A passenger seat system for a cabin of a means of transportation includes: a passenger seat having a seat frame having a holding section and a plurality of supporting elements for coupling to a floor; and, a slide device spaced apart from the holding section and having a base and a retaining device, to be detachably fastened to the base and be coupled to a supporting element. The base has a contact surface for laying onto a cabin seat rail, a locking device for locking the base on the seat rail, and a holding device for releasably holding the retaining device. The slide device is designed to lock the retaining device on the holding device selectively in a first or a second position or to release the retaining device and, when the retaining device is released, to permit motion of the retaining device between the first and the second positions.

A fastening system for fastening fittings to a rail has a supporting element, an opening, and a first radial toothing in an interior space adjoining the opening. The system also has an anchoring element having a second radial toothing. The opening of the supporting element and the first radial toothing are configured in a corresponding manner to the anchoring element such that the anchoring element, in a first rotational position, can be introduced without resistance into the opening and, in a second rotational position, produces an engagement between the first radial toothing and the second radial toothing. At least one form-fitting means is arranged at a first end of the anchoring element and can be introduced into an opening contour of a rail, for producing and releasing a form-fitting connection to an undercut of a rail.

An aircraft monument floor attachment stud may include a body configured to pass through an opening of an aircraft monument, and a head. The body may include a body diameter. The body may be configured to couple to a fitting inserted into a mount point installed within an aircraft cabin floor. The head may include a tool section with a tool section diameter less than the body diameter. The tool section may be configured to receive a predetermined amount of torque from a tool to secure the aircraft monument to the fitting. The head may include a shaped section with an intermediate diameter greater than the tool section diameter and less than the body diameter. The shaped section may include at least one shaped portion with at least one sloped wall, and may be configured to provide a transition between the tool section diameter and the body diameter.

A wall assembly for an interior of an aircraft includes a frame member secured within a cabin of the aircraft having a first side and a second opposing side. The assembly further includes a first decorative panel secured to the frame member on a first side of the frame and a second decorative panel secured to the frame member on a second side of the frame.

A passenger seat includes a seat frame, a plurality of legs extending down from the seat frame where each of the plurality of legs includes an upper end attached to the seat frame and a lower end, and at least one tube attached to the lower end of at least one of the plurality of legs. The at least one tube includes at least two attachments to a floor structure. The at least one tube includes at least one bent portion.

A seat track fitting assembly can include a seat track having a channel sized and shaped to removably, coupleably receive a seat track fitting, which seat track fitting can include a central flange having a lug aperture which is sized and shaped to be coupleable to a payload component, and at least a pair of shear pads, with each one of the shear pads protruding outwardly from opposing sides of the central flange and including a shear flange, and a tensile flange, wherein the tensile flange and the shear flange are integrally formed with the central flange. Related methods are also provided.

Example methods and systems for isolating and alleviating load in an aircraft are described, comprising providing a sliding joint between a seat track and a flight deck floor panel. The sliding joint comprises a lug comprising a first end and a second end opposite the first end, wherein the first end is adapted to attach to the seat track and the second end comprises an elongate aperture, and a clevis comprising an oblate shaped slider bushing that is coupled to the lug.

A system for restraining a cargo container in a cabin of an aircraft is disclosed. The system may include a guide rail, a rail and a plurality of rollers. The guide rail spans a length of a seat track and is releasably coupled to the seat track at one or more locations on a bottom surface of the guide rail. The rail is attached to a surface of the cargo container. The rail engages with the guide rail. The plurality of roller are coupled to the guide rail. The rollers engage a surface of the rail. The rail has two side surfaces that partially enclose two side surfaces of the rollers. When the cargo container deviates from a path defined by the guide rail, one of the side surfaces of the rollers abuts one of the side surfaces of the rail.

A passenger seat system) for a transport means has an elongate carrier structure, to be attached, fixedly with respect to a structure, mutually spaced-apart raster openings on the carrier structure top side, and a seat having a seat frame. The seat frame is displaceable and arrestable on the carrier structure, has a bottom side lying on the carrier structure, a top side holding a seat surface, an arresting device on the bottom side and an operating unit coupled to the arresting device, and movable into an arresting position and an unlocking position. The arresting device has an arresting body, mounted so as to be movable perpendicularly with respect to the carrier structure and pushed by a spring device, by a spring force, into an arresting position, and a locking unit for automatically holding the arresting body in the arresting position when the arresting body reaches the arresting position.

Aircraft, vibration isolation assemblies, and methods of assembling vibration isolation assemblies are provided. An aircraft includes a vibration isolation assembly. The vibration isolation assembly includes a mounting track, a plate, a clamp block, a vibration isolator, and a support fitting. The mounting track defines a cavity and includes flanges that define an opening to the cavity. The plate is configured to be positioned on the flanges outside of the cavity. The clamp block is configured to be fastened to the plate under the flanges of the mounting track within the cavity. The vibration isolator is configured to be laterally constrained by the clamp block within the cavity. The support fitting is configured to be secured to the vibration isolator outside of the cavity.