Design and development
edit
The Trigull was designed as an improved and updated
Republic RC-3 Seabee
. It features a cantilever
high-wing
, a four to six seat enclosed cabin, retractable
tricycle landing gear
and a single engine in
pusher configuration
.
[1]
[3]
The aircraft is made from
aluminum
sheet with the forward cabin made from
fibreglass
. Its 41.8?ft (12.7?m) span wing employs a
NACA
23015 R-4
airfoil
, has an area of 245.2?sq?ft (22.78?m
2
) and
flaps
. Standard engines available were initially intended to be the
Continental Tiara 6-285
285?hp (213?kW) and Tiara 6-320 320?hp (239?kW)
four-stroke
powerplants. Later the 300?hp (224?kW)
Lycoming IO-540-M1A5D
and turbocharged 340?hp (254?kW)
Lycoming TIO-540-J2BD
were used.
[1]
[3]
[4]
[5]
The design incorporates some innovative features, including wing tip floats that retract into the wing tips and provide additional wing area and lift, a nose wheel that retracts into the nose to act as a bumper for mooring on water and drooping
ailerons
.
[1]
The Trigull was specifically designed to compete with the
Republic RC-3 Seabee
,
Lake Buccaneer
and the
SIAI-Marchetti FN.333 Riviera
.
[1]
Trident Aircraft was founded in February 1970 to develop the TR-1. The aircraft first flight was on 5 August 1973, with the second prototype first flying on 2 July 1976. The TR-1 Trigull 285 model's Canadian
Transport Canada
aircraft certification was completed on 28 October 1976 with US
Federal Aviation Administration
certification following on 16 December 1976. Series production was to commence in the early 1980s, and orders were received for 43 aircraft, plus 23 options. The project received technical assistance from both
Canadair
and
Grumman Aerospace Corporation
. Despite financial assistance from the federal government's Ministry of Industry, Trade and Commerce and the provincial government's British Columbia Development Corporation, the company ran out of capital and ceased operations in 1980.
[3]
[6]
[7]
Although intended for series production, only three prototypes were ever built by Trident. Two were registered and flown, CF-TRI (later C-FTRI) and C-GATE, while the third was an engineering test airframe.
[8]
The type certificate has been held by
Viking Air
of Sidney, British Columbia since 2006. Viking Air also owns the two remaining prototype aircraft. In 2003 Viking Air indicated an interest in producing the Trigull as a turbine-powered amphibian, with a price at that time estimated at
US$
400,000, but since then no further news has been released.
[6]
[7]
[8]
[9]
[10]
- TR-1 Trigull 285
- Model with the
Continental Tiara 6-285
285?hp (213?kW) engine and four seats. Type certified in Canada on 28 October 1976 and in the United States on 16 December 1976.
[1]
[6]
[7]
- TR-1 Trigull 320
- Model with the
Continental Tiara 6-320
320?hp (239?kW) engine and six seats.
[1]
Specifications (Trigull 285)
edit
Data from
Plane and Pilot.
[1]
[5]
General characteristics
- Crew:
one
- Capacity:
three passengers
- Length:
29?ft 4?in (8.94?m)
- Wingspan:
41?ft 9?in (12.73?m) with tip floats up
- Height:
12?ft 6?in (3.81?m) on land
- Wing area:
245.2?sq?ft (22.78?m
2
) with tip floats up
- Aspect ratio
:
7.11:1 with tip floats up
- Airfoil
:
NACA 23015R-4 (modified)
- Empty weight:
2,400?lb (1,089?kg)
- Gross weight:
3,800?lb (1,724?kg)
- Fuel capacity:
103 U.S. gallons (390?L; 86?imp?gal)
- Powerplant:
1 ×
Continental Tiara 6-285
six cylinder, air-cooled,
four stroke
aircraft engine
, 285?hp (213?kW)
- Propellers:
3-bladed
Hartzell Propeller
, 7?ft (2.1?m) diameter reversible pitch
Performance
- Maximum speed:
157?mph (253?km/h, 136?kn)
- Cruise speed:
148?mph (238?km/h, 129?kn)
- Stall speed:
52?mph (84?km/h, 45?kn)
- Never exceed speed
:
211?mph (340?km/h, 183?kn)
- Range:
520?mi (840?km, 450?nmi)
- Service ceiling:
16,000?ft (4,900?m)
- Rate of climb:
1,000?ft/min (5.1?m/s)
- Wing loading:
15.5?lb/sq?ft (76?kg/m
2
)
- Taylor, John W.R., ed. (1975).
Jane's all the world's aircraft, 1975-76
(66th annual?ed.). New York: Franklin Watts Inc. pp.?28?29.
ISBN
978-0531032503
.