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NOTAR system precision attitude/directional control
Powerful: Useful load at maximum gross weight
1,764 pounds (800 kg) internal
2,264 pounds (1027 kg) external
HOGE at 6,000 ft (1829 m) @ISA HIGE at 11,200 ft (3414 m) @ISA
ROC of 1,775 feet per minute (9.0 m/s)
Versatile: 20,000 foot (6096 m) Maximum Operating Altitude
Operating temperature range of -40°C to +52°C
15 degree slope landing
Safety: Elimination of tail rotor hazards
Environment: Quiet operations – Flyover at 500 feet AGL = 72.5 dbA
SYSTEM DESCRIPTION
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11.1 MD 520N® Design Description
The MD 520N® is a fast, agile, lightweight, turbine powered, all-purpose helicopter. Advanced
technology has been used in the design and construction of the aircraft, resulting in excellent
speed capabilities, high payload-to-empty-weight ratio, passenger/crew safety and handling and
performance capabilities.
The MD 520N® has been designed to allow a wide variety of rapid configuration options. The
aircraft may be converted rapidly from a personnel transport to a utility cargo configuration. Typical
uses include:
Airborne Law Enforcement
Search and rescue
Surveillance and crowd control
Aerial survey, patrol and photographic missions
Forestry and fire fighting applications
The MDHI MD 520N® helicopter is a turbine powered, rotary-wing aircraft constructed primarily of
aluminum alloy while the NOTAR® system components are primarily graphite composites. The
main rotor is a fully articulated five-bladed system that provides excellent control and
maneuverability characteristics. Power from the turboshaft engine is transmitted through the main
drive shaft to the main rotor transmission. The main transmission drives an intermediate gearbox to
the NOTAR® system fan. An over-running (one-way) clutch placed between the engine and main
rotor transmission, permits freewheeling of the rotor system during autorotation.
The airframe structure is egg-shaped and provides very clean aerodynamic lines. A rigid, threedimensional
truss-type structure increases crew safety by means of its roll bar design and reduces
the potential for airframe collapse into the crew and passenger compartments. The airframe
structure is designed to be energy absorbing while maintaining rotor hub integrity.
11.1.1 MD 520N® Outside Dimensions
The fuselage is a semi-monoque structure that is divided into two main sections. The forward
section is composed of the pilot/co-pilot compartment and directly aft, separated by a bulkhead, a
cabin compartment. The pilot compartments equipped with seats for the pilot and either two
passengers on the co-pilot. A canopy of transparent tinted acrylic panels provides excellent
visibility.
An instrument panel is located forward of the seat structure along the aircraft centerline. The panel
incorporates standard flight and engine instruments in addition to warning and caution lights. The
panel also contains adequate space for avionics and flight instruments. An optional “slant panel” is
available that increases the panel space available when extensive avionics suites are selected or
when armament systems are installed.
SYSTEM DESCRIPTION
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SYSTEM DESCRIPTION
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11.1.2 MD 520N® Inboard Profile and Features
The crashworthy designed fuselage structure beneath the pilot/copilot floor contains space for
the aircraft battery and provision for small cargo storage or installation of avionics equipment.
Access to the compartments is through two floor panels.
The cargo compartment is the center of the aircraft contains provisions for the installation of
passenger seats, auxiliary fuel tanks or cargo/baggage. During cargo-carrying operations, the
compartment floor serves as the cargo deck. The cargo floor is designed to accommodate a
range of cargo requirements.
The aft section includes the structure of the tailboom attachment, NOTAR® system fan and the
engine compartment. Access to the engine compartment is provided through clamshell doors
contoured to the shape of the fuselage.
The lower section is divided by the center “keel beam” and provides housing for the two fuel
cells containing a total of 64 U.S. gallons (242 l) of fuel.
Five-Blade Fully Articulated Main Rotor
Five-Place Seating Capacity
Simple Mechanical Controls
Crashworthy A-Frame Truss
with Integral Crew Seats
Static Mast Rotor Support
Outstanding Outward Visibility
425 shp Drive System
Flat Cargo Floor
Rolls-Royce 250-C20R 450 shp Turbine Engine
NOTA¨R Anti-Torque System
SYSTEM DESCRIPTION
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MD500 Series TechDescription Feb09(13)
