A method for detecting cracks in an aircraft or gas turbine component includes ascertaining geometric data about the component using an optical measurement method, analyzing the geometric data, using an electronic evaluation device, so as to automatically recognize and/or classify at least one of cracks and other damage and storing a position of the at least one of cracks and other damage.

A rotorcraft having a rotor system including a yoke, a plurality of grip assemblies, each of which is hingedly attach a rotor blade to the yoke, a plurality of flap stops, each flap stop attached to a respective grip assembly, a channel bounded by an upper and lower retaining surfaces, and a droop ring slideably disposed in the channel of the droop limiting system. The droop ring has a body with an inner surface, an outer surface, and a first end surface between the inner surface and the outer surface. The droop ring further has a first wear element removably disposed at the first end surface and extending above the first end surface and spaces the first end surface apart from the channel. Each flap stop is arranged to contact the outer surface of the droop ring and limit a downward droop of the respective rotor blade.

A bladder assembly including an inflatable bladder having an elongated body defining an internal volume, the body being formed as a layered structure that includes an elastomeric layer defining an interior surface of the body, a friction-reducing layer defining an exterior surface of the body, and a jacketing layer positioned between the elastomeric layer and the friction-reducing layer, and a pressurized fluid source in selective fluid communication with the internal volume of the body.

A plate-shaped workpiece forming method of post-machining a pocket (3) on a curved inner surface of a plate-shaped workpiece (2) in a state where the plate-shaped workpiece (2) curved by a curving machine (10) is spread flat. The method includes a curving step (A) of setting a net curve radius (R.sub.0) obtained by adding a curve radius contraction amount (R.sub.1) due to spring-in to a finished curve radius (R) of a plate-shaped workpiece (2), taking into account an amount of contraction of the curve radius of the plate-shaped workpiece (2) between before and after machining of a pocket (3) due to spring-in, and curving the plate-shaped workpiece (2) so as to achieve the net curve radius (R.sub.0); and a pocket machining step of post-machining the pocket (3) by flatly spreading the curved plate-shaped workpiece (2).

Disclosed herein in a system for positioning a sub-assembly for installation. The system comprises a tool comprising a base and a sub-assembly support. The sub-assembly support is positioned above the base and pivotably mounted to the base at a pivot axis. The tool is positioned adjacent to an interior surface of an assembling body and configured to support a sub-assembly. The system also comprises at least one actuator that is selectively operable to tilt a first surface of the sub-assembly support toward an opening in the assembling body and adjust an angle of the sub-assembly support, relative to the base. The system further comprises an interior conforming device attached to the tool and configured to interface with the interior surface of the assembling body. The system additionally comprises an exterior conforming device configured to interface with the exterior surface of the assembling body.

Methods for reworking structures and reworked cellular core panels, reworked structures comprising the reworked cellular core panels, and guides and cutting apparatuses for reworking cellular acoustic panels and reworking cellular acoustic and non-acoustic panels are disclosed.

An attachment for an end effector. The attachment may include a clamp and a foot adhesively bonded to an edge of the clamp and having a set of interlocking features that form a mechanical interlock with the clamp.

A fastening system including a frame, a movement control assembly, a fastener drive assembly and a collar presenting assembly. The frame can be coupled to an outside structure, for example, with a part that is to be coupled with a fastener attached to the frame. The movement control assembly is configured to controllably move the fastener drive assembly relative to the frame and the part so as to grasp the collar of the fastener, engage the threaded pin of the fastener and to threadedly engage the two structures together. The collar presenting assembly presents a collar of a fastener to the fastener drive assembly.

The object is to provide an aircraft component positioning device, an aircraft assembly system, and an aircraft assembly method with which it is possible to precisely dispose components on a planar member of an aircraft without using a positioning jig. A positioning device (2) includes a detection unit (5) that detects positions of a plurality of first components installed on a planar member of an aircraft, a virtual position creation unit (6) that creates a virtual position between the plurality of first components on the basis of the positions of the plurality of first components that are detected, and a position determination unit (7) that, on the basis of the virtual position that is created, determines an installation position of a second component, different from the plurality of first components, that is installed on the planar member.

In order to improve and facilitate shimming between two parts, a deformable shim is provided that comprises a main structure of an at least partly cellular region. The main structure is compressible by plastic deformation from an initial volume to a deformed volume, wherein the deformed volume is smaller than the initial volume. In a deformed state, the main structure maintains the deformed volume without further or continuing compression force. Further, the main structure is arrangeable between a first aircraft component and a second aircraft component to create a predefined distance between the first and the second aircraft component.