A method is provided that involves rotational equipment that includes a case and a first rotor blade within the case. During the method, a probe is arranged within the case adjacent the first rotor blade. A magnetic characteristic of the first rotor blade is measured using the probe. Presence of internal corrosion within the first rotor blade is determined based on the measured magnetic characteristic.

A variable geometry suspension structure for suspending a turboprop from a structural element of an aircraft, the structure including a rear cradle for fastening to a structural element of an aircraft and a front cradle for supporting a front portion of the turboprop, the front cradle being connected to the rear cradle, firstly via a pivot connection configured to enable the front cradle to tilt vertically relative to the rear cradle, and secondly by a return spring configured to prevent the front cradle from tilting while thrust from the turboprop is below a predetermined threshold.

A variable geometry suspension structure for suspending a turboprop from a structural element of an aircraft, the structure including a rear cradle for fastening to a structural element of an aircraft and a front cradle for supporting a front portion of the turboprop, the front cradle being connected to the rear cradle, firstly via a pivot connection configured to enable the front cradle to tilt vertically relative to the rear cradle, and secondly by a return spring configured to prevent the front cradle from tilting while thrust from the turboprop is below a predetermined threshold.

A junction of a pylon with an aircraft wing, the pylon including a primary structure extending from front to rear along a longitudinal axis and in the form of a box with a rear face and an upper spar forming an upper face of the box, a longitudinal median plane separating the primary structure into two parts, left and right, the junction comprising a rear attachment system for attaching the pylon to the wing, this system being arranged at the rear of the primary structure, the rear attachment system including a shoe attached beneath the wing, the shoe being connected, via at least one articulated connecting rod, to a fitting attached to the rear face of the pylon by an articulation whose articulation pin, termed the horizontal articulation pin, is perpendicular to the longitudinal median plane, and the shoe being connected to the upper spar via a force reacting system.

An aircraft structure including a heat shield. A heat shield including an interior; a skin enclosing the interior; a plurality of barriers attached in the interior to the skin, each of the barriers spaced to separate a plurality of thermal insulation layers disposed in the interior; and wherein the barriers suppress heat flow between the thermal insulation layers.

An apparatus configured to reduce acoustic interactions between a propeller and a surface of an aircraft positioned downstream of the propeller includes a surface modification element of the surface of the aircraft. The surface modification element defines a modified contour of the surface. The modified contour is configured to decorrelate a phase distribution of a plurality of sound sources within a source field positioned on at least a portion of the surface.

An apparatus configured to reduce acoustic interactions between a propeller and a surface of an aircraft positioned downstream of the propeller includes a surface modification element of the surface of the aircraft. The surface modification element defines a modified contour of the surface. The modified contour is configured to decorrelate a phase distribution of a plurality of sound sources within a source field positioned on at least a portion of the surface.

An engine mount assembly for coupling an engine to an airframe includes a torsion bar, a lateral movement control assembly and a vertical movement control assembly. The torsion bar has a torsional stiffness and is coupled between the engine and the airframe such that torsional movement of the engine causes torsion in the torsion bar. The lateral movement control assembly has a lateral stiffness and is coupled between the torsion bar and the airframe such that lateral movement of the engine causes rotation of the torsion bar which reacts on lateral movement control assembly. The vertical movement control assembly has a vertical stiffness and is coupled between the engine and the airframe such that vertical movement of the engine reacts on the vertical movement control assembly. The engine mount assembly, thereby enables torsional, lateral and vertical movement of the engine to be independently controlled.

An engine mount assembly for coupling an engine to an airframe includes a torsion bar, a lateral movement control assembly and a vertical movement control assembly. The torsion bar has a torsional stiffness and is coupled between the engine and the airframe such that torsional movement of the engine causes torsion in the torsion bar. The lateral movement control assembly has a lateral stiffness and is coupled between the torsion bar and the airframe such that lateral movement of the engine causes rotation of the torsion bar which reacts on lateral movement control assembly. The vertical movement control assembly has a vertical stiffness and is coupled between the engine and the airframe such that vertical movement of the engine reacts on the vertical movement control assembly. The engine mount assembly, thereby enables torsional, lateral and vertical movement of the engine to be independently controlled.

An aeronautical car comprises a ground-travel system including at least one traction device, an air-travel system including at least one flight mechanism configured to be selectively moved between a first position when the aeronautical car is in a driving mode and a second position when the aeronautical car is in a flying mode, and a weather manipulation device. The weather manipulation device may be configured to manipulate at least one aspect of a weather condition while the aeronautical car is in the air.