technical description/options

TECHNICAL DESCRIPTION
MD 600N
HELICOPTER
MD Helicopters, Inc.
Marketing and Sales
4555 E. McDowell Rd.
Mesa, AZ 85215
480-346-6130
www.mdhelicopters.com
sales@mdhelicopters.com
MISSION PROVEN, CHALLENGE READY
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TECHNICAL DESCRIPTION
MD 600N HELICOPTER
MD Helicopters, Inc.
4555 E. McDowell Rd
Mesa, Arizona
CAGE: 1KVX4
DUNS: 054313767
www.mdhelicopters.com
This Technical Description includes information and intellectual property that is the
property of MD Helicopters, Inc. (MDHI). It provides general information for
evaluation of the design, equipment, and performance of the MD 600N helicopter. The
information presented in this Technical Description does not constitute an offer and is
subject to change without notice. This proprietary information, in its entirety, shall not
be duplicated, used, or disclosed—directly or indirectly, in whole or in part—for any
purpose other than for evaluation. MD Helicopters, Inc. reserves the right to revise this
Technical Description at any time
MD 600N
Technical Description
MD14031211-600NTD
REPORT NO.:
NO. OF PAGES: 54
Use or disclosure of data in this Technical Description is subject to the restriction on
the cover page of this document.
ATTACHMENTS: None
Revision By
New
BAH
Approved
Date
Pages and/or Paragraphs Affected
11-Mar-14 All (Initial Issue)
MD 600N
Technical Description
Contents
1. FOREWORD ........................................................................................................ 1 2. KEY ADVANTAGES AND FEATURES ............................................................... 3 3. CERTIFICATION .................................................................................................. 5 4. DIMENSIONS, WEIGHT, AND MISSION CONFIGURATION.............................. 7 4.1 EXTERNAL DIMENSIONS.............................................................................................. 7 4.2 INTERNAL DIMENSIONS ............................................................................................... 7 4.3 WEIGHT ..................................................................................................................... 9 4.4 CONFIGURATIONS ...................................................................................................... 9 5. MD 600N SINGLE-ENGINE HELICOPTER ....................................................... 11 5.1 SYSTEM DESCRIPTION ............................................................................................. 11 5.2 STANDARD EQUIPMENT ............................................................................................ 13 5.3 MD 600N OPTIONAL EQUIPMENT ............................................................................. 14 5.4 FUSELAGE ............................................................................................................... 16 5.5 EXTERIOR ................................................................................................................ 18 5.6 EXTERNAL LIGHTING ................................................................................................ 18 5.7 INTERIOR ................................................................................................................. 18 5.7.1 Cockpit .................................................................................................................... 18 5.7.2 Cabin Compartment ................................................................................................ 20 5.7.3 Engine Compartment .............................................................................................. 20 5.8 SYSTEMS ................................................................................................................. 20 5.8.1 Fuel System ............................................................................................................ 20 5.8.2 Propulsion System .................................................................................................. 21 5.8.3 Engine Controls ....................................................................................................... 21 5.8.4 Fire Detection System ............................................................................................. 21 5.8.5 Drive System ........................................................................................................... 22 5.8.6 Rotor System........................................................................................................... 24 5.8.7 NOTAR® Anti-Torque System ................................................................................. 25 5.8.8 Flight Control System .............................................................................................. 26 5.8.9 Yaw Stability Augmentation System ....................................................................... 26 5.8.10 Electrical System ..................................................................................................... 26 5.8.11 Environmental Control System................................................................................ 26 Report No. MD14031211-600NTD
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MDHI PROPRIETARY
MD 600N
Technical Description
5.8.12 Monitoring Instrumentation ...................................................................................... 27 5.8.13 Caution / Warning Annunciators ............................................................................. 27 5.8.14 Avionics / Communications ..................................................................................... 28 5.8.15 Next-Generation Electronic Flight Instrument System ............................................ 28 6. PERFORMANCE SPECIFICATIONS ................................................................ 29 6.1 MD 600N – ROLLS-ROYCE MODEL 250-C47M TURBOSHAFT ENGINE ....................... 29 6.2 ENVIRONMENTAL IMPACT.......................................................................................... 30 6.3 SAFETY.................................................................................................................... 30 6.4 CRASHWORTHINESS ................................................................................................. 33 6.5 HUMAN SYSTEMS INTERFACE ................................................................................... 33 7. MAINTENANCE AND SERVICING .................................................................... 37 7.1 MAINTENANCE ......................................................................................................... 37 7.2 SERVICING ............................................................................................................... 39 THE MD 600N HAS BUILT-IN STEPS TO PROVIDE ACCESS TO THE MAIN ROTOR HEAD
WITHOUT EXTERNAL GROUND SUPPORT EQUIPMENT ................................................ 40 7.3 HOURLY COST ......................................................................................................... 42 8. PRODUCT SUPPORT ....................................................................................... 45 8.1 TRAINING ................................................................................................................. 45 8.1.1 Pilot Training ........................................................................................................... 45 8.1.2 Transition Flight Training ......................................................................................... 45 8.1.3 Recurrent Flight Training ......................................................................................... 45 8.1.4 Maintenance Training .............................................................................................. 46 8.2 WARRANTY .............................................................................................................. 46 8.2.1 Warranty Claims ...................................................................................................... 46 8.3 SERVICE CENTERS ................................................................................................... 47 8.4 FIELD SERVICE......................................................................................................... 47 Report No. MD14031211-600NTD
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MDHI PROPRIETARY
MD 600N
Technical Description
1. FOREWORD
This document presents basic technical description of the eight-place MD Helicopters, Inc.
(MDHI) MD 600N helicopter built in Mesa, Arizona, USA. It is designed to provide high-level
technical information of the helicopter, advantages / features, and configurations. For more
detailed information, an MD 600N Product Specification is available by contacting one of the
Sales Team Members listed below.
The MD 600N turbine engine helicopter provides a variety of mission applications ranging from
geophysical surveys to air medical services and police surveillance. The 808-shp Rolls-Royce
Model 250-C47M turbine-engine-powered MD 600N includes a fully articulated six-blade main
rotor system for excellent control and maneuverability, and an advanced NOTAR® anti-torque
system for reduced pilot workload and external noise levels..
The MD 600N is certified for single pilot operation under visual flight rules / visual
meteorological conditions.
MD Helicopter, Inc. Sales and Business Development
SALES
Phone: 480.346.6474
FAX: 480.346.6339
E-Mail: sales@mdhelicopters.com
Report No. MD14031211-600NTD
BUSINESS DEVELOPMENT
Andy Pillado
Director, Business Development
Phone: (480) 346.6532
Cell: (480) 435.3996
Fax: (480) 346.6818
E-Mail: andy.pillado@mdhelicopters.com
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MDHI PROPRIETARY
MD 600N
Technical Description
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MDHI PROPRIETARY
MD 600N
Technical Description
2. KEY ADVANTAGES AND FEATURES
The MDHI MD 600N is a single turbine engine, rotary-wing aircraft. It has a cruising speed of
134 knots (248 kph / 154 mph), with a useful internal load at maximum gross weight is 2,000
pounds (907 kg). Hover out of ground effect is 6,000 feet (1,829 m) and hover in ground effect is
11,100 feet (3,383 m). The rate of climb at maximum gross weight is 1,350 feet (6.9 m/sec). The
maximum operating altitude is 20,000 feet (6,097 m) with a -40 to +52C (-40 to 126F) operating
temperature range. Sloped landings of up to 10-degrees are possible due to the articulated main
rotor and the design of the landing gear. The MD 600N employs an advanced NOTAR® antitorque system which reduces pilot workload, external noise levels, and significantly improves
safety in confined areas due to no spinning tail rotor.
THE MD 600N Advantages / Features
Airframe
 Simple system design
 Mature, field-proven systems and
components
 Separate cockpit and cabin
 Eight-place seating capability
 Speed, agility, and load-capable
 Certified to 14 CFR Part 27; VFR
 Approved / certified in over 50 countries
worldwide
Integrated Safety Features
 No tail rotor (NOTAR®) anti-torque
system eliminates the spinning tail rotor,
tail rotor gearbox, and tail rotor drive
shaft
 Designed for operator ease
 Main rotor static mast / base designed to
be fail-safe to 100-percent design load
 Three-dimensional truss-type structure
with integral roll bar
 Energy-absorbing airframe with occupant
seat crush boxes for 20g shock resistance
 Extended, energy-attenuating landing
gear
 Dual, crash-resistant elastomeric fuel
cells mounted between crash-resistant
keel beams and bulkheads below the
cabin floor
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External power receptacle
Integrated landing gear dampers
Fully articulated main rotor blades
Main rotor system removal independent
from main rotor transmission
Main rotor transmission removal
independent from main rotor system
Proven record of high dependability
High availability
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Main rotor transmission and NOTAR®
fan drive shafts incorporate anti-flail
devices if a flexible joint failure were to
occur
 Tail boom end-mounted tail skid
 Shoulder / seat belts attached to primary
structure
 Engine mounted low and at the rear
 Fuel filter automatic bypass if filter
becomes restricted
 Crew-seat four-point restraints
 Passenger seats provided with threepoint restraints
 Caution / warning annunciators / audible
warning tones
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MDHI PROPRIETARY
MD 600N
Technical Description
THE MD 600N Advantages / Features
Supportability Features
 Designed for ease of maintenance and
supportability
 Modular system design
 Designed for reparability
 Low direct operating costs
 Maximum use of line replaceable units:
o Engine
o Avionics / communication
o Flight controls
o Main rotor blades
o Main rotor drive shaft
o Main rotor transmission
o NOTAR® fan
o Main rotor transmission drive shaft
o Main rotor mast
o Landing gear
o Canopies
o Doors
o Door handles
o Door windows
o Seat restraints
o Tail boom
o Oil-cooler / blower
Human Systems Integration Features
 Unobstructed forward 160-degree vertical
and 220-degree horizontal cockpit field of
view
 Cockpit designed to accommodate 25th to
95th percentile male / female flight crew
Engine
 Fuel efficient, field-proven, turboshaft
engine
Monitoring Instrumentation
 Caution / warning annunciator panel
located at the top of the instrument panel
Environmental Impact
 Low noise profile with NOTAR® antitorque system
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Maximum use of line replaceable units
(Contd.):
o Empennage
o Tail boom skid
Built-in Maintenance aids:
o Engine fuel and oil filter impending
bypass indicators
o Engine oil chip detector
o Main rotor transmission oil chip
detector
o Integrated engine compressor wash
system
o Engine oil filler cap / dipstick
o Main rotor transmission filler cap
o Engine and main rotor transmission,
oil level sight gage
o Footsteps located on each side for
upper deck access without ground
support equipment
o Landing gear ground handling
wheel quick attach feature
o Main rotor and NOTAR® fan
balance monitoring system
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Integrated cockpit and cabin entry steps
Integrated visual / audible warning
indication for flight critical functions
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Externally accessible water wash
system
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Digital upgrade pending
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MDHI PROPRIETARY
MD 600N
Technical Description
3. CERTIFICATION
The MDHI MD 600N is a commercial FAA Type Certified aircraft under Code of Federal
Regulations (CFR) Title 14, Part 27. The MD 600N was initially certified on May 1997. The MD
600N is certified to 14 CRF Part 36, Appendix J (Noise) through Amendment 36-21, effective on
the date of the type certification. The MD 600N is also a European Aerospace Safety
Administration (EASA) Type Certified helicopter.
Production, type, and supplemental type certificates are maintained by MDHI.
A standard airworthiness certificate (FAA
form 8100-2), displayed in the aircraft, is
the FAA official authorization allowing
for the operation of type-certificated
aircraft. The airworthiness certificate is
displayed in the aircraft and remains valid
as long as the aircraft meets the approved
type design, is in a condition for safe
operation, and maintenance, preventive
maintenance, and alterations are
performed in accordance with CFR Title
14, Part 21.
The FAA designation for this model is
600N, and the International Civil Aviation Organization (ICAO) Type Designation is MD60.
MD Helicopters, Inc. commercial designation is MD 600N.
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MDHI PROPRIETARY
MD 600N
Technical Description
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MDHI PROPRIETARY
MD 600N
Technical Description
4. DIMENSIONS, WEIGHT, AND MISSION CONFIGURATION
4.1 External Dimensions
The MD 600N external dimensions are provided in the following table and shown in the figure
below.
MD 600N External Dimensions
Dimension,
ft (m)
Parameter
Fuselage Width
Fuselage Length
Horizontal Stabilizer Width
Landing Skid Width
Ground to Rotor Height
Ground to Fuselage Bottom Height
Main Rotor Diameter
4.60 (1.40)
29.60 (9.00)
6.60 (2.00)
8.80 (2.70)
9.20 (2.80)
2.40 (0.70)
27.50 (8.40)
4.2 Internal Dimensions
The MD 600N interior dimensions are provided in the following table and shown in the second
figure below.
MD 600N Internal Dimensions
Second
Figure
Reference
Location
A
B
C
D
D
Parameter
Crew Compartment Width
Crew Seat to Instrument Panel
Crew Compartment Depth
Passenger Compartment Depth
Passenger Compartment Width
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Dimension,
in. (cm)
49.00 (124.50)
18.50 (47.00)
37.50 (95.30)
72.00 (182.90)
48.00 (121.90)
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MDHI PROPRIETARY
MD 600N
Technical Description
MD 600N External Dimensions
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MDHI PROPRIETARY
MD 600N
Technical Description
MD 600N Internal Dimension Locations
4.3 Weight
Using the Rolls-Royce Model 25-C47M turboshaft engine, the MD 600N nominal empty weight
is 2,100 pounds (962 kg) for the standard configuration, and 2,036 pounds (923 kg) for the
industrial configuration.
4.4 Configurations
The MD 600N can be configured for a variety of different configurations. Configuration
examples are shown in the following figures.
MD 600N Standard Configuration
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MDHI PROPRIETARY
MD 600N
Technical Description
MD 600N Corporate Configuration
MD 600N Air Medical Services Configuration
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MDHI PROPRIETARY
MD 600N
Technical Description
5. MD 600N SINGLE-ENGINE HELICOPTER
The MD 600N is a single turbine engine, rotary-wing aircraft. It has a fully articulated six-blade
main rotor, and uses the NOTAR® anti-torque system. The MD 600N is certified for single-pilot
operation under visual flight rules / visual meteorological conditions.
5.1 System Description
MD Helicopters, Inc. MD 600N is an eight-place, single turbine-engine, multi-purpose
helicopter. The fuselage is constructed primarily of aluminum alloy while the NOTAR® antitorque system components are primarily carbon epoxy composite structure. Power from the 808
shaft horsepower (shp) Rolls-Royce Model 250-C47M turboshaft engine is transmitted through
the engine drive shaft to the main rotor transmission, and from the main rotor transmission
through a drive shaft to the NOTAR® system fan The NOTAR® system fan produces a lowpressure, high-volume airflow to pressurize the composite tail boom. Pressurized air is expelled
through two slots which run the length of the tail boom on the right side, causing a boundarylayer control that results in the tail boom acting as a wing, flying in the downwash of the rotor
system, and producing up to 60-percent of the anti-torque required in a hover. The balance of the
direction control is accomplished by a rotating direct jet thruster on the end of the tail boom. A
one-way clutch between the engine and main rotor transmission permits main-rotor freewheeling
of the rotor system during autorotation. The rotor is supported by a hollow static mast mounted
to the primary structure that absorbs all of the flight loads, allowing the transmission to provide
only torque.
The airframe consists of faired sections that provide clean aerodynamic lines. This contributes to
good handling qualities, low vibration levels, and high-speed flight capability. The airframe
structure is designed to be energy-absorbing while maintaining rotor hub integrity. A rigid, threedimensional truss-type structure increases crew and passenger safety by means of its roll-over
structure design.
The MD 600N incorporates an empennage consisting of a composite horizontal and vertical
stabilizer assembly located at the end of tail boom just forward of the jet thruster. A tail skid is
mounted to the bottom, end, of the tail boom. The horizontal portion of the stabilizer is mounted
with an elastomeric isolator that minimizes vibration transfer to the airframe due to wake
turbulence. The vertical endplates are mounted to the horizontal stabilizer at each end, and are
controlled using the yaw stability augmentation system (YSAS).
A diagram, of the major system components of the MD 600N is shown on the following page.
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MDHI PROPRIETARY
MD 600N
Technical Description
MD 600N Major System Components
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MDHI PROPRIETARY
MD 600N
Technical Description
5.2 Standard Equipment
The MD 600N is configured with standard equipment that is included in the basic aircraft
procurement.
MD 600N Standard Equipment
Airframe
 Extended landing gear
 Rapid door removal hinges (cockpit
and cabin)
 Tinted canopy windows
 Tinted door windows
 Dual center-opening, double doors – aft
cabin
 Keyed locks
 Fuselage mounting points
 Carbide skid shoes
 One-color exterior paint
Interior - Cockpit
 Left hand rotor brake
 Dual left-hand command flight controls
 Heater defogger system
 Crew seats with four-point harness
restraint
 Vinyl and fabric cushions
 Vinyl interior trim panels
 Crew compartment floor carpet
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85-amp starter-generator
Rain gutter
Jacking fittings
Passenger steps
Anti-collision lights (2)
Landing light, nose mounted
Position lights (2)
External power receptacle
115 gallon (435 liter)fuel system
NOTAR® anti-torque system
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Map case
Fire extinguisher
First aid kit
Battery-heavy duty Marathon 17ampere-hour
Fresh air ventilation system
Cockpit utility light
Instrument lighting
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Interior - Cabin
 Passenger seats with three-point
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harness restraint
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 Cabin compartment floor carpet
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 Vinyl and fabric cushions
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 Vinyl interior trim panels
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Engine
 Rolls-Royce Model 250-C47M engine,
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808 shp (603 kW)
 Automatic engine re-ignition
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 Engine wash kit
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Rotor and Controls
 Yaw stabilization augmentation system (YSAS)
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Reversible aft cabin bench seat
Cabin 28-volt utility outlet
Cabin convenience light
Cabin soundproofing
Cargo tie down fittings
Engine compartment fire detection
system
Engine anti-ice
Facet oil filter
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MDHI PROPRIETARY
MD 600N
Technical Description
MD 600N Standard Equipment
Monitoring Instrumentation
 Dual tachometer, NR and N2
 Engine oil pressure indicator
 Engine torque meter
 N1 tachometer
 Fuel quantity indicator
 Engine oil temperature indicator
 Digital chronometer
 Airspeed indicator
 Barometric altimeter
 DC ammeter
 Outside air temperature indicator
 Magnetic compass
 Turbine outlet temperature indicator
 Battery over temperature warning light
Miscellaneous
 Engine, airframe, and battery log books
 Rotorcraft flight manual
 System/subsystem maintenance
manuals and illustrated parts catalogs
 Engine exhaust cover
 Engine inlet cover
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Engine chip detector warning light
Engine out warning light
Fuel filter obstruction warning light
Fuel low warning light
Generator out warning light
Low rotor rpm warning light
Main transmission chip detector
warning light
Main transmission oil pressure warning
light
Main transmission oil temperature
warning light
FADEC and ECU caution lights
Pitot tube cover
Fan inlet cover
Main rotor blade tie-downs
Ground handling wheels
NOTAR® inlet, thruster, and tail boom
cover
5.3 MD 600N Optional Equipment
Optional equipment for the MD 600N is available for additional cost, and is literally nonexhaustive.
MD 600N Optional Equipment
Airframe
 Heated pitot tube
 Paravion cockpit door openers
 Comfort windows
 Dual side mount (forward looking
infrared sensor & searchlight)
 Searchlight
 Moveable landing / searchlight
 Landing light pulse system
 Video turret side mount
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Skid mirror
Two-/three-color standard exterior
paint
Sealed lead-acid battery
Cargo hook with hard mount
Cargo hook provisions
On-board cargo hook weighing system
Emergency water floats
High visibility main rotor blades
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MDHI PROPRIETARY
MD 600N
Technical Description
MD 600N Optional Equipment
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Airframe fuel filter
Generator cooling kit
Engine bay door quick release hinges
Exterior crew handles
Air conditioning R-134 w/ forward
evaporator
 Tyler platform
Interior - Cockpit
 Leather covered interior panels
 Leather covered seats
 Black mesh seats
 28-volt receptacle
 Pilot/copilot gooseneck lights
 Right-hand command pilot
 Flat panel monitor mounts
Interior - Cabin
 Leather covered interior panels
 Leather covered seats
Monitoring Instrumentation
 Diamond J turbine outlet temperature
indicator
 Avionics cooling fan
 Blind encoder
 Encoding altimeter 3-inch
 Instantaneous vertical speed indicator
 TRA 3000 radar altimeter w/indicator
 Attitude gyro indicator, 3-inch
 Directional gyro - panel mounted
 Compass system (KCS55A)
 Radio magnetic indicator (K1229-00)
 Turn and bank indicator, 2-inch
 Turn and bank indicator, 3-inch
 Copilot intercom switch
 Garmin G500 system
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Night vision goggle compatible lighting
Wire strike protection kit
Twenty-one gallon (79 liter) auxiliary
tank
Thirty-three gallon (125 liter) auxiliary
tank
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Pilot Mason grip
Right-hand command pilot
Instrument panel face plate
modification
Slant panel pedestal
Night vision goggle compatible lighting
Flat black painted interior
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Black mesh seats
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Emergency locator transmitter
Various NAV / COM / GPS equipment
Various transponders
Various displays, radios, transceivers,
and data links
Various audio panels, intercoms, CD
player, AM / FM radios
Cyclic remote frequency switch
Hand held radio provisions to include
AA-34 universal
Communication headsets External PA /
siren system
Forward looking infrared sensor
Aero Computers mapping system
Avionics master switch
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MDHI PROPRIETARY
MD 600N
Technical Description
5.4 Fuselage
The MD 600N fuselage is a teardrop-shaped, aerodynamically efficient structure that
incorporates a NOTAR® circulation control tail boom and an empennage consisting of horizontal
and vertical stabilizers. The fuselage is a semi-monocoque construction, manufactured primarily
of aluminum alloy. It consists of a rigid, three-dimensional, truss-type structure with an integral
roll-bar design for increased occupant safety. The airframe structure is designed to be energy
absorbing and fails progressively in the event of impact. Occupant seat crush boxes are
incorporated into the design and provide 20g shock resistance. The composite tail boom
incorporates the NOTAR® circulation control and is the mount for the empennage and rotating
direct-jet thruster at the end of the tail boom.
The MD 600N was created by adapting a mid-section extension into a MD 500-series fuselage.
This mid-section extension provides additional, comfortable seating for an additional three
people or with all seats removed, 6 feet (1.83 m) of cabin-floor cargo space. Cabin doors (see
figure below) are center opening for entry ease.
MD 600N Fuselage Structure
The fuselage structure is divided into three main sections as shown in the figure below:
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Forward section – comprised of a pilot compartment and, directly aft separated by a
bulkhead, a passenger/cargo compartment. The pilot compartment is equipped with seats
for the pilot and either one or two passengers. The passenger / cargo compartment,
located in the center of the aircraft, contains provisions for installation of a bench or
individual folding-type seats for up to five passengers. The lower fuselage structure
beneath the pilot / passenger floor contains compartment space for the aircraft battery and
provision for small cargo storage or installation of avionics equipment.
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MDHI PROPRIETARY
MD 600N
Technical Description
MD 600N Main Fuselage Assembly Sections


Aft section – includes the structure for the tail boom attachment, NOTAR® system fan,
and engine compartment. The tail boom is also a monocoque structure manufactured of
aluminum alloy, and is the supporting attachment structure for the direct-jet thruster,
horizontal stabilizer, and vertical stabilizers.
Lower section – divided by the center beam and provides the housing for the two fuel
cells. Provisions for the attachment of a cargo hook are located on the bottom of the
fuselage in line with the center beam.
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MD 600N
Technical Description
5.5 Exterior
The MD 600N exterior can be painted a single-color of the customer choice from available
colors. An additional two, three, or more colors can be painted on the exterior for an additional
cost. The exterior provides mounting locations for external antennas of customer-purchased
avionics / communication equipment, external lighting, main rotor static mast, landing gear, and
tail boom.
5.6 External Lighting
The MD 600N external lighting (shown below) consists of a:
 Rear position light assembly
 Rear anti-collision strobe light assembly
 Lower anti-collision strobe light assembly
 Left-hand red position light assembly
 Right-hand green position light assembly
 Landing hover light.
Standard cockpit lighting includes cockpit lights for the pilot. A passenger compartment
convenience light is optional.
5.7 Interior
The interior of the MD 600N is comprised of the cockpit area, cabin compartment, and engine
compartment. The MD 600N is provided in the utility version.
5.7.1 Cockpit
The cockpit has accommodations for the
pilot and / or copilot. The minimum crew
is one pilot in the command position. The
instrument panel is located in the forward
portion of the cockpit, and the T-shaped
instrument panel provides space for a full
complement of avionics equipment. The
instrument panel layout allows for easy
scanning of flight instruments.
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MD 600N
Technical Description
MD 600N Internal and External Lighting Locations
The cockpit is ergonomically designed to facilitate single-pilot operation in the right-hand or
left-hand command configuration. All controls are within easy pilot reach. In addition, the antitorque control pedals are adjustable for up to 4 inches fore and aft to accommodate 25-percentile
to 95-percentile male / female pilots. Seats are constructed of padded upholstered material and
are attached to the forward bulkhead. Directly aft of the crew station, a bulkhead behind the
forward compartment separates the cockpit and passenger / cargo compartment.
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MD 600N
Technical Description
5.7.2 Cabin Compartment
The passenger / cargo compartment provides space for
passengers, cargo, or multi-mission equipment. With the
seats removed, the aft cabin provides 1.83 meters (6 feet)
of flat floor space. Five passengers can be seated in the
aft cabin in a variety of seating configurations. Seats are
constructed of padded upholstered material and are
attached to the rear bulkhead. However, if the cabin midbench assembly is reversed, the seat belts are attached to
the seat structure. Optional aluminum tube frame and
black mesh seats are also available. An intermediary step
is provided between the landing gear and passenger
compartment for passenger ingress/egress assistance.
5.7.3 Engine Compartment
The engine compartment provides an enclosed mounting platform for the turboshaft engine and
can be easily accessed behind two clam-shell type doors contoured to the shape of the fuselage.
The engine compartment can be easily accessed without GSE or special equipment.
5.8
Systems
5.8.1 Fuel System
The MD600N fuel system consists of two interconnected bladder cells with a total capacity of
116.2 gallons (790 pounds) located in bays below the passenger / cargo compartment floor of the
lower section. The fuel system does not require boost fuel pumps, and is designed to FAR Part
27 criteria for crash resistance. Puncture-resistant bladders and frangible, breakaway connections
are incorporated to prevent fuel spillage in the event of a hard landing.
An engine suction-type fuel pump is used for fuel transfer to the engine. The suction pump
increases system safety by eliminating pressurized fuel lines. An ejector-type scavenge pump in
the forward tank area transfers fuel to the aft fuel pick-up area. All common turbine fuels are
approved for use in the Model 250-C47M engine.
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MD 600N
Technical Description
5.8.2 Propulsion System
The engine used in the MD 600N is the Rolls-Royce Model 250-C47M gas turbine engine. The
Model 250-C47M produces
808 shp, derated to 600 shp for
takeoff, and 530 shp at
maximum continuous
operation. Derating the engine
extends its service life and
reduces maintenance while
offering increased performance
at higher-density altitudes.
The Model 250-C47M engine
is equipped with a full authority
digital engine control (FADEC)
unit. This system greatly
enhances engine control and
provides several features and
Typical Rolls-Royce Model 250 Turboshaft
benefits that reduce pilot
Engine Cross Section
workload, improve flight safety,
and decrease maintenance
requirements. A separate hydro-pneumatic fuel control system is provided for manual backup.
5.8.3 Engine Controls
Engine power management and speed control is accomplished by the FADEC. Electrical power
for engine start is provided by the battery bus, through the throttle control to the start relay,
FADEC, ignition unit, and igniters. The start relay also provides power from the battery bus to
the starter/generator. Engine control is accomplished by fuel control actuation using the throttle
twist grip located at the end of the collective stick. The throttle twist grip has three positions:
cutoff, idle, and full open. Moving the throttle twist grip from cutoff to idle provides automatic
fuel metering for engine starting, acceleration, and idle stabilization. Moving the throttle twist
grip to full open during operation increases the gas producer speed and allows the power turbine
governor speed control. The collective stick throttle twist grip movement friction is adjustable.
The collective stick throttle twist grip can also be locked when the operational gas producer
turbine speed is attained. If a FADEC failure should occur, engine control reverts to manual
back-up operation using the hydro-mechanical fuel control.
5.8.4 Fire Detection System
An engine fire detection system, consisting of a detector cable looped around the inboard
structure of the engine bay. The engine fire detection system consists of a pressure switch
connected to a small diameter tube that is filled with helium gas and a core material that contains
trapped hydrogen. The fire detection system provides a means of detecting high temperature
conditions and provides fire/overheat visual warning (red warning indicator) to the cockpit and a
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MD 600N
Technical Description
vocal warning into the communication system. The fire detection system incorporates built-in
test feature for tube integrity and provides failure detection indication to the cockpit.
5.8.5 Drive System
The MD 600N drive system (shown in the figures below) consists of an:
 Main rotor static mast/base – Non-rotating and rigidly mounted to the mast support
structure. It provides support for the main rotor, main rotor transmission, and main rotor
transmission drive shaft
 Main rotor driveshaft – Transmits torque to the main rotor. Lifting loads are prevented
from being imposed on the main transmission, eliminating thrust loading of transmission
parts
 Main rotor transmission – Mounted to the basic airframe structure above the passenger /
cargo compartment, the main rotor transmission is lubricated by a self-contained aircooled lubrication system
 Overrunning clutch – The overrunning clutch transmits power from the engine to the
main rotor transmission drive shaft
 Main rotor transmission drive shaft – Connects to the main rotor transmission input shaft
 Oil cooler – The oil coolers are two section coolers with an upper and lower part. The
upper part is used to cool the transmission lubricating oil and the lower part is used to
cool the engine lubricating oil.
 Oil-cooler / blower – Belt driven off the main drive shaft, it draws cooling air from the air
inlet fairing to supply ambient air to the engine and transmission oil coolers and to the
engine compartment
 NOTAR® fan transmission drive shaft – Transmits torque from the main rotor
transmission to the NOTAR® fan transmission
 NOTAR® fan transmission – The NOTAR® fan transmission steps-up main transmission
output speed for power transmission to the NOTAR® fan
 NOTAR® fan interconnect drive shaft – Connects the NOTAR® fan transmission to the
NOTAR® fan
 NOTAR® fan – An enclosed variable pitch composite blade fan produces a low-pressure,
high-volume airflow to pressurize the composite tail boom for anti-torque control.
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MD 600N
Technical Description
MD 600N In-Situ Drive System
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MD 600N
Technical Description
MD 600N Main Transmission Drive System.
5.8.6 Rotor System
The static mast-hub support system, unique to MDHI products, uses a static mast, rigidly
attached to the fuselage. All dynamic loads are transmitted through the mast, rather than through
the transmission. A separate, inner drive shaft transmits engine torque to the main rotor hub. This
feature offers improved flight control integrity and helps retain rotor system components in the
event of a main rotor blade strike. Additionally, this approach allows for the design of a main
transmission that is lighter in weight, and can be removed without disturbing the hub or control
system.
The MD 600N features a six-blade, fully articulated main rotor assembly. Rotor blades, pitch
housings, and links are secured to the hub by laminated steel strap sets. These sets are used in
lieu of typical thrust bearing stacks to contain blade centrifugal loading and allow feathering.
The strap sets provide additional functionality:
 The strap set configuration (which is secured firmly to the hub) allows the centrifugal
load exerted by one blade to be countered by the force exerted by the opposite two
blades, resulting in very light centrifugal loads exerted on the hub.
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MD 600N
Technical Description


The V-legs of the strap set rotate as driving members to turn the main rotor blades.
The strap sets are configured to allow feathering and flapping of the blades.
Main rotor blades are retained to the main rotor hub using captive cam-handle-type blade
retention bolts.
5.8.7 NOTAR® Anti-Torque System
The NOTAR® system used in the MD 600N (shown below) is derived from an already-proven
system used in the MD 520N helicopter. Total NOTAR® fleet time for all MD helicopters
exceeds 750,000 hours.
The NOTAR® anti-torque system provides safe, quiet, responsive, foreign object damage
resistant directional control. The enclosed variable-pitch composite-blade fan produces a low
pressure, high volume airflow to pressurize the composite tail boom. Air is expelled through two
slots which run the length of the tail boom on the right side, causing a boundary-layer control
that result in the tail boom acting as a wing, flying in the downwash of the rotor system, and
producing up to 60-percent of the anti-torque required in a hover. The balance of the direction
control is accomplished by a rotating direct jet thruster on the end of the tail boom.
MD 600N NOTAR® Anti-Torque System
The NOTAR® system eliminates the mechanical disadvantages of a tail rotor, including long
drive shafts, hanger bearings, and gearboxes. It reduces the overall helicopter vibrations,
resulting in lowered pilot fatigue and increased passenger comfort. . Total NOTAR® fleet time
for all MD helicopters exceeds 750,000 hours.
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MD 600N
Technical Description
Due to the design of the NOTAR® system which eliminates the spinning tail rotor, potential
incidents caused by an exposed tail rotor are eliminated. The NOTAR® system not only has
proven safety margin, it also provides up to a 50-percent reduction in noise over competitor
helicopters.
5.8.8 Flight Control System
Cyclic, collective, and adjustable pedal controls are provided in the pilot / copilot positions. The
cyclic and collective control sticks incorporate friction devices as a method for the pilot to vary
movement friction and the amount of effort required to move the control sticks. The cyclic stick
lateral and longitudinal movement friction is adjustable. The collective stick vertical movement
friction and the throttle twist grip movement friction are adjustable. The collective stick throttle
twist grip can also be locked when the operational gas producer turbine speed is attained. The
dual flight controls can be easily removed to provide room for passengers or cargo. The dual
flight control system can be easily removed to provide room for passengers or cargo.
5.8.9 Yaw Stability Augmentation System
The MD 600N incorporates a yaw stability augmentation system (YSAS). The YSAS is installed
to the right vertical stabilizer of the empennage, and significantly reduces pilot workload
throughout the flight envelope, especially in gusty / turbulent weather conditions.
Yaw rate data drives the right-side vertical stabilizer, which corrects out-of-trim flight. Pilot
inputs during maneuvers and level flight is significantly reduced. The left-side vertical stabilizer
is not connected to the YSAS.
5.8.10 Electrical System
The MD 520N electrical system is a direct current (dc) system with electrical power supplied by
a 24-volt nickel-cadmium battery and a 28-volt, 85-amp engine-driven generator. The electrical
system incorporates a generic electrical wire harness that is shielded to minimize electromagnetic interference (EMI). Forward and aft line relay contacts protect main power bus and
feeder wires. Over-voltage diodes protect circuits from excessive ground power voltages. An
external power receptacle is available for ground power.
5.8.11 Environmental Control System
Cabin environmental control is accomplished by an integral heating and defogging system and
an external-air circulation system. The heating and defogging system requires no additional
equipment and uses oil cooler blower supplied unheated air and turboshaft engine compressor
supplied heated air.
Cabin ventilation with ambient external air is available using instrument panel mounted
mechanical controls to operate a moveable vane. In addition, adjustable window-mounted
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MD 600N
Technical Description
ventilators are installed in each door window to provide in-flight, outside forced air into the
cabin or provide vent-air exhaust.
An air conditioning system is an available option.
5.8.12 Monitoring Instrumentation
Typical MD 600N monitoring instrumentation provided as standard equipment includes:
 Dual engine tachometer (NR and N2)
 Engine oil pressure
 Engine oil temperature
 Engine torque meter
 Engine N1 tachometer
 Engine turbine outlet temperature
 Fuel quantity
 Airspeed
 Barometric altimeter
 Magnetic compass
 Outside air temperature
 Direct current ammeter
 Fuel quantity
 Digital chronometer
 Annunciator panel caution / warning lights
o Engine chip detector light
o Engine-out warning
o Fuel filter warning
o Fuel low warning
o Generator-out warning
o Battery over-temperature warning
o Low rotor revolutions per minute (rpm) warning
o Main rotor transmission chip detector warning
o Main rotor transmission oil pressure warning
o Main rotor transmission oil temperature warning.
5.8.13 Caution / Warning Annunciators
Caution and warning annunciators (indicators) are located at the top of the instrument panel
above the flight instruments. A caution indication will be displayed by a yellow indicator
illumination. A warning indication will be displayed by a red indicator illumination.
Additionally, a voice warning will sound for an engine out, fire, low-rotor-speed, FADEC
manual, fuel flow fixed (FADEC fail), and power (torque exceedance) with the corresponding
warning indicator illumination. These voice warnings are announced twice each time a warning
condition exists.
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MD 600N
Technical Description
5.8.14 Avionics / Communications
The MD 600N is provided with a standard avionics suite. Optional purchaser configured
avionics, communications, instrumentation, etc., may be added at additional expense. To
accommodate additional avionics / communication equipment, an optional slant console panel
installation is available.
5.8.15 Next-Generation Electronic Flight Instrument System
The MD 500-series helicopters will incorporate a modernized instrumentation/avionics cockpit
consisting of a Garmin G500 suite that includes a multi-function and primary flight displays
(MFD, PFD) and an engine indicating and crew alerting system (EICAS). The EICAS will
replace the caution and warning annunciators. The next-generation electronic flight
instrumentation system will work with additional equipment such as a GTN650 GPS/NAV/COM
and automatic dependent surveillance-broadcast (ADS-B) to provide next-generation air
transportation system compatibility.
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MD 600N
Technical Description
6. PERFORMANCE SPECIFICATIONS
Performance specifications for the MD 600N helicopter with the Rolls-Royce Model 250-C47M
turboshaft engine are provided below.
6.1 MD 600N – Rolls-Royce Model 250-C47M Turboshaft Engine
Using the Rolls-Royce Model 250-C47M turboshaft engine, the MD 600N has a nominal empty
weight of 2,100 pounds (962 kg) for the standard configuration, and 2,036 pounds (923 kg) for
the industrial configuration. Ratings are for the MD 600N with a Rolls-Royce Model 250-C47M
turboshaft engine rated at 808 shp (603 kW), derated to takeoff power – 600 shp (447 kW), and
maximum continuous power – 530 shp (395 kW).
MD 600N Performance Specifications
Parameter
Empty Weight
(Configuration), lb
(kg)
Maximum Cruise
Speed, kt (mph)
[km/hr]
Maximum Permitted
Speed, kt (mph)
[km/hr]
Maximum Range, nm
(mi) [km]
Maximum Endurance,
hr
Imperial
3100 lb
Metric
1406 kg
Imperial
3600 lb
Metric
1633 kg
Imperial
4100 lb
Metric
1860 kg
Standard
--
--
--
--
2,100
(952)
Industrial
--
--
--
--
2,036
(923)
Sea Level
ISA
144
(166)
[267]
139
(160)
[257]
134
(154)
[248]
5000 ft (1524
m)
148
(170)
[274]
143
(165)
[265]
134
(154)
[248]
VNE at Sea
Level
152
(175)
[282]
152
(175)
[282]
1135
(155)
[250]
Sea Level
ISA
347
(399)
[643]
357
(411)
[661]
341
(392)
[632]
5000 ft (1524
m)
423
(487)
[783]
401
(461)
[743]
380
(437)
[703]
Sea Level
ISA
3.9
3.9
3.8
3.8
3.6
3.6
5000 ft (1524
m)
4.4
4.4
4.1
4.1
3.9
3.9
Condition
Maximum Rate of
Climb, (TOP) fpm
(m/sec)
Sea Level
Standard ISA
2,100
(10.7)
1,700
(8.6)
1,350
(6.9)
ISA +20C
1,900
(9.7)
1,500
(7.6)
1,150
(5.8)
Maximum Operating
Altitude, ft (m)
Density
Altitude
20,000
(6,096)
20,000
(6,096)
20,000
(6,096)
Service Ceiling, ft (m)
ISA @ 30.5
20,000+
(6,096+)
20,000+
(6,096)
13,500
(4,115)
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MD 600N
Technical Description
MD 600N Performance Specifications
Imperial
3100 lb
Metric
1406 kg
Imperial
3600 lb
Metric
1633 kg
Imperial
4100 lb
Metric
1860 kg
Standard Day
14,500+
(4,420+)
14,500+
(4,420+)
11,100+
(3,383)
ISA +20C
12,200+
(3,719+)
11,600
(3,536)
7,000
(2,134)
Standard Day
14,500+
(4,420+)
11,700
(3,566)
6,000
(1,829)
ISA +20C
12,200+
(3,719+)
8,000
(2,438)
3,200
(975)
Normal
Category
--
--
--
--
4,100
(1,860)
External
Load
--
--
--
--
4,500
(2,041)
Normal
--
--
--
--
2,000
(907)
External Load, lb (kg)
--
--
--
--
2,400
(1,089)
Cargo Hook Structural
Rating, lb (kg)
--
--
--
--
3,000
(1,360)
--
--
--
--
790
(358)
Parameter
Condition
m/min
Hover-in-Ground
Effect, (HIGE), ft (m)
Hover-Out-of-Ground
Effect (HOGE), ft (m)
Maximum Gross
Weight, lb (kg)
Useful Load, lb (kg)
Fuel Capacity, 116
gallons (432 liters)
Usable
6.2 Environmental Impact
The MD 600N has a measured 79.0 decibel noise signature during a 500-foot above ground level
fly-over. The estimated day / night average sound level (DNL) contour of the MD 600N
compared to two competitors is shown on the following page. The full-page figure (page 34)
provides a comparison of 500-foot overflight effective, perceived noise levels (EPNLs) of
competitor single-engine aircraft using European Aviation Safety Agency (EASA) data. This
figure shows the MD 500E with four-blade tail rotor, MD 520N, and MD 600N helicopters
provide the lowest EPNLs of light single-engine helicopters.
6.3 Safety
The MD 600N has inherent safety features. The fuselage incorporates a rigid, three-dimensional
truss type structure, with an integral roll-bar design for increased occupant safety. The airframe
structure is designed to be energy absorbing and fails progressively in the event of impact. The
fuel cells are separated well away from the outer skin, enclosed by two deep keel beams.
Shoulder and seat belts are attached to the aircraft structure rather than to the seat. The pilot and
cabin doors function both as primary and emergency exits.
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MD 600N
Technical Description
MD 600N Estimated Noise Contour
Occupant seat crush boxes are incorporated into the design and provide 20g shock resistance.
The seat crush boxes were originally designed to meet Civil Aviation Regulation, Part 6 (CAR6)
requirements and have been validated under Title 14 Code of Federal Regulation (CFR), Chapter
1, Part 27, Subpart C, Section 27.562 for the MD 600N air vehicle. Seat crush boxes for the MD
600N are the same as used in the MD 500-series.
Incorporation of the NOTAR® system eliminates the typical spinning tail rotor and reduces the
opportunity for tail rotor strikes, increases ground-personnel safety, and provides for improved
landing zone safety.
Additional safety features include:
 Static mast, hub, and transmission are mounted on titanium struts preventing direct
contact between transmission and upper deck, reducing vibration, and increasing
passenger safety
 Fuel cells, located under the cabin floor, are protected during an impact event due to the
closely spaced fuselage frames and by the center beam
 Unobstructed pilot visibility for situational awareness
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MD 600N
Technical Description
The MD 600N Helicopter has the Lowest 500-Foot Overflight Effective Perceived
Noise Levels of Comparable Light Single-Engine Helicopters
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MD 600N
Technical Description





Crash resistant fuel system
Integral crewmember seats with energy absorbing structure
Low and to-the-rear engine mounting
Energy absorbing landing gear
Main rotor height of 9.0 feet
The NOTAR® system improves safety:
o Elimination of tail rotor strikes
o No dramatic enter of gravity shift with loss of conventional tail-rotor gearbox
o Reduced pilot workload; pilot can concentrate on piloting
o Less sensitive to wind direction
o Enhanced safety in confined areas
o No drive shafts, hangar bearings, or 90-degree gearboxes
o Significant foreign object damage tolerance
o Flyable with fan drive loss.
6.4 Crashworthiness
The MD 500 series and MD 600N aircraft are derivatives of the OH-6A observation helicopter
used extensively by the U.S. Army during the Vietnam conflict, in which nearly 1500 OH-6A
aircraft were operated. The OH-6A earned a reputation for being the most survivable helicopter
in the world due to the inherent design features shown in the figure below.
Tests on the landing gear and fuselage sections verified the crashworthiness capability of the MD
500 series and MD 600N helicopters. Testing indicates that the helicopters will provide occupant
protection for approximately 95-percent of all civil accidents, and that the landing gear and
airframe fuselage in capable of absorbing vertical descents up to 26.3 feet per second with only
moderate crewmember injury.
6.5 Human Systems Interface
The MD 600N incorporates anthropometric design features that are compatible with 25th and
95th percentile male or female crewmembers. Sizing parameters for the 25th and 95th percentile
male and female are provided in the table below. The canopy design meets human engineering
design requirements for windows, canopies, and windshield, as shown in the figures that follow.
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Technical Description
MD 600N Crashworthy Design Features
Anthropometric Sizing Parameters
Parameter
Weight, lb (kg)
Height, in. (cm)
Elbow – Hand
Grip Reach, in.
(cm)
Thumb Tip
Reach, in. (cm)
Functional Leg
Reach Length, in.
(cm)
Report No. MD14031211-600NTD
25th
Percentile
Female
119.3
(54.1)
62.4
(158.5)
95th
Percentile
Female
164.5
(74.6)
68.5
(174.0)
25th
Percentile
Male
142.6
(64.7)
67.0
(170.1)
95th
Percentile
Male
201.8
(91.5)
73.9
(187.7)
12.5
(31.7)
14.1
(35.8)
13.7
(34.8)
15.4
(39.1)
27.9
(70.8)
31.4
(79.7)
30.4
(77.2)
34.2
(86.9)
39.2
(99.6)
43.2
(109.7)
43.5
(110.6)
46.0
(116.8)
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MDHI PROPRIETARY
MD 600N
Technical Description
The MD 600N Provides a 160-Degree Vertical Unobstructed View for the
Pilot and Copilot
The MD 600N Provides a 220-Degree Horizontal Unobstructed View for the
Pilot and Copilot (View is Top-Down)
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MDHI PROPRIETARY
MD 600N
Technical Description
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MDHI PROPRIETARY
MD 600N
Technical Description
7. MAINTENANCE AND SERVICING
The MD 600N helicopter was designed for ease of supportability and low-cost operation.
Helicopter systems and components are easily accessed and can be maintained at the lowest
maintenance level possible. The helicopter was designed for a high level and ease of replacement
of line replaceable units (LRUs). The helicopter can be maintained at the line- / shopmaintenance level using common hand tools, as well as easy to understand technical
publications. The MD 600N helicopter spare parts are readily available, and most parts have a
corresponding U.S. Department of Defense National Stock Number (NSN).
7.1 Maintenance
The MD 600N design provides for the maximum maintenance support at the lowest maintenance
level. The MD 600N can be maintained using a combination of line- and shop-maintenance
support. Components such as engine, avionics, interior components, air-conditioning, etc., are
considered LRUs. Line replaceable units (and any sub-component shop replaceable units) can be
removed and replaced easily and modularly, as necessary, and at the lowest maintenance level
allowed.
Typical for small- to mid-sized helicopter systems are fixed time-between-overhaul (TBO)
intervals for the engine, transmission, main rotor, and flight controls. Within these items are also
life-limited components that must be monitored and replaced at the end of life hours. When
required, components requiring further maintenance action can be removed and forwarded to the
appropriate-level shop.
The MD 600N helicopter airframe uses an on-condition maintenance concept, which allows
scheduled inspections / checks. To be compliant with commercial regulatory requirements, an
MD 600N continued airworthiness inspection program was developed by MDHI. This program
provides for schedule inspections, and also includes life-limited component replacement. The
maintenance and inspection intervals are provided in the Handbook of Maintenance Instruction.
Airframe-related inspection intervals occur every:
 100 hours
 300 hours
 600 hours
 1200 hours
 Yearly
 Special time-phase inspections.
The engine also has life-limited components, a fixed TBO, and inspection intervals. The MD
600N life-limited parts, overhaul intervals, and inspection intervals are listed in the table below.
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MDHI PROPRIETARY
MD 600N
Technical Description
MD 600N Life-Limited Parts, Overhaul, and Inspection Intervals
Life Limit,
hr
Component
MAIN ROTOR
Blade Assembly
Blade Attachment Folding Pin
Hub Assembly
Upper Thrust Bearing Cup
Upper Thrust Bearing Cone
Lower Thrust Bearing Cup
Lower Thrust Bearing Cone
Hub Retention Strap Assembly
Lead-Lag Hub Bolt
Lead-Lag Hub Link Assembly
Lead-Lag Damper
Swashplate
Drive Shaft
Mast Assembly
DRIVE SHAFTS, COUPLINGS, AND
CLUTCHES
Main Rotor Transmission Drive Shaft
Main Rotor Transmission
Overrunning Clutch Assembly
Fan Drive Shaft
Oil Cooler Blower Bearing
Oil Cooler Blower Belt
ANTI-TORQUE SYSTEM
Fan Blade Assembly
Fan Hub
Tension-Torsion Strap
Fan Support Shaft
Fan Support Bearing
Pitch Plate Assembly
Pitch Plate Bearing
Rotating Cone Assembly
TAIL BOOM
Attach Bolts
Tail Boom Assembly
Empennage Fittings
Horizontal Stabilizer Torque Tube
Horizontal Stabilizer Assembly
Report No. MD14031211-600NTD
Overhaul
Interval, hr
3,200
7,600
Inspection
Interval, hr
100
2,700
600
600
5,400
5,400
2,770
5,400
11,080
300/2700
300/2700
100
300
2,700
600/300
100
14,000
3,500
100
3,000
1,800
1,200
100/300
100
1,200
1,200
12,500
7,500
2,500
4,000
2,400
7,500
2,400
10,000
100
1,200
1,200
300
6,000
100
3,000
10,000
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MDHI PROPRIETARY
MD 600N
Technical Description
MD 600N Life-Limited Parts, Overhaul, and Inspection Intervals
Life Limit,
hr
Component
Overhaul
Interval, hr
Inspection
Interval, hr
100
Vertical Stabilizer Assembly
CONTROLS
Cyclic Stick Trim Switch
1,000
Cyclic Stick Socket
1,000
8
Cyclic Tube Assembly
1,200
8
Collective Stick Housing
450
Collective Pitch Control Tube
400
Collective Pitch (Pilot) Tube Assembly
600
Collective Pitch (Co-Pilot) Tube
1,800
Collective Pitch Housing
450
Collective Pitch (Co-Pilot) Tube
1,000
Assembly
YSAS
300
AIRFRAME
Landing Gear Brace
5,900
Landing Gear Strut
696
Landing Gear Foot
3,900
ENGINE
Compressor Module
4,000
Turbine Module
2,000
Starter/Generator
1,200
NOTES:
Detailed maintenance / inspection information is provided in the Handbook of Maintenance
Instruction, Rotorcraft Flight Manual, and Supplier Technical Publications (i.e., RollsRoyce).
Bearing grease re-pack task.
With cargo hook operation
Every 8 hours after initial 100 hour inspection
Value represents hours/cycles.
Hot section inspection.
7.2 Servicing
The MD 600N was designed for ease of maintenance, incorporating built-in features that
eliminate support equipment and aid servicing. These features include:
 Spring loaded doors that provide engine and main rotor head access (refer to figure
below)
 Quick access panels
 Integrated diagnostics
 Integrated engine water wash systems
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MDHI PROPRIETARY
MD 600N
Technical Description
The MD 600N has Built-in Steps to Provide Access to the Main Rotor Head
without External Ground Support Equipment
The MD 600N helicopter has been designed for servicing and operation using common,
commercially-available compounds. Servicing locations are shown in the figure below, and will
be performed in accordance with the corresponding equipment maintenance manuals. Servicing
intervals are detailed in the MD 600N Handbook of Maintenance Instructions. Capacities and
compounds used to service the MD 600N are listed in the table following the figure.
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MDHI PROPRIETARY
MD 600N
Technical Description
MD 600N Servicing Location Points
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MDHI PROPRIETARY
MD 600N
Technical Description
MD 600N Fluid Capacities and Specifications
Component
Engine
Overrunning
Clutch
Main rotor
Transmission
Aft
Transmission
One-Way
Lock
Battery
Fuel Cell
Compound
Lubricant
Lubricant
Lubricant
Lubricant
Lubricant
Distilled
Water
Fuel
Capacity
Specification
Notes
3.0 quarts
(2.84 liters)
3.64 ounces
(108 cc)
14.0 pints
(6.62 liters)
0.5 pint
(0.23 liter)
0.67 ounce
(20 cc)
MIL-PRF-7808G / MIL 
PRF-23699C
As Required
MS36300
64.0 gallons
(242 liters)
416 pounds
ASTM-D-1655, Jet A
ASTM-D-1655. Jet A-1
ASTM-D-1655, Jet B
ASTM-D-1655, JP-1
ASTM-D-1655, RP-3
ASTM-D-6615, Jet B
MIL-DTL-5624, JP-4
MIL-DTL-5624, JP-5
MIL-DTL-83133, JP-8
Mobil AGL

Mobil AGL

Mobil AGL
MIL-PRF-5606 /
MIL-PRF-6083
 
NOTES:
 Refer to Rolls-Royce Operation and Maintenance Manual for approved oils.
 Oil specification type mandated by ambient temperature. Refer to Rolls-Royce Operation and
Maintenance Manual
 Refer to Rolls-Royce Operation and Maintenance Manual for complete fuel specifications.
 At 40F and below, fuel must contain anti-icing additives per MIL-I-27686. Refer to Rolls
Royce Operation and Maintenance Manual
7.3 Hourly Cost
The MD 520N helicopter was designed for ease of supportability and low-cost operation.
Current, estimated direct operating cost per operating hour data for the MD 520N, shown in the
following table, is based on “current-year” 2014 U.S. dollars.
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MDHI PROPRIETARY
MD 600N
Technical Description
MD 600N Estimated Direct Cost Per Hour Using Model 250-C47M Turboshaft
Engine is Based on Current-Year (2014) U.S. Dollars
Cost, U.S.
Dollars ($)
Activity
Total
Rolls-Royce Model 250-C47M Engine
Fuel and Maintenance
Fuel at $3.93 per gallon at approximately 41 gallons per hour
Lubricants at 3-percent of fuel
$161.13
$4.83
$165.96
Airframe Maintenance and Spares
Maintenance Labor Costs:
Scheduled (0.15 man-hour per flight hour) at $75.00 per hour
Unscheduled (0.26 man-hour per flight hour) at $75.00 per hour
$11.25
$19.50
$30.75
Spares Cost:
Scheduled (Inspection) Parts: Used during Periodic Inspection
(e.g., filters, seals, o-rings, etc.)
On-Condition / Unscheduled Part
Reserves: Component Overhaul (Time Between Overhaul)
Reserves: Limited-Life Parts
$5.78
$23.89
$84.20
$81.94
$195.81
Engine
Scheduled Maintenance Labor and Parts
Reserve for Engine Overhaul, Spares, and Accessories
$3.00
$126.04
$129.04
TOTAL DIRECT OPERATING COST
$521.56
Fuel cost and labor rate is based on U.S. average cost while operating under the following
conditions:
Gross Weight: 10-percent less than maximum certified
Speed: Maximum range speed, 117 kias.
Altitude: 1,000 feet (304 m) on a standard day.
Overhaul costs are based on participation in factory exchange program.
Engine fleet maintenance costs provided by Rolls-Royce Engine Company.
Indirect costs such as insurance, hangar, salary, etc., are not included.
Actual costs will vary, depending on local operating conditions, pricing, and supplier practices.
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MDHI PROPRIETARY
MD 600N
Technical Description
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MDHI PROPRIETARY
MD 600N
Technical Description
8. PRODUCT SUPPORT
MD Helicopters, Inc. is dedicated to a successful fielding, training, warranty support, and
customer support of MDHI aircraft. MD Helicopters, Inc. has worldwide service centers and
field service representatives available for localized support.
8.1 Training
The MDHI commercial training center offers cost-effective, factory-designed transition-flight
and maintenance-crew training courses for MDHI-manufactured helicopters. This training,
conducted by senior instructors with extensive product experience, provides customers / students
with the detailed knowledge of MDHI products that will increase safety, reduce insurance costs,
and result in more efficient operation of the aircraft. Training is conducted at the MDHI facility
in Mesa, Arizona. Training using customer aircraft can also be arranged provided insurance,
meeting MDHI requirements, is available.
8.1.1 Pilot Training
Transition flight, maintenance test, and recurrent pilot training are available from MDHI. Flight
transition pilot training for one pilot is included as part of each MDHI helicopter purchase.
8.1.2 Transition Flight Training
The transition flight training course is designed to familiarize a rated helicopter pilot with
operation of the MDHI aircraft. The transition flight training course is a five-day course that
introduces the student to all the associated company publications, as well as detailed
explanations of all aircraft systems and daily / preflight procedures. The ground school requires
16 to 20 hours to complete, including examination and examination review. The student is
expected to pass the examination, demonstrating basic knowledge of the aircraft. The transition
flight training syllabus includes six hours of instructor time and is provided in four flight lessons:
 Normal operations
 Advanced operations (maximum gross weight flight)
 Maintenance and systems operations
 Emergency / malfunction procedures.
8.1.3 Recurrent Flight Training
Additional, optional, recurrent pilot training is available for existing MD 600N pilots. Recurrent
pilot training provides a pilot review of MD 600N helicopter systems and operations, and uses
flight review, proficiency checks, or other checks to review rules, maneuvers, and procedures to
demonstrate existing pilot skills. Training is conducted over a three-day period and consists of
ground school and two to three hours of flight time. Ground school training includes a review
and discussion of airworthiness directives and notices, helicopter systems, pilot flight manual
review, preflight inspection, followed by an open-book examination.
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MDHI PROPRIETARY
MD 600N
Technical Description
8.1.4 Maintenance Training
The airframe maintenance course familiarizes a licensed aircraft and powerplant mechanic with
the maintenance and inspection of aircraft major systems. Training adheres to original equipment
manufacturer standards and includes an overview of supporting maintenance documentation,
service bulletins, service letters, and maintenance logbook. All training materials required to
conduct maintainer training (i.e., instructional materials, handouts, presentations, training guides
/ aids, tests / exercises) are returned to each trainee. Hands-on training using MDHI- or
customer-furnished equipment will be provided as necessary to supplement the classroom
instruction. Training instruction and technical information are conducted in the English
language. Course syllabus includes:
 Airframe
 Flight control system
 Environmental control system
 Power train
 Rotor system.
Maintainer training for one maintainer is provided as part of the helicopter purchase.
8.2 Warranty
The MD 600N commercial helicopters are covered by a commercial warranty which is
administered by MDHI Mesa, Arizona. Supplier products (e.g., turboshaft engine, avionics, etc.)
are separately warranted through the product supplier.
The MDHI Commercial Warranty is a materials and workmanship type warranty that begins
upon customer helicopter / spare parts acceptance / delivery. The customer will perform prompt
repair or replacement of helicopter specific discrepant hardware. For warranty claims pertaining
to aftermarket spare parts and components, the customer, at their option (with prior approval),
either:
 Returns the non-conforming or defective part or component for credit or refund; or
 Requests correction or replacement of the affected part or component. Associated
shipping costs shall be shared by the customer and the vendor.
8.2.1 Warranty Claims
All warranty claims begin with completion of an MDHI service and operations report (SOR)
document. The completed SOR document is submitted to MDHI field services for technical
accuracy and completeness review and to determine if additional action is needed. When the
review is completed, the SOR is forwarded to the MDHI warranty / repair department for
determination of warranty claim status. The circumstances of the failure, aircraft and component
time, date of submittal and nature of the claim, and other factors, are evaluated in accordance
with the current published MDHI warranty. The limited commercial warranty (CSP-A-2) and
SOR forms can be accessed through the MDHI website.
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MDHI PROPRIETARY
MD 600N
Technical Description
8.3 Service Centers
MD Helicopters, Inc. has approved service centers located worldwide. The figure below shows
MDHI worldwide approved service centers locations. Detailed service center information is
provided on the MD Helicopters website.
8.4 Field Service
Dedicated Field Service Representatives are available to support fielded MDHI products. Field
Service Representatives are available for the following locations:
 Asia / India / Australia / New Zealand
 Eastern North America
 Middle East / Africa
 Mexico /Central America / South America
 Russia / Commonwealth of Independent States
 Western North America.
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MDHI PROPRIETARY
MD 600N
Technical Description
MD Helicopters, Inc. Worldwide Service Center Locations
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MDHI PROPRIETARY