A tie-down for attachment to an aft tail section of an aircraft for inhibiting damage to the aircraft when the aircraft is on the ground is disclosed. The tie-down has a mount member configured to attach to the aft tail section and a projection member supported by the mount member. The projection member extends in a generally downward direction from the mount member so as to provide a contact surface with the ground that is lower than the aft tail section.

A fabric barrier for an aircraft compartmental barrier includes a fabric barrier portion and a flexible crosspiece, wherein at least part of one edge of the fabric barrier portion terminates at the flexible crosspiece, wherein the flexible crosspiece is adapted to fit into and be retained within a partially covered groove, wherein the partially covered groove includes a pair of opposing flange portions covering a groove whereby a central longitudinal portion of the groove remains uncovered, wherein the flexible crosspiece is adapted to be released from the partially covered groove by passing between the pair of opposing flange portions during a decompression event. A decompression system for an aircraft compartmental barrier includes said fabric barrier, and a method for isolating two internal volumes within an aircraft using said decompression system.

A fabric barrier for an aircraft compartmental barrier includes a fabric barrier portion and a flexible crosspiece, wherein at least part of one edge of the fabric barrier portion terminates at the flexible crosspiece, wherein the flexible crosspiece is adapted to fit into and be retained within a partially covered groove, wherein the partially covered groove includes a pair of opposing flange portions covering a groove whereby a central longitudinal portion of the groove remains uncovered, wherein the flexible crosspiece is adapted to be released from the partially covered groove by passing between the pair of opposing flange portions during a decompression event. A decompression system for an aircraft compartmental barrier includes said fabric barrier, and a method for isolating two internal volumes within an aircraft using said decompression system.

A partition wall arrangement for a cabin of a passenger aircraft includes a partition wall, a seat arrangement secured to the partition wall in an assembled state and containing a carrier structure, and at least one cabin attendant seat. The carrier structure contains a mechanically load-bearing wall structure for the partition wall, a mechanically load-bearing seat structure for the seat arrangement, and at least one fastening device in order to secure the wall structure and the seat structure to each other in the assembled state. In a method for producing the carrier structure or the partition wall arrangement, the wall structure or at least a main component thereof is produced as a milled component by milling out a solid material plate. In a design method, the entire carrier structure is subjected in the assembled state to a load path optimization.

A partition wall arrangement for a cabin of a passenger aircraft includes a partition wall, a seat arrangement secured to the partition wall in an assembled state and containing a carrier structure, and at least one cabin attendant seat. The carrier structure contains a mechanically load-bearing wall structure for the partition wall, a mechanically load-bearing seat structure for the seat arrangement, and at least one fastening device in order to secure the wall structure and the seat structure to each other in the assembled state. In a method for producing the carrier structure or the partition wall arrangement, the wall structure or at least a main component thereof is produced as a milled component by milling out a solid material plate. In a design method, the entire carrier structure is subjected in the assembled state to a load path optimization.

Embodiments for aircraft keel beam assembly. One embodiment is a keel beam assembly of an aircraft. The keel beam assembly includes a keel attach chord to connect to a wing center section of the aircraft, the keel attach chord extending in a longitudinal direction between a rear spar and front spar of the aircraft. The keel beam assembly also includes a lower chord disposed underneath the keel attach chord and extending in the longitudinal direction between an aft wheel well bulkhead and a forward bulkhead of the aircraft. The keel beam assembly further includes a forward web to couple the keel attach chord and the lower chord, the forward web including a front edge extending in a diagonal direction from the keel attach chord that is downward and aft toward the lower chord to create an open area forward from the front edge.

Embodiments for aircraft keel beam assembly. One embodiment is a keel beam assembly of an aircraft. The keel beam assembly includes a keel attach chord to connect to a wing center section of the aircraft, the keel attach chord extending in a longitudinal direction between a rear spar and front spar of the aircraft. The keel beam assembly also includes a lower chord disposed underneath the keel attach chord and extending in the longitudinal direction between an aft wheel well bulkhead and a forward bulkhead of the aircraft. The keel beam assembly further includes a forward web to couple the keel attach chord and the lower chord, the forward web including a front edge extending in a diagonal direction from the keel attach chord that is downward and aft toward the lower chord to create an open area forward from the front edge.

Several embodiments of buffer zones are provided that are contemplated to be disposed with respect to two or more adjacent elements on an aircraft. The buffer zones adjust for dynamic spacing between the elements to help control different gapping requirements between the elements installed in the aircraft. Embodiments include an aircraft interior panel configuration, an aircraft interior wall panel configuration, an adjustable width aircraft bulkhead, and an aircraft personal service unit.

Several embodiments of buffer zones are provided that are contemplated to be disposed with respect to two or more adjacent elements on an aircraft. The buffer zones adjust for dynamic spacing between the elements to help control different gapping requirements between the elements installed in the aircraft. Embodiments include an aircraft interior panel configuration, an aircraft interior wall panel configuration, an adjustable width aircraft bulkhead, and an aircraft personal service unit.

An aircraft including two main landing gears and also a main landing gear bay configured to house, on either side of a vertical median plane, the two main landing gears in a retracted position, the main landing gear bay including a rear transverse wall, a front transverse wall and also an end wall that is approximately perpendicular to the rear and front transverse walls. The main landing gear bay includes at least one strut connecting the rear or front transverse wall and the end wall, approximately positioned in the vertical median plane.