First flown in 1975 in the original Z 50 L version, the Zlin Z 50 is an all metal low wing monoplane with a mid fin tailplane braced by two struts that attach at the bottom of a tapering vertical fin. It has a fixed spring gear and a Lycoming AEIO-540 D1B5, putting out 260 hp to a three blade Hoffmann wood fiberglass propeller driven through a constant speed hub. The original prototype that appeared in the Zlin literature apparently had six short stacks that exited from the sides of the cowl, but the noise was unbelievable; they had to go to a pair of collectors that exit at the rear of the lower cowl lip. It has an empty weight of 1,254 pounds in aerobatic configuration and an aerobatic performing weight of 1,584 pounds. All up maximum gross weight is 1,760 pounds, and the Zlin is stressed to plus nine or minus six Gs. The wing is fabricated entirely with round head rivets apparently for strength. The Zlin 50 has a truly impressive roll rate, the product of very generous aileron area for its size and weight; its wing span in aerobatic trim is about 28 feet, and it is about 21 and a half feet long. The Z 50 has a symmetrical wing section without dihedral, a single seat cabin under a one piece plexiglas canopy and full inverted systems are standard. The wing area is 120 square feet; with a power loading of 5.5 pounds per horsepower and a maximum rate of climb of around 3,000 fpm, the airplane will possess the vertical capability the elder Zlin lacked. The structure is principally aluminum, with some fabric covered portions and a fiberglass cowling.
Moravan Aeroplanes built the Z-50 as a certified aircraft in the standard category in the Czech Republic.
Eighty-one were built in the various sub-types from 1976 until the ’90s.
The Zlin 50L has a 260 hp Lycoming modified by the Czechs to run all ways up and a three blade German composite propeller.
The Czech team flew five 50 Ls at the 1976 world contest in Russia, and despite the newness of the type, came second in the team prize and third in the men’s individual championships. The undercarriage is of titanium spring.

There appeared to be no ad¬verse aileron yaw, which was remark¬able in view of the almost full span control surfaces. They had an odd tab arrangement: the left aileron had a conventional geared tab; the right one worked through a cam, so that at small deflections it was an anti balance tab, but at larger ones it reverted to acting as a conventional geared tab. The symmetrical wing was thinner at the tip, giving it a washout effect both erect and inverted.
It is a single-seat, low-wing monoplane with an enclosed cockpit and fixed undercarriage. Built predominantly of anodised aluminium, with fabric covered tail and fibreglass engine cowls, the Z-50LS is powered by the 300-hp Lycoming AEIO-L1B5D, driving a three-blade composite Hoffmann propeller.

Later came the Z 50 LS aerobatic version.

Z-50LS
Engine: Lycoming AEIO-L1B5D, 300 hp

Zlin 50
Engine: Lycoming AIO-540, 260hp
Wing span: 27 ft 11 in
Length: 21 ft 2 in
Top speed: 180mph

After successful production of the Z-26 aircraft family, the Czechoslovak aircraft manufacturer Moravan, began design of a new series of training aircraft, known as the Z-40 family. Unlike the previous tandem-seat aircraft, the Z-40 family featured a side-by-side cockpit. It was available in two basic variants, a two-seat trainer, the Zlín Z-42, and a four-seat aircraft, the Zlin Z-43 capable of being used both as a trainer and a tourer.

The resulting design is a single-engined low-wing monoplane of all-metal construction and a fixed nosewheel undercarriage. The Z 43 shares 80% of its structure with the Z 42, but is fitted with a revised fuselage accommodating a four-seater cabin and a more powerful engine. The Z-43’s wings are of greater span and do not have the slight forward sweep of the Z- 42.

The Z-43 first flew on 10 December 1968, with production starting in 1972. It proved less popular than its two-seat contemporary, and production ended in 1977 after 80 aircraft were built.

The Z-143 is a version introduced in 1992, powered by a six-cylinder Lycoming O-540 engine, in parallel to the Z-42 being re-engined with a Lycoming to become the Z-242. The Z143 L four-seat lightplane with Textron Lycoming engine first flew in April 1992.

Pictures released by the Tamil Tigers in Sri Lanka indicate that they operated Czech-built Zlin Z-143 single-engine, four-seater light aircraft modified to carry four bombs mounted on the undercarriage. On 9 September 2008, the Sri Lanka Air Force reportedly brought down an Air Tigers Z-143 over Mullaittivu.

The Air Tigers carried out a Suicide air raid on Colombo on 20 February 2009 using two of these aircraft. Under heavy anti-aircraft fire one of these aircraft crashed into Sri Lanka Inland Revenue Department building in Colombo and the other craft was shot down near Sri Lanka Air Force Base at Katunayake.

Other operators include; Hungarian Police, Hungarian Air Force, Algerian Air Force – producing locally under Safir-43 name, Cuban Air Force, East German Air Force, and Macedonian Air Force.

Algeria’s Aeronautical Manufacturing Enterprise started manufacturing the Safir 43 in 1993, although they initiated the project in 1987. They are built under licence from the Czech Republic, but are manufactured completely in Algeria.

The aircraft were designed by the Zlin company and are marketed by the Aeronautical Manufacturing Enterprise throughout the whole of Africa.

The Safir is used in Algeria for training, recreational flying, coastal and pipeline surveillance and agriculture. Around 50 examples of the four seater had been built since it entered service in 1994.

AME is also building the two-seat Firnas 142 aerobatic trainer, based on the Zlin 143, complete with aerobatic modifications. The Firnas 142 is a two-seater and the Safir 43 a four-seater. AMC has built some 60 of the aircraft, 20 for use by the Algerian Air Force, government departments and parastatal corporations in a variety of roles.

These include basic training, aerobatic training, aerial surveying of powerlines and pipelines, as well as normal general aviation and utility duties, including banner and glider towing.

Both aircraft have fixed tricycle landing gear.

Variants:

Zlín Z 43
Base model
Engine: 1 × Avia M 337 A, 160 kW (210 hp)
Wingspan: 9.76 m (32 ft 0 in)
Wing area: 14.50 sq.m (156.1 sq ft)
Length: 7.75 m (25 ft 5 in)
Height: 2.91 m (9 ft 7 in)
Empty weight: 730 kg (1,609 lb)
Max takeoff weight normal: 1,350 kg (2,976 lb)
Max takeoff weight utility: 1,000 kg (2,204 lb)
Fuel capacity normal: 130 L (34 US gal; 29 imp gal)
Fuel capacity opt/ wingtips: 110 L (29 US gal; 24 imp gal)
Maximum speed: 146 km/h (91 mph, 79 kn) at sea level
Cruise speed: 210 km/h (130 mph, 113 kn)
Stall speed: 103 km/h (64 mph, 56 kn) (flaps down)
Never exceed speed: 273 km/h (170 mph, 147 kn)
Range standard: 610 km (380 mi, 330 nmi)
Range opt/fuel: 1,150 km (710 mi; 620 nmi)
Service ceiling: 3,800 m (12,465 ft)
Rate of climb: 3.5 m/s / 210 m/min (690 ft/min)
Takeoff distance to 15 m (50 ft): 700 m (2,300 ft)
Landing distance to 15 m (50 ft): 590 m (1,940 ft)
Cabin length: 8 ft 2.5 in / 2.50 m
Cabin width: 3 ft 8 in / 1.12 m
Cabin height: 3 ft 11.25 in / 1.20 m
Cabin baggage: 7.1 cu.ft / 0.2 cu.m
Rear baggage: 8,8 cu.ft / 0.25 cu.m
Crew: 1
Capacity: 3 passengers

Zlín Z 43M
Experimental model.
Only one was built

Zlín Z 143
Improved model

Aeronautical Manufacturing Enterprise Safir 43
Engine: LOM M337AK, 157kW (210hp)
Empty weight: 761kg / 1,676lb
Take-off weight: 1,350kg
Maximum speed: 166kt / 307km/h
Cruising speed: 212 km/h
Range: 1,060km / 570nm
Endurance: 6h
Seats: 4

Aeronautical Manufacturing Enterprise Firnas 142
Engine: LOM M337AK, 154 kW / 210 hp max, 103 kW cruise
Propeller: two-blade
Length: 7.33 m
Wingspan: 9.16 m
Height: 2.75 m
Empty weight: 745 kg
MTOW: 1090 kg
Top speed: 333 km/h
Cruising speed: 215 km/h
Endurance: 5+ hr
Maximum range: 1050 km
Maximum ceiling: 5000 m

A two-seat trainer and touring aerobatic aircraft, the Zlin 42 (first flown in 1967) was developed in the late sixties and followed by the Z-142 with a slightly modified cockpit canopy and a more powerful engine. The Z 142 two-seat basic and advanced civil/military trainer was first flown in December 1978.

The Z 242 is a variant of the Z142 with a U.S. Textron Lycoming engine in place of the L0M Prague type.

Gallery

Z-42
Engine: Avia M 137 A, 180 hp
Wing span: 30 ft (9.1m)
Seats: 2

Z-42 M
Seats: 2

Z-142

Z-242L
Engine: Lycoming
Seats: 2

Designed and built in 1947, the Zlin 26 all-wood two-seat tandem trainer was superseded by the metal Zlin 126 Trener, which went into production in 1953.

The basic design was developed subsequently through Z 226, Z 326 Trener Master in 1957.

The Zlin 26 all-wood two-seat tandem trainer was superseded by the metal Zlin 126 Trener, which went into production in 1953.

Zlin built 433 Z-326s.

Zlin developed the Z 526 in 1965, and Z 726 models in both Trener (two-seat) and Akrobat (single-seat competition aircraft) variants with retractable landing gear and a variety of engines. 330 Z-526s were built.

Production included the Z 726 trainer development of the Z-526.

As one of the world’s foremost aerobatic aircraft, the Zlin was also widely exported outside the Eastern bloc.

Gallery

Variants:

Z-26
Initial wood version

Z-126 Trener
Metal version of Z-26

Z-226A Akrobat
Fully Aerobatic version of Z-22T
Seats: 1

Z-226AS Akrobat Special
Fully Aerobatic version of Z-22T
Seats: 1

Z-226B Bohatyr
Glider towing version of Z-226T

Z-226T Trener-6
Development of Z-126

Z-326
Engine: Walter Minor 6-III, 116 hp
Wingspan: 34.777 ft / 10.6 m
Wing area: 166.304 sq.ft / 15.450 sq.m
Length: 25.656 ft / 7.82 m
Height: 6.759 ft / 2.06 m
Max take off weight: 1984.5 lb / 900.0 kg
Weight empty: 1404.6 lb / 637.0 kg
Max speed: 132 kt / 245 km/h
Cruising speed: 116 kt / 215 km/h
Initial climb rate: 866.14 ft/min / 4.4 m/s
Service ceiling: 15748 ft / 4800 m
Wing load: 11.89 lb/sq.ft / 58.0 kg/sq.m
Range: 313 nm / 580 km
Normal crew: 2
Aerobatic crew: 1

Z-326A Akrobat
Fully aerobatic version of Z-326

Z-526 Trener-Master
Development of Z-326
Pilot at rear
Prop: constant speed

Z-526A Akrobat
Fully aerobatic version of Z-526
Engine: Walter Minor 6-III K, 158 hp

Z-526AS Akrobat Special
Fully aerobatic version of Z-526

Z-526L
Engine: 1 x Lycoming AIO-360-B1B, 200 hp
Gross wt: 2175 lb
Empty wt: 1489 lb
Fuel cap: 151/262 lb
Equipped useful load: 585 lb
Payload max fuel: 323 lb
Wing loading: 12.5 lb/sq.ft
Pwr loading: 10.9 lb/hp
Range max fuel/75% pwr: 556nm/3.3hr
Service ceiling: 18,000 ft
75% cruise: 139 kt
Stall: 46-53 kt
1.3 Vso: 60 kt
ROC: 1380 fpm
Min field length: 1050 ft
Seats: 2

Z-526 AFS Akrobat
Single seat version of Z-526F
Engine: Walter Minor 6-III M-137, 130 hp
Wingspan: 29.003 ft / 8.84 m
Wing area: 148.651 sq.ft / 13.81 sq.m
Length: 25.361 ft / 7.73 m
Max take off weight: 1631.7 lb / 740.0 kg
Weight empty: 1334.0 lb / 605.0 kg
Max. speed: 132 kt / 245 km/h
Cruising speed: 116 kt / 215 km/h
Initial climb rate: 1574.8 ft/min / 8.0 m/s
Service ceiling: 16732 ft / 5100 m
Wing load: 11.07 lb/sq.ft / 54.0 kg/sq.m
Range: 421 nm / 780 km
Crew: 1

Z-526 F Trener
Engine: Avia M 137 A, 180 hp
Wingspan: 34 ft 9 in / 10.60 m
Wingspan over tip tanks: 35 ft 11.5 in / 10.96 m
Length: 26 ft 3 in / 8.00 m
Empty weight: 1465 lb / 665 kg
MTOW Aerobatic: 2072 lb / 940 kg
MTOW normal: 2150 lb / 975 kg
Max cruise max norm TOW: 113 kt / 130 mph / 210 kph
ROC SL max norm TOW: 1181 fpm / 360 m/min
Service ceiling max norm TOW: 17,060 ft / 5200 m
Max range std fuel max norm TOW: 255 nm / 295 mi / 480 km
Max range w/tiptanks max norm TOW: 450 nm / 520 mi / 840 km
Seats: 2 tandem
Glider tow option

Z-726 Universal
Similar to Z-526F, shorter wing span
Engine: M 137 AZ, 180 hp

The Zlin 22 appeared in 1947 as a two-seat trainer, powered by a Zlin Persy III engine of 57 hp.

When production of the Persy engine was discontinued, the Zlin 22 was re-engined with a 75 hp Praga D as the Zlin 22D, and a 105 hp Walter Minor 4-III as the three seat Zlin 22M.

Two prototypes of the Zlin 122 version were produced. Three/four seat, they were powered by a 105 hp Zlin Toma 4 engine.

Zlin 22
Engine: Zlin Persy III, 57 hp
Wingspan: 34 ft 9 in
Length: 23 ft 9 in
Height: 6 ft 5 in
Wing area: 157.7 sq,ft
Seats: 2

Zlin 22D
Engine: Praga D, 75 hp
Wingspan: 34 ft 9 in / 10.6 m
Length: 23 ft 9 in / 7.25 m
Height: 6 ft 5 in
Wing area: 157.7 sq,ft / 14.6 sq.m
Empty weight: 804 lb / 365.0 kg
Loaded weight: 1399 lb
Wing load: 8.2 lb/sq.ft / 40.0 kg/sq.m
Max speed: 112 mph / 95 kts / 176 km/h
Cruise: 100 mph / 84 kts / 155 km/h
Service ceiling: 13,780 ft / 4200 m
Range: 435 mi / 270 nm / 500 km
Seats: 2

Zlin 22M
Engine: Walter Minor 4-III, 105 hp
Wingspan: 34 ft 9 in
Length: 23 ft 9 in
Height: 6 ft 5 in
Wing area: 157.7 sq,ft
Empty weight: 926 lb
Loaded weight: 1588 lb
Max speed: 133.5 mph
Cruise: 121 mph
Ceiling: 18,040 ft
Range: 620 mi
Seats: 3

Zlin 122
Engine: Zlin Toma 4, 105 hp
Seats: 3-4