Editing CASA C-212 Aviocar (section)

==Specifications (Series 400)==
[[File:C-212-200 D.3B-04 cabin, radar operator.jpg|thumb|Radar operator's console in the cabin of a C-212]]
[[File:AWS Casa-212 in afghanistan.jpg|thumb|[[Blackwater Worldwide]] C-212 over Afghanistan]]
[[File:EC-025.jpg|thumb|CASA C-212-400 of the [[Vietnam Coast Guard]]]]
{{Aircraft specs
|ref= ''Jane's All The World's Aircraft 1989–90''<ref>{{cite book |title = Jane's all the World's Aircraft 1989–90 |year = 1989 |publisher = Jane's Information Group |location = London |isbn = 978-0710608963 |editor1-last = Taylor |editor1-first = John W.R. |edition = 80th |pages = 216–218}}</ref><ref name="Janes 88 p205-6">Taylor 1988, pp. 205–206.</ref>
|prime units?= met
<!--
        General characteristics
-->
|crew= 2
|capacity= 26 passengers / 25 paratroops / {{cvt|2820|kg|0}} military payload / {{cvt|2700|kg|0}} cargo payload
|length m= 16.15
|length note=
|span m= 20.28
|span note=
|height m= 6.6
|height note=
|wing area sqm= 41
|wing area note=
|aspect ratio= 10
|airfoil= [[NACA airfoil|NACA 65<sub>3</sub>-218]]<ref name="Selig">{{cite web |last1 = Lednicer |first1 = David |title = The Incomplete Guide to Airfoil Usage |url = https://m-selig.ae.illinois.edu/ads/aircraft.html |website = m-selig.ae.illinois.edu |access-date = 16 April 2019}}</ref>
|empty weight kg= 3,780
|empty weight note=
|gross weight kg=
|gross weight note=
|max takeoff weight kg= 8,000
|max takeoff weight note=military {{cvt|7700|kg|0}} standard
|fuel capacity= {{cvt|2040|L|USgal impgal}} / {{cvt|1600|kg|0}} internal and {{cvt|1000|L|USgal impgal}} auxiliary fuel tanks in the cabin or 2x {{cvt|750|L|USgal impgal}} auxiliary fuel tanks in the cabin and/or 2x {{cvt|500|L|USgal impgal}} underwing auxiliary fuel tanks 
|more general=
<!--
        Powerplant
-->
|eng1 number= 2
|eng1 name= [[Garrett AiResearch TPE331-10R-513C]]
|eng1 type= [[turboprop]] engines
|eng1 kw= 671
|eng1 note=

|prop blade number= 4
|prop name= [[Dowty Rotol]] R-334/4-82-F/13 
|prop dia m= 2.74
|prop dia note= constant-speed fully-feathering reversible-pitch propellers
<!--
        Performance
-->
|max speed kmh= 370
|max speed note= V<sub>MO</sub> (maximum operating speed) at MTOW
|max speed mach=<!-- supersonic aircraft -->
|cruise speed kmh= 354
|cruise speed note= (max cruise) at {{cvt|3050|m|-2}}
|stall speed kmh= 145
|stall speed note= in take-off configuration
|never exceed speed kmh=
|never exceed speed note=
|minimum control speed kmh=
|minimum control speed note=
|range km= 835
|range note= with full military payload
|combat range km=
|combat range note=
|ferry range km= 2,680
|ferry range note= with maximum fuel and {{cvt|1192|kg|0}} payload
|endurance=<!-- if range unknown -->
|ceiling m= 7,925
|ceiling sigfig=2
|ceiling note= {{cvt|3380|m|-2}} on one engine
|g limits=<!-- aerobatic -->
|roll rate=<!-- aerobatic -->
|climb rate ms= 8.3
|climb rate note=
|time to altitude=
|wing loading kg/m2=
|wing loading note=
|fuel consumption kg/km=
|power/mass=
|more performance=<br/>
* '''Take-off distance to {{cvt|15|m|0}}:''' {{cvt|610|m}} (MIL-7700C)
* '''Landing distance from {{cvt|15|m|0}}:''' {{cvt|462|m}} (MIL-7700C)
* '''Landing run:''' {{cvt|285|m}} (MIL-7700C)
<!--
        Armament
-->
|armament=
* Up to {{cvt|500|kg|0}} of weapons on two hardpoints. Typically, machine gun pods or rocket launchers.

|avionics=
}}

{| class="wikitable" style="text-align:center"
|+ FAA Data Sheet<ref>{{cite web |url = https://rgl.faa.gov/Regulatory_and_Guidance_Library/rgMakeModel.nsf/0/4ab322dd7032261c86257dc8004d0cee/$FILE/A43EU_Rev_11.pdf |title = Type Certificate Data Sheet No. A43EU |publisher = [[Federal Aviation Administration]] |date = 8 January 2015 |access-date = 27 October 2018 |archive-url = https://web.archive.org/web/20161112164214/http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgMakeModel.nsf/0/4ab322dd7032261c86257dc8004d0cee/$FILE/A43EU_Rev_11.pdf |archive-date = 12 November 2016 |url-status = live}}</ref>
! Variant !! -CB !! -CC/CD/CE/CF/DF !! -DE
|-
! Approved 
| 22 Feb 1977 
| 16 May 1980-30 Mar 1989
| 1 Oct 1991
|-
! 2× Turboprop
| [[Garrett TPE331]]-5
| TPE331-10
| [[Pratt & Whitney Canada PT6|P&WC PT6]]A-65B
|-
! Takeoff power
| {{cvt|750|hp|0|order=flip}}
| {{cvt|900|hp|0|order=flip}}
| {{cvt|1000|hp|0|order=flip}}
|-
! Propellers
| colspan=3 | four-bladed variable pitch
|-
! Manufacturer
| colspan=2 | Hartzell 
| McCauley 
|-
! Propeller Diameter
| {{cvt|107.5|in|cm|order=flip}} 
| {{cvt|110|in|cm|0|order=flip}} 
| {{cvt|106|in|cm|0|order=flip}} 
|-
! [[V speeds|Max. operating]]
| colspan=3 | {{cvt|200|kn|km/h}} [[Indicated airspeed|IAS]]
|-
! [[Minimum control speeds|Min. control]] 
| {{cvt|78|kn|km/h}} IAS 
| {{cvt|85|kn|km/h}} IAS (-CC/CD)<br/>{{cvt|88|kn|km/h}} IAS (-CE/CF)<br/>{{cvt|76|kn|km/h}} IAS (-DF)
| {{cvt|76|kn|km/h}} IAS 
|-
! Chord 
| colspan=3 | {{cvt|86.22|in|cm}}
|-
! [[MTOW]]
| {{cvt|14332|lb|-1|order=flip}}
| colspan=2 | {{cvt|16,976|lb|order=flip}} 
|-
! Flight crew 
| colspan=3 | Two pilots
|-
! Max. passengers
| 19
| colspan=2 | 28
|-
! Usable fuel
| colspan=3 | {{cvt|528|USgal|L|order=flip}}
|-
! Ceiling
| colspan=3 | {{cvt|25,000|ft|order=flip}}
|}