Pratt & Whitney Canada PW200

{{short description|Family of turboshaft engines by Pratt & Whitney Canada}}

{{Infobox aircraft begin

|name= PW200

|image=

|caption=

}}

{{Infobox Aircraft Engine

|type= Turboshaft

|national origin = Canada

|manufacturer= Pratt & Whitney Canada

|first run=

|major applications= AgustaWestland AW109
Bell 429
Eurocopter EC135
MD Explorer
Sikorsky S-76D

|number built = >5,400 {{Cite web|url=https://www.pwc.ca/en/products-and-services/products/helicopter-engines/pw200|title = PW200 - Pratt & Whitney}}

|program cost =

|unit cost =

|developed from =

|developed into =

|variants with their own articles =

}}

The Pratt & Whitney Canada PW200 is a family of turboshaft engines developed specifically for helicopter applications. It entered service in the 1990s.

Variants

;PW205B

:First run 1987. Flown in twin-engine MBB BO105 for demonstration only."Power The Pratt & Whitney Canada Story" Sullivan and Milberry, CANAV Books 1989, {{ISBN|0-921022-01-8}}, p.300

;PW206A

:Maximum continuous power 550 shp (410 kW) for use on the MD Explorer

;PW206B

:Maximum continuous power {{convert|431|shp|abbr=on}}, for use on the Eurocopter EC135

;PW206B2

:Maximum continuous power {{convert|431|shp|abbr=on}}.

;PW206C

:Maximum continuous power {{convert|561|shp|abbr=on}}, for use on the Agusta A109 Power

;PW206E

:Maximum continuous power {{convert|572|shp|abbr=on}}. for use on the MD Explorer

;PW207C

:Maximum continuous power {{convert|572|shp|abbr=on}}.

;PW207D

:Maximum continuous power {{convert|572|shp|abbr=on}}.

;PW207D1

:Variant of the PW207 with increased mechanical power, maximum continuous power {{convert|610|shp|abbr=on}}.

;PW207D2

:Variant of the PW207D1 with a fuel heater installed, maximum continuous power {{convert|610|shp|abbr=on}}.

;PW207E

:Maximum continuous power {{convert|572|shp|abbr=on}}. for use on the MD 902

;PW209T

:Maximum continuous power {{convert|800|shp|abbr=on}}. "Twin-pack" First run 1985, cancelled 1987. Intended for Bell TwinRanger{{Cite web |url=https://www.flightglobal.com/pdfarchive/view/1985/1985%20-%202881.html |title=Archived copy |access-date=2016-12-21 |archive-date=2018-09-26 |archive-url=https://web.archive.org/web/20180926014110/https://www.flightglobal.com/pdfarchive/view/1985/1985%20-%202881.html |url-status=dead }}

;PW210: Enhanced version of the PW200. Enhancements include; Lower fuel consumption, Dual Channel Full Authority Digital Engine Control (FADEC), Reduced environmental emissions and an Increase in power output ranging from {{convert|800|shp|abbr=on}} to {{convert|1000|shp|abbr=on}}{{cite web|url=https://www.pwc.ca/en/products-and-services/products/helicopter-engines/pw210|title=PW210|work=pwc.ca|accessdate=11 March 2021}}

Applications

Specifications

{{jetspecs

|ref={{cite web | title=Gas Turbine Engines. Aviation Week & Space Technology 2009 Source Book. pg. 126. | url=http://web02.aviationweek.com/aw/sourcebook/content.jsp?channelName=eg&headline=Gas-Turbine%20Engines%20&story=xml/sourcebook_xml/2009/01/26/AW_01_26_2009_p0200-09.xml | date=2009-01-26 | publisher=Aviation Week & Space Technology | accessdate=2011-06-30 }}{{dead link|date=March 2018 |bot=InternetArchiveBot |fix-attempted=yes }}{{cite web |title=EASA TYPE-CERTIFICATE DATA SHEET |url=https://www.easa.europa.eu/sites/default/files/dfu/E%20IM%20126_PW210%20%20TCDS%20issue%2003_0.pdf |publisher=EASA |accessdate=17 March 2019 |archive-date=28 November 2020 |archive-url=https://web.archive.org/web/20201128083821/https://www.easa.europa.eu/sites/default/files/dfu/E%20IM%20126_PW210%20%20TCDS%20issue%2003_0.pdf |url-status=dead }}

|type=Turboshaft

|length=35.9 in (91.2 cm)

|diameter=19.7 in (50 cm)

|weight=237 lb (107.5 kg)

|compressor=Single-stage centrifugal. PW210: Two-stage mixed flow and centrifugal

|combustion=Annular

|turbine=Single-stage high pressure turbine, single-stage power turbine. PW210: Two-stage power turbine

|fueltype=

|oilsystem=

|power=561 shp (418 kW)

|compression=

|bypass=

|aircon=

|turbinetemp=

|fuelcon=

|specfuelcon=0.542 lb/hp-hr

|power/weight={{convert|2.4|hp/lb|kW/kg|abbr=on}}

}}

References

{{Reflist|refs=

{{cite web | title=Type Certificate Data Sheet EA E.017 PW206 & PW207 series engines | url=http://easa.europa.eu/ws_prod/c/doc/Design_Appro/Engines/TCDS%20PWC%20PW206%20&%20207%20series%20engines%20Issue%205%20.pdf | date=28 July 2009 | publisher=European Aviation Safety Agency | accessdate=2009-12-26 | url-status=dead | archiveurl=https://web.archive.org/web/20091223071310/http://www.easa.europa.eu/ws_prod/c/doc/Design_Appro/Engines/TCDS%20PWC%20PW206%20%26%20207%20series%20engines%20Issue%205%20.pdf | archivedate=23 December 2009 }}

}}