CROSS-REFERENCES TO RELATED APPLICATIONS

This application claims the benefit of the French patent application No. 1903152 filed on Mar. 26, 2019, the entire disclosures of which are incorporated herein by way of reference.

FIELD OF THE INVENTION

The present invention relates to an assembly for an aircraft, where the assembly comprises a pylon, an engine mount and an attachment system between the pylon and the engine mount, and to an aircraft comprising at least one such assembly.

BACKGROUND OF THE INVENTION

An aircraft conventionally comprises a wing, beneath which there is attached a pylon, to which there is attached an engine. The engine is attached to the pylon via a system of engine mounts which consists, inter alia, of a front engine mount at the front and of a rear engine mount at the rear.

The pylon comprises a sole plate which extends in the lower part of the pylon and the engine mount is secured beneath the sole plate.

The attachment between the pylon and the engine mount is established by means of bolts which press the engine mount against the lower face of the sole plate. To that end, each bolt, the sole plate and the engine mount comprise a through-bore.

Each attachment system comprises a threaded stem, a nut and a bearing washer.

The bearing washer is placed against the upper face of the sole plate, the head of the threaded stem comes to bear against the bearing washer and the threaded stem passes in succession through the bore of the sole plate and the bore of the engine mount. The nut is then screwed onto the end of the threaded stem.

In order to avoid loss of the bearing washers of the various attachment systems, the bearing washers are secured to one another by arms, to which they are welded.

Although an installation of this kind is satisfactory, it is possible that, during installation, the force which is exerted in order to tighten the bolt causes the corresponding bearing washer to rotate. Such a rotation has the consequence of deforming the arms. In order to avoid deformation of this kind, the arms are relatively heavy in order to have adequate rigidity.

SUMMARY OF THE INVENTION

The present invention has an object of proposing an assembly for an aircraft where the assembly comprises a pylon, an engine mount and an attachment system between the pylon and the engine mount, and where the attachment system comprises a bearing washer which is captive and free to rotate about its axis, making it possible to reduce the weight of the elements securing the bearing washers to one another.

To that end, what is proposed is an assembly for an aircraft, the assembly comprising:a pylon having a bearing face and a contact face oriented away from the bearing face,an engine mount having a bearing face and a contact face oriented away from the bearing face, where the contact face of the engine mount bears against the contact face of the pylon,at least two bolts, each one comprising a threaded stem with a head and a nut bearing against the bearing face of the engine mount,for each head, a bearing washer with a first bearing face and a second bearing face, where the second bearing face of the bearing washer bears against the bearing face of the pylon, and where the head bears against the first bearing face of the bearing washer,a shoe, andfor each bearing washer, a clamp that is secured to the shoe and comprises a first branch and a second branch between which the bearing washer is clamped and is free to rotate about its axis.

With such an assembly, the bearing washer cannot escape and remains captive as it is installed, resulting in time saved during installation. Moreover, the bearing washer is free to rotate about its axis so as to avoid deformation of the attachment system when a torque is applied to the bolt.

Advantageously, the first branch is against the first bearing face of the bearing washer and the second branch is against the second bearing face of the bearing washer.

Advantageously, each branch comprises a plate, the bearing washer has a central crown and an outer crown that is thinner than the central crown, and each plate comprises a circular imprint, the diameter of which is between the diameter of the central crown and the diameter of the outer crown.

Advantageously, the assembly comprises, for each bolt, an immobilizing plate removably attached to the shoe, the head has an external imprint, and the immobilizing plate has a counter-imprint, where the external imprint and the counter-imprint cooperate in order to prevent the immobilizing plate from rotating relative to the head of the bolt.

The invention also proposes an aircraft comprising at least one assembly according to one of the above variants.

