4083210: CASE,TURBINE,AIRCRAFT GAS TURBIN.
CASE,TURBINE,AIRCRAFT GAS TURBIN. Key specifications include diameter: 28.330 INCHES MINIMUM AND 28.350 INCHES MAXIMUM IN, material: NICKEL ALLOY OVERALL, design_type: AXIAL COMPRESSOR, overall_length: 5.809 INCHES MINIMUM AND 5.813 INCHES MAXIMUM IN, end_item_identification: F100-PW-229 AIRCRAFT GAS TURBINE ENGINE, engine_section_location: TURBINE. This part is cataloged in the U.S.
Government catalog under NSN 2840-01-448-7540, indicating validated use in U.S. government and defense logistics supply chains. Available through authorized enterprise resellers and TPM (Third Party Maintenance) channels.
Verify compatibility with your specific system configuration before ordering.
| diameter | 28.330 INCHES MINIMUM AND 28.350 INCHES MAXIMUM IN |
| material | NICKEL ALLOY OVERALL |
| design_type | AXIAL COMPRESSOR |
| overall_length | 5.809 INCHES MINIMUM AND 5.813 INCHES MAXIMUM IN |
| end_item_identification | F100-PW-229 AIRCRAFT GAS TURBINE ENGINE |
| engine_section_location | TURBINE |
| criticality_code_justification | CZBJ AND ABMZ AND ABHP AND FEAT |
| material_document_and_classification | PWA1010 MFR REF SINGLE MATERIAL RESPONSE OVERALL |
| NSN | 2840-01-448-7540 |
| DESIGN TYPE | AXIAL COMPRESSOR |
| CRITICALITY CODE JUSTIFICATION | CZBJ AND ABMZ AND ABHP AND FEAT |
| MATERIAL DOCUMENT AND CLASSIFICATION | PWA1010 MFR REF SINGLE MATERIAL RESPONSE OVERALL |
| DIAMETER | 28.330 INCHES MINIMUM AND 28.350 INCHES MAXIMUM IN |
| OVERALL LENGTH | 5.809 INCHES MINIMUM AND 5.813 INCHES MAXIMUM IN |
| ENGINE SECTION LOCATION | TURBINE |
| SPECIAL FEATURES | T.O. 2J-F100-54, FIG 89, IND 71; USE ONLY ON P/N 4084522-800, -801, -802, 4082654-803, AND 4082657-808; LOCATION NEAR NO. 4 BEARING FRONT AIR SEALING RING, FRONT SEAL ASSY, COMPRESSOR EXIT STATOR AND DIFFUSER CASE |
| END ITEM IDENTIFICATION | F100-PW-229 AIRCRAFT GAS TURBINE ENGINE |
| MATERIAL | NICKEL ALLOY OVERALL |
No substitute or cross-reference records for this part.