9A101Turbojet and turbofan engines, other than those specified in 9A001, 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 8 890 N;
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. For the purpose of 9A101.a.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 use in "missiles" or unmanned aerial vehicles specified in 9A012 or 9A112.a.