383766-2-3

38376623 Engine Gas Turbine Starter

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Datasheet. 383766-2-3 specification

General Characteristics Item Description
A recording of the physical,functional,and performance characteristics for an item of supply.

J90.0 horsepower output, single stage radial outflow turbine, compound planetary type reduction gear, 18.3-1.0, counterclockwise rotationoutput shaft cutout speed, 3100 to 3300 rpm, output shaft shear load 850 FT-Lbs

Fsc Application Data
The justification for the assignment of a federal supply class /fsc/ to an item based on the classification of the next higher classifiable assembly.

TF41-A-1 engine, A7D

Answers.

What is the NSN for 383766-2-3?

2995-00-469-0101

How is this classified for shipping?

Schedule B number: 8411997050
Parts of gas turbine aircraft engines, other than for use in civil aircraft

What's the federal classification of 383766-2-3?

FSC 2995 ⁓ Miscellaneous engine accessories, aircraft

Note-items classified in this class must be specifically designed for use with aircraft or quided missile primemovers only.

Excluding exhaust system; (fsc 1560); jet engine hydraulic reservoirs (fsc 2840); jet engine oil tanks (fsc 2840); electrical starters (fsc 2925); cockpit mounted control quadrants (fsc 1680); aircraft engine covers (fsc 1730).

NSN 2995-00-469-0101 STARTER,ENGINE,GAS TURBINE

NIIN
004690101
NIIN Date
06/07/74
Schedule B
8411997050 
Name Code
21907
FIIG
A23900
Item Weight
120.000lbs
Item Dimensions
360 X 260 X 190
DEMIL / ITAR
USML/ITAR controlled item (Code: B)
Hazmat
No hazard information available from HMIRS.
MSDS
N/A
Precious Metals
No precious metals
Enviromental
N/A
Electrostatic ESD & EMI
No ESD or EMI sensitivity

Major End Users Countries and entities

  • - Greece 

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Similar by Design Other starters with similar characteristics

Nothing similar to this part number was found in our inventory

383766-2-3 / Starter,engine,gas turbineWhat is the formal definition of this item?

An item designed to accelerate a gas turbine engine from rest to starter cutoff speed by means of a combustion gas driven turbine and reduction gear assembly constructed to be mounted on the engine starter drive. the combustion gas is generated from ignited liquid fuel and air in the combustion chamber or from a solid propellant cartridge attached to the combustion chamber of the starter. may have provision for energizing the turbine by low pressure air from engine bleed or ground equipment air supply.