UH1

BELL UH-1 Iroquois

Aircraft
Name
UH-1 Iroquois
Manufacturer
Wing
Rotary
Position
Two-blade main rotor
Tail
Two-blade tail rotor
WTC
L
APC
A
Type Code
H1T
Engine
Turboshaft
Engine Count
Single
Position
Above cabin
Landing gear
Skids
Manufacturered as
UNC Ultra Huey
PANHA Shabaviz 2-75
GLOBAL Huey 800
FUJI UH-1
FUJI 204
FUJI 205
DORNIER UH-1
BELL UH-1B Iroquois
BELL UH-1A Iroquois
BELL UH-1L Iroquois
BELL 210
BELL 205
BELL 204
BELL Iroquois
BELL Huey
BELL HH-1 Iroquois
BELL EH-1 Iroquois
BELL CH-118
BELL CUH-1H
BELL UH-1C Iroquois
BELL TH-1H Iroquois
BELL SH-1 Iroquois
BELL TH-1E Iroquois
BELL TH-1F Iroquois
BELL TH-1L Iroquois
BELL UH-1F Iroquois
BELL UH-1V Iroquois
BELL UH-1M Iroquois
BELL UH-1H Iroquois
BELL UH-1E Iroquois
BELL UH-1D Iroquois
AIDC UH-1
AGUSTA Hkp3
AGUSTA AB-204
AGUSTA AB-205

UH1

The UH-1 Iroquois is a military helicopter powered by a single, turboshaft engine, with a two-bladed main rotor and tail rotor. The helicopter was developed by Bell Helicopter to meet the United States Army's requirement for a medical evacuation and utility helicopter in 1952, and first flew on 20 October 1956. Ordered into production in March 1960, the UH-1 was the first turbine-powered helicopter to enter production for the United States military, and more than 16,000 have been produced worldwide.

Technical Data
Wing span (metric)
14.63 m
Length (metric)
17.62 m
Height (metric)
4.42 m
Powerplant

1 x Lycoming T53-L-11 turboshaft, 1,100 shp (820 kW).

Engine Model(s)
Lycoming T53
Indicative Performance Data
Take-Off
V2
n/a
Distance
n/a
MTOW
4309 kg
Initial Climb (to 5000 ft)
IAS
60 kts
ROC
1755 ft/min
Initial Climb (to FL150)
IAS
80 kts
ROC
1000
Initial Climb (to FL240)
IAS
80 kts
ROC
1000 ft/min
MACH Climb
MACH
n/a
ROC
n/a
Cruise
TAS
110 kts
MACH
n/a
Ceiling
190
Range
275 NM
Initial Descent (to FL240)
MACH
n/a
ROD
n/a
Descent (to FL100)
IAS
110 kts
ROD
1200 ft/min
Descent (FL100 & below)
IAS
n/a
MCS
n/a
ROD
n/a
Approach
Vapp (IAS)
40 kts
Distance
n/a

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