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 (recast)

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

• b. Attitude control equipment;

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

• Note:

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

7A117 ‘Guidance sets’, usable in ‘missiles’ capable of achieving system accuracy of 3,33 % or less of the range (e.g., a ‘CEP’ of 10 km or less at a range of 300 km).

Technical Note:

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

7BTest, Inspection and Production Equipment

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’.

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.

7B002Equipment specially designed to characterize mirrors for ring ‘laser’ gyros, as follows:

• NB:

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.

7CMaterials

None.

7DSoftware

7D001 ‘Software’ specially designed or modified for the ‘development’ or ‘production’ of equipment specified in 7A or 7B.

7D002 ‘Source code’ for the operation or maintenance of any inertial navigation equipment, including inertial equipment not specified in 7A003 or 7A004, or Attitude and Heading Reference Systems (‘AHRS’).

• Note:

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

Technical Note:

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

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:
• 1. Doppler radar or sonar velocity data;
• 1. ‘Satellite navigation system’ reference data; or
• 1. 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.

7ETechnology

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’.

• NB:

See Technical Notes to 7B001.

7E004Other ‘technology’ as follows:

• a. ‘Technology’ for the ‘development’ or ‘production’ of any of the following:
• 1. Not used;
• 1. Air data systems based on surface static data only, i.e., which dispense with conventional air data probes;
• 1. Three dimensional displays for ‘aircraft’;
• 1. Not used;
• 1. Electric actuators (i.e., electromechanical, electrohydrostatic and integrated actuator package) specially designed for ‘primary flight control’; Technical Note: ‘Primary flight control’ is ‘aircraft’ stability or manoeuvring control using force/moment generators, i.e. aerodynamic control surfaces or propulsive thrust vectoring.
• 1. ‘Flight control optical sensor array’ specially designed for implementing ‘active flight control systems’; or Technical Note: A ‘flight control optical sensor array’ is a network of distributed optical sensors, using ‘laser’ beams, to provide real-time flight control data for on-board processing.
• 1. ‘DBRN’ systems designed to navigate underwater, using sonar or gravity databases, that provide a positioning ‘accuracy’ equal to or less (better) than 0,4 nautical miles;

• b. ‘Development’‘technology’, as follows, for ‘active flight control systems’ (including ‘fly-by-wire systems’ or ‘fly-by-light systems’):
• 1. Photonic-based ‘technology’ for sensing ‘aircraft’ or flight control component state, transferring flight control data, or commanding actuator movement, ‘required’ for ‘fly-by-light systems’‘active flight control systems’;
• 1. Not used;
• 1. Real-time algorithms to analyse component sensor information to predict and preemptively mitigate impending degradation and failures of components within an ‘active flight control system’; Note:

7E004.b.3. does not control algorithms for purpose of off-line maintenance. - 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’; 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. - 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. Performs 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;
• 1. ‘Circulation-controlled anti-torque or circulation-controlled direction control systems’;
• 1. Rotor blades incorporating ‘variable geometry airfoils’, for use in systems using individual blade control. Technical Note: ‘Variable geometry airfoils’ 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.

CATEGORY 8 – MARINE

8ASystems, Equipment and Components

8A001Submersible vehicles and surface vessels, as follows:

• NB:

For the control status of equipment for submersible vehicles, see:

• — Category 6 for sensors;

• — Categories 7 and 8 for navigation equipment;

- — Category 8A for underwater equipment.

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

• b. Manned, untethered submersible vehicles having any of the following:
• 1. Designed to ‘operate autonomously’ and having a lifting capacity of all of the following:
• a. 10 % or more of their weight in air; and
• b. 15 kN or more;
• 1. Designed to operate at depths exceeding 1 000  m; or
• 1. Having all of the following:
• a. Designed to continuously ‘operate autonomously’ for 10 hours or more; and
• b. ‘Range’ of 25 nautical miles or more; Technical Notes: 1.

For the purposes of 8A001.b., ‘operate autonomously’ means fully submerged, without snorkel, all systems working and cruising at minimum speed at which the submersible can safely control its depth dynamically by using its depth planes only, with no need for a support vessel or support base on the surface, sea-bed or shore, and containing a propulsion system for submerged or surface use. 2.

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

• c. Unmanned submersible vehicles, as follows:
• 1. Unmanned submersible vehicles having any of the following:
• a. Designed for deciding a course relative to any geographical reference without real-time human assistance;
• b. Acoustic data or command link; or
• c. Optical data or command link exceeding 1 000  m;
• 1. Unmanned submersible vehicles, not specified in 8A001.c.1, having all of the following:
• a. Designed to operate with a tether;
• b. Designed to operate at depths exceeding 1 000  m;
• c. Having any of the following:
• 1. Designed for self-propelled manoeuvre using propulsion motors or thrusters specified in 8A002.a.2.; or
• 1. Fibre optic data link;

• d. Not used;

• e. Ocean salvage systems with a lifting capacity exceeding 5 MN for salvaging objects from depths exceeding 250 m and having any of the following:
• 1. Dynamic positioning systems capable of position keeping within 20 m of a given point provided by the navigation system; or
• 1. Seafloor navigation and navigation integration systems, for depths exceeding 1 000  m and with positioning ‘accuracies’ to within 10 m of a predetermined point;

• f. Not used;

• g. Not used;

- h. Not used;

- i. Not used.

8A002Marine systems, equipment and components, as follows:

- Note:

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

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

• 1. Pressure housings or pressure hulls with a maximum inside chamber diameter exceeding 1,5 m;
• 1. Direct current propulsion motors or thrusters;
• 1. Umbilical cables, and connectors therefor, using optical fibre and having synthetic strength members;
• 1. Components manufactured from material specified in 8C001; Technical Note: The objective of 8A002.a.4. should not be defeated by the export of ‘syntactic foam’ specified in 8C001 when an intermediate stage of manufacture has been performed and it is not yet in the final component form.

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

• 1. Enabling a vehicle to move within 10 m of a predetermined point in the water column;
• 1. Maintaining the position of the vehicle within 10 m of a predetermined point in the water column; or
• 1. Maintaining the position of the vehicle within 10 m while following a cable on or under the seabed;

• c. Fibre optic pressure hull penetrators;

• d. Underwater vision systems having all of the following:
• 1. Specially designed or modified for remote operation with an underwater vehicle; and
• 1. Employing any of the following techniques to minimise the effects of back scatter:
• a. Range-gated illuminators; or
• b. Range-gated laser systems;

• e. Not used;

• f. Not used;

• g. Light systems specially designed or modified for underwater use, as follows:
• 1. Stroboscopic light systems capable of a light output energy of more than 300 J per flash and a flash rate of more than 5 flashes per second;
• 1. Argon arc light systems specially designed for use below 1 000  m;

• h. ‘Robots’ specially designed for underwater use, controlled by using a dedicated computer and having any of the following:
• 1. Systems that control the ‘robot’ using information from sensors which measure force or torque applied to an external object, distance to an external object, or tactile sense between the ‘robot’ and an external object; or
• 1. The ability to exert a force of 250 N or more or a torque of 250 Nm or more and using titanium based alloys or ‘composite’‘fibrous or filamentary materials’ in their structural members;

• i. Remotely controlled articulated manipulators specially designed or modified for use with submersible vehicles and having any of the following:
• 1. Systems which control the manipulator using information from sensors which measure any of the following:
• a. Torque or force applied to an external object; or
• b. Tactile sense between the manipulator and an external object; or
• 1. Controlled by proportional master-slave techniques and having 5 degrees of ‘freedom of movement’ or more; Technical Note: Only functions having proportionally related motion control using positional feedback are counted when determining the number of degrees of ‘freedom of movement’.

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

• 1. Brayton or Rankine cycle engine air independent power systems having any of the following:
• a. Chemical scrubber or absorber systems, specially designed to remove carbon dioxide, carbon monoxide and particulates from recirculated engine exhaust;
• b. Systems specially designed to use a monoatomic gas;
• c. Devices or enclosures, specially designed for underwater noise reduction in frequencies below 10 kHz, or special mounting devices for shock mitigation; or
• d. Systems having all of the following:
• 1. Specially designed to pressurise the products of reaction or for fuel reformation;
• 1. Specially designed to store the products of the reaction; and
• 1. Specially designed to discharge the products of the reaction against a pressure of 100 kPa or more;
• 1. Diesel cycle engine air independent systems having all of the following:
• a. Chemical scrubber or absorber systems, specially designed to remove carbon dioxide, carbon monoxide and particulates from recirculated engine exhaust;
• b. Systems specially designed to use a monoatomic gas;
• c. Devices or enclosures, specially designed for underwater noise reduction in frequencies below 10 kHz, or special mounting devices for shock mitigation; and
• d. Specially designed exhaust systems that do not exhaust continuously the products of combustion;
• 1. ‘Fuel cell’ air independent power systems with an output exceeding 2 kW and having any of the following:
• a. Devices or enclosures, specially designed for underwater noise reduction in frequencies below 10 kHz, or special mounting devices for shock mitigation; or
• b. Systems having all of the following:
• 1. Specially designed to pressurise the products of reaction or for fuel reformation;
• 1. Specially designed to store the products of the reaction; and
• 1. Specially designed to discharge the products of the reaction against a pressure of 100 kPa or more;
• 1. Stirling cycle engine air independent power systems having all of the following:
• a. Devices or enclosures, specially designed for underwater noise reduction in frequencies below 10 kHz, or special mounting devices for shock mitigation; and
• b. Specially designed exhaust systems which discharge the products of combustion against a pressure of 100 kPa or more;

• k. Not used;

• l. Not used;

• m. Not used;

• n. Not used;

• o. Propellers, power transmission systems, power generation systems and noise reduction systems, as follows:
• 1. Not used
• 1. Water-screw propeller, power generation systems or transmission systems, designed for use on vessels, as follows:
• a. Controllable-pitch propellers and hub assemblies, rated at more than 30 MW;
• b. Internally liquid-cooled electric propulsion engines with a power output exceeding 2,5 MW;
• c. ‘Superconductive’ propulsion engines or permanent magnet electric propulsion engines, with a power output exceeding 0,1 MW;
• d. Power transmission shaft systems incorporating ‘composite’ material components and capable of transmitting more than 2 MW;
• e. Ventilated or base-ventilated propeller systems, rated at more than 2,5 MW;
• 1. Noise reduction systems designed for use on vessels of 1 000 tonnes displacement or more, as follows:
• a. Systems that attenuate underwater noise at frequencies below 500 Hz and consist of compound acoustic mounts for the acoustic isolation of diesel engines, diesel generator sets, gas turbines, gas turbine generator sets, propulsion motors or propulsion reduction gears, specially designed for sound or vibration isolation and having an intermediate mass exceeding 30 % of the equipment to be mounted;
• b. ‘Active noise reduction or cancellation systems’ or magnetic bearings, specially designed for power transmission systems; Technical Note: ‘Active noise reduction or cancellation systems’ incorporate electronic control systems capable of actively reducing equipment vibration by the generation of anti-noise or anti-vibration signals directly to the source.

• p. Pumpjet propulsion systems having all of the following:
• 1. Power output exceeding 2,5 MW; and
• 1. Using divergent nozzle and flow conditioning vane techniques to improve propulsive efficiency or reduce propulsion-generated underwater-radiated noise;

• q. Underwater swimming and diving equipment as follows:
• 1. Closed circuit rebreathers;
• 1. Semi-closed circuit rebreathers; Note:

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

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

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

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

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

8BTest, Inspection and Production Equipment

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

8CMaterials

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

• NB:

See also 8A002.a.4.

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

• b. A density less than 561 kg/m³.

Technical Note:

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

8DSoftware

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

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

8ETechnology

8E001

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

8E002Other ‘technology’ as follows:

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

• b. ‘Technology’ for the overhaul or refurbishing of equipment specified in 8A001, 8A002.b., 8A002.j., 8A002.o. or 8A002.p.

• c. ‘Technology’ according to the General Technology Note for the ‘development’ or ‘production’ of any of the following:
• 1. Surface-effect vehicles (fully skirted variety) having all of the following:
• a. Maximum design speed, fully loaded, exceeding 30 knots in a significant wave height of 1,25 m or more;
• b. Cushion pressure exceeding 3 830 Pa; and
• c. Light-ship-to-full-load displacement ratio of less than 0,70;
• 1. Surface-effect vehicles (rigid sidewalls) with a maximum design speed, fully loaded, exceeding 40 knots in a significant wave height of 3,25 m or more;
• 1. Hydrofoil vessels with active systems for automatically controlling foil systems, with a maximum design speed, fully loaded, of 40 knots or more in a significant wave height of 3,25 m or more; or
• 1. ‘Small waterplane area vessels’ having any of the following:
• a. Full load displacement exceeding 500 tonnes with a maximum design speed, fully loaded, exceeding 35 knots in a significant wave height of 3,25 m or more; or
• b. Full load displacement exceeding 1 500 tonnes with a maximum design speed, fully loaded, exceeding 25 knots in a significant wave height of 4 m or more. Technical Note: A ‘small waterplane area vessel’ is defined by the following formula: waterplane area at an operational design draft less than 2 × (displaced volume at the operational design draft)^2/3.

CATEGORY 9 – AEROSPACE AND PROPULSION

9ASystems, Equipment and Components

• NB:

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

9A001Aero gas turbine engines having any of the following:

• NB:

SEE ALSO 9A101.

• a. Incorporating any of the ‘technologies’ specified in 9E003.a., 9E003.h. or 9E003.i.; or Note 1:

9A001.a. does not control aero gas turbine engines which meet all of the following: - a. Certified by the civil aviation authorities of one or more EU Member States or Wassenaar Arrangement Participating States; and - b. Intended to power non-military manned ‘aircraft’ for which any of the following has been issued by civil aviation authorities of one or more EU Member States or Wassenaar Arrangement Participating States for the ‘aircraft’ with this specific engine type: - 1. A civil type certificate; or - 2. An equivalent document recognized by the International Civil Aviation Organisation (ICAO). Note 2:

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

• b. Designed to power an ‘aircraft’ to cruise at Mach 1 or higher, for more than thirty minutes.

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

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

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

- Note:

The term ‘marine gas turbine engines’ includes those industrial, or aero-derivative, gas turbine engines adapted for a ship’s electric power generation or propulsion.

Technical Note:

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

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

- a. Specified in 9A001; or

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

9A004Space launch vehicles, ‘spacecraft’, ‘spacecraft buses’, ‘spacecraft payloads’, ‘spacecraft’ on-board systems or equipment, terrestrial equipment, and air-launch platforms as follows:

• NB:

SEE ALSO 9A104.

• a. Space launch vehicles;

• b. ‘Spacecraft’;

- c. ‘Spacecraft buses’;

• d. ‘Spacecraft payloads’ incorporating items specified in 3A001.b.1.a.4., 3A002.g., 5A001.a.1., 5A001.b.3., 5A002.c., 5A002.e., 6A002.a.1., 6A002.a.2., 6A002.b., 6A002.d., 6A003.b., 6A004.c., 6A004.e., 6A008.d., 6A008.e., 6A008.k., 6A008.l. or 9A010.c.;

• e. On-board systems or equipment, specially designed for ‘spacecraft’ and having any of the following functions:
• 1. ‘Command and telemetry data handling’; Note:

For the purpose of 9A004.e.1., ‘command and telemetry data handling’ includes bus data management, storage, and processing. - 2. ‘Payload data handling’; or Note:

For the purpose of 9A004.e.2., ‘payload data handling’ includes payload data management, storage, and processing. - 3. ‘Attitude and orbit control’; Note:

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

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

• f. Terrestrial equipment specially designed for ‘spacecraft’, as follows:
• 1. Telemetry and telecommand equipment specially designed for any of the following data processing functions:
• a. Telemetry data processing of frame synchronisation and error corrections, for monitoring of operational status (also known as health and safe status) of the ‘spacecraft bus’; or
• b. Command data processing for formatting command data being sent to the ‘spacecraft’ to control the ‘spacecraft bus’;
• 1. Simulators specially designed for ‘verification of operational procedures’ of ‘spacecraft’; Technical Note: For the purposes of 9A004.f.2., ‘verification of operational procedures’ is any of the following: 1.

Command sequence confirmation; 2.

Operational training; 3.

Operational rehearsals; or 4.

Operational analysis.

• g. ‘Aircraft’ specially designed or modified to be air-launch platforms for space launch vehicles;

• h. ‘Sub-orbital craft’.

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

• NB:

SEE ALSO 9A105 AND 9A119.

9A006Systems and components, specially designed for liquid rocket propulsion systems, as follows:

• NB:

SEE ALSO 9A106, 9A108 AND 9A120.

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

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

• c. Slush hydrogen storage or transfer systems;

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

• e. High-pressure (exceeding 10,6 MPa) thrust chambers and nozzles therefor;

• f. Propellant storage systems using the principle of capillary containment or positive expulsion (i.e., with flexible bladders);

• g. Liquid propellant injectors with individual orifices of 0,381 mm or smaller in diameter (an area of 1,14 × 10^–3 cm² or smaller for non-circular orifices) and specially designed for liquid rocket engines;

• h. One-piece carbon-carbon thrust chambers or one-piece carbon-carbon exit cones, with densities exceeding 1,4 g/cm³ and tensile strengths exceeding 48 MPa.

9A007Solid rocket propulsion systems having any of the following:

• NB:

SEE ALSO 9A107 AND 9A119.

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

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

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

• d. Components specified in 9A008; or

• e. Insulation and propellant bonding systems, using direct-bonded motor designs to provide a ‘strong mechanical bond’ or a barrier to chemical migration between the solid propellant and case insulation material. Technical Note: ‘Strong mechanical bond’ means bond strength equal to or more than propellant strength.

9A008Components specially designed for solid rocket propulsion systems, as follows:

• NB:

SEE ALSO 9A108.

• a. Insulation and propellant bonding systems, using liners to provide a ‘strong mechanical bond’ or a barrier to chemical migration between the solid propellant and case insulation material; Technical Note: ‘Strong mechanical bond’ means bond strength equal to or more than propellant strength.

• b. Filament-wound ‘composite’ motor cases exceeding 0,61 m in diameter or having ‘structural efficiency ratios (PV/W)’ exceeding 25 km; Technical Note: ‘Structural efficiency ratio (PV/W)’ is the burst pressure (P) multiplied by the vessel volume (V) divided by the total pressure vessel weight (W).

• c. Nozzles with thrust levels exceeding 45 kN or nozzle throat erosion rates of less than 0,075 mm/s;

• d. Movable nozzle or secondary fluid injection thrust vector control systems, capable of any of the following:
• 1. Omni-axial movement exceeding ± 5°;
• 1. Angular vector rotations of 20°/s or more; or
• 1. Angular vector accelerations of 40°/s² or more.

9A009Hybrid rocket propulsion systems having any of the following:

• NB:

SEE ALSO 9A109 AND 9A119.

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

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

9A010Specially designed components, systems and structures, for launch vehicles, launch vehicle propulsion systems or ‘spacecraft’, as follows:

• NB:

SEE ALSO 1A002 AND 9A110.

• a. Components and structures, each exceeding 10 kg and specially designed for launch vehicles manufactured using any of the following:
• 1. ‘Composite’ materials consisting of ‘fibrous or filamentary materials’ specified in 1C010.e. and resins specified in 1C008 or 1C009.b.;
• 1. Metal ‘matrix’‘composites’ reinforced by any of the following:
• a. Materials specified in 1C007;
• b. ‘Fibrous or filamentary materials’ specified in 1C010; or
• c. Aluminides specified in 1C002.a.; or
• 1. Ceramic ‘matrix’‘composite’ materials specified in 1C007; Note:

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

- b. Components and structures, specially designed for launch vehicle propulsion systems specified in 9A005 to 9A009 manufactured using any of the following:

• 1. ‘Fibrous or filamentary materials’ specified in 1C010.e. and resins specified in 1C008 or 1C009.b.;
• 1. Metal ‘matrix’‘composites’ reinforced by any of the following:
• a. Materials specified in 1C007;
• b. ‘Fibrous or filamentary materials’ specified in 1C010; or
• c. Aluminides specified in 1C002.a.; or
• 1. Ceramic ‘matrix’‘composite’ materials specified in 1C007;

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

- d. Pulsed liquid rocket engines with thrust-to-weight ratios equal to or more than 1 kN/kg and a ‘response time’ of less than 30 ms.

Technical Note: For the purposes of 9A010.d., ‘response time’ is the time required to achieve 90 % of total rated thrust from start-up.

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

- NB:

SEE ALSO 9A111 AND 9A118.

Technical Note:

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

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

• — Ramjet or scramjet;

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

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

• NB: 1

SEE ALSO 9A112.

• NB: 2

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

• a. ‘UAVs’ or unmanned ‘airships’, designed to have controlled flight out of the direct ‘natural vision’ of the ‘operator’ and having any of the following:
• 1. Having all of the following:
• a. A maximum ‘endurance’ greater than or equal to 30 minutes but less than 1 hour; and
• b. Designed to take-off and have stable controlled flight in wind gusts equal to or exceeding 46,3 km/h (25 knots); or
• 1. A maximum ‘endurance’ of 1 hour or greater; Technical Notes: 1.

For the purposes of 9A012.a., ‘operator’ is a person who initiates or commands the ‘UAV’ or unmanned ‘airship’ flight. 2.

For the purposes of 9A012.a., ‘endurance’ is to be calculated for ISA conditions (ISO 2533:1975) at sea level in zero wind. 3.

For the purposes of 9A012.a., ‘natural vision’ means unaided human sight, with or without corrective lenses.

• b. Related equipment and components, as follows:
• 1. Not used;
• 1. Not used;
• 1. Equipment or components, specially designed to convert a manned ‘aircraft’ or manned ‘airship’, to a ‘UAV’ or unmanned ‘airship’, specified in 9A012.a.;
• 1. Air breathing reciprocating or rotary internal combustion type engines, specially designed or modified to propel ‘UAVs’ or unmanned ‘airships’, at altitudes above 15 240 metres (50 000 feet).

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

• a. Engines having all of the following characteristics:
• 1. ‘Maximum thrust value’ greater than 400 N excluding civil certified engines with a ‘maximum thrust value’ greater than 8 890  N;
• 1. Specific fuel consumption of 0,15 kg N^–1 h^–1 or less;
• 1. ‘Dry weight’ less than 750 kg; and
• 1. ‘First-stage rotor diameter’ less than 1 m; Technical Notes: 1.

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

2.

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

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

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

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

9A102 ‘Turboprop engine systems’ specially designed for unmanned aerial vehicles specified in 9A012 or 9A112.a., and specially designed components therefor, having a ‘maximum power’ greater than 10 kW.

• Note:

9A102 does not control civil certified engines.

Technical Notes:

• 1.

For the purposes of 9A102, a ‘turboprop engine system’ incorporates all of the following:

• a. Turboshaft engine; and

• b. Power transmission system to transfer the power to a propeller.

- 2.

For the purposes of 9A102, the ‘maximum power’ is achieved un-installed at sea level static conditions using ICAO standard atmosphere.

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

- NB:

SEE ALSO 9A004.

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

- NB:

SEE ALSO 9A119.

• a. Liquid propellant rocket engines or gel propellant rocket motors, usable in ‘missiles’, other than those specified in 9A005, integrated, or designed or modified to be integrated, into a liquid propellant or gel propellant propulsion system which has a total impulse capacity equal to or greater than 1,1 MNs;

• b. Liquid propellant rocket engines or gel propellant rocket motors, usable in complete rocket systems or unmanned aerial vehicles, capable of a range of 300 km, other than those specified in 9A005 or 9A105.a., integrated, or designed or modified to be integrated, into a liquid propellant or gel propellant propulsion system which has a total impulse capacity equal to or greater than 0,841 MNs.

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

• a. Not used;

• b. Not used;

• c. Thrust vector control sub-systems, usable in ‘missiles’; Technical Note: Examples of methods of achieving thrust vector control specified in 9A106.c. are:
• 1. Flexible nozzle;
• 2. Fluid or secondary gas injection;
• 3. Movable engine or nozzle;
• 4. Deflection of exhaust gas stream (jet vanes or probes); or
• 5. Thrust tabs.

• d. Liquid, slurry and gel propellant (including oxidisers) control systems, and specially designed components therefor, usable in ‘missiles’, designed or modified to operate in vibration environments greater than 10 g rms between 20 Hz and 2 kHz; Note:

The only servo valves, pumps and gas turbines specified in 9A106.d., are the following: - a. Servo valves designed for flow rates equal to or greater than 24 litres per minute, at an absolute pressure equal to or greater than 7 MPa, that have an actuator response time of less than 100 ms; - b. Pumps, for liquid propellants, with shaft speeds equal to or greater than 8 000 r.p.m. at a maximum operating mode or with discharge pressures equal to or greater than 7 MPa; - c. Gas turbines, for liquid propellant turbopumps, with shaft speeds equal to or greater than 8 000 r.p.m. at the maximum operating mode.

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

9A107Solid propellant rocket motors, usable in complete rocket systems or unmanned aerial vehicles, capable of a range of 300 km, other than those specified in 9A007, having total impulse capacity equal to or greater than 0,841 MNs.

• NB:

SEE ALSO 9A119.

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

• a. Rocket motor cases and ‘insulation’ components therefor, usable in subsystems specified in 9A007, 9A009, 9A107 or 9A109.a.;

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

• c. Thrust vector control sub-systems, usable in ‘missiles’. Technical Note: Examples of methods of achieving thrust vector control specified in 9A108.c. are:
• 1. Flexible nozzle;
• 2. Fluid or secondary gas injection;
• 3. Movable engine or nozzle;
• 4. Deflection of exhaust gas stream (jet vanes or probes); or
• 5. Thrust tabs.

9A109Hybrid rocket motors and specially designed components as follows:

• a. Hybrid rocket motors usable in complete rocket systems or unmanned aerial vehicles, capable of 300 km, other than those specified in 9A009, having a total impulse capacity equal to or greater than 0,841 MNs, and specially designed components therefor;

• b. Specially designed components for hybrid rocket motors specified in 9A009 that are usable in ‘missiles’.

• NB:

SEE ALSO 9A009 AND 9A119.

9A110Composite structures, laminates and manufactures thereof, other than those specified in 9A010, specially designed for use in ‘missiles’ or the subsystems specified in 9A005, 9A007, 9A105, 9A106.c., 9A107, 9A108.c., 9A116 or 9A119.

• NB:

SEE ALSO 1A002.

Technical Note:

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

9A111Pulse jet or detonation engines, usable in ‘missiles’ or unmanned aerial vehicles specified in 9A012 or 9A112.a., and specially designed components therefor.

• NB:

SEE ALSO 9A011 AND 9A118.

Technical Note:

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

9A112 ‘Unmanned aerial vehicles’ (‘UAVs’), other than those specified in 9A012, as follows:

• a. ‘Unmanned aerial vehicles’ (‘UAVs’) capable of a range of 300 km;

• b. ‘Unmanned aerial vehicles’ (‘UAVs’) having all of the following:
• 1. Having any of the following:
• a. An autonomous flight control and navigation capability; or
• b. Capability of controlled flight out of the direct vision range involving a human operator; and
• 1. Having any of the following:
• a. Incorporating an aerosol dispensing system/mechanism with a capacity greater than 20 litres; or
• b. Designed or modified to incorporate an aerosol dispensing system/mechanism with a capacity greater than 20 litres. Technical Notes: 1.

An aerosol consists of particulate or liquids other than fuel components, by products or additives, as part of the payload to be dispersed in the atmosphere. Examples of aerosols include pesticides for crop dusting and dry chemicals for cloud seeding. 2.

An aerosol dispensing system/mechanism contains all those devices (mechanical, electrical, hydraulic, etc.), which are necessary for storage and dispersion of an aerosol into the atmosphere. This includes the possibility of aerosol injection into the combustion exhaust vapour and into the propeller slip stream.

9A115Launch support equipment as follows:

• a. Apparatus and devices for handling, control, activation or launching, designed or modified for space launch vehicles specified in 9A004, sounding rockets specified in 9A104 or ‘missiles’; Technical Note: In 9A115.a. ‘missile’ means complete rocket systems and unmanned aerial vehicle systems capable of a range exceeding 300 km.

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

9A116Reentry vehicles, usable in ‘missiles’, and equipment designed or modified therefor, as follows:

• a. Reentry vehicles;

• b. Heat shields and components therefor, fabricated of ceramic or ablative materials;

• c. Heat sinks and components therefor, fabricated of light-weight, high heat capacity materials;

• d. Electronic equipment specially designed for reentry vehicles.

9A117Staging mechanisms, separation mechanisms, and interstages, usable in ‘missiles’.

• NB:

SEE ALSO 9A121.

9A118Devices to regulate combustion usable in engines, which are usable in ‘missiles’ or unmanned aerial vehicles specified in 9A012 or 9A112.a., specified in 9A011 or 9A111.

9A119Individual rocket stages, usable in complete rocket systems or unmanned aerial vehicles, capable of a range of 300 km, other than those specified in 9A005, 9A007, 9A009, 9A105, 9A107 and 9A109.

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

• Note:

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

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

Technical Note:

Interstage connectors referred to in 9A121 also include electrical connectors installed between the ‘missile’, space launch vehicle or sounding rocket and their payload.

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

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

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

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

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

• Note:

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

Technical Notes:

• 1.

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

• a. Doppler laser method;

• b. Forward laser diffraction method.

• 2.

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

9BTest, Inspection and Production Equipment

9B001Manufacturing equipment, tooling or fixtures, as follows:

• NB:

SEE ALSO 2B226

• a. Directional solidification or single crystal casting equipment designed for ‘superalloys’;

• b. Casting tooling, specially designed for manufacturing gas turbine engine blades, vanes or ‘tip shrouds’, manufactured from refractory metals or ceramics, as follows:
• 1. Cores;
• 1. Shells (moulds);
• 1. Combined core and shell (mould) units;

• c. Directional-solidification or single-crystal additive-manufacturing equipment, specially designed for manufacturing gas turbine engine blades, vanes or ‘tip shrouds’.

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

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

• b. Incorporating any of the ‘technologies’ specified in 9E003.h. or 9E003.i.

9B003Equipment specially designed for the ‘production’ or test of gas turbine brush seals designed to operate at tip speeds exceeding 335 m/s and temperatures in excess of 773 K (500 °C), and specially designed components or accessories therefor.

9B004Tools, dies or fixtures, for the solid state joining of ‘superalloy’, titanium or intermetallic airfoil-to-disk combinations described in 9E003.a.3. or 9E003.a.6. for gas turbines.

9B005On-line (real time) control systems, instrumentation (including sensors) or automated data acquisition and processing equipment, specially designed for use with any of the following:

• NB:

SEE ALSO 9B105.

• a. Wind tunnels designed for speeds of Mach 1,2 or more; Note:

9B005.a. does not control wind tunnels specially designed for educational purposes and having a ‘test section size’ (measured laterally) of less than 250 mm. Technical Note: ‘Test section size’ means the diameter of the circle, or the side of the square, or the longest side of the rectangle, at the largest test section location.

• b. Devices for simulating flow-environments at speeds exceeding Mach 5, including hot-shot tunnels, plasma arc tunnels, shock tubes, shock tunnels, gas tunnels and light gas guns; or

• c. Wind tunnels or devices, other than two-dimensional sections, capable of simulating Reynolds number flows exceeding 25 × 10⁶.

9B006Acoustic vibration test equipment capable of producing sound pressure levels of 160 dB or more (referenced to 20 μPa) with a rated output of 4 kW or more at a test cell temperature exceeding 1 273 K (1 000  °C), and specially designed quartz heaters therefor.

• NB:

SEE ALSO 9B106.

9B007Equipment specially designed for inspecting the integrity of rocket motors and using Non-Destructive Test (NDT) techniques other than planar x-ray or basic physical or chemical analysis.

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

9B009Tooling specially designed for producing gas turbine engine powder metallurgy rotor components having all of the following:

• a. Designed to operate at stress levels of 60 % of Ultimate Tensile Strength (UTS) or more measured at a temperature of 873 K (600 °C); and

• b. Designed to operate at 873 K (600 °C) or more.

• Note:

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

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

9B105 ‘Aerodynamic test facilities’ for speeds of Mach 0,9 or more, usable for ‘missiles’ and their subsystems.

• NB:

SEE ALSO 9B005.

• Note:

9B105 does not control wind-tunnels for speeds of Mach 3 or less with dimension of the ‘test cross section size’ equal to or less than 250 mm.

Technical Notes:

• 1.

In 9B105 ‘aerodynamic test facilities’ includes wind tunnels and shock tunnels for the study of airflow over objects.

• 2.

In Note to 9B105, ‘test cross section size’ means the diameter of the circle, or the side of the square, or the longest side of the rectangle, or the major axis of the ellipse at the largest ‘test cross section’ location. ‘Test cross section’ is the section perpendicular to the flow direction.

• 3.

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

9B106Environmental chambers and anechoic chambers, as follows:

• a. Environmental chambers having all of the following:
• 1. Capable of simulating any of the following flight conditions:
• a. Altitude equal to or greater than 15 km; or
• b. Temperature range from below 223 K (– 50°C) to above 398 K (125°C); and
• 1. Incorporating, or ‘designed or modified’ to incorporate, a shaker unit or other vibration test equipment to produce vibration environments equal to or greater than 10 g rms, measured ‘bare table’, between 20 Hz and 2 kHz while imparting forces equal to or greater than 5 kN; Technical Notes: 1.

9B106.a.2. describes systems that are capable of generating a vibration environment with a single wave (e.g., a sine wave) and systems capable of generating a broad band random vibration (i.e., power spectrum). 2.

In 9B106.a.2., ‘designed or modified’ means the environmental chamber provides appropriate interfaces (e.g., sealing devices) to incorporate a shaker unit or other vibration test equipment as specified in 2B116.

3.

In 9B106.a.2., ‘bare table’ means a flat table, or surface, with no fixture or fittings.

• b. Environmental chambers capable of simulating the following flight conditions:
• 1. Acoustic environments at an overall sound pressure level of 140 dB or greater (referenced to 20 μPa) or with a total rated acoustic power output of 4 kW or greater; and
• 1. Altitude equal to or greater than 15 km; or
• 1. Temperature range from below 223 K (– 50°C) to above 398 K (125°C).

9B107 ‘Aerothermodynamic test facilities’, usable for ‘missiles’, ‘missile’ rocket propulsion systems, and reentry vehicles and equipment specified in 9A116, having any of the following characteristics:

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

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

Technical Notes:

• 1.

‘Aerothermodynamic test facilities’ include plasma arc jet facilities and plasma wind tunnels for the study of thermal and mechanical effects of airflow on objects.

• 2.

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

9B115Specially designed ‘production equipment’ for the systems, sub-systems and components specified in 9A005 to 9A009, 9A011, 9A101, 9A102, 9A105 to 9A109, 9A111, 9A116 to 9A120.

9B116Specially designed ‘production facilities’ for the space launch vehicles specified in 9A004, or systems, sub-systems, and components specified in 9A005 to 9A009, 9A011, 9A101, 9A102, 9A104 to 9A109, 9A111, 9A116 to 9A120 or ‘missiles’.

Technical Note:

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

9B117Test benches or test stands for solid or liquid propellant rockets or rocket motors, having either of the following characteristics:

• a. The capacity to handle more than 68 kN of thrust; or

• b. Capable of simultaneously measuring the three axial thrust components.

9CMaterials

9C108 ‘Insulation’ material in bulk form and ‘interior lining’, other than those specified in 9A008, for rocket motor cases usable in ‘missiles’ or specially designed for solid propellant rocket engines specified in 9A007 or 9A107.

9C110Resin impregnated fibre prepregs and metal coated fibre preforms therefor, for composite structures, laminates and manufactures specified in 9A110, made either with organic matrix or metal matrix utilising fibrous or filamentary reinforcements having a ‘specific tensile strength’ greater than 7,62 × 10⁴ m and a ‘specific modulus’ greater than 3,18 × 10⁶ m.

• NB:

SEE ALSO 1C010 AND 1C210.

• Note:

The only resin impregnated fibre prepregs specified in entry 9C110 are those using resins with a glass transition temperature (Tg), after cure, exceeding 418 K (145°C) as determined by ASTM D4065 or equivalent.

9DSoftware

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

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

9D003

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

9D004Other ‘software’ as follows:

• a. 2D or 3D viscous ‘software’, validated with wind tunnel or flight test data required for detailed engine flow modelling;

• b. ‘Software’ for testing aero gas turbine engines, assemblies or components, having all of the following:
• 1. Specially designed for testing any of the following:
• a. Aero gas turbine engines, assemblies or components, incorporating ‘technology’ specified in 9E003.a., 9E003.h. or 9E003.i.; or
• b. Multi-stage compressors providing either bypass or core flow, specially designed for aero gas turbine engines incorporating ‘technology’ specified in 9E003.a. or 9E003.h.; and
• 1. Specially designed for all of the following:
• a. Acquisition and processing of data, in real time; and
• b. Feedback control of the test article or test conditions (e.g. temperature, pressure, flow rate) while the test is in progress; Note:

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

- c. ‘Software’ specially designed to control directional solidification or single crystal material growth in equipment specified in 9B001.a. or 9B001.c.;

- d. Not used;

• e. ‘Software’ specially designed or modified for the operation of items specified in 9A012;

• f. ‘Software’ specially designed to design the internal cooling passages of aero gas turbine blades, vans and ‘tip shrouds’;

• g. ‘Software’ having all of the following:
• 1. Specially designed to predict aero thermal, aeromechanical and combustion conditions in aero gas turbine engines; and
• 1. Theoretical modelling predictions of the aero thermal, aeromechanical and combustion conditions, which have been validated with actual aero gas turbine engine (experimental or production) performance data.

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

• NB:

For ‘software’ for items listed in 9A004.d. that are incorporated into ‘spacecrafts payloads’, see the appropriate Categories.

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

9D103

‘Software’ specially designed for modelling, simulation or design integration of the space launch vehicles specified in 9A004, sounding rockets specified in 9A104 or ‘missiles’, or the subsystems specified in 9A005, 9A007, 9A105, 9A106.c., 9A107, 9A108.c., 9A116 or 9A119.

- Note:

‘Software’ specified in 9D103 remains controlled when combined with specially designed hardware specified in 4A102.

9D104 ‘Software’ as follows:

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

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

9D105

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

- Note:

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

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

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

Technical Note:

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

9ETechnology

• Note:

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

9E001

‘Technology’ according to the General Technology Note for the ‘development’ of equipment or ‘software’, specified in 9A001.b., 9A004 to 9A012, 9A350, 9B or 9D.

9E002 ‘Technology’ according to the General Technology Note for the ‘production’ of equipment specified in 9A001.b., 9A004 to 9A011, 9A350 or 9B.

- NB:

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

9E003Other ‘technology’ as follows:

• a. ‘Technology’‘required’ for the ‘development’ or ‘production’ of any of the following gas turbine engine components or systems:
• 1. Gas turbine blades, vanes or ‘tip shrouds’, made from directionally solidified (DS) or single crystal (SC) alloys and having (in the 001 Miller Index Direction) a stress-rupture life exceeding 400 hours at 1 273 K (1 000  °C) at a stress of 200 MPa, based on the average property values; Technical Note: For the purposes of 9E003.a.1., stress-rupture life testing is typically conducted on a test specimen.
• 1. Combustors having any of the following:
• a. ‘Thermally decoupled liners’ designed to operate at ‘combustor exit temperature’ exceeding 1 883 K (1 610  °C);
• b. Non-metallic liners;
• c. Non-metallic shells; or
• d. Liners designed to operate at ‘combustor exit temperature’ exceeding 1 883 K (1 610  °C) and having holes that meet the parameters specified in 9E003.c.; Note:

The ‘required’ ‘technology’ for holes in 9E003.a.2. is limited to the derivation of the geometry and location of the holes. Technical Notes: 1.

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

‘Combustor exit temperature’ is the bulk average gas path total (stagnation) temperature between the combustor exit plane and the leading edge of the turbine inlet guide vane (i.e., measured at engine station T40 as defined in SAE ARP 755A) when the engine is running in a ‘steady state mode’ of operation at the certificated maximum continuous operating temperature. NB:

*See 9E003.c. for ‘technology’