The latest version of the S-65 to be built is the CH-53E Super Stallion for the US Navy. This is a much modified version with three 4380shp General Electric T64-GE-416 engines and strengthened transmission to withstand the increase in power. The fuselage is about 2m longer than that of the CH-53D and the tail pylon is canted to port. The main rotor has also been improved and has seven composite blades (its predecessor had six light alloy ones). Thirty-three CH-53Es were initially ordered by the Marines and 16 by the US Navy. The type is still in production.

G.Apostolo "The Illustrated Encyclopedia of Helicopters", 1984

Phase I development funding for CH-53E Super Stallion allocated 1973; first flight of first of two prototypes 1 March 1974; first flight of first production prototype 8 December 1975; first flight of second production prototype March 1976; deliveries to US Marine Corps started 16 June 1981. First flight of preproduction MH-53E, 1 September 1983; first delivery to US Navy 26 June 1986; in operational service with HM-14 at Norfolk, Virginia, 1 April 1987; first carrier deployment by HM-15 on board USS Tripoli, 9 December 1989.

CURRENT VERSIONS

CH-53E Super Stallion: Used by US Marine Corps for amphibious assault, carrying heavy equipment and armament, and recovering disabled aircraft; also used by US Navy for vertical onboard delivery and recovery of damaged aircraft from aircraft carriers.

Detailed description refers to CH-53E, but applicable also to MH-53E and S-80 export versions, except where indicated.

Planned improvements for CH-53E include, uprated GE T64-GE-416 engines, Omega navigation system, ground proximity warning system, flight crew night vision system (Elbit ANVIS 7 NVG/HUD systems already fitted), improved internal cargo handling system, missile alerting system, chaff/flare dispensers, nitrogen fuel inerting system, and facility for refilling hydraulic system inside cargo compartment. CH-53E will possibly be equipped with self-defence air-to-air missiles; initial trials of AIM-9 Sidewinder conducted at Naval Air Test Center, Patuxent River, Maryland, but no recent developments reported.

Full-scale development of Helicopter Night Vision System (HNVS) for CH-53E began June 1986, in co-operation with Northrop Electro-Mechanical Division; HNVS includes Lockheed Martin Pilot Night Vision System (PNVS) and Honeywell Integrated Helmet and Display Sighting System (IHADSS) from Bell AH-1S surrogate trainer; HNVS will allow low-level operations in night and adverse weather; HNVS ground testing began 1988; operational evaluation began August 1989. Smaller-scale capability authorised 1993, with contract to EER Systems for installation of Hughes AN/AAQ-16B FLIR, Teledyne Ryan Electronics AN/APN-217 Doppler and Rockwell Collins GPS 3A; total 24 upgrades initially authorised; subsequent contracts for 99 HNVS with work scheduled for completion in May 1999. USMC has also evaluated engine-suppression system as means of reducing IR signature, and new multiple cargo hook concept.

MH-53E Sea Dragon: Airborne mine countermeasures helicopter able to tow through water hydrofoil sledge carrying mechanical, acoustic and magnetic sensors; nearly 3,785 litres (1,000 US gallons; 833 Imp gallons) extra fuel carried in enlarged sponsons made of composites; improved hydraulic and electrical systems; minefield, navigation and automatic flight control system with automatic towing and approach and departure from hover modes.

Delivery effected 1994 of MH-53E retrofitted with upgraded avionics package by EER Systems, comprising two 15.2 cm (6 in) horizontal situation display colour screens, Fairchild mission data loader and Rockwell Collins GPS 3A; upgrade of entire MH-53E fleet planned but may be reduced to around 30 as result of defence budget trimming. One MH-53E to West Palm Beach, Florida, for installation of T64-GE-419 engines, late 1993. Trials during 1994 verified performance gains, including recovery and flyaway capability in event of engine failure during hover; retrofit of entire MH-53E fleet underway.

S-80E: Export version of CH-53E. None sold to date.

S-80M: Export version of MH-53E; total of 11 delivered to Japan for Japanese Maritime Self-Defence Force (JMSDF).

CUSTOMERS: US Navy and Marine Corps and Japan.

COSTS: US$24.36 million (1992) projected average unit cost.

DESIGN FEATURES: Fully articulated seven-blade main rotor; blade twist 14°; hydraulic powered blade folding for main rotor; tail pylon folds hydraulically to starboard; four composite-blades tail rotor on pylon canted 20° to port to derive some lift from tail rotor and extend CG range; cranked, strut braced tailplane; rotor brake standard; fuselage stressed for 20 g vertical and 10 g lateral crash loads.

FLYING CONTROLS: Fully powered, with autostabilisation and autopilot. See also Current Versions and Avionics.

STRUCTURE: Fuselage has watertight primary structure of light alloy, steel and titanium; glass fibre/epoxy cockpit section; extensive use of Kevlar in transmission fairing and engine cowlings; main rotor blades have titanium spar, Nomex honeycomb core and glass fibre/epoxy composites skin; titanium and steel rotor head; Sikorsky Inflight Blade Inspection Method (IBIM) sensors detect blade spar cracks occurring in service; tail rotor of aluminium; pylon and tailplane of Kevlar composites.

LANDING GEAR: Retractable tricycle type, with twin wheels on each unit. Main units retract into rear of sponsons on each side of fuselage. Fully castoring nosewheels.

POWER PLANT: Three General Electric T64-GE-416 turboshafts, each with a maximum rating of 3,266kW for 10 minutes, intermediate rating of 3,091kW for 30 minutes and maximum continuous power rating of 2,756kW. Transmission rated at 10,067kW for take-off. Retrofit underway with 3,539kW T64-GE-419 turboshafts.

Self-sealing bladder fuel cell in forward part of each sponson, each with capacity of 1,192 litres. Additional two-cell unit, with capacity of 1,465 litres, brings total standard internal capacity to 3,849 litres. (Total internal capacity of MH-53E is 12,113 litres)

Optional drop tank outboard of each sponson of CH-53E, total capacity 4,921 litres. (MH-53E can carry seven internal range extension tanks, total capacity 7,949 litres) Forward extendable probe for in-flight refuelling. Alternatively, aircraft can refuel by hoisting hose from surface vessel while hovering.

ACCOMMODATION: Crew of three. Main cabin of CH-53E will accommodate up to 55 troops on folding canvas seats along walls and in centre of cabin or 24 litters. Door on forward starboard side of main cabin. Hydraulically operated rear-loading ramp. Typical freight loads include seven standard 1.02 x 1.22m pallets. Dual and single-point central hooks for slung cargo, capacity 16,330kg.

SYSTEMS: Hydraulic system, with four pumps, for collective, cyclic pitch/roll, yaw and feel augmentation flight control servo mechanisms; engine starters; Engine Air Particle Separators (EAPS); engine and hydraulic oil replenishment in flight; landing gear actuation; cargo winches; loading ramp; and blade and tail pylon folding. System pressure 207 bars, except for engine starter system which is rated at 276 bars. (Separate hydraulic system in MH-53E to power AMCM equipment.) Electrical system includes three 115V 400Hz 40 to 60kVA AC alternators, and two 28V 200A transformer-rectifiers for DC power. Solar APU.

AVIONICS: Flight: Hamilton Standard automatic flight control system, using two digital onboard computers and a four-axis autopilot. Retrofit test flown late 1993, comprising four Canadian Marconi CM A-2082 15.2cm square colour displays, tied with GPS, Doppler and AHRS; installation by Teledyne Ryan.

EQUIPMENT: MH-53E equipment includes Westinghouse AN/AQS-14 towed sonar, AN/AQS-17 mine neutralisation device, AN/ALQ-141 electronic sweep and Edo AN/ALQ-166 towed hydrofoil sled for detonating magnetic mines.

ARMAMENT: Window mount provisions for 7.62mm and 12.7mm weapons.

Jane's Helicopter Markets and Systems

- Overall production of the US Marine Corps and Navy Super Stallions is projected to reach 177 aircraft, MH-53Es about 50.

- The first S-80/CH-53E was a test aircraft and made its first flight on 1 March 1974.

- The H-53 family contains the most powerful helicopters used by US forces.

- The first MH-53E minesweeper, which flew in 1983, was not fitted with large sponsons; deliveries began in 1986.

- The first prototype of this series was tragically lost in a ground mishap.

- A CH-53E can lift 16 tonnes - 6 tonnes more than the twin-rotor CH-47 Chinook.