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May 30/02
ELECTRIC POWER
MONITOR Panel
Figure 6 (Sheet 4 of 8)
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ELECTRIC POWER
MONITOR Panel
Figure 6 (Sheet 5 of 8)
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ELECTRIC POWER
MONITOR Panel
Figure 6 (Sheet 6 of 8)
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ELECTRIC POWER
MONITOR Panel
Figure 6 (Sheet 7 of 8)
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ELECTRIC POWER
MONITOR Panel
Figure 6 (Sheet 8 of 8)
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AC Electrical Power System Simplified Block Diagram
Figure 7
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PRODUCTION AIRCRAFT SYSTEMS 2A-24-00
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Converter FAILED FAN Flag
Figure 8
OPERATING MANUAL
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External AC/DC Power Connection Access Panels
Figure 9
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Overhead Annunciator Panel
Figure 10
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APU Control Panel
Figure 11
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APU LOAD/ELWS Annunciators
Figure 12
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2A-24-30: DC Electrical Power System
1. General Description:
The GIV DC electrical power system supplies power to the DC electrical buses
and feeders for distribution to DC systems and equipment.
Figure 1 shows the entire GIV electrical power system in simplified form; Figure
16 shows only the DC electrical power system in simplified form. Units and
components for the DC electrical power system are shown in Figure 2. They are
as follows:
• Two Variable-Speed, Constant-Frequency (VSCF) Converters
• Transformer-Rectifier Unit (TRU)
• Two Nickel Cadmium Batteries
• Two Battery Chargers
• DC External Power System
• Standby Electrical Power System
• Emergency Power System (SN 1000 through 1466)
• Emergency Power System (SN 1467 and Subsequent)
• DC Bus System
• Ground Service Bus (SN 1455 and Subsequent)
• DC Bus Power Control Unit (DCBPCU)
• Power Distribution Box (PDB)
Similar to the AC electrical power system, a DC Bus Power Control Unit
(DCBPCU) controls DC power application from the various power sources to the
DC buses. The DC bus system consists of the Left Main DC bus, Right Main DC
bus and an Essential DC bus.
2. Description of Subsystems, Units and Components:
A. Converters:
Two alternator-powered converters are the primary source of DC power for
the aircraft electrical system. Each converter transforms alternator output
to 28 VDC, 250 ampere current. DC output voltage from the converter is
maintained at 28 (±5) volts at the point-of-regulation from zero load to full
load.
During normal operation the two converters share the DC electrical system
loads with the left converter supplying power to the Left Main and Essential
DC buses, and the right converter supplying power to the Right Main DC
bus. If one converter should fail and the Transformer-Rectifier Unit (TRU) is
failed, the remaining converter assumes all DC loads, although some load
shedding may be necessary.
Both converters are located in the tail compartment. For more information
about the converters, see Section 2A-24-20, AC Electrical Power System.
B. Transformer-Rectifier Unit:
A 300 ampere-rated DC Transformer-Rectifier Unit (TRU) provides 28 VDC
power to the Left and Right Main DC buses during ground operation. If a
converter channel fails in flight, the TRU, powered by three-phase power
from the Left or Right Main AC bus, can supply 300 amperes of DC power
to the Left and Right Main AC buses. The DCBPCU provides overcurrent
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sensing and protection for the TRU. Both the TRU and DCBPCU are
located on the right avionics rack.
Failure of a TRU is accompanied by an amber TRU FAIL message on the
Crew Alerting System (CAS). If TRU temperature exceeds 374° F (190° C),
a thermal switch on the TRU will close, causing an amber TRU HOT
message to be displayed on CAS.
　
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