Technical Description
All metal low wing monoplane. Wing in five sections, consisting of a centre section integral with the fuselage, two outer sections and two wing tips. Structure mainly of aluminium alloy, built up of two spars, ribs and stressed skin covering. Hydraulically operated Fowler type flaps. Flaps are all metal structures with dural skin.
Fuselage of semi monocoque structure of oval cross section. Structure consists of aluminium alloy ring and partition bulkheads, longitudinal stiffeners and circumferentials, the whole covered with smooth dural skin. Automatically controlled supercharging and pressure regulating equipment provided for operation at altitudes of 4,300 to 6,000 metres with a pressure differential of 0.172 bar between outside atmospheric pressure and inside pressure.
Cantilever monoplane type tail unit. Aluminium alloy framework with metal covering on fixed and movable surfaces. Trimming tabs in elevators and rudder.
Retractable tricycle type undercarriage. Electrically operated, with auxiliary manual control. Hydraulic brakes. Twin wheels fitted on all undercarriage units.
Two Brandenburgische Motorenbau 328A eighteen cylinder radial air-cooled engines rated at 2,200 hp for takeoff and 1,950 hp at 7,600 metres. Three bladed VDM controllable pitch airscrews. Fuel tanks located in wing centre section and outer sections.
Pressurised accommodation for a crew of five (pilot, second pilot, flight engineer and two cabin staff) and up to forty-four passengers in eleven rows, four abreast, with a centre aisle.
Span 28.42 metres, length 22.73 metres, height 8.66 metres; wing area 80.27 square metres. Weight empty 13,211 kg, gross weight 20,366 kg.
Maximum speed 500 kph at 6,000 metres, cruising speed 460 kph at 6,000 metres. Initial climb rate 385 metres per minute. Ceiling 8,800 metres. Range with maximum payload of 7,000 kg 770 kilometres. Ferry range 1,700 kilometres.