Page 1
ELECTRICAL
Table of Contents
Introduction ......................................................................................................................... 07-01-01
Electrical System................................................................................................................. 07-01-03
Description ................................................................................................................. 07-01-03
Components and Operation....................................................................................... 07-01-03
Engine and APU Generators ..................................................................................... 07-01-03
External Power........................................................................................................... 07-01-03
Batteries..................................................................................................................... 07-01-05
Power Centers ...........................................................................................................07-01-05
Secondary Power Centers .........................................................................................07-01-06
Hydraulic Motor Driven Generator (HMDG) (Optional) .............................................. 07-01-06
Circuit Breaker Panels ............................................................................................... 07-01-06
Cockpit Floor Heaters ................................................................................................07-01-06
CB 1 Pilot Circuit Breaker Panel (Typical) ................................................................. 07-01-07
CB 2 Copilot Circuit Breaker Panel (Typical) ............................................................. 07-01-08
CB 3 Left Side Equipment Rack Circuit Breaker Panel (Typical)............................... 07-01-09
CB 4 Right Side Equipment Rack Circuit Breaker Panel (Typical) ............................07-01-10
CB 5 Left DC Power Center Circuit Breaker Panel (Typical) ..................................... 07-01-11
CB 6 Right DC Power Center Circuit Breaker Panel (Typical)................................... 07-01-11
Direct Current System ......................................................................................................... 07-01-12
DC Electrical System ................................................................................................ 07-01-12
DC Primary Architecture ............................................................................................ 07-01-13
Controls and Indications...................................................................................................... 07-01-14
External Power Control Panel.................................................................................... 07-01-14
Electrical Summary Page........................................................................................... 07-01-15
Electrical Control Panel.............................................................................................. 07-01-16
Electrical Synoptic Page ............................................................................................ 07-01-17
EICAS Messages....................................................................................................... 07-01-18
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Page 2
Page 3
ELECTRICAL
INTRODUCTION
Primary DC electrical power is provi ded by two engine-dri ven generators and on e APU-driven g enerator s upplying 2 8 volt
power to a split bus electrical system. An automatic electrical load-shedding system prevents generator overload and
prolongs battery duration during a single or dual generator failure. Two main batteries power essential avionics,
communication, and instrumentation. A separate battery powers the independent standby instrument system. An optional
hydraulically driven electrical generator is available to provide electrical power generation in the event all engine and APU
generator power is lost.
A ground power unit can be connected to the aircraft to provide electrical power if desired.
The only AC electrical power requirements are for passenger convenience. This power is provided by inverters located in
the aft accessory compartment.
The electrical system incorporates a split, multiple bus system for power distribution interconnected by co ntactors, fuses,
and circuit breakers. These react automatically to isolate a malfunctioning circuit.
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REV 1 CSP 100-6
07-01-01
Page 4
INTRODUCTION (Cont)
RIGHT SECONDARY
RIGHT CIRCUIT
BREAKER PANEL
POWER CENTER
RIGHT
GENERATOR
ELECTRICAL
RIGHT DC
POWER CENTER
EXTERNAL
DC CONTROL
PANEL
LEFT CIRCUIT
BREAKER PANEL
LEFT SECONDARY
POWER CENTER
LEFT
BATTERY
RIGHT
BATTERY
APU
GENERATOR
LEFT DC
POWER CENTER
LEFT
GENERATOR
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ELECTRICAL
ELECTRICAL SYSTEM
DESCRIPTION
The Challenger 300 electrical system is a 28 vdc system and divided into two main functions:
- Power generation system
- Power distribution system
The electrical power generation system consists of the following power sources:
- Two main generators provide electrical energy to feed the loads under normal operation in flight and
ground operations. Either one of the engines provides sufficient generator power for normal operations
- One APU generator can share electrical loads with the engine generators at medium and low altitudes or provide
enough electrical generation capability to replace one or both engine generators during failure conditions
- Two onboard batteries that feed the essential loads under emergency conditions when the generators
are inoperative, and on the ground for feeding all loads
- One standby instrument battery located in the nose landing gear bay area. It provides power to the
standby instrument system for approximately 5 hours when fully charged
- One optional hydraulic motor driven generator with a non-time limited source of electrical power in the event total
generated power is lost
- Additonally, an external DC power source for ground operation
The electrical power distribution system consists of four distribution boxes:
- Two of the four electrical distribution boxes are direct current power centers (DCPC). These are located in the aft
equipment bay of the aircraft. They are fed by the power sources listed above and their function is to switch electrical power to the distribution buses and then distribute this power to loads in the aft fuselage of the aircraft
- The other two electrical distribution boxes are secondary power centers. They are located in the equipment rack in
the front fuselage of the aircraft and are fed by the distribution buses of the DCPCs. They distribute electrical
power to the loads in the front fuselage of the aircraft
- Two circuit breaker panels are located in the cockpit. They are fed by the distribution buses of the secondary distribution centers and distribute electrical power to loads which require pilot access to the associated circuit breaker.
- The electrical system is electrically and physically segregated into two channels. External DC power and the APU
generator are arranged to connect to these two channels
REV 2
COMPONENTS AND OPERATION
ENGINE AND APU GENERATORS
Two engine driven generators, one on each engine accessory section, provide the normal source of 28 volt power to the
airplane. A third identical generator is installed on the APU. All three generators are air cooled and include an integrated
fan. The engine-driven generators automatically come online after the engines are running, the GPU is disconnected, and
the EXT PWR switch on the electrical control panel is depressed, changing the annunciation from ON to AVAIL. The generators are limited to 12 kVA (400 amp) and the nominal output voltage is 29.5 volts.
When at least two generators are online, the bus tie is normally open. The left generator recharges the left main battery, and
the right generator recharges the right main battery. The generators supply DC power to all DC powered equipment on the
airplane under normal conditions.
EXTERNAL POWER
Ground power can be connected to the airplane through a receptacle located on the lower right side of the fuselage just
below the engine pylon. The anti-flash contactor that connects the output of the GPU to the aircraft electrical system closes
only if the voltage and polarity are within acceptable limits. The acceptable voltage limits are approximately 24 to 32 volts.
The GPU should be regulated to 28 vdc and limited to 1500 amps.
The EXT PWR switch is located on the cockpit electrical control panel. The green AVAIL caption on the EXT PWR switch
illuminates if the GPU is within acceptable parameters. Depressing the EXT PWR switch when the green AVAIL light is
illuminated closes the GPU antiflash contactor, connecting the GPU. The ON caption illuminates, and the green AVAIL
caption extinguishes. The GPU may be deselected with the same switch.
The bus tie contactor automatically closes when a GPU is connected and selected ON. The entire DC system is powered,
assuming the EXT PWR is selected ON.
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ELECTRICAL
ELECTRICAL SYSTEM (Cont)
EXTERNAL POWER (Cont)
Neither the engine-driven nor the APU-driven generators come online with the GPU selected ON. If they are on when the
GPU is selected, they drop offline. Engine-driven generators automatically come online after engine start, but not if the
GPU is selected ON. The aircraft main batteries do not have to be on to close the GPU antiflash contactor.
GPU output voltage is indicated on the SUMMARY page and on the ELECTRICAL system synoptic display. No indication
of amps drawn from the GPU is provided.
With the external power cable connected, the following indications are annunciated on the ELECTRICAL synoptic display.
EXT PWR symbol and line are white when AVAIL, green when selected on, and removed when disconnected. These appear
whenever a GPU cable is connected to the airplane, and a voltage of greater than 5 vdc is sensed by the power monitor.
ELECTRICAL
EXT PWR
AVAIL
ON
R BATT
OFF
STBY
INST
L BATT
OFF
OFF
L AUX
L ESS
L MAIN
L GEN
OFF
BUS TIE
APU GEN
ON
R ESS
R MAIN R AUX
R GEN
OFF
Electrical panel shown with the optional Hydraulic Motor Driven Generator (HMDG) system.
ELECTRICAL
EXT PWR
AVAIL
ON
BUS TIE
R BATT
OFF
HYD GEN
ON
R ESS
STBY
INST
OFF
L BATT
OFF
L ESS
L AUX
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L MAIN
L GEN APU GEN
OFF
ON
CSP 100-6
R MAIN
R GEN
OFF
R AUX
REV 2
Page 7
ELECTRICAL
ELECTRICAL SYSTEM (Cont)
BATTERIES
The batteries are located in the fuselage fairing aft of the left wing. During APU start, the right battery is isolated from the
rest of the aircraft and provides power to the APU starter. The bus tie closes and the left battery provides power to the rest
of the aircraft for emergency operation during total generator failure. They also provide power to the battery buses even
when the batteries are selected off.
The standard batteries are 24 volt nickel-cadmium (NICAD) rated at 44-amp hr.
Gases produced by the main batteries are vented overboard through two tubes that extend from the battery cases.
The batteries are connected to the essential buses when the contactors are closed. When a generator is online, it is connected
to the main buses and charges the battery.
When the batteries are connected on their corresponding buses in parallel with the generators, they are charged by the generators.
Individual battery voltages and temperatures can be read on the ELECTRICAL and SUMMARY synoptic displays on the
MFD.
During a total generator failure, the aircraft batteries provide power for necessary essential equipment for a
limited duration.
Standby Instrument power is supplied by a dedicated 24 vdc battery. The standby instrument is activated by a separate
STBY INST switch located on the ELECTRICAL power panel.
If the batteries are allowed to significantly discharge prior to bringing a generator on-line, the charging current may be large
enough to result in a APU GEN OVERLOAD, or L (R) GEN OVERLOAD caution CAS message for a short time as the
batteries recharge.
POWER CENTERS
The two DC power centers (left and right) provide the following functions:
- Protect the loads from abnormal electrical power quality
- Control and reconfigure the distribution system in response to manual switching or when a fault occurs. This
reconfiguration shall ensure the supply of the buses in accordance with an established priority relating to the power
sources available
- Ensure the coupling of the two channels on the ground when only batteries or external DC power are available, or
in flight when only one generator is available
- Control the automatic load shedding
- Isolate the faulted distribution buses when a short circuit occurs on a feeder or on a bus
- Distribute the electrical power to loads located in the aft of the aircraft
- Distribute the electrical power to secondary power centers located in the front fuselage of the aircraft
- Protect distribution cables from short circuit
Additionally, there is an Auxiliary Power Center for the APU Generator.
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ELECTRICAL
ELECTRICAL SYSTEM (Cont)
SECONDARY POWER CENTERS
The secondary power centers are located on the equipment rack in the front fuselage of the aircraft. They are fed by the
distribution buses of the direct current power centers and distribute electrical power to the loads in the front fuselage of the
aircraft.
HYDRAULIC MOTOR DRIVEN GENERATOR (HMDG) (OPTIONAL)
The optional HMDG system provides a non-time limited source of electrical power in the event total generated power is
lost. The HMDG is powered by the left hydraulic system. It is rated for 65 amp and consists of a hydraulic motor that drives
a DC generator. An ELEC HYD GEN ON (S) message will be displayed on the EICAS when the system is activated.
The HMDG is operated by the HYD GEN switch on the ELECTRICAL cockpit control panel.
CIRCUIT BREAKER PANELS
Two circuit breaker panels are located in the cockpit and are fed by the distribution buses of the secondary power centers.
They distribute power to the loads which require pilot access to the associated circuit breaker.
Two other circuit breaker panels are located in the left and right equipment racks. They are also fed by the distribution buses
of the secondary power centers.
COCKPIT FLOOR HEATERS
Four cockpit floor heaters are installed on the flight compartment floor, one on each side of the two control columns. Each
is covered by a scuff plate to prevent damage to the heat strips. There are no pilot operated controls, as a temperature limiting circuit keeps the temperature between 68 °F (20 ° C) and 95 °F (35 ° C). Also an internal thermal switch prevents the
floor heaters from an overheat condition.
The pilot’s floor heater is connected to the left equipment rack circuit breaker panel, and the copilot’s floor heater is connected to the right equipment rack circuit breaker panel.
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CSP 100-6
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Page 9
CB1 PILOT CIRCUIT BREAKER PANEL (TYPICAL)
AVIONICS
NAVIGATION
NAV 1
DME 1
33 3335
A
L AUDIO
PWR 1
COMMUNICATION
COM 1
GPS 1
HF 1
CDU 1
RIU 1B/
AURAL
XPDR 1
RIU 1A
RAD
TCAS
ALT
AUTO FLIGHT
L FGP/
SERVOSL IAPS
35
B
INDICATING/RECORDING
DISPLAYS
ATT
HDG 1
10 10
3
INDICATING/RECORDING
ANNUNCIATOR
CTRL 1
3
L STBY
STATIC
5
L PWR 1
RDC A
L PITOT
20
L MFD
L DCPL PFD
3
R PWR 2
55
TAT
VANE
15 10
CVR
5 3 0.5
ANTI ICE
L AOA
CASE
7.5
L ICE
DET
15
L WINDSHIELD
C
D
E
AIR
DATA 1
DCU A
55
L PROBE
CTRL
3
WX
APU
SPOILER
CTRL 1
PRI
L IND
330.53
IND DC PUMP
CTRL
PWR
50.5
FUEL
L PUMP
AUX
L WING
BLD LK
1110987654321 1312 1514
FIRE
DET
R CH A
CH ACTRL
PWR
25
FLIGHT CONTROLS
STALL
L PWR
L SHKR PUSHER
3357.53557.537.537.5 33
NWS
R DC
L SOV
5
PUMP
L ENG
5
PWR 1
1110987654321 1312 1514
ENGINE
FADEC
L CH A
15 15
L IND
LDG GEARHYDRAULIC
WOW A/
RET/EXT
55 5 5
ENVIRONMENTAL
ALT LIM/
ECS X VLV
PWR2
33
L TR
CTRL 1 CTRL 2
7.5 7.553
PRI STABFLAP
TRIM/
RUD LIM
CTRL
WOW
INBD
B
BRAKES
L BLEED
PRESS 1
VALVES
/PACK
5
ELECTRICAL
A
B
C
D
E
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ELECTRICAL SYSTEM (Cont)
CB2 COPILOT CIRCUIT BREAKER PANEL (TYPICAL)
ELECTRICAL
ENGINE
R TR
CTRL 2 CTRL 1 L CH B
7.5 7.5
A
AIL
RUD
TRIM
TRIM
353357.553337.53
B
WOW
OUT BD
A/RET
BRAKES
5555
C
ENVIRONMENTAL
R BLEED
PRESS 2
VALVES /TRIM
333
D
LIGHTS
EMER DOME
5
E
FADEC
R CH B
15 15
FLIGHT CONTROLS
SEC STAB
RUD LIM
LDG GEAR
ECS XVLV
5
3350.55
TRIM/
53
WOW
B/EXT
ALT LIM/
PWR 1
FLAP
R IND/
CTRL
NWS
PWR 2
XBLEED
VALVE HEATER
FIRE
DET
CH B
5
R SHKR
L DC
PUMP
0.5 3 3 3
CARGO
3
R ENG
FUEL
R PUMP
PWR CTRL
25
333 3
STALL
SPOILER
R PWR
CTRL 2
HYDRAULIC DISPLAYS
PTU
R SOV
R WING
BLD LK PWR
APU
SEC
R IND
R WINDSHIELD
CTRL
TAWS
AUTO FLIGHT
R FGP/
SERVOS R IAPS
STBY INST
3
FDR
ANTI ICE
R ICE
DET
15
STBY INST
/BATT
R AOA
CASE
7.5
BATT TEST
3
101112131415
AVIONICS
NAVIGATION
XPDR 2
RIU 2B/
AURAL
INDICATING/RECORDING
R MFD
10
INDICATING/RECORDING
ANNUNCIATOR
L PWR 2
55
VANE
10
GPS 2
CDU 2
COMMUNICATION
RIU 1A
HF 2
R DCP
R PFD
333
10
R PWR 1
CTRL 2
3
STBY
R STBY
PITOT
STATIC
5
15
DME 2
R AUDIO
COM 2
ATT
HDG 2
RDC B
55
R PROBE
R PITOT
20
NAV 2
PWR 1
AIR
DATA 2
DCU B
CTRL
3
123456789
C
D
E
A
B
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ELECTRICAL SYSTEM (Cont)
CB3 LEFT SIDE EQUIPMENT RACK CIRCUIT BREAKER PANEL (TYPICAL)
ELECTRICAL
B
C
D
E
F
A
ENG
START A
333 3
L GEN
L ENG
SOV
333
DATA
LOADER
3
IAPS
FAN
3
ENGINE
SYNC/
ENG RUN
IGN A
ELEC
LBATT
NORM
OFF
GRAVITY
X FLOW QTY 1
AVIONICS
SEC BUS
FUEL
LIGHTNING
COM 3
DET
7.5 3 5 5 5 3 7.5 5
CH A
TR INBD
WHL SPD
20
L FORCE
L CKPT
COMM
R AUDIO
PWR 2
FLIGHT CONTROL
MSTR DISC
AUTO FLT TRIM
SNSR
33315
OXYGEN
ELT/
NAV
/PED
3
AUTO DEP
THERAPTC
33
CABIN
SIGNS
RAM AIR/
OFV PWR2
L PFD
DOOR
PAX
ENVIRONMENT
L FOOT
WARM
5255
3
LIGHTS
MAP/
WING
STOW
INSP
INDICATING/RECORDING
DISPLAYS
L MFD
HTR
HTR
10 10 3 3
ANTI ICE
L SIDE WINDOW
PWR CTRL
BCN/
STROBE
CLOCK
ENTRY
CLOCK
PWR
2
1
345
6
8
7
9
CFO0106002_004
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ELECTRICAL SYSTEM (Cont)
CB4 RIGHT SIDE EQUIPMENT RACK CIRCUIT BREAKER PANEL (TYPICAL)
ENGINE
CH B
R BATT
20
QTY 2
SYNC/
START B
IGN B
3333
ELEC
APU GEN
NORM
OFF
FUEL
XFER
VALVE
3333533
SATCOM3rd AUDIO OXYGEN
0.53
ANTI ICE
R SIDE WINDOW
CTRL
PWR
TRIM
R FOOT
WARM
FLIGHT CONTROL
MSTR DISC
AUTO FLT
ENVIRONMENTAL
RAM AIR/
OFV PWR1
HYD GEN
PWR/
TEST
PEDAL
ADJ
DRN
MAST HTR
TR OUTBD
WHL SPD
HTR
7.53
R FORCE
SENSOR
LAV SMK
DET
5535525
ENG RUN
SEC BUS
ENG
R GEN
NORM
R ENG
SOV
MAN DEP
/IND
3
OFF
ELECTRICAL
A
B
C
D
NAV
NAV
PRI
SEC
INDICATING/RECORDING
COMPASS
PAX
ADDRESS
9
LIGHT
LIGHTS
LOGO
NOSE GEAR
LDG
TAXI
101057.5 5 5 3
R MFD
R PFD
HTR
103510
HTR
PHONE
CABIN
COMM
FLT
L AUDIO
15 3
PWR2
WING
STROBE
345678
R CKPT
/CBP
PWR
50 50
CABIN
BUS
CTRL
E
5
PWR
2
1
F
12
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ELECTRICAL SYSTEM (Cont)
CB5 LEFT DC POWER CENTER CIRCUIT BREAKER PANEL (TYPICAL)
ELECTRICAL
LIGHTS
EXT BAG/
AFT BAY
AVNX
FAN
PWR 1
35
B
5525533
5
GROUND SERVICE
PWR 2
25 25
ELECT
EDC
PWR
2345678
CB6 RIGHT DC-POWER CENTER CIRCUIT BREAKER PANEL (TYPICAL)
AVIONICS
A
HF 2
PWR
L DCPC
ESS BUS
SATCOM
CTRL
3555255
ELECTRICAL
R DCPC
ESS BUS
ENGINE
R ATS/
HYD SOL
R SPC
BATT BUS CT RL
FIREX
B
REFUEL DEFUEL
FCTL
SEC STAB
MOTOR R LDG
VALVES
LIGHTS
ENVIRONMENT
BAG COMP HTR
PWR 1 PWR 2
FCTL
PRI STAB
MOTORL LDG
PWR 1
B
FIREX
L SPC
BAT BUS
ENGINE
L ATS/
HYD SOLA
ELECTRICAL
R DCPC
ESS BUS
PWR 2
AVNX
FAN
35
AVNX
HF 1
PWR
L DCPC
ESS BUS
7.525 5
12
A
C
CFO0106002_002
REV 2
57.525 3 3
C
1
23456 8
15 15
7
1
2
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CFO0106002_001
Page 14
DIRECT CURRENT SYSTEM (DC)
V
DC ELECTRICAL SYSTEM
ELECTRICAL
INST
STBY
STANDBY
INSTRUMENT
BATT
STANDBY
INSTRUMENT
R BATT
BUS TIE
L BATT
PANEL
BREAKER
R CIRCUIT
R SECONDARY
POWER CENTER
R BATT
R MAIN
R ESS
R BATT
BUS (CBP)
BUS (CBP)
BUS (CBP)
BUS (SPC)
R AUX
BUS (SPC)
R MAIN
BUS (SPC)
CB2-C6
STBY INST
R ESS
BUS (SPC)
R AUX
R MAIN
R ESS
BUS (DCPC)
BUS (DCPC)
R BATT
BUS (DCPC)
HYD GEN
EXT PWR
R DCPC
R GEN
GEN
RIGHT
APU
RUN
OFF START
BUS (DCPC)
HYD
GEN
GND
SERVICE
APU GEN
R
APU
APU
BATT
STARTER
GEN
EXT
PWR
L ESS
BUS (SPC)
GROUND
SERVICE BUS
L
L ESS
BUS (CBP)
L MAIN
BUS (SPC)
L MAIN
BUS (CBP)
L AUX
BUS (SPC)
L BATT
BUS (CBP)
PANEL
BREAKER
L CIRCUIT
L BATT
BUS (SPC)
L SECONDARY
POWER CENTER
L ESS
BUS (DCPC)
L BATT
BUS (DCPC)
L MAIN
BUS (DCPC)
L AUX
BUS (DCPC)
BATT
GEN
LEFT
L GEN
Circuit Breaker
Contactor
Fuse
LEGEND
L DCPC
Current Sensor
CFO0701002_011
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DIRECT CURRENT SYSTEM (DC) (Cont)
DC PRIMARY ARCHITECTURE
ELECTRICAL
LEFT
AUX BUS
CONTACTOR
L GEN
OFF
LEFT
GEN
LEFT
MAIN BUS
LBAT BUS
ESS BUS
L BATT
OFF
LEFT
EXT
PWR
EXT PWR
AVAIL
PWR
BUS TIE
HYD GEN
ON
STANDBY
INSTRUMENT
BATTERY
APU
APU
STRT
R BATT
OFF
RIGHT
ESS BUS
OFF
ON
RBAT BUS
MAIN BUS
B
R
T
D
I
M
RIGHT
240
220
9
200
1
180
M. 47
CAGE
RIGHT
GEN
ILS
R GEN
OFF
STD
1013.2 hPa
20
10
128
10
29.92 in
BARO
RIGHT
AUX BUS
130
00
40
20
00
125
00
FUSE
CIRCUIT SENSOR
REV 1
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STBY
INST
OFF
CFO0701002_006
07-01-13
Page 16
CONTROLS AND INDICATIONS
EXTERNAL POWER CONTROL PANEL
ELECTRICAL
EXTERNAL POWER
CONTROL PANEL
Gnd
Service
ON
EXT DC
AVAIL
IN USE
APU Shutdown
Lamp
Test
CFO0501002_006
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Page 17
CONTROLS AND INDICATIONS (Cont)
ELECTRICAL SUMMARY PAGE
ELECTRICAL
REV 1
Sep 13/2004 Flight Crew Operating Manual Volume 2
REV 1 CSP 100-6
CKLST
FRMT
A/ICE
CAS
SKIP
TFC
ECS
LR
TR/WX
ELEC
FLT FUEL
AUTO
SHLDR SIDE
ENTER
PLAN
SUMRY
HYD
CFO0701002_009
07-01-15
Page 18
CONTROLS AND INDICATIONS (Cont)
ELECTRICAL CONTROL PANEL
ELECTRICAL
STBY
INST
L BATT R BATT
OFF
EXT PWR
AVAIL
ON
ELECTRICAL
OFF
OFF
L AUX
L ESS
L MAIN
L GEN
OFF
BUS TIE
APU GEN
ON
With optional Hydraulic Motor Driven Generator (HMDG) system.
ELECTRICAL
EXT PWR
AVAIL
ON
BUS TIE
STBY
INST
OFF
L BATT
OFF
R ESS
R MAIN R AUX
R GEN
OFF
CFO0701002_010
R BATT
OFF
HYD GEN
ON
R ESS
R MAIN R AUX
R GEN
OFF
L AUX
L ESS
L MAIN
L GEN APU GEN
OFF
ON
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CSP 100-6
REV 2
CFO0701002_003
REV 2
Page 19
CONTROLS AND INDICATIONS (Cont)
ELECTRICAL SYNOPTIC PAGE
T
T
85.0 MCT 85.0 MCT
85.0 MCT 85.0 MCT
V
V
O
O
93.0 61.0
93.0 61.0
NI
NI
MACH
MACH
HOLD
HOLD
600 600
600 600
ITT
ITT
S
S
84.7
84.7
T
T
46
46
A
A
115
115
R
R
7300
7300
T
T
APU RPM
APU RPM
APU EGT
APU EGT
FUEL QTY LBS
FUEL QTY LBS
TOTAL
TOTAL
6000 6000
6000 6000
N2
N2
OIL PRESS
OIL PRESS
OIL TEMP
OIL TEMP
FF PPH
FF PPH
12000
12000
100
250
250
84.7
84.7
46
46
115
115
7300
7300
S
S
T
T
A
A
R
R
T
T
° C
35
L BATT
24.0
V
TRIM
STAB
STAB
NU
NU
ND
ND
FLAPS
TRIM
6.6
6.6
0
SPOILERS
SPOILERS
CAB ALT
CAB ALT
CAB RATE
CAB RATE
LWD
LWD
L
L
DN DN
ELECTRICAL
24.1
0.0
V
V
HYD
EXT
GEN
PWR
AIL
AIL
RUD
RUD
GEAR
DN
7300
7300
1000
1000
RWD
RWD
R
R
26
R BATT
24.5
ELECTRICAL
° C
V
L AUX BUS
MFD CONTROL
MFD CONTROL
COM1
118.000
TX
L ESS BUS
L MAIN BUS
20
A
GEN GENGEN
28.5
V
NAV1
108.00 1799.5
ATC1/TCAS
1200
STBY
ADF1
190.0108.00118.000
ABV
LR
CAS
CKLST
FRMT
SKIP
TFC
TR/WX
BUS TIE
0
0.0
R ESS BUS
A
V
COM3
118.000
118.000
SUMRY
R AUX BUS
COM2
118.000
118.000
25
R MAIN BUS
A
APU
V
2.0000
30
28.0
HF1
AM
2.0000
AUTO PLAN
SHLDR SIDE
ENTER
REV 1
Sep 13/2004 Flight Crew Operating Manual Volume 2
REV 1 CSP 100-6
A/ICE
ECS
ELEC
FLT FUEL
HYD
CFO0701002_007
07-01-17
Page 20
ELECTRICAL
EICAS MESSAGES
The electrical system messages are shown on the EICAS. In the table below is a list of the electrical system messages,
inhibits, and aural warnings. A brief explanation of each message is provided.
AURAL
MESSAGE INHIBITS MEANING
WARNING
L (R)
BATT OVERHEAT
ESSENTIAL POWER
ONLY
APU GEN FAIL TO/LAND The APU generator failed
APU GEN OVERLOAD TO/LAND
L (R) BATT FAIL
ELEC HYD GEN FAIL TO/LAND
ELECTRICAL FAULT TO/LAND
L (R) GEN FAIL
TO/LAND
TO/LAND
TO/LAND
Respective battery internal temperature
exceeded 70 ° C
The essential buses are powered by the batteries only. AUX and MAIN buses are automatically deactivated in flight
APU generator has exceeded 500 amp
The
Either the respective battery contactor failed or
the battery has been automatically disconnected for overheat protection
The hydraulic generator has failed to come online
An electrical system failure has occurred that
prevents display of electrical indications
The affected generator has failed. If the APU
generators not on line, the BUS-TIE will automatically close and, in-flight, the auxiliary buses
will not be powered
L (R) ESS BUS FAIL TO/LAND Affected bus is not powered
L (R)
GEN OVERLOAD
L (R) MAIN BUS FAIL TO/LAND The affected MAIN bus is not powered
L (R) AUX BUS FAIL
L (R) AUX BUS OFF TO/LAND Respective AUX BUS is selected off
ELECTRICAL FAULT TO/LAND
4
Volume 2 Flight Crew Operating Manual Sep 14/2005
07-01-18
TO/LAND Respective generator load exceeded 500 amp
TO/LAND
The affected auxiliary BUS is not powered with
a power source available
An electrical system fault occurred, resulting in
loss of redundancy in the display of electrical
indications
CSP 100-6
REV 4
Page 21
MESSAGE INHIBITS MEANING
At least one of the following has occurred:
- Standby instrument heater is inoperative
- Standby instrument battery charger is inopera-
STBY INST BATT
FAULT
APU GEN OFF APU GEN switch has been selected OFF
TO/LAND
tive
- Standby instrument battery temperature is
greater than 80 ° C
- At least two cells of the standby instrument
battery have failed
ELECTRICAL
AURAL
WARNING
L (R) BATT OFF
BUS TIE MAN OPEN
ELEC HYD GEN ON
L (R) GEN OFF The affected engine generator switch has been
The affected battery has been selected OFF
The bus tie has been manually selected open.
This prevents automatic operation of the bus
tie. Pressing the BUS TIE switch a second time
restores automatic control
The optional hydraulic motor driven generator
(HMDG) has been activated
selected OFF
REV 4
Sep 14/2005 Flight Crew Operating Manual Volume 2
REV 4 CSP 100-6
07-01-19
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