TITLE:

LOCKHEED 382 'Hercules'

US Air Force designations: C-130, AC-130, DC-130, EC-130, HC-130, JC-130, LC-130, MC-130, NC-130, RC-130 and WC-130 US Navy designations: C-130, DC-130, EC-130, LC-130 and TC-130 US Marine Corps designation: KC-130

TYPE:

Tactical transport and multi-mission aircraft.

PROGRAMME:

US Air Force specification issued 1951; first production contract for C-130A to Lockheed September 1952; two prototypes, 231 C-130As, 230 C-130Bs and 491 C-130Es manufactured. Lockheed delivered 2000th Hercules (C-130H to Kentucky ANG) in April 1992.

DESIGN FEATURES:

Can deliver loads and parachutists over lowered rear ramp and parachutists through side doors; removable external fuel tanks outboard of engines are standard fittings; cargo hold pressurised. Wing section NACA 64A318 at root and NACA 64A412 at tip; dihedral 2 degrees 30'; incidence 3 degrees at root, 0 degrees at tip. Leading-edges of wing, tailplane and fin anti-iced by engine bleed air.

LANDING GEAR:

Hydraulically retractable tricycle type. Each main unit has two wheels in tandem, retracting into fairings built onto the sides of the fuselage. Nose unit has twin wheels and is steerable +/-60 degrees.

POWER PLANT:

Four 3362 kW (4508 shp) Allison T56-A-15 turboprops, each driving a Hamilton Standard type 54H60 four-blade constant-speed fully feathering reversible-pitch propeller. Fuel in six integral tanks in wings, with total capacity of 26344 litres (6960 US gallons; 5795 Imp gallons) and two optional underwing pylon tanks, each with capacity of 5146 litres (1360 US gallons; 1132 Imp gallons). Total fuel capacity 36,636 litres (9680 US gallons; 8060 Imp gallons).

ACCOMMODATION:

Crew of four on flight deck comprising pilot, co-pilot, navigator and systems manager (fully performance qualified flight engineer on USAF aircraft). Provision for fifth man to supervise loading. Sleeping bunks for relief crew and galley.

AVIONICS:

Standard fit specified by US government comprises dual AN/ARC-190 HF com, dual AN/ARC-186 VHC com, dual AN/ARC-164 UHF com, AN/AIC-13 PA system, AN/AIC-18 intercom, AN/APX-100 IFF/AIMS ATC transponder, dual AN/ARN-118 UHF nav, dual AN/ARN-147 VHF nav, self-contained navigation system (SCNS), dual DF-206A ADF, DF-301E UHF direction finder, emergency locator transmitter (ELT).

ARMAMENT:

Fitment of Rockwell Hellfire ASM to AC-130H/U studied 1991-92.

DIMENSIONS: EXTERNAL:

Wing span: 40.41 m (132 ft 7 in)

Wing chord: at root: 4.88 m (16 ft 0 in)

mean: 4.16 m (13 ft 8{1/2} in)

Length overall:

all except HC-130H and C-130H-30: 29.79 m (97 ft 9 in)

C-130H-30: 34.37 m (112 ft 9 in)

Height overall: 11.66 m (38 ft 3 in)

Tailplane span: 16.05 m (52 ft 8 in)

Propeller diameter: 4.11 m (13 ft 6 in)

PERFORMANCE: (C-130H at max normal T-O weight, unless indicated otherwise):

Max cruising speed: 325 knots (602 km/h; 374 mph)

Econ cruising speed: 300 knots (556 km/h; 345 mph)

Stalling speed: 100 knots (185 km/h; 115 mph)

Max rate of climb at S/L: 579 m (1900 ft)/min

Service ceiling at 58,970 kg (130000 lb) AUW: 10,060 m (33,000 ft)

Service ceiling, OEI, at 58,970 kg (130,000 lb) AUW: 8075 m (26,500 ft)

LENGTH (m): 34.37

HEIGHT (m): 11.66

WINGSPAN (m): 40.41

MAX T-O WEIGHT (kg): 79,380

MAX WING LOAD (kg/m/2): 434.50

SERVICE CEILING (m): 10,060

T-O RUN (m): 1091

LANDING RUN (m): 518

MAX RATE CLIMB (m/min): 579