Abstract: A torque link assembly for an aircraft landing gear comprising: an upper torque link; a lower torque link; a joint pin arranged to pivotally couple the upper torque link and lower torque link; an electric motor assembly; a sensor arranged to detect movement of the upper torque link or lower torque link and in response to detecting the movement providing a control signal to the electric motor assembly, wherein the electric motor assembly is configured to linearly translate the joint pin with respect to one of the upper or lower torque links.

Abstract: Embodiments of the invention relate to a landing gear wherein it includes at least one static sealing point, the static sealing point comprising a gasket made of elastically deformable material held between a portion of a first part of the landing gear and a portion of a second part of the landing gear, the first and second parts of the landing gear comprising a steel substrate coated with a zinc and nickel alloy coating, including in mass percentage of the alloy between 12% and 18% and nickel, at most 0.5% of elements other than nickel and zinc, the balance being zinc, and the roughness Ra of the surface of the portions of the first and second parts of the landing gear being less than or equal to 1.6 ?m.

Abstract: A method of monitoring the condition of an aircraft landing gear shock absorber, the shock absorber including at least one spring chamber containing a gas, the method comprising taking a plurality of measurements of the gas pressure and temperature, each gas pressure and temperature measurement pair being taken of at the same instant relative to an operating cycle of the shock absorber; calculating, based on each pair of gas pressure and temperature measurements, a first value; storing the first value in a log; determining a value trend based on the log; and in response to determining that the value trend is outside a first range of values, generating a first notification signal.

Abstract: An aircraft landing gear assembly comprising: a structural pin defining a first bore having a longitudinal insertion axis; a cap for covering the bore, the cap comprising: a base portion; a head portion; a body portion positioned between the base portion and the head portion; and a bolt which extends between the head portion and the base portion and comprises a threaded portion so that engagement of either the head portion or the base portion with the threaded portion moves either the head portion or the base portion relative to the other, the body being formed of an elastically deformable material such that upon tightening of the bolt, the base portion moves towards the head portion and the elastically deformable material moves radially outwards such that a contact surface of the elastically deformable material engages with an inner surface of the first bore in order to retain the cap.

Abstract: A method of determining a service interval for an actuator of a landing gear assembly is suitable for used with a landing gear assembly in which the actuator positions the landing gear assembly between a stowed position and a deployed position. The method includes the steps of determining an actuator travel value for a time interval and increasing a total actuator accumulated travel value by the actuator travel value for the time interval. The method further includes the step of comparing the total actuator accumulated travel value to a predetermined value.

Abstract: A main fitting includes an elongate piston and a cylinder configured to slidingly receive the piston. A first end of the piston extends from a first end of the cylinder, and a second end of the piston extends from a second end of the cylinder. The first end of the cylinder comprises a bearing surface engaging the piston to limit translation of the piston relative to the cylinder to a longitudinal direction.

Abstract: A landing gear assembly for a vehicle, such as a helicopter, includes a linkage coupled to the vehicle and configured to reciprocate between a stowed position and a deployed position. A shock strut forms a part of the linkage. The landing gear assembly further includes a side brace having a first end coupled to the linkage and a second end coupled to the vehicle. The side brace provides a driving force that reciprocates the linkage between the stowed and deployed position. The side brace includes an energy attenuation system that dissipates energy when a compressive load on the side brace exceeds a predetermined threshold.

Abstract: A rim for a braked aircraft wheel includes an outer circular portion whose ends are terminated flanges for receiving a tire. The outer circular portion is connected by a wheel disk to a hub for fitting on an undercarriage axle in order to rotate about an axis of rotation coinciding with a central axis of the rim. The rim is designed to receive the tire on the outside of the outer circular portion and a brake on the inside of the outer circular portion, the outer circular portion presenting on one side of the wheel disk that is to receive the brake, in a plane containing the central axis of the wheel, a profile that has two slopes forming non-zero angles with the central axis, the two slopes extending in the continuation of one another from the wheel disk to the corresponding flange and flaring towards said corresponding flange.

Abstract: An uplock for retaining a capture pin of a movable part includes a hook that is movable between a release position and a retaining position, a locking part that interacts with the hook and is movable between a locking position and an unlocking position, and a detector. The detector includes a first sensor for detecting whether the hook is in the retaining position, and a second sensor for detecting a presence of the mobile part in the immediate vicinity of the uplock in the position occupied by the mobile part when the capture pin is in the hook.

Abstract: A remote towing interface is used to couple a towbar to an aircraft having a fuselage and a steerable landing gear. The remote towing interface includes a towbar coupler mounted to the aircraft and configured to releasably couple a towbar to the aircraft. The remote towing interface further includes a sensor and a controller. The sensor is configured to sense a position of the towbar relative to the aircraft when the towbar is coupled to the towbar coupler, and the controller controls the steerable landing gear according to the sensed position of the towbar relative to the aircraft.

Abstract: An uplock for the selective retention of a capture pin of a movable element includes a hook, a locking member, and a detector. The hook is movable between a release position and a retaining position for retaining the capture pin. The locking member moves between a locked position, and an unlocked position. The detector detects whether the hook is in the retaining position and the capture pin is in the hook. The detector includes a sensor movable relative to a target. The target or the sensor is carried by the locking member and the other by an indicator lever which is movable between a first position indicating absence of the capture pin in the hook and a second position indicating presence. The target and the sensor are only in the proximate position if the locking member is in the locked position and the indicator lever is in the second position.

Abstract: An uplock for selectively retaining a capture pin of a movable element including a hook, a locking member, and a detector. The hook is movable between a release position and a retaining position. The locking member is movable between a locked position that immobilizes the hook and an unlocked position in which the hook is free. The detector detects whether the hook is in the retaining position and the capture pin is present in the hook. The detector includes a sensor associated with a single target which is movable between two positions The sensor emits a signal which is modified when the target passes from one of the positions to the other. The target is independently in kinematic interaction with the hook and the capture pin.

Abstract: A pin for a pinned joint includes a hollow body with a first and second end caps coupled to first and second ends, respectively. The body and the end caps at least partially define a cavity within the body, wherein at least one aperture extends through the hollow body. A main piston is slidably disposed within the cavity and divides the cavity into a first chamber proximate to the first end and a second chamber proximate to the second end and fluidly isolated from an environment around the body. A lubricant is disposed within the first chamber. The main piston moves toward the first end of the body when a pressure in the second chamber is greater than a pressure of the environment. Movement of the main piston toward the first end of the body discharges lubricant through the at least one aperture.

Abstract: A brake assembly is suitable for use with a vehicle wheel that has a rim rotatably mounted to an axle. The brake assembly includes a housing fixedly positioned relative to the axle and a plurality of disks disposed within the housing and fixedly positioned relative to the rim. A fluid is disposed within the housing and has a selectively variable viscosity. The viscosity of the fluid is selectively increased to increase a braking force applied to the wheel.

Abstract: An aircraft has retractable landing gear configured to reciprocate between a deployed position and a stowed position. A landing gear door installation includes a first door rotatably coupled to the aircraft about a first axis for movement between a raided position and lowered position. The door installation further includes a second door located aft of the first door and coupled to the aircraft for movement between a first position when the landing gear is in the stowed position, and a second position when the landing gear is in the deployed position. A portion of the first door overlaps a portion of the second door when the first door is in the raised position and the second door is in the first position so that the first door blocks deployment of the second door to the second position.

Abstract: A connecting device for connecting two mechanical parts includes a rod having a section between a stop and a threaded portion. The rod is inserted into the parts, and a nut is screwed onto the threaded portion in order to hold the parts between the stop and the nut. An anti-rotation system blocks rotation of the nut and includes a washer interacting with the rod to be constrained to rotate with it. The washer has two protuberances, each engaged in a notch of shape complementary to the rod. The anti-rotation system has a ring with an inner periphery of with a shape complementary to that of an outer periphery of the nut in order to be secured to the nut. The ring is secured to the washer by a screw.

Abstract: A motor sub-assembly for an electromechanical brake actuator of an aircraft wheel includes a casing, a shaft mounted in the casing, and an electric motor mounted in the casing rotate the shaft, the shaft having an end connected to a screw-and-nut assembly to exert a force on a stack of disks for braking the aircraft wheel. The shaft has a first set of teeth and the motor sub-assembly has a shuttle mounted to slide relative to the casing and provided with a second set of teeth. The motor sub-assembly includes a selector mechanism that moves the shuttle selectively between first and second positions in which the first set of teeth is engaged and disengaged with the second set of teeth, respectively. The motor sub-assembly includes a holder device that holds the shuttle in the first position and a locking device that continuously prevents the shuttle from rotating relative to the casing.

Abstract: A braking device for braking a wheel of an aircraft, a hub of which is mounted rotatably on an axle includes a stack of discs threaded on a torque tube which is attached to the axle and equipped internally with a heat shield extending opposite an outer surface of the hub facing the stack of discs to protect the hub from heat radiation generated by the stack of discs. The heat shield includes a tubular body which is coaxial to the torque tube and retaining tabs which are resiliently deformable and secured to the tubular body, each of the retaining tabs and an inner surface of the torque tube including additional raised portions to engage with one another so as to axially immobilize the heat shield inside the torque tube.

Abstract: An aircraft wheel including a rim fitted with rotor disks driven in rotation with the rim by first splines secured to the rim and engaged in notches in the rotor disks, stator disks interposed between the rotor disks and provided with notches engaged on second splines secured to a brake torque tube arranged to be fastened to an axle carrying the aircraft wheel, one or more heatpipe extending in one or more of the first and second splines parallel to a plane containing an axis of rotation of the wheel, the heatpipe having an end projecting outside the aircraft wheel, and one or more heatsinks secured to the end of the heatpipe.

Abstract: A feedback system senses a steering position of a nose wheel assembly for an aircraft. The nose wheel assembly has a first element rotatably associated with a second element about an axis, and the rotational position of the first element relative to the second element corresponds to the steering position of the nose wheel assembly. The feedback system includes a first magnetic field sensor fixedly positioned relative to the first element and configured to sense a first element orientation. A second magnetic field sensor is fixedly positioned relative to the second element and configured to sense a second element orientation. The feedback system further includes a controller programmed to determine the steering position of the nose wheel according to the sensed first element orientation and the sensed second element orientation.