Deta Air Dc-10-40F



Type: McDonnell Douglas DC-10-40F

History:Following an unsuccessful proposal for the US Air Force's CX-HLS (Heavy Logistics System) in 1965, Douglas Aircraft began design studies based on its CX-HLS design. In 1966, American Airlines offered a specification to manufacturers for a widebody aircraft smaller than the Boeing 747 but capable of flying similar long-range routes from airports with shorter runways. The DC-10 became McDonnell Douglas's first commercial airliner after the merger between McDonnell Aircraft Corporation and Douglas Aircraft Company in 1967.

The DC-10 first flew on 29 August 1970 and entered commercial service with launch customer American Airlines on 5 August 1971 on a round trip flight between Los Angeles and Chicago, nearly a year before the Lockheed L-1011 Tristar (which was built to a similar specification). The similarity to the L-1011 in terms of passenger capacity and launch in the same time frame resulted in a head to head sales competition which affected profitability of the aircraft. The launch customers for the DC-10 were American Airlines and United Airlines with orders for 25 and 60 respectively of the Series 10 model. Eventually, the DC-10 was able to distinguish itself from its competitors with a second engine supplier, which has the possible effect of controlling costs due to competition, as well as earlier introduction of longer range variants than the L-1011.

Northwest Airlines DC-10-30
The first DC-10 version was the "domestic" series 10 with a range of 3,800 miles (6,112 km). The series 20 (only ordered by Northwest Orient and Japan Airlines) had a typical load range of 5,750 mi (9,265 km) or a maximum payload range of 7,520 km. The series 30 had a typical load range of 6,220 mi (10,010 km) or a maximum payload range of 7,410 km.

The series 20 was powered by Pratt & Whitney JT9D engines, whereas the series 10 and 30 engines were General Electric CF6.
Before delivery of its aircraft, Northwest's president asked that the "series 20" aircraft be redesignated "series 40" because he argued that the aircraft was much improved over the original design. The FAA issued the Series 40 certificate on 27 October 1972.

One of the main visible differences between the models is that the series 10 has three sets of landing gear (one front and two main) while the series 30 and 40 have four gear (one front, three main). The center main 2-wheel landing gear (which extends from the center of the fuselage) was added to accommodate the extra weight by distributing the weight and providing additional braking.

The 446th and final DC-10 rolled off the production line in December 1988 and was delivered to Nigeria Airways in July 1989.[4] The DC-10 was assembled at McDonnell Douglas's Douglas Products Division in Long Beach, California.[1] Even as the final few DC-10 deliveries were occurring, McDonnell Douglas had already started production of the DC-10's successor, the MD-11. Although superficially similar, the MD-11 was longer, featured a two-crew flight deck, updated avionics, and other improvements. However, the MD-11 was not as successful as the DC-10, owing to airlines keeping their first generation widebodies in service longer, increased competition from Airbus and Boeing, and the MD-11's initial failure to meet promised performance specifications.

DC-10-10 DC-10-15 DC-10-30 DC-10-40
Cockpit crew
Three Three Three Three
Fuselage length
170 ft 6 in (51.97 m)
58 ft 1 in (17.7 m)
155 ft 4 in (47.34 m) 165 ft 4 in (50.4 m)
Fuselage width
19 ft 9 in (6.02 m)
Fuselage height
19 ft 9 in (6.02 m)
Max interior width
18 ft 2 in (5.54 m)
Operating empty weight
240,171 lb (108,940 kg) 266,191 lb (120,742 kg) 270,213 lb (122,567 kg)
Maximum take-off weight
430,000 lb
(195,045 kg)
455,000 lb
(206,385 kg)
572,000 lb
(259,459 kg)
555,000 lb
(251,701 kg)
Typical cruise speed
Mach 0.82 (564 mph, 908 km/h, 490 kt)
Max cruise speed
Mach 0.88 (610 mph, 982 km/h, 530 kt)
Max range, loaded
3,800 miles (6,114 km) 4,350 mi (7,000 km) 6,220 mi (10,010 km) 5,750 mi (9,252 km)
Maximum fuel capacity
21,700 US gal
(82,134 L)
26,647 US gal
(100,859 L)
36,650 US gal
(138,720 L)
36,650 US gal
(138,720 L)
Takeoff run on MTOW
8,612 ft (2,625 m) 7,257 ft (2,212 m) 9,341 ft (2,847 m) 9,242 ft (2,817 m)
Service ceiling
42,000 ft (12,802 m)
Engine model (x 3)
GE CF6-6D GE CF6-50C2F GE CF6-50C PW JT9D-59A
Engine thrust (x 3)
40,000 lbf (177.9 kN) 46,500 lbf (206.8 kN) 51,000 lbf (226.9 kN) 53,000 lbf (235.8 kN)