ECCN 1C010
NSNPATFibrous or filamentary materials as follows .
What This ECCN Covers
ECCN 1C010 controls high-performance "fibrous or filamentary materials" — organic, carbon, and inorganic fibers that exceed defined "specific modulus" and "specific tensile strength" thresholds. These fibers are the raw input for the composite structures controlled under 1A002. They are controlled because the same lightweight, high-strength materials used in aircraft and sporting goods are also critical to gas centrifuge rotors and rocket motor cases, giving the entry National Security, Nuclear Nonproliferation, and Anti-Terrorism reasons.
Who needs to check this?
Manufacturers and distributors of carbon fiber, aramid fiber, ceramic fiber, tow, and prepreg, and the composite fabricators who source these materials.
Compliance tip
Control turns on measured "specific modulus" and "specific tensile strength" — calculate both against the thresholds in the entry, since fibers below them fall outside 1C010. Confirm NS and NP requirements on the Commerce Country Chart, and verify license-exception eligibility in the entry, as several exceptions are restricted for NP-controlled items.
Items Covered
- 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;
- 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;
- a."Fibrous or filamentary materials", for the repair of "civil aircraft" structures or laminates, having all of the following:
- 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:
- 1.a. Composed of 50% or more by weight silicon dioxide (SiO2) and having a "specific modulus" exceeding 2.54 × 106 m; or
- 1.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;
- a.Discontinuous, multiphase, polycrystalline alumina fibers in chopped fiber 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 fibers;
- c.Boron fibers;
- d.Discontinuous ceramic fibers 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:
- 1.a. Polyetherimides controlled by 1C008.a; or
- 1.b. Materials controlled by 1C008.b to 1C008.f; or
- 2. Composed of materials controlled by 1C010.d.1.a or 1C010.d.1.b and 'commingled' with other fibers controlled by 1C010.a, 1C010.b or 1C010.c;
- 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 fiber preforms', having all of the following:
- 1. Having any of the following:
- 1.a. Inorganic "fibrous or filamentary materials" controlled by 1C010.c; or
- 1.b. Organic or carbon "fibrous or filamentary materials", having all of the following:
- 1.b.1. "Specific modulus" exceeding 10.15 × 106 m; and
- e.1.b.2 "Specific tensile strength" exceeding 17.7 × 104m; and
- 2. Having any of the following:
- 2.a. Resin or pitch, controlled by 1C008 or 1C009.b;
- 2.b. 'Dynamic Mechanical Analysis glass transition temperature (DMA Tg)' equal to or exceeding 453 K (180 °C) and having a phenolic resin; or
- 2.c. 'Dynamic Mechanical Analysis glass transition temperature (DMA Tg)' equal to or exceeding 505 K (232 °C) and having a resin or pitch, not specified by 1C008 or 1C009.b, and not being a phenolic resin;
- 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:
- 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 by 1C008 or 1C009.b.
Control Reasons
Items controlled for national security reasons under multilateral export control regimes.
Items controlled for nuclear nonproliferation reasons.
Items controlled for anti-terrorism reasons. Most items on the CCL have AT controls.
Disclaimer
This information is for reference only. For official classifications, consult BIS or a qualified export control professional.