McDonnell Douglas MD-90
The McDonnell Douglas MD-90 is a twin-engine, short- to medium-range, single-aisle commercial jet airliner. The MD-90 was developed from the MD-80 series. Differences from the MD-80 include more fuel-efficient International Aero Engines V2500 engines and a longer fuselage. The MD-90 has a seating capacity of up to 172 passengers and was introduced into service with Delta Air Lines in 1995.
|Japan Airlines MD-90-30 on final approach at Tokyo Haneda Airport|
|Role||Narrow-body jet airliner|
|National origin||United States|
Boeing Commercial Airplanes
|First flight||February 22, 1993|
|Introduction||1995 with Delta Air Lines|
|Primary users||Delta Air Lines|
Saudi Arabian Airlines (historical)
Japan Airlines (historical)
EVA Air (historical)
|Developed from||McDonnell Douglas MD-80|
|Variants||McDonnell Douglas MD-94X|
Design and developmentEdit
The Douglas Aircraft Company developed the DC-9 in the 1960s as a short-range companion to their larger DC-8. The DC-9 was an all-new design, using two rear fuselage-mounted turbofan engines, and a T-tail. The DC-9 has a narrow-body fuselage design with a 5-abreast seating with a capacity of 80 to 135 passengers depending on seating arrangement and aircraft version.
The second generation of the DC-9 was originally called the DC-9-80 series or the DC-9 Super 80, but it was later marketed as the MD-80 and entered service in 1980. McDonnell Douglas began studies into shorter derivatives of the MD-80 in 1983, these studies eventually becoming known as the MD-90. For several years, McDonnell Douglas proposed powering the MD-90 with two propfan engines, such as the General Electric GE36 and the Pratt & Whitney/Allison 578-DX. By mid-1989, it was clear that there was insufficient interest in propfan-powered aircraft, so the company reworked its proposals to feature the IAE V2500 turbofan instead. Within six weeks of eliminating the propfan option, the MD-90 secured a large launch order.
The MD-90 was firmly launched on November 14, 1989, when Delta Air Lines placed an order for 50 MD-90s, with options for a further 110 aircraft. The aircraft first flew on February 22, 1993 and the first MD-90 was delivered to Delta in February 1995. The MD-90 was produced adjacent to the Long Beach Airport in Long Beach, California, USA.
The MD-90 is a mid-size, medium-range airliner that was developed from the MD-80 series. It is a 5-foot-longer (1.5 m), updated version of the MD-88 with similar electronic flight instrument system (EFIS) and more powerful, quieter and fuel efficient IAE V2500 engines instead of the JT8D engines, which power the MD-80 series. This made the MD-90 the first derivative variant of the DC-9 to use a high-bypass turbofan engine. Due to the heavier engines, the pylons holding the engines featured flaps that deflect 30° downward to assist in pitching down for stall recovery. The system activates automatically when the control column is pushed fully forward.
Typical seating for the MD-90 ranges from 153 to 172 passengers, depending on the cabin configuration and interior layout. The MD-90 was produced in two versions: -30 and -30ER. The -30 has a range of 2,045 nmi (3,787 km). The -30ER has a higher gross weight and range up to 2,455 nmi (4,547 km) with an extra 565 US gal (2,140 L) auxiliary fuel tank. An even longer-range version, the -50, was offered but was never ordered.
The initial MD-90s feature an EFIS cockpit similar to the MD-88's cockpit. The 29 MD-90s delivered to Saudi Arabian Airlines feature a full glass cockpit with avionics and an overhead display panel similar to the MD-11's cockpit for easy transition for the airline's pilots of the MD-11, also operated by the airline.
No MD-90 orders were received after Boeing and McDonnell Douglas merged in 1997 due to internal competition with Boeing's 737. Delta Air Lines had initially placed a large order for the MD-90 to replace some aging Boeing 727s. After the Boeing-McDonnell Douglas merger, Delta canceled their remaining 19 MD-90 orders in favor of the Boeing 737-800. A total of 40 MD-90s (later 20) were to be assembled under contract in Shanghai, People's Republic of China under the Trunkliner program, but Boeing's decision to phase out the MD-90 resulted in only two built by Shanghai Aircraft.
MD-90 production at Long Beach, California ended in 2000 with the last airplane being delivered to Saudi Arabian Airlines, and MD-90T production at Shanghai ended in 2000. With 116 MD-90 aircraft produced, the MD-90 production run was the smallest among the DC-9 family. Two aircraft were also produced at Jiangwan Airfield in Shanghai, People's Republic of China.
Following the MD-90 in the DC-9 family was the MD-95, which was renamed the Boeing 717-200 after McDonnell Douglas (successor to Douglas Aircraft Company) merged with Boeing in 1997. The main competitors of the MD-90 included the Airbus A320 and the Boeing 737-800.
- A shorter variant with the same length as the MD-87, carrying from 114 passengers in a three-class layout to 139 passengers in a high-density configuration. It has a maximum takeoff weight of 69.49 short tons (63.04 t; 138,980 lb; 63,040 kg) and a range of 2,410 nmi (2,780 mi; 4,470 km) with fuel reserves. This variant was not built.
- Base variant with two V2525-D5 engines and an EFIS cockpit similar to that of the MD-88. This engine also has an option to add 3,000lbf for use in Hot & High conditions if needed by activating a switch in the flight deck.
- Increased Gross Weight version, one built.
- Extended Range (ER) version of MD-90-30, two built.
- MD-90-30T "Trunkliner"
- Variant of the MD-90-30 assembled by Shanghai Aviation Industrial Corporation in the People's Republic of China. Production was initially planned to be 40, later reduced to 20, with only two built in the end. To accommodate the heavy aircraft on unsuitable runways, a dual tandem landing gear with more tires to spread the weight of the aircraft was designed for the Trunkliner, but ultimately not used in the two aircraft produced. The Comac ARJ21 is built using tooling retained by the Chinese after the end of the Chinese MD-90-30 program.
- Enhanced Flight Deck version of MD-90 with the same cockpit as MD-95/B717 and MD-11, 28 built.
- A proposed 172 ft long (52.3 m) variant with a maximum capacity of up to 217 passengers, though the normal three-class layout would hold 170–180 passengers. The derivative would have a storage capacity of 1,610 cu ft (45.6 m3), a maximum takeoff weight of 81.74 short tons (74.15 t; 163,470 lb; 74,150 kg), and a height of 31 ft (9.4 m). This variant was never built.
- A proposed variant with increased MTOW, and up-rated IAE V2528-D5 engines with 28,000 lbf thrust (engines up-rated via software upgrades to FADEC).
As of July 2018, Delta Air Lines is the sole remaining operator with 53 in service. Since 2017, Delta has began phasing the MD-90 out its fleet, placing the aircraft's future in doubt. The airline reportedly plans to retire its MD-90s in 2020.
Accidents and incidentsEdit
- Notable accidents and incidents
- On August 24, 1999, a UNI Air MD-90 caught fire after a passenger's carry-on luggage containing gasoline was ignited by a motorcycle battery contained in another passenger's carry-on luggage. 28 people were injured with one fatality as a result of the cabin fire. The aircraft was damaged beyond economic repair.
|2 class seats||153-158 : 12J@36" + 141/146Y@31-33"|
|1 class seats||163-172Y@29-33"|
|Cargo||1,300 cu ft (36.8 m3)|
ER: 1,177 cu ft (33.3 m3)
|Length||152.6 ft (46.51 m)|
|Fuselage height||142 in (360.7 cm)|
|Fuselage width||131.6 in (334.3 cm)|
|Wing span||107.8 ft (32.86 m)|
|Height||30.6 ft (9.33 m)|
|MTOW||156,000 lb (70,760 kg)|
ER: 166,000 lb (75,296 kg)
|Empty weight||88,200 lb (40,007 kg)|
ER: 88,400 lb (40,098 kg)[a]
|Max payload||41,800 lb (18,960 kg)|
ER: 43,600 lb (19,777 kg)
|Fuel Capacity||39,128 lb (17,748 kg)[b]|
|Turbofans (2×)||25,000 lbf (111.21 kN) IAE V2525-D5[c]|
|VMO||Mach 0.84 (506 kn; 937 km/h) at 27,240 ft (8,303 m)|
|Cruise||Mach 0.76 (438 kn; 812 km/h) at 34,777 ft (10,600 m)|
|Ceiling||37,000 ft (11,278 m)|
|Range, 153 pax||2,045 nmi (3,787 km)|
ER: 2,237 nmi (4,143 km)[d]
|Takeoff||7,000 ft (2,134 m) at 156,000 lb, ISA, SL|
- with aux fuel tank: 89,188 lb (40,455 kg)
- with aux fuel tank: 42,913 lb (19,465 kg)
- Option: 28,000 lbf (124.55 kN) V2528-D5
- 2,455 nmi (4,547 km) with extra 565 US gal (2,140 L) auxiliary fuel tank
Aircraft of comparable role, configuration and era
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