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Gulfstream G 1159 Gulfstream IV / G-IV / SRA-4



In 1982 the company’s name changed to Gulfstream Aerospace Corp. to reflect its worldwide scope, and a new plane, the Gulfstream IV, was conceived.

Launched on 19 April 1983, and first flown in September 1985, the Gulfstream IV received its certification by the FAA on 22 April 1987, and went into full production at the Savannah facility of Chrysler Corp subsidiary Gulfstream Aerospace Corp. A twin turbofan executive transport, although generally similar to the Gulfstream III, the IV includes a redesigned wing, a lengthened fuselage with a sixth window on each side and two 13,850 lb st (61,6 kN) R-R Tay Mk.611-8 turbofans. The cockpit incorporates advanced CRT displays and digital avionics.

At the time of certification, the company held orders for more than 100 Gulfstream IVs and by the end of May 1987 had delivered 16 aircraft. The complete flight management system, including EFIS, is included in the GIV during production, but, as is customary for corporate aircraft, they are delivered to their customers unfinished and go to approved finishing centres for customer-specified in-teriors to be installed.

As well as for the corporate role, the GIV is now being vigorously marketed in a number of military and quasi-military roles as the SRA-4 (Special Requirements Aircraft). The SRA-4 for mainly military roles including electronic warfare, search and rescue, anti-submarine/ ship, and communications.

The performance of the Gulfstream IV, particularly in payload/range terms, has already been demonstrated in several notable flights, including a round-the-world westbound flight (ie, against the prevailing wind patterns) made in the third production aircraft (s/n 1002). Starting and finishing at Le Bourget during the Paris Air Show, this Gulfstream, with a six-man crew headed by Gulfstream Aerospace chairman Allen E Paulson, completed the l9,847-naut ml (36832.44-km) circuit in 45 hrs 25 mm 10 sec. With five ground stops (at Rome, Mid-way, Kinabalu, Dubai and Cairo) the aircraft averaged 4377 kts (810,79 km/h) and en-countered head winds of up to 139 kts (257 km/ h). In addition to 22 city-to-city records, the flight set round-the-world westbound records for jet aircraft of unlimited weight and business jets of up to 35,000 kg (77 140 lb) gross weight.

The Gulfstream IV-SP has more efficient engines and modifications revising operating weights and a better payload range combination.


Gulfstream G4SP N600VC


In 1987, the 200th and last Gulfstream III produced was delivered, and the first delivery of a Gulfstream IV took place. The GIV was the first jet in business aviation to have an all-glass cockpit.

Gulfstream G 1159 Gulfstream IV
Engine: 2 x Rolls Royce Tay 611-8, 60430 N / 6160 kp
Length: 88.255 ft / 26.9 m
Height: 24.934 ft / 7.6 m
Wingspan: 77.756 ft / 23.7 m
Wing area: 950.461 sq.ft / 88.3 sq.m
Max take off weight: 73206.0 lb / 33200.0 kg
Weight empty: 42512.4 lb / 19280.0 kg
Max. weight carried: 30693.6 lb / 13920.0 kg
Max. speed: 509 kts / 943 km/h
Landing speed: 108 kts / 200 km/h
Cruising speed: 459 kts / 850 km/h
Initial climb rate: 3937.01 ft/min / 20.0 m/s
Service ceiling: 44948 ft / 13700 m
Wing loading: 77.08 lb/sq.ft / 376.0 kg/sq.m
Range: 3696 nm / 6845 km
Crew: 2
Payload: 14-19pax

Gulfstram IV (Long range)
Engines: Two Rolls-Royce Tay 610-8 turbofans, 12,420 (5634 kgp)
Fuel capacity, 4,370 US gal (16,540 lt).
Max operating speed (VM0) 340 kts (630 km/h)
CAS, (MM0) M = 088.
Tur-bulent air penetration speed (above 32,000 ft/ 9754 in), M=075.
Max cruising speed, 519 kts (962 km/h) or Mach = 088
Long-range cruise, 459 kts (851 km/h) or M = 080
Take-off balanced field length, 5,100 ft (1 554 m)
Initial rate of climb, 3,816 ft/min (19,4 m/sec)
Single-engine climb rate, 1,278 ft/min (6,5 m/sec)
Max operational altitude, 51,000 ft (15 544 m)
Single-engine cruise ceiling, 27,000 ft (8 230 m)
Landing distance, 3,200 ft (975 m)
Max range (NBAA IFR reserves, long-range cruise), 4,300 naut mls (7965 km) with 8 pax.
Typical operating weight empty, 41,100 lb (18 643 kg)
Max fuel load, 29,500 lb (13 381 kg)
Payload with max fuel, 1,600 lb (726 kg)
Max payload, 3,900 lb (1 769 kg)
Max take-off weight, 71,700 lb (32 523 kg)
Max zero fuel weight, 45,000 lb (20 412 kg)
Max landing weight, 58,500 lb (26 536 kg).
Wing span, 77 ft 10 in (23,7 m)
Overall length, 88 ft 4 in (26,9 m)
Overall height, 24 ft 10 in (7,6 m)
Wing area, 9504 sq ft (88,29 sq.m)
Wing sweepback, at quarter chord line, 2766 deg inboard, 2682 deg outboard.
Accommodation: Flight crew of two.
Typical executive layouts for 14 passengers; max cer-tificated, 19 passengers.
Cabin length, 45 ft 1 in (13,7 m)
Max height, 6 ft 1 in (1,9 m)
Max width, 7 ft 4 in (2,2 m)
Total cabin volume, 1,513 cu ft (42,8 cu.m)
Baggage compartment volume, 169 cu ft (4,8 cu.m).

Engine: Roll-Royce Tay 611-8.

Engines: 2 x Rolls-Royce Tay 610-8 turbofan, 12420 lb thrust.


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