A support bracket for holding interior components of a vehicle includes a base plate and an add-on module, which are engageable with each other to facilitate replacement and maintenance.

A noise attenuating device for reducing acoustic resonance in a cavity of an aircraft with an opening in a skin of the aircraft defining a first surface area and an opening peripheral edge includes a connection mechanism for securing the noise attenuating device in proximity to the opening in the skin of the aircraft and an exterior surface. The exterior surface defines a second surface area that is less than the first surface area of the opening and a device peripheral edge, which has a first section having an edge profile complimentary to at least a portion of the opening peripheral edge and a second section having an indented edge profile in relation to the first section such that when the noise attenuating device is secured within the opening, at least one gap is formed between the device peripheral edge and the opening peripheral edge.

A fastening system for suspended installation of stowage compartments, in particular in aircraft, includes a first fastening element, which fastens on a supporting structure, a second fastening element, which fastens on a stowage compartment, and a connecting arrangement, configured for surface-area fastening on the first fastening element. The connecting arrangement and the second fastening element each include a supporting eyelet for accommodating a fastening bolt, to fasten the connecting arrangement on the second fastening element. The first fastening element and the connecting arrangement each include a fastening surface for fastening on one another, and therefore a continuous insulation layer can be positioned between the fastening surfaces, or between the supporting structure and the first fastening element, for the purpose of insulating the supporting structure, in order for the supporting structure alone or together with the first fastening element to be insulated throughout in relation to the connecting arrangement.

A device for securing at least one thermal protection mat to an internal fixed structure of a nacelle includes at least one removable fastening element for securing the at least one thermal protection mat to the internal fixed structure designed to be arranged between the mat and the internal fixed structure. The device includes at least one gripping element connected to the removable fastening element to project relative to the mat on the opposite side to the internal fixed structure, the removable fastening element being intended to be detached from the internal fixed structure by a pulling force exerted on the gripping element.

An aircraft cabin section includes a door frame, which forms a door opening, a passenger door, which is arranged on the door frame and is configured to close the door opening, and a door insulation arrangement, which is larger in at least one direction than the door opening. The door insulation arrangement is produced from a textile which is heat-insulating and/or airflow-inhibiting. Furthermore, a corresponding door insulation arrangement and an aircraft having such an aircraft cabin section or such a door insulation arrangement are disclosed.

An aircraft line or harness fastening system with a clamp attaching the line or harness to the aircraft. A bobbin within the clamp surrounds the line or harness, wherein the bobbin is smaller than the clamp and is circular in shape to enable rotation of the bobbin within the clamp. The bobbin includes two separate complementary parts that fit together around the line or harness. Each of the two separate complementary parts include a tab and a recess, wherein the tab of one of the complementary parts fits into the recess on the other of the complementary parts.

An assembly including a support panel of an internal fixed structure, a thermal protection element and a plurality of fastening systems. Each fastening system includes a female part secured to the support panel and which has, in its interior, a circular shoulder, and a male part including a sleeve pierced with a main bore, a slide movable in translation in the main bore and a plurality of balls. For each ball, the sleeve has a secondary bore, and each ball is movable along the secondary bore between a locking position and an unlocking position. The slide is movable in translation between a blocking position and an unlocking position. Such an assembly makes it possible to fasten the thermal protection element to the support panel in a simple and rapid manner, also permitting easy removal if necessary.

A noise attenuating device for reducing acoustic resonance in a cavity of an aircraft with an opening in a skin of the aircraft defining a first surface area and an opening peripheral edge includes a connection mechanism for securing the noise attenuating device in proximity to the opening in the skin of the aircraft and an exterior surface. The exterior surface defines a second surface area that is less than the first surface area of the opening and a device peripheral edge, which has a first section having an edge profile complimentary to at least a portion of the opening peripheral edge and a second section having an indented edge profile in relation to the first section such that when the noise attenuating device is secured within the opening, at least one gap is formed between the device peripheral edge and the opening peripheral edge.

A connecting assembly for connecting two structures of an aircraft, the connecting assembly including a central element featuring a through-hole, preferably a bore, configured to make a connection with one of the two structures by virtue of a fastener element including a shank inserted into the through-hole. The connecting assembly further includes a plurality of shock-absorbing elements made from a deformable material. Each of the shock-absorbing elements are, on the one hand, secured to the central element and, on the other hand, configured to bear against a surface of the other of the two structures. An aircraft part includes such a connecting assembly.

An insulation system for an aircraft fuselage uses a plurality of stringers extending longitudinally. An insulation blanket is configured for installation on the stringers and a plurality of stringer clips are attached to and extend from an outboard side of the insulation blanket. Each stringer clip has a connecting flange engaged to a cover of the insulation blanket. A first attachment arm extends outboard from a first end of the connecting flange and terminates in a first hook resiliently engaging the stringer. A second attachment arm extends outboard from a second end of the connecting flange and terminates in a second hook resiliently engaging the stringer.