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Wikipedia,
the free encyclopedia,
http://en.wikipedia.org/wiki/Piper_PA-44_Seminole
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Piper PA-44-180 Seminole |
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Piper PA-44-180 Seminole |
The Piper PA-44 Seminole is an American twin-engined light aircraft manufactured by Piper Aircraft.
The PA-44 is a development of the Piper Cherokee single-engine aircraft and is primarily used for multi-engine flight training.
The Seminole was built in 1979-82, in 1989-90, and again since 1995.
Development
The first production Seminoles are equipped with two 180-hp (135 kW) Lycoming O-360-E1A6D engines. The right hand engine is a Lycoming LO-360-E1A6D variant, which turns in the opposite direction to the left hand engine. This feature eliminates the critical engine and makes the aircraft more controllable in the event an engine needs to be shut down or fails.
The Seminole was first certified on March 10, 1978 and introduced as a 1979 model year in late 1978. Gross weight is 3800 lbs (1723 kg).
Later production Seminoles were built with Lycoming O-360-A1H6 engines.
The PA-44-180T Turbo Seminole version was certified on November 29, 1979 and built between 1981-82. It features two turbocharged 180-hp (135 kW) Lycoming TO-360-E1A6D engines, which offer a significant improvement in performance at high density altitude. The Turbo Seminole had its take-off gross weight raised to 3925 lb (1780 kg), while the landing weight remained at 3800 lbs (1723 kg).
The PA-44 features a high T-tail similar to the T-tailed Arrow IV. The Seminole resembles the competitive Beechcraft Duchess.
Variants
- PA-44-180 Seminole
- Normally aspirated version powered by two Lycoming O-360-E1A6D or two O-360-A1H6 engines.
- PA-44-180T Turbo Seminole
- Turbocharged version powered by two Lycoming TO-360-E1A6D engines.
Specifications (PA-44-180 Seminole)
General characteristics
- Crew: 1 pilot
- Capacity: 3 passengers
- Length: 27 ft 7.2 in (8.41 m)
- Wingspan: 3811.77 m ft 6.6 in ()
- Height: 8 ft 6 in (2.59 m)
- Wing area: 184 ft² (17.1 m²)
- Empty weight: 2,360 lb (1,070 kg)
- Max takeoff weight: 3,800 lb (1,723 kg)
- Powerplant: 2 (opposite rotation)× Lycoming O-360-A1H6 air cooled, direct-drive, horizontally opposed 4 cylinder engines, 180 hp (135 kW) at Sea Level each
- Propellers: 2-bladed, constant speed, fully feathering Hartzell HC-C2Y(K,R)-2 C[L]EUF with pitch controlled by oil/nitrogen pressure. propeller, 1 per engine
- Maximum Ramp Weight: 3 816 lb (1,731 kg)
Fuel: 2 main nacelle tanks, each of 55 U.S. gallon capacity (110 U.S. Gal. total), 2 U.S. gallons unusable.
Performance
Related content
Related development
Comparable aircraft
External links
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Published in July 2009.
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