Controles De Vuelo

Flight Controls

The primary flight control surfaces consist of conventional ailerons, rudder and elevator. Secondary controls are to lift devices (flaps and slats), spoilers (lateral control, brake drag in flight and ground). Alamas systems are provided to stall and take-off side, or conditions of speed.
Primary Flight Controls
Lateral Control
The leaflets are used to control the controlside are connected by cables to a control fin on each wing (control tab) and both are connected by a torque tube that makes both leaflets are moved together. If any part of the system between the torque tube and control any steering wheel locks tab will move the aileron tab unlocked by applying pressure of about 25kg in the command.
The aerodynamic forces on the control tab moves the spoiler. Theailerons are connected by a cable, so that each wing should respond to the opposite wing moviemiento. Each wing has a flap trim (trim tab) which is connected by wire to the knob on the pedestal. The aileron lateral control is enhanced by the flight spoiler (flight spoilers) operating in proportion to the displacement of the command (steering wheel) and / or setting of speedbrakes.
LongitudinalControl
Consists of a pair of elevators attached to the horizontal stabilizer. The elevator control is, for all normal flight, a "asistidor" single fin that moves a control (control tab) in each hoist. Each control tab is moved by an independent system of wires from the corresponding control column in the cockpit (right column right elevator controls and vice versa). The only interconnection betweenthe two control systems is a torque rod that connects both control columns. Moving the control column moves the control tab, and aerodynamic forces generated by this move the elevator. While each elevator is moving, an additional flap, operated by movement of the elevator moves to assist in the control tab. A fin antiflote (anti-float tab) driven by the movement of the horizontal stabilizer isinstalled in each elevator on the outside of the tab for assistance to improve the longitudinal trimeado in a condition of CG forward and landing configuration.
The fins on the engine nacelles are added to improve the longitudinal control after having been in a stall.
A 3000 psi hydraulic power booster provides additional elevator control to lower the nose in extreme conditions, flight high angleof attack. Receives left hydraulic system pressure, this system power booster is activated during an extreme condition stall after the tabs monitoring of elevators have been displaced approximately 10 degrees nose down with respect to the surface of the elevator. This action of the enhancer restored the positive control of the elevator.
 
A blue light (PWR ON ELEVATOR) in the annunciator panelis installed to indicate when using hydraulic pressure to move the elevator.
Trim a Mach spring is connected to the control column of the 1st Official. This is controlled by a trim compensator that provides corrections flying in conditions of high Mach number.
Directional Control
Directional control is obtained through the pedals that control the movement of the rudder, the rudder is usuallypowered by hydraulics right. 
 There are fins on the nose (nose strakes) added to the fuselage to increase directional control during flight with large angles of attack.
Enhanced operation of the rudder.
During operation the enhanced rudder control tab is locked hydraulically. The movements of the rudder pedals activate the trimeado is done by turning the knob on the pedestal. The hydraulicpressure that goes towards the rudder can be cut carrying lever RUDDER POWER CONTROL to the manual position when hydraulic pressure is cut at the wheel, or when the hydraulic pressure in the system drops approx. below 950psi, the wheel automatically switches to manual operation by unlocking the tab control, a light on the annunciator panel lights RUDDER CONTROL MANUAL indicating the operation of manual...