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].
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
VTOL type: Helicopter
Lift configuration: Tandem (Fore/aft) (x2)
Crew required: 3
Crew seating: Side-by-side
Landing gear: Wheels (non-retractable)
Overall Dimensions | ||
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Overall Height: | ||
Overall Length: | 30.14 m | 98.9 ft |
Overall Width: | 17.37 m | 57.0 ft |
Airframe Dimensions | ||
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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 | ||
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Landing Gear Base: | 7.87 m | 25.8 ft |
Landing Gear Track: |
Cabin Dimensions | ||
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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 |
Cruise Speed: 144 mph (231.746 km/h)
Weights | ||
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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 | ||
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Max Rate of Climb: | 8 m/s | 1,570 fpm |
Hover Performance | ||
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Hover Ceiling IGE: | 579 m | 1,900 ft |
Hover Ceiling OGE: |
Limitations | ||
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Max Level Flight Speed: | 267 km/h | 144 kts |
Never Exceed Speed: | ||
Service Ceiling: | 2,164 m | 7,100 ft |
Range and Endurance | ||
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Max Range: | 185 km | 100 nm |
Max Endurance: |
Provided powerplant data is for uninstalled, sea level, static operations.
Powerplant | ||
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Number of engines: | 2 | |
Designation: | Lycoming T55-L-5 turbine | |
Manufacturer: | Lycoming Engines |
Normal Ratings | ||
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Max continuous: | 1642 kW | 2201 hp |
Take-off / rated: | ||
Intermediate: | ||
Maximum: |
OEI Ratings | ||
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OEI contingency: | ||
OEI continuous: | ||
OEI 30-second: | ||
OEI intermediate: |
Main Rotor Characteristics | ||
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Diameter: | 17.37 m | 57.00 ft |
RPM: | ||
Direction of Rotation: | Counter-rotating | |
Hub Type: |
Main Rotor Blade Characteristics | ||
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Blade Construction: | ||
Blade Chord: | 0.810 m | 2.66 ft |
Blade Tip Geometry: | ||
Blade Twist: | ||
Number of Blades: | 3 |
Main Rotor Derived Characteristics | ||
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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 | ||
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Blade area per blade: | 7.04 m² | 75.7 ft² |
Tip Speed: |
Tail Rotor Characteristics | ||
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Diameter: | ||
Configuration: | Unknown | |
Direction of Rotation: | Unknown | |
RPM: |
Tail Rotor Blade Characteristics | ||
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Number of Blades: | ||
Blade Construction: | N/A | |
Blade Chord: | ||
Blade Twist: |
Tail Rotor Derived Characteristics | ||
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Disc Area: | ||
Solidity: |
Tail Rotor Blade Derived Characteristics | ||
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Tip Speed: | ||
Blade Area (per blade): |