‘Composite’ structures or laminates consisting of an organic ‘matrix’ and materials as follows: Note: Does not apply to ‘composite’ structures or laminates, made from epoxy resin impregnated carbon ‘fibrous or filamentary materials’, for the repair of ‘civil aircraft’ structures or laminates, having all of the following: — An area not exceeding 1 m 2 ; — A length not exceeding 2,5 m; — A width exceeding 15 mm. Does not apply to semi-finished items, specially designed for purely civilian applications as follows: sporting goods, automotive industry, machine tool industry, medical applications. Does not apply to finished items specially designed for a specific application. (a) Inorganic ‘fibrous or filamentary materials’ that have a ‘specific modulus’ exceeding 2,54 × 10 6 m and a melting, softening, decomposition or sublimation point exceeding 1 649 °C in an inert environment. Note : Does not apply to the following — Discontinuous, multiphase, polycrystalline alumina fibres in chopped fibre or random mat form containing 3 % by weight or more silica with a ‘specific modulus’ of less than 10 × 10 6 m — Molybdenum and molybdenum alloy fibres — Boron fibres — Discontinuous ceramic fibres with a melting, softening, decomposition or sublimation point lower than 1 770 °C in an inert environment. (b) ‘Fibrous or filamentary materials’ having any of the following: 1. Materials composed of aromatic polyetherimides having a glass transition temperature (Tg) exceeding 290 °C, 2. Polyarylene ketones, 3. Polyarylene sulphides where the arlylene group is biphenylene, triphenylene or combinations thereof, 4. Polybiphenylenethersulphone having a Tg exceeding 290 °C, or 5. Any of the above materials ‘commingled’ with any of the following: a. Organic ‘fibrous or filamentary materials’, with a ‘specific modulus’ exceeding 12,7 × 10 6 m and a ‘specific tensile strength’ exceeding 23,5 × 10 4 m. b. Carbon ‘fibrous or filamentary materials’, having a ‘specific modulus’ exceeding 14,65 × 10 6 m; and specific tensile strength exceeding 26,82 × 10 4 m. c. Inorganic ‘fibrous or filamentary materials’, having a ‘specific modulus’ exceeding 2,54 × 10 6 m; and a melting, softening, decomposition or sublimation point exceeding 1 649 °C in an inert environment. Notes: 1. Does not apply to polyethylene. 2. Does not apply to — ‘fibrous or filamentary materials’, for the repair of civil aircraft structures or laminates, having an area not exceeding 1 m 2 ; a length not exceeding 2,5 m; and a width exceeding 15 mm. — Mechanically chopped, milled or cut carbon ‘fibrous or filamentary materials’ 25,0 mm or less in length. 3. Does not apply to discontinuous, multiphase, polycrystalline alumina fibres in chopped fibre or random mat form, containing 3 % by weight or more silica, with a ‘specific modulus’ of less than 10 × 10 6 m; molybdenum and molybdenum alloy fibres; boron fibres; discontinuous ceramic fibres with a melting, softening, decomposition or sublimation point lower than 1 770 °C in an inert environment. (c) Organic ‘fibrous or filamentary materials’ with a ‘specific modulus’ exceeding 12,7 × 10 6 m and with a ‘specific tensile strength’ exceeding 23,5 × 10 4 m. (d) Carbon ‘fibrous or filamentary materials’ having a ‘specific modulus’ exceeding 14,65 × 10 6 m and a specific tensile exceeding 26,82 × 10 4 m. (e) Fully or partially resin-impregnated or pitch-impregnated ‘fibrous or filamentary materials’ (prepregs), metal or carbon-coated ‘fibrous or filamentary materials’ (preforms) or carbon fibre preforms having any of the following ‘fibrous or filamentary materials’ and resins: 1. Inorganic ‘fibrous or filamentary materials’ with a ‘specific modulus’ exceeding 2,54 × 10 6 m and a melting, softening, decomposition or sublimation point exceeding 1 649 °C in an inert environment, or 2. Organic or carbon ‘fibrous or filamentary materials’, having all of the following: a. ‘Specific modulus’ exceeding 10,15 × 10 6 m; and b. ‘Specific tensile strength’ exceeding 17,7 × 10 4 m; or 3. Resin or pitch, from unprocessed fluorinated compounds such as: a. Fluorinated polyimides containing 10 % by weight or more of combined fluorine; b. Fluorinated phosphazene elastomers containing 30 % by weight or more of combined fluorine; or 4. Phenolic resins with Dynamic Mechanical Analysis glass transition temperature (DMA Tg) equal to, or exceeding, 180 °C and having a phenolic resin; or 5. Other resin or pitch with Dynamic Mechanical Analysis glass transition temperature (DMA Tg) equal to, or exceeding, 232 °C. Note: Does not apply to — Epoxy resin ‘matrix’ impregnated carbon ‘fibrous or filamentary materials’ (prepregs) for the repair of ‘civil aircraft’ structures or laminates, having all of the following; — An area not exceeding 1 m 2 ; — A length not exceeding 2,5 m; and — A width exceeding 15 mm