Abstract: A turbofan engine nacelle has a downstream section which includes at least one front frame. The front frame is attached to a stationary portion of the nacelle, and the downstream section is provided with at least one rail or slide which extends in a longitudinal direction of the nacelle and is capable of engaging with at least one corresponding slide or rail of an attachment pylon of the turbofan engine. The front frame is connected to the rail or slide of the downstream section by means of at least one swiveled connecting rod.

Abstract: The present disclosure relates to a centering device for a nacelle of a turbojet engine providing the flush centering of an outer downstream panel of a thrust reverser with respect to a cowl of a fan casing. The centering device includes, in one single piece: a sub plate allowing the fixing of the centering device to the fan casing; a first positioning arm integrally formed with the sub plate, protruding upstream, in such a manner as to form, with respect to a directing axis (A) of the nacelle; a first radial abutment designed for guiding the cowl of the fan casing; and a second positioning arm, integrally formed with the sub plate, protruding downstream, in such a manner as to form, with respect to the directing axis (A) of the nacelle, a second radial abutment designed for guiding the outer downstream panel.

Abstract: A device for connecting a thrust reverser front frame to a fan casing includes a crenulated flange secured to the front frame, an annular component to accept this flange secured to the fan casing, and a crenulated annulus of a shape that complements the flange and pivot-mounted on the annular component. The crenulated flange, the annular component and the crenulated annulus are designed in such a way that a rotation of the annulus with respect to the annular component has the effect of locking this flange against this annular component through the collaboration between the respective crenulations of the flange and of the annulus.