Airbus Operations Sl

Airbus Espana, S.l.

Francisco De Paula Burgos Gallego

Alberto Balsa Gonzalez

Alberto Balsa González

Manuel Maroto De Hoyos

Alberto Balsa GONZÁLEZ

A repair process for a composite material panel that forms part of a fuselage, wings, or stabilizers of an aircraft, with the panel having large dimensions and including irregular contours in some areas and edges prone to damages occurring from handling and assembly of the panel. The process a) locates the damage in the element of the composite material panel; b) sands the area that includes the damage in an area larger than the damage, makes a cut in the panel, having the cut of a same form as a piece that will serve to repair panel; c) places the piece in the cut, so that it is perfectly flush with the panel to be repaired; and d) attaches the piece to the composite material panel.

Process for repairing airplane panels

Trailing edge () of an aircraft stabilizer surface (), where this surface () is manufactured of a composite material and comprises an outer cladding () and an inner cladding () that are connected by a connecting clip type element () on this trailing edge (), the connecting clip type element () comprising at its ends some recesses () used for coupling to the inner zone of the upper and lower claddings () of the stabilizer surface (), such that the connecting clip type element () is flexible enough to be pinched so that its ends will be housed, by means of these recesses (), between the outer and inner claddings () of the aircraft stabilizer surface (), whereby the outer zone of the stabilizer surface (), on its trailing edge (), is formed by a continuous aerodynamic surface without changes of gradient.

Aircraft stabilizer surface trailing edge

A lifting or stabilising component () for an aircraft comprising in the area of its trailing edge a rotary control element () rotating around an axis () with at least one slot () between the tip () of the component () and the control element (), the edges of which are configured such that the distance therebetween, that is, the dimension of the slot (), is constant for different angles of deflection of the control element (), being located between them a seal () that assure the aerodynamic continuity of the component () when the control element () is at rest. In a preferred embodiment, the component () is a horizontal tail stabilizer and the control element () is a rudder.

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Madrid, Spain

Francisco De Paula Burgos Gallego