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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;
Authority: EUProhibited Supply To: IRProgram: IREU Code: M3A3Code: 9A108Components, 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;
Authority: EUProhibited Supply To: IRProgram: IREU Code: M3A3Code: 9A108Solid 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.
Authority: EUProhibited Supply To: IRProgram: IREU Code: M20A1b1Code: 9A107Solid 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.
Authority: EUProhibited Supply To: IRProgram: IREU Code: M20A1b1Code: 9A107e. Combustion chambers and nozzles, usable in “missiles”, space launch vehicles specified in 9A004 or sounding rockets specified in 9A104.
Authority: EUProhibited Supply To: IRProgram: IREU Code: M3A10Code: 9A106e. Combustion chambers and nozzles, usable in “missiles”, space launch vehicles specified in 9A004 or sounding rockets specified in 9A104.
Authority: EUProhibited Supply To: IRProgram: IREU Code: M3A10Code: 9A106d. 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.
Authority: EUProhibited Supply To: IRProgram: IREU Code: M3A5Code: 9A106d. 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.
Authority: EUProhibited Supply To: IRProgram: IREU Code: M3A5Code: 9A106c. 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.
Authority: EUProhibited Supply To: IRProgram: IREU Code: M2A1eCode: 9A106c. 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.
Authority: EUProhibited Supply To: IRProgram: IREU Code: M2A1eCode: 9A106Systems 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;
Authority: EUProhibited Supply To: IRProgram: IREU Code: M3A3Code: 9A106Systems 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;
Authority: EUProhibited Supply To: IRProgram: IREU Code: M3A3Code: 9A106b. 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
Authority: EUProhibited Supply To: IRProgram: IREU Code: M20A1b2Code: 9A105b. 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
Authority: EUProhibited Supply To: IRProgram: IREU Code: M20A1b2Code: 9A105a. 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;
Authority: EUProhibited Supply To: IRProgram: IREU Code: M2A1c2Code: 9A105a. 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;
Authority: EUProhibited Supply To: IRProgram: IREU Code: M2A1c2Code: 9A105Sounding rockets, capable of a range of at least 300 km. N.B.: SEE ALSO 9A004.
Authority: EUProhibited Supply To: IRProgram: IREU Code: M19A1Code: 9A104Sounding rockets, capable of a range of at least 300 km. N.B.: SEE ALSO 9A004.
Authority: EUProhibited Supply To: IRProgram: IREU Code: M19A1Code: 9A104Sounding rockets, capable of a range of at least 300 km. N.B.: SEE ALSO 9A004.
Authority: EUProhibited Supply To: IRProgram: IREU Code: M1A1Code: 9A104Sounding rockets, capable of a range of at least 300 km. N.B.: SEE ALSO 9A004.
Authority: EUProhibited Supply To: IRProgram: IREU Code: M1A1Code: 9A104‘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.
Authority: EUProhibited Supply To: IRProgram: IREU Code: M3A9Code: 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.
Authority: EUProhibited Supply To: IRProgram: IREU Code: M3A9Code: 9A102Turbojet 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.,
Authority: EUProhibited Supply To: IRProgram: IREU Code: M3A1Code: 9A101Turbojet 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.,
Authority: EUProhibited Supply To: IRProgram: IREU Code: M3A1Code: 9A1013. 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).
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M9A6Code: 9A0123. 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).
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M9A6Code: 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
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M19ACode: 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
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M19ACode: 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
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M1A2Code: 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
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M1A2Code: 9A012Ramjet, scramjet or combined cycle engines, and specially designed components therefor. N.B.: SEE ALSO 9A111 AND 9A118.
Authority: EUProhibited Supply To: IRProgram: IREU Code: M3A2Code: 9A011Ramjet, scramjet or combined cycle engines, and specially designed components therefor. N.B.: SEE ALSO 9A111 AND 9A118.
Authority: EUProhibited Supply To: IRProgram: IREU Code: M3A2Code: 9A011d. 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.
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M3A2Code: 9A010d. 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.
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M3A2Code: 9A010c. Structural components and isolation systems, specially designed to control actively the dynamic response or distortion of “spacecraft” structures;
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M6A1Code: 9A010c. Structural components and isolation systems, specially designed to control actively the dynamic response or distortion of “spacecraft” structures;
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M6A1Code: 9A010b. 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;
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M6A1Code: 9A010b. 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;
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M6A1Code: 9A010Specially 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.
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M6A1Code: 9A010Specially 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.
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M6A1Code: 9A010