CN 235

The CN235 regional airline and military tactical transport was designed and developed under the Airtech banner as A 50. One prototype was built in both countries and these rolled out simultaneously on September 10 1983. The Spanish prototype flew first, on November 11 1983, with the Indonesian built aircraft following on December 30 that year.

Certification by both Spanish and Indonesian authorities and first deliveries (from the Indonesian line) occurred in December 1986. Entry into commercial service was in March 1988. Final assembly lines for the CN235 are in Spain and Indonesia, but all other construction is not duplicated. CASA is responsible for the centre and forward fuselage, wing centre section and inboard flaps, and engine nacelles. IPTN builds outer wings and flaps, ailerons, the rear fuselage and the tail unit. The initial production CN23510 was soon replaced by the CASA built CN235100 and IPTN's CN235110, incorporating CT79C engines in place of CT77As, and new composite engine nacelles. Further improvements led to the CASA CN235200 and similar IPTN CN235220 with increased operating weights, better field performance and greater range, with structural improvements and improved leading edge flaps and rudder. The CN235220 was certificated in March 1992. CASA and IPTN now develop their own CN235 variants independently. Other variants on the CN235 theme are the CN235 QC quick change capable of carrying passengers or freight or both; IPTN's CN235 MPA maritime patrol aircraft and CASA's CN235MP Persuader (which while primarily aimed at military customers, have customs and boarder patrol applications); and the widely ordered CN235 M multirole military freighter. IPTN is marketing military CN235s as the Phoenix. CASA has developed the stretched C-295, primarily for military use. The CN235 has succeeded in achieving only a small number of commercial orders, mostly from Indonesian and Spanish operators. In contrast the CN235's spacious interior and rear loading ramp has helped it win a significant number of military orders. Dimensions Overall Length : 70 ft 3 in (21.40 m) Wing Span : 84 ft 8 in (25.81 m) Height : 26 ft 10 in (8.18 m) Fuselage : 636.17 sq ft Nomenclature Operating Empty Weight : 21, 605 lbs (9800 kg) Max Take Off Weight : 33,290 lbs (9800 kg) Power plant : Two 1395kW (1870shp) General Electric CT79C turboprops.

DHC Twin Otter

The DHC-6 Twin Otter, manufactured by The de Havilland Aircraft of Canada, is an all metal, high-wing monoplane, powered by two Pratt and Whitney PT6A-27 engine driving Hartzell fully feathering, reversing, and constant speed propellers. The aircraft is designed for passengers and provided with a steerable nose wheel fixed tricycle landing gear, or can be fitted with floats or skis.

Dimensions Overall Length : 51 ft 6 in Wing Span : 65 ft 0 in Height : 19 ft 6 in

Design Criteria Max. Take-Off Weight : 12,500 lbs Max. Landing Weight : 12,300 lbs Max. Zero Fuel Weight : 7,000 lbs Cabin Data Front Baggage Comp. : 38 cu ft (300 lb) Rear Baggage Comp. : 88 cu ft (500 lb) Cabin Volume : 384 cu ft Number of Seat : 19 Powerplant : Pratt and Whitney PT6A-27

Cassa 212

The C-212, AVIOCAR, series airplanes are twin-turboprop STOL transport airplanes, cantilever high wing monoplane. Non-retractable tricycle type landing gear. All metal construction with wing and fixed surfaces of the two-spar type, and monocoque fuselage, powered by two Garrett AiResearch Ltd. TPE 331-10-501C engines driving Hartzell propeller.

Dimensions Overall Length : 15.20 m (49 ft 10 in) Wing Span : 19.00 m (62 ft 4 in) Height : 6.30 m (20 ft 8 in) Volume : 22.03 m (776.8 ft)

Design Criteria Max. Take-Off Weight : 7,450 kg Max. Landing Weight : 7,350 kg Max. Zero Fuel Weight : 7,050 kg Max. Taxi Weight : 7,500 kg Cabin Data Main Comp. Total Length : 6.49 m (21 ft 3 in) Cargo Comp. Length : 5.00 m (16 ft 5 in) Floor Area : 10.5 m (113 ft) Volume : 22.03 m (776.8 ft) Number of Seat : Y 22 Doors Passenger Door : 700 mm x 1,580 mm Crew Door : 578 mm x 1,100 mm Emergency Door (forward) : 578 mm x 1,100 mm Emergency Door (sft) : 508 mm x 914 mm Powerplant : Rolls Royce RB 183 MK 555-15P/12 Turbofan Engine

Boing 737-300

The 737-300 is the first of the three member second generation CFM56 powered 737 family, which also comprises the stretched 737-400 and shortened 737-500. The success of the second generation Boeing 737 family pushed sales of the mark to over 3000, a record for a commercial jetliner.

Boeing announced it was developing the 737-300 in March 1981. This new variant started off as a simple stretch over the 737-200 but Boeing decided to adopt the CFM International CFM56 high bypass turbofan (jointly developed by General Electric and SNECMA) to reduce fuel consumption and comply with the then proposed International Civil Aviation Organisation Stage 3 noise limits. Despite the all new engines and the 2.64m (104in) fuselage stretch, the 737-300 retains 80% airframe spares commonality and shares the same ground handling equipment with the 737-200. A number of aerodynamic improvements were incorporated to further improve efficiency including modified leading edge slats and a new dorsal fin extending from the tail. Another feature was the flattened, oval shaped engine nacelles, while the nosewheel leg was extended to increase ground clearance for the new engines. Other internal changes include materials and systems improvements first developed for the 757 and 767 programs, including an early generation EFIS flightdeck (with four colour CRT screens). The 737-300 flew for the first time on February 24 1984, while first deliveries were from November 1984. Since that time well over 1000 737-300s have been sold and it forms the backbone of many airlines' short haul fleets. The stretched 737-400 and shortened 737-500 are described separately. Powerplants Two 89.0kN (20,000lb) CFM International CFM563B1 turbofans, or optionally two 97.9kN (22,000lb) CFM563B2s. Performance Max cruising speed : 908km/h (491kt) Long range cruising speed : 794km/h (429kt) Range : 128 passengers Standard fuel : 3362km (1815nm), range with 128 pax and max fuel 4973km (2685nm) High gross weight version max range : 6300km (3400nm) with 140 passengers. Dimensions Overall Length : 109 ft 7 in (33.4 m) Wing Span : 94 ft 9 in (28.88 m) Height : 36 ft 6 in (11.13 m) Wing Aera : 1135sq ft (105.4 m2) Weight Operating empty : 32,881kg (72,490lb) Standard max takeoff : 56,740kg (124,500lb) High gross weight option : 62,823kg (138,500lb) Wing span : 28.88m (94ft 9in) Length : 33.40m (109ft 7in) height : 11.13m (36ft 6in) Wing area : 105.4m2 (1135sq ft) Capacity Flightcrew of two Typical two class seating : 128 (eight premium class four abreast and 120 economy class six abreast) Standard one class seating : 141 at six abreast and 81cm (31in) pitch Max seating : 149 at 76cm (30in) pitch Production Grand total 737 orders stand at over 4236, of which over 1104 are for the 300. Approximately 1070 737-300s were in service at late 1998.

Boing 737-200

Dimensions Overall Length : 36.35 m (119.3 ft) Wing Span : 28.45 m (93.3 ft) Height : 8.35 m Fuselage Length : 32.60 m (107.0 ft) Diameter : 3.35 m (11.0 ft)

Design Criteria Max. Ram Weight : 49,442 kg (108,999 lbs) Max. Take-Off Weight : 48,989 kg (108,000 lbs) Max. Landing Weight : 44.498 kg (98,000 lbs) Max. Zero Fuel Weight : 39,463 kg (87,000 lbs) Average Basic Weight : 28,000 kg (61,729 lbs) Max. Payload Weight : 10,000 kg (22.046 lbs) Number of Seat : C 20 - Y 76 Powerplant : Pratt and Whitney JT8D-15 Turbofan

Fokker F-27

Probably the closest to being the fabled DC-3 replacement, the Fokker F-27 Friendship, including the Fairchild built F-27 and FH-227, was built in greater numbers than any other western turboprop airliner.

The Fokker F-27 began life as a 1950 design study known as the P275, a 32 seater powered by two RollsRoyce Dart turboprops. With the aid of Dutch government funding the P275 evolved into the F-27, which first flew on November 24 1955. This original prototype was powered by Dart 507s and would have seated 28, by the time the second prototype had flown (in January 1957) the fuselage length grew to allow seating for 32.

Dimensions Overall Length : 82 ft 3 in (23.06 m) Wing Span : 95 ft 2 in (29.00 m) Height : 28 ft 7 in (8.71 m) Wing Area : 753.5 sq ft (70.0 m2) Nomenclature Operating Empty weight : 27,964 lbs (12,684 kg) Max take off weight : 44,996 lbs (20,410 kg) Power plant : Mk 200/500/600 - Two 1730kW (2320ehp) RollsRoyce Dart Mk 5367R turboprops driving four blade Dowty Rotol propellers. FH-227E - Two 1715kW (2300shp) Dart 5327Ls.

Foker F-28 MK4000

The aircraft shall be a twin rear-engine, all metal. low wing monoplane with cantilever swept wings and empennage, monocoque fuselage of cross section, and fully retractable tricycle landing gear.

The aircraft shall be equipped with a pressurized cabin and an auxilliary power unit shall be installed. The aircraft shall be a high performance short-to-medium haul commercial passenger and cargo transport which powered by two Rolls Royce RB 183 MK 555-15P/12 turbofan engine.

Dimensions Overall Length : 29.61 m (97 ft. 1.4 in) Wing Span : 25.07 m (82 ft 3.0 in) Height : 8.47 m (27 ft 9.5 in) Fuselage Length : 26.76 m (87 ft 9.5 in) Diameter : 3.30 m (10 ft 9.9 in) Design Criteria Cabin Length (ecxl. flight comp) : 15.31 m (50 ft 3.0 in) Max. Height : 2.02 m (6 ft 7.5 in) Max. Width : 3.10 m (10 ft 2.0 in) Floor Width : 2.88 m (9 ft 5.3 in) Max. Usable Floor Area : 44 m (474 ft) Height to Cabin Floor : 2.10 m (6 ft 10.6 in) Number of Seat : Y80 Max. Take-Off Weight : 32,207 kg (73,000 lbs) Max. Landing Weight : 29,848 kg (65,800 lbs) Max. Zero Fuel Weight : 26,083 kg (57,500 lbs) Cargo Capacity Forward Belly : 8.78 cu.m (308 cu ft) Rear Belly : 4.8 cu. m (171 cu. ft) Rear Cabin Luggage Compartment : 2.3 cu. m (80 cu. ft) Powerplant : Rolls Royce RB 183 MK 555-15P/12 Turbofan Engine

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