9
AEROSPACE AND PROPULSION
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# 9A.
Systems, Equipment and Components
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# 9A001.
Aero gas turbine engines having any of the following:
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# 9A002.
'Marine gas turbine engines' designed to use liquid fuel and having all of the following, and specially designed assemblies and components therefor:
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# 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
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# b.
'Corrected specific fuel consumption' not exceeding 0.219 kg/kWh at 35% of the maximum continuous power when using liquid fuel.
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# 9A003.
Specially designed assemblies or components, incorporating any of the "technologies" specified in 9E003.a., 9E003.h., 9E003i., or 9E003.k., for any of the following aero gas turbine engines:
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# 9A004.
Space launch vehicles, "spacecraft", "spacecraft buses", "spacecraft mission equipment", "spacecraft" on-board systems or equipment, terrestrial equipment, air-launch platforms and "sub-orbital craft", as follows:
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# a.
Space launch vehicles;
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# b.
"Spacecraft";
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# c.
"Spacecraft buses";
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# d.
"Spacecraft mission equipment" 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.;
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# e.
On-board systems or equipment, specially designed for "spacecraft" and having any of the following functions:
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# f.
Terrestrial equipment specially designed for "spacecraft", as follows:
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# 1.
Telemetry and telecommand equipment specially designed for any of the following data processing functions:
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# 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
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# b.
Command data processing for formatting command data being sent to the "spacecraft" to control the "spacecraft bus";
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# 2.
Simulators specially designed for 'verification of operational procedures' of "spacecraft";
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# g.
"Aircraft" specially designed or modified to be air-launch platforms for space launch vehicles or “sub orbital craft”;
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# h.
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# 9A005.
Liquid rocket propulsion systems containing any of the systems or components, specified in 9A006.
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# 9A006.
Systems and components, specially designed for liquid rocket propulsion systems, as follows:
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# a.
Cryogenic refrigerators, flightweight dewars, cryogenic heat pipes or cryogenic systems, designed to restricted cryogenic fluid losses to less than 30% per year;
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# b.
Cryogenic containers or closed-cycle refrigeration systems, designed to maintain or produce temperatures less than or equal to 100 K (-173.15°C);
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# c.
Slush hydrogen storage or transfer systems;
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# d.
High pressure (exceeding 17.5 MPa) turbo pumps, pump components or their associated gas generator or expander cycle turbine drive systems;
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# e.
High-pressure (exceeding 10.6 MPa) thrust chambers and nozzles therefor;
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# f.
Propellant storage systems using the principle of capillary containment or positive expulsion (i.e., with flexible bladders);
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# g.
Liquid propellant injectors with individual orifices of 0.381 mm or smaller in diameter (an area of 1.14 x 10-3 cm2 or smaller for non-circular orifices) and specially designed for liquid rocket engines;
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# 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.
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# 9A007.
Solid rocket propulsion systems having any of the following:
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# a.
Total impulse capacity exceeding 1.1 MNs;
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# 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;
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# c.
Stage mass fractions exceeding 88% and propellant solid loadings exceeding 86%;
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# d.
Components specified in 9A008; or
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# 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.
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# 9A008.
Components specially designed for solid rocket propulsion systems, as follows:
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# 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;
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# b.
Filament-wound "composite" motor cases exceeding 0.61 m in diameter or having 'structural efficiency ratios (PV/W)' exceeding 25 km;
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# c.
Nozzles with thrust levels exceeding 45 kN or nozzle throat erosion rates of less than 0.075 mm/s;
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# d.
Movable nozzle or secondary fluid injection thrust vector control systems, capable of any of the following:
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# 9A009.
Hybrid rocket propulsion systems having any of the following:
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# 9A010.
Specially designed components, systems and structures, for launch vehicles, launch vehicle propulsion systems or "spacecraft", as follows:
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# a.
Components and structures, each exceeding 10 kg and specially designed for launch vehicles manufactured using any of the following:
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# b.
Components and structures, specially designed for launch vehicle propulsion systems specified in 9A005 to 9A009 manufactured using any of the following:
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# c.
Structural components and isolation systems, specially designed to control actively the dynamic response or distortion of "spacecraft" structures;
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# 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.
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# 9A011.
Ramjet, scramjet or 'combined cycle engines', and specially designed components
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# 9A012.
"Unmanned aerial vehicles" ("UAVs"), unmanned "airships", related equipment and components, as follows:
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# 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:
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# b.
Related equipment and components, as follows:
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# 1.
Not used;
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# 2.
Not used;
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# 3.
Equipment or components, specially designed to convert a manned "aircraft" or manned "airship", to a "UAV" or unmanned "airship", specified in 9A012.a.;
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# 4.
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).
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# 9A101.
Turbojet and turbofan engines, other than those specified in 9A001, as follows;
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# 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.
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# 9A104.
Sounding rockets, capable of a range of at least 300 km.
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# 9A105.
Liquid propellant rocket engines or gel propellant rocket motors, as follows:
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# 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;
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# 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.
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# 9A106.
Systems or components, other than those specified in 9A006 as follows, specially designed for liquid rocket propulsion or gel propellant rocket systems:
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# a.
Not used;
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# b.
Not used;
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# c.
Thrust vector control sub-systems, usable in "missiles";
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# 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;
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# e.
Combustion chambers and nozzles for liquid propellant rocket engines or gel propellant rocket motors specified in 9A005 or 9A105.
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# 9A107.
Solid 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.
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# 9A108.
Components, other than those specified in 9A008, as follows, specially designed for solid and hybrid rocket propulsion systems:
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# 9A109.
Hybrid rocket motors and specially designed components as follows:
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# 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;
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# b.
Specially designed components for hybrid rocket motors specified in 9A009 that are usable in "missiles".
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# 9A110.
Composite 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.
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# 9A111.
Pulse jet or detonation engines, usable in "missiles" or unmanned aerial vehicles specified in 9A012 or 9A112.a., and specially designed components therefor.
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# 9A112.
"Unmanned Aerial Vehicles" ("UAVs"), other than those specified in 9A012, as follows:
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# 9A115.
Launch support equipment as follows:
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# 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';
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# 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".
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# 9A116.
Reentry vehicles, usable in "missiles", and equipment designed or modified therefor, as follows:
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# 9A117.
Staging mechanisms, separation mechanisms, and interstages, usable in "missiles".
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# 9A118.
Devices to regulate combustion usable in engines, which are usable in "missiles" or "Unmanned Aerial Vehicles" ("UAVs") capable of a range of 300 km specified in 9A012 or 9A112.a., specified in 9A011 or 9A111.
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# 9A119.
Individual rocket stages, usable in complete rocket systems or "Unmanned Aerial Vehicles" ("UAVs"), capable of a range of 300 km, other than those specified in 9A005, 9A007, 9A009, 9A105, 9A107 and 9A109.
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# 9A120.
Liquid 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.
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# 9A121.
Umbilical and interstage electrical connectors specially designed for "missiles", space launch vehicles specified in 9A004 or sounding rockets specified in 9A104.
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# 9A350.
Spraying or fogging systems, specially designed or modified for fitting to aircraft, "lighter-than-air vehicles" or "Unmanned Aerial Vehicles" ("UAVs"), and specially designed components therefor, as follows:
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# 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;
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# 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;
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# c.
Aerosol generating units specially designed for fitting to systems specified in 9A350.a. and b.
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# 9B.
Test, Inspection and Production Equipment
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# 9B001.
Manufacturing equipment, tooling or fixtures, as follows:
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# a.
Directional solidification or single crystal casting equipment designed for "superalloys";
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# b.
Casting tooling, specially designed for manufacturing gas turbine engine blades, vanes or "tip shrouds", manufactured from refractory metals or ceramics, as follows:
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# c.
Directional-solidification or single-crystal additive-manufacturing equipment designed for "superalloys";
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# 9B002.
On-line (real time) control systems, instrumentation (including sensors) or automated data acquisition and processing equipment, having all of the following:
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# a.
Specially designed for the "development" of gas turbine engines, assemblies or components; and
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# b.
Incorporating any of the "technologies" specified in 9E003.h. or 9E003.i.
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# 9B003.
Equipment specially designed for the "production" or test of gas turbine engine 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.
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# 9B004.
Tools, dies or fixtures, for the solid-state joining of "superalloy", titanium or intermetallic aerofoil-to-disk combinations described in 9E003.a.3. or 9E003.a.6. for gas turbine engines.
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# 9B005.
On-line (real time) control systems, instrumentation (including sensors) or automated data acquisition and processing equipment, specially designed for use with any of the following:
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# a.
Wind tunnels designed for speeds of Mach 1.2 or more;
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# 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
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# c.
Wind tunnels or devices, other than two-dimensional sections, capable of simulating Reynolds number flows exceeding 25 x 10
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# 9B006.
Acoustic 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.
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# 9B007.
Equipment 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.
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# 9B008.
Direct measurement wall skin friction transducers specially designed to operate at a test flow total (stagnation) temperature exceeding 833 K (560°C).
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# 9B009.
Tooling specially designed for producing gas turbine engine powder metallurgy rotor components having all of the following:
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# 9B010.
Equipment specially designed for the "production" of items specified in 9A012.
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# 9B105.
'Aerodynamic test facilities' for speeds of Mach 0.9 or more, usable for 'missiles' and their subsystems.
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# 9B106.
Environmental chambers and anechoic chambers, as follows:
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# a.
Environmental chambers having all of the following:
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# 1.
Capable of simulating any of the following flight conditions:
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# 2.
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;
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# b.
Environmental chambers capable of simulating the following flight conditions:
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# 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:
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# 9B115.
Specially 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.
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# 9B116.
Specially 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'.
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# 9B117.
Test benches or test stands for solid or liquid propellant rockets or rocket motors, having either of the following characteristics:
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# 9C.
Materials
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# 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.
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# 9C110.
Resin 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 x 104 m and a "specific modulus" greater than 3.18 x 106 m.
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# 9D.
Software
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# 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.
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# 9D002.
"Software", not specified in 9D003 or 9D004, specially designed or modified for the "production" of equipment specified in 9A001 to 9A119 or 9B.
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# 9D003.
"Software" incorporating "technology" specified in 9E003.h. and used in "FADEC Systems" for systems specified in 9A or equipment specified in 9B.
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# 9D004.
Other "software" as follows:
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# a.
2D or 3D viscous "software", validated with wind tunnel or flight test data required for detailed engine flow modelling;
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# b.
"Software" for testing aero gas turbine engines, assemblies or components, having all of the following:
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# 1.
Specially designed for testing any of the following:
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# a.
Aero gas turbine engines, assemblies or components, incorporating "technology" specified in 9E003.a., 9E003.h. or 9E003.i.; or
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# 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
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# 2.
Specially designed for all of the following:
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# c.
"Software" specially designed to control directional solidification or single-crystal material growth in equipment specified in 9B001.a. or 9B001.c.;
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# d.
Not used;
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# e.
"Software" specially designed or modified for the operation of items specified in 9A012;
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# f.
"Software" specially designed to design the internal cooling passages of aero gas turbine blades, vans and "tip shrouds";
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# g.
"Software" having all of the following:
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# 1.
Specially designed to predict aero thermal, aeromechanical and combustion conditions in aero gas turbine engines; and
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# 2.
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.
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# 9D005.
"Software" specially designed or modified for the operation of items specified in 9A004.e. or 9A004.f.
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# 9D101.
"Software" specially designed or modified for the "use" of goods specified in 9B105, 9B106, 9B107, 9B116 or 9B117.
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# 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.
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# 9D104.
"Software" as follows:
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# 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.
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# 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.
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# 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'.
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# 9E.
Technology
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# 9E001.
"Technology" according to the General Technology Note for the "development" of equipment or "software", specified in 9A004 to 9A012, 9A350, 9B or 9D.
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# 9E002.
"Technology" according to the General Technology Note for the "production" of equipment specified in 9A004 to 9A011, 9A350 or 9B.
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# 9E003.
Other "technology" as follows:
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# a.
"Technology" "required" for the "development" or "production" of any of the following gas turbine engine components or systems:
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# 1.
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.
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# 2.
Combustors having any of the following:
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# 1.
For the purposes of 9E003.a.2.a., '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.
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# 2.
For the purposes of 9E003.a.2.a. and 9E003.a.2.d., '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.
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# 3.
For the purposes of 9E003.a.2.e., 'pressure gain combustion' refers to a combustor where the bulk average stagnation pressure at the combustor outlet is greater than the bulk average stagnation pressure at the combustor inlet due primarily to the combustion process, when the engine is running in a "steady state mode" of operation.
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# a.
'Thermally decoupled liners' designed to operate at 'combustor exit temperature' exceeding 1 883K (1 610°C);
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# b.
Non-metallic liners;
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# c.
Non-metallic shells;
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# d.
Liners designed to operate at 'combustor exit temperature' exceeding 1 883K (1 610°C) and having holes that meet the parameters specified in 9E003.c. or;
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# e.
'Pressure gain combustion'
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# 3.
Components that are any of the following:
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# 4.
Uncooled turbine blades, vanes or "tip-shrouds", designed to operate at a 'gas path temperature' of 1 373 K (1 100°C) or more;
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# 5.
Cooled turbine blades, vanes, "tip-shrouds" other than those described in 9E003.a.1., designed to operate at a 'gas path temperature' of 1 693 K (1 420°C) or more;
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# 6.
Aerofoil-to-disk blade combinations using solid-state joining;
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# 7.
Not Used;
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# 8.
'Damage tolerant' rotor components using powder metallurgy materials specified in 1C002.b.; or
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# 9.
Not used;
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# 10.
Not used;
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# 11.
'Fan blades' having all of the following:
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# b.
"Technology" "required" for the "development" or "production" of any of the following:
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# c.
"Technology" "required" for manufacturing cooling holes in gas turbine engine components incorporating any of the "technologies" specified in 9E003.a.1., 9E003.a.2. or 9E003.a.5., and having any of the following:
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# d.
"Technology" "required" for the "development" or "production" of helicopter power transfer systems or tilt rotor or tilt wing "aircraft" power transfer systems;
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# e.
"Technology" for the "development" or "production" of reciprocating diesel engine ground vehicle propulsion systems having all of the following:
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# f.
"Technology" "required" for the "production" of specially designed components for "high output diesel engines", as follows:
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# 1.
"Technology" "required" for the "production" of engine systems having all of the following components employing ceramics materials specified in 1C007:
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# 2.
"Technology" "required" for the "production" of turbocharger systems with single-stage compressors and having all of the following:
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# 3.
"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)) and having all of the following:
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# g.
"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 and 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;
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# h.
"Technology" for gas turbine engine "FADEC systems" as follows:
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# 1.
"Development" "technology" for deriving the functional requirements for the components necessary for the "FADEC system" to regulate engine thrust or shaft power (e.g., feedback sensor time constants and accuracies, fuel valve slew rate);
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# 2.
"Development" or "production" "technology" for control and diagnostic components unique to the "FADEC system" and used to regulate engine thrust or shaft power;
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# 3.
"Development" "technology" for the control law algorithms, including "source code", unique to the "FADEC system" and used to regulate engine thrust or shaft power;
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# i.
"Technology" for gas turbine engine adjustable flow path systems designed to maintain engine stability for gas generator turbines, fan or power turbines, or propelling nozzles, as follows:
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# 1.
"Development" "technology" for deriving the functional requirements for the components that maintain engine stability;
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# 2.
"Development" or "production" "technology" for components unique to the adjustable flow path system and that maintain engine stability;
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# 3.
"Development" "technology" for the control law algorithms, including "source code", unique to the adjustable flow path system and that maintain engine stability;
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# j.
"Technology" "required" for the "development" of wing-folding systems designed for fixed-wing "aircraft" powered by gas turbine engines.
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# k.
"Technology", not specified in 9E003.a., 9E003.h., or 9E003.i., "required" for the "development" of any of the following components or systems, specially designed for aero gas turbine engines to enable "aircraft" to cruise at Mach 1 or greater for more than 30 minutes:
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# 1.
Propulsion inlet systems;
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# 2.
Propulsion exhaust systems; and/or bypass flow downstream of the last turbomachinery stage. 'Reheat systems' are also referred to as afterburners.
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# 3.
'Reheat systems'; oil-to-air cooling or oil-to-fuel cooling, such as vapour cycle systems.
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# 4.
'Active thermal management systems' to condition fluids used to lubricate or cool 'engine rotor supports'; engine inlet face and the combustor that increases gas path pressure through mechanical work.
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# 5.
Oil-free 'engine rotor supports'; or that drives the compression system or turbine rotors.
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# 6.
Systems to remove heat from 'compression system' core gas path flow. Technical Notes For the purposes of 9E003.k.:
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# 9E101.
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# a.
"Technology" according to the General Technology Note for the "development" of goods specified in 9A101, 9A102, 9A104 to 9A111, 9A112.a. or 9A115 to 9A121.
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# b.
"Technology" according to the General Technology Note for the "production" of 'UAV's specified in 9A012 or goods specified in 9A101, 9A102, 9A104 to 9A111, 9A112.a. or 9A115 to 9A121.
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# 9E102.
"Technology" according to the General Technology Note for the "use" of space launch vehicles specified in 9A004, goods specified in 9A005 to 9A011, 'UAV's specified in 9A012 or goods specified in 9A101, 9A102, 9A104 to 9A111, 9A112.a., 9A115 to 9A121, 9B105, 9B106, 9B107, 9B115, 9B116, 9B117, 9D101 or 9D103.
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