Abstract: Method for optimising the design of sealing rings of internal manhole covers which close the manhole openings over the inner surface of the skin of an aircraft structure, the surface that is in contact with the inner surface of the skin being the optimized surface of said sealing rings, the method including dividing the outer contour and the inner contour of the optimised surface into n points; grouping into families Fi the sealing rings of each manhole opening; generating the curves that are best adapted to the set of points taken for the outer contour and for the inner contour of each sealing ring for each one of the families Fi; generating a ruled surface among the curves generated for each one of the families Fi.

Abstract: A manhole assembly in the lower skin (37) of an aircraft wing made of a composite material for giving access to an installation placed inside said aircraft wing such as a fuel tank, comprising an inner cover (31) and an outer cover (33) joined by first fastener means (35); the lower skin (37) being configured with a rebated edge (45) around the manhole so that the outer cover (33) can be mounted over the lower skin (37) maintaining the aerodynamic continuity in the aircraft wing surface; the inner cover (31) being mounted over the lower skin (37) by its inner surface with a sealing profile (41) between them and being joined to the lower skin (37) by second fastener means (47).

Abstract: A manhole assembly in the lower skin (37) of an aircraft wing made of a composite material for giving access to an installation placed inside said aircraft wing such as a fuel tank, comprising an inner cover (31) and an outer cover (33) joined by first fastener means (35); the lower skin (37) being configured with a rebated edge (45) around the manhole so that the outer cover (33) can be mounted over the lower skin (37) maintaining the aerodynamic continuity in the aircraft wing surface; the inner cover (31) being mounted over the lower skin (37) by its inner surface with a sealing profile (41) between them and being joined to the lower skin (37) by second fastener means (47).

Abstract: Interface arrangement between a first component (11) and a second component (21) of an aircraft structure having an aerodynamic contour, such as a wing skin and a wing leading edge panel, the first component (11) having a joggle so that it includes a first area (13) which surface (15) belongs to the aircraft aerodynamic contour and a second area (17) where the joint with the second component (21) takes place, the second component (21) having a surface (23) belonging to the aircraft aerodynamic contour, in which a sealing part (31) suitable shaped to maintain the continuity of the aircraft aerodynamic contour in the interface area between said components (11, 13) as well as to fill the expected gap (25) between said components (11, 13) is joined to the second component (21).