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CNTL Key.............................................................................................................. 6-76
TEST Key.............................................................................................................. 6-77
Fire Test ................................................................................................................ 6-78
Stall Test ............................................................................................................... 6-79
Aural Warning Test ............................................................................................... 6-80
Lamp Test ............................................................................................................. 6-81
EMER CNTL ......................................................................................................... 6-82
System Integration ............................................................................................................ 6-83
For Training Purposes Only
Sept 04
6-1
P I LOT T R A I N I N G GU I D E
ELECTRICAL
INTRODUCTION
VARIABLE FREQUENCY POWER GENERATION SYSTEM
The Global Express utilizes an AC power generation system based on Variable
Frequency Generators (VFG). The use of variable frequency power engenders several
advantages including:
• An increased efficiency of 80% compared with fixed frequency systems where
efficiency is in the order of 65%
• Ease of voltage conversion
• Reduction in system weight due to lighter alternator and distribution cables; and
• Increased reliability due in large part to the eradication of Integrated Drive
Generators (IDGs)
GENERAL
The airplane AC electrical power generation and distribution system (EPGDS)
consists of four 40 kVA, engine-driven, variable frequency generators (VFG), and one
constant frequency 40 kVA APU generator. Control and protection of the generators is
provided by five identical generator control units (GCU). Distribution systems furnish
power to the following buses, through the AC power center (ACPC) and the cockpit
circuit breaker panel (CCBP).
• AC bus 1, 2, 3, 4 (ACPC)
• AC bus 1A, 2A, 3A, essential (CCBP)
A ram air turbine (RAT), deployable during flight, supplies 115-volt, 400-Hz, 3-phase
AC power 9 kVA for emergency use (when all other AC sources have been lost) to
supply AC power to the AC essential bus. Mounted on the RAT is a hydraulic pump
which powers hydraulic system No. 3.
For other load devices requiring DC power, 115-volt AC power is converted to 28-volt
DC power by four 150 Amp transformer-rectifier units (TRU). 28-volt DC power is
distributed through the DC power center (DCPC) and the secondary power
distribution assemblies (SPDA) onto the following buses:
• DC bus 1 and 2
• DC essential bus
• Battery bus
• DC emergency bus
The 25-ampere-hour, 24-volt DC avionics battery provides power to the following:
• Stored energy to selected electronic equipment during normal ground operations
• During flight in an emergency (loss of all generators) to the flight essential DC
loads
6-2 For Training Purposes Only
Sept 04
P I LOT T R A I N I N G GU I D E
ELECTRICAL
The 42 ampere-hour, 25.2 volt DC APU battery provides power to the following:
• Stored energy for starting the APU during both ground and flight operations
• During flight in an emergency (loss of all generators) to the flight essential DC
loads
The following buses are connected directly to their respective battery terminals:
• Avionics battery direct bus
• APU battery direct bus
Battery chargers and battery heaters, powered by the main AC buses, maintain the
main and APU batteries in a charged and warm condition.
An Electrical Control Panel, located in the cockpit, provides control of all generators,
external AC and DC power and battery master.
An Electrical Management System (EMS), located in the cockpit, controls and
displays the status of circuit breaker, on the two control display units (CDU).
External AC power, supplied through the AC receptacle, situated on the aft left side of
the airplane, (on the fairing at the root of the wing trailing edge), provides power to:
• AC bus 1, 2, 3, 4
• AC 1A, 2A, 3A and essential bus
External DC power, supplied through the DC receptacle, situated on the aft underside
of the fuselage, provides power to the APU battery direct bus.
The APU can be started using external DC power, however, a serviceable avionics
battery is required.
The airplane batteries cannot be charged through external DC power, since the APU
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