Bell 205 UH-1 Iroquois 'Huey'
US military designations: UH-1D/H/V, EH-1H and HH-1H
Canadian military designations: CH-118 Iroquois
Spanish military designation: HU.10B
TYPE:
- Single-engined, general purpose, medium-lift helicopter.
PROGRAMME:
- After the success of the Model 204, an improved version Model 205 was proposed in 1960 by the US Army.
- A contract followed in July 1960 for seven YUH-1D service test helicopters.
- Although similar to the earlier Model 204, the Model 205 retained the Lycoming T53-L-11 turboshaft engine, introduced a longer fuselage, increased cabin space to accommodate more passengers as well as other changes.
- The first YUH-1D was flown on August 16 1961 and the type was ordered into production for the US Army with the designation UH-1D.
- A total of 2,008 UH-1D were built for the US Army
- In addition to military exports by Bell, a multi-role utility helicopter for both civil and military use was extensively built in Italy as the Agusta-Bell AB 205.
- Dornier in Germany completed 352 helicopters equivalent to the UH-1D, which serves with the Luftwaffe and Heeresfliegertruppen.
- In Taiwan, AIDC built 118 helicopters similar to the UH-1H for the Chinese Nationalist Army.
- In Japan, Fuji continues to build the Model 205 as the Fuji-Bell HU-1H.
VERSIONS:
CH-118:
- Similar to UH-1H, for Mobile Command in the Canadian Armed Forces.
- Was originally designated CUH-1H.
EH-1H:
- Electronic countermeasures configuration, with the Quick Fix I airborne communications interception, emitter locating and jamming system, including an AN/APR-39(V)2 radar warning receiver, XM130 chaff/flare dispenser and AN/ALQ-144 infrared jammer.
HH-1H:
- 30 HH-1H aircrafts were ordered by the USAF (generally similar to the UH-1H) for use as local base rescue helicopters.
- Under product improvement programmes, these have gained new avionics and equipment, and new composite main rotor blades, as well as Doppler navigation and an improved cockpit.
UH-1D:
- This US Army version of the Model 205 Iroquois has an 820 kW (1,100 shp) Lycoming T53-L-11 turboshaft, 14.63 m (48 ft) rotor, normal fuel capacity of 832 litres (220 US gallons; 183 Imp gallons) and overload capacity of 1,968 litres (520 US gallons; 433 Imp gallons).
- Relocation of the fuel cells increases cabin space to 6.23 m3 (220 cu ft), providing sufficient room for a pilot and 12 troops, or six litters and a medical attendant, or 1,815 kg (4,000 lb) of freight.
UH-1H:
- Following the replacement of the original T53-L-11 turboshaft by the 1,044 kW (1,400 shp) T53-L-13, this version of the Model 205 for the US Army was designated UH-1H.
UH-1V:
- Approximately 220 UH-1Hs were converted by the US Army into a medevac version.
- Avionics and equipment in this version include a radio altimeter, AEL AN/ARN-124 DME, glide slope and rescue hoist.
DESIGN FEATURES:
The following details refer specifically to the military UH-1H:
- A two-blade semi-rigid main rotor.
- Stabilising bar above and at right angles to main rotor blades.
- Two-blade all-metal tail rotor. Shaft drive to both main and tail rotor.
STRUCTURE:
- Interchangeable main blades built up of extruded aluminium spars and laminates.
- Tail rotor blades of honeycomb construction. Blades do not fold.
- The fuselage is a conventional all-metal semi-monocoque structure.
POWER PLANT:
- One 1,044 kW (1,400 shp) Textron Lycoming T53-L-13 turboshaft, mounted aft of the transmission on top of the fuselage and enclosed in cowlings.
- Five interconnected rubber fuel cells, total capacity of 844 litres (223 US gallons; 186 Imp gallons), of which 799 litres (211 US gallons; 176 Imp gallons) are usable.
- Overload fuel capacity of 1,935 litres (511 US gallons; 425 Imp gallons) usable, obtained by installation of a kit comprising of two 568 litre (150 US gallon; 125 Imp gallon) internal auxiliary fuel tanks interconnected with the basic fuel system.
ACCOMMODATION:
- Pilot and 11 to 14 troops, or six litters and a medical attendant, or 1,759 kg (3,880 lb) of freight.
- Crew doors open forward and are jettisonable. Two doors on each side of cargo compartment; front door is hinged to open forward and is removable, rear door slides aft.
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| DIMENSIONS: |
|---|
| Main rotor diameter: | 14.63 m | 48 ft 0 in |
| Tail rotor diameter: | 2.59 m | 8 ft 6 in |
| Length: | |
| | Overall (rotors turning): | 17.62 m | 57 ft 9 5/8 in |
| Fuselage: | 12.77 m | 41 ft 10 3/4 in |
| Height: | | |
| Overall, tail rotor turning (excl fin tip antenna): | 4.41 m | 14 ft 5 1/2 in |
| To top of main rotor head: | 3.60 m | 11 ft 9 3/4 in |
| AREAS: |
|---|
| Main rotor disc: | 168.11 m2 | 1,809.56 sq ft |
| Tail rotor disc: | 5.27 m2 | 56.7 sq ft |
| WEIGHTS AND LOADINGS: |
|---|
| Weight empty: | 2,363 kg | 5,210 lb |
| Max T-O and landing weight: | 4,309 kg | 9,500 lb |
| Max payload: | 1,759 kg | 3,880 lb |
| PERFORMANCE (at max T-O weight): |
|---|
| Max speed: | 110 kt | 204 km/h; 127 mph |
| Max rate of climb at S/L: | 488 m/min | 1,600 ft/min |
| Service ceiling: | 3,840 m | 12,600 ft |
| Max range at S/L: | 276 n miles | 511 km; 318 miles |
