aero thermal, aeromechanical and combustion conditions, which have been validated with actual aero gas turbine engine (experimental or production) performance data.
9D101
"Software" specially designed or modified for the "use" of goods specified in 9B105, 9B106, 9B116 or 9B117.
9D103
"Software" specially designed for modelling, simulation or design integration of the space launch vehicles specified in 9A004 or sounding rockets specified in 9A104, or the subsystems specified in 9A005, 9A007, 9A105, 9A106.c., 9A107, 9A108.c., 9A116 or 9A119.
Note: "Software" specified in 9D103 remains controlled when combined with specially designed hardware specified in 4A102.
9D104
"Software" specially designed or modified for the "use" of goods specified in 9A001, 9A005, 9A006.d., 9A006.g., 9A007.a., 9A008.d., 9A009.a., 9A010.d., 9A011, 9A101, 9A102, 9A105, 9A106.c., 9A106.d., 9A107, 9A108.c., 9A109, 9A111, 9A115.a., 9A116.d., 9A117 or 9A118.
9D105
"Software" which coordinates the function of more than one subsystem, specially designed or modified for "use" in space launch vehicles specified in 9A004 or sounding rockets specified in 9A104.
9E Technology
Note: "Development" or "production""technology" specified in 9E001 to 9E003 for gas turbine engines remains controlled when used for repair or overhaul. Excluded from control are: technical data, drawings or documentation for maintenance activities directly associated with calibration, removal or replacement of damaged or unserviceable line replaceable units, including replacement of whole engines or engine modules.
9E001
"Technology" according to the General Technology Note for the "development" of equipment or "software", specified in 9A001.b., 9A004 to 9A012, 9A350, 9B or 9D.
9E002
"Technology" according to the General Technology Note for the "production" of equipment specified in 9A001.b., 9A004 to 9A011, 9A350 or 9B.
N.B.: For "technology" for the repair of controlled structures, laminates or materials, see 1E002.f.
9E003
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;
2.
Combustors having any of the following:
a.
Thermally decoupled liners designed to operate at 'combustor exit temperature' exceeding 1 883K (1 610 °C);
b.
Non-metallic liners;
c.
Non-metallic shells; or
d.
Liners designed to operate at 'combustor exit temperature' exceeding 1 883K (1 610 °C) and having holes that meet the parameters specified by 9E003.c.;
Note: The "required""technology" for holes in 9E003.a.2. is limited to the derivation of the geometry and location of the holes.
Technical Note:
'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.
3.
Components manufactured from