Falconar Teal
title: "Falconar Teal" type: doc version: 1 created: 2026-02-28 author: "Wikipedia contributors" status: active scope: public tags: ["1960s-canadian-civil-utility-aircraft", "flying-boats", "homebuilt-aircraft", "single-engined-tractor-aircraft", "high-wing-aircraft", "amphibious-aircraft", "falconar-aircraft", "aircraft-first-flown-in-1967"] topic_path: "geography/canada" source: "https://en.wikipedia.org/wiki/Falconar_Teal" license: "CC BY-SA 4.0" wikipedia_page_id: 0 wikipedia_revision_id: 0
::data[format=table title="Infobox aircraft"]
| Field | Value |
|---|---|
| name | Teal |
| type | Utility amphibian |
| manufacturer | Homebuilt |
| designer | Chris Falconar |
| first_flight | December 1967 |
| :: |
NOTOC |name=Teal |image= |caption= |type=Utility amphibian |manufacturer=Homebuilt |designer=Chris Falconar |first_flight=December 1967 |introduction= |retired= |status= |primary_user= |more_users= |produced= |number_built= |variants=
The Falconar Teal was a two-seat homebuilt, amphibious airplane designed by Chris Falconar of Edmonton, Alberta, Canada. From the 1970s to the 1990s plans were sold by Falconar Aviation of Edmonton (downtown municipal airport). A handful were built by amateur aircraft constructors (aka homebuilders) in Canada and the United States. Most were powered by certified Lycoming or Continental engines.
Design and development
The Teal was based on the two- or three-seat AMF Maranda, and was built mostly of wood. It featured strut-braced high wing, with "W" configuration struts running from the wing roots, down to stabilizing floats (which also contained the main wheels), then back up the wings near 70% span; cruciform tail; two pilots seated side by side under the wing; access to the cockpit by side doors; tricycle undercarriage with the main wheels retracting into stabilizing floats only about 25% of the wing span. The nosewheel retracted into the bow and was covered by two conventional (side-hinged) doors. A rarity among flying boats was its engine location in a nacelle, above the wing, with the propeller rotating immediately in front of the windscreen.
Specifications
|ref=Jane's All The World's Aircraft 1971–72 |prime units?=imp General characteristics
|genhide=
|crew=1 |capacity=1 passenger |length m= |length ft=24 |length in=6 |length note= |span m= |span ft=33 |span in=0 |span note= |height m= |height ft=7 |height in=10 |height note= |wing area sqm= |wing area sqft=160 |wing area note= |aspect ratio=6.6:1 |airfoil=NACA 4412 (modified) |empty weight kg= |empty weight lb=1050 |empty weight note= |gross weight kg= |gross weight lb= |gross weight note= |max takeoff weight kg= |max takeoff weight lb=1500 |max takeoff weight note= |fuel capacity= |lift kg= |lift lb= |lift note= |more general= Powerplant
|eng1 number=1 |eng1 name= Lycoming O-320-B2A |eng1 type=air-cooled flat four |eng1 kw= |eng1 hp=160 |eng1 note=
Performance
|perfhide=
|max speed kmh= |max speed mph=130 |max speed kts= |max speed note= |max speed mach= |cruise speed kmh= |cruise speed mph=125 |cruise speed kts= |cruise speed note=(max cruise) |stall speed kmh= |stall speed mph=37 |stall speed kts= |stall speed note= |never exceed speed kmh= |never exceed speed mph=185 |never exceed speed kts= |never exceed speed note= |range km= |range miles=450 |range nmi= |range note=standard fuel |ferry range km= |ferry range miles=700 |ferry range nmi= |ferry range note= |endurance= |ceiling m= |ceiling ft=16400 |ceiling note= |g limits= |roll rate= |climb rate ms= |climb rate ftmin=1100 |climb rate note= |time to altitude= |wing loading kg/m2= |wing loading lb/sqft= |wing loading note= |power/mass=
|more performance=
|avionics=
|see also= |related= |similar aircraft= |lists=
References
References
- Taylor 1971, p.23.
- Taylor 1971, pp. 23–24.
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