The Export of Goods (Control) Order 1994

• (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;

• Note: For the purposes of head a. of this entry, a 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;

• Note: The 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:

• (1) Omni-axial movement exceeding ±5°;

• (2) Angular vector rotations of 20°/s or more; or

• (3) Angular vector accelerations of 40°/s² or more.

• (9A009) Hybrid rocket propulsion systems[^f00076] with:

• (a) Total impulse capacity exceeding 1.1 MNs; or

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

• (9A010) Specially designed components or structures, for launch vehicles or launch vehicle propulsion systems, manufactured using metal matrix composite, organic composite, ceramic matrix or intermetallic reinforced materials specified in entries 1C007 or 1C010[^f00077].

• (9A011) Ramjet, scramjet or combined cycle engines and specially designed components therefor[^f00078].

• (9A101) Lightweight turbojet and turbofan engines (including turbocompound engines) usable in missiles, other than those specified in entry 9A001, as follows;

• (a) Engines having both of the following characteristics:

• (1) Maximum thrust value greater than 1 kN (achieved un-installed) excluding civil certified engines with a maximum thrust value greater than 8.89 kN (achieved un-installed); and

• (2) Specific fuel consumption of 0.13 kg/N/hr or less (at sea level static and standard conditions); or

• (b) Engines designed or modified for use in missiles.

• (9A104) Sounding rockets, capable of a range of at least 300 km.

• (9A105) Liquid propellant rocket engines usable in missiles, other than those specified in entry 9A005, having a total impulse capacity of 0.841 MNs or greater[^f00079].

• (9A106) Systems or components, other than those specified in entry 9A006, usable in missiles, as follows, specially designed for liquid rocket propulsion systems:

• (a) Rocket nozzles;

• (b) Thrust vector control sub-systems;

• Note: Examples of methods of achieving thrust vector control specified in head b. of this entry are: Flexible Nozzle; Fluid or secondary gas injection; Movable engine or nozzle; Deflection of exhaust gas stream (jet vanes or probes); or Thrust tabs.

• (c) Liquid and slurry propellant (including oxidiser) control systems, and specially designed components therefor, designed or modified to operate in vibration environments of more than 10 g rms between 20 Hz and 2000 Hz.

• Note: The only servo valves and pumps specified in head c. of this entry are as follows: Servo valves designed for flow rates of 24 litres per minute or greater, at an absolute pressure of 7 MPa or greater, that have an actuator response time of less than 100 ms; Pumps, for liquid propellants, with shaft speeds equal to or greater than 8,000 rpm or with discharge pressures equal to or greater than 7 MPa.

• (9A107) Solid propellant rocket engines, usable in missiles, other than those specified in entry 9A007 having a total impulse capacity of 0.841 MNs or greater[^f00080].

• (9A108) Components, other than those specified in entry 9A008, usable in missiles, as follows, specially designed for solid rocket propulsion systems:

• (a) Rocket motor cases, interior lining and insulation therefor;

• (b) Rocket nozzles;

• (c) Thrust vector control sub-systems.

• Note: Examples of methods of achieving thrust vector control specified in head c. of this entry are: Flexible Nozzle; Fluid or secondary gas injection; Movable engine or nozzle; Deflection of exhaust gas stream (jet vanes or probes); or Thrust tabs.

• Note: In this entry, “interior lining” means suited for the bond interface between the solid propellant and the case or insulating liner; usually a liquid polymer based dispersion of refractory or insulating materials, e.g. carbon filled hydroxy-terminated polybutadiene (HTPB) or other polymer with added curing agents sprayed or screeded over a case interior.

• (9A109) Hybrid rocket motors, usable in missiles, other than those specified in entry 9A009, and specially designed components therefor[^f00081].

• (9A110) Composite structures, laminates and manufactures thereof, other than those specified in entry 9A010, specially designed for use in the systems specified in entries 9A004 or 9A104 or the subsystems specified in entries 9A005, 9A007, 9A105 to 9A108, 9A116 or 9A119, and resin impregnated fibre prepregs and metal coated fibre preforms therefor, made either with organic matrix or metal matrix utilising fibrous or filamentary reinforcements having a specific tensile strength greater than 7.62 x 10⁴ m and a specific modulus greater than 3.18 x 10⁶ m[^f00082].

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

• (9A111) Pulse jet engines, usable in missiles, and specially designed components therefor[^f00083].

• (9A115) Launch support equipment, designed or modified for systems specified in entries 9A004 or 9A104, as follows:

• (a) Apparatus and devices for handling, control, activation or launching;

• (b) Vehicles for transport, handling, control, activation or launching.

• (9A116) Reentry vehicles, usable in missiles, and equipment designed or modified therefor, as follows:

• (a) Heat shields and components therefor fabricated of ceramic or ablative materials;

• (b) Heat sinks and components therefor fabricated of light-weight, high heat capacity materials;

• (c) Electronic equipment specially designed for reentry vehicles.

• (9A117) Staging mechanisms, separation mechanisms, and interstages, usable in missiles.

• (9A118) Devices to regulate combustion usable in engines, which are usable in missiles, specified in entries 9A011 or 9A111.

• (9A119) Individual rocket stages, usable in missiles, other than those specified in entries 9A005, 9A007, 9A009, 9A105, 9A107 or 9A109.

• (9A990) The export of goods specified in this entry is prohibited to any destination in Libya, Iran, Iraq, Syria or South Africa.

• Aircraft having a maximum all up weight of 390 kg or more, and aeroengines, and equipment or components designed therefor, other than those specified eleswhere in this Schedule.

• (9A991) Aircraft or steerable parachutes other than those specified in entry ML10 of Group 1 of Part III of this Schedule, having a maximum all up weight of not more than 390 kg.

• (9A993) The export of goods specified in this entry is prohibited to any destination in Libya.

• Equipment for simulating or modelling any function of any aircraft or any part of any aircraft, specially designed components and specially designed accessories therefor.

9B

Test, Inspection and Production Equipment

• (9B001) Specially designed equipment, tooling or fixtures, as follows, for manufacturing or measuring gas turbine blades, vanes or tip shroud castings:

• (a) Automated equipment using non-mechanical methods for measuring airfoil wall thickness;

• (b) Tooling, fixtures or measuring equipment for the laser, water jet or ECM/EDM hole drilling processes specified in head c. of entry 9E003;

• (c) Directional solidification or single crystal casting equipment;

• (d) Ceramic cores or shells;

• (e) Ceramic core manufacturing equipment or tools;

• (f) Ceramic core leaching equipment;

• (g) Ceramic shell wax pattern preparation equipment;

• (h) Ceramic shell burn out or firing equipment.

• (9B002) On-line (real time) control systems, instrumentation (including sensors) or automated data acquisition and processing equipment, specially designed for the development of gas turbine engines, assemblies or components incorporating technologies specified in head a. of entry 9E003.

• (9B003) Equipment specially designed for the production or test of gas turbine brush seals designed to operate at tip speeds exceeding 335 m/s, and specially designed parts or accessories therefor.

• (9B004) Tools, dies or fixtures for the solid state joining of gas turbine superalloy or titanium components.

• (9B005) On-line (real time) control systems, instrumentation (including sensors) or automated data acquisition and processing equipment, specially designed for use with the following wind tunnels or devices[^f00084]:

• (a) Wind tunnels designed for speeds of Mach 1.2 or more;

• except:

those specially designed for educational purposes and having a test section size (measured laterally) of less than 250 mm;

• In this head, “Test section size” means the diameter of the circle, or the side of a square, or the longest side of a 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;

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

• (9B006) Specially designed acoustic vibration test equipment capable of producing sound pressure levels of 160 dB or more (referenced to 20 micropascals) with a rated output of 4 kW or more at a test cell temperature exceeding 1,273 K (1,000°C), and specially designed transducers, strain gauges, accelerometers, thermocouples or quartz heaters therefor.

• (9B007) Equipment specially designed for inspecting the integrity of rocket motors using non-destructive test (NDT) techniques other than planar X-ray or basic physical or chemical analysis[^f00085].

• (9B008) Transducers specially designed for the direct measurement of the wall skin friction of the test flow with a stagnation temperature exceeding 833 K (560°C).

• (9B009) Tooling specially designed for producing turbine engine powder metallurgy rotor components capable of operating at stress levels of 60% of ultimate tensile strength (UTS) or more and metal temperatures of 873 K (600°C) or more.

• (9B105) Wind tunnels for speeds of Mach 0.9 or more, usable for missiles and their subsystems.

• (9B106) Environmental chambers and anechoic chambers, as follows:

• (a) Environmental chambers capable of simulating the following flight conditions:

• (1) Vibration environments of 10 g rms or greater between 20 Hz and 2,000 Hz and imparting forces of 5 kN or greater; and

• (2) Altitudes of 15,000 m or greater; or

• (3) Temperature of at least 223 K (-50°C) to 398 K (+ 125°C);

• (b) Anechoic 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 micropascals) or with a rated power output of 4 kW or greater; and

• (2) Altitudes of 15,000 m or greater; or

• (3) Temperature of at least 223 K (-50°C) to 398 K (+ 125°C).

• (9B115) Specially designed production equipment for the systems, sub-systems and components specified in entries 9A005 to 9A009, 9A011, 9A101, 9A105 to 9A109, 9A111, 9A116 to 9A119.

• (9B116) Specially designed production facilities for the systems, sub-systems, and components specified in entries 9A004 to 9A009, 9A011, 9A101, 9A104 to 9A109, 9A111, 9A116 to 9A119.

• (9B117) Test benches and test stands for solid or liquid propellant rockets or rocket motors, having either of the following characteristics:

• (a) The capacity to handle more than 90 kN of thrust; or

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

9C

Materials

• None

9D

Software

• (9D001) Software required for the development of goods or technology specified in sub-categories 9A, 9B or entry 9E003.

• (9D002) Software required for the production of goods specified in sub-categories 9A or 9B.

• (9D003) Software required for the use of full authority digital electronic engine controls (FADEC) for propulsion systems specified in sub-category 9A or equipment specified in sub-category 9B, as follows:

• (a) Software in digital electronic controls for propulsion systems, aerospace test facilities or air breathing aero-engine test facilities;

• (b) Fault-tolerant software used in FADEC systems for propulsion systems and associated test facilities.

• (9D004) Other software, as follows:

• (a) Software specially designed for vibration test equipment, other than that specified in entry 2D101, using real time digital controls with individual exciters (thrusters) with a maximum thrust exceeding 100 kN;

• (b) 2D or 3D viscous software validated with wind tunnel or flight test data required for detailed engine flow modelling;

• (c) Software required for the development or production of real time full authority electronic test facilities for engines or components specified in sub-category 9A;

• (d) Software for testing aero gas turbine engines, assemblies or components, specially designed to collect, reduce and analyse data in real time, and capable of feedback control, including the dynamic adjustment of test articles or test conditions, as the test is in progress;

• (e) Software specially designed to control directional solidification or single crystal casting;

• (f) Software in source code, object code or machine code required for the use of active compensating systems for rotor blade tip clearance control.

• Note: Head f. of this entry does not specify software embedded in non-specified equipment or required for maintenance activities associated with the calibration or repair or updates to the active compensating clearance control system.

• (9D101) Software specially designed for the use of goods specified in entries 9B105, 9B106, 9B116 or 9B117.

• (9D103) Software specially designed for modelling, simulation or design integration of the systems specified in entries 9A004 or 9A104 or the sub-systems specified in entries 9A005, 9A007, 9A105 to 9A108, 9A116 or 9A119.

• Note: Software specified in this entry remains controlled when combined with specially designed hardware specified in entry 4A102.

• (9D993) The export of goods specified in this entry is prohibited to any destination in Libya.

• Software specially designed or modified for the use of goods specified in entry 9A993.

9E

Technology

• (9E001) Technology required for the development of goods specified in head c. of entry 9A001, or entries 9A004 to 9A011, or sub-Categories 9B or 9D.

• (9E002) Technology required for the production of goods[^f00086] specified in head c. of entry 9A001, or entries 9A004 to 9A011 or sub-Category 9B.

• Notes: Development or production technology specified in sub-category 9E for gas turbine engines remains specified when used as use technology for repair, rebuild and overhaul. This entry does not include 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. For technology for the repair of specified structures, laminates or materials, see head f. of entry 1E002.

• (9E003) Other technology, as follows:

• (a) Technology required for the development or production of the following gas turbine engine components or systems:

• (1) Directionally solidified gas turbine blades, vanes or tip shrouds rated to operate at gas path temperatures exceeding 1,593 K (1,320°C);

• (2) Single crystal blades, vanes or tip shrouds;

• (3) Multiple domed combustors operating at average burner outlet temperatures exceeding 1,643 K (1,370°C), or combustors incorporating thermally de-coupled combustion liners, non-metallic liners or non-metallic shells;

• (4) Components manufactured from organic composite materials designed to operate above 588 K (315°C), or from metal matrix composite, ceramic matrix, intermetallic or intermetallic reinforced materials specified in entries 1A002 or 1C007;

• (5) Uncooled turbine blades, vanes, tip-shrouds or other components designed to operate at gas path temperatures of 1,323 K (1,050°C) or more;

• (6) Cooled turbine blades, vanes or tip-shrouds, other than those described in sub-heads a.1. and a.2. of this entry, exposed to gas path temperatures of 1,643 K (1,370°C) or more;

• (7) Airfoil-to-disk blade combinations using solid state joining;

• (8) Gas turbine engine components using diffusion bonding technology specified in head b. of entry 2E003;

• (9) Damage tolerant gas turbine engine rotating components using powder metallurgy materials specified in head b. of entry 1C002;

• (10) FADEC for gas turbine and combined cycle engines and their related diagnostic components, sensors and specially designed components;

• (11) Adjustable flow path geometry and associated control systems for:

• (a) Gas generator turbines;

• (b) Fan or power turbines;

• (c) Propelling nozzles;

• Notes:

• (1) Adjustable flow path geometry and associated control systems do not include inlet guide vanes, variable pitch fans, variable stators or bleed valves for compressors.

• (2) Sub-head a.11. of this entry does not specify development or production technology for adjustable flow path geometry for reverse thrust.

• (12) Rotor blade tip clearance control systems employing active compensating casing technology limited to a design and development data base;

• (13) Gas bearings for gas turbine engine rotor assemblies;

• (14) Wide chord hollow fan blades without part-span support;

• (b) Technology required for the development or production of:

• (1) Wind tunnel aero-models equipped with non-intrusive sensors capable of transmitting data from the sensors to the data acquisition system;

• (2) Composite propeller blades or propfans capable of absorbing more than 2,000 kW at flight speeds exceeding Mach 0.55;

• (c) Technology required for the development or production of gas turbine engine components using laser, water jet or ECM/EDM hole drilling processes to produce holes with:

• (1)

• (a) Depths more than four times their diameter;

• (b) Diameters less than 0.76 mm; and

• (c) Incidence angles equal to or less than 25°; or

• (2)

• (a) Depths more than five times their diameter;

• (b) Diameters less than 0.4 mm; and

• (c) Incidence angles of more than 25°;

• Note: For the purposes of head c. of this entry, incidence angle is measured from a plane tangential to the airfoil surface at the point where the hole axis enters the airfoil surface.

• (d) Technology required for the development or production of helicopter power transfer systems or tilt rotor or tilt wing aircraft power transfer systems:

• (1) Capable of loss-of-lubrication operation for 30 minutes or more; or

• (2) Having an input power-to-weight ratio equal to or more than 8.87 kW/kg;

• (e)

• (1) Technology for the development or production of reciprocating diesel engine ground vehicle propulsion systems having all of the following:

• (a) A box volume of 1.2 m³ or less;

• (b) An overall power output of more than 750 kW based on Council Directive 80/1269/EEC[^f00087] or ISO 2534; and

• (c) A power density of more than 700 kW/m³ of box volume;

• Note: Box volume is the product of three perpendicular dimensions measured in the following way:

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

• Width: The widest of the following:

• (a) The outside dimension from valve cover to valve cover;

• (b) The dimensions of the outside edges of the cylinder heads; or

• (c) The diameter of the flywheel housing;

• Height: The largest of the following:

• (a) The dimension of the crankshaft centre-line to the top plane of the valve cover (or cylinder head) plus twice the stroke; or

• (b) The diameter of the flywheel housing.

• (2) Technology required for the production of specially designed components, as follows, for high output diesel engines:

• (a) Technology required for the production of engine systems having all of the following components employing ceramics materials specified in entry 1C007:

• (1) Cylinder liners;

• (2) Pistons;

• (3) Cylinder heads; and

• (4) One or more other components (including exhaust ports, turbo-chargers, valve guides, valve assemblies or insulated fuel injectors);

• (b) Technology required for the production of turbocharger systems, with single-stage compressors having all of the following:

• (1) Operating at pressure ratios of 4:1 or higher;

• (2) A mass flow in the range from 30 to 130 kg per minute; and

• (3) Variable flow area capability within the compressor or turbine sections;

• (c) Technology required for the production of fuel injection systems with a specially designed multifuel (e.g., diesel or jet fuel) capability covering a viscosity range from diesel fuel (2.5 cSt at 310.8 K (37.8°C)) down to gasoline fuel (0.5 cSt at 310.8 K (37.8°C)), having both of the following:

• (1) Injection amount in excess of 230 mm³ per injection per cylinder; and

• (2) Specially designed electronic control features for switching governor characteristics automatically depending on fuel property to provide the same torque characteristics by using the appropriate sensors;

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

• Note: High output diesel engines are diesel engines with a specified brake mean effective pressure of 1.8 MPa or more at a speed of 2,300 rpm, provided the rated speed is 2,300 rpm or more.

• (9El01) Technology required for the development or production of goods specified in entries 9A101, 9A104 to 9A111 or 9A115 to 9A119.

• (9E102) Technology required for the use of goods specified in entries 9A004 to 9A011, 9A101, 9A104 to 9A111, 9A115 to 9A119, 9B105, 9B106, 9B115 to 9B117, 9D101 or 9D103.

• (9E990) The export of goods specified in this entry is prohibited to any destination in Libya, Iran, Iraq, Syria or South Africa.

• Technology required for the development, production or use of goods specified in entry 9A990.

• (9E991) Technology required for the development, production or use of goods specified in entry 9A991.

• (9E993) The export of goods specified in this entry is prohibited to any destination in Libya.

• Technology required for the development, production or use of goods specified in entry 9A993.

SCHEDULE 2 — REVOCATIONS

PART 1 — INSTRUMENTS PARTIALLY REVOKED

(1)	(2)	(3)
Order Revoked	Reference	Extent of Revocation
The Export of Goods (Control) Order 1992	S.I. 1992/3092	The whole Order except in so far as it applies to the exportation of goods specified in Group 2 of Part 1 of Schedule 1 thereto (“Antiques”).

PART 2 — INSTRUMENTS WHOLLY REVOKED