Author: Terry

Pottier, Jean

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Markets plans and some components to construct a wide range of light aircraft, including P.50 Bouvreuil single-seat monoplane (first flown 1979), P.60 Minacro single-seat aerobatic biplane, P.70S single-seat monoplane, P.80S single-seat monoplane, P.100TS two/three-seat monoplane (first flown 1980), P.110TS three-seat monoplane, P.170S tandem two-seat monoplane, P.180S side-by-side two-seat monoplane, P.190S Castor side-by-side two-seat monoplane as wooden version of metal P.180S, P.210S Coati single-seat monoplane, P.220S Koala side-by-side two-seat version of Coati, P.230S Panda three-seat monoplane, P.240S Saiga four-seat version of Panda, and P.300 Ara three-seat monoplane (kits anticipated).

1998:
4, rue de Poissy
F-78130 Les Mureaux
France

Potez-Heinkel CM 191 / C.M.192

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A new Heinkel company (mid of fifties) began by forming the Flugzeug Union-Süd Group, in collaboration with Messerchmitt AG., to produce 210 Fouga Magister for the new German air force. In cooperation with Potez, it developped from the Magister a new four seat executive, training and liaison aircraft known as the Potez-Heinkel CM-191. Heinkel was entirely responsible of the production.

The prototype of the four-seat Potez-Heinkel CM191 was flown for the first time at Toulouse on 19 March 1962. Jacques Grangette, Potez’s chief pilot was at the controls, with P.Caneill. The CM 191 first flight lasted forty minutes and a second flight of one hour and ten minutes duration was made on the same day.

Two prototypes were built. They were for many years as experimental aircraft to test various equipment or as liaison aircraft

Potez – Heinkel CM191 # 1 received a double registration from the beginning as D- 9504 and D- IHAM. It made its first flight in Toulouse March 19, 1962 and after 109 hr of manufacturer flight testing it was issued to the CEV Istres for testing .

It was subsequently delivered to Germany where it finished its career with 61 Erprobungsstelle Manching. This aircraft was registered in the United States, where it has changed ownership in 2008, to be based in Elk Grove, Illinois.

Potez – Heinkel CM191 # 2 received the registration D- 9532 and completed its career with 61 Erprobungsstelle Manching. This aircraft is now preserved and exhibited at the Am Technik Museum, Speyer, Germany.

Potez – Heinkel CM- 191 # 2 D- 9532

Variants:

CM.191 – 1956 4-seat corporate jet deriv. of CM.170, 2 x Marboré IV, 2 built
CM.191: aka Potez-Heinkel C.M.191, aka Heinkel P.191, first flown 1962

CM.192 – Messier project nos. 48046/48007 and 27457/48008
CM.192: Flight 1 June 1961 ident. Potez-Heinkel C.M.192 as per C.M.191

Gallery

Specifications:

Engines: 2 x Marboré IV
Span, without tip-tanks: 12,02 m (39 ft. 5 in)
Span, with tip-tanks: 12,70 m (41 ft. 8 in)
Length: 9,93 m (32 ft. 7 in.)
Height: 3,20 m (10 ft. 6 in.)
Weigth empty: 2 391 Kg (5,271 lb.)
Max Payload: 380 kg (838 lb.)
Max TO weight: 4 350 Kg (9,590 lb.)
Max 0 fuel weight: 3 005 Kg (6,625 lb.)
Max wing loading: 231 Kg/m² (47.3 lb/sq ft)
Max. Speed: 710 kmh (441 mph)
Max. Permissible speed: 740 kmh (460 mph)
Max. Crusing speed: 605 kmh (376 mph)
Stalling speed: 148 kmh (92 mph)
Max rate of climb: 906 m/mn (2970 ft/mn)
Service ceiling: 12 000 m (39,370 ft)
TO. Run: 900 m (3,250 ft)
TO. Run dist. to 15m: 1 180 m (3,870 ft)
Range with max fuel: 1860 km (1,150 miles)

Potez 4D

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The Potez 4D was a four-cylinder, inverted inline aircraft engine. It was first built shortly before World War II, but did not enter full production until 1949. The cylinders had a bore of 125 mm (4.9 in) and a stroke of 120 mm (4.7 in). Power for different models was in the 100 kW-190 kW (140 hp-260 hp) range.

Variants
4D-01
4D-31
164 kW (220 hp)
4D-33
119 kW (160 hp)
4D-34

Applications:
Morane-Saulnier MS.700 Petrel
S.N.C.A.C. NC-840 Chardonneret
Nord 3202
Nord 3400

Specifications:
Potez 4-D 01
Type: Four-cylinder air-cooled inverted inline engine
Bore: 125 mm (4.92 in)
Stroke: 120 mm (4.72 in)
Displacement: 5.85 L (352 cu.in)
Length: 1,207.5 mm (47.5 in)
Width: 510 mm (20.1 in)
Height: 668.5 mm (26.3 in)
Dry weight: 143 kg (314.6 lb)
Valvetrain: Two valves per cylinder with sodium cooled exhaust valves
Fuel system: One Zenith carburettor
Fuel type: 80 octane minimum
Oil system: Dry sump with one pressure and two scavenge pumps
Cooling system: air-cooled
Power output: 119 kW (160 hp) at 2,520 rpm (take-off), 97 kW (130 hp) at 2,360 rpm (Max cruise)
Compression ratio: 7:1
Specific fuel consumption: 245 gram/hp/hour (take-off)
Power-to-weight ratio: 0.83 kW/kg (0.51 hp/lb) (take-off)

Potez 840

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Prototype 2 F-WJSU

The first prototype of the Potez 840 executive transport made its initial flight on 29 April 1961. An all-metal low-wing cantilever monoplane, it was powered by four 328kW Turbomeca Astazou II turboprops, had fully retractable tricycle landing gear, and carried a crew of three with cabin accommodation for up to 18 passengers. A second prototype, F-WJSU, was flown in June 1962, had Astazou XII engines of 447kW each.

F-WJSU was ferried to the USA as N840HP for use by the Ameriican distributors Turbo-Flight. In 1964 N840HP returned to Frane and became F-BMCY.

After a sales tour in North America by the P-840.02, plans were made for a production batch of 25 Potez 840s, but in fact only two more prototypes were built, one of these being reserved for static testing. Two Potez 841 aircraft followed, powered by 417kW Pratt & Whitney Aircraft of Canada PT6A-6 turboprops. Finally, the modified Potez 842 appeared in 1965, a second aircraft, also powerd by Astazou XIIs following two years later.

These eight light transports were the last aircraft of the Potez marque to be built; one is now exhibited at the Musee de I’Air, Paris, and a second has been restored and is flown under the auspices of the French Association Aeromedicale.

Engines: 4 x Turbomeca Astazou turboprop
Max take-off weight: 7800 kg / 17196 lb
Wingspan: 19.33 m / 63 ft 5 in
Max. speed: 540 km/h / 336 mph
Pax cap: 16

Potez 670 / 671

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Designed to meet a requirement for a three-seat fighter with an endurance of three hours at 90% max speed, the Potez 670 was configurationally similar to the Potez 630 and 631. Flown for the first time on 30 March 1939, the Potez 670 had meanwhile been modified as a two-seat long-range escort fighter and bomber destroyer.

Potez 670

Initially powered by two 700hp Gnome- Rhone 14M radials, it was re-engined after initial flight trials with two 800hp Hispano-Suiza 14AB 12/13 radials, with which it resumed flight tests in July 1939 as the Potez 671.

Potez 671

Several production variants were proposed, but flight trials were incomplete at the time of the French collapse and the sole prototype was destroyed during the German onslaught. At the time, work had begun on an initial batch of 40 Potez 671 C2 fighters.

Potez 670
Engines: 2 x Gnome & Rhone 14M-3, 700 hp
Wingspan: 15.10 m
Wing area: 32.50 sq.m
Length: 10.80 m
Height: 3.27 m
Empty weight: 3120 kg
Maximum take-off weight: 4680 kg
Maximum speed: 460 km / h
Cruising speed: 412 km / h
Practical range: 1800 km
Service ceiling: 10,000 m
Crew: 2
Armament: 2 x 20-mm cannon Hispano-Suiza HS-404 front, 2 x 7.5-mm machine guns MAC 1934, 1 x 20-mm cannon Hispano-Suiza HS-404 rear-firing turret

Potez 671
Engines: 2 x Hispano-Suiza 14AC, 800 hp
Wingspan: 15.10 m / 50 ft 6 in
Wing area: 32.50 sq.m / 349.83 sq ft
Length: 10.80 m / 35 ft 5 in
Height: 3.27 m / 11 ft 9 in
Max take-off weight: 4726 kg / 10419 lb
Empty weight: 3186 kg / 7024 lb
Max. speed: 500 km/h / 311 mph
Cruising speed: 445 km / h
Maximum rate of climb: 876 m / min
Service ceiling: 10,500 m
Range: 2000 km / 1243 miles
Crew: 2
Armament: 2 x 20-mm cannon Hispano-Suiza HS-404 front, 2 x 7.5-mm machine guns MAC 1934, 1 x 20-mm cannon Hispano-Suiza HS-404 rear-firing turret

Potez 670 / 671