Abstract: A fastener insert attached to a mounting fixture is inserted into a hole drilled in a honeycomb panel. The mounting fixture has a rod with a disc at an end depending from a base and a chimney ascending from the base. Two bores are located in the base and are enclosed by the chimney. The mounting fixture base overlaps the head of the fastener insert which has two bores in the head. The bores in the fastener insert head are aligned with bores in the base of the mounting fixture. Epoxy is inserted into one of the bores in the base of the mounting fixture continuously until it returns out the second bore. The epoxy is allowed to cure and thereafter the mounting fixture is removed by a turning motion.

Abstract: A lower support bracket has an integral back wall, pair of side walls and a bottom plate with a through bore. An elastomeric spacer is mounted axially above and below the bottom plate bore and an adjuster device is axially mounted below the lower elastomeric spacer. The bracket is held in place by a bolt through the bore to an aircraft frame structure. The back wall is attached to an escutcheon plate which is in turn attached to a lower portion of an aircraft interior panel. The upper support bracket has a mounting plate attached to an aircraft fuselage frame structure. A pivoting arm at a first end is spaced from the mounting plate by an elastomeric gasket and at a second end is attached to a panel bracket attached to an upper portion of the interior panel so that the interior panel is spaced apart from the aircraft fuselage frame structure.

Abstract: An aircraft interior skeleton spaced apart from the aircraft frame is formed from multiple spaced apart upright U-shaped ribs attached to horizontal intercostal U-shaped members conforming to the aircraft frame members, but not contacting such frame members. Multiple interior honeycomb side panels and overhead panels are hinged from the interior skeleton and interlocked with adjacent panels. An overhead connecting member is attached to a top end of each rib and a dampening device connects the bottom end of each rib to an aircraft frame member. Adjustable cable connectors position the interior skeleton within the aircraft by connecting the horizontal intercostal members to the aircraft frame members.

Abstract: A top and bottom disk with central bores axially aligned for receipt of a through bolt fastener. The disks have descending and ascending integral cylindrical tubes respectively. The descending top disk tube has a side wall vertical channel leading to an eccentric hole in the top disk at one end. The inner diameter of the top disk cylindrical tube is slightly larger than the outer diameter of the bottom disk cylindrical tube and receives the bottom disk tube in axial alignment within a through hole in a two-sided honeycomb panel. Ridges on a surface of each disk, in contact with a honeycomb panel side, seal the disk in place after epoxy is inserted into the eccentric hole in the top disk.

Abstract: The test method employed uses a cylindrical solid aluminum pin having a first stem portion and a threaded second portion separated by a middle necked down portion. The test pin threaded portion is inserted into a flowable adhesive such as an epoxy inside a joining pin located in a hole through abutting honeycomb panels and the epoxy is allowed to cure. A force is exerted on the first portion of the test pin until either the test pin separates at the necked down portion or the test pin is dislodged from the joining pin. In the latter case, the test indicates an improper mixture or a poor curing of the adhesive.

Abstract: A method for mounting an insert fastener to accommodate a bolt in lightweight panels is described. A hole is bored in a panel to penetrate the core and upper facial sheet and then is filled with a quick setting resin. A fastener having a flat circular head and central threaded bore is inserted into the hole. Integral with and depending from the head is a cylindrical body with a pair of radial flanges parallel to each other and to the head. The flanges are spaced apart from each other and the head. The edges of the flanges are serrated. Two holes, one on each side of the central bore, are present in the head to allow excess resin potting material to leave the hole in the lightweight panel. A bolt for holding auxiliary structures to the panel is screwed into the central bore.

Abstract: Two arcuate panel sections having a dampening layer between two honeycomb layers form a module which is mounted in multiple elastomeric isolators located within channel members. Support brackets attached to the interior of the aircraft skin support the channels in the overhead area and along the port and starboard deck edge. The module is thereby spaced apart from the aircraft frame. There is a resulting diminution of acoustic transmission from the aircraft frame to its interior passenger area.

Abstract: An improved insert fastener for use in lightweight panels is described. The fastener has a flat circular head overlapping a hole in the panel. Integral with and depending from the head is a cylindrical body with a pair of radial flanges parallel to each other and to the head. The flanges are spaced apart from each other and the head. The edges of the flanges are serrated. A central threaded bore through the head and cylindrical body receives a bolt for holding auxiliary structures to the panel. Two holes, one on each side of the central bore, are present in the head to allow excess epoxy resin potting material to leave the hole in the lightweight panel.

Abstract: A seat adjustment and locking mechanism employs a pedestal permanently affixed to the deck and having a bore on its top frame member to engage a through bolt. The bolt supports a pin pad with a multiplicity of small pins on its top surface. A seat frame bottom wall containing a slot moves around the bolt and pin pad. A panel containing small holes is located within the seat frame. In a relaxed position the panel rests on the pin pad and causes engagement of the pins with the holes on the bottom surface of the panel to secure the seat in a locked position.