A display device for displaying an activation status of an emergency chute in an aircraft has an optical display device, an acoustic signal device, a sensor for sensing proximity of a person to the display device, and an electronic unit. The electronic unit is configured to operate the optical display device or the acoustic signal device when the detected proximity of a person is less than a predetermined limit distance. The optical display device, the acoustic signal device, the sensor, and the electronic unit form a compact unit that can be integrated into a door panel of an aircraft door.

Air stair support systems, stair support cable assemblies, and hooks are disclosed herein. A stair support system includes, but is not limited to, an aircraft fuselage, a door seal, a stair door, and a stair support cable assembly. The aircraft fuselage defines a door frame and a stair hook receptacle. The stair door has a retracted position within the door frame and an extended position that forms an entry/exit stairway. The stair support cable assembly includes a cable and two hooks. The first hook includes a curved end portion configured to hook onto the stair hook receptacle, a cable end portion secured to the cable, and an intermediate portion having first and second intermediate legs that extend the intermediate portion away from the door seal when installed on the door frame and the stair door. The second hook is configured to hook on the stair door.

An emergency exit assembly for an aircraft, including a window frame, a window assembly having an outer surface abutting the inner surface of the window frame around its perimeter, and retaining elements spaced around the perimeter of the window assembly. The retaining elements are each connected to the window frame and bias the window assembly toward and against the inner surface of the window frame. Each retaining element has a force-release portion so that the window assembly can be disengaged from the window frame through release of the force-release portion. The force-release portion may be a frangible portion breakable upon application of the pulling force. A cable with one or more handle(s) may be connected to the retaining elements to apply the pulling force. A method of accessing an emergency exit of an aircraft is also discussed.

A latch arrangement for a door includes a plurality of steps disposed at an interior of the door. One of the plurality of steps is rotatable relative to the door between a first position and a second position. The door is movable between a closed position and an open position. A latch is in operable communication with the rotatable step. The latch is engageable with a latch receiver to lock the door in the closed position in response to the rotatable step being in the first position. The latch is disengageable from the latch receiver when the step is in the second position thereby allowing the door to move to the open position.

An aircraft door latch apparatus having a latched configuration and an unlatched configuration can include a door structure of an aircraft door assembly, a handle coupled to the door structure and pivotably moveable with respect to the door structure between a latched position and an unlatched position, the handle including at least a first wall and a handle cavity, and a latch apparatus coupled to the handle. The latch apparatus may be operable to move the handle between the latched position and the unlatched position, the latch apparatus received in the handle cavity and arranged to be concealed by the handle when the aircraft door latch apparatus is in the latched configuration and the unlatched configuration. Related methods are also provided.

Methods and structures are disclosed. An example method includes: rotating a tubular mandrel about a longitudinal axis of the tubular mandrel; depositing a composite material on an inner surface of the tubular mandrel to form a composite tubular member on the inner surface of the tubular mandrel; inserting and expanding an inner expandable mandrel within the composite tubular member to cause the inner expandable mandrel to press the composite tubular member against the inner surface of the tubular mandrel; curing the composite tubular member; removing the inner expandable mandrel; placing a frame within the composite tubular member; and removing the tubular mandrel so as to obtain the composite tubular member with the frame placed therein.

An aircraft-fuselage structure with an external skin and reinforcement structure, supporting the external skin and includes transverse reinforcement elements and longitudinal reinforcement elements. A door opening is in the external skin, between two transverse reinforcement elements and between two longitudinal reinforcement elements, and a door arrangement is installed therein, the door arrangement having a door frame fastened in the door opening and a door panel fastened on the door frame. The door frame and/or the door panel have/has an outer surface directed towards the surroundings and having a curvature differing from curvature of the external skin adjacent to the door opening, and an adapter arrangement is on the outer surface of the door frame and/or of the door panel and, on a side directed towards the surroundings, has at least one surface element which steadily continues the curvature of the external skin adjacent to the door opening.

A door structure and method of assembling same. The door structure includes a door frame delimiting a door opening. The door frame has a latch housing portion defining a latch housing cavity extending along a length of the door frame. A door is mounted to the door frame and displaceable between an open position and a closed position. The door has a peripheral portion with an outer wall and an inner wall delimiting a cavity of the peripheral portion. A door latch assembly has a first latch member fixedly mounted to the door, and a door manipulator mounted to one of the door and the fuselage and coupled to a second latch member within the latch housing cavity of the door frame. The door manipulator is configured to be manipulated to displace the second latch member to engage and disengage the first latch member.

A door system with a deceleration mechanism may be adapted to control an opening of a door module that separates compartments of an aircraft and includes a door panel and a door frame. During the opening of the door module, the door panel performs a rotational movement 389 above a floor structure of the aircraft. The deceleration mechanism is operable in a normal operation mode and a deceleration mode and comprises a hinge, a wedge-shaped component that is rotatably attached to the hinge, and an activation device. The activation device is coupled to the wedge-shaped component and switches the deceleration mechanism from operating in the normal operation mode to operating in the deceleration mode when a difference in pressure between the compartments exceeds a predetermined threshold.

A mobile machine includes a fuselage having at least one door, inside which is located a unit for processing measurements taken by at least one measurement device installed outside said fuselage. The system for communication between the processing unit and the measurement device includes a flex circuit that is affixed at least partially flat in the door corner between the door and the rim of the opening formed in the fuselage with which the door is associated and one of the ends, the internal end, of which is located inside the fuselage and the other, external, end of which is located outside. Since the flex circuit makes it possible to pass through the wall of the fuselage via the opening for doors, the need to make substantial modifications to the aircraft is avoided.