AIRBUS HELICOPTERS

A blade for a rotary wing able to rotate about an axis of rotation, the blade extending along the pitch axis from a first end to a second end, the blade comprising a blade body having, from the first end to the second end, a succession of sections substantially perpendicular to the pitch axis. Along its pitch axis, the blade has sections having: increasing and then decreasing chords, a relative thickness that decreases from an initial section to a final section, twist angles that continuously increase from the origin section to an initial section and then decrease, and a changing offset relative to the pitch axis.

An aircraft having a landing gear provided with a stand and a pivoting assembly, the landing gear having a pivot locking system comprising a movable locking finger and a passage provided in a base. A monitoring system is configured to determine the presence of a risk of sudden yaw movement of the aircraft in the event of a take-off or an unlocking of the landing gear when the locking finger is in the locked mode on the ground, the monitoring system being configured to emit a risk signal to a processing system following a determination of the presence of the risk of sudden yaw movement.

An automatic diagnostic method for monitoring a state of health of at least one engine equipping an aircraft, the method comprising the periodic in-flight acquisition of a plurality of flight data, with sensors, the plurality of flight data being representative of a plurality of physico-chemical parameters, the identification, with a controller, from the plurality of flight data, of at least one predetermined engine health check phase and the isolation, with the controller, of a sequence of significant data from the plurality of flight data produced during the at least one engine health check phase.

An aircraft having a landing gear provided with a stand and a pivoting assembly, the landing gear having a pivot locking system comprising a movable locking finger and a passage provided in a base. A monitoring system is configured to determine the presence of a risk of sudden yaw movement of the aircraft in the event of a take-off or an unlocking of the landing gear when the locking finger is in the locked mode on the ground, the monitoring system being configured to emit a risk signal to a processing system following a determination of the presence of the risk of sudden yaw movement.

A control device comprising a lever provided with a magnetic dipole and able to move, at least in rotation, relative to a support about an axis. The control device includes a measuring device configured to measure a magnetic field generated by the magnetic dipole, and a monitoring system for monitoring the integrity of the control device. The monitoring system is configured to signal an anomaly using an alarm when a first norm of a first vector difference between the current magnetic field and a first reference magnetic field relating to an estimated orientation of the lever, is greater than a first magnetic field threshold for a duration greater than a duration threshold.

A method of piloting a multi-engine aircraft having an asymmetric operating mode wherein at least one engine is an active engine regulated by a regulation system by outputting a non-zero active driving power participating in the rotation of a rotor and at least one engine is a passive engine in standby mode. During an asymmetric operating mode, the method comprises the steps of detecting, using the regulation system, an operation of the power plant in an at-risk k flight phase preceding a flight phase unfavorable to an exit from the asymmetric operating mode; and following the detection of an operation of the power plant in the at-risk flight phase, reactivation of the passive engine.

An aircraft with a rotary wing, provided with a tail boom carrying a tail fin. The aircraft comprises a pitch stabilization system that is provided with at least one pitch stabilizer comprising a first aerodynamic segment and a second aerodynamic segment. The first aerodynamic segment extends from the tail boom, from a first root section to a first end section, and the second aerodynamic segment extends from the tail fin, from a second root section to a second end section, the first end section being connected directly to the second end section or via a connecting segment.

A method, comprising: providing a light source, a high contrast providing object, and an image acquisition device; emitting a light beam from the light source through the high contrast providing object, a transparent object and a surface of the transparent object toward the image acquisition device; exposing the surface of the transparent object to icing conditions such that a layer of ice is formed by ice accretion on the surface, wherein the light beam traverses the layer of ice after having traversed the transparent object; acquiring a series of images over time of the high contrast providing object using the image acquisition device; determining blur occurring in the series of images over the time; and quantifying the loss of visibility over the time through the transparent object on the basis of the determined blur.

The disclosure relates to a door locking assembly for locking a door of an aircraft, comprising a locking hook adapted for blocking in a locking position a lockable arm of a door of an aircraft; a release lever connected to the locking hook for moving the locking hook from a releasing position into the locking position in response to being actuated by a lockable arm of a door of an aircraft; an operating handle connected at least to the release lever and rotatable for moving the locking hook from the locking position to the releasing position; and a locking indicator connected to the locking hook for indicating positioning of the locking hook in one of the locking position or the releasing position.

An aircraft provided with an engine compartment, the aircraft comprising an engine at least partially housed in the engine compartment, the engine comprising an exhaust nozzle for at least discharging gases, the aircraft comprising an exhaust duct arranged around the exhaust nozzle, the exhaust duct having an open end opening into the engine compartment. The aircraft comprises a drainage device comprising a guide cooperating with the exhaust duct for collecting liquid flowing along the exhaust duct and exiting the exhaust duct through the end.