Abstract: The invention discloses a trailing edge (2) of an aircraft aerodynamic surface, which comprises an upper skin (6) and a lower skin (7), being the upper and lower skins (6, 7) made of composite material. In the trailing edge (2) a lightweight part (1) is assembled at an end section (13) of the upper and lower skins (6, 7). The lightweight part (1) is covered by a metallic sheet (8), and has a “V”-shaped cross section with arms and peak, where the peak of the “V”-shaped cross section has a rounded shape and is located opposite the end section (13) of the upper and lower skins (6, 7).

Abstract: Optimization of structures subjected to hot gas streams. The invention refers to a fairing (10) for aircraft horizontal stabilizer (3) comprising a front part (11) and a rear part (12), the front part (11) covering a limited extent of the fairing (10) surface, which is the part of the fairing (10) receiving hot air stream (6) coming from the aircraft engines (4), this front part (11) being made of an anti-erosion material, the rear part (12) covering the rest of the surface of the fairing (10), this rear part (12) being made of a material resisting the aerodynamic loads existing on the fairing (10). The invention also refers to an aircraft comprising a horizontal stabilizer (3) with a fairing (10) such as the one described.

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: Optimisation of structures subjected to hot gas streams. The invention refers to a fairing (10) for aircraft horizontal stabilizer (3) comprising a front part (11) and a rear part (12), the front part (11) covering a limited extent of the fairing (10) surface, which is the part of the fairing (10) receiving hot air stream (6) coming from the aircraft engines (4), this front part (11) being made of an anti-erosion material, the rear part (12) covering the rest of the surface of the fairing (10), this rear part (12) being made of a material resisting the aerodynamic loads existing on the fairing (10). The invention also refers to an aircraft comprising a horizontal stabilizer (3) with a fairing (10) such as the one described.

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).