Sikorsky CH-53G of the Heeresflieger (West Germany army aviation)

SIKORSKY S-65A (CH-53A) Sea Stallion

US Navy designation: CH-53A Sea Stallion
USMC designations: CH-53A/D
USAF designations: HH-53B/C

TYPE:

Twin-turbine heavy assault transport helicopter.

CH-53 at a mountain training base - Click to enlarge

Soldiers waiting to board a CH-53 - Click to enlarge

PROGRAMME:

Sikorsky started design and development of large transport helicopters at the beginning of the 1950s.
In the late 1950s the company began work on large flying-crane helicopters and then drew up its proposals to meet a USMC requirement for a ship-based heavy assault transport.
On August 27, 1962, it was announced that Sikorsky had been selected by the US Navy to produce a heavy assault transport helicopter for use by the Marine Corps.
This was identified as the Sikorsky S-65A, with a service designation of CH-53A and name Sea Stallion.
First flight was made on October 14, 1964, and deliveries began in mid-1966.
Some 412 CH-53s were built by Sikorsky and 110 were built by VFW-Fokker in Germany.

Soldiers storm out of a CH-53 - Click to enlarge

VERSIONS:

CH-53A:

Initial version utilising many components based on those of the S-64A Skycrane, but powered by two General Electric T64 turboshaft engines and has a watertight hull.
A full-size rear opening, with built-in ramp, permits easy loading and unloading, with the aid of a special hydraulically operated internal cargo loading system and floor rollers.
The CH-53A is able to operate under all weather and climatic conditions.
Its main rotor blades and tail pylon fold hydraulically for stowage on board ship.
On February 17, 1968, a CH-53A, with two General Electric T64-6 (modified) engines, flew at a gross weight of 23,541 kg (51,900 lb) carrying 12,927 kg (28,500 lb) of payload and fuel, establishing a new unofficial payload and gross weight records for a production helicopter built outside the former Soviet Union.
A Marine Corps CH-53A performed a series of loops and rolls, on October 23, 1968, as part of a joint Naval Air Systems Command and Sikorsky flight test programme aimed at investigating the CH-53A's rotor system dynamics and manoeuvrability characteristics.

CH-53D:

Improved CH-53A for US Marine Corps, the first of which was delivered on March 3, 1969.
Two T64-GE-413 engines, each with a maximum rating of 2,927 kW (3,925 shp).
A total of 55 troops can be carried in a high-density arrangement.
An integral cargo handling system makes it possible for one man to load or unload 1 ton of palletised cargo a minute.
Main rotor and tail pylon fold automatically for carrier stowage.

CH-53G:

Version of the CH-53 for the German armed forces, with T64-GE-7 engines.
A total of 112 was produced, the first of two built by Sikorsky being delivered 31 March 1969.
The next 20 were assembled in Germany from American-built components.
The remainder embody some 50 per cent components of German manufacturers. Prime contractor in Germany was VFW-Fokker, whose first CH-53G flew for the first time on October 11, 1971.
Deliveries completed in 1975.

HH-53B:

Eight ordered by USAF in September 1966 for Aerospace Rescue and Recovery Service.
The first of these flew on March 15, 1967.
The HH-53B is generally similar to the CH-53A, but powered by 2,297 kW (3,080 shp) T64-GE-3 turboshaft engines.
It has the same general equipment as the HH-3E, including a retractable flight refuelling probe, jettisonable auxiliary fuel tanks, rescue hoist, all weather electronics and armament.
Withdrawn from service.

HH-53C:

Improved version of the HH-53B, with 2,927 kW (3,925 shp) T64-GE-7 engines, auxiliary jettisonable fuel tanks each of 1,703 litres (450 US gallons; 374.7 Imp gallons) capacity on new cantilever mounts, flight refuelling probe, and rescue hoist with 76 m (250 ft) of cable.
External cargo hook of 9,070 kg (20,000 lb) capacity.
First HH-53C was delivered to the USAF on August 30, 1968.
A total of 72 HH-53B/Cs was built. Withdrawn from service.

HH-53H Pave Low III:

Special operations version for combat rescue and recovery.
Eight converted to MH-53J Pave Low III.

RH-53D:

Specially equipped minesweeping version for the US Navy and Iran.

YCH-53E:

Three-engined development of the CH-53D.

VH-53D:

Presidential helicopter of US Marine Corps.

S-65-Oe:

Two ordered in 1969 by Austrian Air Force and delivered in 1970.
Used for rescue duties in the Alps, they have the same rescue hoist as the HH-53B/C, fittings for auxiliary fuel tanks and accommodation for 38 passengers. Withdrawn from service.

S-65C:

Commercial intercity helicopter proposal based on military CH-53.

TH-53A:

Training version in service with the USAF.

CH-53E landing on a ship - Click to enlarge

DESIGN FEATURES:

Rotor system and transmission generally similar to those of S-64A Skycrane, but main rotor head is of titanium and steel, and has folding blades.

POWER PLANT:

Normally two 2,125 kW (2,850 shp) General Electric T64-GE-6 turboshaft engines, mounted in pod on each side of main rotor pylon.
The CH-53A can also utilise, without airframe modification, the T64-GE-1 engine of 2,297 kW (3,080 shp) or the later T64-GE-16 (mod) engine of 2,561.5 kW (3,435 shp).
Two self-sealing bladder fuel tanks, each with capacity of 1,192 litres (315 US gallons; 262 Imp gallons), housed in forward part of sponsons.
Total fuel capacity: 2,384 litres (630 US gallons; 524.6 Imp gallons).

CH-53 loading refugees during Operation Allied Force - Click to enlarge

CH-53D lifting a F-15 - Click to enlarge

ACCOMMODATION:

Crew of three.
Main cabin accommodates 37 combat-equipped troops on inward-facing seats.
Provision for carrying 24 stretchers and four attendants.
Roller-skid track combination in floor for handling heavy freight.
Door on starboard side of cabin at front. Rear-loading ramp.

DIMENSIONS:
Diameter of main rotor:	22.02 m	72 ft 3 in
Diameter of tail rotor:	4.88 m	16 ft 0 in
Length overall, rotors turning:	26.90 m	88 ft 3 in
Length of fuselage, excl refuelling probe:	20.47 m	67 ft 2 in
Width overall, rotors folded:	4.72 m	15 ft 6 in
Width of fuselage:	2.69 m	8 ft 10 in
Height to top of rotor hub:	5.22 m	17 ft 1 1/2 in
Height overall:	7.60 m	24 ft 11 in
Wheel track:	3.96 m	13 ft 0 in
Wheelbase:	8.23 m	27 ft 0 in
AREAS:
Main rotor disc:	378.1 m²	4,070 sq ft
Tail rotor disc:	18.67 m²	201 sq ft
WEIGHTS AND LOADINGS:
Weight empty:
CH-53A:	10,180 kg	22,444 lb
HH-53B:	10,490 kg	23,125 lb
HH-53C:	10,690 kg	23,569 lb
CH-53D:	10,653 kg	23,485 lb
Normal T-O weight: CH-53A:	15,875 kg	35,000 lb
Mission T-O weight:
HH-53B:	16,964 kg	37,400 lb
HH-53C:	17,344 kg	38,238 lb
CH-53D:	16,510 kg	36,400 lb
Max T-O weight:
HH-53B/C, CH-53D:	19,050 kg	42,000 lb
PERFORMANCE:
Max level speed at S/L:
HH-53B:	162 kt	299 km/h; 186 mph
HH-53C, CH-53D:	170 kt	315 km/h; 196 mph
Cruising speed:
HH-53B/C, CH-53D:	150 kt	278 km/h; 173 mph
Max rate of climb at S/L:
HH-53B:	440 m/min	1,440 ft/min
HH-53C:	631 m/min	2,070 ft/min
CH-53D:	664 m/min	2,180 ft/min
Service ceiling:
HH-53B:	5,610 m	18,400 ft
HH-53C:	6,220 m	20,400 ft
CH-53D:	6,400 m	1,000 ft
Hovering ceiling in ground effect:
HH-53B:	2,470 m	8,100 ft
HH-53C:	3,565 m	11,700 ft
CH-53D:	4,080 m	13,400 ft
Range:
HH-53B/C, with 4,502 kg (9,926 lb) fuel plus two 1,703 litre; 450 US gallon; 375 Imp gallon auxiliary tanks, including 10% reserves and 2 min warm-up:
468 n miles	869 km	540 miles
CH-53D, with 1,849 kg (4,076 lb) fuel plus 10% reserves at cruising speed and 2 min warm-up:
223 n miles	413 km	257 miles

3 view drawing of the CH-53A - Click to enlarge