Abstract: An aircraft propulsion engine including a fan case, and a cowl forming part of the nacelle of the engine and being designed to at least partially surround the case leaving a space between the cowl and the case, in which space at least one piece of equipment is mounted and extends along the axis of the engine, is provided. The cowl includes a wall and wall stiffeners fixed to the internal face of the wall. At least a part of the stiffeners of the cowl is arranged to form air guide ducts, the air guide ducts being assembled into an air distribution circuit to ventilate the equipment.

Abstract: The invention relates to an aircraft propulsion engine (1) comprising a case, notably a fan case (18), a cowl (20) forming part of the nacelle of the engine (1), the cowl (20) being designed to at least partially surround said case leaving a space (22) between the cowl and the case (18), in which space (22) at least one piece of equipment (24) is mounted and extends along the axis (10) of said engine (1), the cowl comprising a wall and wall stiffeners fixed to the internal face (34) of this wall, wherein at least a part of the stiffeners of the cowl is arranged to form air guide ducts, said air guide ducts being assembled into an air distribution circuit to ventilate said equipment.

Abstract: An integrated propulsive turbojet engine system comprising a downstream cylindrical nacelle structure in two parts, one (26) of which is fixed and comprises a beam (20) for fastening attachment means to the aircraft, and the other (40) of which is able to move between a service position and a maintenance-facilitating open position.

Abstract: The invention relates to thrust reversers comprising at least one mobile element (3), at least one locking device (7) comprising a hook (8) cooperating with a hookable part (6) in order to keep the mobile element (3) in the closed position, and a double detection system (10) detecting closure and locking comprising a sensor (15) for indicating, in particular by a signal, if the mobile element (3) is in the closed position and if the device (7) is in a locked position. According to the invention, the double detection system detecting closure and locking of a mobile element of a turbojet thrust reverser comprises a means (16) of detection of the hookable part (6) and of activation of a second means (17) of detection of the crooked end (13) of the hook (8).

Abstract: A front attachment device for attaching an aircraft engine to an aircraft pylon includes an upper brace fitted with elements rigidly fastened to the pylon and first and a second connecting rods, each connected to the engine, via a first ball joint connection at one end portion and to the upper brace via a second ball joint connection on the other end portion. The device further includes in each connecting rod a third stand-by link. The first and second connecting rods are interchangeable with each other.

Abstract: The present invention relates to a suspension for suspending a jet engine on an aircraft strut, comprising a beam 10 having a platform 11 provided with means for fastening it to the said strut and arranged transversely with respect to the axis of the engine, first 20 and second 40 lateral links each connected by a first pin 21, 41 to the beam 10 and by a second pin 22, 42 to the engine casing, the second lateral link 40 being prolonged in the region of the first pin by a finger 43 housed with clearance in a cavity provided in the beam so as to form a standby safety connection, and a central link 30 arranged between the two lateral links 20, 40 and connected by a first pin 31 to the beam and by a second pin 32 to the said casing.

Abstract: A suspension of the turbo fan engine to an aircraft pylon, includes a fitting arranged to be attached to a pylon, a lever fastened in its central portion to the fitting via a linking device with a pivot pin. Two thrust rods are each connected by an end to the lever and including at the other end of the fastening device to the engine. The linking device is composed on the central portion of the lever, of two parallel branches apart from one another, and on the fitting, of a central fastening tab, whereas the fastening tab and both branches are held together by dint of the pivot pin.

Abstract: A turbine engine mount to a pylon of an aircraft includes a bracket arranged to be attached to the pylon, and a lever attached in its central part to the bracket via a first connection and two thrust links each joined aft to the lever by a second connection. The lever includes a central part with two arms, and the bracket includes an integral attachment lug placed between the two arms and connected to the arms via a pivot pin to form the first connection. The lever is laterally connected to the bracket via pivot pins passing through the lever and mounted with a clearance to form connections on standby.

Abstract: A rear attachment suspension or device of a turbo engine to an aircraft pylon includes an upper brace fitted with a pylon fastening device and hinged by second ball joint connections, first and second rocker bars transversal to the longitudinal axis of the engine on both sides of the axis of the engine and a third rocker bar disposed there between. The rocker bars are linked to the engine by first ball joint connections. The first and second rocker bars each include a third stand-by link and the upper brace is formed of a beam fixed rigidly to the pylon. The rocker bars are designed to ensure their interchangeability, thereby reducing the risks of error during assembly.

Abstract: The invention pertains to an engine mount onto an aircraft structure comprising at least one connection means between a first and a second element such as an engine case and said structure, characterized by the fact that said connection means comprises an eccentric member housed in a bore of the first element, being rotational about a first axis, the eccentric member comprising a trunnion attached to the second element and of axis off-centred with respect to the first axis of rotation, the eccentric member being rotational about said off-centred axis. The solution of the invention has the advantage of allowing a compact assembly.

Abstract: The present invention pertains to turbine engine mounting onto an aircraft pylon, comprising a bracket (12) arranged to be attached to the pylon, a lever (15;15?) attached in its central part (150;150?) to the bracket by first connection means (150-130) with a pivot pin (136;136?) and two thrust links (20,22; 20?,22?) each joined aft to the lever by second connection means (200-155, 220-157; 200?-155?; 220?-157?) and including engine attachment means at the forward end, characterized in that the first connection means (150-130) consists of two parallel arms (151,153) spaced apart on central part (150) of the lever, cooperating with an attachment lug (130) integral with the bracket via a pivot pin, and lever (15,15?) comprises two third side connection means on standby (155-135, 157-137; 155?-135?; 157?-137?) with bracket (12,12?). The invention provides for simplified mounting with improved safety.

Abstract: The present invention relates to a rear attachment suspension or device of a turbo engine (1) to an aircraft pylon including an upper brace (12) fitted with pylon fastening means, whereon are hinged by second ball joint connections (163, 183), three rocker bars transversal to the longitudinal axis of the engine, a first (16) and a second (18) rocker bars on both sides of the axis of the engine and a third rocker bar (17) between both of them, the rocker bars being themselves linked with the engine by first ball joint connections (161, 181). The suspension is characterised in that the first (16) and second (18) rocker bars each include a third (167, 187) stand-by link and in that the upper brace (12) is formed of a beam (120) fixed rigidly to the pylon.

Abstract: The present invention relates to a suspension of the turbo fan engine to an aircraft pylon, including a fitting (12) arranged to be attached to a pylon, a lever (15) fastened in its central portion (150) to the fitting via a linking means with a pivot pin (150P), and two thrust rods (20, 22) each connected by an end to the lever and including at the other end of the fastening means to the engine. It is characterised in that said linking means is composed on said central portion (150) of the lever, of two parallel branches (151, 152) apart from one another, and on the fitting, of a central fastening tab (133), whereas the fastening tab and both branches are held together by dint of said pivot pin (150P).

Abstract: The present invention relates to an attachment device, in particular a front attachment device, for attaching a turbo engine (1) to an aircraft pylon including an upper brace (12, 12′) fitted with rigid fastening means to the pylon, a first (16) and a second (18) connecting rods, each connected to the engine, via a first ball joint connection (161, 181; 161′, 181′), on the one hand, and to the upper brace (12, 12′) via a second ball joint connection (165, 185; 165′, 185′), on the other hand. The device is characterised in that each connecting rod (16, 18) includes a third stand-by link (167, 187; 176′, 187′).