The corresponding systems, equipment and components as identified in Council Regulation (EC) No 428/2009 of 5 May 2009 setting up a Community regime for the control of exports, transfer, brokering and transit of dual-use items

Missile Technology Control Regime (M.TCR): Equipment, software and technology annex

1A002

“Composite” structures or laminates, having any of the following:

a.  Consisting of an organic “matrix” and materials specified in 1C010.c., 1C010.d. or 1C010.e.; or

b.  Consisting of a metal or carbon “matrix”, and any of the following:

1.  Carbon “fibrous or filamentary materials” having all of the following:

a.  A “specific modulus” exceeding 10,15 × 10⁶ m; and

b.  A “specific tensile strength” exceeding 17,7 × 10⁴ m; or

2.  Materials specified in 1C010.c.

Note 1:   1A002 does not control 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:

a.  An area not exceeding 1 m²;

b.  A length not exceeding 2,5 m; and

c.  A width exceeding 15 mm.

Note 2:   1A002 does not control semi-finished items, specially designed for purely civilian applications as follows:

a.  Sporting goods;

b.  Automotive industry;

c.  Machine tool industry;

d.  Medical applications.

Note 3:   1A002.b.1. does not control semi-finished items containing a maximum of two dimensions of interwoven filaments and specially designed for applications as follows:

a.  Metal heat-treatment furnaces for tempering metals;

b.  Silicon boule production equipment.

Note 4:   1A002 does not control finished items specially designed for a specific application.

M6A1

Composite structures, laminates, and manufactures thereof, specially designed for use in the systems specified in 1.A., 19.A.1. or 19.A.2. and the subsystems specified in 2.A. or 20.A.

1A102

Resaturated pyrolized carbon-carbon components designed for space launch vehicles specified in 9A004 or sounding rockets specified in 9A104.

M6A2

Resaturated pyrolised (i.e. carbon-carbon) components having all of the following: a. Designed for rocket systems; and b. Usable in the systems specified in 1.A. or 19.A.1.

The corresponding systems, equipment and components as identified in Council Regulation (EC) No 428/2009 of 5 May 2009 setting up a Community regime for the control of exports, transfer, brokering and transit of dual-use items

Missile Technology Control Regime (M.TCR): Equipment, software and technology annex

1B001

Equipment for the production or inspection of “composite” structures or laminates specified in 1A002 or “fibrous or filamentary materials” specified in 1C010, as follows, and specially designed components and accessories therefor:

N.B.:  SEE ALSO 1B101 AND 1B201.

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”;

M6B1a

Filament winding machines or ‘fibre/tow-placement machines’, of which the motions for positioning, wrapping and winding fibres can be coordinated and programmed in three or more axes, designed to fabricate composite structures or laminates from fibrous or filamentary materials, and co-ordinating and programming controls

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;

Note:   In 1B001.b., ‘missile’ means complete rocket systems and unmanned aerial vehicle systems.

Technical Note:

For the purposes of 1B001.b., ‘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.

M6B1b

‘Tape-laying machines’ of which the motions for positioning and laying tape can be co-ordinated and programmed in two or more axes, designed for the manufacture of composite airframes and missile structures;

Note:   For the purposes of 6.B.1.a. and 6.B.1.b., the following definitions apply:

1.  A ‘filament band’ is a single continuous width of fully or partially resinimpregnated tape, tow, or fibre. Fully or partially resin-impregnated ‘filament bands’ include those coated with dry powder that tacks upon heating.

2.  ‘Fibre/tow-placement machines’ and ‘tape-laying machines’ are machines that perform similar processes that use computer-guided heads to lay one or several ‘filament bands’ onto a mold to create a part or a structure. These machines have the ability to cut and restart individual ‘filament band’ courses during the laying process.

3.  ‘Fibre/tow-placement machines’ have the ability to place one or more ‘filament bands’ having widths less than or equal to 25,4 mm. This refers to the minimum width of material the machine can place, regardless of the upper capability of the machine.

4.  ‘Tape-laying machines’ have the ability to place one or more ‘filament bands’ having widths less than or equal to 304,8 mm, but cannot place ‘filaments bands’ with a width equal to or less than 25,4 mm. This refers to the minimum width of material the machine can place, regardless of the upper capability of the machine.

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;

Technical Note:

For the purposes of 1B001.c., the technique of interlacing includes knitting.

M6B1c

Multi-directional, multi-dimensional weaving machines or interlacing machines, including adapters and modification kits for weaving, interlacing or braiding fibres to manufacture composite structures;

Note:   6.B.1.c. does not control textile machinery not modified for the end-uses stated.

d.  Equipment specially designed or adapted for the production of reinforcement fibres, as follows:

Equipment designed or modified for the production of fibrous or filamentary materials 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;

M6B1d1

1.  Equipment for converting polymeric fibres (such as polyacrylonitrile, rayon, or polycarbosilane) including special provision to strain the fibre during heating;

2.  Equipment for the chemical vapour deposition of elements or compounds, on heated filamentary substrates, to manufacture silicon carbide fibres;

M6B1d2

2.  Equipment for the vapour deposition of elements or compounds on heated filament substrates;

3.  Equipment for the wet-spinning of refractory ceramics (such as aluminium oxide);

M6B1d3

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;

e.  Equipment for producing prepregs specified in 1C010.e. by the hot melt method;

f.  Non-destructive inspection equipment specially designed for “composite” materials, as follows:

1.  X-ray tomography systems for three dimensional defect inspection;

2.  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;

g.  ‘Tow-placement machines’, of which the motions for positioning and laying tows are coordinated and programmed in two or more ‘primary servo positioning’ axes, specially designed for the manufacture of “composite” airframe or ‘missile’ structures.

Technical Note:

For the purposes of 1B001.g., ‘tow-placement machines’ have the ability to place one or more ‘filament bands’ having widths less than or equal to 25 mm, and to cut and restart individual ‘filament band’ courses during the placement process.

Technical Note:

1.  For the purpose of 1B001, ‘primary servo positioning’ axes control, under computer program direction, the position of the end effector (i.e., head) in space relative to the work piece at the correct orientation and direction to achieve the desired process.

2.  For the purposes of 1B001., a ‘filament band’ is a single continuous width of fully or partially resin-impregnated tape, tow or fibre.

M6B1e

Equipment designed or modified for special fibre surface treatment or for producing prepregs and preforms, including rollers, tension stretchers, coating equipment, cutting equipment and clicker dies.

Note:   Examples of components and accessories for the machines specified in 6.B.1. are moulds, mandrels, dies, fixtures and tooling for the preform pressing, curing, casting, sintering or bonding of composite structures, laminates and manufactures thereof

1B002

Equipment for producing metal alloys, metal alloy powder or alloyed materials, specially designed to avoid contamination and specially designed for use in one of the processes specified in 1C002.c.2.

N.B.:  SEE ALSO 1B102.

M4B3d

Metal powder “production equipment” usable for the “production”, in a controlled environment, of spherical, spheroidal or atomised materials specified in 4.C.2.c., 4.C.2.d. or 4.C.2.e. Note: 4.B.3.d. includes: a. Plasma generators (high frequency arc-jet) usable for obtaining sputtered or spherical metallic powders with organization of the process in an argon-water environment; b. Electroburst equipment usable for obtaining sputtered or spherical metallic powders with organization of the process in an argon-water environment; c. Equipment usable for the “production” of spherical aluminium powders by powdering a melt in an inert medium (e.g. nitrogen).

Notes:

1.  The only batch mixers, continuous mixers, usable for solid propellants or propellants constituents specified in 4.C., and fluid energy mills specified in 4.B., are those specified in 4.B.3.

2.  Forms of metal powder “production equipment” not specified in 4.B.3.d. are to be evaluated in accordance with 4.B.2.

1B101

Equipment, other than that specified in 1B001, for the “production” of structural composites as follows; and specially designed components and accessories therefor:

N.B.:  SEE ALSO 1B201.

Note:  Components and accessories specified in 1B101 include moulds, mandrels, dies, fixtures and tooling for the preform pressing, curing, casting, sintering or bonding of composite structures, laminates and manufactures thereof.

a.  Filament winding machines or fibre placement machines, of which the motions for positioning, wrapping and winding fibres can be coordinated and programmed in three or more axes, designed to fabricate composite structures or laminates from fibrous or filamentary materials, and coordinating and programming controls;

M6B1a

Filament winding machines or ‘fibre/tow-placement machines’, of which the motions for positioning, wrapping and winding fibres can be coordinated and programmed in three or more axes, designed to fabricate composite structures or laminates from fibrous or filamentary materials, and co-ordinating and programming controls;

b.  Tape-laying machines of which the motions for positioning and laying tape and sheets can be coordinated and programmed in two or more axes, designed for the manufacture of composite airframe and “missile” structures;

M6B1b

‘Tape-laying machines’ of which the motions for positioning and laying tape can be co-ordinated and programmed in two or more axes, designed for the manufacture of composite airframes and missile structures;

Note:

For the purposes of 6.B.1.a. and 6.B.1.b., the following definitions apply:

1.  A ‘filament band’ is a single continuous width of fully or partially resinimpregnated tape, tow, or fibre. Fully or partially resin-impregnated ‘filament bands’ include those coated with dry powder that tacks upon heating.

2.  ‘Fibre/tow-placement machines’ and ‘tape-laying machines’ are machines that perform similar processes that use computer-guided heads to lay one or several ‘filament bands’ onto a mold to create a part or a structure. These machines have the ability to cut and restart individual ‘filament band’ courses during the laying process.

3.  ‘Fibre/tow-placement machines’ have the ability to place one or more ‘filament bands’ having widths less than or equal to 25,4 mm. This refers to the minimum width of material the machine can place, regardless of the upper capability of the machine.

4.  ‘Tape-laying machines’ have the ability to place one or more ‘filament bands’ having widths less than or equal to 304,8 mm, but cannot place ‘filaments bands’ with a width equal to or less than 25,4 mm. This refers to the minimum width of material the machine can place, regardless of the upper capability of the machine.

c.  Equipment designed or modified for the “production” of “fibrous or filamentary materials” as follows:

1.  Equipment for converting polymeric fibres (such as polyacrylonitrile, rayon or polycarbosilane) including special provision to strain the fibre during heating;

2.  Equipment for the vapour deposition of elements or compounds on heated filament substrates;

3.  Equipment for the wet-spinning of refractory ceramics (such as aluminium oxide);

M6B1d

Equipment designed or modified for the production of fibrous or filamentary materials as follows:

1.  Equipment for converting polymeric fibres (such as polyacrylonitrile, rayon, or polycarbosilane) including special provision to strain the fibre during heating;

2.  Equipment for the vapour deposition of elements or compounds on heated filament substrates;

3.  Equipment for the wet-spinning of refractory ceramics (such as aluminium oxide);

d.  Equipment designed or modified for special fibre surface treatment or for producing prepregs and preforms specified in entry 9C110.

Note:   1B101.d. includes rollers, tension stretchers, coating equipment, cutting equipment and clicker dies.

M6B1e

Equipment designed or modified for special fibre surface treatment or for producing prepregs and preforms, including rollers, tension stretchers, coating equipment, cutting equipment and clicker dies.

Note:   Examples of components and accessories for the machines specified in 6.B.1. are moulds, mandrels, dies, fixtures and tooling for the preform pressing, curing, casting, sintering or bonding of composite structures, laminates and manufactures thereof

1B102

Metal powder “production equipment”, other than that specified in 1B002, and components as follows:

N.B.:  SEE ALSO 1B115.b.

a.  Metal powder “production equipment” usable for the “production”, in a controlled environment, of spherical, spheroidal or atomised materials specified in 1C011.a., 1C011.b., 1C111.a.1., 1C111.a.2. or in the Military Goods Controls.

b.  Specially designed components for “production equipment” specified in 1B002 or 1B102.a.

Note:   1B102 includes:

a.  Plasma generators (high frequency arc-jet) usable for obtaining sputtered or spherical metallic powders with organization of the process in an argon-water environment;

b.  Electroburst equipment usable for obtaining sputtered or spherical metallic powders with organization of the process in an argon-water environment;

c.  Equipment usable for the “production” of spherical aluminium powders by powdering a melt in an inert medium (e.g. nitrogen).

M4B3d

Metal powder “production equipment” usable for the “production”, in a controlled environment, of spherical, spheroidal or atomised materials specified in 4.C.2.c., 4.C.2.d. or 4.C.2.e.

Note:   4.B.3.d. includes:

a.  Plasma generators (high frequency arc-jet) usable for obtaining sputtered or spherical metallic powders with organization of the process in an argon-water environment;

b.  Electroburst equipment usable for obtaining sputtered or spherical metallic powders with organization of the process in an argon-water environment;

c.  Equipment usable for the “production” of spherical aluminium powders by powdering a melt in an inert medium (e.g. nitrogen).

Notes:

1.  The only batch mixers, continuous mixers, usable for solid propellants or propellants constituents specified in 4.C., and fluid energy mills specified in 4.B., are those specified in 4.B.3.

2.  Forms of metal powder “production equipment” not specified in 4.B.3.d. are to be evaluated in accordance with 4.B.2.

1B115

Equipment, other than that specified in 1B002 or 1B102, for the production of propellant and propellant constituents, as follows, and specially designed components therefor:

a.  “Production equipment” for the “production”, handling or acceptance testing of liquid propellants or propellant constituents specified in 1C011.a., 1C011.b., 1C111 or in the Military Goods Controls;

M4B1

“Production equipment”, and specially designed components therefor, for the “production”, handling or acceptance testing of liquid propellants or propellant constituents specified in 4.C.

b.  “Production equipment” for the “production”, handling, mixing, curing, casting, pressing, machining, extruding or acceptance testing of solid propellants or propellant constituents specified in 1C011.a., 1C011.b., 1C111 or in the Military Goods Controls.

Note:   1B115.b. does not control batch mixers, continuous mixers or fluid energy mills. For the control of batch mixers, continuous mixers and fluid energy mills see 1B117, 1B118 and 1B119.

Note 1:   For equipment specially designed for the production of military goods, see the Military Goods Controls.

Note 2:   1B115 does not control equipment for the “production”, handling and acceptance testing of boron carbide.

M4B2

“Production equipment”, other than that described in 4.B.3., and specially designed components therefor, for the production, handling, mixing, curing, casting, pressing, machining, extruding or acceptance testing of solid propellants or propellant constituents specified in 4.C.

1B116

Specially designed nozzles for producing pyrolitically derived materials formed on a mould, mandrel or other substrate from precursor gases which decompose in the 1 573 K (1 300  °C) to 3 173 K (2 900  °C) temperature range at pressures of 130 Pa to 20 kPa.

M6B2

Nozzles specially designed for the processes referred to in 6.E.3.

1B117

Batch mixers with provision for mixing under vacuum in the range of zero to 13,326 kPa and with temperature control capability of the mixing chamber and having all of the following, and specially designed components therefor:

a.  A total volumetric capacity of 110 litres or more; and

b.  At least one ‘mixing/kneading shaft’ mounted off centre.

Note:   In 1B117.b. the term ‘mixing/kneading shaft’ does not refer to deagglomerators or knife-spindles.

M4B3a

Batch mixers with provision for mixing under vacuum in the range of zero to 13,326 kPa and with temperature control capability of the mixing chamber and having all of the following:

1.  A total volumetric capacity of 110 litres or more; and

2.  At least one ‘mixing/kneading shaft’ mounted off centre;

Note:   In Item 4.B.3.a.2. the term ‘mixing/kneading shaft’ does not refer to deagglomerators or knife-spindles.

1B118

Continuous mixers with provision for mixing under vacuum in the range of zero to 13,326 kPa and with a temperature control capability of the mixing chamber having any of the following, and specially designed components therefor:

a.  Two or more mixing/kneading shafts; or

b.  A single rotating shaft which oscillates and having kneading teeth/pins on the shaft as well as inside the casing of the mixing chamber.

M4B3b

Continuous mixers with provision for mixing under vacuum in the range of zero to 13,326 kPa and with a temperature control capability of the mixing chamber having any of the following:

1.  Two or more mixing/kneading shafts; or

2.  A single rotating shaft which oscillates and having kneading teeth/pins on the shaft as well as inside the casing of the mixing chamber;

1B119

Fluid energy mills usable for grinding or milling substances specified in 1C011.a., 1C011.b., 1C111 or in the Military Goods Controls, and specially designed components therefor.

M4B3c

Fluid energy mills usable for grinding or milling substances specified in 4.C

The corresponding systems, equipment and components as identified in Council Regulation (EC) No 428/2009 of 5 May 2009 setting up a Community regime for the control of exports, transfer, brokering and transit of dual-use items

Missile Technology Control Regime (M.TCR): Equipment, software and technology annex

1C001

Materials specially designed for use as absorbers of electromagnetic waves, or intrinsically conductive polymers, as follows:

N.B.:  SEE ALSO 1C101.

a.  Materials for absorbing frequencies exceeding 2 × 10⁸ Hz but less than 3 × 10¹² Hz;

Note 1:   1C001.a. does not control:

a.  Hair type absorbers, constructed of natural or synthetic fibres, with non-magnetic loading to provide absorption;

b.  Absorbers having no magnetic loss and whose incident surface is non-planar in shape, including pyramids, cones, wedges and convoluted surfaces;

c.  Planar absorbers, having all of the following:

1.  Made from any of the following:

a.  Plastic foam materials (flexible or non-flexible) with carbon-loading, or organic materials, including binders, providing more than 5 % echo compared with metal over a bandwidth exceeding ± 15 % of the centre frequency of the incident energy, and not capable of withstanding temperatures exceeding 450 K (177 °C); or

b.  Ceramic materials providing more than 20 % echo compared with metal over a bandwidth exceeding ± 15 % of the centre frequency of the incident energy, and not capable of withstanding temperatures exceeding 800 K (527 °C);

Technical Note:

Absorption test samples for 1C001.a. Note: 1.c.1. should be a square at least 5 wavelengths of the centre frequency on a side and positioned in the far field of the radiating element.

2.  Tensile strength less than 7 × 10⁶ N/m²; and

3.  Compressive strength less than 14 × 10⁶ N/m²;

d.  Planar absorbers made of sintered ferrite, having all of the following:

1.  A specific gravity exceeding 4,4; and

2.  A maximum operating temperature of 548 K (275 °C).

Note 2:   Nothing in Note 1 to 1C001.a. releases magnetic materials to provide absorption when contained in paint.

b.  Materials for absorbing frequencies exceeding 1,5 × 10¹⁴ Hz but less than 3,7 × 10¹⁴ Hz and not transparent to visible light;

Note:   1C001.b. does not control materials, specially designed or formulated for any of the following applications:

a.  Laser marking of polymers; or

b.  Laser welding of polymers.

c.  Intrinsically conductive polymeric materials with a ‘bulk electrical conductivity’ exceeding 10 000  S/m (Siemens per metre) or a ‘sheet (surface) resistivity’ of less than 100 ohms/square, based on any of the following polymers:

1.  Polyaniline;

2.  Polypyrrole;

3.  Polythiophene;

4.  Poly phenylene-vinylene; or

5.  Poly thienylene-vinylene.

Note:   1C001.c. does not control materials in a liquid form.

Technical Note:

‘Bulk electrical conductivity’ and ‘sheet (surface) resistivity’ should be determined using ASTM D-257 or national equivalents.

M17C1

Materials for reduced observables such as radar reflectivity, ultraviolet/infrared signatures and acoustic signatures (i.e. stealth technology), for applications usable for the systems specified in 1.A. or 19.A. or the subsystems specified in 2.A.

Notes:

1.  17.C.1. includes structural materials and coatings (including paints), specially designed for reduced or tailored reflectivity or emissivity in the microwave, infrared or ultraviolet spectra.

2.  17.C.1. does not control coatings (including paints) when specially used for thermal control of satellites.

1C007

Ceramic powders, non-“composite” ceramic materials, ceramic-“matrix”“composite” materials and precursor materials, as follows:

N.B.:  SEE ALSO 1C107.

M6C5

Ceramic composite materials (dielectric constant less than 6 at any frequency from 100 MHz to 100 GHz) for use in missile radomes usable in systems specified in 1.A. or 19.A.1.

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;

Note:   1C007.b. does not control abrasives.

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-Al-O-N; or

d.  Si-O-N; and

2.  Having a “specific tensile strength” exceeding 12,7 × 10³m;

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 in 1C007.c., 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.  Al₂O₃ (CAS 1344-28-1); or

2.  Si-C-N.

Note:   1C007.f. does not control “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 % creep strain at 100 MPa load and 1 273 K (1 000  °C) for 100 hours.

M6C6

Silicon-carbide materials as follows:

a.  Bulk machinable silicon-carbide reinforced unfired ceramic usable for nose tips usable in systems specified in 1.A. or 19.A.1.;

Reinforced silicon-carbide ceramic composites usable for nose tips, re-entry vehicles, nozzle flaps, usable in systems specified in 1.A. or 19.A.1.

1C010

“Fibrous or filamentary materials”, as follows:

N.B.:  SEE ALSO 1C210 AND 9C110.

a.  Organic “fibrous or filamentary materials”, having all of the following:

1.  “Specific modulus” exceeding 12,7 × 10⁶ m; and

2.  “Specific tensile strength” exceeding 23,5 × 10⁴ m;

Note:   1C010.a. does not control polyethylene.

b.  Carbon “fibrous or filamentary materials”, having all of the following:

1.  “Specific modulus” exceeding 14,65 × 10⁶ m; and

2.  “Specific tensile strength” exceeding 26,82 × 10⁴ m;

Note:   1C010.b. does not control:

a.  “Fibrous or filamentary materials”, for the repair of “civil aircraft” structures or laminates, having all of the following:

1.  An area not exceeding 1 m²;

2.  A length not exceeding 2,5 m; and

3.  A width exceeding 15 mm.

b.  Mechanically chopped, milled or cut carbon “fibrous or filamentary materials” 25,0 mm or less in length.

c.  Inorganic “fibrous or filamentary materials”, having all of the following:

1.  “Specific modulus” exceeding 2,54 × 10⁶ m; and

2.  Melting, softening, decomposition or sublimation point exceeding 1 922 K (1 649  °C) in an inert environment;

Note:   1C010.c. does not control:

a.  Discontinuous, multiphase, polycrystalline alumina fibres in chopped fibre or random mat form, containing 3 % by weight or more silica, with a “specific modulus” of less than 10 × 10⁶ m;

b.  Molybdenum and molybdenum alloy fibres;

c.  Boron fibres;

d.  Discontinuous ceramic fibres with a melting, softening, decomposition or sublimation point lower than 2 043 K (1 770  °C) in an inert environment.

Technical Notes:

1.  For the purpose of calculating “specific tensile strength”, “specific modulus” or specific weight of “fibrous or filamentary materials” in 1C010.a., 1C010.b. or 1C010.c., the tensile strength and modulus should be determined by using Method A described in ISO 10618 (2004) or national equivalents.

2.  Assessing the “specific tensile strength”, “specific modulus” or specific weight of non-unidirectional “fibrous or filamentary materials” (e.g., fabrics, random mats or braids) in 1C010. 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”.

d.  “Fibrous or filamentary materials”, having any of the following:

1.  Composed of any of the following:

a.  Polyetherimides specified in 1C008.a.; or

b.  Materials specified in 1C008.b. to 1C008.f.; or

2.  Composed of materials specified in 1C010.d.1.a. or 1C010.d.1.b. and “commingled” with other fibres specified in 1C010.a., 1C010.b. or 1C010.c.;

e.  Fully or partially resin-impregnated or pitch-impregnated “fibrous or filamentary materials” (prepregs), metal or carbon-coated “fibrous or filamentary materials” (preforms) or “carbon fibre preforms”, having all of the following:

1.  Having any of the following:

a.  Inorganic “fibrous or filamentary materials” specified in 1C010.c.; or

b.  Organic or carbon “fibrous or filamentary materials”, having all of the following:

1.  “Specific modulus” exceeding 10,15 × 10⁶ m; and

2.  “Specific tensile strength” exceeding 17,7 × 10⁴ m; and

2.  Having any of the following:

a.  Resin or pitch, specified in 1C008 or 1C009.b.;

b.  ‘Dynamic Mechanical Analysis glass transition temperature (DMA Tg)’ equal to or exceeding 453 K (180 °C) and having a phenolic resin; or

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 in 1C008 or 1C009.b., and not being a phenolic resin;

Note 1:   Metal or carbon-coated “fibrous or filamentary materials” (preforms) or “carbon fibre preforms”, not impregnated with resin or pitch, are specified by “fibrous or filamentary materials” in 1C010.a., 1C010.b. or 1C010.c.

Note 2:   1C010.e. does not control:

a.  Epoxy resin “matrix” impregnated carbon “fibrous or filamentary materials” (prepregs) for the repair of “civil aircraft” structures or laminates, having all the following;

1.  An area not exceeding 1 m²;

2.  A length not exceeding 2,5 m; and

3.  A width exceeding 15 mm.

b.  Fully or partially resin-impregnated or pitch-impregnated mechanically chopped, milled or cut carbon “fibrous or filamentary materials” 25,0 mm or less in length when using a resin or pitch other than those specified by 1C008 or 1C009.b.

Technical Note:

The ‘Dynamic Mechanical Analysis glass transition temperature (DMA T_g)’ for materials specified by 1C010.e. 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.

M6C1

Resin impregnated fibre prepregs and metal coated fibre preforms, for the goods specified in 6.A.1., made either with organic matrix or metal matrix utilising fibrous or filamentary reinforcements having a specific tensile strength greater than 7,62 × 104 m and a specific modulus greater than 3,18 × 106 m.

Note:   The only resin impregnated fibre prepregs specified in 6.C.1. are those using resins with a glass transition temperature (Tg), after cure, exceeding 145 °C as determined by ASTM D4065 or national equivalents.

Technical Notes:

1.  In Item 6.C.1. ‘specific tensile strength’ is the ultimate tensile strength in N/m² divided by the specific weight in N/m³, measured at a temperature of (296 ± 2)K ((23 ± 2)°C) and a relative humidity of (50 ± 5)%.

2.  In Item 6.C.1. ‘specific modulus’ is the Young's modulus in N/m² divided by the specific weight in N/m³, measured at a temperature of (296 ± 2)K ((23 ± 2)°C) and a relative humidity of (50 ± 5)%.

1C011

Metals and compounds, as follows:

N.B.:  SEE ALSO 1C111.

a.  Metals in particle sizes of less than 60 μm whether spherical, atomised, spheroidal, flaked or ground, manufactured from material consisting of 99 % or more of zirconium, magnesium and alloys thereof;

Technical Note:

The natural content of hafnium in the zirconium (typically 2 % to 7 %) is counted with the zirconium.

Note:   The metals or alloys specified in 1C011.a. are controlled whether or not the metals or alloys are encapsulated in aluminium, magnesium, zirconium or beryllium.

M4C2d

Metal powders of any of the following: zirconium (CAS 7440-67-7), beryllium (CAS 7440-41-7), magnesium (CAS 7439-95-4) or alloys of these, if at least 90 % of the total particles by particle volume or weight are made up of particles of less than 60 μm (determined by measurement techniques such as using a sieve, laser diffraction or optical scanning), whether spherical, atomised, spheroidal, flaked or ground, consisting of 97 % by weight or more of any of the above mentioned metals;

Note:   In a multimodal particle distribution (e.g. mixtures of different grain sizes) in which one or more modes are controlled, the entire powder mixture is controlled.

Technical Note:

The natural content of hafnium (CAS 7440-58-6) in the zirconium (typically 2 % to 7 %) is counted with the zirconium.

b.  Boron or boron alloys, with a particle size of 60 μm or less, as follows:

1.  Boron with a purity of 85 % by weight or more;

2.  Boron alloys with a boron content of 85 % by weight or more;

Note:   The metals or alloys specified in 1C011.b. are controlled whether or not the metals or alloys are encapsulated in aluminium, magnesium, zirconium or beryllium.

c.  Guanidine nitrate (CAS 506-93-4);

d.  Nitroguanidine (NQ) (CAS 556-88-7).

N.B.:   See also Military Goods Controls for metal powders mixed with other substances to form a mixture formulated for military purposes.

M4C2e

Metal powders of either boron (CAS 7440-42-8) or boron alloys with a boron content of 85 % or more by weight, if at least 90 % of the total particles by particle volume or weight are made up of particles of less than 60 μm (determined by measurement techniques such as using a sieve, laser diffraction or optical scanning), whether spherical, atomised, spheroidal, flaked or ground;

Note:   In a multimodal particle distribution (e.g. mixtures of different grain sizes) in which one or more modes are controlled, the entire powder mixture is controlled.

1C101

Materials and devices for reduced observables such as radar reflectivity, ultraviolet/infrared signatures and acoustic signatures, other than those specified in 1C001, usable in ‘missiles’, “missile” subsystems or unmanned aerial vehicles specified in 9A012 or 9A112.a.

Note 1:   1C101 includes:

a.  Structural materials and coatings specially designed for reduced radar reflectivity;

b.  Coatings, including paints, specially designed for reduced or tailored reflectivity or emissivity in the microwave, infrared or ultraviolet regions of the electromagnetic spectrum.

Note 2:   1C101 does not include coatings when specially used for the thermal control of satellites.

Technical Note:

In 1C101 ‘missile’ means complete rocket systems and unmanned aerial vehicle systems capable of a range exceeding 300 km.

M17A1

Devices for reduced observables such as radar reflectivity, ultraviolet/infrared signatures and acoustic signatures (i.e. stealth technology), for applications usable for the systems specified in 1.A. or 19.A. or the subsystems specified in 2.A. or 20.A.

M17C1

Materials for reduced observables such as radar reflectivity, ultraviolet/infrared signatures and acoustic signatures (i.e. stealth technology), for applications usable for the systems specified in 1.A. or 19.A. or the subsystems specified in 2.A.

Notes:

1.  17.C.1. includes structural materials and coatings (including paints), specially designed for reduced or tailored reflectivity or emissivity in the microwave, infrared or ultraviolet spectra.

2.  17.C.1. does not control coatings (including paints) when specially used for thermal control of satellites.

1C102

Resaturated pyrolized carbon-carbon materials designed for space launch vehicles specified in 9A004 or sounding rockets specified in 9A104.

M6C2

Resaturated pyrolised (i.e. carbon-carbon) materials having all of the following: a. Designed for rocket systems; and b. Usable in the systems specified in 1.A. or 19.A.1.

1C107

Graphite and ceramic materials, other than those specified in 1C007, as follows:

a.  Fine grain graphites with a bulk density of 1,72 g/cm³ or greater, measured at 288 K (15 °C), and having a grain size of 100 μm or less, usable for rocket nozzles and re-entry vehicle nose tips, which can be machined to any of the following products:

1.  Cylinders having a diameter of 120 mm or greater and a length of 50 mm or greater;

2.  Tubes having an inner diameter of 65 mm or greater and a wall thickness of 25 mm or greater and a length of 50 mm or greater; or

3.  Blocks having a size of 120 mm × 120 mm × 50 mm or greater;

N.B.:   See also 0C004

M6C3

Fine grain graphites with a bulk density of at least 1,72 g/cc measured at 15 °C and having a grain size of 100 × 10^-6 m (100 μm) or less, usable for rocket nozzles and re-entry vehicle nose tips, which can be machined to any of the following products:

a.  Cylinders having a diameter of 120 mm or greater and a length of 50 mm or greater;

b.  Tubes having an inner diameter of 65 mm or greater and a wall thickness of 25 mm or greater and a length of 50 mm or greater; or

c.  Blocks having a size of 120 mm × 120 mm × 50 mm or greater

b.  Pyrolytic or fibrous reinforced graphites, usable for rocket nozzles and reentry vehicle nose tips usable in “missiles”, space launch vehicles specified in 9A004 or sounding rockets specified in 9A104;

N.B.:   See also 0C004

M6C4

Pyrolytic or fibrous reinforced graphites usable for rocket nozzles and reentry vehicle nose tips usable in systems specified in 1.A. or 19.A.1.

c.  Ceramic composite materials (dielectric constant less than 6 at any frequency from 100 MHz to 100 GHz) for use in radomes usable in “missiles”, space launch vehicles specified in 9A004 or sounding rockets specified in 9A104;

M6C5

Ceramic composite materials (dielectric constant less than 6 at any frequency from 100 MHz to 100 GHz) for use in missile radomes usable in systems specified in 1.A. or 19.A.1.

d.  Bulk machinable silicon-carbide reinforced unfired ceramic, usable for nose tips usable in “missiles”, space launch vehicles specified in 9A004 or sounding rockets specified in 9A104;

M6C6a

Bulk machinable silicon-carbide reinforced unfired ceramic usable for nose tips usable in systems specified in 1.A. or 19.A.1.;

e.  Reinforced silicon-carbide ceramic composites, usable for nose tips, reentry vehicles and nozzle flaps usable in “missiles”, space launch vehicles specified in 9A004 or sounding rockets specified in 9A104.

M6C6b

Reinforced silicon-carbide ceramic composites usable for nose tips, re-entry vehicles, nozzle flaps, usable in systems specified in 1.A. or 19.A.1.

1C111

Propellants and constituent chemicals for propellants, other than those specified in 1C011, as follows:

a.  Propulsive substances:

1.  Spherical or spheroidal aluminium powder other than that specified in the Military Goods Controls, in particle size of less than 200 μm and an aluminium content of 97 % by weight or more, if at least 10 % of the total weight is made up of particles of less than 63 μm, according to ISO 2591-1:1988 or national equivalents;

Technical Note:

A particle size of 63 μm (ISO R-565) corresponds to 250 mesh (Tyler) or 230 mesh (ASTM standard E-11).

2.  Metal powders, other than that specified in the Military Goods Controls, as follows:

M4C2c

Spherical or spheroidal aluminium powder (CAS 7429-90-5) in particle size of less than 200 × 10^-6 m (200 μm) and an aluminium content of 97 % by weight or more, if at least 10 % of the total weight is made up of particles of less than 63 μm, according to ISO 2591-1:1988 or national equivalents;

Technical Note:

A particle size of 63 μm (ISO R-565) corresponds to 250 mesh (Tyler) or 230 mesh (ASTM standard E-11).

a.  Metal powders of zirconium, beryllium or magnesium, or alloys of these metals, if at least 90 % of the total particles by particle volume or weight are made up of particles of less than 60 μm (determined by measurement techniques such as using a sieve, laser diffraction or optical scanning), whether spherical, atomized, spheroidal, flaked or ground, consisting 97 % by weight or more of any of the following:

1.  Zirconium;

2.  Beryllium; or

3.  Magnesium;

Technical Note:

The natural content of hafnium in the zirconium (typically 2 % to 7 %) is counted with the zirconium.

M4C2d

Metal powders of any of the following: zirconium (CAS 7440-67-7), beryllium (CAS 7440-41-7), magnesium (CAS 7439-95-4) or alloys of these, if at least 90 % of the total particles by particle volume or weight are made up of particles of less than 60 μm (determined by measurement techniques such as using a sieve, laser diffraction or optical scanning), whether spherical, atomised, spheroidal, flaked or ground, consisting of 97 % by weight or more of any of the above mentioned metals;

Note:   In a multimodal particle distribution (e.g. mixtures of different grain sizes) in which one or more modes are controlled, the entire powder mixture is controlled.

Technical Note:

The natural content of hafnium (CAS 7440-58-6) in the zirconium (typically 2 % to 7 %) is counted with the zirconium.

b.  Metal powders of either boron or boron alloys with a boron content of 85 % or more by weight, if at least 90 % of the total particles by particle volume or weight are made up of particles of less than 60 μm (determined by measurement techniques such as using a sieve, laser diffraction or optical scanning), whether spherical, atomised, spheroidal, flaked or ground;

Note:   1C111a.2.a. and 1C111a.2.b. controls powder mixtures with a multimodal particle distribution (e.g. mixtures of different grain sizes) if one or more modes are controlled.

M4C2e

Metal powders of either boron (CAS 7440-42-8) or boron alloys with a boron content of 85 % or more by weight, if at least 90 % of the total particles by particle volume or weight are made up of particles of less than 60 μm (determined by measurement techniques such as using a sieve, laser diffraction or optical scanning), whether spherical, atomised, spheroidal, flaked or ground

Note:   In a multimodal particle distribution (e.g. mixtures of different grain sizes) in which one or more modes are controlled, the entire powder mixture is controlled.

3.  Oxidiser substances usable in liquid propellant rocket engines as follows:

a.  Dinitrogen trioxide (CAS 10544-73-7);

b.  Nitrogen dioxide (CAS 10102-44-0)/dinitrogen tetroxide (CAS 10544-72-6);

c.  Dinitrogen pentoxide (CAS 10102-03-1);

d.  Mixed Oxides of Nitrogen (MON);

Technical Note:

Mixed Oxides of Nitrogen (MON) are solutions of Nitric Oxide (NO) in Dinitrogen Tetroxide/Nitrogen Dioxide (N₂O₄/NO₂ ) that can be used in missile systems. There are a range of compositions that can be denoted as MONi or MONij, where i and j are integers representing the percentage of Nitric Oxide in the mixture (e.g., MON3 contains 3 % Nitric Oxide, MON25 25 % Nitric Oxide. An upper limit is MON40, 40 % by weight).

e.  SEE MILITARY GOODS CONTROLS FOR Inhibited Red Fuming Nitric Acid (IRFNA);

f.  SEE MILITARY GOODS CONTROLS AND 1C238 FOR Compounds composed of fluorine and one or more of other halogens, oxygen or nitrogen;

M4C4a

Oxidiser substances usable in liquid propellant rocket engines as follows:

1.  Dinitrogen trioxide (CAS 10544-73-7)

2.  Nitrogen dioxide (CAS 10102-44-0) / dinitrogen tetroxide (CAS 10544-72-6);

3.  Dinitrogen pentoxide (CAS 10102-03-1);

4.  Mixed Oxides of Nitrogen (MON);

Technical Note:

Mixed Oxides of Nitrogen (MON) are solutions of Nitric Oxide (NO) in Dinitrogen Tetroxide/Nitrogen Dioxide (N₂O₄/NO₂) that can be used in missile systems. There are a range of compositions that can be denoted as MONi or MONij where i and j are integers representing the percentage of Nitric Oxide in the mixture (e.g. MON3 contains 3 % Nitric Oxide, MON25 25 % Nitric Oxide. An upper limit is MON40, 40 % by weight).

5.  Inhibited Red Fuming Nitric Acid (IRFNA) (CAS 8007-58-7);

6.  Compounds composed of fluorine and one or more of other halogens, oxygen or nitrogen;

Note:   Item 4.C.4.a.6. does not control Nitrogen Trifluoride (NF3) (CAS 7783-54- 2) in a gaseous state as it is not usable for missile applications.

4.  Hydrazine derivatives as follows:

N.B.:  SEE ALSO MILITARY GOODS CONTROLS.

a.  Trimethylhydrazine (CAS 1741-01-1);

b.  Tetramethylhydrazine (CAS 6415-12-9);

c.  N,N diallylhydrazine (CAS 5164-11-4);

d.  Allylhydrazine (CAS 7422-78-8);

e.  Ethylene dihydrazine;

f.  Monomethylhydrazine dinitrate;

g.  Unsymmetrical dimethylhydrazine nitrate;

h.  Hydrazinium azide (CAS 14546-44-2);

i.  Dimethylhydrazinium azide;

j.  Hydrazinium dinitrate (CAS 13464-98-7);

k.  Diimido oxalic acid dihydrazine (CAS 3457-37-2);

l.  2-hydroxyethylhydrazine nitrate (HEHN);

m.  See Military Goods Controls for Hydrazinium perchlorate;

n.  Hydrazinium diperchlorate (CAS 13812-39-0);

o.  Methylhydrazine nitrate (MHN) (CAS 29674-96-2);

p.  Diethylhydrazine nitrate (DEHN);

q.  3,6-dihydrazino tetrazine nitrate (1,4-dihydrazine nitrate) (DHTN);

M4C2b

Hydrazine derivatives as follows:

1.  Monomethylhydrazine (MMH) (CAS 60-34-4);

2.  Unsymmetrical dimethylhydrazine (UDMH) (CAS 57-14-7);

3.  Hydrazine mononitrate (CAS 13464-97-6);

4.  Trimethylhydrazine (CAS 1741-01-1);

5.  Tetramethylhydrazine (CAS 6415-12-9);

6.  N,N diallylhydrazine (CAS 5164-11-4);

7.  Allylhydrazine (CAS 7422-78-8);

8.  Ethylene dihydrazine (CAS 6068-98-0);

9.  Monomethylhydrazine dinitrate;

10.  Unsymmetrical dimethylhydrazine nitrate;

11.  Hydrazinium azide (CAS 14546-44-2);

12.  1,1-Dimethylhydrazinium azide (CAS 227955-52-4) / 1,2-Dimethylhydrazinium azide (CAS 299177-50-7);

13.  Hydrazinium dinitrate (CAS 13464-98-7);

14.  Diimido oxalic acid dihydrazine (CAS 3457-37-2);

15.  2-hydroxyethylhydrazine nitrate (HEHN);

16.  Hydrazinium perchlorate (CAS 27978-54-7);

17.  Hydrazinium diperchlorate (CAS 13812-39-0);

18.  Methylhydrazine nitrate (MHN) (CAS 29674-96-2);

19.  1,1-Diethylhydrazine nitrate (DEHN) / 1,2-Diethylhydrazine nitrate (DEHN) (CAS 363453-17-2);

20.  3,6-dihydrazino tetrazine nitrate (DHTN);

Technical note:

3,6-dihydrazino tetrazine nitrate is also referred to as 1,4-dihydrazine nitrate.

5.  High energy density materials, other than that specified in the Military Goods Controls, usable in ‘missiles’ or unmanned aerial vehicles specified in 9A012 or 9A112.a.;

a.  Mixed fuel that incorporate both solid and liquid fuels, such as boron slurry, having a mass-based energy density of 40 × 10⁶ J/kg or greater;

b.  Other high energy density fuels and fuel additives (e.g., cubane, ionic solutions, JP-10) having a volume-based energy density of 37,5 × 10⁹ J/m³ or greater, measured at 20 °C and one atmosphere (101,325 kPa) pressure;

Note:   1C111.a.5.b. does not control fossil refined fuels and biofuels produced from vegetables, including fuels for engines certified for use in civil aviation, unless specially formulated for ‘missiles’ or unmanned aerial vehicles specified in 9A012 or 9A112.a..

Technical Note:

In 1C111.a.5. ‘missile’ means complete rocket systems and unmanned aerial vehicle systems capable of a range exceeding 300 km.

M4C2f

High energy density materials, usable in the systems specified in 1.A. or 19.A., as follows:

1.  Mixed fuels that incorporate both solid and liquid fuels, such as boron slurry, having a mass- based energy density of 40 × 10⁶ J/kg or greater;

2.  Other high energy density fuels and fuel additives (e.g., cubane, ionic solutions, JP-10) having a volume-based energy density of 37,5 × 10⁹ J/m³ or greater, measured at 20 °C and one atmosphere (101,325 kPa) pressure.

Note:   Item 4.C.2.f.2. does not control fossil refined fuels and biofuels produced from vegetables, including fuels for engines certified for use in civil aviation, unless specifically formulated for systems specified in 1.A. or 19.A.

6.  Hydrazine replacement fuels as follows:

a.  2-Dimethylaminoethylazide (DMAZ) (CAS 86147-04-8);

M4C2g

Hydrazine replacement fuels as follows: 1. 2-Dimethylaminoethylazide (DMAZ) (CAS 86147-04-8).

b.  Polymeric substances:

1.  Carboxy-terminated polybutadiene (including carboxyl-terminated polybutadiene) (CTPB);

2.  Hydroxy-terminated polybutadiene (including hydroxyl-terminated polybutadiene) (HTPB), other than that specified in the Military Goods Controls;

3.  Polybutadiene-acrylic acid (PBAA);

4.  Polybutadiene-acrylic acid-acrylonitrile (PBAN);

5.  Polytetrahydrofuran polyethylene glycol (TPEG);

Technical Note:

Polytetrahydrofuran polyethylene glycol (TPEG) is a block co-polymer of poly 1,4-Butanediol (CAS 110-63-4) and polyethylene glycol (PEG) (CAS 25322-68-3).

6.  Polyglycidyl nitrate (PGN or poly-GLYN) (CAS 27814-48-8).

M4C5

Polymeric substances, as follows:

a.  Carboxy — terminated polybutadiene (including carboxyl — terminated polybutadiene) (CTPB);

b.  Hydroxy — terminated polybutadiene (including hydroxyl — terminated polybutadiene) (HTPB);

c.  Glycidyl azide polymer (GAP);

d.  Polybutadiene — Acrylic Acid (PBAA);

e.  Polybutadiene — Acrylic Acid — Acrylonitrile (PBAN) (CAS 25265-19-4 / CAS 68891-50-9);

f.  Polytetrahydrofuran polyethylene glycol (TPEG).

Technical Note:

Polytetrahydrofuran polyethylene glycol (TPEG) is a block co-polymer of poly 1,4-Butanediol (CAS 110-63-4) and polyethylene glycol (PEG) (CAS 25322-68-3).

g.  Polyglycidyl nitrate (PGN or poly-GLYN) (CAS 27814-48-8)

c.  Other propellant additives and agents:

1.  SEE MILITARY GOODS CONTROLS FOR

Carboranes, decaboranes, pentaboranes and derivatives thereof;

M4C6c1

Carboranes, decaboranes, pentaboranes and derivatives thereof

2.  Triethylene glycol dinitrate (TEGDN) (CAS 111-22-8);

M4C6d1

Triethylene glycol dinitrate (TEGDN) (CAS 111-22-8);

3.  2-Nitrodiphenylamine (CAS 119-75-5);

M4C6e1

2-Nitrodiphenylamine (CAS 119-75-5);

4.  Trimethylolethane trinitrate (TMETN) (CAS 3032-55-1);

M4C6d2

Trimethylolethane trinitrate (TMETN) (CAS 3032-55-1);

5.  Diethylene glycol dinitrate (DEGDN) (CAS 693-21-0);

M4C6d4

Diethylene glycol dinitrate (DEGDN) (CAS 693-21-0)

6.  Ferrocene derivatives as follows:

a.  See Military Goods Controls for catocene;

b.  See Military Goods Controls for Ethyl ferrocene;

c.  See Military Goods Controls for Propyl ferrocene;

d.  See Military Goods Controls for n-butyl ferrocene;

e.  See Military Goods Controls for Pentyl ferrocene;

f.  See Military Goods Controls for Dicyclopentyl ferrocene;

g.  See Military Goods Controls for Dicyclohexyl ferrocene;

h.  See Military Goods Controls for Diethyl ferrocene;

i.  See Military Goods Controls for Dipropyl ferrocene;

j.  See Military Goods Controls for Dibutyl ferrocene;

k.  See Military Goods Controls for Dihexyl ferrocene;

l.  See Military Goods Controls for Acetyl ferrocene / 1,1′-diacetyl ferrocene;

m.  See Military Goods Controls for ferrocene carboxylic acids;

n.  See Military Goods Controls for butacene;

o.  Other ferrocene derivatives usable as rocket propellant burning rate modifiers, other than those specified in the Military Goods Controls.

Note:   1C111.c.6.o. does not control ferrocene derivatives that contain a six carbon aromatic functional group attached to the ferrocene molecule.

M4C6c2

Ferrocene derivatives, as follows:

a.  Catocene (CAS 37206-42-1);

b.  Ethyl ferrocene (CAS 1273-89-8);

c.  Propyl ferrocene;

d.  n-Butyl ferrocene (CAS 31904-29-7);

e.  Pentyl ferrocene (CAS 1274-00-6);

f.  Dicyclopentyl ferrocene (CAS 125861-17-8);

g.  Dicyclohexyl ferrocene;

h.  Diethyl ferrocene (CAS 1273-97-8);

i.  Dipropyl ferrocene;

j.  Dibutyl ferrocene (CAS 1274-08-4);

k.  Dihexyl ferrocene (CAS 93894-59-8);

l.  Acetyl ferrocene (CAS 1271-55-2) / 1,1′-diacetyl ferrocene (CAS 1273-94-5);

m.  Ferrocene carboxylic acid (CAS 1271-42-7) / 1,1′- Ferrocenedicarboxylic acid (CAS 1293-87-4);

n.  Butacene (CAS 125856-62-4);

o.  Other ferrocene derivatives usable as rocket propellant burning rate modifiers;

Note:   Item 4.C.6.c.2.o does not control ferrocene derivatives that contain a six carbon aromatic functional group attached to the ferrocene molecule.

7.  4,5 diazidomethyl-2-methyl-1,2,3-triazole (iso- DAMTR), other than that specified in the Military Goods Controls.

Note:   For propellants and constituent chemicals for propellants not specified in 1C111, see the Military Goods Controls.

M4C6d5

4,5 diazidomethyl-2-methyl-1,2,3-triazole (iso- DAMTR);

1C116

Maraging steels, useable in ‘missiles’, having all of the following:

N.B.:   SEE ALSO 1C216.

M6C8

Maraging steels, usable in the systems specified in 1.A. or 19.A.1., having all of the following:

a.  Having an ultimate tensile strength, measured at 20 °C, equal to or greater than:

1.  0,9 GPa in the solution annealed stage; or

2.  1,5 GPa in the precipitation hardened stage; and

b.  Any of the following forms:

1.  Sheet, plate or tubing with a wall or plate thickness equal to or less than 5,0 mm; or

2.  Tubular forms with a wall thickness equal to or less than 50 mm and having an inner diameter equal to or greater than 270 mm.

Technical Note:

Maraging steels are iron alloys:

a.  Generally characterised by high nickel, very low carbon content and use substitutional elements or precipitates to produce strengthening and agehardening of the alloy; and

b.  Subjected to heat treatment cycles to facilitate the martensitic transformation process (solution annealed stage) and subsequently age hardened (precipitation hardened stage).

1C117

Materials for the fabrication of ‘missiles’ components as follows:

a.  Tungsten and alloys in particulate form with a tungsten content of 97 % by weight or more and a particle size of 50 × 10^-6 m (50 μm) or less;

b.  Molybdenum and alloys in particulate form with a molybdenum content of 97 % by weight or more and a particle size of 50 × 10^-6 m (50 μm) or less;

c.  Tungsten materials in solid form having all of the following:

1.  Any of the following material compositions:

a.  Tungsten and alloys containing 97 % by weight or more of tungsten;

b.  Copper infiltrated tungsten containing 80 % by weight or more of tungsten; or

c.  Silver infiltrated tungsten containing 80 % by weight ot more of tungsten; and

2.  Able to be machined to any of the following products:

a.  Cylinders having a diameter of 120 mm or greater and a length of 50 mm or greater;

b.  Tubes having an inner diameter of 65 mm or greater and a wall thickness of 25 mm or greater and a length of 50 mm or greater; or

c.  Blocks having a size of 120 mm by 120 mm by 50 mm or greater.

Technical Note:

In 1C117 ‘missile’ means complete rocket systems and unmanned aerial vehicle systems capable of a range exceeding 300 km.

M6C7

Materials for the fabrication of missile components in the systems specified in 1.A., 19.A.1. or 19.A.2, as follows:.

a.  Tungsten and alloys in particulate form with a tungsten content of 97 % by weight or more and a particle size of 50 × 10^-6 m (50 μm) or less;

b.  Molybdenum and alloys in particulate form with a molybdenum content of 97 % by weight or more and a particle size of 50 × 10^-6 m (50 μm) or less;

c.  Tungsten materials in the solid form having all of the following:

1.  Any of the following material compositions: i. Tungsten and alloys containing 97 % by weight or more of tungsten; ii. Copper infiltrated tungsten containing 80 % by weight or more of tungsten; or iii. Silver infiltrated tungsten containing 80 % by weight or more of tungsten; and

2.  Able to be machined to any of the following products: i. Cylinders having a diameter of 120 mm or greater and a length of 50 mm or greater; ii. Tubes having an inner diameter of 65 mm or greater and a wall thickness of 25 mm or greater and a length of 50 mm or greater; or iii. Blocks having a size of 120 mm × 120 mm × 50 mm or greater

1C118

Titanium-stabilised duplex stainless steel (Ti-DSS) having all of the following:

a.  Having all of the following characteristics:

1.  Containing 17,0 – 23,0 weight percent chromium and 4,5 – 7,0 weight percent nickel;

2.  Having a titanium content of greater than 0,10 weight percent; and

3.  A ferritic-austenitic microstructure (also referred to as a two-phase microstructure) of which at least 10 percent is austenite by volume (according to ASTM E-1181-87 or national equivalents); and

b.  Having any of the following forms:

1.  Ingots or bars having a size of 100 mm or more in each dimension;

2.  Sheets having a width of 600 mm or more and a thickness of 3 mm or less; or

3.  Tubes having an outer diameter of 600 mm or more and a wall thickness of 3 mm or less.

M6C9

Titanium-stabilized duplex stainless steel (Ti-DSS) usable in the systems specified in 1.A. or 19.A.1. and having all of the following:

a.  Having all of the following characteristics:

1.  Containing 17,0 – 23,0 weight percent chromium and 4,5 – 7,0 weight percent nickel;

2.  Having a titanium content of greater than 0,10 weight percent; and

3.  A ferritic-austenitic microstructure (also referred to as a two-phase microstructure ) of which at least 10 % is austenite by volume (according to ASTM E-1181-87 or national equivalents); and

b.  Any of the following forms:

1.  Ingots or bars having a size of 100 mm or more in each dimension;

2.  Sheets having a width of 600 mm or more and a thickness of 3 mm or less; or

3.  Tubes having an outer diameter of 600 mm or more and a wall thickness of 3 mm or less.

1C238

Chlorine trifluoride (ClF₃).

M4C4a6

Compounds composed of fluorine and one or more of other halogens, oxygen or nitrogen;

Note:  Item 4.C.4.a.6. does not control Nitrogen Trifluoride (NF₃) (CAS 7783-54- 2) in a gaseous state as it is not usable for missile applications.

The corresponding systems, equipment and components as identified in Council Regulation (EC) No 428/2009 of 5 May 2009 setting up a Community regime for the control of exports, transfer, brokering and transit of dual-use items

Missile Technology Control Regime (M.TCR): Equipment, software and technology annex

1D001

“Software” specially designed or modified for the “development”, “production” or “use” of equipment specified in 1B001 to 1B003.

M6D1

“Software” specially designed or modified for the operation or maintenance of equipment specified in 6.B.1.

1D101

“Software” specially designed or modified for the operation or maintenance of goods specified in1B101, 1B102, 1B115, 1B117, 1B118 or 1B119.

M4D1

“Software” specially designed or modified for the operation or maintenance of equipment specified in 4.B. for the “production” and handling of materials specified in 4.C.

M6D1

“Software” specially designed or modified for the operation or maintenance of equipment specified in 6.B.1.

1D103

“Software” specially designed for analysis of reduced observables such as radar reflectivity, ultraviolet/infrared signatures and acoustic signatures.

M17D1

“Software” specially designed for reduced observables such as radar reflectivity, ultraviolet/infrared signatures and acoustic signatures (i.e. stealth technology), for applications usable for the systems specified in 1.A. or 19.A. or the subsystems specified in 2.A.

Note:  17.D.1. includes “software” specially designed for analysis of signature reduction.

The corresponding systems, equipment and components as identified in Council Regulation (EC) No 428/2009 of 5 May 2009 setting up a Community regime for the control of exports, transfer, brokering and transit of dual-use items

Missile Technology Control Regime (M.TCR): Equipment, software and technology annex

1E001

“Technology” according to the General Technology Note for the “development” or “production” of equipment or materials specified in 1A001.b., 1A001.c., 1A002 to 1A005, 1A006.b., 1A007, 1B or 1C.

M

“Technology”, in accordance with the General Technology Note, for the “development”, “production” or “use” of equipment or “software” specified in 1.A., 1.B., or 1.D.

1E101

“Technology” according to the General Technology Note for the “use” of goods specified in 1A102, 1B001, 1B101, 1B102, 1B115 to 1B119, 1C001, 1C101, 1C107, 1C111 to 1C118, 1D101 or 1D103.

M

“Technology”, in accordance with the General Technology Note, for the “development”, “production” or “use” of equipment or “software” specified in 1.A., 1.B., or 1.D.

1E102

“Technology” according to the General Technology Note for the “development” of “software” specified in 1D001, 1D101 or 1D103.

M6E1

“Technology”, in accordance with the General Technology Note, for the “development”, “production” or “use” of equipment, materials or “software” specified in 6.A., 6.B., 6.C. or 6.D.

M17E1

“Technology”, in accordance with the General Technology Note, for the “development”, “production” or “use” of equipment, materials or “software” specified in 17.A., 17.B., 17.C. or 17.D.

Note:  17.E.1. includes databases specially designed for analysis of signature reduction

1E103

[M6E2]“Technology” for the regulation of temperature, pressure or atmosphere in autoclaves or hydroclaves, when used for the “production” of “composites” or partially processed “composites”.

M6E2

“Technical data” (including processing conditions) and procedures for the regulation of temperature, pressures or atmosphere in autoclaves or hydroclaves when used for the production of composites or partially processed composites, usable for equipment or materials specified in 6.A. or 6.C

1E104

“Technology” relating to the “production” of pyrolytically derived materials formed on a mould, mandrel or other substrate from precursor gases which decompose in the 1 573 K (1 300  °C) to 3 173 K (2 900  °C) temperature range at pressures of 130 Pa to 20 kPa.

Note:   1E104 includes “technology” for the composition of precursor gases, flow-rates and process control schedules and parameters.

M6E1

The corresponding systems, equipment and components as identified in Council Regulation (EC) No 428/2009 of 5 May 2009 setting up a Community regime for the control of exports, transfer, brokering and transit of dual-use items

Missile Technology Control Regime (M.TCR): Equipment, software and technology annex

2A001

Anti-friction bearings and bearing systems, as follows, and components therefor:

N.B.:  SEE ALSO 2A101.

Note:  2A001 does not control balls with tolerances specified by the manufacturer in accordance with ISO 3290 as grade 5 or worse.

a.  Ball bearings and solid roller bearings, having all tolerances specified by the manufacturer in accordance with ISO 492 Tolerance Class 4 (or national equivalents), or better, and having both rings and rolling elements (ISO 5593), made from monel or beryllium;

Note:   2A001.a. does not control tapered roller bearings.

b.  Not used;

c.  Active magnetic bearing systems using any of the following:

1.  Materials with flux densities of 2,0 T or greater and yield strengths greater than 414 MPa;

2.  All-electromagnetic 3D homopolar bias designs for actuators; or

3.  High temperature (450 K (177 °C) and above) position sensors.

M3A7

Radial ball bearings having all tolerances specified in accordance with ISO 492 Tolerance Class 2 (or ANSI/ABMA Std 20 Tolerance Class ABEC-9 or other national equivalents), or better and having all the following characteristics:

a)  An inner ring bore diameter between 12 and 50 mm;

b)  An outer ring outside diameter between 25 and 100 mm; and

c)  A width between 10 and 20 mm.

2A101

Radial ball bearings, other than those specified in 2A001, having all tolerances specified in accordance with ISO 492 Tolerance Class 2 (or ANSI/ABMA Std 20 Tolerance Class ABEC-9 or other national equivalents), or better and having all the following characteristics:

a.  An inner ring bore diameter between 12 mm and 50 mm;

b.  An outer ring outside diameter between 25 mm and 100 mm; and

c.  A width between 10 mm and 20 mm.

M3A7

Radial ball bearings having all tolerances specified in accordance with ISO 492 Tolerance Class 2 (or ANSI/ABMA Std 20 Tolerance Class ABEC-9 or other national equivalents), or better and having all the following characteristics:

a)  An inner ring bore diameter between 12 and 50 mm;

b)  An outer ring outside diameter between 25 and 100 mm; and

c)  A width between 10 and 20 mm.

2B004

Hot “isostatic presses” having all of the following, and specially designed components and accessories therefor:

N.B.:  SEE ALSO 2B104 and 2B204.

a.  A controlled thermal environment within the closed cavity and a chamber cavity with an inside diameter of 406 mm or more; and

b.  Having any of the following:

1.  A maximum working pressure exceeding 207 MPa;

2.  A controlled thermal environment exceeding 1 773 K (1 500  °C); or

3.  A facility for hydrocarbon impregnation and removal of resultant gaseous degradation products.

Technical Note:

The inside chamber dimension is that of the chamber in which both the working temperature and the working pressure are achieved and does not include fixtures. That dimension will be the smaller of either the inside diameter of the pressure chamber or the inside diameter of the insulated furnace chamber, depending on which of the two chambers is located inside the other.

N.B.:   For specially designed dies, moulds and tooling see 1B003, 9B009 and the Military Goods Controls.

M6B3

Isostatic presses having all of the following characteristics:

a)  Maximum working pressure equal to or greater than 69 MPa;

b)  Designed to achieve and maintain a controlled thermal environment of 600 °C or greater; and

c)  Possessing a chamber cavity with an inside diameter of 254 mm or greater.

2B009

Spin-forming machines and flow-forming machines, which, according to the manufacturer's technical specification, can be equipped with “numerical control” units or a computer control and having all of the following:

N.B.:  SEE ALSO 2B109 AND 2B209.

a.  Three or more axes which can be coordinated simultaneously for “contouring control”; and

b.  A roller force more than 60 kN.

Technical Note:

For the purpose of 2B009, machines combining the function of spin-forming and flow-forming are regarded as flow-forming machines.

M3B3

Flow-forming machines, and specially designed components therefor, which:

a)  According to the manufacturers technical specification can be equipped with numerical control units or a computer control, even when not equipped with such units at delivery; and

b)  Have more than two axes which can be co-ordinated simultaneously for contouring control.

Note:   This item does not include machines that are not usable in the “production” of propulsion components and equipment (e.g. motor cases) for systems specified in 1.A.

Technical Note:

Machines combining the function of spin-forming and flow-forming are, for the purpose of this item, regarded as flow-forming machines.

2B104

“Isostatic presses”, other than those specified in 2B004, having all of the following:

N.B.:  SEE ALSO 2B204.

a.  Maximum working pressure of 69 MPa or greater;

b.  Designed to achieve and maintain a controlled thermal environment of 873 K (600 °C) or greater; and

c.  Possessing a chamber cavity with an inside diameter of 254 mm or greater.

M6B3

Isostatic presses having all of the following characteristics:

a)  Maximum working pressure equal to or greater than 69 MPa;

b)  Designed to achieve and maintain a controlled thermal environment of 600 °C or greater; and

c)  Possessing a chamber cavity with an inside diameter of 254 mm or greater.

2B105

Chemical vapour deposition (CVD) furnaces, other than those specified in 2B005.a., designed or modified for the densification of carbon-carbon composites.

M6B4

Chemical vapour deposition furnaces designed or modified for the densification of carbon-carbon composites.

2B109

Flow-forming machines, other than those specified in 2B009, and specially designed components as follows:

N.B.:  SEE ALSO 2B209.

a.  Flow-forming machines having all of the following:

1.  According to the manufacturer's technical specification, can be equipped with “numerical control” units or a computer control, even when not equipped with such units; and

2.  With more than two axes which can be coordinated simultaneously for “contouring control”.

b.  Specially designed components for flow-forming machines specified in 2B009 or 2B109.a.

Note:   2B109 does not control machines that are not usable in the production of propulsion components and equipment (e.g. motor cases) for systems specified in 9A005, 9A007.a. or 9A105.a.

Technical Note:

Machines combining the function of spin-forming and flow-forming are for the purpose of 2B109 regarded as flow-forming machines.

M3B3

Flow-forming machines, and specially designed components therefor, which:

a)  According to the manufacturers technical specification can be equipped with numerical control units or a computer control, even when not equipped with such units at delivery; and

b)  Have more than two axes which can be co-ordinated simultaneously for contouring control.

Note:   This item does not include machines that are not usable in the “production” of propulsion components and equipment (e.g. motor cases) for systems specified in 1.A.

Technical Note:

Machines combining the function of spin-forming and flow-forming are, for the purpose of this item, regarded as flow-forming machines.

2B116

Vibration test systems, equipment and components therefor, as follows:

a.  Vibration test systems employing feedback or closed loop techniques and incorporating a digital controller, capable of vibrating a system at an acceleration equal to or greater than 10 g rms between 20 Hz and 2 kHz while imparting forces equal to or greater than 50 kN, measured ‘bare table’;

b.  Digital controllers, combined with specially designed vibration test software, with a ‘real-time control bandwidth’ greater than 5 kHz designed for use with vibration test systems specified in 2B116.a.;

Technical Note:

In 2B116.b., ‘real-time control bandwidth’ means the maximum rate at which a controller can execute complete cycles of sampling, processing data and transmitting control signals.

c.  Vibration thrusters (shaker units), with or without associated amplifiers, capable of imparting a force equal to or greater than 50 kN, measured ‘bare table’, and usable in vibration test systems specified in 2B116.a.;

d.  Test piece support structures and electronic units designed to combine multiple shaker units in a system capable of providing an effective combined force equal to or greater than 50 kN, measured ‘bare table’, and usable in vibration systems specified in 2B116.a.

Technical Note:

In 2B116, ‘bare table’ means a flat table, or surface, with no fixture or fittings.

M15B1

Vibration test equipment, usable for the systems specified in 1.A., 19.A.1. or 19.A.2. or the subsystems specified in 2.A. or 20.A., and components therefor, as follows:

a)  Vibration test systems employing feedback or closed loop techniques and incorporating a digital controller, capable of vibrating a system at an acceleration equal to or greater than 10 g rms between 20 Hz and 2 kHz while imparting forces equal to or greater than 50 kN, measured ‘bare table’;

b)  Digital controllers, combined with specially designed vibration test “software”, with a ‘real-time control bandwidth’ greater than 5 kHz and designed for use with vibration test systems specified in 15.B.1.a.;

Technical Note:

‘Real-time control bandwidth’ is defined as the maximum rate at which a controller can execute complete cycles of sampling, processing data and transmitting control signals.

c)  Vibration thrusters (shaker units), with or without associated amplifiers, capable of imparting a force equal to or greater than 50 kN, measured ‘bare table’, and usable in vibration test systems specified in 15.B.1.a.;

d)  Test piece support structures and electronic units designed to combine multiple shaker units into a complete shaker system capable of providing an effective combined force equal to or greater than 50 kN, measured ‘bare table’, and usable in vibration test systems specified in 15.B.1.a.

Technical Note:

Vibration test systems incorporating a digital controller are those systems, the functions of which are, partly or entirely, automatically controlled by stored and digitally coded electrical signals.

2B117

Equipment and process controls, other than those specified in 2B004, 2B005.a., 2B104 or 2B105, designed or modified for densification and pyrolysis of structural composite rocket nozzles and reentry vehicle nose tips.

M6B5

Equipment and process controls, other than those specified in 6.B.3. or 6.B.4., designed or modified for densification and pyrolysis of structural composite rocket nozzles and re-entry vehicle nose tips.

2B119

Balancing machines and related equipment, as follows:

N.B.:  SEE ALSO 2B219

a.  Balancing machines having all the following characteristics:

1.  Not capable of balancing rotors/assemblies having a mass greater than 3 kg;

2.  Capable of balancing rotors/assemblies at speeds greater than 12 500 rpm;

3.  Capable of correcting unbalance in two planes or more; and

4.  Capable of balancing to a residual specific unbalance of 0,2 g mm per kg of rotor mass;

Note:   2B119.a. does not control balancing machines designed or modified for dental or other medical equipment.

M9B2a

Equipment as follows:

1.  Balancing machines having all the following characteristics:

1.  Not capable of balancing rotors/assemblies having a mass greater than 3 kg;

2.  Capable of balancing rotors/assemblies at speeds greater than 12 500 rpm;

3.  Capable of correcting unbalance in two planes or more; and

4.  Capable of balancing to a residual specific unbalance of 0,2 g mm per kg of rotor mass;

b.  Indicator heads designed or modified for use with machines specified in 2B119.a.

Technical Note:

Indicator heads are sometimes known as balancing instrumentation.

M9B2b

Indicator heads (sometimes known as balancing instrumentation) designed or modified for use with machines specified in 9.B.2.a.;

2B120

Motion simulators or rate tables having all of the following characteristics:

a.  Two axes or more;

b.  Designed or modified to incorporate slip rings or integrated non-contact devices capable of transferring electrical power, signal information, or both; and

c.  Having any of the following characteristics:

1.  For any single axis having all of the following:

a.  Capable of rates of 400 degrees/s or more, or 30 degrees/s or less; and

b.  A rate resolution equal to or less than 6 degrees/s and an accuracy equal to or less than 0,6 degrees/s;

2.  Having a worst-case rate stability equal to or better (less) than plus or minus 0,05 % averaged over 10 degrees or more; or

3.  A positioning “accuracy” equal to or less (better) than 5 arc second.

Note 1:   2B120 does not control rotary tables designed or modified for machine tools or for medical equipment. For controls on machine tool rotary tables see 2B008.

Note 2:   Motion simulators or rate tables specified in 2B120 remain controlled whether or not slip rings or integrated non-contact devices are fitted at time of export.

M9B2c

Motion simulators/rate tables (equipment capable of simulating motion) having all of the following characteristics:

1.  Two axes or more;

2.  Designed or modified to incorporate sliprings or integrated non-contact devices capable of transferring electrical power, signal information, or both; and

3.  Having any of the following characteristics:

a.  For any single axis having all of the following:

1.  Capable of rates of 400 degrees/s or more, or 30 degrees/s or less; and

2.  A rate resolution equal to or less than 6 degrees/s and an accuracy equal to or less than 0,6 degrees/s;

b.  Having a worst-case rate stability equal to or better (less) than plus or minus 0,05 % averaged over 10 degrees or more; or

c.  A positioning “accuracy” equal to or less (better) than 5 arc second.

2B121

Positioning tables (equipment capable of precise rotary positioning in any axes), other than those specified in 2B120, having all the following characteristics:

a.  Two axes or more; and

b.  A positioning “accuracy” equal to or less (better) than 5 arc second.

Note:   2B121 does not control rotary tables designed or modified for machine tools or for medical equipment. For controls on machine tool rotary tables see 2B008

M9B2d

Positioning tables (equipment capable of precise rotary positioning in any axes) having the following characteristics:

1.  Two axes or more; and

2.  A positioning “accuracy” equal to or less (better) than 5 arc second;

2B122

Centrifuges capable of imparting accelerations above 100 g and designed or modified to incorporate slip rings or integrated non-contact devices capable of transferring electrical power, signal information, or both.

Note:   Centrifuges specified in 2B122 remain controlled whether or not slip rings or integrated non-contact devices are fitted at time of export

M9B2e

Centrifuges capable of imparting accelerations above 100 g and designed or modified to incorporate sliprings or integrated non-contact devices capable of transferring electrical power, signal information, or both

The corresponding systems, equipment and components as identified in Council Regulation (EC) No 428/2009 of 5 May 2009 setting up a Community regime for the control of exports, transfer, brokering and transit of dual-use items

Missile Technology Control Regime (M.TCR): Equipment, software and technology annex

2D001

“Software”, other than that specified in 2D002, as follows:

a.  “Software” specially designed or modified for the “development” or “production” of equipment specified in 2A001 or 2B001

b.  “Software” specially designed or modified for the “use” of equipment specified in 2A001.c., 2B001 or 2B003 to 2B009.

Note:   2D001 does not control part programming “software” that generates “numerical control” codes for machining various parts.

M3D

SOFTWARE

2D101

“Software” specially designed or modified for the “use” of equipment specified in 2B104, 2B105, 2B109, 2B116, 2B117 or 2B119 to 2B122.

N.B.:  SEE ALSO 9D004.

M3D1

“Software” specially designed or modified for the “use” of “production facilities” and flow-forming machines specified in 3.B.1. or 3.B.3.

M6D2

“Software” specially designed or modified for the equipment specified in 6.B.3., 6.B.4. or 6.B.5.

M15D1

“Software” specially designed or modified for the “use” of equipment specified in 15.B. usable for testing systems specified in 1.A., 19.A.1. or 19.A.2. or subsystems specified in 2.A. or 20.A.

The corresponding systems, equipment and components as identified in Council Regulation (EC) No 428/2009 of 5 May 2009 setting up a Community regime for the control of exports, transfer, brokering and transit of dual-use items

Missile Technology Control Regime (M.TCR): Equipment, software and technology annex

2E001

“Technology” according to the General Technology Note for the “development” of equipment or “software” specified in 2A, 2B or 2D.

Note:   2E001 includes “technology” for the integration of probe systems into coordinate measurement machines specified in 2B006.a.

M

Means specific information which is required for the “development”, “production” or “use” of a product. The information may take the form of “technical data” or “technical assistance”.

2E002

“Technology” according to the General Technology Note for the “production” of equipment specified in 2A or 2B.

M

Means specific information which is required for the “development”, “production” or “use” of a product. The information may take the form of “technical data” or “technical assistance”.

2E101

“Technology” according to the General Technology Note for the “use” of equipment or “software” specified in 2B004, 2B009, 2B104, 2B109, 2B116, 2B119 to 2B122 or 2D101.

M

Means specific information which is required for the “development”, “production” or “use” of a product. The information may take the form of “technical data” or “technical assistance”.

The corresponding systems, equipment and components as identified in Council Regulation (EC) No 428/2009 of 5 May 2009 setting up a Community regime for the control of exports, transfer, brokering and transit of dual-use items

Missile Technology Control Regime (M.TCR): Equipment, software and technology annex

3A001

Electronic components and specially designed components therefor, as follows:

a.  General purpose integrated circuits, as follows:

Note 1:   The control status of wafers (finished or unfinished), in which the function has been determined, is to be evaluated against the parameters of 3A001.a.

Note 2:   Integrated circuits include the following types:

— “Monolithic integrated circuits”;

— “Hybrid integrated circuits”;

— “Multichip integrated circuits”;

— “Film type integrated circuits”, including silicon-on-sapphire integrated circuits;

— “Optical integrated circuits”;

— “Three dimensional integrated circuits”.

1.  Integrated circuits designed or rated as radiation hardened to withstand any of the following:

a.  A total dose of 5 × 10³ Gy (silicon) or higher;

b.  A dose rate upset of 5 × 10⁶ Gy (silicon)/s or higher; or

c.  A fluence (integrated flux) of neutrons (1 MeV equivalent) of 5 × 10¹³ n/cm² or higher on silicon, or its equivalent for other materials;

Note:   3A001.a.1.c. does not control Metal Insulator Semiconductors (MIS).

M18A1

“Radiation Hardened”“microcircuits” usable in protecting rocket systems and unmanned aerial vehicles against nuclear effects (e.g. Electromagnetic Pulse (EMP), X-rays, combined blast and thermal effects), and usable for the systems specified in 1.A.

M18A2

‘Detectors’ specially designed or modified to protect rocket systems and unmanned aerial vehicles against nuclear effects (e.g. Electromagnetic Pulse (EMP), X-rays, combined blast and thermal effects), and usable for the systems specified in 1.A.

Technical Note:

A ‘detector’ is defined as a mechanical, electrical, optical or chemical device that automatically identifies and records, or registers a stimulus such as an environmental change in pressure or temperature, an electrical or electromagnetic signal or radiation from a radioactive material. This includes devices that sense by one time operation or failure.

3A101

Electronic equipment, devices and components, other than those specified in 3A001, as follows:

a.  Analogue-to-digital converters, usable in “missiles”, designed to meet military specifications for ruggedized equipment;

M14A1

Analogue-to-digital converters, usable in the systems specified in 1.A., having any of the following characteristics:

a)  Designed to meet military specifications for ruggedised equipment; or

b)  Designed or modified for military use and being any of the following types:

M14A1b1

1.  Analogue-to-digital converter “microcircuits”, which are “radiation hardened” or have all of the following characteristics:

a.  Rated for operation in the temperature range from below –54 °C to above +125 °C; and

b.  Hermetically sealed; or

M14A1b2

2.  Electrical input type analogue-to-digital converter printed circuit boards or modules, having all of the following characteristics:

a.  Rated for operation in the temperature range from below –45 °C to above +80 °C; and

b.  Incorporating “microcircuits” specified in 14.A.1.b.1.

b.  Accelerators capable of delivering electromagnetic radiation produced by bremsstrahlung from accelerated electrons of 2 MeV or greater, and systems containing those accelerators.

Note:   3A101.b. above does not specify equipment specially designed for medical purposes.

M15B5

Accelerators capable of delivering electromagnetic radiation produced by bremsstrahlung from accelerated electrons of 2 MeV or greater, and equipment containing those accelerators, usable for the systems specified in 1.A., 19.A.1. or 19.A.2. or the subsystems specified in 2.A. or 20.A.

Note:   15.B.5. does not control equipment specially designed for medical purposes.

Technical Note:

In Item 15.B. ‘bare table’ means a flat table, or surface, with no fixture or fittings.

3A102

‘Thermal batteries’ designed or modified for ‘missiles’.

Technical Notes:

1.  In 3A102 ‘thermal batteries’ are single use batteries that contain a solid non-conducting inorganic salt as the electrolyte. These batteries incorporate a pyrolytic material that, when ignited, melts the electrolyte and activates the battery.

2.  In 3A102 ‘missile’ means complete rocket systems and unmanned aerial vehicle systems capable of a range exceeding 300 km.

M12A6

Thermal batteries designed or modified for the systems specified in 1.A., 19.A.1. or 19.A.2.

Note:   Item 12.A.6. does not control thermal batteries specially designed for rocket systems or unmanned aerial vehicles that are not capable of a “range” equal to or greater than 300 km.

Technical Note:

Thermal batteries are single use batteries that contain a solid non-conducting inorganic salt as the electrolyte. These batteries incorporate a pyrolytic material that, when ignited, melts the electrolyte and activates the battery.

The corresponding systems, equipment and components as identified in Council Regulation (EC) No 428/2009 of 5 May 2009 setting up a Community regime for the control of exports, transfer, brokering and transit of dual-use items

Missile Technology Control Regime (M.TCR): Equipment, software and technology annex

3D101

“Software” specially designed or modified for the “use” of equipment specified in 3A101.b.

M15D1

“Software” specially designed or modified for the “use” of equipment specified in 3A101.b.

The corresponding systems, equipment and components as identified in Council Regulation (EC) No 428/2009 of 5 May 2009 setting up a Community regime for the control of exports, transfer, brokering and transit of dual-use items

Missile Technology Control Regime (M.TCR): Equipment, software and technology annex

3E001

“Technology” according to the General Technology Note for the “development” or “production” of equipment or materials specified in 3A, 3B or 3C;

Note 1:   3E001 does not control “technology” for the “production” of equipment or components controlled by 3A003.

Note 2:   3E001 does not control “technology” for the “development” or “production” of integrated circuits specified in 3A001.a.3. to 3A001.a.12., having all of the following:

a.  Using “technology” at or above 0,130 μm; and

b.  Incorporating multi-layer structures with three or fewer metal layers.

M

Means specific information which is required for the “development”, “production” or “use” of a product. The information may take the form of “technical data” or “technical assistance”.

3E101

“Technology” according to the General Technology Note for the “use” of equipment or “software” specified in 3A001.a.1. or 2., 3A101, 3A102 or 3D101.

M

Means specific information which is required for the “development”, “production” or “use” of a product. The information may take the form of “technical data” or “technical assistance”.

3E102

“Technology” according to the General Technology Note for the “development” of “software” specified in 3D101.

M15E1

“Technology”, in accordance with the General Technology Note, for the “development”, “production” or “use” of equipment or “software” specified in 15.B. or 15.D.

The corresponding systems, equipment and components as identified in Council Regulation (EC) No 428/2009 of 5 May 2009 setting up a Community regime for the control of exports, transfer, brokering and transit of dual-use items

Missile Technology Control Regime (M.TCR): Equipment, software and technology annex

4A001

Electronic computers and related equipment, having any of the following and “electronic assemblies” and specially designed components therefor:

N.B.:  SEE ALSO 4A101.

a.  Specially designed to have any of the following:

1.  Rated for operation at an ambient temperature below 228 K (–45 °C) or above 358 K (85 °C); or

Note:   4A001.a.1. does not control computers specially designed for civil automobile, railway train or “civil aircraft” applications.

2.  Radiation hardened to exceed any of the following specifications:

a.  Total Dose 5 × 10³ Gy (silicon);

b.  Dose Rate Upset 5 × 10⁶ Gy (silicon)/s; or

c.  Single Event Upset 1 × 10^–8 Error/bit/day;

Note:   4A001.a.2. does not control computers specially designed for “civil aircraft” applications.

b.  Not used.

M13A1

Analogue computers, digital computers or digital differential analysers, designed or modified for use in the systems specified in 1.A., having any of the following characteristics:

a)  Rated for continuous operation at temperatures from below –45 °C to above +55 °C; or

b)  Designed as ruggedised or “radiation hardened”.

4A003

“Digital computers”, “electronic assemblies”, and related equipment therefor, as follows and specially designed components therefor:

Note 1:   4A003 includes the following:

— ‘Vector processors’;

— Array processors;

— Digital signal processors;

— Logic processors;

— Equipment designed for “image enhancement”;

— Equipment designed for “signal processing”.

Note 2:   The control status of the “digital computers” and related equipment described in 4A003 is determined by the control status of other equipment or systems provided:

a.  The “digital computers” or related equipment are essential for the operation of the other equipment or systems;

b.  The “digital computers” or related equipment are not a “principal element” of the other equipment or systems; and

N.B. 1:   The control status of “signal processing” or “image enhancement” equipment specially designed for other equipment with functions limited to those required for the other equipment is determined by the control status of the other equipment even if it exceeds the “principal element” criterion.

N.B. 2:   For the control status of “digital computers” or related equipment for telecommunications equipment, see Category 5, Part 1 (Telecommunications).

c.  The “technology” for the “digital computers” and related equipment is determined by 4E.

d.  Not used

e.  Equipment performing analogue-to-digital conversions exceeding the limits specified in 3A001.a.5.;

M14A1b2

Electrical input type analogue-to-digital converter printed circuit boards or modules, having all of the following characteristics:

a)  Rated for operation in the temperature range from below –45 °C to above +80 °C; and

b)  Incorporating “microcircuits” specified in 14.A.1.b.1.

4A101

Analogue computers, “digital computers” or digital differential analysers, other than those specified in 4A001.a.1., which are ruggedized and designed or modified for use in space launch vehicles specified in 9A004 or sounding rockets specified in 9A104.

M13A1b

Designed as ruggedised or “radiation hardened”.

4A102

“Hybrid computers” specially designed for modelling, simulation or design integration of space launch vehicles specified in 9A004 or sounding rockets specified in 9A104.

Note:   This control only applies when the equipment is supplied with “software” specified in 7D103 or 9D103.

M16A1

Specially designed hybrid (combined analogue/digital) computers for modelling, simulation or design integration of systems specified in 1.A. or the subsystems specified in 2.A.

Note:  This control only applies when the equipment is supplied with “software” specified in 16.D.1.

The corresponding systems, equipment and components as identified in Council Regulation (EC) No 428/2009 of 5 May 2009 setting up a Community regime for the control of exports, transfer, brokering and transit of dual-use items

Missile Technology Control Regime (M.TCR): Equipment, software and technology annex

4E001

a.  “Technology” according to the General Technology Note, for the “development”, “production” or “use” of equipment or “software” specified in 4A or 4D.

b.  “Technology”, other than that specified in 4E001.a., specially designed or modified for the “development” or “production” of equipment as follows:

1.  “Digital computers” having an “Adjusted Peak Performance” (“APP”) exceeding 1,0 Weighted TeraFLOPS (WT);

2.  “Electronic assemblies” specially designed or modified for enhancing performance by aggregation of processors so that the “APP” of the aggregation exceeds the limit in 4E001.b.1.

c.  “Technology” for the “development” of “intrusion software”.

M

Means specific information which is required for the “development”, “production” or “use” of a product. The information may take the form of “technical data” or “technical assistance”.

The corresponding systems, equipment and components as identified in Council Regulation (EC) No 428/2009 of 5 May 2009 setting up a Community regime for the control of exports, transfer, brokering and transit of dual-use items

Missile Technology Control Regime (M.TCR): Equipment, software and technology annex

5A101

Telemetry and telecontrol equipment, including ground equipment, designed or modified for ‘missiles’.

Technical Note:

In 5A101 ‘missile’ means complete rocket systems and unmanned aerial vehicle systems capable of a range exceeding 300 km.

Note:   5A101 does not control:

a.  Equipment designed or modified for manned aircraft or satellites;

b.  Ground based equipment designed or modified for terrestrial or marine applications;

c.  Equipment designed for commercial, civil or ‘Safety of Life’ (e.g. data integrity, flight safety) GNSS services;

M12A4

Telemetry and telecontrol equipment, including ground equipment, designed or modified for systems specified in 1.A., 19.A.1. or 19.A.2.

Notes:

1.  12.A.4. does not control equipment designed or modified for manned aircraft or satellites.

2.  12.A.4. does not control ground based equipment designed or modified for terrestrial or marine applications.

3.  12.A.4. does not control equipment designed for commercial, civil or ‘Safety of Life’ (e.g. data integrity, flight safety) GNSS services.

The corresponding systems, equipment and components as identified in Council Regulation (EC) No 428/2009 of 5 May 2009 setting up a Community regime for the control of exports, transfer, brokering and transit of dual-use items

Missile Technology Control Regime (M.TCR): Equipment, software and technology annex

5D101

“Software” specially designed or modified for the “use” of equipment specified in 5A101.

M12D3

“Software” specially designed or modified for the “use” of equipment specified in 12.A.4. or 12.A.5., usable for systems specified in 1.A., 19.A.1. or 19.A.2.

The corresponding systems, equipment and components as identified in Council Regulation (EC) No 428/2009 of 5 May 2009 setting up a Community regime for the control of exports, transfer, brokering and transit of dual-use items

Missile Technology Control Regime (M.TCR): Equipment, software and technology annex

5E101

“Technology” according to the General Technology Note for the “development”, “production” or “use” of equipment specified in 5A101.

M12E1

“Technology”, in accordance with the General Technology Note, for the “development”, “production” or “use” of equipment or “software” specified in 12.A. or 12.D.

The corresponding systems, equipment and components as identified in Council Regulation (EC) No 428/2009 of 5 May 2009 setting up a Community regime for the control of exports, transfer, brokering and transit of dual-use items

Missile Technology Control Regime (M.TCR): Equipment, software and technology annex

6A002

Optical sensors or equipment and components therefor, as follows:

N.B.:  SEE ALSO 6A102.

a.  Optical detectors as follows:

1.  “Space-qualified” solid-state detectors as follows:

Note:   For the purpose of 6A002.a.1., solid-state detectors include “focal plane arrays”.

a.  “Space-qualified” solid-state detectors having all of the following:

1.  A peak response in the wavelength range exceeding 10 nm but not exceeding 300 nm; and

2.  A response of less than 0,1 % relative to the peak response at a wavelength exceeding 400 nm;

M18A2

‘Detectors’ specially designed or modified to protect rocket systems and unmanned aerial vehicles against nuclear effects (e.g. Electromagnetic Pulse (EMP), X-rays, combined blast and thermal effects), and usable for the systems specified in 1.A.

Technical Note:

A ‘detector’ is defined as a mechanical, electrical, optical or chemical device that automatically identifies and records, or registers a stimulus such as an environmental change in pressure or temperature, an electrical or electromagnetic signal or radiation from a radioactive material. This includes devices that sense by one time operation or failure

b.  “Space-qualified” solid-state detectors having all of the following:

1.  A peak response in the wavelength range exceeding 900 nm but not exceeding 1 200  nm; and

2.  A response “time constant” of 95 ns or less;

c.  “Space-qualified” solid-state detectors having a peak response in the wavelength range exceeding 1 200  nm but not exceeding 30 000  nm;

d.  “Space-qualified”“focal plane arrays” having more than 2 048 elements per array and having a peak response in the wavelength range exceeding 300 nm but not exceeding 900 nm.

M11A2

Passive sensors for determining bearings to specific electromagnetic sources (direction finding equipment) or terrain characteristics, designed or modified for use in the systems specified in 1.A.

6A006

“Magnetometers”, “magnetic gradiometers”, “intrinsic magnetic gradiometers”, underwater electric field sensors, “compensation systems”, and specially designed components therefor, as follows:

N.B.:  SEE ALSO 7A103.d.

Note:   6A006 does not control instruments specially designed for fishery applications or biomagnetic measurements for medical diagnostics.

a.  “Magnetometers” and subsystems as follows:

1.  “Magnetometers” using “superconductive” (SQUID) “technology” and having any of the following:

a.  SQUID systems designed for stationary operation, without specially designed subsystems designed to reduce in-motion noise, and having a ‘sensitivity’ equal to or lower (better) than 50 fT (rms) per square root Hz at a frequency of 1 Hz; or

b.  SQUID systems having an in-motion-magnetometer ‘sensitivity’ lower (better) than 20 pT (rms) per square root Hz at a frequency of 1 Hz and specially designed to reduce in-motion noise;

2.  “Magnetometers” using optically pumped or nuclear precession (proton/Overhauser) “technology” having a ‘sensitivity’ lower (better) than 20 pT (rms) per square root Hz at a frequency of 1 Hz;

3.  “Magnetometers” using fluxgate “technology” having a ‘sensitivity’ equal to or lower (better) than 10 pT (rms) per square root Hz at a frequency of 1 Hz;

4.  Induction coil “magnetometers” having a ‘sensitivity’ lower (better) than any of the following:

a.  0,05 nT (rms) per square root Hz at frequencies of less than 1 Hz;

b.  1 × 10^–3 nT (rms) per square root Hz at frequencies of 1 Hz or more but not exceeding 10 Hz; or

c.  1 × 10^–4 nT (rms) per square root Hz at frequencies exceeding 10 Hz;

5.  Fibre optic “magnetometers” having a ‘sensitivity’ lower (better) than 1 nT (rms) per square root Hz;

b.  Underwater electric field sensors having a ‘sensitivity’ lower (better) than 8 nanovolt per metre per square root Hz when measured at 1 Hz;

c.  “Magnetic gradiometers” as follows:

1.  “Magnetic gradiometers” using multiple “magnetometers” specified in 6A006.a.;

2.  Fibre optic “intrinsic magnetic gradiometers” having a magnetic gradient field ‘sensitivity’ lower (better) than 0,3 nT/m rms per square root Hz;

3.  “Intrinsic magnetic gradiometers”, using “technology” other than fibre-optic “technology”, having a magnetic gradient field ‘sensitivity’ lower (better) than 0,015 nT/m rms per square root Hz;

d.  “Compensation systems” for magnetic or underwater electric field sensors resulting in a performance equal to or better than the specified parameters of 6A006.a., 6A006.b. or 6A006.c.;

M9A8

Three axis magnetic heading sensors having all of the following characteristics, and specially designed components therefor:

a)  Internal tilt compensation in pitch (+/– 90 degrees) and having roll (+/– 180 degrees) axes.

b)  Capable of providing azimuthal accuracy better (less) than 0,5 degrees rms at latitudes of +/– 80 degrees, referenced to local magnetic field; and

c)  Designed or modified to be integrated with flight control and navigation systems.

Note:  Flight control and navigation systems in Item 9.A.8. include gyrostabilisers, automatic pilots and inertial navigation systems.

6A007

Gravity meters (gravimeters) and gravity gradiometers, as follows:

N.B.:  SEE ALSO 6A107.

a.  Gravity meters designed or modified for ground use and having a static accuracy of less (better) than 10 μGal;

Note:   6A007.a. does not control ground gravity meters of the quartz element (Worden) type.

b.  Gravity meters designed for mobile platforms and having all of the following:

1.  A static accuracy of less (better) than 0,7 mGal; and

2.  An in-service (operational) accuracy of less (better) than 0,7 mGal having a ‘time-to-steady-state registration’ of less than 2 minutes under any combination of attendant corrective compensations and motional influences;

Technical Note:

For the purposes of 6A007.b., ‘time-to-steady-state registration’ (also referred to as the gravimeter's response time) is the time over which the disturbing effects of platform induced accelerations (high frequency noise) are reduced.

c.  Gravity gradiometers.

M12A3

Gravity meters (gravimeters) or gravity gradiometers, designed or modified for airborne or marine use, usable for systems specified in 1.A., as follows, and specially designed components therefor:

a)  Gravity meters having all the following:

1.  A static or operational accuracy equal to or less (better) than 0,7 milligal (mgal); and

2.  A time to steady-state registration of two minutes or less;

b)  Gravity gradiometers.

6A008

Radar systems, equipment and assemblies, having any of the following, and specially designed components therefor:

N.B.:  SEE ALSO 6A108.

Note:   6A008 does not control:

— Secondary surveillance radar (SSR);

— Civil Automotive Radar;

— Displays or monitors used for air traffic control (ATC);

— Meteorological (weather) radar;

— Precision approach radar (PAR) equipment conforming to ICAO standards and employing electronically steerable linear (1-dimensional) arrays or mechanically positioned passive antennae.

M11A1

Radar and laser radar systems, including altimeters, designed or modified for use in the systems specified in 1.A.

Technical Note:

Laser radar systems embody specialised transmission, scanning, receiving and signal processing techniques for utilisation of lasers for echo ranging, direction finding and discrimination of targets by location, radial speed and body reflection characteristics.

a.  Operating at frequencies from 40 GHz to 230 GHz and having any of the following:

1.  An average output power exceeding 100 mW; or

2.  Locating accuracy of 1 m or less (better) in range and 0,2 degree or less (better) in azimuth;

b.  A tunable bandwidth exceeding ± 6,25 % of the ‘centre operating frequency’;

Technical Note:

The ‘centre operating frequency’ equals one half of the sum of the highest plus the lowest specified operating frequencies.

c.  Capable of operating simultaneously on more than two carrier frequencies;

M12A5b

Range instrumentation radars including associated optical/infrared trackers with all of the following capabilities:

1.  Angular resolution better than 1,5 mrad;

2.  Range of 30 km or greater with a range resolution better than 10 m rms; and

3.  Velocity resolution better than 3 m/s.

6A102

Radiation hardened ‘detectors’, other than those specified in 6A002, specially designed modified for protecting against nuclear effects (e.g. electromagnetic pulse (EMP), X-rays, combined blast and thermal effects) and usable for “missiles”, designed or rated to withstand radiation levels which meet or exceed a total irradiation dose of 5 × 10⁵ rads (silicon).

Technical Note:

In 6A102, a ‘detector’ is defined as a mechanical, electrical, optical or chemical device that automatically identifies and records, or registers a stimulus such as an environmental change in pressure or temperature, an electrical or electromagnetic signal or radiation from a radioactive material. This includes devices that sense by one time operation or failure.

M18A2

‘Detectors’ specially designed or modified to protect rocket systems and unmanned aerial vehicles against nuclear effects (e.g. Electromagnetic Pulse (EMP), X-rays, combined blast and thermal effects), and usable for the systems specified in 1.A.

Technical Note:

A ‘detector’ is defined as a mechanical, electrical, optical or chemical device that automatically identifies and records, or registers a stimulus such as an environmental change in pressure or temperature, an electrical or electromagnetic signal or radiation from a radioactive material. This includes devices that sense by one time operation or failure.

6A107

Gravity meters (gravimeters) and components for gravity meters and gravity gradiometers, as follows:

a.  Gravity meters, other than those specified in 6A007.b, designed or modified for airborne or marine use, and having a static or operational accuracy equal to or less (better) than 0,7 milligal (mgal), and having a time-to-steady-state registration of two minutes or less;

b.  Specially designed components for gravity meters specified in 6A007.b or 6A107.a. and gravity gradiometers specified in 6A007.c.

M12A3

Gravity meters (gravimeters) or gravity gradiometers, designed or modified for airborne or marine use, usable for systems specified in 1.A., as follows, and specially designed components therefor:

a)  Gravity meters having all the following:

1.  A static or operational accuracy equal to or less (better) than 0,7 milligal (mgal); and

2.  A time to steady-state registration of two minutes or less;

b)  Gravity gradiometers.

6A108

Radar systems and tracking systems, other than those specified in entry 6A008, as follows:

a.  Radar and laser radar systems designed or modified for use in space launch vehicles specified in 9A004 or sounding rockets specified in 9A104;

Note:   6A108.a. includes the following:

a.  Terrain contour mapping equipment;

b.  Imaging sensor equipment;

c.  Scene mapping and correlation (both digital and analogue) equipment;

d.  Doppler navigation radar equipment.

M11A1

Radar and laser radar systems, including altimeters, designed or modified for use in the systems specified in 1.A.

Technical Note:

Laser radar systems embody specialised transmission, scanning, receiving and signal processing techniques for utilisation of lasers for echo ranging, direction finding and discrimination of targets by location, radial speed and body reflection characteristics.

b.  Precision tracking systems, usable for ‘missiles’, as follows:

1.  Tracking systems which use a code translator in conjunction with either surface or airborne references or navigation satellite systems to provide real-time measurements of in-flight position and velocity;

2.  Range instrumentation radars including associated optical/infrared trackers with all of the following capabilities:

a.  Angular resolution better than 1,5 milliradians;

b.  Range of 30 km or greater with a range resolution better than 10 m rms;

c.  Velocity resolution better than 3 m/s.

Technical Note:

In 6A108.b. ‘missile’ means complete rocket systems and unmanned aerial vehicle systems capable of a range exceeding 300 km.

M12A5

Precision tracking systems, usable for systems specified in 1.A., 19.A.1. or 19.A.2. as follows:

a.  Tracking systems which use a code translator installed on the rocket or unmanned aerial vehicle in conjunction with either surface or airborne references or navigation satellite systems to provide real-time measurements of inflight position and velocity;

b.  Range instrumentation radars including associated optical/infrared trackers with all of the following capabilities:

1.  Angular resolution better than 1,5 mrad;

2.  Range of 30 km or greater with a range resolution better than 10 m rms; and

3.  Velocity resolution better than 3 m/s.

The corresponding systems, equipment and components as identified in Council Regulation (EC) No 428/2009 of 5 May 2009 setting up a Community regime for the control of exports, transfer, brokering and transit of dual-use items

Missile Technology Control Regime (M.TCR): Equipment, software and technology annex

6B008

Pulse radar cross-section measurement systems having transmit pulse widths of 100 ns or less, and specially designed components therefor.

N.B.:  SEE ALSO 6B108.

M17B1

Systems, specially designed for radar cross section measurement, usable for the systems specified in 1.A., 19.A.1. or 19.A.2. or the subsystems specified in 2.A

6B108

Systems, other than those specified in 6B008, specially designed for radar cross section measurement usable for ‘missiles’ and their subsystems.

Technical Note:

In 6B108 ‘missile’ means complete rocket systems and unmanned aerial vehicle systems capable of a range exceeding 300 km.

M17B1

Systems, specially designed for radar cross section measurement, usable for the systems specified in 1.A., 19.A.1. or 19.A.2. or the subsystems specified in 2.A

The corresponding systems, equipment and components as identified in Council Regulation (EC) No 428/2009 of 5 May 2009 setting up a Community regime for the control of exports, transfer, brokering and transit of dual-use items

Missile Technology Control Regime (M.TCR): Equipment, software and technology annex

6D002

“Software” specially designed for the “use” of equipment specified in 6A002.b., 6A008 or 6B008.

M

Means specific information which is required for the “development”, “production” or “use” of a product. The information may take the form of “technical data” or “technical assistance”.

6D102

“Software” specially designed or modified for the “use” of goods specified in 6A108.

M11D1

“Software” specially designed or modified for the “use” of equipment specified in 11.A.1., 11.A.2. or 11.A.4.

M12D3

“Software” specially designed or modified for the “use” of equipment specified in 12.A.4. or 12.A.5., usable for systems specified in 1.A., 19.A.1. or 19.A.2.

6D103

“Software” which processes post-flight, recorded data, enabling determination of vehicle position throughout its flight path, specially designed or modified for ‘missiles’.

Technical Note:

In 6D103 ‘missile’ means complete rocket systems and unmanned aerial vehicle systems capable of a range exceeding 300 km.

M12D2

“Software” which processes post-flight, recorded data, enabling determination of vehicle position throughout its flight path, specially designed or modified for systems specified in 1.A., 19.A.1. or 19.A.2.

The corresponding systems, equipment and components as identified in Council Regulation (EC) No 428/2009 of 5 May 2009 setting up a Community regime for the control of exports, transfer, brokering and transit of dual-use items

Missile Technology Control Regime (M.TCR): Equipment, software and technology annex

6E001

“Technology” according to the General Technology Note for the “development” of equipment, materials or “software” specified in 6A, 6B, 6C or 6D.

M

Means specific information which is required for the “development”, “production” or “use” of a product. The information may take the form of “technical data” or “technical assistance”.

6E002

“Technology” according to the General Technology Note for the “production” of equipment or materials specified in 6A, 6B or 6C.

M

Means specific information which is required for the “development”, “production” or “use” of a product. The information may take the form of “technical data” or “technical assistance”.

6E101

“Technology” according to the General Technology Note for the “use” of equipment or “software” specified in 6A002, 6A007.b. and c., 6A008, 6A102, 6A107, 6A108, 6B108, 6D102 or 6D103.

Note:   6E101 only specifies “technology” for equipment specified in 6A008 when it is designed for airborne applications and is usable in “missiles”.

M

Means specific information which is required for the “development”, “production” or “use” of a product. The information may take the form of “technical data” or “technical assistance”.

The corresponding systems, equipment and components as identified in Council Regulation (EC) No 428/2009 of 5 May 2009 setting up a Community regime for the control of exports, transfer, brokering and transit of dual-use items

Missile Technology Control Regime (M.TCR): Equipment, software and technology annex

7A001

Accelerometers as follows and specially designed components therefor:

N.B.:  SEE ALSO 7A101.

N.B.:   For angular or rotational accelerometers, see 7A001.b.

a.  Linear accelerometers having any of the following:

1.  Specified to function at linear acceleration levels less than or equal to 15 g and having any of the following:

a.  A “bias”“stability” of less (better) than 130 micro g with respect to a fixed calibration value over a period of one year; or

b.  A “scale factor”“stability” of less (better) than 130 ppm with respect to a fixed calibration value over a period of one year;

2.  Specified to function at linear acceleration levels exceeding 15 g but less than or equal to 100 g and having all of the following:

a.  A “bias”“repeatability” of less (better) than 1 250 micro g over a period of one year; and

b.  A “scale factor”“repeatability” of less (better) than 1 250  ppm over a period of one year; or

3.  Designed for use in inertial navigation or guidance systems and specified to function at linear acceleration levels exceeding 100 g;

Note:   7A001.a.1. and 7A001.a.2. do not control accelerometers limited to measurement of only vibration or shock.

M9A3

Linear accelerometers, designed for use in inertial navigation systems or in guidance systems of all types, usable in the systems specified in 1.A., 19.A.1. or 19.A.2., having all of the following characteristics, and specially designed components therefor:

a.  ‘Scale factor’‘repeatability’ less (better) than 1 250  ppm; and

b.  ‘Bias’‘repeatability’ less (better) than 1 250 micro g.

Note:   Item 9.A.3. does not control accelerometers specially designed and developed as Measurement While Drilling (MWD) sensors for use in downhole well service operations.

Technical Notes:

1.  ‘Bias’ is defined as the accelerometer output when no acceleration is applied.

2.  ‘Scale factor’ is defined as the ratio of change in output to a change in the input.

3.  The measurement of ‘bias’ and ‘scale factor’ refers to one sigma standard deviation with respect to a fixed calibration over a period of one year.

4.  ‘Repeatability’ is defined according to IEEE Standard for Inertial Sensor Terminology 528-2001 in the Definitions section paragraph 2.214 titled repeatability (gyro, accelerometer) as follows: ‘The closeness of agreement among repeated measurements of the same variable under the same operating conditions when changes in conditions or non-operating periods occur between measurements’.

b.  Angular or rotational accelerometers, specified to function at linear acceleration levels exceeding 100 g.

M9A5

Accelerometers or gyros of any type, designed for use in inertial navigation systems or in guidance systems of all types, specified to function at acceleration levels greater than 100 g, and specially designed components therefor.

Note:   9.A.5. does not include accelerometers that are designed to measure vibration or shock.

7A002

Gyros or angular rate sensors, having any of the following and specially designed components therefor:

N.B.:  SEE ALSO 7A102.

N.B.:   For angular or rotational accelerometers, see 7A001.b.

a.  Specified to function at linear acceleration levels less than or equal to 100 g and having any of the following:

1.  A rate range of less than 500 degrees per second and having any of the following:

a.  A “bias”“stability” of less (better) than 0,5 degree per hour, when measured in a 1 g environment over a period of one month, and with respect to a fixed calibration value; or

b.  An “angle random walk” of less (better) than or equal to 0,0035 degree per square root hour; or

Note:   7A002.a.1.b. does not control “spinning mass gyros”.

2.  A rate range greater than or equal to 500 degrees per second and having any of the following:

a.  A “bias”“stability” of less (better) than 4 degrees per hour, when measured in a 1 g environment over a period of three minutes, and with respect to a fixed calibration value; or

b.  An “angle random walk” of less (better) than or equal to 0,1 degree per square root hour; or

Note:   7A002.a.2.b. does not control “spinning mass gyros”.

M9A4

All types of gyros usable in the systems specified in 1.A., 19.A.1 or 19.A.2., with a rated ‘drift rate’‘stability’ of less than 0,5 degrees (1 sigma or rms) per hour in a 1 g environment, and specially designed components therefor.

Technical Notes:

1.  ‘Drift rate’ is defined as the component of gyro output that is functionally independent of input rotation and is expressed as an angular rate. (IEEE STD 528-2001 paragraph 2.56)

2.  ‘Stability’ is defined as a measure of the ability of a specific mechanism or performance coefficient to remain invariant when continuously exposed to a fixed operating condition. (This definition does not refer to dynamic or servo stability.) (IEEE STD 528-2001 paragraph 2.247)

b.  Specified to function at linear acceleration levels exceeding 100 g.

M9A5

Accelerometers or gyros of any type, designed for use in inertial navigation systems or in guidance systems of all types, specified to function at acceleration levels greater than 100 g, and specially designed components therefor.

Note:   9.A.5. does not include accelerometers that are designed to measure vibration or shock.

7A003

‘Inertial measurement equipment or systems’, having any of the following:

N.B.:  SEE ALSO 7A103.

Note 1:   ‘Inertial measurement equipment or systems’ incorporate accelerometers or gyroscopes to measure changes in velocity and orientation in order to determine or maintain heading or position without requiring an external reference once aligned. ‘Inertial measurement equipment or systems’ include:

— Attitude and Heading Reference Systems (AHRSs);

— Gyrocompasses;

— Inertial Measurement Units (IMUs);

— Inertial Navigation Systems (INSs);

— Inertial Reference Systems (IRSs);

— Inertial Reference Units (IRUs).

Note 2:   7A003 does not control ‘inertial measurement equipment or systems’ which are certified for use on “civil aircraft” by civil aviation authorities of one or more “participating states”.

Technical Notes:

1.  ‘Positional aiding references’ independently provide position, and include:

a.  Global Navigation Satellite Systems (GNSS);

b.  “Data-Based Referenced Navigation” (“DBRN”).

2.  ‘Circular Error Probable’ (‘CEP’) — In a circular normal distribution, the radius of the circle containing 50 % of the individual measurements being made, or the radius of the circle within which there is a 50 % probability of being located.

a.  Designed for “aircraft”, land vehicles or vessels, providing position without the use of ‘positional aiding references’, and having any of the following accuracies subsequent to normal alignment:

1.  0,8 nautical miles per hour (nm/hr) ‘Circular Error Probable’ (‘CEP’) rate or less (better);

2.  0,5 % distanced travelled ‘CEP’ or less (better); or

3.  Total drift of 1 nautical mile ‘CEP’ or less (better) in a 24 hr period;

Technical Note:

The performance parameters in 7A003.a.1., 7A003.a.2. and 7A003.a.3. typically apply to ‘inertial measurement equipment or systems’ designed for “aircraft”, vehicles and vessels, respectively. These parameters result from the utilisation of specialised non-positional aiding references (e.g., altimeter, odometer, velocity log). As a consequence, the specified performance values cannot be readily converted between these parameters. Equipment designed for multiple platforms are evaluated against each applicable entry 7A003.a.1., 7A003.a.2., or 7A003.a.3.

b.  Designed for “aircraft”, land vehicles or vessels, with an embedded ‘positional aiding reference’ and providing position after loss of all ‘positional aiding references’ for a period of up to 4 minutes, having an accuracy of less (better) than 10 meters ‘CEP’;

Technical Note:

7A003.b. refers to systems in which ‘inertial measurement equipment or systems’ and other independent ‘positional aiding references’ are built into a single unit (i.e., embedded) in order to achieve improved performance.

c.  Designed for “aircraft”, land vehicles or vessels, providing heading or True North determination and having any of the following:

1.  A maximum operating angular rate less (lower) than 500 deg/s and a heading accuracy without the use of ‘positional aiding references’ equal to or less (better) than 0,07 deg sec(Lat) (equivalent to 6 arc minutes rms at 45 degrees latitude); or

2.  A maximum operating angular rate equal to or greater (higher) than 500 deg/s and a heading accuracy without the use of ‘positional aiding references’ equal to or less (better) than 0,2 deg sec(Lat) (equivalent to 17 arc minutes rms at 45 degrees latitude); or

d.  Providing acceleration measurements or angular rate measurements, in more than one dimension, and having any of the following:

1.  Performance specified by 7A001 or 7A002 along any axis, without the use of any aiding references; or

2.  Being “space-qualified” and providing angular rate measurements having an “angle random walk” along any axis of less (better) than or equal to 0,1 degree per square root hour.

Note:   7A003.d.2. does not control ‘inertial measurement equipment or systems’ that contain “spinning mass gyros” as the only type of gyro.

M2A1d

‘Guidance sets’, usable in the systems specified in 1.A., capable of achieving system accuracy of 3,33 % or less of the “range” (e.g. a ‘CEP’ of 10 km or less at a “range” of 300 km), except as provided in the Note below 2.A.1. for those designed for missiles with a “range” under 300 km or manned aircraft;

M9A6

Inertial or other equipment using accelerometers specified in 9.A.3. or 9.A.5. or gyros specified in 9.A.4. or 9.A.5., and systems incorporating such equipment, and specially designed components therefor.

M9A8

Three axis magnetic heading sensors having all of the following characteristics, and specially designed components therefor:

a.  Internal tilt compensation in pitch (+/– 90 degrees) and having roll (+/– 180 degrees) axes.

b.  Capable of providing azimuthal accuracy better (less) than 0,5 degrees rms at latitudes of +/– 80 degrees, referenced to local magnetic field; and

c.  Designed or modified to be integrated with flight control and navigation systems.

Note:   Flight control and navigation systems in Item 9.A.8. include gyrostabilisers, automatic pilots and inertial navigation systems.

7A004

‘Star trackers’ and components therefor, as follows:

N.B.:  SEE ALSO 7A104.

a.  ‘Star trackers’ with a specified azimuth accuracy of equal to or less (better) than 20 seconds of arc throughout the specified lifetime of the equipment;

b.  Components specially designed for equipment specified in 7A004.a. as follows:

1.  Optical heads or baffles;

2.  Data processing units.

Technical Note:

‘Star trackers’ are also referred to as stellar attitude sensors or gyro-astro compasses.

M9A2

Gyro-astro compasses and other devices which derive position or orientation by means of automatically tracking celestial bodies or satellites, and specially designed components therefor.

7A005

Global Navigation Satellite Systems (GNSS) receiving equipment having any of the following and specially designed components therefor:

N.B.:  SEE ALSO 7A105.

N.B.:   For equipment specially designed for military use, see Military Goods Controls.

a.  Employing a decryption algorithm specially designed or modified for government use to access the ranging code for position and time; or

b.  Employing ‘adaptive antenna systems’.

Note:   7A005.b. does not control GNSS receiving equipment that only uses components designed to filter, switch, or combine signals from multiple omni-directional antennae that do not implement adaptive antenna techniques.

Technical Note:

For the purposes of 7A005.b ‘adaptive antenna systems’ dynamically generate one or more spatial nulls in an antenna array pattern by signal processing in the time domain or frequency domain.

M11A3

Receiving equipment for Global Navigation Satellite Systems (GNSS; e.g. GPS, GLONASS or Galileo), having any of the following characteristics, and specially designed components therefor:

a.  Designed or modified for use in systems specified in 1.A.; or

b.  Designed or modified for airborne applications and having any of the following:

1.  Capable of providing navigation information at speeds in excess of 600 m/s;

2.  Employing decryption, designed or modified for military or governmental services, to gain access to GNSS secure signal/data; or

3.  Being specially designed to employ anti-jam features (e.g. null steering antenna or electronically steerable antenna) to function in an environment of active or passive countermeasures.

Note:   11.A.3.b.2. and 11.A.3.b.3. do not control equipment designed for commercial, civil or ‘Safety of Life’ (e.g. data integrity, flight safety) GNSS services.

7A006

Airborne altimeters operating at frequencies other than 4,2 to 4,4 GHz inclusive and having any of the following:

N.B.:  SEE ALSO 7A106.

a.  “Power management”; or

b.  Using phase shift key modulation.

M11A1

Radar and laser radar systems, including altimeters, designed or modified for use in the systems specified in 1.A.

Technical Note:

Laser radar systems embody specialised transmission, scanning, receiving and signal processing techniques for utilisation of lasers for echo ranging, direction finding and discrimination of targets by location, radial speed and body reflection characteristics.

7A101

Linear accelerometers, other than those specified in 7A001, designed for use in inertial navigation systems or in guidance systems of all types, usable in ‘missiles’, having all the following characteristics, and specially designed components therefor:

a.  A “bias”“repeatability” of less (better) than 1 250 micro g; and

b.  A “scale factor”“repeatability” of less (better) than 1 250  ppm;

Note:   7A101 does not control accelerometers specially designed and developed as Measurement While Drilling (MWD) Sensors for use in downhole well service operations.

Technical Notes:

1.  In 7A101 ‘missile’ means complete rocket systems and unmanned aerial vehicle systems capable of a range exceeding 300 km;

2.  In 7A101 the measurement of “bias” and “scale factor” refers to a one sigma standard deviation with respect to a fixed calibration over a period of one year;

M9A3

Linear accelerometers, designed for use in inertial navigation systems or in guidance systems of all types, usable in the systems specified in 1.A., 19.A.1. or 19.A.2., having all of the following characteristics, and specially designed components therefor:

a.  ‘Scale factor’‘repeatability’ less (better) than 1 250  ppm; and

b.  ‘Bias’‘repeatability’ less (better) than 1 250 micro g.

Note:  Item 9.A.3. does not control accelerometers specially designed and developed as Measurement While Drilling (MWD) sensors for use in downhole well service operations.

Technical Notes:

1.  ‘Bias’ is defined as the accelerometer output when no acceleration is applied.

2.  ‘Scale factor’ is defined as the ratio of change in output to a change in the input.

3.  The measurement of ‘bias’ and ‘scale factor’ refers to one sigma standard deviation with respect to a fixed calibration over a period of one year.

4.  ‘Repeatability’ is defined according to IEEE Standard for Inertial Sensor Terminology 528-2001 in the Definitions section paragraph 2.214 titled repeatability (gyro, accelerometer) as follows: ‘The closeness of agreement among repeated measurements of the same variable under the same operating conditions when changes in conditions or non-operating periods occur between measurements’.

7A102

All types of gyros, other than those specified in 7A002, usable in ‘missiles’, with a rated “drift rate”‘stability’ of less than 0,5° (1 sigma or rms) per hour in a 1 g environment and specially designed components therefor.

Technical Notes:

1.  In 7A102 ‘missile’ means complete rocket systems and unmanned aerial vehicle systems capable of a range exceeding 300 km.

2.  In 7A102 ‘stability’ is defined as a measure of the ability of a specific mechanism or performance coefficient to remain invariant when continuously exposed to a fixed operating condition (IEEE STD 528-2001 paragraph 2.247).

M9A4

All types of gyros usable in the systems specified in 1.A., 19.A.1 or 19.A.2., with a rated ‘drift rate’‘stability’ of less than 0,5 degrees (1 sigma or rms) per hour in a 1 g environment, and specially designed components therefor.

Technical Notes:

1.  ‘Drift rate’ is defined as the component of gyro output that is functionally independent of input rotation and is expressed as an angular rate. (IEEE STD 528-2001 paragraph 2.56)

2.  ‘Stability’ is defined as a measure of the ability of a specific mechanism or performance coefficient to remain invariant when continuously exposed to a fixed operating condition. (This definition does not refer to dynamic or servo stability.) (IEEE STD 528-2001 paragraph 2.247)

7A103

Instrumentation, navigation equipment and systems, other than those specified in 7A003, as follows; and specially designed components therefor:

a.  Inertial or other equipment, using accelerometers or gyros as follows, and systems incorporating such equipment:

1.  Accelerometers specified in 7A001.a.3., 7A001.b. or 7A101 or gyros specified in 7A002 or 7A102; or

2.  Accelerometers specified in 7A001.a.1. or 7A001.a.2., designed for use in inertial navigation systems or in guidance systems of all types, and usable in ‘missiles’;

Note:   7A103.a. does not specify equipment containing accelerometers specified in 7A001 where such accelerometers are specially designed and developed as MWD (Measurement While Drilling) sensors for use in down-hole well services operations.

M9A6

Inertial or other equipment using accelerometers specified in 9.A.3. or 9.A.5. or gyros specified in 9.A.4. or 9.A.5., and systems incorporating such equipment, and specially designed components therefor.

b.  Integrated flight instrument systems which include gyrostabilisers or automatic pilots, designed or modified for use in ‘missiles’;

M9A1

Integrated flight instrument systems which include gyrostabilisers or automatic pilots, designed or modified for use in the systems specified in 1.A., or 19.A.1. or 19.A.2. and specially designed components therefor.

c.  ‘Integrated navigation systems’, designed or modified for ‘missiles’ and capable of providing a navigational accuracy of 200 m Circle of Equal Probability (CEP) or less;

Technical Note:

An ‘integrated navigation system’ typically incorporates the following components:

1.  An inertial measurement device (e.g., an attitude and heading reference system, inertial reference unit, or inertial navigation system);

2.  One or more external sensors used to update the position and/or velocity, either periodically or continuously throughout the flight (e.g., satellite navigation receiver, radar altimeter, and/or Doppler radar); and

3.  Integration hardware and software;

M9A7

‘Integrated navigation systems’, designed or modified for the systems specified in 1.A., 19.A.1. or 19.A.2. and capable of providing a navigational accuracy of 200 m CEP or less.

Technical Note:

An ‘integrated navigation system’ typically incorporates all of the following components:

a.  An inertial measurement device (e.g. an attitude and heading reference system, inertial reference unit, or inertial navigation system);

b.  One or more external sensors used to update the position and/or velocity, either periodically or continuously throughout the flight (e.g. satellite navigation receiver, radar altimeter, and/or Doppler radar); and

c.  Integration hardware and software.

N.B.  For integration “software”, see Item 9.D.4.

d.  Three axis magnetic heading sensors, designed or modified to be integrated with flight control and navigation systems, other than those specified in 6A006, having all the following characteristics, and specially designed components therefor;

1.  Internal tilt compensation in pitch (± 90 degrees) and roll (± 180 degrees) axes;

2.  Capable of providing azimuthal accuracy better (less) than 0,5 degrees rms at latitude of ± 80 degrees, reference to local magnetic field.

Note:   Flight control and navigation systems in 7A103.d. include gyrostabilizers, automatic pilots and inertial navigation systems.

Technical Note:

In 7A103 ‘missile’ means complete rocket systems and unmanned aerial vehicle systems capable of a range exceeding 300 km.

M9A8

Three axis magnetic heading sensors having all of the following characteristics, and specially designed components therefor:

a.  Internal tilt compensation in pitch (+/– 90 degrees) and having roll (+/– 180 degrees) axes.

b.  Capable of providing azimuthal accuracy better (less) than 0,5 degrees rms at latitudes of +/– 80 degrees, referenced to local magnetic field; and

c.  Designed or modified to be integrated with flight control and navigation systems.

Note:   Flight control and navigation systems in Item 9.A.8. include gyrostabilisers, automatic pilots and inertial navigation systems.

7A104

Gyro-astro compasses and other devices, other than those specified in 7A004, which derive position or orientation by means of automatically tracking celestial bodies or satellites and specially designed components therefor.

M9A2

Gyro-astro compasses and other devices which derive position or orientation by means of automatically tracking celestial bodies or satellites, and specially designed components therefor.

7A105

Receiving equipment for Global Navigation Satellite Systems (GNSS; e.g. GPS, GLONASS, or Galileo), other than those specified in 7A005, having any of the following characteristics, and specially designed components therefor:

a.  Designed or modified for use in space launch vehicles specified in 9A004, sounding rockets specified in 9A104 or unmanned aerial vehicles specified in 9A012 or 9A112.a.; or

b.  Designed or modified for airborne applications and having any of the following:

1.  Capable of providing navigation information at speeds in excess of 600 m/s;

2.  Employing decryption, designed or modified for military or governmental services, to gain access to GNSS secured signal/data; or

3.  Being specially designed to employ anti-jam features (e.g. null steering antenna or electronically steerable antenna) to function in an environment of active or passive countermeasures.

Note:   7A105.b.2. and 7A105.b.3. do not control equipment designed for commercial, civil or ‘Safety of Life’ (e.g., data integrity, flight safety) GNSS services.

M11A3

Receiving equipment for Global Navigation Satellite Systems (GNSS; e.g. GPS, GLONASS or Galileo), having any of the following characteristics, and specially designed components therefor:

a.  Designed or modified for use in systems specified in 1.A.; or

b.  Designed or modified for airborne applications and having any of the following:

1.  Capable of providing navigation information at speeds in excess of 600 m/s;

2.  Employing decryption, designed or modified for military or governmental services, to gain access to GNSS secure signal/data; or

3.  Being specially designed to employ anti-jam features (e.g. null steering antenna or electronically steerable antenna) to function in an environment of active or passive countermeasures.

Note:   11.A.3.b.2. and 11.A.3.b.3. do not control equipment designed for commercial, civil or ‘Safety of Life’ (e.g. data integrity, flight safety) GNSS services.

7A106

Altimeters, other than those specified in 7A006, of radar or laser radar type, designed or modified for use in space launch vehicles specified in 9A004 or sounding rockets specified in 9A104.

M11A1

Radar and laser radar systems, including altimeters, designed or modified for use in the systems specified in 1.A.

Technical Note:

Laser radar systems embody specialised transmission, scanning, receiving and signal processing techniques for utilisation of lasers for echo ranging, direction finding and discrimination of targets by location, radial speed and body reflection characteristics.

7A115

Passive sensors for determining bearing to specific electromagnetic source (direction finding equipment) or terrain characteristics, designed or modified for use in space launch vehicles specified in 9A004 or sounding rockets specified in 9A104.

Note:   7A115 includes sensors for the following equipment:

a.  Terrain contour mapping equipment;

b.  Imaging sensor equipment (both active and passive);

c.  Passive interferometer equipment

M11A2

Passive sensors for determining bearings to specific electromagnetic sources (direction finding equipment) or terrain characteristics, designed or modified for use in the systems specified in 1.A.

7A116

Flight control systems and servo valves, as follows; designed or modified for use in space launch vehicles specified in 9A004 or sounding rockets specified in 9A104.

a.  Hydraulic, mechanical, electro-optical, or electro-mechanical flight control systems (including fly-by-wire types);

M10A1

Pneumatic, hydraulic, mechanical, electro-optical, or electromechanical flight control systems (including fly-by-wire and fly-by-light systems) designed or modified for the systems specified in 1.A.

b.  Attitude control equipment;

M10A2

Attitude control equipment designed or modified for the systems specified in 1.A.

c.  Flight control servo valves designed or modified for the systems specified in 7A116.a. or 7A116.b., and designed or modified to operate in a vibration environment greater than 10 g rms between 20 Hz and 2 kHz.

M10A3

Flight control servo valves designed or modified for the systems in 10.A.1. or 10.A.2., and designed or modified to operate in a vibration environment greater than 10 g rms between 20 Hz and 2 kHz.

Note:   Systems, equipment or valves specified in 10.A. may be exported as part of a manned aircraft or satellite or in quantities appropriate for replacement parts for manned aircraft.

7A117

“Guidance sets”, usable in “missiles” capable of achieving system accuracy of 3,33 % or less of the range (e.g., a “CEP” of 10 km or less at a range of 300 km).

M2A1d

‘Guidance sets’, usable in the systems specified in 1.A., capable of achieving system accuracy of 3,33 % or less of the “range” (e.g. a ‘CEP’ of 10 km or less at a “range” of 300 km), except as provided in the Note below 2.A.1. for those designed for missiles with a “range” under 300 km or manned aircraft;

The corresponding systems, equipment and components as identified in Council Regulation (EC) No 428/2009 of 5 May 2009 setting up a Community regime for the control of exports, transfer, brokering and transit of dual-use items

Missile Technology Control Regime (M.TCR): Equipment, software and technology annex

7B001

Test, calibration or alignment equipment, specially designed for equipment specified in 7A.

Note:   7B001 does not control test, calibration or alignment equipment for ‘Maintenance Level I’ or ‘Maintenance Level II’.

Technical Notes:

1.   ‘Maintenance Level I’

The failure of an inertial navigation unit is detected on the aircraft by indications from the Control and Display Unit (CDU) or by the status message from the corresponding sub-system. By following the manufacturer's manual, the cause of the failure may be localised at the level of the malfunctioning Line Replaceable Unit (LRU). The operator then removes the LRU and replaces it with a spare.

2.   ‘Maintenance Level II’

The defective LRU is sent to the maintenance workshop (the manufacturer's or that of the operator responsible for level II maintenance). At the maintenance workshop, the malfunctioning LRU is tested by various appropriate means to verify and localise the defective Shop Replaceable Assembly (SRA) module responsible for the failure. This SRA is removed and replaced by an operative spare. The defective SRA (or possibly the complete LRU) is then shipped to the manufacturer. ‘Maintenance Level II’ does not include the disassembly or repair of controlled accelerometers or gyro sensors.

M2B2

“Production equipment” specially designed for the subsystems specified in 2.A.

M9B1

“Production equipment”, and other test, calibration and alignment equipment, other than that described in 9.B.2., designed or modified to be used with equipment specified in 9.A.

Note:   Equipment specified in 9.B.1. includes the following:

a.  For laser gyro equipment, the following equipment used to characterise mirrors, having the threshold accuracy shown or better:

1.  Scatterometer (10 ppm);

2.  Reflectometer (50 ppm);

3.  Profilometer (5 Angstroms);

b.  For other inertial equipment:

1.  Inertial Measurement Unit (IMU) Module Tester;

2.  IMU Platform Tester;

3.  IMU Stable Element Handling Fixture;

4.  IMU Platform Balance Fixture;

5.  Gyro Tuning Test Station;

6.  Gyro Dynamic Balance Station;

7.  Gyro Run-In/Motor Test Station;

8.  Gyro Evacuation and Filling Station;

9.  Centrifuge Fixture for Gyro Bearings;

10.  Accelerometer Axis Align Station;

11.  Accelerometer Test Station;

12.  Fibre Optic Gyro Coil Winding Machines

M10B1

Test, calibration, and alignment equipment specially designed for equipment specified in 10.A.

7B002

Equipment specially designed to characterize mirrors for ring “laser” gyros, as follows:

N.B.:  SEE ALSO 7B102.

a.  Scatterometers having a measurement accuracy of 10 ppm or less (better);

b.  Profilometers having a measurement accuracy of 0,5 nm (5 angstrom) or less (better).

M9B1

“Production equipment”, and other test, calibration and alignment equipment, other than that described in 9.B.2., designed or modified to be used with equipment specified in 9.A.

Note:  Equipment specified in 9.B.1. includes the following:

a.  For laser gyro equipment, the following equipment used to characterise mirrors, having the threshold accuracy shown or better:

1.  Scatterometer (10 ppm);

2.  Reflectometer (50 ppm);

3.  Profilometer (5 Angstroms);

b.  For other inertial equipment:

1.  Inertial Measurement Unit (IMU) Module Tester;

2.  IMU Platform Tester;

3.  IMU Stable Element Handling Fixture;

4.  IMU Platform Balance Fixture;

5.  Gyro Tuning Test Station;

6.  Gyro Dynamic Balance Station;

7.  Gyro Run-In/Motor Test Station;

8.  Gyro Evacuation and Filling Station;

9.  Centrifuge Fixture for Gyro Bearings;

10.  Accelerometer Axis Align Station;

11.  Accelerometer Test Station;

12.  Fibre Optic Gyro Coil Winding Machines.

7B003

Equipment specially designed for the “production” of equipment specified in 7A.

Note:   7B003 includes:

— Gyro tuning test stations;

— Gyro dynamic balance stations;

— Gyro run-in/motor test stations;

— Gyro evacuation and fill stations;

— Centrifuge fixtures for gyro bearings;

— Accelerometer axis align stations;

— Fibre optic gyro coil winding machines.

M2B2

“Production equipment” specially designed for the subsystems specified in 2.A.

M9B1

“Production equipment”, and other test, calibration and alignment equipment, other than that described in 9.B.2., designed or modified to be used with equipment specified in 9.A.

Note:   Equipment specified in 9.B.1. includes the following:

a.  For laser gyro equipment, the following equipment used to characterise mirrors, having the threshold accuracy shown or better:

1.  Scatterometer (10 ppm);

2.  Reflectometer (50 ppm);

3.  Profilometer (5 Angstroms);

b.  For other inertial equipment:

1.  Inertial Measurement Unit (IMU) Module Tester;

2.  IMU Platform Tester;

3.  IMU Stable Element Handling Fixture;

4.  IMU Platform Balance Fixture;

5.  Gyro Tuning Test Station;

6.  Gyro Dynamic Balance Station;

7.  Gyro Run-In/Motor Test Station;

8.  Gyro Evacuation and Filling Station;

9.  Centrifuge Fixture for Gyro Bearings;

10.  Accelerometer Axis Align Station;

11.  Accelerometer Test Station;

12.  Fibre Optic Gyro Coil Winding Machines.

7B102

Reflectometers specially designed to characterise mirrors, for “laser” gyros, having a measurement accuracy of 50 ppm or less (better).

M9B1

“Production equipment”, and other test, calibration and alignment equipment, other than that described in 9.B.2., designed or modified to be used with equipment specified in 9.A.

Note:   Equipment specified in 9.B.1. includes the following:

a.  For laser gyro equipment, the following equipment used to characterise mirrors, having the threshold accuracy shown or better:

1.  Scatterometer (10 ppm);

2.  Reflectometer (50 ppm);

3.  Profilometer (5 Angstroms);

b.  For other inertial equipment:

1.  Inertial Measurement Unit (IMU) Module Tester;

2.  IMU Platform Tester;

3.  IMU Stable Element Handling Fixture;

4.  IMU Platform Balance Fixture;

5.  Gyro Tuning Test Station;

6.  Gyro Dynamic Balance Station;

7.  Gyro Run-In/Motor Test Station;

8.  Gyro Evacuation and Filling Station;

9.  Centrifuge Fixture for Gyro Bearings;

10.  Accelerometer Axis Align Station;

11.  Accelerometer Test Station;

12.  Fibre Optic Gyro Coil Winding Machines.

7B103

“Production facilities” and “production equipment” as follows:

a.  “Production facilities” specially designed for equipment specified in 7A117;

M2B1

“Production facilities” specially designed for the subsystems specified in 2.A

b.  “Production equipment”, and other test, calibration and alignment equipment, other than that specified in 7B001 to 7B003, designed or modified to be used with equipment specified in 7A.

M2B2*

“Production equipment” specially designed for the subsystems specified in 2.A.

M9B1

“Production equipment”, and other test, calibration and alignment equipment, other than that described in 9.B.2., designed or modified to be used with equipment specified in 9.A.

Note:   Equipment specified in 9.B.1. includes the following:

a.  For laser gyro equipment, the following equipment used to characterise mirrors, having the threshold accuracy shown or better:

1.  Scatterometer (10 ppm);

2.  Reflectometer (50 ppm);

3.  Profilometer (5 Angstroms);

b.  For other inertial equipment:

1.  Inertial Measurement Unit (IMU) Module Tester;

2.  IMU Platform Tester;

3.  IMU Stable Element Handling Fixture;

4.  IMU Platform Balance Fixture;

5.  Gyro Tuning Test Station;

6.  Gyro Dynamic Balance Station;

7.  Gyro Run-In/Motor Test Station;

8.  Gyro Evacuation and Filling Station;

9.  Centrifuge Fixture for Gyro Bearings;

10.  Accelerometer Axis Align Station;

11.  Accelerometer Test Station;

12.  Fibre Optic Gyro Coil Winding Machines.

The corresponding systems, equipment and components as identified in Council Regulation (EC) No 428/2009 of 5 May 2009 setting up a Community regime for the control of exports, transfer, brokering and transit of dual-use items

Missile Technology Control Regime (M.TCR): Equipment, software and technology annex

7D002

“Source code” for the operation or maintenance of any inertial navigation equipment, including inertial equipment not specified in 7A003 or 7A004, or Attitude and Heading Reference Systems (‘AHRS’).

Note:   7D002 does not control “source code” for the “use” of gimballed ‘AHRS’.

Technical Note:

‘AHRS’ generally differ from Inertial Navigation Systems (INS) in that an ‘AHRS’ provides attitude and heading information and normally does not provide the acceleration, velocity and position information associated with an INS.

M2D3

“Software”, specially designed or modified for the operation or maintenance of ‘guidance sets’ specified in 2.A.1.d.

Note:   2.D.3. includes “software”, specially designed or modified to enhance the performance of ‘guidance sets’ to achieve or exceed the accuracy specified in 2.A.1.d.

M9D1

“Software” specially designed or modified for the “use” of equipment specified in 9.A. or 9.B.

7D101

“Software” specially designed or modified for the “use” of equipment specified in 7A001 to 7A006, 7A101 to 7A106, 7A115, 7A116.a., 7A116.b., 7B001, 7B002, 7B003, 7B102 or 7B103.

M2D

“Software” specially designed or modified for the “use” of “production facilities” specified in 2.B.1.

M9D1

“Software” specially designed or modified for the “use” of equipment specified in 9.A. or 9.B.

M10D1

“Software” specially designed or modified for the “use” of equipment specified in 10.A. or 10.B.

Note:   “Software” specified in 10.D.1. may be exported as part of a manned aircraft or satellite or in quantities appropriate for replacement parts for manned aircraft.

M11D1&2

“Software” specially designed or modified for the “use” of equipment specified in 11.A.1., 11.A.2. or 11.A.4.

“Software” specially designed for the “use” of equipment specified in 11.A.3.

7D102

Integration “software” as follows:

a.  Integration “software” for the equipment specified in 7A103.b.;

M9D2

Integration “software” for the equipment specified in 9.A.1.

b.  Integration “software” specially designed for the equipment specified in 7A003 or 7A103.a.

M9D3*

Integration “software” specially designed for the equipment specified in 9.A.6.

c.  Integration “software” designed or modified for the equipment specified in 7A103.c.

Note:   A common form of integration “software” employs Kalman filtering.

M9D4

Integration “software”, designed or modified for the ‘integrated navigation systems’ specified in 9.A.7.

Note:   A common form of integration “software” employs Kalman filtering.

7D103

“Software” specially designed for modelling or simulation of the “guidance sets” specified in 7A117 or for their design integration with the space launch vehicles specified in 9A004 or sounding rockets specified in 9A104.

Note:   “Software” specified in 7D103 remains controlled when combined with specially designed hardware specified in 4A102.

M16D1

“Software” specially designed for modelling, simulation, or design integration of the systems specified in 1.A. or the subsystems specified in 2.A or 20.A.

Technical Note:   The modelling includes in particular the aerodynamic and thermodynamic analysis of the systems.

The corresponding systems, equipment and components as identified in Council Regulation (EC) No 428/2009 of 5 May 2009 setting up a Community regime for the control of exports, transfer, brokering and transit of dual-use items

Missile Technology Control Regime (M.TCR): Equipment, software and technology annex

7E001

“Technology” according to the General Technology Note for the “development” of equipment or “software”, specified in 7A, 7B, 7D001, 7D002, 7D003, 7D005 and 7D101 to 7D103.

Note:   7E001 includes key management “technology” exclusively for equipment specified in 7A005.a.

M

Means specific information which is required for the “development”, “production” or “use” of a product. The information may take the form of “technical data” or “technical assistance”.

7E002

“Technology” according to the General Technology Note for the “production” of equipment specified in 7A or 7B.

M

Means specific information which is required for the “development”, “production” or “use” of a product. The information may take the form of “technical data” or “technical assistance”.

7E003

“Technology” according to the General Technology Note for the repair, refurbishing or overhaul of equipment specified in 7A001 to 7A004.

Note:   7E003 does not control maintenance “technology” directly associated with calibration, removal or replacement of damaged or unserviceable LRUs and SRAs of a “civil aircraft” as described in ‘Maintenance Level I’ or ‘Maintenance Level II’.

N.B.:   See Technical Notes to 7B001.

M2E1

“Technology”, in accordance with the General Technology Note, for the “development”, “production” or “use” of equipment or “software” specified in 2.A., 2.B. or 2.D.

M9E1

“Technology”, in accordance with the General Technology Note, for the “development”, “production” or “use” of equipment or “software” specified in 9.A., 9.B. or 9.D.

Note:   Equipment or “software” specified in 9.A. or 9.D. may be exported as part of a manned aircraft, satellite, land vehicle, marine/submarine vessel or geophysical survey equipment or in quantities appropriate for replacement parts for such applications.

7E004

Other “technology” as follows:

a.  “Technology” for the “development” or “production” of any of the following:

1.  Not used;

2.  Air data systems based on surface static data only, i.e., which dispense with conventional air data probes;

3.  Three dimensional displays for “aircraft”;

4.  Not used;

5.  Electric actuators (i.e., electromechanical, electrohydrostatic and integrated actuator package) specially designed for “primary flight control”;

6.  “Flight control optical sensor array” specially designed for implementing “active flight control systems”; or

7.  “DBRN” systems designed to navigate underwater, using sonar or gravity databases, that provide a positioning accuracy equal to or less (better) than 0,4 nautical miles;

b.  “Development”“technology”, as follows, for “active flight control systems” (including “fly-by-wire systems” or “fly-by-light systems”):

1.  Photonic-based “technology” for sensing aircraft or flight control component state, transferring flight control data, or commanding actuator movement, “required” for “fly-by-light systems”“active flight control systems”;

2.  Not used;

3.  Real-time algorithms to analyze component sensor information to predict and preemptively mitigate impending degradation and failures of components within an “active flight control system”;

Note:   7E004.b.3. does not control algorithms for purpose of off-line maintenance.

4.  Real-time algorithms to identify component failures and reconfigure force and moment controls to mitigate “active flight control system” degradations and failures;

Note:   7E004.b.4. does not control algorithms for the elimination of fault effects through comparison of redundant data sources, or off-line pre-planned responses to anticipated failures.

5.  Integration of digital flight control, navigation and propulsion control data, into a digital flight management system for “total control of flight”;

Note:   7E004.b.5. does not control:

a.  “Development”“technology” for integration of digital flight control, navigation and propulsion control data, into a digital flight management system for “flight path optimisation”;

b.  “Development”“technology” for “aircraft” flight instrument systems integrated solely for VOR, DME, ILS or MLS navigation or approaches.

6.  Not used;

7.  “Technology”“required” for deriving the functional requirements for “fly-by-wire systems” having all of the following:

a.  ‘Inner-loop’ airframe stability controls requiring loop closure rates of 40 Hz or greater; and

Technical Note:

‘Inner-loop’ refers to functions of “active flight control systems” that automate airframe stability controls.

b.  Having any of the following:

1.  Corrects an aerodynamically unstable airframe, measured at any point in the design flight envelope, that would lose recoverable control if not corrected within 0,5 seconds;

2.  Couples controls in two or more axes while compensating for ‘abnormal changes in aircraft state’;

Technical Note:

‘Abnormal changes in aircraft state’ include in-flight structural damage, loss of engine thrust, disabled control surface, or destabilizing shifts in cargo load.

3.  Preforms the functions specified in 7E004.b.5.; or

Note:   7E004.b.7.b.3. does not control autopilots.

4.  Enables aircraft to have stable controlled flight, other than during take-off or landing, at greater than 18 degrees angle of attack, 15 degrees side slip, 15 degrees/second pitch or yaw rate, or 90 degrees/second roll rate;

8.  “Technology”“required” for deriving the functional requirements for “fly-by-wire systems” to achieve all of the following:

a.  No loss of control of the aircraft in the event of a consecutive sequence of any two individual faults within the “fly-by-wire system”; and

b.  Probability of loss of control of the aircraft being less (better) than 1 × 10^–9 failures per flight hour;

Note:   7E004.b. does not control technology associated with common computer elements and utilities (e.g., input signal acquisition, output signal transmission, computer program and data loading, built-in test, task scheduling mechanisms) not providing a specific flight control system function.

c.  “Technology” for the “development” of helicopter systems, as follows:

1.  Multi-axis fly-by-wire or fly-by-light controllers, which combine the functions of at least two of the following into one controlling element:

a.  Collective controls;

b.  Cyclic controls;

c.  Yaw controls;

2.  “Circulation-controlled anti-torque or circulation-controlled directional control systems”;

3.  Rotor blades incorporating “variable geometry airfoils”, for use in systems using individual blade control.

M10E1

Design “technology” for integration of air vehicle fuselage, propulsion system and lifting control surfaces, designed or modified for the systems specified in 1.A. or 19.A.2., to optimise aerodynamic performance throughout the flight regime of an unmanned aerial vehicle.

7E101

“Technology” according to the General Technology Note for the “use” of equipment specified in 7A001 to 7A006, 7A101 to 7A106, 7A115 to 7A117, 7B001, 7B002, 7B003, 7B102, 7B103, 7D101 to 7D103.

M

Means specific information which is required for the “development”, “production” or “use” of a product. The information may take the form of “technical data” or “technical assistance”.

7E102

“Technology” for protection of avionics and electrical subsystems against electromagnetic pulse (EMP) and electromagnetic interference (EMI) hazards, from external sources, as follows:

a.  Design “technology” for shielding systems;

b.  Design “technology” for the configuration of hardened electrical circuits and subsystems;

c.  Design “technology” for the determination of hardening criteria of 7E102.a. and 7E102.b.

M11E1

Design “technology” for protection of avionics and electrical subsystems against Electromagnetic Pulse (EMP) and Electromagnetic Interference (EMI) hazards from external sources, as follows:

a.  Design “technology” for shielding systems;

b.  Design “technology” for the configuration of hardened electrical circuits and subsystems;

c.  Design “technology” for determination of hardening criteria for the above.

7E104

“Technology” for the integration of the flight control, guidance, and propulsion data into a flight management system for optimization of rocket system trajectory.

M10E2

Design “technology” for integration of the flight control, guidance, and propulsion data into a flight management system, designed or modified for the systems specified in 1.A. or 19.A.1., for optimisation of rocket system trajectory.

The corresponding systems, equipment and components as identified in Council Regulation (EC) No 428/2009 of 5 May 2009 setting up a Community regime for the control of exports, transfer, brokering and transit of dual-use items

Missile Technology Control Regime (M.TCR): Equipment, software and technology annex

9A001

Aero gas turbine engines having any of the following:

N.B.:  SEE ALSO 9A101.

a.  Incorporating any of the “technologies” specified in 9E003.a., 9E003.h. or 9E003.i.; or

Note 1:   9A001.a. does not control aero gas turbine engines which meet all of the following:

a.  Certified by the civil aviation authorities of one or more “participating states”; and

b.  Intended to power non-military manned aircraft for which any of the following has been issued by civil aviation authorities of one or more “participating states” for the aircraft with this specific engine type:

1.  A civil type certificate; or

2.  An equivalent document recognized by the International Civil Aviation Organisation (ICAO).

Note 2:   9A001.a. does not control aero gas turbine engines designed for Auxiliary Power Units (APUs) approved by the civil aviation authority in a “participating state”.

b.  Designed to power an aircraft to cruise at Mach 1 or higher, for more than thirty minutes.

M3A1

Turbojet and turbofan engines, as follows:

a.  Engines having both of the following characteristics:

1.  ‘Maximum thrust value’ greater than 400 N (achieved un-installed) excluding civil certified engines with a ‘maximum thrust value’ greater than 8,89 kN (achieved un-installed); and

2.  Specific fuel consumption of 0,15 kg N^–1 h^–1 or less (at maximum continuous power at sea level static conditions using the ICAO standard atmosphere);

Technical Note:

In 3.A.1.a.1., ‘maximum thrust value’ is the manufacturer's demonstrated maximum thrust for the engine type un-installed. The civil type certified thrust value will be equal to or less than the manufacturer's demonstrated maximum thrust for the engine type.

b.  Engines designed or modified for systems specified in 1.A. or 19.A.2., regardless of thrust or specific fuel consumption.

Note:  Engines specified in 3.A.1. may be exported as part of a manned aircraft or in quantities appropriate for replacement parts for a manned aircraft.

9A004

Space launch vehicles, “spacecraft”, “spacecraft buses”, “spacecraft payloads”, “spacecraft” on-board systems or equipment, and terrestrial equipment, as follows:

N.B.:  SEE ALSO 9A104.

a.  Space launch vehicles;

b.  “Spacecraft”;

c.  “Spacecraft buses”;

d.  “Spacecraft payloads” incorporating items specified in 3A001.b.1.a.4., 3A002.g., 5A001.a.1., 5A001.b.3., 5A002.a.5., 5A002.a.9., 6A002.a.1., 6A002.a.2., 6A002.b., 6A002.d., 6A003.b., 6A004.c., 6A004.e., 6A008.d., 6A008.e., 6A008.k., 6A008.l. or 9A010.c.;

e.  On-board systems or equipment, specially designed for “spacecraft” and having any of the following functions:

1.  ‘Command and telemetry data handling’;

Note:   For the purpose of 9A004.e.1., ‘command and telemetry data handling’ includes bus data management, storage, and processing.

2.  ‘Payload data handling’; or

Note:   For the purpose of 9A004.e.2., ‘payload data handling’ includes payload data management, storage, and processing.

3.  ‘Attitude and orbit control’;

Note:   For the purpose of 9A004.e.3., ‘attitude and orbit control’ includes sensing and actuation to determine and control the position and orientation of a “spacecraft”.

N.B.:   For equipment specially designed for military use, see Military Goods Controls.

f.  Terrestrial equipment, specially designed for “spacecraft” as follows:

1.  Telemetry and telecommand equipment;

2.  Simulators.

M1A1

Complete rocket systems (including ballistic missile systems, space launch vehicles, and sounding rockets) capable of delivering at least a 500 kg “payload” to a “range” of at least 300 km.

M19A1

Complete rocket systems (including ballistic missile systems, space launch vehicles, and sounding rockets), not specified in 1.A.1., capable of a “range” equal to or greater than 300 km.

9A005

Liquid rocket propulsion systems containing any of the systems or components, specified in 9A006.

N.B.:  SEE ALSO 9A105 AND 9A119.

M2A1a

Individual rocket stages usable in the systems specified in 1.A.;

M2A1c

Rocket propulsion subsystems, usable in the systems specified in 1.A., as follows;

1.  Solid propellant rocket motors or hybrid rocket motors having a total impulse capacity equal to or greater than 1,1 × 10⁶ Ns;

2.  Liquid propellant rocket engines or gel propellant rocket motors integrated, or designed or modified to be integrated, into a liquid propellant or gel propellant propulsion system which has a total impulse capacity equal to or greater than 1,1 × 10⁶ Ns;

Note:  Liquid propellant apogee engines or station-keeping engines specified in 2.A.1.c.2., designed or modified for use on satellites, may be treated as Category II, if the subsystem is exported subject to end-use statements and quantity limits appropriate for the excepted end-use stated above, when having a vacuum thrust not greater than 1kN.

M20A1

Complete subsystems as follows:

a.  Individual rocket stages, not specified in 2.A.1., usable in systems specified in 19.A.;

b.  Rocket propulsion subsystems, not specified in 2.A.1., usable in the systems specified in 19.A.1., as follows:

1.  Solid propellant rocket motors or hybrid rocket motors having a total impulse capacity equal to or greater than 8,41 × 10⁵ Ns, but less than 1,1 × 10⁶ Ns;

2.  Liquid propellant rocket engines or gel propellant rocket motors integrated, or designed or modified to be integrated, into a liquid propellant or gel propellant propulsion system which has a total impulse capacity equal to or greater than 8,41 × 10⁵ Ns, but less than 1,1 × 10⁶ Ns;

9A006

Systems and components, specially designed for liquid rocket propulsion systems, as follows:

N.B.:  SEE ALSO 9A106, 9A108 AND 9A120.

a.  Cryogenic refrigerators, flightweight dewars, cryogenic heat pipes or cryogenic systems, specially designed for use in space vehicles and capable of restricting cryogenic fluid losses to less than 30 % per year;

b.  Cryogenic containers or closed-cycle refrigeration systems, capable of providing temperatures of 100 K (–173 °C) or less for “aircraft” capable of sustained flight at speeds exceeding Mach 3, launch vehicles or “spacecraft”;

c.  Slush hydrogen storage or transfer systems;

d.  High pressure (exceeding 17,5 MPa) turbo pumps, pump components or their associated gas generator or expander cycle turbine drive systems;

M3A8

Liquid propellant tanks specially designed for the propellants controlled in Item 4.C. or other liquid propellants used in the systems specified in 1.A.1.

M3A5

Liquid, slurry and gel propellant (including oxidisers) control systems, and specially designed components therefor, usable in the systems specified in 1.A., designed or modified to operate in vibration environments greater than 10 g rms between 20 Hz and 2 kHz.

Notes:

1.  The only servo valves, pumps and gas turbines specified in 3.A.5. are the following:

a.  Servo valves designed for flow rates equal to or greater than 24 litres per minute, at an absolute pressure equal to or greater than 7 MPa, that have an actuator response time of less than 100 ms.

b.  Pumps, for liquid propellants, with shaft speeds equal to or greater than 8 000 rpm at the maximum operating mode or with discharge pressures equal to or greater than 7 MPa.

c.  Gas turbines, for liquid propellant turbopumps, with shaft speeds equal to or greater than 8 000 rpm at the maximum operating mode.

2.  Systems and components specified in 3.A.5. may be exported as part of a satellite.

e.  High-pressure (exceeding 10,6 MPa) thrust chambers and nozzles therefor;

M3A10

Combustion chambers and nozzles for liquid propellant rocket engines usable in the subsystems specified in 2.A.1.c.2. or 20.A.1.b.2.

f.  Propellant storage systems using the principle of capillary containment or positive expulsion (i.e., with flexible bladders);

M3A8

g.  Liquid propellant injectors with individual orifices of 0,381 mm or smaller in diameter (an area of 1,14 × 10^–3 cm² or smaller for non-circular orifices) and specially designed for liquid rocket engines;

M3A5

h.  One-piece carbon-carbon thrust chambers or one-piece carbon-carbon exit cones, with densities exceeding 1,4 g/cm³ and tensile strengths exceeding 48 MPa.

M3A10

9A007

Solid rocket propulsion systems having any of the following:

N.B.:  SEE ALSO 9A107 AND 9A119.

a.  Total impulse capacity exceeding 1,1 MNs;

b.  Specific impulse of 2,4 kNs/kg or more, when the nozzle flow is expanded to ambient sea level conditions for an adjusted chamber pressure of 7 MPa;

c.  Stage mass fractions exceeding 88 % and propellant solid loadings exceeding 86 %;

d.  Components specified in 9A008; or

e.  Insulation and propellant bonding systems, using direct-bonded motor designs to provide a ‘strong mechanical bond’ or a barrier to chemical migration between the solid propellant and case insulation material.

Technical Note:

‘Strong mechanical bond’ means bond strength equal to or more than propellant strength.

M2A1

Complete subsystems usable in the systems specified in 1.A., as follows:

a.  Individual rocket stages usable in the systems specified in 1.A.;

b.  Re-entry vehicles, and equipment designed or modified therefor, usable in the systems specified in 1.A., as follows, except as provided in the Note below 2.A.1. for those designed for non-weapon payloads:

1.  Heat shields, and components therefor, fabricated of ceramic or ablative materials;

2.  Heat sinks and components therefor, fabricated of light-weight, high heat capacity materials;

3.  Electronic equipment specially designed for re-entry vehicles;

c.  Rocket propulsion subsystems, usable in the systems specified in 1.A., as follows;

1.  Solid propellant rocket motors or hybrid rocket motors having a total impulse capacity equal to or greater than 1,1 × 10⁶ Ns;

2.  Liquid propellant rocket engines or gel propellant rocket motors integrated, or designed or modified to be integrated, into a liquid propellant or gel propellant propulsion system which has a total impulse capacity equal to or greater than 1,1 × 10⁶ Ns;

Note:   Liquid propellant apogee engines or station-keeping engines specified in 2.A.1.c.2., designed or modified for use on satellites, may be treated as Category II, if the subsystem is exported subject to end-use statements and quantity limits appropriate for the excepted end-use stated above, when having a vacuum thrust not greater than 1kN.

d.  ‘Guidance sets’, usable in the systems specified in 1.A., capable of achieving system accuracy of 3,33 % or less of the “range” (e.g. a ‘CEP’ of 10 km or less at a “range” of 300 km), except as provided in the Note below 2.A.1. for those designed for missiles with a “range” under 300 km or manned aircraft;

Technical Notes:

1.  A ‘guidance set’ integrates the process of measuring and computing a vehicle's position and velocity (i.e. navigation) with that of computing and sending commands to the vehicle's flight control systems to correct the trajectory.

2.  ‘CEP’ (circle of equal probability) is a measure of accuracy, defined as the radius of the circle centred at the target, at a specific range, in which 50 % of the payloads impact.

e.  Thrust vector control subsystems, usable in the systems specified in 1.A., except as provided in the Note below 2.A.1. for those designed for rocket systems that do not exceed the “range”/“payload” capability of systems specified in 1.A.;

Technical Note:

2.A.1.e. includes the following methods of achieving thrust vector control:

a.  Flexible nozzle;

b.  Fluid or secondary gas injection;

c.  Movable engine or nozzle;

d.  Deflection of exhaust gas stream (jet vanes or probes);

e.  Use of thrust tabs.

f.  Weapon or warhead safing, arming, fuzing, and firing mechanisms, usable in the systems specified in 1.A., except as provided in the Note below 2.A.1. for those designed for systems other than those specified in 1.A.

Note:   The exceptions in 2.A.1.b., 2.A.1.d., 2.A.1.e. and 2.A.1.f. above may be treated as Category II if the subsystem is exported subject to end-use statements and quantity limits appropriate for the excepted end-use stated above.

Solid propellant rocket motors or hybrid rocket motors having a total impulse capacity equal to or greater than 1,1 × 10⁶ Ns;

M2A1c1

9A008

Components specially designed for solid rocket propulsion systems, as follows:

N.B.:  SEE ALSO 9A108.

a.  Insulation and propellant bonding systems, using liners to provide a ‘strong mechanical bond’ or a barrier to chemical migration between the solid propellant and case insulation material;

Technical Note:

‘Strong mechanical bond’ means bond strength equal to or more than propellant strength.

M3A3

Rocket motor cases, ‘insulation’ components and nozzles therefor, usable in the systems specified in 1.A. or 19.A.1.

Technical Note:

In 3.A.3. ‘insulation’ intended to be applied to the components of a rocket motor, i.e. the case, nozzle inlets, case closures, includes cured or semi-cured compounded rubber components comprising sheet stock containing an insulating or refractory material. It may also be incorporated as stress relief boots or flaps.

Note:   Refer to 3.C.2. for ‘insulation’ material in bulk or sheet form.

M3C1

‘Interior lining’ usable for rocket motor cases in the subsystems specified in 2.A.1.c.1. or specially designed for subsystems specified in 20.A.1.b.1.

Technical Note:

In 3.C.1. ‘interior lining’ suited for the bond interface between the solid propellant and the case or insulating liner is usually a liquid polymer based dispersion of refractory or insulating materials e.g. carbon filled HTPB or other polymer with added curing agents to be sprayed or screeded over a case interior.

b.  Filament-wound “composite” motor cases exceeding 0,61 m in diameter or having ‘structural efficiency ratios (PV/W)’ exceeding 25 km;

Technical Note:

‘Structural efficiency ratio (PV/W)’ is the burst pressure (P) multiplied by the vessel volume (V) divided by the total pressure vessel weight (W).

M3C2

‘Insulation’ material in bulk form usable for rocket motor cases in the subsystems specified in 2.A.1.c.1. or specially designed for subsystems specified in 20.A.1.b.1.

Technical Note:

In 3.C.2. ‘insulation’ intended to be applied to the components of a rocket motor, i.e. the case, nozzle inlets, case closures, includes cured or semi-cured compounded rubber sheet stock containing an insulating or refractory material. It may also be incorporated as stress relief boots or flaps specified in 3.A.3.

c.  Nozzles with thrust levels exceeding 45 kN or nozzle throat erosion rates of less than 0,075 mm/s;

d.  Movable nozzle or secondary fluid injection thrust vector control systems, capable of any of the following:

1.  Omni-axial movement exceeding ± 5°;

2.  Angular vector rotations of 20°/s or more; or

3.  Angular vector accelerations of 40°/s² or more

M2A1e

Thrust vector control subsystems, usable in the systems specified in 1.A., except as provided in the Note below 2.A.1. for those designed for rocket systems that do not exceed the “range”/“payload” capability of systems specified in 1.A.;

Technical Note:

2.A.1.e. includes the following methods of achieving thrust vector control:

a.  Flexible nozzle;

b.  Fluid or secondary gas injection;

c.  Movable engine or nozzle;

d.  Deflection of exhaust gas stream (jet vanes or probes);

e.  Use of thrust tabs.

9A009

Hybrid rocket propulsion systems having any of the following:

N.B.:  SEE ALSO 9A109 AND 9A119.

a.  Total impulse capacity exceeding 1,1 MNs; or

b.  Thrust levels exceeding 220 kN in vacuum exit conditions.

M2A1c1

Solid propellant rocket motors or hybrid rocket motors having a total impulse capacity equal to or greater than 1,1 × 10⁶ Ns;

M20A1b

Rocket propulsion subsystems, not specified in 2.A.1., usable in the systems specified in 19.A.1., as follows:

1.  Solid propellant rocket motors or hybrid rocket motors having a total impulse capacity equal to or greater than 8,41 × 10⁵ Ns, but less than 1,1 × 10⁶ Ns;

2.  Liquid propellant rocket engines or gel propellant rocket motors integrated, or designed or modified to be integrated, into a liquid propellant or gel propellant propulsion system which has a total impulse capacity equal to or greater than 8,41 × 10⁵ Ns, but less than 1,1 × 10⁶ Ns;

9A010

Specially designed components, systems and structures, for launch vehicles, launch vehicle propulsion systems or “spacecraft”, as follows:

N.B.:  SEE ALSO 1A002 AND 9A110.

a.  Components and structures, each exceeding 10 kg and specially designed for launch vehicles manufactured using any of the following:

1.  “Composite” materials consisting of “fibrous or filamentary materials” specified in 1C0010.e. and resins specified in 1C008 or 1C009.b.;

2.  Metal “matrix”“composites” reinforced by any of the following:

a.  Materials specified in 1C007;

b.  “Fibrous or filamentary materials” specified in 1C010; or

c.  Aluminides specified in 1C002.a.; or

3.  Ceramic “matrix”“composite” materials specified in 1C007;

Note:   The weight cut-off is not relevant for nose cones.

M6A1

Composite structures, laminates, and manufactures thereof, specially designed for use in the systems specified in 1.A., 19.A.1. or 19.A.2. and the subsystems specified in 2.A. or 20.A.

b.  Components and structures, specially designed for launch vehicle propulsion systems specified in 9A005 to 9A009 manufactured using any of the following:

1.  “Fibrous or filamentary materials” specified in 1C010.e. and resins specified in 1C008 or 1C009.b.;

2.  Metal “matrix”“composites” reinforced by any of the following:

a.  Materials specified in 1C007;

b.  “Fibrous or filamentary materials” specified in 1C010; or

c.  Aluminides specified by 1C002.a.; or

3.  Ceramic “matrix”“composite” materials specified in 1C007;

M6A1

Composite structures, laminates, and manufactures thereof, specially designed for use in the systems specified in 1.A., 19.A.1. or 19.A.2. and the subsystems specified in 2.A. or 20.A.

c.  Structural components and isolation systems, specially designed to control actively the dynamic response or distortion of “spacecraft” structures;

M6A1

Composite structures, laminates, and manufactures thereof, specially designed for use in the systems specified in 1.A., 19.A.1. or 19.A.2. and the subsystems specified in 2.A. or 20.A.

d.  Pulsed liquid rocket engines with thrust-to-weight ratios equal to or more than 1 kN/kg and a response time (the time required to achieve 90 % of total rated thrust from start-up) of less than 30 ms.

M3A2

Ramjet/scramjet/pulse jet/‘combined cycle engines’, including devices to regulate combustion, and specially designed components therefor, usable in the systems specified in 1.A. or 19.A.2.

Technical Note:

In Item 3.A.2., ‘combined cycle engines’ are the engines that employ two or more cycles of the following types of engines: gas-turbine engine (turbojet, turboprop, turbofan and turboshaft), ramjet, scramjet, pulse jet, pulse detonation engine, rocket motor (liquid/solid-propellant and hybrid).

9A011

Ramjet, scramjet or combined cycle engines, and specially designed components therefor.

N.B.:  SEE ALSO 9A111 AND 9A118.

M3A2

Ramjet/scramjet/pulse jet/‘combined cycle engines’, including devices to regulate combustion, and specially designed components therefor, usable in the systems specified in 1.A. or 19.A.2.

Technical Note:

In Item 3.A.2., ‘combined cycle engines’ are the engines that employ two or more cycles of the following types of engines: gas-turbine engine (turbojet, turboprop, turbofan and turboshaft), ramjet, scramjet, pulse jet, pulse detonation engine, rocket motor (liquid/solid-propellant and hybrid).

9A012

“Unmanned aerial vehicles” (“UAVs”), unmanned “airships”, related equipment and components, as follows:

N.B.:  SEE ALSO 9A112.

a.  “UAVs” or unmanned “airships”, designed to have controlled flight out of the direct ‘natural vision’ of the ‘operator’ and having any of the following:

1.  Having all of the following:

a.  A maximum ‘endurance’ greater than or equal to 30 minutes but less than 1 hour; and

b.  Designed to take-off and have stable controlled flight in wind gusts equal to or exceeding 46,3 km/h (25 knots); or

2.  A maximum ‘endurance’ of 1 hour or greater;

Technical Notes:

1.  For the purposes of 9A012.a., ‘operator’ is a person who initiates or commands the “UAV” or unmanned “airship” flight.

2.  For the purposes of 9A012.a., ‘endurance’ is to be calculated for ISA conditions (ISO 2533:1975) at sea level in zero wind.

3.  For the purposes of 9A012.a., ‘natural vision’ means unaided human sight, with or without corrective lenses.

b.  Related equipment and components, as follows:

1.  Not used

2.  Not used

M1A2

Complete unmanned aerial vehicle systems (including cruise missile systems, target drones and reconnaissance drones) capable of delivering at least a 500 kg “payload” to a “range” of at least 300 km.

M19A

ITEM 19 OTHER COMPLETE DELIVERY SYSTEMS: equipment, assemblies and components

3.  Equipment or components, specially designed to convert a manned “aircraft” or manned “airship”, to a “UAV” or unmanned “airship”, specified in 9A012.a.;

4.  Air breathing reciprocating or rotary internal combustion type engines, specially designed or modified to propel “UAVs” or unmanned “airships”, at altitudes above 15 240 metres (50 000 feet).

M9A6

Inertial or other equipment using accelerometers specified in 9.A.3. or 9.A.5. or gyros specified in 9.A.4. or 9.A.5., and systems incorporating such equipment, and specially designed components therefor.

9A101

Turbojet and turbofan engines, other than those specified in 9A001, as follows;

a.  Engines having both of the following characteristics:

1.  ‘Maximum thrust value’ greater than 400 N (achieved un-installed) excluding civil certified engines with a ‘maximum thrust value’ greater than 8 890  N (achieved un-installed), and

2.  Specific fuel consumption of 0,15 kg/N/hr or less (at maximum continuous power at sea level static conditions using the ICAO standard atmosphere);

Technical Note:

For the purpose of 9A101.a.1. ‘maximum thrust value’ is the manufacturer's demonstrated maximum thrust for the engine type un-installed. The civil type certified thrust value will be equal or less than the manufacturer's demonstrated maximum thrust for the engine type.

b.  Engines designed or modified for use in “missiles” or unmanned aerial vehicles specified in 9A012 or 9A112.a.,

M3A1

Turbojet and turbofan engines, as follows:

a.  Engines having both of the following characteristics:

1.  ‘Maximum thrust value’ greater than 400 N (achieved un-installed) excluding civil certified engines with a ‘maximum thrust value’ greater than 8,89 kN (achieved un-installed); and

2.  Specific fuel consumption of 0,15 kg N^–1 h^–1 or less (at maximum continuous power at sea level static conditions using the ICAO standard atmosphere);

Technical Note:

In 3.A.1.a.1., ‘maximum thrust value’ is the manufacturer's demonstrated maximum thrust for the engine type un-installed. The civil type certified thrust value will be equal to or less than the manufacturer's demonstrated maximum thrust for the engine type.

b.  Engines designed or modified for systems specified in 1.A. or 19.A.2., regardless of thrust or specific fuel consumption.

Note:   Engines specified in 3.A.1. may be exported as part of a manned aircraft or in quantities appropriate for replacement parts for a manned aircraft.

9A102

‘Turboprop engine systems’ specially designed for unmanned aerial vehicles specified in 9A012 or 9A112.a., and specially designed components therefor, having a ‘maximum power’ greater than 10 kW.

Note:   9A102 does not control civil certified engines.

Technical Notes:

1.  For the purposes of 9A102 a ‘turboprop engine system’ incorporates all of the following:

a.  Turboshaft engine; and

b.  Power transmission system to transfer the power to a propeller.

2.  For the purposes of 9A102 the ‘maximum power’ is achieved uninstalled at sea level static conditions using ICAO standard atmosphere.

M3A9

‘Turboprop engine systems’ specially designed for the systems in 1.A.2. or 19.A.2., and specially designed components therefor, having a maximum power greater than 10 kW (achieved uninstalled at sea level static conditions using the ICAO standard atmosphere), excluding civil certified engines.

Technical Note:

For the purposes of Item 3.A.9., a ‘turboprop engine system’ incorporates all of the following: a. Turboshaft engine; and b. Power transmission system to transfer the power to a propeller.

9A104

Sounding rockets, capable of a range of at least 300 km.

N.B.:  SEE ALSO 9A004.

M1A1

Complete rocket systems (including ballistic missile systems, space launch vehicles, and sounding rockets) capable of delivering at least a 500 kg “payload” to a “range” of at least 300 km.

M19A1

Complete rocket systems (including ballistic missile systems, space launch vehicles, and sounding rockets), not specified in 1.A.1., capable of a “range” equal to or greater than 300 km.

9A105

Liquid propellant rocket engines, as follows:

N.B.:  SEE ALSO 9A119.

a.  Liquid propellant rocket engines usable in “missiles”, other than those specified in 9A005, integrated, or designed or modified to be integrated, into a liquid propellant propulsion system which has a total impulse capacity equal to or greater than 1,1 MNs;

M2A1c2

Liquid propellant rocket engines or gel propellant rocket motors integrated, or designed or modified to be integrated, into a liquid propellant or gel propellant propulsion system which has a total impulse capacity equal to or greater than 1,1 × 10⁶ Ns;

b.  Liquid propellant rocket engines, usable in complete rocket systems or unmanned aerial vehicles, capable of a range of 300 km, other than those specified in 9A005 or 9A105.a., integrated, or designed or modified to be integrated, into a liquid propellant propulsion system which has a total impulse capacity equal to or greater than 0,841 MNs

M20A1b2

Liquid propellant rocket engines or gel propellant rocket motors integrated, or designed or modified to be integrated, into a liquid propellant or gel propellant propulsion system which has a total impulse capacity equal to or greater than 8,41 × 10⁵ Ns, but less than 1,1 × 10⁶ Ns

9A106

Systems or components, other than those specified in 9A006 as follows, specially designed for liquid rocket propulsion systems:

a.  Ablative liners for thrust or combustion chambers, usable in “missiles”, space launch vehicles specified in 9A004 or sounding rockets specified in 9A104;

b.  Rocket nozzles, usable in “missiles”, space launch vehicles specified in 9A004 or sounding rockets specified in 9A104;

M3A3

Rocket motor cases, ‘insulation’ components and nozzles therefor, usable in the systems specified in 1.A. or 19.A.1.

Technical Note:

In 3.A.3. ‘insulation’ intended to be applied to the components of a rocket motor, i.e. the case, nozzle inlets, case closures, includes cured or semi-cured compounded rubber components comprising sheet stock containing an insulating or refractory material. It may also be incorporated as stress relief boots or flaps.

Note:   Refer to 3.C.2. for ‘insulation’ material in bulk or sheet form.

c.  Thrust vector control sub-systems, usable in “missiles”;

Technical Note:

Examples of methods of achieving thrust vector control specified in 9A106.c. are:

1.  Flexible nozzle;

2.  Fluid or secondary gas injection;

3.  Movable engine or nozzle;

4.  Deflection of exhaust gas stream (jet vanes or probes); or

5.  Thrust tabs.

M2A1e

Thrust vector control subsystems, usable in the systems specified in 1.A., except as provided in the Note below 2.A.1. for those designed for rocket systems that do not exceed the “range”/“payload” capability of systems specified in 1.A.; Technical

Technical Note:

2.A.1.e. includes the following methods of achieving thrust vector control:

a.  Flexible nozzle;

b.  Fluid or secondary gas injection;

c.  Movable engine or nozzle;

d.  Deflection of exhaust gas stream (jet vanes or probes);

e.  Use of thrust tabs.

d.  Liquid, slurry and gel propellant (including oxidisers) control systems, and specially designed components therefor, usable in “missiles”, designed or modified to operate in vibration environments greater than 10 g rms between 20 Hz and 2 kHz;

Note:   The only servo valves, pumps and gas turbines specified in 9A106.d., are the following:

a.  Servo valves designed for flow rates equal to or greater than 24 litres per minute, at an absolute pressure equal to or greater than 7 MPa, that have an actuator response time of less than 100 ms;

b.  Pumps, for liquid propellants, with shaft speeds equal to or greater than 8 000 r.p.m. at a maximum operating mode or with discharge pressures equal to or greater than 7 MPa.

c.  Gas turbines, for liquid propellant turbopumps, with shaft speeds equal to or greater than 8 000 r.p.m. at the maximum operating mode.

M3A5

Liquid, slurry and gel propellant (including oxidisers) control systems, and specially designed components therefor, usable in the systems specified in 1.A., designed or modified to operate in vibration environments greater than 10 g rms between 20 Hz and 2 kHz.

Notes:

1.  The only servo valves, pumps and gas turbines specified in 3.A.5. are the following:

a.  Servo valves designed for flow rates equal to or greater than 24 litres per minute, at an absolute pressure equal to or greater than 7 MPa, that have an actuator response time of less than 100 ms.

b.  Pumps, for liquid propellants, with shaft speeds equal to or greater than 8 000 rpm at the maximum operating mode or with discharge pressures equal to or greater than 7 MPa.

c.  Gas turbines, for liquid propellant turbopumps, with shaft speeds equal to or greater than 8 000 rpm at the maximum operating mode.

2.  Systems and components specified in 3.A.5. may be exported as part of a satellite.

e.  Combustion chambers and nozzles, usable in “missiles”, space launch vehicles specified in 9A004 or sounding rockets specified in 9A104.

M3A10

Combustion chambers and nozzles for liquid propellant rocket engines usable in the subsystems specified in 2.A.1.c.2. or 20.A.1.b.2.

9A107

Solid propellant rocket engines, usable in complete rocket systems or unmanned aerial vehicles, capable of a range of 300 km, other than those specified in 9A007, having total impulse capacity equal to or greater than 0,841 MNs.

N.B.:  SEE ALSO 9A119.

M20A1b1

Solid propellant rocket motors or hybrid rocket motors having a total impulse capacity equal to or greater than 8,41 × 10⁵ Ns, but less than 1,1 × 10⁶ Ns;

9A108

Components, other than those specified in 9A008, as follows, specially designed for solid rocket propulsion systems:

a.  Rocket motor cases and “insulation” components therefor, usable in “missiles”, space launch vehicles specified in 9A004 or sounding rockets specified in 9A104;

b.  Rocket nozzles, usable in “missiles”, space launch vehicles specified in 9A004 or sounding rockets specified in 9A104;

M3A3

Rocket motor cases, ‘insulation’ components and nozzles therefor, usable in the systems specified in 1.A. or 19.A.1.

M3A3

Technical Note:

In 3.A.3. ‘insulation’ intended to be applied to the components of a rocket motor, i.e. the case, nozzle inlets, case closures, includes cured or semi-cured compounded rubber components comprising sheet stock containing an insulating or refractory material. It may also be incorporated as stress relief boots or flaps.

Note:  Refer to 3.C.2. for ‘insulation’ material in bulk or sheet form.

c.  Thrust vector control sub-systems, usable in “missiles”.

Technical Note:

Examples of methods of achieving thrust vector control specified in 9A108.c. are:

1.  Flexible nozzle;

2.  Fluid or secondary gas injection;

3.  Movable engine or nozzle;

4.  Deflection of exhaust gas stream (jet vanes or probes); or

5.  Thrust tabs.

M2A1e

Thrust vector control subsystems, usable in the systems specified in 1.A., except as provided in the Note below 2.A.1. for those designed for rocket systems that do not exceed the “range”/“payload” capability of systems specified in 1.A.;

Technical Note:

2.A.1.e. includes the following methods of achieving thrust vector control:

a.  Flexible nozzle;

b.  Fluid or secondary gas injection;

c.  Movable engine or nozzle;

d.  Deflection of exhaust gas stream (jet vanes or probes);

e.  Use of thrust tabs.

9A109

Hybrid rocket motors and specially designed components as follows:

a.  Hybrid rocket motors usable in complete rocket systems or unmanned aerial vehicles, capable of 300 km, other than those specified in 9A009, having a total impulse capacity equal to or greater than 0,841 MNs, and specially designed components therefor;

b.  Specially designed components for hybrid rocket motors specified in 9A009 that are usable in “missiles”.

N.B.:  SEE ALSO 9A009 and 9A119.

M3A6

Specially designed components for hybrid rocket motors specified in 2.A.1.c.1. and 20.A.1.b.1.

M20A1b

Rocket propulsion subsystems, not specified in 2.A.1., usable in the systems specified in 19.A.1., as follows:

1.  Solid propellant rocket motors or hybrid rocket motors having a total impulse capacity equal to or greater than 8,41 × 10⁵ Ns, but less than 1,1 × 10⁶ Ns;

2.  Liquid propellant rocket engines or gel propellant rocket motors integrated, or designed or modified to be integrated, into a liquid propellant or gel propellant propulsion system which has a total impulse capacity equal to or greater than 8,41 × 10⁵ Ns, but less than 1,1 × 10⁶ Ns;

M2A1c

Rocket propulsion subsystems, usable in the systems specified in 1.A., as follows;

1.  Solid propellant rocket motors or hybrid rocket motors having a total impulse capacity equal to or greater than 1,1 × 10⁶ Ns;

2.  Liquid propellant rocket engines or gel propellant rocket motors integrated, or designed or modified to be integrated, into a liquid propellant or gel propellant propulsion system which has a total impulse capacity equal to or greater than 1,1 × 10⁶ Ns;

Note:   Liquid propellant apogee engines or station-keeping engines specified in 2.A.1.c.2., designed or modified for use on satellites, may be treated as Category II, if the subsystem is exported subject to end-use statements and quantity limits appropriate for the excepted end-use stated above, when having a vacuum thrust not greater than 1kN.

9A110

Composite structures, laminates and manufactures thereof, other than those specified in 9A010, specially designed for use in ‘missiles’ or the subsystems specified in 9A005, 9A007, 9A105, 9A106.c., 9A107, 9A108.c., 9A116 or 9A119.

N.B.:  SEE ALSO 1A002.

Technical Note:

In 9A110 ‘missile’ means complete rocket systems and unmanned aerial vehicle systems capable of a range exceeding 300 km.

M6A1

Composite structures, laminates, and manufactures thereof, specially designed for use in the systems specified in 1.A., 19.A.1. or 19.A.2. and the subsystems specified in 2.A. or 20.A.

9A111

Pulse jet engines, usable in “missiles” or unmanned aerial vehicles specified in 9A012 or 9A112.a., and specially designed components therefor.

N.B.:  SEE ALSO 9A011 AND 9A118.

M3A2

Ramjet/scramjet/pulse jet/‘combined cycle engines’, including devices to regulate combustion, and specially designed components therefor, usable in the systems specified in 1.A. or 19.A.2.

Technical Note:

In Item 3.A.2., ‘combined cycle engines’ are the engines that employ two or more cycles of the following types of engines: gas-turbine engine (turbojet, turboprop, turbofan and turboshaft), ramjet, scramjet, pulse jet, pulse detonation engine, rocket motor (liquid/solid-propellant and hybrid)

9A112

“Unmanned aerial vehicles” (“UAVs”), other than those specified in 9A012, as follows:

a.  “Unmanned aerial vehicles” (“UAVs”) capable of a range of 300 km;

b.  “Unmanned aerial vehicles” (“UAVs”) having all of the following:

1.  Having any of the following:

a.  An autonomous flight control and navigation capability; or

b.  Capability of controlled flight out of the direct vision range involving a human operator; and

2.  Having any of the following:

a.  Incorporating an aerosol dispensing system/mechanism with a capacity greater than 20 litres; or

b.  Designed or modified to incorporate an aerosol dispensing system/mechanism with a capacity greater than 20 litres.

Technical Notes:

1.  An aerosol consists of particulate or liquids other than fuel components, by products or additives, as part of the “payload” to be dispersed in the atmosphere. Examples of aerosols include pesticides for crop dusting and dry chemicals for cloud seeding.

2.  An aerosol dispensing system/mechanism contains all those devices (mechanical, electrical, hydraulic, etc.), which are necessary for storage and dispersion of an aerosol into the atmosphere. This includes the possibility of aerosol injection into the combustion exhaust vapour and into the propeller slip stream.

M19A2

Complete unmanned aerial vehicle systems (including cruise missile systems, target drones and reconnaissance drones), not specified in 1.A.2., capable of a “range” equal to or greater than 300 km.

M19A3

Complete unmanned aerial vehicle systems, not specified in 1.A.2. or 19.A.2., having all of the following:

a.  Having any of the following:

1.  An autonomous flight control and navigation capability; or

2.  Capability of controlled flight out of the direct vision range involving a human operator; and

b.  Having any of the following:

1.  Incorporating an aerosol dispensing system/mechanism with a capacity greater than 20 litres; or

2.  Designed or modified to incorporate an aerosol dispensing system/mechanism with a capacity greater than 20 litres.

Note:   Item 19.A.3. does not control model aircraft, specially designed for recreational or competition purposes.

Technical Notes:

1.  An aerosol consists of particulate or liquids other than fuel components, by-products or additives, as part of the “payload” to be dispersed in the atmosphere. Examples of aerosols include pesticides for crop dusting and dry chemicals for cloud seeding.

9A115

Launch support equipment as follows:

a.  Apparatus and devices for handling, control, activation or launching, designed or modified for space launch vehicles specified in 9A004, sounding rockets specified in 9A104 or unmanned aerial vehicles specified in 9A012 or 9A112.a.;

M12A1

Apparatus and devices, designed or modified for the handling, control, activation and launching of the systems specified in 1.A., 19.A.1., or 19.A.2.

b.  Vehicles for transport, handling, control, activation or launching, designed or modified for space launch vehicles specified in 9A004 or sounding rockets specified in 9A104.

M12A2

Vehicles designed or modified for the transport, handling, control, activation and launching of the systems specified in 1.A.

9A116

Reentry vehicles, usable in “missiles”, and equipment designed or modified therefor, as follows:

a.  Reentry vehicles;

b.  Heat shields and components therefor, fabricated of ceramic or ablative materials;

c.  Heat sinks and components therefor, fabricated of light-weight, high heat capacity materials;

d.  Electronic equipment specially designed for reentry vehicles.

M2A1b

Re-entry vehicles, and equipment designed or modified therefor, usable in the systems specified in 1.A., as follows, except as provided in the Note below 2.A.1. for those designed for non-weapon payloads:

1.  Heat shields, and components therefor, fabricated of ceramic or ablative materials;

2.  Heat sinks and components therefor, fabricated of light-weight, high heat capacity materials;

3.  Electronic equipment specially designed for re-entry vehicles;

9A117

Staging mechanisms, separation mechanisms, and interstages, usable in “missiles”.

N.B.:  SEE ALSO 9A121.

M3A4

Staging mechanisms, separation mechanisms, and interstages therefor, usable in the systems specified in 1.A.

Note:   See also Item 11.A.5.

Technical Note:

Staging and separation mechanisms specified in 3.A.4. may contain some of the following components:

— Pyrotechnic bolts, nuts and shackles;

— Ball locks;

— Circular cutting devices;

— Flexible linear shaped charges (FLSC).

9A118

Devices to regulate combustion usable in engines, which are usable in “missiles” or unmanned aerial vehicles specified in 9A012 or 9A112.a., specified in 9A011 or 9A111.

M3A2

Ramjet/scramjet/pulse jet/‘combined cycle engines’, including devices to regulate combustion, and specially designed components therefor, usable in the systems specified in 1.A. or 19.A.2.

Technical Note:

In Item 3.A.2., ‘combined cycle engines’ are the engines that employ two or more cycles of the following types of engines: gas-turbine engine (turbojet, turboprop, turbofan and turboshaft), ramjet, scramjet, pulse jet, pulse detonation engine, rocket motor (liquid/solid-propellant and hybrid).

9A119

Individual rocket stages, usable in complete rocket systems or unmanned aerial vehicles, capable of a range of 300 km, other than those specified in 9A005, 9A007, 9A009, 9A105, 9A107 and 9A109.

M2A1a

Individual rocket stages usable in the systems specified in 1.A.;

M20A1a

Complete subsystems as follows: a. Individual rocket stages, not specified in 2.A.1., usable in systems specified in 19.A.

9A120

Liquid propellant tanks, other than those specified in 9A006, specially designed for propellants specified in 1C111 or ‘other liquid propellants’, used in rocket systems capable of delivering at least a 500 kg payload to a range of at least 300 km.

M3A8

Liquid propellant tanks specially designed for the propellants controlled in Item 4.C. or other liquid propellants used in the systems specified in 1.A.1.

9A121

Umbilical and interstage electrical connectors specially designed for “missiles”, space launch vehicles specified in 9A004 or sounding rockets specified in 9A104.

Technical Note:

Interstage connectors referred to in 9A121 also include electrical connectors installed between the “missile”, space launch vehicle or sounding rocket and their payload.

M11A5

Umbilical and interstage electrical connectors specially designed for systems specified in 1.A.1. or 19.A.1.

Technical Note:

Interstage connectors referred to in 11.A.5. also include electrical connectors installed between systems specified in 1.A.1. or 19.A.1. and their “payload”.

The corresponding systems, equipment and components as identified in Council Regulation (EC) No 428/2009 of 5 May 2009 setting up a Community regime for the control of exports, transfer, brokering and transit of dual-use items

Missile Technology Control Regime (M.TCR): Equipment, software and technology annex

9B005

On-line (real time) control systems, instrumentation (including sensors) or automated data acquisition and processing equipment, specially designed for use with any of the following:

N.B.:  SEE ALSO 9B105.

a.  Wind tunnels designed for speeds of Mach 1,2 or more;

Note:   9B005.a. does not control wind tunnels specially designed for educational purposes and having a ‘test section size’ (measured laterally) of less than 250 mm.

Technical Note:

‘Test section size’ means the diameter of the circle, or the side of the square, or the longest side of the rectangle, at the largest test section location.

b.  Devices for simulating flow-environments at speeds exceeding Mach 5, including hot-shot tunnels, plasma arc tunnels, shock tubes, shock tunnels, gas tunnels and light gas guns; or

c.  Wind tunnels or devices, other than two-dimensional sections, capable of simulating Reynolds number flows exceeding 25 × 10⁶.

M15B2

‘Aerodynamic test facilities’ for speeds of Mach 0,9 or more, usable for the systems specified in 1.A. or 19.A. or the subsystems specified in 2.A. or 20.A.

Note:  Item 15.B.2 does not control wind tunnels for speeds of Mach 3 or less with dimension of the ‘test cross section size’ equal to or less than 250 mm.

Technical Notes:

1.  ‘Aerodynamic test facilities’ includes wind tunnels and shock tunnels for the study of airflow over objects.

2.  ‘Test cross section size’ means the diameter of the circle, or the side of the square, or the longest side of the rectangle, or the major axis of the ellipse at the largest ‘test cross section’ location. ‘Test cross section’ is the section perpendicular to the flow direction.

9B006

Acoustic vibration test equipment capable of producing sound pressure levels of 160 dB or more (referenced to 20 μPa) with a rated output of 4 kW or more at a test cell temperature exceeding 1 273 K (1 000  °C), and specially designed quartz heaters therefor.

N.B.:  SEE ALSO 9B106.

M15B4b

Environmental chambers capable of simulating all of the following flight conditions:

1.  Acoustic environments at an overall sound pressure level of 140 dB or greater (referenced to 2 × 10^–5 N/m² ) or with a total rated acoustic power output of 4 kW or greater; and

2.  Any of the following: a. Altitude equal to or greater than 15 km; or b. Temperature range from below –50 °C to above 125 °C.

9B105

‘Aerodynamic test facilities’ for speeds of Mach 0,9 or more, usable for ‘missiles’ and their subsystems.

N.B.:  SEE ALSO 9B005.

Note:   9B105 does not control wind-tunnels for speeds of Mach 3 or less with dimension of the ‘test cross section size’ equal to or less than 250 mm.

Technical Notes:

1.  In 9B105 ‘aerodynamic test facilities’ includes wind tunnels and shock tunnels for the study of airflow over objects.

2.  In Note to 9B105, ‘test cross section size’ means the diameter of the circle, or the side of the square, or the longest side of the rectangle, or the major axis of the ellipse at the largest ‘test cross section’ location. ‘Test cross section’ is the section perpendicular to the flow direction.

3.  In 9B105 ‘missile’ means complete rocket systems and unmanned aerial vehicle systems capable of a range exceeding 300 km.

M15B2

‘Aerodynamic test facilities’ for speeds of Mach 0,9 or more, usable for the systems specified in 1.A. or 19.A. or the subsystems specified in 2.A. or 20.A.

Note:   Item 15.B.2 does not control wind tunnels for speeds of Mach 3 or less with dimension of the ‘test cross section size’ equal to or less than 250 mm.

Technical Notes:

1.  ‘Aerodynamic test facilities’ includes wind tunnels and shock tunnels for the study of airflow over objects.

2.  ‘Test cross section size’ means the diameter of the circle, or the side of the square, or the longest side of the rectangle, or the major axis of the ellipse at the largest ‘test cross section’ location. ‘Test cross section’ is the section perpendicular to the flow direction.

9B106

Environmental chambers and anechoic chambers, as follows:

a.  Environmental chambers capable of simulating all the following flight conditions:

1.  Having any of the following:

a.  Altitude equal to or greater than 15 km; or

b.  Temperature range from below 223 K (–50 ° C) to above 398 K (+125 °C); and

2.  Incorporating, or ‘designed or modified’ to incorporate, a shaker unit or other vibration test equipment to produce vibration environments equal to or greater than 10 g rms, measured ‘bare table’, between 20 Hz and 2 kHz while imparting forces equal to or greater than 5 kN;

Technical Notes:

1.  9B106.a.2. describes systems that are capable of generating a vibration environment with a single wave (e.g., a sine wave) and systems capable of generating a broad band random vibration (i.e., power spectrum).

2.  In 9B106.a.2., ‘designed or modified’ means the environmental chamber provides appropriate interfaces (e.g., sealing devices) to incorporate a shaker unit or other vibration test equipment as specified in 2B116.

3.  In 9B106.a.2. ‘bare table’ means a flat table, or surface, with no fixture or fittings.

b.  Environmental chambers capable of simulating the following flight conditions:

1.  Acoustic environments at an overall sound pressure level of 140 dB or greater (referenced to 20 μPa) or with a total rated acoustic power output of 4 kW or greater; and

2.  Altitude equal to or greater than 15 km; or

3.  Temperature range from below 223 K (–50 °C) to above 398 K (+125 °C).

M15B4

Environmental chambers as follows, usable for the systems specified in 1.A. or 19.A. or the subsystems specified in 2.A. or 20.A.:

a.  Environmental chambers having all of the following characteristics:

1.  Capable of simulating any of the following flight conditions:

a.  Altitude equal to or greater than 15 km; or

b.  Temperature range from below –50 °C to above 125 °C; and

2.  Incorporating, or designed or modified to incorporate, a shaker unit or other vibration test equipment to produce vibration environments equal to or greater than 10 g rms, measured ‘bare table’, between 20 Hz and 2 kHz while imparting forces equal to or greater than 5 kN;

Technical Notes:

1.  Item 15.B.4.a.2. describes systems that are capable of generating a vibration environment with a single wave (e.g. a sine wave) and systems capable of generating a broad band random vibration (i.e. power spectrum).

2.  In Item 15.B.4.a.2., designed or modified means the environmental chamber provides appropriate interfaces (e.g. sealing devices) to incorporate a shaker unit or other vibration test equipment as specified in this Item.

b.  Environmental chambers capable of simulating all of the following flight conditions:

1.  Acoustic environments at an overall sound pressure level of 140 dB or greater (referenced to 2 × 10^–5 N/m²) or with a total rated acoustic power output of 4 kW or greater; and

2.  Any of the following:

a.  Altitude equal to or greater than 15 km; or

b.  Temperature range from below –50 °C to above 125 °C

9B115

Specially designed “production equipment” for the systems, sub-systems and components specified in 9A005 to 9A009, 9A011, 9A101, 9A102, 9A105 to 9A109, 9A111, 9A116 to 9A120.

M2B2

“Production equipment” specially designed for the subsystems specified in 2.A.

M3B2

“Production equipment” specially designed for equipment or materials specified in 3.A.1., 3.A.2., 3.A.3., 3.A.4., 3.A.5., 3.A.6., 3.A.8., 3.A.9., 3.A.10. or 3.C.

M20B2

“Production equipment” specially designed for the subsystems specified in 20.A.

9B116

Specially designed “production facilities” for the space launch vehicles specified in 9A004, or systems, sub-systems, and components specified in 9A005 to 9A009, 9A011, 9A101, 9A102, 9A104 to 9A109, 9A111, 9A116 to 9A120 or ‘missiles’.

Technical Note:

In 9B116 ‘missile’ means complete rocket systems and unmanned aerial vehicle systems capable of a range exceeding 300 km.

M1B1

“Production facilities” specially designed for the systems specified in 1.A

M2B1

“Production facilities” specially designed for the subsystems specified in 2.A.

M3B1

“Production facilities” specially designed for equipment or materials specified in 3.A.1., 3.A.2., 3.A.3., 3.A.4., 3.A.5., 3.A.6., 3.A.8., 3.A.9., 3.A.10. or 3.C.

M19B1

“Production facilities” specially designed for the systems specified in 19.A.1 or 19.A.2.

M20B1

“Production facilities” specially designed for the subsystems specified in 20.A.

9B117

Test benches and test stands for solid or liquid propellant rockets or rocket motors, having either of the following characteristics:

a.  The capacity to handle more than 68 kN of thrust; or

b.  Capable of simultaneously measuring the three axial thrust components.

M15B3

Test benches/stands, usable for the systems specified in 1.A., 19.A.1. or 19.A.2. or the subsystems specified in 2.A. or 20.A., which have the capacity to handle solid or liquid propellant rockets, motors or engines having a thrust greater than 68 kN, or which are capable of simultaneously measuring the three axial thrust components.

The corresponding systems, equipment and components as identified in Council Regulation (EC) No 428/2009 of 5 May 2009 setting up a Community regime for the control of exports, transfer, brokering and transit of dual-use items

Missile Technology Control Regime (M.TCR): Equipment, software and technology annex

9C108

“Insulation” material in bulk form and “interior lining”, other than those specified in 9A008, for rocket motor cases usable in “missiles” or specially designed for ‘missiles’.

Technical Note:

In 9C108 ‘missile’ means complete rocket systems and unmanned aerial vehicle systems capable of a range exceeding 300 km.

M3C1

‘Interior lining’ usable for rocket motor cases in the subsystems specified in 2.A.1.c.1. or specially designed for subsystems specified in 20.A.1.b.1.

Technical Note:

In 3.C.1. ‘interior lining’ suited for the bond interface between the solid propellant and the case or insulating liner is usually a liquid polymer based dispersion of refractory or insulating materials e.g. carbon filled HTPB or other polymer with added curing agents to be sprayed or screeded over a case interior.

M3C2

‘Insulation’ material in bulk form usable for rocket motor cases in the subsystems specified in 2.A.1.c.1. or specially designed for subsystems specified in 20.A.1.b.1.

Technical Note:

In 3.C.2. ‘insulation’ intended to be applied to the components of a rocket motor, i.e. the case, nozzle inlets, case closures, includes cured or semi-cured compounded rubber sheet stock containing an insulating or refractory material. It may also be incorporated as stress relief boots or flaps specified in 3.A.3.

9C110

Resin impregnated fibre prepregs and metal coated fibre preforms therefor, for composite structures, laminates and manufactures specified in 9A110, made either with organic matrix or metal matrix utilising fibrous or filamentary reinforcements having a “specific tensile strength” greater than 7,62 × 10⁴ m and a “specific modulus” greater than 3,18 × 10⁶ m.

N.B.:  SEE ALSO 1C010 AND 1C210.

Note:   The only resin impregnated fibre prepregs specified in entry 9C110 are those using resins with a glass transition temperature (T_g), after cure, exceeding 418 K (145 °C) as determined by ASTM D4065 or equivalent.

M6C1

Resin impregnated fibre prepregs and metal coated fibre preforms, for the goods specified in 6.A.1., made either with organic matrix or metal matrix utilising fibrous or filamentary reinforcements having a specific tensile strength greater than 7,62 × 10⁴ m and a specific modulus greater than 3,18 × 10⁶ m.

Note:   The only resin impregnated fibre prepregs specified in 6.C.1. are those using resins with a glass transition temperature (Tg), after cure, exceeding 145 °C as determined by ASTM D4065 or national equivalents.

Technical Notes:

1.  In Item 6.C.1. ‘specific tensile strength’ is the ultimate tensile strength in N/m² divided by the specific weight in N/m³, measured at a temperature of (296 ± 2)K ((23 ± 2)°C) and a relative humidity of (50 ± 5)%.

2.  In Item 6.C.1. ‘specific modulus’ is the Young's modulus in N/m² divided by the specific weight in N/m³, measured at a temperature of (296 ± 2)K ((23 ± 2)°C) and a relative humidity of (50 ± 5)%

The corresponding systems, equipment and components as identified in Council Regulation (EC) No 428/2009 of 5 May 2009 setting up a Community regime for the control of exports, transfer, brokering and transit of dual-use items

Missile Technology Control Regime (M.TCR): Equipment, software and technology annex

9D001

“Software” specially designed or modified for the “development” of equipment or “technology”, specified in 9A001 to 9A119, 9B or 9E003.

M3D3

“Software” specially designed or modified for the “development” of equipment specified in 3.A.2., 3.A.3. or 3.A.4.

9D002

“Software” specially designed or modified for the “production” of equipment specified in 9A001 to 9A119 or 9B.

M2D2

“Software” specially designed or modified for the “use” of rocket motors or engines specified in 2.A.1.c.

9D004

Other “software” as follows:

a.  2D or 3D viscous “software”, validated with wind tunnel or flight test data required for detailed engine flow modelling;

b.  “Software” for testing aero gas turbine engines, assemblies or components, specially designed to collect, reduce and analyse data in real time and capable of feedback control, including the dynamic adjustment of test articles or test conditions, as the test is in progress;

c.  “Software” specially designed to control directional solidification or single-crystal material growth in equipment specified in 9B001.a. or 9B001.c.;

d.  Not used;

e.  “Software” specially designed or modified for the operation of items specified in 9A012;

f.  “Software” specially designed to design the internal cooling passages of aero gas turbine blades, vans and “tip shrouds”;

g.  “Software” having all of the following:

1.  Specially designed to predict aero thermal, aeromechanical and combustion conditions in aero gas turbine engines; and

2.  Theoretical modelling predictions of the aero thermal, aeromechanical and combustion conditions, which have been validated with actual aero gas turbine engine (experimental or production) performance data.

M19D1

“Software” which coordinates the function of more than one subsystem, specially designed or modified for “use” in the systems specified in 19.A.1. or 19.A.2.

9D101

“Software” specially designed or modified for the “use” of goods specified in 9B105, 9B106, 9B116 or 9B117.

M1D1

“Software” specially designed or modified for the “use” of “production facilities” specified in 1.B.

M2D1

“Software” specially designed or modified for the “use” of “production facilities” specified in 2.B.1.

M3D1

“Software” specially designed or modified for the “use” of “production facilities” and flow-forming machines specified in 3.B.1. or 3.B.3.

M12D1

“Software” specially designed or modified for the “use” of equipment specified in 12.A.1.

M15D1

“Software” specially designed or modified for the “use” of equipment specified in 15.B. usable for testing systems specified in 1.A., 19.A.1. or 19.A.2. or subsystems specified in 2.A. or 20.A.

M20D1

“Software” specially designed or modified for the systems specified in 20.B.1.

9D103

“Software” specially designed for modelling, simulation or design integration of the space launch vehicles specified in 9A004, sounding rockets specified in 9A104 or “missiles”, or the subsystemsspecified in 9A005, 9A007, 9A105, 9A106.c., 9A107, 9A108.c., 9A116 or 9A119.

Note:   “Software” specified in 9D103 remains controlled when combined with specially designed hardware specified in 4A102.

M16D1

“Software” specially designed for modelling, simulation, or design integration of the systems specified in 1.A. or the subsystems specified in 2.A or 20.A.

Technical Note:

The modelling includes in particular the aerodynamic and thermodynamic analysis of the systems.

9D104

“Software” specially designed or modified for the “use” of goods specified in 9A001, 9A005, 9A006.d., 9A006.g., 9A007.a., 9A008.d., 9A009.a., 9A010.d., 9A011, 9A101, 9A102, 9A105, 9A106.c., 9A106.d., 9A107, 9A108.c., 9A109, 9A111, 9A115.a., 9A116.d., 9A117 or 9A118.

M2D2

M2D4

M3D2

M2D5

M20D2

“Software” specially designed or modified for the “use” of rocket motors or engines specified in 2.A.1.c.

“Software” specially designed or modified for the operation or maintenance of subsystems or equipment specified in 2.A.1.b.3.

“Software” specially designed or modified for the “use” of equipment specified in 3.A.1., 3.A.2., 3.A.4., 3.A.5., 3.A.6. or 3.A.9.

Notes:

1.  “Software” specially designed or modified for the “use” of engines specified in 3.A.1. may be exported as part of a manned aircraft or as replacement “software” therefor.

2.  “Software” specially designed or modified for the “use” of propellant control systems specified in 3.A.5. may be exported as part of a satellite or as replacement “software” therefor.

“Software” specially designed or modified for the operation or maintenance of subsystems in 2.A.1.e.

“Software”, not specified in 2.D.2., specially designed or modified for the “use” of rocket motors or engines specified in 20.A.1.b.

9D105

“Software” which coordinates the function of more than one subsystem, other than that specified in 9D003.e., specially designed or modified for “use” in space launch vehicles specified in 9A004 or sounding rockets specified in 9A104 or ‘missiles’.

Technical Note:

In 9D105 ‘missile’ means complete rocket systems and unmanned aerial vehicle systems capable of a range exceeding 300 km.

M1D2

“Software” specially designed or modified to coordinate the function of more than one subsystem in systems specified in 1.A.

M19D1

“Software” which coordinates the function of more than one subsystem, specially designed or modified for “use” in the systems specified in 19.A.1. or 19.A.2.

The corresponding systems, equipment and components as identified in Council Regulation (EC) No 428/2009 of 5 May 2009 setting up a Community regime for the control of exports, transfer, brokering and transit of dual-use items

Missile Technology Control Regime (M.TCR): Equipment, software and technology annex

9E001

“Technology” according to the General Technology Note for the “development” of equipment

M

Means specific information which is required for the “development”, “production” or “use” of a product. The information may take the form of “technical data” or “technical assistance”.

9E002

“Technology” according to the General Technology Note for the “production” of equipment materials, see 1E002.f.

M

Means specific information which is required for the “development”, “production” or “use” of a product. The information may take the form of “technical data” or “technical assistance”.

9E101

a.  “Technology” according to the General Technology Note for the “development” of goods specified in 9A101, 9A102, 9A104 to 9A111, 9A112.a. or 9A115 to 9A121.

b.  “Technology” according to the General Technology Note for the “production” of ‘UAV’s specified in 9A012 or goods specified in 9A101, 9A102, 9A104 to 9A111, 9A112.a. or 9A115 to 9A121.

Technical Note:

In 9E101.b. ‘UAV’ means unmanned aerial vehicle systems capable of a range exceeding 300 km.

M

Means specific information which is required for the “development”, “production” or “use” of a product. The information may take the form of “technical data” or “technical assistance”.

9E102

“Technology” according to the General Technology Note for the “use” of space launch vehicles specified in9A004, goods specified in 9A005 to 9A011, ‘UAV’s specified in 9A012 or goods specified in 9A101, 9A102, 9A104 to 9A111, 9A112.a., 9A115 to 9A121, 9B105, 9B106, 9B115, 9B116, 9B117, 9D101 or 9D103.

Technical Note:

In 9E102 ‘UAV’ means unmanned aerial vehicle systems capable of a range exceeding 300 km.

M

Means specific information which is required for the “development”, “production” or “use” of a product. The information may take the form of “technical data” or “technical assistance”.