Abstract: An aircraft component assembly system (10; 10?; 10?) for the assembly of an interior component, a pipe and/or an electric line in an aircraft comprises at least one arc-shaped frame element (12; 12?; 12?), a connection element (32) that extends between a first and a second end of the frame element (12; 12?; 12?), a fastening apparatus for fastening the interior component, the pipe and/or the electric line to the frame element (12; 12?; 12?) and/or the connection element (32), and a first guide device (46) that is provided on the frame element (12; 12?; 12?) and/or the connection element (32) and is devised to interact with a second guide device (52), which is complementary to the first guide device (46) and provided on an aircraft structure (40), in such a way that the aircraft component assembly system (10; 10; 10?) is connectable to the aircraft structure (40) in a manner displaceable relative to the aircraft structure (40).

Abstract: A frame element (10; 10?) for use in an aircraft air-conditioning system is attachable to an aircraft structure (36) and includes at least one strut (12, 14, 16, 18; 12?, 14?, 16?) which is formed at least in sections as a hollow cylinder, wherein an air inlet connection (12a, 14a; 12a?, 14a?) of the at least one section-wise hollow cylindrically formed strut (12, 14, 16, 18; 12?, 14?, 16?) of the frame element (10; 100 is connectable to an air outlet duct of an aircraft air-conditioning unit, and an air outlet connection (12b, 14b; 12b?, 14b?) of the at least one section-wise hollow cylindrically formed strut (12, 14, 16, 18; 12?, 14?, 16?) of the frame element (10; 100 is connectable to an air outlet opening terminating in a cabin region of an aircraft.

Abstract: In a replacement gate approach in sophisticated semiconductor devices, a tantalum nitride etch stop material may be efficiently removed on the basis of a wet chemical etch recipe using ammonium hydroxide. Consequently, a further work function adjusting material may be formed with superior uniformity, while the efficiency of the subsequent adjusting of the work function may also be increased. Thus, superior uniformity, i.e., less pronounced transistor variability, may be accomplished on the basis of a replacement gate approach in which the work function of the gate electrodes of P-channel transistors and N-channel transistors is adjusted after completing the basic transistor configuration.

Abstract: During a manufacturing sequence for forming a sophisticated high-k metal gate structure, a cover layer, such as a silicon layer, may be deposited on a metal cap layer in an in situ process in order to enhance integrity of the metal cap layer. The cover layer may provide superior integrity during the further processing, for instance in view of performing wet chemical cleaning processes and the subsequent deposition of a silicon gate material.

Abstract: The work function of a high-k gate electrode structure may be adjusted in a late manufacturing stage on the basis of a lanthanum species in an N-channel transistor, thereby obtaining the desired high work function in combination with a typical conductive barrier material, such as titanium nitride. For this purpose, in some illustrative embodiments, the lanthanum species may be formed directly on the previously provided metal-containing electrode material, while an efficient barrier material may be provided in the P-channel transistor, thereby avoiding undue interaction of the lanthanum species in the P-channel transistor.

Abstract: A frame element (10; 10?) for use in an aircraft component assembly system (46) is attachable to an aircraft structure (36) and comprises at least one fastening device for fastening at least one aircraft interior component (34) or at least one insulation pack (52) to the frame element (10; 10?). An aircraft component assembly system (46) comprises a plurality of such frame elements (10; 10?). In a method of fitting a component (34, 52) in an aircraft, a frame element (10; 10?) is provided. At least one interior component (34) or at least one insulation pack (52) is fastened to the frame element (10; 10?). Then the frame element (10; 10?) having the at least one interior component (34) or the at least one insulation pack (52) fastened thereto is attached to an aircraft structure (36).

Abstract: A frame element (10) for use in an aircraft component installation system (46) is attachable to an aircraft structure (36) and comprises a storage bin fastening device which is designed to fasten a storage bin (26) at various positions on the frame element (10). A storage bin (26) for use in an aircraft comprises a complementary device to the storage bin fastening device of the frame element (10), in order to fasten the storage bin (26) at various positions on the frame element (10). In a method for the installation of a storage bin (26) in an aircraft a frame element (10) is provided. A storage bin (26) is fastened in a desired position on the frame element (10). The frame element (10) is attached to an aircraft structure (36).