Abstract: A device and method for assembling two aircraft fuselage sections each comprising a skin and longitudinal stiffeners, the device comprising fishplates fishing couples of mutually aligned longitudinal stiffeners belonging respectively to said sections, each fishplate comprising two fishplate pieces each comprising at least one longitudinal sole plate intended to be fixed to a longitudinal stiffener, and a transverse support head, and at least one demountable connecting member able to mutually clamp the respective support heads of said fishplate pieces to allow a transmission of longitudinal forces between these fishplate pieces.

Abstract: A damping connecting rod that can be converted into a rigid connecting rod in the case of abnormal vibrations. The damping connecting rod comprises a body having a cavity and a shaft inside the cavity, with a clevis associated with the body and allowing the clevis to be fixed to an element. The shaft can be longitudinally displaced inside the body or the body about the shaft. The connecting rod includes an arrangement for longitudinally immobilizing the shaft with respect to the clevis comprising at least one hook and at least one hollow, which are borne by two connecting rod pieces, respectively, which are configured to be displaced toward one another and with a shape such that, with the displacement of the pieces longitudinally with respect to one another, the hook driven into the corresponding hollow longitudinally immobilizes the shaft with respect to the clevis.

Abstract: A joint including first and second rib components, the first rib having an abutment surface and a plurality of lugs disposed adjacent to the abutment surface; and the second rib having an abutment surface and a plurality of lugs disposed adjacent to the abutment surface, wherein the abutment surfaces of the respective ribs are abutting and joined with a tension joint, and wherein the lugs are pinned to form a pinned lug joint by aligning respective holes in the plurality of lugs such that the lugs of the first and second ribs are interleaved and have one or more pins passing through the aligned lug holes. The joint may be used for attaching a wing tip device to the outboard end of an aircraft wing.

Abstract: An aircraft cockpit including a viewing device comprising a screen pivotably mounted on a mounting that allows height adjustment. A screen may also be placed at the top central portion of the instrument panel. The central screen is movable between an extended position and a retracted position in which the screen does not block the view of the pilots through the cockpit windscreen. A glare screen cowl, made at least partially of a taut fabric is used to cover the viewing screens, except optionally the mobile central screen which can pass through the cowl via an opening provided for that purpose. An avionics rack may be positioned forward of the screens of the instrument panel, in which the mounting is advantageously also used to support other devices such as a rudder control system and writing shelves.

Abstract: A joint including first and second rib components, the first rib having an abutment surface and a plurality of lugs disposed adjacent to the abutment surface; and the second rib having an abutment surface and a plurality of lugs disposed adjacent to the abutment surface, wherein the abutment surfaces of the respective ribs are abutting and joined with a tension joint, and wherein the lugs are pinned to form a pinned lug joint by aligning respective holes in the plurality of lugs such that the lugs of the first and second ribs are interleaved and have one or more pins passing through the aligned lug holes. The joint may be used for attaching a wing tip device to the outboard end of an aircraft wing.

Abstract: A joint comprising first and second rib components, the first rib having an abutment surface and a plurality of lugs disposed adjacent to the abutment surface; and the second rib having an abutment surface and a plurality of lugs disposed adjacent to the abutment surface, wherein the abutment surfaces of the respective ribs are abutting and joined with a tension joint, and wherein the lugs are pinned to form a pinned lug joint by aligning respective holes in the plurality of lugs such that the lugs of the first and second ribs are interleaved and have one or more pins passing through the aligned lug holes. The joint may be used for attaching a wing tip device to the outboard end of an aircraft wing.

Abstract: An aircraft including at least one door for passengers to board the aircraft, and at least one interconnection device connecting an aircraft internal structure component and a skin of a fuselage of the aircraft, the interconnection device being positioned near an internal periphery of the door in a region subject to external knocks and including at least one region that is weakened in terms of compression so as to absorb the knocks experienced by an external face of the skin of the fuselage, the device also being configured to withstand tensile forces applies to an internal face of the skin of the fuselage by internal pressure inside the aircraft.

Abstract: A device for mixing at least two separate streams of components which, when mixed, form a combined fluid stream. The device comprises a conduit with at least two separate passageways leading to exit openings at an end face of the conduit. Each passageway communicates with a separate component stream and is arranged to direct the separate component stream in a downstream direction. The exit openings each have a predetermined cross-sectional flow area. A separate channel is located at a downstream end of each passageway exit opening. The channels are arranged to redirect the flow from each passageway to an axial direction. A single mixing chamber communicates with all of the separate channels, the mixing chamber being arranged to receive each of the component streams at an upstream end thereof and to permit a mixing of the component streams. An outlet is arranged downstream of the mixing chamber through which the combined fluid stream is dispensed.

Abstract: Devices associated with an interface that is advantageous for the customized attachment of pieces of furniture to the floor of an aircraft. The interface includes rails extending longitudinally in the aircraft cabin, able to receive anchoring devices for connecting the furniture elements to these rails. The anchoring devices include axial and radial claw clamping devices which are associated together in pairs and operated together in pairs by a single and same lever (58, 95).

Abstract: An aircraft door closing device, and an aircraft incorporating such a device. The door includes a leaf and, connected to the aircraft fuselage, a frame including an opening configured to take the leaf, the leaf adopting a closed position to block the opening and another position to reveal the opening. The device includes a bearing mechanism, some on the leaf and some on the frame, each formed by a crenelated structure, two crenelated structures being arranged such that the teeth of one pass through notches of the other as the leaf moves from one position to the other, and such that the teeth of the leaf structure bear, in the closed position, on the inside face of the corresponding teeth of the frame structure.

Abstract: Device for assembling two aircraft fuselage sections each comprising a skin and longitudinal stiffeners, the device comprising fishplates fishing couples of mutually aligned longitudinal stiffeners belonging respectively to said sections, each fishplate comprising two fishplate pieces each comprising at least one longitudinal sole plate intended to be fixed to a longitudinal stiffener, and a transverse support head, and at least one demountable connecting member able to mutually clamp the respective support heads of said fishplate pieces to allow a transmission of longitudinal forces between these fishplate pieces. Set of fuselage sections assembled by means of a device of the type described above. Method of assembling two fuselage sections by means of a device of the type described above.

Abstract: A structural element of an aircraft includes a hollow part. An indicator provides a visual indication, for example by moving, if ice forms in a given region of the hollow part.

Abstract: An aircraft having a fuselage of composite type and more particularly to that of aircraft fuselage panels bearing cabin windows. The invention thus concerns a fuselage panel bearing a window comprising a composite structure cast in one piece, the structure comprising a main portion and at least one opening to accommodate a window, the structure having, on a zone surrounding the opening, a thickness more or less constant and greater than the thickness of the main portion of the structure. The invention also concerns an aircraft comprising a composite fuselage, the latter comprising such a panel or a similar panel made of metal material.

Abstract: An aircraft door closing device, and an aircraft incorporating such a device. The door includes a leaf and, connected to the aircraft fuselage, a frame including an opening configured to take the leaf, the leaf adopting a closed position to block the opening and another position to reveal the opening. The device includes a bearing mechanism, some on the leaf and some on the frame, each formed by a crenelated structure, two crenelated structures being arranged such that the teeth of one pass through notches of the other as the leaf moves from one position to the other, and such that the teeth of the leaf structure bear, in the closed position, on the inside face of the corresponding teeth of the frame structure.

Abstract: A method of fitting-out of an aircraft by laying of a floor, particularly in a cockpit of an aircraft, and such a fitted-out aircraft. The aircraft includes a fuselage part defining an interior volume and at least one internal on-board structure, the on-board structure being secured to the fuselage part and configured to accept a floor module. The method then involves introducing the floor module into the volume and attaching the floor module to the on-board structure.

Abstract: A structural element of an aircraft includes a hollow part. An indicator provides a visual indication, for example by moving, if ice forms in a given region of the hollow part.

Abstract: An aircraft including at least one door for passengers to board the aircraft, and at least one interconnection device connecting an aircraft internal structure component and a skin of a fuselage of the aircraft, the interconnection device being positioned near an internal periphery of the door in a region subject to external knocks and including at least one region that is weakened in terms of compression so as to absorb the knocks experienced by an external face of the skin of the fuselage, the device also being configured to withstand tensile forces applies to an internal face of the skin of the fuselage by internal pressure inside the aircraft.

Abstract: The invention relates to a pressurised aircraft door that minimises risk of ingress of precipitation inside the aircraft, while maintaining venting of the aircraft before unlocking the door. The purpose of the invention is achieved using a vent flap (15) controlled by a door control member (14) and designed such that the flap (15) successively occupies the following positions during the opening movement of the control member (14): a closed position when the control member (14) occupies a first end position putting the door in a closed/locked position; at least one partially open position before the door is in a closed/unlocked position; then once again in the closed position when the control member (14) occupies a second end position putting the door in an open position.

Abstract: This invention relates to the design of aircraft (100) having a fuselage (104, 106, 110) of composite type and more particularly to that of aircraft fuselage panels (110) bearing cabin windows (206, 306). The invention thus concerns a fuselage panel (110) bearing a window (206) comprising a composite structure cast in one piece (200, 212), the said structure comprising a main portion (200) and at least one opening (204) to accommodate a window (206), the said structure having, on a zone (213, 214, 216)) surrounding the said opening (204), a thickness more or less constant and greater than the thickness of the main portion (200) of the said structure. The invention also concerns an aircraft (100) comprising a composite fuselage (104, 106, 110), the latter comprising such a panel or a similar panel made of metal material (110).

Abstract: Boarding device for aircraft and flying wings equipped with such a device. The boarding device consists of at least one tunnel (20) connected to the outside of the aerodynamic shell (12) of the aircraft. More precisely, the tunnel is attached to the trailing edge of the fairing (12) and it extends aft approximately parallel to the longitudinal axis of the aircraft. A door (22) closes off the opening between the passenger cabin (10) and the tunnel (20). The rear part (26) of the tunnel (20) is articulated and/or detachable. In order to evacuate the passengers in an emergency, the front, fixed part of the tunnel (24) can be fitted with an inflatable escape slide or an articulated floor.