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Components and Operation
Ailerons
Lateral (roll) control is provided by ailerons. Two separate control paths are provided from the pilot’s and copilot’s control wheels. The pilot’s side controls the left aileron and the copilot’s side controls the right aileron. Movement of both pilot’s and copilot’s controls is simultaneous when the controls are interconnected (normal operation). Rotating either control wheel activates, via cables and pulleys, the PCUs (actuators) for the ailerons. Two actuators are used for each aileron. The left aileron PCUs use hydraulic pressure from systems 1 and 3, and the right aileron PCUs use hydraulic systems 2 and 3. A position transmitter, linked to each aileron, provides visual indication of the aileron deflection on the FLIGHT CONTROLS synoptic page
Aileron Disconnect
In the event of a control cable jam or PCU malfunction, the left and right sides of the aileron control circuit can be isolated by pulling the ROLL DISCONNECT handle on the center pedestal. This disengages a locking pin on the interconnect torque tube to isolate the failed circuit. The aileron on the operable circuit provides roll control at a reduced roll rate. The ROLL DISCONNECT handle can be reset at any time, locking the two control circuits together again.
FLIGHT CONTROLS Description Vol. 2 10.10.3
Oct 05/06
Roll Control . Schematic
Figure 10.10.2
FLIGHT CONTROLS Description Vol. 2 10.10.4
Oct 05/06
Aileron Power Control Unit Protection
If a PCU is malfunctioning, a failure detection will cause the EICAS to display a PCU valve jam symbol on the FLIGHT CONTROLS synoptic page (an amber half-circle above the aileron outline), and an amber AILERON PCU caution EICAS message to appear. Two sets of shear rivets on each aileron PCU provide additional protection against internal PCU linkage jams. If the linkage to one cylinder jams, the pilot can overpower the jammed condition, which will shear the rivets on that side and allow the other cylinder to operate the aileron.
Flutter Dampers
A flutter damper is installed on each aileron. This prevents control surface flutter in flight, in the event of a complete loss of hydraulic fluid at the PCU. A breakaway link provides jam protection in the case of flutter damper seizure.
Elevators
Longitudinal (pitch) control is provided by elevators, and supplemented by a movable horizontal stabilizer. Two separate control paths are provided through the pilot’s and copilot’s control columns. The pilot’s control column controls the left elevator, and the copilot’s control column controls the right elevator. Movement of both pilot’s and copilot’s controls is simultaneous when the systems are interconnected (normal operation). Moving either control column activates, via cables and pulleys, the PCUs (hydraulic actuators) for the elevators. Two actuators are used for each elevator. The left elevator PCUs use hydraulic pressure from systems 1 and 3, and the right PCUs use systems 2 and 3.
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