MCDONNELL DOUGLAS F/A-18E/F SUPER HORNET

Single/two seat carrier-based strike/attack and maritime air supremacy aircraft.

Proposed in 1991 as a replacement for the cancelled GD/MDC A-2 and the aging F/A-18As of the
USN/USMC as they are phased out.
Development for funding approved by Congress in FY92 with contract awarded in June 1992.
Work began with subcontractor Northrop Grumman on May 24, 1994 with roll-out on September 18, 1995.
First flight on November 29, 1995. assembly of production F/A-18E began at Northrop Grumman in May 1997 and in September 1997 at Boeing.
First flight of prototype F/A-18F on April 1, 1996.
Supersonic speed exceeded for the first time on April 12, 1996 with Mach 1.1 on the first F/A-18E prototype.
By November 16, 1996, five Super Hornets had completed 346 sorties and 575 flight hours of development testing, with had also recorded a maximum altitude of 15,100 m (49,500 ft), flown at Mach 1.54, and achieved +7/-1.7 load factors.
Approval for low-rate initial production (LRIP) of 62 aircraft in 3 lots given on March 26, 1997. first composed of 8 F/A-18E's and 4 F/A-18Fs.

Stretched versions of the F/A-18C/D with gross landing weight increased by 4,536 kg (10,000 lb).
Wings photo-metrically increased in size to provide 9.29 m{2} (100.0 sq ft) extra area and 1.31 m (4 ft 3 ˝ in) span increase.
Control surfaces disproportionately enlarged and dogtooth added to leading-edge for increased aileron authority.
Additional 1,637 kg (3,600 lb) of internal and 1,406 kg (3,100 lb) of external fuel incorporated into design, thus 40% extra range.
Two further weapon hardpoints (making a total of 11).
Air intakes redesigned and slewed to increase mass flow of more powerful F414-GE-400 engines and also changed to 'caret' shape to reduce radar signature.
Incorporates other stealth features to reduce radar cross-section, including saw-toothed doors and panels, realigned joints and edges and angled antennae.

Two General Electric F414-GE-400 turbofans, each rated at approx. 97.9 kN (22,000 lb st) with afterburning.
Internal fuel capacity: 8,062 litres (2,130 US gallons, 1,774 Imp gallons).
Wing tanks protected from combat damage by low-density foam.
Provision for three 1,818 litre (480 US gallon, 400 Imp gallon) external fuel tanks.

Full range of USN offensive and defensive ordanance.
'Bring-back' load increased to 4,082 kg (9,000 lb).
Some 30 weapons combinations will be cleared prior to service entry.
Lightweight internal cannon due to be installed in place of M61A1 as used by standard Hornet and will also be compatible with forthcoming AIM-9X missile.