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SPLIT BUS SYSTEM
The split bus electrical system has a left and right generator bus (GEN
BUS) located in a left and right Power Distribution Panel (PDP) in the
tailcone. The generator buses supply power to the respective left and
right essential, left and right main and left and right non-essential
buses located on the left and right circuit breaker panels in the cockpit.
Under normal flight conditions, the generator buses are split (bus-tie
open), increasing safety in that any major electrical system fault will
only affect one side of the system.
GENERATOR BUSES
The generator buses are the central distribution point for the split bus
system. The left generator bus powers the left side buses and the right
generator bus powers the right side buses. Some services including
landing lights, taxi lights, navigation lights, recognition lights and baggage
heat are connected through fuses and circuit breakers directly to
the generator buses. Each generator bus is connected to a starter/
generator and a main battery, with the GPU connecting to the left generator
bus. Normally, the two buses operate independently; however,
they are automatically “tied” through a bus-tie contactor when the
GPU is connected to the electrical system, during engine starting and in
flight following a single generator failure. The generator buses can be
tied or split manually using the BUS-TIE switch on the electrical control
panel, except the bus-tie cannot be manually opened when a GPU is being
used.
The CAS presents a BUS TIE CLSD message when the bus-tie is closed
and a BUS TIE MANUAL message when closed manually. Also, the bar
on the BUS-TIE switch illuminates any time the BUS-TIE is closed and
it extinguishes when the bus-tie is open.
Pilot’s Manual
4-18 PM-132A
MAIN BUSES
The left and right main buses are fed by the respective left and right
generator buses through fuses and contactors. The main buses, in turn,
supply power to the left and right main avionics buses through circuit
breakers and contactors. Both of the main buses are automatically
disconnected in the unlikely event of a dual generator failure and the
OFF caption will illuminate on the MAIN bus switches. The main
avionics buses will also be depowered in this case, but the OFF caption
does not illuminate on the AV MSTR switches since the essential
avionics buses will still be powered. The main and main avionics buses
may be reconnected by manual selection after reducing the bus load.
MAIN AVIONICS BUSES
The left and right main avionics buses are supplied by the respective
main buses through contactors and circuit breakers. The essential and
main avionics bus contactors are closed and opened by manual
selection of the left and right AV MSTR switches. If the AV MSTR
switches are on, the main avionics buses are automatically depowered
during engine starting to prevent possible equipment damage from
voltage spikes.
The essential avionics buses remain powered during engine start since
they power flight critical display units. The AV MSTR switches need
not be on during ground starts since the primary flight displays are not
needed and DU2 (EICAS) is still powered with the AV MSTR switches
OFF.
Pilot’s Manual
PM-132A 4 -1 9/ /4 -2 0 ((Bllank))
L ESS AV BUS L ESS BUS
GPU
L MAIN AV BUS L MAIN BUS
L GEN BUS
L MAIN
BATT
GCU
EMER BATT BUS R ESS BUS R ESS AV BUS
RMAIN BUS R MAIN AVBUS
EMER
BATT
R GEN BUS
GCU
R MAIN
BATT
REAR HOT BUS
GEN
L START R START
GEN
35A
20A 100A 80A
150A
15A
L ISOLATION
*
CONTACTOR
80A 100A
35A
35A 35A
R ESSENTIAL
*
CONTACTOR
ANTI-FLASH
CONTACTOR
L ESSENTIAL
*
CONTACTOR
40A
40A
20A
40A
40A
L NON-ESS BUS
80A 130A 150A
RNON-ESS BUS
150A 130A 80A
L HOT BUS R HOT BUS
15A 15A
L EMER HOT BUS REMERHOTBUS
BATTERY POWER
GENERATOR POWER
GPU POWER CURRENT SENSOR CONTACTOR
(SHUNT)
LEGEND
CIRCUIT BREAKER
FUSE DIODE
* AUTO OPN ONLY
MAN
L GEN L BATT BUS-TIE R BATT R GEN
EXT PWR
ON
AVAIL
L START R START
R MAIN
OFF
R
NON-ESS
OFF
L MAIN
OFF
L
NON-ESS
OFF
R AV
MSTR
OFF
L AV
MSTR
OFF
EMER BATT
OFF
EMER
OFF OFF OFF OFF
R
CONTACTOR
ISOLATION
*
ON ON
DC POWER DISTRIBUTION
Figure 4-1
　
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