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Commission Implementing Regulation (EU) 2016/1375 of 29 July 2016 amending Council Regulation (EU) No 267/2012 concerning restrictive measures against Iran

Type Implementing Regulation
Publication 2016-08-16
State In force
Text As published
Department European Commission
Source EUR-Lex
articles 2

This is the act as published. Later amendments are not folded into the text below: each one is a separate act in this repository and an entry in this law's history.

Reform history JSON API
The corresponding systems, equipment and components as identified in Council Regulation (EC) No 428/2009 of 5 May 2009 setting up a Community regime for the control of exports, transfer, brokering and transit of dual-use items The corresponding systems, equipment and components as identified in Council Regulation (EC) No 428/2009 of 5 May 2009 setting up a Community regime for the control of exports, transfer, brokering and transit of dual-use items Missile Technology Control Regime (M.TCR): Equipment, software and technology annex Missile Technology Control Regime (M.TCR): Equipment, software and technology annex
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; 2. 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 3. 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. M9A3 Linear accelerometers, designed for use in inertial navigation systems or in guidance systems of all types, usable in the systems specified in 1.A., 19.A.1. or 19.A.2., having all of the following characteristics, and specially designed components therefor: a. ‘Scale factor’‘repeatability’ less (better) than 1 250 ppm; and b. ‘Bias’‘repeatability’ less (better) than 1 250 micro g. Note: Item 9.A.3. does not control accelerometers specially designed and developed as Measurement While Drilling (MWD) sensors for use in downhole well service operations. Technical Notes: 1. ‘Bias’ is defined as the accelerometer output when no acceleration is applied. 2. ‘Scale factor’ is defined as the ratio of change in output to a change in the input. 3. 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. 4. ‘Repeatability’ is defined according to IEEE Standard for Inertial Sensor Terminology 528-2001 in the Definitions section paragraph 2.214 titled repeatability (gyro, accelerometer) as follows: ‘The closeness of agreement among repeated measurements of the same variable under the same operating conditions when changes in conditions or non-operating periods occur between measurements’.
7A001 b. Angular or rotational accelerometers, specified to function at linear acceleration levels exceeding 100 g. M9A5 Accelerometers or gyros of any type, designed for use in inertial navigation systems or in guidance systems of all types, specified to function at acceleration levels greater than 100 g, and specially designed components therefor. Note: 9.A.5. does not include accelerometers that are designed to measure vibration or shock.
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. A 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”. 2. A 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”. M9A4 All types of gyros usable in the systems specified in 1.A., 19.A.1 or 19.A.2., with a rated ‘drift rate’‘stability’ of less than 0,5 degrees (1 sigma or rms) per hour in a 1 g environment, and specially designed components therefor. Technical Notes: 1. ‘Drift rate’ is defined as the component of gyro output that is functionally independent of input rotation and is expressed as an angular rate. (IEEE STD 528-2001 paragraph 2.56) 2. ‘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. (This definition does not refer to dynamic or servo stability.) (IEEE STD 528-2001 paragraph 2.247)
7A002 b. Specified to function at linear acceleration levels exceeding 100 g. M9A5 Accelerometers or gyros of any type, designed for use in inertial navigation systems or in guidance systems of all types, specified to function at acceleration levels greater than 100 g, and specially designed components therefor. Note: 9.A.5. does not include accelerometers that are designed to measure vibration or shock.
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 “participating states”. Technical Notes: 1. ‘Positional aiding references’ independently provide position, and include: a. Global Navigation Satellite Systems (GNSS); b. “Data-Based Referenced Navigation” (“DBRN”). 2. ‘Circular Error Probable’ (‘CEP’) — In a circular normal distribution, the radius of the circle containing 50 % of the individual measurements being made, or the radius of the circle within which there is a 50 % probability of being located. 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); 2. 0,5 % distanced travelled ‘CEP’ or less (better); or 3. 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 2. 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 by 7A001 or 7A002 along any axis, without the use of any aiding references; or 2. 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. M2A1d ‘Guidance sets’, usable in the systems specified in 1.A., 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), except as provided in the Note below 2.A.1. for those designed for missiles with a “range” under 300 km or manned aircraft;
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 “participating states”. Technical Notes: 1. ‘Positional aiding references’ independently provide position, and include: a. Global Navigation Satellite Systems (GNSS); b. “Data-Based Referenced Navigation” (“DBRN”). 2. ‘Circular Error Probable’ (‘CEP’) — In a circular normal distribution, the radius of the circle containing 50 % of the individual measurements being made, or the radius of the circle within which there is a 50 % probability of being located. 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); 2. 0,5 % distanced travelled ‘CEP’ or less (better); or 3. 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 2. 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 by 7A001 or 7A002 along any axis, without the use of any aiding references; or 2. 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. M9A6 Inertial or other equipment using accelerometers specified in 9.A.3. or 9.A.5. or gyros specified in 9.A.4. or 9.A.5., and systems incorporating such equipment, and specially designed components therefor.
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 “participating states”. Technical Notes: 1. ‘Positional aiding references’ independently provide position, and include: a. Global Navigation Satellite Systems (GNSS); b. “Data-Based Referenced Navigation” (“DBRN”). 2. ‘Circular Error Probable’ (‘CEP’) — In a circular normal distribution, the radius of the circle containing 50 % of the individual measurements being made, or the radius of the circle within which there is a 50 % probability of being located. 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); 2. 0,5 % distanced travelled ‘CEP’ or less (better); or 3. 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 2. 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 by 7A001 or 7A002 along any axis, without the use of any aiding references; or 2. 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. M9A8 Three axis magnetic heading sensors having all of the following characteristics, and specially designed components therefor: a. Internal tilt compensation in pitch (+/– 90 degrees) and having roll (+/– 180 degrees) axes. b. Capable of providing azimuthal accuracy better (less) than 0,5 degrees rms at latitudes of +/– 80 degrees, referenced to local magnetic field; and c. Designed or modified to be integrated with flight control and navigation systems. Note: Flight control and navigation systems in Item 9.A.8. include gyrostabilisers, automatic pilots and inertial navigation systems.
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. M9A2 Gyro-astro compasses and other devices which derive position or orientation by means of automatically tracking celestial bodies or satellites, and specially designed components therefor.
7A005 Global Navigation Satellite Systems (GNSS) 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 GNSS receiving equipment that only uses components designed to filter, switch, or combine signals from multiple omni-directional antennae that do not implement adaptive antenna techniques. Technical Note: For the purposes of 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. M11A3 Receiving equipment for Global Navigation Satellite Systems (GNSS; e.g. GPS, GLONASS or Galileo), having any of the following characteristics, and specially designed components therefor: a. Designed or modified for use in systems specified in 1.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; 2. Employing decryption, designed or modified for military or governmental services, to gain access to GNSS secure signal/data; or 3. 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: 11.A.3.b.2. and 11.A.3.b.3. do not control equipment designed for commercial, civil or ‘Safety of Life’ (e.g. data integrity, flight safety) GNSS services.
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. M11A1 Radar and laser radar systems, including altimeters, designed or modified for use in the systems specified in 1.A. Technical Note: Laser radar systems embody specialised transmission, scanning, receiving and signal processing techniques for utilisation of lasers for echo ranging, direction finding and discrimination of targets by location, radial speed and body reflection characteristics.
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 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 a one sigma standard deviation with respect to a fixed calibration over a period of one year; M9A3 Linear accelerometers, designed for use in inertial navigation systems or in guidance systems of all types, usable in the systems specified in 1.A., 19.A.1. or 19.A.2., having all of the following characteristics, and specially designed components therefor: a. ‘Scale factor’‘repeatability’ less (better) than 1 250 ppm; and b. ‘Bias’‘repeatability’ less (better) than 1 250 micro g. Note: Item 9.A.3. does not control accelerometers specially designed and developed as Measurement While Drilling (MWD) sensors for use in downhole well service operations. Technical Notes: 1. ‘Bias’ is defined as the accelerometer output when no acceleration is applied. 2. ‘Scale factor’ is defined as the ratio of change in output to a change in the input. 3. 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. 4. ‘Repeatability’ is defined according to IEEE Standard for Inertial Sensor Terminology 528-2001 in the Definitions section paragraph 2.214 titled repeatability (gyro, accelerometer) as follows: ‘The closeness of agreement among repeated measurements of the same variable under the same operating conditions when changes in conditions or non-operating periods occur between measurements’.
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° (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). M9A4 All types of gyros usable in the systems specified in 1.A., 19.A.1 or 19.A.2., with a rated ‘drift rate’‘stability’ of less than 0,5 degrees (1 sigma or rms) per hour in a 1 g environment, and specially designed components therefor. Technical Notes: 1. ‘Drift rate’ is defined as the component of gyro output that is functionally independent of input rotation and is expressed as an angular rate. (IEEE STD 528-2001 paragraph 2.56) 2. ‘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. (This definition does not refer to dynamic or servo stability.) (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 or other equipment, using accelerometers or gyros as follows, and systems incorporating such equipment: 1. Accelerometers specified in 7A001.a.3., 7A001.b. or 7A101 or gyros specified in 7A002 or 7A102; or 2. 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. does not specify equipment containing accelerometers specified in 7A001 where such accelerometers are specially designed and developed as MWD (Measurement While Drilling) sensors for use in down-hole well services operations. M9A6 Inertial or other equipment using accelerometers specified in 9.A.3. or 9.A.5. or gyros specified in 9.A.4. or 9.A.5., and systems incorporating such equipment, and specially designed components therefor.
7A103 b. Integrated flight instrument systems which include gyrostabilisers or automatic pilots, designed or modified for use in ‘missiles’; M9A1 Integrated flight instrument systems which include gyrostabilisers or automatic pilots, designed or modified for use in the systems specified in 1.A., or 19.A.1. or 19.A.2. and specially designed components therefor.
7A103 c. ‘Integrated navigation systems’, designed or modified for ‘missiles’ and capable of providing a navigational accuracy of 200 m Circle of Equal Probability (CEP) or less; Technical Note: An ‘integrated navigation system’ typically incorporates the following components: 1. An inertial measurement device (e.g., an attitude and heading reference system, inertial reference unit, or inertial navigation system); 2. 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 3. Integration hardware and software; M9A7 ‘Integrated navigation systems’, designed or modified for the systems specified in 1.A., 19.A.1. or 19.A.2. and capable of providing a navigational accuracy of 200 m CEP or less. Technical Note: An ‘integrated navigation system’ typically incorporates all of 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. N.B. For integration “software”, see Item 9.D.4.
7A103 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 the following characteristics, and specially designed components therefor; 1. Internal tilt compensation in pitch (± 90 degrees) and roll (± 180 degrees) axes; 2. Capable of providing 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 gyrostabilizers, 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. M9A8 Three axis magnetic heading sensors having all of the following characteristics, and specially designed components therefor: a. Internal tilt compensation in pitch (+/– 90 degrees) and having roll (+/– 180 degrees) axes. b. Capable of providing azimuthal accuracy better (less) than 0,5 degrees rms at latitudes of +/– 80 degrees, referenced to local magnetic field; and c. Designed or modified to be integrated with flight control and navigation systems. Note: Flight control and navigation systems in Item 9.A.8. include gyrostabilisers, automatic pilots and inertial navigation systems.
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. M9A2 Gyro-astro compasses and other devices which derive position or orientation by means of automatically tracking celestial bodies or satellites, and specially designed components therefor.
7A105 Receiving equipment for Global Navigation Satellite Systems (GNSS; e.g. GPS, GLONASS, or Galileo), 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; 2. Employing decryption, designed or modified for military or governmental services, to gain access to GNSS secured signal/data; or 3. 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) GNSS services. M11A3 Receiving equipment for Global Navigation Satellite Systems (GNSS; e.g. GPS, GLONASS or Galileo), having any of the following characteristics, and specially designed components therefor: a. Designed or modified for use in systems specified in 1.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; 2. Employing decryption, designed or modified for military or governmental services, to gain access to GNSS secure signal/data; or 3. 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: 11.A.3.b.2. and 11.A.3.b.3. do not control equipment designed for commercial, civil or ‘Safety of Life’ (e.g. data integrity, flight safety) GNSS services.
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. M11A1 Radar and laser radar systems, including altimeters, designed or modified for use in the systems specified in 1.A. Technical Note: Laser radar systems embody specialised transmission, scanning, receiving and signal processing techniques for utilisation of lasers for echo ranging, direction finding and discrimination of targets by location, radial speed and body reflection characteristics.
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: 7A115 includes sensors for the following equipment: a. Terrain contour mapping equipment; b. Imaging sensor equipment (both active and passive); c. Passive interferometer equipment M11A2 Passive sensors for determining bearings to specific electromagnetic sources (direction finding equipment) or terrain characteristics, designed or modified for use in the systems specified in 1.A.
7A116 Flight control systems and servo valves, as follows; designed or modified for use in space launch vehicles specified in 9A004 or sounding rockets specified in 9A104. a. Hydraulic, mechanical, electro-optical, or electro-mechanical flight control systems (including fly-by-wire types); M10A1 Pneumatic, hydraulic, mechanical, electro-optical, or electromechanical flight control systems (including fly-by-wire and fly-by-light systems) designed or modified for the systems specified in 1.A.
7A116 b. Attitude control equipment; M10A2 Attitude control equipment designed or modified for the systems specified in 1.A.
7A116 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. M10A3 Flight control servo valves designed or modified for the systems in 10.A.1. or 10.A.2., and designed or modified to operate in a vibration environment greater than 10 g rms between 20 Hz and 2 kHz. Note: Systems, equipment or valves specified in 10.A. may be exported as part of a manned aircraft or satellite or in quantities appropriate for replacement parts for manned aircraft.
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). M2A1d ‘Guidance sets’, usable in the systems specified in 1.A., 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), except as provided in the Note below 2.A.1. for those designed for missiles with a “range” under 300 km or manned aircraft;

7B   Test, Inspection and Production Equipment

The corresponding systems, equipment and components as identified in Council Regulation (EC) No 428/2009 of 5 May 2009 setting up a Community regime for the control of exports, transfer, brokering and transit of dual-use items The corresponding systems, equipment and components as identified in Council Regulation (EC) No 428/2009 of 5 May 2009 setting up a Community regime for the control of exports, transfer, brokering and transit of dual-use items Missile Technology Control Regime (M.TCR): Equipment, software and technology annex Missile Technology Control Regime (M.TCR): Equipment, software and technology annex
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. M2B2 “Production equipment” specially designed for the subsystems specified in 2.A.
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. M9B1 “Production equipment”, and other test, calibration and alignment equipment, other than that described in 9.B.2., designed or modified to be used with equipment specified in 9.A. Note: Equipment specified in 9.B.1. includes the following: a. For laser gyro equipment, the following equipment used to characterise mirrors, having the threshold accuracy shown or better: 1. Scatterometer (10 ppm); 2. Reflectometer (50 ppm); 3. Profilometer (5 Angstroms); b. For other inertial equipment: 1. Inertial Measurement Unit (IMU) Module Tester; 2. IMU Platform Tester; 3. IMU Stable Element Handling Fixture; 4. IMU Platform Balance Fixture; 5. Gyro Tuning Test Station; 6. Gyro Dynamic Balance Station; 7. Gyro Run-In/Motor Test Station; 8. Gyro Evacuation and Filling Station; 9. Centrifuge Fixture for Gyro Bearings; 10. Accelerometer Axis Align Station; 11. Accelerometer Test Station; 12. Fibre Optic Gyro Coil Winding Machines
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. M10B1 Test, calibration, and alignment equipment specially designed for equipment specified in 10.A.
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). M9B1 “Production equipment”, and other test, calibration and alignment equipment, other than that described in 9.B.2., designed or modified to be used with equipment specified in 9.A. Note: Equipment specified in 9.B.1. includes the following: a. For laser gyro equipment, the following equipment used to characterise mirrors, having the threshold accuracy shown or better: 1. Scatterometer (10 ppm); 2. Reflectometer (50 ppm); 3. Profilometer (5 Angstroms); b. For other inertial equipment: 1. Inertial Measurement Unit (IMU) Module Tester; 2. IMU Platform Tester; 3. IMU Stable Element Handling Fixture; 4. IMU Platform Balance Fixture; 5. Gyro Tuning Test Station; 6. Gyro Dynamic Balance Station; 7. Gyro Run-In/Motor Test Station; 8. Gyro Evacuation and Filling Station; 9. Centrifuge Fixture for Gyro Bearings; 10. Accelerometer Axis Align Station; 11. Accelerometer Test Station; 12. Fibre Optic Gyro Coil Winding Machines.
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. M2B2 “Production equipment” specially designed for the subsystems specified in 2.A.
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. M9B1 “Production equipment”, and other test, calibration and alignment equipment, other than that described in 9.B.2., designed or modified to be used with equipment specified in 9.A. Note: Equipment specified in 9.B.1. includes the following: a. For laser gyro equipment, the following equipment used to characterise mirrors, having the threshold accuracy shown or better: 1. Scatterometer (10 ppm); 2. Reflectometer (50 ppm); 3. Profilometer (5 Angstroms); b. For other inertial equipment: 1. Inertial Measurement Unit (IMU) Module Tester; 2. IMU Platform Tester; 3. IMU Stable Element Handling Fixture; 4. IMU Platform Balance Fixture; 5. Gyro Tuning Test Station; 6. Gyro Dynamic Balance Station; 7. Gyro Run-In/Motor Test Station; 8. Gyro Evacuation and Filling Station; 9. Centrifuge Fixture for Gyro Bearings; 10. Accelerometer Axis Align Station; 11. Accelerometer Test Station; 12. 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). M9B1 “Production equipment”, and other test, calibration and alignment equipment, other than that described in 9.B.2., designed or modified to be used with equipment specified in 9.A. Note: Equipment specified in 9.B.1. includes the following: a. For laser gyro equipment, the following equipment used to characterise mirrors, having the threshold accuracy shown or better: 1. Scatterometer (10 ppm); 2. Reflectometer (50 ppm); 3. Profilometer (5 Angstroms); b. For other inertial equipment: 1. Inertial Measurement Unit (IMU) Module Tester; 2. IMU Platform Tester; 3. IMU Stable Element Handling Fixture; 4. IMU Platform Balance Fixture; 5. Gyro Tuning Test Station; 6. Gyro Dynamic Balance Station; 7. Gyro Run-In/Motor Test Station; 8. Gyro Evacuation and Filling Station; 9. Centrifuge Fixture for Gyro Bearings; 10. Accelerometer Axis Align Station; 11. Accelerometer Test Station; 12. Fibre Optic Gyro Coil Winding Machines.
7B103 “Production facilities” and “production equipment” as follows:
7B103 a. “Production facilities” specially designed for equipment specified in 7A117; M2B1 “Production facilities” specially designed for the subsystems specified in 2.A
7B103 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. M2B2* “Production equipment” specially designed for the subsystems specified in 2.A.
7B103 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. M9B1 “Production equipment”, and other test, calibration and alignment equipment, other than that described in 9.B.2., designed or modified to be used with equipment specified in 9.A. Note: Equipment specified in 9.B.1. includes the following: a. For laser gyro equipment, the following equipment used to characterise mirrors, having the threshold accuracy shown or better: 1. Scatterometer (10 ppm); 2. Reflectometer (50 ppm); 3. Profilometer (5 Angstroms); b. For other inertial equipment: 1. Inertial Measurement Unit (IMU) Module Tester; 2. IMU Platform Tester; 3. IMU Stable Element Handling Fixture; 4. IMU Platform Balance Fixture; 5. Gyro Tuning Test Station; 6. Gyro Dynamic Balance Station; 7. Gyro Run-In/Motor Test Station; 8. Gyro Evacuation and Filling Station; 9. Centrifuge Fixture for Gyro Bearings; 10. Accelerometer Axis Align Station; 11. Accelerometer Test Station; 12. Fibre Optic Gyro Coil Winding Machines.

7D   Software

The corresponding systems, equipment and components as identified in Council Regulation (EC) No 428/2009 of 5 May 2009 setting up a Community regime for the control of exports, transfer, brokering and transit of dual-use items The corresponding systems, equipment and components as identified in Council Regulation (EC) No 428/2009 of 5 May 2009 setting up a Community regime for the control of exports, transfer, brokering and transit of dual-use items Missile Technology Control Regime (M.TCR): Equipment, software and technology annex Missile Technology Control Regime (M.TCR): Equipment, software and technology annex
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. M2D3 “Software”, specially designed or modified for the operation or maintenance of ‘guidance sets’ specified in 2.A.1.d. Note: 2.D.3. includes “software”, specially designed or modified to enhance the performance of ‘guidance sets’ to achieve or exceed the accuracy specified in 2.A.1.d.
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. M9D1 “Software” specially designed or modified for the “use” of equipment specified in 9.A. or 9.B.
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. M2D “Software” specially designed or modified for the “use” of “production facilities” specified in 2.B.1.
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. M9D1 “Software” specially designed or modified for the “use” of equipment specified in 9.A. or 9.B.
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. M10D1 “Software” specially designed or modified for the “use” of equipment specified in 10.A. or 10.B. Note: “Software” specified in 10.D.1. may be exported as part of a manned aircraft or satellite or in quantities appropriate for replacement parts for manned aircraft.
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. M11D1&2 “Software” specially designed or modified for the “use” of equipment specified in 11.A.1., 11.A.2. or 11.A.4. “Software” specially designed for the “use” of equipment specified in 11.A.3.
7D102 Integration “software” as follows: a. Integration “software” for the equipment specified in 7A103.b.; M9D2 Integration “software” for the equipment specified in 9.A.1.
7D102 b. Integration “software” specially designed for the equipment specified in 7A003 or 7A103.a. M9D3* Integration “software” specially designed for the equipment specified in 9.A.6.
7D102 c. Integration “software” designed or modified for the equipment specified in 7A103.c. Note: A common form of integration “software” employs Kalman filtering. M9D4 Integration “software”, designed or modified for the ‘integrated navigation systems’ specified in 9.A.7. 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. M16D1 “Software” specially designed for modelling, simulation, or design integration of the systems specified in 1.A. or the subsystems specified in 2.A or 20.A. Technical Note: The modelling includes in particular the aerodynamic and thermodynamic analysis of the systems.

7E   Technology

The corresponding systems, equipment and components as identified in Council Regulation (EC) No 428/2009 of 5 May 2009 setting up a Community regime for the control of exports, transfer, brokering and transit of dual-use items The corresponding systems, equipment and components as identified in Council Regulation (EC) No 428/2009 of 5 May 2009 setting up a Community regime for the control of exports, transfer, brokering and transit of dual-use items Missile Technology Control Regime (M.TCR): Equipment, software and technology annex Missile Technology Control Regime (M.TCR): Equipment, software and technology annex
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. M Means specific information which is required for the “development”, “production” or “use” of a product. The information may take the form of “technical data” or “technical assistance”.
7E002 “Technology” according to the General Technology Note for the “production” of equipment specified in 7A or 7B. M Means specific information which is required for the “development”, “production” or “use” of a product. The information may take the form of “technical data” or “technical assistance”.
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 maintenance “technology” 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. M2E1 “Technology”, in accordance with the General Technology Note, for the “development”, “production” or “use” of equipment or “software” specified in 2.A., 2.B. or 2.D.
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 maintenance “technology” 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. M9E1 “Technology”, in accordance with the General Technology Note, for the “development”, “production” or “use” of equipment or “software” specified in 9.A., 9.B. or 9.D. Note: Equipment or “software” specified in 9.A. or 9.D. may be exported as part of a manned aircraft, satellite, land vehicle, marine/submarine vessel or geophysical survey equipment or in quantities appropriate for replacement parts for such applications.
7E004 Other “technology” as follows: a. “Technology” for the “development” or “production” of any of the following: 1. Not used; 2. Air data systems based on surface static data only, i.e., which dispense with conventional air data probes; 3. Three dimensional displays for “aircraft”; 4. Not used; 5. Electric actuators (i.e., electromechanical, electrohydrostatic and integrated actuator package) specially designed for “primary flight control”; 6. “Flight control optical sensor array” specially designed for implementing “active flight control systems”; or 7. “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”; 2. Not used; 3. Real-time algorithms to analyze 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. 4. 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. 5. Integration of digital flight control, navigation and propulsion control data, into a digital flight management system for “total control of flight”;
7E004 Note: 7E004.b.5. does not control: a. “Development”“technology” for integration of digital flight control, navigation and propulsion control data, into a digital flight management system for “flight path optimisation”; b. “Development”“technology” for “aircraft” flight instrument systems integrated solely for VOR, DME, ILS or MLS navigation or approaches. 6. Not used; 7. “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; 2. 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 destabilizing shifts in cargo load. 3. Preforms the functions specified in 7E004.b.5.; or Note: 7E004.b.7.b.3. does not control autopilots. 4. 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; 8. “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; 2. “Circulation-controlled anti-torque or circulation-controlled directional control systems”; 3. Rotor blades incorporating “variable geometry airfoils”, for use in systems using individual blade control. M10E1 Design “technology” for integration of air vehicle fuselage, propulsion system and lifting control surfaces, designed or modified for the systems specified in 1.A. or 19.A.2., to optimise aerodynamic performance throughout the flight regime of an unmanned aerial vehicle.
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. M Means specific information which is required for the “development”, “production” or “use” of a product. The information may take the form of “technical data” or “technical assistance”.
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. M11E1 Design “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 determination of hardening criteria for the above.
7E104 “Technology” for the integration of the flight control, guidance, and propulsion data into a flight management system for optimization of rocket system trajectory. M10E2 Design “technology” for integration of the flight control, guidance, and propulsion data into a flight management system, designed or modified for the systems specified in 1.A. or 19.A.1., for optimisation of rocket system trajectory.

CATEGORY 9 — AEROSPACE AND PROPULSION

9A   Systems, Equipment and Components

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