An aircraft door controller 100 including a receiver 110 configured to receive a command 14 to move an aircraft door between an open position and a closed position relative to a door frame. The aircraft door controller 100 is configured to not store the command 14 when power to move the aircraft door between the open position and the closed position relative to the door frame is unavailable.

An automated and versatile autonomously climbing undercarriage with flight capability that automatically reaches a suitable area for cleaning purposes, repair purposes, and monitoring purposes without being constantly connected to a supply station or base station in the process, and that independently goes to the surface of the facade and independently moves along the surface and away from the surface. The automated and versatile autonomously climbing undercarriage with vacuum suction units as per the invention involves a multicopter with two, three or more rotors or propellers attached to the autonomously climbing undercarriage.

An automated and versatile autonomously climbing undercarriage with flight capability that automatically reaches a suitable area for cleaning purposes, repair purposes, and monitoring purposes without being constantly connected to a supply station or base station in the process, and that independently goes to the surface of the facade and independently moves along the surface and away from the surface. The automated and versatile autonomously climbing undercarriage with vacuum suction units as per the invention involves a multicopter with two, three or more rotors or propellers attached to the autonomously climbing undercarriage.

Landing gear doors may be opened in an emergency event, e.g., a failure of the normal landing gear actuation system that requires a gravity free-fall deployment. The retractable aircraft landing gear door actuation mechanism will include a landing gear door and a door support bracket attached to the landing gear door. The support bracket is attached to aircraft structure for pivotal movement about a pivot axis between a closed condition whereby the landing gear door covers an aircraft landing gear when retracted relative to the aircraft structure, and an opened condition whereby the landing gear door is moved laterally and upwardly relative to the aircraft landing gear when extended relative to the aircraft structure. A gear door actuation assembly is operatively connected to the door support bracket for moving the door support bracket and the gear door supported thereby between the closed and opened conditions thereof. The gear door actuation assembly will include an over-the-center spring assembly which assists in pivotal movement of the door support bracket and the gear door supported thereby from the closed condition into the opened condition thereof.

Landing gear doors may be opened in an emergency event, e.g., a failure of the normal landing gear actuation system that requires a gravity free-fall deployment. The retractable aircraft landing gear door actuation mechanism will include a landing gear door and a door support bracket attached to the landing gear door. The support bracket is attached to aircraft structure for pivotal movement about a pivot axis between a closed condition whereby the landing gear door covers an aircraft landing gear when retracted relative to the aircraft structure, and an opened condition whereby the landing gear door is moved laterally and upwardly relative to the aircraft landing gear when extended relative to the aircraft structure. A gear door actuation assembly is operatively connected to the door support bracket for moving the door support bracket and the gear door supported thereby between the closed and opened conditions thereof. The gear door actuation assembly will include an over-the-center spring assembly which assists in pivotal movement of the door support bracket and the gear door supported thereby from the closed condition into the opened condition thereof.

An operating device for operating at least one door of an aircraft comprises a chassis that is fixed and secured to a fuselage of the aircraft, a control handle that is rotationally and translationally movable with respect to the chassis, a mechanism for converting a rotational movement of the control handle into an opening movement of the door. The translational movement allows the control handle to be in an in position in which it is aligned with the exterior surface of the fuselage and an out position in which it projects beyond the exterior surface of the fuselage. The control handle includes a cylindrical body and a head connected to one end of the body. The head of the control handle includes a fixed part rigidly connected to the body of the control handle and extending perpendicular thereto, and a movable part rotatably connected to the body and having a folded-down position against the fixed part and a deployed position in which the control handle has a T shape.

An operating device for operating at least one door of an aircraft comprises a chassis that is fixed and secured to a fuselage of the aircraft, a control handle that is rotationally and translationally movable with respect to the chassis, a mechanism for converting a rotational movement of the control handle into an opening movement of the door. The translational movement allows the control handle to be in an in position in which it is aligned with the exterior surface of the fuselage and an out position in which it projects beyond the exterior surface of the fuselage. The control handle includes a cylindrical body and a head connected to one end of the body. The head of the control handle includes a fixed part rigidly connected to the body of the control handle and extending perpendicular thereto, and a movable part rotatably connected to the body and having a folded-down position against the fixed part and a deployed position in which the control handle has a T shape.

A structural assembly for an aircraft having pairs of main gantries distributed in the longitudinal direction, two transverse panels fixed to the front and the rear of the pairs of main gantries to together define a compartment for a landing gear of the aircraft, at least one pair of secondary gantries between the main gantries, at least one crossmembers parallel to the transverse panels and that straddles at least one secondary gantry, and, for each secondary gantry and each crossmember straddling the secondary gantry, a connecting rod mounted to be able to freely rotate, via a first end, on a lower part of the crossmember and, via a second end, on an outer lateral part of the secondary gantry. Such an arrangement reduces the vertical bulk of the structural assembly.

A structural assembly for an aircraft having pairs of main gantries distributed in the longitudinal direction, two transverse panels fixed to the front and the rear of the pairs of main gantries to together define a compartment for a landing gear of the aircraft, at least one pair of secondary gantries between the main gantries, at least one crossmembers parallel to the transverse panels and that straddles at least one secondary gantry, and, for each secondary gantry and each crossmember straddling the secondary gantry, a connecting rod mounted to be able to freely rotate, via a first end, on a lower part of the crossmember and, via a second end, on an outer lateral part of the secondary gantry. Such an arrangement reduces the vertical bulk of the structural assembly.

An aircraft assembly jig for fitting a number of landing gear door components to an aircraft. The jig includes a lifting device for elevating the components towards the aircraft for fitting, and a number of adjustable platforms attached to the lifting device, each of which holds one of the landing gear door components. The adjustable platforms allow each of the components to be positioned independently so that when elevated together towards the aircraft by the lifting device, each component is correctly and independently aligned and positioned for installation at the aircraft.