Resin-impregnated or pitch-impregnated fibres (prepregs), metal or carbon-coated fibres (preforms) or ‘carbon fibre preforms’, as follows: a. Made from ‘fibrous or filamentary materials’ specified in II.A1.009 above; b. Epoxy resin ‘matrix’ impregnated carbon ‘fibrous or filamentary materials’ (prepregs), specified in 1C010.a, 1C010.b or 1C010.c, for the repair of aircraft structures or laminates, of which the size of individual sheets does not exceed 50 cm × 90 cm; c. Prepregs specified in 1C010.a, 1C010.b or 1C010.c, when impregnated with phenolic or epoxy resins having a glass transition temperature (Tg) less than 433 K (160 o C) and a cure temperature lower than the glass transition temperature. Note: This item does not cover ‘fibrous or filamentary materials’ defined in item 1C010.e.

1C010

II.A1.010

A1. Materials, chemicals, ‘microorganisms’ and ‘toxins’

EU Regulation No 267/2012

Resin impregnated fibre prepregs and metal coated fibre preforms, for the goods specified in 6.A.1., made either with organic matrix or metal matrix utilising fibrous or filamentary reinforcements having a specific tensile strength greater than 7,62 × 104 m and a specific modulus greater than 3,18 × 106 m.Note:The only resin impregnated fibre prepregs specified in 6.C.1. are those using resins with a glass transition temperature (Tg), after cure, exceeding 145 °C as determined by ASTM D4065 or national equivalents.Technical Notes:1.In Item 6.C.1. ‘specific tensile strength’ is the ultimate tensile strength in N/m2divided by the specific weight in N/m3, measured at a temperature of (296 ± 2)K ((23 ± 2)°C) and a relative humidity of (50 ± 5)%.2.In Item 6.C.1. ‘specific modulus’ is the Young's modulus in N/m2divided by the specific weight in N/m3, measured at a temperature of (296 ± 2)K ((23 ± 2)°C) and a relative humidity of (50 ± 5)%.