LegalizeCommission Implementing Regulation (EU) 2019/1083 of 21 June 2019 amending Council Regulation (EU) 2017/1509 concerning restrictive measures against the Democratic People's Republic of Korea
This is the act as published. Later amendments are not folded into the text below: each one is a separate act in this repository and an entry in this law's history.
| No | Description | Related item from Annex I to Regulation (EC) No 428/2009 |
|---|---|---|
| IX.A7.001 | “Star trackers” and components therefor, as follows: (a) “Star trackers” with a specified azimuth “accuracy” of equal to or less (better) than 20 seconds of arc throughout the specified lifetime of the equipment; (b) Components specially designed for equipment specified in item (a), as follows: 1. Optical heads or baffles; 2. Data processing units. Technical note: “Star trackers” are also referred to as stellar attitude sensors or gyro-astro compasses. | 7A004 |
| IX.A7.002 | Global Navigation Satellite Systems (GNSS) receiving equipment having any of the following and specially designed components therefor: (a) Employing a decryption algorithm specially designed or modified for government use to access the ranging code for position and time; or (b) Employing “adaptive antenna systems”. Note: Item (b) does not apply to GNSS receiving equipment that only uses components designed to filter, switch or combine signals from multiple omni-directional antennae that do not implement adaptive antenna techniques. Technical note: For the purposes of item (b), “adaptive antenna systems” dynamically generate one or more spatial nulls in an antenna array pattern by signal processing in the time domain or frequency domain. | 7A005 |
| IX.A7.003 | Airborne altimeters operating at frequencies other than 4,2 to 4,4 GHz inclusive and having any of the following: (a) “Power management”; or (b) Using phase shift key modulation. | 7A006 |
| IX.A7.004 | Test, calibration or alignment equipment, specially designed for equipment specified in the section above. | 7B001 |
| IX.A7.005 | Equipment specially designed to characterize mirrors for ring “laser” gyros, as follows: (a) Scatterometers having a measurement “accuracy” of 10 ppm or less (better); (b) Profilometers having a measurement “accuracy” of 0,5 nm (5 angstrom) or less (better). | 7B002 |
| IX.A7.006 | Equipment specially designed for the “production” of equipment specified IN IX.A7. Note: Including: — Gyro tuning test stations; — Gyro dynamic balance stations; — Gyro run-in/motor test stations; — Gyro evacuation and fill stations; — Centrifuge fixtures for gyro bearings; — Accelerometer axis align stations; — Fibre-optic gyro coil winding machines. | 7B003 |
IX.A8. MARINE
| No | Description | Related item from Annex I to Regulation (EC) No 428/2009 |
|---|---|---|
| IX.A8.001 | Systems, equipment and components, specially designed or modified for submersible vehicles and designed to operate at depths exceeding 1 000 m, as follows: 1. Pressure housings or pressure hulls with a maximum inside chamber diameter exceeding 1,5 m; 2. Direct current propulsion motors or thrusters; 3. Umbilical cables, and connectors therefor, using optical fibre and having synthetic strength members; 4. Components manufactured from material as follows: “Syntactic foam” designed for underwater use and having all of the following: a. Designed for marine depths exceeding 1 000 m; and b. A density less than 561 kg/m3; | 8A002.a. |
| IX.A8.002 | Systems specially designed or modified for the automated control of the motion of submersible vehicles specified above, using navigation data, having closed loop servo-controls and having any of the following: 1. Enabling a vehicle to move within 10 m of a predetermined point in the water column; 2. Maintaining the position of the vehicle within 10 m of a predetermined point in the water column; or 3. Maintaining the position of the vehicle within 10 m while following a cable on or under the seabed; | 8A002.b. |
| IX.A8.003 | Fibre-optic pressure hull penetrators; | 8A002.c. |
| IX.A8.004 | “Robots” specially designed for underwater use, controlled by using a dedicated computer and having any of the following: (a) Systems that control the “robot” using information from sensors which measure force or torque applied to an external object, distance to an external object, or tactile sense between the “robot” and an external object; or (b) The ability to exert a force of 250 N or more or a torque of 250 Nm or more and using titanium-based alloys or “composite”“fibrous or filamentary materials” in their structural members; | 8A002.h. |
| IX.A8.005 | Stirling cycle engine air independent power systems having all of the following: (a) Devices or enclosures, specially designed for underwater noise reduction in frequencies below 10 kHz, or special mounting devices for shock mitigation; and (b) Specially designed exhaust systems which discharge the products of combustion against a pressure of 100 kPa or more; | 8A002.j. |
| IX.A8.006 | Noise reduction systems designed for use on vessels of 1 000 tonnes displacement or more, as follows: (a) Systems that attenuate underwater noise at frequencies below 500 Hz and consist of compound acoustic mounts for the acoustic isolation of diesel engines, diesel generator sets, gas turbines, gas turbine generator sets, propulsion motors or propulsion reduction gears, specially designed for sound or vibration isolation and having an intermediate mass exceeding 30 % of the equipment to be mounted; (b) “Active noise reduction or cancellation systems” or magnetic bearings, specially designed for power transmission systems. Technical note: “Active noise reduction or cancellation systems” incorporate electronic control systems capable of actively reducing equipment vibration by the generation of anti-noise or anti-vibration signals directly to the source. | 8A002.j. |
IX.A9. AEROSPACE AND PROPULSION
| No | Description | Related item from Annex I to Regulation (EC) No 428/2009 |
|---|---|---|
| IX.A9.001 | Aero gas turbine engines: (a) Incorporating any of the “technologies” specified in paragraph 2 of the section below entitled “Technology”; or Note 1: This item does not apply to aero gas turbine engines which meet all of the following: (a) Certified by civil aviation authorities; and (b) Intended to power non-military manned “aircraft” for which any of the following has been issued by civil aviation authorities for the “aircraft” with this specific engine type: 1. A civil type certificate; or 2. An equivalent document recognized by ICAO. Note 2: This item does not apply to aero gas turbine engines designed for Auxiliary Power Units (APUs) approved by the civil aviation authority of the Member State. (b) Designed to power an “aircraft” designed to cruise at Mach 1 or higher, for more than 30 minutes. | 9A001 |
| IX.A9.002 | “Marine gas turbine engines” with an ISO standard continuous power rating of 24 245 kW or more and a specific fuel consumption not exceeding 0,219 kg/kWh in the power range from 35 to 100 %, and specially designed assemblies and components therefor. Note: The term “marine gas turbine engines” includes those industrial, or aero-derivative, gas turbine engines adapted for a ship's electric power generation or propulsion. | 9A002 |
| IX.A9.003 | Specially designed assemblies or components, incorporating any of the “technologies” specified in paragraph 2 of the section below entitled “Technology”, for any of the following aero gas turbine engines: (a) Specified in item 1 above; or (b) Whose design or production origins are unknown to the manufacturer. | 9A003 |
| IX.A9.004 | Space launch vehicles, “spacecraft”, “spacecraft buses”, “spacecraft payloads”, “spacecraft” on-board systems or equipment, and terrestrial equipment, as follows: (a) Space launch vehicles; (b) “Spacecraft”; (c) “Spacecraft buses”; (d) “Spacecraft payloads” incorporating items specified in this list; (e) On-board systems or equipment, specially designed for “spacecraft” and having any of the following functions: 1. “Command and telemetry data handling”; (f) Terrestrial equipment specially designed for “spacecraft”, as follows: 1. Telemetry and telecommand equipment; 2. Simulators. | 9A004 |
| IX.A9.005 | Liquid rocket propulsion systems. | 9A005 |
| IX.A9.006 | Systems and components, specially designed for liquid rocket propulsion systems, as follows: (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; (e) High-pressure (exceeding 10,6 MPa) thrust chambers and nozzles therefor; (f) Propellant storage systems using the principle of capillary containment or positive expulsion (i.e., with flexible bladders); (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; (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 | 9A006 |
| IX.A9.007 | Solid rocket propulsion systems. | 9A007 |
| IX.A9.008 | Components specially designed for solid rocket propulsion systems, as follows: (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; (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). (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. | 9A008 |
| IX.A9.009 | Hybrid rocket propulsion systems. | 9A009 |
| IX.A9.010 | Specially designed components, systems and structures, for launch vehicles, launch vehicle propulsion systems or “spacecraft”, as follows: (a) Components and structures, specially designed for launch vehicle propulsion systems manufactured using any of the following: 1. “Fibrous or filamentary materials”; 2. Metal “matrix”“composite” materials; or 3. Ceramic “matrix”“composite” materials. | 9A010 |
| IX.A9.011 | “Unmanned Aerial Vehicles” (“UAVs”), unmanned “airships”, related equipment and components, as follows: (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 the item above, “operator” is a person who initiates or commands the “UAV” or unmanned “airship” flight. 2. For the purposes of the item above, “endurance” is to be calculated for International Standard Atmosphere (ISA) conditions (ISO 2533:1975) at sea level in zero wind. 3. For the purposes of the item above, “natural vision” means unaided human sight, with or without corrective lenses. (b) Related equipment and components, as follows: 1. Equipment or components, specially designed to convert a manned “aircraft” or a manned “airship” to a “UAV” or unmanned “airship”, specified in item (a) above; 2. 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). | 9A012 |
| IX.A9.012 | On-line (real-time) control systems, instrumentation (including sensors) or automated data acquisition and processing equipment specially designed for the “development” of gas turbine engines, assemblies or components and incorporating any of the “technologies” specified in paragraph 2 (b) or 2 (c) of the section below entitled “Technology”. | 9B002 |
| IX.A9.013 | Equipment specially designed for the “production” or test of gas turbine brush seals designed to operate at tip speeds exceeding 335 m/s and temperatures in excess of 773 K (500 °C), and specially designed components or accessories therefor. | 9B003 |
| IX.A9.014 | Tools, dies or fixtures, for the solid-state joining of “superalloy”, titanium or intermetallic airfoil-to-disk combinations described in paragraph 2 of the section below entitled “Technology” for gas turbines. | 9B004 |
| IX.A9.015 | On-line (real-time) control systems, instrumentation (including sensors) or automated data acquisition and processing equipment, specially designed for use in wind tunnels designed for speeds of Mach 1,2 or more. | 9B005 |
| IX.A9.016 | Acoustic vibration test equipment capable of producing sound pressure levels of 160 dB or more (referenced to 20 Pa) 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. | 9B006 |
| IX.A9.017 | Equipment specially designed for inspecting the integrity of rocket motors and using Non-Destructive Test (NDT) techniques other than planar X-ray or basic physical or chemical analysis. | 9B007 |
| IX.A9.018 | Direct measurement wall skin friction transducers specially designed to operate at a test flow total (stagnation) temperature exceeding 833 K (560 °C). | 9B008 |
| IX.A9.019 | Tooling specially designed for producing gas turbine engine powder metallurgy rotor components having all of the following: (a) Designed to operate at stress levels of 60 % of ultimate tensile strength (UTS) or more measured at a temperature of 873 K (600 °C); and (b) Designed to operate at 873 K (600 °C) or more. Note: The item above does not specify tooling for the production of powder. | 9B008 |
| IX.A9.020 | Equipment specially designed for the production of items specified by “Unmanned Aerial Vehicles” (“UAVs”), unmanned “airships” and components. | 9B010 |
B. SOFTWARE
| No | Description | Related item from Annex I to Regulation (EC) No 428/2009 |
|---|---|---|
| IX.B.001 | “Software” specially designed or modified for the “development”, “production” or “use” of equipment specified in IX.A1. | 1D001 1D002 1D003 |
| IX.B.002 | “Software” for the “development” of material specified in IX.A1. | 1D001 1D002 1D003 |
| IX.B.003 | “Software” specially designed or modified to enable non-listed equipment to perform the functions of any equipment specified in IX.A1. | 1D001 1D002 1D003 |
| IX.B.004 | “Software” specially designed or modified for the “development”, “production” or “use” of equipment specified in IX.A2 | 2D001 |
| IX.B.005 | “Software” specially designed or modified to allow non-listed equipment to function as equipment specified IX.A2 | 2D003 2D101 2D202 |
| IX.B.006 | “Software” specially designed for the “development”, “production” or “use” of equipment specified in IX.A3. | 3D001 3D002 3D003 |
| IX.B.007 | “Software” specially designed or modified to allow non-listed equipment to function as equipment specified in IX.A3 | 3D001 3D002 3D003 |
| IX.B.008 | “Software” specially designed for the “development”, “production” or “use” of equipment specified in IX.A6. | 6D001 6D003 6D002 6D102 6D203 6D203 |
| IX.B.009 | “Software” specially designed or modified to allow non-listed equipment to function as equipment specified in IX.A6. | 6D001 6D003 6D002 6D102 6D203 6D203 |
| IX.B.010 | “Software” specially designed or modified for the “development”, “production” or “use” of equipment specified in IX.A7. | 7D001 7D002 7D003 7D004 7D005 7D102 7D103 7D104 |
| IX.B.011 | “Software” specially designed or modified to allow non-listed equipment to function as equipment specified IX.A7. | 7D001 7D002 7D003 7D004 7D005 7D102 7D103 7D104 |
| IX.B.012 | “Source code” for the operation or maintenance of equipment specified IX.A7. | 7D001 7D002 7D003 7D004 7D005 7D102 7D103 7D104 |
| IX.B.013 | Computer-Aided Design (CAD) “software” specially designed for the “development” of “active flight control systems”, helicopter multi-axis fly-by-wire or fly-by-light controllers or helicopter “circulation controlled anti-torque or circulation-controlled direction control systems”. | 7D001 7D002 7D003 7D004 7D005 7D102 7D103 7D104 |
| IX.B.014 | “Software” specially designed or9modified for the “development”, “production” or “use” of equipment. Specified in IX.A9. | 9D001 9D002 9D003 9D004 9D005 9D101 9D103 9D104 9D105 |
| IX.B.015 | “Software” specially designed or modified to allow non-listed equipment to function as equipment specified in IX.A9. | 9D001 9D002 9D003 9D004 9D005 9D101 9D103 9D104 9D105 |
C. TECHNOLOGY
| No | Description | Related item from Annex I to Regulation (EC) No 428/2009 |
|---|---|---|
| IX.C.001 | “Technology” for the “development”, “production” or “use” of equipment or “software” specified in IX.A1. | 2E001 |
| IX.C.002 | “Technology” for the “development”, “production” or “use” of equipment or materials specified in IX.A3 | 3E001 3E003 3E101 3E102 3E201 |
| IX.C.003 | “Technology” for the “development”, “production” and “use” of equipment or “software”, specified in IX.A7. | 7E001 7E002 7E003 7E004 7D005 7E101 7E102 7E104 |
| IX.C.004 | “Technology” for the “development”, “production” or “use” of equipment or software, specified in IX.A9. | 9E001 9E002 |
| IX.C.005 | Other “technology”, as follows: (a) “Technology”“required” for the “development” or “production” of any of the following gas turbine engine components or systems: 1. Gas turbine blades, vanes or “tip shrouds”, made from directionally solidified (DS) or single crystal (SC) alloys and having (in the 001 Miller Index Direction) a stress-rupture life exceeding 400 hours at 1 273 K (1 000 °C) at a stress of 200 MPa, based on the average property values; 2. Combustors having any of the following: a. “Thermally decoupled liners” designed to operate at “combustor exit temperature” exceeding 1 883 K (1 610 °C); b. Non-metallic liners; c. Non-metallic shells; or d. Liners designed to operate at “combustor exit temperature” exceeding 1 883 K (1 610 °C) and having holes that meet the parameters specified by 9E003.c.; 3. Components that are any of the following: a. Manufactured from organic “composite” materials designed to operate above 588 K (315 °C); b. Manufactured from any of the following: 1. Metal “matrix”“composites”; or 2. Ceramic “matrix”“composites”; or c. Stators, vanes, blades, tip seals (shrouds), rotating blings, rotating blisks, or “splitter ducts”, that are all of the following: 1. Not specified above; 2. Designed for compressors or fans; and 3. Manufactured from material “fibrous or filamentary materials” with resins; 4. Uncooled turbine blades, vanes or “tip-shrouds”, designed to operate at a “gas path temperature” of 1 373 K (1 100 °C) or more; 5. Cooled turbine blades, vanes, “tip-shrouds”, designed to operate at a “gas path temperature” of 1 693 K (1 420 °C) or more; 6. Airfoil-to-disk blade combinations using solid-state joining; 7. Gas turbine engine components using “diffusion bonding”“technology”; 8. “Damage tolerant” gas turbine engine rotor components using powder metallurgy materials; 9. Hollow fan blades. | 9E003.a. |
| IX.C.006 | “Technology” for gas turbine engine “Full Authority Digital Engine Control (FADEC) systems”, as follows: 1. “Development”“technology” for deriving the functional requirements for the components necessary for the “FADEC system” to regulate engine thrust or shaft power (e.g., feedback sensor time constants and accuracies, fuel valve slew rate); 2. “Development” or “production”“technology” for control and diagnostic components unique to the “FADEC system” and used to regulate engine thrust or shaft power; 3. “Development”“technology” for the control law algorithms, including “source code”, unique to the “FADEC system” and used to regulate engine thrust or shaft power; Note: Item (b) above does not apply to technical data related to engine-“aircraft“ integration required by civil aviation authorities of one or more Member States to be published for general airline use (e.g., installation manuals, operating instructions, instructions for continued airworthiness) or interface functions (e.g., input/output processing, airframe thrust or shaft power demand). | 9E003.h. |
| IX.C.007 | “Technology” for adjustable flow path systems designed to maintain engine stability for gas generator turbines, fan or power turbines, or propelling nozzles, as follows: 1. “Development”“technology” for deriving the functional requirements for the components that maintain engine stability; 2. “Development” or “production”“technology” for components unique to the adjustable flow path system and that maintain engine stability; 3. “Development”“technology” for the control law algorithms, including “source code”, unique to the adjustable flow path system and that maintain engine stability | 9E003.i |
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