|Zlín 42, 142 and 242 series|
|Moravan Zlín 242L|
|Role||Sport, personal and trainer aircraft|
|First flight||17 October 1967|
|Variants||Zlín Z 43|
The Zlín Z 42 is a single-engine two-seat Czechoslovakian trainer aircraft manufactured by Moravan Otrokovice. A developed version, the Z 142, is the most popular aircraft variant in the manufacturer's aircraft line.
Design and development
The aircraft were built by Moravan Aviation, founded in 1934 by Tomáš Baťa in Czechoslovakia.
As a follow-on and replacement for the successful Zlín Trener series of tandem aerobatic trainers, Moravan developed a new family of light aircraft, featuring a side-by-side seat layout, and comprising a two-seat trainer, the Zlín Z 42 and a four-seat trainer/tourer aircraft, the Zlín Z 43. The Z 42 first flew on 17 October 1967, achieving airworthiness certification on 7 September 1970.
The aircraft fuselage center section is of welded steel tube, covered with sheet metal and fiberglass panels. The tailcone is of monocoque construction. The empennage is of sheet metal. The two-spar wings are of all-metal construction. The tricycle landing gear is fixed, with a steerable nosewheel. Designed for aerobatics instruction, it was certified to +6.0 and -4.0 limit maneuvering load factors, and was equipped with full inverted fuel and oil systems, permitting extended inverted flight. The Z 42 is powered by a Walter inverted six-cylinder engine rated at 134 kW (180 hp).
The revised Zlín Z 42M flew in November 1972, with a revised tail taken from the Z 43, and a Constant speed propeller replacing the variable pitch propeller (where the propeller pitch is controlled by the pilot) of the original Z 42. When early Z 42s were refitted with the new propeller, they were redesignated Z 42 MU.
Development continued, with the Zlín Z 142, featuring a slightly enlarged two-seat airframe based on that of the Z 42 and the more powerful (157 kW (210 hp)) Walter (now LOM) M 337 fuel-injected inverted six-cylinder, supercharged air-cooled engine of the Z 43 replacing the unsupercharged LOM M137 engine of the Z 42. The prototype Z-142 first flew on 29 December 1978.
In the late 1980s, further development work was initiated. The inverted inline engine was replaced with a four-cylinder horizontally-opposed Lycoming IO-360 engine. This variant is designated the Z 242, and is immediately distinguishable by its relatively wide cowling which houses the flat-four engine.
Licence production of the Z 142 has been carried out in Algeria by ECA Fernas (sometimes known as just Fernas) as the ECA-Fernas 142, complete with aerobatic modifications.
Two Z-142s were used by the Liberation Tigers of Tamil Eelam in bombing sorties on the Sri Lankan airforce bases in Sri Lanka in 2007. In October 2008 the Zlíns were also used in an attack on a military base of the Sri Lanka Army, and a power station on the outskirts of the city of Colombo, Sri Lanka.
- Zlín Z 42
- Zlín Z 42M
- Zlín Z 142
- Zlín Z 242
- 200 hp (149 kW) 
- Zlín Z 242L
- Fernas 142 / ECA Fernas 142
- (ECA - Entreprise de construction aéronautique) Algerian licence production of the Z 142, first flown in 1993.
The aircraft is popular with flying training organizations. One of the largest fleet operators is Sault College of Sault Ste. Marie, Ontario, Canada, which operates twelve 242Ls.
- Government Flying Service 
- Separatist organizations
Specifications (Zlin 42M)
Data from Jane's all the world's aircraft 1975–76
- Crew: 1 or 2
- Capacity: (1 pax 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 takeoff 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
- Maximum speed: 226 km/h (140 mph; 122 kn) TAS(aerobatic TOW) at 600 m (1,969 ft) ISA
- Cruising 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 (329 mi; 286 nmi) standard fuel
- Ferry range: 1,200 km (746 mi; 648 nmi) with wingtip fuel tanks
- Service ceiling: 4,250 m (13,944 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: 0.084 hp/lb (0.138 kW/kg) normal
- 0.0886 hp/lb (0.1457 kW/kg) aerobatic
- 0.0886 hp/lb (0.1457 kW/kg) 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)
VHF radio and IFR instrumentation optional
- J W R Taylor 1971, p.32.
- J W R Taylor 1980, p,43.
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- Jackson 2003, p. 114.
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- ^ Moravan official site. Accessed October 31, 2005.
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