A metallic-composite joint fitting is provided. The fitting may comprise a frustoconical internal bearing having a bore, a conical sleeve configured to be disposed about the frustoconical internal bearing, a composite structure configured to couple between the frustoconical internal bearing and the conical sleeve, a metallic end fitting configured to be disposed within the bore and couple to the frustoconical internal bearing, and an external nut configured to couple to the metallic end fitting and the conical sleeve, wherein at least one of the frustoconical internal bearing or the conical sleeve comprises a flanged portion mutually configured to couple the conical sleeve to the frustoconical internal bearing via a locking ring.

A packaged bearing unit is disclosed including an outer surface for receiving an aircraft landing gear wheel and an inner surface for receiving an axle. The unit may include first and second spaced-apart sets of tapered roller bearings, held between inner and outer raceways. There may be a bearing setting spacer which can be used when setting and pre-loading the bearings. The bearing unit may be a sealed unit which includes a pre-set amount of lubricant (grease) for lubricating the bearings. One or more sensors may be retained in a void between the sets of bearings. The bearing unit may remain fixed to the axle when the wheel is removed. The bearing unit may be serviced less frequently than the wheels, and may thus have a longer lifetime, possibly comparable with the lifetime of the major components of the landing gear.

A bearing assembly includes a housing, a spherical bearing located within the housing, and two outer races positioned between the spherical bearing and the housing. The outer races are configured in sliding engagement with the spherical bearing to allow the spherical bearing to rotate relative to the housing. The assembly also includes a tightening element configured to engage a first of the two outer races and tighten the outer races against the spherical bearing. The assembly is configured to provide a primary load path from the tightening element to the housing, wherein the primary load path leads from the tightening element to the housing via the outer races whilst bypassing the spherical bearing.

An actuation system includes a power drive unit that drives a plurality of drive shafts that each has a first end individually connected to the power drive unit. The power drive unit includes a geartrain including a plurality of individual gears that are offset relative to each other along the gearbox, and a motor-driven rotation of one of the plurality of individual gears drives rotation of the other individual gears, and each of the plurality of individual gears rotates to drive rotation of a respective one of the plurality of drive shafts. A plurality of torque brakes is mounted to the gearbox, the torque brakes being mechanically coupled to respective individual gears and drive shafts. When the torque being passed through is above a predetermined threshold value, a locking of one of the torque brakes stops rotation of all gears simultaneously to maintain positional symmetry in the actuation system.

A sensor bearing unit includes a bearing having a first ring and a second ring centered on an axis, an impulse ring secured to the first ring of the bearing, and a sensor device for detecting rotational characteristics of the impulse ring. The sensor device includes a sensor housing secured to the second ring and at least one sensor element supported by the sensor housing and configured to cooperate with the impulse ring. The sensor housing is secured to a groove, having side walls, on a cylindrical surface of the second ring of the bearing, and the groove is located on a side of the second ring radially opposite the first ring.

An aircraft assembly includes a first body connected to a second body via a flexible coupling that limits separation of the bearing faces while permitting relative rotational movement between the bodies. The flexible coupling includes one or more first flexible straps attached to the first side of the first body and attached to the second side of the second body, and one or more second flexible straps attached to the second side of the first body and attached to the first side of the second body. The bearing faces include planar central portions to react compressive loads while the parts are aligned, and convex outer rolling surfaces to react loads during rotational movement between the bodies, such that a point of contact between the first body and the second body moves along curves of the respective curved end regions during the rotational movement between the bodies.

A drive shaft extends between axial ends and has at least one portion through which an outer diameter of the drive shaft changes through an infinite number of diameters, with the at least one portion extending across at least 15% of an axial distance between the axial ends of the drive shaft. A drive shaft with a generally spiral undulation at its outer periphery is also disclosed.

A shimmy damper for centering a landing gear includes a cap and a housing. The shimmy damper further includes a damper shaft extending from the cap to the housing. The shimmy damper further includes a plurality of magnets configured to exert an opposing force on the cap and the housing via the damper shaft, providing a centering mechanism of the damper shaft within the housing. This centering action in turn provides for the centering of the landing gear during flight.

A pivoting connection device connecting at least two components and comprising an end fitting having first and second branches, an arm positioned between the first and second branches of the end fitting, a cylindrical axle connecting the end fitting and the arm and having, at one of the ends thereof, a first portion configured to expand radially, a cylindrical rod configured to be screwed into a tapped portion of the cylindrical axle, an insert fitted on the cylindrical rod and movable between a first position, in which the first portion is not expanded, and a second position, in which the first portion is expanded radially, and a nut configured to be screwed on the cylindrical rod to urge the insert into the second position.

An aircraft landing gear includes a landing gear provided with a yoke supporting a spindle on which is mounted a capture pin to be hooked by a hook of a locking box to be mounted on a structure of an aircraft to immobilize the landing gear in a given position with respect to the structure. The capture pin includes a body provided with a longitudinal opening enabling the capture pin to be mounted on the spindle, and an outer surface of revolution having a central portion having a convex profile to cooperate with the hook. A central portion of the outer surface is formed on a central ring which is mounted so as to rotate freely on a central portion of the body.