Originally designed by Hughes Helicopters and designated the Hughes Model 77, the AH-64 resulted from the US Army Advanced Attack Helicopter Competition. It was developed beginning in the 1970s by Hughes Helicopters as a replacement for the Bell AH-1 Cobra. The prototype YAH-64 first flew in 1975.

The primary mission for the Apache was as a tank killer to deter the Soviet threat to Europe at that time. The first production Apache was delivered to the U.S. Army in January 1984 and first saw combat in 1989 during Operation Just Cause in Panama. Armaments included the Hellfire anti-tank missile, Hydra 70mm unguided rockets and a 30mm chain gun mounted under the nose.

The AH-64A is still in service, but has been largely replaced by the AH-64D Longbow Apache which entered service in 1997. Its missions have expanded to also include armed reconnaissance, armed escort, and close combat support.


Data on design, manufacture and status

Latest or last design authority: The Boeing Company
Originally designed by Hughes Helicopters

Latest or last primary manufacturer: The Boeing Company
Originally manufactured by Hughes Helicopters

Parent type: Boeing AH-64 Apache

Aircraft status: Operational


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: Wheels (non-retractable)

Layout and Dimensions

Data on aircraft size

Overall Dimensions
Overall Height: 4.66 m 15.3 ft
Overall Length: 17.73 m 58.2 ft
Overall Width: 14.63 m 48.0 ft
Airframe Dimensions
Airframe Length: 14.96 m 49.1 ft
Airframe Width: 5.23 m 17.1 ft
Airframe Height: 3.52 m 11.5 ft
Landing Gear Dimensions
Landing Gear Base: 10.59 m 34.7 ft
Landing Gear Track: 2.03 m 6.7 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): 9,525 kg 21,000 lb
Max Gross Weight (airborne): 9,525 kg 21,000 lb
Max Take-off Weight: 9,525 kg 21,000 lb
Empty Weight: 4,881 kg 10,760 lb
Useful Load: 4,645 kg 10,240 lb
Empty Weight Fraction: 0.512
Climb Performance
Max Rate of Climb: 13 m/s 2,500 fpm
Hover Performance
Hover Ceiling IGE: 4,572 m 15,000 ft
Hover Ceiling OGE: 3,505 m 11,500 ft
Max Level Flight Speed: 296 km/h 160 kts
Never Exceed Speed: 365 km/h 197 kts
Service Ceiling: 6,401 m 21,000 ft
Range and Endurance
Max Range: 482 km 260 nm
Max Endurance: 2 hrs 2 hrs

Engine Details

Aircraft powerplant (lift and/or propulsion)

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

Number of engines: 2
Designation: GE T700-GE-701 turbine
Manufacturer: GE Aviation
Normal Ratings
Max continuous:  
Take-off / rated: 1265 kW 1696 hp
OEI Ratings
OEI contingency:  
OEI continuous:  
OEI 30-second: 1285 kW 1723 hp
OEI intermediate:  

Primary Lift Device

Data on primary lift devices such as main rotors

The multiple spar design of the AH-64A main rotor blade allows the blade to survive an impact from a 23mm high-explosive round, while still retaining sufficient blade life to permit safe flight and landing.

Main Rotor Characteristics
Diameter: 14.63 m 48.00 ft
RPM: 284.0 rpm 284.0 rpm
Direction of Rotation: Counterclockwise
Hub Type: Offset hinge articulated rotor with static mast and strap retention
Main Rotor Blade Characteristics
Blade Construction: Five stainless steel / fiberglass spars with stainless steel leading edge. Nomex honeycomb aft section covered in fiberglass.
Blade Chord: 0.533 m 1.75 ft
Blade Tip Geometry: 20° swept tip
Blade Twist: -0.157 rad -9.000 deg
Number of Blades: 4
Main Rotor Derived Characteristics
Disc Area: 168.10 m² 1809.5 ft²
Disc Loading: 56.66 kg/m² 11.606 lb/ft²
Solidity: 0.0928
Main Rotor Blade Derived Characteristics
Blade area per blade: 3.90 m² 42.0 ft²
Tip Speed: 217.55 m/s 713.7 fps

Primary Control Device

Data on primary control devices such as tail rotors

"Scissor"-type tail rotor features unequally-spaced blade pairs (set at 55° / 125° to each other) so as to improve air transport portability and reduce noise.

Tail Rotor Characteristics
Diameter: 2.79 m 9.17 ft
Configuration: Pusher
Direction of Rotation: Top blade aft
RPM: 1341 rpm 1341 rpm
Tail Rotor Blade Characteristics
Number of Blades: 4
Blade Construction: Stainless steel and aluminum spars with titanium fork
Blade Chord: 0.253 m 0.83 ft
Blade Twist: -0.14 rad -8.0 deg
Tail Rotor Derived Characteristics
Disc Area: 6.13 m² 66.0 ft²
Solidity: 0.2306
Tail Rotor Blade Derived Characteristics
Tip Speed: 196.22 m/s 643.8 fps
Blade Area (per blade): 0.353 m² 3.80 ft²

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