Thursday 29 November 2012

The Rockwell Commander 112 & 114






Type  

Four seat high performance light aircraft

History  

The Rockwell Commander 112 and 114 are high performance, retractable undercarriage light aircraft.

Rockwell's General Aviation Division began development of the original Commander 111 and 112 during the late 1960s, and announced its new range in late 1970. Both models featured conventional construction and a low wing configuration but the 111 had fixed undercarriage and the 112 had retractable gear. The prototype 112 first flew on December 4 1970, and was powered by a 135kW (180hp) Lycoming O360, while a prototype 111 flew for the first time late in 1971. The loss of the 112 prototype during flight testing due to the structural failure of the tail unit delayed certification and production of both models until a fix was found. Deliveries of production aircraft took place from late 1972.

Production 111s were powered by 135kW (180hp) O360s, production 112s were powered by more powerful 150kW (200hp) IO360s. Only a few 111s were built before Rockwell decided to concentrate on the higher performance retractable gear 112. The updated 112A appeared in 1974 with a higher max takeoff weight, improved cabin ventilation and detail refinements, while the turbocharged 112TC was introduced in 1976.

Also introduced in 1976 was the 114, which is basically a 112 with a more powerful six cylinder IO540. The 114 remained in production basically unchanged until production ceased in 1979, by which stage it had been named the Gran Turismo Commander. Meanwhile the improved 112B had appeared in 1977, featuring an increased max takeoff weight and the extended wingtips introduced on the 112TC. By that stage the 112TC was designated the 112TCA, later it became known as the Alpine Commander.

The Commander Aircraft Company has been building the improved 114B and 114TC since 1992, but these are described separately.


Country of origin  

United States of America

Powerplants  

112B - One 140kW (200hp) Lycoming IO360C1D6 fuel injected flat four piston engine driving a two blade constant speed propeller. 114 - One 195kW (260hp) Lycoming IO540T4A5D fuel injected flat six driving a three blade constant speed prop.

Performance  

112B - Max speed 277km/h (150kt), max cruising speed 251km/h (135kt), long range cruising speed 222km/h (120kt). Initial rate of climb 880ft/min. Service ceiling 15,200ft. Max range with reserves 1085km (585nm), or 1647km (890nm) with optional fuel. 114 - Max speed 307km/h (166kt), max cruising speed 290km/h (157kt), long range cruising 254km/h (137kt). Initial rate of climb 1088ft/min. Service ceiling 17,400ft. Max range with reserves 1355km (730nm).

Weights  

112B - Empty 804kg (1773lb), max takeoff 1270kg (2800lb). 114 - Empty 885kg (1885lb), max takeoff 1425kg (3140lb).

Dimensions  

Wing span 10.85m (35ft 8in), length 7.63m (25ft 1in), height 2.57m (8ft 5in). Wing area 15.2m2 (164sq ft). 114 - Same except wing span 9.98m (32ft 9in). Wing area 14.1m2 (152.0sq ft).

Capacity  

Typical seating for four.

Production  

Production of the 112 and 114 series ceased in 1979.






Er Neha Godbole B.E (Computer Science), PGDM (PM & HRD) 
Executive HR 
www.AeroSoftCorp.com  
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