Cessna 441 Conquest II

Dérivé du Cessna 404, le biturbopropulseur Cessna 441 Conquest II de 1975 vu par Wikipedia.en

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The Cessna 441 Conquest II was the first turboprop designed by Cessna and was meant to fill the gap between their jets and piston-engined aircraft.

It was developed in November 1974, with the first aircraft delivered in September 1977. It is a pressurized, turbine development of the Cessna 404.

Design and development

The aircraft has retractable tricycle landing gear and on takeoff has a ground roll of 1,785 ft (544 m).

The Conquest is powered by two Garrett TPE331 turboprops powering two four-bladed McCauley propellers.

A 441 with Pratt & Whitney Canada PT6A-112 turboprops was flown in 1986 but did not enter production.

Modifications

The majority of Cessna 441s have been modified by installing Garrett TPE331-10 engines in place of the earlier versions of this same engine that it was delivered with.

This modification reduces maintenance costs while increasing horsepower, service ceiling, fuel efficiency and range.

Cessna 441s with this conversion tend to have higher resale values than aircraft that have not been converted.

Converting from the standard three blade propellers to smaller diameter Hartzell four blade propellers results in a climb rate improved by 200 fpm (1.01 m/s) and a 5 kn (9 km/h) increase in cruise speed as well as reducing cabin noise and improving ground clearance.

Airframe Limitations

The Cessna 441 is limited to 22,500 hours of air time by a Cessna Supplementary Inspection Document (SID).

This life-limit SID is mandatory in the USA for air carriers operating the aircraft but is advisory only for private operators

Designation

The ICAO designator for the Cessna Conquest as used in flight plans is C441.

Further developments

A smaller aircraft was marketed as the Cessna 425 Conquest I, itself a turbine development of the Cessna 421.

Specifications (Conquest II)

Data from Jane's All The World's Aircraft 1982–83

General characteristics

Crew: 1 or 2 pilots

Capacity: 8-10 passengers

Length: 39 ft 0 in (11.89 m)

Wingspan: 49 ft 4 in (15.04 m)

Height: 5 ft 9 in (1.75 m)

Wing area: 253.6 sq ft (23.56 m2)

Aspect ratio: 9.6:1

Airfoil: NACA 23018 at root, NACA 23019 at tip

Empty weight: 5,682 lb (2,577 kg)

Gross weight: 9,850 lb (4,468 kg)

Powerplant: 2 × Garrett TPE331-8-403S turboprops, 636 shp (474 kW) each

Propellers: 3-bladed McCauley

Un quadripale

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Performance

Maximum speed: 340 mph (547 km/h; 295 kn) at 16,000 ft (4,875 m)

Cruise speed: 298 mph (259 kn; 480 km/h) at 35,000 ft (10,700 m)

Stall speed: 86 mph; 75 kn (139 km/h) flaps and gear down

Range: 2,525 mi (2,194 nmi; 4,064 km) at 35,000 ft (10,700 m)

Service ceiling: 35,000 ft (10,668 m)

Rate of climb: 2,435 ft/min (12.37 m/s)