<item><hi format=bold>Rotor system:</hi> main rotor diameter 44 ft 0 in (13.41 m); tail rotor diameter 8 ft 6 in (2.59 m); main rotor disc area 1,520.53 sq ft (141.26 m<su>2</su>); tail rotor disc area 56.8 sq ft (5.27 m<su>2</su>)
<item><hi format=bold>Fuselage and tail:</hi> length 41 ft 5 in (12.80 m); height 14 ft 4.5 in (4.39 m)
<item><hi format=bold>Powerplant:</hi> one General Electric T58-GE-3 rated at 1,290 shp (962 kW)
<item><hi format=bold>Weights:</hi> empty equipped 4,427 lb (2,008 kg); maximum take-off 9,000 lb (4,082 kg)
<item><hi format=bold>Fuel and load:</hi> internal fuel 410 US gal (1,552 liters); maximum payload 4,000 lb (1,814 kg)
<item><hi format=bold>Speed:</hi> maximum level speed at sea level 138 mph (222 km/h); cruising speed at sea level 130 mph (209 km/h)
<item><hi format=bold>Range:</hi> 380 miles (612 km)
<item><hi format=bold>Performance:</hi> maximum rate of climb at sea level 2,123 ft (647 m) per minute; service ceiling 6705 m (22,000 ft)
</list>
<hi style=hdr1>Bell—HH-1H</hi>
<list style=aflst>
<item><hi format=bold>generally similar to the UH-1F except in the following particulars:</hi>
<item><hi format=bold>Fuselage and tail:</hi> length overall, fuselage 41 ft 10.75 in (12.77 m); height 14 ft 6 in (4.42 m)
<item><hi format=bold>Powerplant:</hi> one Avco Lycoming T53-L-13 rated at 1,400 shp (1,044 kW)
<item><hi format=bold>Weight:</hi> maximum take-off 9,500 lb (4,309 kg)
<item><hi format=bold>Fuel and load:</hi> internal fuel 222 US gal (832 liters) increasable to 520 US gal (832 liters) with two overload tanks; maximum payload 3,880 lb (1,759 kg)
<item><hi format=bold>Range:</hi> 327 miles (526 km)
<item><hi format=bold>Performance:</hi> maximum rate of climb at sea level 1,760 ft (535 m) per minute; service ceiling about 19,400 ft (5,910 m)
</list>
<hi style=hdr1>Bell—UH-1N</hi>
<list style=aflst>
<item><hi format=bold>Rotor system:</hi> main rotor diameter 48 ft 2.25 in (14.69 m) with tracking tips; tail rotor diameter 8 ft 6 in (2.59 m); main rotor disc area 1,871.91 sq ft (173.90 m<su>2</su>) and tail rotor disc area 56.74 sq ft (5.27 m<su>2</su>)
<item><hi format=bold>Fuselage and tail:</hi> length overall, rotors turning 57 ft 3.25 in (17.46 m) and fuselage 42 ft 4.75 in (12.92 m); height overall 14 ft 10.25 in (4.53 m) and to top of rotor head 12 ft 10 in (3.91 m); tailplane span 9 ft 4.5 in (2.86 m)
<item><hi format=bold>Powerplant:</hi> one Pratt & Whitney Canada T400-CP-400 rated at 1,800 shp (1,342 kW) but flat-rated to 1,290 shp (962 kW) for take-off and 1,130 shp (842 kW) for continuous running
<item><hi format=bold>Weights:</hi> empty 6,143 lb (2,787 kg); maximum take-off 11,200 lb (5,080 kg)
<item><hi format=bold>Fuel and load:</hi> internal fuel 215 US gal (814 liters); maximum payload 4,000 lb (1,814 kg)
<item><hi format=bold>Speed:</hi> never exceed at sea level 161 mph (259 km/h); maximum cruising speed at sea level 142 mph (230 km/h)
<item><hi format=bold>Range:</hi> maximum standard at sea level 261 miles (420 km)
<item><hi format=bold>Performance:</hi> maximum rate of climb at sea level 1,320 ft (402 m) per minute; service ceiling 14,200 ft (4,330 m); hovering ceiling 11,000 ft (3,355 m) in ground effect.