Vertipedia - Sikorsky CH-53A Sea Stallion

Utility variant for the U.S. Marine Corps.

By the glossary definition, with a Useful Load of 12556 lb (5695 kg), the calculated Empty Weight is approximately 10180 kg.

Overview

Data on design, manufacture and status

Design authority: Sikorsky Aircraft Corp.

Primary manufacturer: Sikorsky Aircraft Corp.

Parent type: Sikorsky S-65/H-53

Aircraft status: No longer flying

Configuration

Primary flight and mechanical characteristics

VTOL type: Helicopter

Lift devices: 1 Single main rotor

Dedicated control device: 1 Tail rotor

Crew required: 2 in Side-by-side arrangement

Landing gear: Wheels (all retractable)

Key Characteristics

Data on key physical features

Aircraft Details

Data on aircraft configuration, weights, flight performance and equipment

Layout and Dimensions

Weights and Performance

Engine Details

Primary Lift Device

Primary Control Device

Overall Dimensions
Overall Height:	7.57 m	24.8 ft
Overall Length:	28.63 m	93.9 ft
Overall Width:

Airframe Dimensions
Airframe Length:
Airframe Width:	7.29 m	23.9 ft
Airframe Height:

Landing Gear Dimensions
Landing Gear Base:	8.31 m	27.3 ft
Landing Gear Track:	3.96 m	13.0 ft

Cabin Dimensions
Cabin Internal Height:
Cabin Internal Length:
Cabin Internal Width:

Weights
Max Gross Weight (ground):	15,876 kg	35,000 lb
Max Gross Weight (airborne):
Max Take-off Weight:	15,876 kg	35,000 lb
Empty Weight:	10,180 kg	22,444 lb

Climb Performance
Max Rate of Climb:

Hover Performance
Hover Ceiling IGE:
Hover Ceiling OGE:

Limitations
Max Level Flight Speed:	315 km/h	170 kts
Never Exceed Speed:
Service Ceiling:

Range and Endurance
Max Range:	482 km	260 nm
Max Endurance:

Provided powerplant data is for uninstalled, sea level, static operations.

Powerplant
Number of engines:	2
Designation:	GE T64-GE-6/1 turbine
Manufacturer:	GE Aviation

Normal Ratings
Max continuous:
Take-off / rated:
Intermediate:
Maximum:

OEI Ratings
OEI contingency:
OEI continuous:
OEI 30-second:
OEI intermediate:

Main Rotor Characteristics
Diameter:	22.01 m	72.22 ft
RPM:
Direction of Rotation:	Unknown
Hub Type:	Fully articulated

Main Rotor Blade Characteristics
Blade Construction:
Blade Chord:
Blade Tip Geometry:
Blade Twist:
Number of Blades:	6

Main Rotor Derived Characteristics
Disc Area:	380.62 m²	4097.1 ft²
Disc Loading:	41.71 kg/m²	8.543 lb/ft²
Solidity:

Main Rotor Blade Derived Characteristics
Blade area per blade:
Tip Speed:

Tail Rotor Characteristics
Diameter:	4.88 m	16.00 ft
Configuration:	Unknown
Direction of Rotation:	Unknown
RPM:

Tail Rotor Blade Characteristics
Number of Blades:	4
Blade Construction:
Blade Chord:
Blade Twist:

Tail Rotor Derived Characteristics
Disc Area:	18.68 m²	201.1 ft²
Solidity:

Tail Rotor Blade Derived Characteristics
Tip Speed:
Blade Area (per blade):

References

References and sources used

S-65 / H-53 Product History

Vinny Devine, Sikorsky Archives
Sikorsky Archives News October 2007, 2013
Website

Related VFS Resources

Resources related to the CH-53A Sea Stallion, provided by the Vertical Flight Society.

Forum Proceedings

Vertiflite articles

Enter a search term in the box above.

Web files from vtol.org

Enter a search term in the box above.

Webpages from vtol.org

Enter a search term in the box above.

Images from the VFS Gallery

Enter a search term in the box above.

Refine / filter your search or find more resources

Related Public Resources

Resources related to the CH-53A Sea Stallion, provided by public sources across the internet.

Publicly-funded resources provided by the US Government

Search at NASA Technical Reports Server (NTRS).

Search at Defense Technical Information Center (DTIC).

Search at SciTech Connect (OSTI).

Public resources provided by select scholarly and academic sources

Search at European Rotorcraft Forum Document Repository.

Search at IOPScience.

Search at CiteSeerX.

Additional links

Search for at Google Scholar.

Search for at Bielefeld Academic Search Engine (BASE).

Search for at Semantic Scholar.

Search for at CORE (COnnecting REpositories).

Search for at JSTOR.

Images

Overview

Attribution

Number of engines:	2 Turbines
Max Level Flight Speed:	315 km/h	170 kts
Max Range:	482 km	260 nm
Max Endurance:

Main Rotor Diameter:	22.01 m	72.22 ft
Max Gross Weight (ground):	15,876 kg	35,000 lb