- List
- Wassenaar Arrangement – List of Dual-Use Goods and Technologies – WA-LIST (25) 1
- Corresponding EU entry
- 1C010
Technical Notes
1. For the purposes of calculating "specific tensile strength", "specific modulus" or specific weight of "fibrous or filamentary materials" in 1.C.10.a., 1.C.10.b., 1.C.10.c. or 1.C.10.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 1.C.10., 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 x 10⁶ m; and
2. "Specific tensile strength" exceeding 23.5 x 10⁴ m;
Note 1.C.10.a. does not apply to polyethylene.
b. Carbon "fibrous or filamentary materials", having all of the following:
1. "Specific modulus" exceeding 14.65 x 10⁶ m; and
2. "Specific tensile strength" exceeding 26.82 x 10⁴ m;
Note 1.C.10.b. does not apply to:
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 x 10⁶ m; or
b. Not specified in 1.C.10.c.1.a. and having a "specific modulus" exceeding 5.6 x 10⁶ m; and
2. Melting, softening, decomposition or sublimation point exceeding 1,922 K (1,649°C) in an inert environment;
Note 1.C.10.c. does not apply to:
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 x 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 1.C.8.a.; or
b. Materials specified in 1.C.8.d. to 1.C.8.f.; or
2. Composed of materials specified in 1.C.10.d.1.a. or 1.C.10.d.1.b. and 'commingled' with other fibres specified in 1.C.10.a., 1.C.10.b. or 1.C.10.c.;
Technical Note
For the purposes of 1.C.10.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 1.C.10.c.; or
b. Organic or carbon "fibrous or filamentary materials", having all of the following:
1. "Specific modulus" exceeding 10.15 x 10⁶ m; and
2. "Specific tensile strength" exceeding 17.7 x 10⁴ m; and
e. 2. Having any of the following:
a. Resin or pitch, specified in 1.C.8. or 1.C.9.b.;
b. 'Dynamic Mechanical Analysis glass transition temperature (DMA T_(g))' equal to or exceeding 453 K (180C) and having a phenolic resin; or
c. 'Dynamic Mechanical Analysis glass transition temperature (DMA T_(g))' equal to or exceeding 505 K (232C) and having a resin or pitch, not specified in 1.C.8. or 1.C.9.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 1.C.10.a., 1.C.10.b. or 1.C.10.c.
Note 2 1.C.10.e. 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 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 1.C.8. or 1.C.9.b.
Technical Notes
1. For the purposes of 1.C.10.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 1.C.10.e.2. materials, 'Dynamic Mechanical Analysis glass transition temperature (DMA T_(g))' 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.
1. For the purposes of calculating "specific tensile strength", "specific modulus" or specific weight of "fibrous or filamentary materials" in 1.C.10.a., 1.C.10.b., 1.C.10.c. or 1.C.10.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 1.C.10., 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 x 10⁶ m; and
2. "Specific tensile strength" exceeding 23.5 x 10⁴ m;
Note 1.C.10.a. does not apply to polyethylene.
b. Carbon "fibrous or filamentary materials", having all of the following:
1. "Specific modulus" exceeding 14.65 x 10⁶ m; and
2. "Specific tensile strength" exceeding 26.82 x 10⁴ m;
Note 1.C.10.b. does not apply to:
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 x 10⁶ m; or
b. Not specified in 1.C.10.c.1.a. and having a "specific modulus" exceeding 5.6 x 10⁶ m; and
2. Melting, softening, decomposition or sublimation point exceeding 1,922 K (1,649°C) in an inert environment;
Note 1.C.10.c. does not apply to:
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 x 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 1.C.8.a.; or
b. Materials specified in 1.C.8.d. to 1.C.8.f.; or
2. Composed of materials specified in 1.C.10.d.1.a. or 1.C.10.d.1.b. and 'commingled' with other fibres specified in 1.C.10.a., 1.C.10.b. or 1.C.10.c.;
Technical Note
For the purposes of 1.C.10.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 1.C.10.c.; or
b. Organic or carbon "fibrous or filamentary materials", having all of the following:
1. "Specific modulus" exceeding 10.15 x 10⁶ m; and
2. "Specific tensile strength" exceeding 17.7 x 10⁴ m; and
e. 2. Having any of the following:
a. Resin or pitch, specified in 1.C.8. or 1.C.9.b.;
b. 'Dynamic Mechanical Analysis glass transition temperature (DMA T_(g))' equal to or exceeding 453 K (180C) and having a phenolic resin; or
c. 'Dynamic Mechanical Analysis glass transition temperature (DMA T_(g))' equal to or exceeding 505 K (232C) and having a resin or pitch, not specified in 1.C.8. or 1.C.9.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 1.C.10.a., 1.C.10.b. or 1.C.10.c.
Note 2 1.C.10.e. 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 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 1.C.8. or 1.C.9.b.
Technical Notes
1. For the purposes of 1.C.10.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 1.C.10.e.2. materials, 'Dynamic Mechanical Analysis glass transition temperature (DMA T_(g))' 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.