Flight Controls

IN FLIGHT, ROLL CONTROL IS ACHIEVED BY: Two ailerons. Two ailerons each one with a servo tab. Two ailerons each one with a servo tab and two spoilers.

ROLL CONTROL OPERATION IS ACHIEVED BY ACTUATING: Mechanically the ailerons and hydraulically the spoilers. Mechanically the spoilers and hydraulically the ailerons. Mechanically the ailerons and the spoilers.

ROLL TRIM CONTROL IS PERFORMED USING: Only right aileron tab. Only left aileron tab. Both left and right aileron tabs.

SPLR LIGHTS ILLUMINATE TO INDICATE: Associated spoiler has failed. Associated spoiler is in the retracted position. Associated spoiler is not in the retracted position.

EACH OF THE TWO ROLL SPOILERS HAS AN HYDRAULIC ACTUATOR WHICH IS CONTROLLED: Mechanically, by the related aileron linkage. Mechanically, by control of aileron deflection. Electrically, by control of WHEEL position.

AIRCRAFT EQUIPPED WITH SPRING TAB: A spring tab provides a flexible compensation in the left aileron only. A spring tab provides a flexible compensation, which automatically increase with the aerodynamic load on the aileron. A spring tab provides a fixed compensation on the aileron.

AIRCRAFT EQUIPPED WITH ELECTROMECHANICAL LOCKING DEVICE: Each aileron is immobilized by an electro mechanical locking device. Each locking device is electrically actuated through switches installed on the gust lock lever. An AIL LOCK light, installed on the pedestal, will illuminate with CCAS activation whenever one of the locking actuators is in disagreement with the gust lock lever position. A+B+C are correct.

SPOILERS START TO MOVE AFTER A GIVEN AILERON DEFLECTlON (2.5degrees): At low speeds (after landing gear extension). At low speeds (flaps fully extended). At all speeds.

PITCH CONTROL IS ACHIEVED BY: Two hydraulic elevators. Two mechanical drive elevators, each fitted with an automatic tab. One mechanical drive elevator.

PITCH TRIM IS OBTAINED BY: Off setting both automatic tab neutral position. Off setting left automatic tab neutral position. Off setting right automatic tab neutral position.

PITCH TRIM ACTUATION: Both, NORMAL TRIM (control column) and STBY TRIM (pedestal) disconnect AUTO PILOT if engaged. Simultaneous action on NORMAL TRIM and STBY TRIM is not recommended. A + B are correct.

IF ONE CONTROL COLUMN IS JAMMED: Pitch uncoupling procedure allows the other channel to operate one elevator. Pitch uncoupling procedure allows the other channel to operate the two elevators. An automatic pitch uncoupling allows the other channel to operate the two elevators.

IN THE YAW AXIS, PILOT'S INPUTS ACT DIRECTLY ON THE: Rudder. Rudder tab and through a spring on the rudder itself. Rudder via an HYDRAULIC ACTUATOR.

FUNCTION REDUCES PILOT'S EFFORT ON THE PEDAL: At high speed only. When airload is present on rudder surface. At low speed only.

THE RELEASABLE "CENTERING UNIT" (RCU), LOCATED BETWEEN THE RUDDER AND THE LINKAGE TO THE PILOT'S PEDALS: Enables a stabilization of the rudder position, when no action is applied on the pedals. As soon as the yaw trim is moved, disengages to allow trim setting. A + B are correct.

THE YAW TRIM IS ACTUATED BY: An electrical trim actuator, shifting the trim tab zero position. An hydraulic trim actuator, shifting the rudder zero position. An electrical trim actuator, shifting the rudder zero position.

THE YAW TRIM POSITION INDICATOR SHOWS: Units of trim motor displacement from neutral. Rudder. Tab.

THE YAW TRIM POSITION INDICATOR SHOWS: Limits pedals stroke and rudder clearance (unlimited until 195 Kt in acceleration, limited until 190 Kt in deceleration). Can by controlled manually in case of MFC 1A and 2A or two ADC failure. A + B are correct.

'LO SPD "LIGHT ASSOCIATED TO ''TLU'': Illuminates green when rudder travel is not limited. Illuminates amber when rudder travel is not limited. Illuminates green when rudder travel is limited.

THE GUST LOCK SYSTEM ACTS ON: Roll control, pitch control and rudder control. Roll control and pitch control. Roll control and rudder control.

HOW IS THE RUDDER PROTECTED, ON GROUND, FOR EXCESSIVE MOVEMENT GENERATED BY GUST?. No protection is necessary. By an hydraulic damper. By the TLU.

STICK SHAKER ADVICE IS ACTIVATED BY: One STICK SHAKER ACTUATOR, attached directly on F/O's control column. One STICK SHAKER ACTUATOR, attached directly on CAPT’s control column. Two STICK SHAKER ACTUATORS, each one attached directly on F/O's and CAPT's control columns.

THE STICK PUSHER ACTUATOR IS ATTACHED TO THE LINKAGE OF: CAPT’s control column. F/O’s control column. CAPT’s and F/O’s control columns.

THE FLAPS ARE CONTROLLED BY ACTUATORS POWERED BY THE BLUE HYD SYSTEM, HOW IS THE FLAP HYD VALVE BLOCK CONTROLLED?. Electrically by DC STBY BUS. Mechanically. Electrically by DC BUS 1.