Zlin Z 142

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Zlin 42, 142 and 242 series
Moravan Zlin 242L
Type	Sport, personal and trainer aircraft
Manufacturer	Moravan Otrokovice

Zlin Z-142

Zlin Z42 M, tail number SP-AKE (nr 0170).

The Zlin Z 142 is a single-engine two-seat Czechoslovakian trainer aircraft manufactured by Moravan Otrokovice. The Z 142 is the most popular aircraft variant in its aircraft line, with the base model being the Z 42. In contrast to the older Z 40 which had both seats in tandem, all Z 42 series aircraft use side-by-side seating.

[edit] Design and development

The aircraft were built by Moravan Aviation, founded in 1934 in aviation by Tomas Bata in the Czech Republic.

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, and incorporates an all-flying tail. The two-spar wings are of all-metal construction. The tricycle landing gear is fixed, with a steerable nose wheel. The Z 42 is powered by a Walter inverted six-cylinder engine rated at 134 kW (180 hp).

The prototype Z-42 first flew on December 28, 1978.

The Zlin Z 142 is a development of the Zlin Z 42 M platform, equipped with a Walter (now LOM) fuel-injected inverted 6 cylinder, supercharged air-cooled engine rated at 157 kW (210 hp), driving a constant speed propeller.

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.

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.

[edit] Operational history

The Z 42 variants are used for basic and intermediate VFR flight training, for basic aerobatics training, for night and instrument flight training, and for glider towing.

The aircraft were largely used in former COMECON countries for air club and basic air force training. It was also used by the air forces of Algeria, Mexico and Slovenia. According to the Tamil Eelam Airforce, it was used in bombing sorties on the Sri Lankan airforce bases in occupied Tamil Eelam and southern Sri Lanka.[1][http:www.theaustralian.news.com.au/story/0,20867,21672616-2703,00.html]

There have been wing difficulties resulting in restriction of permitted aerobatic flight time for original aircraft. The factory offers a retrofit package of replacement wings and an AMU-1 fatigue monitoring system, which extends overall airframe life to 5 500 hours, all of which may be aerobatic.

[edit] Aerobatics and maneuvers

The Zlin Z 142 was not designed as a fully-aerobatic plane, but it is equipped for inverted flying, and can be used for aerobatic instruction. The following figures are allowed:

Spins (normal and inverted)
Loops (except inverted)
Barrel rolls (except snap rolls)
Immelmanns
Wing-overs
Split-s slides and Tail-slides
Inverted flight

[edit] Specifications

This aircraft article has not been updated to WikiProject Aircraft's current standards. Please see the relevant category for more details.

Measurement	Z 42	Z 42 M & Z 42 MU	Z 142 & Z 142 C	Z 242 & Z 242 L
Minimum crew	One	One	One	One
Maximum seating	Two	Two	Two	Two
Length	7.33 m or 24' 1"	7.33 m or 24' 1"	7.33 m or 24' 1"	6.94 m or 22.77'
Wingspan	9.16 m or 30' 1"	9.16 m or 30' 1"	9.16 m or 30' 1"	9.34 m or 30.64'
Height	2.75 m or 9' 0"	2.75 m or 9' 0"	2.75 m or 9' 0"	2.95 m or 9.68'
Wing Area	?	?	?	13.86 m² or 149.13 sq.ft
Weight empty	?	?	730 kg or 1,609 lb	730 kg or 1,609 lb
Maximum take-off weight	?	?	1,090 kg or 2,403 lb (normal)	970 kg or 2,140 (acrobatic) 1,020 kg or 2,250 lb (utility) 1,090 kg or 2,400 lb (normal)
Never Exceed speed	?	?	?	319 km/h or 172 kt IAS
Operating speed limit	?	?	273 km/h or 147 kt IAS	250 km/h or 135 kt IAS
Cruise speed	?	?	190 km/h or 105 knots IAS without wheel spats at 75%	207 km/h or 112 kt IAS (75% MC) 176 km/h or 95 kt IAS (65% MC)
Stall speed (clean)	?	?	103 km/h or 55 kt IAS (acrobatic) 107 km/h or 58 kt IAS (utility) 110 km/h or 60 kt IAS (normal)	105 km/h or 57 kt IAS (acrobatic) 108 km/h or 58 kt IAS (utility) 111 km/h or 60 kt IAS (normal)
Full range	?	?	?	1,056 km or 570 nm (65% MC)
Service Ceiling	?	?	4700 m or 15420 ft	4500 m or 14764 ft
Rate of climb	?	?	?	5.5 m/s or 1080 ft/min (acrobatic) 4.25 m/s or 850 ft/min (normal)
Wing loading	?	?	?	70 kg/m² or 14.3 lb/sq.ft (acrobatic) 73.6 kg/m² or 15.1 lb/sq.ft (utility) 78.6 kg/m² or 16.1 lb/sq.ft (normal)
Power/mass	?	?	?	6.51 kg/kW or 10.7 lb/Hp (acrobatic) 6.85 kg/kW or 11.3 lb/Hp (utility) 7.32 kg/kW or 12.0 lb/Hp (normal)
Fuel capacity	?	?	2 x 60L main, 2 x 50 L aux	2 x 60 L or 2 x 16 USG (main) 2 x 55 L or 2 x 14.5 USG (aux)
Engine model	M137A	M137AZ	M337AK supercharged	AEIO-360-A1B6
Engine power	134 kW or 180 hp	134 kW or 180 hp	156 kW or 210 hp	150 kW or 200 hp
Propeller	?	?	Avia V-500A two bladed constant speed	MTV-9-B-C/C-188-18a (LBA) HC-C3YR-4BF/FC6890 (FAA)