Abstract: A first embodiment of a hollow dorsal fin that can be selectively releasably connected to the fuselage of an aircraft is described herein. An interior of the hollow dorsal fin comprises a compartment. A second embodiment of a hollow dorsal fin is described comprising a compartment in an interior of the hollow dorsal fin, an opening configured to provide access to the compartment and a cover for covering the opening. An aircraft comprising the hollow dorsal fin, a fuselage, and electrical equipment is also provided. Methods for providing a hollow dorsal fin, and methods for installing electrical equipment on aircraft are also described.

Abstract: A first embodiment of a hollow wingtip device that can be selectively releasably connected to the wing of an aircraft is described herein. An interior of the hollow wingtip device comprises a compartment. A second embodiment of a hollow wingtip device is described comprising a compartment in an interior of the hollow wingtip device, an opening configured to provide access to the compartment and a cover for covering the opening. An aircraft comprising the hollow wingtip devices, a wing, and electrical equipment is also provided. Methods for providing a hollow wingtip device, and methods for installing electrical equipment on aircraft are also described.

Abstract: There is provided a method for retrofitting an aircraft with a removable panel comprising one or more of a connector and a feedthrough extending through the panel, and a connection assembly for fitting to an aircraft using the method. By providing a number of removable pre-made panels, each having different configurations of connectors and/or feedthroughs, the connection assembly allows the aircraft to which it is fitted to be conveniently reconfigured to support new equipment. Accordingly, there is also provided a structure forming at least part of the fuselage of an aircraft, the structure comprising the connection assembly, and a method for modifying such an aircraft having the connection assembly.

Abstract: There is provided a method of mounting equipment to an aircraft. The method comprises attaching a mounting structure to the fuselage of the aircraft, the fuselage extending lengthwise along a longitudinal axis. This comprises irremovably attaching a plurality of substantially planar frames to the exterior of the fuselage, such that each frame is oriented orthogonal to the longitudinal axis and spaced apart from an adjacent frame; and irremovably attaching a plurality of intercostal ribs between pairs of adjacent frames of the plurality frames, such that each rib is oriented parallel to the longitudinal axis and attached to each of a pair of said adjacent frames. The method further comprises mounting equipment to or within the mounting structure; and covering the mounting structure and the equipment mounted thereon or therein with a cover. The method further comprises removably attaching the cover to the mounting structure or the fuselage. An assembly, structure, tailplane and aircraft are also provided.

Abstract: There is provided a method of mounting equipment to an aircraft having an empennage. The method comprises mounting equipment to a mounting structure for mounting to the aircraft; removing an access panel from the outer skin of the empennage of the aircraft to reveal an access panel opening into the empennage; and attaching the mounting structure to or within the access panel opening such that at least a portion of the equipment extends beyond the outer skin of the empennage. The shape of the mounting structure at least partly conforms to the shape of the access panel opening. The method also comprises covering the mounting structure and the equipment mounted thereon with a cover, and attaching the cover to the mounting structure or the empennage. An assembly, structure, tailplane and aircraft are also provided.

Abstract: There is provided a method of mounting equipment to an aircraft having an empennage. The method comprises mounting equipment to a mounting structure for mounting to the aircraft; removing an access panel from the outer skin of the empennage of the aircraft to reveal an access panel opening into the empennage; and attaching the mounting structure to or within the access panel opening such that at least a portion of the equipment extends beyond the outer skin of the empennage. The shape of the mounting structure at least partly conforms to the shape of the access panel opening. The method also comprises covering the mounting structure and the equipment mounted thereon with a cover, and attaching the cover to the mounting structure or the empennage. An assembly, structure, tailplane and aircraft are also provided.

Abstract: There is provided a method of mounting equipment to an aircraft. The method comprises attaching a mounting structure to the fuselage of the aircraft, the fuselage extending lengthwise along a longitudinal axis. This comprises irremovably attaching a plurality of substantially planar frames to the exterior of the fuselage, such that each frame is oriented orthogonal to the longitudinal axis and spaced apart from an adjacent frame; and irremovably attaching a plurality of intercostal ribs between pairs of adjacent frames of the plurality frames, such that each rib is oriented parallel to the longitudinal axis and attached to each of a pair of said adjacent frames. The method further comprises mounting equipment to or within the mounting structure; and covering the mounting structure and the equipment mounted thereon or therein with a cover. The method further comprises removably attaching the cover to the mounting structure or the fuselage. An assembly, structure, tailplane and aircraft are also provided.

Abstract: The present invention relates to ligands, nanocrystal complexed with said ligands and their use for bio-imaging.