Commission Delegated Regulation (EU) 2023/996 of 23 February 2023 amending Regulation (EU) 2021/821 of the European Parliament and of the Council as regards the list of dual-use items

• d. Radiation-hardened TV cameras, or lenses therefor, specially designed or rated as radiation hardened to withstand a total radiation dose greater than 50 × 10³ Gy(silicon) (5 × 10⁶ rad (silicon)) without operational degradation.

Technical Note:

The term Gy(silicon) refers to the energy in Joules per kilogram absorbed by an unshielded silicon sample when exposed to ionising radiation.

6A205

"Lasers", "laser" amplifiers and oscillators, other than those specified in 0B001.g.5., 0B001.h.6. and 6A005, as follows:

• N.B. For copper vapour lasers, see 6A005.b.

• a. Argon ion "lasers" having both of the following characteristics:

• 1. Operating at wavelengths between 400 nm and 515 nm; and

• 1. An "average output power" greater than 40 W;

• b. Tunable pulsed single-mode dye laser oscillators having all of the following characteristics:

• 1. Operating at wavelengths between 300 nm and 800 nm;

• 1. An "average output power" greater than 1 W;

• 1. A repetition rate greater than 1 kHz; and

• 1. Pulse width less than 100 ns;

• c. Tunable pulsed dye laser amplifiers and oscillators, having all of the following characteristics:

• 1. Operating at wavelengths between 300 nm and 800 nm;

• 1. An "average output power" greater than 30 W;

• 1. A repetition rate greater than 1 kHz; and

• 1. Pulse width less than 100 ns;

• Note: 6A205.c. does not control single mode oscillators.

• d. Pulsed carbon dioxide (CO2) "lasers" having all of the following characteristics:

• 1. Operating at wavelengths between 9 000 nm and 11 000 nm;

• 1. A repetition rate greater than 250 Hz;

• 1. An "average output power" greater than 500 W; and

- 4. Pulse width of less than 200 ns;

• e. Para-hydrogen Raman shifters designed to operate at 16 μm output wavelength and at a repetition rate greater than 250 Hz;

• f. Neodymium-doped (other than glass) "lasers" with an output wavelength between 1 000 and 1 100 nm having either of the following:

• 1. Pulse-excited and Q-switched with a pulse duration equal to or more than 1 ns, and having either of the following:

• a. A single–transverse mode output with an "average output power" greater than 40W; or

• b. A multiple-transverse mode output having an average power greater than 50 W; or

• 1. Incorporating frequency doubling to give an output wavelength between 500 and 550 nm with an "average output power" of more than 40 W;

• g. Pulsed carbon monoxide (CO) "lasers", other than those specified in 6A005.d.2., having all of the following:

• 1. Operating at wavelengths between 5 000 and 6 000 nm;

• 1. A repetition rate greater than 250 Hz;

• 1. An "average output power" greater than 200 W; and

• 1. Pulse width of less than 200 ns.

6A225 Velocity interferometers for measuring velocities exceeding 1 km/s during time intervals of less than 10 microseconds.

• Note: 6A225 includes velocity interferometers such as VISARs (Velocity Interferometer Systems for Any Reflector), DLIs (Doppler Laser Interferometers) and PDV (Photonic Doppler Velocimeters) also known as Het-V (Heterodyne Velocimeters).

6A226 Pressure sensors, as follows:

• a. Shock pressure gauges capable of measuring pressures greater than 10 GPa, including gauges made with manganin, ytterbium, and polyvinylidene fluoride (PVDF) / polyvinyl difluoride (PVF2);

• b. Quartz pressure transducers for pressures greater than 10 GPa.

6B Test, Inspection and Production Equipment

6B002 Masks and reticles, specially designed for optical sensors specified in 6A002.a.1.b. or 6A002.a.1.d.

6B004 Optical equipment as follows:

• a. Equipment for measuring absolute reflectance to an "accuracy" of equal to or better than 0,1 % of the reflectance value;

• b. Equipment other than optical surface scattering measurement equipment, having an unobscured aperture of more than 10 cm, specially designed for the non-contact optical measurement of a non-planar optical surface figure (profile) to an "accuracy" of 2 nm or less (better) against the required profile.

• Note: 6B004 does not control microscopes.

6B007 Equipment to produce, align and calibrate land-based gravity meters with a static "accuracy" of better than 0,1 mGal.

6B008 Pulse radar cross-section measurement systems having transmit pulse widths of 100 ns or less, and specially designed components therefor.

• N.B. SEE ALSO 6B108.

6B108 Systems, other than those specified in 6B008, specially designed for radar cross section measurement usable for ‘missiles’ and their subsystems.

Technical Note:

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

6C Materials

6C002 Optical sensor materials as follows:

• a. Elemental tellurium (Te) of purity levels of 99,9995 % or more;

• b. Single crystals (including epitaxial wafers) of any of the following:

• 1. Cadmium zinc telluride (CdZnTe), with zinc content of less than 6 % by ‘mole fraction’;

• 1. Cadmium telluride (CdTe) of any purity level; or

- 3. Mercury cadmium telluride (HgCdTe) of any purity level.

Technical Note:

‘Mole fraction’ is defined as the ratio of moles of ZnTe to the sum of moles of CdTe and ZnTe present in the crystal.

6C004 Optical materials as follows:

• a. Zinc selenide (ZnSe) and zinc sulphide (ZnS) "substrate blanks", produced by the chemical vapour deposition process and having any of the following:

• 1. A volume greater than 100 cm³; or

• 1. A diameter greater than 80 mm and a thickness of 20 mm or more;

• b. Electro-optic materials and non-linear optical materials, as follows:

• 1. Potassium titanyl arsenate (KTA) (CAS 59400-80-5);

• 1. Silver gallium selenide (AgGaSe2, also known as AGSE) (CAS 12002-67-4);

• 1. Thallium arsenic selenide (Tl3AsSe3, also known as TAS) (CAS 16142-89-5);

• 1. Zinc germanium phosphide (ZnGeP2, also known as ZGP, zinc germanium biphosphide or zinc germanium diphosphide); or

• 1. Gallium selenide (GaSe) (CAS 12024-11-2);

• c. Non-linear optical materials, other than those specified in 6C004.b., having any of the following:

• 1. Having all of the following:

• a. Dynamic (also known as non-stationary) third order non-linear susceptibility (χ⁽³⁾, chi 3) of 10^–6 m²/V² or more; and

• b. Response time of less than 1 ms; or

- 2. Second order non-linear susceptibility (χ⁽²⁾, chi 2) of 3,3 × 10^–11 m/V or more;

- d. "Substrate blanks" of silicon carbide or beryllium beryllium (Be/Be) deposited materials, exceeding 300 mm in diameter or major axis length;

- e. Glass, including fused silica, phosphate glass, fluorophosphate glass, zirconium fluoride (ZrF4) (CAS 7783-64-4) and hafnium fluoride (HfF4) (CAS 13709-52-9) and having all of the following:

- 1. A hydroxyl ion (OH-) concentration of less than 5 ppm;

• 1. Integrated metallic purity levels of less than 1 ppm; and

• 1. High homogeneity (index of refraction variance) less than 5 × 10^–6;

• f. Synthetically produced diamond material with an absorption of less than 10^–5 cm^–1 for wavelengths exceeding 200 nm but not exceeding 14 000 nm.

6C005

"Laser" materials as follows:

• a. Synthetic crystalline "laser" host material in unfinished form as follows:

• 1. Titanium doped sapphire;

• 1. Not used.

• b. Rare-earth-metal doped double-clad fibres having any of the following:

• 1. Nominal "laser" wavelength of 975 nm to 1 150 nm and having all of the following:

• a. Average core diameter equal to or greater than 25 μm; and

• b. Core ‘Numerical Aperture’ (‘NA’) less than 0,065; or

• Note: 6C005.b.1. does not control double-clad fibres having an inner glass cladding diameter exceeding 150 μm and not exceeding 300 μm.

• 1. Nominal "laser" wavelength exceeding 1 530 nm and having all of the following:

• a. Average core diameter equal to or greater than 20 μm; and

• b. Core ‘Numerical Aperture’ (‘NA’) less than 0,1.

Technical Notes:

• 1. For the purposes of 6C005.b., the core ‘Numerical Aperture’ (‘NA’) is measured at the emission wavelengths of the fibre.

• 2. 6C005.b. includes fibres assembled with end caps.

6D Software

6D001

"Software" specially designed for the "development" or "production" of equipment specified in 6A004, 6A005, 6A008 or 6B008.

6D002

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

6D003 Other "software" as follows:

• a. "Software" as follows:

• 1. "Software" specially designed for acoustic beam forming for the "real-time processing" of acoustic data for passive reception using towed hydrophone arrays;

• 1. "Source code" for the "real-time processing" of acoustic data for passive reception using towed hydrophone arrays;

• 1. "Software" specially designed for acoustic beam forming for "real-time processing" of acoustic data for passive reception using bottom or bay cable systems;

• 1. "Source code" for "real-time processing" of acoustic data for passive reception using bottom or bay cable systems;

• 1. "Software" or "source code", specially designed for all of the following:

• a. "Real-time processing" of acoustic data from sonar systems specified in 6A001.a.1.e.; and

• b. Automatically detecting, classifying and determining the location of divers or swimmers;

• N.B. For diver detection "software" or "source code", specially designed or modified for military use, SEE THE MILITARY GOODS CONTROLS.

• b. Not used;

• c. "Software" designed or modified for cameras incorporating "focal plane arrays" specified in 6A002.a.3.f. and designed or modified to remove a frame rate restriction and allow the camera to exceed the frame rate specified in 6A003.b.4. Note 3.a.

• d. "Software" specially designed to maintain the alignment and phasing of segmented mirror systems consisting of mirror segments having a diameter or major axis length equal to or larger than 1 m;

• e. Not used;

• f. "Software" as follows:

• 1. "Software" specially designed for magnetic and electric field "compensation systems" for magnetic sensors designed to operate on mobile platforms;

• 1. "Software" specially designed for magnetic and electric field anomaly detection on mobile platforms;

• 1. "Software" specially designed for "real-time processing" of electromagnetic data using underwater electromagnetic receivers specified in 6A006.e.;

• 1. "Source code" for "real time processing" of electromagnetic data using underwater electromagnetic receivers specified in 6A006.e.;

• g. "Software" specially designed to correct motional influences of gravity meters or gravity gradiometers;

• h. "Software" as follows:

• 1. Air Traffic Control (ATC) "software" designed to be hosted on general purpose computers located at Air Traffic Control centres and capable of accepting radar target data from more than four primary radars;

• 1. "Software" for the design or "production" of radomes having all of the following:

• a. Specially designed to protect the electronically scanned array antennae specified in 6A008.e.; and

• b. Resulting in an antenna pattern having an ‘average side lobe level’ more than 40 dB below the peak of the main beam level.

Technical Note:

‘Average side lobe level’ in 6D003.h.2.b. is measured over the entire array excluding the angular extent of the main beam and the first two side lobes on either side of the main beam.

6D102

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

6D103

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

Technical Note:

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

6D203

"Software" specially designed to enhance or release the performance of cameras or imaging devices to meet the characteristics of 6A203.a. to 6A203.c.

6E Technology

6E001

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

6E002

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

6E003 Other "technology" as follows:

• a. "Technology" as follows:

• 1. "Technology""required" for the coating and treatment of optical surfaces to achieve an ‘optical thickness’ uniformity of 99,5 % or better for optical coatings 500 mm or more in diameter or major axis length and with a total loss (absorption and scatter) of less than 5 × 10^–3;

• N.B. See also 2E003.f.

Technical Note:

‘Optical thickness’ is the mathematical product of the index of refraction and the physical thickness of the coating.

• 1. "Technology" for the fabrication of optics using single point diamond turning techniques to produce surface finish "accuracies" of better than 10 nm rms on non-planar surfaces exceeding 0,5 m²;

• b. "Technology""required" for the "development", "production" or "use" of specially designed diagnostic instruments or targets in test facilities for "SHPL" testing or testing or evaluation of materials irradiated by "SHPL" beams;

6E101

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

• Note: 6E101 only controls "technology" for items specified in 6A002, 6A007 and 6A008 if the items were designed for airborne applications and are usable in "missiles".

6E201

"Technology" according to the General Technology Note for the "use" of equipment specified in 6A003, 6A005.a.2., 6A005.b.2., 6A005.b.3., 6A005.b.4., 6A005.b.6., 6A005.c.2., 6A005.d.3.c., 6A005.d.4.c., 6A202, 6A203, 6A205, 6A225 or 6A226.

• Note 1: 6E201 only controls "technology" for cameras specified in 6A003 if the cameras are also specified by any of the control parameters of 6A203.

• Note 2: 6E201 only controls “technology” for lasers in 6A005.b.6. that are neodymium-doped and specified by any of the control parameters of 6A205.f.

6E203

"Technology", in the form of codes or keys, to enhance or release the performance of cameras or imaging devices to meet the characteristics of 6A203.a. to 6A203.c.

PART IX

Category 7

CATEGORY 7 - NAVIGATION AND AVIONICS

7A Systems, Equipment and Components

• N.B. For automatic pilots for underwater vehicles, see Category 8.

For radar, see Category 6.

7A001 Accelerometers as follows and specially designed components therefor:

• N.B. SEE ALSO 7A101.

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

• a. Linear accelerometers having any of the following:

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

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

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

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

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

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

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

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

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

7A002 Gyros or angular rate sensors, having any of the following and specially designed components therefor:

• N.B. SEE ALSO 7A102.

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

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

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

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

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

• Note: 7A002.a.1.b. does not control "spinning mass gyros".

• 1. An angular rate range greater than or equal to 500 degrees per second and having any of the following:

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

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

• Note: 7A002.a.2.b. does not control "spinning mass gyros".

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

7A003

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

• N.B. SEE ALSO 7A103.

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

• — Attitude and Heading Reference Systems (AHRSs);

• — Gyrocompasses;

• — Inertial Measurement Units (IMUs);

• — Inertial Navigation Systems (INSs);

• — Inertial Reference Systems (IRSs);

• — Inertial Reference Units (IRUs).

• Note 2: 7A003 does not control ‘inertial measurement equipment or systems’ which are certified for use on "civil aircraft" by civil aviation authorities of one or more EU Member States or Wassenaar Arrangement Participating States.

Technical Note:

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

• a. "Satellite navigation system";

• b. "Data-Based Referenced Navigation" ("DBRN").

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

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

• 1. 0,5 % distanced travelled "CEP" or less (better); or

• 1. Total drift of 1 nautical mile "CEP" or less (better) in a 24 hr period;

Technical Note:

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

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

Technical Note:

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

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

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

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

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

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

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

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

7A004

‘Star trackers’ and components therefor, as follows:

• N.B. SEE ALSO 7A104.

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

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

• 1. Optical heads or baffles;

- 2. Data processing units.

Technical Note:

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

7A005

"Satellite navigation system" receiving equipment having any of the following and specially designed components therefor:

• N.B. SEE ALSO 7A105.

• N.B. For equipment specially designed for military use, SEE MILITARY GOODS CONTROLS.

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

• b. Employing ‘adaptive antenna systems’.

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

Technical Note:

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

7A006 Airborne altimeters operating at frequencies other than 4,2 to 4,4 GHz inclusive and having any of the following:

• N.B. SEE ALSO 7A106.

• a. ‘Power management’; or

• b. Using phase shift key modulation.

Technical Note:

‘Power management’ is changing the transmitted power of the altimeter signal so that received power at the "aircraft" altitude is always at the minimum necessary to determine the altitude.

7A008 Underwater sonar navigation systems using doppler velocity or correlation velocity logs integrated with a heading source and having a positioning "accuracy" of equal to or less (better) than 3 % of distance travelled "Circular Error Probable" ("CEP") and specially designed components therefor.

• Note: 7A008 does not control systems specially designed for installation on surface vessels or systems requiring acoustic beacons or buoys to provide positioning data.

• N.B. See 6A001.a. for acoustic systems, and 6A001.b. for correlation-velocity and Doppler-velocity sonar log equipment.

See 8A002 for other marine systems.

7A101 Linear accelerometers, other than those specified in 7A001, designed for use in inertial navigation systems or in guidance systems of all types, usable in ‘missiles’, having all of the following characteristics, and specially designed components therefor:

• a. A "bias""repeatability" of less (better) than 1 250 micro g; and

• b. A "scale factor""repeatability" of less (better) than 1 250 ppm;

- Note: 7A101 does not control accelerometers specially designed and developed as Measurement While Drilling (MWD) Sensors for use in downhole well service operations.

Technical Notes:

- 1. In 7A101 ‘missile’ means complete rocket systems and unmanned aerial vehicle systems capable of a range exceeding 300 km;

• 2. In 7A101 the measurement of "bias" and "scale factor" refers to one sigma standard deviation with respect to a fixed calibration over a period of one year;

7A102 All types of gyros, other than those specified in 7A002, usable in ‘missiles’, with a rated "drift rate" ‘stability’ of less than 0,5^o (1 sigma or rms) per hour in a 1 g environment and specially designed components therefor.

Technical Notes:

• 1. In 7A102 ‘missile’ means complete rocket systems and unmanned aerial vehicle systems capable of a range exceeding 300 km.

• 2. In 7A102 ‘stability’ is defined as a measure of the ability of a specific mechanism or performance coefficient to remain invariant when continuously exposed to a fixed operating condition (IEEE STD 528-2001 paragraph 2.247).

7A103 Instrumentation, navigation equipment and systems, other than those specified in 7A003, as follows; and specially designed components therefor:

• a. ‘Inertial measurement equipment or systems’, using accelerometers or gyros as follows:

• 1. Accelerometers specified in 7A001.a.3., 7A001.b. or 7A101 or gyros specified in 7A002 or 7A102; or

• Note: 7A103.a.1. does not control equipment containing accelerometers specified in 7A001.a.3. that are designed to measure vibration or shock.

• 1. Accelerometers specified in 7A001.a.1. or 7A001.a.2., designed for use in inertial navigation systems or in guidance systems of all types, and usable in ‘missiles’;

• Note: 7A103.a.2. does not control equipment containing accelerometers specified in 7A001.a.1. or 7A001.a.2. where such accelerometers are specially designed and developed as MWD (Measurement While Drilling) sensors for use in down-hole well services operations

Technical Note:

‘Inertial measurement equipment or systems’ specified in 7A103.a. incorporate accelerometers or gyros to measure changes in velocity and orientation in order to determine or maintain heading or position without requiring an external reference once aligned.

• Note: ‘Inertial measurement equipment or systems’ in 7A103.a. include:

• — Attitude and Heading Reference Systems (AHRSs);

• — Gyrocompasses;

• — Inertial Measurement Units (IMUs);

• — Inertial Navigation Systems (INSs);

• — Inertial Reference Systems (IRSs);

• — Inertial Reference Units (IRUs).

• b. Integrated flight instrument systems which include gyrostabilisers or automatic pilots, designed or modified for use in ‘missiles’;

• c. ‘Integrated navigation systems’, designed or modified for ‘missiles’ and capable of providing a navigational accuracy of 200 m ‘CEP’ or less;

Technical Notes:

• 1. An ‘integrated navigation system’ typically incorporates the following components:

• a. An inertial measurement device (e.g., an attitude and heading reference system, inertial reference unit, or inertial navigation system);

• b. One or more external sensors used to update the position and/or velocity, either periodically or continuously throughout the flight (e.g., satellite navigation receiver, radar altimeter, and/or Doppler radar); and

• c. Integration hardware and software;

• 2. In 7A103.c. ‘CEP’ (Circular Error Probable or Circle of Equal Probability) is a measure of accuracy, defined as the radius of the circle inside of which there is a 50 % probability of being located.

• d. Three axis magnetic heading sensors, designed or modified to be integrated with flight control and navigation systems, other than those specified in 6A006, having all of the following characteristics, and specially designed components therefor:

• 1. Internal tilt compensation in pitch (± 90 degrees) and roll (± 180 degrees) axes; and

• 1. Azimuthal accuracy better (less) than 0,5 degrees rms at latitude of ± 80 degrees, reference to local magnetic field.

• Note: Flight control and navigation systems in 7A103.d. include gyrostabilisers, automatic pilots and inertial navigation systems.

Technical Note:

In 7A103 ‘missile’ means complete rocket systems and unmanned aerial vehicle systems capable of a range exceeding 300 km.

7A104

Gyro-astro compasses and other devices, other than those specified in 7A004, which derive position or orientation by means of automatically tracking celestial bodies or satellites and specially designed components therefor.

7A105 Receiving equipment for ‘navigation satellite systems’, other than those specified in 7A005, having any of the following characteristics, and specially designed components therefor:

• a. Designed or modified for use in space launch vehicles specified in 9A004, sounding rockets specified in 9A104 or unmanned aerial vehicles specified in 9A012 or 9A112.a.; or

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

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

• 1. Employing decryption, designed or modified for military or governmental services, to gain access to a ‘navigation satellite system’ secured signal/data; or

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

• Note: 7A105.b.2. and 7A105.b.3. do not control equipment designed for commercial, civil or ‘Safety of Life’ (e.g., data integrity, flight safety) ‘navigation satellite system’ services.

Technical Note:

In 7A105, ‘navigation satellite system’ includes Global Navigation Satellite Systems (GNSS; e.g., GPS, GLONASS, Galileo or BeiDou) and Regional Navigation Satellite Systems (RNSS; e.g., NavIC, QZSS).

7A106 Altimeters, other than those specified in 7A006, of radar or laser radar type, designed or modified for use in space launch vehicles specified in 9A004 or sounding rockets specified in 9A104.

7A115 Passive sensors for determining bearing to specific electromagnetic source (direction finding equipment) or terrain characteristics, designed or modified for use in space launch vehicles specified in 9A004 or sounding rockets specified in 9A104.

• Note: Equipment specified in 7A105, 7A106, and 7A115 includes the following:

• a. Terrain contour mapping equipment;

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

• c. Doppler navigation radar equipment;

• d. Passive interferometer equipment;

• e. Imaging sensor equipment (both active and passive).

7A116 Flight control systems and servo valves, as follows; designed or modified for use in space launch vehicles specified in 9A004, sounding rockets specified in 9A104 or "missiles".

• a. Pneumatic, hydraulic, mechanical, electro-optical, or electro-mechanical flight control systems (including fly-by-wire and fly-by-light systems);

• b. Attitude control equipment;

• c. Flight control servo valves designed or modified for the systems specified in 7A116.a. or 7A116.b., and designed or modified to operate in a vibration environment greater than 10 g rms between 20 Hz and 2 kHz.

• Note: For conversion of manned aircraft to operate as "missiles", 7A116 includes the systems, equipment and valves designed or modified to enable operation of manned aircraft as unmanned aerial vehicles.

7A117

"Guidance sets", usable in "missiles" capable of achieving system accuracy of 3,33 % or less of the range (e.g., a ‘CEP’ of 10 km or less at a range of 300 km).

Technical Note:

In 7A117 ‘CEP’ (Circular Error Probable or Circle of Equal Probability) is a measure of accuracy, defined as the radius of the circle centred at the target, at a specific range, in which 50 % of the payloads impact.

7B Test, Inspection and Production Equipment

7B001 Test, calibration or alignment equipment, specially designed for equipment specified in 7A.

• Note: 7B001 does not control test, calibration or alignment equipment for ‘Maintenance Level I’ or ‘Maintenance Level II’.

Technical Notes:

• 1. ‘ Maintenance Level I ’

The failure of an inertial navigation unit is detected on the "aircraft" by indications from the Control and Display Unit (CDU) or by the status message from the corresponding sub-system. By following the manufacturer's manual, the cause of the failure may be localised at the level of the malfunctioning Line Replaceable Unit (LRU). The operator then removes the LRU and replaces it with a spare.

• 2. ‘ Maintenance Level II ’

The defective LRU is sent to the maintenance workshop (the manufacturer's or that of the operator responsible for level II maintenance). At the maintenance workshop, the malfunctioning LRU is tested by various appropriate means to verify and localise the defective Shop Replaceable Assembly (SRA) module responsible for the failure. This SRA is removed and replaced by an operative spare. The defective SRA (or possibly the complete LRU) is then shipped to the manufacturer. ‘Maintenance Level II’ does not include the disassembly or repair of controlled accelerometers or gyro sensors.

7B002 Equipment specially designed to characterize mirrors for ring "laser" gyros, as follows:

• N.B. SEE ALSO 7B102.

• a. Scatterometers having a measurement "accuracy" of 10 ppm or less (better);

• b. Profilometers having a measurement "accuracy" of 0,5 nm (5 angstrom) or less (better).

7B003 Equipment specially designed for the "production" of equipment specified in 7A.

• Note: 7B003 includes:

• — Gyro tuning test stations;

• — Gyro dynamic balance stations;

• — Gyro run-in/motor test stations;

• — Gyro evacuation and fill stations;

• — Centrifuge fixtures for gyro bearings;

• — Accelerometer axis align stations;

• — Fibre optic gyro coil winding machines.

7B102 Reflectometers specially designed to characterise mirrors, for "laser" gyros, having a measurement accuracy of 50 ppm or less (better).

7B103

"Production facilities" and "production equipment" as follows:

• a. "Production facilities" specially designed for equipment specified in 7A117;

• b. "Production equipment", and other test, calibration and alignment equipment, other than that specified in 7B001 to 7B003, designed or modified to be used with equipment specified in 7A.

7C Materials

None.

7D Software

7D001

"Software" specially designed or modified for the "development" or "production" of equipment specified in 7A or 7B.

7D002

"Source code" for the operation or maintenance of any inertial navigation equipment, including inertial equipment not specified in 7A003 or 7A004, or Attitude and Heading Reference Systems (‘AHRS’).

• Note: 7D002 does not control "source code" for the "use" of gimballed ‘AHRS’.

Technical Note:

‘AHRS’ generally differ from Inertial Navigation Systems (INS) in that an ‘AHRS’ provides attitude and heading information and normally does not provide the acceleration, velocity and position information associated with an INS.

7D003 Other "software" as follows:

• a. "Software" specially designed or modified to improve the operational performance or reduce the navigational error of systems to the levels specified in 7A003, 7A004 or 7A008;

- b. "Source code" for hybrid integrated systems which improves the operational performance or reduces the navigational error of systems to the level specified in 7A003 or 7A008 by continuously combining heading data with any of the following:

- 1. Doppler radar or sonar velocity data;

- 2. "Satellite navigation system" reference data; or

- 3. Data from "Data-Based Referenced Navigation" ("DBRN") systems;

• c. Not used;

• d. Not used;

• e. 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", whose "technology" is specified in 7E004.b.1., 7E004.b.3. to 7E004.b.5., 7E004.b.7., 7E004.b.8., 7E004.c.1. or 7E004.c.2.

7D004

"Source code" incorporating "development" "technology" specified in 7E004.a.2., 7E004.a.3., 7E004.a.5., 7E004.a.6. or 7E004.b., for any of the following:

• a. Digital flight management systems for "total control of flight";

• b. Integrated propulsion and flight control systems;

• c. "Fly-by-wire systems" or "fly-by-light systems";

• d. Fault-tolerant or self-reconfiguring "active flight control systems";

• e. Not used;

• f. Air data systems based on surface static data; or

• g. Three dimensional displays.

• Note: 7D004. does not control "source code" associated with common computer elements and utilities (e.g., input signal acquisition, output signal transmission, computer program and data loading, built-in test, task scheduling mechanisms) not providing a specific flight control system function.

7D005

"Software" specially designed to decrypt "satellite navigation system" ranging code designed for government use.

7D101

"Software" specially designed or modified for the "use" of equipment specified in 7A001 to 7A006, 7A101 to 7A106, 7A115, 7A116.a., 7A116.b., 7B001, 7B002, 7B003, 7B102 or 7B103.

7D102 Integration "software" as follows:

• a. Integration "software" for the equipment specified in 7A103.b.;

• b. Integration "software" specially designed for the equipment specified in 7A003 or 7A103.a.;

• c. Integration "software" designed or modified for the equipment specified in 7A103.c.

• Note: A common form of integration "software" employs Kalman filtering.

7D103

"Software" specially designed for modelling or simulation of the "guidance sets" specified in 7A117 or for their design integration with the space launch vehicles specified in 9A004 or sounding rockets specified in 9A104.

• Note: "Software" specified in 7D103 remains controlled when combined with specially designed hardware specified in 4A102.

7D104

"Software" specially designed or modified for the operation or maintenance of "guidance sets" specified in 7A117.

• Note: 7D104 includes ″software″, specially designed or modified to enhance the performance of ″guidance sets″ to achieve or exceed the accuracy specified in 7A117.

7E Technology

7E001

"Technology" according to the General Technology Note for the "development" of equipment or "software", specified in 7A, 7B, 7D001, 7D002, 7D003, 7D005 and 7D101 to 7D103.

• Note: 7E001 includes key management "technology" exclusively for equipment specified in 7A005.a.

7E002

"Technology" according to the General Technology Note for the "production" of equipment specified in 7A or 7B.

7E003

"Technology" according to the General Technology Note for the repair, refurbishing or overhaul of equipment specified in 7A001 to 7A004.

• Note: 7E003 does not control "technology" for maintenance, directly associated with calibration, removal or replacement of damaged or unserviceable LRUs and SRAs of a "civil aircraft" as described in ‘Maintenance Level I’ or ‘Maintenance Level II’.

• N.B. See Technical Notes to 7B001.

7E004 Other "technology" as follows:

• a. "Technology" for the "development" or "production" of any of the following:

• 1. Not used;

• 1. Air data systems based on surface static data only, i.e., which dispense with conventional air data probes;

• 1. Three dimensional displays for "aircraft";

• 1. Not used;

• 1. Electric actuators (i.e., electromechanical, electrohydrostatic and integrated actuator package) specially designed for ‘primary flight control’;

Technical Note:

‘Primary flight control’ is "aircraft" stability or manoeuvring control using force/moment generators, i.e. aerodynamic control surfaces or propulsive thrust vectoring.

• 1. ‘Flight control optical sensor array’ specially designed for implementing "active flight control systems"; or

Technical Note:

A ‘flight control optical sensor array’ is a network of distributed optical sensors, using "laser" beams, to provide real-time flight control data for on-board processing.

• 1. "DBRN" systems designed to navigate underwater, using sonar or gravity databases, that provide a positioning "accuracy" equal to or less (better) than 0,4 nautical miles;

• b. "Development""technology", as follows, for "active flight control systems" (including "fly-by-wire systems" or "fly-by-light systems"):

• 1. Photonic-based "technology" for sensing "aircraft" or flight control component state, transferring flight control data, or commanding actuator movement, "required" for "fly-by-light systems""active flight control systems";

• 1. Not used;

• 1. Real-time algorithms to analyse component sensor information to predict and preemptively mitigate impending degradation and failures of components within an "active flight control system";

• Note: 7E004.b.3. does not control algorithms for purpose of off-line maintenance.

• 1. Real-time algorithms to identify component failures and reconfigure force and moment controls to mitigate "active flight control system" degradations and failures;

• Note: 7E004.b.4. does not control algorithms for the elimination of fault effects through comparison of redundant data sources, or off-line pre-planned responses to anticipated failures.

• 1. Integration of digital flight control, navigation and propulsion control data, into a digital flight management system for "total control of flight";

• Note: 7E004.b.5. does not control:

• a. "Technology" for integration of digital flight control, navigation and propulsion control data, into a digital flight management system for ‘flight path optimisation’;

• b. "Technology" for "aircraft" flight instrument systems integrated solely for VOR, DME, ILS or MLS navigation or approaches.

Technical Note:

‘Flight path optimisation’ is a procedure that minimises deviations from a four-dimensional (space and time) desired trajectory based on maximising performance or effectiveness for mission tasks.

• 1. Not used;

• 1. "Technology""required" for deriving the functional requirements for "fly-by-wire systems" having all of the following:

• a. ‘Inner-loop’ airframe stability controls requiring loop closure rates of 40 Hz or greater; and

Technical Note:

‘Inner-loop’ refers to functions of "active flight control systems" that automate airframe stability controls.

• b. Having any of the following:

• 1. Corrects an aerodynamically unstable airframe, measured at any point in the design flight envelope, that would lose recoverable control if not corrected within 0,5 seconds;

• 1. Couples controls in two or more axes while compensating for ‘abnormal changes in aircraft state’;

Technical Note:

‘Abnormal changes in aircraft state’ include in-flight structural damage, loss of engine thrust, disabled control surface, or destabilising shifts in cargo load.

• 1. Performs the functions specified in 7E004.b.5.; or

• Note: 7E004.b.7.b.3. does not control autopilots.

• 1. Enables "aircraft" to have stable controlled flight, other than during take-off or landing, at greater than 18 degrees angle of attack, 15 degrees side slip, 15 degrees/second pitch or yaw rate, or 90 degrees/second roll rate;

• 1. "Technology""required" for deriving the functional requirements for "fly-by-wire systems" to achieve all of the following:

• a. No loss of control of the "aircraft" in the event of a consecutive sequence of any two individual faults within the "fly-by-wire system"; and

• b. Probability of loss of control of the "aircraft" being less (better) than 1 × 10^–9 failures per flight hour;

• Note: 7E004.b. does not control "technology" associated with common computer elements and utilities (e.g., input signal acquisition, output signal transmission, computer program and data loading, built-in test, task scheduling mechanisms) not providing a specific flight control system function.

• c. "Technology" for the "development" of helicopter systems, as follows:

• 1. Multi-axis fly-by-wire or fly-by-light controllers, which combine the functions of at least two of the following into one controlling element:

• a. Collective controls;

• b. Cyclic controls;

• c. Yaw controls;

• 1. "Circulation-controlled anti-torque or circulation-controlled direction control systems";

• 1. Rotor blades incorporating ‘variable geometry aerofoils’, for use in systems using individual blade control.

Technical Note:

‘Variable geometry aerofoils’ use trailing edge flaps or tabs, or leading edge slats or pivoted nose droop, the position of which can be controlled in flight.

7E101

"Technology" according to the General Technology Note for the "use" of equipment specified in 7A001 to 7A006, 7A101 to 7A106, 7A115 to 7A117, 7B001, 7B002, 7B003, 7B102, 7B103, 7D101 to 7D103.

7E102

"Technology" for protection of avionics and electrical subsystems against electromagnetic pulse (EMP) and electromagnetic interference (EMI) hazards, from external sources, as follows:

• a. Design "technology" for shielding systems;

• b. Design "technology" for the configuration of hardened electrical circuits and subsystems;

• c. Design "technology" for the determination of hardening criteria of 7E102.a. and 7E102.b.

7E104

"Technology" for the integration of the flight control, guidance, and propulsion data into a flight management system for optimisation of rocket system trajectory.

PART X

Category 8

CATEGORY 8 - MARINE

8A Systems, Equipment and Components

8A001 Submersible vehicles and surface vessels, as follows:

• N.B. For the control status of equipment for submersible vehicles, see:

• — Category 6 for sensors;

• — Categories 7 and 8 for navigation equipment;

• — Category 8A for underwater equipment.

• a. Manned, tethered submersible vehicles designed to operate at depths exceeding 1 000 m;

• b. Manned, untethered submersible vehicles having any of the following:

• 1. Designed to ‘operate autonomously’ and having a lifting capacity of all of the following:

• a. 10 % or more of their weight in air; and

• b. 15 kN or more;

• 1. Designed to operate at depths exceeding 1 000 m; or

• 1. Having all of the following:

• a. Designed to continuously ‘operate autonomously’ for 10 hours or more; and

• b. ‘Range’ of 25 nautical miles or more;

Technical Notes:

• 1. For the purposes of 8A001.b., ‘operate autonomously’ means fully submerged, without snorkel, all systems working and cruising at minimum speed at which the submersible can safely control its depth dynamically by using its depth planes only, with no need for a support vessel or support base on the surface, sea-bed or shore, and containing a propulsion system for submerged or surface use.

• 2. For the purposes of 8A001.b., ‘range’ means half the maximum distance a submersible vehicle can ‘operate autonomously’.

• c. Unmanned submersible vehicles, as follows:

- 1. Unmanned submersible vehicles having any of the following:

• a. Designed for deciding a course relative to any geographical reference without real-time human assistance;

- b. Acoustic data or command link; or

• c. Optical data or command link exceeding 1 000 m;

• 1. Unmanned submersible vehicles, not specified in 8A001.c.1., having all of the following:

• a. Designed to operate with a tether;

• b. Designed to operate at depths exceeding 1 000 m;

• c. Having any of the following:

• 1. Designed for self-propelled manoeuvre using propulsion motors or thrusters specified in 8A002.a.2.; or

- 2. Fibre optic data link;

• d. Not used;

• e. Ocean salvage systems with a lifting capacity exceeding 5 MN for salvaging objects from depths exceeding 250 m and having any of the following:

- 1. Dynamic positioning systems capable of position keeping within 20 m of a given point provided by the navigation system; or

• 1. Seafloor navigation and navigation integration systems, for depths exceeding 1 000 m and with positioning "accuracies" to within 10 m of a predetermined point;

• f. Not used;

• g. Not used;

• h. Not used;

• i. Not used.

8A002 Marine 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:

• 1. Pressure housings or pressure hulls with a maximum inside chamber diameter exceeding 1,5 m;

• 1. Direct current propulsion motors or thrusters;

• 1. Umbilical cables, and connectors therefor, using optical fibre and having synthetic strength members;

• 1. Components manufactured from material specified in 8C001;

Technical Note:

The objective of 8A002.a.4. should not be defeated by the export of ‘syntactic foam’ specified in 8C001 when an intermediate stage of manufacture has been performed and it is not yet in the final component form.

• 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:

• 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;

- c. Fibre optic pressure hull penetrators;

- d. Underwater vision systems having all of the following:

• 1. Specially designed or modified for remote operation with an underwater vehicle; and

• 1. Employing any of the following techniques to minimise the effects of back scatter:

• 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:

• 1. Stroboscopic light systems capable of a light output energy of more than 300 J per flash and a flash rate of more than 5 flashes per second;

• 1. Argon arc light systems specially designed for use below 1 000 m;

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

• 1. 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

• 1. 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;

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

• 1. Systems which control the manipulator using information from sensors which measure 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

• 1. Controlled by proportional master-slave techniques and having 5 degrees of ‘freedom of movement’ or more;

Technical Note:

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:

• 1. Brayton or Rankine cycle engine air independent power systems having any 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; or

• d. Systems having all of the following:

• 1. Specially designed to pressurise the products of reaction or for fuel reformation;

• 1. Specially designed to store the products of the reaction; and

• 1. Specially designed to discharge the products of the reaction against a pressure of 100 kPa or more;

• 1. Diesel cycle engine air independent 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;

• 1. "Fuel cell" air independent power systems with an output exceeding 2 kW and having any 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; or

• b. Systems having all of the following:

• 1. Specially designed to pressurise the products of reaction or for fuel reformation;

• 1. Specially designed to store the products of the reaction; and

• 1. Specially designed to discharge the products of the reaction against a pressure of 100 kPa or more;

• 1. 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;

• k. Not used;

• l. Not used;

• m. Not used;

• n. Not used;

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

• 1. Not used

• 1. Water-screw propeller, power generation systems or transmission systems, designed for use on vessels, as follows:

• a. Controllable-pitch propellers and hub assemblies, rated at more than 30 MW;

• b. Internally liquid-cooled electric propulsion engines with a power output exceeding 2,5 MW;

• c. "Superconductive" propulsion engines or permanent magnet electric propulsion engines, with a power output exceeding 0,1 MW;

• d. Power transmission shaft systems incorporating "composite" material components and capable of transmitting more than 2 MW;

• e. Ventilated or base-ventilated propeller systems, rated at more than 2,5 MW;

• 1. 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.

• p. Pumpjet propulsion systems having all of the following:

• 1. Power output exceeding 2,5 MW; and

• 1. Using divergent nozzle and flow conditioning vane techniques to improve propulsive efficiency or reduce propulsion-generated underwater-radiated noise;

• q. Underwater swimming and diving equipment as follows:

• 1. Closed circuit rebreathers;

• 1. Semi-closed circuit rebreathers;

• 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.

8B Test, Inspection and Production Equipment

8B001 Water 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.

8C Materials

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.

Technical Note:

‘Syntactic foam’ consists of hollow spheres of plastic or glass embedded in a resin "matrix".

8D Software

8D001

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

8D002 Specific "software" specially designed or modified for the "development", "production", repair, overhaul or refurbishing (re-machining) of propellers specially designed for underwater noise reduction.

8E Technology

8E001

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

8E002 Other "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:

• 1. Surface-effect vehicles (fully skirted variety) having all 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;

• 1. Surface-effect vehicles (rigid sidewalls) with a maximum design speed, fully loaded, exceeding 40 knots in a significant wave height of 3,25 m or more;

• 1. Hydrofoil vessels with active systems for automatically controlling foil systems, with a maximum design speed, fully loaded, of 40 knots or more in a significant wave height of 3,25 m or more; or

• 1. ‘Small waterplane area vessels’ having any of the following:

• 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:

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

9A Systems, Equipment and Components

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

9A001 Aero gas turbine engines having any of the following:

• N.B. SEE ALSO 9A101.

• a. Incorporating any of the "technologies" specified in 9E003.a., 9E003.h. or 9E003.i.; or

• Note 1: 9A001.a. does not control aero gas turbine engines which meet all of the following:

• a. Certified by the civil aviation authorities of one or more 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.a. 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. Designed to power an "aircraft" to cruise at Mach 1 or higher, for more than thirty minutes.

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.

Technical Note:

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).

9A003 Specially designed assemblies or components, incorporating any of the "technologies" specified in 9E003.a., 9E003.h. or 9E003.i., 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.

9A004 Space launch vehicles, "spacecraft", "spacecraft buses", "spacecraft payloads", "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";

• c. "Spacecraft buses";

• d. "Spacecraft payloads" 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:

• 1. ‘Command and telemetry data handling’;

• Note: For the purpose of 9A004.e.1., ‘command and telemetry data handling’ includes bus data management, storage, and processing.

• 1. ‘Payload data handling’; or

• Note: For the purpose of 9A004.e.2., ‘payload data handling’ includes payload data management, storage, and processing.

• 1. ‘Attitude and orbit control’;

• Note: For the purpose of 9A004.e.3., ‘attitude and orbit control’ includes sensing and actuation to determine and control the position and orientation of a "spacecraft".

• N.B. For equipment specially designed for military use, SEE MILITARY GOODS CONTROLS.

• f. Terrestrial equipment specially designed for "spacecraft", as follows:

• 1. Telemetry and telecommand equipment specially designed for any of the following data processing functions:

• 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";

• 1. Simulators specially designed for ‘verification of operational procedures’ of "spacecraft";

Technical Note:

For the purposes of 9A004.f.2., ‘verification of operational procedures’ is any of the following:

• 1. Command sequence confirmation;

• 2. Operational training;

• 3. Operational rehearsals; or

• 4. Operational analysis.

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

• h. "Sub-orbital craft".

9A005 Liquid rocket propulsion systems containing any of the systems or components, specified in 9A006.

• N.B. SEE ALSO 9A105 AND 9A119.

9A006 Systems and components, specially designed for liquid rocket propulsion systems, as follows:

• N.B. SEE ALSO 9A106, 9A108 AND 9A120.

• a. Cryogenic refrigerators, flightweight dewars, cryogenic heat pipes or cryogenic systems, specially designed for use in space vehicles and capable of restricting cryogenic fluid losses to less than 30 % per year;

• b. Cryogenic containers or closed-cycle refrigeration systems, capable of providing temperatures of 100 K (– 173 °C) or less for "aircraft" capable of sustained flight at speeds exceeding Mach 3, launch vehicles or "spacecraft";

• c. Slush hydrogen storage or transfer systems;

• d. High pressure (exceeding 17,5 MPa) turbo pumps, pump components or their associated gas generator or expander cycle turbine drive systems;

• 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.

9A007 Solid rocket propulsion systems having any of the following:

• N.B. SEE ALSO 9A107 AND 9A119.

• a. Total impulse capacity exceeding 1,1 MNs;

• b. Specific impulse of 2,4 kNs/kg or more, when the nozzle flow is expanded to ambient sea level conditions for an adjusted chamber pressure of 7 MPa;

• c. Stage mass fractions exceeding 88 % and propellant solid loadings exceeding 86 %;

• d. Components specified in 9A008; or

• e. Insulation and propellant bonding systems, using direct-bonded motor designs to provide a ‘strong mechanical bond’ or a barrier to chemical migration between the solid propellant and case insulation material.

Technical Note:

‘Strong mechanical bond’ means bond strength equal to or more than propellant strength.

9A008 Components specially designed for solid rocket propulsion systems, as follows:

• N.B. SEE ALSO 9A108.

• a. Insulation and propellant bonding systems, using liners to provide a ‘strong mechanical bond’ or a barrier to chemical migration between the solid propellant and case insulation material;

Technical Note:

‘Strong mechanical bond’ means bond strength equal to or more than propellant strength.

• 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^o;

• 1. Angular vector rotations of 20^o/s or more; or

• 1. Angular vector accelerations of 40^o/s² or more.

9A009 Hybrid rocket propulsion systems having any of the following:

• N.B. SEE ALSO 9A109 AND 9A119.

• a. Total impulse capacity exceeding 1,1 MNs; or

• b. Thrust levels exceeding 220 kN in vacuum exit conditions.

9A010 Specially designed components, systems and structures, for launch vehicles, launch vehicle propulsion systems or "spacecraft", as follows:

• N.B. SEE ALSO 1A002 AND 9A110.

• a. Components and structures, each exceeding 10 kg and specially designed for launch vehicles manufactured using any of the following:

• 1. "Composite" materials consisting of "fibrous or filamentary materials" specified in 1C010.e. and resins specified in 1C008 or 1C009.b.;

• 1. 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

• 1. Ceramic "matrix""composite" materials specified in 1C007;

• 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:

• 1. "Fibrous or filamentary materials" specified in 1C010.e. and resins specified in 1C008 or 1C009.b.;

• 1. 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

• 1. Ceramic "matrix""composite" materials specified in 1C007;

• 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.

9A011 Ramjet, scramjet or ‘combined cycle engines’, and specially designed components therefor.

• N.B. SEE ALSO 9A111 AND 9A118.

Technical Note:

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:

• 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

• 1. A maximum ‘endurance’ of 1 hour or greater;

Technical Notes: