Piper PA 44 Seminole

Design and 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 that 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 and 1982. 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 takeoff 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.

Civil

The PA-44 is popular with air charter companies and flight schools, and is operated by private individuals and companies.

Military

 Jordan

Royal Jordanian Air Force

Specifications (PA-44-180 Seminole)

Data from Airliners.net

General characteristics

Crew: one pilot

Capacity: three passengers

Length: 27 ft 7.2 in (8.41 m)

Wingspan: 38 ft 8 in (11.77 m)

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)

Maximum Ramp Weight: 3 816 lb (1,731 kg)
Fuel: two main nacelle tanks, each of 55 U.S. gallon capacity (110 U.S. Gal. total), two U.S. gallons unusable.

Powerplant: × 1 Lycoming O-360-A1H6, 1 Lycoming LO-360-A1H6 air-cooled, direct-drive, horizontally opposed four-cylinder engine, 180 hp (135 kW) at Sea Level each

Propellers: Hartzell HC-C2Y(K,R)-2 two-bladed, constant speed, fully feathering, with pitch controlled by oil/nitrogen pressure propeller, one per engine

Performance

Cruise speed: 155 kt

Range: 1,000 miles (1,630 km)

Service ceiling: 17,100 ft (5,213 m)

Rate of climb: 1,200 ft/min (366 m/min)

Wing loading: 21.1 lb/ft² (100.8 kg/m²)

Power/mass: 10.55 lb/hp (0.16 kW/kg)

Single Engine Service ceiling 3,800 ft

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