1807M24G01 — BLADE,TURBINE ROTOR,AIRCRAFT GAS

✓ Government record, cited

— · COMPONENT

PRODUCT OVERVIEW

1807M24G01: BLADE,TURBINE ROTOR,AIRCRAFT GAS.

BLADE,TURBINE ROTOR,AIRCRAFT GAS. Key specifications include material: ALUMINUM BLADE, design_type: AXIAL COMPRESSOR, overall_width: 1.347 INCHES MINIMUM AND 1.352 INCHES MAXIMUM IN, overall_length: 5.388 INCHES MINIMUM AND 5.400 INCHES MAXIMUM IN, blade_attachment_method: FIR TREE, end_item_identification: ACFT ENG TF39. This part is cataloged in the U.S.

Government catalog under NSN 2840-01-444-7701, 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.

WHERE IT FITS

1807M24G01

NSN: 2840-01-444-7701
FSC: 2840 — Gas Turbines and Jet Engines, Aircraft, Prime Moving; and Components
CAGE: 07482 — GENERAL ELECTRIC COMPANY (USA)

SPECIFICATIONS

material	ALUMINUM BLADE
design_type	AXIAL COMPRESSOR
stage_number	2
overall_width	1.347 INCHES MINIMUM AND 1.352 INCHES MAXIMUM IN
overall_length	5.388 INCHES MINIMUM AND 5.400 INCHES MAXIMUM IN
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
blade_attachment_method	FIR TREE
end_item_identification	ACFT ENG TF39
engine_section_location	HIGH PRESSURE TURBINE
criticality_code_justification	AGAV
NSN	2840-01-444-7701

COMPONENT DIAGRAM

KEY FEATURES

•

STAGE NUMBER: 2

•

DESIGN TYPE: AXIAL COMPRESSOR

•

CRITICALITY CODE JUSTIFICATION: AGAV

•

BLADE ATTACHMENT METHOD: FIR TREE

•

ENGINE SECTION LOCATION: HIGH PRESSURE TURBINE

TECHNICAL CHARACTERISTICS

STAGE NUMBER	2
DESIGN TYPE	AXIAL COMPRESSOR
CRITICALITY CODE JUSTIFICATION	AGAV
BLADE ATTACHMENT METHOD	FIR TREE
OVERALL LENGTH	5.388 INCHES MINIMUM AND 5.400 INCHES MAXIMUM IN
OVERALL WIDTH	1.347 INCHES MINIMUM AND 1.352 INCHES MAXIMUM IN
ENGINE SECTION LOCATION	HIGH PRESSURE TURBINE
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
END ITEM IDENTIFICATION	ACFT ENG TF39
MATERIAL	ALUMINUM BLADE

OTHER ITEMS IN FSC 2840 — Gas Turbines and Jet Engines, Aircraft, Prime Moving; and Components

Items in the same Federal Supply class. No interchangeability or substitution relationship is implied.

2840-00-004-4242 2840-00-021-4702 2840-00-043-0981 2840-00-043-0982 2840-00-048-5261 2840-00-407-9165 2840-01-171-0875

SUBSTITUTES & CROSS-REFERENCES 1

1807M24Reference document

Same NSN cross-reference

Reference document — Drawing number reference only

LIFECYCLE

NSN statusActive· U.S. Government catalog

Demilitarization required — mutilation + specific procedure

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FREQUENTLY ASKED QUESTIONS

What is 1807M24G01?

1807M24G01 is a BLADE,TURBINE ROTOR,AIRCRAFT GAS.

What parts can replace 1807M24G01?

There is 1 known substitute for 1807M24G01: 1807M24. Substitute compatibility should be verified for your specific system.

What is the NSN for 1807M24G01?

1807M24G01 is cataloged in the U.S. Government catalog under NSN 2840-01-444-7701. This indicates validated use in U.S. government and defense supply chains.

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1807M24G01 — BLADE,TURBINE ROTOR,AIRCRAFT GAS

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