曝光臺 注意防騙 網曝天貓店富美金盛家居專營店坑蒙拐騙欺詐消費者

• Externally through use of an external AC power supply
AC electrical power can be provided to the aircraft under abnormal/
emergency conditions through the use of an Emergency Inverter
(commonly referred to as the E-Inverter) and/or a Standby Electrical Power
System for Transformer Rectifier Unit (TRU) operation.
An AC Bus Power Control Unit (ACBPCU) controls distribution of AC power
from its various sources to the AC distribution buses.
The ELECTRIC POWER MONITOR Panel (EPMP), located on the cockpit
overhead panel, contains the majority of the electrical control and
monitoring functions. In addition, some electrical system annunciators are
incorporated on the overhead annunciator panel.
B. DC Electrical Power System:
(See Figure 1, Figure 2 and Figure 16.)
DC electrical power can be provided to the aircraft under normal conditions
in the following manner:
• Internally by two (2) VSCF converters
• Internally by a Transformer Rectifier Unit (TRU), where fixed
frequency AC power is rectified by the TRU to provide a 28 VDC
nominal output
• Internally by two (2) nickel cadmium batteries, which are provided to
start the APU, run the Auxiliary Hydraulic System (AUX) pump, and
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-24-00
Page 1
May 30/02
Revision 7
to supply power to the Essential DC Bus when not powered by the
TRU. Each battery has a dedicated battery charger to provide
battery charging.
• Externally through use of an external DC power supply
DC electrical power can be provided to the aircraft under abnormal/
emergency conditions through the use of a battery-operated Emergency
Power System and/or a Standby Electrical Power System to provide 28
VDC for Emergency Inverter operation.
Like the AC electrical power system, a DC Bus Power Control Unit
(DCBPCU) controls distribution of DC power from its various sources to the
DC distribution buses.
Also like the AC electrical power system, the EPMP contains the majority of
the electrical control and monitoring functions. In addition, some electrical
system annunciators are incorporated on the overhead annunciator panel.
C. ELECTRIC POWER MONITOR Panel (EPMP):
Shown in Figure 3, the EPMP is the major switching and indication control
panel for the electrical power system. Located on the cockpit overhead
panel, the EPMP provides the automatic (AUTO) mode of system
operation. Provisions exist, however, to manually override AUTO operation
and select any and all buses to any one of the possible desired power
sources. (This provision is called hard selection.) Each channel of the
system is provided with metering to read voltage, frequency and percent of
loading.
Out-of-limit range markings consist of a red bar to the left of the indications
for voltage, frequency and percent of loading. It should be noted here that
out-of-limit ranges do not “latch”, rather, when normal ranges return, the
out-of-limit range indicator extinguishes.
D. Remote Power Supply:
A remote power supply, located in the right avionics bay (Figure 2), is
dedicated to the EPMP for switchlight, digit and out-of-limit indicators
illumination. It contains redundant power supplies in the form of two
identical boards having individual inputs and outputs; these boards being
crosstied for reliability. All remote power supply outputs are fed directly to
the EPMP through a dedicated interface.
If a power supply failure occurs or a single battery switchlight capsule is
selected OFF, the remote power supply has an alarm circuit that will prompt
an amber EPMP POWER FAIL message for display on the Crew Alerting
System (CAS).
Input power sources to the remote power supply include two sources from
the Essential DC bus and one source from each battery. In addition to the
two power supply boards, one additional card provides EPMP light dimmer
control and failure detection circuitry power.
3. Subsystems of the Electrical Power System:
The electrical power system is divided into the following subsystems:
• 2A-24-20: AC Electrical Power System
• 2A-24-30: DC Electrical Power System
OPERATING MANUAL
2A-24-00 PRODUCTION AIRCRAFT SYSTEMS
Page 2
May 30/02
Revision 7
GIV Electrical Power
System Simplified Block
Diagram
Figure 1
OPERATING MANUAL
2A-24-00
Page 3 / 4
May 30/02
GIV Electrical Power System Component Locations
Figure 2
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-24-00
Page 5
May 30/02
Revision 7
GIV ELECTRIC POWER MONITOR Panel
Figure 3
　
中國航空網 m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：灣流4操作手冊 Gulfstream IV Operating Manual 1(63)