example, when the control wheel, or control stick, is moved  to produce a left roll, the interconnect cable and spring pulls  forward on the left rudder pedal just enough to prevent the  nose of the aircraft from yawing to the right. The force applied  to the rudder by the springs can be overridden if it becomes  necessary to slip the aircraft.  [Figure 6-8]  Flaperons combine both aspects of flaps and ailerons. In  addition to controlling the bank angle of an aircraft like  conventional ailerons, flaperons can be lowered together  to function much the same as a dedicated set of flaps. The  pilot retains separate controls for ailerons and flaps. A mixer  is used to combine the separate pilot inputs into this single  set of control surfaces called flaperons. Many designs that  incorporate flaperons mount the control surfaces away from  the wing to provide undisturbed airflow at high angles of  attack and/or low airspeeds.  [Figure 6-9]  The elevator controls pitch about the lateral axis. Like the  ailerons on small aircraft, the elevator is connected to the  control column in the flight deck by a series of mechanical  As mentioned earlier, stability, power, thrustline, and the  position of the horizontal tail surfaces on the empennage  are factors in elevator effectiveness controlling pitch. For  linkages. Aft movement of the control column deflects  the trailing edge of the elevator surface up. This is usually  referred to as the up-elevator position.  [Figure 6-10]  The up-elevator position decreases the camber of the elevator  and creates a downward aerodynamic force, which is greater  than the normal tail-down force that exists in straight-and­ level flight. The overall effect causes the tail of the aircraft  to move down and the nose to pitch up. The pitching moment  occurs about the center of gravity (CG). The strength of the  pitching moment is determined by the distance between  the CG and the horizontal tail surface, as well as by the  aerodynamic effectiveness of the horizontal tail surface.  Moving the control column forward has the opposite effect.  In this case, elevator camber increases, creating more lift  (less tail-down force) on the horizontal stabilizer/elevator.  This moves the tail upward and pitches the nose down. Again,  the pitching moment occurs about the CG.  Figure 6-9.  Flaperons on a Skystar Kitfox MK 7.  Figure 6-8.  Coupled ailerons and rudder.  Figure 6-10.  The elevator is the primary control for changing the  pitch attitude of an aircraft.  6-5  Elevator  Flaperons  Rudder/Aileron interconnecting springs  Rudder deflects with ailerons  N o s e u p  T a i l d o w n Control column  aft  Up elevator  Downward  aerodynamic force  CG 