Patent ID: 9745043
Date: 2017-08-29
CPC Classifications: B64C,Y10T

Claim:
1. An aircraft fuselage frame element comprising: a heel; a footing; at least one core, which comprises one or more through-openings for passing of a fuselage stiffener through at least a portion of the at least one core; and a tab associated with at least one of the one or more through-openings for fastening the aircraft fuselage frame element onto the fuselage stiffener, wherein the tab: wherein the aircraft fuselage frame element is configured to reinforce a fuselage skin of an aircraft fuselage, and wherein, in an area of the fuselage stiffener, the aircraft fuselage frame element is not, when assembled with the fuselage stiffener in an aircraft fuselage, directly joined to the fuselage skin.