Abstract: An aircraft undercarriage including a wheel, a support, a drive system, a mover system, a first pair of links, and a locking actuator. The drive system drives rotation of the wheel and is mounted to move relative to the support between an engaged position and a disengaged position. The mover system moves the drive system between the engaged and disengaged positions. The first pair of links are hinged to each other about a first hinge axis to pivot during the movement of the drive system between the engaged and disengaged positions. The locking actuator acts on a first target to lock or unlock the drive system. The first target is carried by one of the links.

Abstract: An aircraft wheel comprising a hub for mounting the wheel on a landing gear axle for rotation, and a rim with edge flanges for receiving a tire, the rim being secured to the hub by a web. The hub receives releasably a bearing box comprising two bearings, each having an inner and an outer ring mounted between a bushing for engaging on the axle with an outside wall shaped to receive the inner rings, the bushing having one end shaped as an abutment and another end shaped to receive a pre-loading nut. A sleeve extends around the bushing and has (1) an inside wall with shoulders to hold the outer rings axially and (2) an outer wall shaped to be received as a sliding fit in a bearing of the hub, with one end shaped as an abutment and another end shaped to receive a stop nut.

Abstract: A landing gear (0) for an aircraft comprising a wheel (R), a system (1) for rotationally driving the wheel that is mobile between a clutched position and a safety position by passing through a declutched position, and a manoeuvring system (3) to displace the driving system (1) between its declutched and clutched positions. The gear comprises an elastic return (4) for returning the driving system (1) to its safety position and first and second abutments (51a, 52a) that are separated as long as the driving system (1) is away from its safety position and in contact with one another when the driving system (1) is in safety position. The first and second abutments (51a, 52a) oppose the passing of the driving system (1) from its safety position to its declutched position when the abutments are in contact with one another.

Abstract: An aircraft undercarriage (0) comprising: a wheel (R); a support (2); a drive system (1) for driving rotation of the wheel, the drive system being mounted to move relative to said support (2) between an engaged position and a disengaged position; a mover system (3) for moving the drive system (1) between its positions; a first pair of links (51, 52) hinged to each other about a first hinge axis (X1) to pivot during the movement of the drive system between its engaged and disengaged positions; and a locking actuator (V) and at least one first target (V1), the locking actuator (V) acting on the first target (V1) to lock or unlock the drive system (1) and the first target (V1) being carried by one of the links (52).

Abstract: The invention relates to a method for connecting in rotation an output member (5) of an electric motor (1) and an element (2) that is to be driven in rotation, comprising the use of at least one fusible pin (11) that links the output member and the element that is to be driven, and that has at least one section that is prone to fail in shear when a torque transmitted by the fusible pin exceeds a predetermined threshold. The method comprises the step of interposing, between the pin and either the output member or the element that is to be driven, at least one elastic member (20) comprising a first travel with a first stiffness followed by a second travel with a second stiffness greater than the first stiffness.

Abstract: The invention relates to a method for adapting a stop that is adjustable by screwing onto the extremity of a fine tube (1), including the following stages: slipping onto the extremity of the tube (5) a ferrule (10) that is threaded on its external surface and is immobilized on the extremity of the tube by means of a plurality of pins (8) engaged in orifices (7,9) facing towards the ferrule and the tube; screwing onto the ferrule a nut (14) having a first end face (15) acting as a stop in order to preload any element (4, 4) mounted on the tube in front of the ferrule, and a second opposing end face (18) containing forms (25) adapted for it to be driven in rotation by a tool, the nut covering the pins in service.

Abstract: The invention relates to a method for adapting a stop that is adjustable by screwing onto the extremity of a fine tube (1), including the following stages: slipping onto the extremity of the tube (5) a ferrule (10) that is threaded on its external surface and is immobilized on the extremity of the tube by means of a plurality of pins (8) engaged in orifices (7,9) facing towards the ferrule and the tube; screwing onto the ferrule a nut (14) having a first end face (15) acting as a stop in order to preload any element (4, 4) mounted on the tube in front of the ferrule, and a second opposing end face (18) containing forms (25) adapted for it to be driven in rotation by a tool, the nut covering the pins in service.

Abstract: The invention relates to an aircraft wheel comprising a hub (52) for mounting the wheel on a landing gear axle to enable the wheel to rotate about an axis of rotation, and a rim (55) with edge flanges for receiving a tire, the rim being secured to the hub by a web (56). The hub is adapted to receive releasably a bearing box (60) comprising two bearings (53, 54) each having an inner ring and an outer ring mounted between a bushing (61) for engaging on the axle with an outside wall shaped to receive the inner rings of the bearings, the bushing having one end (63) shaped as an abutment and another end shaped to receive a pre-loading nut (67); and a sleeve (62) extending around the bushing and having an inside wall presenting two shoulders to hold the outer rings of the bearings axially, the sleeve having an outer wall shaped to be received as a sliding fit in a bearing of the hub, with one end (68) shaped as an abutment and another end shaped to receive a stop nut (70).

Abstract: The invention relates to a method for connecting in rotation an output member (5) of an electric motor (1) and an element (2) that is to be driven in rotation, comprising the use of at least one fusible pin (11) that links the output member and the element that is to be driven, and that has at least one section that is prone to fail in shear when a torque transmitted by the fusible pin exceeds a predetermined threshold. The method comprises the step of interposing, between the pin and either the output member or the element that is to be driven, at least one elastic member (20) comprising a first travel with a first stiffness followed by a second travel with a second stiffness greater than the first stiffness.

Abstract: A landing gear (0) for an aircraft comprising a wheel (R), a system (1) for rotationally driving the wheel that is mobile between a clutched position and a safety position by passing through a declutched position, and a manoeuvring system (3) to displace the driving system (1) between its declutched and clutched positions. The gear comprises an elastic return (4) for returning the driving system (1) to its safety position and first and second abutments (51a, 52a) that are separated as long as the driving system (1) is away from its safety position and in contact with one another when the driving system (1) is in safety position. The first and second abutments (51a, 52a) oppose the passing of the driving system (1) from its safety position to its declutched position when the abutments are in contact with one another.