Boeing 717
USA - 1999

The 100 seat Boeing 717-200 twinjet was designed specifically for short range, high frequency flights. Since entering service in September 1999, with launch customer AirTran Airways, over 100 aircraft have been delivered and are operating in Asia, Australia, Europe and North America with ten airlines and operators.

The aircraft was originally launched as the MD-95 in 1995 and was redesignated the Boeing 717 after the Boeing Company and McDonnell Douglas merged in 1997. The 717 has a distinctive appearance with low wing, rear mounted engines and a T-tail and is similar in size to its predecessor the DC-9-30. The wingspan is 28.4m and length is 37.98m. The maximum take-off weight is 49,895kg and the range is 2,648km.

In January 2005 it was reported that Boeing planned to shut down the production line of the 717, its smallest jetliner, after all orders are filled. The company closed the assembly line in spring 2006. Demand for the 717, which Boeing inherited when it purchased McDonnell Douglas, dwindled in 2004 with just eight new orders placed.


The 717-200 is a 106-seater airliner. Boeing considered some shorter and stretched derivatives: the 86-seat 717-100, the 75-seat 717-100X Lite and the 130-seat 717-300.

The two-crew flight deck is equipped with an electronic flight information system (EFIS), with six interchangeable 8in x 8in (203 x 203mm) liquid crystal displays showing flight, navigation and systems status. The 717 is fitted with the advanced air flight control system (AFCS) installed on the MD-11 aircraft. The controls are mounted on the glareshield. The windscreen is fitted with an electrical de-icing system.

The overhead instrument panel is the cockpit integrated flight crew warning and alerting panel (IFWAP), equipped with four liquid crystal displays. A Honeywell Versatile Integrated Avionics VIA 2000 computer controls the avionics suite, which includes a Honeywell flight management system (FMS), a digital air data computer, a digital flight guidance system, an inertial reference system and a windshear detection system.

The aircraft has CAT IIIa capability. A program is underway for the installation of an improved global positioning system and other instruments for CAT III b certification.



Boeing subcontracts the manufacture of aircraft components and subassemblies to aerospace contractors worldwide. The components are shipped to the Boeing production facilities at Long Beech, California for final assembly and testing. Subcontractors include: AIDC: empennage (tail unit); Andalucia Aerospacial: a range of subsystems; Aerospace Division of Korean Airlines: the nose section; Alenia: sections of the fuselage; Boeing Canada and Hyundai: wings; Auxiliary Power Corporation: auxiliary power unit; Fischer Advanced Composite Components: cabin interior furnishing; Honeywell: avionics, wheels and brakes; Goodrich: engine nacelles; Hamilton Sundstrand: electrical power generators; IAI SHL Servo Systems: landing gear; Labinal: electrical assemblies; Parker-Hannifin Corporation: hydraulics and control systems; Rolls Royce Deutschland: engines; and ShinMaywa Industries: engine pylons and sections of the tail.

The cabin interior is manufactured by the Austrian based company Fischer Advanced Composite Components. The cabin accommodates typically 106 seats in a two-class configuration with four-abreast first class and five-abreast standard class seating. The cabin is air conditioned with digital cabin air controllers and a Honeywell dual air cycle air conditioning using engine bleed air.

The underfloor baggage and cargo holds, capacity 26.5m, are equipped with a conveyor system and movable bulkheads.

The engine nacelles, manufactured by Goodrich, are mounted on the rear of the fuselage. The engine pylons manufactured by ShinMaywa Industries Inc are based on the design for the MD-80 aircraft but are thinner and are strengthened with an extra frame.

The engines are Rolls Royce Deutschland BR 715 A1-30 turbofan engines rated at 82.3 to 93.4kN. The high bypass ratio engines give very high fuel efficiency.

There are three fuel tanks of 13,904l capacity installed in the wing roots and in the centre section of the fuselage. Two auxiliary fuel tanks can be installed in the cargo holds in the underfloor section increasing the fuel capacity to 16,667l. A fuel recirculation system prevents ice formation and build up on the wing.

The landing gear is hydraulically operated retractable tricycle type with twin wheels on all three units. The landing gear, manufactured by Israeli Aircraft Industries SHL Servo Systems, is fitted with an anti-skid system and all steel brakes.


Length  37.80m 
Height  8.86m 
Wingspan  28.45m 
Tailplane span  11.18m 
Cabin width  3.12m 
Cabin height  2.03m 
Forward cargo and freight hold  18.3m 
Rear cargo and freight hold  8.2m 
Empty operating weight  30,447kg 
Range  2,648km 
Maximum speed  811 km/h 
Maximum altitude  11,278m 
Take-off field length  1,905m 
Landing field length  1,402m 
Maximum fuel  10,913kg 

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