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Federal Register / Vol. 86, No. 58 / Monday, March 29, 2021 / Rules and Regulations
Width: The widest of any 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 any of the following:
a. The dimension of the crankshaft centerline to the top plane of the valve cover or cylinder head plus twice the stroke; or b. The diameter of the flywheel housing.
f. Technology required for the production of specially designed parts or components for high output diesel engines, as follows:
f.1. Technology required for the production of engine systems having all of the following parts and components employing ceramics materials controlled by 1C007:
f.1.a Cylinder liners;
f.1.b. Pistons;
f.1.c. Cylinder heads; and f.1.d. One or more other part or component including exhaust ports, turbochargers, valve guides, valve assemblies or insulated fuel injectors;
f.2. Technology required for the production of turbocharger systems with single-stage compressors and having all of the following:
f.2.a. Operating at pressure ratios of 4:1 or higher;
f.2.b. Mass flow in the range from 30 to 130
kg per minute; and f.2.c. Variable flow area capability within the compressor or turbine sections;
f.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:
f.3.a. Injection amount in excess of 230
mm3 per injection per cylinder; and f.3.b. Electronic control features specially designed for switching governor characteristics automatically depending on fuel property to provide the same torque characteristics by using the appropriate sensors;
g. Technology required for the development or production of high
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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;
Technical 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 r.p.m., provided the rated speed is 2,300 r.p.m. or more.
h. Technology for gas turbine engine FADEC systems as follows:
h.1. Development technology for deriving the functional requirements for the parts or 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;
h.2. Development or production technology for control and diagnostic parts or components unique to the FADEC system and used to regulate engine thrust or shaft power;
h.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;
Note: 9E003.h does not apply to technical data related to engine-aircraft integration required by civil aviation authorities of one or more Wassenaar Arrangement Participating States see Supplement No. 1 to part 743 of the EAR to be published for general airline use e.g., installation manuals, operating instructions, instructions for continued airworthiness or interface functions e.g., input/output processing, airframe thrust or shaft power demand.
i. Technology for adjustable flow path systems designed to maintain engine stability for gas generator turbines, fan or power turbines, or propelling nozzles, as follows:
i.1. Development technology for deriving the functional requirements for the parts or components that maintain engine stability;
i.2. Development or production technology for parts or components unique to the adjustable flow path system and that maintain engine stability;
i.3. Development technology for the control law algorithms, including source
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code, unique to the adjustable flow path system and that maintain engine stability;
Note: 9E003.i does not apply to technology for any of the following:
a. Inlet guide vanes;
b. Variable pitch fans or prop-fans;
c. Variable compressor vanes;
d. Compressor bleed valves; or e. Adjustable flow path geometry for reverse thrust.
j. Technology required for the development of wing-folding systems designed for fixed-wing aircraft powered by gas turbine engines.
N.B.: For technology required for the development of wing-folding systems designed for fixed-wing aircraft specified in USML Category VIII a, see USML
Category VIII i.
k. Technology not otherwise controlled in 9E003.a.1 through a.8, a.10, and .h and used in the development, production, or overhaul of hot section parts or components of civil derivatives of military engines controlled on the USML.

35. Supplement no. 6 to part 774 is amended in Category 1 by revising paragraphs 1i and 1vi to read as follows:

Supplement No. 6 to Part 774Sensitive List

1 Category 1
i 1A002.a.1Composite structures or laminates made from an organic matrix and fibrous or filamentary materials specified by 1C010.c or 1C010.d.

vi 1D002Software for the development of organic matrix, metal matrix, or carbon matrix laminates or composites controlled under 1A002.a.1, 1C001, 1C007.c, 1C010.c, 1C010.d, or 1C012.

Matthew S. Borman, Deputy Assistant Secretary for Export Administration.
FR Doc. 202105481 Filed 32621; 8:45 am BILLING CODE 351033P

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