Temperature of a structural member is maintained at allowable temperature or less by suppressing heat transfer from a high-temperature duct to the structural member. An insertion sheet according to the present invention is inserted between a flange and a partition panel. The flange is provided on a bleed duct and is fastened to the partition panel. The bleed duct penetrates through a partition wall of an aircraft. The insertion sheet includes first parts and a second part. The first parts are disposed near respective shafts of rivets provided at a plurality of positions of the insertion sheet. The second part extends among the first parts. The first parts bear a load of fastening, and the second part has thermal conductivity lower than thermal conductivity of the first parts.

A support arrangement include a mount, a cover, and a metallic mesh body. The mount has a base portion and a mount clamping portion. The cover has a plate portion and a cover clamping portion, the cover fixed to the base portion of the mount and the cover clamping portion registered to the mount clamping portion. The metallic mesh body is arranged between the mount clamping portion and the cover clamping portion to compressively support a sensor element between the mount clamping portion and the cover clamping portion. Fire and overheat detection systems, gas turbine engines with fire and overheat detection systems, and methods of making support arrangements for fire and overheat detection systems are also described.

There is provided a sidewall closeout area assembly for an aircraft. The assembly includes a raceway with a first end to attach to a sidewall assembly, a second end to attach to aircraft floor structure(s), and a raceway body with first access opening(s) providing access to one or more of, a crown area and an underfloor area, for conductive elements routed along the raceway. The assembly further includes a raceway cover removably coupled to the raceway and having second access opening(s) providing access to the cabin and to an overfloor area in the cabin for the conductive elements. The assembly further includes a closeout area formed between the raceway body and the raceway cover, to house and protect the conductive elements. The assembly facilitates accessibility to the conductive elements, and provides a routing path for the conductive elements that does not need to be reconfigured for different aircraft cabin layouts.

A transport element clamp system comprising a lower portion, an upper portion, and a channel system. The lower portion has a first number of cutouts and the upper portion has a second number of cutouts. The lower portion is configured to bridge a gap between two support structures in an aircraft. The upper portion is configured to interlock with the lower portion. The channel system is formed by the first number of cutouts and the second number of cutouts. The channel system is configured to receive a number of transport elements when the upper portion and the lower portion are coupled to each other. The transport element clamp system electrically isolates the number of transport elements from the two support structures.

Improved methods and devices for shielding electrical and electronic aircraft components and their associated cables and wires from cross-coupling and electrical and magnetic interference and dissipating excess heat from the electrical and electronic aircraft components and cables and wires. An aircraft structure formed primarily of composite materials includes an outer wall; an inner wall; and a plurality of spaced-apart dividers extending transversely from and integrally formed with the inner wall. The dividers define a series of spaced-apart channels that are each partially enclosed by adjacent pairs of the dividers. A layer of electrically conductive foil covers the dividers and the channels to create a current return network in the channels. Wires and cables may be placed in the channels between adjacent pairs of the dividers to reduce cross-coupling between the wires and cables and shield the wires and cables from electromagnetic fields.

A multi-function support assembly supports, grounds, and shields numerous different types of aircraft systems and simultaneously stabilizes aircraft structures to which the support assembly is mounted. The support assembly includes a support tray and a number of support brackets attached to and spaced along the length of the support tray. The support tray attaches to aircraft floor beams or other aircraft structures to stabilize the structures while providing a mounting location for the support brackets. The support tray also provides electromagnetic and structural shielding for aircraft systems and a ground path for electrical and electronic components in the aircraft. The support brackets are formed of electrically insulative materials and attach to the support tray to support various aircraft systems below the support tray and to electrically isolate the support tray from the aircraft structures and the aircraft systems from the support tray.

A wall covering panel for a nose of an aircraft. The panel comprises a rigid carrying framework preferably having an alveolar structure obtained by 3-D printing, a decor carried by the carrying framework and an acoustically and thermally insulating padding fixed to the carrying framework, and also attachments for fixing the carrying framework to the primary structure of the aircraft. Preferably, the panel also integrates systems, such as electrical route portions or ventilation route portions that traverse the panel from one side to the other or lead to an outlet equipment item also integrated in the panel. Only the carrying structure of the panel, which carries the decor, the insulating padding and any route portions and equipment items, is fixed to the primary structure of the aircraft. The number of attachments is low; the kitting-out and the finishing of the nose of the aircraft are greatly simplified.

A mounting assembly for restricting movement of an electrical harness of a gas turbine engine includes a base, a first channel formed in the base and extending between a first surface and a second surface of the base, and a second channel formed in the base and extending between the first surface and a third surface of the base. The second surface and the third surface are distinct. At least one flexible connector is receivable within the first channel and the second channel. At least a portion of the at least one flexible connector extends about the electrical harness to couple the electrical harness to the base.

In order to facilitate the thermoacoustic insulation of an aircraft portion, a method for manufacturing a thermoacoustic insulation module for an aircraft comprises a step of providing a mat configured to provide thermoacoustic insulation of an aircraft portion, followed by a step of attaching a bendable structure to the mat, followed by a step of bending the bendable structure, along a bending axis parallel to a longitudinal direction of the mat, such that the bendable structure forms a load-bearing structure supporting the mat in a curved shape.

A panelling part for a cabin of a means of transportation is proposed, which includes at least one display unit and at least one control unit, which are produced by printing and equipping at least one film, which is applied to a panelling element. The control unit can communicate wirelessly with an external electronics unit, so that the panelling part only requires a power terminal to implement electronic functions. Functions can be retrofitted easily by replacing the at least one film.