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FCOM 19 AUG 10
DISTRIBUTION TABLE
Applicable to: ,
A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
ELECTRICAL
DESCRIPTION - OPERATIONS
A330/A340 FLEET DSC-24-10-30-40 P 4/4
FCOM 19 AUG 10
White compartments : Same supply as in normal configuration.
Shaded
compartments
: Back up supply.
EMER CONFIG AC
BUS 1
AC
BUS 2
AC
ESS
BUS
AC
ESS
GND
AC
ESS
SHED
AC
LAND
REC
DC
BUS
1
DC
BUS
2
DC
BAT
BUS
DC
ESS
BUS
DC
ESS
SHED
DC
LAND
REC
SHED
LAND
REC
• BATTERIES ONLY
(in flight)
– – STAT
INV
BAT 1-2
– – STAT
INV
BAT
1-2
– – See BAT
1-2
– BAT
1-2
–
• EMER GEN
SUPPLIED BY
ENGINE DRIVEN
PUMP
– – EMER
GEN
– EMER
GEN
EMER
GENSee
– – – ESS
TR
EMER
GEN
ESS
TR
EMER
GEN
ESS
TR
EMER
GENSee
ESS
TR
EMER
GENSee
• EMER GEN
SUPPLIED BY RAT
– – EMER
GEN
– – EMER
GENSee
– – – ESS
TR
EMER
GEN
– ESS
TR
EMER
GENSee
–
ON GROUND AC
BUS 1
AC
BUS 2
AC
ESS
BUS
AC
ESS
GND
AC
ESS
SHED
AC
LAND
REC
DC
BUS 1
DC
BUS 2
DC
BAT
BUS
DC
ESS
BUS
DC
ESS
SHED
DC
LAND
REC
SHED
LAND
REC
BAT only, V>50 kt – – STAT
INV
BAT
1-2
– – STAT
INV
BAT
1-2
– – – BAT
1-2
– BAT
1-2
–
BAT only, V<50 kt – – STAT
INV
BAT
1-2
STAT
INV
BAT
1-2
– STAT
INV
BAT
1-2
– – BAT
1-2
BAT
1-2
– BAT
1-2
–
(1) Supplied when LAND RECOVERY pushbutton is at ON.
(2) Lost in case of overcurrent on the faulty TR.
(3) In case of differential protection failure :
• The affected generator is not replaced ;
• The associated TR is switched off.
(4) Lost after 7 s.
A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
ELECTRICAL
CONTROLS AND INDICATORS
A330/A340 FLEET DSC-24-20 P 1/48
FCOM 19 AUG 10
OVERHEAD PANEL
Applicable to:
(1) BAT 1 (2 or APU) sel
Selects the battery for voltage indication.
(2) BAT 1 (2 or APU) voltage indication
Selected battery voltage.
(3) BAT 1 (2) pb sw
Controls the operation of the corresponding Battery Charge Limiter.
A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
ELECTRICAL
CONTROLS AND INDICATORS
A330/A340 FLEET DSC-24-20 P 2/48
FCOM 19 AUG 10
Auto : The Battery Charge Limiter controls automatically the connection and the
disconnection of the corresponding battery to the DC BAT BUS by closing and
opening of the battery line contactor.
The batteries are connected to ‐ the DC BAT BUS in the following cases :
• Battery voltage below 26.5 V (battery charge). The charging cycle ends
when battery charge current goes below 4 A (for 10 s on ground, 30 min in
flight).
• On the ground (with speed below 50 kt), when batteries only are supplying
the aircraft.
• In flight DC generation lost (limited to 7 s).
‐ The batteries are connected to the DC ESS BUS when batteries only are
supplying :
• in flight
• on the ground (speed below 50 kt) provided they are both selected auto.
Note: 1. In normal configuration the batteries are disconnected most of the
time.
2. A battery automatic cut off logic prevents batteries from discharging
completely discharge when the aircraft on the ground (parking).
Automatic battery contactors open when :
‐ The aircraft is on the ground.
‐ The main power supply (external power plus all generators) is cut
off.
‐ The battery voltage is lower than 23 V for more than 16 s.
The flight crew can reset the contactors by switching the BAT
pushbutton switch to OFF then AUTO.
OFF : The Battery Charge Limiter is not operating, the DC ESS BUS is not connected to
　
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