US 9,809,325 B2
Aircraft system component carrier system and mounting method
Sabrina Moje, Hamburg (DE); and Dirk Humfeldt, Hamburg (DE)
Assigned to AIRBUS OPERATIONS GMBH, Hamburg (DE)
Filed by AIRBUS OPERATIONS GMBH, Hamburg (DE)
Filed on Jun. 19, 2013, as Appl. No. 13/922,057.
Application 13/922,057 is a continuation of application No. PCT/EP2011/006443, filed on Dec. 20, 2011.
Claims priority of provisional application 61/426,579, filed on Dec. 23, 2010.
Claims priority of provisional application 61/426,596, filed on Dec. 23, 2010.
Claims priority of application No. 10 2010 055 962 (DE), filed on Dec. 23, 2010; and application No. 10 2010 055 995 (DE), filed on Dec. 23, 2010.
Prior Publication US 2013/0277901 A1, Oct. 24, 2013
Int. Cl. B64F 5/00 (2017.01); B64C 1/06 (2006.01); B64D 11/00 (2006.01); B64F 5/10 (2017.01)
CPC B64F 5/0009 (2013.01) [B64C 1/06 (2013.01); B64C 1/068 (2013.01); B64D 11/00 (2013.01); B64D 11/003 (2013.01); B64F 5/10 (2017.01); Y10T 29/49764 (2015.01); Y10T 29/49826 (2015.01)] 10 Claims
OG exemplary drawing
 
1. An aircraft system component carrier system comprising:
a plurality of aircraft system component carrier modules,
at least one aircraft system component, which is fastened by aircraft system component holders to the plurality of the aircraft system component carrier modules, and
a plurality of aircraft structural elements of a fuselage upper shell that are disposed successively along the longitudinal axis of the fuselage upper shell, wherein each of the aircraft structural elements is formed by a rib of the fuselage upper shell, wherein each of the plurality of aircraft system component carrier modules is fastened by a structural holder to one of the aircraft structural elements of the fuselage upper shell, wherein the aircraft structural elements of the fuselage upper shell are connected to one another by stringers extending along a longitudinal axial of the fuselage upper shell, wherein the aircraft system component carrier modules, the aircraft system components, the stringers and the aircraft structural elements form a pre-assembled assembly group, and wherein the pre-assembled assembly group is configured to be connected to a bottom shell and lateral areas of an aircraft fuselage, when assembling the aircraft, wherein the pre-assembled assembly group is configured to be handled independently from the bottom shell and lateral areas of the aircraft fuselage prior to its connection to the bottom shell and lateral areas of the aircraft fuselage.