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  • Good

    Ceramic powders, non-‘composite’ ceramic materials, ceramic-‘matrix’‘composite’ materials and precursor materials, as follows: (a) Ceramic powders of single or complex borides of titanium, having total metallic impurities, excluding intentional additions, of less than 5 000 ppm, an average particle size equal to or less than 5 μm and no more than 10 % of the particles larger than 10 μm; (b) Non-‘composite’ ceramic materials in crude or semi-fabricated form, composed of borides of titanium with a density of 98 % or more of the theoretical density; (c) Ceramic-ceramic ‘composite’ materials with a glass or oxide-‘matrix’ and reinforced with fibres having all of the following: 1. Made from any of the following materials: a. Si-N; b. Si-C; c. Si-A1-O-N; or d. Si-O-N; and 2. Having a ‘specific tensile strength’ exceeding 12,7 × 10 3 m (d) Ceramic-ceramic ‘composite’ materials, with or without a continuous metallic phase, incorporating particles, whiskers or fibres, where carbides or nitrides of silicon, zirconium or boron form the ‘matrix’; (e) Precursor materials (i.e., special purpose polymeric or metallo-organic materials) for producing any phase or phases of the materials specified above, as follows: 1. Polydiorganosilanes (for producing silicon carbide); 2. Polysilazanes (for producing silicon nitride); 3. Polycarbosilazanes (for producing ceramics with silicon, carbon and nitrogen components); (f) Ceramic-ceramic ‘composite’ materials with an oxide or glass ‘matrix’ reinforced with continuous fibres from any of the following systems: 1. Al 2 O 3 (CAS 1344-28-1); or 2. Si-C-N. Notes: 1. Does not apply to abrasives. 2. Does not apply to ‘composites’ containing fibres from these systems with a fibre ‘tensile strength’ of less than 700 MPa at 1 273 K (1 000 °C) or fibre tensile creep resistance of more than 1 per cent creep strain at 100 MPa load and 1 273 K (1 000 °C) for 100 hours.

    Authority: EU
    Prohibited Supply To: IRKP
    Program: KP
    EU Code: VII.A1.009
    Code: 1C007
    Good

    Ceramic powders, non-‘composite’ ceramic materials, ceramic-‘matrix’‘composite’ materials and precursor materials, as follows: (a) Ceramic powders of single or complex borides of titanium, having total metallic impurities, excluding intentional additions, of less than 5 000 ppm, an average particle size equal to or less than 5 μm and no more than 10 % of the particles larger than 10 μm; (b) Non-‘composite’ ceramic materials in crude or semi-fabricated form, composed of borides of titanium with a density of 98 % or more of the theoretical density; (c) Ceramic-ceramic ‘composite’ materials with a glass or oxide-‘matrix’ and reinforced with fibres having all of the following: 1. Made from any of the following materials: a. Si-N; b. Si-C; c. Si-A1-O-N; or d. Si-O-N; and 2. Having a ‘specific tensile strength’ exceeding 12,7 × 10 3 m (d) Ceramic-ceramic ‘composite’ materials, with or without a continuous metallic phase, incorporating particles, whiskers or fibres, where carbides or nitrides of silicon, zirconium or boron form the ‘matrix’; (e) Precursor materials (i.e., special purpose polymeric or metallo-organic materials) for producing any phase or phases of the materials specified above, as follows: 1. Polydiorganosilanes (for producing silicon carbide); 2. Polysilazanes (for producing silicon nitride); 3. Polycarbosilazanes (for producing ceramics with silicon, carbon and nitrogen components); (f) Ceramic-ceramic ‘composite’ materials with an oxide or glass ‘matrix’ reinforced with continuous fibres from any of the following systems: 1. Al 2 O 3 (CAS 1344-28-1); or 2. Si-C-N. Notes: 1. Does not apply to abrasives. 2. Does not apply to ‘composites’ containing fibres from these systems with a fibre ‘tensile strength’ of less than 700 MPa at 1 273 K (1 000 °C) or fibre tensile creep resistance of more than 1 per cent creep strain at 100 MPa load and 1 273 K (1 000 °C) for 100 hours.

    Authority: EU
    Prohibited Supply To: IRKP
    Program: KP
    EU Code: VII.A1.009
    Code: 1C007
  • Good

    Fluids and lubricating materials, as follows: (a) Lubricating materials containing, as their principal ingredients, any of the following: 1. Phenylene or alkylphenylene ethers or thio-ethers, or their mixtures, containing more than two ether or thio-ether functions or mixtures thereof; or 2. Fluorinated silicone fluids with a kinematic viscosity of less than 5 000 mm 2 /s (5 000 centistokes) measured at 25 °C; (b) Damping or flotation fluids having all of the following: 1. Purity exceeding 99,8 %; 2. Containing less than 25 particles of 200 μm or larger in size per 3. 100 ml; and 4. Made from at least 85 % of any of the following: a. Dibromotetrafluoroethane (CAS 25497-30-7, 124-73-2, 27336-23-8); b. Polychlorotrifluoroethylene (oily and waxy modifications only); or c. Polybromotrifluoroethylene (c) Fluorocarbon electronic cooling fluids having all of the following: 1. Containing 85 % by weight or more of any of the following, or mixtures thereof: a. Monomeric forms of perfluoropolyalkylether-triazines or perfluoroaliphatic-ethers; b. Perfluoroalkylamines; c. Perfluorocycloalkanes; or d. Perfluoroalkanes e. Density at 298 K (25 °C) of 1,5 g/ml or more; f. In a liquid state at 273 K (0 °C); and g. Containing 60 % or more by weight of fluorine Note : Does not apply to materials specified and packages as medical products

    Authority: EU
    Prohibited Supply To: IRKP
    Program: KP
    EU Code: VII.A1.008
    Code: 1C006
    Good

    Fluids and lubricating materials, as follows: (a) Lubricating materials containing, as their principal ingredients, any of the following: 1. Phenylene or alkylphenylene ethers or thio-ethers, or their mixtures, containing more than two ether or thio-ether functions or mixtures thereof; or 2. Fluorinated silicone fluids with a kinematic viscosity of less than 5 000 mm 2 /s (5 000 centistokes) measured at 25 °C; (b) Damping or flotation fluids having all of the following: 1. Purity exceeding 99,8 %; 2. Containing less than 25 particles of 200 μm or larger in size per 3. 100 ml; and 4. Made from at least 85 % of any of the following: a. Dibromotetrafluoroethane (CAS 25497-30-7, 124-73-2, 27336-23-8); b. Polychlorotrifluoroethylene (oily and waxy modifications only); or c. Polybromotrifluoroethylene (c) Fluorocarbon electronic cooling fluids having all of the following: 1. Containing 85 % by weight or more of any of the following, or mixtures thereof: a. Monomeric forms of perfluoropolyalkylether-triazines or perfluoroaliphatic-ethers; b. Perfluoroalkylamines; c. Perfluorocycloalkanes; or d. Perfluoroalkanes e. Density at 298 K (25 °C) of 1,5 g/ml or more; f. In a liquid state at 273 K (0 °C); and g. Containing 60 % or more by weight of fluorine Note : Does not apply to materials specified and packages as medical products

    Authority: EU
    Prohibited Supply To: IRKP
    Program: KP
    EU Code: VII.A1.008
    Code: 1C006
  • Good

    ‘Superconductive’ composite conductors in lengths exceeding 100 m or with a mass exceeding 100 g, as follows: (a) ‘Superconductive’‘composite’ conductors containing one or more niobium-titanium ‘filaments’, having all of the following: 1. Embedded in a ‘matrix’ other than a copper or copper-based mixed ‘matrix’; and 2. Having a cross-section area less than 0,28x 10 – 4 mm 2 (6 μm in diameter for circular ‘filaments’); (b) ‘Superconductive’‘composite’ conductors consisting of one or more ‘superconductive’‘filaments’ other than niobium-titanium, having all of the following: 1. A ‘critical temperature’ at zero magnetic induction exceeding – 263,31 °C; and 2. Remaining in the ‘superconductive’ state at a temperature of – 268,96 °C when exposed to a magnetic field oriented in any direction perpendicular to the longitudinal axis of conductor and corresponding to a magnetic induction of 12 T with critical current density exceeding 1 750 A/mm 2 on overall cross-section of the conductor. (c) ‘Superconductive’‘composite’ conductors consisting of one or more ‘superconductive’‘filaments’, which remain ‘superconductive’ above – 158,16 °C

    Authority: EU
    Prohibited Supply To: KP
    Program: KP
    EU Code: VII.A1.007
    Code: 1C005
    Good

    ‘Superconductive’ composite conductors in lengths exceeding 100 m or with a mass exceeding 100 g, as follows: (a) ‘Superconductive’‘composite’ conductors containing one or more niobium-titanium ‘filaments’, having all of the following: 1. Embedded in a ‘matrix’ other than a copper or copper-based mixed ‘matrix’; and 2. Having a cross-section area less than 0,28x 10 – 4 mm 2 (6 μm in diameter for circular ‘filaments’); (b) ‘Superconductive’‘composite’ conductors consisting of one or more ‘superconductive’‘filaments’ other than niobium-titanium, having all of the following: 1. A ‘critical temperature’ at zero magnetic induction exceeding – 263,31 °C; and 2. Remaining in the ‘superconductive’ state at a temperature of – 268,96 °C when exposed to a magnetic field oriented in any direction perpendicular to the longitudinal axis of conductor and corresponding to a magnetic induction of 12 T with critical current density exceeding 1 750 A/mm 2 on overall cross-section of the conductor. (c) ‘Superconductive’‘composite’ conductors consisting of one or more ‘superconductive’‘filaments’, which remain ‘superconductive’ above – 158,16 °C

    Authority: EU
    Prohibited Supply To: KP
    Program: KP
    EU Code: VII.A1.007
    Code: 1C005
  • Good

    Uranium titanium alloys or tungsten alloys with a ‘matrix’ based on iron, nickel or copper, having all of the following: (a) A density exceeding 17,5 g/cm 3 ; (b) An elastic limit exceeding 880 MPa; (c) An ultimate tensile strength exceeding 1 270 MPa; and (d) An elongation exceeding 8 %.

    Authority: EU
    Prohibited Supply To: KP
    Program: KP
    EU Code: VII.A1.006
    Code: 1C004
    Good

    Uranium titanium alloys or tungsten alloys with a ‘matrix’ based on iron, nickel or copper, having all of the following: (a) A density exceeding 17,5 g/cm 3 ; (b) An elastic limit exceeding 880 MPa; (c) An ultimate tensile strength exceeding 1 270 MPa; and (d) An elongation exceeding 8 %.

    Authority: EU
    Prohibited Supply To: KP
    Program: KP
    EU Code: VII.A1.006
    Code: 1C004
  • Good

    Magnetic metals, of all types and of whatever form, having any of the following: (a) Initial relative permeability of 120 000 or more and a thickness of 0,5 mm or less (b) Magnetostrictive alloys having any of the following: 1. A saturation magnetostriction of more than 5 × 10 – 4 ; or 2. A magnetomechanical coupling factor (k) of more than 0,8; or (c) Amorphous or ‘nanocrystalline’ alloy strips, having all of the following: 1. A composition having a minimum of 75 % by weight of iron, cobalt or nickel; 2. A saturation magnetic induction (Bs) of 1,6 T or more; and any of the following: a. A strip thickness of 0,02 mm or less; or b. An electrical resistivity of 2 × 10 – 4 ohm cm or more.

    Authority: EU
    Prohibited Supply To: KP
    Program: KP
    EU Code: VII.A1.005
    Code: 1C003
    Good

    Magnetic metals, of all types and of whatever form, having any of the following: (a) Initial relative permeability of 120 000 or more and a thickness of 0,5 mm or less (b) Magnetostrictive alloys having any of the following: 1. A saturation magnetostriction of more than 5 × 10 – 4 ; or 2. A magnetomechanical coupling factor (k) of more than 0,8; or (c) Amorphous or ‘nanocrystalline’ alloy strips, having all of the following: 1. A composition having a minimum of 75 % by weight of iron, cobalt or nickel; 2. A saturation magnetic induction (Bs) of 1,6 T or more; and any of the following: a. A strip thickness of 0,02 mm or less; or b. An electrical resistivity of 2 × 10 – 4 ohm cm or more.

    Authority: EU
    Prohibited Supply To: KP
    Program: KP
    EU Code: VII.A1.005
    Code: 1C003
  • Good

    Metal alloys, metal alloy powder and alloyed materials including the following: (a) Aluminides, including: 1. Nickel aluminides containing a minimum of 15 % by weight aluminium, a maximum of 38 % by weight aluminium and at least one additional alloying element; 2. Titanium aluminides containing 10 % by weight or more aluminium and at least one additional alloying element. (b) Metal alloys made from the powder or particulate material including: 1. Nickel alloys having a stress-rupture life of 10 000 hours or longer at 650 °C at a stress of 676 MPa or a low cycle fatigue life of 10 000 cycles or more at 550 °C at a maximum stress of 1 095 MPa; 2. Niobium alloys having a stress-rupture life of 10 000 hours or longer at 800 °C at a stress of 400 MPa or a low cycle fatigue life of 10 000 cycles or more at 700 °C at a maximum stress of 700 MPa; 3. Titanium alloys having a stress-rupture life' of 10 000 hours or longer at 450 °C at a stress of 200 MPa or a low cycle fatigue life of 10 000 cycles or more at 450 °C at a maximum stress of 400 MPa; 4. Aluminium alloys having a tensile strength of 240 MPa or more at 200 °C or a tensile strength of 415 MPa or more at 25 °C; 5. Magnesium alloys having a tensile strength of 345 MPa or more and a corrosion rate of less than 1 mm/year in 3 % sodium chloride aqueous solution measured in accordance with ASTM standard G-31 or national equivalents; 6. Metal alloy powder or particulate material, having all of the following and made from any of the following composition systems: a. Nickel alloys (Ni-Al-X, Ni-X-Al) qualified for turbine engine parts or components, i.e. with less than 3 non-metallic particles (introduced during the manufacturing process) larger than 100 μm in 10 9 alloy particles b. Niobium alloys (Nb-Al-X or Nb-X-Al, Nb-Si-X or Nb-X-Si, Nb Ti X or Nb-X-Ti) c. Titanium alloys (Ti-Al-X or Ti-X-Al) d. Aluminium alloys (Al-Mg-X or Al-X-Mg, Al-Zn-X or Al-X-Zn, Al Fe-X or Al-X-Fe) or e. Magnesium alloys (Mg-Al-X or Mg-X-Al) 7. Made in a controlled environment by any of the following processes: a. ‘Vacuum atomization’ b. ‘Gas atomization’ c. ‘Rotary atomization’ d. ‘Splat quenching’ e. ‘Melt spinning and comminution’ Note: Unless provision to the contrary is made, the words ‘metals’ and ‘alloys’ cover crude and semi-fabricated forms. Crude forms: anodes, balls, bars (including notched bars and wire bars), billets, blocks, blooms, brickets, cakes, cathodes, crystals, cubes, dice, grains, granules, ingots, lumps, pellets, pigs, powder, rondelles, shot, slabs, slugs, sponge, sticks. Semi-fabricated forms: Wrought or worked materials fabricated by rolling, drawing, extruding, forging, impact extruding, pressing, graining, atomising, and grinding, i.e.: angles, channels, circles, discs, dust, flakes, foils and leaf, forging, plate, powder, pressings and stampings, ribbons, rings, rods (including bare welding rods, wire rods, and rolled wire), sections, shapes, sheets, strip, pipe and tubes (including tube rounds, squares, and hollows), drawn or extruded wire. Cast material produced by casting in sand, die, metal, plaster or other types of moulds, including high pressure castings, sintered forms, and forms made by powder metallurgy.

    Authority: EU
    Prohibited Supply To: IRKP
    Program: KP
    EU Code: VII.A1.004
    Code: 1C202
    Good

    Metal alloys, metal alloy powder and alloyed materials including the following: (a) Aluminides, including: 1. Nickel aluminides containing a minimum of 15 % by weight aluminium, a maximum of 38 % by weight aluminium and at least one additional alloying element; 2. Titanium aluminides containing 10 % by weight or more aluminium and at least one additional alloying element. (b) Metal alloys made from the powder or particulate material including: 1. Nickel alloys having a stress-rupture life of 10 000 hours or longer at 650 °C at a stress of 676 MPa or a low cycle fatigue life of 10 000 cycles or more at 550 °C at a maximum stress of 1 095 MPa; 2. Niobium alloys having a stress-rupture life of 10 000 hours or longer at 800 °C at a stress of 400 MPa or a low cycle fatigue life of 10 000 cycles or more at 700 °C at a maximum stress of 700 MPa; 3. Titanium alloys having a stress-rupture life' of 10 000 hours or longer at 450 °C at a stress of 200 MPa or a low cycle fatigue life of 10 000 cycles or more at 450 °C at a maximum stress of 400 MPa; 4. Aluminium alloys having a tensile strength of 240 MPa or more at 200 °C or a tensile strength of 415 MPa or more at 25 °C; 5. Magnesium alloys having a tensile strength of 345 MPa or more and a corrosion rate of less than 1 mm/year in 3 % sodium chloride aqueous solution measured in accordance with ASTM standard G-31 or national equivalents; 6. Metal alloy powder or particulate material, having all of the following and made from any of the following composition systems: a. Nickel alloys (Ni-Al-X, Ni-X-Al) qualified for turbine engine parts or components, i.e. with less than 3 non-metallic particles (introduced during the manufacturing process) larger than 100 μm in 10 9 alloy particles b. Niobium alloys (Nb-Al-X or Nb-X-Al, Nb-Si-X or Nb-X-Si, Nb Ti X or Nb-X-Ti) c. Titanium alloys (Ti-Al-X or Ti-X-Al) d. Aluminium alloys (Al-Mg-X or Al-X-Mg, Al-Zn-X or Al-X-Zn, Al Fe-X or Al-X-Fe) or e. Magnesium alloys (Mg-Al-X or Mg-X-Al) 7. Made in a controlled environment by any of the following processes: a. ‘Vacuum atomization’ b. ‘Gas atomization’ c. ‘Rotary atomization’ d. ‘Splat quenching’ e. ‘Melt spinning and comminution’ Note: Unless provision to the contrary is made, the words ‘metals’ and ‘alloys’ cover crude and semi-fabricated forms. Crude forms: anodes, balls, bars (including notched bars and wire bars), billets, blocks, blooms, brickets, cakes, cathodes, crystals, cubes, dice, grains, granules, ingots, lumps, pellets, pigs, powder, rondelles, shot, slabs, slugs, sponge, sticks. Semi-fabricated forms: Wrought or worked materials fabricated by rolling, drawing, extruding, forging, impact extruding, pressing, graining, atomising, and grinding, i.e.: angles, channels, circles, discs, dust, flakes, foils and leaf, forging, plate, powder, pressings and stampings, ribbons, rings, rods (including bare welding rods, wire rods, and rolled wire), sections, shapes, sheets, strip, pipe and tubes (including tube rounds, squares, and hollows), drawn or extruded wire. Cast material produced by casting in sand, die, metal, plaster or other types of moulds, including high pressure castings, sintered forms, and forms made by powder metallurgy.

    Authority: EU
    Prohibited Supply To: IRKP
    Program: KP
    EU Code: VII.A1.004
    Code: 1C202
  • Good

    Metal alloys, metal alloy powder and alloyed materials including the following: (a) Aluminides, including: 1. Nickel aluminides containing a minimum of 15 % by weight aluminium, a maximum of 38 % by weight aluminium and at least one additional alloying element; 2. Titanium aluminides containing 10 % by weight or more aluminium and at least one additional alloying element. (b) Metal alloys made from the powder or particulate material including: 1. Nickel alloys having a stress-rupture life of 10 000 hours or longer at 650 °C at a stress of 676 MPa or a low cycle fatigue life of 10 000 cycles or more at 550 °C at a maximum stress of 1 095 MPa; 2. Niobium alloys having a stress-rupture life of 10 000 hours or longer at 800 °C at a stress of 400 MPa or a low cycle fatigue life of 10 000 cycles or more at 700 °C at a maximum stress of 700 MPa; 3. Titanium alloys having a stress-rupture life' of 10 000 hours or longer at 450 °C at a stress of 200 MPa or a low cycle fatigue life of 10 000 cycles or more at 450 °C at a maximum stress of 400 MPa; 4. Aluminium alloys having a tensile strength of 240 MPa or more at 200 °C or a tensile strength of 415 MPa or more at 25 °C; 5. Magnesium alloys having a tensile strength of 345 MPa or more and a corrosion rate of less than 1 mm/year in 3 % sodium chloride aqueous solution measured in accordance with ASTM standard G-31 or national equivalents; 6. Metal alloy powder or particulate material, having all of the following and made from any of the following composition systems: a. Nickel alloys (Ni-Al-X, Ni-X-Al) qualified for turbine engine parts or components, i.e. with less than 3 non-metallic particles (introduced during the manufacturing process) larger than 100 μm in 10 9 alloy particles b. Niobium alloys (Nb-Al-X or Nb-X-Al, Nb-Si-X or Nb-X-Si, Nb Ti X or Nb-X-Ti) c. Titanium alloys (Ti-Al-X or Ti-X-Al) d. Aluminium alloys (Al-Mg-X or Al-X-Mg, Al-Zn-X or Al-X-Zn, Al Fe-X or Al-X-Fe) or e. Magnesium alloys (Mg-Al-X or Mg-X-Al) 7. Made in a controlled environment by any of the following processes: a. ‘Vacuum atomization’ b. ‘Gas atomization’ c. ‘Rotary atomization’ d. ‘Splat quenching’ e. ‘Melt spinning and comminution’ Note: Unless provision to the contrary is made, the words ‘metals’ and ‘alloys’ cover crude and semi-fabricated forms. Crude forms: anodes, balls, bars (including notched bars and wire bars), billets, blocks, blooms, brickets, cakes, cathodes, crystals, cubes, dice, grains, granules, ingots, lumps, pellets, pigs, powder, rondelles, shot, slabs, slugs, sponge, sticks. Semi-fabricated forms: Wrought or worked materials fabricated by rolling, drawing, extruding, forging, impact extruding, pressing, graining, atomising, and grinding, i.e.: angles, channels, circles, discs, dust, flakes, foils and leaf, forging, plate, powder, pressings and stampings, ribbons, rings, rods (including bare welding rods, wire rods, and rolled wire), sections, shapes, sheets, strip, pipe and tubes (including tube rounds, squares, and hollows), drawn or extruded wire. Cast material produced by casting in sand, die, metal, plaster or other types of moulds, including high pressure castings, sintered forms, and forms made by powder metallurgy.

    Authority: EU
    Prohibited Supply To: KP
    Program: KP
    EU Code: VII.A1.004
    Code: 1C002
    Good

    Metal alloys, metal alloy powder and alloyed materials including the following: (a) Aluminides, including: 1. Nickel aluminides containing a minimum of 15 % by weight aluminium, a maximum of 38 % by weight aluminium and at least one additional alloying element; 2. Titanium aluminides containing 10 % by weight or more aluminium and at least one additional alloying element. (b) Metal alloys made from the powder or particulate material including: 1. Nickel alloys having a stress-rupture life of 10 000 hours or longer at 650 °C at a stress of 676 MPa or a low cycle fatigue life of 10 000 cycles or more at 550 °C at a maximum stress of 1 095 MPa; 2. Niobium alloys having a stress-rupture life of 10 000 hours or longer at 800 °C at a stress of 400 MPa or a low cycle fatigue life of 10 000 cycles or more at 700 °C at a maximum stress of 700 MPa; 3. Titanium alloys having a stress-rupture life' of 10 000 hours or longer at 450 °C at a stress of 200 MPa or a low cycle fatigue life of 10 000 cycles or more at 450 °C at a maximum stress of 400 MPa; 4. Aluminium alloys having a tensile strength of 240 MPa or more at 200 °C or a tensile strength of 415 MPa or more at 25 °C; 5. Magnesium alloys having a tensile strength of 345 MPa or more and a corrosion rate of less than 1 mm/year in 3 % sodium chloride aqueous solution measured in accordance with ASTM standard G-31 or national equivalents; 6. Metal alloy powder or particulate material, having all of the following and made from any of the following composition systems: a. Nickel alloys (Ni-Al-X, Ni-X-Al) qualified for turbine engine parts or components, i.e. with less than 3 non-metallic particles (introduced during the manufacturing process) larger than 100 μm in 10 9 alloy particles b. Niobium alloys (Nb-Al-X or Nb-X-Al, Nb-Si-X or Nb-X-Si, Nb Ti X or Nb-X-Ti) c. Titanium alloys (Ti-Al-X or Ti-X-Al) d. Aluminium alloys (Al-Mg-X or Al-X-Mg, Al-Zn-X or Al-X-Zn, Al Fe-X or Al-X-Fe) or e. Magnesium alloys (Mg-Al-X or Mg-X-Al) 7. Made in a controlled environment by any of the following processes: a. ‘Vacuum atomization’ b. ‘Gas atomization’ c. ‘Rotary atomization’ d. ‘Splat quenching’ e. ‘Melt spinning and comminution’ Note: Unless provision to the contrary is made, the words ‘metals’ and ‘alloys’ cover crude and semi-fabricated forms. Crude forms: anodes, balls, bars (including notched bars and wire bars), billets, blocks, blooms, brickets, cakes, cathodes, crystals, cubes, dice, grains, granules, ingots, lumps, pellets, pigs, powder, rondelles, shot, slabs, slugs, sponge, sticks. Semi-fabricated forms: Wrought or worked materials fabricated by rolling, drawing, extruding, forging, impact extruding, pressing, graining, atomising, and grinding, i.e.: angles, channels, circles, discs, dust, flakes, foils and leaf, forging, plate, powder, pressings and stampings, ribbons, rings, rods (including bare welding rods, wire rods, and rolled wire), sections, shapes, sheets, strip, pipe and tubes (including tube rounds, squares, and hollows), drawn or extruded wire. Cast material produced by casting in sand, die, metal, plaster or other types of moulds, including high pressure castings, sintered forms, and forms made by powder metallurgy.

    Authority: EU
    Prohibited Supply To: KP
    Program: KP
    EU Code: VII.A1.004
    Code: 1C002
  • Good

    Equipment for the ‘production’ or inspection of ‘composite’ structures Specially designed components and accessories to include: (a) Filament winding machines, of which the motions for positioning, wrapping and winding fibres are coordinated and programmed in three or more ‘primary servo positioning’ axes, specially designed for the manufacture of ‘composite’ structures or laminates, from ‘fibrous or filamentary materials’. (b) ‘Tape-laying machines’, of which the motions for positioning and laying tape are coordinated and programmed in five or more ‘primary servo positioning’ axes, specially designed for the manufacture of ‘composite’ airframe or missile structures. (c) Multidirectional, multidimensional weaving machines or interlacing machines, including adapters and modification kits, specially designed or modified for weaving, interlacing or braiding fibres for ‘composite’ structures. (d) Equipment specially designed or adapted for the ‘production’ of reinforcement fibres, as follows: 1. Equipment for converting polymeric fibres (such as polyacrylonitrile, rayon, pitch or polycarbosilane) into carbon fibres or silicon carbide fibres, including special equipment to strain the fibre during heating; 2. Equipment for the chemical vapor deposition of elements or compounds, on heated filamentary substrates, to manufacture silicon carbide fibres; 3. Equipment for the wet-spinning of refractory ceramics (such as aluminium oxide); 4. Equipment for converting aluminium containing precursor fibres into alumina fibres by heat treatment; 5. Equipment for producing prepregs specified in VII.A1.003, paragraph ‘d’, under ‘Materials’, by the hot melt method; 6. Non-destructive inspection equipment specially designed for ‘composite’ materials, as follows: a. X-ray tomography systems for three dimensional defect inspection; b. Numerically controlled ultrasonic testing machines of which the motions for positioning transmitters or receivers are simultaneously coordinated and programmed in four or more axes to follow the three dimensional contours of the component under inspection. Notes: 1. For the purposes of this ‘tape-laying machines’ have the ability to lay one or more ‘filament bands’ limited to widths greater than 25 mm and less than or equal to 305 mm, and to cut and restart individual ‘filament band’ courses during the laying process. 2. The technique of interlacing includes knitting.

    Authority: EU
    Prohibited Supply To: IRKP
    Program: KP
    EU Code: VII.A1.003
    Code: 1B201
    Good

    Equipment for the ‘production’ or inspection of ‘composite’ structures Specially designed components and accessories to include: (a) Filament winding machines, of which the motions for positioning, wrapping and winding fibres are coordinated and programmed in three or more ‘primary servo positioning’ axes, specially designed for the manufacture of ‘composite’ structures or laminates, from ‘fibrous or filamentary materials’. (b) ‘Tape-laying machines’, of which the motions for positioning and laying tape are coordinated and programmed in five or more ‘primary servo positioning’ axes, specially designed for the manufacture of ‘composite’ airframe or missile structures. (c) Multidirectional, multidimensional weaving machines or interlacing machines, including adapters and modification kits, specially designed or modified for weaving, interlacing or braiding fibres for ‘composite’ structures. (d) Equipment specially designed or adapted for the ‘production’ of reinforcement fibres, as follows: 1. Equipment for converting polymeric fibres (such as polyacrylonitrile, rayon, pitch or polycarbosilane) into carbon fibres or silicon carbide fibres, including special equipment to strain the fibre during heating; 2. Equipment for the chemical vapor deposition of elements or compounds, on heated filamentary substrates, to manufacture silicon carbide fibres; 3. Equipment for the wet-spinning of refractory ceramics (such as aluminium oxide); 4. Equipment for converting aluminium containing precursor fibres into alumina fibres by heat treatment; 5. Equipment for producing prepregs specified in VII.A1.003, paragraph ‘d’, under ‘Materials’, by the hot melt method; 6. Non-destructive inspection equipment specially designed for ‘composite’ materials, as follows: a. X-ray tomography systems for three dimensional defect inspection; b. Numerically controlled ultrasonic testing machines of which the motions for positioning transmitters or receivers are simultaneously coordinated and programmed in four or more axes to follow the three dimensional contours of the component under inspection. Notes: 1. For the purposes of this ‘tape-laying machines’ have the ability to lay one or more ‘filament bands’ limited to widths greater than 25 mm and less than or equal to 305 mm, and to cut and restart individual ‘filament band’ courses during the laying process. 2. The technique of interlacing includes knitting.

    Authority: EU
    Prohibited Supply To: IRKP
    Program: KP
    EU Code: VII.A1.003
    Code: 1B201
  • Good

    Equipment for the ‘production’ or inspection of ‘composite’ structures Specially designed components and accessories to include: (a) Filament winding machines, of which the motions for positioning, wrapping and winding fibres are coordinated and programmed in three or more ‘primary servo positioning’ axes, specially designed for the manufacture of ‘composite’ structures or laminates, from ‘fibrous or filamentary materials’. (b) ‘Tape-laying machines’, of which the motions for positioning and laying tape are coordinated and programmed in five or more ‘primary servo positioning’ axes, specially designed for the manufacture of ‘composite’ airframe or missile structures. (c) Multidirectional, multidimensional weaving machines or interlacing machines, including adapters and modification kits, specially designed or modified for weaving, interlacing or braiding fibres for ‘composite’ structures. (d) Equipment specially designed or adapted for the ‘production’ of reinforcement fibres, as follows: 1. Equipment for converting polymeric fibres (such as polyacrylonitrile, rayon, pitch or polycarbosilane) into carbon fibres or silicon carbide fibres, including special equipment to strain the fibre during heating; 2. Equipment for the chemical vapor deposition of elements or compounds, on heated filamentary substrates, to manufacture silicon carbide fibres; 3. Equipment for the wet-spinning of refractory ceramics (such as aluminium oxide); 4. Equipment for converting aluminium containing precursor fibres into alumina fibres by heat treatment; 5. Equipment for producing prepregs specified in VII.A1.003, paragraph ‘d’, under ‘Materials’, by the hot melt method; 6. Non-destructive inspection equipment specially designed for ‘composite’ materials, as follows: a. X-ray tomography systems for three dimensional defect inspection; b. Numerically controlled ultrasonic testing machines of which the motions for positioning transmitters or receivers are simultaneously coordinated and programmed in four or more axes to follow the three dimensional contours of the component under inspection. Notes: 1. For the purposes of this ‘tape-laying machines’ have the ability to lay one or more ‘filament bands’ limited to widths greater than 25 mm and less than or equal to 305 mm, and to cut and restart individual ‘filament band’ courses during the laying process. 2. The technique of interlacing includes knitting.

    Authority: EU
    Prohibited Supply To: IRKP
    Program: KP
    EU Code: VII.A1.003
    Code: 1B101
    Good

    Equipment for the ‘production’ or inspection of ‘composite’ structures Specially designed components and accessories to include: (a) Filament winding machines, of which the motions for positioning, wrapping and winding fibres are coordinated and programmed in three or more ‘primary servo positioning’ axes, specially designed for the manufacture of ‘composite’ structures or laminates, from ‘fibrous or filamentary materials’. (b) ‘Tape-laying machines’, of which the motions for positioning and laying tape are coordinated and programmed in five or more ‘primary servo positioning’ axes, specially designed for the manufacture of ‘composite’ airframe or missile structures. (c) Multidirectional, multidimensional weaving machines or interlacing machines, including adapters and modification kits, specially designed or modified for weaving, interlacing or braiding fibres for ‘composite’ structures. (d) Equipment specially designed or adapted for the ‘production’ of reinforcement fibres, as follows: 1. Equipment for converting polymeric fibres (such as polyacrylonitrile, rayon, pitch or polycarbosilane) into carbon fibres or silicon carbide fibres, including special equipment to strain the fibre during heating; 2. Equipment for the chemical vapor deposition of elements or compounds, on heated filamentary substrates, to manufacture silicon carbide fibres; 3. Equipment for the wet-spinning of refractory ceramics (such as aluminium oxide); 4. Equipment for converting aluminium containing precursor fibres into alumina fibres by heat treatment; 5. Equipment for producing prepregs specified in VII.A1.003, paragraph ‘d’, under ‘Materials’, by the hot melt method; 6. Non-destructive inspection equipment specially designed for ‘composite’ materials, as follows: a. X-ray tomography systems for three dimensional defect inspection; b. Numerically controlled ultrasonic testing machines of which the motions for positioning transmitters or receivers are simultaneously coordinated and programmed in four or more axes to follow the three dimensional contours of the component under inspection. Notes: 1. For the purposes of this ‘tape-laying machines’ have the ability to lay one or more ‘filament bands’ limited to widths greater than 25 mm and less than or equal to 305 mm, and to cut and restart individual ‘filament band’ courses during the laying process. 2. The technique of interlacing includes knitting.

    Authority: EU
    Prohibited Supply To: IRKP
    Program: KP
    EU Code: VII.A1.003
    Code: 1B101
  • Good

    Equipment for the ‘production’ or inspection of ‘composite’ structures Specially designed components and accessories to include: (a) Filament winding machines, of which the motions for positioning, wrapping and winding fibres are coordinated and programmed in three or more ‘primary servo positioning’ axes, specially designed for the manufacture of ‘composite’ structures or laminates, from ‘fibrous or filamentary materials’. (b) ‘Tape-laying machines’, of which the motions for positioning and laying tape are coordinated and programmed in five or more ‘primary servo positioning’ axes, specially designed for the manufacture of ‘composite’ airframe or missile structures. (c) Multidirectional, multidimensional weaving machines or interlacing machines, including adapters and modification kits, specially designed or modified for weaving, interlacing or braiding fibres for ‘composite’ structures. (d) Equipment specially designed or adapted for the ‘production’ of reinforcement fibres, as follows: 1. Equipment for converting polymeric fibres (such as polyacrylonitrile, rayon, pitch or polycarbosilane) into carbon fibres or silicon carbide fibres, including special equipment to strain the fibre during heating; 2. Equipment for the chemical vapor deposition of elements or compounds, on heated filamentary substrates, to manufacture silicon carbide fibres; 3. Equipment for the wet-spinning of refractory ceramics (such as aluminium oxide); 4. Equipment for converting aluminium containing precursor fibres into alumina fibres by heat treatment; 5. Equipment for producing prepregs specified in VII.A1.003, paragraph ‘d’, under ‘Materials’, by the hot melt method; 6. Non-destructive inspection equipment specially designed for ‘composite’ materials, as follows: a. X-ray tomography systems for three dimensional defect inspection; b. Numerically controlled ultrasonic testing machines of which the motions for positioning transmitters or receivers are simultaneously coordinated and programmed in four or more axes to follow the three dimensional contours of the component under inspection. Notes: 1. For the purposes of this ‘tape-laying machines’ have the ability to lay one or more ‘filament bands’ limited to widths greater than 25 mm and less than or equal to 305 mm, and to cut and restart individual ‘filament band’ courses during the laying process. 2. The technique of interlacing includes knitting.

    Authority: EU
    Prohibited Supply To: IRKP
    Program: KP
    EU Code: VII.A1.003
    Code: 1B001
    Good

    Equipment for the ‘production’ or inspection of ‘composite’ structures Specially designed components and accessories to include: (a) Filament winding machines, of which the motions for positioning, wrapping and winding fibres are coordinated and programmed in three or more ‘primary servo positioning’ axes, specially designed for the manufacture of ‘composite’ structures or laminates, from ‘fibrous or filamentary materials’. (b) ‘Tape-laying machines’, of which the motions for positioning and laying tape are coordinated and programmed in five or more ‘primary servo positioning’ axes, specially designed for the manufacture of ‘composite’ airframe or missile structures. (c) Multidirectional, multidimensional weaving machines or interlacing machines, including adapters and modification kits, specially designed or modified for weaving, interlacing or braiding fibres for ‘composite’ structures. (d) Equipment specially designed or adapted for the ‘production’ of reinforcement fibres, as follows: 1. Equipment for converting polymeric fibres (such as polyacrylonitrile, rayon, pitch or polycarbosilane) into carbon fibres or silicon carbide fibres, including special equipment to strain the fibre during heating; 2. Equipment for the chemical vapor deposition of elements or compounds, on heated filamentary substrates, to manufacture silicon carbide fibres; 3. Equipment for the wet-spinning of refractory ceramics (such as aluminium oxide); 4. Equipment for converting aluminium containing precursor fibres into alumina fibres by heat treatment; 5. Equipment for producing prepregs specified in VII.A1.003, paragraph ‘d’, under ‘Materials’, by the hot melt method; 6. Non-destructive inspection equipment specially designed for ‘composite’ materials, as follows: a. X-ray tomography systems for three dimensional defect inspection; b. Numerically controlled ultrasonic testing machines of which the motions for positioning transmitters or receivers are simultaneously coordinated and programmed in four or more axes to follow the three dimensional contours of the component under inspection. Notes: 1. For the purposes of this ‘tape-laying machines’ have the ability to lay one or more ‘filament bands’ limited to widths greater than 25 mm and less than or equal to 305 mm, and to cut and restart individual ‘filament band’ courses during the laying process. 2. The technique of interlacing includes knitting.

    Authority: EU
    Prohibited Supply To: IRKP
    Program: KP
    EU Code: VII.A1.003
    Code: 1B001
  • Good

    ‘Fibrous or filamentary materials’ having any of the following: (a) Materials composed of aromatic polyetherimides having a glass transition temperature (Tg) exceeding 290 °C. (b) Polyarylene ketones. (c) Polyarylene sulphides where the arlylene group is biphenylene, triphenylene or combinations thereof (d) Polybiphenylenethersulphone having a Tg exceeding 290 °C, or (e) Any of the above materials commingled with any of the following: 1. Organic ‘fibrous or filamentary materials’, with a ‘specific modulus’ exceeding 12,7 × 10 6 m and ‘specific tensile strength’ exceeding 23,5 × 10 4 m, 2. Carbon ‘fibrous or filamentary materials’, having a ‘specific modulus’ exceeding 14,65 × 10 6 m and ‘specific tensile strength’ exceeding 26,82 × 10 4 m, 3. Inorganic ‘fibrous or filamentary materials’, having a ‘specific modulus’ exceeding 2,54 × 10 6 m and melting, softening, decomposition or sublimation point exceeding 1 649 °C in an inert environment. 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 an area not exceeding 1 m 2 ; a length not exceeding 2,5 m; and a width exceeding 15 mm. — Mechanically chopped, milled or cut carbon ‘fibrous or filamentary materials’ 25,0 mm or less in length. 3. Does not apply to 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; molybdenum and molybdenum alloy fibres; boron fibres; discontinuous ceramic fibres with a melting, softening, decomposition or sublimation point lower than 1 770 °C in an inert environment

    Authority: EU
    Prohibited Supply To: IRKP
    Program: KP
    EU Code: VII.A1.002
    Code: 9C110
    Good

    ‘Fibrous or filamentary materials’ having any of the following: (a) Materials composed of aromatic polyetherimides having a glass transition temperature (Tg) exceeding 290 °C. (b) Polyarylene ketones. (c) Polyarylene sulphides where the arlylene group is biphenylene, triphenylene or combinations thereof (d) Polybiphenylenethersulphone having a Tg exceeding 290 °C, or (e) Any of the above materials commingled with any of the following: 1. Organic ‘fibrous or filamentary materials’, with a ‘specific modulus’ exceeding 12,7 × 10 6 m and ‘specific tensile strength’ exceeding 23,5 × 10 4 m, 2. Carbon ‘fibrous or filamentary materials’, having a ‘specific modulus’ exceeding 14,65 × 10 6 m and ‘specific tensile strength’ exceeding 26,82 × 10 4 m, 3. Inorganic ‘fibrous or filamentary materials’, having a ‘specific modulus’ exceeding 2,54 × 10 6 m and melting, softening, decomposition or sublimation point exceeding 1 649 °C in an inert environment. 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 an area not exceeding 1 m 2 ; a length not exceeding 2,5 m; and a width exceeding 15 mm. — Mechanically chopped, milled or cut carbon ‘fibrous or filamentary materials’ 25,0 mm or less in length. 3. Does not apply to 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; molybdenum and molybdenum alloy fibres; boron fibres; discontinuous ceramic fibres with a melting, softening, decomposition or sublimation point lower than 1 770 °C in an inert environment

    Authority: EU
    Prohibited Supply To: IRKP
    Program: KP
    EU Code: VII.A1.002
    Code: 9C110
  • Good

    ‘Fibrous or filamentary materials’ having any of the following: (a) Materials composed of aromatic polyetherimides having a glass transition temperature (Tg) exceeding 290 °C. (b) Polyarylene ketones. (c) Polyarylene sulphides where the arlylene group is biphenylene, triphenylene or combinations thereof (d) Polybiphenylenethersulphone having a Tg exceeding 290 °C, or (e) Any of the above materials commingled with any of the following: 1. Organic ‘fibrous or filamentary materials’, with a ‘specific modulus’ exceeding 12,7 × 10 6 m and ‘specific tensile strength’ exceeding 23,5 × 10 4 m, 2. Carbon ‘fibrous or filamentary materials’, having a ‘specific modulus’ exceeding 14,65 × 10 6 m and ‘specific tensile strength’ exceeding 26,82 × 10 4 m, 3. Inorganic ‘fibrous or filamentary materials’, having a ‘specific modulus’ exceeding 2,54 × 10 6 m and melting, softening, decomposition or sublimation point exceeding 1 649 °C in an inert environment. 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 an area not exceeding 1 m 2 ; a length not exceeding 2,5 m; and a width exceeding 15 mm. — Mechanically chopped, milled or cut carbon ‘fibrous or filamentary materials’ 25,0 mm or less in length. 3. Does not apply to 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; molybdenum and molybdenum alloy fibres; boron fibres; discontinuous ceramic fibres with a melting, softening, decomposition or sublimation point lower than 1 770 °C in an inert environment

    Authority: EU
    Prohibited Supply To: IRKP
    Program: KP
    EU Code: VII.A1.002
    Code: 1C210
    Good

    ‘Fibrous or filamentary materials’ having any of the following: (a) Materials composed of aromatic polyetherimides having a glass transition temperature (Tg) exceeding 290 °C. (b) Polyarylene ketones. (c) Polyarylene sulphides where the arlylene group is biphenylene, triphenylene or combinations thereof (d) Polybiphenylenethersulphone having a Tg exceeding 290 °C, or (e) Any of the above materials commingled with any of the following: 1. Organic ‘fibrous or filamentary materials’, with a ‘specific modulus’ exceeding 12,7 × 10 6 m and ‘specific tensile strength’ exceeding 23,5 × 10 4 m, 2. Carbon ‘fibrous or filamentary materials’, having a ‘specific modulus’ exceeding 14,65 × 10 6 m and ‘specific tensile strength’ exceeding 26,82 × 10 4 m, 3. Inorganic ‘fibrous or filamentary materials’, having a ‘specific modulus’ exceeding 2,54 × 10 6 m and melting, softening, decomposition or sublimation point exceeding 1 649 °C in an inert environment. 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 an area not exceeding 1 m 2 ; a length not exceeding 2,5 m; and a width exceeding 15 mm. — Mechanically chopped, milled or cut carbon ‘fibrous or filamentary materials’ 25,0 mm or less in length. 3. Does not apply to 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; molybdenum and molybdenum alloy fibres; boron fibres; discontinuous ceramic fibres with a melting, softening, decomposition or sublimation point lower than 1 770 °C in an inert environment

    Authority: EU
    Prohibited Supply To: IRKP
    Program: KP
    EU Code: VII.A1.002
    Code: 1C210
  • Good

    ‘Fibrous or filamentary materials’ having any of the following: (a) Materials composed of aromatic polyetherimides having a glass transition temperature (Tg) exceeding 290 °C. (b) Polyarylene ketones. (c) Polyarylene sulphides where the arlylene group is biphenylene, triphenylene or combinations thereof (d) Polybiphenylenethersulphone having a Tg exceeding 290 °C, or (e) Any of the above materials commingled with any of the following: 1. Organic ‘fibrous or filamentary materials’, with a ‘specific modulus’ exceeding 12,7 × 10 6 m and ‘specific tensile strength’ exceeding 23,5 × 10 4 m, 2. Carbon ‘fibrous or filamentary materials’, having a ‘specific modulus’ exceeding 14,65 × 10 6 m and ‘specific tensile strength’ exceeding 26,82 × 10 4 m, 3. Inorganic ‘fibrous or filamentary materials’, having a ‘specific modulus’ exceeding 2,54 × 10 6 m and melting, softening, decomposition or sublimation point exceeding 1 649 °C in an inert environment. 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 an area not exceeding 1 m 2 ; a length not exceeding 2,5 m; and a width exceeding 15 mm. — Mechanically chopped, milled or cut carbon ‘fibrous or filamentary materials’ 25,0 mm or less in length. 3. Does not apply to 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; molybdenum and molybdenum alloy fibres; boron fibres; discontinuous ceramic fibres with a melting, softening, decomposition or sublimation point lower than 1 770 °C in an inert environment

    Authority: EU
    Prohibited Supply To: IRKP
    Program: KP
    EU Code: VII.A1.002
    Code: 1C010
    Good

    ‘Fibrous or filamentary materials’ having any of the following: (a) Materials composed of aromatic polyetherimides having a glass transition temperature (Tg) exceeding 290 °C. (b) Polyarylene ketones. (c) Polyarylene sulphides where the arlylene group is biphenylene, triphenylene or combinations thereof (d) Polybiphenylenethersulphone having a Tg exceeding 290 °C, or (e) Any of the above materials commingled with any of the following: 1. Organic ‘fibrous or filamentary materials’, with a ‘specific modulus’ exceeding 12,7 × 10 6 m and ‘specific tensile strength’ exceeding 23,5 × 10 4 m, 2. Carbon ‘fibrous or filamentary materials’, having a ‘specific modulus’ exceeding 14,65 × 10 6 m and ‘specific tensile strength’ exceeding 26,82 × 10 4 m, 3. Inorganic ‘fibrous or filamentary materials’, having a ‘specific modulus’ exceeding 2,54 × 10 6 m and melting, softening, decomposition or sublimation point exceeding 1 649 °C in an inert environment. 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 an area not exceeding 1 m 2 ; a length not exceeding 2,5 m; and a width exceeding 15 mm. — Mechanically chopped, milled or cut carbon ‘fibrous or filamentary materials’ 25,0 mm or less in length. 3. Does not apply to 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; molybdenum and molybdenum alloy fibres; boron fibres; discontinuous ceramic fibres with a melting, softening, decomposition or sublimation point lower than 1 770 °C in an inert environment

    Authority: EU
    Prohibited Supply To: IRKP
    Program: KP
    EU Code: VII.A1.002
    Code: 1C010
  • Good

    ‘Fibrous or filamentary materials’ having any of the following: (a) Materials composed of aromatic polyetherimides having a glass transition temperature (Tg) exceeding 290 °C. (b) Polyarylene ketones. (c) Polyarylene sulphides where the arlylene group is biphenylene, triphenylene or combinations thereof (d) Polybiphenylenethersulphone having a Tg exceeding 290 °C, or (e) Any of the above materials commingled with any of the following: 1. Organic ‘fibrous or filamentary materials’, with a ‘specific modulus’ exceeding 12,7 × 10 6 m and ‘specific tensile strength’ exceeding 23,5 × 10 4 m, 2. Carbon ‘fibrous or filamentary materials’, having a ‘specific modulus’ exceeding 14,65 × 10 6 m and ‘specific tensile strength’ exceeding 26,82 × 10 4 m, 3. Inorganic ‘fibrous or filamentary materials’, having a ‘specific modulus’ exceeding 2,54 × 10 6 m and melting, softening, decomposition or sublimation point exceeding 1 649 °C in an inert environment. 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 an area not exceeding 1 m 2 ; a length not exceeding 2,5 m; and a width exceeding 15 mm. — Mechanically chopped, milled or cut carbon ‘fibrous or filamentary materials’ 25,0 mm or less in length. 3. Does not apply to 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; molybdenum and molybdenum alloy fibres; boron fibres; discontinuous ceramic fibres with a melting, softening, decomposition or sublimation point lower than 1 770 °C in an inert environment

    Authority: EU
    Prohibited Supply To: KP
    Program: KP
    EU Code: VII.A1.002
    Code: 1C008
    Good

    ‘Fibrous or filamentary materials’ having any of the following: (a) Materials composed of aromatic polyetherimides having a glass transition temperature (Tg) exceeding 290 °C. (b) Polyarylene ketones. (c) Polyarylene sulphides where the arlylene group is biphenylene, triphenylene or combinations thereof (d) Polybiphenylenethersulphone having a Tg exceeding 290 °C, or (e) Any of the above materials commingled with any of the following: 1. Organic ‘fibrous or filamentary materials’, with a ‘specific modulus’ exceeding 12,7 × 10 6 m and ‘specific tensile strength’ exceeding 23,5 × 10 4 m, 2. Carbon ‘fibrous or filamentary materials’, having a ‘specific modulus’ exceeding 14,65 × 10 6 m and ‘specific tensile strength’ exceeding 26,82 × 10 4 m, 3. Inorganic ‘fibrous or filamentary materials’, having a ‘specific modulus’ exceeding 2,54 × 10 6 m and melting, softening, decomposition or sublimation point exceeding 1 649 °C in an inert environment. 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 an area not exceeding 1 m 2 ; a length not exceeding 2,5 m; and a width exceeding 15 mm. — Mechanically chopped, milled or cut carbon ‘fibrous or filamentary materials’ 25,0 mm or less in length. 3. Does not apply to 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; molybdenum and molybdenum alloy fibres; boron fibres; discontinuous ceramic fibres with a melting, softening, decomposition or sublimation point lower than 1 770 °C in an inert environment

    Authority: EU
    Prohibited Supply To: KP
    Program: KP
    EU Code: VII.A1.002
    Code: 1C008
  • Good

    ‘Composite’ structures or laminates consisting of an organic ‘matrix’ and materials as follows: Note: Does not apply to ‘composite’ structures or laminates, made from epoxy resin impregnated carbon ‘fibrous or filamentary materials’, for the repair of ‘civil aircraft’ structures or laminates, having all of the following: — An area not exceeding 1 m 2 ; — A length not exceeding 2,5 m; — A width exceeding 15 mm. Does not apply to semi-finished items, specially designed for purely civilian applications as follows: sporting goods, automotive industry, machine tool industry, medical applications. Does not apply to finished items specially designed for a specific application. (a) Inorganic ‘fibrous or filamentary materials’ that have a ‘specific modulus’ exceeding 2,54 × 10 6 m and a melting, softening, decomposition or sublimation point exceeding 1 649 °C in an inert environment. Note : Does not apply to the following — 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 — Molybdenum and molybdenum alloy fibres — Boron fibres — Discontinuous ceramic fibres with a melting, softening, decomposition or sublimation point lower than 1 770 °C in an inert environment. (b) ‘Fibrous or filamentary materials’ having any of the following: 1. Materials composed of aromatic polyetherimides having a glass transition temperature (Tg) exceeding 290 °C, 2. Polyarylene ketones, 3. Polyarylene sulphides where the arlylene group is biphenylene, triphenylene or combinations thereof, 4. Polybiphenylenethersulphone having a Tg exceeding 290 °C, or 5. Any of the above materials ‘commingled’ with any of the following: a. Organic ‘fibrous or filamentary materials’, with a ‘specific modulus’ exceeding 12,7 × 10 6 m and a ‘specific tensile strength’ exceeding 23,5 × 10 4 m. b. Carbon ‘fibrous or filamentary materials’, having a ‘specific modulus’ exceeding 14,65 × 10 6 m; and specific tensile strength exceeding 26,82 × 10 4 m. c. Inorganic ‘fibrous or filamentary materials’, having a ‘specific modulus’ exceeding 2,54 × 10 6 m; and a melting, softening, decomposition or sublimation point exceeding 1 649 °C in an inert environment. 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 an area not exceeding 1 m 2 ; a length not exceeding 2,5 m; and a width exceeding 15 mm. — Mechanically chopped, milled or cut carbon ‘fibrous or filamentary materials’ 25,0 mm or less in length. 3. Does not apply to 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; molybdenum and molybdenum alloy fibres; boron fibres; discontinuous ceramic fibres with a melting, softening, decomposition or sublimation point lower than 1 770 °C in an inert environment. (c) Organic ‘fibrous or filamentary materials’ with a ‘specific modulus’ exceeding 12,7 × 10 6 m and with a ‘specific tensile strength’ exceeding 23,5 × 10 4 m. (d) Carbon ‘fibrous or filamentary materials’ having a ‘specific modulus’ exceeding 14,65 × 10 6 m and a specific tensile exceeding 26,82 × 10 4 m. (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 any of the following ‘fibrous or filamentary materials’ and resins: 1. Inorganic ‘fibrous or filamentary materials’ with a ‘specific modulus’ exceeding 2,54 × 10 6 m and a melting, softening, decomposition or sublimation point exceeding 1 649 °C in an inert environment, or 2. Organic or carbon ‘fibrous or filamentary materials’, having all of the following: a. ‘Specific modulus’ exceeding 10,15 × 10 6 m; and b. ‘Specific tensile strength’ exceeding 17,7 × 10 4 m; or 3. Resin or pitch, from unprocessed fluorinated compounds such as: a. Fluorinated polyimides containing 10 % by weight or more of combined fluorine; b. Fluorinated phosphazene elastomers containing 30 % by weight or more of combined fluorine; or 4. Phenolic resins with Dynamic Mechanical Analysis glass transition temperature (DMA Tg) equal to, or exceeding, 180 °C and having a phenolic resin; or 5. Other resin or pitch with Dynamic Mechanical Analysis glass transition temperature (DMA Tg) equal to, or exceeding, 232 °C. Note: Does not apply to — Epoxy resin ‘matrix’ impregnated carbon ‘fibrous or filamentary materials’ (prepregs) for the repair of ‘civil aircraft’ structures or laminates, having all of the following; — An area not exceeding 1 m 2 ; — A length not exceeding 2,5 m; and — A width exceeding 15 mm

    Authority: EU
    Prohibited Supply To: IRKP
    Program: KP
    EU Code: VII.A1.001
    Code: 1A202
    Good

    ‘Composite’ structures or laminates consisting of an organic ‘matrix’ and materials as follows: Note: Does not apply to ‘composite’ structures or laminates, made from epoxy resin impregnated carbon ‘fibrous or filamentary materials’, for the repair of ‘civil aircraft’ structures or laminates, having all of the following: — An area not exceeding 1 m 2 ; — A length not exceeding 2,5 m; — A width exceeding 15 mm. Does not apply to semi-finished items, specially designed for purely civilian applications as follows: sporting goods, automotive industry, machine tool industry, medical applications. Does not apply to finished items specially designed for a specific application. (a) Inorganic ‘fibrous or filamentary materials’ that have a ‘specific modulus’ exceeding 2,54 × 10 6 m and a melting, softening, decomposition or sublimation point exceeding 1 649 °C in an inert environment. Note : Does not apply to the following — 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 — Molybdenum and molybdenum alloy fibres — Boron fibres — Discontinuous ceramic fibres with a melting, softening, decomposition or sublimation point lower than 1 770 °C in an inert environment. (b) ‘Fibrous or filamentary materials’ having any of the following: 1. Materials composed of aromatic polyetherimides having a glass transition temperature (Tg) exceeding 290 °C, 2. Polyarylene ketones, 3. Polyarylene sulphides where the arlylene group is biphenylene, triphenylene or combinations thereof, 4. Polybiphenylenethersulphone having a Tg exceeding 290 °C, or 5. Any of the above materials ‘commingled’ with any of the following: a. Organic ‘fibrous or filamentary materials’, with a ‘specific modulus’ exceeding 12,7 × 10 6 m and a ‘specific tensile strength’ exceeding 23,5 × 10 4 m. b. Carbon ‘fibrous or filamentary materials’, having a ‘specific modulus’ exceeding 14,65 × 10 6 m; and specific tensile strength exceeding 26,82 × 10 4 m. c. Inorganic ‘fibrous or filamentary materials’, having a ‘specific modulus’ exceeding 2,54 × 10 6 m; and a melting, softening, decomposition or sublimation point exceeding 1 649 °C in an inert environment. 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 an area not exceeding 1 m 2 ; a length not exceeding 2,5 m; and a width exceeding 15 mm. — Mechanically chopped, milled or cut carbon ‘fibrous or filamentary materials’ 25,0 mm or less in length. 3. Does not apply to 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; molybdenum and molybdenum alloy fibres; boron fibres; discontinuous ceramic fibres with a melting, softening, decomposition or sublimation point lower than 1 770 °C in an inert environment. (c) Organic ‘fibrous or filamentary materials’ with a ‘specific modulus’ exceeding 12,7 × 10 6 m and with a ‘specific tensile strength’ exceeding 23,5 × 10 4 m. (d) Carbon ‘fibrous or filamentary materials’ having a ‘specific modulus’ exceeding 14,65 × 10 6 m and a specific tensile exceeding 26,82 × 10 4 m. (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 any of the following ‘fibrous or filamentary materials’ and resins: 1. Inorganic ‘fibrous or filamentary materials’ with a ‘specific modulus’ exceeding 2,54 × 10 6 m and a melting, softening, decomposition or sublimation point exceeding 1 649 °C in an inert environment, or 2. Organic or carbon ‘fibrous or filamentary materials’, having all of the following: a. ‘Specific modulus’ exceeding 10,15 × 10 6 m; and b. ‘Specific tensile strength’ exceeding 17,7 × 10 4 m; or 3. Resin or pitch, from unprocessed fluorinated compounds such as: a. Fluorinated polyimides containing 10 % by weight or more of combined fluorine; b. Fluorinated phosphazene elastomers containing 30 % by weight or more of combined fluorine; or 4. Phenolic resins with Dynamic Mechanical Analysis glass transition temperature (DMA Tg) equal to, or exceeding, 180 °C and having a phenolic resin; or 5. Other resin or pitch with Dynamic Mechanical Analysis glass transition temperature (DMA Tg) equal to, or exceeding, 232 °C. Note: Does not apply to — Epoxy resin ‘matrix’ impregnated carbon ‘fibrous or filamentary materials’ (prepregs) for the repair of ‘civil aircraft’ structures or laminates, having all of the following; — An area not exceeding 1 m 2 ; — A length not exceeding 2,5 m; and — A width exceeding 15 mm

    Authority: EU
    Prohibited Supply To: IRKP
    Program: KP
    EU Code: VII.A1.001
    Code: 1A202
  • Good

    ‘Composite’ structures or laminates consisting of an organic ‘matrix’ and materials as follows: Note: Does not apply to ‘composite’ structures or laminates, made from epoxy resin impregnated carbon ‘fibrous or filamentary materials’, for the repair of ‘civil aircraft’ structures or laminates, having all of the following: — An area not exceeding 1 m 2 ; — A length not exceeding 2,5 m; — A width exceeding 15 mm. Does not apply to semi-finished items, specially designed for purely civilian applications as follows: sporting goods, automotive industry, machine tool industry, medical applications. Does not apply to finished items specially designed for a specific application. (a) Inorganic ‘fibrous or filamentary materials’ that have a ‘specific modulus’ exceeding 2,54 × 10 6 m and a melting, softening, decomposition or sublimation point exceeding 1 649 °C in an inert environment. Note : Does not apply to the following — 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 — Molybdenum and molybdenum alloy fibres — Boron fibres — Discontinuous ceramic fibres with a melting, softening, decomposition or sublimation point lower than 1 770 °C in an inert environment. (b) ‘Fibrous or filamentary materials’ having any of the following: 1. Materials composed of aromatic polyetherimides having a glass transition temperature (Tg) exceeding 290 °C, 2. Polyarylene ketones, 3. Polyarylene sulphides where the arlylene group is biphenylene, triphenylene or combinations thereof, 4. Polybiphenylenethersulphone having a Tg exceeding 290 °C, or 5. Any of the above materials ‘commingled’ with any of the following: a. Organic ‘fibrous or filamentary materials’, with a ‘specific modulus’ exceeding 12,7 × 10 6 m and a ‘specific tensile strength’ exceeding 23,5 × 10 4 m. b. Carbon ‘fibrous or filamentary materials’, having a ‘specific modulus’ exceeding 14,65 × 10 6 m; and specific tensile strength exceeding 26,82 × 10 4 m. c. Inorganic ‘fibrous or filamentary materials’, having a ‘specific modulus’ exceeding 2,54 × 10 6 m; and a melting, softening, decomposition or sublimation point exceeding 1 649 °C in an inert environment. 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 an area not exceeding 1 m 2 ; a length not exceeding 2,5 m; and a width exceeding 15 mm. — Mechanically chopped, milled or cut carbon ‘fibrous or filamentary materials’ 25,0 mm or less in length. 3. Does not apply to 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; molybdenum and molybdenum alloy fibres; boron fibres; discontinuous ceramic fibres with a melting, softening, decomposition or sublimation point lower than 1 770 °C in an inert environment. (c) Organic ‘fibrous or filamentary materials’ with a ‘specific modulus’ exceeding 12,7 × 10 6 m and with a ‘specific tensile strength’ exceeding 23,5 × 10 4 m. (d) Carbon ‘fibrous or filamentary materials’ having a ‘specific modulus’ exceeding 14,65 × 10 6 m and a specific tensile exceeding 26,82 × 10 4 m. (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 any of the following ‘fibrous or filamentary materials’ and resins: 1. Inorganic ‘fibrous or filamentary materials’ with a ‘specific modulus’ exceeding 2,54 × 10 6 m and a melting, softening, decomposition or sublimation point exceeding 1 649 °C in an inert environment, or 2. Organic or carbon ‘fibrous or filamentary materials’, having all of the following: a. ‘Specific modulus’ exceeding 10,15 × 10 6 m; and b. ‘Specific tensile strength’ exceeding 17,7 × 10 4 m; or 3. Resin or pitch, from unprocessed fluorinated compounds such as: a. Fluorinated polyimides containing 10 % by weight or more of combined fluorine; b. Fluorinated phosphazene elastomers containing 30 % by weight or more of combined fluorine; or 4. Phenolic resins with Dynamic Mechanical Analysis glass transition temperature (DMA Tg) equal to, or exceeding, 180 °C and having a phenolic resin; or 5. Other resin or pitch with Dynamic Mechanical Analysis glass transition temperature (DMA Tg) equal to, or exceeding, 232 °C. Note: Does not apply to — Epoxy resin ‘matrix’ impregnated carbon ‘fibrous or filamentary materials’ (prepregs) for the repair of ‘civil aircraft’ structures or laminates, having all of the following; — An area not exceeding 1 m 2 ; — A length not exceeding 2,5 m; and — A width exceeding 15 mm

    Authority: EU
    Prohibited Supply To: IRKP
    Program: KP
    EU Code: VII.A1.001
    Code: 1A002
    Good

    ‘Composite’ structures or laminates consisting of an organic ‘matrix’ and materials as follows: Note: Does not apply to ‘composite’ structures or laminates, made from epoxy resin impregnated carbon ‘fibrous or filamentary materials’, for the repair of ‘civil aircraft’ structures or laminates, having all of the following: — An area not exceeding 1 m 2 ; — A length not exceeding 2,5 m; — A width exceeding 15 mm. Does not apply to semi-finished items, specially designed for purely civilian applications as follows: sporting goods, automotive industry, machine tool industry, medical applications. Does not apply to finished items specially designed for a specific application. (a) Inorganic ‘fibrous or filamentary materials’ that have a ‘specific modulus’ exceeding 2,54 × 10 6 m and a melting, softening, decomposition or sublimation point exceeding 1 649 °C in an inert environment. Note : Does not apply to the following — 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 — Molybdenum and molybdenum alloy fibres — Boron fibres — Discontinuous ceramic fibres with a melting, softening, decomposition or sublimation point lower than 1 770 °C in an inert environment. (b) ‘Fibrous or filamentary materials’ having any of the following: 1. Materials composed of aromatic polyetherimides having a glass transition temperature (Tg) exceeding 290 °C, 2. Polyarylene ketones, 3. Polyarylene sulphides where the arlylene group is biphenylene, triphenylene or combinations thereof, 4. Polybiphenylenethersulphone having a Tg exceeding 290 °C, or 5. Any of the above materials ‘commingled’ with any of the following: a. Organic ‘fibrous or filamentary materials’, with a ‘specific modulus’ exceeding 12,7 × 10 6 m and a ‘specific tensile strength’ exceeding 23,5 × 10 4 m. b. Carbon ‘fibrous or filamentary materials’, having a ‘specific modulus’ exceeding 14,65 × 10 6 m; and specific tensile strength exceeding 26,82 × 10 4 m. c. Inorganic ‘fibrous or filamentary materials’, having a ‘specific modulus’ exceeding 2,54 × 10 6 m; and a melting, softening, decomposition or sublimation point exceeding 1 649 °C in an inert environment. 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 an area not exceeding 1 m 2 ; a length not exceeding 2,5 m; and a width exceeding 15 mm. — Mechanically chopped, milled or cut carbon ‘fibrous or filamentary materials’ 25,0 mm or less in length. 3. Does not apply to 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; molybdenum and molybdenum alloy fibres; boron fibres; discontinuous ceramic fibres with a melting, softening, decomposition or sublimation point lower than 1 770 °C in an inert environment. (c) Organic ‘fibrous or filamentary materials’ with a ‘specific modulus’ exceeding 12,7 × 10 6 m and with a ‘specific tensile strength’ exceeding 23,5 × 10 4 m. (d) Carbon ‘fibrous or filamentary materials’ having a ‘specific modulus’ exceeding 14,65 × 10 6 m and a specific tensile exceeding 26,82 × 10 4 m. (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 any of the following ‘fibrous or filamentary materials’ and resins: 1. Inorganic ‘fibrous or filamentary materials’ with a ‘specific modulus’ exceeding 2,54 × 10 6 m and a melting, softening, decomposition or sublimation point exceeding 1 649 °C in an inert environment, or 2. Organic or carbon ‘fibrous or filamentary materials’, having all of the following: a. ‘Specific modulus’ exceeding 10,15 × 10 6 m; and b. ‘Specific tensile strength’ exceeding 17,7 × 10 4 m; or 3. Resin or pitch, from unprocessed fluorinated compounds such as: a. Fluorinated polyimides containing 10 % by weight or more of combined fluorine; b. Fluorinated phosphazene elastomers containing 30 % by weight or more of combined fluorine; or 4. Phenolic resins with Dynamic Mechanical Analysis glass transition temperature (DMA Tg) equal to, or exceeding, 180 °C and having a phenolic resin; or 5. Other resin or pitch with Dynamic Mechanical Analysis glass transition temperature (DMA Tg) equal to, or exceeding, 232 °C. Note: Does not apply to — Epoxy resin ‘matrix’ impregnated carbon ‘fibrous or filamentary materials’ (prepregs) for the repair of ‘civil aircraft’ structures or laminates, having all of the following; — An area not exceeding 1 m 2 ; — A length not exceeding 2,5 m; and — A width exceeding 15 mm

    Authority: EU
    Prohibited Supply To: IRKP
    Program: KP
    EU Code: VII.A1.001
    Code: 1A002
  • Good

    Nerve agent chemoprophylaxis: — Butyrylcholinesterase (BCHE) — Pyridostigmine bromide (CAS 101-26-8) — Obidoxime chloride (CAS 114-90-9)

    Authority: EU
    Prohibited Supply To: KP
    Program: KP
    EU Code: VI.A1.011
    Good

    Nerve agent chemoprophylaxis: — Butyrylcholinesterase (BCHE) — Pyridostigmine bromide (CAS 101-26-8) — Obidoxime chloride (CAS 114-90-9)

    Authority: EU
    Prohibited Supply To: KP
    Program: KP
    EU Code: VI.A1.011
  • Good

    Additional chemicals suitable for decontamination of chemical warfare agents: Diethylenetriamine (CAS 111-40-0)

    Authority: EU
    Prohibited Supply To: KP
    Program: KP
    EU Code: VI.A1.010
    Good

    Additional chemicals suitable for decontamination of chemical warfare agents: Diethylenetriamine (CAS 111-40-0)

    Authority: EU
    Prohibited Supply To: KP
    Program: KP
    EU Code: VI.A1.010
  • Good

    Full face-mask air-purifying and air-supplying respirators except those used in breathing apparatus for firefighters

    Authority: EU
    Prohibited Supply To: KP
    Program: KP
    EU Code: VI.A1.009
    Code: 2B352
    Good

    Full face-mask air-purifying and air-supplying respirators except those used in breathing apparatus for firefighters

    Authority: EU
    Prohibited Supply To: KP
    Program: KP
    EU Code: VI.A1.009
    Code: 2B352
  • Good

    Filament winding machines and related equipment: Filament winding machines or fibre/tow-placement machines, of which the motions for positioning, wrapping and winding fibres can be coordinated and programmed in two or more axes and which are designed to fabricate composite structures or laminates from fibrous or filamentary materials, coordinating and programming controls and precision mandrels for such equipment

    Authority: EU
    Prohibited Supply To: IRKP
    Program: KP
    EU Code: VI.A1.008
    Code: 1B201
    Good

    Filament winding machines and related equipment: Filament winding machines or fibre/tow-placement machines, of which the motions for positioning, wrapping and winding fibres can be coordinated and programmed in two or more axes and which are designed to fabricate composite structures or laminates from fibrous or filamentary materials, coordinating and programming controls and precision mandrels for such equipment

    Authority: EU
    Prohibited Supply To: IRKP
    Program: KP
    EU Code: VI.A1.008
    Code: 1B201
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