Abstract: An aircraft that includes a floor, a tank and a connection between the tank to the floor. The connection include guide rails fixed to the floor, a cradle with guide grooves cooperating with the guide rails, two rear links articulated between the cradle and the tank, two front links fixed to the cradle and articulated on the tank, a lateral link articulated between the cradle and a lower part of the tank, and two intermediate links articulated between the cradle and the tank.

Abstract: A pressurization bulkhead for an aircraft includes a membrane having a plane main surface and an articulation for connecting the membrane to the fuselage of the aircraft. The articulation is a pivot. A flexible liner is rigidly attached to the articulation and extends between the membrane and the articulation. The membrane has a circular contour.

Abstract: An assembly for reinforcing a fuselage of an aircraft, the aircraft including a fuselage including an opening and a removable panel received in the opening. The assembly including a first support fixed to an exterior face of the fuselage around and outside an opening in the fixed fuselage. A sub-assembly is to an exterior face of the removable panel and housed inside the first support. The first support is fixed to the fuselage. The sub-assembly is fixed to the removable panel.

Abstract: An assembly for reinforcing a fuselage of an aircraft, the aircraft including a fuselage including an opening and a removable panel received in the opening. The assembly including a first support fixed to an exterior face of the fuselage around and outside an opening in the fixed fuselage. A sub-assembly is to an exterior face of the removable panel and housed inside the first support. The first support is fixed to the fuselage. The sub-assembly is fixed to the removable panel.

Abstract: An aircraft comprising a structure, a tank housed in the fuselage, and fastening means which comprise a front fastening system, a rear fastening system and a lateral fastening system. The front system comprises a front plate, two lateral connecting rods and a central connecting rod that are fastened between the front plate and the tank. The rear system comprises a rear plate and a rear connecting rod fastened between the rear plate and the tank. The lateral system comprises a lateral connecting rod fastened between the structure and the tank, wherein one of the connection points is behind the other connection point.

Abstract: A fastening system for an aircraft to fasten at least one tank to contain liquid hydrogen, allowing easy access to the tank. The fastening system includes a longitudinal box, upper formers fastened to the upper end of the longitudinal box and lower formers fastened to the lower end of the longitudinal box, at least two upper formers including two fastening devices to each connect a fastening point of the tank to an upper former, at least one lower former including two second fastening devices to each connect a second fastening point of the tank to the lower former. The fastening system allows an operator to access the tanks that are capable of being fastened by the fastening system.

Abstract: An aircraft including a fuselage including an opening and beams that are aligned and that are interrupted at the edges of the opening, a removable panel where for each pair of aligned beams of the fuselage interrupted at the opening a beam of the removable panel extends between the two beams of the pair and each end of the beam of the removable panel faces an end of a beam of the pair and at the end of at least one beam of the fuselage facing an end of a beam of the removable panel, fixing means providing a removable fixing between the ends.

Abstract: A fastening system for an aircraft configured to fasten at least one tank intended to contain liquid hydrogen includes a longitudinal box, an upper structure fastened to an upper side of the longitudinal box, a lower structure fastened to a lower side of the longitudinal box and at least two fastening frames including, on either side of the vertical plane of symmetry (P1), a fastening device for connecting a tank to the upper structure. The fastening system further includes at least two fastening devices for connecting a fastening point of the tank to the longitudinal box and at least two fastening devices for connecting a fastening point of the tank to the lower structure. The fastening system makes it possible to securely fasten at least one hydrogen tank on board an aircraft (AC).

Abstract: An access door assembly for a fuselage having a structure delimiting an access hatch, an upper part and a lower part of an access door, hinges fastened between the structure and the upper part in the vicinity of an upper edge, a guiding system between the lower part and the structure and guiding the lower part in translation, upper locks between the upper part and the lower part and/or the structure and lower locks between the lower part and the structure.

Abstract: A fastening system for an aircraft to fasten at least one tank to contain liquid hydrogen, allowing easy access to the tank. The fastening system includes a longitudinal box, upper formers fastened to the upper end of the longitudinal box and lower formers fastened to the lower end of the longitudinal box, at least two upper formers including two fastening devices to each connect a fastening point of the tank to an upper former, at least one lower former including two second fastening devices to each connect a second fastening point of the tank to the lower former. The fastening system allows an operator to access the tanks that are capable of being fastened by the fastening system.

Abstract: An aircraft comprising a structure, a tank housed in the fuselage, and fastening means which comprise a front fastening system, a rear fastening system and a lateral fastening system. The front system comprises a front plate, two lateral connecting rods and a central connecting rod that are fastened between the front plate and the tank. The rear system comprises a rear plate and a rear connecting rod fastened between the rear plate and the tank. The lateral system comprises a lateral connecting rod fastened between the structure and the tank, wherein one of the connection points is behind the other connection point.

Abstract: An aircraft including a fuselage including an opening and beams that are aligned and that are interrupted at the edges of the opening, a removable panel where for each pair of aligned beams of the fuselage interrupted at the opening a beam of the removable panel extends between the two beams of the pair and each end of the beam of the removable panel faces an end of a beam of the pair and at the end of at least one beam of the fuselage facing an end of a beam of the removable panel, fixing means providing a removable fixing between the ends.

Abstract: A fastening system for an aircraft configured to fasten at least one tank intended to contain liquid hydrogen includes a longitudinal box, an upper structure fastened to an upper side of the longitudinal box, a lower structure fastened to a lower side of the longitudinal box and at least two fastening frames including, on either side of the vertical plane of symmetry (P1), a fastening device for connecting a tank to the upper structure. The fastening system further includes at least two fastening devices for connecting a fastening point of the tank to the longitudinal box and at least two fastening devices for connecting a fastening point of the tank to the lower structure. The fastening system makes it possible to securely fasten at least one hydrogen tank on board an aircraft (AC).

Abstract: An aircraft engine attachment including a beam fixed to a pylon and including a yoke with two walls, and a connecting rod with an articulation housed in the yoke, in which the connecting rod has a front flank and a rear flank which are facing inner faces of the walls. For each wall, a wearing part is disposed against the inner face of the wall and between the wall and the corresponding flank of the connecting rod. A Fixing arrangement ensures the fixing of the wearing part to the wall. Thus, the wearing parts prevent an excessive tilting of the connecting rod and the wearing of the connecting rod or of the yoke.

Abstract: A front engine attachment system for an engine of an aircraft, the front engine attachment system having an engine pylon having, in its front part, a frontal part having an attachment wall with a front face, and a front engine attachment having a beam, which is fastened to the front face and to which a link rod is fastened on either side of a median plane. Each link rod is fastened to the beam in an articulated manner by at least one first connection point and is configured to be fastened to the engine in an articulated manner by at least one second connection point. The beam is made up of front, intermediate and rear plates. The rear plate is pressed against the front face. The front plate is disposed in front of the rear plate. The intermediate plate is disposed between the front plate and the rear plate.

Abstract: A rear engine attachment having a beam fixed to a pylon, a spreader pivotally mounted on the beam, the spreader comprising two ends situated on either side of a median plane, two rods located one on either side of the median plane, each rod having a first end fixed to one end of the spreader by a ball joint and a second end fixed to the engine, each ball joint comprising a clevis with two arms at the first end of the rod, a swivel bearing arranged on the end of the spreader, and a hinge pin passing through the two arms, the swivel bearing arranged between the two arms and fitted on the hinge pin. For each ball joint, an interface part is removably interposed between the end of the spreader and the first end of the rod and forms a contact surface between the spreader and the rod.

Abstract: An aircraft propulsive assembly comprising a pylon and a turbomachine attached to the pylon by an engine attachment system. The attachment system comprises two engine attachments each secured to the pylon and to the turbomachine. Each engine attachment comprises at least one fitting attached to the pylon by a first main link, and attached to the turbomachine by a second main link. Each main link has a clearance-free fit. The fitting being, moreover, secured to either the pylon or the turbomachine by an additional link, referred to as a safety link, which backs up one of the main links. The safety link is in the form of an assembly with a clearance. The assembly of the safety link comprises at least one passage which receives, in a sliding manner, a tool for checking a presence of the clearance.

Abstract: A linking device connecting an aircraft engine and a primary structure of an aircraft pylon, comprising a support connected to the primary structure, a spreader, extending between first and second ends that has a central part connected to the support by a principal link comprising a principal rotation axis, at least one system for limiting the deflection of the spreader comprising an extension secured to the spreader and also upper and lower stops, secured to a fitting secured to the support, between which the extension is positioned.

Abstract: An aircraft engine attachment including a beam fixed to a pylon and including a yoke with two walls, and a connecting rod with an articulation housed in the yoke, in which the connecting rod has a front flank and a rear flank which are facing inner faces of the walls. For each wall, a wearing part is disposed against the inner face of the wall and between the wall and the corresponding flank of the connecting rod. A Fixing arrangement ensures the fixing of the wearing part to the wall. Thus, the wearing parts prevent an excessive tilting of the connecting rod and the wearing of the connecting rod or of the yoke.

Abstract: A front engine attachment system for an engine of an aircraft, the front engine attachment system having an engine pylon having, in its front part, a frontal part having an attachment wall with a front face, and a front engine attachment having a beam, which is fastened to the front face and to which a link rod is fastened on either side of a median plane. Each link rod is fastened to the beam in an articulated manner by at least one first connection point and is configured to be fastened to the engine in an articulated manner by at least one second connection point. The beam is made up of front, intermediate and rear plates. The rear plate is pressed against the front face. The front plate is disposed in front of the rear plate. The intermediate plate is disposed between the front plate and the rear plate.