曝光台 注意防骗
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Lo/Lo/Lo Autothrottle Disconnect 7
Lo/Hi/Lo Manual Autopilot Disconnect 8
Warning and caution CAS alerts can be silenced by pressing the
associated switch on the warning/caution inhibition panel. Advisory CAS
alerts cannot be manually silenced, but will automatically silence after two
(2) seconds. Airplane overspeed cannot be silenced as long as the
overspeed condition exists. The landing gear unsafe warning can be
silenced, either manually or automatically, in all cases except when the
flaps are fully extended without the landing gear being down and locked.
The airplane has a radio altimeter-activated automatic horn silencing
system that will function above 1200 ft AGL except when the flaps are fully
extended without the landing gear being down and locked.
H. SPZ-8400 Tone Generator:
A tone generator is incorporated into each fault warning computer to
provide audible sounds, calling the attention of the flight crew to an
associated message or condition. Tone volume is adjusted from the TONE
prompt on the TEST page of the pilot’s display controller. The aural tones
provided by the tone generator are:
Type of Aural Tone: Condition:
Klaxon™ (Hi/Lo - Hi/Lo) Landing Gear Unsafe
OPERATING MANUAL
2A-31-00 PRODUCTION AIRCRAFT SYSTEMS
Page 22
January 31/02
Revision 6
Type of Aural Tone: Condition:
Cricket Airplane Overspeed
Beep Altitude Alert
1 Chime CAS Advisory (1)
2 Chimes CAS Caution
3 Chimes CAS Warning
Lo/Lo/Lo A/T Disconnect
Lo/Hi/Lo Manual A/P Disconnect
NOTE(S):
(1) Only those messages not resulting from deliberate crew action.
Warning and caution CAS alerts can be silenced by pressing the
associated switch on the warning/caution inhibition panel. Advisory CAS
alerts cannot be manually silenced, but will automatically silence after one
cycle. Airplane overspeed cannot be silenced as long as the overspeed
condition exists. The landing gear unsafe warning can be silenced, either
manually or automatically, in all cases except when the flaps are fully
extended without the landing gear being down and locked. The airplane
has a radio altimeter-activated automatic horn silencing system that will
function above 1200 ft AGL except when the flaps are fully extended
without the landing gear being down and locked.
The following CAS advisory messages do not generate a tone when
activated:
AC EXT POWER FMS 3 ACTIVE ISOLATION VLV OPEN
APU ALT OFF FUEL INT TANK OPEN MAINT SWITCH ON
L-R COWL AI ON FUEL XFLOW OPEN SPD BRAKE EXTENDED
DC EXT POWER GND SPOILER UNARM TONE GEN 1-2 FAIL
EXT BATT SWITCH ON IRS 1-2 HI LAT ALN L-R WING AI
FGC NOT USING IRS 1-2
I. Maintenance Test Switch:
A maintenance test switch is installed above the left and right radio racks
(Figure 12). Airplanes having ASC 221 have an additional switch on the
copilot’s circuit breaker panel. The maintenance test switches are labeled
MAINT TEST and are guarded to OFF. When any MAINT TEST switch is
selected ON, advisory CAS messages that are normally suppressed can
be viewed. Trend and limit monitoring is also inhibited. A blue MAINT
SWITCH ON advisory message is also displayed to alert the flight crew
that the MAINT TEST switch is on.
J. Trend and Limit Monitoring System:
Each fault warning computer contains a trend and limit monitoring function
designed to record, store and display the following types of data:
• Engine exceedances of the following maximum limits:
• Turbine Gas Temperature (TGT)
• Low Pressure Turbine Speed (LP RPM)
• High Pressure Turbine Speed (HP RPM)
• Low Pressure Turbine Vibration (LP EVM)
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-31-00
Page 23
January 31/02
Revision 6
• High Pressure Turbine Vibration (HP EVM)
• Parameter that tripped the exceedance monitor
• APU exceedances of the following maximum limits:
• Turbine Gas Temperature (TGT)
• Turbine Speed (RPM)
• Parameter that tripped the exceedance monitor
• Brake temperature exceedances and time of occurrence
• Parameter that tripped the exceedance monitor
Trend data recording is used to monitor the long term histories and relative
health of the engines and APU. Engine trend data is automatically recorded
when the airplane reaches approximately 100 knots on takeoff, again when
the airplane establishes steady cruise flight and thereafter at approximately
ninety (90) minute intervals. APU trend data is recorded just prior to the first
engine start of a flight. In addition to these trend recordings, an engine start
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