Abstract: The disclosed embodiments concern a floor panel for a transport vehicle such as an aircraft and an installation for fixing cabin layout elements including such panels. The disclosed embodiments are wherein the floor panel includes at least one mounting rail having a lengthwise axis, inserted into the layer of the aforementioned panel.

Abstract: These disclosed embodiments relates to a device for fixing a light-weight panel onto a support. Such device includes an insert including at least one flange, such insert being intended for receiving a fixing device of the bolt type. According to the disclosed embodiments, such flange has an outer surface including toothing elements and the device includes a part made of a ductile material including an opening for the passage of the fixing member. The toothing elements are intended for cooperating, upon fixing the panel onto the support, with the part made of a ductile material to allow such fixing without causing any deformation of the panel.

Abstract: The disclosed embodiments concerns a floor panel for a transport vehicle such as an aircraft and an installation for fixing cabin layout elements including such panels. The disclosed embodiments are characterized in that the floor panel includes at least one mounting rail having a lengthwise axis, inserted into the layer of said panel.

Abstract: These disclosed embodiments relates to a device for fixing a light-weight panel onto a support. Such device includes an insert including at least one flange, such insert being intended for receiving a fixing device of the bolt type. According to the disclosed embodiments, such flange has an outer surface including toothing elements and the device includes a part made of a ductile material including an opening for the passage of the fixing member. The toothing element are intended for cooperating, upon fixing the panel onto the support, with the part made of a ductile material to allow such fixing without causing any deformation of the panel.

Abstract: The nose gear of an aircraft comprises a main group of at least one wheel (10) in permanent contact with the ground and a secondary group of at least one wheel (12), which is normally spaced from the ground, when the aircraft is on the ground. In the case of emergency braking due to an aborted takeoff or in the case of a blowout of a tire of a wheel (10) of the main group, the wheel or wheels (12) come into contact with the ground. This avoids an oversizing of the nose gear.

Abstract: An airbrake located on the wing of an aircraft between a rear spar and a wing flap comprises two panels aligned with the upper surface of the wing when the airbrake is closed. In the open state or fully deployed position, the two panels are contiguous and behave as a single panel. However, in the intermediate states, the panel closest to the flap is deflected more than the other panel, so that a slot is formed between them. This slot makes it possible to significantly decrease turbulence on either side of the airbrake when the latter is used in low deflection flight.

Abstract: In a turbofan engine, the mechanical connection between the pod (12) and the fan stator case (10) is limited to a centering system (22) in the immediate vicinity of the arms (20) by which the fan stator case is mounted on the central portion (16) of the engine. The aerodynamic and inertia loads applied to the pod (12), particularly on take-off and landing, consequently only lead to an acceptable deformation of the fan stator case (10). Thus, the gap between said case and the fan (18) can be kept to a very small value, which ensures maximum engine efficiency. Moreover, the centering system (22) prevents an excessive radial displacement (J') between the front of the fan stator case (10) and the adjacent portion of the pod.

Abstract: The present invention relates to an aircraft of which the structure comprises a longitudinal floor separating the passenger cabin from at least one luggage compartment pressurized normally and communicating via peripheral openings in said floor, these openings being concealed on the cabin side by air shafts, fixed obliquely to the inner wall of the cabin and arranged so that their orifice near said floor opens into said cabin and their other orifice communicates with one of said openings, creating an air-circulation baffle, in which aircraft said air shafts are articulated, on the side away from said floor, to said inner wall of the cabin, to be able spontaneously to clear the corresponding opening in the case of a sudden decompression in said luggage compartment, thus providing protection against the effects of such an abrupt decompression therein.

Abstract: The invention relates to aircraft wings, wherein the fairing element between the leading edge of a wing and the fuselage comprises a streamlining flap movable between a folded position in which it is housed in a recess in the fairing element and forms a part of the leading edge and the part adjacent the lower surface of said fairing element, and an extended position in which it ensures continuity of the leading edge between the fuselage and the high-lift spoiler likewise in extended position. Moreover, there is a communication between the housing of the streamlining flap and the housing of the high-lift spoiler so that, when these two flap elements are in their extended positions, the air penetrating in the housing of the streamlining flap disposed on the lower surface side emerges through the housing of the high-lift spoiler disposed on the upper surface side, with the result that there is an increased upper surface blowing.