LOCKHEED S-3 VIKING

In late 1966, the Navy realized the need advanced ASW aircraft. Therefore, procurement for this VSX requirement began.
Lockheed teamed with LTV (Ling-Temco-Vought) for its experience with carrierborne aircraft and also with Univac Federal Systems for its skill in ASW systems.
LTV designed and built the engine pods, landing gear, tail unit and wing. Univac produced the complete ASW system. Lockheed built the fuselage, integrated the systems and carried out final assembly and test.
First of eight YS-3A made the first flight on January 21, 1972.
First production of S-3A authorized in April of 1972.
Production of 187 S-3As ended in mid-1978.
Early 1980, US-3A (Carrier Onboard Delivery, COD) and KS-3A (dedicated tanker) demonstrators were evaluated by the Navy.
Three YS-3As were converted to US-3As with one KS-3A built, and later converted to US-3As.
S-3As with the fitting of a Sargent-Fletcher buddy back under port wing (to transfer fuel from internal tanks) and external tanks under starboard wing were tested and adopted in 1984, without affecting ASW capability.

Lockheed was awarded a Weapon System Improvement Program (WSIP) under US Navy contract in 1980.
Full-scale development ordered August 18, 1981 and designated S-3B.
First flight of first of S-3B on September 13, 1984.
Flight testing completed in August 1985. 22 kits and spares and support were orderd on April 28, 1986.
24 more kits ordered December 1988 for delivery by August 1992.

Contract for development of electronic reconnaissance E-3A awarded in march of 1988.
Used to replace the EA-3B in the Elint and ECM roles.
First flight in April 1991.
Nine modification kits ordered early 1989 for delivery by August 1991.
Weapons bay used for avionics as well as rear fuselage.
Starboard dual controls replaced by displays and controls for Electronic Warfare Combat Co-ordinator (EWCC).

Cantilever shoulder-wing monoplane.
Cantilever all-metal tail unit structure with swept vertical and horizontal surfaces.
Fin and rudder are folded downward by hydraulic servos for carrier stowage.
During fin-folding sequence, the pedal input the rudder servo is disconnected to allow the pilot to steer the nose wheel by the rudder pedals.

All-metal fail-safe wing structure.
Wings fold upward and inward hydraulically, outboard of engine pylons for stowage.
The fuselage is semi-monocoque all-metal fail-safe structure, incorporating split weapons bays with clamshell doors.
Launch tubes for 60 sonobuoys in belly.
Frangible canopies in top of fuselage are designed for crew to eject through them in emergencies.
Electronics bay with external access doors in forward and aft fuselage.
An illuminated in-flight refuelling probe, mounted within the fuselage on the top centreline, is operated by an electric drive and protected by a positive-seal door.
It can also be extended/retracted by hand crank in emergencies.

Two General Electric TF34-GE-2 high bypass ratio turbofan engines, each rated at 41.25 kN (9,275 lb st), pylon-mounted beneath the wings.
Fuel in integral wing tanks, entirely within the wing box beam, one on each side of the fuselage centreline and onboard of the wing fold-line.
Usable fuel capacity approx. 7,192 litres (1,900 US gallons, 1,583 Imp gallons).
Two 1,136 litre (300 US gallon, 250 Imp gallon) jettisonable fuel tanks can be carried on underwing pylons.
Single-point pressure refuelling adapter located on starboard side of fuselage aft of main landing gear door.
Anti-icing of engine inlet nozzles by engine bleed air.

S-3A/B weapon options include:
Four Mk 46/50 torpedoes, two B57 nuclear depth charges, four Mk 82 560 lb bombs or four Mk 36 destructors all stowed internally.
Plus underwing armament of six Mk 82/86s, two Mk 52/55/56 mines, two Mk 60 torpedoes, two AGM-84 Harpoon anti-ship missiles, or six LAU-10C/68A/69A rocket pods/SUU-44A flare pods.

DIMENSIONS:
Wing span:	20.93 m	68 ft 8 in
Wing span, folded:	8.99 m	29 ft 6 in
Length overall:	16.26 m	53 ft 4 in
Length overall, tail folded:	15.06 m	49 ft 5 in
Height overall:	6.93 m	22 ft 9 in
Height overall, tail folded:	4.65 m	15 ft 3 in
Tailplane span:	8.23 m	27 ft 0 in
WEIGHTS AND LOADINGS:
Max zero-fuel weight:	13,290 kg	29,299 lb
Max carrier landing weight:	16,676 kg	36,766 lb
Max T-O weight:	23,831 kg	52,539 lb
Empty:	12,088 kg	26,650 lb
PERFORMANCE: (Max T-O weight)
Max level speed at 6,100 m (20,000 ft):	450 kt	834 km/h, 518 mph
Patrol speed:	160 kt	296 km/h, 184 mph
Service ceiling:	12,200 m	40,000 ft
Operational ceiling (with passengers):	10,670 m	35,000 ft
Range with max payload:	2,000 n miles	3,706 km, 2,303 miles
Max ferry range:	3,230 n miles	6,085 km, 3,719 miles