Gulfstream G200

TYPE: Business jet.

PROGRAMME: Initiated as IAI 1126 derivative of Astra SP; design (then called Astra IV) finalised late 1992 in anticipation of 1993 launch; co-production with Yakovlev of Russia discussed during early part of 1993; formal announcement of launch as Galaxy, with minor design changes, announced 20 September 1993 just before NBAA Convention in Atlanta, Georgia, USA, followed next day by news that Yakovlev to be risk-sharing partner; other partners to be Rockwell Collins (avionics supplier) and eventual engine manufacturer (P&WC since selected). Replacement for Yakovlev sought in 1995, and Sogerma (France) contracted August 1996 to build production aircraft fuselages and tail units, but latter contract terminated mid-2001.

Four prototypes (003 and 004 flying plus 001 static and 002 fatigue test); first flight rescheduled for fourth quarter 1996 (later changed to second quarter 1997 and later still to fourth quarter 1997); 003 rolled out 4 September 1997 and made first flight (4X-IGA) 25 December 1997. Static testing of 001 completed September 1998. Second flight test aircraft (4X-IGO, c/n 004) made first flight 21 May 1998; 005 (company demonstrator 4X-IGB/N505GA) first flew on 23 September 1998; combined total of 750 hours in 260 flights by three aircraft by December 1998. Israeli CAA and US FAA certification to FAR Pt 25 Amendment 25 and FAR Pts 34 and 36 awarded 16 December 1998; European JAA certification process started mid-1999. First customer delivery, to TTI of Fort Worth, Texas, made in January 2000. Production rate two per month in mid-2000. Type certificate acquired by Gulfstream Aerospace in June 2001, aircraft renamed Gulfstream 200 and formally unveiled as such at Paris on 17 June 2001; name Gulfstream G200 adopted in September 2002 although Type Certificate had been amended with new designation on 16 January 2002. G200 applies to c/n 057 and subsequent aircraft, although retrospective redesignation is permissible under US rules. Civil Aviation Administration of China certification achieved 10 September 2002.

CURRENT VERSIONS: Seen as four/eight-passenger business/ executive (standard model), with option of alternative interior seating up to 18 passengers for regional transport operation.

CUSTOMERS: Between 45 and 50 commitments by October 1999, of which about 35 per cent from non-US operators in Canada, Europe, Israel, Mexico and South America. First bulk order, for seven, plus option on 15 more, placed mid-1999 by charter operator ILI Aviation of Zurich, Switzerland. IAI estimates break even at 100 sales and potential market for 200. Totals of one delivered in 1999, six in 2000, 24 in 2001, and 12 in the first six months of 2002. Orders by September 2002 included 50 firm and 50 options by Executive Jet Inc, three by Hainan Airlines of Beijing, China, and one by MetroJet of Hong Kong. Total 82 (including protoypes) supplied to completion centres or customers by July 2003.

GALAXY/G200 PRODUCTION (at October 2003)
Variant Qty Remarks
Prototypes(flying) 2 Eligible for change of designation
Galaxy 48
G200 32
Total 82

COSTS: Approximately US$18 million flyaway (July 2000); total development programme cost forecast at approximately US$152 million (1993).

Detailed description applies to Gulfstream G200 from c/n 40 onwards.

DESIGN FEATURES: Designed for transatlantic range (non-stop Paris to New York). Essentially same wing as Gulfstream 100, except for 34° 30' inboard leading-edge sweep and addition of Krueger flaps; new wide-body fuselage is longer and has more headroom.

FLYING CONTROLS: All-hydraulic dual actuation except for rudder (manual); aileron movement 10° up/15° down, elevators 27° up/20° down, rudder 20° left/right; tailplane and rudder tab have electric trim. Wings fitted with outboard leading-edge slats (25° fully out), inboard Krueger leading-edge flaps (110°), four-segment upper surface airbrakes/lift dumpers (45° fully up) and Fowler single-slotted inboard and outboard trailing-edge flaps (settings 0, 12, 20 and 40°). Ailerons and elevators can be operated manually in event of hydraulic failure.

STRUCTURE: Generally similar to that described for G100. Sogerma (France) produced tail units, doors, access panels, tailcones and wing/fuselage fairings for prototypes. Flight Environments cabin flame protection and sound attenuation system.

LANDING GEAR: Hydraulically retractable tricycle type; twin wheels and oleo-pneumatic shock-absorbers on each unit. Nose unit has electrohydraulic steering (± 60°) and retracts forward. Trailing-link mainwheel units retract inward and are equipped with Honeywell multidisc anti-skid carbon brakes.

POWER PLANT: Two FADEC-equipped Pratt & Whitney Canada PW306A turbofans, each flat rated at 26.9 kN (6,040 lb st), pylon-mounted on sides of rear fuselage. Nordam nacelles and thrust reversers. Fuel in seven tanks: right and left wing, each 1,334 litres (352.5 US gallon; 293-5 Imp gallons); right and left feed, each 102 litres (26.9 US gallons; 22.4 Imp gallons); centre 1,533 litres (405 US gallons; 337 Imp gallons); forward 1,011 litres (267 US gallons; 222 Imp gallons); and fuselage 3,115 litres (823 US gallons; 685 Imp gallons). Total fuel 8,532 litres (2,254 US gallons; 1,877 Imp gallons), of which 8,479 litres (2,240 US gallons 1,865 Imp gallons) are usable.

ACCOMMODATION: One or two pilots; provision for jump-seat for third crew member. Standard club-type seating for four to eight persons in business/executive version; legroom between facing seats allows enough space for full reclining and berthing; large galley with room for refrigerator, microwave oven, coffee maker and storage. Alternative 10-passenger layout has four club seats at front, with a four-place conference group and two on a divan to the rear, plus optional lavatory and additional baggage space aft. Three-abreast seating for up to 18 passengers, with single aisle, can be provided in corporate shuttle configuration. Generous baggage compartment in rear fuselage, accessed by external airstair door, can accommodate baggage for all 18 passengers. Entire accommodation, including baggage compartment, is pressurised. Airshow in-flight cabin entertainment system optional.

SYSTEMS: Dual hydraulic systems, each 207 bar (3,000 lb/sq in). Electrical system comprises three (including one on APU) Lucas Aerospace 28 V 400 Ah engine-driven starter/generators, two 24 V 43 Ah Ni/Cd batteries and a Honeywell GTCP36-150 APU. Third (24 V 27 Ah) battery for back-up powering of essential flight instruments and emergency systems. Pneumatic system for emergency extension of landing gear, actuation of wheel brakes and thrust reversers, and de-icing of wing leading-edges. Cabin pressurisation and air conditioning system, differential 0.61 bar (8.8 lb/sq in). One (optionally two) oxygen bottles.

AVIONICS: Rockwell Collins Pro Line 4 suite standard
Comms: Dual VHF-422C radios, RTU-4220 radio tuners, TDR-94D transponders, Bendix/King KHF 950HF and Baker B1045-F512 audio systems; triple Magnastar Flightphones; single Avtech Selcal, Artex ELT and Universal CVR-30B CVR.
Radar: TWR-850 colour weather radar with turbulence detection and WXP-4220 control panel.
Flight: Dual Universal UNS-1C FMS with embedded GPS, Rockwell Collins FCC-4005 autopilots, AHS-3000 AHRS, ADC-850C air data systems, VIR-432 VOR/ILS/GS/markers and DME-442; single ADF-462, ALT-4000 radio altimeter, TCAS-4000, Honeywell Laseref IV IRS, EGPWS Mk V and FDR.
Instrumentation: Rockwell Collins EFD-4077 EFIS displays all flight and EICAS information on five 18.4 cm (7 1/4 in) screens; dual Davtron M850A digital clocks; Flight Line 8047-10 standby altimeter, 8059-2B standby ASI, Jet AI-804CE standby AI, Precision PAI-700-04 standby compass and Hobbs 15007 hour meter.

Wing span 17.70 m (58 ft 1 in)
Length overall 18.97 m (62 ft 3 in)
Wing aspect ratio 9.1
Height overall 6.53 m (21 ft 5 in)
Tailplane span 6.86 m (22 ft 6 in)
Wheel track 3.30 m (10 ft 10in)
Wheelbase 7.39 m (24 ft 3 in)
Passenger door:
Height 1.83 m (6 ft 0 in)
Width 0.84 m (2 ft 9 in)
Baggage compartment door:
Height 1.14 m (3 ft 9 in)
Width 0.89 m (2 ft 11in)
Cabin: Length: incl flight deck 9.30 m ( 30 ft 6 in)
excl flight deck 7.44 m (24 ft 5 in)
Max width 2.18 m (7 ft 2 in)
Max height 1.91 m (6 ft 3 in)
Volume, exel flight deck 24.6 m3 (868 cu ft)
Baggage compartment volume 3.5 m3 (125 cu ft )
Wings, gross 34.28 m2 (369.0 sq ft)
Basic operating weight empty 8,981 kg (19,800 lb)
Max usable fuel weight 6,804 kg (15,000 lb)
Max payload 1,905 kg (4,200 lb)
Baggage compartment capacity 898 kg (1,980 lb)
Payload with max fuel 363 kg (800 lb)
Max ramp weight 16,148 kg (35,600 lb)
Max T-O weight 16,079 kg (35,450 lb)
Max landing weight 13,608 kg (30,000 lb)
Max zero-fuel weight 10,886 kg (24,000 lb)
Max wing loading 469.1 kg/m2 (96.07 lb/sq ft)
Max power loading 299 kg/kN (2.93 lb/lb st)
PERFORMANCE (estimated):
Max operating Mach No. (Ммо) 0.85
Max operating speed (Vмо):
S/L to FL100 310 kt (574km/h; 356 mph) IAS
FL100-FL200 310-330 kt (574-611 km/h; 356-379 mph) IAS
FL200-FL250 360 kt (667 km/h; 414 mph) IAS
Max cruising speed (Vмc) at FL310, mid-cruise weight of 12,247 kg (27,000 lb) 494 kt (915 km/h; 568 mph)
Typical cruising speed at FL390 475 kt (880 km/h; 547 mph)
Long-range cruising speed 430 kt (797 km/h; 495 mph)
Stalling speed, flaps and gear down, at MLW 112 kt (208 km/h; 129 mph) IAS
Max certified altitude 13,715 m (45,000 ft)
T-O distance (S/L, ISA) 1,855 m (6,080 ft)
Landing distance at MLW (S/L, ISA) 1,001 m (3,285 ft)
Range with four passengers, NBAA IFR reserves 3,600 n miles (6,667 km; 4,142 miles)
g limits, flaps and gear up +2.63/-1.0
T-O 81.4 EPNdB
Sideline 85.8 EPNdB
Approach 90.9 EPNdB

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