Abstract: A fluidic connector to connect two ducts of a system such as an air conditioning system. The connector includes at least one elastic material, and includes a duct surrounded by an adjustable clamping collar which, when tightened, serves to deform it to reduce the internal space of the duct. The clamping of the collar makes it possible to easily and quickly regulate the rate of flow in the ducts.

Abstract: A fluidic connector to connect two ducts of a system such as an air conditioning system. The connector includes at least one elastic material, and includes a duct surrounded by an adjustable clamping collar which, when tightened, serves to deform it to reduce the internal space of the duct. The clamping of the collar makes it possible to easily and quickly regulate the rate of flow in the ducts.

Abstract: A method for constructing at least two fleets of aircraft of different families for which each aircraft has a front part comprising windows, a framing of the windows and a windshield front fairing, comprising, for each aircraft, constructing a module composed of the framing of all of the windows allowing outward visibility from the cockpit and of the windshield front fairing whose form is identical and constant for all the aircraft of the fleets and independent of a form of the fuselages thereof, and constructing a section of fuselage of which at least a part of an edge of the fuselage is of a form identical to an edge of the module, such that the module can be assembled directly with the contiguous fuselage section, whatever the aircraft of the fleets.

Abstract: A method for constructing at least two fleets of aircraft of different families for which each aircraft has a front part comprising windows, a framing of the windows and a windshield front fairing, comprising, for each aircraft, constructing a module composed of the framing of all of the windows allowing outward visibility from the cockpit and of the windshield front fairing whose form is identical and constant for all the aircraft of the fleets and independent of a form of the fuselages thereof, and constructing a section of fuselage of which at least a part of an edge of the fuselage is of a form identical to an edge of the module, such that the module can be assembled directly with the contiguous fuselage section, whatever the aircraft of the fleets.

Abstract: An antifreeze system for a pipework, the antifreeze system comprising a framework configured to be fixed to the pipework, and at least one thermally insulating sleeve maintained around the pipework by the framework. Each sleeve is configured so that a space is produced between the sleeve and the pipework. The framework has an inlet and an outlet which are configured to produce a fluid communication between the outer side of the antifreeze system and the space. The inlet is fluidly connected to a source of hot air. Such an antifreeze system thus enables a flow of hot air around the pipework which thus prevents the liquid which flows therein from freezing.

Abstract: An aircraft with a landing gear, a compartment to stow the landing gear and doors for the compartment movable between an open position and a closed position. The movement of the doors is controlled by a maneuvering system having two transmission chains or linkages each connecting one of the doors to an actuation member that includes a rotatable arm and an actuating cylinder. Each transmission chain or linkage has a relay element mounted pivotably on a structural element of the aircraft, a first connection element between the arm and the relay element, and a second connection element between the door and the relay element.

Abstract: An aircraft comprising a first door and a second door, each being mobile between an open position and a closed position, and a maneuvering system. The maneuvering system includes an actuation mechanism, a first transmission chain configured to transmit the movements of the actuation mechanism to the first door, a second transmission chain configured to transmit the movements of the actuation mechanism to the second door. Such a maneuvering system uses a single actuation mechanism, which results in a simplification of the mechanism and a weight saving.

Abstract: A cover plate, to cover part of a space between a door and a door surround, comprising at least one pressure element secured to at least part of the external face of the cover plate. The pressure element comprises two sheets, an external sheet and an internal sheet, these two sheets being superposed and fixed together. The internal and external sheets are respectively made from materials that have different thermal expansion properties causing at least a contraction of the internal sheet with respect to the external sheet, at least for a range of temperatures comprised between ?20° C. and ?50° C.

Abstract: A device for concomitant opening or closing of two flaps of a door of an aircraft retractable landing gear. The device comprises a single actuating means for the opening or the closing of the two flaps under the effect of its extension or of its retraction. The actuating means comprises a first end linked to the structure of the aircraft, and a movable part. The device comprises a swinging arm comprising a first end linked by a pivot to the structure, and a second end linked to the movable part of the actuating means by a link having a degree of rotational freedom about an axis parallel to the axis of the pivot. The second end of the swinging arm is furthermore respectively linked to a first tie rod linked to a first of the two flaps, and to a second tie rod linked to a second of the two flaps.

Abstract: An antifreeze system for a pipework, the antifreeze system comprising a framework configured to be fixed to the pipework, and at least one thermally insulating sleeve maintained around the pipework by the framework. Each sleeve is configured so that a space is produced between the sleeve and the pipework. The framework has an inlet and an outlet which are configured to produce a fluid communication between the outer side of the antifreeze system and the space. The inlet is fluidly connected to a source of hot air.

Abstract: An aircraft with a landing gear, a compartment to stow the landing gear and doors for the compartment movable between an open position and a closed position. The movement of the doors is controlled by a maneuvering system having two transmission chains or linkages each connecting one of the doors to an actuation member that includes a rotatable arm and an actuating cylinder. Each transmission chain or linkage has a relay element mounted pivotably on a structural element of the aircraft, a first connection element between the arm and the relay element, and a second connection element between the door and the relay element.

Abstract: An aircraft comprising a first door and a second door, each being mobile between an open position and a closed position, and a maneuvering system. The maneuvering system includes an actuation mechanism, a first transmission chain configured to transmit the movements of the actuation mechanism to the first door, a second transmission chain configured to transmit the movements of the actuation mechanism to the second door. Such a maneuvering system uses a single actuation mechanism, which results in a simplification of the mechanism and a weight saving.

Abstract: A cover plate, to cover part of a space between a door and a door surround, comprising at least one pressure element secured to at least part of the external face of the cover plate. The pressure element comprises two sheets, an external sheet and an internal sheet, these two sheets being superposed and fixed together. The internal and external sheets are respectively made from materials that have different thermal expansion properties causing at least a contraction of the internal sheet with respect to the external sheet, at least for a range of temperatures comprised between ?20° C. and ?50° C.

Abstract: A device for concomitant opening or closing of two flaps of a door of an aircraft retractable landing gear. The device comprises a single actuating means for the opening or the closing of the two flaps under the effect of its extension or of its retraction. The actuating means comprises a first end linked to the structure of the aircraft, and a movable part. The device comprises a swinging arm comprising a first end linked by a pivot to the structure, and a second end linked to the movable part of the actuating means by a link having a degree of rotational freedom about an axis parallel to the axis of the pivot. The second end of the swinging arm is furthermore respectively linked to a first tie rod linked to a first of the two flaps, and to a second tie rod linked to a second of the two flaps.

Abstract: A fastening assembly for the fastening of systems in an aircraft comprising frames, a skin, and clips between the skin and the frames. The fastening assembly includes: ramps, that extend between two consecutive frames of the aircraft; brackets for fastening the ramps to two of the clips situated respectively on two consecutive frames of the aircraft; system supports, fastened to the ramps, each system support being able to receive at least one system.

Abstract: The invention relates to a device for holding an insulating blanket and for fastening systems in an aircraft, comprising a base having two ends from each of which an arm extends. At least one arm has a U-shaped part having two more or less parallel branches, and in that the said device further comprises at least one support for accommodating a system. The invention also relates to an aircraft fuselage section comprising frames, an outer skin, stabilizers and at least one insulating blanket. This section comprises at least one holding device such as described above, mounted so that a frame is situated between the arms of the holding device so that the blanket is between the frame and the holding device.

Abstract: The invention relates to a fastening assembly for the fastening of systems in an aircraft comprising frames (104), a skin (102) and connecting parts between the skin and the frames, referred to as clips (106), comprising: ramps (2), each ramp being adapted for extending between two consecutive frames of the aircraft; for each ramp, means (4) for fastening the ramp allowing fastening of the said ramp to two clips (106) situated respectively on two consecutive frames of the aircraft, system supports (18, 34), fastened or adapted for being fastened to the ramps, each system support being able to receive at least one system.

Abstract: The invention concerns a system for maneuvering an aircraft landing gear mounted in a landing gear box closed by a set of hatches, comprising: a general control unit of the landing gear box to trigger the different maneuvers, a control channel for the hatches (16), a control channel for the landing gear (15), the general control unit, the hatch control channel and the landing gear control channel being controlled by an electric power source, when the aircraft is in normal operating conditions, emergency operating conditions and in maintenance phase. The invention also concerns an aircraft comprising such a system.

Abstract: A system for opening and closing the flap of a casing for the landing gear of an aircraft includes a mechanical connection between the landing gear and the flap. The connection includes a first connecting rod which is fixed to the landing gear, and a second connecting rod which is fixed to the flap, the first and second connecting rods being connected by an articulation mechanism.

Abstract: The invention relates to a device for holding an insulating blanket and for fastening systems in an aircraft, comprising a base having two ends from each of which an arm extends. At least one arm has a U-shaped part having two more or less parallel branches, and in that the said device further comprises at least one support for accommodating a system. The invention also relates to an aircraft fuselage section comprising frames, an outer skin, stabilizers and at least one insulating blanket. This section comprises at least one holding device such as described above, mounted so that a frame is situated between the arms of the holding device so that the blanket is between the frame and the holding device.