Abstract: 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.

Abstract: A stiffener skeleton that is configured to be mounted to an upper deck of a rotary wing aircraft in a maintenance phase, comprising an upper stiffening structure with a plurality of supporting arms for providing upside stiffening support, and a lateral stiffening structure with a plurality of supporting legs for providing lateral stiffening support, wherein the plurality of supporting arms and the plurality of supporting legs form a self-supporting frame structure.

Abstract: 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.

Abstract: A stiffener skeleton that is configured to be mounted to an upper deck of a rotary wing aircraft in a maintenance phase, comprising an upper stiffening structure with a plurality of supporting arms for providing upside stiffening support, and a lateral stiffening structure with a plurality of supporting legs for providing lateral stiffening support, wherein the plurality of supporting arms and the plurality of supporting legs form a self-supporting frame structure.

Abstract: A commercial vehicle comprises a functional arrangement comprising at least one drive motor for providing at least one working or operating function and a parameterisable electronic control arrangement configured to control the functional arrangement depending on a parameter dataset stored in the control arrangement. A data memory is provided, which is rigidly attached in the vehicle, separate from the control arrangement and in which at least one dataset relevant to the vehicle is stored or can be stored. The control arrangement is configured to read data of the dataset relevant to the vehicle from the data memory and/or to write data to the data memory for recording in the dataset relevant to the vehicle or to update the dataset relevant to the vehicle.

Abstract: For a commercial vehicle, in particular for a fork-lift truck (10) or industrial truck, comprising: a functional arrangement comprising at least one drive motor for providing at least one working or operating function including a travelling function; and a parameterisable electronic control arrangement (12), which is configured or programmed to control the functional arrangement depending on a parameter dataset stored in the control arrangement in relation to switching on or off the working or operating function or a respective working or operating function and/or in relation to a type of implementation of the working or operating function or a respective working or operating function.