LegalizeCouncil Regulation (EU) No 267/2012 of 23 March 2012 concerning restrictive measures against Iran and repealing Regulation (EU) No 961/2010
| 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 | ||
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| 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”. |
9B Test, Inspection and Production Equipment
| 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. |
9C Materials
| 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 (Tg), 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)% |
9D Software
| 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. |
9E Technology
| 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”. |
ANNEX IV
| HS Code | Description |
|---|---|
| 2709 00 | Petroleum oils and oils obtained from bituminous minerals, crude. |
| 2710 | Petroleum oils and oils obtained from bituminous minerals, other than crude; preparations not elsewhere specified or included, containing by weight 70 % or more of petroleum oils or of oils obtained from bituminous minerals, these oils being the basic constituents of the preparations; waste oils (save that the purchase, in Iran, of kerosene jet fuel of CN code 2710 19 21 is not prohibited provided that it is intended and used solely for the purpose of the continuation of the flight operation of the aircraft into which it is loaded). |
| 2712 | Petroleum jelly; paraffin wax, microcrystalline petroleum wax, slack wax, ozokerite, lignite wax, peat wax, other mineral waxes, and similar products obtained by synthesis or by other processes, whether or not coloured. |
| 2713 | Petroleum coke, petroleum bitumen and other residues of petroleum oils or of oils obtained from bituminous minerals. |
| 2714 | Bitumen and asphalt, natural; bituminous or oil-shale and tar sands; asphaltites and asphaltic rocks. |
| 2715 00 00 | Bituminous mixtures based on natural asphalt, on natural bitumen, on petroleum bitumen, on mineral tar or on mineral tar pitch (for example, bituminous mastics, cut-backs). |
ANNEX IVa
| HS code | Description |
|---|---|
| 2709 00 10 | Natural gas condensates |
| 2711 11 00 | Natural Gas – in liquefied state |
| 2711 21 00 | Natural Gas – in gaseous state |
| 2711 12 | Propane |
| 2711 13 | Butanes |
| 2711 19 00 | Other |
ANNEX V
| HS code | Description |
|---|---|
| 2812 10 94 | Phosgene (carbonyl chloride) |
| 2814 | Ammonia |
| 3102 30 | Ammonium Nitrate |
| 2901 21 00 | Ethylene |
| 2901 22 00 | Propene (propylene) |
| 2902 20 00 | Benzene |
| 2902 30 00 | Toluene |
| 2902 41 00 | o-Xylene |
| 2902 42 00 | m-Xylene |
| 2902 43 00 | p-Xylene |
| 2902 44 00 | Mixed xylene isomers |
| 2902 50 00 | Styrene |
| 2902 60 00 | Ethyl benzene |
| 2902 70 00 | Cumene |
| 2903 11 00 | Chloromethane |
| 2903 29 00 | Unsaturated chlorinated derivatives of acyclic hydrocarbons – other |
| 2903 81 00 | Hexachlorocyclohexane [(HCH (ISO)], including lindane (ISO, DCI) |
| 2903 82 00 | Aldrin (ISO), chlordane (ISO) and heptachlor (ISO) |
| 2903 89 90 | Other halogenated derivatives of hydrocarbons |
| 2903 91 00 | Chlorobenzene, o-dichlorobenzene and p-dichlorobenzene |
| 2903 92 00 | Hexachlorobenzene (ISO) and DDT (ISO) [clofenotane (DCI), 1,1,1-trichloro-2,2-bis(p-chlorophenyl)ethane] |
| 2903 99 90 | Other halogenated derivatives of aromatic hydrocarbons |
| 2909 | Ether-alcohols and their halogenated, sulphonated, nitrated or nitrosated derivatives |
| 2909 41 | Oxydiethanol (diethylene glycol) |
| 2909 43 | Monobutyl ethers of ethylene-glycol or diethylene glycol |
| 2909 44 | Other monoalkyl ethers of ethylene-glycol or diethylene glycol |
| 2909 49 | Other ether-alcohols and their halogenated, sulphonated, nitrated or nitrosated derivatives |
| 2905 11 00 | Methanol (methyl alcohol) |
| 2905 12 00 | Propan-1-ol (propyl alcohol) and propan-2-ol (isopropyl alcohol |
| 2905 13 00 | Butan-1-ol (n-butyl alcohol) |
| 2905 31 00 | Ethylene glycol (ethanediol) |
| 2907 11 – 2907 19 | Phenols |
| 2910 10 00 | Oxirane (ethylene oxide) |
| 2910 20 00 | Methyloxirane (propylene oxide) |
| 2914 11 00 | Acetone |
| 2917 14 00 | Maleic anhydride (MA) |
| 2917 35 00 | Phthalic anhydride (PA) |
| 2917 36 00 | Terephthalic acid and its salts |
| 2917 37 00 | Dimethyl terephthalate (DMT) |
| 2926 10 00 | Acrylonitrile |
| Ex 2929 10 00 | Methylene diphenyl diisocyanate (MDI) |
| Ex 2929 10 00 | Hexamethylene diisocyanate (HDI) |
| Ex 2929 10 00 | Toluene diisocyanate (TDI) |
| 3901 | Polymers of ethylene, in primary forms |
| HS code | Description |
| --- | --- |
| 2707 10 | Benzol (benzene) |
| 2707 20 | Toluol (toluene) |
| 2707 30 | Xylol (xylenes) |
| 2707 40 | Naphthalene |
| 2707 99 80 | Phenols |
| 2711 14 00 | Ethylene, propylene, butadiene |
ANNEX VI
GENERAL NOTES
1.The object of the prohibitions contained in this Annex should not be defeated by the export of any non-prohibited goods (including plant) containing one or more prohibited components when the prohibited component or components are the principal element of the goods and can feasibly be removed or used for other purposes.
N.B.:
In judging whether the prohibited component or components are to be considered the principal element, it is necessary to weigh the factors of quantity, value and technological know-how involved and other special circumstances which might establish the prohibited component or components as the principal element of the goods being procured.
2.The goods specified in this Annex include both new and used goods.
3.Definitions of terms between ‘single quotation marks’ are given in a technical note to the relevant item.
4.Definitions of terms between ‘double quotation marks’ can be found in Annex I to Regulation (EC) No 428/2009.
GENERAL TECHNOLOGY NOTE (GTN)
1.The ‘technology’‘required’ for the ‘development’, ‘production’ or ‘use’ of prohibited goods remains under prohibition even when applicable to non-prohibited goods.
2.Prohibitions do not apply to that ‘technology’ which is the minimum necessary for the installation, operation, maintenance (checking) and repair of those goods which are not prohibited or the export of which has been authorised in accordance with Regulation (EC) No 423/2007, Regulation (EU) No 961/2010 or this Regulation.
3.Prohibitions on ‘technology’ transfer do not apply to information ‘in the public domain’, to ‘basic scientific research’ or to the minimum necessary information for patent applications.
EXPLORATION AND PRODUCTION OF CRUDE OIL AND NATURAL GAS
1.A Equipment
1.Geophysical survey equipment, vehicles, vessels and aircraft specially designed or adapted to acquire data for oil and gas exploration and specially designed components therefore.
2.Sensors specially designed for downhole well operations in oil and gas wells, including sensors used for measurement whilst drilling and the associated equipment specially designed to acquire and store data from such sensors.
3.Drilling equipment designed to drill rock formations, specifically for the purpose of exploring for, or producing oil, gas and other naturally occurring, hydrocarbon materials.
4.Drill bits, drill pipes, drill collars, centralisers and other equipment, specially designed for use in and with oil and gas well drilling equipment.
5.Drilling wellheads, ‘blowout preventers’ and ‘Christmas or production trees’ and the specially designed components thereof, meeting the ‘API and ISO specifications’ for use with oil and gas wells.
Technical Notes:
a. A ‘blowout preventer’ is a device typically used at ground level (or if drilling underwater, at the seabed) during drilling to prevent the uncontrolled escape of oil and/or gas from the well.
b. A ‘Christmas tree or production tree’ is a device typically used to control flow of fluids from the well when it is complete and oil and/or gas production has started.
c. For the purpose of this item, ‘API and ISO specifications’ refers to the American Petroleum Institute specifications 6A, 16A, 17D and 11IW and/or the International Standards Organisation specifications 10423 and 13533 for blowout preventers, wellhead and Christmas trees for use on oil and/or gas wells.
6.Drilling and production platforms for crude oil and natural gas.
7.Vessels and barges incorporating drilling and/or petroleum processing equipment used for producing oil, gas and other naturally occurring flammable materials.
8.Liquid/gas separators meeting API specification 12J, specially designed to process the production from an oil or gas well, to separate the petroleum liquids from any water and any gas from the liquids.
9.Gas compressor with a design pressure of 40 bar (PN 40 and/or ANSI 300) or more and having a suction volume capacity of 300 000 Nm3/h or more, for the initial processing and transmission of natural gas, excluded gas compressors for CNG (Compressed Natural Gas) filling stations, and specially designed components therefore.
10.Subsea production control equipment and the components thereof meeting ‘API and ISO specifications’ for use with oil and gas wells.
Technical Note:
For the purposes of this entry, ‘API and ISO specifications’ refers to the American Petroleum Institute specification 17 F and/or the International Standards Organisation specification 13268 for subsea production control systems.
11.Pumps, typically high capacity and/or high pressure (in excess of 0,3 m3 per minute and/or 40 bar), specially designed to pump drilling muds and/or cement into oil and gas wells.
1.B Test and inspection equipment
1.Equipment specially designed for sampling, testing and analysing the properties of drilling mud, oil well cements and other materials specially designed and/or formulated for use in oil and gas wells.
2.Equipment specially designed for sampling, testing and analysing the properties of rock samples, liquid and gaseous samples and other materials taken from an oil and/or gas well either during or after drilling, or from the initial processing facilities attached thereto.
3.Equipment specially designed for collecting and interpreting information about the physical and mechanical condition of an oil and/or gas well, and for determining the in situ properties of the rock and reservoir formation.
1.C Materials
1.Drilling mud, drilling mud additives and the components thereof, specially formulated to stabilise oil and gas wells during drilling, to recover drill cuttings to the surface and to lubricate and cool the drilling equipment in the well.
2.Cements and other materials meeting the ‘API and ISO specifications’ for use in oil and gas wells.
Technical Note:
‘API and ISO specification’ refers to the American Petroleum Institute specification 10A or the International Standards Organisation specification 10426 for oil well cements and other materials specially formulated for use in the cementing of oil and gas wells.
3.Corrosion inhibiting, emulsion treatment, defoaming agents and other chemicals specially formulated to be used in the drilling for, and the initial processing of, petroleum produced from an oil and/or gas well.
1.D Software
1.‘Software’ specially designed to collect and interpret data acquired from seismic, electromagnetic, magnetic or gravity surveys for the purpose of establishing oil or gas prospectivity.
2.‘Software’ specially designed for storing, analysing and interpreting information acquired during drilling and production to assess the physical characteristics and behaviour of oil or gas reservoirs.
3.‘Software’ specially designed for the ‘use’ of petroleum production and processing facilities or specific sub-units of such facilities.
1.E Technology
1.‘Technology’‘required’ for the ‘development’, ‘production’ and ‘use’ of equipment specified in 1.A.01 – 1.A.11.
REFINING OF CRUDE OIL AND LIQUEFACTION OF NATURAL GAS
2.A Equipment
1.Heat exchangers as follows and specially designed components therefore:
a. Plate-fin heat exchangers with a surface/volume ratio greater than 500 m2/m3, specially designed for pre-cooling of natural gas;
b. Coil-wound heat exchangers specially designed for liquefaction or sub-cooling of natural gas.
2.Cryogenic pumps for the transport of media at a temperature below – 120 oC having a transport capacity of more than 500 m3/h and specially designed components therefore.
3.‘Coldbox’ and ‘coldbox’ equipment not specified by 2.A.1.
Technical Note:
‘Coldbox’ equipment refers to a specially designed construction, which is specific for LNG plants and incorporates the process stage of liquefaction. The ‘coldbox’ comprises heat exchangers, piping, other instrumentation and thermal insulators. The temperature inside the ‘coldbox’ is below – 120 oC (conditions for condensation of natural gas). The function of the ‘coldbox’ is the thermal insulation of the above described equipment.
4.Equipment for shipping terminals of liquefied gases having a temperature below – 120 oC and specially designed components therefore.
5.Flexible and non-flexible transfer line having a diameter greater than 50 mm for the transport of media below – 120 oC.
6.Maritime vessels specially designed for the transport of LNG.
7.Electrostatic desalters specially designed to remove contaminants such as salts, solids and water from crude oil and specially designed components therefore.
8.All crackers, including hydrocrackers, and cokers, specially designed for conversion of vacuum gas oils or vacuum residuum, and specially designed components therefore.
9.Hydrotreaters specially designed for desulphurisation of gasoline, diesel cuts and kerosene and specially designed components therefore.
10.Catalytic reformers specially designed for conversion of desulphurised gasoline into high-octane gasoline, and specially designed components therefore.
11.Refinery units for C5-C6 cuts isomerisation, and refinery units for alkylation of light olefins, to improve the octane index of the hydrocarbon cuts.
12.Pumps specially designed for the transport of crude oil and fuels, having a capacity of 50 m3/h or more and specially designed components therefore.
13.Tubes with an outer diameter of 0,2 m or more and made from any of the following materials:
a. Stainless steels with 23 % chromium or more by weight;
b. Stainless steels and nickel bases alloys with a ‘Pitting resistance equivalent’ number higher than 33.
Technical Note:
‘Pitting resistance equivalent’ (PRE) number characterises the corrosion resistance of stainless steels and nickel alloys to pitting or crevice corrosion. The pitting resistance of stainless steels and nickel alloys is primarily determined by their compositions, primarily: chromium, molybdenum, and nitrogen. The formula to calculate the PRE number is:
14.‘Pigs’ (Pipeline Inspection Gauge(s)) and specially designed components therefore.
15.‘Pig’ launchers and ‘pig’ catchers for the integration or removing of ‘pigs’
Technical Note:
‘Pig’ is a device typically used for cleaning or inspection of a pipeline from inside (corrosion state or crack formation) and is propelled by the pressure of the product in the pipeline.
16.Tanks for the storage of crude oil and fuels with a volume greater than 1 000 m3 (1 000 000 litres) as follows, and specially designed components therefore:
a. fixed roof tanks;
b. floating roof tanks.
17.Subsea flexible pipes specially designed for the transportation of hydrocarbons and injection fluids, water or gas, having a diameter greater than 50 mm.
18.Flexible pipes used for high pressure for topside and subsea application.
19.Isomeration equipment specially designed for production of high-octane gasoline based on light hydrocarbons as feed, and specially designed components therefore.
2.B Test and inspection equipment
1.Equipment specially designed for testing and analysing of quality (properties) of crude oil and fuels.
2.Interface control systems specially designed for controlling and optimising of the desalting process.
2.C Materials
1.Diethyleneglycol (CAS 111-46-6), Triethylene glycol (CAS 112-27-6)
2.N-Methylpyrrolidon (CAS 872-50-4), Sulfolane (CAS 126-33-0)
3.Zeolites, of natural or synthetic origin, specially designed for fluid catalytic cracking or for the purification and/or dehydration of gases, including natural gases.
4.Catalysts for the cracking and conversion of hydrocarbons as follows:
a. Single metal (platinum group) on alumina type or on zeolite, specially designed for catalytic reforming process;
b. Mixed metal species (platinum in combination with other noble metals) on alumina type or on zeolite, specially designed for catalytic reforming process;
c. Cobalt and nickel catalysts doped with molybdenum on alumina type or on zeolite, specially designed for catalytic desulphurisation process;
d. Palladium, nickel, chromium and tungsten catalysts on alumina type or on zeolite, specially designed for catalytic hydrocracking process.
5.Gasoline additives specially formulated for increasing the octane number of gasoline.
Note:
This entry includes Ethyl tertiary butyl ether(ETBE) (CAS 637-92-3) and Methyl tertiary butyl ether (MTBE) CAS 1634-04-4).
2.D Software
1.‘Software’ specially designed for the ‘use’ of LNG plants or specific sub-units of such plants.
2.‘Software’ specially designed for the ‘development’, ‘production’ or ‘use’ of plants (including their sub-units) for oil refining.
2.E Technology
1.‘Technology’‘required’ for the ‘development’, ‘production’ or ‘use’ of equipment for the conditioning and purification of raw natural gas (dehydration, sweetening, removal of impurities).
2.‘Technology’ for the liquefaction of natural gas, including ‘technology’ required for the ‘development’, ‘production’ or ‘use’ of LNG plants.
3.‘Technology’‘required’ for the ‘development’, ‘production’ or ‘use’ of equipment for the shipment of liquefied natural gas.
4.‘Technology’‘required’ for the ‘development’, ‘production’ or ‘use’ of maritime vessels specially designed for the transport of liquefied natural gas.
5.‘Technology’‘required’ for the ‘development’, ‘production’ or ‘use’ of tanks for the storage of crude oil and fuels.
6.‘Technology’‘required’ for the ‘development’, ‘production’ or ‘use’ of a refinery plant, such as:
6.1. ‘Technology’ for conversion of light olefin to gasoline;
6.2. Catalytic reforming and isomerisation technology;
6.3. Catalytic and thermal cracking technology.
PETROCHEMICAL INDUSTRY
3.A Equipment
a. specially designed for production of phosgene (CAS 506-77-4) and specially designed components therefor;
b. for phosgenation specially designed for the production of HDI, TDI, MDI and specially designed components therefor, with the exception of secondary reactors;
c. specially designed for low pressure (up to max 40 bar) polymerisation of ethylene and propylene and specially designed components therefore;
d. specially designed for the thermal cracking of EDC (ethylene dichloride) and specially designed components therefor, with the exception of secondary reactors;
e. specially designed for chlorination and oxychlorination in the production of vinyl chloride and specially designed components therefor, with the exception of secondary reactors;
2.Thin film evaporators and falling film evaporators consisting of materials resistant to hot concentrated acetic acid and specially designed components therefor, and the relevant software developed therefor;
3.Plants for the separation of hydrochloric acid by electrolysis and specially designed components therefore, and the relevant software developed therefor;
4.Columns having a diameter larger than 5 000 mm and specially designed components therefor;
5.Ball valves and plug valves with ceramic balls or plugs, having a nominal diameter of 10 mm or more, and specially designed components therefor;
6.Centrifugal and/or reciprocating compressor having an installed power above 2 MW and meeting specification API 617 or API 618;
3.B Test and inspection equipment
3.C Materials
1.Catalysts applicable to processes of production of trinitrotoluene, ammonium nitrate and other chemical and petrochemical processes used for explosive manufacturing, and the relevant software developed therefor;
2.Catalysts used for the production of monomers such as ethylene and propylene (steam cracking units and/or Gas to petrochemicals units), and the relevant software developed therefor;
3.D Software
1.‘Software’ specially designed for the ‘development’, ‘production’ or ‘use’ of equipment specified in 3.A;
2.‘Software’ specially designed for the ‘use’ in methanol plants;
3.E Technology
1.‘Technology’ for the ‘development’, ‘production’ or ‘use’ of Gas-To-Liquid (GTL) or Gas-To-Petrochemicals (GTP) processes or for GTL- or GTP- plants;
2.‘Technology’‘required’ for the ‘development’, ‘production’ or ‘use’ of equipment designed for the manufacture of ammonia and methanol plants;
3.‘Technology’ for the ‘production’ of MEG (Mono ethylene glycol), EO (Ethylene oxide)/EG (Ethylene glycol)
Note:
‘Technology’ means specific information necessary for the ‘development’, ‘production’ or ‘use’ of goods. This information takes the form of ‘technical data’ or ‘technical assistance’.
ANNEX VIa
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