Abstract: A method for applying a corrosion protection layer to a surface to be protected of a component: including providing the corrosion protection layer having a first surface and a second surface arranged opposite this, laying the first surface of the corrosion protection layer on a bottom face of a mold, laying the surface to be protected of the component on the second surface of the corrosion protection layer so as to enclose a layer of hardenable sealing compound, closing the mold by applying a bend-flexible cover so as to enclose the corrosion protection layer and the component, evacuating the mold so that the cover presses the component in the direction of the corrosion protection layer, and removing the vacuum and the cover after hardening of the sealing compound.

Abstract: A method for the connection of moulded parts, wherein a locking collar pin with locking grooves or with an external thread, is driven through the moulded parts and subsequently a locking collar is locked together with at least some of the locking grooves, or with threaded sections of the locking collar pin, by the application of radial pressure, or by means of a screwing operation. A connecting system with a locking ring pin, which has a punching section for purposes of punching through the moulded parts, and also locking grooves for purposes of active engagement with a locking ring; the latter extends over at least two adjacent locking grooves in the axial direction, or over at least two adjacent threads in the axial direction.

Abstract: A device for the temporary position fixing of adjacently arranged aircraft structures to be interconnected includes a support frame with at least one vacuum suction cup for temporary surface attachment and with clamping means for the position fixing of the aircraft structures to be interconnected. The support frame with the at least one vacuum suction cup in the region of a transverse gap is attached on the side of one aircraft structure. The support frame includes mechanical contact pressure means for the gap-bridging position fixing of the adjacent other aircraft structure. On the support frame there is a counter support to pressure elements of the contact pressure means.

Abstract: Disclosed is a method for the manufacture of an aircraft fuselage with at least two fuselage barrels wherein connecting segments are firstly prepared for the formation of a transverse joint region for a later transverse joint, and the fuselage barrels are then constructed around the connecting segments; also disclosed is an aircraft fuselage with ring-type connecting segments for the formation of such a transverse joint.

Abstract: A method for assembling an aircraft fuselage includes different steps. In a first step the secondary structural components and interior components are assembled to form a core structure. The core structure comprises a cabin floor, side wall panels and ceiling panels. In another step of the method a primary structure is arranged around the core structure to form a part of a fuselage.

Abstract: Disclosed are a method and a device for the connection of two components indirectly or directly in an overlap joint, wherein component sections located in the overlap are pressed together for each drilling procedure by means of a clamping unit formed from a pressure application device on the drilling machine side and a guide on the component side, such that any penetration of chips between the component sections is prevented and temporary connecting elements can be dispensed with.

Abstract: A clamping device is provided for an assembly of a stringer coupling in a region of a lateral butt joint between a first and a second fuselage section of an aircraft for coaxially connecting a respective first and second stringer of the first and the second fuselage sections, the stringer coupling intersecting a frame element profile in the region of the lateral butt joint. A supporting yoke is configured to bridge the frame element profile in an arc-shaped manner and includes a first end foot supported by the stringer coupling on the first side of the frame element profile and a second end foot supported by the stringer coupling on the second side of the frame element profile. The supporting yoke includes a middle tensioning hook configured to interact with the frame element profile. The first and the second end feet are tensionable against the stringer coupling.

Abstract: A device for the temporary position fixing of adjacently arranged aircraft structures to be interconnected includes a support frame with at least one vacuum suction cup for temporary surface attachment and with clamping means for the position fixing of the aircraft structures to be interconnected. The support frame with the at least one vacuum suction cup in the region of a transverse gap is attached on the side of one aircraft structure. The support frame includes mechanical contact pressure means for the gap-bridging position fixing of the adjacent other aircraft structure. On the support frame there is a counter support to pressure elements of the contact pressure means.

Abstract: A method for the connection of moulded parts, wherein a locking collar pin with locking grooves or with an external thread, is driven through the moulded parts and subsequently a locking collar is locked together with at least some of the locking grooves, or with threaded sections of the locking collar pin, by the application of radial pressure, or by means of a screwing operation. A connecting system with a locking ring pin, which has a punching section for purposes of punching through the moulded parts, and also locking grooves for purposes of active engagement with a locking ring; the latter extends over at least two adjacent locking grooves in the axial direction, or over at least two adjacent threads in the axial direction.

Abstract: A method for tolerance compensation in an overlap joint between a first and a second body section of adjacent fuselage rings includes introducing a plurality of holes into a first body section corresponding to a pattern of rivets; arranging the first and second body section in an overlapping configuration so as to form an overlap; injecting a filler mass through the plurality of holes into a gap formed in the overlap; and hardening the filler mass.

Abstract: Disclosed are a method and a device for the connection of two components indirectly or directly in an overlap joint, wherein component sections located in the overlap are pressed together for each drilling procedure by means of a clamping unit formed from a pressure application device on the drilling machine side and a guide on the component side, such that any penetration of chips between the component sections is prevented and temporary connecting elements can be dispensed with.

Abstract: Disclosed is a method for the manufacture of an aircraft fuselage with at least two fuselage barrels wherein connecting segments are firstly prepared for the formation of a transverse joint region for a later transverse joint, and the fuselage barrels are then constructed around the connecting segments; also disclosed is an aircraft fuselage with ring-type connecting segments for the formation of such a transverse joint.

Abstract: A clamping device is provided for an assembly of a stringer coupling in a region of a lateral butt joint between a first and a second fuselage section of an aircraft for coaxially connecting a respective first and second stringer of the first and the second fuselage sections, the stringer coupling intersecting a frame element profile in the region of the lateral butt joint. A supporting yoke is configured to bridge the frame element profile in an arc-shaped manner and includes a first end foot supported by the stringer coupling on the first side of the frame element profile and a second end foot supported by the stringer coupling on the second side of the frame element profile. The supporting yoke includes a middle tensioning hook configured to interact with the frame element profile. The first and the second end feet are tensionable against the stringer coupling.

Abstract: A method for tolerance compensation in an overlap joint between a first and a second body section of adjacent fuselage rings includes introducing a plurality of holes into a first body section corresponding to a pattern of rivets; arranging the first and second body section in an overlapping configuration so as to form an overlap; injecting a filler mass through the plurality of holes into a gap formed in the overlap; and hardening the filler mass.