Model: 2-140-073-06
Turbine Engine Turbine Rotor CaseSpecial Features:
Flange, cres ams5645, body, cres ams5510, rockwell b scale 90 max hardness, 125 microinch aa surface finish, 7.165 in. Nom o/a lg, 19.240 in. Nom od flange, tapered body, 18.279 in. Min, 18.280 in. Max largest od body, 16.730 in. Min, 16.731 in. Max smallest od body, tapered id, 16.560 in. Min, 16.561 in. Max smallest id countersunk 0.015 in. Nom lg by 45 deg, 18.000 in. Min, 18.001 in. Max largest id countersunk 0.060 in. Nom lg by 45 deg, 42 holes 0.271 in. Min, 0.291 in. Max diameter through flange equally spaced on 18.740 in. Nom bolt circle dia, 3 holes 0.190 in.-32 nf series cl 3b thd through flange on 18.740 in. Nom bolt circle dia, thd holes countersunk 90 degrees by 0.220 in. Nom diameter on back surface of flange, 3 thd holes, 0.250 in.-28 unf series cl 3b thd, through flange on 18.740 in. Nom bolt circle dia, thd holes countersunk 90 degrees by 0.280 in. Nom diameter on back surface of flange, 14 holes 0.256 in. Min, 0.261 in. Max diameter through body equally spaced on outer periphery, 2.264 in. Min, 2.274 in. Ma
Properties:
Inc 61679 cancelled/replaced by ,inc 50554, fiig a10700, app-key d ,inc 50553, fiig a10700, app-key d ,on 021513 ~(all except usa) a case designed to surround a turbine rotor,turbine engine. Excludes case and nozzle,turbine,turbine engine.
Part 2-140-073-06 NSN 2840-00-582-1471
Material Classification
Hazardous material, precious metals, criticality, enviroment, and electrostatic discharge indicatorsFreight Classification
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Schedule B and Export
- Schedule B: 8411997050
- SITC: 71499
- End Use: Engines and turbines for military aircraft
- NAICS: 336412
- USDA: 1
Freight Class: Parts of gas turbine aircraft engines, other than for use in civil aircraft
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