Patent ID: 8940215
Filing Date: 2015-01-27
Classification: B64C,Y10T

Abstract:
1. A method for assembling frames on a fuselage of an aircraft, wherein fuselage elements comprising a fuselage skin, presenting an internal side and an external side, frames and ribbands are assembled in a supply phase, the skin and the frames being made of composite materials based on carbon fibers, comprising the steps: with each frame presenting a globally crown-shaped wall, injecting a glue film, in a preparation phase, on an interface between a substantially plan external side of the frame crown and an internal side of the skin according to predefined places, introducing the so-assembled unit into an enclosure to perform a co-gluing phase combining gluing of the frames, and fuselage skin baking, in determined conditions of time, temperature and pressure, forming window openings in a machining phase by cutting an annular part of the crown made by the frame and the opposite fuselage skin connected to this part, according to a profile being complementary of this of the windows to be mounted,