曝光台 注意防骗
网曝天猫店富美金盛家居专营店坑蒙拐骗欺诈消费者
AIRSPEED DISPLAY
The airspeed display is a moving vertical tape, with the digital display of the current airspeed in the fixed window. The
display is located to the left of the attitude sphere on the PFDs. The current Mach number is indicated as a digital value
at the bottom of the tape. If the aircraft speed is greater than 0.4 Mach, the crew can select a Mach tape, which replaces the
airspeed tape.
The indicated airspeed tape has an airspeed range from 40 to 400 kt. The tape has a scale that is marked every 5 kt and
numerically marked every 20 kt.
REFERENCE SPEEDS
The takeoff reference speeds are presented on the speed scale as a V1, VR, V2, and VT. Manually set V speed values show
in cyan characters; optional FMS-calculated V speed characters show in magenta.
The FGP SPEED knob is used to select and set the airspeed reference bug to the desired speed on the airspeed tape. The
speed bug is located beside the selected speed with a ± 5 knot deviation indication.
When the center of the SPEED knob is depressed, the speed reference toggles between Mach and speed.
LOW/OVERSPEED/FLAP SPEED CUES
A low speed cue indicates a calculated airspeed of 1.06 VS. It appears from the lower portion of the airspeed scale and is
displayed as a solid red line that changes to an expanded alternating red and black band when the aircraft is within a few
knots of activating the stickshaker. The top of this cue visually represents the speed at which the stick shaker will activate.
An overspeed cue is provided to indicate the maximum operating speed. It appears in the upper portion of the airspeed scale
and is displayed as a solid redline that changes to an alternating red and black band when approaching overspeed.The overspeed
cue reduces to the flap operating speed limit when the flaps are extended.
TREND VECTOR
The airspeed trend vector originates from the tail of the indicated airspeed arrow. The magenta trend vector moves vertically
in response to the aircraft acceleration or deceleration indicating the speed predicted in the next 10 seconds.
FLIGHT INSTRUMENTS
Volume 2 Flight Crew Operating Manual Sep 13/2004
11-01-12 CSP 100-6 REV 1
AIR DATA SYSTEM (Cont)
ALTIMETER BAROMETER KNOB
The ALTM BARO knob is rotated to increase or decrease barometric pressure setting. The barometric setting is displayed
on the PFD. The standard barometric pressure setting of 29.92 inches of mercury, or 1013 hPa, is selected when the center
of the BARO knob is pressed.
AIR DATA REVERSION SWITCH
The AIR DATA switch is located on the reversion panel on the center pedestal. When NORM is selected, the pilot’s and
copilot’s adaptive flight displays receive data from their respective air data computer (ADC).
When ‘1’ is selected, the pilot’s and copilot’s adaptive flight displays receive data from ADC 1 only. An amber ADC 1
message is displayed on both PFDs.
When ‘2’ is selected, the pilot’s and copilot’s adaptive flight displays receive data from ADC 2 only. An amber ADC 2
message is displayed on both PFDs.
AIR DATA COMPUTERS
Each ADC senses total pressure, static pressure, and total temperature. The pressure sensors are solid-state piezoresistive
type, and transform the pressure to an analog electrical signal. The analog signal is then digitized and used for all ADC
calculations. Data is then passed from the ADCs to the cockpit displays, IAPS, other aircraft systems.
The ADC calculates the following air data parameters:
- Pressure altitude
- Static pressure
- Total pressure
- Vertical speed
- Airspeed
- Mach number
- Maximum airspeed (VMO)/maximum mach number (MMO)
- Baro correction
- Barometric corrected altitude
- Static air temperature
- Total air temperature
- True AIRSPEED
- Temperature difference from standard (ISA)
FLIGHT INSTRUMENTS
Feb 22/2006 Flight Crew Operating Manual Volume 2
REV 5 CSP 100-6 11-01-13
AIR DATA SYSTEM (Cont)
PITOT STATIC SYSTEM
The aircraft is equipped with a primary pitot static system and a standby pitot static system. The primary pitot static system
provides total and static pressures to air data computers (ADC) 1 and 2. The pressures are sensed by left and right pitot
static probes. The standby pitot static system provides total and static pressures to the integrated standby instrument. The
pressures are sensed by a standby pitot probe and two flush mounted standby static ports.
The primary pitot static probes each have one total pressure port and two static pressure ports. The standby pitot probe has
a single pressure port. All of the probes and the flush standby static ports are electrically heated. Probe heat is discussed in
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：
Bombardier_Challenger_Global_00-Flight_Instruments(8)
