- List
- EU dual-use list – Annex I to Regulation (EU) 2021/821, updated annually
- Originating regime
- Thỏa ước Wassenaar
N.B. SEE ALSO 1C210 AND 9C110.
Technical Notes:
1. For the purposes of calculating "specific tensile strength", "specific modulus" or specific weight of "fibrous or filamentary materials" in 1C010.a., 1C010.b., 1C010.c. or 1C010.e.1.b., the tensile strength and modulus should be determined by using Method A described in ISO 10618:2004 or national equivalents.
2. For the purposes of assessing the "specific tensile strength", "specific modulus" or specific weight of non-unidirectional "fibrous or filamentary materials" (e.g., fabrics, random mats or braids) in 1C010, this is to be based on the mechanical properties of the constituent unidirectional monofilaments (e.g., monofilaments, yarns, rovings or tows) prior to processing into the non-unidirectional "fibrous or filamentary materials".
a. Organic "fibrous or filamentary materials", having all of the following:
1. "Specific modulus" exceeding 12,7 × 106 m; and
2. "Specific tensile strength" exceeding 23,5 × 104 m;
Note:
1C010.a. does not control polyethylene.
b. Carbon "fibrous or filamentary materials", having all of the following:
1. "Specific modulus" exceeding 14,65 × 106 m; and
2. "Specific tensile strength" exceeding 26,82 × 104 m;
Note:
1C010.b. does not control:
a. "Fibrous or filamentary materials", for the repair of "civil aircraft" structures or laminates, having all of the following:
1. An area not exceeding 1 m2;
2. A length not exceeding 2,5 m;
and
3. A width exceeding 15 mm;
b. Mechanically chopped, milled or cut carbon "fibrous or filamentary materials" 25,0 mm or less in length.
c. Inorganic "fibrous or filamentary materials", having all of the following:
1. Having any of the following:
a. Composed of 50 % or more by weight silicon dioxide and having a "specific modulus" exceeding 2,54 × 106 m; or
b. Not specified in 1C010.c.1.a. and having a "specific modulus" exceeding 5,6 × 106 m; and
2. Melting, softening, decomposition or sublimation point exceeding 1 922 K (1 649 °C) in an inert environment;
Note:
1C010.c. does not control:
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 × 106 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.
d. "Fibrous or filamentary materials", having any of the following:
1. Composed of any of the following:
a. Polyetherimides specified in 1C008.a.; or
b. Materials specified in 1C008.d. to 1C008.f.; or
2. Composed of materials specified in 1C010.d.1.a. or 1C010.d.1.b. and 'commingled' with other fibres specified in 1C010.a., 1C010.b. or 1C010.c.;
Technical Note:
For the purposes of 1C010.d.2., 'commingled' is filament to filament blending of thermoplastic fibres and reinforcement fibres in order to produce a fibre reinforcement "matrix" mix in total fibre form.
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 in 1C010.c.; or
b. Organic or carbon "fibrous or filamentary materials", having all of the following:
1. "Specific modulus" exceeding 10,15 × 106 m; and
2. "Specific tensile strength" exceeding 17,7 × 104 m; and
2. Having any of the following:
a. Resin or pitch, specified in 1C008 or 1C009.b.;
b. 'Dynamic Mechanical Analysis glass transition temperature (DMA Tg)' equal to or exceeding 453 K (180oC) and having a phenolic resin; or
c. 'Dynamic Mechanical Analysis glass transition temperature (DMA Tg)' equal to or exceeding 505 K (232oC) and having a resin or pitch, not specified in 1C008 or 1C009.b., and not being a phenolic resin.
Note 1:
Metal or carbon-coated "fibrous or filamentary materials" (preforms) or 'carbon fibre preforms', not impregnated with resin or pitch, are specified by "fibrous or filamentary materials" in 1C010.a., 1C010.b. or 1C010.c.
Note 2:
1C010.e. does not control:
a. Epoxy resin "matrix" impregnated carbon "fibrous or filamentary materials" (prepregs) for the repair of "civil aircraft" structures or laminates, having all the following:
1. An area not exceeding 1 m2;
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 in 1C008 or 1C009.b.
Technical Notes:
1. For the purposes of 1C010.e. and Note 1, 'carbon fibre preforms' are an ordered arrangement of uncoated or coated fibres intended to constitute a framework of a part before the "matrix" is introduced to form a "composite".
2. For the purposes of 1C010.e.2. materials, 'Dynamic Mechanical Analysis glass transition temperature (DMA Tg)' is determined using the method described in ASTM D 7028-07, or equivalent national standard, on a dry test specimen. In the case of thermoset materials, degree of cure of a dry test specimen shall be a minimum of 90 % as defined by ASTM E 2160-04 or equivalent national standard.
Technical Notes:
1. For the purposes of calculating "specific tensile strength", "specific modulus" or specific weight of "fibrous or filamentary materials" in 1C010.a., 1C010.b., 1C010.c. or 1C010.e.1.b., the tensile strength and modulus should be determined by using Method A described in ISO 10618:2004 or national equivalents.
2. For the purposes of assessing the "specific tensile strength", "specific modulus" or specific weight of non-unidirectional "fibrous or filamentary materials" (e.g., fabrics, random mats or braids) in 1C010, this is to be based on the mechanical properties of the constituent unidirectional monofilaments (e.g., monofilaments, yarns, rovings or tows) prior to processing into the non-unidirectional "fibrous or filamentary materials".
a. Organic "fibrous or filamentary materials", having all of the following:
1. "Specific modulus" exceeding 12,7 × 106 m; and
2. "Specific tensile strength" exceeding 23,5 × 104 m;
Note:
1C010.a. does not control polyethylene.
b. Carbon "fibrous or filamentary materials", having all of the following:
1. "Specific modulus" exceeding 14,65 × 106 m; and
2. "Specific tensile strength" exceeding 26,82 × 104 m;
Note:
1C010.b. does not control:
a. "Fibrous or filamentary materials", for the repair of "civil aircraft" structures or laminates, having all of the following:
1. An area not exceeding 1 m2;
2. A length not exceeding 2,5 m;
and
3. A width exceeding 15 mm;
b. Mechanically chopped, milled or cut carbon "fibrous or filamentary materials" 25,0 mm or less in length.
c. Inorganic "fibrous or filamentary materials", having all of the following:
1. Having any of the following:
a. Composed of 50 % or more by weight silicon dioxide and having a "specific modulus" exceeding 2,54 × 106 m; or
b. Not specified in 1C010.c.1.a. and having a "specific modulus" exceeding 5,6 × 106 m; and
2. Melting, softening, decomposition or sublimation point exceeding 1 922 K (1 649 °C) in an inert environment;
Note:
1C010.c. does not control:
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 × 106 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.
d. "Fibrous or filamentary materials", having any of the following:
1. Composed of any of the following:
a. Polyetherimides specified in 1C008.a.; or
b. Materials specified in 1C008.d. to 1C008.f.; or
2. Composed of materials specified in 1C010.d.1.a. or 1C010.d.1.b. and 'commingled' with other fibres specified in 1C010.a., 1C010.b. or 1C010.c.;
Technical Note:
For the purposes of 1C010.d.2., 'commingled' is filament to filament blending of thermoplastic fibres and reinforcement fibres in order to produce a fibre reinforcement "matrix" mix in total fibre form.
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 in 1C010.c.; or
b. Organic or carbon "fibrous or filamentary materials", having all of the following:
1. "Specific modulus" exceeding 10,15 × 106 m; and
2. "Specific tensile strength" exceeding 17,7 × 104 m; and
2. Having any of the following:
a. Resin or pitch, specified in 1C008 or 1C009.b.;
b. 'Dynamic Mechanical Analysis glass transition temperature (DMA Tg)' equal to or exceeding 453 K (180oC) and having a phenolic resin; or
c. 'Dynamic Mechanical Analysis glass transition temperature (DMA Tg)' equal to or exceeding 505 K (232oC) and having a resin or pitch, not specified in 1C008 or 1C009.b., and not being a phenolic resin.
Note 1:
Metal or carbon-coated "fibrous or filamentary materials" (preforms) or 'carbon fibre preforms', not impregnated with resin or pitch, are specified by "fibrous or filamentary materials" in 1C010.a., 1C010.b. or 1C010.c.
Note 2:
1C010.e. does not control:
a. Epoxy resin "matrix" impregnated carbon "fibrous or filamentary materials" (prepregs) for the repair of "civil aircraft" structures or laminates, having all the following:
1. An area not exceeding 1 m2;
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 in 1C008 or 1C009.b.
Technical Notes:
1. For the purposes of 1C010.e. and Note 1, 'carbon fibre preforms' are an ordered arrangement of uncoated or coated fibres intended to constitute a framework of a part before the "matrix" is introduced to form a "composite".
2. For the purposes of 1C010.e.2. materials, 'Dynamic Mechanical Analysis glass transition temperature (DMA Tg)' is determined using the method described in ASTM D 7028-07, or equivalent national standard, on a dry test specimen. In the case of thermoset materials, degree of cure of a dry test specimen shall be a minimum of 90 % as defined by ASTM E 2160-04 or equivalent national standard.