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

number.
The manual trim rate is 0.5 degrees per second at low Mach number and decreases
gradually to 0.3 degrees per second as the Mach number increases.
Mach Trim
Mach trim is available only if autopilot is off (manual pitch trim mode). The Mach
trim system provides longitudinal stability, using Mach speed information from the
ADCs and varies the angle of incidence of the horizontal stabilizer by commanding
the horizontal stabilizer actuator. Mach trim provides automatic compensation of
airplane pitching with changes of Mach number. The trim rate follows a schedule
dependent on Mach number. The Mach number is transmitted to the FCUs from the
airplane Air Data Computers (ADCs) which pass command signals to the MDU.
The Mach trim authority ranges from 0.5° nose up at 0.85 Mach to 1.8° nose up @ 0.9
Mach. The trim rate varies between 0.06 and 0.03 degrees per second as Mach
increases.
Automatic Pitch Trim
In the auto mode, the Mach trim inputs are inhibited. When automatic flight is
engaged, the trim system will take its commands from the AFCS. The AFCS function
is performed by the Integrated Avionics Computers (IACs). The FCU will receive
motor commands from the AFCS through the IACs, then pass the command signals to
the MDU. Trim rate and motion is received by the AFCS and monitoring is also
performed in the FCU.
NOSE
DN
NO SE UP
DISC
MASTER
GX_10_021
Stabilizer Trim Lever Switches
Enables pilot to vary stabilizer trim according
to flight requirement. Both levers must be
pushed fully up or fully down to activate the
pitch trim.
Master Disconnect Switch
Provides a disconnect command to
the AFCS, and disconnects the
pitch trim function and stall pusher
while the switch is held.
NOTE:
The pilot control column
is shown, copilot's is similar.
IC
R/T
P I LOT T R A I N I N G GU I D E
FLIGHT CONTROLS
10-26 For Training Purposes Only
Sept 04
Manual trim has priority over autopilot pitch trim and mach trim. If the pilot or copilot
trim switches are activated with the autopilot engaged, the FCU will generate a signal,
causing the autopilot to disengage. The automatic pitch trim rate operation is from 0.5
to 0.015 degrees per second.
Stabilizer Trim Display
The EICAS page provides a full time display of the horizontal stabilizer trim position
and system status. The display is grouped with the display for the aileron and rudder
trims. The horizontal stabilizer trim position is represented by a pointer, moving on a
vertical linear scale. The pointer includes a digital readout of the trim value. The range
of stabilizer movement in degrees is converted to units from 0 to 14 for the purpose of
position display.
A “CONFIG STAB TRIM” red warning message is accompanied by a “NO
TAKEOFF” voice message, and is displayed during the takeoff roll if the stabilizer
trim is set outside the allowable takeoff range.
The color of the pointer and digital readout is dependent on system status:
• WHITE - on ground or during takeoff if the horizontal stabilizer trim is trimmed
outside the takeoff range (green band)
• GREEN - operative, and when on the ground or during takeoff, trimmed within the
takeoff range
When the airplane is on the ground or during takeoff, the trim takeoff range is
displayed as a green band within the white scale. In flight, the takeoff range (green
band) is removed.
ND
STAB
3.5
NU
ND
STAB
7.2
NU
GX_10_022
Green Band (takeoff)
Between 4.5 and
11 units.
Trim Scale
Pitch trim range for the
horizontal stabilzer
trim position indication.
Position Pointer/Digital Readout
Moves vertically (in 0.1 units)
along the scale to indicate the trim
setting.
NU
ND
– Nose Up
– Nose Down
Top and bottom of
the scale.
The pointer/digital readout will turn
white with a “ ”
warning message.
CONFIG STAB TRIM
For Training Purposes Only
Sept 04
10-27
P I LOT T R A I N I N G GU I D E
FLIGHT CONTROLS
Stabilizer in Motion Aural Warning
The stabilizer in motion aural clacker signals operation of the horizontal stabilizer
under the following conditions:
• Operation of more than 3 seconds at a rate greater than 0.2 deg/sec OR
• More than 6 seconds at a rate greater than 0.08 deg/sec
Horizontal stabilizer trim position and condition is continuously monitored and any
fault detected is displayed on EICAS.
SPLRS/STAB In Test
An advisory message “SPLRS/STAB IN TEST” will be displayed when the spoilers
　
中國航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：龐巴迪挑戰(zhàn)者手冊5(125)