McDonnell Douglas DC-9
| DC-9 | |
|---|---|
| |
| A Northwest Airlines DC-9-41, 2006 | |
| Role | Narrow-body jet airliner |
| Manufacturer | Douglas Aircraft Company McDonnell Douglas |
| First flight | February 25, 1965 |
| Introduction | December 8, 1965 with Delta Air Lines |
| Status | In limited service |
| Primary users | USA Jet Airlines Aeronaves TSM Northwest Airlines (historical) Delta Air Lines (historical) |
| Produced | 1965–1982 |
| Number built | 976 |
| Unit cost |
US$5.2M (-40, 1972)[1]
|
| Variants | McDonnell Douglas C-9 |
| Developed into | McDonnell Douglas MD-80 McDonnell Douglas MD-90 Boeing 717 |
The McDonnell Douglas DC-9 is a twin-engine, short-range jet airliner seating 110 passengers.
Specifications
| Variant | -15 (-21) | -32 | -41 | -51 |
|---|---|---|---|---|
| Cockpit crew[3]:66 | Two | |||
| 1-class seating:15–18 | 90Y@31-32" | 115Y@31-33" | 125@31-34" | 135@32-33" |
| Exit limit[3]:80 | 109 | 127 | 128 | 139 |
| Cargo:4 | 600 ft³ / 17.0m³ -15F: 2,762 ft³ / 78.2m³ |
895 ft³ / 25.3m³ -33F: 4,195 ft³ / 119.0m³ |
1,019 ft³ / 28.9m³ | 1,174 ft³ / 33.2m³ |
| Length:5–9 | 104 ft 4.8in / 31.82m | 119 ft 3.6in / 36.36m | 125 ft 7.2in / 38.28m | 133 ft 7in / 40.72m |
| Wingspan:10–14 | 89 ft 4.8in / 27.25m -21: 93 ft 3.6in / 28.44m |
93 ft 3.6in / 28.44m | 93 ft 4.2in / 28.45m | |
| Height:10–14 | 27 ft 7in / 8.4m | 27 ft 9in / 8.5m | 28 ft 5in / 8.7m | 28 ft 9in / 8.8m |
| Fuselage width:23 | 131.6in / 334.3 cm | |||
| Cabin width:24 | 122.4in / 311cm | |||
| Max. takeoff:4 | 90,700 lb / 41,141 kg -21: 98,000 lb / 45,359 kg |
108,000 lb / 48,988 kg | 114,000 lb / 51,710 kg | 121,000 lb / 54,885 kg |
| Max. Landing:4 | 81,700 lb (37,058 kg) -21: 95,300 lb (43,227 kg) |
99,000 lb (44,906 kg) | 102,000 lb (46,266 kg) | 110,000 lb (49,895 kg) |
| Empty:4 | 49,162 lb / 22,300 kg -15F: 53,200 lb / 24,131 kg -21: 52,644 lb / 23,879 kg |
56,855 lb / 25,789 kg -33F: 56,430 lb / 25,596 kg |
61,335 lb / 27,821 kg | 64,675 lb / 29,336 kg |
| Fuel:4 | 24,743 lb / 11,223 kg | 24,649 lb / 11,181 kg | ||
| Engine (2×)[3] | JT8D-1(A/B) -5 -7(B) -9(A) -11 -15 -17; -21: -9(A) -11 | -1(A/B) -5 -7(A/B) -9(A) -11 -15(A) -17(A) | -9(A) -11 -15(A) -17(A) | -15(A) -17(A) |
| Thrust (2×)[3] | -1(A/B) -7(A/B) : 14,000 lbf (62 kN), -5/-9(A): 12,250 lbf (54.5 kN), -11: 15,000 lbf (67 kN), -15(A): 15,500 lbf (69 kN), -17(A) : 16,000 lbf (71 kN) | |||
| Ceiling[3]:67 | 35,000 ft (11,000 m) | |||
| MMo[3] | Mach 0.84 (484 kn; 897 km/h) | |||
| Range:36–45 | 1,300 nmi (2,400 km) -21: 1,500 nmi (2,800 km) |
1,500 nmi (2,800 km) | 1,200 nmi (2,200 km) | 1,300 nmi (2,400 km) |
References
- ↑ "Airliner price index". Flight International. 10 August 1972. p. 183.
- ↑ "DC-9 airplane characteristics for airport planning" (PDF). Douglas aircraft company. June 1984.
- ↑ 3.0 3.1 3.2 3.3 3.4 3.5 "Type Certificate Data Sheet no. A6WE" (PDF). FAA. March 25, 2014. Archived from the original (PDF) on December 28, 2016. Retrieved January 12, 2019.
