Abstract: A beam for reinforcing the structure of an aircraft is located inside the fuselage of the aircraft. The fuselage includes at least one pressurized zone (P) that is separated by at least one airtight wall (18) of at least one other non-pressurized zone (16), the beam and the at least one airtight wall being intersecting. The beam traverses the at least one airtight wall (18) that includes a cutaway that is adapted to the section of the beam, whereby sealing elements (30) are provided to ensure the sealing between the beam and the airtight wall (18) that is traversed.

Abstract: A method for assembling a cabin window to a bay in a side wall of an aircraft fuselage, the cabin window including an outer transparent element and at least one inner transparent element. A non-through hole is made in a portion of the side wall along the edge of the bay. Subsequently, the outer transparent element is positioned in the bay from the exterior of the fuselage. The element includes a first part 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 in the bay both laterally and longitudinally. A second part of the outer transparent element has a groover that projects into the fuselage. The outer transparent element and the at least one inner transparent element are welded to the fuselage using a strap which presses a seal against at least the fuselage and the inner wall of the groove.

Abstract: The invention relates to an aircraft fuselage comprising a nose cone, a tail section and a central section, the central section comprising longitudinal panels assembled directly with one another, at least one of these longitudinal panels having a length corresponding to the distance between the nose cone and the tail section in order to connect said nose cone with said tail section.