Air drawn through two intakes enters the fan . leaving the fan the air is divided , one flow passing to an annular plenum chamber from which it is ducted through front left and right , cold nozzles , the other flow passes through variable inlet guide vanes
In the remaining portions of this manual F402-RR-406 nomenclature will be used to indicate either the F402-RR-406A or F402-RR-F406B engines , and F402-RR-408 engine nomenclature shall be used to indicate either the F402-RR408 , F402-RR-408A , or the F402-RR-408B engine
The F402-RR-408 series engine , with water injection , develops a nominal (static test bed) thrust of 23,400 pounds in optimum ICAO conditions or 22,200 pound without water injection
The F402-RR-406B engine uses improved turbine section materials that result in increased engine life . functionally . the F402-RR-406B engine is the same as the F402-RR-406 engine
the F402-RR-406A/F402-RR-406B engine . with water injection , develops a nominal (static test bed ) thrust of 21,550 pounds in optimum International Civil Aviation Organization (ICAO) conditions or 20.280 pounds without water injection
Each of the aircraft is powered by a rolls royce F402-RR-406B. F402-RR-408.F402-RR-408A. or F402-RR-408B dual spool .axial flow,turbo fan engine with thrust-vectoring exhaust nozzles . one of the spool is a 3-stage low pressure compressor(fan)driven by a 2-stage low pressure turbine and the...