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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
ELECTRICAL
Description
Vol. 2 07−10−24
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
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.
ELECTRICAL
Description
Vol. 2 07−10−25
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
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
　
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