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DC SYSTEM SYNOPTIC
The DC electrical page contains digital readouts of TRU and battery output (voltage
and ampere output), input/output flow on the bus bars, generated status information
via color logic and the following messages:
• CHARGER message (adjacent to APU BATT symbol) - APU battery is not
charging. Corresponds to APU BATT CHGR FAIL advisory message
• CHARGER message (adjacent to AV BATT symbol) - Main airplane battery is not
charging. AV BATT CHGR FAIL advisory message displayed on EICAS
• SHED message - Corresponding DC bus has been shed
• MAN OFF message - Corresponding DC bus is isolated. DC BUS 1, (2) MAN
OFF, DC ESS MAN OFF and/or BATT BUS MAN OFF status message displayed
on EICAS
DC
ELEC
STAT
HYD
AC
ELEC
BLEED
AIR
COND
DC
ELEC
FUEL
FLT
CTRL
SCROLL
EICAS
SYSTEMS SELECT
NORM
MFD 1 MFD 2
DC ELECTRICAL
AC BUS 2
FEEDER
DC BUS 1
26V 24V
0A 0A
-10°C
AC BUS 1
FEEDER
DC ESS BUS
ESS
TRU 1
28V
35A
AC ESS
BUS
BATT BUS
DC EMER
BUS
AV BATT
DIR BUS
AV
BATT
20°C
APU
BATT
APU BATT
DIR BUS
ESS
TRU 2
28V
35A
AC BUS 3
FEEDER
DC BUS 2
TRU 2
28V
35A
TRU 1
28V
35A
EICAS Control Panel
GX_06_027
6-28 For Training Purposes Only
Sept 04
P I LOT T R A I N I N G GU I D E
ELECTRICAL
DC BUS FEED SYSTEM
Each DC bus is normally powered by its respective TRU. Each TRU is normally
powered by its own AC BUS FEEDER (ESS TRU 2 is powered by AC ESS BUS). In
the event of a TRU malfunction, the priority system will automatically provide an
alternate TRU feed to power the respective DC bus. As soon as one TRU fails, the
emergency tie contactor (ETC) closes to allow power distribution.
ESS TRU 2 can be powered (through the AC ESS BUS) when the RAT is deployed
and RAT generator is selected ON.
The DC buses are powered by the TRUs in the following descending order:
• DC BUS 1 - TRU 1, ESS TRU 1
• DC ESS BUS - ESS TRU 1, ESS TRU 2, TRU 2, TRU 1
• BATT BUS - ESS TRU 2, ESS TRU 1, TRU 2, TRU 1
• DC BUS 2 - TRU 2, ESS TRU 2
DC BUS 1 and DC BUS 2 are automatically load shed when a single TRU is powering
the buses. External DC power will power the APU BATT DIR BUS and consequently,
the BATT BUS and the DC EMER BUS. External DC power is normally used by
maintenance personnel or to start the APU in the event of a low APU BATT voltage.
Note that a serviceable avionics battery is required to start the APU in this way.
The DC bus feed is displayed on the DC ELECTRICAL synoptic page as follows:
APU BATT CHGR FAIL
AV BATT CHGR FAIL
DC BUS 1 MAN OFF
DC BUS 2 MAN OFF
DC ESS MAN OFF
BATT BUS MAN OFF
-10°C
AV
BATT
20°C
APU
CHARGER CHARGER BATT
DC BUS 2
SHED
DC BUS 1
MAN OFF
GX_06_028
For Training Purposes Only
Sept 04
6-29
P I LOT T R A I N I N G GU I D E
ELECTRICAL
DC BUS 1
DC ELECTRICAL
AC BUS 2
FEEDER
26V 24V
0A 0A
-10°C
AC BUS 1
FEEDER
AC ESS
BUS
BATT BUS
DC EMER
BUS
AV BATT
DIR BUS
AV
BATT
20°C
APU
BATT
APU BATT
DIR BUS
ESS
TRU 2
AC BUS 3
FEEDER
DC BUS 2
TRU 2
28
35
V
A
28
35
V
A
GX_06_029
DC BUS 1
DC ELECTRICAL
AC BUS 2
FEEDER
DC BUS 1
26V 24V
0A 0A
-10°C
AC BUS 1
FEEDER
DC ESS BUS
ESS
TRU 1
28V
35A
AC ESS
BUS
BATT BUS
DC EMER
BUS
AV BATT
DIR BUS
AV
BATT
20°C
APU
BATT
APU BATT
DIR BUS
ESS
TRU 2
28V
35A
AC BUS 3
FEEDER
DC BUS 2
TRU 2
28V
35A
TRU 1
28V
35A
TRU 1
28
35
V
A
ESS
TRU 1
28
35
V
A
TRU 1
ESS TRU 1
-Normally powered by TRU 1, alternately powered by the following, in descending order:
ESS
TRU 1
TRU 1
0
0
V
A
28
45
V
A
DC ESS BUS
DC BUS 1
6-30 For Training Purposes Only
Sept 04
P I LOT T R A I N I N G GU I D E
ELECTRICAL
　
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