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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REV 2
Flight Crew Operating Manual
CSP 100-6
Volume 2
07-00-01
ELECTRICAL
INTRODUCTION
Primary DC electrical power is provided by two engine-driven generators and one APU-driven generator supplying 28 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 contactors, fuses,
and circuit breakers. These react automatically to isolate a malfunctioning circuit.
REV 1
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REV 1
Flight Crew Operating Manual
CSP 100-6
Volume 2
07-01-01
ELECTRICAL
INTRODUCTION (Cont)
RIGHT SECONDARY
RIGHT CIRCUIT
POWER CENTER
BREAKER PANEL
LEFT CIRCUIT
BREAKER PANEL
LEFT SECONDARY
POWER CENTER
APU
GENERATOR
LEFT DC
POWER CENTER
RIGHT
BATTERY
LEFT
GENERATOR
CFO0701002_001
LEFT
BATTERY
RIGHT DC
POWER CENTER
RIGHT
GENERATOR
EXTERNAL
DC CONTROL
PANEL
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Sep 13/2004
REV 1
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
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.
REV 2
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.
May 06/2005
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Flight Crew Operating Manual
CSP 100-6
Volume 2
07-01-03
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
L BATT
EXT PWR
R BATT
AVAIL
OFF
STBY
INST
OFF
L AUX
OFF
ON
BUS TIE
L ESS
R ESS
L MAIN
R MAIN
L GEN
APU GEN
R GEN
OFF
ON
OFF
R AUX
Electrical panel shown with the optional Hydraulic Motor Driven Generator (HMDG) system.
ELECTRICAL
L BATT
EXT PWR
R BATT
AVAIL
OFF
OFF
STBY
INST
ON
HYD GEN
OFF
BUS TIE
ON
L AUX
L ESS
R ESS
L MAIN
R MAIN
L GEN
APU GEN
R GEN
OFF
ON
OFF
R AUX
EV 2
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REV 2
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.
REV 2
May 06/2005
REV 2
Flight Crew Operating Manual
CSP 100-6
Volume 2
07-01-05
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.
Volume 2
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CSP 100-6
May 06/2005
REV 2
ELECTRICAL
CB1 PILOT CIRCUIT BREAKER PANEL (TYPICAL)
1
2
3
4
5
6
7
8
9
10
AVIONICS
FUEL
NAVIGATION
NAV 1
DME 1
GPS 1
3
3
3
A
CDU 1 XPDR 1
3
B
TCAS
ALT
5
3
3
COM 1
3
7.5
HF 1
5
3
3
3
7.5
14
15
ENGINE
FADEC
L TR
PWR
CH A
R CH A
L CH A
CTRL 1
CTRL 2
3
25
5
15
15
7.5
7.5
FLAP
PRI STAB
TRIM/
SPOILER
PRI
7.5
A
FLIGHT CONTROLS
STALL
L FGP/
AURAL RIU 1A L IAPS SERVOS
13
CTRL
AUTO FLIGHT
RIU 1B/
PWR 1
WX
12
FIRE
DET
APU
COMMUNICATION
L AUDIO
L PUMP
RAD
11
CTRL 1 L PWR L SHKR PUSHER
5
3
3
L IND
CTRL
RUD LIM
7.5
3
5
5
NWS
WOW A/
B
INDICATING/RECORDING
C
HYDRAULIC
LDG GEAR
ATT
HDG 1
L PFD
L DCP
L MFD
L IND
L SOV
PUMP
3
3
10
3
10
3
3
0.5
R DC
PWR 1 RET/EXT
5
DCU A
RDC A
5
5
D
CTRL 1 L PWR 1 R PWR 2
3
5
AUX
CVR
IND
DC PUMP
5
3
0.5
5
ANTI ICE
L AOA
L PROBE
CTRL
E
3
1
May 06/2005
REV 2
L STBY
L PITOT STATIC
INBD
B
BRAKES
5
5
C
ENVIRONMENTAL
ALT LIM/
INDICATING/RECORDING
ANNUNCIATOR
5
WOW
ECS X VLV PRESS 1 L BLEED
/PACK VALVES
PWR2
3
5
13
14
3
D
L WINDSHIELD
L ICE
TAT
VANE
CASE
DET
CTRL
PWR
L WING
BLD LK L ENG
20
5
15
10
7.5
15
5
0.5
5
2
3
4
5
6
7
8
9
10
E
5
11
Flight Crew Operating Manual
CSP 100-6
12
15
CFO0106002_006
DISPLAYS
AIR
DATA 1
Volume 2
07-01-07
ELECTRICAL
ELECTRICAL SYSTEM (Cont)
CB2 COPILOT CIRCUIT BREAKER PANEL (TYPICAL)
ENGINE
A
7.5
AIL
TRIM
B
CTRL 1 L CH B
7.5
CH B
PWR
CTRL
15
5
25
3
5
LDG GEAR
WOW
OUT BD WOW
B/EXT
BRAKES A/RET
C
R CH B
FLIGHT CONTROLS
SEC STAB FLAP
STALL
SPOILER
TRIM/
RUD
R IND/
R SHKR R PWR CTRL 2
TRIM RUD LIM
CTRL
3
3
15
5
5
5
3
AVIONICS
FUEL
R PUMP
3
5
NAVIGATION
TAWS XPDR 2 CDU 2
3
APU
SEC
7.5
5
5
L DC
PUMP
0.5
PTU
R SOV
3
3
5
3
5
3
3
7.5
3
B
STBY INST STBY INST
/BATT R MFD R DCP R PFD
3
3
3
3
10
10
ATT
HDG 2
AIR
DATA 2
3
3
C
3
ANNUNCIATOR
L PWR 2 R PWR 1 CTRL 2 RDC B DCU B
FDR
5
3
5
3
5
5
D
ANTI ICE
DOME
5
3
15
14
07-01-08
3
R IND BATT TEST
R WINDSHIELD
EMER
Volume 2
A
INDICATING/RECORDING
LIGHTS
E
3
AUTO FLIGHT
COMMUNICATION
R FGP/
R AUDIO
RIU 2B/
SERVOS R IAPS AURAL RIU 1A HF 2 COM 2 PWR 1
ENVIRONMENTAL
3
NAV 2
INDICATING/RECORDING
DISPLAYS
ALT LIM/
R BLEED PRESS 2 ECS XVLV XBLEED CARGO
VALVES /TRIM
VALVE HEATER
PWR 1
D
DME 2
3
HYDRAULIC
NWS
PWR 2
GPS 2
R WING
R ENG BLD LK
13
12
R AOA
PWR
CTRL
R ICE
DET
CASE
VANE
R PROBE
R STBY STBY
STATIC PITOT R PITOT CTRL
5
3
0.5
5
15
7.5
10
5
15
20
3
11
10
9
8
7
6
5
4
3
2
1
Flight Crew Operating Manual
CSP 100-6
E
CFO0106002_005
CTRL 2
FIRE
DET
FADEC
R TR
May 06/2005
REV 2
ELECTRICAL
ELECTRICAL SYSTEM (Cont)
CB3 LEFT SIDE EQUIPMENT RACK CIRCUIT BREAKER PANEL (TYPICAL)
ENGINE
A
ENG
SYNC/
ENG RUN
TR INBD
START A
IGN A
CH A
WHL SPD
3
3
3
3
ELEC
LBATT
L GEN
SEC BUS
NORM
B
20
OFF
FUEL
C
L FORCE
MSTR DISC
GRAVITY
SOV
X FLOW
QTY 1
SNSR
AUTO FLT
TRIM
PAX
3
3
3
3
3
3
15
ELT/
NAV
OXYGEN
AVIONICS
DATA
ENVIRONMENT
ANTI ICE
L SIDE WINDOW
AUTO DEP
RAM AIR/
L FOOT
THERAPTC
OFV PWR2
WARM
PWR
CTRL
3
3
3
5
25
5
LIGHTNING
L CKPT
CABIN
WING
LOADER
D
DOOR
FLIGHT CONTROL
L ENG
3
LIGHTS
MAP/
BCN/
FAN
COM 3
DET
/PED
SIGNS
INSP
STOW
STROBE
ENTRY
3
7.5
3
5
5
5
3
7.5
5
IAPS
E
INDICATING/RECORDING
COMM
DISPLAYS
F
2
3
L MFD
PWR 2
HTR
HTR
CLOCK
PWR
3
10
10
3
3
6
7
8
9
4
5
CLOCK
CFO0106002_004
1
R AUDIO
L PFD
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CSP 100-6
Volume 2
07-01-09
ELECTRICAL
ELECTRICAL SYSTEM (Cont)
CB4 RIGHT SIDE EQUIPMENT RACK CIRCUIT BREAKER PANEL (TYPICAL)
ENGINE
SYNC/
ENG
WHL SPD
CH B
IGN B
START B
3
3
3
3
R BATT
APU GEN
TR OUTBD ENG RUN
A
ELEC
HYD GEN
PWR/
TEST
HTR
SEC BUS
3
7.5
20
R GEN
NORM
NORM
OFF
OFF
FLIGHT CONTROL
MSTR DISC
PEDAL R FORCE
AUTO FLT
TRIM
3
ANTI ICE
R SIDE WINDOW
RAM AIR/
QTY 2
VALVE
SOV
5
3
3
3
3
DRN
3rd AUDIO
PWR
WARM
5
25
5
NAV
LOGO
LDG
TAXI
7.5
5
10
10
SATCOM
LAV SMK
OFV PWR1 MAST HTR
CTRL
3
R ENG
SENSOR
ENVIRONMENTAL
R FOOT
FUEL
XFER
ADJ
3
5
3
0.5
LIGHTS
3
D
CABIN
NOSE GEAR
NAV
C
OXYGEN
MAN DEP
/IND
DET
5
B
WING
R CKPT
BUS
CABIN
STROBE
/CBP
CTRL
5
5
3
5
PRI
E
SEC
INDICATING/RECORDING
COMM
PAX
COMPASS
R MFD
R PFD
FLT
L AUDIO
ADDRESS
LIGHT
HTR
HTR
PHONE
PWR2
5
3
10
10
15
3
9
8
7
6
4
3
PWR
1
50
50
2
F
1
CFO0106002_003
5
PWR
2
REV 2
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Flight Crew Operating Manual
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REV 2
ELECTRICAL
ELECTRICAL SYSTEM (Cont)
CB5 LEFT DC POWER CENTER CIRCUIT BREAKER PANEL (TYPICAL)
LIGHTS
FCTL
EXT BAG/
PRI STAB
L LDG
AFT BAY
MOTOR
5
5
25
FIREX
A
ENGINE
AVNX
L ATS/
HF 1
HYD SOL
PWR
AVNX
FAN
5
3
3
PWR 1
R DCPC
L DCPC
PWR
PWR 2
PWR 1
BAT BUS
ESS BUS
ESS BUS
5
25
25
25
5
7.5
6
5
4
3
2
1
EDC
8
7
L SPC
C
CFO0106002_002
2
ELECTRICAL
GROUND SERVICE
ELECT
B
35
A
CB6 RIGHT DC-POWER CENTER CIRCUIT BREAKER PANEL (TYPICAL)
AVIONICS
ENGINE
FIREX
FCTL
LIGHTS
SEC STAB
HF 2
SATCOM
R ATS/
PWR
CTRL
HYD SOL
B
MOTOR
R LDG
3
5
5
5
25
5
AVNX
A
ELECTRICAL
REFUEL DEFUEL
ENVIRONMENT
R DCPC
R SPC
ESS BUS
ESS BUS
BATT BUS
CTRL
VALVES
PWR 1
PWR 2
5
7.5
25
3
3
15
15
1
2
3
4
5
6
7
35
B
BAG COMP HTR
L DCPC
8
1
2
CFO0106002_001
C
FAN
PWR 2
REV 2
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REV 2
Flight Crew Operating Manual
CSP 100-6
Volume 2
07-01-11
Volume 2
07-01-12
Flight Crew Operating Manual
CSP 100-6
L GEN
Current Sensor
Contactor
L MAIN
BUS (CBP)
LEFT
GEN
L ESS
BUS (CBP)
L
BATT
EXT
PWR
L ESS
BUS (SPC)
GROUND
SERVICE BUS
L ESS
BUS (DCPC)
L MAIN
BUS (SPC)
L BATT
BUS (DCPC)
L MAIN
BUS (DCPC)
L AUX
BUS (SPC)
Circuit Breaker
Fuse
LEGEND
L AUX
BUS (DCPC)
L BATT
BUS (SPC)
L BATT
BUS (CBP)
CFO0701002_011
L DCPC
L SECONDARY
POWER CENTER
L CIRCUIT
BREAKER
PANEL
GND
SERVICE
APU
GEN
R BATT
APU
STARTER
HYD GEN
BUS TIE
APU GEN
EXT PWR
L BATT
HYD
GEN
R ESS
BUS (SPC)
R
BATT
OFF
R BATT
BUS (DCPC)
R ESS
BUS (DCPC)
APU
RUN
START
RIGHT
GEN
R AUX
BUS (DCPC)
R BATT
BUS (SPC)
R BATT
BUS (CBP)
STANDBY
INSTRUMENT
R GEN
R AUX
BUS (SPC)
R MAIN
BUS (CBP)
R MAIN
BUS (DCPC)
R MAIN
BUS (SPC)
CB2-C6
STBY INST
R ESS
BUS (CBP)
STANDBY
INSTRUMENT
BATT
R DCPC
R SECONDARY
POWER CENTER
R CIRCUIT
BREAKER
PANEL
STBY
INST
ELECTRICAL
DIRECT CURRENT SYSTEM (DC)
DC ELECTRICAL SYSTEM
V2
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REV 2
ELECTRICAL
DIRECT CURRENT SYSTEM (DC) (Cont)
DC PRIMARY ARCHITECTURE
L BATT
LEFT
GEN
OFF
R BATT
EXT
PWR
APU
APU
STRT
RIGHT
GEN
OFF
RBAT BUS
LBAT BUS
L GEN
R GEN
EXT PWR
OFF
OFF
AVAIL
PWR
BUS TIE
LEFT
AUX BUS
LEFT
MAIN BUS
LEFT
ESS BUS
HYD GEN
ON
RIGHT
ESS BUS
RIGHT
MAIN BUS
RIGHT
AUX BUS
STD
1013.2 hPa
ILS
240
OFF
ON
B
R
T
D
I
M
20
220
130 00
10
9
200
1
128
180
10
CONTACTOR
M. 47
CAGE
FUSE
STBY
INST
CIRCUIT SENSOR
OFF
40
20
00
125 00
29.92 in
BARO
CFO0701002_006
STANDBY
INSTRUMENT
BATTERY
REV 1
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Volume 2
07-01-13
ELECTRICAL
CONTROLS AND INDICATIONS
EXTERNAL POWER CONTROL PANEL
Gnd
Service
EXT DC
APU Shutdown
Lamp
Test
AVAIL
ON
EXTERNAL POWER
CONTROL PANEL
CFO0501002_006
IN USE
V2
Volume 2
07-01-14
Flight Crew Operating Manual
CSP 100-6
May 06/2005
REV 2
ELECTRICAL
CONTROLS AND INDICATIONS (Cont)
ELECTRICAL SUMMARY PAGE
R
CAS
CKLST
SKIP
FRMT
TFC
TR/WX
A/ICE
ECS
ELEC
AUTO
PLAN
SHLDR
SIDE
ENTER
FLT
FUEL
REV 1
Sep 13/2004
REV 1
Flight Crew Operating Manual
CSP 100-6
SUMRY
HYD
CFO0701002_009
L
Volume 2
07-01-15
ELECTRICAL
CONTROLS AND INDICATIONS (Cont)
ELECTRICAL CONTROL PANEL
ELECTRICAL
L BATT
EXT PWR
R BATT
AVAIL
OFF
OFF
STBY
INST
ON
OFF
L ESS
R ESS
L MAIN
R MAIN
L GEN
APU GEN
R GEN
OFF
ON
OFF
R AUX
CFO0701002_010
L AUX
BUS TIE
With optional Hydraulic Motor Driven Generator (HMDG) system.
ELECTRICAL
L BATT
EXT PWR
R BATT
AVAIL
OFF
OFF
STBY
INST
ON
HYD GEN
OFF
BUS TIE
ON
R ESS
L MAIN
R MAIN
L GEN
OFF
APU GEN
R GEN
ON
OFF
R AUX
CFO0701002_003
L AUX
L ESS
REV 2
Volume 2
07-01-16
Flight Crew Operating Manual
CSP 100-6
May 06/2005
REV 2
ELECTRICAL
CONTROLS AND INDICATIONS (Cont)
OV
T
ELECTRICAL SYNOPTIC PAGE
85.0 MCT
85.0 MCT
93.0
61.0
TRIM
AIL
STAB
NU
NI
MACH
6.6
HOLD
RWD
LWD
RUD
ND
L
600
R
600
0
FLAPS
ITT
GEAR
DN
DN
S
T
A
R
T
84.7
46
115
7300
S
84.7
N2
T
OIL PRESS 46
A
OIL TEMP 115 R
7300 T
FF PPH
DN
SPOILERS
100
250
APU RPM
APU EGT
FUEL QTY LBS
TOTAL 12000
6000
6000
CAB ALT
7300
CAB RATE
1000
ELECTRICAL
35 ° C
26 ° C
L BATT
24.1V
0.0 V
R BATT
24.0 V
EXT
PWR
HYD
GEN
24.5 V
L ESS BUS
R ESS BUS
BUS TIE
L AUX BUS
R MAIN BUS
L MAIN BUS
20 A
30 A
0 A
GEN
GEN
28.5 V
0.0 V
R AUX BUS
APU
GEN
28.0 V
MFD CONTROL
NAV1
118.000
ADF1
ATC1/TCAS
1200
STBY
108.00
COM3
HF1
1799.5
2.0000 AM
2.0000
190.0
COM2
118.000
118.000
118.000
118.000
25
ABV
L
R
CAS
CKLST
SKIP
FRMT
TFC
TR/WX
A/ICE
ECS
ELEC
AUTO
PLAN
SHLDR
SIDE
ENTER
FLT
FUEL
SUMRY
HYD
CFO0701002_007
COM1
118.000 TX 108.00
REV 1
Sep 13/2004
REV 1
Flight Crew Operating Manual
CSP 100-6
Volume 2
07-01-17
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.
MESSAGE
INHIBITS
L (R)
BATT OVERHEAT
TO/LAND
MEANING
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
ESSENTIAL POWER
ONLY
APU GEN FAIL
TO/LAND
The APU generator failed
APU GEN OVERLOAD
TO/LAND
The APU generator has exceeded 500 amp
TO/LAND
Either the respective battery contactor failed or
the battery has been automatically disconnected for overheat protection
ELEC HYD GEN FAIL
TO/LAND
The hydraulic generator has failed to come online
ELECTRICAL FAULT
TO/LAND
An electrical system failure has occurred that
prevents display of electrical indications
TO/LAND
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
TO/LAND
Respective generator load exceeded 500 amp
L (R) MAIN BUS FAIL
TO/LAND
The affected MAIN bus is not powered
TO/LAND
The affected auxiliary BUS is not powered with
a power source available
L (R) AUX BUS OFF
TO/LAND
Respective AUX BUS is selected off
ELECTRICAL FAULT
TO/LAND
An electrical system fault occurred, resulting in
loss of redundancy in the display of electrical
indications
L (R) BATT FAIL
L (R) GEN FAIL
L (R) AUX BUS FAIL
AURAL
WARNING
4
Volume 2
07-01-18
Flight Crew Operating Manual
CSP 100-6
Sep 14/2005
REV 4
ELECTRICAL
MESSAGE
STBY INST BATT
FAULT
APU GEN OFF
L (R) BATT OFF
INHIBITS
MEANING
TO/LAND
At least one of the following has occurred:
- Standby instrument heater is inoperative
- Standby instrument battery charger is inoperative
- Standby instrument battery temperature is
greater than 80 ° C
- At least two cells of the standby instrument
battery have failed
APU GEN switch has been selected OFF
The affected battery has been selected OFF
BUS TIE MAN OPEN
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
ELEC HYD GEN ON
The optional hydraulic motor driven generator
(HMDG) has been activated
L (R) GEN OFF
AURAL
WARNING
The affected engine generator switch has been
selected OFF
REV 4
Sep 14/2005
REV 4
Flight Crew Operating Manual
CSP 100-6
Volume 2
07-01-19