Part Details | AIRCRAFT GAS TURBINE ENGINE COMPRESSOR DISK AND HUB
2840-01-459-1286 An item that consists of a DISK, COMPRESSOR, AIRCRAFT GAS TURBINE ENGINE and a HUB, COMPRESSOR, AIRCRAFT GAS TURBINE ENGINE.
Alternate Parts: 1559M63G04118, 1559M63G04-118, 1559M63, 2840-01-459-1286, 01-459-1286, 2840014591286, 014591286
| Supply Group (FSG) | NSN Assigned | NIIN | Item Name Code (INC) |
|---|---|---|---|
| 28 | SEP 21, 1998 | 01-459-1286 | 50561 ( DISK AND HUB, COMPRESSOR, AIRCRAFT GAS TURBINE ENGINE ) |
REFERENCE DRAWINGS & PICTURES
Cross Reference | NSN 2840-01-459-1286
| Part Number | Cage Code | Manufacturer |
|---|---|---|
| 1559M63G04-118 | 98748 | AIR FORCE UNITED STATES DEPARTMENTOF THE |
| 1559M63 | 07482 | GENERAL ELECTRIC COMPANYDBA GE |
Technical Data | NSN 2840-01-459-1286
| Characteristic | Specifications |
|---|---|
| DESIGN TYPE | AXIAL COMPRESSOR |
| ENGINE SECTION LOCATION | COMPRESSOR |
| OVERALL LENGTH | 6.425 INCHES MINIMUM AND 6.455 INCHES MAXIMUM |
| DIAMETER | 17.225 INCHES MINIMUM AND 17.229 INCHES MAXIMUM |
| SPECIAL FEATURES | T.O. 2J-F110-4, FIG 67, IND 5; HPCR STG 1-2, SPOOL OIL DRAIN HOLES ARE ENLARGED 1.48 LARGER THAN THE CURRENT ELLIPTICAL HOLES TO ALLOW BETTER DRAINAGE; CAN ONLY BE USED ON THE F118-GE-100 AIRCRAFT JET TURBINE ENGINE |
| CRITICALITY CODE JUSTIFICATION | AABHP$$AABMZ$$AFEAT |
| END ITEM IDENTIFICATION | F118-GE-100 AIRCRAFT GAS TURBINE ENGINE |
| PART NAME ASSIGNED BY CONTROLLING AGENCY | ORIGINAL NAME HPC COMPRESSOR SPOOL |