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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.
TRU 1 Failed and MAIN BUS TIE Closed
Figure 07−10−17
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.
ELECTRICAL
Description
Vol. 2 07−10−22
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
DC ELECTRICAL POWER SYSTEM (CONT'D)
The BATT BUS also supplies the DC EMER BUS.
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.
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 aft equipment bay. The
main battery is a 24-volt, 17-amp/hour battery. The APU battery is a 24-volt, 43-amp/hour
battery.
The batteries supply DC electrical power to the following buses:
• MAIN BATT DIR BUS
• APU BATT DIR BUS
• DC EMER BUS
• 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 to indicate a failure.
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.
ELECTRICAL
Description
Vol. 2 07−10−23
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
DC ELECTRICAL POWER SYSTEM (CONT'D)
BATT Bus
Refer to the TRU distribution section of this chapter.
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 07−10−18
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.
ELECTRICAL
Description
Vol. 2 07−10−24
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
DC ELECTRICAL POWER SYSTEM (CONT'D)
External DC Power Connected
　
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