Abstract: Structural panels for use in manufacturing fuselage bodies and other aircraft structures are disclosed herein. In one embodiment, a monolithic integrated structural panel is configured to include a skin, an array of stiffeners and an array of frames which are preferably arranged in a mutually orthogonal layout, without the need of cut-outs in any of the crossing elements. One advantage of the disclosed embodiments is that the frame and stringer members have continuous flanges and spliced webs. The disclosed embodiments herein are compatible with composite materials technology, offering another advantage, namely the possibility of manufacturing integrated products in a single cure (“one-shot”) cycle. A structure of composite materials, e.g. carbon fiber reinforced plastics, typically comprises a skin panel, reinforced by frame and stringer members.

Abstract: A simplified air bleed balancing control system for a pair of aircraft gas turbine engines reduces the number of pressure transducers and differential pressure transducers. Advantages include lower weight, less expensive system, better total system MTBF (mean time before failure), acceptable differential pressure transducer drift identification and compensation by the digital controller, and fewer maintenance tasks.

Abstract: Modular configuration for an aircraft interior floor plan design is provided by an fuselage having starboard and port side attachment rails disposed longitudinally parallel to one another. Each of the starboard and port side attachment rails are comprised of outboard and inboard rails and a center rail positioned therebetween. A plurality of interior fixtures are provided with fixed attachment posts asymmetrically oriented relative to a longitudinal centerline plane of the fixture. Such fixtures can therefore be attached to predetermined pairs of the starboard and port side attachment rails to provide for a desired configuration of the fixtures within the fuselage.

Abstract: Auxiliary fuel tanks are provided with an inner barrier wall defining an interior volume for containing aircraft fuel, an outer barrier wall adjacent the inner barrier wall so as to define a space therebetween, and a drain part having a port in fluid communication with the space to allow leaked fuel within the space to be discharged therefrom. The drain part may be positioned at a corner junction between at least side and bottom walls of the outer barrier wall. In some advantageous embodiments, the drain part is positioned at a corner junction between the side wall, the bottom wall and an end wall of the outer barrier wall. One or more drain parts may be provided on each auxiliary aircraft fuel tank.

Abstract: Friction plug welding methods and systems plug a hole extending through a component part from front and back faces thereof. A sacrificial plate having an opening therethrough may be positioned against the back face of the component part with assistance from a restraint part (which is also preferably provided with a space of sufficient dept to receive a terminal end of the male plug) so that the opening is coaxially aligned with the hole to be plugged. Upon advancing a male plug of a plug rod into the hole under friction plug welding conditions, a friction weld region will therefore be formed between the male plug and defining surfaces of both the hole extending through the component part and the opening extending through the sacrificial plate. The plug rod may include an annular shoulder flange which defines a plane parallel to the front face of the component part so that flash flow from the friction welding will be displaced laterally of the hole. The male plug may be frustroconically shaped.

Abstract: An aircraft fuselage assembly of basic construction in composite materials employs metallic frames with reduced quantity of metallic shear ties attached to the composite stiffened skin, formed by two or more longitudinal panels, spliced with longitudinal metallic splice members. Typically, the latitudinal metallic frame members are fastened to the inward outstanding flange portion of the composite stringers which are in turn integrated to the skin. As such, the frame members are spaced from (floating over) the fuselage skin. An electrical path may thus be established so as to protect the fuselage structure against the impact of electrical discharges commonly encountered in the atmosphere by providing metallic shear ties interconnecting the frame and splice members so as to span the space therebetween.

Abstract: An exemplary implementation of an aircraft interior table includes a base unit which includes a storage compartment having laterally projecting ends. A bi-fold table comprised of a table panels is horizontally stowed and supported on the upper surface of the base unit. Thus, in a stowed condition, one of the table panels is folded so as to be sandwiched between the other of the table panels and the upper surface of the base unit. The edge of the other table panel opposite to its hinged edge adjoining both table panels is pivotally connected to the base unit by means of a primary hinge. In use, the table panels may be rotated as a unit about the primary hinge so as to achieve an intermediate fold-out condition. While in such a position, the table will present itself half-sized so as to provide the associated aircraft seat occupant with minimal forward obstruction.

Abstract: Adapter devices are provided that, when installed on an aircraft seat track break area, allow for the installation and/or positioning of passenger seats thereat. The devices include a main body having two portions. One end of the portion is integrated to a fork-shaped part 2 which defines a half-opening 3. Close to the end of the other portion there is provided a pair of half-tabs which are symmetrically disposed in relation to one another on each side of the body. Pairs of symmetrically disposed semi-circular tabs are provided on the main body. Threaded pass-through holes are located one of the body portions so as to threadably accommodate retaining discs in the form of screw screws heads provided with screws which are installed in the threaded holes.

Abstract: Impact tools (e.g., riveters) are provided with anti-vibration protection by a cushion pad and an elastomeric sheath. The cushion pad may be formed of a shape-conformable elastomeric material which is adapted to being conformably placed onto a rear surface of the impact tool handle, while the elastomeric sheath is preferably sized and configured so as to removeably envelop the impact tool handle and the cushion pad. The cushion pad may have a widthwise dimension such that lateral edge regions of the cushion pad are adapted to being at least partly folded over and onto respective side surface portions of the impact tool handle. In some implementations, the cushion pad has a lengthwise dimension such that the cushion pad is adapted to being positioned adjacent to a rear end of the impact tool housing and extends therefrom to a position adjacent a lower surface of the impact tool handle.

Abstract: Aircraft fuel tanks, systems and methods increase an aircraft's fuel capacity. The fuel tanks have a tank body defining an interior space for holding aircraft fuel, and a relief manifold assembly operatively associated to the tank body to prevent an overpressure condition within the interior space of the fuel tank body. The relief manifold assembly preferably includes a buffer vessel defining a buffer chamber in fluid communication with the interior space defined by the fuel tank body. The buffer vessel may advantageously be fixed to the tank body within the interior space thereof. At least one of a fuel vent manifold assembly for venting the interior space of the fuel tank and a fuel refill/transfer manifold assembly for supplying fuel to and withdrawing fuel from the interior space of the fuel tank. At least one control box (e.g.