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provides DC power to the APU battery direct bus. The APU batery has a nominal
output voltage of 24 Vdc with a capacity of 43 ampere--hours. The main battery is
located in the nose avionics compartment and provides DC power to the main battery
direct bus. The main batery has a nominal output voltage of 24 Vdc with a capacity of
17 ampere--hours.
Each battery is maintained at full charge by its related battery charger. The main
battery charger is powered from AC bus 1 and the APU battery charger is powered from
the AC service bus. Battery charging is controlled automatically. Each charger
monitors the battery voltage and temperature to control the charge rate and prevent
overheating (thermal runaway).
C. DC Distribution
DC power is distributed through two DC power centers (DCPCs) located in the avionics
compartment. DC bus 1 and DC bus 2 are powered from TRU 1 and TRU 2
respectively with connection controlled by the DCPC control logic. The DC essential,
battery and DC emergency buses are normally powered from the essential TRUs. In
the event that both essential TRUs fail, the DC essential, battery and emergency bus
will be powered by TRU 2 via the automatic CROSS TIE.
Vol. 1 07--30--2
ELECTRICAL
DC Electrical System Sep 09/02
Flight Crew Operating Manual
CSP C--013--067
The Main battery direct bus, APU battery direct bus, and the emergency bus are all hot
buses (they are continuously powered at all times from the batteries). When the
BATTERY MASTER switch is selected ON, an input signal is supplied to the two power
controllers (PC) to connect their respective batteries to the DCPCs for power
distribution. Each battery direct bus can power the DC battery bus. Both the battery
bus and the APU battery direct bus feed the DC emergency bus. The DC service bus
is normally powered from DC bus 2. If the DC SERVICE switch on the electrical power
panel is selected ON, the DC service bus is powered from the APU battery direct bus.
If a complete loss of AC power occurs, the ESS TIE will close to connect the DC
essential bus to the battery bus for emergency power. If TRU 1 or TRU 2 fails, the
MAIN TIE will close to connect DC Bus 1 and DC Bus 2 to functioning TRU (1 or 2)
When the MAIN TIE closes, the DC utility bus is shed to reduce load draw on the
remaining TRUs. When both essential TRUs fail or when both TRU 1 and TRU 2 fail,
the CROSS TIE closes. If AC bus 2 fails, essential TRU 2 will be powered from the AC
essential bus.
Vol. 1 07--30--3
ELECTRICAL
DC Electrical System REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
DC Electrical System --- Schematic
Figure 07---30---1
CONTROL LOGIC
AC BUS 1
LDCPC
AC ESS BUS AC BUS 2
DC BUS 1 DC ESS BUS
ESS TIE
CONTROL LOGIC
TRU1
TRU1
CONT
ESS TRU1 ESS TRU2 TRU2
ESS
TRU1
CONT
TRU2
CONT
ESS
TRU2
CONT
CROSS TIE
MAIN
TIE
DC UTIL BATT BUS DC BUS 2
EMER BUS
RDCPC
MAIN BATT DIRECT BUS
MAIN
BATT
CHRG
MAIN
BATT
APU BATT DIRECT BUS
APU
BATT
CHRG
APU
BATT
SERV BUS
BATTERY
MASTER
SWITCH
AC SERVICE
ESS TRU 2
XFR
CONTACTOR
PWR
CONTACTOR
PWR
CONTACTOR
Vol. 1 07--30--4
ELECTRICAL
DC Electrical System Sep 09/02
Flight Crew Operating Manual
CSP C--013--067
Electrical Power Overhead Panel
Figure 07---30---2
Electrical Power Panel
Overhead Panel
BATTERY MASTER
Used to connect the APU
and main battery direct
busses to the battery bus.
NOTE
Battery master should
always be in the ON
position in flight.
DC SERVICE
Used to connect the DC
service bus to the APU
battery direct bus.
FAULT
DISC
DISC
GEN 2
OFF/
RESET
APU GEN
OFF/
RESET
OFF/
RESET
GEN 1
FAIL
OFF
FAIL
AUTO OFF
XFER
AC ESS XFER
ALTN
FAULT
DISC
DISC
BATTERY
MASTER
OFF
ON
OFF
ON
DC
SERVICE
IDG 1 AC POWER IDG 2
ELECTRICAL POWER
AC
AVAIL
IN USE
AUTO AUTO AUTO
Vol. 1 07--30--5
ELECTRICAL
DC Electrical System Sep 09/02
Flight Crew Operating Manual
CSP C--013--067
DC Electrical Page Tru Voltage
Figure 07---30---3
DC ELEC Page
EICAS Secondary Display
Center Instrument Panel
TRU Load
Displays the load
on the TRU.
TRU Voltage
Displays the TRU
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