Systems and methods are provided for trimming and installation. One embodiment is a system for cutting out portions of a fuselage section. The system includes an Inner Mold Line (IML) tool comprising an inner gripping element configured to apply suction to a portion of the fuselage section, and further comprising an outer gripping element configured to apply suction to an area surrounding the portion, an Outer Mold Line (OML) tool configured to operate a cutter to cut the portion out from the fuselage section while suction is applied to the portion and to the area surrounding the portion, and a track that is disposed between the IML tool and the OML tool, wherein the fuselage section is configured to be pulsed in a process direction along the track, such that the fuselage section remains disposed between the IML tool and the OML tool when pulsed in the process 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.

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 system for protection of at least one aircraft door sill, including a rigid panel having shape and dimensions configured to cover and to protect the sill at least partially having an attachment face oriented toward the sill of the aircraft and configured to come to rest on the latter and a step face oriented in the direction away from the attachment face. The panel includes, on one transverse side, at least one cavity forming a housing and, on the other side, an arrangement for removably fixing to the sill. The protection system equally includes at least one bar having a shape at least partially complementary to the cavity to assure the nesting thereof. In this way the panel protects the sill and can easily be replaced: the sill is provided with a rapidly interchangeable protection system.

A door arrangement contains a door for a room with a door leaf, a wall portion of a wall structure laterally adjacent to the door, and a locking arrangement for the door. The locking arrangement includes a locking device in the door leaf with a blocking element, which can be moved in and contrary to a blocking direction in order to block or release the door, and a lock actuator in the wall portion with a first mechanical actuating element, which is unconnected to the blocking element in order to shift the blocking element, by mechanical contact pressure, from the movement position into the blocking position and vice versa. A control and information system contains the door arrangement, a control device for the lock actuator, a human/machine interface, and a communication interface for an authorized body different from the user.

A monitoring system and method are configured to detect a status of a door for a component on a vehicle. The monitoring system includes a sound sensor positioned within an auditory range of the door. The sound sensor detects sound energy generated in relation to a closed position of the door and an open position of the door. The sound sensor outputs a sound signal indicative of the sound energy. A monitoring control unit is in communication with the sound sensor. The monitoring control unit receives the sound signal and analyzes the sound signal to determine the status of the door.

Aircraft door designed to assume a first configuration and a second configuration, having a bistable mechanism biasing the aircraft door towards either the first or second configuration, the bistable mechanism including: a first yoke having a base attached to the first member and a first pivot rotatably mounted on the bas; a second yoke having: a base attached to the first member; a lever a first end of which is mounted so as to pivot on the base; a second pivot mounted so as to rotate on the second end of the lever; a coupling device for coupling the lever to the second member of the door; an arch which can be elastically deformed by bending and a first end of which is attached to the first pivot and a second end attached to the second pivot.

Disclosed herein is an apparatus for variable fluid damping. The apparatus comprises a mount. The apparatus also comprises a damper coupled to the mount to apply a damping force in response to movement of the mount. The apparatus further comprises an electrical element positioned to correspond to the damper. The apparatus additionally comprises a rheological fluid disposed in the damper. The rheological fluid changes viscosity in response to a change in an output of the electrical element to change the damping force of the damper. The apparatus also comprises a controller to provide input to the electrical element in response to a normal operating condition or an emergency operating condition.

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.

Aircraft door (1) having: an opening panel (2) provided with engagement abutments (26); a frame (3) intended to be attached to the fuselage (4) of the aircraft and including engagement counter-abutments (27); a hinge arm (5); a lifting lever (10); and a rotary control lever (20) which can be operated in a disengagement direction in order to unlock the opening panel (2). The door includes a one-way operating rod (18) which connects the control lever (20) to the lifting lever (10) and is designed to drive the lifting lever (10) only when the control lever (20) is actuated in the direction of disengagement.