Abstract: A device attaches an engine to an aircraft. The device (10) is inserted between the engine (14) and a pylon (12) designed to be attached to an aircraft structure, such as a wing or fuselage section. The attachment device (10) generally includes two brackets (18a, 18b) joined together and secured to the pylon (12) and two pairs of rods (20a, 20b, 22a, 22b) inserted between the two brackets (18a, 18b) and a part (24) of the structure of the engine (14). Thus the integrity of the link between the pylon (12) and the engine (14) is preserved in the event of failure of any of the parts which constitute the device, without there being any need for a backup attachment system.

Abstract: A device for recovering forces generated by an aircraft engine has an engine strut (10), capable of being fixed to a wing or a fuselage of an aircraft, and an attachment device (12) fixed to the engine strut (10) and on which the engine is mounted. An intermediate fitting (24) of large dimensions, capable of recovering exceptionally high forces is fixed to several strut fittings (30) independent from each other, for example by bolts (28), across a lower spar (14) of the engine strut (10).

Abstract: Device for recovering forces generated by an aircraft engine.

Abstract: This device is designed to transmit lateral and vertical forces generated by the engine to the nacelle stub (10), together with the engine torque, and comprises a main attachment structure and an emergency attachment structure (38). The main attachment structure includes two half-fittings (18a, 18b), connecting rods (20a, 20c) connecting the two half-fittings to the engine and attachment devices for the half-fittings on the nacelle stub. The emergency attachment structure transmits forces between one of the two half-fittings and the nacelle stub when the other half-fitting or its devices for attachment to the nacelle stub are defective. For example, it comprises a hinge pin (42) supported by the nacelle stub and passing through a hole (44) formed in the half-fittings with a clearance.

Abstract: The attachment device (10) is inserted between the engine (14) and a pylon (12) designed to be attached to an aircraft structure, such as a wing or fuselage section. The attachment device (10) generally includes two brackets (18a, 18b) joined together and secured to the pylon (12) and two pairs of rods (20a, 20b, 22a, 22b) inserted between the two brackets (18a, 18b) and a part (24) of the structure of the engine (14). Thus the integrity of the link between the pylon (16) and the engine (14) is preserved in the event of failure of any of the parts which constitute the device, without there being any need for a backup attachment system.

Abstract: This device is designed to transmit lateral and vertical forces generated by the engine to the nacelle stub (10), together with the engine torque, and comprises a main attachment structure and an emergency attachment structure (38). The main attachment structure includes two half-fittings (18a, 18b), connecting rods (20a, 20c) connecting the two half-fittings to the engine and attachment devices for the half-fittings on the nacelle stub. The emergency attachment structure transmits forces between one of the two half-fittings and the nacelle stub when the other half-fitting or its devices for attachment to the nacelle stub are defective. For example, it comprises a hinge pin (42) supported by the nacelle stub and passing through a hole (44) formed in the half-fittings with a clearance.