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bus; the No. 2 battery charger is powered by the Right Main AC bus. The
BATT 1 and/or BATT 2 switchlights must be selected to ON in order for the
chargers to operate. On aircraft SN 1465 and subsequent and aircraft with
ASC 54 incorporated, the No. 1 battery charger is controlled through the
BATT 1 switchlight; the No. 2 battery charger is controlled through the
BATT 2 switchlight. The battery chargers have two modes of operation:
charge mode and Transformer-Rectifer (TR) mode.
In the charge mode (Main AC buses powered and BATT switchlights ON),
each charger provides a constant 38 ampere charge current at a
approximately 28 to 36 volts, depending on battery state-of-charge and
load resistance, stabilizing at 27.75 volts. At this point, the charge is
complete and the battery ammeter should read 0 (±003). If battery voltage
drops to 23 volts, the charge cycle resumes. A normal battery should
completely recharge within approximately 75 minutes from a fully
discharged state.
Battery voltage must be a minimum of 4 volts in order for the charger to
initiate a charge cycle. Automatic shutdown of the chargers will take place
should any of the following occur:
• The battery terminal connector is disconnected with power applied
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• The battery sense and control cable is not connected
• Charger input voltage over 134 VAC or under 94 VAC
• Charger input voltage absent
• Charger output current exceeds 38 amperes (charger mode) or 64
amperes (TR mode)
• Battery temperature reaches 145° F (63° C)
Shutdown or failure of the battery chargers is annunciated to the flight crew
by an associated amber CHGR FAIL light illuminating on the EPMP. If CAS
is operating, an amber BATT 1-2 CHGR FAIL message is also displayed.
The TR mode of battery charger operation is initiated if the Main AC buses
are powered, the BATT switchlights are ON and any one the following
events occur:
• The Auxiliary Hydraulic Pump (AUX PUMP) is selected ON (any
method)
• The APU START switch is depressed
• Selection of the ESS DC BUS BATT switch to ON (automatically or
manually)
In the TR mode, the battery chargers are each capable of supplying a
continuous 50 amperes of DC power to the Essential DC bus in order to
meet demands. If demand exceeds the total 100 amperes supplied by the
chargers, the batteries themselves will begin to share the load and a
discharge will be reflected on the battery ammeters.
E. DC External Power System:
The DC power system includes provisions for connecting an external
source of regulated 28 VDC (29 VDC maximum) power. An external DC
power receptacle is located on the lower right forward fuselage (Figure 9).
Working in conjunction with the DCBPCU, the external DC receptacle has
provisions to protect aircraft electrical circuits from overvoltage,
undervoltage and reversed polarity. Detected faults or input voltage greater
than 29 VDC will cause external DC power to be automatically
disconnected.
With the external DC power source connected and operating, a blue DC
EXT PWR indicator on the cockpit overhead panel (Figure 17) will
illuminate. If CAS is operating, an blue DC EXT POWER message is also
displayed. With all EPMP AUTO/SEL switchlights in AUTO, selection of the
AUX PWR switch (Figure 0) provides external DC power to the Left Main,
Right Main and Essential DC buses. The Essential DC bus in turn supplies
power to the Essential AC bus through the E-inverter.
F. Standby Electrical Power System:
The standby electrical power system consists of a hydraulic motor-driven
generator and a Generator Control Unit (GCU). When no AC power is
available from either main AC bus or the auxiliary power source, Phase A of
the Essential AC bus and the Essential DC bus can receive power from this
system.
With the motor-generator operating, selection of the E INVERT switchlight
(STANDBY ELECTRICAL POWER control panel, Figure 4) to ON supplies
50 amperes of filtered 28 VDC power to the E-inverter. The E-inverter in
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turn supplies AC power for Phase A of the Essential AC bus. Selection of
the TRU switchlight to ON supplies 5 kVA of 115 VAC, 400 Hz power from
the motor-generator to the TRU. The TRU in turn supplies DC power to the
Essential DC bus.
For more information about the standby electrical power system, see
Section 2A-24-20, AC Electrical Power System.
G. Emergency Power System (SN 1000 through 1466):
　
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