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main AC buses or single-phase power from the E-inverter powered by the
Essential DC bus.
The ACBPCU automatically connects the AC buses to the appropriate
power source in a set order. If more than one power source is available, the
system automatically assigns power to the:
(1) Left Main AC bus from:
(a) Left alternator/converter
(b) APU alternator or external AC power
(c) Right alternator/converter
(2) Right Main AC bus from:
(a) Right alternator/converter
(b) APU alternator or external AC power
(c) Left alternator/converter
(3) Essential AC bus from:
(a) Left Main AC bus
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(b) Right Main AC bus
(c) E-inverter
Circuit breakers and overload sensors protect the AC bus distribution
system from shorts and overloads. If a circuit breaker’s rated amperage is
exceeded, the circuit breaker will automatically open to protect the
component. Circuit breakers may also be manually opened as necessary
by the flight crew. Regardless of how circuit breakers are opened, they
must always be manually closed.
Overload sensors are used in large current applications to disconnect a
system when an overload condition exists. The sensors are operated
thermally and although the sensor itself is self-resetting, the circuit
breakers that the sensors may open as a result of overload must be
manually closed.
3. AC Electrical Power System Operation:
(See Figure 6.)
The flight crew controls the electrical power system through the EPMP. It consists
of 13 digital displays and 33 switchlights that allow the selection of electrical
power sources and display of voltages, amperages, frequencies and percentages
of total load.
When normally configured (L MAIN, R MAIN and ESS AC BUS switches selected
to AUTO), the EPMP allows automatic operation and selection of electrical power
sources in order to minimize flight crew workload. Manual operation is always
available, however, in order to hard-select or deactivate power sources.
With external AC power available and the ELECTRIC MASTER AUX PWR switch
selected ON, external AC power is supplied to the Left Main, Right Main and
Essential AC buses. Power is also available to both battery chargers and the
TRU.
With the alternators operating and converters supplying power, selection of the
ELECTRIC MASTER LEFT PWR and RIGHT PWR switches to ON allows left
converter output to the Left Main AC bus and Essential AC bus, and right
converter output to the Right Main AC bus. Simultaneous bus connection to two
power sources is impossible, thus no interlock is incorporated.
If the APU is the only source of power and the AUX PWR switch is selected to ON,
the APU alternator powers the Left Main AC bus, Right Main AC bus and Essential
AC bus (through the Left Main AC bus).
The Essential AC bus provides power to equipment essential for safe flight.
Normally, the Left Main AC bus supplies the Essential AC bus, but the Right Main
AC bus, E-inverter (Phase A only) or batteries (through the E-inverter) are also
capable of powering the bus.
Illumination of the AC RESET amber switchlight indicates a transient problem, bus
fault or logic problem. If the problem is a Left Main or Right Main AC bus fault or
overcurrent condition, depressing the switchlight resets the system. If the
switchlight extinguishes, the fault has been cleared. If it remains illuminated, the
fault remains. If the problem is an Essential AC bus fault or overcurrent condition,
the ACBPCU will automatically transfer the bus to another power source in an
attempt to remain powered.
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PRODUCTION AIRCRAFT SYSTEMS 2A-24-00
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4. Controls and Indications:
A. Circuit Breakers:
Circuit breakers controlling the AC bus distribution system are shown in
bold print in the tables that follow. Circuit breakers receiving power from the
controlling circuit breaker are shown immediately following that circuit
breaker.
Example: The L TEMP CONT AC circuit breaker receives power from the
PILOT φA section of the Essential AC bus. Thus the PILOT φA circuit
breaker is the controlling circuit breaker.
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2A-24-00 PRODUCTION AIRCRAFT SYSTEMS
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Revision 7
Essential AC Bus CBs
Table 1
Circuit Breaker Name CB Panel Location (PDB Section)
PILOT φ A PDB AC ESS
L TEMP CONT AC P H-11
R TEMP CONT AC P I-11
BLEED AIR ISO S/O V PO D-12
CABIN PRESS 115V PO D-11
ESS AC φA VM P A-13
BOT A/C LT
　
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