A control and information system is for a lavatory of an aircraft, where the lavatory has a door. The system contains a door actuator for opening and closing, a lock actuator for locking and unlocking the door, a control device for controlling the door actuator and the lock actuator, a human-machine interface for actuating the door by a user, as well as a communication interface for exchanging information between an authorized entity and the control device. The lavatory contains a wall structure supporting the door, and the control and information system. A user controls the door via the human-machine interface. Information about the communication interface is exchanged between the control device and the authorized entity.

A system for monitoring a pressure change within at least one compartment of an aircraft and operating a pyrotechnic device associated with a door latch, includes a securing mechanism arranged in an aircraft door that includes a pyrotechnic actuator and a latch bolt. The system includes the pyrotechnic actuator configured to move the latch bolt when the pyrotechnic actuator is actuated. The system also includes a pressure sensor configured to provide a pressure signal. The system also includes a controller configured to determine a pressure drop representing a decompression event. The system also includes an output driver configured to generate an output signal to actuate the pyrotechnic actuator when the controller determines the occurrence of a decompression event.

A hinge assembly 8a for an aircraft component including first and second hinge plates 9, 10, having an aerodynamic surface. A first seal assembly 28 to 32 is provided and arranged to seal between the aerodynamic surfaces of the hinge plates. A second seal assembly 38 to 42 is arranged to seal between the undersides of the hinge plates in order to reduce pressure leakage between voids under the hinge. The provision of two seal assemblies, each having a dedicated function, addresses the competing demands made on the sealing arrangement of an aircraft hinge assembly in use.

A hinge assembly for receiving a door includes: a wall including a wall body defining an inner surface, and an outer surface that is opposed to the inner surface, and a wall panel extending from one of the inner surface and the outer surface and defining part of a perimeter of an opening closable by the door; a pivot connected to the wall panel and defining a pivot axis intersecting the wall panel; and a hinge arm having a portion engaged to the pivot and extending away from the wall panel.

A hinge assembly for a swinging door includes a shifting pivot point movable between a first concealed positioned and a second extended position to provide clearance for protruding trim pieces and the like upon opening the swinging door. A double action spring mechanism energizes to drive the shifting pivot point between the first and second positions. An assembly including a link arm and a bell crank is driven by the double action spring mechanism to shift the shifting pivot point and locking mechanisms are provided to lock each of the link arm and the bell crank in their respective extended positions. A compartment assembly includes a swinging door, a fixed structure to which the swinging door is movably coupled, at least one hinge assembly according to the present disclosure.

A bifold door includes a first hinge and a second hinge configured to rotatably couple the bifold door to a doorframe. The bifold door includes a slider configured to slide within a track of the doorframe as the bifold door is opened and closed. At least one of the first hinge, the second hinge, and the slider includes a spherical bearing and a pin.

In order to simplify the kinematics involved in opening an aircraft door, a plurality of mobile stop members is provided at the periphery of the door, these being intended to press against complementary stop arrangement provided on the door frame. A door control device is configured to bring the door from its closed position into a set-back intermediate position by moving it towards the interior of the compartment, and a stop arrangement control device is configured to allow the mobile stop members to be moved, when the door is occupying its set-back intermediate position, from a deployed locking position to a retracted unlocking position, allowing the door to be moved outward through the opening in the fuselage.

An aircraft door, an aircraft region and an aircraft with an aircraft door. The aircraft door through which passengers enter and leave the aircraft and is held towards the outer side by stops and is locked exclusively on a hinge side opposite the stops. Also, an aircraft region and an aircraft with such an aircraft door.

Cabinets, methods for making cabinets, and aircraft including cabinets are provided. In one example, a cabinet includes a cabinet body that at least partially surrounds a cabinet space and that defines a cabinet opening that allows access to the cabinet space. A cabinet door at least partially covers the cabinet opening when in a closed position and extends upward from a lower edge portion to an upper edge portion. The cabinet door has an outer exposed surface facing generally in a first direction away from the cabinet space when in the closed position. The cabinet door is operatively coupled to the cabinet body for opening from the closed position to an open position including the lower edge portion moving generally upward and the upper edge portion moving generally upward and towards the first direction to expose the cabinet opening.

A gatebox system for delivering fire retardant fluid from a firefighting aircraft. A first and second gate opening are formed through a lower portion of a gatebox. The gates are hingedly connected along edges of the openings. One or two drive shafts in the gatebox are rotatable in gates-closing and gates-opening directions. Crank arms are fixed to the drive shafts and coupled to the gates by connecting links, which define an over-center geometry while the gates are at a closed position, such that weight of the fluid on the first gate induces torque on the drive shaft in the gates-closing direction. Rotation of the drive shafts in the gates-opening direction enables control of the fluid flow from the hopper according to an angular position of the drive shaft.