曝光台 注意防骗
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represents 20 degres down.
Maximum Spoileron
Deployment Mark (white)
Indicates full deployment
point of respective spoileron.
Aileron Position
Indicator (white)
Indicates relative position
of respective aileron.
Aileron Position
Readout (white)
Numeric value represents
position of respective
aileron in degrees.
Flutter Damper Icons
(aileron)
If displayed (white),
indicates respective flutter
damper(s) has failed, or has
low hydraulic fluid level.
Aileron Outlines (blue)
Spoiler Deployment
Readout (white)
Indicates angle of deployment,
in degrees, of respective
spoiler. Two amber dashes
are displayed when input
data is invalid.
FLT Control
Synoptic Page
Spoileron Position
Indicator (white)
Indicates relative position of
respective spoiler. Indicator
is not displayed when
respective spoiler is retracted
or input data is invalid.
An amber X is displayed when
input data is invalid, and
position indicator (arrow) is
removed.
A spoileron with an amber X
indication may still operate
normally.
<0039>
<0039>
<0039>
<0039>
25 RUDDER 25
<0039>
Spoileron Outlines
Green -- Both respective
spoiler electronic control
units (SECU) and both
respective power control
units (PCU) are operative.
White -- One of the SECU
or one of the PCU is
inoperative.
Amber -- Both respective
SECUs and/or both
respective PCUs are
inoperative.
Half--Intensity Magenta --
Input data invalid.
<0039>
<0039>
REV 56, Jan 31/03
Vol. 1 11--20--6
FLIGHT CONTROLS
Ailerons
Flight Crew Operating Manual MASTER
CSP A--013
B. System Circuit Breakers
SYSTEM SUB--SYSTEM CB NAME BUS BAR CB
PANEL
CB
LOCATION
NOTES
Ailerons Trim AILERON DC BUS 2 2 F7
TRIM
Vol. 1 11--30--1
REV 56, Jan 31/03
FLIGHT CONTROLS
Rudder
Flight Crew Operating Manual
CSP A--013
MASTER
1. RUDDER
Directional control about the yaw axis is provided by the rudder control system and assisted
by yaw dampers.
The rudder is hydraulically powered by three power control units (PCU’s) located in the
vertical stabilizer. The PCUs receive mechanical inputs from the rudder pedals via cable
runs and quadrants. Each hydraulic system powers one of the three PCU’s. Both sets of
pedals move simultaneously when operated from either the pilot or the copilot station. Two
yaw dampers (controlled by the flight control computers) are connected to the rudder control
system and are used to improve the aircraft lateral stability.
Rudder pedal centering and artificial feel is provided by a primary feel unit, located on the
copilots rudder pedal pivot assembly. A secondary feel unit, located in the aft fuselage,
ensures that the rudder remains centered in the event of a control disconnect.
In the event of a control jam, the pilots and copilot’s pedals will remain operable through
anti-jam mechanisms, however additional pedal force will be required to obtain rudder
deflection.
Two rudder load limiter assemblies, installed in the vertical stabilizer, give overload (stress)
protection to the rudder control system mechanical components. A rudder load limiter,
installed in the PCU input assembly, allows continued control input movement to the
remaining PCU’s if one PCU becomes jammed.
REV 56, Jan 31/03
Vol. 1 11--30--2
FLIGHT CONTROLS
Rudder
Flight Crew Operating Manual MASTER
CSP A--013
Rudder System
Figure 11---30---1
PILOT
PEDALS
FORWARD
QUADRANT
& ANTI--JAM
MECHANISM
COPILOT
PEDALS
PCU INPUT
LOAD
LIMITER
RUDDER POWER
CONTROL UNITS
RUDDER TRIM
ACTUATOR
SUMMING
MECHANISM
AFT
QUADRANT
LOAD
LIMITERS
SECONDARY
FEEL
MECHANISM
PRIMARY
FEEL UNIT YAW
DAMPERS
Vol. 1 11--30--3
REV 56, Jan 31/03
FLIGHT CONTROLS
Rudder
Flight Crew Operating Manual
CSP A--013
MASTER
The rudder trim is electrically operated and manually controlled using the trim selector on the
center pedestal. Operating the trim selector to the NL/NR (nose left/nose right) repositions
the rudder control cables to move the rudder. Hydraulic pressure from at least one of the
hydraulic system is required to move the rudder. Actuation of the rudder trim will not cause
rudder pedal deflection.
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