TL-232 CONDOR

TYPE: Tandem-seat ultralight/kitbuilt.

PROGRAMME: Side-by-side seat TL-132 (Rotax 503 engine) first flown 1993; entered production, and TL-232 introduced, in 1994. Tl-132 subsequently discontinued.

CURRENT VERSIONS: TL-232 Condor Plus: Compared to Tl-132, has modified wing profile; option of more powerful engine; cut-down rear fuselage and additional glazing for rear cockpit.
Power Condor: Version with 73.5 kW (98.6 hp) Rotax 912 ULS and glider-towing equipment; able to aero-tow sailplanes of up to 400 kg (882 lb) AUW.
Condor S: Aerotowing version, certified 23 October 2001. Prototype (D-MPAK) fitted with Hirth fuel-injected engine.

CUSTOMERS: Operators in Czech Republic, Germany, Netherlands, Poland and Sweden. Total of 51 (including nine kits) registered in Czech Republic by late 2000, at which time more than 100 flying in Europe.

COSTS: Kit only €21,010; with Rotax 582 UL-DCDI €38,000; Rotax 912 UL €47,700; Rotax 912S UL €58,800 (all 2003).

DESIGN FEATURES: Constant-chord, high wing V-strut bracing; mid-mounted tailplane; sweptback fin with long fillet. Wings and horizontal tail surfaces foldable for transportation and storage.

FLYING CONTROLS: Conventional and manual. In-flight-adjustable tab in starboard elevator. Two-position flaps. Dual controls.

STRUCTURE: Fabric-covered metal. Composites rear top-decking.

LANDING GEAR: Non-retractable. Choice of tricycle or tailwheel configuration; tyre sizes 16x4 (main), 400x100 (nose). Cable brakes. Leg and wheel speed fairings optional.

POWER PLANT: One 47.8 kW (64.1 hp) Rotax 582 UL-DCDI two-cylinder two-stroke in-line engine in basic TL-232, driving a three-blade Albastar ground-adjustable pitch propeller. Optional alternatives include 59.6 kW (79.9 hp) Rotax 912 UL-DCDI or 73.5 kW (98.6 hp) Rotax 912 ULS flat-four with Ivoprop three-blade composites propeller. Fuel capacity 50 litres (13.2 US gallons; 11.0 Imp gallons) standard, 70 litres (18.5 US gallons; 15.4 Imp gallons) optional.

 

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