A blocking mechanism which is integrated with a threaded fastener is proposed for improving the reusability and handling of locking devices for threaded fasteners, such as threaded bolts or nuts. The blocking mechanism can be switched to and from between a blocked state, in which the threaded fastener is gripped in a positively locking manner, and an unblocked state, in which the threaded fastener can be rotated. The blocking mechanism can have a blocking element which can engage into a blocking groove of the threaded fastener in a positively locking manner in the blocked state, and thus prevents rotation. For example, a nut which is provided with the blocking mechanism can be used to pivotably fasten a fastening rod to a fastening rail.

A landing gear bay including a bottom wall which includes longitudinal beams and at least one panel forming an airtight barrier between first and second zones disposed on either side of the panel. The panel has first and second longitudinal edges each linked to one of the longitudinal beams. The second zone is configured to sustain a pressure greater than that of the first zone. The panel has a profile that is substantially constant in the longitudinal direction and includes at least one central part offset toward the second zone with respect to its first and second longitudinal edges. This solution makes it possible to limit the vertical stresses applied to the longitudinal beams by virtue of the pressure difference between the first and second zones.

A landing gear bay including a bottom wall which includes longitudinal beams and at least one panel forming an airtight barrier between first and second zones disposed on either side of the panel. The panel has first and second longitudinal edges each linked to one of the longitudinal beams. The second zone is configured to sustain a pressure greater than that of the first zone. The panel has a profile that is substantially constant in the longitudinal direction and includes at least one central part offset toward the second zone with respect to its first and second longitudinal edges. This solution makes it possible to limit the vertical stresses applied to the longitudinal beams by virtue of the pressure difference between the first and second zones.

An aircraft floor including at least one hinge connecting movable and fixed floor parts, which has a pivot axis parallel to a longitudinal direction. The floor also includes at least two beams, each including first and second beam portions secured respectively to the fixed and movable floor parts and connected together by a pivot link, and at least one rail including at least one first rail portion secured to the movable floor part and at least one second rail portion secured to the fixed floor part of the floor, extending the first rail portion.

A fuselage for an aircraft includes a pressure deck assembly extending along a roll axis of the fuselage. The pressure deck assembly includes longitudinal beams and a pressure deck. The longitudinal beams extend lengths along the roll axis of the fuselage. The pressure deck extends between the longitudinal beams along the lengths of the longitudinal beams. The pressure deck is compliant along a pitch axis of the fuselage. The fuselage includes a bulkhead extending along a yaw axis of the fuselage. The bulkhead is joined to the pressure deck assembly at a corner joint. The fuselage includes a compression chord extending a length along the pitch axis of the fuselage. The compression chord is joined between the pressure deck assembly and the bulkhead at the corner joint such that the compression chord extends on an outside of the corner joint.

A fuselage for an aircraft includes a pressure deck assembly extending along a roll axis of the fuselage. The pressure deck assembly includes longitudinal beams and a pressure deck. The longitudinal beams extend lengths along the roll axis of the fuselage. The pressure deck extends between the longitudinal beams along the lengths of the longitudinal beams. The pressure deck is compliant along a pitch axis of the fuselage. The fuselage includes a bulkhead extending along a yaw axis of the fuselage. The bulkhead is joined to the pressure deck assembly at a corner joint. The fuselage includes a compression chord extending a length along the pitch axis of the fuselage. The compression chord is joined between the pressure deck assembly and the bulkhead at the corner joint such that the compression chord extends on an outside of the corner joint.

A structural assembly for an aircraft having pairs of main gantries distributed in the longitudinal direction, two transverse panels fixed to the front and the rear of the pairs of main gantries to together define a compartment for a landing gear of the aircraft, at least one pair of secondary gantries between the main gantries, at least one crossmember parallel to the transverse panels and that straddles at least one secondary gantry, and, for each secondary gantry and each crossmember straddling the secondary gantry, a connecting rod mounted to be able to freely rotate, via a first end, on a lower part of the crossmember and, via a second end, on an outer lateral part of the secondary gantry. Such an arrangement reduces the vertical bulk of the structural assembly.

An aircraft including a floor positioned above a central wing box and in a front fuselage portion positioned in front of the central wing box. The floor includes at least one rail which has at least first and second rail portions and at least one articulation connecting the first and second rail portions and configured to allow a pivoting movement, about a transverse and horizontal pivot pin, between the connected first and second rail portions. By virtue of this articulation, it is possible to integrate the rails into the floor and not to position them on the floor.

An aircraft including a floor positioned above a central wing box and in a front fuselage portion positioned in front of the central wing box. The floor includes at least one rail which has at least first and second rail portions and at least one articulation connecting the first and second rail portions and configured to allow a pivoting movement, about a transverse and horizontal pivot pin, between the connected first and second rail portions. By virtue of this articulation, it is possible to integrate the rails into the floor and not to position them on the floor.

A sealed component assembly within an aircraft, comprising first 10 and second 12 components each facing surfaces, and a sealing member 20 extending between the facing surfaces. The sealing member includes a conductive portion 22 sandwiched between first 24 and second 26 sealing portions. The sealing portions extend between and in contact with the facing surfaces, and are made of a sealing material. The conductive portion is in contact with conductive regions of the facing surfaces and defines an electrical connection therebetween. The conductive portion is more conductive than the sealing portions. In a particular embodiment, the components are a floor panel and a floor beam. A sealing member 20 for a connection between two aircraft components is also discussed.