Chapter 6: Electrical TABLE OF CONTENTSmotor dc ext power ac ext power ac power center dc power center electrical control panel lh engine rh engine gen 1 gen 2 4 gcu gcu gcu gcu gen

For Training Purposes OnlySept 04

6-i

P I L O T T R A I N I N G G U I D E

ELECTRICAL

Chapter 6: Electrical

TABLE OF CONTENTS

Page

Introduction .........................................................................................................................6-1Variable Frequency Power Generation System............................................................6-1General .........................................................................................................................6-1

EPGDS Components ..............................................................................................6-3EPGDS Architecture ...............................................................................................6-4

AC System ....................................................................................................................6-5Emergency AC Power...................................................................................................6-6

AC System Distribution ...........................................................................................6-7Electrical Panel .......................................................................................................6-8Electrical Management System...............................................................................6-9AC System EICAS Messages ...............................................................................6-12AC System Synoptic .............................................................................................6-14AC Bus Feed System............................................................................................6-15AC Bus 1 ...............................................................................................................6-16AC Bus 2 ...............................................................................................................6-17AC Bus 3 ...............................................................................................................6-18AC Bus 4 ...............................................................................................................6-19AC ESS Bus..........................................................................................................6-20EXT AC Power ......................................................................................................6-21

DC System..................................................................................................................6-22DC System Distribution .........................................................................................6-23Electrical Panel .....................................................................................................6-24DC System EICAS Messages...............................................................................6-25DC System Synoptic .............................................................................................6-27DC Bus Feed System............................................................................................6-28DC Bus 1...............................................................................................................6-29DC ESS Bus..........................................................................................................6-30BATT Bus..............................................................................................................6-31DC Bus 2...............................................................................................................6-32External DC Power................................................................................................6-33RAT GEN Feed .....................................................................................................6-34Emergency DC Power...........................................................................................6-35DC Power Emergency Override............................................................................6-36EICAS Philosophy.................................................................................................6-37

EMS Circuit Protection ................................................................................................6-38Cockpit Circuit Breaker Panel (CCBP)..................................................................6-38EMS CDU..............................................................................................................6-39SYSTEM Key ........................................................................................................6-39ELEC SYSTEM Key..............................................................................................6-40BUS Key................................................................................................................6-41AC Bus 2 ...............................................................................................................6-42AC Bus 3 ...............................................................................................................6-43

6-ii For Training Purposes OnlySept 04


ELECTRICAL

AC Bus 4 ............................................................................................................... 6-44AC ESS Bus.......................................................................................................... 6-45DC EMER Bus ...................................................................................................... 6-46DC Bus 1............................................................................................................... 6-47DC Bus 2............................................................................................................... 6-54DC ESS Bus.......................................................................................................... 6-61BATT Bus.............................................................................................................. 6-67AV BATT Bus ........................................................................................................ 6-74APU BATT Bus ..................................................................................................... 6-75CNTL Key.............................................................................................................. 6-76TEST Key.............................................................................................................. 6-77Fire Test ................................................................................................................ 6-78Stall Test ............................................................................................................... 6-79Aural Warning Test ............................................................................................... 6-80Lamp Test ............................................................................................................. 6-81EMER CNTL ......................................................................................................... 6-82

System Integration ............................................................................................................ 6-83


6-1


ELECTRICAL

INTRODUCTION

VARIABLE FREQUENCY POWER GENERATION SYSTEMThe Global Express utilizes an AC power generation system based on Variable Frequency Generators (VFG). The use of variable frequency power engenders several advantages including:

• An increased efficiency of 80% compared with fixed frequency systems where efficiency is in the order of 65%

• Ease of voltage conversion• Reduction in system weight due to lighter alternator and distribution cables; and• Increased reliability due in large part to the eradication of Integrated Drive

Generators (IDGs)

GENERALThe airplane AC electrical power generation and distribution system (EPGDS) consists of four 40 kVA, engine-driven, variable frequency generators (VFG), and one constant frequency 40 kVA APU generator. Control and protection of the generators is provided by five identical generator control units (GCU). Distribution systems furnish power to the following buses, through the AC power center (ACPC) and the cockpit circuit breaker panel (CCBP).

• AC bus 1, 2, 3, 4 (ACPC)• AC bus 1A, 2A, 3A, essential (CCBP)

A ram air turbine (RAT), deployable during flight, supplies 115-volt, 400-Hz, 3-phase AC power 9 kVA for emergency use (when all other AC sources have been lost) to supply AC power to the AC essential bus. Mounted on the RAT is a hydraulic pump which powers hydraulic system No. 3.

For other load devices requiring DC power, 115-volt AC power is converted to 28-volt DC power by four 150 Amp transformer-rectifier units (TRU). 28-volt DC power is distributed through the DC power center (DCPC) and the secondary power distribution assemblies (SPDA) onto the following buses:

• DC bus 1 and 2• DC essential bus• Battery bus• DC emergency bus

The 25-ampere-hour, 24-volt DC avionics battery provides power to the following:

• Stored energy to selected electronic equipment during normal ground operations• During flight in an emergency (loss of all generators) to the flight essential DC

loads

6-2 For Training Purposes OnlySept 04


ELECTRICAL

The 42 ampere-hour, 25.2 volt DC APU battery provides power to the following:

• Stored energy for starting the APU during both ground and flight operations• During flight in an emergency (loss of all generators) to the flight essential DC

loads

The following buses are connected directly to their respective battery terminals:

• Avionics battery direct bus• APU battery direct bus

Battery chargers and battery heaters, powered by the main AC buses, maintain the main and APU batteries in a charged and warm condition.

An Electrical Control Panel, located in the cockpit, provides control of all generators, external AC and DC power and battery master.

An Electrical Management System (EMS), located in the cockpit, controls and displays the status of circuit breaker, on the two control display units (CDU).

External AC power, supplied through the AC receptacle, situated on the aft left side of the airplane, (on the fairing at the root of the wing trailing edge), provides power to:

• AC bus 1, 2, 3, 4• AC 1A, 2A, 3A and essential bus

External DC power, supplied through the DC receptacle, situated on the aft underside of the fuselage, provides power to the APU battery direct bus.

The APU can be started using external DC power, however, a serviceable avionics battery is required.

The airplane batteries cannot be charged through external DC power, since the APU BATT charger and the avionics BATT charger are powered by AC bus 2 and 3 respectively.


6-3


ELECTRICAL

EPGDS COMPONENTS

GX

_0

6_

00

1

TRUs

AvionicsBattery

APU Batteryand Battery

Charger

APUGenerator

APU StartContactorAssembly

DC PowerReceptacle

DC PowerCenter

AC PowerCenter

AC PowerReceptacle

Cockpit CircuitBreaker Panel

SecondaryPower Distribution

Assemblies

GeneratorControlUnits

ControlDisplayUnits

LH EngineVF Generators

RH EngineVF Generators

Ram AirTurbine

ControlPanel External

ServicePanelBattery

Charger



ELECTRICAL

EPGDS ARCHITECTURE

TRU 1 ESSTRU 1

ESSTRU 2

TRU 2

APUSTARTMOTOR

DC EXTPOWER

AC EXTPOWER

AC POWER CENTER

DC POWER CENTER

ELECTRICALCONTROL

PANEL

LH Engine RH Engine

GEN1

GEN2

GEN4

GEN GENGCU GCU GCU GCU GCU GCURAT

115/200 V, 3 PHASE, 324-596 Hz

28 V, DC

CONTROL, PROTECTION, COMMUNICATIONS

APU

GX

_0

6_

00

2

EXT PWRCONTROL

PANEL

SPDA 1 SPDA 2 SPDA 3 SPDA 4

AVIONICSBATTERY

AVIONICSBATTERYCHARGER

APUBATTERYCHARGER

GEN3

COCKPIT CIRCUIT BREAKER PANEL

APUBATTERY

APUSTART CONTROL

ASSEMBLY (ASCA)

EMSCDU 1

EMSCDU 2


6-5


ELECTRICAL

AC SYSTEMAC power is normally supplied by four variable frequency generators (VFG), two on each engine, rated at 115 volt, 40 kVA, 3-phase, 324-596 Hz output.

The generators are brushless, oil cooled and are a three stage machine type generator. The first machine is a permanent magnet generator (PMG), generator excitation function, which provides output power. The second machine, is the main exciter which receives its field excitation through the generator control unit (GCU).The GCU will remove the generator from its bus and de-energize the generator, in the event of malfunction. The third machine, is the main alternator, which incorporates current transformers that are used for feeder fault and overcurrent protection.

All VFG output is routed through the AC power center (ACPC), which protects, controls and distributes primary AC power to the main airplane buses. VFG output is then routed through the CCBP to bus feeders 1A, 2A and 3A and the AC ESS BUS for power distribution to the 4 transformer rectifier units (TRU). Each generator normally powers its own bus, through a generator line contactor (GLC). In the event of a generator malfunction, the generator transfer contactors (GTC), will automatically switch to an alternate generator, to supply the affected bus. AC bus 2 and 3 are automatically shed during single generator operations and AC bus 1 and 4 are priority.

AC power can also be supplied by the auxiliary power unit (APU) generator. The APU constant frequency generator, rated at 115 volt, 40 kVA, 3-phase, 400 Hz output.

External AC power, 115 volt, 3-phase, can also be used to supply power to the AC system.

BATTERYMASTER

GROUNDSERVICE

EXT AC EXT DC

BATTON

ONAVAIL

IN USE

AVAIL

IN USE

MIC HDPHLAMPTEST

APUSHUT-OFF

GX

_06_003

External AC/DC Power StatusIndicatorsDisplays status of external AC orDC power.

Ground Service Mode SwitchEnables maintenance personnel to power selected ACloads in the cabin, when AC external power is available.

Battery Master Status IndicatorDisplays status of the battery masterswitch (EMS or ON position).

External AC PowerReceptacle



ELECTRICAL

EMERGENCY AC POWEREmergency AC power is supplied by the ram air turbine (RAT) in flight, rated at 115 volts, 9 kVA, 3-phase. With engines running, the RAT will deploy with a 14-second time delay following the loss of all AC power, if the slat/flap handle is at the in/zero position. It will deploy automatically if the slat/flap handle is not at the in/zero position. With a dual-engine failure, the RAT will deploy automatically, regardless of slat/flap handle position. The RAT can also be manually deployed by pulling RAT manual deploy handle, located on the center pedestal. Once deployed, the RAT will power the AC ESS BUS via the ram air turbine line contactor (RATLC).

The RAT also incorporates a hydraulic pump, which powers hydraulic system No. 3. At approximately 147 KIAS and below, the RAT sheds its electrical output, giving priority to hydraulics. A ground safety pin is installed in the nosewheel well area to secure the RAT in position while on ground.

RATManual DeployHandle

GX

_0

6_

00

4

GX

_06_005

DeploymentActuator

RetractionPump

Uplock

Ram AirTurbine

Hydraulic Pump

Generator

GroundSafetyPin

DownlockRelease


6-7


ELECTRICAL

AC SYSTEM DISTRIBUTION

GX

_0

6_

00

6

GEN 1

GEN 2

GEN 3

GEN 4

GTC 9

GTC 8

GTC 10 GTC 2

GTC 12

GTC 11

GTC 1GTC 7

K2

K3

K4

K6

EPLC APULC

K1 K8

K11

GLC 1 GLC 2

GLC 3

GLC 4

GTC 5 GTC 4

GTC 6 GTC 3

K5 K7

K10

K9

K13

K12

K14

K15

K17

K20

K18

K21

K22

K24

K16

K19

K23

K25

K26

CBA14

CBA20

CBB7

CBA8

CBA2

CBA1

RATLCK3

ACMP3B

CABINFEEDS

C/BLOADS

C/BLOADS

APU BATTCHGR

APUBATTHTR

SSPCLOADS

SSPCLOADS

SSPCLOADS

SSPCLOADSCABIN

FEEDS

CABINFEEDS

CABINFEEDSACMP

2BC/B

LOADSC/B

LOADSACMP1B

ACMP3A

AC BUS 1

AC BUS 1A

AC BUS 2

AC BUS 2A

AC BUS 3

AC BUS 3A

AC BUS 4

CCBP

ACPC

GEN 1 GEN 3GEN 2 GEN 4

EXTAC

APUGEN

ENG 2ENG 1

RATGEN

EXT AC

APU GEN

RAT GEN

AC ESS BUS



ELECTRICAL

ELECTRICAL PANELThe generators and external power can be controlled manually, by selecting the appropriate switch on the electrical panel, located on the overhead panel. GEN 1, 2, 3, 4 and APU GEN switches are normally ON.

NOTEIf RAT GEN is powering AC ESS BUS, and a main generator is available, stow the RAT deploy handle and select RAT GEN to OFF, to transfer AC ESS BUS to the main generator. The RAT GEN will remain armed to ensure RAT GEN priority in the event of loss of all main generators.

ELECTRICALEXT AC

AVAIL

ON

FAIL

OFF

GEN 1

FAIL

OFF

EXT DC

AVAIL

ON

GEN 3 GEN 4

FAIL

OFF

GEN 2

FAIL

OFF

PUSH OFF/RESET

PUSHOFF/RESET

APU GEN

FAIL

OFF

RAT GEN

ON

OFF

BATT MASTER

EMS

OFF

ON

ASTE

E

OF

External AC Switch

AVAIL Light

ON Light

Displays status of AC external power• - Comes on to indicate thatexternal AC power is connected and is thecorrect phase, voltage and frequency.• - Indicates that external poweris being used or can be used by theairplane power distribution system tomaintain power to the AC buses.

GEN 1, 2, 3, 4 Switches

FAIL Light

OFF Light

Used to reset or to turnapplicable generator off.• - Indicates a failedgenerating channel (GEN, GCU,GLC) / FAIL Light illuminateswhen fire discharge handle ispulled.• - Indicatesgenerator operation inhibited.

RAT GEN Switch

ON Light

OFF Light

Used to reset a fault or to turn RATgenerator off.• - Indicates that RATgenerator is on line.• - Indicates that RATgenerator operation is inhibited.

APU GEN Switch

FAIL LightOFF Light

Used to reset or to turn APU generator off.• - Indicates a failed generating channel.• - Indicates generator operationinhibited.

GX

_0

6_

00

7


6-9


ELECTRICAL

ELECTRICAL MANAGEMENT SYSTEMLoad control consists of smart contactors, Solid State Power Controllers (SSPC) and control logic. Smart contactors and SSPC are functionally similar to a switch in series with a circuit breaker. The status of all circuit breakers is monitored (trips are automatically displayed) and can be acknowledged and reset via the Electrical Management System (EMS). EMS Control Display Units (CDU) are installed on the pilot’s and copilot’s side panel.

M

M

STANDBY

BRT

CIRCUIT BREAKER SYSTEM

STAT SYS BUSPREVPAGE

NEXTPAGE

CNTL TEST

BUS

EMERCONT

LINE SELECT KeysUsed to selectdisplayed items.

Page TitleDisplayed when aselection has beenmade using pageselect key.

Page NumberDisplays which page isselected and how many pagesare available.

Activation KeysUsed to switchcurrent status andselect display items.

STATUS KeyDisplays the statusof tripped, out andlocked circuitbreakers. System Key

Displays circuitbreaker status byaircraft system.

BUS KeyDisplays circuitbreaker status byelectrical buses.

PREVIOUS PAGEKeyScrolls list toprevious page.

NEXT PAGE keyScrolls list to nextpage.

TEST KeyDisplays system'stest options.

CNTL KeyDisplays system'scontrol options. EMER CONT

KeyDisplays busisolation status.

NOTE:If no action is taken within 45to 60 secs of page activation orselection, the display will revertback to STBY page.

GX

_0

6_

00

8

BRIGHTNESSControl

CIRCUIT BREAKER - SYSTEM

DOORS

ELECAIR COND/PRESS

AFCS

ENGINE

FIRE

FLT CONTROLS

APU

BLEED

CAIMS

COMM FUEL

1/2



ELECTRICAL

The circuit breaker STATUS page will automatically appear, anytime a circuit breaker trips, if the screen is blank and has been blank for 2 seconds, (CB TRIP message appears on EICAS) or can be selected using STAT page select key.

M

CIRCUIT BREAKER - STATUS 1/1

STAB TRIM 1

STAB TRIM 2

FUEL COMPUTR CH B

DU 1

RAD ALT 1

AC1

AC ESS

DC ESS

DC ESS

DC 1

LOCKED

OUT

OUT

LOCKED

TRIP

ACPC

CCBP

M

BRT



NEXTPAGE

CNTL TEST

BUS

EMERCONT


STAB TRIM 1

STAB TRIM 2

FUEL COMPUTR CH B

DU 1

RAD ALT 1

AC1

AC ESS

DC ESS

DC ESS

DC 1

LOCKED

OUT

OUT

LOCKED

TRIP

ACPC

CCBP

GX

_0

6_

00

9

FUEL COMP BCircuit breakeridentification

DC 1BUS location ofaffected circuitbreaker.

ACPCThermal circuit breakerlocated on the component withinACPC.

LOCKEDCircuit breaker hasbeen locked bymaintenance personnel.

OUTCircuit breaker hasbeen selected out.

TRIPCircuit breakerhas tripped.

CCBPThermal circuit breakerlocated on Cockpit CircuitBreaker Panel.

NOTE: Thermal circuit breakers cannot be reset via the EMS CDU.


6-11


ELECTRICAL

Circuit breakers can be acknowledged, or acknowledged and reset, using the line select keys.

BRT



NEXTPAGE

CNTL TEST

BUS

EMERCONT


STAB TRIM 1

FUEL COMPUTR CH B

DU 1

RAD ALT 1

STAB TRIM 2

AC1

DC ESS

DC ESS

DC 1

AC ESS

LOCKED

IN

LOCKED

TRIP

OUT

ACPC

CCBP

THERM CB CAN’T BE CHANGED FROM CDU

M

BRT



NEXTPAGE

CNTL TEST

BUS

EMERCONT


STAB TRIM 1

STAB TRIM 2

DU 1

RAD ALT 1

FUEL COMPUTR CH B

AC1

AC ESS

DC ESS

DC 1

DC ESS

LOCKED

OUT

LOCKED

TRIP

OUT

ACPC

CCBP

M

BRT



NEXTPAGE

CNTL TEST

BUS

EMERCONT


STAB TRIM 1

STAB TRIM 2

DU 1

RAD ALT 1

FUEL COMPUTR CH B

AC1

AC ESS

DC ESS

DC 1

DC ESS

LOCKED

OUT

LOCKED

TRIP

OUT

ACPC

CCBP

NOTE: (OUT IN)Affected circuit breaker font sizeis reduced when reset. The resetcircuit breaker will automaticallybe removed from STATUS pagelist, after successful reset and anew page is selected.message goes out.

CB TRIP

THERM CB CAN’T BE CHANGED FROM CDU

NOTE:Will appear if an attempt to resetis carried out on a thermal circuitbreaker. A thermal breakercannot be reset using EMS CDU.The affected circuit breaker canonly be manually reset at itslocation.

Most recent tripped circuit breakerwill automatically highlight.To select another circuit breaker,use the line select key, thisacknowledges and highlightsthe displayed breaker.Once acknowledged or reset,the message goes out.CB TRIP

Select activation key adjacenthighlighted circuit breaker.

GX

_0

6_

01

0

ACPC

CCBP

M


STAB TRIM 1

STAB TRIM 2

FUEL COMPUTR CH B

DU 1

RAD ALT 1

AC1

AC ESS

DC ESS

DC ESS

DC 1

LOCKED

OUT

IN

LOCKED

TRIP



ELECTRICAL

AC SYSTEM EICAS MESSAGES

1 . 65

789

EMER PWR ONLYIndicates that RAT ispowering AC ESS BUS,or batteries arefeeding DC ESS andbattery buses inemergency condition.

APU GEN OVLDIndicates an overloadon the APU generator.

CB TRIP AC FEEDIndicates that a circuitbreaker for an ACfeeder/AC cabin feederhas tripped.

GEN 1 (2,3,4) OVLDIndicates an overloadon affected generatorchannel.

RAT GEN FAIL(on ground only)Indicates that a fault hasbeen detected in the RATgenerator system duringbuilt-in test (BIT).

AC BUS 1 (2, 3, 4) FAILIndicates that affected busis not powered, or hasa fault.

AC ESS BUS FAILIndicates that AC ESSis not powered orhas a fault.

APU GEN OVERHEATIndicates that the APUgenerator oil hasoverheated.

CB TRIP DC FEEDIndicates that a circuitbreaker for a DC feeder/DC cabin feeder has tripped.

GX

_0

6_

011

EMER PWR ONLYAC BUS 1 FAILAC BUS 2 FAILAC BUS 3 FAILAC BUS 4 FAILAC ESS BUS FAILAPU GEN OVERHEATAPU GEN OVLDCB TRIP AC FEEDCB TRIP DC FEEDELEC SYS FAILGEN 1 OVLDGEN 2 OVLDGEN 3 OVLDGEN 4 OVLDRAT GEN FAIL

ELEC SYS FAILCAIMS level A fault.Prevents A/C dispatch untilfixed.


6-13


ELECTRICAL

AC SYSTEM EICAS MESSAGES

789

1 . 65

AC BUS 1 (2,3,4) XFER FAULTIndicates that transfer ofalternate power supply toaffected AC bus is lost.

CB TRIPIndicates that a circuitbreaker has tripped.

APU GEN FAILIndicates that APUGEN has failed.

RAT GEN ONIndicates that the RAT ispowering AC ESS BUSand is the only gen online

AC BUS 1 (2,3,4) MAN OFFIndicates that the affected bushas been manually isolated. All4 buses cannot be manuallyisolated concurrently.

RAT GEN OFFIndicates that the RAT isdeployed and the RAT lineconnector is selected off.

ELEC SYS FAULTIndicates loss ofredundancy on EGPDSlogic. CAIMS level Cfault. Fault must be fixedwithin 10 days.

EXT AC PWR AVAILIndicates that externalpower is available.

GEN 1 (2,3,4) FAILIndicates a GCU fault inthe applicable generator.

APU GEN OFFIndicates thatAPU GEN is selected off.

EXT AC PWR ONIndicates that externalAC power has beenselected on.

GEN 1 (2,3,4) OFFIndicates that affectedgenerator is selected off.

GX

_0

6_

01

2

AC BUS1 XFER FAULTAC BUS2 XFER FAULTAC BUS3 XFER FAULTAC BUS4 XFER FAULTAPU GEN FAILELEC SYS FAULTEXT AC PWR AVAILCB TRIPGEN 1 FAILGEN 2 FAILGEN 3 FAILGEN 4 FAILRAT GEN ONAC BUS 1 MAN OFFAC BUS 2 MAN OFFAC BUS 3 MAN OFFAC BUS 4 MAN OFFAPU GEN OFFEXT AC PWR ONGEN 1 OFFGEN 2 OFFGEN 3 OFFGEN 4 OFFRAT GEN OFF



ELECTRICAL

AC SYSTEM SYNOPTICElectrical system warnings, cautions advisories and status messages are presented on the EICAS primary display. General views of airplane electrical systems (either AC or DC) are presented through synoptic diagrams on the EICAS secondary display (after selecting the appropriate key on the EICAS control panel).

STAT

HYDAC

ELECBLEED

AIRCOND

DCELEC

FUELFLT

CTRL

SCROLL

EICAS

SYSTEMS SELECT

NORMMFD 2MFD 1

AC ELECTRICAL

000

V

KVA

HZ

GEN

APU

AC BUS 1

11515

V

KVA

AC BUS 2

11512

V

KVA

GEN2

GEN1

AC ESS BUS

AC BUS 4

AC BUS 3

11512

V

KVA

11515

V

KVA

GEN3

GEN4

GX

_0

6_

01

3

EICAS Control Panel

Generator VoltageReadoutDisplays, in VAC, thegenerator voltage level.• Green - 100 - 125VAC

• Amber - GCU fault• White - GEN off• Magenta - Invaliddata.

Generator LoadReadoutDisplays, in KVA, theload on the generator.

APU Generator Frequency ReadoutDisplays, in Hz, the generator frequencylevel.

Generator OutputFlow Line (Lower)• Green - Generatoris on.

• Blank - Generatoris off.

Generator OutputFlow Line (Upper)• Green - Generatorline contactor atgenerator position.• Blank - Generatorline contactor at tieposition.


6-15


ELECTRICAL

The AC electrical page contains digital readouts of generator output voltage, frequency (APU only), load in kVA, input/output flow on the bus bars, general status indications via color logic and the following messages:

• SHED message - Corresponding AC bus has been shed

• AC BUS 1, 2, 3, 4 MAN OFF icon - Corresponding AC bus is isolatedAC BUS 1, 2, 3, 4 MAN OFF status message displayed on EICAS

AC BUS FEED SYSTEMEach AC bus is normally powered by its own generator through generator line contactors. In the event of a generator malfunction, the priority system will automatically provide an alternate generator (feed), to power that bus (APU must be started to be available to the feed system), through generator transfer contactors.

The AC buses are normally powered by their own generator, but can be powered by alternate generators in the following descending order:

• AC BUS 1 - GEN 1, GEN 4, GEN 3, GEN 2, APU GEN • AC BUS 2 - GEN 2, GEN 3, GEN 4, APU GEN• AC BUS 3 - GEN 3, GEN 2, GEN 1, APU GEN• AC BUS 4 - GEN 4, GEN 1, GEN 2, GEN 3, APU GEN• AC ESS BUS - RAT generator (if deployed), GEN 4, GEN 1, GEN 2, GEN 3,

APU GEN. Normal power for AC ESS BUS is generator 4. When the RAT is deployed and RAT generator is ON, the AC ESS Bus is fed directly from the RAT generator

AC buses 2 and 3 are automatically load shed when a single generator is powering the buses.

External AC power will power all AC buses when selected ON and interacts with other generator power as per APU.

The AC bus feed is displayed on the AC ELECTRICAL synoptic page as follows:

GX

_0

6_

01

4AC BUS 2 AC BUS 3

SHED SHED

GX

_0

6_

01

5

AC BUS 1 MAN OFFAC BUS 2 MAN OFFAC BUS 3 MAN OFFAC BUS 4 MAN OFF

AC BUS 1

MAN OFF

Note:A maximum of 3 busses onlycan be manually isolatedconcurrently.



ELECTRICAL

AC BUS 1

AC ELECTRICAL

0HZ

AC ELECTRICAL

000

V

KVA

HZ

GEN

APU

00

V

KVA

AC BUS 2

11512

V

KVA

GEN2

GEN1

AC BUS 3

11512

V

KVA

GEN3

AC BUS 1

AC ESS BUS

AC BUS 4

11524

V

KVA

GEN4

AC ELECTRICAL

000

V

KVA

HZ

GEN

APU

AC BUS 1

11512

V

KVA

AC BUS 2

11512

V

KVA

GEN2

GEN1

AC ESS BUS

AC BUS 4

AC BUS 3

11512

V

KVA

11515

V

KVA

GEN3

GEN4

APU

GEN1

GEN4

GEN3

GEN2

GEN

GEN 1 GEN 4

GEN 3

APUGEN

GEN 2

AC BUS 1 -Normally powered by GEN 1, alternately powered by the following, in descending priority:

GX

_0

6_

01

6

PRIORITY

AC ELECTRICAL

000

VKVA

HZ

GEN

APU

AC BUS 1

00

VKVA

AC BUS 2

115VKVA

GEN2

GEN1

AC ESS BUS

AC BUS 4

AC BUS 3

00

VKVA

00

VKVA

GEN3

GEN4

SHED SHED

AC ELECTRICAL

V

KVA

0000

V

KVA

GEN3

GEN4

00

V

KVA

00

V

KVA

11524

V

KVA

00

V

KVA

11524

V

KVA

AC BUS 2

AC ESS BUS

AC BUS 4

AC BUS 3

AC BUS 1

GEN

APU

GEN2

GEN1

GEN4

GEN3

00

V

KVA

V

KVA

GEN2

GEN1

11524

11528

400

V

KVA

HZ

GEN

APU

AC BUS 2 AC BUS 3

AC BUS 1

AC ESS BUS

AC BUS 4


6-17


ELECTRICAL

AC BUS 2

AC ELECTRICAL

AC BUS 1

11524

V

KVA

00

V

KVA

GEN2

GEN1

AC ESS BUS

AC BUS 4

00

V

KVA

GEN4

AC BUS 2 AC BUS 3

11528

400

V

KVA

HZ

GEN

APU

00

V

KVA

GEN3

AC ELECTRICAL

AC BUS 2

AC ESS BUS

AC BUS 4

AC BUS 3

AC ELECTRICAL

AC BUS 1

11512

V

KVA

00

V

KVA

GEN2

GEN1

AC ESS BUS

AC BUS 4

11524

V

KVA

GEN4

AC BUS 2 AC BUS 3

000

V

KVA

HZ

GEN

APU

11512

V

KVA

GEN3

AC ELECTRICAL

000

VKVA

HZ

GEN

APU

AC BUS 1

11512

VKVA

AC BUS 2

11512

VKVA

GEN2

GEN1

AC ESS BUS

AC BUS 4

AC BUS 3

11512

VKVA

11515

VKVA

GEN3

GEN4

APU

GEN2

GEN3

GEN4

GEN

GEN 2 GEN 3

GEN 4 APUGEN

AC BUS 2

GX

_0

6_

01

7

-Normally powered by GEN 2, alternately powered by the following, in descending priority:

PRIORITY

000

V

KVA

HZ

GEN

APU

00

V

KVA

GEN2

11524

V

KVA

GEN4

00

V

KVA

GEN3

11524

V

KVA

GEN1

AC BUS 1



ELECTRICAL

AC BUS 3

AC ELECTRICALAC ELECTRICAL

AC ELECTRICAL

000

V

KVA

HZ

GEN

APU

AC BUS 1

11512

V

KVA

GEN1

AC ESS BUS

AC BUS 4

11524

V

KVA

GEN4

00

V

KVA

GEN3

AC ELECTRICAL

000

V

KVA

HZ

GEN

APU

AC BUS 1

11512

V

KVA

AC BUS 2

11512

V

KVA

GEN2

GEN1

AC ESS BUS

AC BUS 4

AC BUS 3

11512

V

KVA

11515

V

KVA

GEN3

GEN4

APU

GEN3

GEN2

GEN1

GEN

GEN 3 GEN 2

GEN 1 APUGEN

AC BUS 3

GX

_0

6_

01

8


PRIORITY

AC BUS 2 AC BUS 3

11512

V

KVA

GEN2

00

V

KVA

00

V

KVA

GEN2

GEN1

11524

V

KVA

GEN4

11528

400

V

KVA

HZ

GEN

APU

00

V

KVA

GEN3

000

VKVA

HZ

GEN

APU

00

VKVA

GEN2

11524

VKVA

GEN4

00

VKVA

GEN3

11524

VKVA

GEN1

AC BUS 2

AC ESS BUS

AC BUS 4

AC BUS 3

AC BUS 1 AC BUS 1

AC ESS BUS

AC BUS 4

AC BUS 2 AC BUS 3


6-19


ELECTRICAL

AC BUS 4

AC ELECTRICAL

AC ELECTRICAL

AC ELECTRICAL

AC BUS 2

AC BUS 2

AC BUS 3

AC BUS 3

SHED

SHED

SHED

SHED

AC ELECTRICAL

000

V

KVA

HZ

GEN

APU

AC BUS 2

11512

V

KVA

GEN2

00

V

KVA

GEN4

AC BUS 3

11512

V

KVA

GEN3

AC ELECTRICAL

000

V

KVA

HZ

GEN

APU

AC BUS 2

11512

V

KVA

GEN2

AC BUS 3

11512

V

KVA

GEN3

AC BUS 1

AC ESS BUS

AC BUS 4

00

V

KVA

GEN4

V

KVA

GEN1

11512

APU

GEN4

GEN1

GEN2

GEN3

GEN

GEN 4 GEN 1

GEN 2 GEN 3

APU GEN

AC BUS 4

GX

_0

6_

01

9


PRIORITY

0

0

0

0

V

V

KVA

KVA

V

V

KVA

KVA

GEN2

GEN2

GEN1

GEN1

115

0

32

0

400

0

V

V

KVA

KVA

HZ

HZ

GEN

GEN

APU

APU

V

V

KVA

KVA

0

0

0

115

0

0

0

32

V

V

KVA

KVA

GEN3

GEN3

GEN4

GEN4

0

0

0

0

AC BUS 1

AC BUS 1

AC ESS BUS

AC ESS BUS

AC BUS 4

AC BUS 4

AC ESS BUS

AC BUS 4AC BUS 1

11524

V

KVA

GEN1

AC BUS 2 AC BUS 3

AC BUS 1

AC ESS BUS

AC BUS 4

000

VKVA

HZ

GEN

APU

00

VKVA

11524

VKVA

GEN2

GEN1

11524

VKVA

00

VKVA

GEN3

GEN4



ELECTRICAL

AC ESS BUS

AC ELECTRICAL

00

V

KVA

AC BUS 2

V

KVA

GEN2

GEN1

AC BUS 3

SHED SHED

AC BUS 1

AC ESS BUS

AC BUS 4

11532

400

V

KVA

HZ

GEN

APU

V

KVA

0000

V

KVA

GEN3

GEN4

00

AC ELECTRICAL

000

V

KVA

HZ

GEN

APU

00

V

KVA

AC BUS 2

00

V

KVA

GEN2

GEN1

AC BUS 3

SHED SHED

AC BUS 1

AC ESS BUS

AC BUS 4

11532

V

KVA

00

V

KVA

GEN3

GEN4

AC ELECTRICAL

000

V

KVA

HZ

GEN

APU

00

V

KVA

11524

V

KVA

GEN2

GEN1

AC ESS BUS

AC BUS 4

00

V

KVA

GEN4

11524

V

KVA

GEN3

AC BUS 1

AC ELECTRICAL

000

V

KVA

HZ

GEN

APU

AC BUS 2

11512

V

KVA

GEN2

11512

V

KVA

GEN3

AC BUS 1

AC ESS BUS

AC BUS 4

00

V

KVA

GEN4

V

KVA

GEN1

11512

AC ELECTRICAL

000

V

KVA

HZ

GEN

APU

AC BUS 1

11515

V

KVA

AC BUS 2

11512

V

KVA

GEN2

GEN1

AC ESS BUS

AC BUS 4

AC BUS 3

11512

V

KVA

11515

V

KVA

GEN3

GEN4

AC ELECTRICAL

000

VKVA

HZ

GEN

APU

AC BUS 1

00

VKVA

AC BUS 2

VKVA

GEN2

GEN1

AC ESS BUS

AC BUS 4

AC BUS 3

VKVA

VKVA

GEN3

GEN4

0 0 00 0 0

115400

V

HZGENRAT

RAT GEN GEN 4

GEN 1 GEN 2

APUGEN

GEN 3

AC ESS BUS

GX

_0

6_

02

0

APU

GEN

GEN

RAT

GEN4

GEN1

GEN3

GEN2

NOTE: The RAT GEN has priority, only if it has been deployed and RAT GEN ON


AC BUS 3 AC BUS 2 AC BUS 3

PRIORITY

ON

OFF

RAT GEN


6-21


ELECTRICAL

EXT AC POWER

AC ELECTRICAL

EXTAC

1150

400

V

KVA

HZ

AC ELECTRICAL

GEN

APU

00

V

KVA

00

V

KVA

GEN2

GEN1

00

V

KVA

00

V

KVA

GEN3

GEN4

EXTAC

11523

400

V

KVA

HZ

EXTAC

1150

400

V

KVA

HZ

EXTAC

1150

400

V

KVA

HZ

• - Comes on to indicate thatexternal AC power is connected and is thecorrect phase, voltage and frequency.• - Indicates that external poweris being used or can be used by theairplane power distribution system tomaintain power to the AC buses.

AVAIL Light

ON LIGHT

NOTE:The ON light will remain illuminated, evenwhen another source(s) is powering ACbuses, to indicate that the priority systemcan call upon EXT AC if needed.

GX

_0

6_

02

1

EXTAC

11528

400

V

KVA

HZ

00

V

KVA

00

V

KVA

GEN2

GEN1

GEN

APU

00

V

KVA

00

V

KVA

GEN3

GEN4

AC BUS 1

AC BUS 2

AC ESS BUS

AC BUS 4

AC BUS 3

AC ESS BUS

AC BUS 4

AC BUS 3

AC BUS 1

AC BUS 2

11523

400

V

KVA

HZ

000

V

KVA

HZ

AVAIL

ON

EXT AC

AVAIL

ON

EXT AC

AVAIL

ON

EXT AC



ELECTRICAL

DC SYSTEMThere are six primary DC power sources: four identical transformer rectifier units (TRU), an Avionics battery and an APU battery. All sources are routed through the DC power center (DCPC).

The six primary sources are monitored, switched, distributed and controlled by the DCPC. The DCPC reconfigures the buses automatically in the event of a TRU failure.

Four main DC buses provide DC power to the secondary airplane loads. Each TRU normally powers a bus, through a TRU line contactor (TLC). In the event of a TRU malfunction, the TRU transfer contactors (TTC), will automatically switch to an alternate TRU, to supply the affected bus. DC bus 1 and 2 are automatically shed during single TRU operations.

The avionics battery direct bus and DC emergency bus power is distributed to their secondary loads, through circuit breakers.

Two nickel cadmium batteries are installed in the airplane. Both batteries are used together in an emergency to provide DC power for a minimum of 15 minutes.

Each battery has a separate dedicated battery charger, to maintain that battery in a fully charged condition. The battery charger provides protection against battery overtemperature, defective or unbalanced cell, open/short battery temperature sense thermistor, open/short battery voltage sense lines and charger overtemperature. The charger will shut itself off and annunciate, when it senses a battery fault or charger fault.

External DC power is supplied to the airplane via DC external power receptacle. The APU start contactor assembly (ASCA) checks the power being delivered from the power unit, before connecting it to the airplane buses.

GX

_0

6_

02

2

External DC PowerReceptacle


6-23


ELECTRICAL

DC SYSTEM DISTRIBUTION

GX

_0

6_

02

3

ACBUS2A

ACBUS1A

ACESSBUS

DC BUS 1 DC BUS 2

TLC 1

TTC 2

TLC 3 TTC 4TTC 1

TLC 2

TTC 3 TLC 4

ETCK5

TRU 1ESS TRU 1

ESS TRU 1ESS TRU 2TRU 2TRU 1

ESS TRU 2ESS TRU 1TRU 2TRU 1

TRU 2ESS TRU 2

APU BATTDIRECT BUS

EXTDC

EXTPWR

EPC

AVIONICS BATTDIRECT BUS

EBBC 1K6

SSPC 4K10

SSPC 5K3 (ASCA)

SSPC 1K7

SSPC 2K8

SSPC 3K9

ETTC

TRU 1

ESS TRU 1

ESS TRU 2

TRU 2

AVIONICS BATT

APU BATT

EXT DC

AVIONICSBATTERY

APUBATTERY

ACBUS3A

K1

K1

K2

K3 K4

ESSTRU 2

TRU 2ESS

TRU 1TRU 1

CCBP

DCPC

ASCA

CR 1

CR 4

CR 6 CR 7

CR 5

CR 2 CR 3

CBC6

CBC4

DC ESS BUS BATT BUS

DCEMERGENCY

BUS



ELECTRICAL

ELECTRICAL PANELExternal DC power is controlled manually. Battery master must be selected ON for all phases of flight.

ELECTRICALEXT AC

AVAIL

ON

FAIL

OFF

GEN 1

FAIL

OFF

EXT DC

AVAIL

ON

GEN 3 GEN 4

FAIL

OFF

GEN 2

FAIL

OFF

PUSH OFF/RESET

PUSHOFF/RESET

APU GEN

FAIL

OFF

RAT GEN

ON

OFF

BATT MASTER

EMS

OFF

ON

ASTE

E

OF

BATT MASTER Switch

OFF

EMS

ON

Used to control battery power.• - Isolates the battery busfrom the batteries.• - Electrical ManagementSystem is in maintenancemode. Batteries supply power toEMS only.• - Battery bus is poweredby battery (only if no AC poweron the airplane)

External DC Switch

AVAIL Light

ON Light

Displays status of DC external power:• - Comes on to indicatethat external DC power is connected andis operating limits.• - Indicates external DCpower is powering APU BATT DIR BUS.

within

GX

_0

6_

02

4


6-25


ELECTRICAL

DC SYSTEM EICAS MESSAGES

BATT MASTER OFFIndicates that thebattery switch is off.

BATT BUS FAILIndicates that batterybus is not powered,due to a fault.

DC EMER BUS FAILIndicates that DCEMER BUS is notpowered due to a fault.

APU (AV) BATT FAILIndicates that APU (AV)battery has failed, voltageor temperature is out ofrange.

DC BUS 1 (2) FAILIndicates that affectedDC bus is not powereddue to a fault or is shed.

DC ESS BUS FAILIndicates that DC ESS BUSis not powered, due to afault.

GX

_0

6_

02

5

789

1 . 65

APU BATT FAILAV BATT FAILBATT MASTER OFFBATT BUS FAILDC BUS 1 FAILDC BUS 2 FAILDC ESS BUS FAILDC EMER BUS FAIL



ELECTRICAL

DC SYSTEM EICAS MESSAGES

789

1 . 65

GX

_0

6_

02

6

DC BUS 1(2) XFER FAULTDC ESS BUS XFER FAULTBATT BUS XFER FAULTIndicates that transfer ofalternate power supply toaffected bus is lost.

EXT DC PWR AVAILIndicates that externalDC power is available.

BATT EMER PWR ONIndicates that the batteriesare feeding the DC ESSBUS and BATT buses inan emergency condition.

BATT BUS MAN OFFDC BUS 1 (2) MAN OFFDC ESS BUS MAN OFFIndicates that affectedDC bus has beenmanually isolated.

APU (AV) BATT CHGR FAILIndicates that affected batterycharger has detected a faultand has shut down.

TRU 1 (2) FAIL orESS TRU 1 (2) FAILIndicates that affectedTRU has failed.

EXT DC PWR ONIndicates that externalDC power has beenselected on.

APU BATT CHGR FAILAV BATT CHGR FAILDC BUS1 XFER FAULTDC BUS2 XFER FAULTDC ESS XFER FAULTBATT BUS XFER FAULTEXT DC PWR AVAILBATT EMER PWR ONTRU 1 FAILTRU 2 FAILESS TRU 1 FAILESS TRU 2 FAILBATT BUS MAN OFFDC BUS 1 MAN OFFDC BUS 2 MAN OFFDC ESS BUS MAN OFFEXT DC PWR ON


6-27


ELECTRICAL

DC SYSTEM SYNOPTIC

The DC electrical page contains digital readouts of TRU and battery output (voltage and ampere output), input/output flow on the bus bars, generated status information via color logic and the following messages:

• CHARGER message (adjacent to APU BATT symbol) - APU battery is not charging. Corresponds to APU BATT CHGR FAIL advisory message

• CHARGER message (adjacent to AV BATT symbol) - Main airplane battery is not charging. AV BATT CHGR FAIL advisory message displayed on EICAS

• SHED message - Corresponding DC bus has been shed• MAN OFF message - Corresponding DC bus is isolated. DC BUS 1, (2) MAN

OFF, DC ESS MAN OFF and/or BATT BUS MAN OFF status message displayed on EICAS

DCELEC

STAT

HYDAC

ELECBLEED

AIRCOND

DCELEC

FUELFLT

CTRL

SCROLL

EICAS

SYSTEMS SELECT

NORMMFD 2MFD 1

DC ELECTRICAL

AC BUS 2FEEDER

DC BUS 1

26V 24V0A 0A

-10°C

AC BUS 1FEEDER

DC ESS BUS

ESSTRU 1

28V35A

AC ESSBUS

BATT BUS

DC EMERBUS

AV BATTDIR BUS

AVBATT

20°C

APUBATT

APU BATTDIR BUS

ESSTRU 2

28V35A

AC BUS 3FEEDER

DC BUS 2

TRU 2

28V35A

TRU 1

28V35A

EICAS Control Panel

GX

_0

6_

02

7



ELECTRICAL

DC BUS FEED SYSTEMEach DC bus is normally powered by its respective TRU. Each TRU is normally powered by its own AC BUS FEEDER (ESS TRU 2 is powered by AC ESS BUS). In the event of a TRU malfunction, the priority system will automatically provide an alternate TRU feed to power the respective DC bus. As soon as one TRU fails, the emergency tie contactor (ETC) closes to allow power distribution.

ESS TRU 2 can be powered (through the AC ESS BUS) when the RAT is deployed and RAT generator is selected ON.

The DC buses are powered by the TRUs in the following descending order:

• DC BUS 1 - TRU 1, ESS TRU 1• DC ESS BUS - ESS TRU 1, ESS TRU 2, TRU 2, TRU 1• BATT BUS - ESS TRU 2, ESS TRU 1, TRU 2, TRU 1• DC BUS 2 - TRU 2, ESS TRU 2

DC BUS 1 and DC BUS 2 are automatically load shed when a single TRU is powering the buses. External DC power will power the APU BATT DIR BUS and consequently, the BATT BUS and the DC EMER BUS. External DC power is normally used by maintenance personnel or to start the APU in the event of a low APU BATT voltage. Note that a serviceable avionics battery is required to start the APU in this way.

The DC bus feed is displayed on the DC ELECTRICAL synoptic page as follows:

APU BATT CHGR FAILAV BATT CHGR FAILDC BUS 1 MAN OFFDC BUS 2 MAN OFFDC ESS MAN OFFBATT BUS MAN OFF

-10°C

AVBATT

20°C

APUBATTCHARGER CHARGER

DC BUS 2

SHED

DC BUS 1

MAN OFF

GX

_0

6_

02

8


6-29


ELECTRICAL

DC BUS 1

DC ELECTRICAL

AC BUS 2FEEDER

26V 24V0A 0A

-10°C

AC BUS 1FEEDER

AC ESSBUS

BATT BUS

DC EMERBUS

AV BATTDIR BUS

AVBATT

20°C

APUBATT

APU BATTDIR BUS

ESSTRU 2

AC BUS 3FEEDER

DC BUS 2

TRU 2

2835

V

A

2835

V

A

GX

_0

6_

02

9

DC BUS 1

DC ELECTRICAL

AC BUS 2FEEDER

DC BUS 1

26V 24V0A 0A

-10°C

AC BUS 1FEEDER

DC ESS BUS

ESSTRU 1

28V35A

AC ESSBUS

BATT BUS

DC EMERBUS

AV BATTDIR BUS

AVBATT

20°C

APUBATT

APU BATTDIR BUS

ESSTRU 2

28V35A

AC BUS 3FEEDER

DC BUS 2

TRU 2

28V35A

TRU 1

28V35A

TRU 1

2835

V

A

ESSTRU 12835

V

A

TRU 1

ESS TRU 1

-Normally powered by TRU 1, alternately powered by the following, in descending order:

ESSTRU 1

TRU 1

00

V

A

2845

V

A

DC ESS BUS

DC BUS 1



ELECTRICAL

DC ESS BUS

DC ELECTRICAL

AC BUS 2FEEDER

DC BUS 1

26V 24V0A 0A

-10°C

AC BUS 1FEEDER

DC ESS BUS

ESSTRU 1

AC ESSBUS

BATT BUS

DC EMERBUS

AV BATTDIR BUS

AVBATT

20°C

APUBATT

APU BATTDIR BUS

ESSTRU 2

AC BUS 3FEEDER

DC BUS 2

TRU 2TRU 1

2875

V

A

00

V

A

00

V

A

00

V

A

SHEDSHED

DC ELECTRICAL

AC BUS 2FEEDER

DC BUS 1

26V 24V0A 0A

-10°C

AC BUS 1FEEDER

DC ESS BUS

ESSTRU 1

AC ESSBUS

BATT BUS

DC EMERBUS

AV BATTDIR BUS

AVBATT

20°C

APUBATT

APU BATTDIR BUS

ESSTRU 2

AC BUS 3FEEDER

DC BUS 2

TRU 2TRU 1

2835

V

A

2854

V

A

00

V

A

00

V

A

SHED

DC ELECTRICAL

AC BUS 2FEEDER

DC BUS 1

26V 24V0A 0A

-10°C

AC BUS 1FEEDER

DC ESS BUS

ESSTRU 1

AC ESSBUS

BATT BUS

DC EMERBUS

AV BATTDIR BUS

AVBATT

20°C

APUBATT

APU BATTDIR BUS

ESSTRU 2

AC BUS 3FEEDER

DC BUS 2

TRU 2TRU 1

2835

V

A

2835

V

A

2845

V

A

00

V

A

DC ELECTRICAL

AC BUS 2FEEDER

DC BUS 1

26V 24V0A 0A

-10°C

AC BUS 1FEEDER

DC ESS BUS

ESSTRU 1

28V35A

AC ESSBUS

BATT BUS

DC EMERBUS

AV BATTDIR BUS

AVBATT

20°C

APUBATT

APU BATTDIR BUS

ESSTRU 2

28V35A

AC BUS 3FEEDER

DC BUS 2

TRU 2

28V35A

TRU 1

28V35A

ESSTRU 1

ESSTRU 2

TRU 2 TRU 1

GX

_0

6_

03

0

DC ESS BUS

ESSTRU 12835

V

A

TRU 2

2835

V

A

ESSTRU 22835

V

A

TRU 1

2835

V

A

-Normally powered by ESS TRU 1, alternately powered by the following, in descending order:


6-31


ELECTRICAL

BATT BUS

DC ELECTRICAL

AC BUS 2FEEDER

DC BUS 1

26V 24V0A 0A

-10°C

AC BUS 1FEEDER

DC ESS BUS

ESSTRU 1

AC ESSBUS

BATT BUS

DC EMERBUS

AV BATTDIR BUS

AVBATT

20°C

APUBATT

APU BATTDIR BUS

ESSTRU 2

AC BUS 3FEEDER

DC BUS 2

TRU 2TRU 1

2875

V

A

00

V

A

00

V

A

00

V

A

SHEDSHED

DC ELECTRICAL

AC BUS 2FEEDER

DC BUS 1

26V 24V0A 0A

-10°C

AC BUS 1FEEDER

DC ESS BUS

ESSTRU 1

AC ESSBUS

BATT BUS

DC EMERBUS

AV BATTDIR BUS

AVBATT

20°C

APUBATT

APU BATTDIR BUS

ESSTRU 2

AC BUS 3FEEDER

DC BUS 2

TRU 2TRU 1

2835

V

A

2854

V

A

00

V

A

00

V

A

SHED

DC ELECTRICAL

AC BUS 2FEEDER

DC BUS 1

26V 24V0A 0A

-10°C

AC BUS 1FEEDER

DC ESS BUS

ESSTRU 1

AC ESSBUS

BATT BUS

DC EMERBUS

AV BATTDIR BUS

AVBATT

20°C

APUBATT

APU BATTDIR BUS

ESSTRU 2

AC BUS 3FEEDER

DC BUS 2

TRU 2TRU 1

2835

V

A

2835

V

A

00

V

A

2842

V

A

DC ELECTRICAL

AC BUS 2FEEDER

DC BUS 1

26V 24V0A 0A

-10°C

AC BUS 1FEEDER

DC ESS BUS

ESSTRU 1

28V35A

AC ESSBUS

BATT BUS

DC EMERBUS

AV BATTDIR BUS

AVBATT

20°C

APUBATT

APU BATTDIR BUS

ESSTRU 2

28V35A

AC BUS 3FEEDER

DC BUS 2

TRU 2

28V35A

TRU 1

28V35A

ESSTRU 2

ESSTRU 1

TRU 2 TRU 1

GX

_0

6_

03

1

BATT BUS

ESSTRU 22835

V

A

TRU 2

2835

V

A

ESSTRU 12835

V

A

TRU 1

2835

V

A

-Normally powered by ESS TRU 2, alternately powered by the following, in descending order:



ELECTRICAL

DC BUS 2

DC ELECTRICAL

AC BUS 2FEEDER

DC BUS 1

26V 24V0A 0A

-10°C

AC BUS 1FEEDER

DC ESS BUS

ESSTRU 1

AC ESSBUS

BATT BUS

DC EMERBUS

AV BATTDIR BUS

AVBATT

20°C

APUBATT

APU BATTDIR BUS

ESSTRU 2

AC BUS 3FEEDER

DC BUS 2

TRU 2TRU 1

2835

V

A

00

V

A

2345

V

A

2842

V

A

DC ELECTRICAL

AC BUS 2FEEDER

DC BUS 1

26V 24V0A 0A

-10°C

AC BUS 1FEEDER

DC ESS BUS

ESSTRU 1

28V35A

AC ESSBUS

BATT BUS

DC EMERBUS

AV BATTDIR BUS

AVBATT

20°C

APUBATT

APU BATTDIR BUS

ESSTRU 2

28V35A

AC BUS 3FEEDER

DC BUS 2

TRU 2

28V35A

TRU 1

28V35A

GX

_0

6_

03

2

DC BUS 2

TRU 2

2835

V

A

ESSTRU 22835

V

A

TRU 2

ESS TRU 2

-Normally powered by TRU 2, alternately powered by the following, in descending order:


6-33


ELECTRICAL

EXTERNAL DC POWER

EXT DC

AVAIL

ON

EXT DC

AVAIL

ON

GX

_0

6_

03

3

APUBATT20°C

EXTDC

24

APUBATT20°C

0V

AEXTDC

AVAIL LightIndicates that external DC poweris connected (not on-line) and iswithin limits.

ON LightIndicates external DC power ispowering APU BATT DIR BUS.

DC ELECTRICAL

AC BUS 2FEEDER

DC BUS 1

26V 24V0A 0A

-10°C

AC BUS 1FEEDER

DC ESS BUS

ESSTRU 1

AC ESSBUS

DC EMERBUS

AVBATT

20°C

APUBATT

ESSTRU 2

AC BUS 3FEEDER

DC BUS 2

TRU 2TRU 1

00

V

A

00

V

A

00

V

A

00

V

A

EXTDC

2410

V

A

AV BATTDIR BUS

BATT BUS

APU BATTDIR BUS

CHARGER CHARGER



ELECTRICAL

RAT GEN FEEDEmergency AC power is supplied by the ram air turbine (RAT) in flight, rated at 115 volts, 9 kVA, 3-phase. With engines running, the RAT will deploy with a 14-second time delay following the loss of all AC power, if the slat/flap handle is at the in/zero position. It will deploy automatically if the slat/flap handle is not at the in/zero position. With a dual-engine failure, the RAT will deploy automatically, regardless of slat/flap handle position. The RAT can also be manually deployed by pulling RAT manual deploy handle, located on the center pedestal. Once deployed, the RAT will power the AC ESS BUS via the ram air turbine line contactor (RATLC).

This delay is implemented to allow the pilot to regain GEN 1-2-3 or 4, or APU GEN power.

NOTEThe AC ESS BUS will power ESS TRU 2 which will then feed the BATT BUS and the DC ESS BUS through the emergency tie contactor (ETC). Should ESS TRU 2 be unavailable, the emergency TRU tie contactor (ETTC) will close rerouting the power via ESS TRU 1.

In the event that an operating generator is restored, select the RAT GEN switch to OFF. The RAT GEN will remain in a standby mode.

RAT GEN

ON

OFF

AC ELECTRICAL

000

V

KVA

HZ

GEN

APU

AC BUS 1

00

V

KVA

AC BUS 2

V

KVA

GEN2

GEN1

AC ESS BUS

AC BUS 4

AC BUS 3

V

KVA

V

KVA

GEN3

GEN4

0 0 00 0 0

115400

V

HZGENRAT

DC ELECTRICAL

AC BUS 2FEEDER

DC BUS 1

-10°C

AC BUS 1FEEDER

DC ESS BUS

ESSTRU 1

AC ESSBUS

BATT BUS

DC EMERBUS

AV BATTDIR BUS

AVBATT

20°C

APUBATT

APU BATTDIR BUS

ESSTRU 2

AC BUS 3FEEDER

DC BUS 2

TRU 2TRU 1

00

V

A

260

240

V

A

V

A

00

V

A

2875

V

A

00

V

A

RAT GEN

GX

_0

6_

03

4

CHARGER CHARGER


6-35


ELECTRICAL

EMERGENCY DC POWERIn the event of loss of all AC power, or the airplane speed is 147 knots or less with the RAT deployed, a BATTERY EMER PWR ON EICAS message will be displayed. If the RAT is deployed and speed is less than 147 knots, the RAT GCU will automatically shed RAT electrical output, giving priority to hydraulics.

DC ELECTRICAL

AC BUS 2FEEDER

DC BUS 1

-10°C

AC BUS 1FEEDER

DC ESS BUS

ESSTRU 1

AC ESSBUS

BATT BUS

DC EMERBUS

AV BATTDIR BUS

AVBATT CHARGER CHARGER

20°C

APUBATT

APU BATTDIR BUS

ESSTRU 2

AC BUS 3FEEDER

DC BUS 2

TRU 2TRU 1

00

V

A

2624

2424

V

A

V

A

00

V

A

00

V

A

00

V

A

AC ELECTRICAL

000

V

KVA

HZ

GEN

APU

AC BUS 1

00

V

KVA

AC BUS 2

V

KVA

GEN2

GEN1

AC ESS BUS

AC BUS 4

AC BUS 3

V

KVA

V

KVA

GEN3

GEN4

0 0 00 0 0

0400

V

HZGENRAT

GX

_0

6_

03

5

147

180

170

160

150

140

130

120

1478

6

NOTE:Battery emergency power is available for a minimum of 15 minutes.

BATTERY EMER PWR ON



ELECTRICAL

DC POWER EMERGENCY OVERRIDEIn the event of loss of all DC power, selecting the DC POWER EMERGENCY OVERRIDE switch (located on the pedestal) to OVERRIDE, will allow ESS TRU 1 and 2 to bypass the DCPC and power the SPDAs directly. All components normally powered by the DC ESS BUS and the BATT BUS will be powered directly from the ESS TRUs.

ELECT DC PWREMER OVRD

OVRD

NORM

20

10

30

20

10

30

09

8

7

65

4

3

2

1100 FEET

ALT

1 00032

4

10 13

mb/hPa

29 9 2

IN HG

IAS KNOTS

220200180 250

BARO

Honeywell HoneywellHoneywell Honeywell

WX

ET

NO BEARINGRA 9 . 8NM +13TA 4 . 5NM -04

SAT

GSPD

TERR

-56

TAT

TAS

-40

234

345

INHIB

LX

00 : 10 0 . 05L

MAG2HDG315

ETE 1+36

12 . 5KDVT

NM

FLBELOW

TCAS TEST

FMS1360

N

5 5

3

6

33

30

- 02

- 02

+ 12- 04

KABC

KKLM

KKLM

TOC

TOC

KGHJ

KGHJ

LUF

KDEF

KDEF

4000 4000

FL180

+ 09

TOTAL FUEL (LBS) 25750

1.021.02

25.425.4

443443

12950 1280000

NDSTAB

NU

RUDDERNL

LWD RWD

NR

AIL

– TRIMS –

6.0

N2

FF (PPH)

OIL TEMP

OIL PRESS

61.4690

7551

61.4690

8049

1 . 641 . 64

98.5 98.5

T/OEPR

N1

ITT

GEAR

PARK/EMER BRAKE ONNO TAKEOFF

IGN

START START

IGN

IN

0

DN DN DN

END

Honeywell

13000.00

00

90

13 13

2019 20

22 2220

OXYGEN

AFTCABIN (°C)

FWDCABIN (°C)

CKPT (°C)

OPEN OPEN

OUTFLOW VALVES

CAB ALT

P

CAB RATE

LDG ELEV

00

1 2

1 2

1 2

QTY

ENG

APU

RES

OIL (QTS)

APU DOOR 11.2°

RPM EGT

BRAKE TEMP

11.5

650100

0603 03 03

11.55.26.0

%

% %

Honeywell

9500

29.92

AT1

VTA

M

0.450M

FMS1LOC1DTK

360

HDG330

10400

20

20

10

10

20

20

10

10

9500

10500

300

220

210

200

190

180

170

F3

LE

F1

2160

150

1856

4

N33

30

W24

21S

15

12

E6

3

0

1

2

3

1

2

3

ATT

HDGT

EICAS

GS

LOC

HDG

RAD

IASALT

HDG2

VOR 1

ADF 2

0010020

80

THRUST HDG ASEL ATT 2AP1VAPP VNAV ADC 3

GX

_0

6_

03

6

DC POWER EMERGENCY OVERRIDE Switch

OVERRIDE

NORMAL

Used in the event of a total loss of DC powercontrol, to connect ESS TRU 1 and ESS TRU 2directly to the SPDAs to power the componentsnormally powered by the BATT BUS and DCESS BUS.

– SPDAs normally powered by theBATT BUS and DC ESS BUS are powereddirectly by the ESS TRU 1 and ESS TRU 2.

BATT BUS and DC ESS BUS arepowered by TRUs.

–

20

10

30

20

10

30

09

8

7

65

4

3

2

1100 FEET

ALT

1 00032

4

10 13

mb/hPa

29 9 2

IN HG

IAS KNOTS

220200180 250

BARO

Honeywell HoneywellHoneywell Honeywell HoneywellHoneywell

ELECT DC PWREMER OVRD

OVRD

NORM


6-37


ELECTRICAL

EICAS PHILOSOPHYThe following represents the EICAS symbols and logic for the AC and DC synoptic pages. The symbols are shown in serviceable SHED, MAN OFF and failure conditions.

GX

_0

6_

03

7

ELECTRICAL SYSTEM LOGIC

BUS

TRUs

BATTERIES

POWEREDMAN OFF or

SHED FAILED INVALID

GEN

ENGINE

APU

RAT

OPERATINGNOT

OPERATING FAILED INVALID

RAT GEN GEN GEN GENRAT RAT RAT

EXT AC

EXT DC

ON FAILEDAVAILABLE INVALID

EXTAC

11528

400

VKVAHZ

EXTDC

240

VA

EXTAC

EXTDC

1150

400

2412

VKVAHZ

VA

EXTAC

EXTDC

000

2412

VKVAHZ

VA

EXTAC

EXTDC

000

2412

VKVAHZ

VA



ELECTRICAL

EMS CIRCUIT PROTECTION

COCKPIT CIRCUIT BREAKER PANEL (CCBP)

GX

_0

6_

03

8

69

14

13

12

11

10

87

54

32

1

ES

ST

RU

1A

LT

SL

AT

/F

LA

PP

WR

2

STA

BT

RIM

CH

2

ES

ST

RU

2

AC

ES

SB

US

20

15

15

15

69

14

13

12

11

10

87

54

32

1

ST

BY

PIT

OT

HT

R

AC

BU

S4

MO

NIT

OR

RA

TV

/FM

ON

ITO

R

TAT

HT

1L

AO

AH

TR

PIT

OT

1H

TB

PIT

OT

3H

TL

ICE

DE

TE

CT

OR

RA

OA

HE

AT

B

TAT

HT

2

LW

IND

OW

HE

AT

2.5

57

.57

.55

2.5

7.5

57

.51

57

.5

E F

69

13

12

11

10

87

54

32

1

LW

SH

LD

HT

R1

LW

SH

LD

HT

R2

SA

TC

OM

FR

EQ

UN

IT

RA

OA

HT

RA

RIC

ED

ET

EC

TP

ITO

T1

HT

AA

/TC

TL

RAC

BU

S1

2.5

7.5

2.5

7.5

20

20

5

69

13

12

11

10

87

54

32

1

SL

AT

/F

LA

PP

WR

1

TR

UB

AY

FAN

ES

ST

RU

1

15

20

2.5

G H

AV

BA

TT

RC

CB

AP

UB

AT

TR

CC

B

AV

BA

TT

HE

AT

TAT

HT

3

RW

SH

LD

HE

AT

1

RW

SH

LD

HE

AT

2

TR

U2

AV

BA

TT

CH

GR

PIT

OT

2H

T

RW

IND

OW

HE

AT

TR

U1

6

6 6

6

8 8

81

097 7

7

5

5 5

5

4

4 4

4

3

3 3

3

2

2 2

2

1

1 1

1

AC

BU

S2

AC

BU

S3

DC

15

7.5

15

15

7.5

20

20

5.5

5

ST

BY

AD

I

2.5

.5

A B C D


6-39


ELECTRICAL

EMS CDUThe EMS CDU keys are used to access the following:

SYSTEM KEYThe SYSTEM key is used to access status and location of applicable system circuit breakers and to reset page from 1 to 2.

MM

CIRCUIT BREAKER - SYSTEM 2/2

HYD

ICE

IND/RECORD

LDG GEAR

LIGHTS

NAV

OIL

OXYGEN

THRUST REV


AFCS

AIR COND/PRESS

APU

BLEED

CAIMS

COMM

DOORS

ELEC

ENGINE

FIRE

FLT CONTROLS

FUEL

NEXTPAGE

PREVPAGE

M

BRT



NEXTPAGE

CNTL TEST

BUS

EMERCONT

GX

_0

6_

03

9


AFCS

AIR COND/PRESS

APU

BLEED

CAIMS

COMM

DOORS

ELEC

ENGINE

FIRE

FLT CONTROLS

FUEL

PREVIOUS PAGE key usedto return to previous page.

NEXT PAGE key usedto scroll to next page.



ELECTRICAL

ELEC SYSTEM KEY

M M M

MMM

MMM

MMM

M

BRT



NEXTPAGE

CNTL TEST

BUS

EMERCONT

GX

_0

6_

04

0

CB - ELEC SYSTEM 1/12

AC 1 CABIN FEED

AC 2 CABIN FEED

AC 3 CABIN FEED

AC 4 CABIN FEED

AC BUS 1 FEED

AC BUS 2 FEED

AC 1

AC 2

AC 3

AC 4

AC 1

AC 2

ACPC

ACPC

ACPC

ACPC

IN

IN

IN

IN

IN

IN


BATT BUS FEED 1

BATT BUS FEED 2

FEED 3

BATT BUS FEED 4

DC1 CABIN FEED

DC2 CABIN FEED1

BATT BUS

BATT

BATT

BATT

BATT

DC 1

DC 2

IN

IN

IN

IN

IN

IN


EMS CDU 1 PWR B

EMS CDU 1/2 PWR C

EMS CDU 2 PWR A

EMS CDU 2 PWR B

ESS TRU 1 ALT

ESS TRU 1

BATT

EXT AC

BATT

AC 1

AC ESS

APU BATT

IN

IN

IN

IN

IN

IN

ACPC

ASCA

CCBP

CCBP


AC BUS 3 FEED

AC BUS 4 FEED

AC BUS 4 MONITOR

ACPC CTL PWR A

ACPC CTL PWR B

ACPC CTL PWR C

AC 3

AC 4

AC 4

BATT

DC ESS

DC 1

IN

IN

IN

IN

IN

IN

CCBP


DC 2 CABIN FEED 2

DC 2 CABIN FEED 3

DC BUS 1 FEED 1

DC BUS 1 FEED 2

DC BUS 1 FEED 3

DC BUS 1 FEED 4

DC 2

DC 2

DC 1

DC 1

DC 1

DC 1

IN

IN

IN

IN

IN

IN


ESS TRU 2

EXT AC INTERLOCK

EXT AC PBA LTS

GCU 1

GCU 2

GCU 3

AC ESS

EXT AC

EXT AC

BATT

BATT

BATT

IN

IN

IN

IN

IN

IN


ACPC CTL PWR D

APU BATT CHGR

APU BATT CHGR LD

APU BATT HEAT

APU BATT MSTR

APU BATT RCCB

APU BATT

AC 2

APU BATT

AC 4

APU BATT

APU BATT

IN

IN

IN

IN

IN

IN

ASCA

ACPC

ASCA

ACPC

ASCA

CCBP


DC BUS 2 FEED 1

DC BUS 2 FEED 2

DC BUS 2 FEED 3

DC BUS 2 FEED 4

DC EMER FEED 1

DC EMER FEED 2

DC 2

DC 2

DC 2

DC 2

AV BATT

BATT

IN

IN

IN

IN

IN

IN


GCU 4

RAT DEPLOY

RAT GCU TEST

RAT GEN HEATER

RAT U/H MONITOR

TRU 1

BATT

BATT

DC 1

DC 1

AC ESS

AC 2

IN

IN

IN

IN

IN

IN

CCBP

CCBP


TRU 2 AC 3 INCCBP


APU GCU

AV BATT CHGR

AV BATT CHGR LD

AV BATT HEAT

AV BATT MSTR

AV BATT RCCB

BATT

AC3

AV BATT

AC3

AV BATT

AV BATT

IN

IN

IN

IN

IN

IN

CCBP

DCPC

CCBP

DCPC

CCBP


DC ESS BUS FEED 1

DC ESS BUS FEED 2

DC ESS BUS FEED 3

DC ESS BUS FEED 4

DCPC EXT CTL PWR

EMS CDU 1 PWR A

DC ESS

DC ESS

DC ESS

DC ESS

EXT AC

AV BATT

IN

IN

IN

IN

IN

IN

ACPC

DCPC

DCPC

DCPC

CCBP

ACPC

ACPC


AFCS

AIR COND/PRESS

APU

BLEED

CAIMS

COMM

DOORS

ELEC

ENGINE

FIRE

FLT CONTROLS

FUEL


6-41


ELECTRICAL

BUS KEYThe BUS key is used to display circuit breaker status and location by individual buses.

MM

MM

M

BRT



NEXTPAGE

CNTL TEST

BUS

EMERCONT

M

BRT



NEXTPAGE

CNTL TEST

BUS

EMERCONT

GX

_0

6_

04

1CB - AC BUS 1 1/4

A/T CTLR

AC 1 CABIN FEED

AC BUS 1 FEED

ESS TRU 1

HYD PUMP 3B

L AFT PRI PUMP

IN

IN

IN

IN

IN

IN

CCBP

ACPC

CCBP

CB - AC BUS 1 3/4

PITOT 1 HT A

R AOA HEAT A

R ICE DETECTOR

SAT COM FREQ UNIT

SLAT/FLAP PWR 1

STAB TRIM CH 1

IN

IN

IN

IN

IN

IN

CCBP

CCBP

CCBP

CCBP

CCBP

ACPC

CB - AC BUS 1 2/4

L CTR XFER PUMP

L RECIRC FAN

L TAXI LT

L WING LDG LT

L WSHLD HEAT 1

L WSHLD HEAT 2

IN

IN

IN

IN

IN

IN

CCBP

CCBP

CB - AC BUS 1 4/4

TRU BAY FAN INCCBP

AC BUS 1

1/2CIRCUIT BREAKER - SYSTEM

AFCS

AIR COND/PRESS

APU

BLEED

CAIMS

COMM

DOORS

ELEC

ENGINE

FIRE

FLT CONTROLS

FUEL

CIRCUIT BREAKER - BUS 1/1

AC 1

AC 2

AC 3

AC 4

AC ESS

DC EMER

DC 1

DC 2

DC ESS

BATT

AV BATT

APU BATT



ELECTRICAL

AC BUS 2

M

M

M

BRT



NEXTPAGE

CNTL TEST

BUS

EMERCONT

GX

_0

6_

04

2

CB - AC BUS 2 1/2

AC 2 CABIN FEED

AC BUS 2 FEED

AFT TANK L PUMP

APU BATT CHGR

HYD PUMP 2B

L FWD PRI PUMP

IN

IN

IN

IN

IN

IN

ACPC

ACPC


AC 1

AC 2

AC 3

AC 4

AC ESS

DC EMER

DC 1

DC 2

DC ESS

BATT

AV BATT

APU BATT

CB - AC BUS 2 2/2

PITOT 2 HT

R WINDOW HEAT

SATCOM AMP

TRU 1

IN

IN

IN

IN

CCBP

CCBP

ACPC

CCBP

M

M

CB - AC BUS 2 1/2

AC 2 CABIN FEED

AC BUS 2 FEED

AFT TANK L PUMP

APU BATT CHGR

HYD PUMP 2B

L FWD PRI PUMP

IN

IN

LOCKED

IN

IN

IN

ACPC

ACPC

CB - AC BUS 2 2/2

PITOT 2 HT

R WINDOW HEAT

SATCOM AMP

TRU 1

IN

IN

IN

IN

CCBP

CCBP

ACPC

CCBP

GLOBAL EXPRESS GLOBAL 5000


6-43


ELECTRICAL

AC BUS 3

MM

M M


M

BRT



NEXTPAGE

CNTL TEST

BUS

EMERCONT

GX

_0

6_

04

3

CB - AC BUS 3 1/2

AC 3 CABIN FEED

AC BUS 3 FEED

AFT TANK R PUMP

AV BATT CHGR

AV BATT HEAT

HYD PUMP 1B

IN

IN

IN

IN

IN

IN

ACPC

CCBP

CCBP


AC 1

AC 2

AC 3

AC 4

AC ESS

DC EMER

DC 1

DC 2

DC ESS

BATT

AV BATT

APU BATT

CB - AC BUS 3 2/2

R FWD PRI PUMP

R WSHLD HEAT 1

R WSHLD HEAT 2

TAT HT 3

TRU 2

IN

IN

IN

IN

IN

CCBP

CCBP

CCBP

CCBP

CB - AC BUS 3 1/2

AC 3 CABIN FEED

AC BUS 3 FEED

AFT TANK R PUMP

AV BATT CHGR

AV BATT HEAT

HYD PUMP 1B

IN

IN

LOCKED

IN

IN

IN

ACPC

CCBP

CCBP

CB - AC BUS 3 2/2

R FWD PRI PUMP

R WSHLD HEAT 1

R WSHLD HEAT 2

TAT HT 3

TRU 2

IN

IN

IN

IN

IN

CCBP

CCBP

CCBP

CCBP



ELECTRICAL

AC BUS 4

M

M

M

BRT



NEXTPAGE

CNTL TEST

BUS

EMERCONT

GX

_0

6_

04

4

CB - AC BUS 4 1/2

AC 4 CABIN FEED

AC BUS 4 FEED

AC BUS 4 MONITOR

APU BATT HEAT

APU OIL HEAT

AVIONICS FAN

IN

IN

IN

IN

IN

IN

ACPC

CCBP

ACPC

CB - AC BUS 4 2/2

HYD PUMP 3A

R AFT PRI PUMP

R CTR XFER PUMP

R RECIRC FAN

R TAXI LT

R WING LDG LT

IN

IN

IN

IN

IN

IN

1/1

DC 1

DC 2

DC ESS

BATT

AV BATT

APU BATT

AC 1

AC 2

AC 3

AC 4

AC ESS

DC EMER

CIRCUIT BREAKER - BUS


6-45


ELECTRICAL

AC ESS BUS

M

M

M

M

BRT



NEXTPAGE

CNTL TEST

BUS

EMERCONT

GX

_0

6_

04

5

CB - AC ESS BUS 1/3

ESS TRU 1 ALT

ESS TRU 2

L AOA HEAT

L ICE DETECTOR

L WINDOW HEAT

PITOT 1 HT B

IN

IN

IN

IN

IN

IN

CCBP

CCBP

CCBP

CCBP

CCBP

CCBP

CB - AC ESS BUS

CB - AC ESS BUS

2/3

3/3

PITOT 3 HT

R AOA HEAT B

RAT V/F MONITOR

SLAT/FLAP PWR 2

STAB TRIM CH 2

STBY PITOT HT

TAT HT 1

TAT HT 2

IN

IN

CCBP

CCBP

CCBP

CCBP

CCBP

CCBP

CCBP

CCBP

IN

IN

IN

IN

IN

IN

AC 1

AC 2

AC 3

AC 4

AC ESS

DC EMER


DC 1

DC 2

DC ESS

BATT

AV BATT

APU BATT



ELECTRICAL

DC EMER BUS

M

M

M

BRT



NEXTPAGE

CNTL TEST

BUS

EMERCONT

GX

_0

6_

04

6

CB - DC EMER BUS 1/2

APU FIRE SOV

FIREX CH A

FIREX CH B

L ENG FUEL SOV

L HYD SOV

R ENG FUEL SOV

IN

IN

IN

IN

IN

IN

DCPC

DCPC

DCPC

DCPC

DCPC

DCPC


AC 1

AC 2

AC 3

AC 4

AC ESS

DC EMER

DC 1

DC 2

DC ESS

BATT

AV BATT

APU BATT

CB - DC EMER BUS 2/2

R HYD SOV INDCPC


6-47


ELECTRICAL

DC BUS 1

MM

M

M

BRT



NEXTPAGE

CNTL TEST

BUS

EMERCONT

M

BRT



NEXTPAGE

CNTL TEST

BUS

EMERCONT

GX

_0

6_

04

7

CB - DC BUS 1, SPDA1 1/3

A/T SERVOS

CKPT PRINTER

CLOCK 2

DU 3 PWR B

FMS 3 CDU

L FOOTWARMER

IN

IN

IN

IN

IN

IN

CB - DC BUS 1, SPDA 1 3/3

RAT GCU TEST

WX RADAR

WX RADAR CTLR 1

WX RADAR CTLR 2

RAT GEN HEATER

IN

IN

IN

IN

IN


L NOSE LDG LT

NOSE STEER PWR 1

OVHD 2 INTG LTS

PBA BRT/DIM 1B

PBA BRT/DIM 3B

R WINDOW HEAT CTL

IN

IN

IN

IN

IN

IN


AC 1

AC 2

AC 3

AC 4

AC ESS

DC EMER

DC 1

DC 2

DC ESS

BATT

AV BATT

APU BATT

SPDA1 FEED

SPDA2 FEED

SPDA3 FEED

SPDA4 FEED

CABIN FEED

ALL




ELECTRICAL

DC BUS 1 (Cont)

M

M

M

M

M

M

M

BRT



NEXTPAGE

CNTL TEST

BUS

EMERCONT

GX

_0

6_

04

8


ADF 1

AFT TANK L SOV C

AFT TANK L SOV O

AIRFONE REPEATER

AP 1 SERVOS

BRAKE CTL CH A

IN

IN

IN

IN

IN

IN

CB - DC BUS 1, SPDA2

CB - DC BUS 1, SPDA 2

2/3

3/3

CAB TEMP SENSOR

FLT CTL 1 CH A

IRS 3 PWR A

L BMC CH A

L ECS PRESS XDCR

L FRTT

L PACK CTLR CH A

P FEEL/RUD LIM 1

R PACK DUCT HEAT

RAD ALT 1

YD HEAT 1

IN

IN

IN

IN

IN

IN

IN

IN

IN

IN

IN

SPDA1 FEED

SPDA2 FEED

SPDA3 FEED

SPDA4 FEED

CABIN FEED

ALL

1/1DC BUS 1 FEEDERS



ADF 1

AFT TANK L SOV C

AFT TANK L SOV O

AIRFONE REPEATER

AP 1 SERVOS

BRAKE CTL CH A

IN

LOCKED

LOCKED

IN

IN

IN



2/3

3/3

CAB TEMP SENSOR

FLT CTL 1 CH A

IRS 3 PWR A

L BMC CH A

L ECS PRESS XDCR

L FRTT

L PACK CTLR CH A

P FEEL/RUD LIM 1

R PACK DUCT HEAT

RAD ALT 1

YD HEAT 1

IN

IN

IN

IN

IN

IN

IN

IN

IN

IN

IN


6-49


ELECTRICAL

DC BUS 1 (Cont)

M

M

M

M

BRT



NEXTPAGE

CNTL TEST

BUS

EMERCONT

GX

_0

6_

04

9


ACPC CTL PWR C

DAU 1 CH B

GPS 1

GPWS

HF 2 COUPLER

HF 2 TRANSCVR

IN

IN

IN

IN

IN

IN



2/3

3/3

HYD 1 PRESS XDCR

IRS 3 FAN

LIGHTNING SENSOR

R BMC CH B

R PACK CTLR CH B

TAIL STROBE LTS

TOILET FAN

VIBE MONITOR

WING INSPECT LTS

WING STROBE LTS

IN

IN

IN

IN

IN

IN

IN

IN

IN

IN

SPDA1 FEED

SPDA2 FEED

SPDA3 FEED

SPDA4 FEED

CABIN FEED

ALL

DC BUS 1 FEEDERS 1/1



ELECTRICAL

DC BUS 1 (Cont)

M

M

M

M

M

M

M

BRT



NEXTPAGE

CNTL TEST

BUS

EMERCONT

GX

_0

6_

05

0


ADC 2

AIRFONE SYSTEM

AUDIO PANEL 1A

AUDIO PANEL 3A

CAIMS PMAT LAPTOP

COPILOT INTG LTS

IN

IN

IN

IN

IN

IN


DATA LINK

DAU 4 CH B

GEAR CTL A PWR 1

LIGHT DETECTOR

L LOGO LT

RMU 1 PWR A

IN

IN

IN

IN

IN

IN

SPDA1 FEED

SPDA2 FEED

SPDA3 FEED

SPDA4 FEED

CABIN FEED

ALL

DC BUS 1 FEEDERS 1/1


IN

IN

IN

IN

IN

SATCOM ANT CTLR

SATCOM DATA UNIT

SE

Documents

Chapter 6: Electrical TABLE OF CONTENTSmotor dc ext power ac ext power ac power center dc power center electrical control panel lh engine rh engine gen 1 gen 2 4 gcu gcu gcu gcu gen