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Aviation History
1997
1997 - 2154.PDF
COMMERCIAL AIRCRAFT Mountain Air/Lone Star has also ordered the type. The aircraft is expected to have a top cruise speed of 375kt at 22,000ft, compared with the standard 328-110 turboprop's 335kt, and it should have a range of 1,650km. Configurations for a stretched, 50-seat, swept-wing 528JET, are also being considered. Production Final assembly will be in Oberpfaffenhofen, Germany. Ordered 10 METRO/EXPEDITER Developed originally by Swearingen from the Merlin business twin-turboprop, the 19-seat Metro was first flown in August 1969. The ini tial production version, powered by the AlliedSignal TPE331, was superseded by the Metro II in 1975, and the III in 1981. An increased MTOW variant, die Metro 23, was introduced in 1994. The Metro III is the basis for the USAF C-26 transport. Fairchild has also developed an all-cargo ver sion, the Expediter, which has a reinforced cabin floor and a reduced empty weight, per mitting a maximum cargo payload of more than 2,170kg. It developed a Metro 2 3 equipped with an EFIS for the USAF, dubbed the 23E, which is now being delivered to civil customers. Production Final assembly is undertaken at Fairchild's San Antonio plant in Texas. Seven aircraft were delivered in 1996. Delivered 600+ Model Engines Dimensions Span(m) Length (ml Height (m) wing area Infl 228-212 Landing Accomodation Max Fuel gear weights (kg) litres) Track (m) Seats Take-off Standard Wheelbase(m) Pitch Landing Optional Turn Zero radius (m) Abreast fuel Cabin Operating width empty 2 x 580kW AlliedSignal TPE331-5A 252D tuiboprop 16.97 16.56 4.86 32 328-110 3.3 19 6,400 2.386 6.3 75 6.100 14.8 2 5.940 1.34 3.740 2 x 1.625kW Pratt & Whitney Canada PW119B turboprop 20.98 21.28 7.2 40 328JET 3.22 34 13.990 4.268 7.42 79 13.230 8.57 3 12.610 2.18 8,810 2 x 26.9kN Pratt & Whitney Canada PW 306B turbofan 20.98 21.28 7.2 34 14,990 79 2.18 9,200 Metro 23-12 2 x 745kW AlliedSignal TPE33112UAR turboprop 17.7 18.1 5.1 28.7 4.57 19 7,490 2,455 5.8 75 7,115 11.7 2 6.680 1.58 4.255 FAR new lengths takeoff landing ISA ISA sea-level sea-level ISA+20'c BA+20'c sea-level sea-level ISA ISA 5,000ft 5,000ft ISA+20 c ISA+20 c 5,000ft 5,000ft 795 450 1,035 480 1.100 520 1.645 550 1.065 1,010 1.615 850 1.675 865 2,045 1,005 2,225 1.070 Speeds Ikt) (mach) Vno Mno Vmo Mmo Vne Mne - Cruise performance Max cruise speed Ikt) Max alt m Max cruise fuel cons (kg/hi 235 10.000 320 335 25.000 375 295 12,000 395 Long range speed Ikt) At alt (111 Long range fuel cons (kg/hi 210 10,000 260 250 25,000 225 Payload details Max (kg) Range with max p/1 (km) Payload with max fuel (kg) range with max fuel 2,200 635 776 2.582 3,690 3.410 . 2.325 1.610 1.265 3,713 Fokker Aircraft, P0 Box 7600,1117ZJ Schiphol Cost, Netherlands; tet+31120) 605 2730; fax:+31 (20) 605 2929. Fokker declared bankruptcy on 15 March 1996. Despite talks on reviving or selling the company over the past 12 months, no backer was secured, and production of Fokker aircraft finally ceased during 1997. Spares and support services have transferred to Fokker Aviation, a new company owned by Stork of the Netherlands, which will continue to support the existing Fokker fleet. FOKKER/FAIRCHILD F27/F-27/FH-227 The R-R Dart-powered F27 twin turboprop had its first flight in November 1955, and pro duction of the civil versions continued until 1985. Several versions of the 40- to 50-seater were developed, including mixed passenger/ cargo and freighter variants, and a stretched version (the Mk500), all powered by two Darts. A Fairchild-built version, produced under licence in the USA, was dubbed the F-2 7. A US- developed stretched derivative, the 48- to 52- seat FH-227, was also produced. TAT's division, LAB, offers a cargo-door retrofit programme for the F2 7, which requires eight to ten weeks' downtime and costs about $600,000. Delivered 787 (580 F27s, 29 F-27s and 78 FH-227s) Model Dimensions Span (m) Length (m) Height (m) wing area (m1! notes Fokker 50 Engines Landing Accomodation Max Fuel Sear weights (kg) (litres) Track |m) Seats Take-off Standard Wheelbase(m) Pitch Landing Optional Turn Zero radius (m) Abreast fuel Cabin Operating width empty 2 x 1.865kW Pratt & Whitney Canada PW125B turboprop 29 25.25 8.32 70 7.2 58 19.950 5,136 9.7 76 19.500 18.07 4 18,600 2.5 12,520 No longer in production Fokker 50 High Performance 2 x 2,050kW Pratt & Whitney Canada PW127 turboprop 29 25.25 8.32 70 7.2 58 19.950 5.136 9.7 76 19.500 18.07 4 18.600 1.96 12.520 No longer in production Fokker 60 (Utility) 2 x 2.050kW Pratt & Whitney Canada PW127 turboprop 29 26.87 8.34 70 7.2 68 21,950 5.136 10.72 76 21,750 4 20,700 2.5 No longer in production FAR field lengths takeoff ISA sea-level ISA+20c sea-level ISA 5,000ft ISA+20 c 5,000ft 1.126 1.364 1.454 2.174 1,050 1,194 1,315 1.840 1,347 1,559 1,806 2,251 landing ISA sea-level BA+20/c sea-level ISA 5,000ft ISA+20 c 5,000ft 1.116 1,116 1,243 1.317 1.116 1.116 1.243 1.243 1.175 1.175 1.310 1.305 Speeds (kt) Vno Vmo Vne 227 227 -- 250 (mach) Mno Mmo Mne 0.507 0.507 0.507 Cruise performance Max cruise speed |kt) Max alt (ft) Max cruise fuel cons lkg/h) 282 16,000 679 284 18.000 695 276 16.000 726 Long range speed (kt) At alt (ft) Long range fuel cons Ikg/h) 242 25,000 424 239 25,000 430 245 25,000 479 Payload detaib Max (kg) Range with max p/l (km) Payload with max fuel (kg) range with max fuel 6,080 2.038 4.205 4.017 6.080 2.007 4.205 3.934 7.372 1.807 5,531 62 FLIGHT INTERNATIONAL 27 August - 2 September 1997
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