Abstract: A forward secondary structure for a mounting pylon for a turbomachine, the forward secondary structure extending from upstream to downstream along a longitudinal axis and having a chassis clad with an aerodynamic fairing. The aerodynamic fairing includes two adjacent cowls each having an upstream portion, where each of the cowls extends lengthwise along the longitudinal direction and includes in its upstream portion a system for articulating the cowl to the chassis, by which system the cowl can pivot with respect to the chassis about an axis of rotation normal to the longitudinal axis, between a closed position in which all of an inner face of the cowl is pressed against the chassis and an open position in which the cowl frees up an opening in the forward secondary structure.

Abstract: A forward secondary structure for a mounting pylon for a turbomachine, the forward secondary structure extending from upstream to downstream along a longitudinal axis and having a chassis clad with an aerodynamic fairing. The aerodynamic fairing includes two adjacent cowls each having an upstream portion, where each of the cowls extends lengthwise along the longitudinal direction and includes in its upstream portion a system for articulating the cowl to the chassis, by which system the cowl can pivot with respect to the chassis about an axis of rotation normal to the longitudinal axis, between a closed position in which all of an inner face of the cowl is pressed against the chassis and an open position in which the cowl frees up an opening in the forward secondary structure.

Abstract: A connection device of a female pipe and a male pipe, with a head which is configured to be accommodated in a receptacle of the female pipe, and comprising a peripheral groove in which a seal is accommodated. The male pipe comprises at least one extension which is configured to limit the pivoting of the male pipe around an axis of rotation which is perpendicular to the longitudinal axis of the female pipe. This configuration makes it possible to limit the risks of damaging the seal.

Abstract: An assembly including a first pipe length and a second accommodating mechanical pipe length, said first length being assembled in said second length by means of an interface joint, that is a conductor of electric current. As it is assumed that said first length and said second length are also conductors of electric current, the joint thus provides good sealing between the first pipe length and the second pipe length in order to prevent leakages of fluid and to prevent the formation of inopportune electric arcs due, for example, to static electricity.

Abstract: A connector for securing floating double skin pipework to a structure includes mechanism for securing to the structure, and an external body forming an outer channel and an internal tube forming an inner channel around the longitudinal axis of the connector. The mechanism for securing to the structure includes a fixed connection backed up by a sliding connection along the longitudinal axis of the connector. The connector includes at least one bore for producing the fixed connection and at least one holding rail for producing the sliding connection.

Abstract: In an aircraft duct formed with pipes connected in pairs via connectors in which the pipes are mounted with the possibility of axial displacement, there exists a risk that a pipe of the duct, with a dimension greater that the dimension of the nominal pipe, is mounted instead and in place of the latter. In this case, the wrongly mounted pipe would risk not having sufficient clearance in axial translation. In order to solve this problem, it is disclosed to equip one of the relevant connectors with an obstacle limiting the travel of the nominal pipe and preventing the mounting of a pipe with a greater dimension belonging to the duct. A method for assembling an aircraft portion is also proposed, in order to benefit from the particularities of the duct.

Abstract: A fastening device (10) is disclosed for attaching a fluid transport circuit to an element of a structure of an aircraft, with the fluid transport circuit containing two portions (23, 42), each of which is made up of an external tube (22, 44) positioned around an internal tube (21, 43). The fastening device (10) is positioned at a connection (40) between the two portions (23, 42) of the fluid transport circuit, and contains a body (26) with a plate (27) to attach the fastening device (10) to an element (61) of the structure of the aircraft. The body (26) provides at least one sealed connection between the external tubes (22, 44) of the two portions (23, 42) and a support system provides a constant radial clearance between the internal tubes (21, 43) and the external tubes (22, 44) of the two portions (23, 42) of the fluid transport circuit.

Abstract: A device to attach an aircraft's piping that includes a clamping ring made up of two jaws shaped into a gliding arc breaker separator and including at least one transverse support cut-out for at least one tube.

Abstract: In an aircraft duct formed with pipes connected in pairs via connectors in which the pipes are mounted with the possibility of axial displacement, there exists a risk that a pipe of the duct, with a dimension greater that the dimension of the nominal pipe, is mounted instead and in place of the latter. In this case, the wrongly mounted pipe would risk not having sufficient clearance in axial translation. In order to solve this problem, it is disclosed to equip one of the relevant connectors with an obstacle limiting the travel of the nominal pipe and preventing the mounting of a pipe with a greater dimension belonging to the duct. A method for assembling an aircraft portion is also proposed, in order to benefit from the particularities of the duct.

Abstract: A connection device of a female pipe and a male pipe, with a head which is configured to be accommodated in a receptacle of the female pipe, and comprising a peripheral groove in which a seal is accommodated. The male pipe comprises at least one extension which is configured to limit the pivoting of the male pipe around an axis of rotation which is perpendicular to the longitudinal axis of the female pipe. This configuration makes it possible to limit the risks of damaging the seal.

Abstract: A coupling device for piping including a duct; a coupling with a hermetic longitudinal sliding connection with an extremity of the duct along a total distance parallel to a longitudinal axis of the duct; a device to stop the translational movement of a first extremity of the duct in the coupling for a travel distance less than the total distance. The device being withdrawable for a defined compression condition of the duct.

Abstract: The invention relates to an assembly including a first pipe length (1) and a second accommodating mechanical pipe length (2), said first length (1) being assembled in said second length (2) by means of an interface joint (4), conductor of electric current. As it is assumed that said first length (1) and said second length (2) are also conductors of electric current, the joint (4) thus provides good sealing between the first pipe length (1) and the second pipe length (2) in order to prevent leakages of fluid and to prevent the formation of inopportune electric arcs due, for example, to static electricity.

Abstract: A device for protecting piping from lightning. The piping includes tubular metal sections connected to each other by connection parts, a first portion of the connection parts being plastic material parts and a second portion of the connection parts being metal parts.

Abstract: The aircraft includes: a fuel tank panel; a fuel pump bell, the bell being fastened to the panel; and a metal support arranged so that the bell is fastened to the panel entirely via the support.

Abstract: A connector for securing floating double skin pipework to a structure includes means for securing to the structure, and an external body forming an outer channel and an internal tube forming an inner channel around the longitudinal axis of the connector. The means for securing to the structure includes a fixed connection backed up by a sliding connection along the longitudinal axis of the connector. The connector includes at least one bore for producing the fixed connection and at least one holding rail for producing the sliding connection.

Abstract: The aircraft comprises: a fuel valve; an actuator for controlling the valve; and a tank panel extending between the valve and the actuator. It is arranged in such a manner that the bearing point(s) between the panel and a first one of the members selected from the valve and the actuator, and preferably the actuator, is/are provided by means of the second one of these members.

Abstract: A fuel piping connection device for aircraft includes a male end fitting and a female end fitting that are configured to engage one another. The male and female end fittings are made of a resistive material that is an insulating material loaded with conducting fibers. Each of the male and female end fittings is configured to be bonded to a radial outer wall at an extremity of a respective tube in the fuel piping or to a radial outer wall at an extremity of a respective piping connector. Each of the male and female end fittings includes an inwardly projecting shoulder configured to engage with an axial end surface of the respective tube in the fuel piping or with an axial end surface of the respective piping connector.

Abstract: The invention relates to a coupling device for a duct (201) in piping, comprising: a duct (201); a coupling (231) comprising means (255) for realizing a hermetic longitudinal sliding connection with an extremity of the duct (201) along a total distance d parallel to the axis (210), referred to as longitudinal, of said duct (201); means (265) of stopping the translational movement of the first extremity of the duct (201) in the coupling (231) for a travel d1 less than d. The translational movement stopper means (265) are withdrawable for defined compression conditions of the duct.

Abstract: A device for connecting aircraft fuel piping that includes male/female end fittings made of highly resistive material, designed to be bonded at the extremities of tubes in the piping and/or of piping connectors.

Abstract: A device to attach an aircraft's piping that includes a clamping ring made up of two jaws shaped into a gliding arc breaker separator and including at least one transverse support cut-out for at least one tube.