An interior space for an aircraft includes a cockpit, a cockpit wall separating the cockpit from the remaining interior space, a cabin door arranged directly behind the cockpit wall for accessing the interior space of the aircraft from outside the fuselage, a modular installation space for installation equipment, a plurality of seat rows, a longitudinal aisle extending along the interior space through the seat rows to separate adjacent groups of seats from each other, and an access path for the cabin door. The access path extends from the cabin door to the longitudinal aisle to create an intersection region between the access path and the longitudinal aisle. The modular installation space is arranged directly forward of the seat rows. The access path extends at an angle of at least 100° to the longitudinal aisle in a forward direction.

A gas distribution assembly for providing gas to an actuator for opening an aircraft door and to an aircraft evacuation slide, the assembly comprising a single common gas supply and valve means for controlling distribution of gas from the common supply between the slide and the door actuator based on door opening position.

Arrangements for an aircraft passenger cabin including a seating area containing first and second passenger seats, a monument disposed at one end of the seating area, and at least one privacy divider deployable in a longitudinal direction of the seating area to divide at least a portion of the seating area for privacy. In some embodiments, the at least one privacy divider includes a first privacy divider adapted to deploy to divide the seating area forward of the first and second passenger seats and a second privacy divider deployable to the seating area between the first and second passenger seats.

A device for emergency opening of an aircraft door having: a tubular actuating member (7) which includes a first end plate (8) and a second end plate (9); an elastic compression device having a tubular spring (10) compressed between the first end plate (8) and the second end plate (9); an expansion regulator (17, 18) arranged inside the tubular spring (10); a retaining member which includes at least one peripheral attachment connecting the first end plate (8) to the second end plate (9), the peripheral attachment being radially outside the tubular spring (10).

A negator spring tool for winding a negator spring output drum around a rotational axis includes: a pair of tool handles; and a tool disk having an outer edge which is generally circular except for a cutout. The tool disk is configured to be releasably attached to the output drum. The tool disk has a drum-facing side which includes protruding teeth protruding from the drum-facing side to engage radial spokes of the output drum. The outer edge of the tool disk includes handle slots which are spaced circumferentially. The distal end of each tool handle is insertable into a handle slot to rotate the tool disk around the rotational axis. The protruding teeth of the tool disk each having a T-shaped cross section, each T-shaped protruding tooth and the drum-facing side forming an I-shaped cross section having two opposite facing cavities on two opposite sides of the I-shaped cross section.

An aircraft pressurized cabin door (1) having a fuselage panel (2) and a door structure (3) that includes: two circumferential beams (4) arranged on the lateral edges of the door (1); a plurality of longitudinal beams (5). Each longitudinal beam (5) is an open profile having an outer face to which the fuselage panel (2) is fixed and an inner face, the door structure (3) further including an internal force-absorbing frame (12) fixed to the inner face of each longitudinal beam (5), this internal force-absorbing frame (12) having a plurality of uprights (13) each extending opposite a circumferential beam (4), each upright (13) being fixed to several longitudinal beams (5).

Double-curved aircraft door having a pair of stops in contact over a contact area. The isobarycentre (31A) of each contact area of a first lateral edge is substantially arranged in a first plane perpendicular to the longitudinal axis (21) and the same applies to a second lateral edge. For each contact area, the normal to the contact area passing through its isobarycentre (31A, 31B) substantially passes through the axis (41) of a medium cylinder (42). For each contact area, the normal to the contact area passing through its isobarycentre (31A, 31B) forms a deflection angle with a plane perpendicular to the longitudinal axis (21), the deflection angles of all the contact areas being equal.

A coaxial pressure lock assembly of an aircraft door, the coaxial pressure lock assembly comprises a pressure panel positioned adjacent an opening formed in the aircraft door such that the pressure panel is seated in the opening when the pressure panel is in a closed position, and a latch shaft extending through a clevis of the pressure panel. The latch shaft is configured to rotate about a latch shaft rotational axis extending through the latch shaft. The pressure panel is rotatable between the closed position and an open position about the latch shaft rotational axis. The latch shaft is a portion of a latch assembly configured to allow or prevent unlatching the aircraft door.

A saloon-type door assembly that includes left and right door assemblies that each include a frame adapter having a curved inner surface with a first apex, a front portion and a rear portion, a door adapter that includes a curved outer surface with a second apex a front portion and a rear portion, a door panel associated with the door adapter, at least one front hinge strip secured along a front hinge strip path, and at least one rear hinge strip that is secured along a rear hinge strip path. The front hinge strip path extends from the front portion of the curved outer surface of the door adapter to the rear portion of the curved inner surface of the frame adapter. The rear hinge strip path extends from the rear portion of the curved outer surface of the door adapter to the front portion of the curved inner surface of the frame adapter. The door panels are movable between a front open position, a closed position and a rear open position.

Method for manufacturing an aircraft door having a monolithic structure, including the following steps: producing a forged blank; die-cutting the forged blank between a substantially smooth lower die and an upper die defining cells, and producing a die-cut part with a cellular structure having an open face and a face closed by a wall; machining the internal walls of the cellular structure to define at least one recess delimited by a web connecting the closed face and the open face and by a base projecting substantially perpendicular to the web, on the open face of the die-cut part.