The CAP 10 was developed by CAARP and first flown in 1968.

The CAP 10 aerobatic trainer is a side-by-side monoplane, powered by a 190 hp injected Lycoming engine.

The construction is all wood with a cotton-covered rear-fuselage. (By law, all fabric must be replaced every 3 yrs in France). In 1967 they were priced at US$30,000 with no radio or gyros.

Production of the CAP.10B lightweight, fully aerobatic piston-engined primary trainer continued, and 88 have been delivered to military customers by 1987.

Total production exceeded 220 aircraft by 1997, and a glider-towing version, the CAP.10R, was available.

Gallery

CAP 10
Engine: Lycoming IO-360-B2F
Wing span: 26 ft 5 in / 8,06 m
Length: 23 ft 11 in / 7.30 m
Empty weight equipped: 1168 lb / 530 kg
MTOW aerobatic: 1666 lb / 756 kg
MTOW utility: 1829 lb / 830 kg
Max cruise 75%: 129 kt / 149 mph / 240 kph
ROC SL: 1180+ fpm / 360+ m/min
Service ceiling: 18,050+ ft / 5500+ m
Range: 647 nm / 745 mi / 1200 km
Seats: 2 side-by-side
Baggage: 44 lb / 20 kg
Cabin max width: 3 ft 5 in / 1.054 m

CAP 10B
Engine: Lycoming AEIO-360-B2F, 180 hp
TBO: 1400 hrs
Prop: Hoffmann 2-blade, 67-in
Seats: 2
Length: 23 ft
Height: 7.5 ft
Wingspan: 26.4 ft
Wing area: 117 sq.ft
Wing aspect ratio: 5.96
Maximum ramp weight: 1829 lb
Maximum takeoff weight: 1829 lbs
Standard empty weight: 1200 lbs
Maximum useful load: 629 lbs
Maximum landing weight: 1829 lb
Wing loading: 15.6 lbs/sq.ft
Power loading: 10.1 lbs/hp
Maximum usable fuel: 246 lbs
Best rate of climb: 1600 fpm
Service ceiling: 16,400 ft
Maximum speed: 146 kt
Normal cruise @ 65% pwr @ 8000 ft: 139 kt
Fuel flow @ normal cruise: 51 pph
Endurance at normal cruise: 4.6 hrs
Stalling speed clean: 50 kt
Stalling speed flaps down: 44 kt
Turbulent-air penetration speed: 126 kt
Fixed tail wheel under carriage

Produced by the former J,Meaz works (Chocen plant) the M-3 Bonzo was designed by J. Mraz.

The M-3 Bonzo is a four-seat produced in prototype form only. Of all-wood construction, it is powered by a 160 hp Walter Minor 6-III engine. A retractable nosewheel undercarriage is fitted.

Engine: 160 hp Walter Minor 6-III
Wingspan: 34 ft 9 in
Wing area: 148.5 sq.ft
Length: 25 ft 4 in
Height: 7 ft 4.5 in
Empty weight: 1278 lb
Loaded weight: 2424 lb
Max speed: 165 mph
Cruise: 150 mph
ROC: 708 fpm
Ceiling: 16,400 ft
Range: 620 mi

The Czechoslovak aircraft factory Mráz introduced several new sport aircraft after World War II. One of them was the M-2 Skaut, designed by Zdeněk Rublič. His aim was to design an easily flyable and reliable aircraft for basic club pilot training, with moderate operating costs and requiring little maintenance.

The Mráz M-2 Skaut was a wooden two-seat, single engine, low wing aircraft.

To simplify production, the wing and tail from his earlier, successful M-1C Sokol design was used. Like the Sokol, the Skaut was a wood framed, fabric covered aircraft. Their shared straight tapered wing had a swept leading edge but no sweep on the trailing edge They had marked dihedral beyond a very short centre section. The fin also had a swept leading edge and carried a rounded rudder. The tailplane was set well to the rear and near the top of the fuselage with a single piece elevator; the rudder moved above it. The Skaut had fixed tricycle landing gear.

The prototype, first flown in mid-1948, showed that the Skaut was a stable and safe aircraft, pleasantly controllable and with a good field of view. These characteristics together with a side-by-side cockpit and a tricycle landing gear made it a promising civil trainer aircraft. However, the new communist government nationalised the Mráz factory and directed it to produce military aircraft, so only the prototype Skaut was completed in the 20th century.

The only wooden prototype Skaut, OK-CEB Svazák, served at several flying clubs, mostly in Vrchlabí, and became very popular. There are rumours that it was flown solo by glider pilots without any previous experience of powered aircraft. In the early 1960s it was damaged during an emergency landing after an engine failure and was scrapped.

In 2005 the design was revisited, resulting in the metal framed, modernised Kubicek M-2 Scout which first flew in 2009 with plans for production and first deliveries in 2011.

Variation: Kubicek M-2 Scout

Powerplant: 1 × Praga D, 56 kW (75 hp)
Propeller: 2-bladed fixed pitch
Wingspan: 10 m (32 ft 10 in)
Wing area: 13.8 m2 (149 sq ft)
Length: 6.75 m (22 ft 2 in)
Height: 1.9 m (6 ft 3 in)
Empty weight: 370 kg (816 lb)
Gross weight: 660 kg (1,455 lb)
Fuel capacity: 70 L (18 US gal; 15 imp gal)
Maximum speed: 185 km/h (115 mph, 100 kn)
Cruise speed: 150 km/h (93 mph, 81 kn)
Range: 700 km (430 mi, 380 nmi)
Service ceiling: 4,200 m (13,800 ft)
Rate of climb: 2.7 m/s (530 ft/min)
Crew: 2

The Mráz M.1 Sokol (English: “Falcon”) was a light aircraft built in Czechoslovakia in the years following the end of the Second World War. Designed in secret by Zdeněk Rublič at the Beneš-Mráz factory during the German occupation.

The Sokol was a conventional, low-wing monoplane that took the pre-war Beneš-Mráz Bibi as its starting point. Two seats were provided side-by-side in an enclosed cabin, and the main units of the tailwheel undercarriage were retractable. Construction throughout was of wood.

The prototype, then designated the M.1/1 and registered as OK-ZHA, first flew on 9 March 1946, following test flights the prototype was designated the M.1A as the two-seat-version. A re-engined two-seater was built designated the M.1B with a ZLAS Toma 4 engine, it first flew on 19 May 1946 but only one was built. The design was then modified as the M.1C with a third-seat in the rear and first flying on 16 February 1947. The M.1C became the main production variant and 183 aircraft were built.

In 1948 the M.1C was further developed as the M.1D with an enlarged single-piece canopy and a revised rudder. The M.1D first flew on 4 October 1948 and 104 were built. One M.1D was fitted with locally produced floats and re-designated the M.1E, it first flew in September 1949. A minor variant was the Para-Sokol which was fitted with rearward sliding canopy to allow parachutists to leave the aircraft.

Some were operated by the Czechoslovakian National Security Guard and Egyptian Air Force.

Around 284 aircraft were built but the wooden-glued airframes were condemned in the early 1960s and withdrawn from use, under 20 were still in existence in the 2010s but only a few were flyable.

Some are on display at Museums in the Czech Republic, Hungary, Beijing, China, and Datangshan, China.

Gallery

M-1A
Original two-seat version
Engine: Walter Minor

M-1B
Similar to M-1A
Engine: ZLAS Toma
1 built

M-1C
Revised version, with longer fuselage and third seat, and swept leading edges on wing
183 built

M-1D
Similar to M-1C with new, single-piece canopy and larger rear windows
Engine: 1 × Walter Minor 4-III, 78 kW (105 hp)
Wingspan: 10.0 m (32 ft 10 in)
Length: 7.35 m (24 ft 1 in)
Wing area: 13.8 m2 (149 sq ft)
Height: 2.20 m (7 ft 3 in) (tail up)
Empty weight: 425 kg (937 lb)
Gross weight: 780 kg (1,720 lb)
Maximum speed: 240 km/h (150 mph, 130 kn)
Cruise speed: 212 km/h (132 mph, 114 kn)
Range: 1,000 km (620 mi, 540 nmi)
Service ceiling: 4,800 m (15,700 ft)
Rate of climb: 3.0 m/s (590 ft/min)
Crew: 1
Capacity: 2 passengers
104 built

M-1E
Similar to M-1D but equipped with pontoons
at least 1 built