A method for removing a component fixed to an aeronautical part, the aeronautical part comprising a first material, and the component comprising a second material different from the first material, the method comprising steps of determining the thicknesses of the component as a function of the position on the component, and of removing the component by means of a pressurized water jet moving over the component as a function of the thicknesses determined in the determination step.

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 system for use in servicing a machine. The system includes a tubular body including a longitudinal axis, a tip end, a dispensing nozzle defined at the tip end, and an interior channel in flow communication with the dispensing nozzle. The tubular body is configured to be flexible. An actuator is configured to selectively modify an orientation of the tubular body, and a reservoir is in flow communication with the interior channel. The reservoir is configured to supply a maintenance fluid to the tubular body for discharge from the dispensing nozzle.

A method for holding a part blank inside a holding assembly. The holding assembly includes a first holding portion. The first holding portion includes an inner cavity containing a fluid. The part blank and the first holding portion are at least partially manufactured by additive manufacturing. The holding method includes a heating of the holding assembly and the part blank to deform the first holding portion by fluid expansion in the inner cavity and to reduce a gap between the part blank and the holding assembly by expansion of the first holding portion in relation to the part blank.

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 tool for installing segments of a coupling having male and female couplers drivingly engaged to one another by the segments, the tool has: a coupler-engaging section engageable to the a female coupler of the couplers for radially supporting the tool relative to the female coupler about a rotation axis of the coupling; and a peripheral wall secured to the coupler-engaging section and extending circumferentially around the rotation axis, a diameter (D2) of the peripheral wall selected to allow insertion of the segments between the female coupler and the peripheral wall, the peripheral wall defining an abutting surface against which radially inner ends of the segments abut during insertion of the segments between the female coupler and the peripheral wall.

A safety apparatus for containing a release of energy from a tension stud of a rotor assembly, the safety apparatus including a containment member configured to pivot about a pivot location, the containment member including a retaining arm located on a first side of the pivot location and a catch located on a second side of the pivot location, wherein the containment member is movable about the pivot location to a first position in which the catch is engaged with a lip of a disc of the rotor assembly to position the retaining arm in a containment position.

A probe adapter includes an adapter body including a probe aperture and a slot. The probe adapter further includes a driver slidably mounted within the slot and slidable between a first position and a second position. The driver includes a first end and a second end opposite the first end. The first end includes a ramped recess extending in a direction from the first end toward the second end. The probe adapter further includes a threaded fastener configured to contact the second end of the driver so as to retain the driver in the first position.

In this method for mounting a combustor component, a component hanging step for attaching a string material to a hanging jig mounted on a combustor component and hanging the combustor component with the string material together with the hanging jig, and a component mounting step for mounting a mounting flange of the combustor component at a combustor mounting position of a gas turbine casing are executed. The hanging jig has a hanging tool having a portion which becomes a suspension point contacted by the string material when the string material is attached and hanging the combustor component. The suspension point is positioned on the distal end side of the center of gravity of the combustor component in the combustor axial line direction when the hanging jig has been mounted to the mounting flange.

A component according to the disclosure may include a body having an aperture therein for receiving one of a turbomachine shaft or a lathe chuck, wherein in response to the body being coupled to the lathe chuck, the aperture is oriented substantially axially relative to an axis of rotation of the body with the lathe chuck; and a flange coupled to and in direct axial contact with the body, the flange including a surface that extends axially relative to the axis of rotation of the body, wherein the surface of the flange comprises a matingly engageable face configured to contact an axially aligned surface during operation of the component and having a sanding indentation thereon, wherein a surface roughness of the surface of the flange is less than a surface roughness of a remainder of the component.