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

DESCRIPTION
Figure 07−10−36 DC Synoptic Page − DC Electrical Power Distribution 07−10−46
ELECTRICAL
Table of Contents
Vol. 2 07−00−3
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
Page
ELECTRICAL
Table of Contents
Vol. 2 07−00−4
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
THIS PAGE INTENTIONALLY LEFT BLANK
GENERAL
The Challenger 604 primarily uses 115-volt AC power and also 28-volt DC electrical power.
Engine-driven integrated drive generators (IDGs) supply the primary source of AC electrical power. A
generator mounted on the auxiliary power unit (APU) provides an alternate source of AC electrical
power. In flight, if a total loss of AC power occurs, the air-driven generator (ADG) is deployed from
the right side of the forward fuselage to provide an emergency source of AC electrical power.
External AC electrical power is supplied through an electrical power receptacle located on the right
side of the forward fuselage.
Various aircraft systems and components require DC electrical power for operation. DC electrical
power needs are primarily supplied by four transformer rectifier units (TRUs) mounted in the nose
compartment. Two nickel-cadmium (NiCad) batteries, located in the aft equipment bay, store and
provide a source of DC electrical power for normal and emergency operations.
The aircraft is capable of accepting 28-volt DC external electrical power through a DC power
receptacle installed on the rear fuselage below the right engine.
Five circuit breaker panels provide power distribution. Four circuit breaker panels are located in the
flight compartment and the fifth panel is in the aft equipment bay.
Control and operation are accomplished through the ELECTRICAL POWER panel located on the left
side of the overhead panel. AC and DC electrical system information is provided on the EICAS.
AC Electrical Power Sources
Figure 07−10−1
ELECTRICAL
Description
Vol. 2 07−10−1
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
GENERAL (CONT'D)
DC Electrical Power Sources
Figure 07−10−2
ALTERNATING CURRENT (AC) SYSTEM
Description
Three AC generators provide AC power for the aircraft electrical systems. Two engine-driven
generators power all AC buses during normal operations. An APU generator provides a source of
AC electrical power when the aircraft is on the ground with the engines off, and during flight if both
engine-driven generators become inoperative.
ELECTRICAL
Description
Vol. 2 07−10−2
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
ALTERNATING CURRENT (AC) SYSTEM (CONT'D)
AC Electrical System
Figure 07−10−3
Components and Operation
Integrated Drive Generators (IDGs)
Two engine-driven IDGs supply 115-volt AC, 400-Hz, three-phase electrical power to the AC
buses. The IDG consists of two subcomponents, a constant speed drive and an electrical
generator.
The generators are identified on the EICAS AC electrical synoptic page by the symbols GEN 1
and GEN 2 (see Figure 07−10−4). The nominal rating of each generator is 30 kilovolt-amperes
(kVA) to an altitude of 35,000 feet MSL, then 25 kVA to 41,000 feet MSL. In the event of a
single generator failure, the remaining generator is capable of supplying sufficient power for
operation of the main systems.
ELECTRICAL
Description
Vol. 2 07−10−3
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
ALTERNATING CURRENT (AC) SYSTEM (CONT'D)
The generators are controlled by two-position GEN 1 or GEN 2 switches located on the
ELECTRICAL POWER panel. Selecting GEN 1 or GEN 2 switch to ON connects the respective
generator to the main AC buses, provided they are operating normally. Selecting the switches to
OFF/RESET will disconnect the respective generator from the main AC buses. The OFF/RESET
position can also be used to reset the generator control circuit when a fault occurs.
Generator Control Unit
Each IDG is controlled and monitored by its respective generator control unit (GCU). The
GCUs provide protection and bus priority logic during normal and non-normal operations. The
engine generator is tripped off and removed from the AC buses if any of the following
conditions occur:
• Over- and undervoltage
• Over- and underfrequency
• Generator and bus overcurrent
ELECTRICAL
Description
Vol. 2 07−10−4
REV 66, Feb 01/07
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：龐巴迪挑戰者604操作手冊 Operating Manual 3(70)