An aircraft comprising a structure comprising a leakproof tank delimited by walls, of which at least one is in contact with the air outside the aircraft, and filled partly with a two-phase heat-transfer fluid, a fuel cell that is passed through by a heat-transfer fluid, and a line which takes the heat-transfer fluid at an output of the fuel cell and which reintroduces this heat-transfer fluid at an input of the fuel cell. The line passes through the leakproof tank immersed in the heat-transfer fluid in liquid phase.

Systems and methods for loading a cargo aircraft are described. The system includes at least one rail disposed in an interior cargo bay of a cargo aircraft that extends at an angle relative to an interior bottom contact surface of a forward portion of the interior cargo bay, through a kinked portion and an aft portion of the interior cargo bay. Payload-receiving fixtures are described that can be used in conjunction with the rail system, allowing for large cargo, such as wind turbine blades, to be transported by aircraft. Methods of loading a cargo aircraft can include advancing the large payload into the interior cargo bay of the aircraft such that at least one of the payload-receiving fixtures rises relative to a plane defined by the interior bottom contact surface of the forward portion of the interior cargo bay. Various systems, methods, components, and related tooling are also provided.

An isolator fitting for an opening in a metallic rib of an aircraft wing. The isolator fitting has first isolator mountable to the rib to position a first isolator opening in alignment with the opening of the rib. A second isolator is mountable to the rib and has a nut housing segment defining a second isolator opening to be positioned in alignment with the opening of the rib. A conduit extends between a first end and a second end, and a nut is mountable about an outer surface of the conduit to abut against the first isolator and mount the conduit thereto. The conduit is positionable to extend through the opening of the rib and through the first and second isolator openings to position the nut within the nut housing segment of the second isolator such that the nut housing segment is positioned between the nut and the rib.

An isolator fitting for an opening in a metallic rib of an aircraft wing. The isolator fitting has first isolator mountable to the rib to position a first isolator opening in alignment with the opening of the rib. A second isolator is mountable to the rib and has a nut housing segment defining a second isolator opening to be positioned in alignment with the opening of the rib. A conduit extends between a first end and a second end, and a nut is mountable about an outer surface of the conduit to abut against the first isolator and mount the conduit thereto. The conduit is positionable to extend through the opening of the rib and through the first and second isolator openings to position the nut within the nut housing segment of the second isolator such that the nut housing segment is positioned between the nut and the rib.

An assembly with an aircraft fuel tank is disclosed having a captive nut with an internal thread, a secondary structure, and a fastener which secures the secondary structure to the fuel tank. The fastener has a shaft which passes through the secondary structure and has an external thread coupled to the internal thread of the captive nut. The fuel tank has a fuel tank element with a hole, and the captive nut has a sleeve which is located in the hole with an interference fit between an outer surface of the sleeve and an inner surface of the wall of the hole.

An assembly with an aircraft fuel tank is disclosed having a captive nut with an internal thread, a secondary structure, and a fastener which secures the secondary structure to the fuel tank. The fastener has a shaft which passes through the secondary structure and has an external thread coupled to the internal thread of the captive nut. The fuel tank has a fuel tank element with a hole, and the captive nut has a sleeve which is located in the hole with an interference fit between an outer surface of the sleeve and an inner surface of the wall of the hole.

An integral sealant O-ring for sealing fasteners in mating surfaces of a fuel tank includes a fastener hole through an inner mating surface and an outer mating surface, the fastener hole has a chamfer along a fay interface between the mating surfaces. A layer of sealant is applied along the fay interface, and upon tightening of the fastener, the inner and outer mating surfaces are pulled together squeezing the sealant into the chamfer and forming an integral sealant O-ring around the fastener. A method of forming an integral sealant O-ring includes forming a chamfer in a first mating surface substantially concentric with a fastener hole, applying a layer of sealant along the first mating surface, pulling together the first mating surface with a second mating surface by tightening a fastener to trap sealant within the chamfer for forming an integral sealant O-ring.

An integral sealant O-ring for sealing fasteners in mating surfaces of a fuel tank includes a fastener hole through an inner mating surface and an outer mating surface, the fastener hole has a chamfer along a fay interface between the mating surfaces. A layer of sealant is applied along the fay interface, and upon tightening of the fastener, the inner and outer mating surfaces are pulled together squeezing the sealant into the chamfer and forming an integral sealant O-ring around the fastener. A method of forming an integral sealant O-ring includes forming a chamfer in a first mating surface substantially concentric with a fastener hole, applying a layer of sealant along the first mating surface, pulling together the first mating surface with a second mating surface by tightening a fastener to trap sealant within the chamfer for forming an integral sealant O-ring.

An aircraft includes a fuselage defining a longitudinal axis between a forward end and an aft end. The aircraft includes an electrical system having an electric storage. The electric storage is positioned within the fuselage.

The present disclosure relates to a secondary airfoil apparatus, system and method for improving lift, takeoff, landing and aerodynamic performance of a floatplane. The secondary airfoil can be integrated into the floatplane during manufacture, or retrofitted to an existing floatplane after manufacture. The secondary airfoil is itself of sufficient structural rigidity to withstand any and all forces added by the airfoil during floatplane operation. The secondary airfoil is fixedly attached between the floats of the floatplane, and are purposefully not attached to spreader bars that can exist typically between the floats. The secondary airfoil can be arranged at an optimal angle of incidence and vertical lift position relative to the primary airfoil, or wing of the aircraft, and relative to the floats center of gravity and drag for optimal maneuverability of the floatplane.