A method of repairing or, in certain cases, strengthening a metallic substrate at a damage site is provided and includes removing material from the substrate around the damage site to form a recess, and cold spraying particulate material into the recess to form a bead of deposited material.

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.

Systems are provided for fabricating a preform for a fuselage section of an aircraft. The system includes advancing a series of arcuate mandrel sections in a process direction through an assembly line, laying up fiber reinforced material onto the arcuate mandrel sections via layup stations, uniting the series of arcuate mandrel sections into a combined mandrel; and splicing the fiber reinforced material laid-up onto the arcuate mandrel sections.

A manufacture configured to and process for inhibiting, from wear, a lock in a latching system comprising: a gland surrounding an actuator translating the lock through: a first fixed lock receptor and a moveable lock receptor. The manufacture and process include: inhibiting a skewing, of a lock central axis of the lock with the lock translating through the first opening and the opening in the moveable lock receptor, away from substantially aligning with: a first central axis of a first opening of the first fixed lock receptor, and an actuator central axis of the actuator, via fitting a first translation guide into the first fixed lock receptor. Also included is inhibiting: wear of a gland around an actuator in the lock while translating, and leaking, past the gland, of an actuator fluid within the lock; and skewing of an actuator central axis of the actuator.

The invention relates to design and production methods for a rotor which is both a turbine and a propeller having blades that are hollow along the entire length thereof and which lead into peripheral circular chambers that operate as an engine (THRA) that can be powered by working fluids.

Systems and methods are provided for advancing a fuselage section of an aircraft. One embodiment is a system that includes a series of plates configured to be sequentially affixed along a length of the fuselage section, and a track configured to form a frictional fit with the plates. The track includes drive units configured to form nips retaining the series of plates, and that are configured to advance the fuselage section along the track in a process direction, and indexing elements that are configured to engage with indexing elements at the plates during pauses between operation of the drive units. The system also includes tools configured to perform work on the fuselage section while the indexing elements of the track are engaged.

A tool configured to install and torque multiple fasteners, such as nuts and/or bolts, positioned in confined and/or hard to reach areas. The tool includes a body portion, a plurality of fastener retainers, and a structure which permits both the remote tightening and torquing of such fasteners. The tool also provides an actuator for the remote release of torque loads which may build up in the fastener retainers during such torquing of the fasteners. The actuator includes a lever arm pivotally connected to the body portion and a cam that is rotatable between a first position and a second position. A linkage is engaged by the cam and urges the lever arm to a torquing position upon the cam being in the first position and to a torque release position upon the cam being in the second position.

According to one embodiment, a bearing is situated between a pitch link and a swashplate or a hub. The bearing comprises an outer housing having a first opening therethrough, an intermediate housing adjacent the housing inside the first opening and having a second opening therethrough, and an inner housing adjacent the intermediate housing inside the second opening and having a third opening therethrough. The inner housing comprising a first inner surface and a second inner surface defining the third opening. A first member is adjacent the first inner surface inside the third opening having a fourth opening therethrough. A second member is adjacent the second inner surface inside the third opening having a fifth opening therethrough coaxial with the fourth opening.

An assembling device includes a holding member and a processing device. The holding member is configured to hold a first assembly component and a second assembly component. The processing device is configured to process a first excess thickness portion and a second excess thickness portion. The first excess thickness portion is provided at the first assembly component and is configured to adjust a gap between the first assembly component and the second assembly component. The second excess thickness portion is provided at the second assembly component and is configured to adjust the gap.

A method for repairing a fan casing in which the inner surface is damaged, includes attaching a reinforcement element to the fan casing, the reinforcement element being attached to the outer surface of the fan casing opposite the damage.