DC9 basic facts

DC9 BASIC FACTS.

Aircraft
Number of seats
Max takeoff weight
Max payload
Length
Wing span
Cruising speed
Range
Fuel consumption
Engine

DC9 41 / 21
105-122 / 75
51,7 / 44,5 tons
12,5 / 11,4 tons
38,3 / 31,9 meters
28,5 meters
815 kmph/505kt
2 600km
0.054 liters per seat per km.
PW JT8-11

The DC-9 is a short to medium range aircraft built by Mc Donnell Douglas Co., Long Beach, California. It is manufactured in several different models of which SAS uses the -21 and the -41. Those two models are equipped with two Pratt & Whitney JT8D-11 engines rated at 15.000 lb (6.800 kp) takeoff thrust.

The -21 model is chiefly intended for short routes and/or operation out of fields requiring optimum takeoff and landing performance. The aircraft seats up to 75 passengers and normally has a crew of two pilots and three cabin attendants. Maximum takeoff weight is 44.450 kg.

The -41 is a medium range aircraft featuring a stretched fuselage with increased capacity for passengers and freight. A total of 105 or 122 passengers can be carried and the crew normally consists of two pilots and four cabin attendants. Maximum takeoff weight is 51.700 kg.

Operational Limitations

Maximum pressure altitude enroute: 35.000 ft.

Minimum enroute temperature: -76 degrees C.

Maximum enroute temperature: Std + 35 degrees C.

Flight maneouvering load acceleration limits:
- clean configuration: +2.5 g to -1.0 g.
- flaps and/or slats extended: +2.0 g to 0 g.

Hard landing limits: More than +2.0 g or sink rate in excess of 10 ft/s (600 ft/min)
If any of these values is exceeded a hard landing inspection must be performed.

Takeoff and landing altitude limitations:
- Maximum altitude: 8.500 ft.
- Minimum altitude: -1.000 ft.

Takeoff and landing temperature limitations:
- Maximum temperature: +50 degrees C.
- Minimum temperature: -54 degrees C.

Aerobatics are prohibited with the exception of stalls during test and training flights with the minimum number of persons onboard necessary for handling and testing the aircraft.

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