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

actuator to annunciate to the pilot when the display position may not
be accurate. The secondary section structure, construction, and operation
is the same as the primary and both sections drive a common
screwjack-type actuator to move the leading edge of the horizontal stabilizer
up or down. The primary motor is actuated by manual primary
pitch trim (control wheel trim switch), configuration trim, and Mach
trim systems. The secondary motor is provided as a backup for primary
trim and is operated by the secondary pitch trim and the autopilot.
The following CAS illuminations are specific to the pitch trim system:
PITCH TRIM SELECTOR SWITCH
This switch, as shown in Figure 5-4, is located on the trim switch panel
(pedestal) and is used to select which trim system will be used. The PRI
position enables the primary trim switches in the control wheels, while
the SEC position will enable the secondary trim switches in the panel.
Selecting OFF or SEC will disable all #1 IC-600 trim functions. When set
to OFF position, the power and ground circuits for the motor command
functions in the actuator control box are disconnected and a CAS is
posted.
The following CAS illumination is specific to the pitch trim system:
CAS Color Description
PIT TRIM MISCMP Red Miscompare between the primary and secondary
pitch trim on the ground and either
thrust lever is advanced to MCR or above.
PIT TRIM MISCMP White Miscompare between the primary and secondary
pitch trim in flight.
CAS Color Description
PITCH TRIM OFF White Pitch trim is selected to OFF.
Pilot’s Manual
5-16 PM-132A
PRIMARY PITCH TRIM
Each control wheel has a control wheel trim switch located on the outboard
horn of each control wheel (Figure 5-1). Each switch is a four position
(LWD, RWD, NOSEDOWN and NOSEUP) barrel switch with a
momentary-action push button switch in the center of the barrel. This
switch is used to input trim commands for pitch and roll and autopilot
functions. Normally, the pitch trim control switch (Figure 5-4) is positioned
to PRI. This position enables the control wheel trim switches and
causes commands from either of these switches to be processed by the
#1 IC. To complete the trim command circuit, the arming switch (button)
on the top of the barrel must be depressed simultaneously with
movement of the barrel. Trim commands from the pilot’s control wheel
trim switch will override commands from the copilot’s. Primary trim
speed is variable and is automatically controlled by the #1 IC based on
indicated airspeed. The IC uses airspeed information from both ADCs
to schedule trim speed and Mach trim. The #1 IC sends the primary
trim commands to the primary trim actuator. The trim actuator and the
IC both monitor the trim operation. The primary trim actuator performs
a power-up circuit check. If the actuator detects a fault during the
power-up check, a fault is posted on the CAS. Primary trim will still be
available with the fault displayed; however, operation may be at a low
trim rate and configuration trim and Mach trim may be inoperative depending
on the malfunction. The primary trim actuator and #1 IC both
monitor primary trim operations for a number of possible malfunctions
including uncommanded trim and trim in the wrong direction. If either
of these malfunctions is detected by the trim actuator, a fail is displayed
on the CAS and primary trim is disabled.
NUP
NDN
SEC
PITCH TRIM
PRI
O
F
F
SEC
NOSE
LEFT
OFF
NOSE
RIGHT
RUDDER TRIM
TRIM SWITCH PANEL
Figure 5-4
Pilot’s Manual
PM-132A 5-17
Electrical power for primary pitch trim is provided by the L ESS BUS
and is protected by the TRIM-PRI PITCH circuit breaker located on the
pilot’s circuit breaker panel (FLIGHT group). The dc electrical power to
the #1 IC is also required for primary pitch trim, except for primary bypass
trim. The power for #1 IC is provided by the L ESS BUS and is
protected by IC/SG 1 circuit breaker located on the pilot’s circuit
breaker panel (INSTRUMENT/INDICATIONS group).
Bypass Trim
Primary trim reverts to bypass as a result of a detected malfunction or
#1 IC failure and cannot be selected by the crew. When in bypass trim a
fault is displayed on CAS and control wheel trim switch commands go
directly to the primary trim actuator, bypassing the IC circuits. The #1
IC trim functions (IC controller/monitored primary trim, configuration
trim, and Mach trim) are all disabled in this case. When in bypass trim,
the primary trim actuator operates at only two speeds (high or low).
　
中國航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：BOMBARDIER_Learjet_0-Flight_Controls_and_Avionics(10)