1559M63G02-129: ROTOR,COMPRESSOR,AIRCRAFT GAS TU.
ROTOR,COMPRESSOR,AIRCRAFT GAS TU. Key specifications include diameter: 17.300 INCHES NOMINAL IN, material: TITANIUM ALLOY OVERALL, design_type: AXIAL COMPRESSOR, overall_length: 6.143 INCHES MINIMUM AND 6.163 INCHES MAXIMUM IN, end_item_identification: F110-GE-129 AIRCRAFT GAS TURBINE ENGINE, engine_section_location: HIGH PRESSURE COMPRESSOR. This part is cataloged in the U.S.
Government catalog under NSN 2840-01-438-8399, 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 | 17.300 INCHES NOMINAL IN |
| material | TITANIUM ALLOY OVERALL |
| design_type | AXIAL COMPRESSOR |
| stage_number | 1 |
| overall_length | 6.143 INCHES MINIMUM AND 6.163 INCHES MAXIMUM IN |
| end_item_identification | F110-GE-129 AIRCRAFT GAS TURBINE ENGINE |
| engine_section_location | HIGH PRESSURE COMPRESSOR |
| criticality_code_justification | FEAT AND ABHP AND ABMZ AND CZBJ |
| material_document_and_classification | TI-17 MFR REF SINGLE MATERIAL RESPONSE OVERALL |
| part_name_assigned_by_controlling_agency | ORIGINAL NAME SPOOL,COMPRESSOR ROTOR |
| NSN | 2840-01-438-8399 |
| STAGE NUMBER | 1 |
| DESIGN TYPE | AXIAL COMPRESSOR |
| CRITICALITY CODE JUSTIFICATION | FEAT AND ABHP AND ABMZ AND CZBJ |
| MATERIAL DOCUMENT AND CLASSIFICATION | TI-17 MFR REF SINGLE MATERIAL RESPONSE OVERALL |
| DIAMETER | 17.300 INCHES NOMINAL IN |
| OVERALL LENGTH | 6.143 INCHES MINIMUM AND 6.163 INCHES MAXIMUM IN |
| ENGINE SECTION LOCATION | HIGH PRESSURE COMPRESSOR |
| SPECIAL FEATURES | T.O. 2J-F110-14, FIG 67, IND 5 UNDER P/N 1559M63G02; INCLUDES STAGE 2; ALSO CONSISTS NO. 1 DISK AND NO. 2 DISK AND FORWARD SHAFT THAT MAKES A 1 PIECE CONSTRUCTION THAT HOLDS BOTH STGS; WEIGHS 40.3 LBS; BASIC P/N CAN BE USED ON ALL ENGINE TYPES, BUT ONCE USED ON THE F110-GE-129, IT CAN ONLY BE USED ON A F110-GE-129 ENGINE; REIDENTIFICATION WILL CONSIST OF ADDING THE ENGINE TYPE AS A DASH NUMBER FOLLOWING THE P/N LBS |
| PART NAME ASSIGNED BY CONTROLLING AGENCY | ORIGINAL NAME SPOOL,COMPRESSOR ROTOR |
| END ITEM IDENTIFICATION | F110-GE-129 AIRCRAFT GAS TURBINE ENGINE |
No substitute or cross-reference records for this part.