Document ID: chunk:federal_register_of_legislation:F2024L01024:front:0:p239
Version: federal_register_of_legislation:F2024L01024
Segment Type: other
Provision Reference: 
Character Range: 682114–684992

vehicles" ("UAVs"), unmanned "airships", related equipment and components, as follows:
N.B.: For "UAVs" that are "sub‑orbital craft", see 9A004.h.
9. A. 012. 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:
1. Having all of the following:
                  a. A maximum 'endurance' greater than or equal to 30 minutes but less than 1 hour; and
                  b. Designed to take‑off and have stable controlled flight in wind gusts equal to or exceeding 46.3 km/h (25 knots); or
2. A maximum 'endurance' of 1 hour or greater;
Technical Notes:
1. For the purposes of 9A012.a., 'operator' is a person who initiates or commands the "UAV" or unmanned "airship" flight.
2. For the purposes of 9A012.a., 'endurance' is to be calculated for ISA conditions (ISO 2533:1975) at sea level in zero wind.
3. For the purposes of 9A012.a., 'natural vision' means unaided human sight, with or without corrective lenses.
9. A. 012. b. Related equipment and components, as follows:
1. Not used;
2. Not used;
3. Equipment or components, specially designed to convert a manned "aircraft" to a "UAV" or unmanned "airship", specified by 9A012.a.;
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).
Note: Certain items specified in 9A012 may be subject to the MTCR Guidelines for Sensitive Missile‑Relevant Transfers.
9. A. 101. Turbojet and turbofan engines, as follows:
a. Engines having all of the following characteristics:
1. 'Maximum thrust value' greater than 400 N (achieved un‑installed) excluding civil certified engines with a 'maximum thrust value' greater than 8.89 kN (achieved un‑installed);
2. Specific fuel consumption of 0.15 kg N‑1 h‑1 or less (at maximum continuous power at sea level static conditions using the ICAO standard atmosphere);
3. 'Dry weight' less than 750 kg; and
4. 'First‑stage rotor diameter' less than 1 m;
9. A. 101. b. Engines designed or modified for use in "missiles", or in other "unmanned aerial vehicles" capable of a range exceeding 300 km, regardless of thrust, specific fuel consumption, 'dry weight' or 'first‑stage rotor diameter'.
Technical Notes:
1. In 9A101, '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.
2. 'Dry weight' is the weight of the engine without fluids (fuel, hydraulic fluid, oil, etc.) and does not include the nacelle (housing).
3. 'First‑stage rotor diameter' is the diameter of the first rotating stage of the engine,