The Export of Goods (Control) Order 1994

Equipment, Assemblies and Components

9A—9A001 Aero gas turbine engines incorporating any of the technologies specified in head a. of entry 9E003., as follows(1):

a. Not certified for the specific civil aircraft for which they are intended;

b. Not certified for civil use by the aviation authorities in a relevant country;

In this head, “relevant country” means an authority in Australia, Belgium, Canada, Denmark, Eire, France, Germany, Greece, Italy, Japan, Luxembourg, Netherlands, Norway, Portugal, Spain, Turkey, United Kingdom or United States of America.

c. Designed to cruise at speeds exceeding Mach 1.2 for more than thirty minutes.

9A002 Marine gas turbine engines with an ISO standard continuous power rating of 24,245 kW or more and a specific fuel consumption of less than 0.219 kg/kWh at any point in the power range from 35 to 100%, and specially designed assemblies and components therefor.

• Note: Marine gas turbine engines includes those industrial, or aero-derivative, gas turbine engines adapted for marine propulsion or shipboard power generation.

9A003 Specially designed assemblies and components, incorporating any of the technologies specified in head a. of entry 9E003, for the following gas turbine engine propulsion systems:

a. Specified in entry 9A001; or

b. Whose design or production origins are unknown to the manufacturer.

• Note: This entry does not specify multiple domed combustors operating at average burner outlet temperatures equal to or less than 1,813 K (1,540°C).

9A004 Space launch vehicles or spacecraft (not including their payloads)(2).

9A005 Liquid rocket propulsion systems containing any of the systems or components specified in entry 9A006(3).

9A006 Systems or components, as follows(4), specially designed for liquid rocket propulsion systems:

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).

9A007 Solid rocket propulsion systems with any of the following,(5):

a. 1. Total impulse capacity exceeding 1.1 MNs; or

2. 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;

b. 1. Stage mass fractions exceeding 88%; and

2. Propellant solid loadings exceeding 86%;

c. Any of the components specified in entry 9A008; or

d. 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.

• Note: For the purposes of head d. of this entry, a strong mechanical bond means bond strength equal to or more than propellant strength.

9A008 Components, as follows(6), specially designed for solid rocket propulsion systems:

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(7) 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(8).

9A011 Ramjet, scramjet or combined cycle engines and specially designed components therefor(9).

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(10).

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:

  a.

  Flexible Nozzle;

  b.

  Fluid or secondary gas injection;

  c.

  Movable engine or nozzle;

  d.

  Deflection of exhaust gas stream (jet vanes or probes); or

  e.

  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:

  a.

  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;

  b.

  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(11).

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:

  a.

  Flexible Nozzle;

  b.

  Fluid or secondary gas injection;

  c.

  Movable engine or nozzle;

  d.

  Deflection of exhaust gas stream (jet vanes or probes); or

  e.

  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(12).

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(13).

• Note: The only resin impregnated fibre prepregs specified in this entry are those using resins with a glass transition temperature (T_g), 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(14).

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.

(1)

See also entry 9A101.

(2)

See also entry 9A104. See the appropriate categories for products contained in spacecraft payloads.

(3)

See also entries 9A105 and 9A119.

(4)

See also entry 9A106.

(5)

See also entry 9A119.

(6)

See also entry 9A108.

(7)

See also entries 9A109 and 9A119.

(8)

See also entries IA002 and 9A110.

(9)

See also entries 9A111 and 9A118.

(10)

See also entry 9A119.

(11)

See also entry 9A119.

(12)

See also entry 9A119.

(13)

See also entry 1A002.

(14)

See also entries 9A011 and 9A118.