LegalizeRegulation (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)
Wavelength equal to or greater than 1 900 nm and average or CW output power exceeding 10 W;
d. Semiconductor "laser" 'stacked arrays' (two-dimensional arrays) having any of the following:
Wavelength less than 1 400 nm and having any of the following:
a. Average or CW total output power less than 3 kW and having average or CW output 'power density' greater than 500 W/cm2; b. Average or CW total output power equal to or exceeding 3 kW but less than or equal to 5 kW, and having average or CW output 'power density' greater than 350 W/cm2; c. Average or CW total output power exceeding 5 kW; d. Peak pulsed 'power density' exceeding 2 500 W/cm2; or Note:
6A005.d.1.d.1.d. does not control epitaxially-fabricated monolithic devices. e. Spatially coherent average or CW total output power, greater than 150 W;
Wavelength greater than or equal to 1 400 nm but less than 1 900 nm, and having any of the following:
a. Average or CW total output power less than 250 W and average or CW output 'power density' greater than 150 W/cm2; b. Average or CW total output power equal to or exceeding 250 W but less than or equal to 500 W, and having average or CW output 'power density' greater than 50 W/cm2; c. Average or CW total output power exceeding 500 W; d. Peak pulsed 'power density' exceeding 500 W/cm2; or Note:
6A005.d.1.d.2.d. does not control epitaxially-fabricated monolithic devices. e. Spatially coherent average or CW total output power, exceeding 15 W;
Wavelength greater than or equal to 1 900 nm and having any of the following:
a. Average or CW output 'power density' greater than 50 W/cm2; b. Average or CW output power greater than 10 W; or c. Spatially coherent average or CW total output power, exceeding 1,5 W; or
At least one "laser" 'bar' specified in 6A005.d.1.c.;
Technical Note: For the purposes of 6A005.d.1.d., 'power density' means the total "laser" output power divided by the emitter surface area of the 'stacked array'. e. Semiconductor "laser" 'stacked arrays', other than those specified in 6A005.d.1.d., having all of the following:
Specially designed or modified to be combined with other 'stacked arrays' to form a larger 'stacked array'; and
Integrated connections, common for both electronics and cooling;
Note 1:
'Stacked arrays', formed by combining semiconductor "laser" 'stacked arrays' specified in 6A005.d.1.e., that are not designed to be further combined or modified are specified in 6A005.d.1.d. Note 2:
'Stacked arrays', formed by combining semiconductor "laser" 'stacked arrays' specified in 6A005.d.1.e., that are designed to be further combined or modified are specified in 6A005.d.1.e. Note 3:
6A005.d.1.e. does not control modular assemblies of single 'bars' designed to be fabricated into end-to-end stacked linear arrays.
Carbon monoxide (CO) "lasers" having any of the following:
a. Output energy exceeding 2 J per pulse and "peak power" exceeding 5 kW; or b. Average or CW output power exceeding 5 kW;
Carbon dioxide (CO2) "lasers" having any of the following:
a. CW output power exceeding 15 kW; b. Pulsed output with a "pulse duration" exceeding 10 μs and any of the following:
"Average output power" exceeding 10 kW; or
"Peak power" exceeding 100 kW; or
c. Pulsed output with a "pulse duration" equal to or less than 10 μs and any of the following:
Pulse energy exceeding 5 J per pulse; or
"Average output power" exceeding 2,5 kW;
Excimer "lasers" having any of the following:
a. Output wavelength not exceeding 150 nm and any of the following:
Output energy exceeding 50 mJ per pulse; or
"Average output power" exceeding 1 W;
b. Output wavelength exceeding 150 nm but not exceeding 190 nm and any of the following:
Output energy exceeding 1,5 J per pulse; or
"Average output power" exceeding 120 W;
c. Output wavelength exceeding 190 nm but not exceeding 360 nm and any of the following:
Output energy exceeding 10 J per pulse; or
"Average output power" exceeding 500 W; or
d. Output wavelength exceeding 360 nm and any of the following:
Output energy exceeding 1,5 J per pulse; or
"Average output power" exceeding 30 W;
N.B.
For excimer "lasers" specially designed for lithography equipment, see 3B001.
'Chemical lasers' as follows:
Technical Note: For the purposes of 6A005.d.5., 'chemical laser' is a "laser" in which the excited species is produced by the output energy from a chemical reaction. a. Hydrogen Fluoride (HF) "lasers"; b. Deuterium Fluoride (DF) "lasers"; c. 'Transfer lasers' as follows:
Oxygen Iodine (O2-I) "lasers";
Deuterium Fluoride-Carbon dioxide (DF-CO2) "lasers";
Technical Note: For the purposes of 6A005.d.5.c., 'transfer lasers' are "lasers" in which the lasing species are excited through the transfer of energy by collision of a non- lasing atom or molecule with a lasing atom or molecule species.
"Non-repetitive pulsed" Nd:glass "lasers" having any of the following:
a. "Pulse duration" not exceeding 1 μs and output energy exceeding 50 J per pulse; or b. "Pulse duration" exceeding 1 μs and output energy exceeding 100 J per pulse;
e. Components as follows:
Mirrors cooled either by 'active cooling' or by heat pipe cooling;
Technical Note: For the purposes of 6A005.e.1., 'active cooling' is a cooling technique for optical components using flowing fluids within the subsurface (nominally less than 1 mm below the optical surface) of the optical component to remove heat from the optic.
Optical mirrors or transmissive or partially transmissive optical or electro-optical components, other than fused tapered fibre combiners and Multi-Layer Dielectric gratings (MLDs), specially designed for use with specified "lasers";
Note:
Fibre combiners and MLDs are specified in 6A005.e.3.
Fibre "laser" components as follows:
a. Multimode to multimode fused tapered fibre combiners having all of the following:
An insertion loss better (less) than or equal to 0,3 dB maintained at a rated total average or CW output power (excluding output power transmitted through the single mode core if present) exceeding 1 000 W; and
Number of input fibres equal to or greater than 3;
b. Single mode to multimode fused tapered fibre combiners having all of the following:
An insertion loss better (less) than 0,5 dB maintained at a rated total average or CW output power exceeding 4 600 W;
Number of input fibres equal to or greater than 3; and
Having any of the following:
a. A Beam Parameter Product (BPP) measured at the output not exceeding 1,5 mm mrad for a number of input fibres less than or equal to 5; or b. A BPP measured at the output not exceeding 2,5 mm mrad for a number of input fibres greater than 5; c. MLDs having all of the following:
Designed for spectral or coherent beam combination of 5 or more fibre "lasers"; and
CW "Laser" Induced Damage Threshold (LIDT) greater than or equal to 10 kW/cm2;
f. Optical equipment as follows: N.B.
For shared aperture optical elements, capable of operating in "Super High Power Laser" ("SHPL") applications, see the Military Goods Controls.
Not used;
"Laser" diagnostic equipment specially designed for dynamic measurement of "SHPL" system angular beam steering errors and having an angular "accuracy" of 10 μrad (microradians) or less (better);
Optical equipment and components, specially designed for coherent beam combination in a phased-array "SHPL" system and having any of the following:
a. An "accuracy" of 0,1 μm or less (better), for wavelengths greater than 1 μm; or b. An "accuracy" of λ/10 or less (better) at the designed wavelength, for wavelengths equal to or less than 1 μm;
Projection telescopes specially designed for use with "SHPL" systems;
g. 'Laser acoustic detection equipment' having all of the following:
CW "laser" output power equal to or exceeding 20 mW;
"Laser" frequency stability equal to or less (better) than 10 MHz;
"Laser" wavelengths equal to or exceeding 1 000 nm but not exceeding 2 000 nm;
Optical system resolution less (better) than 1 nm; and
Optical Signal to Noise ratio equal to or exceeding 103.
Technical Note: For the purposes of 6A005.g., 'laser acoustic detection equipment' is sometimes referred to as a "Laser" Microphone or Particle Flow Detection Microphone.
6A006"Magnetometers", "magnetic gradiometers", "intrinsic magnetic gradiometers", underwater electric field sensors, "compensation systems", and specially designed components therefor, as follows:
N.B.
SEE ALSO 7A103.d.
Note:
6A006 does not control instruments specially designed for fishery applications or biomagnetic measurements for medical diagnostics.
a. "Magnetometers" and subsystems as follows:
"Magnetometers" using "superconductive" (SQUID) "technology" and having any of the following:
a. SQUID systems designed for stationary operation, without specially designed subsystems designed to reduce in-motion noise, and having a 'sensitivity' equal to or less (better) than 50 fT (rms) per square root Hz at a frequency of 1 Hz; or b. SQUID systems having an in-motion-magnetometer 'sensitivity' less (better) than 20 pT (rms) per square root Hz at a frequency of 1 Hz and specially designed to reduce in-motion noise;
"Magnetometers" using optically pumped or nuclear precession (proton/Overhauser) "technology" having a 'sensitivity' less (better) than 20 pT (rms) per square root Hz at a frequency of 1 Hz;
"Magnetometers" using fluxgate "technology" having a 'sensitivity' equal to or less (better) than 10 pT (rms) per square root Hz at a frequency of 1 Hz;
Induction coil "magnetometers" having a 'sensitivity' less (better) than any of the following:
a. 0,05 nT (rms) per square root Hz at frequencies of less than 1 Hz; b. 1 × 10-3 nT (rms) per square root Hz at frequencies of 1 Hz or more but not exceeding 10 Hz; or c. 1 × 10-4 nT (rms) per square root Hz at frequencies exceeding 10 Hz;
Fibre optic "magnetometers" having a 'sensitivity' less (better) than 1 nT (rms) per square root Hz;
b. Underwater electric field sensors having a 'sensitivity' less (better) than 8 nanovolt per metre per square root Hz when measured at 1 Hz;
c. "Magnetic gradiometers" as follows:
"Magnetic gradiometers" using multiple "magnetometers" specified in 6A006.a.;
Fibre optic "intrinsic magnetic gradiometers" having a magnetic gradient field 'sensitivity' less (better) than 0,3 nT/m rms per square root Hz;
"Intrinsic magnetic gradiometers", using "technology" other than fibre-optic "technology", having a magnetic gradient field 'sensitivity' less (better) than 0,015 nT/m rms per square root Hz;
d. "Compensation systems" for magnetic or underwater electric field sensors resulting in a performance equal to or better than the specified parameters of 6A006.a., 6A006.b. or 6A006.c.;
e. Underwater electromagnetic receivers incorporating magnetic field sensors specified in 6A006.a. or underwater electric field sensors specified in 6A006.b.
For the purposes of 6A006, 'sensitivity' (noise level) is the root mean square of the device-limited noise floor which is the lowest signal that can be measured.
6A007Gravity meters (gravimeters) and gravity gradiometers, as follows:
N.B.
SEE ALSO 6A107.
a. Gravity meters designed or modified for ground use and having a static "accuracy" of less (better) than 10 μGal; Note: 6A007.a. does not control ground gravity meters of the quartz element (Worden) type.
b. Gravity meters designed for mobile platforms and having all of the following:
A static "accuracy" of less (better) than 0,7 mGal; and
An in-service (operational) "accuracy" of less (better) than 0,7 mGal having a "time-to-steady-state registration" of less than 2 minutes under any combination of attendant corrective compensations and motional influences;
c. Gravity gradiometers.
6A008Radar systems, equipment and assemblies, having any of the following, and specially designed components therefor:
N.B.
SEE ALSO 6A108.
Note:
6A008 does not control:
— Secondary surveillance radar (SSR);
— Civil Automotive Radar;
— Displays or monitors used for air traffic control (ATC);
— Meteorological (weather) radar;
— Precision approach radar (PAR) equipment conforming to ICAO standards and employing electronically steerable linear (1-dimensional) arrays or mechanically positioned passive antennae.
a. Operating at frequencies from 40 GHz to 230 GHz and having any of the following:
An average output power exceeding 100 mW; or
Locating "accuracy" of 1 m or less (better) in range and 0,2 degree or less (better) in azimuth;
b. A “tunable” bandwidth exceeding ± 6,25 % of the 'centre operating frequency'; Technical Note: For the purposes of 6A008.b., the 'centre operating frequency' equals one half of the sum of the highest plus the lowest specified operating frequencies.
c. Capable of operating simultaneously on more than two carrier frequencies;
d. Capable of operating in synthetic aperture (SAR), inverse synthetic aperture (ISAR) radar mode, or sidelooking airborne (SLAR) radar mode;
e. Incorporating electronically scanned array antennae; Technical Note: For the purposes of 6A008.e., electronically scanned array antennae are also known as electronically steerable array antennae.
f. Capable of heightfinding non-cooperative targets;
g. Specially designed for airborne (balloon or airframe mounted) operation and having Doppler "signal processing" for the detection of moving targets;
h. Employing processing of radar signals and using any of the following:
"Radar spread spectrum" techniques; or
'Radar frequency agility' techniques;
Technical Note: For the purposes of 6A008.h., 'radar frequency agility' applies to any technique which changes, in a pseudo-random sequence, the carrier frequency of a pulsed radar transmitter between pulses or between groups of pulses by an amount equal to or larger than the pulse bandwidth.
i. Providing ground-based operation with a maximum 'instrumented range' exceeding 185 km; Note:
6A008.i. does not control: a. Fishing ground surveillance radar; b. Ground radar equipment specially designed for enroute air traffic control and having all the following: 1. A maximum 'instrumented range' of 500 km or less; 2. Configured so that radar target data can be transmitted only one way from the radar site to one or more civil ATC centres; 3. Contains no provisions for remote control of the radar scan rate from the enroute ATC centre; and 4. Permanently installed; c. Weather balloon tracking radars. Technical Note: For the purposes of 6A008.i. 'instrumented range' is the specified unambiguous display range of a radar.
j. Being "laser" radar or Light Detection and Ranging (LIDAR) equipment and having any of the following:
"Space-qualified";
Employing coherent heterodyne or homodyne detection techniques and having an angular resolution of less (better) than 20 μrad (microradians); or
Designed for carrying out airborne bathymetric littoral surveys to International Hydrographic Organization (IHO) Order 1a Standard (5th Edition February 2008) for Hydrographic Surveys or better, and using one or more "lasers" with a wavelength exceeding 400 nm but not exceeding 600 nm;
Note 1:
LIDAR equipment specially designed for surveying is only specified in 6A008.j.3. Note 2:
6A008.j. does not control LIDAR equipment specially designed for meteorological observation. Note 3:
Parameters in the IHO Order 1a Standard (5th Edition February 2008) are summarised as follows: — Horizontal Accuracy (95 % Confidence Level) = 5 m + 5 % of depth. — Depth Accuracy for Reduced Depths (95 % confidence level) = ±√(a2+(b × d)2), where: a = 0,5 m = constant depth error, i.e., the sum of all constant depth errors b = 0,013 = factor of depth dependent error b × d = depth dependent error, i.e., the sum of all depth dependent errors d = depth — Feature Detection = Cubic features > 2 m in depths up to 40 m; 10 % of depth beyond 40 m.
k. Having "signal processing" sub-systems using "pulse compression" and having any of the following:
A "pulse compression" ratio exceeding 150; or
A compressed pulse width of less than 200 ns; or
Note:
6A008.k.2. does not control two dimensional 'marine radar' or 'vessel traffic service' radar, having all of the following; a. "Pulse compression" ratio not exceeding 150; b. Compressed pulse width of greater than 30 ns; c. Single and rotating mechanically scanned antenna; d. Peak output power not exceeding 250 W; and e. Not capable of "frequency hopping".
l. Having data processing sub-systems and having any of the following:
'Automatic target tracking' providing, at any antenna rotation, the predicted target position beyond the time of the next antenna beam passage; or
Note:
6A008.l.1. does not control conflict alert capability in ATC systems, or 'marine radar'. Technical Note: For the purposes of 6A008.l.1., 'automatic target tracking' is a processing technique that automatically determines and provides as output an extrapolated value of the most probable position of the target in real time.
Not used;
Not used;
Configured to provide superposition and correlation, or fusion, of target data within six seconds from two or more 'geographically dispersed' radar sensors to improve the aggregate performance beyond that of any single sensor specified in 6A008.f. or 6A008.i.
Technical Note: For the purposes of 6A008.l.4., sensors are considered 'geographically dispersed' when each location is distant from any other more than 1 500 m in any direction. Mobile sensors are always considered 'geographically dispersed'. N.B.
See also Military Goods Controls. Note:
6A008.l.4. does not control systems, equipment and assemblies designed for 'vessel traffic service'.
For the purposes of 6A008:
1.
'Marine radar' is a radar that is designed to navigate safely at sea, inland waterways or near-shore environments.
2.
'Vessel traffic service' is a vessel traffic monitoring and control service similar to air traffic control for "aircraft".
6A102Radiation hardened 'detectors', other than those specified in 6A002, specially designed or modified for protecting against nuclear effects (e.g. electromagnetic pulse (EMP), X-rays, combined blast and thermal effects) and usable for "missiles", designed or rated to withstand radiation levels which meet or exceed a total irradiation dose of 5 × 105 rads (silicon).
In 6A102, a 'detector' is defined as a mechanical, electrical, optical or chemical device that automatically identifies and records, or registers a stimulus such as an environmental change in pressure or temperature, an electrical or electromagnetic signal or radiation from a radioactive material. This includes devices that sense by one time operation or failure.
6A107Gravity meters (gravimeters) and components for gravity meters and gravity gradiometers, as follows:
a. Gravity meters, other than those specified in 6A007.b., designed or modified for airborne or marine use, and having a static or operational accuracy equal to or less (better) than 0,7 milligal (mgal), and having a time-to-steady-state registration of two minutes or less;
b. Specially designed components for gravity meters specified in 6A007.b. or 6A107.a. and gravity gradiometers specified in 6A007.c.
6A108Radar systems, tracking systems and radomes, other than those specified in entry 6A008, as follows:
a. Radar and laser radar systems designed or modified for use in space launch vehicles specified in 9A004 or sounding rockets specified in 9A104; Note:
6A108.a. 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).
b. Precision tracking systems, usable for 'missiles', as follows:
Tracking systems which use a code translator in conjunction with either surface or airborne references or navigation satellite systems to provide real-time measurements of in-flight position and velocity;
Range instrumentation radars including associated optical/infrared trackers with all of the following capabilities:
a. Angular resolution better than 1,5 milliradians; b. Range of 30 km or greater with a range resolution better than 10 m rms; and c. Velocity resolution better than 3 m/s; Technical Note: In 6A108.b. 'missile' means complete rocket systems and unmanned aerial vehicle systems capable of a range exceeding 300 km.
c. Radomes designed to withstand a combined thermal shock greater than 4,184 × 106 J/m2 accompained by a peak over pressure of greater than 50 kPa, and usable in "missiles" for protecting against nuclear effects (e.g. electromagnetic pulse (EMP), X-rays, combined blast and thermal effects).
6A202Photomultiplier tubes having both of the following characteristics:
a. Photocathode area of greater than 20 cm2; and
b. Anode pulse rise time of less than 1 ns.
6A203Cameras and components, other than those specified in 6A003, as follows:
N.B.1.
"Software" specially designed to enhance or release the performance of a camera or imaging device to meet the characteristics of 6A203.a., 6A203.b. or 6A203.c. is specified in 6D203.
N.B.2.
"Technology" in the form of codes or keys to enhance or release the performance of a camera or imaging device to meet the characteristics of 6A203.a., 6A203.b. or 6A203.c. is specified in 6E203.
Note:
6A203.a. to 6A203.c. does not control cameras or imaging devices if they have hardware, "software" or "technology" constraints that limit the performance to less than that specified below, provided they meet any of the following:
1. They need to be returned to the original manufacturer to make the enhancements or release the constraints;
2. They require "software" as specified in 6D203 to enhance or release the performance to meet the characteristics of 6A203; or
3. They require "technology" in the form of keys or codes as specified in 6E203 to enhance or release the performance to meet the characteristics of 6A203.
a. Streak cameras, and specially designed components therefor, as follows:
Streak cameras with writing speeds greater than 0,5 mm/μs;
Electronic streak cameras capable of 50 ns or less time resolution;
Streak tubes for cameras specified in 6A203.a.2.;
Plug-ins specially designed for use with streak cameras which have modular structures and that enable the performance specifications in 6A203.a.1. or 6A203.a.2.;
Synchronizing electronics units, rotor assemblies consisting of turbines, mirrors and bearings specially designed for cameras specified in 6A203.a.1.;
b. Framing cameras, and specially designed components therefor, as follows:
Framing cameras with recording rates greater than 225 000 frames per second;
Framing cameras capable of 50 ns or less frame exposure time;
Framing tubes and solid-state imaging devices having a fast image gating (shutter) time of 50 ns or less specially designed for cameras specified in 6A203.b.1. or 6A203.b.2.;
Plug-ins specially designed for use with framing cameras which have modular structures and that enable the performance specifications in 6A203.b.1. or 6A203.b.2.;
Synchronizing electronics units, rotor assemblies consisting of turbines, mirrors and bearings specially designed for cameras specified in 6A203.b.1. or 6A203.b.2.;
Technical Note: In 6A203.b., high speed single frame cameras can be used alone to produce a single image of a dynamic event, or several such cameras can be combined in a sequentially-triggered system to produce multiple images of an event.
c. Solid-state or electron tube cameras, and specially designed components therefor, as follows:
Solid-state cameras or electron tube cameras with a fast image gating (shutter) time of 50 ns or less;
Solid-state imaging devices and image intensifiers tubes having a fast image gating (shutter) time of 50 ns or less specially designed for cameras specified in 6A203.c.1.;
Electro-optical shuttering devices (Kerr or Pockels cells) with a fast image gating (shutter) time of 50 ns or less;
Plug-ins specially designed for use with cameras which have modular structures and that enable the performance specifications in 6A203.c.1.
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:
Operating at wavelengths between 400 nm and 515 nm; and
An "average output power" greater than 40 W;
b. Tunable pulsed single-mode dye laser oscillators having all of the following characteristics:
Operating at wavelengths between 300 nm and 800 nm;
An "average output power" greater than 1 W;
A repetition rate greater than 1 kHz; and
Pulse width less than 100 ns;
c. Tunable pulsed dye laser amplifiers and oscillators, having all of the following characteristics:
Operating at wavelengths between 300 nm and 800 nm;
An "average output power" greater than 30 W;
A repetition rate greater than 1 kHz; and
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:
Operating at wavelengths between 9 000 nm and 11 000 nm;
A repetition rate greater than 250 Hz;
An "average output power" greater than 500 W; and
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:
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
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:
Operating at wavelengths between 5 000 and 6 000 nm;
A repetition rate greater than 250 Hz;
An "average output power" greater than 200 W; and
Pulse width of less than 200 ns.
6A225Velocity 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), PDV (Photonic Doppler Velocimeters) also known as Het-V (Heterodyne Velocimeters) and microwave velocity interferometers including optic-microvawe mixing velocimeters.
6A226Pressure 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.
6B002Masks and reticles, specially designed for optical sensors specified in 6A002.a.1.b. or 6A002.a.1.d.
6B004Optical equipment as follows:
a. Equipment for measuring absolute reflectance to an "accuracy" of equal to or less (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.
6B007Equipment to produce, align and calibrate land-based gravity meters with a static "accuracy" of less (better) than 0,1 mGal.
6B008Pulse radar cross-section measurement systems having transmit pulse widths of 100 ns or less, and specially designed components therefor.
N.B.
SEE ALSO 6B108.
6B108Systems, other than those specified in 6B008, specially designed for radar cross section measurement usable for 'missiles' and their subsystems.
In 6B108 'missile' means complete rocket systems and unmanned aerial vehicle systems capable of a range exceeding 300 km.
6C002Optical 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:
Cadmium zinc telluride (CdZnTe), with zinc content of less than 6 % by 'mole fraction';
Cadmium telluride (CdTe) of any purity level; or
Mercury cadmium telluride (HgCdTe) of any purity level.
Technical Note: For the purposes of 6C002.b.1., 'mole fraction' is defined as the ratio of moles of ZnTe to the sum of moles of CdTe and ZnTe present in the crystal.
6C004Optical 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:
A volume greater than 100 cm3; or
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:
Potassium titanyl arsenate (KTA) (CAS 59400-80-5);
Silver gallium selenide (AgGaSe2, also known as AGSE) (CAS 12002-67-4);
Thallium arsenic selenide (Tl3AsSe3 , also known as TAS) (CAS 16142-89-5);
Zinc germanium phosphide (ZnGeP2, also known as ZGP, zinc germanium biphosphide or zinc germanium diphosphide);
Gallium selenide (GaSe) (CAS 12024-11-2);
c. Non-linear optical materials, other than those specified in 6C004.b., having any of the following:
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
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:
A hydroxyl ion (OH-) concentration of less than 5 ppm;
Integrated metallic purity levels of less than 1 ppm; and
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:
Titanium doped sapphire;
Not used.
b. Rare-earth-metal doped double-clad fibres having any of the following:
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.
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. Note:
6C005.b. includes fibres assembled with end caps. Technical Note: For the purposes of 6C005.b., the core 'Numerical Aperture' ('NA') is measured at the emission wavelengths of the fibre.
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.
6D003Other "software" as follows:
a. "Software" as follows:
"Software" specially designed for acoustic beam forming for the "real-time processing" of acoustic data for passive reception using towed hydrophone arrays;
"Source code" for the "real-time processing" of acoustic data for passive reception using towed hydrophone arrays;
"Software" specially designed for acoustic beam forming for "real-time processing" of acoustic data for passive reception using bottom or bay cable systems;
"Source code" for "real-time processing" of acoustic data for passive reception using bottom or bay cable systems;
"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:
"Software" specially designed for magnetic and electric field "compensation systems" for magnetic sensors designed to operate on mobile platforms;
"Software" specially designed for magnetic and electric field anomaly detection on mobile platforms;
"Software" specially designed for "real-time processing" of electromagnetic data using underwater electromagnetic receivers specified in 6A006.e.;
"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:
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;
"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: For the purposes of 6D003.h.2.b., 'average side lobe level' 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'.
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.
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.
6E003Other "technology" as follows:
a. "Technology" as follows:
"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: For the purposes of 6E003.a.1., 'optical thickness' is the mathematical product of the index of refraction and the physical thickness of the coating.
"Technology" for the fabrication of optics using single point diamond turning techniques to produce surface finish "accuracies" of less (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
N.B.
For automatic pilots for submersible vehicles, see Category 8.
For radar, see Category 6.
7A001Accelerometers 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:
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;
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
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.
7A002Gyros 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:
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".
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:
7A003. does not apply to '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.
For the purposes of 7A003:
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).
2.
'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:
0,8 nautical miles per hour (nm/hr) "Circular Error Probable" ("CEP") rate or less (better);
0,5 % distanced travelled "CEP" or less (better); or
Total drift of 1 nautical mile "CEP" or less (better) in a 24 hr period;
Technical Note: For the purposes of 7A003.a.1., 7A003.a.2. and 7A003.a.3., the performance parameters 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"; 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:
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
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:
Performance specified in 7A001 or 7A002 along any axis, without the use of any aiding references; or
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:
Optical heads or baffles;
Data processing units.
For the purposes of 7A004.a., '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.
7A006Airborne 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: For the purposes of 7A006.a., '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.
7A008Underwater 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.
For acoustic systems, see 6A001.a., and for correlation-velocity and Doppler-velocity sonar log equipment, see 6A001.b.
For other marine systems, see 8A002.
7A101Linear 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.
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;
7A102All types of gyros, other than those specified in 7A002, usable in 'missiles', with a rated "drift rate" 'stability' of less than 0,5° (1 sigma or rms) per hour in a 1 g environment and specially designed components therefor.
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).
7A103Instrumentation, 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:
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.
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:
Internal tilt compensation in pitch (± 90 degrees) and roll (± 180 degrees) axes; and
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.
In 7A103 'missile' means complete rocket systems and unmanned aerial vehicle systems capable of a range exceeding 300 km.
7A104Gyro-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.
7A105Receiving 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:
Capable of providing navigation information at speeds in excess of 600 m/s;
Employing decryption, designed or modified for military or governmental services, to gain access to a 'navigation satellite system' secured signal/data; or
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.
1.
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.
2.
In 7A105, navigation satellite system include Global Navigation Satellite Systems (GNSS; e.g., GPS, GLONASS, Galileo or BeiDou) and Regional Navigation Satellite Systems (RNSS; e.g., NavIC, QZSS).
7A106Altimeters, 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.
7A115Passive 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).
7A116Flight 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).
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.
7B001Test, 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".
7B002Equipment 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).
7B003Equipment 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.
7B102Reflectometers 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.
None.
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'.
For the purposes of 7D002, '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.
7D003Other "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:
Doppler radar or sonar velocity data;
"Satellite navigation system" reference data; or
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.
7D102Integration "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.
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".
7E004Other "technology" as follows:
a. "Technology" for the "development" or "production" of any of the following:
Not used;
Air data systems based on surface static data only, i.e., which dispense with conventional air data probes;
Three dimensional displays for "aircraft";
Not used;
Electric actuators (i.e., electromechanical, electrohydrostatic and integrated actuator package) specially designed for 'primary flight control';
Technical Note: For the purposes of 7E004.a.5., 'primary flight control' is "aircraft" stability or manoeuvring control using force/moment generators, i.e., aerodynamic control surfaces or propulsive thrust vectoring.
'Flight control optical sensor array' specially designed for implementing "active flight control systems"; or
Technical Note: For the purposes of 7E004.a.6., 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.
"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"):
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";
Not used;
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.
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.
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.
Not used;
"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: For the purposes of 7E004.b.7.a., 'inner-loop' refers to functions of "active flight control systems" that automate airframe stability controls. b. Having any of the following:
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;
Couples controls in two or more axes while compensating for 'abnormal changes in aircraft state';
Technical Note: For the purposes of 7E004.b.7.b.2., 'abnormal changes in aircraft state' include in-flight structural damage, loss of engine thrust, disabled control surface, or destabilising shifts in cargo load.
Performs the functions specified in 7E004.b.5.; or
Note:
7E004.b.7.b.3. does not control autopilots.
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;
"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:
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;
"Circulation-controlled anti-torque or circulation-controlled direction control systems";
Rotor blades incorporating 'variable geometry aerofoils', for use in systems using individual blade control.
Technical Note: For the purposes of 7E004.c.3., '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
8A001Submersible 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:
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;
Designed to operate at depths exceeding 1 000 m; or
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.3.b., 'range' means half the maximum distance a submersible vehicle can 'operate autonomously'.
c. Unmanned submersible vehicles, as follows:
Unmanned submersible vehicles having any of the following:
a. Designed for deciding a course relative to any geographical reference without real-time human assistance; or b. Acoustic data or command link; c. Not used;
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:
Designed for self-propelled manoeuvre using propulsion motors or thrusters specified in 8A002.a.2.; or
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:
Dynamic positioning systems capable of position keeping within 20 m of a given point provided by the navigation system; or
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