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EFFECTIVITY
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GUN 001-012, 016-099, 101-110, 115 (Continued)
GUN 013-015, 111-114, 201-999
The main battery and the auxiliary battery supply at least 60
minutes of AC and DC power when normal sources are not
available. The batteries supply DC power to the DC standby bus
and the battery buses. The batteries use the static inverter to
supply power for the AC standby bus. The inverter receives DC
power from the batteries through the static inverter remote
control circuit breaker (RCCB) in the J9. This RCCB is normally
closed so the static inverter normally has power. This lets you
monitor the static inverter output on the P5-13.
The dual battery remote control circuit breaker (RCCB) closes
to put the two batteries in parallel. This RCCB, which is also in
the J9, is normally open and only closes when the batteries
supply standby power. See the DC generation system section
for more information about the operation of this RCCB.
GUN ALL
CAUTION: WHEN YOU CLOSE THE BATTERY SWITCH, THE
BATTERY AND STANDBY BUSES HAVE POWER.
YOU WILL DISCHARGE THE BATTERY TO ZERO
VOLTS VERY FAST. YOU SHOULD GET AN AC
POWER SOURCE ON THE ELECTRICAL SYSTEM
QUICKLY.
STANDBY POWER SYSTEM - GENERAL DESCRIPTION
EFFECTIVITY
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BOEING PROPRIETARY - Copyright#- Unpublished Work - See title page for details.
737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
24-34-00-005
STANDBY POWER SYSTEM - GENERAL DESCRIPTION
STANDBY POWER SYSTEM - GENERAL DESCRIPTION
EFFECTIVITY
GUN 001-012, 016-099, 101-110, 115 24-34-00
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737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
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STANDBY POWER SYSTEM - GENERAL DESCRIPTION
STANDBY POWER SYSTEM - GENERAL DESCRIPTION
EFFECTIVITY
GUN 013-015, 111-114, 201-999 24-34-00
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THIS PAGE IS INTENTIONALLY LEFT BLANK
STANDBY POWER SYSTEM - GENERAL DESCRIPTION
24-34-00
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D633A101-GUN Jun 10/2005
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737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
Purpose
The standby power control unit (SPCU) gives manual and
automatic power source selection control of the battery and
standby buses.
The SPCU supplies DC system failure data to the P5-13
electrical meters, battery, and galley power module.
The SPCU also controls some power distribution relays in the
electrical system.
Location
The SPCU is in the P6 panel. The P6 panel is in the flight
compartment, behind the first officer seat.
General Description
The SPCU monitors the position of the battery and standby
power switches. It also monitors AC, DC, and battery buses to
control the connection of these items to the correct power
source:
* Battery bus
* Switched hot battery bus
* AC standby buses
* DC standby buses.
The SPCU controls electrical power distribution by these
internal relays:
* Battery bus normal relay (K2)
* Battery bus alternate relay (K1)
* Standby normal relay (K5)
* Standby DC alternate relay (K3)
* Switched hot battery bus relay (K8).
The SPCU monitors and sends standby power system controls
and relay failure data to the P5-13 module. These are the
failures:
* SPCU fail (power supply or relay not in correct position)
* Battery charger does not operate.
See the electrical power section for more information about
how to use P5-13 built-in test equipment (BITE).
The SPCU controls power distribution with these relays:
* TRU 3 transfer relay (R622)
* Bus tie relay (R9).
The SPCU has circuit breakers on its front panel. These circuits
breakers are for electrical bus sections and for indication
circuits.
STANDBY POWER SYSTEM - STANDBY POWER CONTROL UNIT (SPCU)
EFFECTIVITY
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D633A101-GUN Jun 10/2005
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24-34-00-020
STANDBY POWER SYSTEM - STANDBY POWER CONTROL UNIT (SPCU)
STANDBY POWER SYSTEM - STANDBY POWER CONTROL UNIT (SPCU)
　
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