Utility variant for the U.S. Marine Corps.

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: Operational

Configuration

Primary flight and mechanical characteristics

VTOL type: Helicopter

Lift configuration: Single main rotor

Dedicated control device: Tail rotor

Crew required: 2

Crew seating: Side-by-side

Landing gear: Wheels (all retractable)

Layout and Dimensions

Data on aircraft size

Overall Dimensions
Overall Height: 7.59 m 24.9 ft
Overall Length: 26.88 m 88.2 ft
Overall Width: 21.95 m 72.0 ft
Airframe Dimensions
Airframe Length: 20.48 m 67.2 ft
Airframe Width: 7.29 m 23.9 ft
Airframe Height: 5.18 m 17.0 ft
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 and Performance

Data on aircraft weight and flight characteristics

Weights
Max Gross Weight (ground): 19,051 kg 42,000 lb
Max Gross Weight (airborne):  
Max Take-off Weight: 19,051 kg 42,000 lb
Empty Weight: 12,020 kg 26,500 lb
Useful Load: 7,031 kg 15,500 lb
Empty Weight Fraction: 0.631
Climb Performance
Max Rate of Climb: 13 m/s 2,461 fpm
Hover Performance
Hover Ceiling IGE:  
Hover Ceiling OGE:  
Limitations
Max Level Flight Speed: 304 km/h 164 kts
Never Exceed Speed: 241 km/h 130 kts
Service Ceiling: 5,106 m 16,752 ft
Range and Endurance
Max Range: 543 km 293 nm
Max Endurance:  

Engine Details

Aircraft powerplant (lift and/or propulsion)

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

Powerplant
Number of engines: 2
Designation: GE T64-GE-413 turbine
Manufacturer: GE Aviation
Normal Ratings
Max continuous:  
Take-off / rated:  
Intermediate:  
Maximum:  
OEI Ratings
OEI contingency:  
OEI continuous:  
OEI 30-second:  
OEI intermediate:  

Primary Lift Device

Data on primary lift devices such as main rotors

Data shown is for the CH-53D Improved Rotor Blade introduced in 1971. Previous CH-53 main rotor blades were aluminum spars filled with pressurized nitrogen to detect cracks.

Main Rotor Characteristics
Diameter: 21.95 m 72.01 ft
RPM: 185.0 rpm 185.0 rpm
Direction of Rotation: Unknown
Hub Type:  
Main Rotor Blade Characteristics
Blade Construction: Titanium spar with Nomex honeycomb pockets wrapped in fiberglass epoxy
Blade Chord:  
Blade Tip Geometry:  
Blade Twist: -0.279 rad -16.000 deg
Number of Blades: 6
Main Rotor Derived Characteristics
Disc Area: 378.41 m² 4073.3 ft²
Disc Loading: 50.35 kg/m² 10.311 lb/ft²
Solidity:  
Main Rotor Blade Derived Characteristics
Blade area per blade:  
Tip Speed: 212.62 m/s 697.6 fps

Primary Control Device

Data on primary control devices such as tail rotors

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):  

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

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