A Breguet designed four-engined STOL transport that would be suitable for civil or military use the Bre.941 relied upon the deflected-slipstream technique to generate additional lift. The four engines were mounted in nacelles at the wing leading edges so that slipstream from the propellers was distributed over the entire span of the wing.
Only 17% prop thrust is lost should one of the four 1250 shp Turbomeca Turmo IIID shaft turbines fail during takeoff since all props remain operative. Four 13 ft 8.5in diameter Ratier-Figeac hydraulically operated variable pitch fully reversible propellers provide airflow across the full 76 ft 1 in wing span. High-lift for slow speed is obtained by deflecting the slipstream with full span double-slotted flaps that work through 100 degrees, plus four hinged spoilers on each wing. Ailerons which extend across 42% of wing also droop for STOL operation.
Full-span double-slotted trailing edge flaps were provided, these also being within the slipstream when deployed to maximise their effect, and with no wing trailing edge available for ailerons to be installed for roll control, four hinged spoilers were provided on the upper surface of each wing.
Once power settings of the four engines are made by individual controls, uniform rpm is maintained by the co-pilot’s single long-arm throttle at the right of the console. In the pilot’s position duplicate master throttle is to the left of seat. Downward visibility windows are on each side of cockpit at end of instrument panel. Main landing gear which retracts into fairings on each side of fuselage is the Messier “Jockey” trailing arm design where two wheels of each unit are hydraulically interconnected. This provides wheel movement in both fore-and-aft and vertical directions for rough terrain operations.
The French air ministry ordered a prototype on 22 February 1960. It was of cantilever high-wing configuration, with an upswept rear fuselage to incorporate a rear loading ramp. Undercarriage was retractable tricycle landing gear that incorporated twin nosewheels, with tandem-wheel main units that retracted into fairings on each side of the fuselage. Powerplant was four 895kW Turbomeca Turmo HID turboprops, and the prototype was flown for the first time on 1 June 1961. Subsequent testing of the prototype resulted in Breguet receiving a contract from the French government for the supply of four production transports under the designation Breguet 941S.
Production aircraft were fitted with more powerful Turbomeca Turmo engines, a longer nose to permit the installation of a large radome, and modification of the rear cargo door to allow for the airdrop of heavy loads.
Operated by a crew of two, these aircraft could carry up to 57 civil passengers, or 40 fully-equipped troops, or 24 stretchers. The first of the production Br.941S aircraft made its initial flight on 19 April 1967, and testing proved that with an all-up weight of 22000kg, which was in excess of an assault mission take-off weight, the Br.941S could become airborne in only 185m.
All four of the production aircraft entered service with the Armee de I’Air, but no additional examples were built. There had been hopes that, with assistance from the McDonnell Aircraft Corporation, orders might be generated in the USA, but despite a demonstration tour in America, no production orders were received.
As there was a possibility the 941 may be made under licence in the US, during the 1969 demonstration tour it was designated McDonnell 188.
Engines: 4 x Turbomeca Turmo III D-3 turbo-prop, 1105kW
Wingspan: 23.4 m / 76 ft 9 in
Length: 23.8 m / 72 ft 11.5 in
Height: 9.4 m / 30 ft 7 in
Wing area: 83.4 sq.m / 897.71 sq ft
Take-off weight: 26500 kg / 58423 lb
Empty weight: 13120 kg / 28925 lb
Max payload: 15,000 lb
Max. speed: 520 km/h / 323 mph
Max speed at 10,000ft: 280 mph
Cruise speed: 480 km/h / 298 mph
Stall: 56 mph
Ceiling: 8500 m / 27900 ft
Range w/max.fuel: 3100 km / 1926 miles
Range w/max.payload: 800 km / 497 miles
Landing dist: 360 ft
Crew: 2
Passengers: 55-60
All Aero 