Abstract: This invention relates to an aft pylon fairing (30) for a suspension system of an aircraft engine, comprising two side panels (44) assembled to each other by inner cross stiffening ribs (46) spaced at intervals from each other along a longitudinal direction (X) of the fairing, and also comprising a heat protection deck (32) designed to delimit an engine core flow (36). According to the invention, it also comprises two longitudinal connecting walls (58) offsetting the deck (32) from the ribs (46), each of these two longitudinal walls (58) being provided with a first side end (62) fixed to one or the other of the two side ends (60, 60) of the deck (32), and a second side end (64) rigidly fixed to the ribs (46).

Abstract: An engine mount for an aircraft engine. The engine mount includes a rigid structure forming a box closed at its forward end by a forward closure rib, and a mounting system including a forward engine attachment having an attachment body fixedly mounted on the rigid structure. The attachment body lies against a forward surface, and the engine mount includes at least one shear pin passing at least in part through the attachment body and forward closure rib.

Abstract: The device for locking an engine (1) on a pylon (2) comprises a front attachment region (12) at the location of the separation between two compressors (5) and (6) and a rear attachment system (13) positioned at the rear of the turbines (9), close to the center of gravity (C). Further the rear attachment system (13) is more flexible than the other either by its own design or by being suspended from the pylon by a more flexible portion (21). This device is advantageous for reducing the level of vibrations transmitted to the aircraft (24) by the engine (1). The extension of the pylon is reduced relatively to customary designs and disk shots have less to be feared. The invention symmetrically applies to “towed” engines, the fan of which is at the front rather than at the rear.

Abstract: An engine assembly including an engine mount, the engine mount including a rigid structure including a box and a mounting system positioned between the engine and the rigid structure. This mounting system includes an aft attachment. The assembly further includes a thermal protection system for the box, including a preferably ventilated duct forming a heat barrier and extending between the box and the engine. The duct extends rearward beyond the aft engine attachment.

Abstract: An aircraft engine assembly including a turbojet, a turbojet attachment pylon, and a nacelle mounted on the attachment pylon and surrounding the turbojet. The nacelle includes at least one mobile nacelle portion forming a single piece envelope all around a section of the turbojet, this mobile nacelle portion being mounted free to slide on the attachment pylon so that it can be moved from the forward position in the aft direction, and vice versa.

Abstract: The invention refers to a suspension pylon (4) for an aircraft engine (2), the pylon including a rigid structure (10) forming a box provided with a lower spar (28) and an upper spar (26), and an engine mounting system (11) installed fixed on the structure (10) and in particular including a forward attachment (6) with an attachment body provided with a horizontal fixing surface (40) held in contact with a horizontal fixing surface (38) of the structure (10). According to the invention, the attachment body is arranged such that its horizontal fixing surface (40) is located along a vertical direction (Z) of the pylon, upwards from a forward end (28a) of the lower spar and downwards from a forward end (26a) of the upper spar. Furthermore, the structure (10) includes at least one forward fitting (42a, 42b) making up a forward closing rib (36) of the box, this fitting (42a, 42b) defining said horizontal fixing surface (38).

Abstract: An engine mount for an aircraft engine. The engine mount includes a rigid structure forming a box closed at its forward end by a forward closure rib, and a mounting system including a forward engine attachment having an attachment body fixedly mounted on the rigid structure. The attachment body lies against a forward surface, and the engine mount includes at least one shear pin passing at least in part through the attachment body and forward closure rib.

Abstract: The invention relates to an engine suspension pylon for an aircraft including a rigid structure provided with a box (24), this pylon also including an engine aft attachment (8) provided with an attachment body (38), and a thrust resistance device (9) generated by the engine. The rigid structure according to the invention includes an offset rib (35) for the attachment body (38), this rib (35) being mounted fixed on the box (24) between the box and the engine (2) and carrying the attachment body. Furthermore, the device (9) includes a thrust resistance spar (9b) of which the forward end is mounted fixed on the rib (35), and the aft end is mounted fixed on the box.

Abstract: An aircraft engine assembly including an engine, an engine suspension pylon, and a heat exchanger system including a second outlet located between the box and the engine, aft from the aft engine suspension. Furthermore, the exchanger in the heat exchanger system is at least partially arranged inside an aft aerodynamic fairing of the suspension pylon, the aft aerodynamic fairing being located entirely aft from the aft engine suspension.

Abstract: An aircraft engine assembly including an engine, an engine suspension pylon, and a heat exchanger system including an outlet located between the box and the engine, aft from the aft engine suspension. Furthermore, the outlet of the heat exchanger system is provided on an outlet pipe connected to the exchanger and passing through a structural block fixed on a box, between the box and the engine.

Abstract: The invention concerns a method to mount an aircraft engine on a rigid structure of an engine mount, comprising a securing step, on the structure, to secure an attachment body (46) for an engine attachment, this attachment body being intended to lie against a contact surface of the rigid structure oriented forwardly, and secured to this structure by at least one shear pin (68) passing through a first and a second primary orifice, the securing step of the body (46) comprising the following operations: pre-positioning the engine relative to the engine mount for the purpose of placing the first orifice opposite the second orifice; and inserting a pin fitted with a convex centering head through the two orifices, so that this pin forms the shear pin.

Abstract: An engine assembly including an engine mount, the engine mount including a rigid structure including a box and a mounting system positioned between the engine and the rigid structure. This mounting system includes an aft attachment. The assembly further includes a thermal protection system for the box, including a preferably ventilated duct forming a heat barrier and extending between the box and the engine. The duct extends rearward beyond the aft engine attachment.

Abstract: The invention relates to an engine suspension pylon for an aircraft including a rigid structure provided with a box (24), this pylon also including an engine aft attachment (8) provided with an attachment body (38), and a thrust resistance device (9) generated by the engine. The rigid structure according to the invention includes an offset rib (35) for the attachment body (38), this rib (35) being mounted fixed on the box (24) between the box and the engine (2) and carrying the attachment body. Furthermore, the device (9) includes a thrust resistance spar (9b) of which the forward end is mounted fixed on the rib (35), and the aft end is mounted fixed on the box.

Abstract: The invention refers to a suspension pylon (4) for an aircraft engine (2), the pylon including a rigid structure (10) forming a box provided with a lower spar (28) and an upper spar (26), and an engine mounting system (11) installed fixed on the structure (10) and in particular including a forward attachment (6) with an attachment body provided with a horizontal fixing surface (40) held in contact with a horizontal fixing surface (38) of the structure (10). According to the invention, the attachment body is arranged such that its horizontal fixing surface (40) is located along a vertical direction (Z) of the pylon, upwards from a forward end (28a) of the lower spar and downwards from a forward end (26a) of the upper spar. Furthermore, the structure (10) includes at least one forward fitting (42a, 42b) making up a forward closing rib (36) of the box, this fitting (42a, 42b) defining said horizontal fixing surface (38).