曝光臺 注意防騙 網曝天貓店富美金盛家居專營店坑蒙拐騙欺詐消費者

crew alerting system (EICAS) display, a white
horizontal analog scale and cyan pointer indicate
position of aileron trim (Figure 15-6).
If cockpit displays are set to reversionary
mode, the trim display does not appear.
The aileron trim circuit breaker is on the left CB
panel in the FLIGHT CONTROLS grouping.
Rudder (Yaw) Trim
The cockpit rudder trim tab is on the center of
the trailing edge of the rudder. It is driven by
an electrical trim actuator in the leading edge
of the rudder, controlled by the RUDDER
TRIM switch. The RUDDER TRIM switches
(centering dual sliding rocker switches) are on
the lower pedestal (see Figure 15-5).
Pushing the RUDDER TRIM switches to the
left, toward the NOSE–L position, causes the
aircraft to yaw toward the left. Pushing it right,
toward NOSE–R, causes opposite movement.
Near the bottom of the EICAS display, a white
horizontal analog scale and cyan pointer indicate
position of rudder trim (Figure 15-6).
If displays are set to reversionary mode, the
trim display does not appear.
The yaw trim circuit breaker is on the left CB
panel in the FLIGHT CONTROLS grouping.
Elevator (Pitch) Trim
The elevator trim tabs are at the trailing edges
of both elevator surfaces. Both tabs travel synchronously.
Each trim tab is connected to a mechanical
actuator by two control rods. The trim
tabs are controlled mechanically through cables
by a mechanical trim control wheel on the left
side of the pedestal beside the throttle controls
(Figure 15-7), or electrically by split switches
on the outboard grip of the control yokes.
The mechanical elevator trim system is a single
cable loop system that routes from the
command wheel in the cockpit to the tail cone,
then through the vertical tail to mechanical actuators
in each of the horizontal tail. The mechanical
actuators move linkages, which move
the trim tabs.
Additional cables connect the autopilot elevator
trim servo to the system. When the control
yoke switches are used or the autopilot is
active, the autopilot servo electrically commands
the entire mechanical system through
its cable linkage.
The elevator pitch trim servo is powered from
the left avionics bus through the AFCS circuit
breaker on the FLIGHT CONTROL pilot CB
panel. It operates only if the AVN PWR switch
is set to the up position. The AVN PWR switch
is on the AVIONICS switch panel, below the
pilot PFD.
Manual Trim
By rotating the trim wheel forward toward the
nose-down position, the trim tabs rotate upward,
causing the elevator system to pitch the
nose of the aircraft down. By rotating the trim
wheel aft, the opposite is true.
TRIM
AILERON
RUDDER
Figure 15-6. Trim Display
Elevator trim position is indicated by a mechanical
pointer, which rides in a slot of the
LED-backlit panel of the throttle quadrant,
connected to the elevator trim cable loop.
Electric Trim
Electric elevator trim is controlled by a split-element
centering thumb switch on the outboard
side of each control yoke (see Figure 15-7).
When the pilot moves both elements of the
rocker switch, the electric elevator trim actuator
moves the cables to trim the aircraft in the
direction selected. Selecting forward trims nosedown.
The electric trim can be overridden by the
mechanical trim. Additionally, pilot pitch trim
inputs override the copilot trim inputs. As the
trim switch is moved to the UP or DOWN
DRAFT
15-8 510OM-00
CITATION MUSTANG OPERATING MANUAL
MANUAL TRIM
ELECTRIC TRIM
LEGEND
MECHANICAL
ELECTRICAL
Figure 15-7. Elevator Trim System
510OM-00 15-9
position, the elevator tabs are repositioned as
indicated by the elevator trim indicator.
Prior to flight, the electric pitch trim system
can be checked for proper operation by moving
both elements of the switch in both directions,
noting whether trim occurs in the
appropriate directions. Check for system malfunction
by attempting to trim with one element
of the switch. If trimming occurs, the
system is malfunctioning and must be restored
to normal operation prior to flight.
NOTE
If a pilot holds only one element of
the trim switch in either the UP or
DOWN position for more than 3 seconds,
the red PTRM message appears
on the upper left of the PFD.
Interrupt runaway or malfunctioning trim by
depressing the red AP/TRIM DISC switch on
the control yoke (see Figure 15-5) and pulling
the AFCS circuit breaker in the FLIGHT CONTROLS
　
中國航空網 m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：CITATION MUSTANG OPERATING MANUAL 2(4)