Document ID: chunk:federal_register_of_legislation:F2024L01024:front:0:p250
Version: federal_register_of_legislation:F2024L01024
Segment Type: other
Provision Reference: 
Character Range: 711724–714790

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 of the following:
a. Manufactured from organic "composite" materials designed to operate above 588 K (315°C);
b. Manufactured from any of the following:
                     1. Metal "matrix" "composites" reinforced by any of the following:
                         a. Materials specified by 1C007;
                         b. "Fibrous or filamentary materials" specified by 1C010; or
                         c. Aluminides specified by 1C002.a.; or
                     2. Ceramic "matrix" "composites" specified by 1C007; or
9. E. 003. a. 3. c. Stators, vanes, blades, tip seals (shrouds), rotating blings, rotating blisks, or 'splitter ducts', that are all of the following:
                     1. Not specified by 9E003.a.3.a.;
                     2. Designed for compressors or fans; and
                     3. Manufactured from material specified by 1C010.e. with resins specified by 1C008;
                     Technical Note:
                  For the purposes of 9E003.a.3.c., a 'splitter duct' performs the initial separation of the air-mass flow between the bypass and core sections of the engine.
9. E. 003. a. 4. Uncooled turbine blades, vanes or "tip shrouds", designed to operate at a 'gas path temperature' of 1,373 K (1,100°C) or more;
5. Cooled turbine blades, vanes, "tip shrouds" other than those described in 9E003.a.1., designed to operate at a 'gas path temperature' of 1,693 K (1,420°C) or more;
Technical Note:
For the purposes of 9E003.a.5., 'gas path temperature' is the bulk average gas path total (stagnation) temperature at the leading edge plane of the turbine component when the engine is running in a "steady state mode" of operation at the certificated or specified maximum continuous operating temperature.
6. Aerofoil‑to‑disk blade combinations using solid state joining;
7. Not used since 2019;
9. E. 003. a. 8. 'Damage tolerant' gas turbine engine rotor components using powder metallurgy materials specified by 1C002.b.; or
Technical Note:
For the purposes of 9E003.a.8., 'damage tolerant' components are designed using methodology and substantiation to predict and limit crack growth.
9. Not used;
10. Not used;
9. E. 003. a. 11. 'Fan blades' having all of the following:
a. 20% or more of the total volume being one or more closed cavities containing vacuum or gas only; and
b. One or more closed cavities having a volume of 5 cm3 or larger;
Technical Note:
For the purposes of 9E003.a.11., a 'fan blade' is the aerofoil portion of the rotating stage or stages, which provide both compressor and bypass flow in a gas turbine engine.
9. E. 003. b. "Technology" "required" for the "development" or "production" of any of the following:
1. Wind tunnel aero‑models equipped with non‑intrusive sensors capable of transmitting data from the sensors to