Document ID: chunk:federal_register_of_legislation:F2024L01024:front:0:p249
Version: federal_register_of_legislation:F2024L01024
Segment Type: other
Provision Reference: 
Character Range: 708826–712000

9A012, 9A350, 9B or 9D.
Note: Certain items specified in 9E001 may be subject to the MTCR Guidelines for Sensitive Missile‑Relevant Transfers.
9. E. 002. "Technology" according to the General Technology Note for the "production" of equipment specified by 9A004 to 9A011, 9A350 or 9B.
N.B.: For "technology" for the repair of controlled structures, laminates or materials, see 1E002.f.
Note: Certain items specified in 9E002 may be subject to the MTCR Guidelines for Sensitive Missile‑Relevant Transfers.
9. E. 003. Other "technology" as follows:
a. "Technology" "required" for the "development" or "production" of any of the following gas turbine engine components or systems:
1. Gas turbine blades, vanes or "tip shrouds", made from directionally solidified (DS) or single crystal (SC) alloys and having (in the 001 Miller Index Direction) a stress‑rupture life exceeding 400 hours at 1,273 K (1,000°C) at a stress of 200 MPa, based on the average property values;
Technical Note:
For the purposes of 9E003.a.1., stress‑rupture life testing is typically conducted on a test specimen.

9. E. 003. a. 2. Combustors having any of the following:
                  1. 'Thermally decoupled liners' designed to operate at 'combustor exit temperature' exceeding 1,883 K (1,610°C);
                  2. Non‑metallic liners;
                  3. Non‑metallic shells; or
                  4. Liners designed to operate at 'combustor exit temperature' exceeding 1,883 K (1,610°C) and having holes that meet the parameters specified by 9E003.c.;
                  5. Utilising 'pressure gain combustion';
                Technical Note:
                For the purposes of 9E003.a.2.e., in 'pressure gain combustion' the bulk average stagnation pressure at the combustor outlet is greater than the bulk average stagnation pressure at the combustor inlet due primarily to the combustion process, when the engine is running in a "steady state mode" of operation.

                    Note: The "required" "technology" for holes in 9E003.a.2. is limited to the derivation of the geometry and location of the holes.
              Technical Notes:
                   1. For the purposes of 9E003.a.2.a., 'thermally decoupled liners' are liners that feature at least a support structure designed to carry mechanical loads and a combustion facing structure designed to protect the support structure from the heat of combustion. The combustion facing structure and support structure have independent thermal displacement (mechanical displacement due to thermal load) with respect to one another, i.e. they are thermally decoupled.
                   2. For the purposes of 9E003.a.2.d., 'combustor exit temperature' is the bulk average gas path total (stagnation) temperature between the combustor exit plane and the leading edge of the turbine inlet guide vane (i.e., measured at engine station T40 as defined in SAE ARP 755A) when the engine is running in a "steady state mode" of operation at the certificated maximum continuous operating temperature.
                   N.B.: See 9E003.c. for "technology" "required" for manufacturing cooling holes.
9. E. 003. a. 3. Components that are any