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Elevator position is displayed on the FLIGHT CONTROLS synoptic page. A full-scale deflection of the elevator’s position indicator corresponds to maximum travel. Pilot inputs to the elevator are through dual control columns. The control columns are normally connected through a torque tube, so they rotate in unison. A control rod transmits pilot commands to the left and right forward quadrants. The left side quadrant assembly includes a cable interface with the stick pusher servo of the stall protection system. Separate left and right cable circuits carry the elevator command through the fuselage and terminate at the respective aft quadrants located in the rear section of the fuselage. The aft quadrants each drive an output rod that is connected to two control rods in series. The first control rod is connected to a gain changer mechanism, which is a four bar linkage that pro-vides a non-linear gearing between control column movement and elevator surface. The second rod is connected to a pitch feel simulator that provides artificial feel forces. Aft of the gain changer mechanism, a series of control rods, levers, and a torque tube transmit the elevator command to two elevator power control units per elevator. Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 PITCH DISCONNECT PITCH DISC PULL & TURN
PITCH DISC LEVER
INPUT FLIGHT CONTROL Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 SECONDARY FLIGHT CONTROLS Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6 COMPONENTS AND OPERATION AILERON TRIM |
