Abstract: A method of producing a sealed structural joint between two components (23, 24) and such a sealed joint are provided. The method includes the steps of applying a layer of sealant (27) to the first component (23), applying liquid shim (28) to the second component (24), inserting an intermediate layer (29) between the sealant (27) and the liquid shim (28), the intermediate layer (29) having a series of raised structural features (31) to engage the first component (23). The features (31) are positioned to allow the sealant (27) to extend across the joint between the raised features (31) to form a continuous seal. The joint is then closed and cure of the liquid shim (28) and sealant (27) takes place to solidify the shim (28) to the desired thickness within the joint.

Abstract: An external part of an aircraft (such as a fairing) comprising a skin made with flexible materials attached to rigid supporting elements (such as longerons and frames) arranged in, at least, two directions. The skin comprises inner inflatable panels in all bays delimited by the rigid supporting elements and/or an external inflatable panel. The skin is joined to the supporting elements so that its external surface complies with aerodynamic requirements.

Abstract: A method of producing a sealed structural joint between two components (23, 24) and such a sealed joint are provided. The method includes the steps of applying a layer of sealant (27) to the first component (23), applying liquid shim (28) to the second component (24), inserting an intermediate layer (29) between the sealant (27) and the liquid shim (28), the intermediate layer (29) having a series of raised structural features (31) to engage the first component (23). The features (31) are positioned to allow the sealant (27) to extend across the joint between the raised features (31) to form a continuous seal. The joint is then closed and cure of the liquid shim (28) and sealant (27) takes place to solidify the shim (28) to the desired thickness within the joint.

Abstract: An aircraft frame structure including a grid support (such as a geodetic support) (2) and (i) an impact-resistant barrier (6) including a shear thickening fluid, and (ii) a water-resistant, elastically-deformable cover (4). Methods to make and repair an aircraft using the aircraft frame structure.

Abstract: An external part of an aircraft (such as a fairing) comprising a skin made with flexible materials attached to rigid supporting elements (such as longerons and frames) arranged in, at least, two directions. The skin comprises inner inflatable panels in all bays delimited by the rigid supporting elements and/or an external inflatable panel. The skin is joined to the supporting elements so that its external surface complies with aerodynamic requirements.

Abstract: The present invention proposes a cap for forming a sealed cavity around one end of a fastener to thereby contain out-gassing and sparking events in the event of a lightning strike to the fastener. The invention also proposes a joint comprising such a cap, and a kit of parts and method for installing such a cap. A cap according to the invention comprises: an inner cap member having an annular base terminating at an edge which surrounds an opening into an air cavity for enclosing the one end of a fastener; and an outer cap member having an annular skirt or flange which extends radially outwardly away from the annular base, the annular skirt or flange and annular base between them defining an annular sealing cavity.

Abstract: An apparatus and method for testing material to determine if the materials have exceeding their useable life based an analysis of the chemical degradation of the material. An infrared (IR) spectroscopic measurement is made of the material. The measurement results are compared to a database of previously obtained measurement results. Depending on the comparison of the measurement result to the database of previously obtained measurement results, an indication of a measure of the lifespan of the chemically reactive material is determined and provided.

Abstract: The present invention proposes a cap for forming a sealed cavity around one end of a fastener to thereby contain out-gassing and sparking events in the event of a lightning strike to the fastener. The invention also proposes a joint comprising such a cap, and a kit of parts and method for installing such a cap. A cap according to the invention comprises: an inner cap member having an annular base terminating at an edge which surrounds an opening into an air cavity for enclosing the one end of a fastener; and an outer cap member having an annular skirt or flange which extends radially outwardly away from the annular base, the annular skirt or flange and annular base between them defining an annular sealing cavity.