2840-98-104-2848

Turbo-Shaft Aircraft Engine

2840981042848 981042848 MK503C MK10301 MK10301C

A continuous-combustion type engine, may be with or without container, designed to use superheated air to drive a turbine rotor which is connected to the rotorshaft of a helicopter by way of reduction gears. View more Turbo-Shaft Aircraft Engine

2840-98-104-2848 ENGINE,AIRCRAFT,TURBO-SHAFT 2840981042848 981042848

Managed by New Zealand
NSN Created on 1 Jun 1990
Data Last Changed
January 2023
NATO Update Count
1
NATO Data Quality
2840-98-104-2848 ENGINE,AIRCRAFT,TURBO-SHAFT 2840981042848 981042848 1/1
NSN 2840-98-104-2848 (Generic Image) 1/1

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2840-98-104-2848 Related Documents Related Documents 2840-98-104-2848 5+ Documents (More...)

test and cable and conduit assembly, electrical. https//www.nsnlookup.com /fsg-28/fsc-2840/nz 2840-98-104-2848
Turbo-Shaft Aircraft Engine 2840981042848 2840-98-104-2848 2840981042848 981042848 is a continuous-combustion
/www.nsnlookup.com /nato/nato-stock-numbers/inc Turbo-Shaft Aircraft Engine (INC 32600) 1978 2840-98-104-2848
2840-12-175-9125 Turbo-Shaft Aircraft Engine 2G-2ALI1-4RNCC: 6 | RNVC: 9 | DAC: 9 25 Oct 1978 2840-98-104-2848
2840-99-766-0507 2840997660507 997660507 is a continuous-combustion type power unit, may be with or without container, designed to exert thrust. it's prime physical characteristics include air compressor(s), combustion chamber(s) and gas turbine. the operating principle is as follows: atmospheric air is inducted into the unit at its front, compressed, heated by combustion of a fuel, expanded through the gas turbine, and ejected at high velocity. it may incorporate features to vary direction of the thrust.
DAC: 2 10 Mar 1988 5306-99-617-0466 Machine Bolt AS21911RNCC: 5 | RNVC: 2 | DAC: 2 25 Apr 1991 2840-98-104-2848

2840-98-104-2848 Demil Restrictions 2840-98-104-2848

DEMIL: | DEMILI: | CRITICALITY: | HMIC: | PMIC: | EDC: | ADPEC:

2840-98-104-2848 is a Turbo-Shaft Aircraft Engine

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