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A
747-400 MAINTENANCE MANUAL
SEE A
P180
P180-1 APU BATTERY
MAIN BATTERYTRANSFER RELAY
RELAY SEE C
SEE B
BATTERY TRANSFER RELAY
SEE B
P180 DC POWER DISTRIBUTION PANEL A
TRANSFER RELAY(EXAMPLE)
APU BATTERY BUS
TRANSFER RELAY
B
C
Main Battery, Battery Transfer, and APU Battery
Transfer Relay Location
Figure 5
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A
747-400
MAINTENANCE MANUAL
Main Battery/Battery Charger Simplified Schematic
Figure 6
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A
747-400
MAINTENANCE MANUAL
APU Battery/Battery Charger Simplified Schematic
Figure 7
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747-400
MAINTENANCE MANUAL
(6)
Two self-protective functions are incorporated into the battery charger which will interrupt charger operation when overvoltage (135 volts) and undervoltage (94 volts) input power is applied, or when an overcurrent fault condition exists. The charger will restart automatically when the fault condition is removed. The battery charger output is current-limited to 65 amps and the battery charger output wiring is rated for 75 amps continuous current.
(7)
A discharged battery (20 volts) should completely recharge within 75 minutes. If the charge command continues beyond this maximum charge time and approaches 100 minutes, the charger will switch into the constant voltage charge mode (27.75 volts).
(8)
If the battery sensing connector is disconnected, a sensing loop in the charger will be opened causing the charger to shut down.
(9)
The battery charger will not start unless the battery voltage is above 4 volts when power is first applied to the battery charger.
(10)
These last two protective circuits prevent charger operation if a battery is not connected to the system.
(11)
A failure annunciation circuit is incorporated in the battery charger which opens an internal ground when the charger shuts down due to battery overtemperature, open battery connectors, or when input three-phase power is removed. A failure of the battery charger is annunciated by an advisory level message BAT CHARGER MAIN and/or BAT CHARGER APU on EICAS.
(12)
Some battery chargers have two annunciator lights. One light is used to moniter the battery charger condition. The other light is used to moniter the battery condition. These lights are in addition to the EICAS message signals. This battery charger operates in the same manner as battery chargers without annunciator lights.
(13)
The battery cells have an initial acceptance capacity of 47 ampere-hours and a minimum return to service capacity of 40 ampere-hours. The battery is capable of supplying 70 amps for a minimum of 30 minutes to a cutoff voltage of 20 volts when cold soaked at a temperature of 0°F.
(14)
During standby conditions, the voltage at the battery terminals will not be less than 20 volts.
(15)
The battery charger is installed in the airplane to perform two different functions, namely, to provide a dc output of 18.0 to 36.0 volts for regulated charging of the battery, and to operate as a transformer-rectifier to supply 23.0 to 29.5 volts power should three or more TRUs fail.
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