-
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
P I L O T T R A I N I N G G U I D E
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
-
For Training Purposes OnlySept 04
6-1
P I L O T T R A I N I N G G U I D E
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
P I L O T T R A I N I N G G U I D E
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.
-
For Training Purposes OnlySept 04
6-3
P I L O T T R A I N I N G G U I D E
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
-
6-4 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
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
-
For Training Purposes OnlySept 04
6-5
P I L O T T R A I N I N G G U I D E
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
-
6-6 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
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
-
For Training Purposes OnlySept 04
6-7
P I L O T T R A I N I N G G U I D E
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
-
6-8 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
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
-
For Training Purposes OnlySept 04
6-9
P I L O T T R A I N I N G G U I D E
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
-
6-10 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
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
CIRCUIT BREAKER SYSTEM
STAT SYS BUSPREVPAGE
NEXTPAGE
CNTL TEST
BUS
EMERCONT
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
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.
-
For Training Purposes OnlySept 04
6-11
P I L O T T R A I N I N G G U I D E
ELECTRICAL
Circuit breakers can be acknowledged, or acknowledged and reset,
using the line select keys.
BRT
CIRCUIT BREAKER SYSTEM
STAT SYS BUSPREVPAGE
NEXTPAGE
CNTL TEST
BUS
EMERCONT
CIRCUIT BREAKER - STATUS 1/1
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
CIRCUIT BREAKER SYSTEM
STAT SYS BUSPREVPAGE
NEXTPAGE
CNTL TEST
BUS
EMERCONT
CIRCUIT BREAKER - STATUS 1/1
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
CIRCUIT BREAKER SYSTEM
STAT SYS BUSPREVPAGE
NEXTPAGE
CNTL TEST
BUS
EMERCONT
CIRCUIT BREAKER - STATUS 1/1
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
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
IN
LOCKED
TRIP
-
6-12 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
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.
-
For Training Purposes OnlySept 04
6-13
P I L O T T R A I N I N G G U I D E
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
-
6-14 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
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.
-
For Training Purposes OnlySept 04
6-15
P I L O T T R A I N I N G G U I D E
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.
-
6-16 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
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
-
For Training Purposes OnlySept 04
6-17
P I L O T T R A I N I N G G U I D E
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
-
6-18 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
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
-Normally powered by GEN 3, alternately powered by the
following, in descending priority:
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
-
For Training Purposes OnlySept 04
6-19
P I L O T T R A I N I N G G U I D E
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
-Normally powered by GEN 4, alternately powered by the
following, in descending priority:
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
-
6-20 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
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
-Normally powered by GEN 4, alternately powered by the
following, in descending priority:
AC BUS 3 AC BUS 2 AC BUS 3
PRIORITY
ON
OFF
RAT GEN
-
For Training Purposes OnlySept 04
6-21
P I L O T T R A I N I N G G U I D E
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
-
6-22 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
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
-
For Training Purposes OnlySept 04
6-23
P I L O T T R A I N I N G G U I D E
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
-
6-24 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
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
-
For Training Purposes OnlySept 04
6-25
P I L O T T R A I N I N G G U I D E
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
-
6-26 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
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
-
For Training Purposes OnlySept 04
6-27
P I L O T T R A I N I N G G U I D E
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
-
6-28 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
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
-
For Training Purposes OnlySept 04
6-29
P I L O T T R A I N I N G G U I D E
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
-
6-30 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
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:
-
For Training Purposes OnlySept 04
6-31
P I L O T T R A I N I N G G U I D E
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:
-
6-32 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
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:
-
For Training Purposes OnlySept 04
6-33
P I L O T T R A I N I N G G U I D E
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
-
6-34 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
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
-
For Training Purposes OnlySept 04
6-35
P I L O T T R A I N I N G G U I D E
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
-
6-36 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
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
-
For Training Purposes OnlySept 04
6-37
P I L O T T R A I N I N G G U I D E
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
-
6-38 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
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
-
For Training Purposes OnlySept 04
6-39
P I L O T T R A I N I N G G U I D E
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
CIRCUIT BREAKER - SYSTEM 1/2
AFCS
AIR COND/PRESS
APU
BLEED
CAIMS
COMM
DOORS
ELEC
ENGINE
FIRE
FLT CONTROLS
FUEL
NEXTPAGE
PREVPAGE
M
BRT
CIRCUIT BREAKER SYSTEM
STAT SYS BUSPREVPAGE
NEXTPAGE
CNTL TEST
BUS
EMERCONT
GX
_0
6_
03
9
CIRCUIT BREAKER - SYSTEM 1/2
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.
-
6-40 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
ELECTRICAL
ELEC SYSTEM KEY
M M M
MMM
MMM
MMM
M
BRT
CIRCUIT BREAKER SYSTEM
STAT SYS BUSPREVPAGE
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
CB - ELEC SYSTEM 5/12
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
CB - ELEC SYSTEM 9/12
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
CB - ELEC SYSTEM 2/12
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
CB - ELEC SYSTEM 6/12
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
CB - ELEC SYSTEM 10/12
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
CB - ELEC SYSTEM 3/12
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
CB - ELEC SYSTEM 7/12
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
CB - ELEC SYSTEM 11/12
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
CB - ELEC SYSTEM 12/12
TRU 2 AC 3 INCCBP
CB - ELEC SYSTEM 4/12
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
CB - ELEC SYSTEM 8/12
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
CIRCUIT BREAKER - SYSTEM 1/2
AFCS
AIR COND/PRESS
APU
BLEED
CAIMS
COMM
DOORS
ELEC
ENGINE
FIRE
FLT CONTROLS
FUEL
-
For Training Purposes OnlySept 04
6-41
P I L O T T R A I N I N G G U I D E
ELECTRICAL
BUS KEYThe BUS key is used to display circuit breaker status and
location by individual buses.
MM
MM
M
BRT
CIRCUIT BREAKER SYSTEM
STAT SYS BUSPREVPAGE
NEXTPAGE
CNTL TEST
BUS
EMERCONT
M
BRT
CIRCUIT BREAKER SYSTEM
STAT SYS BUSPREVPAGE
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
-
6-42 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
ELECTRICAL
AC BUS 2
M
M
M
BRT
CIRCUIT BREAKER SYSTEM
STAT SYS BUSPREVPAGE
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
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
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
-
For Training Purposes OnlySept 04
6-43
P I L O T T R A I N I N G G U I D E
ELECTRICAL
AC BUS 3
MM
M M
GLOBAL EXPRESS GLOBAL 5000
M
BRT
CIRCUIT BREAKER SYSTEM
STAT SYS BUSPREVPAGE
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
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
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
-
6-44 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
ELECTRICAL
AC BUS 4
M
M
M
BRT
CIRCUIT BREAKER SYSTEM
STAT SYS BUSPREVPAGE
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
-
For Training Purposes OnlySept 04
6-45
P I L O T T R A I N I N G G U I D E
ELECTRICAL
AC ESS BUS
M
M
M
M
BRT
CIRCUIT BREAKER SYSTEM
STAT SYS BUSPREVPAGE
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
CIRCUIT BREAKER - BUS 1/1
DC 1
DC 2
DC ESS
BATT
AV BATT
APU BATT
-
6-46 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
ELECTRICAL
DC EMER BUS
M
M
M
BRT
CIRCUIT BREAKER SYSTEM
STAT SYS BUSPREVPAGE
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
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
CB - DC EMER BUS 2/2
R HYD SOV INDCPC
-
For Training Purposes OnlySept 04
6-47
P I L O T T R A I N I N G G U I D E
ELECTRICAL
DC BUS 1
MM
M
M
BRT
CIRCUIT BREAKER SYSTEM
STAT SYS BUSPREVPAGE
NEXTPAGE
CNTL TEST
BUS
EMERCONT
M
BRT
CIRCUIT BREAKER SYSTEM
STAT SYS BUSPREVPAGE
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
CB - DC BUS 1, SPDA1 2/3
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
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
SPDA1 FEED
SPDA2 FEED
SPDA3 FEED
SPDA4 FEED
CABIN FEED
ALL
CIRCUIT BREAKER - BUS 1/1
-
6-48 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
ELECTRICAL
DC BUS 1 (Cont)
M
M
M
M
M
M
M
BRT
CIRCUIT BREAKER SYSTEM
STAT SYS BUSPREVPAGE
NEXTPAGE
CNTL TEST
BUS
EMERCONT
GX
_0
6_
04
8
CB - DC BUS 1, SPDA2 1/3
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
GLOBAL EXPRESS GLOBAL 5000
CB - DC BUS 1, SPDA2 1/3
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
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
-
For Training Purposes OnlySept 04
6-49
P I L O T T R A I N I N G G U I D E
ELECTRICAL
DC BUS 1 (Cont)
M
M
M
M
BRT
CIRCUIT BREAKER SYSTEM
STAT SYS BUSPREVPAGE
NEXTPAGE
CNTL TEST
BUS
EMERCONT
GX
_0
6_
04
9
CB - DC BUS 1, SPDA3 1/3
ACPC CTL PWR C
DAU 1 CH B
GPS 1
GPWS
HF 2 COUPLER
HF 2 TRANSCVR
IN
IN
IN
IN
IN
IN
CB - DC BUS 1, SPDA3
CB - DC BUS 1, SPDA 3
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
-
6-50 For Training Purposes OnlySept 04
P I L O T T R A I N I N G G U I D E
ELECTRICAL
DC BUS 1 (Cont)
M
M
M
M
M
M
M
BRT
CIRCUIT BREAKER SYSTEM
STAT SYS BUSPREVPAGE
NEXTPAGE
CNTL TEST
BUS
EMERCONT
GX
_0
6_
05
0
CB - DC BUS 1, SPDA4 1/3
ADC 2
AIRFONE SYSTEM
AUDIO PANEL 1A
AUDIO PANEL 3A
CAIMS PMAT LAPTOP
COPILOT INTG LTS
IN
IN
IN
IN
IN
IN
CB - DC BUS 1, SPDA4 2/3
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
CB - DC BUS 1, SPDA4 3/3
IN
IN
IN
IN
IN
SATCOM ANT CTLR
SATCOM DATA UNIT
SE