The Zlín Z 42 is a trainer aircraft manufactured by Moravan Otrokovice, a Czechoslovakian company. It is a single-engine, two-seat aircraft.
Within the manufacturer’s aircraft line, the Z 142, an enhanced version, stands as the most widely favoured variant.
Moravan has developed a new range of light aircraft to succeed and replace the prosperous Zlín Trener series of tandem aerobatic trainers.
This new family of aircraft features a side-by-side seat layout and includes a two-seat trainer, the Zlín Z 42, and a four-seat trainer/tourer aircraft, the Zlín Z 43.
The Z 42 successfully completed its maiden flight on 17 October 1967 and obtained airworthiness certification on 7 September 1970.
The aircraft fuselage centre section is constructed using welded steel tubes, which are then covered with sheet metal and fiberglass panels.
The tail cone is built using monocoque construction techniques.
The empennage is made of sheet metal.
The wings, on the other hand, are constructed using a two-spar design and are made entirely of metal.
The landing gear is of the tricycle type and is fixed, with a nosewheel that can be steered.
This aircraft, which has been specifically designed for aerobatics instruction, has been certified to withstand manoeuvring load factors of up to +6.0 and -4.0.
It is equipped with full inverted fuel and oil systems, allowing for extended periods of inverted flight.
Powering the Z 42 is a Walter inverted six-cylinder engine, which has a power rating of 134 kW (180 hp).
The modified Zlín Z 42M took its inaugural flight in November 1972, featuring an altered tail derived from the Z 43 model, as well as a Constant speed propeller that replaced the original Z 42’s variable pitch propeller, which allowed the pilot to control the propeller pitch.
Subsequently, when the early Z 42 aircraft were retrofitted with the new propeller, they were reclassified as Z 42 MU.
The process of development continued, resulting in the creation of the Zlín Z 142.
This aircraft featured a slightly larger two-seat structure, which was based on the design of the Z 42.
Additionally, it was equipped with a more powerful Walter (now LOM) M 337 fuel-injected inverted six-cylinder, supercharged air-cooled engine, generating 157 kW (210 hp), replacing the unsupercharged LOM M137 engine used in the Z 42.
The first prototype of the Z-142 took its maiden flight on 29 December 1978.
In the late 1980s, further advancements were made in the development of this aircraft.
The inverted inline engine was substituted with a four-cylinder horizontally opposed Lycoming IO-360 engine.
This particular variant, known as the Z 242L Guru, can be easily identified by its wider cowling, designed to accommodate the flat-four engine.
In the year 2021, Zlin unveiled an updated version of the 242L aircraft, which they named the Zeus.
This iteration features a redesigned tail with smoother contours, as well as a more aerodynamic cockpit and modifications to the undercarriage. Variants Zlín Z 42 Initial production version, powered by 180 hp (130 kW) Avia M-137 engine. Zlín Z 42M Revised dorsal fin and constant speed propeller fitted. Zlín Z 142 Forward-sliding bubble cockpit canopy. Powered by 225 hp (168 kW) M-337AK engine. Zlín Z 242 200 hp (149 kW) Zlín Z 242L Guru Zlín Z 242L Zeus Fernas 142 / ECA Fernas 142 (ECA – Entreprise de construction aéronautique)
Algerian licence production of the Z 142, first flown in 1993. Specifications Crew 1 or 2 Capacity 1 passenger or student Length 7.07 m (23 ft 2 in) Wingspan 9.11 m (29 ft 11 in) 9.19 m (30 ft) over tip-tanks Height 2.69 m (8 ft 10 in) Wing area 13.15 m2 (141.5 sq ft) Airfoil NACA 632416.5 Empty weight 645 kg (1,422 lb) Max take-off weight 970 kg (2,138 lb) normal 920 kg (2,028 lb) aerobatic Fuel capacity 130 L (34 US gal; 29 imp gal) in wing leading edges Powerplant 1 × Avia M 137 AZ 6-cylinder inverted air-cooled in-line piston engine, 130 kW (180 hp) Propellers 2-bladed Avia V 503, 2 m (6 ft 7 in) diameter fully automatic constant-speed propeller Performance Maximum speed 226 km/h (140 mph, 122 kn) TAS (aerobatic TOW) at 600 m (1,969 ft) ISA Cruise speed 215 km/h (134 mph, 116 kn) TAS at 600 m (1,969 ft) ISA Stall speed 89 km/h (55 mph, 48 kn) flaps down power off Never exceed speed 315 km/h (196 mph, 170 kn) Range 530 km (330 mi, 290 nmi) standard fuel Ferry range 1,200 km (750 mi, 650 nmi) with wingtip fuel tanks Service ceiling 4,250 m (13,940 ft) G limits +3.8 -1.5 normal +6 -3.5 aerobatic Rate of climb 5.2 m/s (1,020 ft/min) Wing loading 74 kg/m2 (15 lb/sq ft) normal 70 kg/m2 (14 lb/sq ft) Power/mass 0.138 kW/kg (0.084 hp/lb) normal 0.143 kW/kg (0.087 hp/lb) aerobatic Take-off run to 15 m (49 ft) 380 m (1,247 ft) Landing run from 15 m (49 ft) 410 m (1,345 ft) Avionics VHF radio and IFR instrumentation optional.
