Abstract: Detection of the overstepping of design loads of an aircraft tailplane may include determining current bending and twisting moments applied to the aircraft. The determined bending and twisting moments are compared with a safety envelope to determine the risk of developing permanent deformations on the tailplane. A determination is made as to whether a structural inspection of the tailplane should be performed based on the comparison result.

Abstract: Detection of the overstepping of design loads of an aircraft tailplane may include determining current bending and twisting moments applied to the aircraft. The determined bending and twisting moments are compared with a safety envelope to determine the risk of developing permanent deformations on the tailplane. A determination is made as to whether a structural inspection of the tailplane should be performed based on the comparison result.

Abstract: A method and device for detecting an overstepping of design loads of the fin of an aircraft. The device includes a set of information sources and a section for determining, with the aid of information emanating from the set of information sources, a current bending moment. The device further includes a section for determining, with the aid of information emanating from the set of information sources, a current twisting moment, and a section for carrying out a comparison by comparing the pair formed by the current bending moment and the current twisting moment with a safety envelope representing a chart formed in a plane on the basis of pairs of values of bending and twisting moments and defined so that, for any pair which lies outside the safety envelope, there exists a risk of appearance of permanent deformation on the fin.

Abstract: The device (1) comprises a set (2) of information sources, means (3) for determining, with the aid of information emanating from said set (2), a current bending moment, means (5) for determining, with the aid of information emanating from said set (2), a current twisting moment, means (7) for carrying out a comparison by comparing the pair formed by the current bending moment and the current twisting moment with a safety envelope representing a chart formed in a plane on the basis of pairs of values of bending and twisting moments and defined so that, for any pair which lies outside the safety envelope, there exists a risk of appearance of permanent deformations on the fin, and means (10) for determining whether a structural inspection of the fin has to be performed, at least on the basis of the result of said comparison.

Abstract: A process and device for detecting on an aircraft an overshoot of design loads at the level of a structural part of the aircraft. The detection device includes a speed measuring device for measuring an effective speed of the aircraft. A first comparator compares the measured effective speed with a maximum speed relating to the current flight configuration of the aircraft. A vertical load measuring device measures a vertical load factor of the aircraft, and a second comparator compares the measured vertical load factor with a limit value of the vertical load factor. An inspection determining device determines whether a structural inspection needs to be performed at the level of the structural part, based of the results of the first and second comparisons.

Abstract: Process and device for detecting on an aircraft an overshoot of design loads at the level of a structural part of said aircraft. The detection device (1) comprises means (2) for measuring an effective speed of the aircraft, means (3) for carrying out a first comparison, by comparing this measured effective speed with at least one maximum speed relating at least to the current flight configuration of the aircraft, means (7) for measuring a vertical load factor of the aircraft, means (8) for carrying out a second comparison, by comparing said measured vertical load factor with at least one limit value of vertical load factor, and means (5) for determining whether a structural inspection needs to be performed at the level of said structural part, at least on the basis of the results of said first and second comparisons.

Abstract: An electrical fly-by-wire system for operating an aircraft rudder includes a low-pass filter, arranged between a rudder bar and an actuator of a rudder. The low-pass filter receives a control command from the rudder bar corresponding to the degree of travel the rudder bar has experienced from a neutral position. Based on the amplitude of the control command, the filter generates an operating command for the actuator. Additionally, the filter operates such that the higher the fraction of the rudder bar's travel away from the neutral position, with respect to its maximum value of travel, the higher the filter's time constant is set.

Abstract: Electrical fly-by-wire system for operating an aircraft rudder.