Vertipedia - Mil Mi-28A

The Mi-28A is an antitank helicopter, a variant of the Mil Mi-28. It is quipped with a 30 mm gun moun, armor, and shock abosorbant seats and landing gear. The TV3-117VMA turboshaft engines have deflectors and separators for the prevention of dust ingestion.

Overview

Data on design, manufacture and status

Design authority: MVZ Mil

Primary manufacturer: MVZ Mil

Parent type: Mil Mi-28

Aircraft status: Status unknown

Configuration

Primary flight and mechanical characteristics

VTOL type: Helicopter

Lift devices: 1 Single main rotor

Dedicated control device: 1 Tail rotor

Crew required: 2 in Tandem arrangement

Landing gear: Wheels (non-retractable)

Key Characteristics

Data on key physical features

Aircraft Details

Data on aircraft configuration, weights, flight performance and equipment

Layout and Dimensions

Weights and Performance

Engine Details

Primary Lift Device

Primary Control Device

Overall Dimensions
Overall Height:	4.81 m	15.8 ft
Overall Length:	16.85 m	55.3 ft
Overall Width:	17.20 m	56.4 ft

Airframe Dimensions
Airframe Length:
Airframe Width:
Airframe Height:

Landing Gear Dimensions
Landing Gear Base:
Landing Gear Track:

Cabin Dimensions
Cabin Internal Height:
Cabin Internal Length:
Cabin Internal Width:

Cruise Speed: 260 km/h

Weights
Max Gross Weight (ground):	11,500 kg	25,353 lb
Max Gross Weight (airborne):
Max Take-off Weight:	11,500 kg	25,353 lb
Empty Weight:	7,890 kg	17,394 lb

Climb Performance
Max Rate of Climb:

Hover Performance
Hover Ceiling IGE:
Hover Ceiling OGE:	3,600 m	11,811 ft

Limitations
Max Level Flight Speed:	300 km/h	162 kts
Never Exceed Speed:
Service Ceiling:	5,750 m	18,865 ft

Range and Endurance
Max Range:	460 km	248 nm
Max Endurance:

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

Powerplant
Number of engines:	2
Designation:	Motor Sich TV3-117VMA turbine
Manufacturer:	Motor Sich

Normal Ratings
Max continuous:
Take-off / rated:	1640 kW	2198 hp
Intermediate:	1618 kW	2169 hp
Maximum:

OEI Ratings
OEI contingency:	1765 kW	2366 hp
OEI continuous:
OEI 30-second:
OEI intermediate:	1618 kW	2169 hp

Main Rotor Characteristics
Diameter:	17.20 m	56.43 ft
RPM:
Direction of Rotation:	Clockwise
Hub Type:	Elastomeric Bearing

Main Rotor Blade Characteristics
Blade Construction:	Composite
Blade Chord:
Blade Tip Geometry:	Conventional
Blade Twist:
Number of Blades:	5

Main Rotor Derived Characteristics
Disc Area:	232.35 m²	2501.1 ft²
Disc Loading:	49.49 kg/m²	10.137 lb/ft²
Solidity:

Main Rotor Blade Derived Characteristics
Blade area per blade:
Tip Speed:

Tail Rotor Characteristics
Diameter:
Configuration:	Pusher
Direction of Rotation:	Top blade aft
RPM:

Tail Rotor Blade Characteristics
Number of Blades:	4
Blade Construction:	Asymmetrical X-shape
Blade Chord:
Blade Twist:

Tail Rotor Derived Characteristics
Disc Area:
Solidity:

Tail Rotor Blade Derived Characteristics
Tip Speed:
Blade Area (per blade):

References

References and sources used

Mil Moscow Helicopter Plant 50 Years

Lyubimaya Kniga
1998 (page 240)
Book

Russia's Arms Catalog: Volume II (Air Force)

Military Parade Ltd.
1996 (page 169)
Book

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Number of engines:	2 Turbines
Max Level Flight Speed:	300 km/h	162 kts
Max Range:	460 km	248 nm
Max Endurance:

Main Rotor Diameter:	17.20 m	56.43 ft
Max Gross Weight (ground):	11,500 kg	25,353 lb