Systems and methods for removeably adding a cargo bay floor to the interior cargo bay of cargo aircraft bay are disclosed. The system includes a rail disposed in a cargo bay of a cargo aircraft with the rail extending longitudinally along both a length of a forward portion and an aft portion of the fuselage. The system includes a cargo floor segment configured to be removeably attached to the rail. When attached, the cargo floor segment can transform between a first arrangement with the cargo floor segment translatable along the rail, and a second arrangement with the cargo floor segment fixedly secured to a location along the rail. The cargo floor segment is configured to, when secured to the rail, define a section of a floor of the cargo bay of the cargo aircraft. Multiple floor segments can be used together to form a continuous floor for the aircraft.

A mounting rail arrangement for an aircraft floor, floor structure and aircraft having the same. To allow full floor structural decoupling for monuments and/or cabin attendant seats, a mounting rail arrangement includes two mounting rails having mounting holes distributed along their longitudinal direction. A mounting bolt is inserted into the mounting holes and an attachment bolt for fixing a cabin monument and/or a cabin attendant seat is inserted into the mounting bolt. As a result, the cabin monument and/or cabin attendant seat may be installed on at different locations and/or with different orientations using all kinds of configurations enabled by the mounting holes.

A convertiplane is described that comprises a fuselage, having a first longitudinal axis, with a nose and a tail portion; a pair of wings arranged on respective opposite sides of said fuselage, carrying respective rotors; a pair of engines operatively connected to respective said rotors; at least one first lifting surface arranged on said tail portion; and a pair of canards arranged on said nose of said fuselage and defining respective second lifting surfaces adapted to generate a third lift/negative lift value; each rotor comprising a mast rotatable about a second axis and about an relative third axis transversal to said second axis and with respect to the fuselage, so as to set said convertiplane between a helicopter configuration and an aeroplane configuration; each second axis, in use, being transversal to the first axis of said convertiplane in said helicopter configuration and being parallel to said first axis in said aeroplane configuration.

A convertiplane is described that comprises a fuselage, having a first longitudinal axis, with a nose and a tail portion; a pair of wings arranged on respective opposite sides of said fuselage, carrying respective rotors; a pair of engines operatively connected to respective said rotors; at least one first lifting surface arranged on said tail portion; and a pair of canards arranged on said nose of said fuselage and defining respective second lifting surfaces adapted to generate a third lift/negative lift value; each rotor comprising a mast rotatable about a second axis and about an relative third axis transversal to said second axis and with respect to the fuselage, so as to set said convertiplane between a helicopter configuration and an aeroplane configuration; each second axis, in use, being transversal to the first axis of said convertiplane in said helicopter configuration and being parallel to said first axis in said aeroplane configuration.

A convertiplane is described that comprises: a fuselage, having a first longitudinal axis and, in turn, comprising a nose and a tail portion; a pair of wings arranged on respective opposite sides of the fuselage, carrying respective rotors and generating a lift value; and a pair of engines operatively connected to respective rotors; each rotor comprising a mast rotatable about a second axis between a helicopter configuration and an aeroplane configuration; each rotor is interposed between the fuselage and the relative rotor along the direction of extension of the relative wing.

A convertiplane is described that comprises: a fuselage, having a first longitudinal axis and, in turn, comprising a nose and a tail portion; a pair of wings arranged on respective opposite sides of the fuselage, carrying respective rotors and generating a lift value; and a pair of engines operatively connected to respective rotors; each rotor comprising a mast rotatable about a second axis between a helicopter configuration and an aeroplane configuration; each rotor is interposed between the fuselage and the relative rotor along the direction of extension of the relative wing.

A seat track assembly for use in a vehicle. The seat track assembly includes a floor joist including a main body extending in a longitudinal direction, a seat track channel defined in the main body, and at least one support flange extending in a lateral direction from the main body. A raceway is on the at least one support flange, wherein the raceway extends longitudinally along the floor joist, and has an interior sized to receive wiring therein. The seat track assembly also includes a track cover including a top plate. The raceway is positioned between the at least one support flange and the top plate, and the top plate extends past the raceway in the lateral direction.

A rail arrangement for an inner space of an aircraft has a first portion having first rails for receiving passenger seats and having second rails which extend transversely relative to the first rails for receiving fittings. The rails are secured to a floor structure which is arranged in the inner space. The securing of the fittings is consequently decoupled from the floor structure.

Embodiments for commercial freighter configuration for aircraft with composite wings. One embodiment is cargo floor structure for a wing center section of an aircraft. The cargo floor structure includes over wing floor beams extending longitudinally between a rear spar and a front spar of the aircraft. The over wing floor beams are coupled with an upper skin panel of a composite wing. The cargo floor structure also includes intercostals extending spanwise across the over wing floor beams. The intercostals suspended over the upper skin panel of the composite wing. The cargo floor structure also includes a truss box structure disposed between a middle pair of the over wing floor beams and configured to shear a spanwise load from the intercostals into the upper skin panel of the composite wing.

Embodiments for commercial freighter configuration for aircraft with composite wings. One embodiment is cargo floor structure for a wing center section of an aircraft. The cargo floor structure includes over wing floor beams extending longitudinally between a rear spar and a front spar of the aircraft. The over wing floor beams are coupled with an upper skin panel of a composite wing. The cargo floor structure also includes intercostals extending spanwise across the over wing floor beams. The intercostals suspended over the upper skin panel of the composite wing. The cargo floor structure also includes a truss box structure disposed between a middle pair of the over wing floor beams and configured to shear a spanwise load from the intercostals into the upper skin panel of the composite wing.