A derivative of the YHC-1A with more cabin space, meeting the requirement of carrying an entire platoon [Ref Hirschberg. The American Helicopter, pg 50].  Developed in 1959, the YHC-1B Chinook was redesignated CH-47A in 1962; the commercial version designation is Model 234.  The helicopter had won a competition for 'Army medium transport helicopter June 1959'; the cabin capacity is either 32 troops, 24 litters, or 2 to 3 U.S. customary tons of cargo [Ref 312].

Overview

Data on design, manufacture and status

Design authority: The Boeing Company - Vertol Division

Primary manufacturer: The Boeing Company - Vertol Division

Parent type: Boeing-Vertol Model 234/H-47 Chinook

Aircraft status: No longer flying

Configuration

Primary flight and mechanical characteristics

VTOL type: Helicopter

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

Crew required: 3

Crew seating: Side-by-side

Landing gear: Wheels (non-retractable)

Layout and Dimensions

Data on aircraft size

Overall Dimensions
Overall Height:  
Overall Length: 30.14 m 98.9 ft
Overall Width: 17.37 m 57.0 ft
Airframe Dimensions
Airframe Length: 15.54 m 51.0 ft
Airframe Width: 3.78 m 12.4 ft
Airframe Height: 5.65 m 18.6 ft
Landing Gear Dimensions
Landing Gear Base: 7.87 m 25.8 ft
Landing Gear Track:  
Cabin Dimensions
Cabin Internal Height: 1.98 m 6.5 ft
Cabin Internal Length: 9.30 m 30.5 ft
Cabin Internal Width: 2.29 m 7.5 ft

Weights and Performance

Data on aircraft weight and flight characteristics

Cruise Speed: 144 mph (231.746 km/h)

Weights
Max Gross Weight (ground): 14,969 kg 33,000 lb
Max Gross Weight (airborne):  
Max Take-off Weight: 14,969 kg 33,000 lb
Empty Weight: 8,134 kg 17,932 lb
Useful Load: 6,835 kg 15,067 lb
Empty Weight Fraction: 0.543
Climb Performance
Max Rate of Climb: 8 m/s 1,570 fpm
Hover Performance
Hover Ceiling IGE: 579 m 1,900 ft
Hover Ceiling OGE:  
Limitations
Max Level Flight Speed: 267 km/h 144 kts
Never Exceed Speed:  
Service Ceiling: 2,164 m 7,100 ft
Range and Endurance
Max Range: 185 km 100 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 T55-L-5 turbine
Manufacturer: Lycoming Engines
Normal Ratings
Max continuous: 1642 kW 2201 hp
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

Main Rotor Characteristics
Diameter: 17.37 m 57.00 ft
RPM:  
Direction of Rotation: Counter-rotating
Hub Type:
Main Rotor Blade Characteristics
Blade Construction:
Blade Chord: 0.810 m 2.66 ft
Blade Tip Geometry:
Blade Twist:  
Number of Blades: 3
Main Rotor Derived Characteristics
Disc Area: 237.07 m² 2551.8 ft²
Disc Loading: 31.57 kg/m² 6.466 lb/ft²
Solidity: 0.0890
Main Rotor Blade Derived Characteristics
Blade area per blade: 7.04 m² 75.7 ft²
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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