TYPE: Primary prop trainer/sportplane.
PROGRAMME: Lycoming-powered version of Z 142. Design started December 1988; first flight (OK-076) 14 February 1990; second prototype (SE-KMS) followed, both converted on production line from Z 142; Czech certification to FAR Pt 23 (A, U and N categories) 22 March 1992; now certified in Argentina, Australia, Austria, Belgium, Canada, Israel, Luxembourg, Slovenia, Sweden, UK and USA.
CURRENT VERSIONS: Z 242 L: Aerobatics-capable trainer.
Description applies to this version.
Z 242 LA: Lower-powered, non-aerobatic version for primary, day/night and IFR training and glider/banner towing; g limits +4.4/-1.76. Prototype (OK-ANA) on test early 1996. No subsequent information received.
CUSTOMERS: Total of 120 delivered by late 2002, for customers in Argentina (one), Australia (one), Canada (15), Czech Republic (four), Israel (three), Macedonia (four), Peru (Air Force, 18), Slovenia (Defence Force, seven), Sweden (two), UK (three), USA (38) and elsewhere. Yemen Air Force received 12 in 2002. Ten ordered by Mexican Navy for Escuela de Aviacion at Baja; delivered 13 June 2002, with negotiations continuing for up to 10 more. Bolivia and Ecuador also discussing possible orders at that time. Company reported an order backlog of more than 100 for US flying schools in mid-2001; was also then bidding (unsuccessfully) for USAF T-3A Firefly replacement contract.
COSTS: Mexican Navy contract reported as approximately US$2.6 million (2002).
DESIGN FEATURES: Conventional low-wing monoplane. Constant-chord horizontal surfaces with wingroot glove. Sweptback fin with fillet. Changes from Z 142, apart from new engine, include redesigned (and shorter) engine cowling and front fuselage, wing incidence, 0o sweep, wingroot glove, redesigned wing- and tailplane tips, redesigned fuel system and updated instruments. Spin recovery strake each side of cowling.
Wing section NACA 632416.5.
FLYING CONTROLS: Conventional and manual. Slotted, mass-balanced surfaces used for ailerons and flaps; horn-balanced elevator with trim tab; ground-adjustable tabs in ailerons and rudder; ailerons and elevator operated by rods, rudder by cables.
STRUCTURE: Mainly metal; wing has main and auxiliary spars; duralumin skins, fluted on control surfaces; metal engine cowlings; centre-fuselage is steel tube cage with composites skin panels.
LANDING GEAR: Non-retractable tricycle type, with nosewheel offset 13 cm (5.1 in) to port. Oleo-pneumatic nosewheel shock-absorber. Mainwheels carried on flat spring steel legs. Nosewheel steered (±38o) by rudder pedals. Mainwheels and Barum tyres size 420x150 or Goodyear 6.00-6.5, pressure 1.90 bar (28 lb/sq in); nosewheel and Barum tyre size 350x135 or Goodyear 5.00-5, pressure 2.50 bar (36 lb/sq in). Hydraulic disc brakes on mainwheels can be operated from either seat. Parking brake standard.
POWER PLANT: One Textron Lycoming AEIO-360-A1B6 flat-four engine (149 kW; 200 hp at 2,700 rpm) driving an MTV-9-B-C/C-188-18a three-blade constant-speed wood/composites propeller or Hartzell HC-C3YR-4BF/FC 6890 three-blade constant-speed metal propeller. Fuel capacity 120 litres (31.7 US gallons; 26.4 Imp gallons); Normal category version wingtip tanks 55 litres (14.5 US gallons; 12.1 Imp gallons) each, bringing usable capacity to 230 litres (60.7 US gallons; 50.6 Imp gallons). Inverted flight limited to 1 minute. Oil capacity 8 litres (2.1 US gallons; 1.8 Imp gallons).
ACCOMMODATION: Side-by-side seats for two persons, instructor's seat to port. Both seats adjustable and permit use of back-type parachutes. Baggage space (20 kg; 44 lb) aft of seats. Cabin and windscreen heating and ventilation standard. Forward-sliding cockpit canopy. Dual controls standard.
SYSTEMS: Electrical system includes 1.6 kW 28 V engine-driven generator and 24 V 19 Ah Gill battery. External power source can be used for engine starting.
AVIONICS: To customer's specification, usually from Bendix/King Silver Crown or Garmin range.
EQUIPMENT: Standrad equipment includes EGT gauge, fuel flow indicator, g meter and anti-collision beacon, Optional items include cockpit/instrumental/cabin lights, landing/taxying lights, anti-collision lights, and towing gear for gliders of up to 500 kg (1,102 lb) weight.