Technical Specifications
Crew
2/3
Passengers
80 / 90, max. 139
Propulsion
2 Turbofan Engines
Engine Model
Pratt & Whitney JT8D-9A, -15A, -17A
Engine Power (each)
71,2 kN
16000 lbf
Speed
898 km/h
485 kts
558 mph
Service Ceiling
10.668 m
35.000 ft
Range
2.632 km
1.421 NM
1.635 mi
Empty Weight
29.336 kg
64.675 lbs
max. Takeoff Weight
54.885 kg
121.000 lbs
max. Landing Weight
49.895 kg
110.000 lbs
Wing Span
28,45 m
93 ft 4 in
Wing Area
93,0 m²
1001 ft²
Length
40,72 m
133 ft 7 in
Height
8,53 m
27 ft 12 in
Production Status
out of production
Production Range
1965-1982
McDonnell
Douglas DC-9
HISTORY
The DC – 9 was designed specifically to operate from short runways and on short – to medium-range router so that the speed, comfort, and reliability of jet transportation could be extended to hundreds of communities previously served only by propeller-driven airliners.
Smaller than he Dc – 8, the trim DC – 9 has a distinctive high-level horizontal stabilizer atop the rudder, commonly called a “T” tail. Two engines mounted on the aft fuselage power the aircraft at cruising speeds exceeding 500 mph (800 km/h) and altitudes over 30,000 feet (9,144 m).
Design, development, and production of the DC – 9 was centered in Long Beach, Calif., at what is now the Long Beach Division of Boing Commercial Airplanes, where 976 of the twin jets were built during an 18 – year production run. The first flight was Feb 25, 1965; the final DC – 9 was delivered in October 1982.
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