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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)
• 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 the main AC buses remain powered
at all times.
ELECTRICAL
Description
Vol. 2 07−10−10
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
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 (see
Figure 07−10−9).
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 Synoptic page (see Figure 07−10−9).
ELECTRICAL
Description
Vol. 2 07−10−11
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
AC ELECTRICAL POWER DISTRIBUTION (CONT'D)
AC Bus Automatic Transfer
Figure 07−10−9
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.
ELECTRICAL
Description
Vol. 2 07−10−12
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
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 07−10−10
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.
Load shedding of AC UTILITY BUS 1 and 2 is indicated by the appearance of AC UTIL 1(2)
OFF status EICAS messages and the SHED icons on the AC electrical synoptic page.
ELECTRICAL
Description
Vol. 2 07−10−13
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
AC ELECTRICAL POWER DISTRIBUTION (CONT'D)
AC Utility Bus Shedding
Figure 07−10−11
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
　
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