‘Fibrous or filamentary materials’ as follows: (a) Organic ‘fibrous or filamentary materials’, having all of the following: 1. ‘specific modulus’ exceeding 12,7 × 10 6 m; and 2. ‘specific tensile strength’ exceeding 23,5 × 10 4 m; (b) Carbon ‘fibrous or filamentary materials’, having all of the following: 1. ‘specific modulus’ exceeding 14,65 × 10 6 m; and 2. ‘specific tensile strength’ exceeding 26,82 × 10 4 m; (c) Inorganic ‘fibrous or filamentary materials’, having all of the following: 1. ‘Specific modulus’ exceeding 2,54 × 10 6 m; and 2. Melting, softening, decomposition or sublimation point exceeding 1 649 °C in an inert environment (d) ‘Fibrous or filamentary materials’, having any of the following: 1. Composed of any of the following: a. Polyetherimides specified in VII.A1.010 b. Other materials specified in VII.A1.010 2. Composed of materials specified above and commingled with other fibres specified in VII.A1.012. (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 all of the following: 1. Having any of the following: a. Inorganic ‘fibrous or filamentary materials’ specified above b. Organic or carbon ‘fibrous or filamentary materials’, having all of the following: 1. ‘Specific modulus’ exceeding 10,15 × 10 6 m; and 2. ‘Specific tensile strength’ exceeding 17,7 × 10 4 m; and 2. Having any of the following: a. Resin or pitch, specified in previous sections; b. ‘Dynamic Mechanical Analysis glass transition temperature (DMA Tg)’ equal to or exceeding 180 °C and having a phenolic resin; or c. ‘Dynamic Mechanical Analysis glass transition temperature (DMA Tg)’ equal to or exceeding 232 °C and having a resin or pitch, not specified earlier and not being a phenolic resin. 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 all of the following: (a) An area not exceeding 1 m 2 ; (b) A length not exceeding 2,5 m; and (c) A width exceeding 15 mm. Or to mechanically chopped, milled or cut carbon ‘fibrous or filamentary materials’ 25,0 mm or less in length. 3. Does not apply to the following: (a) 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; (b) Molybdenum and molybdenum alloy fibres; (c) Boron fibres; (d) Discontinuous ceramic fibres with a melting, softening, decomposition or sublimation point lower than 2 043 K (1 770 °C) in an inert environment. 4. Does not apply to: (a) Epoxy resin ‘matrix’ impregnated carbon ‘fibrous or filamentary materials’ (prepregs) for the repair of ‘civil aircraft’ structures or laminates, having all of the following; 1. An area not exceeding 1 m 2 ; 2. A length not exceeding 2,5 m; and 3. A width exceeding 15 mm. (b) Fully or partially resin-impregnated or pitch-impregnated mechanically chopped, milled or cut carbon ‘fibrous or filamentary materials’ 25,0 mm or less in length when using a resin or pitch other than those specified previously.