AIDC UH-1H

The UH-1H has a two-bladed semi-rigid seesaw bonded all metal main rotor and a two-bladed rigid delta hinge bonded all metal tail rotor.

The UH-1H is powered by a single Lycoming T53-L-13B 1400 shp turboshaft engine.

The UH-1H was licenced for co-production at AIDC.

From 1970 to 1976, there were 118 UH-1H built for ROC Army.

Specifications

UH-1H

Crew

1–4
Capacity

3,880 pounds (1,760 kg) including 11-14 troops,

6 stretchers and attendants, or equivalent cargo
Length

57 ft 9+5⁄8 in (17.618 m) with rotors
Width

9 ft 6+1⁄2 in (2.908 m) (over skids)
Height

14 ft 5+1⁄2 in (4.407 m) (tail rotor turning)
Empty weight

5,210 lb (2,363 kg)
Gross weight

9,039 lb (4,100 kg) (mission weight)
Max take-off weight

9,500 lb (4,309 kg)
Powerplant

1 × Lycoming T53-L-13 turboshaft,

1,400 shp (1,000 kW) (limited to 1,100 shp (820 kW) by transmission)
Main rotor diameter

48 ft 0 in (14.63 m)
Main rotor area

1,809.56 sq ft (168.114 m2)
Performance

Maximum speed

127 mph (204 km/h, 110 kn) (at maximum take-off weight; also Vne at this weight)
Cruise speed

127 mph (204 km/h, 110 kn) (at 5,700 ft (1,700 m) at maximum takeoff weight)
Range

318 mi (511 km, 276 nmi) (with maximum fuel, no reserves, at sea level)
Service ceiling

12,600 ft (3,800 m) (at maximum takeoff weight)
Rate of climb

1,600 ft/min (8.1 m/s) at sea level (at maximum take-off weight)
Disc loading

5.25 lb/sq ft (25.6 kg/m2)
Power/mass

0.1159 hp/lb (0.1905 kW/kg)
Armament
various including

7.62 mm machine guns
2.75 in (70 mm) rocket pods

Sources

Aerospace Industrial Development Corporation (AIDC)