TYPE: Four-seat lightplane.
PROGRAMME: Original Rockwell 112 first flew (N112AC) 4 December 1970; 149 kW (200 hp) Lycoming IO-360; production deliveries began August 1972 and ended in February 1978; more powerful Rockwell 114 subsequently added to range; all production terminated in September 1979. Following formation of Commander Aircraft, 114B recertified 5 May 1992. Commander 114 series was withdrawn in early 2000 in favour of the 115. New version uses type certificate for 114 and continues to be registered as such.
CURRENT VERSIONS: Commander 115: Basic version, announced in early 2000. Improvements over 114B include increased fuel capacity; wing-mounted landing lights; taxying lights on landing gear; flush fuel and panel access covers; and redesigned electrical system, instrumentation and cabin environment.
Description applies to Commander 115.
Commander 115AT: Optimised for pilot training.
Commander 115TC: Replaces turbocharged 114TC in product line. Powered by 201 kW (270 hp) Textron Lycoming TIO-540-AG1A turbocharged six-cylinder engine driving McCauley B3D32C419/82NHA-5 three-blade constant-speed propeller. Total fuel capacity 341 litres (90.0 US gallons; 74.9 Imp gallons) in two integral wing tanks, of which 333 litres (88.0 US gallons; 73.3 Imp gallons) are usable. Oil capacity 9.46 litres (2.5 US gallons; 2.1 Imp gallons).
CUSTOMERS: Rockwell built 800 Model 112s (plus one static airframe), 429 Model 114/114As and two fixed-gear Model 111s. Commander Aircraft had added at least 126 Model 114Bs and 28 Model 114TCs before change to Model 115; by mid-2002, when production was suspended, had registered 17 115s and 17 115TCs, although two of the latter appear not to have been completed.
COSTS: 115 US$515,000; 115TC US$565,000 (2002).
DESIGN FEATURES: Rockwell 111 (fixed gear; two prototypes only) and 112 conceived as competitors to Piper Cherokee and Beech Bonanza.
Low wing with root glove, unswept leading-edge and sweptforward trailing-edge; sweptback fin with mid-mounted, tapered tailplane and small ventral strake.
Wing section NACA 63-415 modified; dihedral 7° incidence 2° at root; sweepforward 2° 30' at quarter-chord.
FLYING CONTROLS: Conventional and manual. Electrically actuated single-slotted flaps; horn-balanced tail control surfaces; anti-servo tabs in both elevators.
LANDING GEAR: Retractable tricycle type; mainwheels retract inward; nosewheel aft. Nosewheel (steerable) tyre size 5.00-5 (6 ply); mainwheel tyres size 6.00-6 (6 ply); dual brakes and oleo-pneumatic shock-absorbers.
POWER PLANT: One 194 kW (260 hp) Textron Lycoming IO-540-T4B5 flat-six engine, driving a McCauley B3D32C419/82NHA-5 three-blade, constant-speed (hydraulic) metal propeller. Fuel in two integral wing tanks, total capacity 341 litres (90.0 US gallons; 74.9 Imp gallons), of which 333 litres (88.0 US gallons; 73.3 Imp gallons) are usable. Refuelling points in upper surface of each wing. Maximum oil capacity 7.6 litres (2.0 US gallons; 1.7 Imp gallons).
ACCOMMODATION: Four persons on two individual seats (forward, with dual controls) and bench seat. Forward-hinged door each side. Externally accessed baggage compartment, port side, aft of wing. Provision for heating and ventilation.
SYSTEMS: 28 V DC electrical; 85 A alternator. Hydraulic system with electric pump. Optional air conditioning in 115 and 115TC. TKS fluid anti-icing system for wings and tail surfaces.
AVIONICS: Comms: Standard includes Garmin GMA 340, dual Garmin GNS 430 com/nav/GPS and Garmin GTX 327 transponder.