A fastening system includes a plurality of fasteners having different sizes, and is provided with a pressurizing pump which pressurizes a fluid to a prescribed pressure, a plurality of pressurizing units which each have a pressure receiving surface, are each disposed in a position capable of pressurizing each respective fastener, and which receive the fluid on the pressure receiving surface to pressurize each fastener. A supply system includes a base end connected to the pressurizing pump and a plurality of branch ends connected to each pressurizing unit, which branches from the base end toward the branch ends, and which is capable of supplying the fluid from the base end throughout the branch ends. Each pressure receiving surface has an individual pressure receiving surface area corresponding to the corresponding size, and the fluid is supplied at the prescribed pressure from the base end throughout the pressure receiving surfaces.

Embodiments of the present invention are related to a Y-shaped airliner including an elongate main fuselage bifurcated into two outwardly angled fuselage extensions defined as a first fuselage extension and a second fuselage extension. The airliner includes a NACA inlet, a medial fan, a pair of forward canard wings, and a pair of side wings each including at least one engine. The medial fan is positioned between the first fuselage extension and the second fuselage extension. The NACA inlet is positioned on the main fuselage rear skin and is structured to feed airflow into the medial fan.

A replaceable web structure for an aircraft frame is described and includes a plurality of structural members fabricated from a first type of material, the replaceable web structure comprising a plurality of web members fabricated from thin sheets of a second type of material, wherein each of the web members is fastened to a web frame of one of the structural members to replace a web portion of the one of the structural members; wherein the second type of material is lighter weight than the first type of material; and wherein the second type of material is more heat-resistant than the first material.

A door system with a deceleration mechanism may be adapted to control an opening of a door module that separates compartments of an aircraft and includes a door panel and a door frame. During the opening of the door module, the door panel performs a rotational movement 389 above a floor structure of the aircraft. The deceleration mechanism is operable in a normal operation mode and a deceleration mode and comprises a hinge, a wedge-shaped component that is rotatably attached to the hinge, and an activation device. The activation device is coupled to the wedge-shaped component and switches the deceleration mechanism from operating in the normal operation mode to operating in the deceleration mode when a difference in pressure between the compartments exceeds a predetermined threshold.

A door system with a deceleration mechanism may be adapted to control an opening of a door module that separates compartments of an aircraft and includes a door panel and a door frame. During the opening of the door module, the door panel performs a rotational movement 389 above a floor structure of the aircraft. The deceleration mechanism is operable in a normal operation mode and a deceleration mode and comprises a hinge, a wedge-shaped component that is rotatably attached to the hinge, and an activation device. The activation device is coupled to the wedge-shaped component and switches the deceleration mechanism from operating in the normal operation mode to operating in the deceleration mode when a difference in pressure between the compartments exceeds a predetermined threshold.

The invention provides a firefighting float plane having a fuselage and two floats mounted to the fuselage. The fuselage has a water tank with open and closed configurations. In some embodiments, the water tank is integrated into the fuselage, and/or both the water tank and the fuselage have a generally triangular cross-sectional configuration. The water tank has a closed bottom in its closed configuration and an open bottom in its open configuration. In some embodiments, the plane has specified ratio of water tank holding capacity to total power of two engine assemblies. It can optionally also have the above-noted fuselage configuration, tank configuration, or both. In some embodiments, the plane has dual propellers, two engine assemblies, and two tail booms, optionally together with specified ratio of water tank holding capacity to total power of two engine assemblies. It may also have the above-noted fuselage configuration, tank configuration, or both.

The invention relates to a thin metal sheet which is made of an alloy based on substantially recrystallized aluminum and which has a thickness of 0.25 to 12 mm, the alloy comprising, in percent by weight, Cu 3.4-4.0; Mg 0.5-0.8; Mn 0.1-0.7; Fe #0.15; Si #0.15; Zr #0.04; Ag #0.65; Zn #0.5; inevitable impurities #0.05 each and #0.15 in total, the remainder consisting of aluminum. The invention also relates to a process for manufacturing such a metal sheet and to the use thereof as a fuselage panel or sheet metal for the production of composite products such as fiber metal laminates (FML) for wing or fuselage applications in the aeronautical industry.

The invention relates to a thin metal sheet which is made of an alloy based on substantially recrystallized aluminum and which has a thickness of 0.25 to 12 mm, the alloy comprising, in percent by weight, Cu 3.4-4.0; Mg 0.5-0.8; Mn 0.1-0.7; Fe #0.15; Si #0.15; Zr #0.04; Ag #0.65; Zn #0.5; inevitable impurities #0.05 each and #0.15 in total, the remainder consisting of aluminum. The invention also relates to a process for manufacturing such a metal sheet and to the use thereof as a fuselage panel or sheet metal for the production of composite products such as fiber metal laminates (FML) for wing or fuselage applications in the aeronautical industry.

A single piece gasket is disclosed having a skeletal member, typically metallic, and a pliable body. The pliable body includes a first portion having a first firmness and a second perimeter portion have a firmer consistency. When such a composite body is placed under compression, the perimeter will tend to limit the flow of the softer inner material past the firmer perimeter region or portion of the gasket. In this manner, creep or overrun of the less firm portion material will be reduced.

A single piece gasket is disclosed having a skeletal member, typically metallic, and a pliable body. The pliable body includes a first portion having a first firmness and a second perimeter portion have a firmer consistency. When such a composite body is placed under compression, the perimeter will tend to limit the flow of the softer inner material past the firmer perimeter region or portion of the gasket. In this manner, creep or overrun of the less firm portion material will be reduced.