US 11,912,402 B2
Rotary wing aircraft with a firewall arrangement
Aurelien Vayssiere, Niederschoenenfeld GT Feldheim (DE); Hubert Neukirch, Dilligen (DE); Markus Kammerer, Alerheim (DE); and Bernhard Rein, Rain Am Lech (DE)
Assigned to AIRBUS HELICOPTERS DEUTSCHLAND GmbH, Donauworth (DE)
Filed by AIRBUS HELICOPTERS DEUTSCHLAND GMBH, Donauworth (DE)
Filed on Feb. 7, 2022, as Appl. No. 17/666,317.
Claims priority of application No. 21400008 (EP), filed on Apr. 9, 2021.
Prior Publication US 2022/0332411 A1, Oct. 20, 2022
Int. Cl. B64C 27/00 (2006.01); B64C 1/12 (2006.01); B64D 27/26 (2006.01); B64D 45/00 (2006.01); B64C 27/06 (2006.01)
CPC B64C 27/006 (2013.01) [B64C 1/12 (2013.01); B64C 27/00 (2013.01); B64D 27/26 (2013.01); B64D 45/00 (2013.01); B64C 27/06 (2013.01); B64D 2045/009 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A rotary wing aircraft comprising:
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;
a firewall arrangement comprising a front firewall;
wherein the aircraft upper deck comprises an engine accommodating region with the firewall arrangement arranged therein, the engine accommodating region comprising an engine accommodating compartment bounded in part by the firewall arrangement, the engine accommodating region accommodating at least one aircraft engine within the engine accommodating compartment such that the firewall arrangement defines a fire proof separation and a flammable fluids tightness at least between the at least one aircraft engine and the aircraft interior region;
the firewall arrangement comprises within the engine accommodating compartment at least one gasket, the at least one gasket being removably attached within the engine accommodating compartment to the front firewall for tightening pass-through, through the front firewall, of a torque tube that connects the at least one aircraft engine to a main gear box of the rotary wing aircraft that is outside of the engine accommodating compartment; and
the at least one gasket comprises at least two fire proof shells that are removably attached to each other to form a tube-shaped structure for accommodating therein the torque tube, and a ring-shaped flexible fire proof bellows which forms a cuff-like structure for accommodating therein the torque tube and that is removably mounted to the at least two fire proof shells and configured to compensate movements of the torque tube relative to the firewall arrangement, the ring-shaped flexible fire proof bellows being attached within the engine accommodating compartment to an associated counterpart of the at least one aircraft engine by mushroom head pins.