A flap adjusting system for an aircraft, featuring: - at least one flap (A1, A2, B1, B2, K) that is respectively adapted to be coupled to one of the airfoils of an aircraft by means of at least two bearing devices and to be movable relative to the airfoil, - at least one adjusting device (A11, A12, B11, B12, A21, A22, B21, B22) for adjusting the flap (A1, A2; B1, B2), wherein each adjusting device features: an actuator (20; 120) and adjusting kinematics comprising an actuator lever (22, 122) connecting the actuator (20, 120) to a drive rod (30, 130), the adjusting kinematics being foreseen for kinematically coupling the actuator (20; 120) to the regulating flap (A1, A2; B1, B2) with the drive rod (30, 130) that couples the actuator to the flap (A1, A2, B1, B2, K), as well as a load sensor (S-K) arranged in at least one of the at least one adjusting device (A11, A12, B11, B12, A21, A22, B21, B22) that is respectively arranged on the flap (A1, A2, B1, B2, K) and in a second joint (32, 132), by means of which the drive rod (30, 130) is coupled to the regulating flap (A1, A2, B1, B2, K), wherein the load sensor (S-K) is realized in such a way that it measures the forces occurring in this load path, - at least one drive unit (PA1, PA2, PA3, PA4) for driving the adjusting devices (A11, A12, B11, B12, A21, A22, B21, B22), and - a control and monitoring device that is functionally connected to the at least one drive unit (PA1, PA2, PA3, PA4) in order to adjust the adjusting devices (A11, A12, B11, B12, A21, A22, B21, B22), as well as functionally connected to the at least one load sensor (S-K) in order to receive the sensor signals generated by the load sensors (S-K), characterized - in that the drive rod (30, 130) couples the actuator (20; 120) to the flap (A1, A2; B1, B2, K) by means of a first and the second joint (31, 32, 131, 132), which are both adapted to be moveable relative to the airfoil, the second joint (32; 132) being between the drive rod (30; 130) and the regulating flap (A1, A2; B1, B2), and - in that the adjusting kinematics is realized in such a way that, during maximum adjustment travel of the flap (A1, A2, B1, B2, K), the angle between the drive rod (30, 130) and the flap (A1, A2, B1, B2, K) changes by a relative angle that amounts to less than 50% of the angular change occurring between the drive rod (30, 130) and the actuator lever (22, 122). - at least one flap (A1, A2, B1, B2, K) that is respectively adapted to be coupled to one of the airfoils of an aircraft by means of at least two bearing devices and to be movable relative to the airfoil, - at least one adjusting device (A11, A12, B11, B12, A21, A22, B21, B22) for adjusting the flap (A1, A2; B1, B2), wherein each adjusting device features: an actuator (20; 120) and adjusting kinematics comprising an actuator lever (22, 122) connecting the actuator (20, 120) to a drive rod (30, 130), the adjusting kinematics being foreseen for kinematically coupling the actuator (20; 120) to the regulating flap (A1, A2; B1, B2) with the drive rod (30, 130) that couples the actuator to the flap (A1, A2, B1, B2, K), as well as a load sensor (S-K) arranged in at least one of the at least one adjusting device (A11, A12, B11, B12, A21, A22, B21, B22) that is respectively arranged on the flap (A1, A2, B1, B2, K) and in a second joint (32, 132), by means of which the drive rod (30, 130) is coupled to the regulating flap (A1, A2, B1, B2, K), wherein the load sensor (S-K) is realized in such a way that it measures the forces occurring in this load path, - at least one drive unit (PA1, PA2, PA3, PA4) for driving the adjusting devices (A11, A12, B11, B12, A21, A22, B21, B22), and - a control and monitoring device that is functionally connected to the at least one drive unit (PA1, PA2, PA3, PA4) in order to adjust the adjusting devices (A11, A12, B11, B12, A21, A22, B21, B22), as well as functionally connected to the at least one load sensor (S-K) in order to receive the sensor signals generated by the load sensors (S-K), characterized - in that the drive rod (30, 130) couples the actuator (20; 120) to the flap (A1, A2; B1, B2, K) by means of a first and the second joint (31, 32, 131, 132), which are both adapted to be moveable relative to the airfoil, the second joint (32; 132) being between the drive rod (30; 130) and the regulating flap (A1, A2; B1, B2), and - in that the adjusting kinematics is realized in such a way that, during maximum adjustment travel of the flap (A1, A2, B1, B2, K), the angle between the drive rod (30, 130) and the flap (A1, A2, B1, B2, K) changes by a relative angle that amounts to less than 50% of the angular change occurring between the drive rod (30, 130) and the actuator lever (22, 122).