The AH-1Q was an anti-armor version of the AH-1G with an M28A1E1 turret (later standardized as the M28A2), XM65 TOW/Cobra missile subsystem, infrared sight, and XM128 helmet sight subsystem (HSS). The AH-1Q was equipped to fire eight Hughes BGM-71 130mm TOW (Tube-Launched, Optically Tracked, Wire Command-Link Guided) anti-tank missiles mounted in a pair of two-round pods on the outboard pylons. The AH-1Q was the first Cobra to feature the snub-nosed Telescopic Sight Unit (TSU). Considered an interim development, the first AH-1Qs were delivered to the Army in 1973, with initial production units entering service in early 1975. 93 AH-1Qs were produced or converted from AH-1Gs; all were subsequently converted to the AH-1S configuration.


Data on design, manufacture and status

Design authority: Bell Helicopter Textron, Inc.

Primary manufacturer: Bell Helicopter Textron, Inc.

Parent type: Bell Model 209/AH-1 Cobra

Aircraft status: No longer flying


Primary flight and mechanical characteristics

VTOL type: Helicopter

Lift configuration: Single main rotor

Dedicated control device: Tail rotor

Crew required: 2

Crew seating: Tandem

Landing gear: Skids

Layout and Dimensions

Data on aircraft size

Airframe width includes stub wings. While there is some variation among Cobra variants, most fuselage widths without stub wings are .914 m (3 ft).

Overall Dimensions
Overall Height: 4.10 m 13.5 ft
Overall Length: 16.14 m 53.0 ft
Overall Width: 13.41 m 44.0 ft
Airframe Dimensions
Airframe Length: 13.77 m 45.2 ft
Airframe Width: 3.15 m 10.3 ft
Airframe Height: 3.11 m 10.2 ft
Landing Gear Dimensions
Landing Gear Base: 3.27 m 10.7 ft
Landing Gear Track: 2.13 m 7.0 ft
Cabin Dimensions
Cabin Internal Height:  
Cabin Internal Length:  
Cabin Internal Width:  

Weights and Performance

Data on aircraft weight and flight characteristics

Max Gross Weight (ground): 4,309 kg 9,500 lb
Max Gross Weight (airborne):  
Max Take-off Weight: 4,309 kg 9,500 lb
Empty Weight: 2,858 kg 6,301 lb
Useful Load: 1,451 kg 3,199 lb
Empty Weight Fraction: 0.663
Climb Performance
Max Rate of Climb: 9 m/s 1,680 fpm
Hover Performance
Hover Ceiling IGE:  
Hover Ceiling OGE:  
Max Level Flight Speed: 275 km/h 149 kts
Never Exceed Speed: 352 km/h 190 kts
Service Ceiling: 3,505 m 11,500 ft
Range and Endurance
Max Range: 583 km 315 nm
Max Endurance:  

Engine Details

Aircraft powerplant (lift and/or propulsion)

Provided powerplant data is for uninstalled, sea level, static operations.

Number of engines: 1
Designation: Lycoming T53-L-13 turbine
Manufacturer: Lycoming Engines
Normal Ratings
Max continuous: 933 kW 1250 hp
Take-off / rated: 1045 kW 1400 hp
OEI Ratings
OEI contingency:  
OEI continuous:  
OEI 30-second:  
OEI intermediate:  

Primary Lift Device

Data on primary lift devices such as main rotors

B540 blade for two-bladed Cobra main rotors.

Main Rotor Characteristics
Diameter: 13.40 m 43.96 ft
RPM: 324.0 rpm 324.0 rpm
Direction of Rotation: Counterclockwise
Hub Type: Flex-beam, stiff-in-plane teetering hub
Main Rotor Blade Characteristics
Blade Construction: Bonded aluminum spar and skin; nomex honeycomb core
Blade Chord: 0.686 m 2.25 ft
Blade Tip Geometry: Square-edged tips
Blade Twist: -0.175 rad -10.000 deg
Number of Blades: 2
Main Rotor Derived Characteristics
Disc Area: 141.03 m² 1518.0 ft²
Disc Loading: 30.56 kg/m² 6.258 lb/ft²
Solidity: 0.0652
Main Rotor Blade Derived Characteristics
Blade area per blade: 4.59 m² 49.5 ft²
Tip Speed: 227.33 m/s 745.8 fps

Primary Control Device

Data on primary control devices such as tail rotors

Tail Rotor Characteristics
Configuration: Tractor
Direction of Rotation: Top blade aft
Tail Rotor Blade Characteristics
Number of Blades: 2
Blade Construction:  
Blade Chord:  
Blade Twist:  
Tail Rotor Derived Characteristics
Disc Area:  
Tail Rotor Blade Derived Characteristics
Tip Speed:  
Blade Area (per blade):  

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