Abstract: A microphone calibration method, in particular a microphone for aeronautical use, comprising the following steps, coupling a reference microphone to a first end of a first standing-wave tube; coupling a microphone subjected to calibration to a first end CI a) of a second standing-wave tube; supplying an acoustic input signal to the second end of the first and second tubes so that plane standing-waves propagate in the tubes; measuring the sound pressure of the acoustic signal detected by the first and second microphones; increasing the sound pressure of the acoustic input signal from an initial value until a first sound pressure value DB1r is measured by means of the reference microphone and simultaneously detecting a first sound pressure value DB1t by means of the microphone subjected to calibration; further increasing the sound pressure of the acoustic input signal by a first amount ?DB1 and detecting a second sound pressure value DB2r by means of the reference microphone and simultaneously detecting a secon

Abstract: An apparatus for carrying out load testing on an aircraft part is described. In one aspect, the apparatus includes means for constraining the aircraft part and a linear actuator for applying a test load. The linear actuator has a first part being tiltable and being pivotally constrained about a first and a second geometrical axes, orthogonal to one another, and a second part being slidably mounted on the first part to slide along a longitudinal direction. A load cell, mounted on the second part, measures force acting on the aircraft part along the longitudinal direction. In one aspect, a first clinometer and a second clinometer are mounted on the linear actuator, each clinometer measuring a respective angle representative of rotation of the linear actuator respectively about the first and second geometrical axes. A displacement transducer measures sliding of the second part relative to the first part of the linear actuator.

Abstract: Method for monitoring the operation of a pair of turboprop engines of an aircraft comprising the steps of: detecting the sound pressure generated by the first or second turboprop engine generating a respective first or second signal x(t); iteratively calculating by means of a function Rx/Ry the similarity between the first/second signal x(t)/y(t) at a time T1 and at a time T2 subsequent to time T1; and storing the degrees of similarity calculated in successive iterations in order to detect situations of normal operation of the engines when the degrees of similarity fall in successive iterations within the interval of a first value and to detect a potential fault situation in the engines when the degrees of similarity depart from this interval.

Abstract: An apparatus for carrying out load testing on an aircraft part has constraint means for constraining the aircraft part, a linear actuator for applying a test load, having a tiltable first part, pivotally constrained about a first and a second geometrical axes, orthogonal to one another, and a second part, slidably mounted on the first part to slide along a longitudinal direction. A load cell, mounted on the second part, measures a force acting on the aircraft part along the longitudinal direction. A first clinometer and a second clinometer are mounted on the linear actuator. Each clinometer measures a respective angle representative of rotation of the linear actuator respectively about the first and second geometrical axes. A displacement transducer, mounted on the first part, measures sliding of the second part relative to the first part of the linear actuator.