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Federal Register / Vol. 86, No. 58 / Monday, March 29, 2021 / Rules and Regulations Special Conditions for STA
STA: License Exception STA may not be used to ship or transmit any technology in 9E003.a.1, 9E003.a.2 to a.5, 9E003.a.8, or 9E003.h to any of the destinations listed in Country Group A:6 See Supplement No.1
to part 740 of the EAR.
List of Items Controlled Related Controls: 1 Hot section technology specifically designed, modified, or equipped for military uses or purposes, or developed principally with Department of Defense funding, is subject to the ITAR see 22 CFR parts 120 through 130. 2 Technology is subject to the EAR when actually applied to a commercial aircraft engine program.
Exporters may seek to establish commercial application either on a caseby-case basis through submission of documentation demonstrating application to a commercial program in requesting an export license from the Department Commerce in respect to a specific export, or in the case of use for broad categories of aircraft, engines, parts or components, a commodity jurisdiction determination from the Department of State.
Related Definitions: N/A
Items:
a. Technology required for the development or production of any of the following gas turbine engine parts, components or systems:
a.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 stressrupture 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.
a.2. Combustors having any of the following:
a.2.a. Thermally decoupled liners designed to operate at combustor exit temperature exceeding 1,883K 1,610 C;
a.2.b. Non-metallic liners;
a.2.c. Non-metallic shells; or a.2.d. Liners designed to operate at combustor exit temperature exceeding 1,883K 1,610 C and having holes that meet the parameters specified by 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
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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.
N.B.: See 9E003.c for technology required for manufacturing cooling holes.
a.3. Parts or components, that are any of the following:
a.3.a. Manufactured from organic composite materials designed to operate above 588 K 315 C;
a.3.b. Manufactured from any of the following:
a.3.b.1. Metal matrix composites reinforced by any of the following:
a.3.b.1.a. Materials controlled by 1C007;
a.3.b.1.b. Fibrous or filamentary materials specified by 1C010; or a.3.b.1.c. Aluminides specified by 1C002.a;
or a.3.b.2. Ceramic matrix composites specified by 1C007; or a.3.c. Stators, vanes, blades, tip seals shrouds, rotating blings, rotating blisks or splitter ducts, that are all of the following:
a.3.c.1. Not specified in 9E003.a.3.a;
a.3.c.2. Designed for compressors or fans;
and a.3.c.3. Manufactured from material controlled by 1C010.e with resins controlled by 1C008;
Technical Note: A splitter duct performs the initial separation of the air-mass flow between the bypass and core sections of the engine.
a.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;
a.5. Cooled turbine blades, vanes or tipshrouds, 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;
Technical Note: Gas path temperature is the bulk average gas path total stagnation temperature at the leading edge plane of the turbine component when the engine is running in a steady state mode of operation at the certificated or specified maximum continuous operating temperature.
a.6. Airfoil-to-disk blade combinations using solid state joining;
a.7. Reserved a.8. Damage tolerant gas turbine engine rotor parts or components using powder metallurgy materials controlled by 1C002.b;
or Technical Note: Damage tolerant parts and components are designed using methodology and substantiation to predict and limit crack growth.
a.9. Reserved N.B.: For FADEC systems, see 9E003.h.
a.10. Reserved N.B.: For adjustable flow path geometry, see 9E003.i.
a.11. Fan blades having all of the following:
a.11.a. 20% or more of the total volume being one or more closed cavities containing vacuum or gas only; and a.11.b. One or more closed cavities having a volume of 5 cm3 or larger;

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Technical Note: For the purposes of 9E003.a.11, a fan blade is the aerofoil portion of the rotating stage or stages, which provide both compressor and bypass flow in a gas turbine engine.
b. Technology required for the development or production of any of the following:
b.1. Wind tunnel aero-models equipped with non-intrusive sensors capable of transmitting data from the sensors to the data acquisition system; or b.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 manufacturing cooling holes, in gas turbine engine parts or components incorporating any of the technologies specified by 9E003.a.1, 9E003.a.2 or 9E003.a.5, and having any of the following:
c.1. Having all of the following:
c.1.a. Minimum cross-sectional area less than 0.45 mm2;
c.1.b. Hole shape ratio greater than 4.52;
and c.1.c. Incidence angle equal to or less than 25; or c.2. Having all of the following:
c.2.a. Minimum cross-sectional area less than 0.12 mm2;
c.2.b. Hole shape ratio greater than 5.65;
and c.2.c. Incidence angle more than 25;
Note: 9E003.c does not apply to technology for manufacturing constant radius cylindrical holes that are straight through and enter and exit on the external surfaces of the component.
Technical Notes:
1. For the purposes of 9E003.c, the crosssectional area is the area of the hole in the plane perpendicular to the hole axis.
2. For the purposes of 9E003.c, hole shape ratio is the nominal length of the axis of the hole divided by the square root of its minimum cross-sectional area.
3. For the purposes of 9E003.c, incidence angle is the acute angle measured between the plane tangential to the airfoil surface and the hole axis at the point where the hole axis enters the airfoil surface.
4. Techniques for manufacturing holes in 9E003.c include laser beam machining, water jet machining, Electro-Chemical Machining ECM.
d. Technology required for the development or production of helicopter power transfer systems or tilt rotor or tilt wing aircraft power transfer systems;
e. Technology for the development or production of reciprocating diesel engine ground vehicle propulsion systems having all of the following:
e.1. Box volume of 1.2 m3 or less;
e.2. An overall power output of more than 750 kW based on 80/1269/EEC, ISO 2534 or national equivalents; and e.3. Power density of more than 700 kW/
m3 of box volume;
Technical 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;

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