3.A.1.Turbojet and turbofan engines, as follows:

a. Engines having all of the following characteristics:
1. 'Maximum thrust value' greater than 400 N excluding civil certified engines with a 'maximum thrust value' greater than 8.89 kN;
2. Specific fuel consumption of 0.15 kg N⁻¹ h⁻¹ or less;
3. 'Dry weight' less than 750 kg; and
4. 'First-stage rotor diameter' less than 1 m;
Technical Notes:
1. 'Maximum thrust value' is the manufacturer’s demonstrated maximum thrust for the engine type un-installed at sea level static conditions using the ICAO standard atmosphere. The civil type certified thrust value will be equal to or less than the manufacturer’s demonstrated maximum thrust for the engine type un-installed.
2. Specific fuel consumption is determined at maximum continuous thrust for engine type un-installed at sea level static conditions using the ICAO standard atmosphere.
3. 'Dry weight' is the weight of the engine without fluids (fuel, hydraulic fluid, oil, etc.) and does not include the nacelle (housing).
4. 'First-stage rotor diameter' is the diameter of the first rotating stage of the engine, whether a fan or compressor, measured at the leading edge of the blade tips.
b. Engines designed or modified for systems specified in 1.A. or 19.A.2., regardless of thrust, specific fuel consumption, 'dry weight' or 'first-stage rotor diameter'.
Note:
Engines specified in 3.A.1. may be exported as part of a manned aircraft or in quantities appropriate for replacement parts for a manned aircraft.