Abstract: Assemblies and methods for the handling, transporting and/or positioning component parts include a jig assembly for supporting a component part is provided with an elongate spar assembly, a plurality of rib assemblies attached to the spar, and a plurality of tensionable strap assemblies operatively associated with the rib assemblies for capturing and holding the component part against the rib assemblies. The strap assemblies may include a strap ratchet mechanism and a strap, so that operation of the strap ratchet mechanism allows strap slack to be removed thereby tensioning the strap. The jig assembly may be positioned and oriented by suspension cables and a hoist mechanism to allow it to be removably connected to a moveable transport dolly.

Abstract: A process for joining parts together is provided by positioning and temporarily clamping parts to be joined together. A number (n) of pilot holes may then be drilled through the temporarily clamped parts (e.g., by means of Cleco fasteners), wherein the number (n) of pilot holes is less than a total number (N) of holes required to be drilled to allow the parts to be joined together by permanent fasteners and to receive temporary fasteners therein. A remaining number (?) of holes to achieve the total number (N) of holes required for the parts to be joined together by permanent fasteners may thereafter be drilled so that permanent fasteners may be installed both, by automated system, in the number (n) of pilot holes and the remaining number (?) of holes that have been drilled to thereby permanently join the parts together.

Abstract: A safe takeoff monitoring system checks the actual physical parameters of an airplane during takeoff, determines the actual takeoff weight, and warns the pilot to interrupt the takeoff if any dangerous situation is developing, before a high energy abort is necessary.

Abstract: There is disclosed a structural arrangement (10) for an access window (30) to a fuel tank (20) with composite coating (40), this structural arrangement (10) comprising an external lid (11) associated to the access window (30) by fastening means (12), the structural arrangement (10) for an access window (30) to a fuel tank (20) with composite coating (40) further comprising a continuous metal frame (31) disposed on an internal portion of the fuel tank (20), fastened to the composite coating (40) internally and perimetrally circumventing the access window (30), the continuous metal frame (31) being cooperative with the external lid (11) in the conduction of an electric current.

Abstract: A method for joining components through mechanical adhesion comprising the following stages is disclosed: a) curing a resin laminate (1) on a surface (10) of a first component (11) imprinting a texture portion (30) upon the resin laminate (1); b) positioning an adhesive material laminate (2) on the texture portion (30); c) positioning a second component (12) on the adhesive material laminate (2); and d) curing the adhesive material laminate (2) and penetration of the adhesive material laminate (2) into the texture portion (30). Also described is a mechanical adhesion joint (20) for joining components, comprising an anchorage (40) formed by a texture portion (30) disposed on a first component (11) and permeated by an adhesive material laminate (2) contained in a second component (12), the texture portion (30) comprising a locking profile (31).

Abstract: Self-aligning couplers and methods for aligning superposed surfaces include a circular and semi-spherical base formed on a first surface, a fastening element perpendicularly passing through the circular and semi-spherical base and associated to a second surface, and at least a semi-spherical insert disposed on the circular and semi-spherical base and concentric to the fastening element. The semi-spherical insert is cooperative with the circular and semi-spherical base and the fastening element for the self-alignment and superposed fastening of the first and second surfaces.

Abstract: Diverter assemblies for aircraft air inlets include a diverter structure at least substantially surrounding the air inlet, and a fairing mounted to an upper edge of the diverter structure forwardly of the air inlet.

Abstract: To create an environment in which the passenger has the same emotion, feel and visual experience that a pilot has with regard to freedom of flight and proximity to the exterior of the aircraft and where passengers have the impression that they are looking out of an actual panoramic window, a “virtual window” includes internal and the external aspects of a real window. The internal part can comprise a folded or flexible high resolution color display that conforms to the internal profile of the aircraft fuselage as if it were an actual window. The external part comprises a paint scheme that is indistinguishable from an actual window and which is placed on the outside of the aircraft fuselage in registry with the conformal display in the aircraft's interior.

Abstract: Aircraft fuselage structures have reinforcement members in the vicinity of the stringer openings formed in frame members and are rigidly lap joined to a surface region of the frame members by a friction stir weld region. Such aircraft fuselage structural components may thus be provided with plural longitudinally spaced-apart frame members defining a transversal cross-section of an aircraft fuselage section, the frame members having a plurality of stringer holes therethrough, and plural longitudinally oriented stringers each being positioned within a respective one of the stringer holes of the frame member. The reinforcement members are lap joined to corresponding surfaces of frame members in the vicinity of the stringer holes such that the reinforcement members are joined rigidly to the corresponding surfaces of the frame members by a friction stir weld region.