24Category XIX—Gas Turbine Engines and Associated Equipment

24  Category XIX—Gas Turbine Engines and Associated Equipment

 (a) Turbofan and Turbojet engines (including technology demonstrators) capable of 15,000 lbf (66.7 kN) of thrust or greater that have any of the following:

 (1) with or specially designed for thrust augmentation (afterburner);

 (2) thrust or exhaust nozzle vectoring;

 (3) parts or components controlled in paragraph (f)(6);

 (4) specially designed for sustained 30 second inverted flight or negative g manoeuvre;

 (5) specially designed for high power extraction (greater than 50% of engine thrust at altitude) at altitudes greater than 50,000 feet.

 (b) Turboshaft and Turboprop engines (including technology demonstrators) capable of 1500 mechanical shp (1119 kW) or greater and are specially designed with oil sump sealing when the engine is in the vertical position.

 (c) Engines (including technology demonstrators) specially designed for armed or military unmanned aerial vehicle systems, cruise missiles, or target drones (MT if for an engine used in an unmanned aerial vehicle, drone, or missile that has a “range” equal to or greater than 300 km).

 (d) GE38, AGT1500, CTS800, TF40B, T55, TF60, and T700 engines.

 (e) Digital engine control systems (for example, Full Authority Digital Engine Controls (FADEC) and Digital Electronic Engine Controls (DEEC)) specially designed for gas turbine engines controlled in this category (MT if the digital engine control system is for an unmanned aerial vehicle, drone, or missile that has a range equal to or greater than 300 km).

Note: Digital electronic control systems autonomously control the engine throughout its whole operating range from demanded engine start until demanded engine shut‑down, in both normal and fault conditions. For the definition of “range,” see note 2 to paragraph (a) of Category VIII.

 (f) Parts, components, accessories, attachments, associated equipment, and systems as follows:

 (1) parts, components, accessories, attachments, and equipment specially designed for the following United States‑origin engines (and military variants thereof): AE1107C, F101, F107, F112, F118, F119, F120, F135, F136, F414, F415, J402, GE38, TF40B, and TF60;

 (2) hot section components (that is, combustion chambers and liners; high pressure turbine blades, vanes, disks and related cooled structure; cooled low pressure turbine blades, vanes, disks and related cooled structure; cooled augmenters; and cooled nozzles) specially designed for gas turbine engines controlled in this category;

 (3) uncooled turbine blades, vanes, disks, and tip shrouds specially designed for gas turbine engines controlled in this category;