Developed in 1958, the Model 107 is an Amphibious transport prototype helicopter.  Designated YHC-1A in the US Army, under which the helicopter made its first flight as a military aircraft in August 1959.  Capable of operation in any weather condition, equipped with a Stability Augmentation System (SAS) device.

Source:   Paul Lambermont with Anthony Pirie.  Helicopters & Autogyros of the World.  Cassell & Company, 1959.  Pages 400-401.

Overview

Data on design, manufacture and status

Design authority: Vertol Aircraft Corporation

Primary manufacturer: Vertol Aircraft Corporation

Parent type: Vertol Model 107/CH-46

Aircraft status: No longer flying

Configuration

Primary flight and mechanical characteristics

VTOL type: Helicopter

Lift configuration: Tandem (Fore/aft) (x2)

Crew required: 2

Crew seating: Side-by-side

Landing gear: Wheels (non-retractable)

Layout and Dimensions

Data on aircraft size

Cabin Dimensions exclude flight deck.

Overall Dimensions
Overall Height: 5.13 m 16.8 ft
Overall Length: 25.40 m 83.3 ft
Overall Width: 15.24 m 50.0 ft
Airframe Dimensions
Airframe Length: 13.59 m 44.6 ft
Airframe Width: 4.42 m 14.5 ft
Airframe Height: 5.13 m 16.8 ft
Landing Gear Dimensions
Landing Gear Base: 7.59 m 24.9 ft
Landing Gear Track: 3.94 m 12.9 ft
Cabin Dimensions
Cabin Internal Height: 1.83 m 6.0 ft
Cabin Internal Length: 7.37 m 24.2 ft
Cabin Internal Width: 1.83 m 6.0 ft

Weights and Performance

Data on aircraft weight and flight characteristics

Cruise Speed: 150 mph (241.402 km/h)

Weights
Max Gross Weight (ground): 9,707 kg 21,400 lb
Max Gross Weight (airborne):  
Max Take-off Weight: 9,707 kg 21,400 lb
Empty Weight: 5,702 kg 12,571 lb
Useful Load: 4,005 kg 8,830 lb
Empty Weight Fraction: 0.587
Climb Performance
Max Rate of Climb: 7 m/s 1,401 fpm
Hover Performance
Hover Ceiling IGE:  
Hover Ceiling OGE:  
Limitations
Max Level Flight Speed: 261 km/h 141 kts
Never Exceed Speed:  
Service Ceiling: 4,508 m 14,790 ft
Range and Endurance
Max Range: 431 km 233 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: Lycoming T53-L-1 turbine
Manufacturer: Lycoming Engines
Normal Ratings
Max continuous:  
Take-off / rated: 641 kW 860 hp
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

May be folded for storage/transport

Main Rotor Characteristics
Diameter: 15.24 m 50.00 ft
RPM:  
Direction of Rotation: Counter-rotating
Hub Type: Fully articulated
Main Rotor Blade Characteristics
Blade Construction:
Blade Chord:  
Blade Tip Geometry: Flat
Blade Twist:  
Number of Blades: 3
Main Rotor Derived Characteristics
Disc Area: 182.41 m² 1963.6 ft²
Disc Loading: 26.61 kg/m² 5.450 lb/ft²
Solidity:  
Main Rotor Blade Derived Characteristics
Blade area per blade:  
Tip Speed:  

Primary Control Device

Data on primary control devices such as tail rotors

Tail Rotor Characteristics
Diameter:  
Configuration: Unknown
Direction of Rotation: Unknown
RPM:  
Tail Rotor Blade Characteristics
Number of Blades:  
Blade Construction: N/A
Blade Chord:  
Blade Twist:  
Tail Rotor Derived Characteristics
Disc Area:  
Solidity:  
Tail Rotor Blade Derived Characteristics
Tip Speed:  
Blade Area (per blade):  

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