The DC-9-40 is a narrow-body jet aircraft built by McDonnell Douglas in response to a Scandinavian Airlines System (SAS) requirement. The aircraft is powered by more powerful Pratt and Whitney engines and can accommodate up to 125 passengers in a single-class configuration.

McDonnell Douglas
United States
1965 to: 1982
US$5.2 million (1972)
2x JT8D-17
16,000 pound-force
Max Cruise Speed:
485 knots
898 Km/h
Approach Speed (Vref):
131 knots
Travel range:
1,200 Nautical Miles
2,222 Kilometers
Fuel Economy:
Service Ceiling:
35,000 feet
Rate of Climb:
3000 feet / minute
15.24metre / second
Take Off Distance:
2000 metre - 6,561.60 feet
Landing Distance:
1500 metre - 4,921.20 feet
Max Take Off Weight:
51,710 Kg
114,000 lbs
Max Landing Weight:
46,266 Kg
101,998 lbs
Max Payload:
14,363 Kg
31,665 lbs
Fuel Tank Capacity:
3,679 gallon
13,926 litre
Baggage Volume:
28.9 m3 / 1,021 ft3
Seats - Economy / General:
125 seats
Seats - Business Class:
Seats - First Class:
Cabin Height:
2.05 metre - 6.73 feet
Cabin Width:
3.12 metre - 10.24 feet
Cabin Length:
24.6 metre - 80.71 feet
Exterior Length:
38.28 metre - 125.59 feet
Tail height:
8.7 metre - 28.54 feet
Fuselage Diameter:
3.35 metre - 10.99 feet
Wing Span / Rotor Diameter:
28.44 metre - 93.31 feet
Wing Tips:
No Winglets

On November 28, 1967, the first flight of the McDonnell Douglas D-9-40 occurred. The DC-9-40 is a further lengthened version of the McDonnell Douglas DC-9 single-aisle airliner. In response to a request from the Scandinavian Airlines System (SAS) who needed a larger capacity development of the DC-9, McDonnell Douglas came up with the DC-9-40. In comparison with the previous series DC-9-30, the fuselage of the latter aircraft is 2-meter longer, increasing seating capacity in a single-class configuration up to 125 passengers. Other versions include the DC-9-10 and DC-9-20.

The Series 40 was powered by Pratt and Whitney JT8D engines. The JT8D is a low-bypass turbofan engine with a rated thrust range of 14,500 lbf to 16,000 lbf. It is an axial-flow front turbofan incorporating the dual-spool design. There are two coaxially-mounted independent rotating assemblies in the engine such as the first rotating assembly for the low-pressure compressor (LPC) which composed of the first six stages driven by the second downstream turbine, and the second rotating assembly which is in-charged for the high-pressure compressor (HPC) section that has seven stages and is driven by the first upstream single-stage turbine.

The DC-9-40 has an exterior length of 38.28 meters, an exterior height of 4.7 meters, a tail height of 8.7 meters, and a fuselage diameter of 3.35 meters. It has a wingspan of 28.44 meters, a wing area of 93 square meters, and a wheelbase of 17.1 meters. The cabin height is 2.05 meters, the cabin width is 3.12 meters, and the cabin length is 24.6 meters.

The aircraft has a maximum cruising speed of 485 knots and a long-range cruising speed of 443 knots. It can fly up to 35,000 feet, can climb at a rate of 3,000 feet per minute, and has a travel range of 1,200 nautical miles. It has a maximum takeoff distance of 2,000 meters and a maximum landing distance of 1,500 meters.

On March 12, 1968, the DC-9-40 first entered service with Scandinavian Airlines System. There were 71 DC-9-40s produced in total.

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