Bombardier Challenger 605 - Electrical
Bombardier Challenger 605 - Electrical
GENERAL
The Challenger 605 primarily uses 115-volt AC power, and also 28-volt DC electrical power.
Engine-driven integrated drive generators (IDGs) supply the primary source of AC electrical power. A
generator mounted on the auxiliary power unit (APU) provides an alternate source of AC electrical
power. In flight, if a total loss of AC power occurs, the air-driven generator (ADG) is deployed from
the right side of the forward fuselage to provide an emergency source of AC electrical power.
External AC electrical power is supplied through an electrical power receptacle, located on the right
side of the forward fuselage.
Various aircraft systems and components require DC electrical power for operation. DC electrical
power needs are primarily supplied by four transformer rectifier units (TRU) mounted in the nose
compartment. The aircraft is equipped with two nickel-cadmium (NiCad) batteries that store and
provide a source of DC electrical power for normal and emergency operations. The main battery is
located in the nose section, the APU battery is in the aft equipment bay.
The aircraft is capable of accepting 28-volt DC external electrical power through a DC power
receptacle, installed on the rear fuselage below the right engine.
Five circuit breaker panels provide power distribution. Four circuit breaker panels are located in the
flight compartment, and the fifth panel is in the aft equipment bay.
Control and operation are accomplished through the ELECTRICAL POWER panel, located on the left
side of the overhead panel. AC and DC electrical system information is provided on the EICAS.
AC Electrical Power Sources
Figure 07−10−1
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Bombardier Challenger 605 - Electrical
GENERAL (CONT'D)
DC Electrical Power Sources
Figure 07−10−2
ALTERNATING CURRENT (AC) SYSTEM
Description
Three AC generators provide AC power for the aircraft electrical systems. Two engine-driven
generators power all AC buses during normal operations. An APU generator provides a source of
AC electrical power when the aircraft is on the ground with the engines off, and during flight if both
engine-driven generators become inoperative.
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Bombardier Challenger 605 - Electrical
ALTERNATING CURRENT (AC) SYSTEM (CONT'D)
AC Electrical System
Figure 07−10−3
Components and Operation
Integrated Drive Generators (IDGs)
Two engine-driven IDGs supply 115-volt AC, 400-Hz, three-phase electrical power to the AC
buses. The IDG consists of two subcomponents, a constant speed drive and an electrical
generator.
The generators are identified on the EICAS AC electrical synoptic page by the symbols GEN 1
and GEN 2 (see Figure 07−10−4). The nominal rating of each generator is 30 kilovolt-amperes
(kVA) to an altitude of 35,000 feet MSL, then 25 kVA to 41,000 feet MSL. In the event of a
single generator failure, the remaining generator is capable of supplying sufficient power for
operation of the main systems.
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Bombardier Challenger 605 - Electrical
ALTERNATING CURRENT (AC) SYSTEM (CONT'D)
The generators are controlled by two-position GEN 1 or GEN 2 switches, located on the
ELECTRICAL POWER panel. Selecting GEN 1 or GEN 2 switch to ON connects the respective
generator to the main AC buses, provided they are operating normally. Selecting the switches to
OFF/RESET will disconnect the respective generator from the main AC buses. The OFF/RESET
position can also be used to reset the generator control circuit when a fault occurs.
Generator Control Unit
Each IDG is controlled and monitored by its respective generator control unit (GCU). The
GCUs provide protection and bus priority logic during normal and non-normal operations. The
engine generator is tripped off and removed from the AC buses if any of the following
conditions occur:
• Over- and undervoltage;
• Over- and underfrequency; or
• Generator and bus overcurrent.
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Bombardier Challenger 605 - Electrical
ALTERNATING CURRENT (AC) SYSTEM (CONT'D)
GEN 1 and GEN 2 Power
Figure 07−10−4
APU Generator
The APU generator supplies 115-volt AC, 400-Hz, three-phase electrical power to the AC buses
during ground operations with the engines off. The APU generator may also be used in flight as
a backup power source to the AC buses following a failure of both engine generators. The APU
generator is mounted on the APU generator adapter, and is driven at a constant speed,
maintaining its frequency output at 400 Hz.
The APU generator is identified on the AC ELECTRICAL synoptic page by the symbol GEN
above the APU icon (see Figure 07−10−5). The nominal rating of the APU generator is 30 kVA
from sea level up to the APU’s maximum operating altitude of 20,000 feet MSL.
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Bombardier Challenger 605 - Electrical
ALTERNATING CURRENT (AC) SYSTEM (CONT'D)
The two-position APU GEN switch, located on the ELECTRICAL POWER panel, controls the
APU generator. Selecting the APU GEN switch to ON connects the APU generator to the main
AC buses, providing it is operating normally. Selecting the switch to OFF/RESET disconnects
the APU generator from the main AC buses. The OFF/RESET position can also be used to
reset the generator control circuit when a fault occurs.
NOTE
Use of the APU generator in flight is permitted when one main
generator has failed or is off-line.
Generator Control Unit
The APU generator is controlled and monitored by the APU generator control unit (GCU). The
APU GCU, in conjunction with the engine GCUs, provide protection and bus priority logic
during normal and non-normal operations. The APU GENERATOR is tripped off and removed
from the AC buses if any of the following conditions occur:
• Over- and undervoltage;
• Over- and underfrequency; or
• Generator and bus overcurrent.
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Bombardier Challenger 605 - Electrical
ALTERNATING CURRENT (AC) SYSTEM (CONT'D)
APU Power
Figure 07−10−5
External AC Electrical Power
The aircraft is capable of being powered by an external AC power source when both engines
and APU are off. External AC electrical power is connected at an external AC receptacle,
located on the forward right side of the fuselage.
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Bombardier Challenger 605 - Electrical
ALTERNATING CURRENT (AC) SYSTEM (CONT'D)
External AC Receptacle
Figure 07−10−6
Operation
External AC ground power is controlled by the EXT POWER switch/light, located on the
ELECTRICAL POWER panel. When connected, the external AC ground power is checked by
an external power monitor for proper voltage, frequency, and phase. When the external power
is within limits, the green AVAIL annunciator on the EXT POWER switch/light illuminates.
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Bombardier Challenger 605 - Electrical
ALTERNATING CURRENT (AC) SYSTEM (CONT'D)
External AC Electrical Power Available
Figure 07−10−7
When the EXT POWER switch/light is pressed with the AVAIL annunciator illuminated,
external AC electrical power is connected to the aircraft main AC buses via the auxiliary
power/external power contactor. The IN USE annunciator then illuminates.
External AC ground power is identified on the AC ELECTRICAL synoptic page by the symbol
EXT AC. This symbol appears only if external AC power is connected to the aircraft.
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Bombardier Challenger 605 - Electrical
ALTERNATING CURRENT (AC) SYSTEM (CONT'D)
External AC Electrical Power In Use
Figure 07−10−8
AC ELECTRICAL POWER DISTRIBUTION
Description
115-volt AC electrical power, from the aircraft generators and APU generator, is distributed to five
AC buses through circuit breaker panels. Monitoring of system status is done using the AC
ELECTRICAL synoptic page.
The aircraft AC bus system consists of the following five buses:
• AC BUS 1 (Main);
• AC BUS 2 (Main);
• AC ESS BUS (Essential);
• AC UTILITY BUS 1; and
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Bombardier Challenger 605 - Electrical
AC ELECTRICAL POWER DISTRIBUTION (CONT'D)
•
AC UTILITY BUS 2.
AC ELECTRICAL Synoptic Page
Figure 07−10−9
Components and Operation
AC BUS 1 and AC BUS 2
AC BUS 1 and AC BUS 2 are the main AC buses of the aircraft, and receive power from any of
the three generators, or from external AC power. AC BUS 1 normally supplies power to the AC
ESS BUS and AC UTIL BUS 1. AC BUS 2 normally powers AC UTIL BUS 2.
Bus Priority
AC BUS 1 and AC BUS 2 are protected by a bus priority logic, to ensure that the buses remain
powered at all times. The generator control units (GCUs) determine the bus priority for AC
BUS 1 and AC BUS 2 via the generator line contactors (GLCs) and generator transfer
contactors (GTCs). The bus priority logic for AC BUS 1 and AC BUS 2 is as follows:
• On-side engine-driven generator (example: AC BUS 1 powered by GEN 1);
• APU generator;
• Cross-side engine-driven generator (example: AC BUS 1 powered by GEN 2); and
• External AC power.
According to the above priority logic, the GLCs and GTCs will automatically tie the main AC
buses to any of the available AC power sources, to ensure that the main AC buses remain
powered at all times.
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Bombardier Challenger 605 - Electrical
AC ELECTRICAL POWER DISTRIBUTION (CONT'D)
AC BUS 1 (2) Automatic Transfer (AUTOXFER) Switch/Lights
The flight crew may manually inhibit the automatic bus transfer priority logic by pressing the
appropriate AUTOXFER switch/light, located on the ELECTRICAL POWER panel. This
prevents the corresponding AC BUS from being powered by any source except its on-side
engine-driven generator. This may be used to isolate a main AC bus in the event of an
electrical emergency (example: electrical smoke or fire). Selection of the AUTOXFER
switch/light is indicated by illumination of the corresponding white OFF annunciator on the
switch/light, and white AUTO XFER OFF icon on the AC electrical synoptic page.
AC BUS Automatic Transfer
Figure 07−10−10
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Bombardier Challenger 605 - Electrical
AC ELECTRICAL POWER DISTRIBUTION (CONT'D)
Should a bus fault or generator overcurrent condition occur on a main AC bus, the automatic
bus transfer priority logic will be inhibited, isolating the fault from the remaining AC electrical
system. This condition is indicated by the AC 1 (2) AUTOXFER caution EICAS message,
illumination of the corresponding amber FAIL annunciator on the AUTOXFER switch/light, and
the amber AUTO XFER FAIL icon on the AC ELECTRICAL synoptic page.
AC BUS Automatic Transfer Fail
Figure 07−10−11
AC ESS (Essential) Bus
The AC ESS BUS supplies power to the equipment essential for flight. It is normally powered by
AC BUS 1, but may also be powered by AC BUS 2 or the ADG BUS. The AC ESS BUS supplies
power to ESS TRU 1, which provides DC power to the DC ESS BUS and the BATT BUS.
Refer to the ADG section in this chapter for information on the ADG BUS.
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Bombardier Challenger 605 - Electrical
AC ELECTRICAL POWER DISTRIBUTION (CONT'D)
AC ESS Bus Transfer
If a loss of power on AC BUS 1 is sensed, the AC ESS BUS is automatically transferred to AC
BUS 2. When an automatic transfer to AC BUS 2 occurs, the AC ESS XFER switch/light
located on the ELECTRICAL POWER panel illuminates and the AC ESS ALTN status EICAS
message appears.
If the automatic transfer fails to occur, the AC ESS BUS can be manually transferred to AC
BUS 2 by pressing the AC ESS XFER switch/light.
AC Essential Bus on Alternate Source
Figure 07−10−12
AC Utility Buses
AC UTILITY BUS 1 and 2 receive power from AC BUS 1 and 2 respectively. The AC utility
buses supply AC power to nonessential cabin equipment.
Utility Bus Shedding
During single-generator operation in flight, AC UTILITY BUS 1 and 2 are automatically load
shed, to reduce the electrical load on the remaining generator.
During ground operations, AC UTILITY BUS 1 and 2 are load shed when a single generator (or
external AC power only) is supplying AC power, and the flaps are not retracted.
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Bombardier Challenger 605 - Electrical
AC ELECTRICAL POWER DISTRIBUTION (CONT'D)
Manual load shedding of utility buses can be accomplished by pressing the AC UTILITY
switch/light on the ELECTRICAL POWER panel.
Load shedding is indicated by the illumination of the AC UTILITY switch/light and the
respective bus SHED icons on the AC ELECTRICAL synoptic page.
AC Utility Bus Shedding
Figure 07−10−13
AIR-DRIVEN GENERATOR (ADG)
Description
The ADG provides 115-volt, 400-Hz, 15-kVA power to the AC ESS BUS and 3B hydraulic pump, in
the event of a complete loss of AC power in flight. The ADG is located in the forward right fuselage
beside the nose gear, and is deployed automatically or manually. Once deployed, the ADG can
only be restowed when the aircraft is on the ground.
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Bombardier Challenger 605 - Electrical
AIR-DRIVEN GENERATOR (ADG) (CONT'D)
Air-Driven Generator
Figure 07−10−14
Components and Operation
Air-Driven Generator
The ADG consists of an AC generator mounted on a pivoted support leg, and a variable-pitch
two-bladed propeller that turns in the airstream. The constant speed of the ADG is achieved by
using a counterweight system to control the propeller pitch angle. This ADG is commonly
referred to as the “dry ADG”.
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Bombardier Challenger 605 - Electrical
AIR-DRIVEN GENERATOR (ADG) (CONT'D)
An internal heating element is installed around the circumference of the stator, to protect against
condensation or frost which may form when a cold soaked ADG enters a hot, high humidity
environment.
ADG Generator Control Unit
The ADG generator is controlled and monitored by the ADG generator control unit (GCU). The
ADG GCU provides the following functions:
• Monitors and controls ADG voltage output;
• Protects against overvoltage, overfrequency and underfrequency to the ADG BUS; and
• Provides a signal to the ADG auto deploy control unit, to energize the HYD PUMP 3B
transfer contactor, emergency AC transfer contactor, and emergency DC transfer
contactor when the ADG voltage and frequency are within limits.
ADG AUTO DEPLOY CONTROL Unit
Located on the lower center pedestal, the ADG AUTO DEPLOY CONTROL unit controls the
automatic deployment of the ADG.
Automatic deployment of the ADG occurs when:
• Both AC BUS 1 and AC BUS 2 become unpowered; and
• The aircraft is in flight.
Another ADG deployment prerequisite is that one of the three main generators must be on line
prior to both AC main buses going off. This prevents the ADG from deploying during ground
maintenance tests, with external power being connected and disconnected with the aircraft on
jacks.
The red EMER PWR ONLY warning EICAS message indicates loss of all normal electrical power,
and ADG deployment.
When the ADG unit is fully extended, the two-blade propeller is unlocked and rotates in the
airstream. Once the ADG voltage and frequency are within normal limits, the AUTO DEPLOY
CONTROL unit energizes the appropriate transfer contactors, and allows the ADG to provide
power to the AC ESS BUS and to hydraulic pump 3B via the ADG BUS.
The ADG AUTO DEPLOY CONTROL unit sends a signal to release the solenoid of the ADG
uplock mechanism.
ADG Manual Deploy Handle and ADG AUTO DEPLOY CONTROL Panel
Figure 07−10−15
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Bombardier Challenger 605 - Electrical
AIR-DRIVEN GENERATOR (ADG) (CONT'D)
ADG Manual Deploy Handle
In the event of an auto-deploy failure, the ADG can be manually deployed using the ADG
manual deploy handle, located on the lower center pedestal. Pulling the handle manually
releases the uplock, allowing the ADG to deploy. In addition, the emergency AC transfer
contactor and emergency DC transfer contactor are energized immediately.
In the event the ADG fails, operating the ADG manual deploy handle enables the DC ESS
BUS to be supplied by the BATT BUS through the emergency DC transfer contactor.
NOTE
If the ADG is not operating properly and the airplane is on battery
power only, then all electrical power may be lost after 30 minutes.
Hydraulic pump 3B will be inoperative when on battery power.
Manual deployment of the ADG handle is also required for landing, when the ADG is the only
source of AC electrical power. This ensures that the DC ESS BUS remains powered by the
BATT BUS throughout the landing rollout, when the ADG is no longer capable of generating
AC power.
ADG LAMP/UNIT Switch
The ADG auto deploy control unit may be tested using the two-position ADG LAMP/UNIT
switch, located on the ADG AUTO DEPLOY CONTROL panel.
Selecting the switch to the UNIT position tests the continuity of the uplock circuit, the three
transfer contactors, and the ADG AUTO DEPLOY CONTROL unit internal logic circuitry. Both
engine generators must be operating, and AC BUS 1 and AC BUS 2 must be powered, to
ensure a proper test.
Selecting the switch to the LAMP position checks the serviceability of the green TEST lamp
only.
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Bombardier Challenger 605 - Electrical
AIR-DRIVEN GENERATOR (ADG) (CONT'D)
ADG Operation
Figure 07−10−16
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Bombardier Challenger 605 - Electrical
AIR-DRIVEN GENERATOR (ADG) (CONT'D)
PWR TXFR OVERRIDE
With the ADG deployed, it may be possible to restore normal AC electrical power by resetting
an engine-driven generator, or by using the APU generator. If AC electrical power is restored,
the PWR TXFR OVERRIDE switch should be selected, to reset the three transfer contactors
and regain normal AC distribution. This returns the AC ESS BUS to AC BUS 1, and the 3B
hydraulic pump to normal operation.
NOTE
The ADG manual deploy handle must be stowed to allow the
transfer contactors to reset.
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Bombardier Challenger 605 - Electrical
AIR-DRIVEN GENERATOR (ADG) (CONT'D)
ADG Operation
Figure 07−10−17
DC ELECTRICAL POWER SYSTEM
Description
Four transformer-rectifier units (TRUs), two NiCad batteries, and an external DC power receptacle
supply direct current (DC) power to the DC buses. The TRUs carry the majority of the DC electrical
loads, and the batteries provide emergency power in-flight and allow the APU to be started on the
ground.
DC power is distributed to the DC buses directly from the TRUs or batteries, and from various
contactors which provide alternate sources of power.
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Bombardier Challenger 605 - Electrical
DC ELECTRICAL POWER SYSTEM (CONT'D)
Electrical power is supplied to the buses through the circuit breaker panels.
DC System Schematic
Figure 07−10−18
Monitoring of system status is done using the DC ELECTRICAL synoptic page. The aircraft DC
bus system consists of the following nine buses:
• DC BUS 1;
• DC BUS 2;
• DC ESS (Essential) BUS;
• DC EMER (Emergency) BUS;
• BATT (Battery) BUS;
• DC UTIL (Utility) BUS 1;
• DC UTIL (Utility) BUS 2;
• MAIN BATTERY DIRECT BUS; and
• APU BATTERY DIRECT BUS.
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Bombardier Challenger 605 - Electrical
DC ELECTRICAL POWER SYSTEM (CONT'D)
DC ELECTRICAL Synoptic Page
Figure 07−10−19
Components and Operation
Transformer-Rectifier Units (TRUs)
The normal sources of 28-volt DC electrical power for the DC system are the four TRUs. Each
TRU converts 115-volt AC to 28-volt DC, and supplies it to its respective DC buses. Each TRU
is rated at 100 amps.
The four TRUs are identified as:
• TRU 1;
• TRU 2;
• ESS (Essential) TRU 1; and
• ESS (Essential) TRU 2.
The TRUs supply the following buses:
• TRU 1 normally supplies DC BUS 1 and DC UTIL BUS 1;
• TRU 2 normally supplies DC BUS 2 and DC UTIL BUS 2;
• ESS TRU 1 normally supplies DC ESS BUS and DC BATT BUS; and
• ESS TRU 2 normally supplies DC ESS BUS and DC BATT BUS.
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Bombardier Challenger 605 - Electrical
DC ELECTRICAL POWER SYSTEM (CONT'D)
TRU Power Distribution System
The TRU power distribution system supplies the following buses:
DC BUS 1 and DC BUS 2
DC BUS 1 is supplied by TRU 1, and DC BUS 2 is supplied by TRU 2. If either TRU fails, both
buses can be supplied by either TRU by selecting the MAIN BUS TIE switch/light on the
ELECTRICAL POWER panel.
DC UTIL BUS 1 and DC UTIL BUS 2
The DC UTIL buses supply power to nonessential cabin equipment. TRU 1 and TRU 2 power
DC UTILITY BUS 1 and 2 respectively.
Whenever the MAIN BUS TIE switch/light is selected following a TRU 1 or 2 failure, the DC
UTIL buses are load shed to reduce the DC electrical load.
TRU 1 Failed and MAIN BUS TIE Closed
Figure 07−10−20
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Bombardier Challenger 605 - Electrical
DC ELECTRICAL POWER SYSTEM (CONT'D)
DC ESS BUS
The DC ESS BUS powers equipment essential for safe flight and, therefore, may be supplied
by numerous DC sources to ensure redundancy of its power supply. Normally, ESS TRU 1 and
ESS TRU 2 power the DC ESS BUS. In the event of a single ESS TRU failure, either ESS
TRU is capable of sustaining the DC ESS BUS load. Should both ESS TRUs fail with the
aircraft in flight, the APU BATT DIR BUS, through the DC ESS solid-state contactor, will power
the DC ESS BUS.
During ADG operation, the AC ESS BUS powers ESS TRU 1, which in turn powers the DC
ESS BUS. The DC ESS BUS can also be powered by the APU and main batteries, through the
emergency DC transfer contactor. Refer to the ADG section of this chapter for additional
information.
BATT BUS
The BATT BUS powers equipment essential for safe flight, and may be supplied by several DC
sources to ensure redundancy. Normally, ESS TRU 1 and ESS TRU 2 power the BATT BUS
when the main AC buses are powered. If the ESS TRUs are not operating (no AC power or
ESS TRU failures), the BATT BUS will be powered by the APU BATT DIR BUS and MAIN
BATT DIR BUS, provided the BATT MASTER switch is selected ON.
The BATT MASTER switch, located on the ELECTRICAL POWER panel, controls the APU
BATT and MAIN BATT contactors to supply the BATT BUS, as described above.
The BATT BUS also supplies the DC EMER BUS.
Battery Power Distribution System
The battery power distribution system represents a small portion of the aircraft’s total DC load.
The batteries primarily provide the energy needed to start the APU, which can then be used to
supply AC power to the aircraft. The batteries also supply emergency DC power in-flight, should
all AC power be lost and the ADG become inoperative.
Two rechargeable nickel-cadmium (NiCad) batteries are installed in the aircraft. The main
battery is a 24-volt, 17-amp/hour battery located in the nose section. The APU battery is a
24-volt, 43-amp/hour battery, installed in the aft equipment bay.
The batteries supply DC electrical power to the following buses:
• MAIN BATT DIR BUS;
• APU BATT DIR BUS;
• DC EMER BUS; and
• BATT BUS.
Battery Charging
The main battery charger and APU battery charger are in a charging configuration at all times,
when the applicable main AC buses are powered.
• AC BUS 1 for main battery charger
• AC BUS 2 for APU battery charger
The battery chargers operate automatically in various modes, based on battery temperatures.
Should a battery or battery charger fault be detected, the respective battery charger will shut
down. A MAIN (APU) BATT CHGR FAIL status EICAS message will appear, and the CHGR OFF
icon will be displayed on the DC ELECTRICAL synoptic page, indicating a failure.
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Bombardier Challenger 605 - Electrical
DC ELECTRICAL POWER SYSTEM (CONT'D)
MAIN and APU BATT DIR Buses
These DC buses are continuously powered from the associated battery, regardless of the
BATT MASTER switch position. The main battery is connected to the MAIN BATT DIR BUS,
and the APU battery is connected to the APU BATT DIR BUS. These buses provide power to
the aircraft systems which primarily relate to ground service operation (refueling, service lights,
etc.) The APU BATT DIR BUS also supplies the DC EMER BUS.
DC Emergency Bus
The DC EMER BUS provides power to the engine and APU fire extinguishers, and the fuel and
hydraulic shutoff valves. The bus is connected to the APU BATT DIR BUS and the BATT BUS,
and is continuously powered.
External DC Electrical Power
External DC ground power may be used to start the APU, if the APU battery charge is low. The
external DC receptacle is located at the rear of the aircraft, near the right engine pylon.
External DC Receptacle
Figure 07−10−21
When connected, external DC ground power automatically supplies the APU BATT DIR BUS
through the external DC contactor, and the BATT BUS when the BATT MASTER switch is
selected ON. The DC EXTERNAL POWER white IN USE light, on the ELECTRICAL POWER
panel, illuminates whenever DC external power is connected.
External DC ground power is identified on the DC electrical synoptic page by the symbol EXT
DC. This symbol appears only if DC external power is connected to the aircraft.
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Bombardier Challenger 605 - Electrical
DC ELECTRICAL POWER SYSTEM (CONT'D)
External DC Power Connected
Figure 07−10−22
Circuit Breakers
Description
Electrical power distribution is accomplished through five circuit breaker panels. Four circuit
breaker panels are installed in the flight deck, and the fifth panel is in the aft equipment bay.
They are identified as follows:
• Circuit breaker panel 1 (CBP−1);
• Circuit breaker panel 2 (CBP−2);
• Circuit breaker panel 3 (CBP−3);
• Circuit breaker panel 4 (CBP−4); and
• Circuit breaker panel 5 (CBP−5).
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Bombardier Challenger 605 - Electrical
DC ELECTRICAL POWER SYSTEM (CONT'D)
Electrical equipment protection is provided by conventional thermal circuit breakers. When a
circuit breaker is tripped, a white collar is exposed. Depending on airplane completion
specification, circuit breakers may also be located in other parts of the airplane. Should a circuit
breaker trip while the airplane is in flight, the circuit breaker should be allowed to cool for as long
as possible before resetting.
NOTE
Do not attempt more than one reset of a circuit breaker.
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Bombardier Challenger 605 - Electrical
DC ELECTRICAL POWER SYSTEM (CONT'D)
Circuit Breaker Panels (CBPs)
Figure 07−10−23
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Bombardier Challenger 605 - Electrical
DC ELECTRICAL POWER SYSTEM (CONT'D)
Circuit Breaker Grid System
A circuit breaker can be located, when called for in a procedure, by using the grid reference on
the circuit breaker panel.
For example, the “VOLTS & FREQ IND” circuit breaker location is identified as (3A13), and
therefore found on panel CBP−3, row A, column 13.
Circuit Breaker Grid System
Figure 07−10−24
CONTROLS AND INDICATORS
The overhead ELECTRICAL POWER panel and the air-driven generator (ADG) panel provide the
system controls. The AC ELECTRICAL and DC ELECTRICAL synoptic pages provide a pictorial
representation of system status. The EICAS pages provide system caution and advisory messages
respectively. Circuit breaker panel (CBP) diagrams are also located in this section.
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Bombardier Challenger 605 - Electrical
CONTROLS AND INDICATORS (CONT'D)
AC Electrical Power
ELECTRICAL POWER Panel
Figure 07−10−25
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Bombardier Challenger 605 - Electrical
CONTROLS AND INDICATORS (CONT'D)
Air-Driven Generator (ADG)
Air-Driven Generator (ADG)
Figure 07−10−26
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Bombardier Challenger 605 - Electrical
CONTROLS AND INDICATORS (CONT'D)
DC Electrical Power
ELECTRICAL POWER Panel
Figure 07−10−27
Circuit Breaker Panels
Page 33
Page 34
PSP 605−6
CL−605 Flight Crew Operating Manual
CONTROLS AND INDICATORS (CONT'D)
Description
ELECTRICAL
Vol. 2
Circuit Breaker Panel 1
Figure 07−10−28
Oct 05/06
07−10−35
Bombardier Challenger 605 - Electrical
Page 35
PSP 605−6
CL−605 Flight Crew Operating Manual
CONTROLS AND INDICATORS (CONT'D)
Description
ELECTRICAL
Vol. 2
Circuit Breaker Panel 2
Figure 07−10−29
Oct 05/06
07−10−37
Bombardier Challenger 605 - Electrical
CONTROLS AND INDICATORS (CONT'D)
Circuit Breaker Panels 3 & 4
Figure 07−10−30
Bombardier Challenger 605 - Electrical
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Bombardier Challenger 605 - Electrical
CONTROLS AND INDICATORS (CONT'D)
Circuit Breaker Panel 5
Figure 07−10−31
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Bombardier Challenger 605 - Electrical
CONTROLS AND INDICATORS (CONT'D)
EICAS Synoptic Pages
AC Synoptic Page
AC Synoptic Page Colour Coding − Integrated Drive Generators
Figure 07−10−32
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Bombardier Challenger 605 - Electrical
CONTROLS AND INDICATORS (CONT'D)
AC Synoptic Page Colour Coding − Integrated Drive Generators
Figure 07−10−33
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Bombardier Challenger 605 - Electrical
CONTROLS AND INDICATORS (CONT'D)
AC Synoptic Page Colour Coding − APU Generator
Figure 07−10−34
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Bombardier Challenger 605 - Electrical
CONTROLS AND INDICATORS (CONT'D)
AC Synoptic Page Colour Coding − APU Generator
Figure 07−10−35
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Bombardier Challenger 605 - Electrical
CONTROLS AND INDICATORS (CONT'D)
AC Synoptic Page Colour Coding − AC Electrical Power Distribution
Figure 07−10−36
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Bombardier Challenger 605 - Electrical
CONTROLS AND INDICATORS (CONT'D)
AC Synoptic Page Colour Coding − AC Electrical Power Distribution
Figure 07−10−37
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Bombardier Challenger 605 - Electrical
CONTROLS AND INDICATORS (CONT'D)
AC Synoptic Page Colour Coding − External AC Electrical Power
Figure 07−10−38
Page 44
Bombardier Challenger 605 - Electrical
CONTROLS AND INDICATORS (CONT'D)
AC Synoptic Page Colour Coding − Air-Driven Generator
Figure 07−10−39
Page 45
Bombardier Challenger 605 - Electrical
CONTROLS AND INDICATORS (CONT'D)
DC Synoptic Page
DC Synoptic Page − TRU Power Distribution System
Figure 07−10−40
Page 46
Bombardier Challenger 605 - Electrical
CONTROLS AND INDICATORS (CONT'D)
DC Synoptic Page − TRU Power Distribution System
Figure 07−10−41
Page 47
Bombardier Challenger 605 - Electrical
CONTROLS AND INDICATORS (CONT'D)
DC Synoptic Page − Battery Power Distribution System
Figure 07−10−42
Page 48
Bombardier Challenger 605 - Electrical
CONTROLS AND INDICATORS (CONT'D)
DC Synoptic Page − Battery Power Distribution System
Figure 07−10−43
Page 49
Bombardier Challenger 605 - Electrical
CONTROLS AND INDICATORS (CONT'D)
DC Synoptic Page − DC Electrical Power Distribution
Figure 07−10−44
Page 50
Bombardier Challenger 605 - Electrical
CONTROLS AND INDICATORS (CONT'D)
DC Synoptic Page − DC Electrical Power Distribution
Figure 07−10−45
Page 51
Bombardier Challenger 605 - Electrical
EICAS MESSAGES
MESSAGE
EMER POWER ONLY
AC 1 AUTOXFER
AC 2 AUTOXFER
AC BUS 1
AC BUS 2
MEANING
AURAL WARNING
(IF ANY)
ADG is supplying the AC essential bus, and no power
is available from AC BUS 1 or 2.
WARNING
Triple Chime
Respective automatic AC bus tie function has been inhibited because of an
overcurrent condition on the respective AC bus.
Respective AC bus is unpowered.
AC ESS BUS
AC essential bus is unpowered.
APU BATTERY OFF
APU battery is not available.
APU GEN OFF
APU generator is off-line with the APU running.
APU GEN OVLD
Load current on any phase of APU GEN exceeds 100 Amp.
BATTERY BUS
Battery bus is unpowered.
DC BUS 1
DC BUS 2
Respective DC bus is unpowered.
DC EMER BUS
DC emergency bus is unpowered.
DC ESS BUS
DC essential bus is unpowered.
GEN 1 OFF
GEN 2 OFF
Respective generator is OFF.
GEN 1 OVLD
Load current on any phase of GEN 1 exceeds 100 Amp.
GEN 2 OVLD
Load current on any phase of GEN 2 exceeds 100 Amp.
MAIN BATTERY OFF
Main battery is not available.
AC ESS ALTN
AC essential bus is powered by AC BUS 2.
APU BATT CHGR FAIL
APU battery is not charging, or APU battery charger has failed.
ESS TRU 1 FAIL
ESS TRU 2 FAIL
MAIN BATT CHGR FAIL
Respective essential transformer-rectifier unit output is less than 18 VDC.
Main battery is not charging, or main battery charger has failed.
Page 52
Bombardier Challenger 605 - Electrical
POWER SUPPLY AND CIRCUIT BREAKER SUMMARY
SYSTEM
AC Power
SUB-SYSTEM
Emergency Power
and Control
AC Distribution
Control and
Protection
CB NAME
BUS BAR
CB
PANEL
CB
LOCATION
ADG AUTO
MAIN BATT
DIRECT
6
B5
ESS HYD PUMP
SUPPLY
AC ADG
BUS
3
A11
ADG MAN
MAIN BATT
DIRECT
6
B4
ADG DEPLOY
CONT AUTO
DC BATT
2
N6
ADG DEPLOY
CONT MAN
DC BATT
2
N7
ADG DEPLOY
SENSE
AC BUS 1
1
C10
ADG DEPLOY
SENSE
AC BUS 2
2
C10
ADG HEATER
AC BUS 2
2
C11
AC ESS FEED
AC ADG
BUS
3
A8
VOLTS & FREQ
IND
AC ADG
BUS
3
A13
FREQ CONV
AC BUS 1
1
D11
115VAC ESS FEED AC BUS 1
1
B5
115VAC ESS FEED AC BUS 2
6
A4
AC ESS PWR
CONT
DC MAIN
BATT
DIRECT
5
A12
ESS AC XFER
BATT BUS CONT
DC BATT
1
Q1
GCU 1
DC BATT
1
P1
GCU 2
DC BATT
1
P2
GCU 3
DC BATT
1
P3
UTIL BUS CONT
DC BUS 1
1
E11
UTIL BUS CONT
DC BUS 2
2
E11
EXT AC PWR
CONT
DC APU
BATT
DIRECT
5
B12
Page 53
NOTES
Bombardier Challenger 605 - Electrical
POWER SUPPLY AND CIRCUIT BREAKER SUMMARY (CONT'D)
SYSTEM
DC Power
SUB-SYSTEM
Distribution
CB NAME
BUS BAR
CB
PANEL
CB
LOCATION
PWR SENSE
DC UTILITY
BUS 1
1
E6
UTILITY BUS 1
FEED
DC UTILITY
BUS 1
1
E7
FEED
DC BUS 1
CONTROL
1
E8
TIE & UTIL
DC BUS 1
CONTROL
2
E9
PWR SENSE
DC BUS 1
1
E12
PWR SENSE
DC
EMERGENCY
1
R7
FEED
DC
EMERGENCY
1
S7
EMERG BUS FEED DC BATT
1
M1
UTILITY BUS PWR DC UTILITY
SENSE 2
BUS 2
2
E6
FEED
DC UTILITY
BUS 2
2
E7
FEED
DC BUS 2
CONTROL
2
E8
TIE & UTIL
DC BUS 2
CONTROL
2
E9
DC BUS 2 PWR
SENSE
DC BUS 2
2
E12
BATT BUS POWER DC ESS
SENSE
2
M3
RCCB CONT DC
ESS
2
M6
FEED 1 BATT BUS W35PA
2
M7
FEED 1 DC ESS
W35PA
2
M8
FEED 2 BATT BUS W36PA
2
M9
FEED 2 DC ESS
W36PA
2
M10
PWR SENSE
DC ESS
4
A3
ESS/EMER BUS
FEED
DC APU
BATT
DIRECT
5
B1
DC ESS
Page 54
NOTES
Bombardier Challenger 605 - Electrical
POWER SUPPLY AND CIRCUIT BREAKER SUMMARY (CONT'D)
SYSTEM
DC Power
Batteries
SUB-SYSTEM
CB
PANEL
CB
LOCATION
AC BUS 1
1
B2
DC BUS 1
CONTROL
1
E10
TRU 2
AC BUS 2
2
B2
TRU 2 SENSE
DC BUS 2
CONTROL
2
E10
ESS TRU 1
AC ESS
3
A2
ESS TRU SENSE 1 DC ESS
4
A1
ESS TRU 2
2
A8
ESS TRU SENSE 2 DC ESS
4
A2
CONTACTOR
LOGIC ESS 1
BATT BUS
2
M1
CONTACTOR
LOGIC ESS 2
BATT BUS
2
M2
APU BATT CONT
DC APU
BATT
DIRECT
5
B2
APU BATT CHGR
O/P
DC APU
BATT
DIRECT
5
B13
RCCB CONT APU
BATT
DC ESS AND
BATT BUS
CONTROL
2
M5
APU BATT CHGR
AC BUS 2
2
C2
MAIN BATT PWR
SENSE REF
BATT
DIRECT
6
A2
MAIN BATT PWR
SENSE
BATT
DIRECT
6
A1
MAIN BATT PWR
O/P
BATT
DIRECT
6
A2
RCCB CONT MAIN DC ESS AND
BATT
BATT BUS
CONTROL
2
M4
MAIN BATT CHGR
O/P
1
C2
CB NAME
Transformer Rectifier TRU 1
Units
TRU 1 SENSE
APU Battery
Main Battery
Page 55
BUS BAR
AC BUS 2
AC BUS 1
NOTES
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