MD Helicopters MD500 Series Technical Description
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MD Helicopters MD500 Series Technical Description

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Summary of Contents for MD Helicopters MD500 Series

  • Page 2: Technical Description

    January 2001 products and therefore the right is reserved to make changes without notice in the design or manufacture of the MD 500 © 2001 MD Helicopters, Inc. All rights reserved. series helicopter which may be considered necessary. MD 500E ®...

  • Page 4: Table Of Contents

    M D 6 0 0 N CONTENTS Paragraph Page HIGH PERFORMANCE................3 EQUIPMENT.....................4-5 PERFORMANCE SPECIFICATIONS ...........6-7 HIGE / C20B ...................8 HOGE / C20B..................9 Gross Weight Worksheet / C20B............10 Payload & Range / C20B...............11 Speed for Best Range / C20B ...............12 Speed for Best Endurance / C20B ............13 Fuel Consumption / C20B ..............14-17 3.11 HIGE / C20R ..................18...
  • Page 5 M D 6 0 0 N – 2 –...

  • Page 6: High Performance

    M D 6 0 0 N THE HIGH PERFORMANCE LIGHT HELICOPTER 1.0 High performance. The MD 500E delivers the highest speed, payload and productivity in its class. Rear seat passengers have greater headroom and visibility than earlier Model 500s. Refinements pro- vide first class front and rear seating with ample legroom.

  • Page 7: Equipment

    M D 6 0 0 N STANDARD EQUIPMENT 2.0 Equipment. Airframe Engine and Electrical Tinted canopy panels Allison 250-C20B engine, 420 shp (313 kw) Tinted door/window panel-left front Automatic engine reignition Tinted door/window panel-left rear Engine wash kit, MD 500 series Tinted door/window panel-right front Engine compressor anti-ice Tinted door/window panel-right rear...
  • Page 8 M D 6 0 0 N STANDARD EQUIPMENT Annunciator Panel Optional Accessory Examples Battery overtemp warning light Heater/defogger Engine chip detector warning light Dual flight controls, LH standard, RH optional Engine out warning light Engine wash kit Fuel filter obstruction warning light Particle separator (with air filter clog caution light) Fuel low warning light Heated pitot tube...

  • Page 9: Performance Specifications

    M D 6 0 0 N WITH C20B ENGINE PERFORMANCE SPECIFICATIONS Characteristics Metric Imperial at Design Gross Weight 1361 kg 3,000 lb Maximum Cruise Speed: Sea level 249 km/hr 135 kt (155 mph) 1524 m (5,000 ft) 246 km/hr 133 kt (153 mph) Maximum Permitted Speed: V NE at sea level 282 km/hr...
  • Page 10 M D 6 0 0 N WITH C20R ENGINE PERFORMANCE SPECIFICATIONS Characteristics Metric Imperial at Design Gross Weight 1361 kg 3,000 lb Maximum Cruise Speed: Sea level 249 km/hr 135 kt (155 mph) 1524 m (5,000 ft) 251 km/hr 136 kt (156 mph) Maximum Permitted Speed: V NE at sea level 282 km/hr...

  • Page 11: Hige / C20B

    M D 6 0 0 N WITH C20B ENGINE 3.1 Hover-In-Ground-Effect. – 8 –...

  • Page 12: Hoge / C20B

    M D 6 0 0 N WITH C20B ENGINE 3.2 Hover-Out of-Ground-Effect. – 9 –...

  • Page 13: Gross Weight Worksheet / C20B

    M D 6 0 0 N WITH C20B ENGINE 3.3 Takeoff Gross Weight Worksheet. C20B Mission #1 Mission #2 Empty Weight 1,481 lb (672 kg) Pilot 170 lb (77 kg) Fuel 403 lb (183 kg) Payload 946 lb (428 kg) Takeoff GW 3,000 lb (1361 kg)

  • Page 14: Payload & Range / C20B

    M D 6 0 0 N WITH C20B ENGINE 3.4 Payload vs Range (5000’, ISA). RANGE   n m – 11 –...

  • Page 15: Speed For Best Range / C20B

    M D 6 0 0 N WITH C20B ENGINE 3.5 Speed for Best Range. – 12 –...

  • Page 16: Speed For Best Endurance / C20B

    M D 6 0 0 N WITH C20B ENGINE 3.6 Speed for Best Endurance. – 13 –...

  • Page 17: Fuel Consumption / C20B

    WITH C20B ENGINE 3.7 Fuel Flow, Sea Level, ISA (15°C). Note: Use for Estimates Only. Not FAA Approved. Based on clean aircraft, level flight performance, minimum specification engine, particle separator and 10 ampere electrical load. – 14 –...
  • Page 18 M D 6 0 0 N WITH C20B ENGINE 3.8 Fuel Flow, Sea Level, ISA +20°C (35°C). Note: Use for Estimates Only. Not FAA Approved. Based on clean aircraft, level flight performance, minimum specification engine, particle separator and 10 ampere electrical load. –...
  • Page 19 M D 6 0 0 N WITH C20B ENGINE 3.9 Fuel Flow, 4,000 feet, ISA (7°C). Note: Use for Estimates Only. Not FAA Approved. Based on clean aircraft, level flight performance, minimum specification engine, particle separator and 10 ampere electrical load. –...
  • Page 20 M D 6 0 0 N WITH C20B ENGINE 3.10 Fuel Flow, 4,000 feet, ISA +20°C (27°C). Note: Use for Estimates Only. Not FAA Approved. Based on clean aircraft, level flight performance, minimum specification engine, particle separator and 10 ampere electrical load. –...

  • Page 21: Hige / C20R

    M D 6 0 0 N WITH C20R ENGINE 3.11 Hover-In-Ground-Effect. – 18 –...

  • Page 22: Hoge / C20R

    M D 6 0 0 N WITH C20R ENGINE 3.12 Hover-Out of-Ground-Effect. – 19 –...

  • Page 23: Gross Weight Worksheet / C20R

    M D 6 0 0 N WITH C20R ENGINE 3.13 Takeoff Gross Weight Worksheet. C20R Mission #1 Mission #2 Empty Weight 1,517 lb (688 kg) Pilot 170 lb (77 kg) Fuel 403 lb (183 kg) Payload 910 lb (413 kg) Takeoff GW 3,000 lb (1361 kg)

  • Page 24: Payload & Range / C20R

    M D 6 0 0 N WITH C20R ENGINE 3.14 Payload vs Range (5000’, ISA). RANGE   n m – 21 –...

  • Page 25: Speed For Best Range / C20R

    M D 6 0 0 N WITH C20R ENGINE 3.15 Speed for Best Range. – 22 –...

  • Page 26: Speed For Best Endurance / C20R

    M D 6 0 0 N WITH C20R ENGINE 3.16 Speed for Best Endurance. – 23 –...

  • Page 27: Fuel Consumption / C20R

    M D 6 0 0 N WITH C20R ENGINE 3.17 Fuel Flow, Sea Level, ISA (15°C). Note: Use for Estimates Only. Not FAA Approved. Based on clean aircraft, level flight performance, minimum specification engine, particle separator and 10 ampere electrical load. –...
  • Page 28 M D 6 0 0 N WITH C20R ENGINE 3.18 Fuel Flow, Sea Level, ISA +20°C (35°C). Note: Use for Estimates Only. Not FAA Approved. Based on clean aircraft, level flight performance, minimum specification engine, particle separator and 10 ampere electrical load. –...
  • Page 29 M D 6 0 0 N WITH C20R ENGINE 3.19 Fuel Flow, 4,000 feet, ISA (7°C). Note: Use for Estimates Only. Not FAA Approved. Based on clean aircraft, level flight performance, minimum specification engine, particle separator and 10 ampere electrical load. –...
  • Page 30 M D 6 0 0 N WITH C20R ENGINE 3.20 Fuel Flow, 4,000 feet, ISA +20°C (27°C). Note: Use for Estimates Only. Not FAA Approved. Based on clean aircraft, level flight performance, minimum specification engine, particle separator and 10 ampere electrical load. –...

  • Page 31: Direct Operating Cost

    M D 6 0 0 N 2001 ESTIMATED DIRECT OPERATING COST 4.0 Direct Operating Cost. Estimated Direct Operating Cost Per Hour (Based upon year 2001 US $) C20 B C20 RS Engine Engine Fuel and Lubricants 1 : Fuel @ $2.06* per gallon @ approx. 25/27 gallons per hour ..$ 51.50 55.62 Lubricants @ 3% of fuel ..............1.55 1.67...
  • Page 32 M D 6 0 0 N TOTAL COST OF OPERATION WORKSHEET Direct Operating Cost per Hour Fuel and Lubricants Fuel @ $_______ per gallon @ approx._____ gallons per hour ....$ ________ Lubricants @ _____ % of fuel ..............$ ________ ....................$ ________ (A) Total Fuel Cost Airframe Maintenance and Spares Scheduled maintenance labor rate @ $_____ per hour...
  • Page 33 M D 6 0 0 N COMPONENT MAINTENANCE SCHEDULE LIMITED-LIFE PARTS OVERHAUL SYSTEMS Component Finite Time (hr) Component Finite Time (hr) Transmission/MR 5,000 Main Rotor Blade 3,530 M/R Swashplate 2,770 Blade Pin 7,600 M/R Hub 2,770 Main Rotor Hub 8,900 Overrunning, Clutch 1,800 Pitch Housing/MR...
  • Page 34 M D 6 0 0 N CONTENTS Paragraph Page HIGH PERFORMANCE................33 EQUIPMENT ....................34 PERFORMANCE SPECIFICATIONS.............35 HIGE .....................36 HOGE ....................37 Gross Weight Worksheet ...............38 Payload & Range ...................39 Speed for Best Range ................40 Speed for Best Endurance..............41 Fuel Consumption ................42-45 DIRECT OPERATING COST .............46-48 –...
  • Page 35 M D 6 0 0 N – 32 –...

  • Page 36: High Performance

    M D 6 0 0 N HOT DAY/HIGH ALTITUDE HELICOPTER 1.0 Hot Day/High Altitude Helicopter. The MD 530F is engineered to meet your requirements for hot-day, high-altitude opera- tion. Equipped with the 650 shp Allison 250-C30 engine, the MD 530F operates more effectively in hot, high environments than other helicopters in its class.

  • Page 37: Equipment

    M D 6 0 0 N STANDARD EQUIPMENT 2.0 Equipment. Airframe Rotor and Controls Tinted canopy panels Flight controls, single, left hand command Tinted door/window panel-left front Flight and Engine Instruments Tinted door/window panel-left rear Dual tachometer, N R and N 2 Tinted door/window panel-right front Engine oil pressure indicator Tinted door/window panel-right rear...

  • Page 38: Performance Specifications

    M D 6 0 0 N HOT DAY/HIGH ALTITUDE HELICOPTER 3.0 Performance Specifications. Characteristics Metric Imperial at Design Gross Weight 1406 kg 3,100 lb Maximum Cruise Speed: Sea level 248 km/hr 134 kt (154 mph) 1524 m (5,000 ft) 249 km/hr 135 kt (155 mph) Maximum Permitted Speed: V NE at sea level...

  • Page 39: Hige

    M D 6 0 0 N WITH C30 ENGINE 3.1 Hover-In-Ground-Effect. – 36 –...

  • Page 40: Hoge

    M D 6 0 0 N WITH C30 ENGINE 3.2 Hover-Out of-Ground-Effect. – 37 –...

  • Page 41: Gross Weight Worksheet

    M D 6 0 0 N WITH C30 ENGINE 3.3 Takeoff Gross Weight Worksheet. Example Mission #1 Mission #2 Empty Weight 1,591 lb (722 kg) Pilot 170 lb (77 kg) Fuel 403 lb (183 kg) Payload 936 lb (424 kg) Takeoff GW 3,100 lb (1406 kg)

  • Page 42: Payload & Range

    M D 6 0 0 N WITH C30 ENGINE 3.4 Payload vs Range (5000’, ISA). RANGE   n m – 39 –...

  • Page 43: Speed For Best Range

    M D 6 0 0 N WITH C30 ENGINE 3.5 Speed for Best Range. – 40 –...

  • Page 44: Speed For Best Endurance

    M D 6 0 0 N WITH C30 ENGINE 3.6 Speed for Best Endurance. – 41 –...

  • Page 45: Fuel Consumption

    M D 6 0 0 N WITH C30 ENGINE 3.7 Fuel Flow, Sea Level, ISA (15°C). Note: Use for Estimates Only. Not FAA Approved. Based on clean aircraft, level flight performance, minimum specification engine, particle separator and 10 ampere electrical load. –...
  • Page 46 M D 6 0 0 N WITH C30 ENGINE 3.8 Fuel Flow, Sea Level, ISA +20°C (35°C). Note: Use for Estimates Only. Not FAA Approved. Based on clean aircraft, level flight performance, minimum specification engine, particle separator and 10 ampere electrical load. –...
  • Page 47 M D 6 0 0 N WITH C30 ENGINE 3.9 Fuel Flow, 4,000 feet, ISA (7°C). Note: Use for Estimates Only. Not FAA Approved. Based on clean aircraft, level flight performance, minimum specification engine, particle separator and 10 ampere electrical load. –...
  • Page 48 M D 6 0 0 N WITH C30 ENGINE 3.10 Fuel Flow, 4,000 feet, ISA +20°C (27°C). Note: Use for Estimates Only. Not FAA Approved. Based on clean aircraft, level flight performance, minimum specification engine, particle separator and 10 ampere electrical load. –...

  • Page 49: Direct Operating Cost

    M D 6 0 0 N 2001 ESTIMATED DIRECT OPERATING COST 4.0 Direct Operating Cost. Estimated Direct Operating Cost Per Hour (Based upon year 2001 US $) C30 Engine Fuel and Lubricants 1 : Fuel @ $2.06* per gallon @ approx. 32 gallons per hour ....$ 65.92 Lubricants @ 3% of fuel ..............1.98 Total Fuel Cost ........................$ 67.90 Airframe Maintenance and Spares 2 :...
  • Page 50 M D 6 0 0 N TOTAL COST OF OPERATION WORKSHEET Direct Operating Cost per Hour Fuel and Lubricants Fuel @ $_______ per gallon @ approx._____ gallons per hour ....$ ________ Lubricants @ _____ % of fuel ..............$ ________ ....................$ ________ (A) Total Fuel Cost Airframe Maintenance and Spares Scheduled maintenance labor rate @ $_____ per hour...
  • Page 51 COMPONENT MAINTENANCE SCHEDULE LIMITED-LIFE PARTS OVERHAUL SYSTEMS Component Finite Time (hr) Component Finite Time (hr) Main Rotor Transmission 5,000 Main Rotor Blade 3,430 Main Rotor Swashplate 2,770 Blade Pin 7,600 Main Rotor Hub 2,770 Main Rotor Hub 8,900 Overrunning Clutch 1,800 Pitch Housing/MR 9,100...
  • Page 52 M D 6 0 0 N CONTENTS Paragraph Page LAW ENFORCEMENT CONFIGURATION ..........50 SYSTEM DESCRIPTION ..............51-61 EQUIPMENT ....................62 PERFORMANCE SPECIFICATIONS.............63 HIGE......................64 HOGE ....................65 Gross Weight Worksheet ...............66 Payload & Range ...................67 Speed for Best Range ................68 Speed for Best Endurance..............69 Fuel Consumption ................70-73 DIRECT OPERATING COST .............74-76 –...

  • Page 53: Law Enforcement Configuration

    M D 6 0 0 N SYSTEM DESCRIPTION 1.0 MD 520N Airborne Law Enforcement Configuration Fast: Vne of l75 miles per hour (250 kph) 154 Miles per hour cruise speed (244 kph) Agile: Zero -0.5 g maneuvers NOTAR system precision attitude/directional control Powerful: Useful load at maximum gross weight: 1,764 pounds (800 kg) internal...
  • Page 54 M D 6 0 0 N SYSTEM DESCRIPTION 2.0 MD 520N Design Description The MDHI 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, passen- ger/crew safety and handling and performance capabilities.
  • Page 55 M D 6 0 0 N SYSTEM DESCRIPTION 1.9 m 1.4 m 2.0 m (6.3 ft) (4.6 ft) (6.6 ft) 8.3 m (27.4 ft) Dia. 9.8 m (32.1 ft) 7.8 m (25.5 ft) 2.9 m (9.7 ft) 2.8 m 2.8 m (9.3 ft) (9.2 ft) 2.4 m...
  • Page 56 M D 6 0 0 N SYSTEM DESCRIPTION Five-Blade Fully Articulated Main Rotor Crashworthy A-Frame Truss with Integral Crew Seats Static Mast Rotor Support Outstanding Outward Visibility ® NOTAR Anti-Torque System 425 shp Drive System Simple Mechanical Controls Rolls-Royce 250-C20R 450 shp Turbine Engine Flat Cargo Floor Five-Place Seating Capacity MD 520N Inboard Profile and Features...
  • Page 57 M D 6 0 0 N SYSTEM DESCRIPTION MD 520N On Patrol Four doors are installed on the MD 520N - two on each side. The two forward doors permit access to the forward compartment for pilot and copilot/passengers. The two aft doors allow entry to the passenger/cargo compartment.
  • Page 58 M D 6 0 0 N SYSTEM DESCRIPTION Torque is transmitted independently to the rotor through an internal main rotor drive shaft. Lifting loads reacted by the static mast are prevented from being imposed through the drive shaft onto the main transmission, thus eliminating thrust loading of transmission parts.
  • Page 59 M D 6 0 0 N SYSTEM DESCRIPTION Interchangeability Parts and assemblies listed below are interchangeable. Main rotor blade (tracking of new blades may be required) Main rotor hub assembly Lead-lag damper Main rotor drive shaft Main rotor mast Main transmission Overrunning clutch Main drive shaft Engine assembly...
  • Page 60 M D 6 0 0 N SYSTEM DESCRIPTION NOTAR ® ANTI-TORQUE SYSTEM Greater Safety U.S. FAA, NTSB and U.S. Army Studies have shown that 22% of all crashes are due to tailrotor strikes and loss of tail rotor effectiveness. NOTAR® systems eliminate these problems.
  • Page 61 M D 6 0 0 N SYSTEM DESCRIPTION DESCRIPTION OF THE NOTAR® SYSTEM The NOTAR system is an anti-torque system made up of an enclosed fan driven by the main rotor transmission, a circulation control tailboom, a direct jet thruster and a hori- zontal stabilizer with two vertical stabilators.
  • Page 62 M D 6 0 0 N SYSTEM DESCRIPTION In hover flight, the circulation control tail boom provides the majority of the required main rotor anti-torque. This is accomplished by two slots along the tailboom that energize the downwash flow from the main rotor. The result is lift in a horizontal direction that replaces the push of a conventional tail rotor.
  • Page 63 M D 6 0 0 N SYSTEM DESCRIPTION LOW EXTERNAL NOISE The elimination of the high-tip-speed tail rotor assembly makes the MD 520N the qui- etest turbine helicopter in the world. Recent comparative FAA tests conducted by MDHI indicate the MD 520N is a minimum of 50 percent quieter than comparable helicopters. This lower noise signature makes the MD 520N a “good neighbor’...
  • Page 64 M D 6 0 0 N SYSTEM DESCRIPTION INHERENT SAFETY The NOTAR anti-torque system eliminates accidents 6% All Accidents 14% Accidents Saved and mishaps caused by the exposed tail rotor strik- Avoidable With NOTAR System ing objects in flight, and significantly reduces ground incidents with people or equipment.

  • Page 65: Equipment

    M D 6 0 0 N STANDARD EQUIPMENT 3.0 Equipment. Airframe Rotor and Controls Tinted canopy panels Flight controls, single, left hand command Tinted door/window panel-left front Flight and Engine Instruments Tinted door/window panel-left rear Dual tachometer, N R and N 2 Tinted door/window panel-right front Engine oil pressure indicator Tinted door/window panel-right rear...

  • Page 66: Performance Specifications

    M D 6 0 0 N WITH NOTAR SYSTEM 4.0 Performance Specifications Characteristics Metric Imperial Metric Imperial at Gross Weight 1361 kg 3,000 lb 1519 kg 3,350 lb Maximum Cruise Speed: Sea level 237 km/hr 128 kt (147 mph) 229 km/hr 123 kt (142 mph) 1524 m (5,000 ft) 245 km/hr 132 kt (152 mph) 230 km/hr 124 kt (143 mph)

  • Page 67: Hige

    M D 6 0 0 N WITH C20R ENGINE 4.1 Hover-In-Ground-Effect. – 64 –...

  • Page 68: Hoge

    M D 6 0 0 N WITH C20R ENGINE 4.2 Hover-Out of-Ground-Effect. – 65 –...

  • Page 69: Gross Weight Worksheet

    M D 6 0 0 N WITH C20R ENGINE 4.3 Takeoff Gross Weight Worksheet. Example Mission #1 Mission #2 Empty Weight 1,585 lb (719 kg) Pilot 170 lb (77 kg) Fuel 403 lb (183 kg) Payload 1192 lb (540 kg) Takeoff GW 3,350 lb (1519 kg)

  • Page 70: Payload & Range

    M D 6 0 0 N WITH C20R ENGINE 4.4 Payload vs Range (5000’, ISA). RANGE   n m – 67 –...

  • Page 71: Speed For Best Range

    M D 6 0 0 N WITH C20R ENGINE 4.5 Speed for Best Range. – 68 –...

  • Page 72: Speed For Best Endurance

    M D 6 0 0 N WITH C20R ENGINE 4.6 Speed for Best Endurance. – 69 –...

  • Page 73: Fuel Consumption

    M D 6 0 0 N WITH C20R ENGINE 4.7 Fuel Flow, Sea Level, ISA (15°C). Note: Use for Estimates Only. Not FAA Approved. Based on clean aircraft, level flight performance, minimum specification engine, particle separator and 10 ampere electrical load. –...
  • Page 74 M D 6 0 0 N WITH C20R ENGINE 4.8 Fuel Flow, Sea Level, ISA +20°C (35°C). Note: Use for Estimates Only. Not FAA Approved. Based on clean aircraft, level flight performance, minimum specification engine, particle separator and 10 ampere electrical load. –...
  • Page 75 M D 6 0 0 N WITH C20R ENGINE 4.9 Fuel Flow, 4,000 feet, ISA (7°C). Note: Use for Estimates Only. Not FAA Approved. Based on clean aircraft, level flight performance, minimum specification engine, particle separator and 10 ampere electrical load. –...
  • Page 76 M D 6 0 0 N WITH C20R ENGINE 4.10 Fuel Flow, 4,000 feet, ISA +20°C (27°C). Note: Use for Estimates Only. Not FAA Approved. Based on clean aircraft, level flight performance, minimum specification engine, particle separator and 10 ampere electrical load. –...

  • Page 77: Direct Operating Cost

    M D 6 0 0 N 2001 ESTIMATED DIRECT OPERATING COST 5.0 Direct Operating Cost. Estimated Direct Operating Cost Per Hour (Based upon year 2001 US $) C20RS Engine Fuel and Lubricants 1 : Fuel @ $2.06* per gallon @ approx. 27 gallons per hour ....$ 55.62 Lubricants @ 3% of fuel ..............1.67 Total Fuel Cost ........................$ 57.29 Airframe Maintenance and Spares 2 :...
  • Page 78 M D 6 0 0 N TOTAL COST OF OPERATION WORKSHEET Direct Operating Cost per Hour Fuel and Lubricants Fuel @ $_______ per gallon @ approx._____ gallons per hour ....$ ________ Lubricants @ _____ % of fuel ..............$ ________ ....................$ ________ (A) Total Fuel Cost Airframe Maintenance and Spares Scheduled maintenance labor rate @ $_____ per hour...
  • Page 79 M D 6 0 0 N COMPONENT MAINTENANCE SCHEDULE LIMITED-LIFE PARTS OVERHAUL SYSTEMS Component Finite Time (hr) Component Finite Time (hr) Transmission/MR 5,000 Main Rotor Blade 3,430 M/R Swashplate 2,770 Blade Pin 7,600 M/R Hub 2,770 Main Rotor Hub 8,900 Overrunning Clutch 1,800 Pitch Housing/MR...
  • Page 80 M D 6 0 0 N MDHI PRODUCT SUPPORT PLAN With the launch of the new helicopter company, MD Helicopters, Inc. announces its new Product Support Plan. Named The MDHI Support Plan 2000 , it signifies MDHI’s commit- ment to satisfy the operators of its products now and well into the next century.
  • Page 81 MDHI PRODUCT SUPPORT PLAN IInitial Fielding All new aircraft customers will be greeted at their facility by a Customer Support Technical Representative who is trained specifically on the operation and maintenance of MDHI heli- copters. These Technical Representatives are backed up by a factory team of MDHI Product Support Engineers who can be called upon at any time to support specific tech- nical issues or questions that may arise.
  • Page 82 M D 6 0 0 N TRAINING 7.0 Training The MDHI Commercial Training Center offers cost-effective factory designed training courses for MD 500 series pilots and maintenance crews. This training, given by senior instructors with extensive experience in our products, provides our customers/students with the detailed knowledge of our products that will increase safety, reduce insur-...
  • Page 83 M D 6 0 0 N TRAINING Maintenance Training The Airframe Maintenance Course is designed to familiarize a licensed A & P mechanic with the maintenance and inspection of all major systems on the aircraft. This 2-week course will require the student to learn and demonstrate the skill and knowledge required to safely perform selected maintenance tasks on the MD 500 series.
  • Page 84 M D 6 0 0 N OPTIONAL EQUIPMENT Airspeed/Time ASTROTECH LC-6 CLOCK DAVTRON N877 CLOCK HEATED PITOT Altitude KRA10-00 RADAR ALT W/KI250 IND KRA405B-15 RADAR ALT W/KNI416 IND 10.5 UNITED 5035 ENCODING ALTIMETER UNITED 5120 BLIND ENCODER UNITED 7130-C41 IVSI Altitude/Heading AIM ATITUDE GYRO 510-1B AIM DIRECTIONAL GYRO 205-1BL...
  • Page 85 M D 6 0 0 N OPTIONAL EQUIPMENT Comm/Intercom FLIGHT TRAILS AVIONICS MASTER SWITCH FLIGHT TRAILS COPILOT ICS FOOT SWITCH FLIGHT TRAILS CYCLIC REMOTE FREQ SWITCH ONLY FLIGHT TRAILS REAR SEAT TRANSMIT HEADSET BOSE SERIES II HEADSET BOSE SERIES X HEADSET DAVID CLARK H10-56 HEADSET WIRE HARNESS (W/O ICS) W/ADAPTS KFM985 FM TRANSCEIVER...
  • Page 86 M D 6 0 0 N OPTIONAL EQUIPMENT Comm/Nav Emergency LOC TRANS, ARTEX-100HM Emergency LOC transmitter pointer 3000 FOXTRONICS 3050 wide band antennna KDF806-00 ADF w/KFS586 freq selector KI202-00 VOR/LOC indicator KI203-00 VOR/LOC indicator KI204-02 VOR/LOC/GS indicator KI206-04 VOR/LOC/GS indicator KI208-00 VOR/LOC indicator KI209-01 VOR/LOC/GS indicator KN53-00 NAV receiver w/GLS...
  • Page 87 M D 6 0 0 N OPTIONAL EQUIPMENT Engine ENGINE COMPRESSOR ANTI-ICE ENGINE OIL EXHAUST BREATHER FACET OIL FILTER - MD530FF HOBBS COLLECTIVE RUNNING TIME METER MIST ELIMINATOR PARTICLE SEPARATOR 13.0 SYSTRON DONNER FIRE DETECTION SYSTEM Environmental AERO-AIRE BOOST FAN AIR CONDITIONING, INTEGRATED FLIGHT SYSTEMS 88.8 40.3...
  • Page 88 M D 6 0 0 N OPTIONAL EQUIPMENT Fuel System AIRFRAME FUEL FILTER FARGO 21 GAL (79L) AUX FUEL TANK 44.5 20.2 POVISIONS FARGO 21 GAL (79L) AUX FUEL TANK ROBERTSON 38.5 GAL (146L) AUX FUEL TANK 56.0 25.4 PROVISIONS ROBERTSON 38.5 GAL (146L) AUX FUEL TANK SELF SEALING FUEL CELLS 21.2 SHADIN DIGIDATA FUEL AIR DATA SYSTEM...
  • Page 89 OPTIONAL EQUIPMENT Interior Accessories CABIN LIGHTER/28-VOLT UTILITY OUTLET COCKPIT UTILITY-MAP GOOSENECK LIGHT - NVG COCKPIT UTILITY-MAP LUMINATOR LIGHT - NON-NVG COCKPIT UTILITY-MAP LUMINATOR LIGHT - NVG FLIGHT TRAILS INSTRUMENT PANEL MAP CASE FLIGHT TRAILS LH FWD MAP CASE LITTER KIT RIGHT HAND 66.0 29.9 ROTOR BRAKE LH COMMAND...
  • Page 90 OPTIONAL EQUIPMENT Paint HIGH VISIBILITY MAIN ROTOR BLADE PAINT PAINT 0 COLOR PRIMER ONLY 500 SERIES -20.0 -9.1 PAINT 2 COLOR AMBASSADOR PAINT 2 COLOR CUSTOM 2 PAINT 2 COLOR DIPLOMAT PAINT 2 COLOR ENVOY PAINT 2 COLOR STATESMAN PAINT 2 COLOR VICEROY PAINT 3 COLOR AMBASSADOR PAINT 3 COLOR CUSTOM 3 PAINT 3 COLOR DIPLOMAT...
  • Page 91 MD HELICOPTERS, INC. phone 1-480-346-6300 fax 1-480-346-6339 helicoptersales@mdhelicopters.com www.mdhelicopters.com...

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