A nacelle for a propulsion assembly, the nacelle including a front internal structure having a framework formed of longitudinal beams and including removable, dismountable or retractable panels which are provided to facilitate the access for maintenance to the parts of the motor shrouded by these panels.

A nacelle for a propulsion assembly, the nacelle including a front internal structure having a framework formed of longitudinal beams and including removable, dismountable or retractable panels which are provided to facilitate the access for maintenance to the parts of the motor shrouded by these panels.

A fuselage rear end of an aircraft, comprising a structural part comprising a skin and longitudinal and transversal reinforcing members and a fairing. The structural part longitudinally spans over the whole rear end and comprises a first portion in which the transversal reinforcing members occupy the whole perimeter of the corresponding fuselage section and at least a second portion in which the transversal reinforcing members occupy only a portion of the perimeter of the corresponding fuselage section. The fairing is located below the second portion of the structural part.

An aircraft propulsion assembly has a hinge for articulating a first and a second of its panels. The hinge includes a yoke rigidly connected to the first panel and a counter-yoke rigidly connected to the second panel, which is received between two lugs of the yoke.The yoke and the counter-yoke are passed through by a hinge pin that is movable between an extended position between the lugs of the yoke and a retracted position outside the yoke. The hinge further includes bayonet mounting means interposed between the pin and the yoke.

An aircraft propulsion assembly has a hinge for articulating a first and a second of its panels. The hinge includes a yoke rigidly connected to the first panel and a counter-yoke rigidly connected to the second panel, which is received between two lugs of the yoke.The yoke and the counter-yoke are passed through by a hinge pin that is movable between an extended position between the lugs of the yoke and a retracted position outside the yoke. The hinge further includes bayonet mounting means interposed between the pin and the yoke.

A removable closure member is configured to close a female portion received in an external opening formed in the external surface of a nacelle for an aircraft engine. The female portion includes at least one air inlet opening. The closure member includes a base that forms the external contour of the member and that extends beyond the external opening of the nacelle so as to move into abutment against the external surface of the nacelle. The closure member further includes at least one resiliently deformable position retention member that projects from the base and is configured to be inserted into the air inlet opening.

A removable closure member is configured to close a female portion received in an external opening formed in the external surface of a nacelle for an aircraft engine. The female portion includes at least one air inlet opening. The closure member includes a base that forms the external contour of the member and that extends beyond the external opening of the nacelle so as to move into abutment against the external surface of the nacelle. The closure member further includes at least one resiliently deformable position retention member that projects from the base and is configured to be inserted into the air inlet opening.

A latch mechanism includes a hook-handle assembly coupled to a first panel and a clevis coupled to a second panel. The hook-handle assembly engages the clevis to secure the first panel relative to the second panel.

A nacelle for an aircraft engine comprising a first fan cowl and a second fan cowl , each fan cowl comprising a hinged end and a closing end , each fan cowl being mobile between a closed operating position and an open maintenance position, the first fan cowl having a larger angular coverage than the second fan cowl, the first fan cowl comprising an upper part connected to a lower part by an intermediate hinge so as to allow the lower part to fold towards the upper part.

A nacelle for an aircraft engine comprising a first fan cowl and a second fan cowl , each fan cowl comprising a hinged end and a closing end , each fan cowl being mobile between a closed operating position and an open maintenance position, the first fan cowl having a larger angular coverage than the second fan cowl, the first fan cowl comprising an upper part connected to a lower part by an intermediate hinge so as to allow the lower part to fold towards the upper part.