Regulation (EU) 2021/821 of the European Parliament and of the Council of 20 May 2021 setting up a Union regime for the control of exports, brokering, technical assistance, transit and transfer of dual-use items (recast)

f. Not used;

g. Not used;

h. Not used;

i. Not used.

8A002Marine systems, equipment and components, as follows:

Note:

For underwater communications systems, see Category 5, Part 1 - Telecommunications.

a. Systems, equipment and components, specially designed or modified for submersible vehicles and designed to operate at depths exceeding 1 000  m, as follows:

Technical Note: For the purposes of 8A002.a.2., brushless direct current motors may be referred to as Permanent Magnet Alternating Current (PMAC) motors.

b. Systems specially designed or modified for the 'automated control' of the motion of submersible vehicles specified in 8A001, using navigation data, having closed loop servo-controls and having any of the following:

Technical Note: For the purposes of 8A002.b., 'automated control' systems apply to systems onboard submersible vehicles.

c. Fibre optic pressure hull penetrators;

d. Underwater vision systems having all of the following:

a. Range-gated illuminators; or b. Range-gated "laser" systems;

e. Not used;

f. Not used;

g. Light systems specially designed or modified for underwater use, as follows:

h. "Robots" specially designed for underwater use, controlled by using a dedicated computer and having any of the following:

i. Remotely controlled articulated manipulators specially designed or modified for use with submersible vehicles and having any of the following:

a. Torque or force applied to an external object; or b. Tactile sense between the manipulator and an external object; or

Technical Note: For the purposes of 8A002.i.2., only functions having proportionally related motion control using positional feedback are counted when determining the number of degrees of 'freedom of movement'.

j. Air independent power systems specially designed for underwater use, as follows:

a. Chemical scrubber or absorber systems, specially designed to remove carbon dioxide, carbon monoxide and particulates from recirculated engine exhaust; b. Systems specially designed to use a monoatomic gas; c. Devices or enclosures, specially designed for underwater noise reduction in frequencies below 10 kHz, or special mounting devices for shock mitigation; or d. Systems having all of the following:

a. Chemical scrubber or absorber systems, specially designed to remove carbon dioxide, carbon monoxide and particulates from recirculated engine exhaust; b. Systems specially designed to use a monoatomic gas; c. Devices or enclosures, specially designed for underwater noise reduction in frequencies below 10 kHz, or special mounting devices for shock mitigation; and d. Specially designed exhaust systems that do not exhaust continuously the products of combustion;

a. Devices or enclosures, specially designed for underwater noise reduction in frequencies below 10 kHz, or special mounting devices for shock mitigation; or b. 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;

k. Not used;

l. Not used;

m. Not used;

n. Not used;

o. Propellers, power transmission systems, power generation systems and noise reduction systems and related equipment, as follows:

a. Controllable-pitch propellers and hub assemblies, rated at more than 30 MW; b. Internally liquid-cooled electric propulsion motors with a power output exceeding 2,5 MW; c. "Superconductive" propulsion motors, with a power output exceeding 0,1 MW; d. Power transmission systems incorporating "composite" shafts and designed to transmit power exceeding 10 MW; e. Ventilated or base-ventilated propeller systems, rated at more than 2,5 MW;

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: For the purposes of 8A002.o.3.b., '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.

Note:

8A002.o.4. includes rim-driven propulsion systems.

p. Pumpjet propulsion systems having all of the following:

q. Underwater swimming and diving equipment as follows:

Note:

8A002.q. does not control individual rebreathers for personal use when accompanying their users. N.B.

For equipment and devices specially designed for military use, SEE THE MILITARY GOODS CONTROLS.

r. Diver deterrent acoustic systems specially designed or modified to disrupt divers and having a sound pressure level equal to or exceeding 190 dB (reference 1 μPa at 1 m) at frequencies of 200 Hz and below. Note 1:

8A002.r. does not control diver deterrent systems based on underwater explosive devices, air guns or combustible sources. Note 2:

8A002.r. includes diver deterrent acoustic systems that use spark gap sources, also known as plasma sound sources.

8B001Water tunnels designed to have a background noise of less than 100 dB (reference 1 μPa, 1 Hz) within the frequency range exceeding 0 Hz but not exceeding 500 Hz and designed for measuring acoustic fields generated by a hydro-flow around propulsion system models.

8C001'Syntactic foam' designed for underwater use and having all of the following:

N.B.

See also 8A002.a.4.

a. Designed for marine depths exceeding 1 000  m; and

b. A density less than 561 kg/m³.

For the purposes of 8C001, 'syntactic foam' consists of hollow spheres of plastic or glass embedded in a resin "matrix".

8D001"Software" specially designed or modified for the "development", "production" or "use" of equipment or materials, specified in 8A, 8B or 8C.

8D002Specific "software" specially designed or modified for the "development", "production", repair, overhaul or refurbishing (re-machining) of propellers specially designed for underwater noise reduction.

8E001"Technology" according to the General Technology Note for the "development" or "production" of equipment or materials, specified in 8A, 8B or 8C.

8E002Other "technology" as follows:

a. "Technology" for the "development", "production", repair, overhaul or refurbishing (re-machining) of propellers specially designed for underwater noise reduction;

b. "Technology" for the overhaul or refurbishing of equipment specified in 8A001, 8A002.b., 8A002.j., 8A002.o. or 8A002.p.;

c. "Technology" according to the General Technology Note for the "development" or "production" of any of the following:

a. Maximum design speed, fully loaded, exceeding 30 knots in a significant wave height of 1,25 m or more; b. Cushion pressure exceeding 3 830  Pa; and c. Light-ship-to-full-load displacement ratio of less than 0,70;

a. Full load displacement exceeding 500 tonnes with a maximum design speed, fully loaded, exceeding 35 knots in a significant wave height of 3,25 m or more; or b. Full load displacement exceeding 1 500 tonnes with a maximum design speed, fully loaded, exceeding 25 knots in a significant wave height of 4 m or more. Technical Note: For the purposes of 8E002.c.4., a 'small waterplane area vessel' is defined by the following formula: waterplane area at an operational design draft less than 2 × (displaced volume at the operational design draft)^2/3.

PART XI

Category 9

CATEGORY 9 – AEROSPACE AND PROPULSION

N.B.

For propulsion systems designed or rated against neutron or transient ionising radiation, SEE THE MILITARY GOODS CONTROLS.

9A001Aero 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. Note 1:

9A001 does not control aero gas turbine engines which meet all of the following: a. Certified by the civil aviation authorities of one or more EU Member States or Wassenaar Arrangement 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 EU Member States or Wassenaar Arrangement Participating States for the "aircraft" with this specific engine type: 1. A civil type certificate; or 2. An equivalent document recognised by the International Civil Aviation Organization (ICAO). Note 2:

9A001 does not control aero gas turbine engines designed for Auxiliary Power Units (APUs) approved by the civil aviation authority in a EU Member States or Wassenaar Arrangement Participating States.

b. Not used.

9A002'Marine gas turbine engines' designed to use liquid fuel and having all of the following, and specially designed assemblies and components therefor:

a. Maximum continuous power when operating in "steady state mode" at standard reference conditions specified by ISO 3977-2:1997 (or national equivalent) of 24 245  kW or more; and

b. 'Corrected specific fuel consumption' not exceeding 0,219 kg/kWh at 35 % of the maximum continuous power when using liquid fuel.

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.

For the purposes of 9A002, 'corrected specific fuel consumption' is the specific fuel consumption of the engine corrected to a marine distillate liquid fuel having a net specific energy (i.e. net heating value) of 42MJ/kg (ISO 3977-2:1997).

9A003Specially designed assemblies or components, incorporating any of the "technologies" specified in 9E003.a., 9E003.h. 9E003.i., or 9E003.k, for any of the following aero gas turbine engines:

a. Specified in 9A001; or

b. Whose design or production origins are either non-EU Member States or Wassenaar Arrangement Participating States or unknown to the manufacturer.

9A004Space launch vehicles, "spacecraft", "spacecraft buses", "spacecraft mission equipment", "spacecraft" on-board systems or equipment, terrestrial equipment, air-launch platforms and "sub-orbital craft" as follows:

N.B.

SEE ALSO 9A104.

a. Space launch vehicles;

b. "Spacecraft"; N.B.

For "sub-orbital craft", see 9A004.h.

c. "Spacecraft buses";

d. "Spacecraft mission equipment" incorporating items specified in 3A001.b.1.a.4., 3A002.g., 5A001.a.1., 5A001.b.3., 5A002.c., 5A002.e., 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:

Note:

9A004.e.1. includes bus data management, storage, and processing.

Note:

9A004.e.2. includes management, storage, and processing of "spacecraft mission equipment" data.

Note:

9A004.e.3 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:

a. Telemetry data processing of frame synchronisation and error corrections, for monitoring of operational status (also known as health and safe status) of the "spacecraft bus"; or b. Command data processing for formatting command data being sent to the "spacecraft" to control the "spacecraft bus";

Technical Note: For the purposes of 9A004.f.2., 'verification of operational procedures' is any of the following:

or

g. "Aircraft" specially designed or modified to be air-launch platforms for space launch vehicles or "sub-orbital craft";

h. "Sub-orbital craft".

9A005Liquid rocket propulsion systems containing any of the systems or components, specified in 9A006.

N.B.

SEE ALSO 9A105 AND 9A119.

9A006Systems 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, designed to restrict cryogenic fluid losses to less than 30 % per year;

b. Cryogenic containers or closed-cycle refrigeration systems, designed to maintain or produce temperatures less than or equal to 100 K (-173,15 °C);

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.

9A007Solid 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.

9A008Components 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;

b. Filament-wound "composite" motor cases exceeding 0,61 m in diameter or having 'structural efficiency ratios (PV/W)' exceeding 25 km; Technical Note: For the purposes of 9A008.b., '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:

9A009Hybrid 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.

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:

a. Materials specified in 1C007; b. "Fibrous or filamentary materials" specified in 1C010; or c. Aluminides specified in 1C002.a.; or

Note:

The weight cut-off is not relevant for nose cones.

b. Components and structures, specially designed for launch vehicle propulsion systems specified in 9A005 to 9A009 manufactured using 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

c. Structural components and isolation systems, specially designed to control actively the dynamic response or distortion of "spacecraft" structures;

d. Pulsed liquid rocket engines with thrust-to-weight ratios equal to or more than 1 kN/kg and a 'response time' of less than 30 ms. Technical Note: For the purposes of 9A010.d., 'response time' is the time required to achieve 90 % of total rated thrust from start-up.

9A011Ramjet, scramjet or 'combined cycle engines', and specially designed components therefor.

N.B.

SEE ALSO 9A111 AND 9A118.

For the purposes of 9A011, 'combined cycle engines' combine two or more of the following types of engines:

— Gas turbine engine (turbojet, turboprop and turbofan);

— Ramjet or scramjet;

— Rocket motor or engine (liquid/gel/solid-propellant and hybrid).

9A012"Unmanned aerial vehicles" ("UAVs"), unmanned "airships", related equipment and components, as follows:

N.B.1.

SEE ALSO 9A112.

N.B.2.

For "UAVs" that are "sub-orbital craft", see 9A004.h.

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:

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

Technical Notes: For the purposes of 9A012.a.: 1. 'Operator' is a person who initiates or commands the "UAV" or unmanned "airship" flight. 2. 'Endurance' is to be calculated for ISA conditions (ISO 2533:1975) at sea level in zero wind. 3. 'Natural vision'means unaided human sight, with or without corrective lenses.

b. Related equipment and components, as follows:

9A101Turbojet and turbofan engines, other than those specified in 9A001, as follows;

a. Engines having all of the following characteristics:

Technical Notes: 1.

For the purpose of 9A101.a.1., 'maximum thrust value' is the manufacturer’s demonstrated maximum thrust for the engine type un-installed at sea level static conditions using the ICAO standard atmosphere. The civil type certified thrust value will be equal to or less than the manufacturer’s demonstrated maximum thrust for the engine type un-installed. 2.

Specific fuel consumption is determined at maximum continuous thrust for engine type un-installed at sea level static conditions using the ICAO standard atmosphere. 3.

'Dry weight' is the weight of the engine without fluids (fuel, hydraulic fluid, oil, etc.) and does not include the nacelle (housing). 4.

'First-stage rotor diameter' is the diameter of the first rotating stage of the engine, whether a fan or compressor, measured at the leading edge of the blade tips.

b. Engines designed or modified for use in "missiles" or unmanned aerial vehicles specified in 9A012 or 9A112.a.

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.

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 un-installed at sea level static conditions using ICAO standard atmosphere.

9A104Sounding rockets, capable of a range of at least 300 km.

N.B.

SEE ALSO 9A004.

9A105Liquid propellant rocket engines or gel propellant rocket motors, as follows:

N.B.

SEE ALSO 9A119.

a. Liquid propellant rocket engines or gel propellant rocket motors, usable in "missiles", other than those specified in 9A005, 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 MNs;

b. Liquid propellant rocket engines or gel propellant rocket motors, 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 or gel propellant propulsion system which has a total impulse capacity equal to or greater than 0,841 MNs.

9A106Systems or components, other than those specified in 9A006 as follows, specially designed for liquid rocket propulsion or gel propellant rocket systems:

a. Not used;

b. Not used;

c. Thrust vector control sub-systems, usable in "missiles"; Technical Note: Examples of methods of achieving thrust vector control specified in 9A106.c. are:

or

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.

e. Combustion chambers and nozzles for liquid propellant rocket engines or gel propellant rocket motors specified in 9A005 or 9A105.

9A107Solid propellant rocket motors, 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.

9A108Components, other than those specified in 9A008, as follows, specially designed for solid and hybrid rocket propulsion systems:

a. Rocket motor cases and insulation components therefor, usable in subsystems specified in 9A007, 9A009, 9A107 or 9A109.a.; N.B. For insulation material in bulk or sheet form, SEE ALSO 9C108. Note: In 9A108, 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.

b. Rocket nozzles, usable in subsystems specified in 9A007, 9A009, 9A107 or 9A109.a.;

c. Thrust vector control sub-systems, usable in "missiles". Technical Note: Examples of methods of achieving thrust vector control specified in 9A108.c. are:

or

9A109Hybrid 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.

9A110Composite 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.

In 9A110 'missile' means complete rocket systems and unmanned aerial vehicle systems capable of a range exceeding 300 km.

9A111Pulse jet or detonation 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.

In 9A111 detonation engines utilise detonation to produce a rise in effective pressure across the combustion chamber. Examples of detonation engines include pulse detonation engines, rotating detonation engines or continuous wave detonation engines.

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:

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

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.

9A115Launch 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 'missiles'; Technical Notes: 1.

In 9A115.a 'missile' means complete rocket systems and unmanned aerial vehicle systems capable of a range exceeding 300 km. 2.

Apparatus and devices specified in 9A115.a include those installed on a manned aircraft or an unmanned aerial vehicle.

b. Vehicles for transport, handling, control, activation or launching, designed or modified for space launch vehicles specified in 9A004, sounding rockets specified in 9A104 or "missiles".

9A116Reentry 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.

9A117Staging mechanisms, separation mechanisms, and interstages, usable in "missiles".

N.B. SEE ALSO 9A121.

9A118Devices 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.

9A119Individual 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.

9A120Liquid or gel propellant tanks, other than those specified in 9A006, specially designed for propellants specified in 1C111 or 'other liquid or gel propellants' used in rocket systems capable of delivering at least a 500 kg payload to a range of at least 300 km.

Note:

In 9A120 'other liquid or gel propellants' includes, but is not limited to, propellants specified in THE MILITARY GOODS CONTROLS.

9A121Umbilical and interstage electrical connectors specially designed for "missiles", space launch vehicles specified in 9A004 or sounding rockets specified in 9A104.

In 9A121, interstage electrical connectors also include electrical connectors installed between the "missile", space launch vehicle or sounding rocket and their payload.

9A350Spraying or fogging systems, specially designed or modified for fitting to aircraft, "lighter-than-air vehicles" or unmanned aerial vehicles, and specially designed components therefor, as follows:

a. Complete spraying or fogging systems capable of delivering, from a liquid suspension, an initial droplet 'VMD' of less than 50 μm at a flow rate of greater than two litres per minute;

b. Spray booms or arrays of aerosol generating units capable of delivering, from a liquid suspension, an initial droplet 'VMD' of less than 50 μm at a flow rate of greater than two litres per minute;

c. Aerosol generating units specially designed for fitting to systems specified in 9A350.a. and .b. Note:

Aerosol generating units are devices specially designed or modified for fitting to aircraft such as nozzles, rotary drum atomisers and similar devices.

Note:

9A350 does not control spraying or fogging systems and components that are demonstrated not to be capable of delivering biological agents in the form of infectious aerosols.

1.

Droplet size for spray equipment or nozzles specially designed for use on aircraft, "lighter-than-air vehicles" or unmanned aerial vehicles should be measured using either of the following:

a. Doppler laser method;

b. Forward laser diffraction method.

2.

In 9A350 'VMD' means Volume Median Diameter and for water-based systems this equates to Mass Median Diameter (MMD).

Note

9B includes test, inspection and production equipment applicable to aero, aero-derivative, industrial or marine gas turbine engines.

9B001Manufacturing equipment, tooling or fixtures, as follows:

N.B.

SEE ALSO 2B226

a. Directional solidification or single crystal casting equipment designed for "superalloys";

b. Casting tooling, specially designed for manufacturing gas turbine engine blades, vanes or "tip shrouds", manufactured from refractory metals or ceramics, as follows:

c. Directional-solidification or single-crystal additive-manufacturing equipment, designed for "superalloys".

9B002On-line (real time) control systems, instrumentation (including sensors) or automated data acquisition and processing equipment, having all of the following:

a. Specially designed for the "development" of gas turbine engines, assemblies or components; and

b. Incorporating any of the "technologies" specified in 9E003.h. or 9E003.i.

9B003Equipment specially designed for the "production" or test of gas turbine engine 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.

9B004Tools, dies or fixtures, for the solid-state joining of "superalloy", titanium or intermetallic aerofoil-to-disk combinations described in 9E003.a.3. or 9E003.a.6. for gas turbine engines.

9B005On-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 apply to wind tunnels specially designed for educational purposes and having a 'test section size' (measured laterally) of less than 250 mm. Technical Note: For the purposes of 9B005.a. 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.

9B006Acoustic 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.

9B007Equipment 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.

9B008Direct measurement wall skin friction transducers specially designed to operate at a test flow total (stagnation) temperature exceeding 833 K (560 °C).

9B009Tooling 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:

9B009 does not control tooling for the "production" of powder.

9B010Equipment specially designed for the "production" of items specified in 9A012.

9B105Aerodynamic test facilities for speeds of Mach 0,9 or more, usable for 'missiles' and their subsystems.

N.B.

SEE ALSO 9B005.

1.

9B105 includes wind tunnels and shock tunnels for the study of airflow over objects.

2.

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.

1.

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.

2.

In 9B105 'missile' means complete rocket systems and unmanned aerial vehicle systems capable of a range exceeding 300 km.

9B106Environmental chambers and anechoic chambers, as follows:

a. Environmental chambers having all 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

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:

9B107Aerothermodynamic test facilities, usable for 'missiles', 'missile' rocket propulsion systems, and reentry vehicles and equipment specified in 9A116, having any of the following characteristics:

a. An electrical power supply equal to or greater than 5 MW; or

b. A gas supply total pressure equal to or greater than 3 MPa.

1.

9B107 includes plasma arc jet facilities and plasma wind tunnels for the study of thermal and mechanical effects of airflow on objects.

2.

In 9B107 'missile' means complete rocket systems and unmanned aerial vehicle systems capable of a range exceeding 300 km.

9B115Specially 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.

9B116Specially 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'.

In 9B116 'missile' means complete rocket systems and unmanned aerial vehicle systems capable of a range exceeding 300 km.

9B117Test benches or 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.

9C108Insulation material in bulk form and "interior lining", other than those specified in 9A008, for rocket motor cases usable in "missiles" or specially designed for solid propellant rocket engines specified in 9A007 or 9A107.

In 9C108, 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 9A108.

9C110Resin 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.

9D001"Software", not specified in 9D003 or 9D004, specially designed or modified for the "development" of equipment or "technology", specified in 9A001 to 9A119, 9B or 9E003.

9D002"Software", not specified in 9D003 or 9D004, specially designed or modified for the "production" of equipment specified in 9A001 to 9A119 or 9B.

9D003"Software" incorporating "technology" specified in 9E003.h. and used in "FADEC Systems" for systems specified in 9A or equipment specified in 9B.

9D004Other "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, having all of the following:

a. Aero gas turbine engines, assemblies or components, incorporating "technology" specified in 9E003.a., 9E003.h. or 9E003.i.; or b. Multi-stage compressors providing either bypass or core flow, specially designed for aero gas turbine engines incorporating "technology" specified in 9E003.a. or 9E003.h.; and

a. Acquisition and processing of data, in real time; and b. Feedback control of the test article or test conditions (e.g. temperature, pressure, flow rate) while the test is in progress; Note:

9D004.b. does not control software for operation of the test facility or operator safety (e.g. overspeed shutdown, fire detection and suppression), or "production", repair or maintenance acceptance-testing limited to determining if the item has been properly assembled or repaired.

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:

9D005"Software" specially designed or modified for the operation of items specified in 9A004.e. or 9A004.f.

N.B.

For "software" for items specified in 9A004.d. that are incorporated into "spacecraft mission equipment", see the appropriate Categories.

9D101"Software" specially designed or modified for the "use" of goods specified in 9B105, 9B106, 9B107, 9B116 or 9B117.

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 subsystems specified 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.

9D104"Software" as follows:

a. "Software" specially designed or modified for the "use" of goods specified in 9A001, 9A005, 9A006.d., 9A006.g., 9A007.a., 9A009.a., 9A010.d., 9A011, 9A101, 9A102, 9A105, 9A106.d., 9A107, 9A109, 9A111, 9A115.a., 9A117 or 9A118.

b. "Software" specially designed or modified for the operation or maintenance of subsystems or equipment specified in 9A008.d., 9A106.c., 9A108.c. or 9A116.d.

9D105"Software" specially designed or modified to coordinate the function of more than one subsystem, other than that specified in 9D004.e., in space launch vehicles specified in 9A004 or sounding rockets specified in 9A104 or 'missiles'

Note:

9D105 includes "software" specially designed for a manned "aircraft" converted to operate as "unmanned aerial vehicle", as follows:

a. "Software" specially designed or modified to integrate the conversion equipment with the "aircraft" system functions; and

b. "Software" specially designed or modified to operate the "aircraft" as an "unmanned aerial vehicle".

In 9D105 'missile' means complete rocket systems and unmanned aerial vehicle systems capable of a range exceeding 300 km.

Note:

"Development" or "production" "technology" specified in 9E001 to 9E003 for gas turbine engines remains controlled when used for repair or overhaul. Excluded from control are: technical data, drawings or documentation for maintenance activities directly associated with calibration, removal or replacement of damaged or unserviceable line replaceable units, including replacement of whole engines or engine modules.

9E001"Technology" according to the General Technology Note for the "development" of equipment or "software", specified in 9A004 to 9A012, 9A350, 9B or 9D.

9E002"Technology" according to the General Technology Note for the "production" of equipment specified in 9A004 to 9A011, 9A350 or 9B.

N.B.

For "technology" for the repair of controlled structures, laminates or materials, see 1E002.f.

9E003Other "technology" as follows:

Note

9E003 includes technology applicable to aero, aero-derivative, marine or industrial gas turbine engines.

a. "Technology" "required" for the "development" or "production" of any of the following gas turbine engine components or systems:

Technical Note: For the purposes of 9E003.a.1., stress-rupture life testing is typically conducted on a test specimen.

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; d. Liners designed to operate at 'combustor exit temperature' exceeding 1 883 K (1 610 °C) and having holes that meet the parameters specified in 9E003.c.; or e. 'Pressure gain combustion'; Note:

The "required" "technology" for holes in 9E003.a.2. is limited to the derivation of the geometry and location of the holes.

Technical Notes: 1.

For the purposes of 9E003.a.2.a., 'thermally decoupled liners' are liners that feature at least a support structure designed to carry mechanical loads and a combustion facing structure designed to protect the support structure from the heat of combustion. The combustion facing structure and support structure have independent thermal displacement (mechanical displacement due to thermal load) with respect to one another, i.e., they are thermally decoupled. 2.

For the purposes of 9E003.a.2.a. and 9E003.a.2.d., 'combustor exit temperature' is the bulk average gas path total (stagnation) temperature between the combustor exit plane and the leading edge of the turbine inlet guide vane (i.e., measured at engine station T40 as defined in SAE ARP 755A) when the engine is running in a "steady state mode" of operation at the certificated maximum continuous operating temperature. 3.

For the purposes of 9.E.3.a.2.e., 'pressure gain combustion' refers to a combustor where the bulk average stagnation pressure at the combustor outlet is greater than the bulk average stagnation pressure at the combustor inlet due primarily to the combustion process, when the engine is running in a "steady state mode" of operation. N.B.

For "technology" "required" for manufacturing cooling holes, see 9E003.c.

a. Manufactured from organic "composite" materials designed to operate above 588 K (315 °C); b. Manufactured from 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

c. Stators, vanes, blades, tip seals (shrouds), rotating blings, rotating blisks, or 'splitter ducts', that are all of the following:

Technical Note: For the purposes of 9E003.a.3.c., a 'splitter duct' performs the initial separation of the air-mass flow between the bypass and core sections of the engine.

Technical Note: For the purposes of 9E003.a.4. and 9E003.a.5., 'gas path temperature' is the bulk average gas path total (stagnation) temperature at the leading edge plane of the turbine component when the engine is running in a "steady state mode" of operation at the certificated or specified maximum continuous operating temperature.

Technical Note: For the purposes of 9E003.a.8., 'damage tolerant' components are designed using methodology and substantiation to predict and limit crack growth.

a. 20 % or more of the total volume being one or more closed cavities containing vacuum or gas only; and b. One or more closed cavities having a volume of 5 cm³ or larger; Technical Note: For the purposes of 9E003.a.11., a 'fan blade' is the aerofoil portion of the rotating stage or stages, which provide both compressor and bypass flow in a gas turbine engine.

b. "Technology" "required" for the "development" or "production" of any of the following:

c. "Technology" "required" for manufacturing cooling holes in gas turbine engine components incorporating any of the "technologies" specified in 9E003.a.1., 9E003.a.2. or 9E003.a.5., and having any of the following:

a. Minimum 'cross-sectional area' less than 0,45 mm²; b. 'Hole shape ratio' greater than 4,52; and c. 'Incidence angle' equal to or less than 25°; or

a. Minimum 'cross-sectional area' less than 0,12 mm²; b. 'Hole shape ratio' greater than 5,65; and c. 'Incidence angle' more than 25°; Note:

9E003.c. does not control "technology" for manufacturing constant radius cylindrical holes that are straight through and enter and exit on the external surfaces of the component. Technical Notes: For the purposes of 9E003.c.: 1. The 'cross-sectional area' is the area of the hole in the plane perpendicular to the hole axis. 2. 'Hole shape ratio' is the nominal length of the axis of the hole divided by the square root of its minimum 'cross-sectional area'. 3. 'Incidence angle' is the acute angle measured between the plane tangential to the aerofoil surface and the hole axis at the point where the hole axis enters the aerofoil surface. 4. Methods for manufacturing holes include "laser" beam machining, water jet machining, Electro-Chemical Machining (ECM) or Electrical Discharge Machining (EDM).

d. "Technology" "required" for the "development" or "production" of helicopter power transfer systems or tilt rotor or tilt wing "aircraft" power transfer systems;

e. "Technology" for the "development" or "production" of reciprocating diesel engine ground vehicle propulsion systems having all of the following:

Technical Note: For the purposes of 9E003.e., 'box volume' in 9E003.e. is the product of three perpendicular dimensions measured in the following way: Length:

The length of the crankshaft from front flange to flywheel face; Width:

The largest of any of the following: a. The outside dimension from valve cover to valve cover; b. The dimensions of the outside edges of the cylinder heads; or c. The diameter of the flywheel housing; Height:

The largest of any of the following: a. The dimension of the crankshaft centre-line to the top plane of the valve cover (or cylinder head) plus twice the stroke; or b. The diameter of the flywheel housing.

f. "Technology" "required" for the "production" of specially designed components for "high output diesel engines", as follows:

a. Cylinder liners; b. Pistons; c. Cylinder heads; and d. One or more other components (including exhaust ports, turbochargers, valve guides, valve assemblies or insulated fuel injectors);

a. Operating at pressure ratios of 4:1 or higher; b. Mass flow in the range from 30 to 130 kg per minute; and c. Variable flow area capability within the compressor or turbine sections;

a. Injection amount in excess of 230 mm³ per injection per cylinder; and b. Electronic control features specially designed for switching governor characteristics automatically depending on fuel property to provide the same torque characteristics by using the appropriate sensors;

g. "Technology" "required" for the "development" or "production" of "high output diesel engines" for solid, gas phase or liquid film (or combinations thereof) cylinder wall lubrication and permitting operation to temperatures exceeding 723 K (450 °C), measured on the cylinder wall at the top limit of travel of the top ring of the piston;

h. "Technology" for gas turbine engine "FADEC systems" as follows:

Note:

9E003.h. does not control technical data related to engine-"aircraft" integration required by the civil aviation authorities of one or more EU Member States or Wassenaar Arrangement Participating 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).

i. "Technology" for gas turbine engine adjustable flow path systems designed to maintain engine stability for gas generator turbines, fan or power turbines, or propelling nozzles, as follows:

Note:

9E003.i. does not control "technology" for any of the following:

a. Inlet guide vanes; b. Variable pitch fans or prop-fans; c. Variable compressor vanes; d. Compressor bleed valves; or e. Adjustable flow path geometry for reverse thrust.

j. "Technology" "required" for the "development" of wing-folding systems designed for fixed-wing "aircraft" powered by gas turbine engines;

N.B.

For "technology" "required" for the "development" of wing-folding systems designed for fixed-wing "aircraft" SEE ALSO MILITARY GOODS CONTROLS.

k. "Technology", not specified in 9E003.a., 9E003.h., or 9E003.i., "required" for the "development" of any of the following components or systems, specially designed for aero gas turbine engines to enable "aircraft" to cruise at Mach 1 or greater for more than 30 minutes:

Technical Notes: For the purposes of 9E003.k.: 1. Propulsion inlet systems include core flow pre-coolers. 2. 'Reheat systems' provide additional thrust by combusting fuel in exhaust and/or bypass flow downstream of the last turbomachinery stage. 'Reheat systems' are also referred to as afterburners. 3. 'Active thermal management systems' employ methods other than passive oil-to-air cooling or oil-to-fuel cooling, such as vapour cycle systems. 4. 'Compression system' is any stage or combination of stages between the engine inlet face and the combustor that increases gas path pressure through mechanical work. 5. An 'engine rotor support' is the bearing supporting the main engine shaft that drives the compression system or turbine rotors. N.B.1

For engine control technology, see 9E003.h. N.B.2

For adjustable flow path systems technology, see 9E003i.

9E101“Technology” as follows:

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.

9E102"Technology" according to the General Technology Note for the "use" of space launch vehicles specified in 9A004, 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, 9B107, 9B115, 9B116, 9B117, 9D101 or 9D103.

In 9E102 'UAV' means unmanned aerial vehicle systems capable of a range exceeding 300 km.

ANNEX II

The following sections set out the Union general export authorisations for certain exports.

A. EXPORTS TO AUSTRALIA, CANADA, ICELAND, JAPAN, NEW ZEALAND, NORWAY, SWITZERLAND, INCLUDING LIECHTENSTEIN, THE UNITED KINGDOM AND THE UNITED STATES

UNION GENERAL EXPORT AUTHORISATION No EU001

(referred to in point (d) of Article 12(1) of this Regulation)

This authorisation covers all dual-use items specified in any entry in Annex I, except those listed in Section I of this Annex.

This authorisation is valid throughout the customs territory of the Union for exports to the following destinations:

— Australia,

— Canada,

— Iceland,

— Japan,

— New Zealand,

— Norway,

— Switzerland, including Liechtenstein,

— United Kingdom (without prejudice to the application of this Regulation to and in the United Kingdom in respect of Northern Ireland, in accordance with point 47 of Annex 2 to the Protocol on Ireland/Northern Ireland (the ‘Protocol’) annexed to the Agreement on the withdrawal of the United Kingdom of Great Britain and Northern Ireland from the European Union and the European Atomic Energy Community (¹¹), listing the provisions of Union law referred to in Article 5(4) of the Protocol),

— United States.

1.This authorisation does not authorise the export of items where:

(a) the exporter has been informed by the competent authority of the Member State in which the exporter is resident or established that the items in question are or may be intended, in their entirety or in part: (i) for use in connection with the development, production, handling, operation, maintenance, storage, detection, identification or dissemination of chemical, biological or nuclear weapons or other nuclear explosive devices, or the development, production, maintenance or storage of missiles capable of delivering such weapons; (ii) for a military end-use as defined in point (b) of Article 4(1) of this Regulation in a country subject to an arms embargo; or (iii) for use as parts or components of military items listed in the national military list that have been exported from the territory of the Member State concerned without authorisation or in breach of an authorisation prescribed by the national legislation of that Member State;

(b) the exporter is aware that the items in question are intended, in their entirety or in part, for any of the uses referred to in point (a); or

(c) the relevant items are exported to a customs-free zone or a free warehouse which is located in a destination covered by this authorisation.

2.The exporter shall declare that the items are being exported under Union general export authorisation No EU001 in the customs declaration.

3.The exporter who uses this authorisation shall notify the competent authority of the Member State where the exporter is resident or established of the first use of this authorisation within 30 days from the date when the first export took place or, alternatively, and in accordance with a requirement by the competent authority of the Member State where the exporter is resident or established, prior to the first use of this authorisation. Member States shall notify the Commission of the notification mechanism chosen for this authorisation. The Commission shall publish the information notified to it in the C series of the Official Journal of the European Union.

Reporting requirements attached to the use of this authorisation and additional information that the Member State from which the export is made might require on items exported under this authorisation shall be defined by Member States.

A Member State may require exporters resident or established in that Member State to register prior to the first use of this authorisation. Registration shall be automatic and acknowledged by the competent authority to the exporter without delay and in any case within 10 working days of receipt, subject to Article 12(7) of this Regulation.

Where applicable, the requirements set out in the second and third subparagraphs shall be based on those defined for the use of national general export authorisations granted by those Member States which provide for such authorisations.

B. EXPORTS OF CERTAIN DUAL-USE ITEMS TO CERTAIN DESTINATIONS

UNION GENERAL EXPORT AUTHORISATION No EU002

(referred to in point (d) of Article 12(1) of this Regulation)

This authorisation covers the following dual-use items specified in Annex I:

— 1A001,

— 1A003,

— 1A004,

— 1C003.b.,

— 1C003.c.,

— 1C004,

— 1C005,

— 1C006,

— 1C008,

— 1C009,

— 2B008,

— 3A001.a.3.,

— 3A001.a.6.,

— 3A001.a.7.,

— 3A001.a.9.,

— 3A001.a.10.,

— 3A001.a.11.,

— 3A001.a.12.,

— 3A002.c.,

— 3A002.d.,

— 3A002.e.,

— 3A002.f.,

— 3C001,

— 3C002,

— 3C003,

— 3C004,

— 3C005,

— 3C006.

This authorisation is valid throughout the customs territory of the Union for exports to the following destinations:

— Argentina,

— South Africa,

— South Korea,

— Turkey.

1.This authorisation does not authorise the export of items where:

(a) the exporter has been informed by the competent authority of the Member State in which the exporter is resident or established that the items in question are or may be intended, in their entirety or in part: (i) for use in connection with the development, production, handling, operation, maintenance, storage, detection, identification or dissemination of chemical, biological or nuclear weapons or other nuclear explosive devices, or the development, production, maintenance or storage of missiles capable of delivering such weapons; (ii) for a military end-use as defined in point (b) of Article 4(1) of this Regulation in a country subject to an arms embargo; or (iii) for use as parts or components of military items listed in national military lists that have been exported from the territory of the Member State concerned without authorisation or in breach of an authorisation prescribed by the national legislation of that Member State;

(b) the exporter is aware that the items in question are intended, in their entirety or in part, for any of the uses referred to in point (a); or

(c) the relevant items are exported to a customs-free zone or a free warehouse which is located in a destination covered by this authorisation.

2.The exporter shall declare that the items are being exported under Union general export authorisation No EU002 in the customs declaration.

3.The exporter who uses this authorisation shall notify the competent authority of the Member State where the exporter is resident or established of the first use of this authorisation within 30 days from the date when the first export took place or, alternatively, and in accordance with a requirement by the competent authority of the Member State where the exporter is resident or established, prior to the first use of this authorisation. Member States shall notify the Commission of the notification mechanism chosen for this authorisation. The Commission shall publish the information notified to it in the C series of the Official Journal of the European Union.

Reporting requirements attached to the use of this authorisation and additional information that the Member State from which the export is made might require on items exported under this authorisation are defined by Member States.

A Member State may require exporters resident or established in that Member State to register prior to the first use of this authorisation. Registration shall be automatic and acknowledged by the competent authority to the exporter without delay and in any case within 10 working days of receipt, subject to Article 12(7) of this Regulation.

Where applicable, the requirements set out in the second and third subparagraphs shall be based on those defined for the use of national general export authorisations granted by those Member States which provide for such authorisations.

C. EXPORT AFTER REPAIR/REPLACEMENT

UNION GENERAL EXPORT AUTHORISATION No EU003

(referred to in point (d) of Article 12(1) of this Regulation)

1.This authorisation covers all dual-use items specified in any entry in Annex I, except those listed in paragraph 2 of this Section where:

(a) the items were reimported into the customs territory of the Union for the purpose of maintenance, repair or replacement, and are exported or re-exported to the country of consignment without any changes to their original characteristics within a period of 5 years after the date when the original export authorisation has been granted; or

(b) the items are exported to the country of consignment in exchange for items of the same quality and number which were reimported into the customs territory of the Union for maintenance, repair or replacement within a period of 5 years after the date when the original export authorisation has been granted.

2.Items excluded:

(a) all items listed in Section I of this Annex;

(b) all items listed in Sections D and E of each Category of Annex I;

(c) the following items specified in Annex I: — 1A002.a., — 1C012.a., — 1C227, — 1C228, — 1C229, — 1C230, — 1C231, — 1C236, — 1C237, — 1C240, — 1C350, — 1C450, — 5A001.b.5., — 5A002.c., — 5A002.d., — 5A002.e., — 5A003.a., — 5A003.b., — 6A001.a.2.a.1., — 6A001.a.2.a.5., — 6A002.a.1.c., — 8A001.b., — 8A001.c.1., — 9A011.

This authorisation is valid throughout the customs territory of the Union for exports to the following destinations:

— Albania,

— Argentina,

— Bosnia and Herzegovina,

— Brazil,

— Chile,

— China (including Hong Kong and Macao),

— French overseas territories,

— India,

— Kazakhstan,

— Mexico,

— Montenegro,

— Morocco,

— North Macedonia,

— Serbia,

— Singapore,

— South Africa,

— South Korea,

— Tunisia,

— Turkey,

— Ukraine,

— United Arab Emirates.

1.This authorisation can only be used when the initial export has taken place under a Union general export authorisation or an initial export authorisation has been granted by the competent authority of the Member State where the original exporter was resident or established for the export of the items which have subsequently been reimported into the customs territory of the Union for the purposes of maintenance, repair or replacement. This authorisation is valid only for exports to the original end-user.

2.This authorisation does not authorise the export of items where:

(a) the exporter has been informed by the competent authority of the Member State in which the exporter is resident or established that the items in question are or may be intended, in their entirety or in part: (i) for use in connection with the development, production, handling, operation, maintenance, storage, detection, identification or dissemination of chemical, biological or nuclear weapons or other nuclear explosive devices or the development, production, maintenance or storage of missiles capable of delivering such weapons; (ii) for a military end-use as defined in point (b) of Article 4(1) of this Regulation where the purchasing country or country of destination is subject to an arms embargo; or (iii) for use as parts or components of military items listed in the national military list that have been exported from the territory of the Member State concerned without authorisation or in breach of an authorisation prescribed by the national legislation of that Member State;

(b) the exporter is aware that the items in question are intended, in their entirety or in part, for any of the uses referred to in point (a);

(c) the relevant items are exported to a customs-free zone or a free warehouse which is located in a destination covered by this authorisation;

(d) the initial authorisation has been annulled, suspended, modified or revoked; or