BOMBARDIER Challenger 300 Operating instructions
- Type
- Operating instructions
The BOMBARDIER Challenger 300 is a versatile and powerful aircraft designed to meet the needs of discerning travelers. With a range of up to 3,450 nautical miles and a top speed of Mach 0.83, the Challenger 300 can connect you to destinations around the world. Its spacious cabin, advanced avionics, and smooth ride make it the perfect choice for business or leisure travel.
The BOMBARDIER Challenger 300 is a versatile and powerful aircraft designed to meet the needs of discerning travelers. With a range of up to 3,450 nautical miles and a top speed of Mach 0.83, the Challenger 300 can connect you to destinations around the world. Its spacious cabin, advanced avionics, and smooth ride make it the perfect choice for business or leisure travel.
ELECTRICAL
Table of Contents
May 06/2005 Flight Crew Operating Manual Volume 2
REV 2 CSP 100-6
07-00-01
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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ELECTRICAL
Sep 13/2004 Flight Crew Operating Manual Volume 2
REV 1 CSP 100-6
07-01-01
REV 1
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.
ELECTRICAL
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07-01-02
CSP 100-6
REV 1
INTRODUCTION (Cont)
RIGHT CIRCUIT
BREAKER PANEL
RIGHT SECONDARY
POWER CENTER
LEFT CIRCUIT
BREAKER PANEL
LEFT SECONDARY
POWER CENTER
RIGHT DC
POWER CENTER
RIGHT
BATTERY
LEFT
GENERATOR
APU
GENERATOR
EXTERNAL
DC CONTROL
PANEL
RIGHT
GENERATOR
LEFT DC
POWER CENTER
LEFT
BATTERY
CFO0701002_001
ELECTRICAL
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REV 2 CSP 100-6
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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 elec-
trical 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 distri-
bution 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 gen-
erators 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.
REV 2
ELECTRICAL
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CSP 100-6
REV 2
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 panel shown with the optional Hydraulic Motor Driven Generator (HMDG) system.
EXT PWR
L BATT
R BATT
OFF
AVAIL
ON
ELECTRICAL
OFF
OFF
OFF
ON
BUS TIE
L GEN
APU GEN
R GEN
R ESS
R MAIN R AUX
L ESS
L AUX
L MAIN
STBY
INST
OFF
EXT PWR
L BATT
R BATT
OFF
AVAIL
ON
ELECTRICAL
OFF
OFF
OFF
ON
BUS TIE
L GEN APU GEN
R GEN
R ESS
R MAIN
R AUX
L ESS
L AUX
L MAIN
STBY
INST
OFF
ON
HYD GEN
E
V 2
ELECTRICAL
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07-01-05
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 gen-
erators.
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
ELECTRICAL
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CSP 100-6
REV 2
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 lim-
iting 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 con-
nected to the right equipment rack circuit breaker panel.
ELECTRICAL
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REV 2 CSP 100-6
07-01-07
CB1 PILOT CIRCUIT BREAKER PANEL (TYPICAL)
A
C
B
D
E
1110987654321 1312 1514
L CH A
R CH A
CTRL 1 CTRL 2
CH ACTRL
PWR
L TR
FADEC
ENGINE
FIRE
DET
FUEL
L PUMP
NAV 1
DME 1
GPS 1
CDU 1
XPDR 1
TCAS
NAVIGATION
AVIONICS
PRI
APU
L FGP/
SERVOSL IAPS
RIU 1B/
AURAL
RIU 1A
HF 1
COM 1
AUTO FLIGHT
COMMUNICATION
INBD
BRAKES
WOW A/
RET/EXT
NWS
PWR 1
R DC
PUMP
L SOV
L IND
LDG GEARHYDRAULIC
L MFD
L DCPL PFD
ATT
HDG 1
AIR
DATA 1
DISPLAYS
INDICATING/RECORDING
L BLEED
VALVES
PRESS 1
/PACK
ENVIRONMENTAL
DCU A
RDC A
CTRL 1
L PWR 1
R PWR 2
ANNUNCIATOR
L PITOT
TAT
VANE
CASE
CTRL
PWR
L ENG
INDICATING/RECORDING
ANTI ICE
L WINDSHIELD
L AOA
15 15
7.5 7.553
25
33 3335
3357.53557.537.537.5 33
55 5 5
330.53
3
10 10
3
5
33
55
3
55
20
5
15 10
7.5
15
50.5
5
5
L WING
BLD LK
L ICE
DET
L STBY
STATIC
L PROBE
CTRL
WOW
B
3
CFO0106002_006
5 3 0.5
35
WX
RAD
ALT
L AUDIO
PWR 1
CVR
IND DC PUMP
AUX
ALT LIM/
ECS X VLV
PWR2
1110987654321 1312 1514
A
C
B
D
E
TRIM/
RUD LIM
L PWR
SPOILER
CTRL 1
PRI STABFLAP
STALL
FLIGHT CONTROLS
L SHKR PUSHER
L IND
CTRL
ELECTRICAL
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CSP 100-6
REV 2
ELECTRICAL SYSTEM (Cont)
CB2 COPILOT CIRCUIT BREAKER PANEL (TYPICAL)
A
C
B
D
E
123456789
101112131415
CTRL 2 CTRL 1 L CH B
R CH B
CH B
PWR CTRL
R TR
FADEC
ENGINE
FIRE
DET
FUEL
R PUMP
TAWS
XPDR 2
CDU 2
GPS 2
DME 2
NAV 2
NAVIGATION
AVIONICS
R SHKR
R PWR
SPOILER
CTRL 2
SEC
FLAP
STALL
FLIGHT CONTROLS
APU
R FGP/
SERVOS R IAPS
RIU 2B/
AURAL
RIU 1A
HF 2
COM 2
AUTO FLIGHT
COMMUNICATION
OUT BD
BRAKES
WOW
A/RET
NWS
PWR 2
L DC
PUMP
PTU
R SOV
R IND
LDG GEAR
HYDRAULIC DISPLAYS
INDICATING/RECORDING
FDR
L PWR 2
R PWR 1
CTRL 2
RDC B
DCU B
ANNUNCIATOR
EMER DOME
LIGHTS
R ENG
R WING
BLD LK PWR
CTRL
R ICE
DET
CASE
VANE
R STBY
STATIC
STBY
PITOT
R PITOT
R PROBE
CTRL
INDICATING/RECORDING
ANTI ICE
R WINDSHIELD
R AOA
CFO0106002_005
7.5 7.5
15 15
5
25
333 3
353357.553337.53
5555
0.5 3 3 3
5
333
55
3
55
5
3350.55
15
7.5
10
5
15
20
3
53
SEC STAB
TRIM/
RUD LIM
AIL
TRIM
RUD
TRIM
R IND/
CTRL
R AUDIO
PWR 1
3
STBY INST
BATT TEST
STBY INST
/BATT
R MFD
R DCP
R PFD
ATT
HDG 2
AIR
DATA 2
3
10
333
10
WOW
B/EXT
3
VALVES /TRIM
PWR 1
VALVE HEATER
R BLEED
PRESS 2
ECS XVLV
XBLEED
CARGO
ALT LIM/
ENVIRONMENTAL
A
C
B
D
E
ELECTRICAL
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ELECTRICAL SYSTEM (Cont)
CB3 LEFT SIDE EQUIPMENT RACK CIRCUIT BREAKER PANEL (TYPICAL)
345
6
7
8
1
2
9
A
C
B
D
E
F
L PFD
HTR
L MFD
HTR
INDICATING/RECORDING
TR INBD
WHL SPD
ENG RUN
CH A
SYNC/
IGN A
ENG
START A
ENGINE
ELEC
L ENG
SOV
GRAVITY
X FLOW QTY 1
FUEL
FLIGHT CONTROL
PAX
DOOR
ENVIRONMENT
L SIDE WINDOW
ANTI ICE
L FORCE
SNSR
MSTR DISC
AUTO FLT TRIM
ENTRY
LIGHTS
L CKPT
/PED
CABIN
SIGNS
WING
INSP
MAP/
STOW
BCN/
STROBE
DISPLAYS
CLOCK
CLOCK
PWR
AVIONICS
DATA
LOADER
IAPS
FAN
COM 3
LIGHTNING
DET
CFO0106002_004
333 3
333
33315
3
3
5255
7.5 3 5 5 5 3 7.5 5
10 10 3 3
LBATT
SEC BUS
20
NORM
OFF
L GEN
COMM
R AUDIO
PWR 2
3
3
OXYGEN
33
NAV
ELT/
AUTO DEP
THERAPTC
RAM AIR/
OFV PWR2
L FOOT
WARM
PWR CTRL
ELECTRICAL
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CSP 100-6
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ELECTRICAL SYSTEM (Cont)
CB4 RIGHT SIDE EQUIPMENT RACK CIRCUIT BREAKER PANEL (TYPICAL)
A
C
B
D
E
F
CFO0106002_003
345678
12
9
TR OUTBD
WHL SPD
ENG RUN
CH B
SYNC/
IGN B
ENG
START B
ENGINE
NORM
ELEC
R ENG
SOV
XFER
VALVE
QTY 2
FUEL
R FORCE
SENSOR
PEDAL
ADJ
AUTO FLT
TRIM
MSTR DISC
FLIGHT CONTROL
CABIN
LIGHTS
BUS
CTRL
PWR
1
PWR
2
INDICATING/RECORDING
3333
3333533
3
5
50 50
103510
NORM
20
HYD GEN
APU GEN
R GEN
R BATT
SEC BUS
7.53
PWR/
TEST
HTR
0.53
ENVIRONMENTAL
PWR
CTRL
R SIDE WINDOW
ANTI ICE
5535525
NOSE GEAR
WING
STROBE
R CKPT
/CBP
CABIN
TAXI
LDG
LOGO
NAV
NAV
101057.5 5 5 3
PRI
SEC
SATCOM3rd AUDIO OXYGEN
/IND
MAN DEP
LAV SMK
DET
DRN
MAST HTR
RAM AIR/
OFV PWR1
R FOOT
WARM
R PFD
HTR
R MFD
HTR
PAX
ADDRESS
COMPASS
LIGHT
COMM
15 3
FLT
PHONE
L AUDIO
PWR2
OFF
OFF
REV 2
ELECTRICAL
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ELECTRICAL SYSTEM (Cont)
CB5 LEFT DC POWER CENTER CIRCUIT BREAKER PANEL (TYPICAL)
CB6 RIGHT DC-POWER CENTER CIRCUIT BREAKER PANEL (TYPICAL)
2345678
A
C
B
12
HF 1
PWR
L ATS/
HYD SOLA
PRI STAB
MOTORL LDG
L DCPC
ESS BUS
L SPC
BAT BUS
R DCPC
ESS BUS
AVNX
ENGINE
FIREX
FCTL
LIGHTS
ELECTRICAL
EXT BAG/
AFT BAY
5525533
7.525 5
CFO0106002_002
FAN
PWR 1
AVNX
35
PWR 2
GROUND SERVICE
PWR 1
25 25
ELECT
5
EDC
PWR
HF 2
PWR
R ATS/
HYD SOL
B
SEC STAB
MOTOR R LDG
L DCPC
ESS BUS
R SPC
BATT BUS CTRL
VALVES
R DCPC
ESS BUS
AVIONICS
ENGINE
FIREX
FCTL
LIGHTS
ELECTRICAL
REFUEL DEFUEL
1
23456 8
A
C
B
1
2
3555255
57.5253 3
CFO0106002_001
7
SATCOM
CTRL
PWR 1 PWR 2
ENVIRONMENT
15 15
BAG COMP HTR
FAN
PWR 2
AVNX
35
REV 2
ELECTRICAL
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CSP 100-6
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DIRECT CURRENT SYSTEM (DC)
DC ELECTRICAL SYSTEM
R
BATT
APU
STARTER
LEFT
GEN
RIGHT
GEN
EXT
PWR
L
BATT
GROUND
SERVICE BUS
L BATT
BUS (DCPC)
L AUX
BUS (DCPC)
L MAIN
BUS (DCPC)
L ESS
BUS (DCPC)
L BATT
BUS (SPC)
L AUX
BUS (SPC)
L MAIN
BUS (SPC)
L ESS
BUS (SPC)
L ESS
L MAIN
BUS (CBP)
L BATT
BUS (CBP)
R ESS
BUS (CBP)
R MAIN
BUS (CBP)
R BATT
BUS (CBP)
CB2-C6
STBY INST
R ESS
BUS (SPC)
R MAIN
BUS (SPC)
R AUX
BUS (SPC)
R BATT
BUS (SPC)
R BATT
BUS (DCPC)
R ESS
BUS (DCPC)
R MAIN
BUS (DCPC)
R AUX
BUS (DCPC)
L SECONDARY
POWER CENTER
L CIRCUIT
BREAKER
PANEL
L DCPC
R DCPC
R SECONDARY
POWER CENTER
STANDBY
INSTRUMENT
R CIRCUIT
BREAKER
PANEL
STBY
INST
APU
OFF START
RUN
CFO0701002_011
L BATT
LEGEND
Fuse
Circuit Breaker
Contactor
Current Sensor
APU
GEN
R GEN
STANDBY
INSTRUMENT
BATT
EXT PWR
HYD
GEN
BUS (CBP)
APU GEN
L GEN
HYD GEN
GND
SERVICE
R BATT
BUS TIE
V
2
ELECTRICAL
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DIRECT CURRENT SYSTEM (DC) (Cont)
DC PRIMARY ARCHITECTURE
CFO0701002_006
LEFT
GEN
L BATT
OFF
EXT
PWR
APU
APU
STRT
RIGHT
GEN
LEFT
AUX BUS
LEFT
MAIN BUS
LEFT
ESS BUS
RIGHT
ESS BUS
RIGHT
MAIN BUS
RIGHT
AUX BUS
LBAT BUS
RBAT BUS
R BATT
OFF
R GEN
OFF
L GEN
OFF
CAGE
STD
B
R
T
D
I
M
BARO
240
220
200
180
M. 47
1013.2 hPa
29.92 in
130
00
128
40
20
00
9
1
10
10
20
ILS
125
00
CONTACTOR
FUSE
CIRCUIT SENSOR
STANDBY
INSTRUMENT
BATTERY
OFF
STBY
INST
OFF
ON
EXT PWR
AVAIL
PWR
BUS TIE
HYD GEN
ON
REV 1
ELECTRICAL
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CSP 100-6
REV 2
CONTROLS AND INDICATIONS
EXTERNAL POWER CONTROL PANEL
CFO0501002_006
EXTERNAL POWER
CONTROL PANEL
ON
Gnd
Service
EXT DC
AVAIL
IN USE
APU Shutdown
Lamp
Test
V
2
ELECTRICAL
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07-01-15
CONTROLS AND INDICATIONS (Cont)
ELECTRICAL SUMMARY PAGE
CFO0701002_009
CAS
CKLST
SKIP
FRMT
TFC
TR/WX
ENTER
A/ICE
FLT FUEL
HYD
LR
ECS
AUTO
PLAN
SHLDR SIDE
ELEC
SUMRY
REV 1
ELECTRICAL
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CSP 100-6
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CONTROLS AND INDICATIONS (Cont)
ELECTRICAL CONTROL PANEL
With optional Hydraulic Motor Driven Generator (HMDG) system.
CFO0701002_010
EXT PWR
L BATT R BATT
OFF
AVAIL
ON
ELECTRICAL
OFF
OFF
OFF
ON
BUS TIE
L GEN
APU GEN
R GEN
R ESS
R MAIN R AUX
L ESS
L AUX
L MAIN
STBY
INST
OFF
CFO0701002_003
EXT PWR
L BATT
R BATT
OFF
AVAIL
ON
ELECTRICAL
OFF
OFF
OFF
ON
BUS TIE
L GEN APU GEN
R GEN
R ESS
R MAIN R AUX
L ESS
L AUX
L MAIN
STBY
INST
OFF
ON
HYD GEN
REV 2
ELECTRICAL
Sep 13/2004 Flight Crew Operating Manual Volume 2
REV 1 CSP 100-6
07-01-17
CONTROLS AND INDICATIONS (Cont)
ELECTRICAL SYNOPTIC PAGE
CFO0701002_007
CAS
CKLST
SKIP
FRMT
TFC
TR/WX
ENTER
SUMRY
A/ICE
FLT FUEL
HYD
LR
ECS
600 600
93.0 61.0
NI
MACH
HOLD
ITT
N2
OIL PRESS
OIL TEMP
FF PPH
84.7
46
115
7300
84.7
46
115
7300
APU RPM
250
APU EGT
FUEL QTY LBS
TOTAL
12000
6000 6000
S
T
A
R
T
S
T
A
R
T
STAB
AIL
LWD
RWD
RUD
L
R
NU
ND
6.6
SPOILERS
CAB ALT
CAB RATE
7300
1000
MFD CONTROL
O
85.0 MCT 85.0 MCT
TRIM
V
T
600 600
93.0 61.0
NI
MACH
HOLD
ITT
N2
OIL PRESS
OIL TEMP
FF PPH
84.7
46
115
7300
84.7
46
115
7300
APU RPM
100
250
APU EGT
FUEL QTY LBS
TOTAL
12000
6000 6000
S
T
A
R
T
S
T
A
R
T
STAB
AIL
LWD
RWD
RUD
L
R
NU
ND
6.6
SPOILERS
CAB ALT
CAB RATE
7300
1000
MFD CONTROL
COM1
NAV1
ATC1/TCAS
ADF1
HF1
COM3
COM2
118.000
108.00 1799.5
118.000
118.000
118.000
118.000
2.0000
190.0108.00118.000
STBY
ABV
TX
O
2.0000
AM
85.0 MCT 85.0 MCT
TRIM
V
T
25
ELECTRICAL
° C
35
° C
26
24.0
V
L BATT
24.5
V
R BATT
0.0
V
GEN
HYD
L ESS BUS
L MAIN BUS
R ESS BUS
R MAIN BUS
BUS TIE
20
A
30
A
0
A
28.5
V
28.0
V
GEN GENGEN
0.0
V
APU
R AUX BUS
L AUX BUS
ELEC
1200
AUTO PLAN
SHLDR SIDE
PWR
EXT
24.1
V
DN
GEAR
FLAPS
0
DN DN
REV 1
ELECTRICAL
Volume 2 Flight Crew Operating Manual Sep 14/2005
07-01-18
CSP 100-6
REV 4
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 MEANING
AURAL
WARNING
L (R)
BATT OVERHEAT
TO/LAND
Respective battery internal temperature
exceeded 70 ° C
ESSENTIAL POWER
ONLY
The essential buses are powered by the batter-
ies only. AUX and MAIN buses are automati-
cally deactivated in flight
APU GEN FAIL TO/LAND The APU generator failed
APU GEN OVERLOAD TO/LAND
The
APU generator has exceeded 500 amp
L (R) BATT FAIL
TO/LAND
Either the respective battery contactor failed or
the battery has been automatically discon-
nected for overheat protection
ELEC HYD GEN FAIL TO/LAND
The hydraulic generator has failed to come on-
line
ELECTRICAL FAULT TO/LAND
An electrical system failure has occurred that
prevents display of electrical indications
L (R) GEN FAIL
TO/LAND
The affected generator has failed. If the APU
generators not on line, the BUS-TIE will auto-
matically 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
L (R) AUX BUS FAIL
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
4
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BOMBARDIER Challenger 300 Operating instructions
- Type
- Operating instructions
The BOMBARDIER Challenger 300 is a versatile and powerful aircraft designed to meet the needs of discerning travelers. With a range of up to 3,450 nautical miles and a top speed of Mach 0.83, the Challenger 300 can connect you to destinations around the world. Its spacious cabin, advanced avionics, and smooth ride make it the perfect choice for business or leisure travel.
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