Engine assembly for an aircraft comprising a support cradle for a fan shroud mounted on two separate elements

13:

• An engine assembly according to claim 11,
• wherein the forward mounting means are in a form of a forward attachment configured to transmit loads exerted in a longitudinal direction of the engine, in a transverse direction of the engine, and in a vertical direction of the engine.

14:

• An engine assembly according to claim 12,
• wherein the aft mounting means comprises two aft semi-attachments arranged on either side of a forward part of the rigid structure of the mounting structure, each of the two aft semi-attachments configured to transmit loads exerted in a transverse direction to the engine and in a vertical direction of the engine, and each allowing relative limited movement in a longitudinal direction of the engine between an aft part of the cradle of the forward aerodynamic structure and a forward part of the rigid structure.

15:

• An engine assembly according to claim 14, wherein the aft semi-attachments are arranged symmetrically relative to a median plane of the assembly, passing through a longitudinal axis of the engine.

16:

• An engine assembly according to claim 12, wherein the nacelle comprises an air intake lying flush with the fan cowls, and positioned forwardly relative to the cowls.

17:

• An engine assembly according to claim 12, wherein the aerodynamic cowling is fixedly mounted on the cradle carrying the forward and aft mounting means.

18:

• Engine assembly according to claim 12, wherein a forward part of the rigid structure of the mounting structure enters into an aft portion of the cradle.

19:

• An engine assembly according to claim 12, further comprising a plurality of fan cowl hinge fittings, at least some of the hinge fittings being fixed to the cradle.

20:

• An engine assembly according to claim 12, wherein the mounting structure further comprises a plurality of engine attachments amongst which a forward engine attachment is attached firstly to the rigid structure and secondly to the fan case of the engine.

21:

• An engine assembly according to claim 20, wherein the forward engine attachment is positioned, in a longitudinal direction of the engine, between the forward and aft mounting means of the cradle of the forward aerodynamic structure.

22:

• An aircraft comprising at least one engine assembly according to claim 12, assembled on a wing or an aft part of the fuselage of the aircraft.