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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 (see Figure 7-7).
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 (AP/EPC).
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 (see Figure 7-7).
P604_07_055
ELECTRICAL
For Training Purposes Only
May 03
7-9
P I LOT T R A I N I N G GU I D E
External AC Electrical Power
Figure 7-7
ELECTRICAL POWER
BATT MASTER EXT. POWER
APU GEN GEN 2
OFF/
RESET
OFF/
RESET
ON
ON
OFF
ESS. POWER DC POWER
AC ESS XFER MAIN BUS TIE
AC POWER
GEN 1
OFF/
RESET
AVAIL
IN USE
IN
USE
ON
AUTOXFER
FAIL
OFF
FAIL
OFF
ALTN CLOSED
ON
AC DC
P604_07_031
AC ELECTRICAL
UTIL BUS 1
BUS 2
GEN
2
GEN
1
APU
BUS 1
UTIL BUS 2
0
0
0
GEN
ESS BUS
KVA
V
HZ
0
0
0
KVA
V
HZ
0
0
0
KVA
V
HZ
EXT
AC
116
400
V
HZ
EXTERNAL AC POWER SUPPLYING MAIN AC BUSES
P604_07_030
AC ELECTRICAL
UTIL BUS 1
BUS 2
GEN
2
GEN
1
APU
BUS 1
UTIL BUS 2
0
0
0
GEN
ESS BUS
KVA
V
HZ
0
0
0
KVA
V
HZ
0
0
0
KVA
V
HZ
EXT
AC
116
400
V
HZ
EXTERNAL AC POWER CONNECTED TO AIRCRAFT
ELECTRICAL POWER
BATT MASTER EXT. POWER
APU GEN GEN 2
OFF/
RESET
OFF/
RESET
ON
ON
OFF
ESS. POWER DC POWER
AC ESS XFER MAIN BUS TIE
AC POWER
GEN 1
OFF/
RESET
AVAIL
IN USE
IN
USE
ON
AUTOXFER
FAIL
OFF
FAIL
OFF
ALTN CLOSED
ON
AC DC
ELECTRICAL
7-10 For Training Purposes Only
May 03
P I LOT T R A I N I N G GU I D E
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 EICAS 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
• AC UTILITY BUS 2
EICAS AC Electrical Synoptic Page
Figure 7-8
AC ELECTRICAL
UTIL BUS 1
BUS 2
GEN
2
GEN
1
APU
BUS 1
UTIL BUS 2
GEN
ESS BUS
P604_07_032
4
115
400
KVA
V
HZ
4
115
400
KVA
V
HZ
0
0
0
KVA
V
HZ
AC UTILITY BUS 1
AC BUS 1 (Main)
AC ESS BUS (Essential)
AC UTILITY BUS 2
AC BUS 2 (Main)
ELECTRICAL
For Training Purposes Only
Jan 04
7-11
P I LOT T R A I N I N G GU I D E
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 logic 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.
　
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