Editing Europrop TP400 (section)

==Specifications (TP400-D6)==
{{jetspecs
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|ref=''EASA type certificate data sheet for TP400-D6, issue 07, page 6''<ref name="TP400-D6-TypeSpec"/>
|type = 3-spool [[axial flow]] [[turboprop]]
|length = {{cvt|4180|mm|m ftin|order=out|lk=on}}
|diameter = {{cvt|1218|mm|m ftin|order=out|lk=on}}
*'''Propeller diameter''': {{cvt|5.334|m|ftin|lk=on}}<ref name="FH385-FH386-TypeSpec"/>
|weight = {{cvt|1938.1|kg|lk=on}} for baseline engine (propeller clockwise); {{cvt|1965.1|kg|lk=on}} for handed engine (propeller anti-clockwise)
* '''Propeller weight''': {{cvt|683|kg|lk=on}}<ref name="FH385-FH386-TypeSpec"/>
|compressor=MTU 5-stage intermediate pressure compressor, Rolls-Royce 6-stage high pressure compressor with 2 variable stages<ref name="PowerStation"/>
|combustion=Snecma<ref name="PowerStation"/> annular combustion chamber with 18 fuel nozzles<ref name="MilTech201002"/>
|turbine=Snecma single-stage high pressure turbine; MTU single-stage intermediate pressure turbine; ITP 3-stage low pressure turbine<ref name="PowerStation"/>
|fueltype=[[Jet A]], [[Jet A1]], [[Jet B]], [[JP4]], [[JP5]], [[JP8]], and [[JP-8#Variants|JP8+100]]<ref name="A400M-TypeSpec"/>
|oilsystem=
|power=''Uprated takeoff'': {{cvt|8251|kW|0|lk=on}}; ''Maximum continuous'': {{cvt|7971|kW|-1|lk=on}}<ref name="FH385-FH386-TypeSpec"/>
|compression=25<ref name="MilTech201002"/>
|aircon={{cvt|26.3|kg/s|lb/s}}<ref name="MilTech201002"/>
|turbinetemp={{cvt|1200|C|F}}<ref name="MilTech201002"/>
|specfuelcon= ''In cruise'': {{cvt|0.35|lb/hph|g/kWh|order=flip}}<ref name="HectoPressure"/>
|power/weight={{cvt|{{#expr:8251/1938.1round2}}|kW/kg}}
}}