCS) (left fan)

BATTERY BUS (CBP--1) BATTERY BUS (CBP--2)

Passenger Oxygen (manual deploy and leftpassengers)Fuel System ControlLeft Fuel Pump (Control and Power)Fuel X--Feed ControlLeft Engine oil PressurePassenger AddressLights (Standby instrument and compass, mapdome,chart holder,overhead and copilot flood)Fire Detector (A, B, Test)Passenger SignsEICAS/RTU DimmingStall Protection (stick pusher CH 1)Audio Control Panel (pilot’s)Air Data Computer(1 and 2) Alternate powersupplyVHF Comm Radio 1Emergency Tuning UnitIDG Disconnect (1 and 2)Essential AC Transfer ControlGCU (1, 2 and 3)DC Emergency bus FeedEngine Ignition (A & B) ControlEngine Start (L and R)Transfer/APU (manual x--flow, fuel pump,controller, ECU)

Clock 1Ram Air Shutoff ValveCPAMCrew Oxygen MonitorPassenger Oxygen (auto deploy and rightpassengers)Anti--ice Valves (L and R manual 2)Proximity Sensor (Landing Gear Control/Door 1and 2) (Weight--on--wheels 1 and 2)EICAS Control PanelDCU 1 and 2 (CH A and B)Standby Horizon IndicatorEICAS Display 1 (ED1)EICAS Display 2 (ED2)Lamp Driver UnitBright/Dim Power Supply UnitHyd 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)

07--30--11Vol. 1




MASTER

MAIN BATTERY DIRECT BUS(CBP--5)

APU BATTERY DIRECT BUS(CBP--5)

BATTERY BUS (CBP--5)

Main Battery ContactorAPU ECUDCU’s 1 and 2Standby Power ControllerAttitude HeadingClocks 1 and 2PSEULights (service, boarding andmaintenance)

APU Battery ContactorService Bus FeedOil Bypass IndicatorEngine Oil ReplenishmentSystemADG (auto and manual deploy)External DC PowerEssential Power ControlRefuel/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 andTRU)

REV 56, Jan 31/03




F. System Circuit Breakers

SYSTEM SUB--SYSTEM CB NAME BUS BAR CBPANEL

CBLOCATION

NOTES

TRU 1 AC BUS 1 B2

FEED 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

DC BUS 22 E14

TRU 2 PWRSENS

DC BUS 2E15

DC PowerDistribution DC TIE

CONTACTS

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 DCFEED 1 DCESS

DC BAT 2M6

DC Essential

FEED 2 DCESS

DC BAT 2M8

DC EssentialBus ESS TRU 1

PWR SENS M3

ESS TRU 2PWR SENS

DCESSENTIAL

2 M4

28 VDC ESSSENS 4 B3

07--30--13Vol. 1




MASTER

SYSTEM SUB--SYSTEM CB NAME BUS BAR CBPANEL

CBLOCATION

NOTES

FEED 1 BATTBUS

DC BATM5

Battery BusFEED 2 BATTBUS

DC BAT2 M7

BAT BUS PWRSENS M9--M10

DC UtilityB 1

UTLY BUS 1FEED DC BUS 1

1E13

Bus 1 PWR SENS DC UTIL 11

L10

DC UtilityB 2

UTLY BUS 2FEED DC BUS 2

2E13

Bus 2 PWR SENS DC UTIL 22

L10

DC PowerDistribution

SERVICE BUSFEED

APU BATTDIRECT BUS 5 B3

Distribution

BUS FEED DC SERVICEBUS

1T5

DC ServiceSERVICE TRU AC SERVICE

BUS

1R5

Bus PWRSENS/SERVBUS DC SERVICE 2

T6

PWRSENS/SERV

DC SERVICEBUS

T7SENS/SERVTRU

T7

DCEmergencyBus

APU BATTDIRECT FEED

DC EMERBUS 1 S6

APU BATTCONT

APU BAT DIR 5B2

Main and

EMER BUSFEED

APU BAT DIR 5B4

Main andAPU Batteries APU Battery RCCB

CONT/APUBATT

BATT &28VDC ESSCONT 2

M12

APUCHARGER AC UTIL 2

2

E5

REV 56, Jan 31/03




SYSTEM NOTESCBLOCATION

CBPANEL

BUS BARCB NAMESUB--SYSTEM

MAIN BATTCONT

MAINBATTERYDIRECT BUS

5 C5

Main andAPU Batteries Main Battery

RCCBCONT/MAINBATT

BATT &28VDC ESSCONT

2 M11

MAIN BATTCHARGER AC UTIL 1 1 E5

07--40--1Vol. 1


Circuit Breaker Panels


MASTER

1. CIRCUIT BREAKER PANELS

There are six circuit breaker panels (CBP’s) located in the aircraft. Four CBP’s (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.

REV 56, Jan 31/03




Circuit Breaker Panel 1 <MST>Figure 07---40---1 Sheet 1

<0008>

--M9

<0010>

--H9

<0011>

--E8,E9,E10

<0014>

--M9

<0027>

--H13

<0031>

--H1

<0047>

--H13

<0055>

--G10

<0060>

--E8,E9,E10

CIR

CU

ITB

RE

AK

ER

PAN

EL

1(BehindPilot’s

Seat)

3

3

115VA

CUTILITY

BUS1

A B C D E F G H

J

K

L

M N P Q

POWERMUSTBEOFFBEFOREOPENINGPA

NEL

CBP--1

12

10 3

DISPL

PRIM

10 4

DISPL

SEC

3 5LLD

UEICAS

7 61BRT/D

IMPWRSUP

7 72

89

1011

1213

14

3 1

3 2

3 3

3 4

SKID

ANTI

15 5

MOTO

RWIPER

5 6

CONT

3 7

FLOOR

CKPT

5 8

A/C

OLL

REAR

LIGHTS

5 9

INSP

WING

10

12

PWR1

SECS

3

3 4

CH1

CONT

FLAPS

3 56

LGC/DI

78

910

11

1

25 2

FEED

UTLYBUS

34

56

78

910

1112

20 13

FEED

BUS1

UTLY

3 14

SENS

PWR

DC1

12

34

56

781

OVEN

910

1112

1314

1

20 2

FEED

ACESS

34

7 5

FAN

EXHAUST

6

3 78

3 9

PWR

REC

FLIGHT

1011

1213

5 14

NOSE

L

12

34

52

6

115VA

CBUS1

7

3 8

FAN

HYDSYST

9

20 10

WSHLD

LEFT

20 11

3 12TAT

HEATERS

3 13RAOA

7 14RPITOT

7 1

PUSHER

STICK

2

CHAN

LHSTALL

PROT

7 31COMM

VHF

3 4

TUNING

EMER

5

5 6

PILOT

5 7

C/PLT

AUDIO

5 8

OBS

9

1 10

2GCU

11

3

3

LT/VIB

INSTR

3

2

MAP

PLT

3

3

MAP

C/PLT

OBS

LIGHTS 3

4

DOME

3

5

PNL

O/H

3

6

DIMMING

EICAS/R

TU

7

3

8

MANUAL

PASSOXYGEN

5

910

11

5 1

LOOPA

FIREDET

5 2

LOOPB

34

56

781

SECU

5 9

SOV

XFE

R

20 10

PUMP

FUEL

3 11

CONT

3 1

OILPRESS

LENG

23

4RENGSTART

5L

20 6

PUMP

FUEL

L

3 7

CONT

PUMP

LFU

EL

8

LEFT

CABIN

READINGLTS

3

9

SENS

5

10

SIGNS

PASS

3

11

CONT

SYST

FUEL

5 1

SIGNS

PASS

2

3

3

SOV

O/B 4

5 5

FWD

5 6

MIDFW

D

5 7

MIDAFT

5 8

AFT

910

7

1

R/T

2

CONT1

WEATHERRDR

34

56

3 7

ALT

RAD

5 1

UNIT

COND

LAIR

23

3 4

CONT

BUS

ACUTLY

12

34

56

78

910

1112

1314

251 2

115VAC

BUS1

1 2

115VA

CUTILITY

BUS1

28VDC

BUS1

28VDC

BUS1

1 21 2

28VDC

BUS1

28VDC

BUS1

1 2

28VDCUTILITY

BUS1

28VDCBATTE

RYBUS

1 21 2

CONTR

OL

DCTIE

3

CONT2

15

WARN

PROX

GND

15151515

HYDPUMP

253B

5

HEATER

COMPT

BAGG

115VAC

BUS1

101TR

U

15

FDU1

FLAPS

AVIONICSCOOLING

7FAN

CKPT 1 2

3

SENS

DEPLO

YADG

3

LDG/TAXILTG W

INGL

LTS

NAV

5

153

FAN2

DISPLAY

AVIONICSCOOLING

FAN

COMPT

BAGG

115VA

CBUS1

MAKER

COFFEE

10

CHARGER

MAIN

BATT

AC

3

SENS

PWR

MON

VIB

ENG

10

RX/TX

HF1

28VDC

BUS1

CPLR 3

10

FEED

3

SENS

PWR

TRU1

2028VDC

BUS1CONTR

OL

71 2

3

12

WSHLD

CONTL

HEATERS

3 13

CONT2

ADS

3 14RSTATIC

3

HTR

SOVL

B/AIR

10ST 3 11

CONT3B

ACPUMP

3 12

CONT

FANHYDSYST

3 132IND

3 14

CONT2

ACPUMP

MON

TEMP

BRAKE

1AUTO

A/IC

E

2FIREX

CARGO

3

WOW1

3

STE

ER

NOSE

3

ISOL

3

SOVL

71 2

71 2

CH1

FEEL

PITCH

31CDU

LOAD

DATA 3

31DME

73 1 23

CAL

SEL

3

FMS/MDC

LEFT

IAPS

5

CONT

5

CONT

MAN

CKPTTE

MP

3

CONT

REC

FLIGHT

3

DET

SMOKE

3AENGIGN

3B

77

1 21 2

20

FEED

BUS

EMER

SOV

X/FLO

W3

COMM

VHF

77

1 21 2

12

5

ACT

DOOR

PASS

3

CONT

COMP

BAGG

PWR

28VDCBUS1

3

TEST

28VDCBATTE

RYBUS

3

LEVEL

OIL

ENG

10 12

71 2

ECU

APU

XFE

R/APU

DEPLO

YLE

FTPA

SS

12

5

DISC

IDG1

5

DISC

IDG2

STB

Y

5 11FIREX

CARGO

3

STB

YADC

71 2

ADDR

PASS

71 2

71 2

71 2

71 2

11

3

CONT

XFR

ESSAC

3

PROXSENS

B/AIR

14ST

28VDC

BUS1

28VDCBATTE

RYBUS

28VDCBATTE

RYBUS

3LTS

PULS

E

3

5

MAINT

ACT

3IND

15

DOOR

1GPS

3

NO

TE

ForsingleHFinstallation<0011>,

circuitbreakersE--8

toE--10are

deactivated

(collared)andlabeled

asinoperative.

07--40--3Vol. 1




MASTER

Circuit Breaker Panel 1 <7072 & subs, SB601R--28--022><7300 & subs><7390 & subs><7452 & subs>Figure 07---40---1 Sheet 2

CIR

CU

ITB

RE

AK

ER

PAN

EL

1(BehindPilot’s

Seat)

3

3

115VA

CUTILITY

BUS1

A B C D E F G H

J

K

L

M N P Q


NEL

CBP--1

12

10 3

DISPL

PRIM

10 4

DISPL

SEC

3 5LLD

UEICAS

7 61BRT/D

IMPWRSUP

7 72

89

1011

1213

14

3 1

3 2

3 3

3 4

SKID

ANTI

15 5

MOTO

RWIPER

5 6

CONT

3 7

FLOOR

CKPT

5 8

A/C

OLL

REAR

LIGHTS

5 9

INSP

WING

10

12

PWR1

SECS

3

3 4

CH1

CONT

FLAPS

3 56

LGC/DI

78

910

11

1

25 2

FEED

UTLYBUS

34

56

78

910

1112

20 13

FEED

BUS1

UTLY

3 14

SENS

PWR

DC1

12

34

56

781

OVEN

910

1112

1314

1

20 2

FEED

ACESS

34

7 5

FAN

EXHAUST

6

3 78

3 9

PWR

REC

FLIGHT

1011

1213

5 14

NOSE

L

12

34

52

6

115VA

CBUS1

7

3 8

FAN

HYDSYST

9

20 10

WSHLD

LEFT

20 11

3 12TAT

HEATERS

3 13RAOA

7 14RPITOT

7 1

PUSHER

STICK

2

CHAN

LHSTALL

PROT

7 31COMM

VHF

3 4

TUNING

EMER

5

5 6

PILOT

5 7

C/PLT

AUDIO

5 8

OBS

9

1 10

2GCU

11

3

3

LT/VIB

INSTR

3

2

MAP

PLT

3

3

MAP

C/PLT

OBS

LIGHTS 3

4

DOME

3

5

PNL

O/H

3

6

DIMMING

EICAS/R

TU

7

3

8

MANUAL

PASSOXYGEN

5

910

11

5 1

LOOPA

FIREDET

5 2

LOOPB

34

56

781

SECU

5 9

20 10

3 11

3 1

OILPRESS

LENG

23

4RENGSTART

5L

20 6

PUMP

FUEL

L

3 7

CONT

PUMP

LFU

EL

8

LEFT

CABIN

READINGLTS

3

9

SENS

5

10

SIGNS

PASS

3

11

CONT

SYST

FUEL

5 1

SIGNS

PASS

2

3

3

SOV

O/B 4

5 5

FWD

5 6

MIDFW

D

5 7

MIDAFT

5 8

AFT

910

7

1

R/T

2

CONT1

WEATHERRDR

34

56

3 7

ALT

RAD

5 1

UNIT

COND

23

3 4

CONT

BUS

ACUTLY

12

34

56

78

910

1112

1314

251 2

115VAC

BUS1

1 2

115VA

CUTILITY

BUS1

28VDC

BUS1

28VDC

BUS1

1 21 2

28VDC

BUS1

28VDC

BUS1

1 2

28VDCUTILITY

BUS1

28VDCBATTE

RYBUS

1 21 2

CONTR

OL

DCTIE

3

CONT2

15

WARN

PROX

GND

15151515

HYDPUMP

253B

5

HEATER

COMPT

BAGG

115VAC

BUS1

101TR

U

15

FDU1

FLAPS

AVIONICSCOOLING

7FAN

CKPT 1 2

3

SENS

DEPLO

YADG

2

LDG/TAXILTG W

INGL

LTS

NAV

5

153

FAN2

DISPLAY

AVIONICSCOOLING

FAN

COMPT

BAGG

115VA

CBUS1

MAKER

COFFEE

10

CHARGER

MAIN

BATT

AC

3

SENS

PWR

MON

VIB

ENG

RX/TX

HF1

28VDC

BUS1

CPLR

FEED

3

SENS

PWR

TRU1

2028VDC

BUS1CONTR

OL

71 2

3

12

WSHLD

CONTL

HEATERS

3 13

CONT2

ADS

3 14RSTATIC

3

HTR

SOVL

B/AIR

10ST 3 11

CONT3B

ACPUMP

3 12

CONT

FANHYDSYST

3 132IND

3 14

CONT2

ACPUMP

MON

TEMP

BRAKE

1AUTO

A/IC

E

2FIREX

CARGO

3

WOW1

3

STE

ER

NOSE

3

ISOL

3

SOVL

71 2

71 2

CH1

FEEL

PITCH

31CDU

LOAD

DATA 3

31DME

73 1 23

FMS/MDC

LEFT

IAPS

5

CONT

5

CONT

CKPTTE

MP

3

CONT

REC

FLIGHT

3

DET

SMOKE

3AENGIGN

3B

77

1 21 2

20

FEED

BUS

EMER

SOV

X/FLO

W

12

5

ACT

DOOR

PASS

3

CONT

COMP

BAGG

PWR

28VDCBUS1

3

TEST

28VDCBATTE

RYBUS

3

LEVEL

OIL

ENG

10 12

71 2

DEPLO

YLE

FTPA

SS

12

5

DISC

IDG1

5

DISC

IDG2

STB

Y

5 11FIREX

CARGO

3

STB

YADC

71 2

ADDR

PASS

71 2

71 2

71 2

71 2

11

3

CONT

XFR

ESSAC

3

PROXSENS

B/AIR

14ST

28VDC

BUS1

28VDCBATTE

RYBUS

28VDCBATTE

RYBUS

ACT

3IND

15

DOOR

PUMP

FUEL

CONT

ECU

APU

71 2

SOV

FUEL

LEFT

XFE

R/APU

Effe

ctiv

ity:

Airp

lane

s70

722

and

subs

eque

nt,

and

Airp

lane

sin

corp

ora

ting

the

follo

win

gS

ervi

ceB

ulle

tin:

SB

601R

--28

--022

.

Effe

ctiv

ity:

Airp

lane

s73

90an

dsu

bseq

uent

,equ

ippe

dw

ithP

hase

IIIor

Pha

seIV

Pas

seng

erD

oor.

Effe

ctiv

ity:

Airp

lane

s73

00an

dsu

bseq

uent

,C13

is2

AM

PS

.C13

--

F1,F2--

L2--

Effe

ctiv

ity:

Airp

lane

s74

52an

dsu

bseq

uent

,C

ircui

tBre

aker

Gua

rdIn

stal

latio

n.

GUARD

LAIR

MAN

3

REV 56, Jan 31/03




Circuit Breaker Panel 1 (Sub---Panel) <Aircraft 7003 to 7067, 7069 & subs,SB601R--21--039>Figure 07---40---2

CIRCUIT BREAKER PANEL 1(Sub--Panel)

Effectivity:Airplanes 7003 to 7067, 7069 andsubsequent, incorporatingthe following Service Bulletin:

SB 601R--21--039.

07--40--5Vol. 1




MASTER

Circuit Breaker Panel 2 <MST>Figure 07---40---3 Sheet 1

<0011>

--E8,E9,E10

<0019>

--K6,K7

<0027>

--H13

<0045>

--L1

<0047>

--H13

<0060>

--E8,E9,E10

<0082>

--C11

CIR

CU

ITB

RE

AK

ER

PAN

EL

2(BehindCopilot’s

Seat)

3

A B C D E F G H

J

K

L

M N P Q


NEL

CBP--2

12

3

3

4

2CDU

5

2COMM

6

2

7

2

89

1011

1213

14

3

1

3

2

3

3

3

4

CONT

3

5

CONT

20

6

PUMP

7

5 8

A/C

OLL

3

9

MAP

C/PLT

10

12

WIND

R

3

3

4

WSHLDR

3

56

SOVR

78

910

11

1

25

2

FEED

UTLYBUS

34

56

78

910

1112

20 13

TIE&

UTLY

3 14

SENS

PWR

DC2

12

34

56

782

OVEN

910

1112

1314

1

20 2

FEED

ACESS

34

56

3 78

910

1112

13

5 14

NOSE

R

12

34

51

6

115VA

CBUS2

7

10 82

9

20 10

WSHLD

RIGHT

20 11

15 12

WING

HEATERS

1314

12

34

5

10

610

7

3

89

CHB

10

CHA

11

3

3

DEPLO

YAUTO

3

23

10

45

3 67

8

PROXSENS

910

11

3

1

3

23

45

67

8

2MAN

3

9

REND

VALVE

3

1011

1

APU

23

4

SENSBAT

BUS

5

ESS

50

6

BUS

BATT 7

ESS

DC

8

RIGHTCABIN

READINGLTS

3

9

SENS

10

F6PA

11

F5PA

3 1

ALT

2RAD

2

3

3

SOV

I/B 4

5 5

FWD

5 6

MIDFW

D

5 7

MIDAFT

5 8

AFT

910

12

2

34

56

10

7

2PFD

5 1

UNIT

COND

RAIR

23

41

23

45

67

89

1011

1213

14

25

115VAC

BUS2

115VA

CUTILITY

BUS2

28VDC

BUS2

28VDC

BUS2

28VDC

BUS2

28VDC

BUS2

28VDCUTILITY

BUS2

BATT&28

VDCESSCONTR

OL

CONTR

OL

DCTIE

15 15151515

HYDPUMP

253A

HEATER

STABCH1

115VAC

BUS2

31IRU

HTR

SGALLEY

3

FAN

CABIN

3

SENS

DEPLO

YADG

3

L/TLTS

WING

RPNL

O/H

5

153

FAN2

ARINC

AVIONICSCOOLING

115VA

CBUS2

MAKER2

10

CHARGER

APU

AC

3

SENS

PWR

DET2

ICE

10

RX/TX

HF1

28VDC

BUS2

CPL 3

10

FEED

3

SENS

PWR

TRU2

2028VDC

BUS2CONTR

OL

12

CH2

CONT

13

PWD2

SECS

14

FLAPS

HSTC

USTABCH1

15

11

MOTO

R

3

12

SKID

ANTI

3

13

IND

PRESS

3

14

2AUTO

1IND

CONT1

ACPUMP

CONT3A

PUMP

3

WOW2

3

STE

ER

NOSE

3

TRIM

3

TRIM

33

OBS

AUDIO

2CLO

CK

32ADC

2

32ADF

32AHRS

5

CONT 5CABIN

TEMP

3

CHA

EICAS

3

CHB

DCU3

BATT

RCCBCONT

3

BUS

BATT

SENS

PWR2

12

32CONT

3

SOV

CKPT

PWR

28VDCBUS2

3

28VDCBATTE

RYBUS

3

MAN

12

LGC/DI

12

5

WOW1+2

LGC/D2

5

1

PASS

RIGHT

3

3

12

3

28VDC

BUS2

32FAN

3

CONT

FAN

3

CH2

10

AFC

S

10

28VDCBATTE

RYBUS

28VDCBATTE

RYBUS

333

SENS

PWR1

353

371 2

3

3

3

15 15 15

3

CONT

BUS

ACUTLY

MAN

CONT

102MFD

PNL2

CONT

EFIS

RTU

AVIONIC

COOLING

350

5050

371 2

71 2

PWR

DC

MAIN

FEED1

FEED2

ESSTR

U2

ESSTR

USHUNTFU

SES

SENS

PWR

BATT

71 2

71 2

33

ESSTR

U1

A/IC

E

F8PA

F7PA

SHUNTFU

SES

LEND

VALVE

CONT

AUTO

DET

OVHT

INSTR

STB

Y1

CLO

CK

IND3

SYST

HYD

2SECU

MLG

BAY

3BRT/D

IMPWDSUP

21

71 2

712

71 2

DISPL

PRIM

DISPL

SEC

PNL

CONT

EICAS

RLD

UDCU1

CHB

CHADCU2

MONITOR

OXYGEN

CREW

AFC

SLE

FTIAPS

FAN

LEFT

IAPS

MOD

PRESS

CABIN

SOV

AIR

RAM

71 2

71 2

PASSOXYGEN

COFFEE

TANKS

10LAV

10

LINESHTR

S

TRU

ESS

RIGHT

102TR

U

15

FDU2

FLAPS

71 2

71 2

3

PNL

C/PLTIN

STLTG

RUDDER

AIL

HTR

CONT

SENS

PROX

B/AIR

14ST

SOVR

B/AIR

10ST

FEEL

PITCH

RIGHT

IAPS

71 2

LIGHTS

WIPER2

HYDSYST

HTR

SGALLEY

PUMP

RFU

EL

FUEL

RWING

BRAKE

A/IC

E

71 2

71 2

33

3

FMS

RIGHT

IAPS

RIGHT

IAPS

XPDR

DME

NAV

VHF

AHRS

VHF

WATERSYSTE

M

10

GALLEY

HTR

S

115VA

CUTILITY

BUS2

3

ACARS

32GPS

NO

TE

ForsingleHFinstallation<0011>,

circuitbreakersE--8

toE--10are

deactivated

(collared)andlabeled

asinoperative.

ADGDEPLO

Y

REV 56, Jan 31/03




Circuit Breaker Panel 2 <7002, 7076 & subs, SB601R--24--036><7072 & subs, SB601R--28--022><7452 &subs><7676, 7686, 7784 and 7807>Figure 07---40---3 Sheet 2

CIR

CU

ITB

RE

AK

ER

PAN

EL

2(BehindCopilot’s

Seat)

3

GUARD

A B C D E F G H

J

K

L

M N P Q


NEL

CBP--2

12

3

3

4

2CDU

5

2COMM

6

2

7

2

89

1011

1213

14

3

1

3

2

3

3

3

4

CONT

3

5

CONT

20

6

PUMP

7

5 8

A/C

OLL

3

9

MAP

C/PLT

10

12

WIND

R

3

3

4

WSHLDR

3

56

SOVR

78

910

11

1

25

2

FEED

UTLYBUS

34

56

78

910

1112

20 13

TIE&

UTLY

3 14

SENS

PWR

DC2

12

34

56

782

OVEN

910

1112

1314

1

20 2

FEED

ACESS

34

3 5

FAN

LAVATO

RY

6

3 78

910

1112

13

5 14

NOSE

R

12

34

51

6

115VA

CBUS2

7

10 82

9

20 10

WSHLD

RIGHT

20 11

15 12

WING

HEATERS

1314

12

34

5

10

610

7

3

89

CHB

10

CHA

11

3

3

DEPLO

YAUTO

3

23

10

45

3 67

8

PROXSENS

910

11

3

1

3

23

45

67

8

2MAN

3

9

REND

VALVE

3

1011

1

APU

23

4

SENSBAT

BUS

5

ESS

50

6

BUS

BATT 7

ESS

DC

8

RIGHTCABIN

READINGLTS

3

9

SENS

10

F6PA

11

F5PA

12

3

3

SOV

I/B 4

5 5

FWD

5 6

MIDFW

D

5 7

MIDAFT

5 8

AFT

910

12

2

34

56

10

7

2PFD

5 1

UNIT

COND

RAIR

23

41

23

45

67

89

1011

1213

14

25

115VAC

BUS2

115VA

CUTILITY

BUS2

28VDC

BUS2

28VDC

BUS2

28VDC

BUS2

28VDC

BUS2

28VDCUTILITY

BUS2

BATT&28

VDCESSCONTR

OL

CONTR

OL

DCTIE

15 15151515

HYDPUMP

253A

HEATER

STABCH1

115VAC

BUS2

31IRU

HTR

SGALLEY

GALLEY&

3

FAN

CABIN

3

SENS

DEPLO

YADG

3

L/TLTS

WING

RPNL

O/H

5

153

FAN2

ARINC

AVIONICSCOOLING

115VA

CBUS2

MAKER2

10

CHARGER

APU

AC

3

SENS

PWR

DET2

ICE

RX/TX

HF1

28VDC

BUS2

CPL

FEED

3

SENS

PWR

TRU2

2028VDC

BUS2CONTR

OL

12

CH2

CONT

13

PWD2

SECS

14

FLAPS

HSTC

USTABCH1

15

11

MOTO

R

3

12

SKID

ANTI

3

13

IND

PRESS

3

14

2AUTO

1IND

CONT1

ACPUMP

CONT3A

PUMP

3

WOW2

3

STE

ER

NOSE

3

TRIM

3

TRIM

33

OBS

AUDIO

2CLO

CK

32ADC

2

32ADF

32AHRS

5

CONT 5CABIN

TEMP BATT

RCCBCONT

3

BUS

BATT

SENS

PWR2

12

32CONT

3

SOV

CKPT

PWR

28VDCBUS2

3

28VDCBATTE

RYBUS

3

MAN

12

LGC/DI

12

5

WOW1+2

LGC/D2

5

1

PASS

RIGHT

3

3

12

3

28VDC

BUS2

32FAN

3

CONT

FAN

3

CH2

10

AFC

S

10

28VDCBATTE

RYBUS

28VDCBATTE

RYBUS

333

SENS

PWR1

353

3

71 2

3

3

3

15 15 15

3

CONT

BUS

ACUTLY

MAN

CONT

102MFD

PNL2

CONT

EFIS

RTU

AVIONIC

COOLING

350

5050

371 2

71 2

PWR

DC

MAIN

FEED1

FEED2

ESSTR

U2

ESSTR

USHUNTFU

SES

SENS

PWR

BATT

71 2

71 2

33

ESSTR

U1

A/IC

E

F8PA

F7PA

SHUNTFU

SES

LEND

VALVE

AUTO

DET

OVHT

INSTR

STB

Y1

CLO

CK

IND3

SYST

HYD

2SECU

MLG

BAY

3BRT/D

IMPWDSUP

21

71 2

71 2

71 2

DISPL

PRIM

DISPL

SEC

PNL

CONT

EICAS

RLD

UDCU1

CHB

CHADCU2

MONITOR

OXYGEN

CREW

AFC

SLE

FTIAPS

FAN

LEFT

IAPS

MOD

PRESS

CABIN

SOV

AIR

RAM

71 2

712

PASSOXYGEN

COFFEE

TANKS

10LAV

10

LINESHTR

S

TRU

ESS

RIGHT

102TR

U

15

FDU2

FLAPS

71 2

71 2

3

PNL

C/PLTIN

STLTG

RUDDER

AIL

HTR

CONT

SENS

PROX

B/AIR

14ST

SOVR

B/AIR

10ST

FEEL

PITCH

RIGHT

IAPS

71 2

LIGHTS

WIPER2

HYDSYST

HTR

SGALLEY

PUMP

RFU

EL

FUEL

RWING

BRAKE

A/IC

E

71 2

71 2

33

3

FMS

RIGHT

IAPS

RIGHT

IAPS

XPDR

DME

NAV

VHF

AHRS

VHF

WATERSYSTE

M

10

GALLEY

HTR

S

115VA

CUTILITY

BUS2

3

PRINTE

RACARS

Effe

ctiv

ity:

Airp

lane

s70

72an

dsu

bseq

uent

,an

dA

irpla

nes

inco

rpo

ratin

gth

efo

llow

ing

Ser

vice

Bul

letin

:S

B60

1R--2

8--0

22.

P9--

Effe

ctiv

ity:

Airp

lane

s70

02,7

076

and

subs

eque

nt,

and

Airp

lane

sin

corp

ora

ting

the

follo

win

gS

ervi

ceB

ulle

tin:

SB

601R

--24

--036

.

C5--

Effe

ctiv

ity:

Airp

lane

s74

52an

dsu

bseq

uent

,C

ircui

tBre

aker

Gua

rdIn

stal

latio

n.E

ffect

ivity

:A

irpla

nes

7676

,768

6,77

84an

d78

07,

inco

rpo

ratin

gth

efo

llow

ing

Cus

tom

erR

eque

st:

CR

601R

--23

--372

.

A13

--

5

SOV

XFE

RFU

EL

RIGHT

CONT

ADGDEPLO

Y

07--40--7Vol. 1




MASTER

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


<0009> -- S 6

<0020> -- R 7

<0035> -- T 2

REV 56, Jan 31/03




Circuit Breaker Panel 2 (Sub---Panel) <7036 & subs, SB601R--24--017>Figure 07---40---4 Sheet 2

Effectivity:Airplanes 7036 and subsequent,incorporating the followingService Bulletin:

SB 601R--24--017.


SPARE FUSES

07--40--9Vol. 1




MASTER

Circuit Breaker Panel 3 <MST>Figure 07---40---5

CIRCUIT BREAKER PANEL 3 <0026> -- C 4

REV 56, Jan 31/03




Circuit Breaker Panel 4 <MST>Figure 07---40---6

CIRCUIT BREAKER PANEL 4

07--40--11Vol. 1




MASTER

Circuit Breaker Panel 5Figure 07---40---7 Sheet 1

CIRCUIT BREAKER PANEL 5(AFT side of JB--5 inAFT Compartment)

A CB--5 B

ADG

28VDCMAIN

BATTERYDIRECTBUS

EICAS

APUBATTERYDIRECTBUS

BATTBUS

MAIN

BATT

CONT

APU

ECU

STBY

PWR

CONT

CLK 1

CLK 2

ENG

IGN B

APU

BATT

CONT

SERV

BUS

FEED

OIL

BYPS

IND

ENG

OIL

PWR

AUTO

MAN

EXT

PWR

ESS

PWR

CONT

EMER

BUS

FEED

1

15

14

13

12

3

11

3

10

9

8

37

5

6

5

4

3

71 2

5

2

1

15

14

3

13

12

3

11

3

10

109

3

8

7

6

5

20

4

20

3

2

71 2

20

DCU

2/3

71 2

FUEL

DEFL

EMRG

REFL

53

REV 56, Jan 31/03




Circuit Breaker Panel 5 <7072, 7068 & subs, SB601R--34--045><7072, 7068, 7295 & subs,SB601R--24--090><7036 & subs, SB601R--24--017>

Figure 07---40---7 Sheet 2

CIRCUIT BREAKER PANEL 5(AFT side of JB--5 inAFT Compartment)

A CB--5 B

ADG

28VDCMAIN

BATTERYDIRECTBUS

EICAS

APUBATTERYDIRECTBUS

BATTBUS

MAIN

BATT

CONT

APU

ECU

STBY

PWR

CONT

ATT

1CLK 1

CLK 2

ENG

IGN B

APU

BATT

CONT

SERV

BUS

FEED

OIL

BYPS

IND

ENG

OIL

PWR

AUTO

MAN

EXT

PWR

ESS

PWR

CONT

HDG

ATT

2HDG

FUEL

DEFL

EMRG

REFL

MAIN

BATT

CHGR

O/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

204

20

3

2

71 2

20

DCU

2/3

71 2

Effectivity:Airplanes 7072, 7068, 7295 andsubsequent, and Airplanes incorporatingthe following Service Bulletin:

SB 601R--24--090.Effectivity:

Airplanes 7036 and subsequent,and Airplanes incorporatingthe following Service Bulletin:

SB 601R--24--017.

SPAREFUSES

B 6, B 7B14, B15 --

Effectivity:Airplanes 7002, 7068 andsubsequent, incorporatingthe following Service Bulletin:

SB 601R--34--045.

A 8, A 9 --

07--40--13Vol. 1




MASTER

Miscellaneous PanelsFigure 07---40---8

Water System Control Panel (1)Galley Area

5 5

15

15 10

Galley System CircuitBreakersUsed to protect ovensand coffee maker.

Water System CircuitBreakersUsed to protect thefollowing:Control logic circuits.Galley and lavatory pumps.Galley and lavatory lineheaters, waste valve, anddrain mast heaters.

REV 56, Jan 31/03




THIS PAGE INTENTIONALLY LEFT BLANK

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