Part Details | AIRCRAFT GAS TURBINE ENGINE TURBINE ROTOR BLADE
2840-01-444-7701 An item mounted on a DISK, TURBINE, AIRCRAFT GAS TURBINE ENGINE. It is designed to create the flow of air in the turbine section of an ENGINE, GAS TURBINE, AIRCRAFT.
Alternate Parts: 1807M24G01, 1807M24, 2840-01-444-7701, 01-444-7701, 2840014447701, 014447701
| Supply Group (FSG) | NSN Assigned | NIIN | Item Name Code (INC) |
|---|---|---|---|
| 28 | MAY 15, 1997 | 01-444-7701 | 50535 ( BLADE, TURBINE ROTOR, AIRCRAFT GAS TURBINE ENGINE ) |
REFERENCE DRAWINGS & PICTURES
Cross Reference | NSN 2840-01-444-7701
| Part Number | Cage Code | Manufacturer |
|---|---|---|
| 1807M24G01 | 07482 | GENERAL ELECTRIC COMPANYDBA GE |
| 1807M24 | 07482 | GENERAL ELECTRIC COMPANYDBA GE |
Technical Data | NSN 2840-01-444-7701
| Characteristic | Specifications |
|---|---|
| DESIGN TYPE | AXIAL COMPRESSOR |
| ENGINE SECTION LOCATION | HIGH PRESSURE TURBINE |
| STAGE NUMBER | 2 |
| BLADE ATTACHMENT METHOD | FIR TREE |
| OVERALL LENGTH | 5.388 INCHES MINIMUM AND 5.400 INCHES MAXIMUM |
| OVERALL WIDTH | 1.347 INCHES MINIMUM AND 1.352 INCHES MAXIMUM |
| SPECIAL FEATURES | THIS ITEM IS PART OF THE HT90 MODFOR THE TF39 ENGINE, EXTERNAL COATING PLATINUM ALUMINIDE, ORIGINAL DRAWING NAME BLADE,HIGH PRESSURE TURBINE ROTOR STAGE 2, LEAD |
| CRITICALITY CODE JUSTIFICATION | AGAV |
| END ITEM IDENTIFICATION | ACFT ENG TF39 |