Abstract: The detection method is performed by a characteristic tool (1) constituting the detection device, incorporating a lateral tab (10) and a front end edge (11), so that when the tool is applied to determine whether a banded sleeve has migrated, it happens that if the same is located correctly, such side tab (10) is supported by its front seat (12) on a centered portion (13) of the free edge of the respective lug (4) of the hardware (5). In contrast, when the banded sleeve (2) has migrated axially moving from its location, in this case of anomaly, the front end edge (11) of the tool (1) will contact with the projection of the banded sleeve (2) instead of contacting the side tab (10) on the central portion (13).

Abstract: The invention relates to a device (1) for joining torsion boxes (5, 6) of aircraft structures, said structures carrying fuel therein, characterized in that the mentioned device (1) comprises three sides (2, 3, 4) by means of which it is secured to the inner part of the structural parts of the joint of the torsion boxes (5, 6) of the aircraft in a permanent manner, said device (1) thus closing the joint of the boxes (5, 6) and preventing possible fuel leaks, the device (1) being a non-structural component of the mentioned joint since it does not withstand the loads of the structure of the joint of torsion boxes (5, 6).

Abstract: It is intended for joining two pieces (1 and 2) that are in contact with each other via their respective inner faces (3 and 4), with one of them having a blind threaded hole (5) in which is coupled a first threaded end segment (6) of a bolt (7) which includes an annular extension (9) that limits the tightening rotation of the bolt (7) with the interposition of a characteristic elastic washer (8) as means for immobilizing the bolt (7) preventing it from coming loose. The other piece of the pair includes through holes (13) in correspondence with each of which is housed a section (11) of the respective bolt (7), projecting out of which said piece is a second threaded end segment (14) of the bolt (7), in which segment is coupled a self-locking nut (15) which fixes the two pieces together.

Abstract: Trailing edge (3) of an aircraft stabilizer surface (1), where this surface (1) is manufactured of a composite material and comprises an outer cladding (40) and an inner cladding (41) that are connected by a connecting clip type element (20) on this trailing edge (3), the connecting clip type element (20) comprising at its ends some recesses (23) used for coupling to the inner zone of the upper and lower claddings (40, 41) of the stabilizer surface (1), such that the connecting clip type element (20) is flexible enough to be pinched so that its ends will be housed, by means of these recesses (23), between the outer and inner claddings (40, 41) of the aircraft stabilizer surface (1), whereby the outer zone of the stabilizer surface (1), on its trailing edge (3), is formed by a continuous aerodynamic surface without changes of gradient.