A system includes a robotic arm, a rotisserie control linkage, and a computer system. The robotic arm includes a touch probe and laser head. The rotisserie control linkage is configured to couple to a transport cart. The computer system is communicatively coupled to the robotic arm and the rotisserie control linkage and is configured to control the system to probe, using the touch probe of the robotic arm, a transparent outer layer of an aircraft canopy located on the transport cart in order to determine surface measurements of the aircraft canopy. The computer system also controls the system to ablate, using a plurality of predetermined parameters and the laser head of the robotic arm, an interface layer located between the transparent outer layer and the aircraft canopy, wherein movements of the robotic arm during the ablation are based on the surface measurements.

A movable carriage system for an aircraft element, such as an aeroplane engine, has a first movable module (10) and a second movable module (20). Each movable module has a frame (12, 22) equipped with at least three wheels, a lifting device adapted to be able to move said aircraft element at least in a vertical direction, and at least one link arm (16, 17) adapted to be able to secure together the frame of said first module and the frame of said second module and to allow data to be transferred between them. The movable modules are adapted to be able to be controlled in a mutually coordinated manner.

A movable carriage system for an aircraft element, such as an aeroplane engine, has a first movable module (10) and a second movable module (20). Each movable module has a frame (12, 22) equipped with at least three wheels, a lifting device adapted to be able to move said aircraft element at least in a vertical direction, and at least one link arm (16, 17) adapted to be able to secure together the frame of said first module and the frame of said second module and to allow data to be transferred between them. The movable modules are adapted to be able to be controlled in a mutually coordinated manner.

Tooling for placing a propulsive assembly from a horizontal position to a vertical position includes a front tool and a rear tool. The front tool has a first assembly with a frame configured to be positioned and maintained with respect to a front casing. The frame has a first connection interface configured to be connected to a first lifting system such that the frame is movable about an axis of rotation (R). The front tool also has a second assembly with a shaft configured to be positioned and maintained with respect to a rotor and a member for connection between the first assembly and the second assembly. The tooling further includes a rear tool configured to be positioned and maintained with respect to the rear casing. The rear tool has a second connection interface configured to be connected to a second lifting system.

Tooling for placing a propulsive assembly from a horizontal position to a vertical position includes a front tool and a rear tool. The front tool has a first assembly with a frame configured to be positioned and maintained with respect to a front casing. The frame has a first connection interface configured to be connected to a first lifting system such that the frame is movable about an axis of rotation (R). The front tool also has a second assembly with a shaft configured to be positioned and maintained with respect to a rotor and a member for connection between the first assembly and the second assembly. The tooling further includes a rear tool configured to be positioned and maintained with respect to the rear casing. The rear tool has a second connection interface configured to be connected to a second lifting system.

A method of assembling a structure in aircraft or spacecraft production wherein two components to be joined together at a joint are provided, each component comprising a joining region. Sealant is applied to one of the component joining regions. An arrangement is formed by positioning the components relative to each other, whereby an uncured layer of the sealant is formed between associated joining regions. The associated joining regions are clamped against each other using a clamping device, and a clamped state is maintained until the layer of sealant has cured to a pre-defined degree, the clamping device being installable on and transportable along with the arrangement. After the layer of sealant has cured to the pre-defined degree, drilling at a plurality of fastening positions is performed to obtain a hole of final dimension at each fastening position, and installation of a final fastener at each fastening position is performed.

A system for providing maintenance and repair units for maintenance work on an aircraft includes a maintenance and repair unit having a frame structure which carries equipment and which is transportable, and a transport vehicle having a lifting device which can raise, set down, and transport the maintenance and repair unit.

A system for providing maintenance and repair units for maintenance work on an aircraft includes a maintenance and repair unit having a frame structure which carries equipment and which is transportable, and a transport vehicle having a lifting device which can raise, set down, and transport the maintenance and repair unit.

Positioning system and method for positioning engine components on an aircraft, the system including a moveable support for the engine component, a laser assembly, and a system controller. First and second lasers of the laser assembly align their respective beams with an engine target position on the aircraft and provide an indication of a first angle of the first laser beam to a reference line, and an indication of a second angle of the second laser beam to the reference line; and the system controller is configured to rotate the moveable support to rotationally position the engine component, determine the vertical distance between the engine component and the target position based at least in part on the first and second angles, and to control a lift mechanism to reduce the vertical distance between the engine component and the engine.

A movable carriage system for an aircraft element, such as an aeroplane engine, has a first movable module (10) and a second movable module (20). Each movable module has a frame (12, 22) equipped with at least three wheels, a lifting device adapted to be able to move said aircraft element at least in a vertical direction, and at least one link arm (16, 17) adapted to be able to secure together the frame of said first module and the frame of said second module and to allow data to be transferred between them. The movable modules are adapted to be able to be controlled in a mutually coordinated manner.