Abstract: A method for manufacturing a structural element for a fuselage of an aircraft. To improve the manufacture of structural elements, a method includes laying up textile material members on a mandrel to form a plurality of structural element preforms that are space apart along an extended direction of the mandrel. The structural element preforms form closed loops and are subsequently cured to obtain annular structural elements. The annular structural elements are used as basic building blocks for stiffening panel members or are directly used as structural frame elements reinforcing cut-outs in a fuselage for windows and/or doors.

Abstract: The present invention concerns a prefilled injection device having a container and a dose setting mechanism encapsulated inside a housing. The injection device incorporates an axial variable connection such that a distance between a distal end of a piston rod and a plunger is minimized preferably to zero.

Abstract: A storage compartment for a passenger cabin of an aircraft is provided. The storage compartment comprises a storage compartment body, a mounting, a fixing brace and a pull rod. The fixing brace is connected to a frame of the primary structure of an aircraft and to the mounting and takes up forces transversely to the direction of flight. The pull rod is connected to a stringer of the aircraft primary structure and also to the mounting and takes up forces in the direction of flight in such a way that even in the event of an impact event, only low torques are to be taken up by the supporting primary structure of the aircraft.

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: A housing-free hatrack for a passenger cabin of an aircraft includes a hatrack body, at least one fixing brace and a support which is arranged between the hatrack body and one end of the fixing brace in such a way that the hatrack body is pivotable about a pivot axis. The other end of the fixing brace may be connected to a frame of an aircraft structure of the aircraft. This hatrack dispenses with the double-walled construction of conventional hatracks and the hatrack is therefore directly fixed to the structure of the aircraft.

Abstract: A cargo door arrangement for an aircraft includes a fuselage portion, a cargo door and a locking mechanism. The fuselage portion includes a skin portion, at least one fuselage former and an opening. The cargo door includes at least one door former. The locking mechanism includes a first engagement element, a second engagement element and a connecting means. The first engagement element has a tapered portion and is rigidly connected to the door former. The second engagement element includes a tapered cavity having a shape matching the shape of the tapered portion and is rigidly connected the fuselage former. In the closed position the tapered portion is engageable with the cavity. The connecting means is adapted to rigidly connect in the closed position the door former to the first or second engagement element.

Abstract: A storage compartment for a passenger cabin of an aircraft is provided. The storage compartment comprises a storage compartment body, a mounting, a fixing brace and a pull rod. The fixing brace is connected to a frame of the primary structure of an aircraft and to the mounting and takes up forces transversely to the direction of flight. The pull rod is connected to a stringer of the aircraft primary structure and also to the mounting and takes up forces in the direction of flight in such a way that even in the event of an impact event, only low torques are to be taken up by the supporting primary structure of the aircraft.

Abstract: A housing-free hatrack for a passenger cabin of an aircraft includes a hatrack body, at least one fixing brace and a bearing which is arranged between the hatrack body and one end of the fixing brace in such a way that the hatrack body is pivotable about a pivot axis. The other end of the fixing brace may be connected to a former of an aircraft structure of the aircraft. This hatrack dispenses with the double-walled construction of conventional hatracks and the hatrack is therefore directly fixed to the structure of the aircraft.

Abstract: The present invention concerns a prefilled injection device having a container and a dose setting mechanism encapsulated inside the housing. The injection device incorporates an axial variable connection such that the distance between the distal end of the piston rod means and the plunger is minimized preferably to zero.