Document ID: chunk:federal_register_of_legislation:F2024L01024:front:0:p253
Version: federal_register_of_legislation:F2024L01024
Segment Type: other
Provision Reference: 
Character Range: 719665–722846

for gas turbine engine "FADEC systems" as follows:
1. "Development" "technology" for deriving the functional requirements for the 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);
2. "Development" or "production" "technology" for control and diagnostic components unique to the "FADEC system" and used to regulate engine thrust or shaft power;
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 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).
9. E. 003. 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:
1. "Development" "technology" for deriving the functional requirements for the components that maintain engine stability;
2. "Development" or "production" "technology" for components unique to the adjustable flow path system and that maintain engine stability;
9. E. 003. i. 3. "Development" "technology" for the control law algorithms, including "source 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.
9. E. 003. 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 by ML10., see ML22.
9. E. 003. k. "Technology", not specified in 9E003.a., 9E003.h., or 9E003.i., "required" for the "development" of any of the following components or systems, specially designed for aero gas turbine engines to enable "aircraft" to cruise at Mach 1 or greater for more than 30 minutes:
1. Propulsion inlet systems;
2. Propulsion exhaust systems;
3. 'Reheat systems';
4. 'Active thermal management systems' to condition fluids used to lubricate or cool 'engine rotor supports';
5. Oil-free 'engine rotor supports'; or
6. Systems to remove heat from 'compression system' core gas path flow.
Technical Notes:
For the purposes of 9E003.k.:
              1. Propulsion inlet systems include core flow pre-coolers.
              2. 'Reheat systems' provide additional thrust by combusting fuel in exhaust and/or bypass flow downstream of the last turbomachinery stage. 'Reheat systems' are also referred to as afterburners.
              3. 'Active thermal management