Abstract: Device for assembly of landing gear on an aircraft structure. The device comprises two segments (14a, 14b) of the shaft aligned along the same center line and fixed to a fitting of the landing gear, two support devices (10a, 10b) fixed to the aircraft structure, two ball joint balls (12a, 12b) installed between the corresponding shaft segments and the support devices and a tension bar (24) connecting the two support devices. One (10a) of the two support devices, preferably turned towards the outside of the aircraft, is deformable by bending or articulation. Advantageously, the tension bar bears on the bearing balls (20a, 20b) and the guide rings are placed between the bar and the shaft segments, to prevent vibrations.

Abstract: The device comprises two segments (14a, 14b) of the shaft aligned along the same center line and fixed to a fitting of the landing gear, two support devices (10a, 10b) fixed to the aircraft structure, two ball joint balls (12a, 12b) installed between the corresponding shaft segments and the support devices and a tension bar (24) connecting the two support devices. One (10a) of the two support devices, preferably turned towards the outside of the aircraft, is deformable by bending or articulation. Advantageously, the tension bar bears on the bearing balls (20a, 20b) and the guide rings are placed between the bar and the shaft segments, to prevent vibrations.

Abstract: A landing gear hinge shaft is installed on an aircraft structure using at least two ball joints (22), at least one of which is adjustable. The differences between the theoretical and real positions of the centers of the balls are measured, and the adjustments that have to be made to bring the centers of the balls back to their theoretical positions is deduced. This is done by making a first adjustment in the axial direction using a shim (30) and a second adjustment in the radial direction by adjusting the rotation of an inner cage (34) and an outer cage (36) of the ball joint. The inner and outer cages have eccentric axes that facilitate the adjustment.

Abstract: Lubrication device for a ball joint bearing block. The device comprises at least one reservoir grease (30), a pump (34) capable of circulating grease between the reservoir and at least one bearing block lubrication groove (28), and a system (36) designed to actuate the pump (34) at every rotation movement of a hinge pin (16) of the bearing block. Preferably, there is a first groove (28) between the cage (24) and the ball (22) of the ball joint, and a second groove between the ball (22) and the hinge pin (16). Each rotation of the hinge pin (16) thus alternately controls injection of grease into one of the two grooves. One preferred application is lubrication of the hinge pins of aircraft landing gear.

Abstract: A landing gear hinge shaft is installed on an aircraft structure using at least two ball joints (22), at least one of which is adjustable. The differences between the theoretical and real positions of the centers of the balls are measured, and the adjustments that have to be made to bring the centers of the balls back to their theoretical positions is deduced. This is done by making a first adjustment in the axial direction using a shim (30) and a second adjustment in the radial direction by adjusting the rotation of an inner cage (34) and an outer cage (36) of the ball joint. The inner and outer cages have eccentric axes that facilitate the adjustment.

Abstract: Lubrication device for a ball joint bearing block.