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midpoint of the torque tube is a roll disconnect mechanism designed to allow for
separation of the left and right side control circuits once a design torque is achieved.
Separation of control circuits would occur in response to a jammed control situation.
As an example: If the pilot’s aileron jammed so that he was unable to physically move
his aileron control, it would necessitate turning control over to the copilot. As the
copilot applies pressure to his aileron control he will meet with some initial resistance.
As he continues to apply pressure the designed torque limit of the roll disconnect
mechanism will be reached and a physical separation of the torque tube will occur. The
copilot would now have full control of his onside aileron and through the Flight
Control Units (FCUs) control over the Multifunction Spoilers (MFS).
NOTE
The autopilot should be disconnected if a jammed aileron control
circuit condition occurs.
A transducer is mounted at the outboard end of each torque tube assembly (forward
quadrant). They provide the command inputs to the multifunctional spoilers system for
roll assist.
Rotating either control wheel provides an input (via cables and pulleys) to the aileron
forward quadrant which directs the control cable to the aft quadrant.
Each aft quadrant has an artificial feel and centering unit. An aileron trim unit is
installed with input to each aft quadrant and provides trim input to the aileron control
system.
A separate cable circuit is provided for the autopilot servo motor (controlled by the
AFCS) assembly which inputs the right aft quadrant.
Disconnecting the autopilot by the pilot overpowering the aileron servo will not cause
the roll disconnect system to separate the control wheels.
NOTE
Overpowering the aileron servo to disconnect the autopilot is not
recommended.
The control cables from the aft quadrant continue outboard to the hydraulically driven
PCUs. There are two PCUs for each aileron control surface.
P I LOT T R A I N I N G GU I D E
FLIGHT CONTROLS
10-10 For Training Purposes Only
Sept 04
Aileron Surface Position Indication
Left and right aileron positions are displayed by a moving pointer on the EICAS
FLIGHT CONTROL page. Separate pointers indicate the aileron surface position on
each wing.
Aileron Trim
Aileron trim is accomplished by selecting the AIL TRIM switches on the trim control
panel (pedestal) in the desired direction. Actuating both switches provides arming and
direction signals to reposition the ailerons through the use of a trim actuator. Since
trim is commanded through the PCUs it is necessary to have hydraulic system pressure
to trim the aircraft. Aileron trim position is displayed on the EICAS page, along with
the allowable takeoff green band.
FLIGHT CONTROLS
FLAP 3O
AIL
ELEV
RUDDER
SLAT IN
AIL
ELEV
GX_10_007
Scale Pointer
Unfilled triangle moves
vertically to indicate the
range of travel. The
surface position pointer
will change color (green
or amber) based on
hydraulic pressure
availability.
Scale
Indicates the full range
available for aileron up
and down travel.
Surface Outline
The surface outline has
no movement but will
change color, (green or
amber) based on hydraulic
pressure availability.
SLAT/FLAP SURFACES EXTENDED
For Training Purposes Only
Sept 04
10-11
P I LOT T R A I N I N G GU I D E
FLIGHT CONTROLS
A “CONFIG AIL TRIM” red warning message is accompanied by a “NO
TAKEOFF” voice message. These indications occur during the takeoff roll if the
aileron trim is set outside the allowable takeoff range.
NL NR
CH1 CH2
STAB
RUD
PUSH OFF/RESET
AIL
TRIMS
R
W
D
L
W
D
OFF OFF
GX_10_008
Aileron Trim Switch
Located on the Trim Control
Panel (center pedestal). Push
both switches full left or right
to activate the trim.
Trim Scales
Aileron trim range for
left wing down, center
and right wing down
indications.
LWD
RWD
– Left wing down.
– Right wing down.
Pointer
Pivots about the center
dot and indicates the
trim setting.
Green Band (takeoff)
Replaces the center
tick mark visible on
ground only.
–TRIMS–
AIL
LWD RWD
P I LOT T R A I N I N G GU I D E
FLIGHT CONTROLS
10-12 For Training Purposes Only
Sept 04
Aileron Control Schematic
5O
O
3.4
　
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