Announced simultaneously with the Model 757, the Boeing Model 767 introduced a completely new fuselage structure which is 1.24m wider, providing seven- or eight- abreast seating with two aisles. The go-ahead for the Model 767 programme was announced on 14 July 1978, following receipt of an order for 30 from United Airlines. By March 1990 orders and options totalled 483.
Computer Aided Design (CAD) was used to speed the preparation of drawings for much of the principal structure, their high accuracy being of great benefit when, as in this case, a large amount of the construction is being carried out by other companies. These include Aeritalia, Canadair, Grumman and Vought, plus a Japanese consortium, Civil Transport Development Corporation, that comprises Fuji, Kawasaki and Mitsubishi. Together, 28 companies are manufacturing assemblies and components which, in terms of value, represent some 45% of the total cost.
Wing design differs from the Model 757, and features increased sweepback, and greater span and wing chord, to provide approximately 53% increase in wing area. The tail unit and landing gear are similar in configuration, and the Model 767 shares with the Model 757 twin turbofan engines pod-mounted beneath the wings.
The 767 has alternative Pratt & Whitney JT9D-7R4D and General Electric CF6-80A powerplants, each in the 21,772kg thrust class, being specified by early airlines.
Boeing planned initially to offer two versions: a Model 767-100 with a shorter fuselage and accommodation for approximately 180 passengers, and the basic Model 767-200. It was then decided not to build the shorter-fuselaged Model 767-100, and instead the Model 767-200 is available at alternative gross weights. Thus the version which was ordered initially by United Airlines for US domestic service has a maximum take-off weight of 127,913kg. That, with a gross weight of 140,614kg, can carry 211 passengers over a range of up to 6013km, making it suitable for non-stop transcontinental services, and also for many international routes.
With an optional flight crew of two or three, provided with the same avionics equipment as the Model 757, the new fuselage also offers significant air freight capacity, with a cargo hold able to accept up to 22.LD-2 containers, or LD-3/-4/-8 containers to similar volume. With the inclusion of an optional forward cargo door measuring 1.75m by 3.4m, Type 2 pallets can be loaded. The first Model 767 was rolled out at Everett, Washington, on 4 August 1981, and made a 2 hour 4 minute maiden flight there on 26 September, which was a few days ahead of the target date set when the programme was launched in 1978.
Taking off at a weight of 240,000 lb (108 864 kg), the 767 was airborne after a 3,000-ft (915-m) run and reached 17,000ft (5182 m) and 260 mph (418 kph) during the 2 hr 4 min flight, in which handling characteristics and minimum flying speeds were assessed and landing gear, speed brake and flap operation were checked. The Boeing 767 embarked upon a 1,100-hr flight test programme to achieve FAA certification.
Certification of the -200 with Pratt and Whitney JT9D-74 power was accomplished by July 1982 and approval of a General Electric CF6-80A engine fit followed after tests with a fifth B.767-200.
Air New Zealand announced an order for three of the extended range variant of the Boeing 767 in July 1984, three years after the type's maiden flight from Everett. The first orders had been placed in 1978 when United Airlines signed for 30.
The Boeing 767-200ER, 50,000 lb thrust GE CF6-80A2 powered, were delivered and in service by September 1988. The Boeing 767-200ER can fly at 41,000 feet and gain height faster due to a better thrust to weight ratio. Other economics are gained from requiring 9 cabin crew, and no third flight crew member required with the departure of the flight engineer.
In February 1983 Boeing announced the 767-300, first flying on 30 Januaray 1986. Both -200 and -300 are offered in ER (Extended Range) variants, with increased fuel capacity and take-off weight for long-range operations.
B.767-300ER - 11,600 km range -300ERs incorporate a fuselage stretch of 6.48 metres on the -200, and an increased takeoff weight of 184.6 tonnes. The later variant has beefed up nose and main landing gear as well as additional fuselage and wing strengthening. Accompanying the fuselage stretch is an increase in thrust from the CF6-80 en-gines, the new -C2 model providing an extra 11,500 lbs a side.
Less obvious are a number of potentially useful features such as a retractable tail skid which lowers with the undercarriage, an additional two over-wing exits to a total of four, and fuel jettison system. The centre wing tankage has been increased by 11,000 kg to 36,500 kg and a nozzle fitted to the trailing edge of the port wing to provide for jettison. The 767-300 program was initiated by Boeing in September 1983, with the ER variant being announced in August 1985. The first -300ER rolled out for certification flying in November 1986 with the General Electric engines. FAA approvals came in May 1987.
The 767-400ER has been stretched by 6.4m (21 ft), which enables a three class for 245 or a single class 410 passengers. The model also features 2.4 m (7 ft 8 in) swept back wing tip extensions, and first flew on 9 October 1999.
In the case of a standard 767, most of the fuel is contained in two main tanks located in the wings, with a 'center' auxiliary in the wing roots. Extended Range 767s (either -200/300 variants) may have either one or two additional tanks placed in the wing center section.
The 92nd Air Refueling Wing at Fairchild AFB, Wash, is to be the first base to operate the new KC-767s, when deliveries begin to the Air Force in 2006.
Engines: 2 x Pratt & Whitney JT9D-7R4D turbofans, 213.4kN
Take-off weight: 136078 kg / 300002 lb
Empty weight: 81230 kg / 179082 lb
Wingspan: 47.57 m / 156 ft 1 in
Length: 48.51 m / 159 ft 2 in
Height: 15.85 m / 52 ft 0 in
Wing area: 283.35 sq.m / 3049.95 sq ft
Max. speed: 952 km/h / 592 mph
Cruise speed: 930 km/h / 578 mph
Ceiling: 11885 m / 39000 ft
Range: 5150 km / 3200 miles
Engines: 2 x CFM-56-80C2B6, 60,000 lb thrust.
Fuel cap: 72 tonne.
MTOW: 187.33 tonne
Engines: 2 x GE CF6-300.
Max brake release wt: 185.05 tonnes.
MLW: 145.10 tonnes.
Zero fuel wt: 130.65 tonnes.
Range: 11,600 km.
Pax cap: 245.
MTOW: 204,120 kg.
Wing span: 170 ft 4 in.