Aircraft cabin window assembly method

Details Aircraft cabin window assembly method Aircraft cabin window assembly method

B - Operations, Transporting

64

C

B64C 1/14 (2006.01)

Patent

CA 2674450

The invention relates to a method for assembling a cabin window to a bay in a side wall (12) of an aircraft fuselage, said cabin window comprising an outer transparent element (10) and at least one inner transparent element (11). According to the invention, a non-through hole is made in a portion of the side wall (12) along the edge of the bay. Subsequently, the outer transparent element (10) is positioned in the bay from the exterior of the fuselage, said element including a first part (13) which has a diameter greater than that of the bay and which is shaped to co-operate with the above-mentioned portion such as to block the outer transparent element (10) in the bay both laterally and longitudinally. The outer transparent element (10) also includes a second part (16) having a groove (17) that projects into the fuselage. The outer transparent element (10) and the at least one inner transparent element (11) are welded to the fuselage using a strap (22) which presses a seal (21) against at least the fuselage and the inner wall of the groove (17).

L'invention concerne un procédé d'assemblage d'un hublot sur une ouverture définie dans une paroi latérale (12) du fuselage d un aéronef, ce hublot comprenant un élément transparent externe (10) et au moins un élément transparent interne (11). Selon l'invention, on réalise un évidement non débouchant sur une portion de la paroi latérale (12) le long du pourtour de l'ouverture. Puis on positionne depuis l extérieur du fuselage l'élément transparent externe(10) dans cette ouverture, l'élément ayant une première partie (13) dont le diamètre est supérieur au diamètre de l'ouverture, cette première partie (13) ayant une forme coopérant avec cette portion de manière à bloquer latéralement et longitudinalement l'élément transparent externe (10) dans l'ouverture. L'élément transparent externe (10) comprenant une deuxième partie (16) présentant une gorge (17) venant en saillie à l'intérieur du fuselage, on solidarise l'élément transparent externe (10) et ledit au moins un élément transparent interne (11) au fuselage par un cerclage (22), ce cerclage (22) plaquant un joint (21) contre au moins le fuselage et la paroi interne de la gorge (17).

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