TRIDENT TR-1 TRIGULL SPECIFICATIONS |
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GENERAL |
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| Manufacturer | Trident Aircraft Ltd. |
| Address | Sidney, British Columbia, Canada |
| Model | TR-1 Trigull |
| Seats | 4 + 2 |
| Approved Type Certificate No. | Canadian DOT Type
Approval A119 US ATC No: A19EA |
| Issue Date | 1976-10-28 (Canada) 1976-12-16 (USA) |
| Type Certifcate Holder | 1987-05-20 Viking Air Ltd. #9 - 9600 Canora Road Sidney, British Columbia Canada V8L 4R1 |
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DIMENSIONS |
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Length (Wheels down) |
29 ft 4 in |
| Height (Max Land) | 12 ft 6 in |
| Cabin Width (interior) | 3 ft 11 in |
| Cabin Height (interior) | 4 ft 2.2 in |
| Cabin Length (interior) | 8 ft 0.8 in |
| Baggage Compartment (volume) | 12.9 cu ft |
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LANDING GEAR |
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| Main Gear | Tricycle, hydraulic
retraction. Oleo-pneumatic shock-absorbers. |
| Track | 12 ft 0 in |
| Base | 12 ft 1 in |
| Main Wheels | 7.00-6 |
| Inflate to | 35 psi |
| Brakes | Cleveland hydraulic disc |
| Nose Wheel | 6.00-6 |
| Inflate to | 35 psi |
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WINGS |
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| Airfoil Section | NACA 23015R-4 (modified) |
| Span | wing floats up: 41
ft 9 in wing floats down: 38 ft 10 in |
| Chord | 6 ft 0 in |
| Aspect Ratio | wing floats
up: 7.11 wing floats down: 6.55 |
| Incidence | 2° 15' deg |
| Dihedral | 2° |
| Total Area | wing floats up:
245.2 sq ft wing floats down: 230.2 sq.ft |
| Aileron Total Area | 9.6 sq ft |
| Flap Total Area | 44.2 sq ft |
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EMPENNAGE |
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| Tailplane Area | 29.6 sq ft |
| Elevator Span | 15 ft 5 in |
| Elevator Total Area | 26.3 sq ft |
| Fin Area | 31.3 sq ft |
| Rudder Area | 9.8 sq ft |
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WEIGHTS |
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| Gross - Normal | 3800 lbs |
| Gross - Turbo | 3950 lbs |
| Empty | 2500 lbs |
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SURFACE MOVEMENTS |
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| Rudder | ± 30 ° |
| Ailerons | ± 20 ° |
| Elevators | ± 28 ° |
| Elevator Tabs | ± 25 ° |
| Water Rudder | ± 30 ° |
| Flaps | Down 30 ° |
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ENGINE |
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| Models | (1) Teledyne
Continental Tiara 6-320 (2) Lycoming IO-540-M1A5D (3) Lycoming TIO-540-J2BD |
| Rated Power | (1) 320 hp @ 4400
rpm (2) 300 hp (3) 340 hp |
| Power Loading | 12.67 lbs/hp(2) |
| Propeller to Crankshaft Ratio | 0.5:1 (1) |
| Fuel Grade | 100/130 minimum grade aviation |
| Fuel Consumption (Cruise 75%) | 16 US gal/hr (1) |
| Fuel Pressure | 2 to 9 psi |
| Compression Ratio | ?:1 |
| Piston Displacement | ? cu in |
| Bore | ? cu in |
| Stroke | ? cu in |
| Fuel Capacity | 100 US gal |
| Oil Capacity | (2) 12 qts |
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PROPELLER |
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| Model (Standard) | Hartzell c/s |
| Blades | 3 reversible |
| Diameter | 84 in |
| Model (Reversible Option) | Hartzell HC12x20-2 |
| Blades | 2 x L8427 wooden |
| Diameter | 84 in |
| Pitch | +18 deg to -12 deg (reverse) |
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PERFORMANCE |
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| Max Structural Cruise Speed (Vno) | 178 mph TIAS |
| Max Maneuvering Speed (Va) | ? mph TIAS |
| Never Exceed Speed (Vne) | 211 mph TIAS |
| Max Flaps Extended Speed (Vfe) | ? mph TIAS |
| Max Gear Extended Speed (Vle) | ? mph |
| Cruise Speed (Vc) @ 75% pwr | ? mph |
| Best Range Speed (Vbr) | ? |
| Best Endurance Speed (Vbe) | ? |
| Approach Speed (Vref) | ? mph IAS |
| Best Power-Off Glide Speed (Vbg) | ? |
| Minimum Descent Speed (Vmd) | ? |
| Stalling Speed (Vs0) - Gear/Flaps Down | ? mph IAS |
| Stalling Speed (Vs1) - Gear/Flaps Up | ? mph IAS |
| Best Climb Angle Speed (Vx) | ? |
| Best Rate of Climb Speed (Vy) | ? mph IAS |
| Rate of Climb (Sea Level) | ? ft/min |
| Service Ceiling | 18 000 ft |
| Range at Cruising (71 US gal) | 520 miles |
| Take-off Distance - Land | 800 ft |
| Take-off Distance - Water | 1000 ft |
| Take-off Time - Water | 25 secs |
| Landing Run - Land | 400 ft |
| Landing Run - Water | 700 ft |
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Updated: 2007-10-18 |
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Copyright © 2003-2007 Steinar Saevdal |