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ELECTRICAL
Table of Contents
May 06/2005 Flight Crew Operating Manual Volume 2REV 2 CSP 100-6 07-00-01
Introduction ......................................................................................................................... 07-01-01Electrical System................................................................................................................. 07-01-03
Description ................................................................................................................. 07-01-03Components and Operation....................................................................................... 07-01-03Engine and APU Generators ..................................................................................... 07-01-03External Power........................................................................................................... 07-01-03Batteries..................................................................................................................... 07-01-05Power Centers ........................................................................................................... 07-01-05Secondary Power Centers ......................................................................................... 07-01-06Hydraulic Motor Driven Generator (HMDG) (Optional) .............................................. 07-01-06Circuit Breaker Panels ............................................................................................... 07-01-06Cockpit Floor Heaters ................................................................................................ 07-01-06CB 1 Pilot Circuit Breaker Panel (Typical) ................................................................. 07-01-07CB 2 Copilot Circuit Breaker Panel (Typical) ............................................................. 07-01-08CB 3 Left Side Equipment Rack Circuit Breaker Panel (Typical)............................... 07-01-09CB 4 Right Side Equipment Rack Circuit Breaker Panel (Typical) ............................07-01-10CB 5 Left DC Power Center Circuit Breaker Panel (Typical) ..................................... 07-01-11CB 6 Right DC Power Center Circuit Breaker Panel (Typical)................................... 07-01-11
Direct Current System.........................................................................................................07-01-12DC Electrical System ................................................................................................ 07-01-12DC Primary Architecture ............................................................................................07-01-13
Controls and Indications...................................................................................................... 07-01-14External Power Control Panel.................................................................................... 07-01-14Electrical Summary Page........................................................................................... 07-01-15Electrical Control Panel.............................................................................................. 07-01-16Electrical Synoptic Page ............................................................................................07-01-17EICAS Messages....................................................................................................... 07-01-18
REV 2
ELECTRICAL
Sep 13/2004 Flight Crew Operating Manual Volume 2REV 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 voltpower to a split bus electrical system. An automatic electrical load-shedding system prevents generator overload andprolongs 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 optionalhydraulically driven electrical generator is available to provide electrical power generation in the event all engine and APUgenerator 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 inthe 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
Volume 2 Flight Crew Operating Manual Sep 13/200407-01-02 CSP 100-6 REV 1
INTRODUCTION (Cont)
RIGHT CIRCUITBREAKER PANEL
RIGHT SECONDARYPOWER CENTER
LEFT CIRCUITBREAKER PANEL LEFT SECONDARY
POWER CENTER
RIGHT DC POWER CENTER
RIGHTBATTERY
LEFTGENERATOR
APUGENERATOR
EXTERNALDC CONTROLPANEL
RIGHTGENERATOR
LEFT DC POWER CENTER
LEFTBATTERY
CF
O07
0100
2_00
1
ELECTRICAL
May 06/2005 Flight Crew Operating Manual Volume 2REV 2 CSP 100-6 07-01-03
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 andground 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 provideenough 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 generatorsare 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 thestandby 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 totalgenerated 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 aftequipment 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 inthe front fuselage of the aircraft and are fed by the distribution buses of the DCPCs. They distribute electricalpower 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 APUgenerator 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 theairplane. A third identical generator is installed on the APU. All three generators are air cooled and include an integratedfan. The engine-driven generators automatically come online after the engines are running, the GPU is disconnected, andthe 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, andthe right generator recharges the right main battery. The generators supply DC power to all DC powered equipment on theairplane 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 justbelow the engine pylon. The anti-flash contactor that connects the output of the GPU to the aircraft electrical system closesonly 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 switchilluminates if the GPU is within acceptable parameters. Depressing the EXT PWR switch when the green AVAIL light isilluminated closes the GPU antiflash contactor, connecting the GPU. The ON caption illuminates, and the green AVAILcaption 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
Volume 2 Flight Crew Operating Manual May 06/200507-01-04 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 theGPU is selected, they drop offline. Engine-driven generators automatically come online after engine start, but not if theGPU 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 indicationof 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 appearwhenever 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 PWRL 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
STBYINST
OFF
EXT PWRL 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
STBYINST
OFF
ON
HYD GEN
EV 2
ELECTRICAL
May 06/2005 Flight Crew Operating Manual Volume 2REV 2 CSP 100-6 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 therest of the aircraft and provides power to the APU starter. The bus tie closes and the left battery provides power to the restof the aircraft for emergency operation during total generator failure. They also provide power to the battery buses evenwhen 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 connectedto 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 theMFD.
During a total generator failure, the aircraft batteries provide power for necessary essential equipment for alimited duration.
Standby Instrument power is supplied by a dedicated 24 vdc battery. The standby instrument is activated by a separateSTBY 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 largeenough to result in a APU GEN OVERLOAD, or L (R) GEN OVERLOAD caution CAS message for a short time as thebatteries 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 powersources available
- Ensure the coupling of the two channels on the ground when only batteries or external DC power are available, orin 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
Volume 2 Flight Crew Operating Manual May 06/200507-01-06 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 thedistribution buses of the direct current power centers and distribute electrical power to the loads in the front fuselage of theaircraft.
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 islost. The HMDG is powered by the left hydraulic system. It is rated for 65 amp and consists of a hydraulic motor that drivesa 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 busesof 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. Eachis 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 thefloor 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
May 06/2005 Flight Crew Operating Manual Volume 2REV 2 CSP 100-6 07-01-07
CB1 PILOT CIRCUIT BREAKER PANEL (TYPICAL)
A
C
B
D
E1110987654321 1312 1514
L CH AR CH A CTRL 1 CTRL 2CH ACTRL PWR
L TRFADEC
ENGINEFIREDET
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 1AHF 1COM 1
AUTO FLIGHTCOMMUNICATION
INBD
BRAKES
WOW A/
RET/EXT
NWS
PWR 1
R DC
PUMPL SOVL IND
LDG GEARHYDRAULIC
L MFDL 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 ICEL WINDSHIELDL AOA
15 15 7.5 7.553 253 3 3 3 3 5
335 7.5 3 5 57.53 7.53 7.5 3 3
5 5 5 53 3 0.53 3 10 103
53 35 5 3 5 5
20 5 15 10 7.5 15 5 0.5 5 5
L WING
BLD LK
L ICE
DET
L STBYSTATIC
L PROBE
CTRL
WOW
B
3
CF
O0106002_006
5 3 0.5
3 5
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 LIML PWR
SPOILER
CTRL 1
PRI STABFLAPSTALL
FLIGHT CONTROLS
L SHKR PUSHER L IND CTRL
ELECTRICAL
Volume 2 Flight Crew Operating Manual May 06/200507-01-08 CSP 100-6 REV 2
ELECTRICAL SYSTEM (Cont)
CB2 COPILOT CIRCUIT BREAKER PANEL (TYPICAL)
A
C
B
D
E123456789101112131415
CTRL 2 CTRL 1 L CH B R CH B CH B PWR CTRL
R TR FADECENGINE FIRE
DETFUEL
R PUMP
TAWS XPDR 2 CDU 2 GPS 2 DME 2 NAV 2
NAVIGATION
AVIONICS
R SHKR R PWRSPOILERCTRL 2 SEC
FLAP STALLFLIGHT CONTROLS APU
R FGP/SERVOS R IAPS
RIU 2B/AURAL RIU 1A HF 2 COM 2
AUTO FLIGHT COMMUNICATION
OUT BDBRAKES
WOWA/RET
NWSPWR 2
L DCPUMP 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 ENGR WINGBLD LK PWR CTRL
R ICEDET CASE VANE
R STBYSTATIC
STBYPITOT R PITOT
R PROBECTRL
INDICATING/RECORDING
ANTI ICER WINDSHIELD R AOA
CF
O01
0600
2_00
5
7.5 7.5 15 15 5 25 3 3 3 3
3 5 3 3 5 7.5 5 3 3 3 7.5 3
5 5 5 5 0.5 3 3 3
53 3 3 5 5 3 5 5
5 3 35 0.5 5 15 7.5 10 5 15 20 3
53
SEC STABTRIM/
RUD LIMAIL
TRIMRUDTRIM
R IND/CTRL
R AUDIOPWR 1
3
STBY INSTBATT TEST
STBY INST/BATT R MFD R DCP R PFD
ATTHDG 2
AIRDATA 2
3 10 3 3 310
WOWB/EXT
3
VALVES /TRIM PWR 1 VALVE HEATERR BLEED PRESS 2 ECS XVLV XBLEED CARGO
ALT LIM/ENVIRONMENTAL
A
C
B
D
E
ELECTRICAL
May 06/2005 Flight Crew Operating Manual Volume 2REV 2 CSP 100-6 07-01-09
ELECTRICAL SYSTEM (Cont)
CB3 LEFT SIDE EQUIPMENT RACK CIRCUIT BREAKER PANEL (TYPICAL)
3 4 5 6 7 81 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
AVIONICSDATA
LOADER
IAPS
FAN COM 3
LIGHTNING
DET
CF
O0106002_004
3 3 3 3
3 3 3 3 3 3 15
3
3
5 25 5
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
NAVELT/
AUTO DEP
THERAPTC
RAM AIR/
OFV PWR2
L FOOT
WARM PWR CTRL
ELECTRICAL
Volume 2 Flight Crew Operating Manual May 06/200507-01-10 CSP 100-6 REV 2
ELECTRICAL SYSTEM (Cont)
CB4 RIGHT SIDE EQUIPMENT RACK CIRCUIT BREAKER PANEL (TYPICAL)
A
C
B
D
E
F
CF
O0106002_003
345678 129
TR OUTBD
WHL SPD
ENG RUN
CH B
SYNC/
IGN B
ENG
START B
ENGINE
NORM
ELEC
R ENG
SOV
XFER
VALVEQTY 2
FUEL
R FORCE
SENSOR
PEDAL
ADJAUTO FLTTRIM
MSTR DISC
FLIGHT CONTROL
CABINLIGHTS
BUS
CTRL
PWR1
PWR2
INDICATING/RECORDING
3 33 3
3 33 3533
3
5
50 501035 10
NORM
20
HYD GEN
APU GEN R GENR BATT
SEC BUS
7.53
PWR/
TEST HTR
0.53
ENVIRONMENTAL
PWRCTRL
R SIDE WINDOW
ANTI ICE
55355 25
NOSE GEAR WING
STROBE
R CKPT
/CBPCABINTAXILDGLOGONAV
NAV
101057.5 5 5 3
PRI
SEC
SATCOM3rd AUDIO OXYGEN
/INDMAN DEPLAV 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
May 06/2005 Flight Crew Operating Manual Volume 2REV 2 CSP 100-6 07-01-11
ELECTRICAL SYSTEM (Cont)
CB5 LEFT DC POWER CENTER CIRCUIT BREAKER PANEL (TYPICAL)
CB6 RIGHT DC-POWER CENTER CIRCUIT BREAKER PANEL (TYPICAL)
2 345678
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
AVNXENGINEFIREXFCTLLIGHTS
ELECTRICAL
EXT BAG/
AFT BAY
5 5 25 5 3 3
7.525 5
CF
O0106002_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 2 3 4 5 6 8
A
C
B
1 2
3 5 5 5 25 5
5 7.5 25 3 3
CF
O0106002_001
7
SATCOM
CTRL
PWR 1 PWR 2
ENVIRONMENT
15 15
BAG COMP HTR
FAN
PWR 2
AVNX
35
REV 2
ELECTRICAL
Volume 2 Flight Crew Operating Manual May 06/200507-01-12 CSP 100-6 REV 2
DIRECT CURRENT SYSTEM (DC)
DC ELECTRICAL SYSTEM
RB
AT
T
AP
US
TA
RT
ER
LEF
TG
EN
RIG
HT
GE
N
EX
TP
WR
LB
AT
T
GR
OU
ND
SE
RV
ICE
BU
SL
BA
TT
BU
S (
DC
PC
)
L A
UX
BU
S (
DC
PC
)L
MA
INB
US
(D
CP
C)
L E
SS
BU
S (
DC
PC
)
L B
AT
TB
US
(S
PC
)L
AU
XB
US
(S
PC
)L
MA
INB
US
(S
PC
)L
ES
SB
US
(S
PC
)
L E
SS
L M
AIN
BU
S (
CB
P)
L B
AT
TB
US
(C
BP
)
R E
SS
BU
S (
CB
P)
R M
AIN
BU
S (
CB
P)
R B
AT
TB
US
(C
BP
)
CB
2-C
6S
TB
Y IN
ST
R E
SS
BU
S (
SP
C)
R M
AIN
BU
S (
SP
C)
R A
UX
BU
S (
SP
C)
R B
AT
TB
US
(S
PC
)
R B
AT
TB
US
(D
CP
C)
R E
SS
BU
S (
DC
PC
)R
MA
INB
US
(D
CP
C)
R A
UX
BU
S (
DC
PC
)
L S
EC
ON
DA
RY
PO
WE
R C
EN
TE
R
L C
IRC
UIT
BR
EA
KE
RP
AN
EL
L D
CP
CR
DC
PC
R S
EC
ON
DA
RY
PO
WE
R C
EN
TE
R
ST
AN
DB
YIN
ST
RU
ME
NT
R C
IRC
UIT
BR
EA
KE
RP
AN
EL
ST
BY
INS
T
AP
U
OF
F
ST
AR
T
RU
N
CF
O07
0100
2_01
1
L B
AT
T
LE
GE
ND
Fus
e
Circ
uit B
reak
er
Con
tact
or
Cur
rent
Sen
sor
AP
UG
EN
R G
EN
ST
AN
DB
YIN
ST
RU
ME
NT
BA
TT
EX
T P
WR
HY
DG
EN
BU
S (
CB
P)
AP
U G
EN
L G
EN
HY
D G
EN
GN
DS
ER
VIC
E
R B
AT
TB
US
TIE
V 2
ELECTRICAL
Sep 13/2004 Flight Crew Operating Manual Volume 2REV 1 CSP 100-6 07-01-13
DIRECT CURRENT SYSTEM (DC) (Cont)
DC PRIMARY ARCHITECTURE
CF
O07
0100
2_00
6
LEFTGEN
L BATT
OFFEXTPWR APU
APUSTRT
RIGHTGEN
LEFTAUX BUS
LEFTMAIN BUS
LEFTESS BUS RIGHT
ESS BUS
RIGHTMAIN BUS
RIGHTAUX BUS
LBAT BUS
RBAT BUS
R BATT
OFF
R GEN
OFF
L GEN
OFF
CAGE
STD
BRT
DIM
BARO
240
220
200
180
M. 47
1013.2 hPa
29.92 in
130 00
128402000
9
1
10
10
20
ILS
125 00
CONTACTOR
FUSE
CIRCUIT SENSOR
STANDBYINSTRUMENT
BATTERY
OFF
STBYINST
OFF
ON
EXT PWR
AVAIL
PWR
BUS TIE
HYD GEN
ON
REV 1
ELECTRICAL
Volume 2 Flight Crew Operating Manual May 06/200507-01-14 CSP 100-6 REV 2
CONTROLS AND INDICATIONS
EXTERNAL POWER CONTROL PANEL
CF
O0501002_006
EXTERNAL POWER
CONTROL PANEL
ON
GndService EXT DC
AVAIL
IN USE
APU ShutdownLampTest
V 2
ELECTRICAL
Sep 13/2004 Flight Crew Operating Manual Volume 2REV 1 CSP 100-6 07-01-15
CONTROLS AND INDICATIONS (Cont)
ELECTRICAL SUMMARY PAGE
CF
O0701002
_009
CAS
CKLST SKIP
FRMT TFC TR/WX ENTER
A/ICE FLT FUEL HYD
L R
ECS
AUTO PLAN
SHLDR SIDE
ELEC
SUMRY
REV 1
ELECTRICAL
Volume 2 Flight Crew Operating Manual May 06/200507-01-16 CSP 100-6 REV 2
CONTROLS AND INDICATIONS (Cont)
ELECTRICAL CONTROL PANEL
With optional Hydraulic Motor Driven Generator (HMDG) system.
CF
O0701002_010
EXT PWRL 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
STBYINST
OFF
CF
O0701002_
003
EXT PWRL 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
STBYINST
OFF
ON
HYD GEN
REV 2
ELECTRICAL
Sep 13/2004 Flight Crew Operating Manual Volume 2REV 1 CSP 100-6 07-01-17
CONTROLS AND INDICATIONS (Cont)
ELECTRICAL SYNOPTIC PAGE
CF
O0701002_007
CAS
CKLST SKIP
FRMT TFC TR/WX ENTER SUMRY
A/ICE FLT FUEL HYD
L R
ECS
600 600
93.0 61.0NI
MACH
HOLD
ITT
N2OIL PRESS
OIL TEMP
FF PPH
84.7
46
115
7300
84.7
46
115
7300
APU RPM250APU EGT
FUEL QTY LBS
TOTAL 120006000 6000
START
START
STAB AIL
LWD RWDRUD
L R
NU
ND
6.6
SPOILERS
CAB ALT
CAB RATE
7300
1000
MFD CONTROL
O
85.0 MCT 85.0 MCT TRIM
VT
600 600
93.0 61.0NI
MACH
HOLD
ITT
N2OIL PRESS
OIL TEMP
FF PPH
84.7
46
115
7300
84.7
46
115
7300
APU RPM 100250APU EGT
FUEL QTY LBS
TOTAL 120006000 6000
START
START
STAB AIL
LWD RWDRUD
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
118.000 118.0002.0000190.0108.00118.000 STBY
ABV
TX
O
2.0000 AM
85.0 MCT 85.0 MCT TRIM
VT
25
ELECTRICAL
° C35 ° C26
24.0 V
L BATT
24.5 V
R BATT0.0 V
GENHYD
L ESS BUS
L MAIN BUS
R ESS BUS
R MAIN BUS
BUS TIE
20 A 30 A0 A
28.5 V 28.0 V
GEN GENGEN
0.0 V
APU
R AUX BUSL AUX BUS
ELEC
1200
AUTO PLAN
SHLDR SIDE
PWREXT
24.1V
DN
GEARFLAPS 0
DN DN
REV 1
ELECTRICAL
Volume 2 Flight Crew Operating Manual Sep 14/200507-01-18 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 MEANINGAURAL
WARNING
L (R)BATT OVERHEAT
TO/LANDRespective 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 FAILTO/LAND
Either the respective battery contactor failed or the battery has been automatically discon-nected for overheat protection
ELEC HYD GEN FAIL TO/LANDThe hydraulic generator has failed to come on-line
ELECTRICAL FAULT TO/LANDAn electrical system failure has occurred that prevents display of electrical indications
L (R) GEN FAILTO/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 FAILTO/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/LANDAn electrical system fault occurred, resulting in loss of redundancy in the display of electrical indications
4
ELECTRICAL
Sep 14/2005 Flight Crew Operating Manual Volume 2REV 4 CSP 100-6 07-01-19
STBY INST BATT FAULT
TO/LAND
At least one of the following has occurred:- Standby instrument heater is inoperative- Standby instrument battery charger is inopera-
tive- Standby instrument battery temperature is
greater than 80 ° C- At least two cells of the standby instrument
battery have failed
APU GEN OFF APU GEN switch has been selected OFF
L (R) BATT OFFThe 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 ONThe optional hydraulic motor driven generator (HMDG) has been activated
L (R) GEN OFF The affected engine generator switch has been selected OFF
MESSAGE INHIBITS MEANINGAURAL
WARNING
REV 4
