A flexible strengthening joint for a pressurized vessel includes an outer skin having a localized abrupt change in shape. The outer skin includes a first skin section and a second skin section, the localized abrupt change in shape being located at a junction between the first skin section and the second skin section. A reinforcing bulkhead is located in the interior of the pressurized vessel. The reinforcing bulkhead includes a first bulkhead section that is directly attached to the first section of the outer skin and a second bulkhead section that unattached directly to the first section. A kick frame is located in the interior, the kick frame spanning at least the second bulkhead section. At least one intercostal is secured to the second bulkhead section. The at least one intercostal is also secured to the kick frame.

A fire seal end cap including a cap portion and a plug portion, wherein the plug portion protrudes from the cap portion, and wherein the cap portion and the plug portion are formed from a fire-resistant material.

A fire seal end cap including a cap portion and a plug portion, wherein the plug portion protrudes from the cap portion, and wherein the cap portion and the plug portion are formed from a fire-resistant material.

A barrier for providing isolation between two internal volumes within an aircraft, comprises: a wall section adapted for location within an aircraft, the wall section having an aperture formed therein; mounting means located on the wall section proximate the aperture; and a substantially planar burst panel member having first and second opposingly-facing sides, the burst panel member adapted for location within the mounting means and dimensioned so as to overlie the aperture when received by the mounting means; the burst panel member comprising a line of weakness provided therein, adapted such that, in use, exposure of the burst panel member to an atmospheric pressure differential between air volumes respectively adjacent the first and second sides exceeding a predetermined value causes the burst panel member to rupture along said line of weakness.

A barrier for providing isolation between two internal volumes within an aircraft, comprises: a wall section adapted for location within an aircraft, the wall section having an aperture formed therein; mounting means located on the wall section proximate the aperture; and a substantially planar burst panel member having first and second opposingly-facing sides, the burst panel member adapted for location within the mounting means and dimensioned so as to overlie the aperture when received by the mounting means; the burst panel member comprising a line of weakness provided therein, adapted such that, in use, exposure of the burst panel member to an atmospheric pressure differential between air volumes respectively adjacent the first and second sides exceeding a predetermined value causes the burst panel member to rupture along said line of weakness.

A lavatory for an aircraft cabin includes a wall having a forward wall portion disposed immediately aft of and substantially conforming to an exterior aft surface of an aircraft cabin structure, such as a passenger seat, that is substantially not flat in a vertical plane. The forward wall portion includes a forward projection over an aft portion of the adjacent passenger seat. The forward wall portion can define a secondary space in the interior lavatory space, which can provide an amenity stowage space, and can include design elements providing visual space.

A lavatory for an aircraft cabin includes a wall having a forward wall portion disposed immediately aft of and substantially conforming to an exterior aft surface of an aircraft cabin structure, such as a passenger seat, that is substantially not flat in a vertical plane. The forward wall portion includes a forward projection over an aft portion of the adjacent passenger seat. The forward wall portion can define a secondary space in the interior lavatory space, which can provide an amenity stowage space, and can include design elements providing visual space.

A panel structure for a vehicle, and especially for an aircraft or spacecraft, includes an area member, especially a skin member, that defines an areal expanse with a first surface and an opposite second surface and having a thickness between the first and second surfaces; and a plurality of elongate stiffener members which are attached to the area member and extend over at least one of the first and second surfaces; wherein at least one of the stiffener members is bifurcated at a bifurcation point into two or more branch stiffener members.

A panel structure for a vehicle, and especially for an aircraft or spacecraft, includes an area member, especially a skin member, that defines an areal expanse with a first surface and an opposite second surface and having a thickness between the first and second surfaces; and a plurality of elongate stiffener members which are attached to the area member and extend over at least one of the first and second surfaces; wherein at least one of the stiffener members is bifurcated at a bifurcation point into two or more branch stiffener members.

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.