曝光臺 注意防騙 網(wǎng)曝天貓店富美金盛家居專營店坑蒙拐騙欺詐消費者

used to reset the ELT system from operating to armed by selection from
ARM to ON for one second, then returning the switch to ARM. This is
confirmed by the red LED indicator extinguishing. It should be noted that
reset cannot take place if either the ELT transmitter unit control switch or
the remote switch is selected to ON.
D. Antenna:
The ELT system uses a high performance, externally mounted antenna. It
is located on the top aft portion of the fuselage adjacent to the left engine.
E. Aural Monitor:
An aural monitor provides a distinct signal enabling an airplane with a
transmitting ELT to be located in an area with a large number of aircraft
(e.g., an airport). A beeper, powered by the ELT transmitter is installed to
provide this function. The beeper is not designed to operate continuously,
but to sound at predetermined intervals. The beeper will sound for shorter
periods toward the end of the battery life.
The beeper is loud enough to be heard outside the airplane in areas with
low ambient noise. In areas with high ambient noise, the airplane will have
to be physically checked for a blinking red LED indicator on either the ELT
transmitter unit or remote switch panel.
The aural monitor beeper is usually located in the tail compartment. The
actual location may vary, however, depending on outfitting requirements.
3. Controls and Indications:
(See Figure 12 and Figure 13).
4. Limitations:
A. Flight Manual Limitations:
There are no limitations established for this system as of this revision.
OPERATING MANUAL
2A-23-00 PRODUCTION AIRCRAFT SYSTEMS
Page 50
May 30/02
Revision 7
B. System Notes:
WARNING
DO NOT ALLOW OPERATIONAL TEST DURATION
TO EXCEED FIFTEEN (15) SECONDS.
TRANSMISSIONS THAT EXCEED 15 SECONDS
MAY BE INTERPRETED BY THE SATELLITE
SYSTEM AS A VALID DISTRESS SIGNAL. UNIT
TESTING SHOULD BE COORDINATED WITH THE
LOCAL FAA ATC TOWER AND BE CONDUCTED
WITHIN FIVE (5) MINUTES AFTER THE HOUR.
(1) Reset of a transmitting ELT system cannot take place if either the
ELT transmitter unit control switch or the cockpit remote switch is
selected to ON.
(2) The ARTEX 406 MHz ELT battery must be replaced on or before the
replacement date noted on the battery pack. Tests to verify proper
operation of the unit must be accomplished after battery
replacement.
(3) Operational tests, including ’G’ switch testing, of the ARTEX 406
MHz ELT must be accomplished every twelve (12) calendar months
unless operational regulatory requirements dictate a more frequent
schedule.
(4) The cockpit remote switch is required under TSO-C126 and may not
be disabled or rendered inoperative.
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-23-00
Page 51
May 30/02
Revision 7
ELT Transmitter Unit Front Panel
Figure 12
OPERATING MANUAL
2A-23-00 PRODUCTION AIRCRAFT SYSTEMS
Page 52
May 30/02
Revision 7
ELT Remote Switch
Figure 13
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-23-00
Page 53
May 30/02
Revision 7
OPERATING MANUAL
THIS PAGE IS INTENTIONALLY LEFT BLANK.
2A-23-00 PRODUCTION AIRCRAFT SYSTEMS
Page 54
May 30/02
ELECTRICAL POWER
2A-24-10: General
1. Purpose:
The purpose of the electrical power system is to provide the aircraft with
Alternating Current (AC) and Direct Current (DC) power, and to provide a means
of control, protection and distribution of electrical power required for ground and
flight operations. The Gulfstream IV meets these needs through the use of its
Variable-Speed, Constant-Frequency (VSCF) electrical power system, based
primarily on AC power. The AC power is frequency regulated and converted to DC
power for use by the standard aircraft systems. The AC and DC power is
distributed by separate bus systems. Provisions to convert DC power back to AC
through the use of an emergency inverter are incorporated.
2. General Description:
A. AC Electrical Power System:
(See Figure 1, Figure 2 and Figure 7.)
The primary source of electrical power for the Gulfstream IV is the AC
electrical power system. AC electrical power can be provided to the aircraft
under normal conditions in the following manner:
• Internally by two (2) engine-driven alternators, one mounted on
each engine-driven gearbox, and the respective converter
• Internally through the use of an alternator mounted on the Auxiliary
Power Unit (APU). Normally used for ground operations, the APU
alternator can also serve as an alternate source of power in flight if
one or both alternators fail.
　
中國航空網(wǎng) 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(62)