# US 8,740,151 B1 · Adjustable splice fitting for shimless connection of structual members > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 8,740,151 B1 - Document ID: US8740151B1 - Status: Granted - Kind: B1 - Application number: 13/342,418 - Filed: 2012-01-03 - Granted: 2014-06-03 - Earliest claimed: 2012-01-03 - Assignees: The Boeing Company - Applicants: Richard R. Rosman; Branko Lakic; Kenneth Cominsky; Douglas Marciniak; Steven Edward Pearson - Inventors: Richard R. Rosman; Branko Lakic; Kenneth Cominsky; Douglas Marciniak; Steven Edward Pearson - Web page: https://patentgrep.com/patent/US8740151B1 ## CPC - B64C 1/18: Floors - B64C 1/061: {Frames} - B64C 1/064: {Stringers; Longerons} - B64C 1/065: {Spars} - B64C: AEROPLANES; HELICOPTERS ## Abstract A fuselage section may include a structural member and a frame member having a stub frame extending over the structural member. The stub frame may have a web. The fuselage section may include an intercostal extending from a terminal end of the stub frame and having an end flange. The fuselage section may additionally include an adjustable splice fitting having a web, a lower flange, and an end flange being mountable in faying contact with respective ones of the stub frame web, the structural member, and the intercostal end flange. ## Claims ### Claim 1 A fuselage, comprising: a fuselage section including a structural member; a frame member including a stub frame extending over the structural member and having a web; an intercostal extending from a terminal end of the stub frame and having an end flange; and an adjustable splice fitting having a web, a lower flange, and an end flange being mountable in faying contact with respective ones of the stub frame web, the structural member, and the intercostal end flange. ### Claim 2 (depends on 1) The fuselage of claim 1 wherein: the adjustable splice fitting is adjustably positionable in a manner such that the end flange and the lower flange are positionable in substantially faying contact with respective ones of the intercostal end flange and the structural member. ### Claim 3 (depends on 1) The of claim 1 wherein: the web, the lower flange, and the end flange of the adjustable splice fitting are mechanically fastened to respective ones of the stub frame web, the structural member, and the intercostal end flange. ### Claim 4 (depends on 1) The fuselage of claim 1 wherein the stub frame has an upper flange, the intercostal having an upper flange, the fuselage further comprising: an upper chord splice fitting interconnecting the upper flange of the stub frame to the upper flange of the intercostal. ### Claim 5 (depends on 1) The fuselage of claim 1 wherein the intercostal has a lower flange, the fuselage further comprising: a lower chord splice strap mounted to a lower side of the structural member and interconnecting the lower flange of the adjustable splice fitting to the lower flange of the intercostal. ### Claim 6 (depends on 1) The fuselage of claim 1 further including: at least one continuous beam mounted to the structural member; and the intercostal terminating at the continuous beam. ### Claim 7 (depends on 1) The fuselage of claim 1 wherein the fuselage has a longitudinal axis, the intercostal has an upper flange, the fuselage further including: at least one beam segment mounted to the structural member and being oriented generally parallel to the longitudinal axis, the beam segment including an upper flange; and at least one beam splice strap interconnecting the beam segment upper flange to the intercostal upper flange. ### Claim 8 (depends on 1) The fuselage of claim 1 further including: a stiffener mounted to a lower side of the structural member and overlapping at least a portion of a length of the intercostal. ### Claim 9 (depends on 1) The fuselage of claim 1 wherein: the intercostal is generally tapered in height along a laterally inward direction from the stub frame. ### Claim 10 A fuselage, comprising: a fuselage section including a structural member and a fuselage skin; a frame member including a vertical frame and a stub frame, the vertical frame being coupled to the skin, the stub frame extending laterally inwardly from the vertical frame over the structural member and having an upper flange and a web; an intercostal extending laterally inwardly from the stub frame and being mounted to the structural member, the intercostal having an upper flange, a lower flange, and a web having an end flange; and an adjustable splice fitting interconnecting the stub frame to the structural member and to the intercostal, the adjustable splice fitting having a web, a lower flange, and an end flange being mountable in faying contact with respective ones of the frame member web, the structural member, and the intercostal end flange; an upper chord splice fitting connecting the upper flange of the stub frame to the intercostal; and a lower chord splice strap mounted to a lower side of the structural member and connecting the lower flange of the adjustable splice fitting to the lower flange of the intercostal. ### Claim 11 A method of assembling an aircraft, comprising the steps of: providing a fuselage section including a structural member; extending a stub frame inwardly over the structural member, the stub frame having a web and a terminal end; mounting an intercostal to the structural member such that a terminal end of the intercostal is positioned adjacent to the terminal end of the stub frame, the intercostal having an end flange; interconnecting the stub frame to the structural member and to the intercostal using an adjustable splice fitting having a web, a lower flange, and an end flange; and adjustably positioning the adjustable splice fitting such that the web, the lower flange, and the end flange of the adjustable splice fitting are placed in faying contact with respective ones of the frame member web, the structural member, and the intercostal end flange. ### Claim 12 (depends on 11) The method of claim 11 further comprising the step of: interconnecting the stub frame to the structural member and to the intercostal using a single one of the adjustable splice fittings. ### Claim 13 (depends on 11) The method of claim 11 further comprising the step of: adjusting the position of the adjustable splice fitting along the stub frame web in a manner such that the end flange and the lower flange are positioned in substantially faying contact with respective ones of the intercostal end flange and the structural member. ### Claim 14 (depends on 11) The method of claim 11 further comprising the step of: interconnecting an upper flange of the stub frame to an upper flange of the intercostal using an upper chord splice fitting. ### Claim 15 (depends on 11) The method of claim 11 further comprising the step of: interconnecting the lower flange of the adjustable splice fitting to a lower flange of the intercostal using a lower chord splice strap mounted to a lower side of the structural member. ### Claim 16 (depends on 11) The method of claim 11 further comprising the steps of: mounting at least one beam segment to the structural member, the beam segment being oriented in non-parallel relation to the intercostal and including an upper flange; and interconnecting the beam segment upper flange to an upper flange of the intercostal using a beam splice strap. ### Claim 17 (depends on 11) The method of claim 11 wherein the fuselage has a longitudinal axis, the method further comprising the step of: coupling the intercostal to a continuous beam supporting the structural member. ### Claim 18 (depends on 17) The method of claim 17 further comprising the step of: orienting the continuous beam generally parallel to a longitudinal axis of the fuselage. ### Claim 19 (depends on 11) The method of claim 11 further comprising the step of: tapering the intercostal in height along a laterally inward direction from a terminal end of the stub frame. ### Claim 20 (depends on 11) The method of claim 11 further comprising the steps of: mounting a stiffener to a lower side of the structural member; and overlapping the stiffener with at least a portion of a length of the intercostal.