WesWorld

Placeholder for information for civilian aircraft manufactured in Germany for home use and for export

Service History

The appearance in European skies of the Lockheed Orion high-speed airliner sparked the development of the Ju160, in order to provide Lufthansa with an aircraft to compete with the American machine. Junkers responded with a low-wing cantilever monoplane with a smooth metal skin. The design employed the Junkers double wing, but featured a swept leading edge and straight trailing edges. The prototype aircraft was flown on 11 April 1934, being shown to the representatives of the Air Ministry and the Luftwaffe, leading to the purchase of two aircraft for evaluation. The company owned demonstrator (D-UPAL) was used for several record-breaking flights and was leased for short periods to a number of foreign airlines for test purposes.

Forty-eight aircraft of this type were manufactured by the Junkers firm, the majority of which were acquired by Lufthansa for use on its domestic routes. With the introduction of more modern twin-engine aircraft Lufthansa’s Ju160s were relegated to night mail services or converted as aerial survey aircraft for operation by its subsidiary Hansa Luftbild GmbH.

Technical Description

Low wing cantilever monoplane with marked taper in chord and thickness. Wings attached by ball joints to centre section, which is built integral with the fuselage. Only two main spar girders. Corrugated metal covering. The entire trailing edge is hinged, the outer sections acting as ailerons and the inner sections as flaps.

Fuselage of oval cross section. Structure consists of four longitudinals and transverse frames. Smooth metal covering. Open sections of internal framework facilitate inspection.

Normal monoplane type tail unit. Metal structure. Corrugated covering for fin, rudder and elevators, smooth covering for tailplane. Horn balanced elevators. Rudder has inset hinges.
Retractable type undercarriage. Each wheel is carried in a sprung fork and each unit swings upwards into the underside of the wing.

One 660 hp Bayrische Motorenwerke 132E nine cylinder radial air-cooled engine on a detachable engine mounting. NACA cowling. Fuel tanks in wings outside centre section. Two bladed adjustable pitch metal airscrew.

Two pilots sit side by side within closed cabin, with wireless set. Behind is enclosed cabin for six passengers. One seat for two across front well faces aft, other seats arranged in pairs, facing forward. Door on port side aft. Access to pilots' compartment through cabin.

Span 14.25 metres, length 11.98 metres, height 4 metres, wing area 34 square metres. Empty weight 2,315 kg, weight loaded 3,542 kg.

Maximum speed at 1,000 metres 340 kph, cruising speed at 2,000 metres 318 kph. Climb to 1,000 metres 3.7 minutes, to 3,000 metres 15 minutes. Service ceiling 5,400 metres. Cruising range 1,200 kilometers at 2,000 metres.

Technical Description

Low wing cantilever monoplane. Wing in three sections, the centre section supporting the four engines, plus two outer sections. All metal structure built up of a main rectangular girder and two secondary spars, with former ribs supporting a series of lateral stringers to which the smooth metal skin is riveted in panels parallel to the stringers. Split flaps, divided into seven sections, extend between ailerons. Slotted ailerons have Flettner tabs.

Light metal monocoque fuselage built of a number of closely spaced frames with four main longerons and a number of stringers, the whole covered with a smooth metal skin.

Cantilever monoplane tail unit. All metal structure with fixed surfaces metal covered and movable surfaces fabric covered. Aerodynamically balanced elevator. Flettner trim tabs in elevator and rudder operated from cockpit through electrical relays.

Retractable undercarriage. Each unit consists of two oleo pneumatic shock absorber legs carrying between them a balloon tyre and a series of hinged struts that retract the wheels up into the inner engine nacelles. Hydraulic retraction and wheel brakes. Retractable tail wheel.

Four Junkers Motorenbau 208C twelve-cylinder diesel engines rated at 1,230 hp for takeoff and 1,150 hp at 4,000 metres. Three bladed VDM controllable pitch airscrews. Long chord NACA cowlings. Fuel tanks in wings for 4,000 litres. Oil tanks (total 164 litres) located in each engine nacelle.

Flight deck seats two pilots side by side with dual controls, and wireless operator on the starboard side behind the second pilot. Wireless apparatus located in the nose behind a bakelite fairing. Bulkhead door leads to a passageway on the right of which is located the stewards’ pantry. Further aft is the forward passenger compartment, seating twelve smoking passengers, the main passenger cabin, seating eighteen passengers, a lavatory and the main baggage compartment in the extreme aft of the fuselage. Controllable heat and ventilation. Windows push out for emergency exit.

Span 32.99 metres, length 23.85 metres, height 5.41 metres, wing area 120.30 square metres. Empty weight 9,516 kg, payload 4,400 kg, weight loaded 15,100 kg.

Maximum speed 450 km/hr, cruising speed 410 km/hr at 4,000 metres. Landing speed 104 km/hr. Initial climb rate 500 metres per minute, climb to 4,000 metres 13 minutes. Service ceiling 6,000 metres. Range with 4,400 kg payload and full fuel load 2,000 kilometers.

Technical Description

High wing cantilever monoplane. Centre portion of wing to points just outboard of outer engine nacelles of parallel chord, outer potions tapered. All metal structure with single tubular spar 1,450 mm in diameter extending through the hull. The spar is subdivided by bulkheads within the centre section to form fuel tanks. A passage inside the wing gives access to the engines in flight. Electric de-icing equipment fitted.

All metal two-step hull covered with corrosion resistant alloy sheet varying in thickness from 3mm to 5mm. The all metal wing tip stabilizing floats are split vertically, each half retracting outwardly flush with the underside of the wing. Electric retraction.

Cantilever monoplane type tail unit. High tapering single fin with tail unit mounted slightly above the top line of the hull. All metal structure.

Four Junkers Motorenbau 208F radial diesel engines rated at 1,620 hp at 5,000 metres. Fuel is carried in tubular wing spar.

Accommodation is on two decks – upper or control deck, lower or main deck – providing for a crew of eleven (including two stewards) and fifty-four passengers, each of whom is provided with both day and night accommodations. Aft of the control cabin on the main deck are the main cargo, mail and baggage holds with cargo-loading hatch. Additional cargo space is provided in the bow of the hull. Mail and cargo holds have a total capacity of approximately 6,000 kg. Passenger accommodations include a lounge seating up to twelve, galley and lavatories for men and women. Complete wireless, interphone and signal light systems. Soundproofing, controlled heating and ventilation.

Wing span 48 metres; length 32 metres, height 11.20 metres. Maximum width of hull 3 metres. Wing area 255 square metres.

Empty weight 30,650 kg; normal load 45,580 kg; maximum loaded weight 49,000 kg.

Maximum speed at seal level 330 kph; at 5,000 metres, 390 kph. Cruising speed at sea level 300 kph, at 5,000 metres 340 kph. Initial rate of climb 144 metres per minute; time to 6,000 metres 52 minutes. Maximum range 6,099 kilometers at 245 kph. Maximum endurance 28 hours.

Technical Description

Low wing cantilever monoplane. Centre-section integral with the fuselage. Tapering outer sections attached to centre section by ball and socket joints. Structure consists of two main and one auxiliary girders with smooth sheet covering reinforced internally by profile stiffeners. Along the whole of the trailing edge is the adjustable auxiliary which, with the main wing, forms the Junkers “Double Wing”. Outer sections of the latter act as ailerons. An anti-dive safety device is provided whereby the auxiliary wing is automatically adjusted by means of the total head pressure to a setting proportionate to the speed.

Fuselage is a metal structure of predominately oval cross section with circular forward taper from the pilot’s cabin and gradual wedge-shaped taper aft. Fuselage frame consists of four longerons of open section connected by oval frames and covered with a smooth outer skin attached by flush rivets.

Monoplane type tail unit with twin fins and rudders. Tail-plane is a double-wing of symmetrical section and both tail-plane proper and auxiliary trailing profile is adjustable from the pilot’s cockpit. Balanced elevator, which is also the trailing member of the double wing, has a trimming tab. Cantilever fin and rudder of double wing design at extremities of tail-plane. Rudders have controllable trimming tabs.

Retractable type undercarriage. Each unit consists of an oleo shock-absorber leg, the upper end of which is attached to the retracting mechanism with the lower end hinged to a triangular-shaped radius member which, with the hinged fairing on the wheel closes the aperture in the wing when the gear is retracted. Electrical retracting mechanism with emergency manual gear. Oil pressure wheel brakes. Fully swiveling tail wheel with centering device.

Two Brandenburgische Motorenwerke Fafnir 323A nine-cylinder radial air cooled radial engines each rated at 900 hp for takeoff and 1,000 hp at 3,500 metres. One fuel tank of 320 litres capacity in each wing root outside of the engine nacelle; auxiliary tank of 250 litres capacity located behind each engine. All tanks are equipped with quick emptying devices. Two oil tanks (each 50 litres) in leading edge of the wing outside engines. Three-bladed constant pitch airscrews.

Luggage compartment of 1.2 cubic metres capacity located in the nose. Pilot’s compartment immediately behind, with side-by-side seating in echelon. Entrance through cabin. Cabin has accommodation for ten passengers in adjustable seats, five on either side of a central gangway. Entrance aft on port side and behind entrance vestibule is a lavatory and the main baggage compartment (2.8 cubic metres capacity). Cabin walls are sound proofed and overhead strip lighting is provided. Controlled heating and ventilation.

Wing span 22.5 metres; length 17.5 metres; height 4.8 metres. Wing area 82 square metres.

Weight empty 5,070 kg; total disposable load 2,930 kg; weight loaded 8,000 kg.

Maximum speed at sea level 345 kph, at 3,000 metres 400 kph. Cruising speed at 3,500 metres 358 kph. Landing speed (fully loaded) 100 kph. Service ceiling 7,800 metres. Cruising range at 320 kph at 4,300 metres 1,500 kilometers.

Technical Description

High wing cantilever monoplane. Centre portion of wing to points just outboard of outer engine nacelles of parallel chord, outer potions tapered. Two spar, stressed skin light alloy construction. Slotted light alloy flaps. Mass balanced light alloy ailerons. Electric de-icing equipment fitted.

Fuselage of all metal semi-monocoque stressed skin structure.

Cantilever monoplane type tail unit. Single piece tailplane, two identical elevators, single fin and rudder, all of stressed skin light alloy construction.

Retractable tricycle type undercarriage. Pneumatic retraction. Electro-hydraulic oleo pneumatic shock absorbers.

Two BMW Flugmotorenbau 801MA fourteen-cylinder two-row radial air-cooled geared and supercharged engine in low-drag cowling with induced fan cooling, rated at 1,700 hp for takeoff. VDM three-bladed constant speed fully feathering airscrews. Fuel in four interconnected crash proof tanks, two in each wing. Inboard tanks 437 litres each, outboard tanks 518 litres each; total fuel capacity 1910 litres. Two oil tanks, one in each nacelle, 75 litres gallons each.

Accommodation for pilot, second pilot/navigator, wireless operator, steward and eighteen passengers. Pilots' compartment in the nose, with side-by-side seating with dual controls. Main cabin seats eighteen to twenty-two passengers depending upon configuration. Freight compartment in the rear of the aircraft can carry up to 500 kg of mail and freight. Pressurised cabin with soundproofing, controlled heating and ventilation.

Wing span 27 metres; length 21.8 metres, height 5.94 metres. Wing area 88 square metres.

Empty weight 8,100 kg; normal load 13,000 kg.

Maximum speed at 5,000 metres 470 kph. Cruising speed 440 kph. Maximum range 1,550 kilometers.

Technical Description

Low wing cantilever monoplane with constant taper from roots to tip. Incidence at root four degrees. Centre-section of three spar construction, spars passing through the fuselage to which they are permanently attached. Self-sealing fuel tanks built integrally with the structure. Outer wings have a single main spar. Structure of centre-section and outer wings completed by former ribs, spanwise stringers and a smooth metal skin. Slotted flaps from fuselage to ailerons. Flap doors on wing under surface are automatically retracted to permit smooth flow of air through slot when flaps are down. Both flaps and ailerons are single-spar metal structures. Controllable tabs in ailerons.

Fuselage is a semi-monocoque structure, consisting of aluminium-alloy ring and partition bulkheads, longitudinal stiffeners and circumferentials, the whole covered with smooth metal skin. Automatically-controlled supercharging and pressure regulating equipment provided, with a pressure differential of 1750 kg per square meter between outside atmospheric pressure and inside pressure.

Cantilever monoplane type tail unit. Fin and tailplane have two-spar frames covered with smooth metal sheet. Tailplane units have removable leading edges and detachable tips, and are interchangeable from right to left. Rudder, which is statically, aerodynamically and dynamically balanced by lead weights, has single-spar and metal covering. Elevators, with similar balances to rudder, have single spar frames, metal leading edges and metal covering.

Retractable tricycle-type undercarriage. Each unit of the main gear has twin wheels and single shock-strut. Steerable nose wheel has single wheel. Hydraulic retraction, the main wheels being raised forward into the inboard nacelles and the nose wheel backward into the fuselage. Manual emergency hear. Automatic devices provided to prevent retraction while any load remains on the undercarriage. Dual hydraulic brakes on each main wheel.

Four Brandenburgische Motorenbau 328 eighteen cylinder radial air-cooled engines rated at 2,100 hp for takeoff and 1,950 hp at 7,600 metres. Three bladed VDM controllable pitch airscrews. Long chord NACA cowlings. Fuel tanks in wings for 6,800 litres. Oil tanks (total 164 litres) located in each engine nacelle.

Accommodation for a crew of six, comprising pilot, second pilot, flight engineer and wireless operator, plus two stewards. Flight deck accommodates pilot and second pilot side-by-side with dual controls, and flight engineer and wireless operator behind. Compartment aft of the flight deck provides accommodation for the stewards, with lavatory and galley. Main compartment is equipped with fifty-eight seats, but this could be increased to seventy-two in high-density configuration; the main compartment is fitted with overhead racks for passenger luggage. Coat room, buffet and food storage spaces, plus additional lavatory, aft of the main compartment. All spaces are pressurised and sound-proofed. Heating and ventilating system, full wireless equipment and air navigation equipment including Lorenz blind approach receiver, etc.

Span 35.8 metres; Length 32.5 metres; Height 8.66 metres. Wing area 135.75 square metres. Maximum gross take off weight 40,550 kg.

Maximum cruising speed 534 kph at 7,600 metres. Normal cruising speed 445 kph. Range with payload of 8,800 kg – 5,500 kilometres.

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.

Technical Description

High wing cantilever monoplane. Centre-section and detachable outer sections. Metal structure consists of a box spar; elementary rib structure and metal skin plating complete the leading edge. The rear of the centre section and outer sections is fabric-covered over duralumin ribs cantilevered from the rear face of the spar. Vacuum operated split trailing edge flaps from hull to ailerons.

Two-step metal hull. Rectangular section tapering towards the rear of the hull. Six watertight bulkheads.

Cantilever monoplane type tail unit with twin fins and rudders. Tailplane and fins each have two spars and the entire unit, including the movable surfaces, is covered with a metal skin. Fins are fitted with fixed slots, the trailing edges of the slats being on the inside of the fins. Rudders have very narrow horn balances, used mostly for mass balancing, and trimming tabs.

Retractable undercarriage with main units located inside the wing pontoons and retractable tail unit with centering lock.

Two Brandenburgische Motorenbau 322 nine-cylinder radial air cooled engines each rated at 590 hp for takeoff and 500 hp at 1,500 metres. Steel tube mountings bolted to lower flanges of box spar and to upper edges of duralumin anchors built into the upper surfaces of wing spar at extremities. Fuel tanks integral in engine mountings. Total fuel capacity 880 litres. Oil tanks in engine mountings. Total oil capacity 56 litres.

In the nose is a mooring compartment with stowage for anchor and marine gear, vacuum storage tank, wireless unit and excess baggage. Pilot’s compartment seats two side-by-side with dual control and a wide aisle in between. Thereafter follows the cabin, to which access is gained through a hatch on the port side of the aircraft. Emergency batch on starboard side, opposite the main hatch. Up to six passengers may be accommodated in the main cabin, but equipment and furnishings vary according to the function of the aircraft.

Span 14.95 metres; Length 11.7 metres; Height 4.57 metres (on wheels). Wing area 34.8 metres. Empty weight 2,461 kg; disposable load 1,168 kg; Weight loaded 3,629 kg.

Maximum speed at 1,500 metres 350 kph; cruise speed at 1,500 metres 320 kph. Rate of climb at sea level 335 metres per minute. Service ceiling 6,400 metres. Maximum range 1,280 kilometres.

Technical Description

High-wing braced monoplane. Wings attached direct to built-in centre section in top of fuselage and braced to lower longerons by streamlined steel-tube Vee struts. Two-spar metal wing structure with fabric covering. Slotted ailerons on underhung hinges. Fixed slots in leading edge ahead of ailerons.

Fuselage is a rectangular welded steel-tube framework covered with fabric over metal fairing structure.

Cantilever monoplane-type tail unit. Welded steel tube structure covered with fabric.

Divided type undercarriage. Consists of two side Vees and two inclined half-axles hinged at their inner ends to a Vee cabane beneath the fuselage. Oleo shock absorber struts form front legs of side Vees. Castering tail wheel. Low pressure tyres.

One Hirth HM-504 four-cylinder air-cooled inverted inline engine rated at 105 hp for takeoff on a welded steel tube mounting. Fuel capacity 58 litres; oil capacity 4 litres.

Enclosed cabin seating two in tandem with dual controls. Entrance door on port side. Space for baggage behind rear seat.

Span 10.1 metres. Length 6.65 metres. Height 1.95 metres. Wing area 17 sq. metres. Empty weight 360 kg; weight loaded 580 kg.

Maximum speed 180 kph. Cruising speed 160 kph. Initial rate of climb 200 metres per minute. Service ceiling 4,000 metres. Range 500 kilometres.

Technical Description

Accommodation: Pilot and one passenger in individual seats in the front of the cockpit, two additional passengers on a single bench seat at the rear of the cockpit. Rear seat can be removed for carriage of cargo or other equipment.

Powerplant: Hirth HM506C 6-cylinder air-cooled inverted inline rated at 190 hp for take-off.

Dimensions: Length: 8.54 metres, wingspan 13.96 metres, height 2.72 metres; wing area 24.30 sq. metres.

Weights: Empty 968 kg; loaded 1,460 kg; Max take-off 1,560 kg.

Performance: Maximum speed 193 kph, cruise speed 175 kph, stall speed 52 kph; range 720 km; service ceiling 4,200 metres; climb to 1,000 metres 4.3 minutes.

Technical Description

Four Brandenburgische Motorenbau 328G eighteen cylinder radial air-cooled engines rated at 2,800 hp for takeoff and 2,500 hp at 7,600 metres

Accommodation for a crew of six, comprising pilot, second pilot, flight engineer and wireless operator, plus two stewards. Passenger accommodation for sixty-four to ninety-four passengers depending upon layout.

Span 38.3 metres; Length 34.2 metres; Height 8.95 metres. Maximum gross takeoff weight 51,900 kg.

Maximum cruising speed 530 kph at 7,600 metres. Range with maximum fuel 8,000 kilometres; range with maximum payload 5,500 kilometres.

Crew: One pilot
Capacity: Four passengers, or equivalent freight
Length: 9.6 metres
Wingspan: 12.0 metres
Height: 2.33 metres
Wing area: 22.61 sq. metres
Empty weight: 1,070 kg
Maximum take-off weight: 1,850 kg
Powerplant: One Walter Super-Castor seven-cylinder radial air cooled engine rated at 270 hp

Performance

Maximum speed: 230 kph
Cruise speed: 210 kph
Stall speed: 74 kph
Range: 1,150 km
Service ceiling: 3,290 metres
Rate of climb: 3.6 metres/second
Take off run: 155 metres
Landing run: 130 metres

The Bölkow Bo107 is a two-seat light sportplane of all-metal design, featuring a conventional cantilever wing with fixed undercarriage. It has been designed by Ludwig Bölkow, and production undertaken by Bölkow Entwicklungen GmbH of Stuttgart.

General characteristics

Crew: one pilot and one passenger
Length: 8.16 metres
Wingspan: 10.87 metres
Height: 2.06 metres
Wing area: 15.7 square metres
Empty weight: 475 kg
Gross weight: 625 kg
Powerplant: one Hirth HM 504 4 cylinder air cooled inverted inline engine rated at 105 hp

Performance

Maximum speed: 190 kph
Range: 670 km
Service ceiling: 5,550 metres

General Characteristics

Crew: one
Capacity: one passenger
Length: 6.25 metres
Wingspan: 8.92 metres
Height: 2.54 metres
Wing area: 13.70 sq. metres
Empty weight: 503 kg
Gross weight: 907 kg
Fuel capacity: 140 litres
Powerplant: one Hirth HM 506 six-cylinder air cooled inverted inline rated at 160 hp

Performance

Maximum speed: 227 kph
Cruise speed: 216 kph
Stall speed: 79 kph
Range: 805 kilometres with reserves
Endurance: 3:30 at 65% power with one hour reserve
Service ceiling: 5,000 metres
Rate of climb: 4.1 metres per second
Wing loading: 66 kg per square metre

General Characteristics

Crew: two
Length: 6.20 metres
Wingspan: 9.87 metres
Height: 2.18 metres
Wing area: 12.16 sq. metres
Powerplant: One Hirth HM504 four-cylinder inverted Vee air cooled inline engine rated at 105hp

Performance

Maximum speed: 175 kph
Never exceed speed: 250 kph

Technical Description

Crew: One pilot
Capacity: Nine passengers, or equivalent freight
Length: 10.50 metres
Wingspan: 15.60 metres
Height: 3.60 metres
Wing area: 32.40 sq. metres
Empty weight: 1,550 kg
Maximum take-off weight: 2,700 kg
Powerplant: Two Hirth HM-508E eight-cylinder inverted Vee inline engines each rated at 290 hp

Performance

Maximum speed: 260 kph
Cruise speed: 230 kph
Stall speed: 72 kph
Range: 1,100 km
Service ceiling: 5,500 metres
Rate of climb: 6.0 metres/second
Take off run: 160 metres
Landing run: 130 metres


The Dornier Do31 was designed to complement the single-engine Do27 utility transport, and offering excellent short take-off and landing performance. The aircraft is designed such that the passenger seats are easily removed for the carriage of cargo, and tie-downs are provided in the floor of the aircraft. If required, the port-side cargo door can be removed to permit the air dropping of personnel or supplies.

Project History

Derived from the piston-engine Junkers Ju252 commercial transport the first aircraft delivered to Lufthansa were in fact converted from the airline’s existing airframes under the designation Ju352A. Subsequently new-build aircraft were acquired and the type continues in low-rate production for domestic service and export.

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 Junkers Jumo 022 turbo-propeller engines each rated at 3,800 eshp. 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 fifty-six passengers in high density configuration, in fourteen rows, four abreast, with a centre aisle.

Span 32.05 metres, length 24.15 metres, height 8.66 metres; wing area 85.47 square metres. Weight empty 14,200 kg, gross weight 24,950 kg.

Maximum speed 580 kph at 3,500 metres, cruising speed 525 kph at 3,500 metres. Initial climb rate 1,000 metres per minute. Ceiling 8,800 metres. Range with maximum payload of 8,500 kg 1300 kilometres. Ferry range 2,200 kilometres

The He500 was designed by the Heinkel company as a fast, twin-engine executive transport. A prototype flew in August 1947 with the anticipation of production commencing some time in 1948.

General characteristics

Crew: Two
Capacity: Up to six passengers or equivalent freight
Length: 11.22 metres
Wingspan: 14.95 metres
Height: 4.42 metres
Wing area: 23.69 square metres
Aspect ratio: 9.45:1
Empty weight: 2,102 kilograms
Maximum take-off weight: 3,062 kilograms
Powerplant: Two Hirth HM-508E eight-cylinder inverted Vee inline engines each rated at 290 hp

Performance

Maximum speed: 346 kilometres per hour at sea level
Cruise speed: 326 kilometres per hour at 2,750 metres
Stall speed: 109 kilometres per hour
Range: 1,735 kilometres
Service ceiling: 5,900 metres
Rate of climb: 6.8 metres per second

The AGO Flugzeugwerke Oschersleben, the aircraft construction subsidiary of the Apparatebau GmbH Oschersleben, is the heir to the Gustav Otto Flugmaschinenwerke firm that had been founded in 1911. It has long functioned as a member of the Focke Wulf Fw340 production group. The firm has maintained a design office since 1935 under the leadership of engineer Paul Klages. The Ao225 design, in effect a modernised version of the Ao192 Kurier of 1936, is intended for the growing civil aviation market.

General characteristics

Capacity: four-seats, payload 255 kg
Length: 9.29 metres
Wingspan: 14.2 metres
Height: 3.4 metres
Wing area: 26.5 square metres
Empty weight: 1,895 kilograms
Gross weight: 2,470 kilograms
Powerplant: Two Argus As10C air-cooled inline engines, each rated at 240 horsepower

Performance

Maximum speed: 340 kph at 1,500 metres
Cruise speed: 300 kph at 1,000 metres
Range: 1,200 kilometres with maximum payload
Service ceiling: 6,200 metres
Wing loading: 93.2 kilograms/square metre
Take-off distance: 400 m to clear 20 metres