A hybrid electric powerplant can include an electric motor configured to convert electrical energy into kinetic energy to turn a propulsor, and a heat engine configured to convert a fuel into kinetic energy to turn the propulsor. The powerplant can include a firewall disposed around at least one of the electric motor or the heat engine to create an electric motor fire zone and a heat engine fire zone separate from the electric motor fire zone such that the electric motor is protected against a heat engine fire, and vice versa.

A rotary wing aircraft with a fuselage that forms an aircraft interior region, the fuselage comprising an upper primary skin that separates the aircraft interior region from an aircraft upper deck arranged above the fuselage, wherein the aircraft upper deck comprises an engine accommodating region with a firewall arrangement, the engine accommodating region accommodating at least one aircraft engine within the firewall arrangement, wherein the firewall arrangement comprises at least one gasket for tightening pass-through of a torque tube that connects the at least one aircraft engine to a main gear box of the rotary wing aircraft, and wherein the at least one gasket comprises at least two fire proof shells and a ring-shaped flexible fire proof bellows.

Fireworthy sealants may have a variety of compositions and be made by a variety of techniques. In certain implementations, a fireworthy sealant may include a body comprised of a cured, tacky, soft, deformable non-adhesive gel. The gel body may have an upper surface, a lower surface, and a perimeter, wherein the upper and lower surfaces of the gel body, in an uncompressed state, define a body thickness. The sealant may, in an uncompressed state, be dimensioned to fit in a first opening between a wall and an aircraft component surface and deformable when under compression to fit in a second opening, smaller than the first opening. The sealant may be flame retardant and produce low smoke density and low smoke toxicity.

A method of additively manufacturing a fire and overheat detection system (FODS) clamp onto a rail tube is provided. The method includes building a base of a clamp body on the rail tube, sequentially building portions of a locking feature and holders of the clamp body on the base and sequentially building remaining portions of the holders and flanges forming grooves at each of the holders of the clamp body on the base.

An aircraft propulsion unit is described. The unit may include a gas generator with a fan surrounded by a casing. A nacelle may extend around the casing and define an annular compartment with the casing wherein some equipment may be housed. An air inlet may be configured so a ventilation air flow penetrates inside the compartment. An air outlet may be configured so a ventilation air flow is evacuated from the compartment. The propulsion unit may also include an air flow adjustment regulator. The air flow adjustment regulator may be configured to maintain a nominal value of the ventilation air flow circulating through at least one of the air inlet and of the air outlet under nominal operating conditions, and to reduce the value of this ventilation air flow when a fire is detected inside the compartment.

A heatable leading-edge apparatus for an aircraft having a main structure and a heating layer. The heating layer comprises a fiber composite layer with fibers and with a matrix which surrounds the fibers. The fibers are at least partially formed as conducting fibers, such as carbon fibers, with an electrically insulating coating. Owing to the conducting fibers, which act as electrical heating elements, a desired surface temperature can be established on an outer side of the leading-edge apparatus.

An apparatus for inerting a space includes a metal-air battery, a feed channel for the introduction of air from an air source to the metal-air battery, and a discharge channel for the discharge of air from the metal-air battery to a volume of the space. A control unit controls an electrochemical reaction of the metal-air battery as a function of a fire situation within the space. A method for inerting a space, an inerting system, an inerting method and an aircraft or spacecraft are also provided.

An auxiliary power unit for an aircraft. It includes an air compressor coupled to an air-drawing device for drawing in air from outside the aircraft, the compressor supplying compressed air to a manifold. The manifold is configured to supply air to an environmental control system and a start-up module of at least one propulsion system of the aircraft running on hydrogen. The manifold is also configured to supply air to a fuel cell stack arranged to provide an electric generation function configured to power non-propulsive systems of the aircraft, the fuel cell stack also being supplied with hydrogen from a tank supplying hydrogen to the at least one propulsion system of the aircraft.

An equipment dry bay is provided. The equipment dry bay includes at least one partition that subdivides the equipment dry bay into a plurality of compartments, wherein the at least one partition includes a plate, and at least one flame arrestor positioned within the plate and providing vapor and fluid communication between a first compartment and a second compartment of the plurality of compartments, the at least one flame arrestor configured to vent combustion gases in the first compartment into the second compartment.

The present disclosure provides a system, method, and apparatus for a protective finish for an airfoil. In one or more embodiments, the disclosed method involves providing a sheath, and applying the sheath to the surface of the airfoil. In one or more embodiments, the sheath wraps around the surface of the airfoil from the leading edge of the airfoil towards the trailing edge of the airfoil. In at least one embodiment, the sheath covers approximately 50 percent to approximately 70 percent of the chord length of the airfoil. In some embodiments, the sheath is manufactured from at least one polymer, such as a polyurethane and/or a floropolymer. In one or more embodiments, the airfoil is a winglet, a raked wing tip, and/or a wing.