Other ‘technology’, as follows: (a) ‘Technology’‘required’ for the ‘development’ or ‘production’ of any of the following gas turbine engine components or systems: 1. Gas turbine blades, vanes or ‘tip shrouds’, made from directionally solidified (DS) or single crystal (SC) alloys and having (in the 001 Miller Index Direction) a stress-rupture life exceeding 400 hours at 1 273 K (1 000 °C) at a stress of 200 MPa, based on the average property values; 2. Combustors having any of the following: a. ‘Thermally decoupled liners’ designed to operate at ‘combustor exit temperature’ exceeding 1 883 K (1 610 °C); b. Non-metallic liners; c. Non-metallic shells; or d. Liners designed to operate at ‘combustor exit temperature’ exceeding 1 883 K (1 610 °C) and having holes that meet the parameters specified by 9E003.c.; 3. Components that are any of the following: a. Manufactured from organic ‘composite’ materials designed to operate above 588 K (315 °C); b. Manufactured from any of the following: 1. Metal ‘matrix’‘composites’; or 2. Ceramic ‘matrix’‘composites’; or c. Stators, vanes, blades, tip seals (shrouds), rotating blings, rotating blisks, or ‘splitter ducts’, that are all of the following: 1. Not specified above; 2. Designed for compressors or fans; and 3. Manufactured from material ‘fibrous or filamentary materials’ with resins; 4. Uncooled turbine blades, vanes or ‘tip-shrouds’, designed to operate at a ‘gas path temperature’ of 1 373 K (1 100 °C) or more; 5. Cooled turbine blades, vanes, ‘tip-shrouds’, designed to operate at a ‘gas path temperature’ of 1 693 K (1 420 °C) or more; 6. Airfoil-to-disk blade combinations using solid-state joining; 7. Gas turbine engine components using ‘diffusion bonding’‘technology’; 8. ‘Damage tolerant’ gas turbine engine rotor components using powder metallurgy materials; 9. Hollow fan blades.