MD Helicopters MD500, MD500E, MD530F, MD520N Technical Description

Download

600

Technical Description

Comments and/or questions may be directed to:

e-mail: helicoptersales@mdhelicopters.com

Revised January 2001

MD 500E

. MD 530F®, MD 520N®are trademarks of MD Helicopters, Inc.

Marketing and Sales

4555 E. McDowell Road

Mesa, Arizona 85215-9797

Sales: (480) 346-6300

Fax: (480) 346-6339

This Technical Description is not subject to a revision service. It is the manufacturer’s practice to continuously improve its products and therefore the right is reserved to make changes without notice in the design or manufacture of the MD 500 series helicopter which may be considered necessary.

600

CONTENTS

Paragraph Page

1.0 HIGH PERFORMANCE..............................................................................3

2.0 EQUIPMENT.............................................................................................4-5

3.0 PERFORMANCE SPECIFICATIONS ...................................................6-7

3.1 HIGE / C20B ...........................................................................................8

3.2 HOGE / C20B..........................................................................................9

3.3 Gross Weight Worksheet / C20B...........................................................10

3.4 Payload & Range / C20B.......................................................................11

3.5 Speed for Best Range / C20B ...............................................................12

3.6 Speed for Best Endurance / C20B ........................................................13

3.7 Fuel Consumption / C20B................................................................14-17

3.11 HIGE / C20R .........................................................................................18

3.12 HOGE / C20R........................................................................................19

3.13 Gross Weight Worksheet / C20R...........................................................20

3.14 Payload & Range / C20R.......................................................................21

3.15 Speed for Best Range / C20R ...............................................................22

3.16 Speed for Best Endurance / C20R ........................................................23

3.17 Fuel Consumption / C20R................................................................24-27

4.0 DIRECT OPERATING COST ..................................................................28

– 1 –

600

– 2 –

1.4 m

(4.6 ft)

Dia

1.0 m

(3.3 ft)

3.0 m

(9.8 ft)

2.8 m

(9.2 ft)

2.4 m

(7.8 ft)

2.9 m

(9.7 ft)

0.7 m (2.4 ft)

9.4 m (30.8 ft)

7.5 m (24.6 ft)

600

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 provide first class front and rear seating with ample legroom. The T-shaped instrument panel provides space for a full complement of modern avionics.

With a five-bladed main rotor and the choice of a 420-shp Allison 250-C20B or 450-shp Allison 250-C20R turbine engine, the MD 500E is the best performing helicopter in its class.

The MD 500E light turbine helicopter allows easy configuration conversions from a deluxe, five-place executive transport to a utility cargo carrier. Typical uses include urban and remote location transportation of key personnel, technicians and craftsmen; aerial survey, patrol and photography; agricultural and fire-fighting appli-cations; air rescue operations; and numerous other tasks within the construction, petroleum and forestry industries.

Optional high-clearance skids permit operations in rough terrain, while other optional equipment, such as inflatable floats, litter kit and external baggage pods increase the MD 500E’s versatility.

Proven reliability of the derated turbine engine, fail-safe design and a worldwide network of factory-authorized service centers assure customer satisfaction.

1.9 m

(6.3 ft)

1.4 m

(4.6 ft)

8.1 m

(26.4 ft)

Dia

1.7 m

(5.4 ft)

MD 500E with optional extended landing gear.

NOTES

1. Helicopter on ground with full fuel. Typical attitude of cargo deck 5.3 degrees nose up.

2. Height-above-ground dimensions vary with installed equipment, center of gravity and terrain features.

3. If standard landing gear is installed, all vertical dimensions will be 0.3 m (1.0 ft) less.

– 3 –

STANDARD EQUIPMENT

2.0 Equipment.

Airframe

n Tinted canopy panels n Tinted door/window panel-left front n Tinted door/window panel-left rear n Tinted door/window panel-right front n Tinted door/window panel-right rear n Rain gutter set n Short landing gear n Keyed locks (4) n Fuselage hard points n Jacking fittings n Passenger steps n Anti-collision lights (2) n Landing light, nose mounted n Position lights n Paint 1 color standard

Interior

n Crew seats with 4-point harness restraint n Passenger seats with 3-point harness restraint n Vinyl and fabric cushions - 5 seats n Vinyl interior trim panels n Crew and cabin compartment floor carpet n Map case n Fire extinguisher n First aid kit n Crew ashtray and lighter/28-volt utility outlet n Cabin lighter/28-volt utility outlet n Battery-heavy duty Marathon 17-ampere-hour n Ventilation system n Cockpit utility light n Cabin convenience light n Instrument lighting n Cabin soundproofing n Cargo tie-down fittings

600

Engine and Electrical

n Allison 250-C20B engine, 420 shp (313 kw) n Automatic engine reignition n Engine wash kit, MD 500 series n Engine compressor anti-ice n 64 gallon (242 l) fuel system n 85 amp starter generator n External power receptacle

Rotor and Controls

n Flight controls, single, left hand command

Flight and Engine Instruments

n Dual tachometer, N

and N

n Engine oil pressure indicator n Engine torque meter n N

tachometer

n Hobbs engine running time meter n Fuel quantity indicator n Digital chronometer n Airspeed indicator n Barometric altimeter n DC ammeter n Outside air temperature indicator n Magnetic compass n Turbine outlet temp indicator n Engine oil temp indicator

– 4 –

STANDARD EQUIPMENT

600

Annunciator Panel

n Battery overtemp warning light n Engine chip detector warning light n Engine out warning light n Fuel filter obstruction warning light n Fuel low warning light n Generator out warning light n Low rotor rpm warning light n Main transmission chip detector warning light n Main transmission oil pressure warning light n Main transmission oil temp warning light n Tail rotor transmission chip detector warning light

Miscellaneous

n Ground handling wheels n Engine and airframe log books n Engine maintenance manual n Battery manual n Flight manual n Handbook of maintenance instructions n Illustrated parts catalog n Engine exhaust cover n Engine inlet cover n Pitot tube cover n Main rotor blade tie-downs

Optional Accessory Examples

n Heater/defogger n Dual flight controls, LH standard, RH optional n Engine wash kit n

Particle separator (with air filter clog caution light)

n Heated pitot tube n Cargo hook n Rotor brake n Airframe fuel filter (with airframe filter clog

caution light)

n Air conditioning n Comfort windows n Single litter kit n Wire strike n Emergency floats n Right-hand command controls n Accessories:

VHF, UHF, FM, AM transceivers Intercommunications system Custom soundproofing Sliding windows Mesh seats Floor intercom/transmit switch Slant instrument panel

n Avionics:

Encoding altimeter Stereo tape system Public address system Headset and microphone Master avionics switch Radar altimeter Transceiver Transponder GPS receiver Fuel totalizer Radio telephone Emergency locator transmitter

n Instruments:

Turn and bank indicator Instantaneous vertical speed indicator Attitude gyro Directional gyro

– 5 –

600

WITH C20B ENGINE

3.0

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: VNEat sea level 282 km/hr 152 kt (175 mph)

Maximum Range: Sea level 443 km 239 nm (275 mi)

1524 m (5,000 ft) 488 km 264 nm (304 mi)

Maximum Endurance: Sea level 2.7 hr 2.7 hr

Maximum Rate of Climb:(TOP) Sea level, Standard day 9.0 m/sec 1,770 fpm

ISA +20° C day 9.0 m/sec 1,776 fpm

Maximum Operating Altitude: Density Altitude 4877 m 16,000 ft

Service Ceiling: ISA 4227 m 13,900 ft

Maximum Hook Capacity: 907 kg 2,000 lb

Hovering Performance:

In-ground effect: Standard day 2591 m 8,500 ft

ISA + 20° C day 1829 m 6,000 ft

Out-of-ground effect: Standard day 1829 m 6,000 ft

ISA + 20° C day 945 m 3,100 ft

WEIGHTS

Characteristics Metric Imperial

Maximum Gross Weight: Normal category 1361 kg 3,000 lb

External load operations 1610 kg 3,550 lb

Empty Weight: Standard configuration 672 kg 1,481 lb

Useful Load: Normal category 689 kg 1,519 lb

External load operations 938 kg 2,069 lb

Usable Fuel Capacity: 242 L (64 gal) 183 kg 403 lb

POWER PLANT

Characteristics Metric Imperial

Allison Model 250-C20B gas turbine, Rated power: 313 kw 420 shp

Derated for reliability and safety to: Takeoff power: 280 kw 375 shp

Max. continuous power: 261 kw 350 shp

– 6 –

600

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: VNEat sea level 282 km/hr 152 kt (175 mph)

Maximum Range: Sea level 431 km 233 nm (268 mi)

1524 m (5,000 ft) 478 km 258 nm (297 mi)

Maximum Endurance: Sea level 2.5 hr 2.5 hr

Maximum Rate of Climb:(TOP) Sea level, Standard day 9.0 m/sec 1,770 fpm

ISA +20° C day 9.0 m/sec 1,776 fpm

Maximum Operating Altitude: Density Altitude 4877 m 16,000 ft

Service Ceiling: ISA 5029 m 16,500 ft

Maximum Hook Capacity: 907 kg 2,000 lb

Hovering Performance:

In-ground effect: Standard day 3444 m 11,300 ft

ISA + 20° C day 2103 m 6,900 ft

Out-of-ground effect: Standard day 2652 m 8,700 ft

ISA + 20° C day 1250 m 4,100 ft

WEIGHTS

Characteristics Metric Imperial

Maximum Gross Weight: Normal category 1361 kg 3,000 lb

External load operations 1610 kg 3,550 lb

Empty Weight: Standard configuration 688 kg 1,517 lb

Useful Load: Normal category 673 kg 1,483 lb

External load operations 922 kg 2,033 lb

Usable Fuel Capacity: 242 L (64 gal) 183 kg 403 lb

POWER PLANT

Characteristics Metric Imperial

Allison Model 250-C20R gas turbine, Rated power: 336 kw 450 shp

Derated for reliability and safety to: Takeoff power: 280 kw 375 shp

Max. continuous power: 261 kw 350 shp

– 7 –

3.1 Hover-In-Ground-Effect.

600

WITH C20B ENGINE

– 8 –

WITH C20B ENGINE

3.2 Hover-Out of-Ground-Effect.

600

– 9 –

WITH C20B ENGINE

3.3 Takeoff Gross Weight Worksheet.

600

Empty Weight

Pilot

Fuel

Payload

Takeoff GW

C20B

1,481 lb (672 kg)

170 lb (77 kg)

403 lb

(183 kg)

946 lb

(428 kg)

3,000 lb

(1361 kg)

Mission #1 Mission #2

– 10 –

WITH C20B ENGINE

3.4 Payload vs Range (5000’, ISA).

PAYLOAD

GW – empty weight – pilot – fuel

600

RANGE nm

0 50 100 150 200 250 300 350 0 93 185 278 370 463 557 648

– 11 –

3.5 Speed for Best Range.

600

WITH C20B ENGINE

– 12 –

WITH C20B ENGINE

3.6 Speed for Best Endurance.

600

– 13 –

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 –

600

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.

– 15 –

WITH C20B ENGINE

3.9 Fuel Flow, 4,000 feet, ISA (7°C).

600

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.

– 16 –

600

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.

– 17 –

3.11 Hover-In-Ground-Effect.

600

WITH C20R ENGINE

– 18 –

WITH C20R ENGINE

3.12 Hover-Out of-Ground-Effect.

600

– 19 –

WITH C20R ENGINE

3.13 Takeoff Gross Weight Worksheet.

600

Empty Weight

Pilot

Fuel

Payload

Takeoff GW

C20R

1,517 lb

(688 kg)

170 lb

(77 kg)

403 lb

(183 kg)

910 lb

(413 kg)

3,000 lb

(1361 kg)

Mission #1 Mission #2

– 20 –

WITH C20R ENGINE

3.14 Payload vs Range (5000’, ISA).

PAYLOAD

GW – empty weight – pilot – fuel

600

RANGE nm

0 50 100 150 200 250 300 350 0 93 185 278 370 463 557 648

– 21 –

3.15 Speed for Best Range.

600

WITH C20R ENGINE

– 22 –

WITH C20R ENGINE

3.16 Speed for Best Endurance.

600

– 23 –

WITH C20R ENGINE

3.17 Fuel Flow, Sea Level, ISA (15°C).

600

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.

– 24 –

600

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.

– 25 –

WITH C20R ENGINE

3.19 Fuel Flow, 4,000 feet, ISA (7°C).

600

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.

– 26 –

600

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.

– 27 –

2001 ESTIMATED DIRECT OPERATING COST

4.0 Direct Operating Cost.

Estimated Direct Operating Cost Per Hour (Based upon year 2001 US $)

600

C20 B C20 RS

Engine Engine

n Fuel and Lubricants

Fuel @ $2.06* per gallon @ approx. 25/27 gallons per hour ........$ 51.50 55.62

Lubricants @ 3% of fuel......................................................................1.55 1.67

Total Fuel Cost ..........................................................................................................$53.05 $57.29

n Airframe Maintenance and Spares

Maintenance labor costs:

Scheduled (.15 Manhours/Flight Hours) @ $58.00/Hour*................$ 8.70

Unscheduled (.26 Manhours/Flight Hours) @ $58.00/Hour* ............15.08

Spares Cost: Scheduled (Inspection) Parts: Used during periodic

inspection i.e. filters, seals, o-rings, etc. ..........................................$ 5.78

On-Condition/Unscheduled Part ......................................................20.11

Reserves: Component Overhaul (TBO) ............................................26.48

Reserves: Limited-Life Parts ............................................................25.29

Total Airframe Cost ..............................................................................................$ 101.44 $101.44

n Engine

Scheduled maintenance labor and parts ......................................$ 3.00 3.00

Reserve for engine overhaul, spares and accessories ..................44.86 43.76

Total Engine Cost ......................................................................................................$47.86 $46.76

n Total Direct Operating Cost

* Fuel Cost and labor rate is based on Conklin & deBecker book, “The Aircraft Cost Evaluator” dated Spring 2000. 1

Average cost while operating under the following conditions:

Gross Weight: 10% less than maximum certified Speed: Maximum Range Speed, 118 KIAS Altitude: 1,000 feet on a standard day

Overhaul costs (Projected) 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 excluded.

Cost figures shown are extrapolated from a broad data base and are intended for example purposes only. Actual costs will vary, depending on local operating conditions, pricing and supplier practices. We encourage you to compare these figures with other manufacturers’, using the same unit costs for fuel, labor, etc.

..............................................................................$202.35 $205.49

Data Subject to Change Without Notice

– 28 –

600

TOTAL COST OF OPERATION WORKSHEET

Direct Operating Cost per Hour

n Fuel and Lubricants

Fuel @ $_______ per gallon @ approx._____ gallons per hour ................$ ________

Lubricants @ _____ % of fuel ..................................................................$ ________

Total Fuel Cost ................................................................................................$ ________ (A)

n Airframe Maintenance and Spares

Scheduled maintenance labor rate @ $_____ per hour

(Maintenance man-hour/flight hour=$_____) ..........................................$ ________

Unscheduled maintenance labor rate @ $_____ per hour

(Maintenance man-hour/flight hour=$_____) ..........................................$ ________

Scheduled (Inspection) Parts: ..................................................................$ ________

On-Condition/Unscheduled Part ..............................................................$ ________

Reserves: Component Overhaul (TBO) ....................................................$ ________

Reserves: Limited-Life Parts ....................................................................$ ________

Total Airframe Cost ........................................................................................$ ________ (B)

n Engine

Scheduled maintenance labor rate @ $_____ per hour

(Maintenance man-hour/flight hour=$_____) ..........................................$ ________

Unscheduled maintenance labor rate @ $_____ per hour

(Maintenance man-hour/flight hour=$_____) ..........................................$ ________

Reserves for engine overhaul and spares ................................................$ ________

Total Engine Cost ............................................................................................$ ________ (C)

Total Direct Maintenance/Spares Cost (B+C)........................................................$ ________

n Total Direct Operating Cost (A+B+C) ..........................................................$ ________ (D)

Fixed Operating Cost

n Depreciation

Hull insurance ..........................................................................................$ ________

Liability insurance......................................................................................$ ________

Pilot salary ................................................................................................$ ________

Hangar rental............................................................................................$ ________

Total Annual Fixed Operating Cost ................................................$ ________ (E)

Total Hours (_______) flown annually (F)

Total Fixed Operating Cost Per Hour (E÷F) ................................................$ ________ (G)

Total Direct Operating Cost Per Hour (from above) ....................................$ ________ (D)

n Total Hourly Fixed Operating Cost (D+G) ..................................................$ ________

– 29 –

600

COMPONENT MAINTENANCE SCHEDULE

LIMITED-LIFE PARTS

Component Finite Time (hr)

Main Rotor Blade 3,530

Blade Pin 7,600

Main Rotor Hub 8,900

Pitch Housing/MR 9,100

Retention Strap/MR 2,770

Bolt-Lead Lag/MR 6,120

Lead Lag Link/MR 11,080

Drive Shaft 5,020

Mast 10,450

Transmission Coupling 4,300

T/R Drive Shaft 13,900

T/R Transmission Input Shaft 12,000

T/R Transmission Output Shaft 7,290

T/R Blade 5,140

T/R Hub 3,450

T/R Retention Strap 5,100

Tail Boom Bolts 21,950

Tail Boom 10,300

Vertical Stabilizer 12,700

Horizontal Stabilizer 7,700

Idler Bellcrank 6,500

OVERHAUL SYSTEMS

Component Finite Time (hr)

Transmission/MR 5,000

M/R Swashplate 2,770

M/R Hub 2,770

Overrunning, Clutch 1,800

T/R Transmission 4,800

Starter, Generator 1,200

Blower Bearings 1,200

Blower Belt 1,200

Landing Gear Dampers 1,000

– 30 –

600

CONTENTS

Paragraph Page

1.0 HIGH PERFORMANCE............................................................................33

2.0 EQUIPMENT ..............................................................................................34

3.0 PERFORMANCE SPECIFICATIONS.....................................................35

3.1 HIGE .....................................................................................................36

3.2 HOGE....................................................................................................37

3.3 Gross Weight Worksheet .......................................................................38

3.4 Payload & Range ...................................................................................39

3.5 Speed for Best Range ...........................................................................40

3.6 Speed for Best Endurance.....................................................................41

3.7 Fuel Consumption ............................................................................42-45

4.0 DIRECT OPERATING COST.............................................................46-48

– 31 –

600

– 32 –

600

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. It offers the performance you need...at a lower cost of ownership.

In a typical working configuration, at a design gross weight of 3,100 lb (1406 kg) and a useful load of over 1,509 lb (684 kg), it can hover out-of-ground effect at 11,600 ft (3536 m) ISA + 20°C. Its cruise speed follows the tradition of the MD 500E...making it one of the fastest helicopters in its class. An optional cargo hook rated for 2,000 lb (907 kg) provides outstanding external load capability. Internal loading is made easy by the flat aft cargo compartment floor of the helicopter.

The MD 530F’s high altitude lift capability is achieved by main-rotor blades six inches longer than the MD 500E. The tailboom is extended eight inches and the tail rotor blades have been lengthened to provide increased thrust and directional control at high altitudes.

The MD 530F features the same streamlined, extended nose and interior design as the MD 500E, making it one of the most spacious, quiet, comfortable and versatile McDonnell Douglas helicopters. The T-shaped instrument panel can provide space for a full complement of modern avionics.

1.9 m

(6.3 ft)

1.4 m

(4.6 ft)

Rear seat passengers have increased headroom and visibility.

1.7 m

(5.4 ft)

The MD 530F light turbine helicopter allows easy conversion to a utility cargo carrier. The aft compartment is roomy enough to carry two 55-gallon drums on a flat floor. Outsized, bulky loads can be carried externally by the cargo hook, which is rated at 2,000 lb (907 kg). Optional high-clearance skids permit operation in rough terrain, while other optional equipment, such as inflatable floats, litter kit and external baggage pods increase the MD 530F’s versatility.

Proven reliability, fail-safe design and the worldwide network of factory-authorized service centers assure customer satisfaction.

8.3 m

(27.4 ft)

Dia

9.8 m

(32.6 ft)

7.5 m

(24.6 ft)

2.9 m

(9.7 ft)

2.8 m

(9.2 ft)

2.4 m

(7.8 ft)

MD 530F with optional extended landing gear.

NOTES

1. Helicopter on ground with full fuel. Typical attitude of cargo deck 5.3 degrees nose up.

2. Height-above-ground dimensions vary with installed equipment, center of gravity and terrain features.

3. If standard landing gear is installed, all vertical dimensions will be 0.3 m (1.0 ft) less.

0.7 m (2.4 ft)

1.5 m

(4.8 ft)

Dia

1.0 m

(3.3 ft)

3.0 m

(9.8 ft)

– 33 –

STANDARD EQUIPMENT

2.0 Equipment.

Airframe

Interior

n Crew seats with 4-point harness restraint n Passenger seats with 3-point harness restraint n Vinyl and fabric cushions - 5 seats n Vinyl interior trim panels n Crew and cabin compartment floor carpet n Map case n Fire extinguisher n First aid kit n Crew ashtray and lighter/28-volt utility outlet n Cabin lighter/28-volt utility outlet n Battery-heavy duty Marathon 17-ampere-hour n Ventilation system n Cockpit utility light n Instrument lighting n Cabin soundproofing n Cargo tie-down fittings

Engine and Electrical

n Allison 250-C30R engine, 650 shp (485 kw) n Automatic engine reignition n Engine wash kit, MD 500 series n Engine compressor anti-ice n 64 gallon (242 l) fuel system n 85 amp starter generator n 140 amp starter generator cooling kit n External power receptacle

600

Rotor and Controls

n Flight controls, single, left hand command

Flight and Engine Instruments

n Dual tachometer, N

and N

n Engine oil pressure indicator n Engine torque meter n N

tachometer

Annunciator Panel

Miscellaneous

– 34 –

600

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: VNEat sea level 282 km/hr 152 kt (175 mph)

Maximum Range: Sea level 381 km 206 nm (237 mi)

1524 m (5,000 ft) 430 km 232 nm (267 mi)

Maximum Endurance: Sea level 2.0 hr 2.0 hr

Maximum Rate of Climb: (TOP) Sea level, Standard day 10.5 m/sec 2,069 fpm

ISA +20° C day 10.5 m/sec 2,061 fpm

Maximum Operating Altitude: Density Altitude 6096 m 20,000 ft

Service Ceiling: ISA 5700 m 18,700 ft

Maximum Hook Capacity: 907 kg 2,000 lb

Hovering Performance:*

In-ground effect: Standard day 4877 m 16,000 ft

ISA + 20° C day 4359 m 14,300 ft

Out-of-ground effect: Standard day 4389 m 14,400 ft

ISA + 20° C day 3536 m 11,600 ft

*No wind

WEIGHTS

Characteristics Metric Imperial

Maximum Gross Weight: Normal category 1406 kg 3,100 lb

External load operations 1701 kg 3,750 lb

Empty Weight: Standard configuration 722 kg 1,591 lb

Useful Load: Normal category 684 kg 1,509 lb

External load operations 979 kg 2,159 lb

Usable Fuel Capacity: 242 L (64 gal) 183 kg 403 lb

POWER PLANT

Characteristics Metric Imperial

Allison Model 250-C30 gas turbine, Rated power: 485 kw 650 shp

Derated for reliability and safety to: Takeoff power: 317 kw 425 shp

Max. continuous power: 280 kw 375 shp

– 35 –

3.1 Hover-In-Ground-Effect.

600

WITH C30 ENGINE

– 36 –

WITH C30 ENGINE

3.2 Hover-Out of-Ground-Effect.

600

– 37 –

WITH C30 ENGINE

3.3 Takeoff Gross Weight Worksheet.

Example Mission #1 Mission #2

600

Empty Weight

Pilot

Fuel

Payload

Takeoff GW

1,591 lb

(722 kg)

170 lb

(77 kg)

403 lb

(183 kg)

936 lb

(424 kg)

3,100 lb

(1406 kg)

– 38 –

WITH C30 ENGINE

3.4 Payload vs Range (5000’, ISA).

PAYLOAD

GW – empty weight – pilot – fuel

600

RANGE nm

0 50 100 150 200 250 300 350 0 93 185 278 370 463 557 648

– 39 –

3.5 Speed for Best Range.

600

WITH C30 ENGINE

– 40 –

WITH C30 ENGINE

3.6 Speed for Best Endurance.

600

– 41 –

WITH C30 ENGINE

3.7 Fuel Flow, Sea Level, ISA (15°C).

600

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.

– 42 –

600

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.

– 43 –

WITH C30 ENGINE

3.9 Fuel Flow, 4,000 feet, ISA (7°C).

600

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.

– 44 –

600

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.

– 45 –

600

2001 ESTIMATED DIRECT OPERATING COST

4.0 Direct Operating Cost.

Estimated Direct Operating Cost Per Hour (Based upon year 2001 US $)

C30 Engine

n Fuel and Lubricants

Fuel @ $2.06* per gallon @ approx. 32 gallons per hour ..............$ 65.92

Lubricants @ 3% of fuel......................................................................1.98

Total Fuel Cost ....................................................................................................................$ 67.90

n Airframe Maintenance and Spares

Maintenance labor costs:

Scheduled (.15 Manhours/Flight Hours) @ $58.00/Hour*................$ 8.70

Unscheduled (.26 Manhours/Flight Hours) @ $58.00/Hour* ............15.08

Spares Cost: Scheduled (Inspection) Parts: Used during periodic

inspection i.e. filters, seals, o-rings, etc. ..........................................$ 5.78

On-Condition/Unscheduled Part ......................................................20.11

Reserves: Component Overhaul (TBO) ............................................27.44

Reserves: Limited-Life Parts ............................................................29.16

Total Airframe Cost ........................................................................................................$ 106.27

n Engine

Scheduled maintenance labor & parts ............................................$ 3.00

Reserve for engine overhaul, spares and accessories ......................47.93

Total Engine Cost ............................................................................................................$ 51.93

n Total Direct Operating Cost

* Fuel Cost and labor rate is based on Conklin & deBecker book, “The Aircraft Cost Evaluator” dated Spring 2000. 1

Average cost while operating under the following conditions:

Gross Weight: 10% less than maximum certified Speed: Maximum Range Speed, 118 KIAS Altitude: 1,000 feet on a standard day

Overhaul costs (Projected) 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 excluded.

......................................................................................$ 226.00

Data Subject to Change Without Notice

– 46 –

600

TOTAL COST OF OPERATION WORKSHEET

Direct Operating Cost per Hour

n Fuel and Lubricants

Fuel @ $_______ per gallon @ approx._____ gallons per hour ................$ ________

Lubricants @ _____ % of fuel ..................................................................$ ________

Total Fuel Cost ................................................................................................$ ________ (A)

n Airframe Maintenance and Spares

Scheduled maintenance labor rate @ $_____ per hour

(Maintenance man-hour/flight hour=$_____) ..........................................$ ________

Unscheduled maintenance labor rate @ $_____ per hour

(Maintenance man-hour/flight hour=$_____) ..........................................$ ________

Scheduled (Inspection) Parts: ..................................................................$ ________

On-Condition/Unscheduled Part ..............................................................$ ________

Reserves: Component Overhaul (TBO) ....................................................$ ________

Reserves: Limited-Life Parts ....................................................................$ ________

Total Airframe Cost ........................................................................................$ ________ (B)

n Engine

Scheduled maintenance labor rate @ $_____ per hour

(Maintenance man-hour/flight hour=$_____) ..........................................$ ________

Unscheduled maintenance labor rate @ $_____ per hour

(Maintenance man-hour/flight hour=$_____) ..........................................$ ________

Reserves for engine overhaul and spares ................................................$ ________

Total Engine Cost ............................................................................................$ ________ (C)

Total Direct Maintenance/Spares Cost (B+C)........................................................$ ________

n Total Direct Operating Cost (A+B+C) ..........................................................$ ________ (D)

Fixed Operating Cost

n Depreciation

Hull insurance ..........................................................................................$ ________

Liability insurance......................................................................................$ ________

Pilot salary ................................................................................................$ ________

Hangar rental............................................................................................$ ________

Total Annual Fixed Operating Cost ................................................$ ________ (E)

Total Hours (_______) flown annually (F)

Total Fixed Operating Cost Per Hour (E÷F) ................................................$ ________ (G)

Total Direct Operating Cost Per Hour (from above) ....................................$ ________ (D)

n Total Hourly Fixed Operating Cost (D+G) ..................................................$ ________

– 47 –

COMPONENT MAINTENANCE SCHEDULE

LIMITED-LIFE PARTS

Component Finite Time (hr)

Main Rotor Blade 3,430

Blade Pin 7,600

Main Rotor Hub 8,900

Pitch Housing/MR 9,100

Retention Strap/MR 2,770

Bolt-Lead Lag/MR 6,120

Lead Lag Link/MR 11,080

Drive Shaft 3,675

Mast 10,450

Coupling 4,300

T/R Drive Shaft 14,610

T/R Transmission Input Shaft 3,365

T/R Transmission Output Shaft 7,290

T/R Blade 5,140

T/R Hub 3,450

T/R Retention Straps 5,100

Tail Boom 10,300

Vertical Stabilizer 3,388

Horizontal Stabilizer 7,700

Idler Bellcrank 6,500

OVERHAUL SYSTEMS

Component Finite Time (hr)

Main Rotor Transmission 5,000

Main Rotor Swashplate 2,770

Main Rotor Hub 2,770

Overrunning Clutch 1,800

T/R Transmission 3,365

Starter Generator 1,200

Blower Bearings 1,200

Blower Belt 1,200

Landing Gear Dampers 1,000

– 48 –

600

CONTENTS

Paragraph Page

1.0 LAW ENFORCEMENT CONFIGURATION ..........................................50

2.0 SYSTEM DESCRIPTION ...................................................................51-61

3.0 EQUIPMENT ..............................................................................................62

4.0 PERFORMANCE SPECIFICATIONS.....................................................63

4.1 HIGE......................................................................................................64

4.2 HOGE....................................................................................................65

4.3 Gross Weight Worksheet .......................................................................66

4.4 Payload & Range ...................................................................................67

4.5 Speed for Best Range ...........................................................................68

4.6 Speed for Best Endurance.....................................................................69

4.7 Fuel Consumption ............................................................................70-73

6.0 DIRECT OPERATING COST.............................................................74-76

– 49 –

600

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

2264 pounds (1027 kg) external HOGE at 6,000 ft (1829 m) @ISA HIGE at 11,200 ft (3414 m) @ ISA ROC of 1775 feet per minute (9.0 m/s)

Versatile: 20,000 foot (6096 m) Maximum Operating Altitude

Operating temperature range of -40oC to +52oC 15 degree slope landings

Safety & Elimination of tail rotor hazards Environment: Quiet operations - Flyover at 500 feet AGL = 72.5 dbA

– 50 –

600

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, passenger/crew safety and handling and performance capabilities.

The MD 520N has been designed to allow a wide variety of rapid configuration options. The aircraft may be converted rapidly from a personnel transport to a utility cargo configuration. Typical uses include:

Airborne Law Enforcement

Search and rescue

Surveillance and crowd control

Aerial survey, patrol and photographic missions

Forestry and fire fighting applications

The MDHI MD 520N helicopter is a turbine powered, rotary-wing aircraft constructed primarily of aluminum alloy while the NOTAR® system components are primarily graphite composites. The main rotor is a fully articulated six bladed system which provides excellent control and maneuverability characteristics. Power from the turboshaft engine is transmitted through the main drive shaft to the main rotor transmission. The main transmission drives an intermediate gearbox to the NOTAR systems fan. An overrunning (one-way) clutch placed between the engine and main rotor transmission, permits freewheeling of the rotor system during autorotation.

The airframe structure is egg-shaped and provides very clean aerodynamic lines. A rigid, three-dimensional truss-type structure increases crew safety by means of its roll bar design and reduces the potential for airframe collapse into the crew and passenger compartments. The airframe structure is designed to be energy absorbing while maintaining rotor hub integrity.

– 51 –

1.9 m

(6.3 ft)

600

SYSTEM DESCRIPTION

1.4 m

(4.6 ft)

8.3 m (27.4 ft) Dia.

2.0 m

(6.6 ft)

9.8 m (32.1 ft)

7.8 m (25.5 ft)

2.9 m

(9.7 ft)

2.8 m

(9.2 ft)

2.4 m

(7.8 ft)

0.7 m (2.4 ft)

2.8 m

(9.3 ft)

MD 520N Outside Dimensions

The fuselage is a semimonocoque structure that is divided into two main sections. The forward section is composed of the pilot/co-pilot compartment and directly aft, separated by a bulkhead, a cabin compartment. The pilot compartments equipped with seats for the pilot and either two passengers on the co-pilot. A canopy of transparent tinted acrylic panels provides excellent visibility.

An instrument panel is located forward of the seat structure along the aircraft centerline. The panel incorporates standard flight and engine instruments in addition to warning and caution lights. The panel also contains adequate space for avionics and flight instruments. An optional “slant panel” is available which increases the panel space available when extensive avionics suites are selected or when armament systems are installed.

– 52 –

Five-Blade Fully Articulated Main Rotor

Crashworthy A-Frame Truss

with Integral Crew Seats

600

SYSTEM DESCRIPTION

Static Mast Rotor Support

Outstanding Outward Visibility

Simple Mechanical Controls

Flat Cargo Floor

425 shp Drive System

Rolls-Royce 250-C20R 450 shp Turbine Engine

Five-Place Seating Capacity

Anti-Torque System

NOTAR

MD 520N Inboard Profile and Features

The crashworthy designed fuselage structure beneath the pilot/copilot floor contains space for the aircraft battery and provision for small cargo storage or installation of avionics equipment. Access to the compartments is through two floor panels.

The cargo compartment is the center of the aircraft contains provisions for the installation of passenger seats, auxiliary fuel tanks or cargo/baggage. During cargo-carrying operations, the compartment floor serves as the cargo deck. The cargo floor is designed to accommodate a range of cargo requirements.

The aft section includes the structure of the tailboom attachment, NOTAR® system fan and the engine compartment. Access to the engine compartment is provided through clamshell doors contoured to the shape of the fuselage.

The lower section is divided by the center “keel beam” and provides housing for the two fuel cells containing a total of 64 U.S. gallons (242 l) of fuel.

– 53 –

600

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. The design permits flight with doors removed without major speed restrictions. Transparent tinted windows are contained in the doors.

An Allison Model 250-C20RS gas turbine engine with a takeoff power rating of 450 shp powers the MD 520N. Only 425 shp at l00 percent N2 rpm is used for takeoff; 375 maximum continuous shp provides power for all other flight modes.

An overrunning clutch transmits power from the engine to the main drive shaft. The clutch has no external controls and disengages automatically during autorotation and engine shutdown. The main drive shaft connects to the main rotor transmission input shaft. The engine oil cooler blower is belt-driven off the main drive shaft and draws cooling air from the air inlet fairing to supply ambient air to the engine and transmission oil coolers and to the engine compartment. The main rotor transmission is mounted on the airframe structure above the passenger/cargo compartment. The transmission is lubricated by its own air-cooled oil lubrication system. The main rotor static mast is nonrotating and is rigidly mounted to the fuselage mast support structure. This static mast is used to separate the lift and torque loads of the rotor.

– 54 –

600

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. This accomplishes a design that reduces main transmission weight and reduces the probability of injury during a crash

The MD 520N utilizes a five-blade, fully articulated main rotor assembly. The MDHI strap pack design provides restraint and allows all three degrees of rotor hub and rotor blade travel. The strap configuration, while 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.

Thus, very light centrifugal loads are sensed by the hub. The “V” legs of the strap pack rotate as driving members to turn the blades and allow feathering, lead, lag and flapping of the blades. The main rotor blades are secured to the hub with quick-release lever type pins.

Adjustable pedal controls are provided for rudder/thruster control. Adjustable friction devices are incorporated in the cyclic, collective and throttle controls. In addition, electrical cyclic trim actuators allow flight loads to be trimmed out. Control forces are low; hence, a hydraulic boost system is not required.

The landing gear is a skid type attached to the fuselage at l2 points and is not retractable. Aerodynamic faring cover the struts. Nitrogen charged landing gear dampers act as springs and shock absorbers to cushion landings and provide ground resonance stability. Provisions for ground handling wheels are incorporated on the skid tubes.

Maintenance made easy

The MD 520N incorporates proven engineering features that are unsurpassed for design simplicity, safety, reliability and ease of maintenance. There are no hydraulic boost systems, intermediate drive shaft bearings or grease fittings on any MD 500 series helicopters.

Blade Retention System:

The mechanical simplicity of the main rotor system provides high reliability at low cost. Main rotor blades are retained by an exclusive strap pack system that accommodates main rotor blade flapping, lead-lag and feathering motions. Fewer parts result in higher reliability.

Main Rotor Transmission:

The main transmission has four gears and two gear meshes. It is light but rugged for maximum reliability. The static mast design allows one mechanic to easily change the transmission without removing any other component on the rotor head.

– 55 –

600

SYSTEM DESCRIPTION

Interchangeability

Parts and assemblies listed below are interchangeable.

1. Main rotor blade (tracking of new blades may be required) 2 Main rotor hub assembly

3. Lead-lag damper

4. Main rotor drive shaft

5. Main rotor mast

6. Main transmission

7. Overrunning clutch

8. Main drive shaft

9. Engine assembly

10. Engine mount

11. Engine exhaust duct

12. NOTAR drive shaft

13. NOTAR gearbox

14. NOTAR blades

15. Control system components

16. Oil tank

17. Oil coolers (engine and main transmission)

18. Tail boom assembly

19. Vertical and Horizontal stabilizers

20. Fuel cells (left and right)

21. Electronic component assemblies and associated wire harnesses

22. Instruments

23. Landing gear assembly

– 56 –

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.

Reduced Noise

Designed and tested to be 50% quieter than any other helicopter. This results in detection distances that are far superior to other aircraft.

600

Reduced Pilot Workload

Using the Coanda Effect to provide tail boom lift and anti-torque, the system is more stable and easier to control. This effect reduces the sensitivity to wind direction on helicopter control, through providing an important tactical advantage during combat operations.

Low Pressure Air System

Since the NOTAR system uses low-pressure air, it is not sensitive to holes made in the tailboom by fire from automatic weapons. Studies have shown the NOTAR® system is 60% less vulnerable to small arms fire than tail rotor systems on comparable helicopters.

– 57 –

600

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 horizontal stabilizer with two vertical stabilators.

Air Intake

Vertical

Varible Pitch Fan

Stabilizers

Tailboom with Circulation Control Slots

Direct Jet Thruster

NOTAR® System Components

The vertical stabilizers are connected to the pilot’s anti-torque (rudder) pedals. The left stabilizer moves through approximately 29 degrees of motion and provides sufficient control power for autorotation. It serves the additional purpose of unloading the thruster during forward flight to permit optimum cruise performance.

NOTAR

Conventional airfoil

Main rotor wake and slot air produce lift/anti-torque

Boundary Layer Control Produces Anti-Torque Force

System Circulation Control

Downwash

LIFT

Circulation

control

tailboom

cross

section

– 58 –

LIFT

600

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. The direct jet thruster provides the remaining anti-torque and maneuverability for yaw control and directional changes.

In forward flight, the vertical stabilators in conjunction with the direct-jet thruster provide the required anti-torque and directional control.

REDUCED AIRCRAFT VIBRATION

The inherent stability of the standard MD 500 is further improved by the elimination of the exposed tail rotor assembly, which reduces overall helicopter vibrations and increases passenger comfort while reducing pilot fatigue.

– 59 –

600

SYSTEM DESCRIPTION

LOW EXTERNAL NOISE

The elimination of the high-tip-speed tail rotor assembly makes the MD 520N the quietest 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’ when used in areas where noise is objectionable. Lower noise levels also increase survivability in hostile operational roles.

3,000

500 ft AGL at 110 knots

2,000

1,000

Feet

-1,000

-2,000

-3,000

-3,000 -2,000 -1,000 0 1,000 2,000 3,000

Noise inside each respective contour is 65 dBA or greater,

about the same level as a noisy residential environment

The NOTAR® System

“Quiet Advantage”

AS 350B

Flight Path

Feet

Bell Jet Ranger

65 dBA Footprint

MD 520N Bell Jet Ranger AS350B

MD 520N

Observer’s Distance from Helicopter Meters/(Feet)

0152305457610

(0)(500)(1,000)(1,500)(2,000)

– 60 –

INHERENT SAFETY

600

SYSTEM DESCRIPTION

The NOTAR anti-torque system eliminates accidents and mishaps caused by the exposed tail rotor strik-

6% All Accidents

Avoidable

ing objects in flight, and significantly reduces ground incidents with people or equipment. Potential damage caused by foreign objects is also eliminated. Inherent design capabilities of the MD 520N reduces the susceptibility to loss of tail rotor effectiveness and

80% Accidents Other Than Tail Rotor

the problems associated with quartering tail winds. The MD 520N’s power and stability in various wind conditions increase operational safety.

IMPROVED HANDLING

The excellent handling qualities of the MD 500 series have been further improved with the addition of the NOTAR system. The MD 520N has high control response provided by the fully articulated five-blade rotor system. Transient positive load factors of 2.8 g’s and negative load factors of 0.0g’s are attainable with the MD 520N. The NOTAR system allows side and rearward flight speeds above 30 knots, low sensitivity to wind direction, 80% fewer pilot controls inputs and rapid turning rates.

14% Accidents Saved With NOTAR System

– 61 –

STANDARD EQUIPMENT

3.0 Equipment.

Airframe

n Tinted canopy panels n Tinted door/window panel-left front n Tinted door/window panel-left rear n Tinted door/window panel-right front n Tinted door/window panel-right rear n Rain gutter set n Short landing gear n Keyed locks (4) n Fuselage hard points n Jacking fittings n Passenger steps n Anti-collision lights (3) n Landing light, nose mounted n Position lights n Paint 1 color standard

Interior

Engine and Electrical

n Allison 250-C20R engine, 450 shp (336 kw) n Automatic engine reignition n Engine wash kit, MD 500 series n Engine compressor anti-ice n 64 gallon (242 l) fuel system n 85 amp starter generator n External power receptacle n Facet oil filter

600

Rotor and Controls

n Flight controls, single, left hand command

Flight and Engine Instruments

n Dual tachometer, N

and N

n Engine oil pressure indicator n Engine torque meter n N

tachometer

n Hobbs engine running time meter n Fuel quantity indicator n Digital chronometer n Airspeed indicator n Barometric altimeter n DC ammeter n Outside air temperature indicator n Magnetic compass n Digital/analog turbine outlet temp indicator n Engine oil temp indicator

Annunciator Panel

n Battery overtemp warning light n Engine chip detector warning light n Engine out warning light n Fan transmission chip detector warning light n Fuel filter obstruction warning light n Fuel low warning light n Generator out warning light n Low rotor rpm warning light n Main transmission chip detector warning light n Main transmission oil pressure warning light n Main transmission oil temp warning light

Miscellaneous

– 62 –

600

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)

Maximum Permitted Speed: VNEat sea level 282 km/hr 152 kt (175 mph) 282 km/hr 152 kt (175 mph)

Maximum Range: Sea level 378 km 204 nm (235 mi) 365 km 197 nm (227 mi)

1524 m (5,000 ft) 412 km 222 nm (256 mi) 389 km 210 nm (242 mi)

Maximum Endurance: Sea level 2.4 hr 2.4 hr 2.2 hr 2.2 hr

Maximum Rate of Climb:(TOP) Sea level, Standard day 9.7 m/sec 1,913 fpm 7.9 m/sec 1,546 fpm

ISA +20° C day 8.6 m/sec 1,687 fpm 6.5 m/sec 1,280 fpm

Maximum Operating Altitude: Density altitude 6097 m 20,000 ft 6097 m 20,000 ft

Service Ceiling: ISA 4970 m 16,300 ft 4024 m 13,200 ft

Maximum Hook Capacity: 907 kg 2,000 lb 907 kg 2,000 lb

Hovering Performance:

In-ground effect: Standard day 3901 m 12,800 ft 2835 m 9,300 ft (extended landing gear) ISA + 20° C day 2743 m 9,000 ft 1554 m 5,100 ft

Out-of-ground effect: Standard day 2865 m 9,400 ft 1707 m 5,600 ft

ISA + 20° C day 1707 m 5,600 ft 427 m 1,400 ft

WEIGHTS

Characteristics Metric Imperial

Maximum gross weight: Normal category 1519 kg 3,350 lb

External load operations 1746 kg 3,850 lb

Empty weight: Standard configuration 719 kg 1,585 lb

Industrial configuration 674 kg 1,486 lb

Useful load: Standard configuration Normal category 800 kg 1,764 lb

External load operations 1027 kg 2,264 lb

Industrial configuration Normal category 845 kg 1,864 lb

External load operations 1072 kg 2,364 lb

Usable Fuel Capacity: 242 L (64 gal) 183 kg 403 lb

POWER PLANT

Characteristics Metric Imperial

Allison Model 250-C20R gas turbine: Rated power 336 kw 450 shp

Derated for reliability and safety to: Takeoff power 317 kw 425 shp

Max. continuous power 280 kw 375 shp

– 63 –

4.1 Hover-In-Ground-Effect.

600

WITH C20R ENGINE

– 64 –

WITH C20R ENGINE

4.2 Hover-Out of-Ground-Effect.

600

– 65 –

WITH C20R ENGINE

4.3 Takeoff Gross Weight Worksheet.

Example Mission #1 Mission #2

600

Empty Weight

Pilot

Fuel

Payload

Takeoff GW

1,585 lb

(719 kg)

170 lb

(77 kg)

403 lb

(183 kg)

1192 lb (540 kg)

3,350 lb

(1519 kg)

– 66 –

WITH C20R ENGINE

4.4 Payload vs Range (5000’, ISA).

PAYLOAD

GW – empty weight – pilot – fuel

600

RANGE nm

0 50 100 150 200 250 300 350 0 93 185 278 370 463 557 648

– 67 –

4.5 Speed for Best Range.

600

WITH C20R ENGINE

– 68 –

WITH C20R ENGINE

4.6 Speed for Best Endurance.

600

– 69 –

WITH C20R ENGINE

4.7 Fuel Flow, Sea Level, ISA (15°C).

600

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.

– 70 –

600

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.

– 71 –

WITH C20R ENGINE

4.9 Fuel Flow, 4,000 feet, ISA (7°C).

600

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.

– 72 –

600

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.

– 73 –

600

2001 ESTIMATED DIRECT OPERATING COST

5.0 Direct Operating Cost.

Estimated Direct Operating Cost Per Hour (Based upon year 2001 US $)

C20RS Engine

n Fuel and Lubricants

Fuel @ $2.06* per gallon @ approx. 27 gallons per hour ..............$ 55.62

Lubricants @ 3% of fuel......................................................................1.67

Total Fuel Cost ....................................................................................................................$ 57.29

n Airframe Maintenance and Spares

Maintenance labor costs:

Scheduled (.15 Manhours/Flight Hours) @ $58.00/Hour*................$ 8.70

Unscheduled (.26 Manhours/Flight Hours) @ $58.00/Hour* ............15.08

Spares Cost: Scheduled (Inspection) Parts: Used during periodic

inspection i.e. filters, seals, o-rings, etc. ..........................................$ 5.78

On-Condition/Unscheduled Part ......................................................20.11

Reserves: Component Overhaul (TBO) ............................................25.89

Reserves: Limited-Life Parts ............................................................29.31

Total Airframe Cost ........................................................................................................$ 104.87

n Engine

Scheduled maintenance labor & parts ............................................$ 3.00

Reserve for engine overhaul, spares and accessories ......................43.76

Total Engine Cost ............................................................................................................$ 46.76

n Total Direct Operating Cost

* Fuel Cost and labor rate is based on Conklin & deBecker book, “The Aircraft Cost Evaluator” dated Spring 2000. 1

Average cost while operating under the following conditions:

Gross Weight: 10% less than maximum certified Speed: Maximum Range Speed, 117 KIAS Altitude: 1,000 feet on a standard day

Overhaul costs (Projected) 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 excluded.

......................................................................................$ 208.92

Preliminary Data Subject to Change Without Notice

– 74 –

600

TOTAL COST OF OPERATION WORKSHEET

Direct Operating Cost per Hour

n Fuel and Lubricants

Fuel @ $_______ per gallon @ approx._____ gallons per hour ................$ ________

Lubricants @ _____ % of fuel ..................................................................$ ________

Total Fuel Cost ................................................................................................$ ________ (A)

n Airframe Maintenance and Spares

Scheduled maintenance labor rate @ $_____ per hour

(Maintenance man-hour/flight hour=$_____) ..........................................$ ________

Unscheduled maintenance labor rate @ $_____ per hour

(Maintenance man-hour/flight hour=$_____) ..........................................$ ________

Scheduled (Inspection) Parts: ..................................................................$ ________

On-Condition/Unscheduled Part ..............................................................$ ________

Reserves: Component Overhaul (TBO) ....................................................$ ________

Reserves: Limited-Life Parts ....................................................................$ ________

Total Airframe Cost ........................................................................................$ ________ (B)

n Engine

Scheduled maintenance labor rate @ $_____ per hour

(Maintenance man-hour/flight hour=$_____) ..........................................$ ________

Unscheduled maintenance labor rate @ $_____ per hour

(Maintenance man-hour/flight hour=$_____) ..........................................$ ________

Reserves for engine overhaul and spares ................................................$ ________

Total Engine Cost ............................................................................................$ ________ (C)

Total Direct Maintenance/Spares Cost (B+C)........................................................$ ________

n Total Direct Operating Cost (A+B+C) ..........................................................$ ________ (D)

Fixed Operating Cost

n Depreciation

Hull insurance ..........................................................................................$ ________

Liability insurance......................................................................................$ ________

Pilot salary ................................................................................................$ ________

Hangar rental............................................................................................$ ________

Total Annual Fixed Operating Cost ................................................$ ________ (E)

Total Hours (_______) flown annually (F)

Total Fixed Operating Cost Per Hour (E÷F) ................................................$ ________ (G)

Total Direct Operating Cost Per Hour (from above) ....................................$ ________ (D)

n Total Hourly Fixed Operating Cost (D+G) ..................................................$ ________

– 75 –

600

COMPONENT MAINTENANCE SCHEDULE

LIMITED-LIFE PARTS

Component Finite Time (hr)

Main Rotor Blade 3,430

Blade Pin 7,600

Main Rotor Hub 8,900

Pitch Housing/MR 9,100

Retention Strap/MR 2,770

Bolt-Lead Lag/MR 6,120

Lead Lag Link/MR 11,080

Drive Shaft 3,260

Mast Assy 10,450

Coupling 3,200

Bellcrank 2,870

Control Rod 7,740

Fan Drive Shaft 2,620

Fan - Blade Assy 7,500

Fan Hub 7,500

Pitch Plate 7,500

Rotating Cone Assembly 10,000

Tailboom Assembly 10,000

Tube, Torque 5,000

Idler Long. Pitch Mixer 6,050

OVERHAUL SYSTEMS

Component Finite Time (hr)

Transmission/MR 5,000

M/R Swashplate 2,770

M/R Hub 2,770

Overrunning Clutch 1,800

Starter Generator 1,200

Blower Bearings 1,200

Blower Belt 1,200

Fan Bearings 2,400

Fan Pitch Plate Bearings 2,400

Landing Gear Dampers 1,000

– 76 –

600

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.

6.0 The MDHI Support Plan 2000

MDHI is dedicated to a successful fielding of its new helicopters and to improve the support it currently offers operators of its commercial helicopters. The following items highlight how the MDHI helicopters will be the best-supported aircraft of its type anywhere in the world.

Operator Input

Input from many of our existing fleet operators has been actively solicited by our support team. We have created Customer Satisfaction Advisory Teams, composed of operators from all over the world who are chartered to work together with MDHI technical representatives to lower operating costs, and to improve our products and the way we support them. As a result of this improved level of two-way communication, many improvements suggested by our customers are being included in our production, publications, and maintenance procedures.

Training

MDHI offers pilot and maintenance training to our new customers at no extra charge. Customers will be trained at the MDHI Commercial Training Center by our staff of specially trained pilots and technical representatives. At the training center, we stress hands-on experience in both our flight and ground schools. The materials we use for our school are continually updated to reflect the latest product and maintenance developments by our technical staff.

– 77 –

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 helicopters. 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 technical issues or questions that may arise. The Technical Representatives will spend as much time with the customers as required to familiarize them with their new aircraft.

Regular Maintenance

Follow-up visits by our Customer Support Technical Representatives will be performed as required at the regularly scheduled maintenance periods. This provides the customer with the latest maintenance information, and provides the factory with feedback on the operation, reliability and maintainability of their new aircraft. In addition, we plan to offer all models maintenance and parts manuals on CD-ROM.

Direct Operating Costs

The operating costs of MDHI helicopters are planned to be clearly the lowest in their classes. The plan is to keep the parts costs down, maximize the reliability of the helicopter systems, and minimize maintenance hours. This is accomplished by “benchmarking” all of these areas against the existing fleet of MD 500

helicopters, already one of the most reliable turbine helicopter lines in the world. Every part, system and maintenance procedure has undergone scrutiny before being incorporated on new production aircraft.

Spare Parts

The MDHI recognizes the importance of timely deliveries of spare parts to our customers. A thorough review of spare parts utilization has been conducted with the intent to significantly improve turnaround time of AOG spares. Additionally, we will increase our activities in using customer advanced spares requirement notification to eliminate known spare part requirements. On-line spares ordering and statusing is in our near future. Additionally, we have established a MDHI Support Center in Europe, where a significant inventory of spare parts, exchange components and tools are maintained.

– 78 –

600

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 insurance costs and result in more efficient operation of the aircraft. Training is customarily conducted at our facility in Mesa, but offsite training at the customer’s facility can also be arranged. We can also arrange for pilot training in the customer’s aircraft, as long as MDHI’s insurance requirements are met before training begins.

Pilot Training

The transition flight training course is designed to familiarize a rated helicopter pilot with the operation of the MD 500 series helicopter. This five-day course introduces the student to all the associated company publications as well as detailed explanations of all aircraft systems and daily/preflight inspection procedures. The ground school, including the exam and exam review, requires 16 to 20 hours to complete. The student will be expected to pass an exam demonstrating basic knowledge of the aircraft. The flight training syllabus includes five hours of instructor time and is broken down into four flight lessons:

• Normal Operations (pattern and hover work)

• Normal Operations and emergency procedures

• Heavy Weight Performance

• Emergency Procedures (autorotations)

Recurrent pilot training consists of a two-day refresher course for any pilot who has previously attended the transition flight training course. Ground school includes a closed-book exam, review of AD’s and notices, and a daily/preflight inspection review. A BFR (biennial flight review) can also be given in conjunction with this course and includes review of FAR Part 91 and an open book exam. Flight training consists of three hours of intensive emergency procedures review.

– 79 –

600

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. The 1-week course is available to selected students with prior knowledge of MD products (the 500 series aircraft). The 80-hour syllabus is comprised of the following sections:

• Intro to helicopter design • Airframe

• Landing gear • Drive system

• Fan assembly • Anti-torque

• Rotor assembly, controls and rigging • Track and balance

• Lubrication/fuel • Powerplant

• Engine controls • Electrical systems

Other Training

The other types of training that are currently available to 500 series customers are:

• Instructor pilot training

• Maintenance test flight pilot training

– 80 –

600

OPTIONAL EQUIPMENT

Airspeed/Time

lb kg

ASTROTECH LC-6 CLOCK 0.3 0.1 DAVTRON N877 CLOCK 0.2 0.1 HEATED PITOT 0.4 0.2

Altitude

lb kg

KRA10-00 RADAR ALT W/KI250 IND 4.4 2.0 KRA405B-15 RADAR ALT W/KNI416 IND 10.5 4.8 UNITED 5035 ENCODING ALTIMETER 3.7 1.7 UNITED 5120 BLIND ENCODER 2.0 0.9 UNITED 7130-C41 IVSI 2.5 1.1

Altitude/Heading

AIM ATITUDE GYRO 510-1B 3.1 1.4 AIM DIRECTIONAL GYRO 205-1BL 3.0 1.4 EHS 40 ELECTRONIC FLIGHT INTRUMENT SYSTEM 23.9 10.8

lb kg

KCS55A-01 COMP SYS WKI525A HSI, KA51B 10.3 4.7 KI229-00 RADIO MAGNETIC INDICATOR 2.0 0.9 MID-CONTINENT 9510 3-INCH TURN AND BANK INDICATOR 1.6 0.7 UNITED 9551 2-INCH TURN AND BANK INDICATOR 1.4 0.6

– 81 –

OPTIONAL EQUIPMENT

600

Comm/Intercom

FLIGHT TRAILS AVIONICS MASTER SWITCH 1.5 0.7

lb kg

FLIGHT TRAILS COPILOT ICS FOOT SWITCH 0.5 0.2 FLIGHT TRAILS CYCLIC REMOTE FREQ SWITCH ONLY .3 0.1 FLIGHT TRAILS REAR SEAT TRANSMIT 2.5 1.1 HEADSET BOSE SERIES II 1.1 0.5 HEADSET BOSE SERIES X 1.1 0.5 HEADSET DAVID CLARK H10-56 1.1 0.5 HEADSET WIRE HARNESS (W/O ICS) W/ADAPTS 2.0 0.9 KFM985 FM TRANSCEIVER 3.0 1.4 KHF990-00 HF SYSTEM WITH BELLY MOUNTED ANT 22.5 10.2

KMA24H-71 AUDIO CONTROL/INTERCOM (5-PLACE) 3.1 1.4 KMA24H-71 DUAL AUDIO CONTROL/INTERCOM 6.2 2.8 KY196A-30 TRANSCEIVER 5.2 2.4 KY196A-30 TRANSCEIVER W/CYCLIC REMOTE SWITCH 5.5 2.5 MOTOROLA DVP-DVS ENCODER 0.0 0.0 NAT 138 FMNPX HIGH BAND TRANSCEIVER 3.1 1.4 NAT 150 VHF HI BAND TRANSCEIVER 8.5 3.9 NAT 403-00 UHF TRANSCEIVER 0.0 0.0 NAT 806 UHF 800MHZ BAND TRANSCEIVER 6.0 2.7 NAT AA22-163 100 WATT PA AND SIREN 21.6 9.8 NAT AA22-163 220 WATT PA AND SIREN 21.4 9.7 NAT AA34-200 UNIVERSAL RADIO INTERFACE 0.0 0.0 NAT AA94-SSD DUAL CHANNEL AUDIO CONTROLLER 2.3 1.0 NAT AA95-512 SINGLE CHANNEL AUDIO CONTROLLER 2.5 1.1 NAT AA95-512 SINGLE CHANNEL AUDIO DUAL CONTROLLERS 5.0 2.3 NAT AA97-400 SINGLE CHANNEL AUDIO CONTROLLER 2.5 1.1 NAT AMS44 DUAL CHANNEL AUDIO CONTROLLER 2.8 1.3 NAT CC250 COMMUNICATIONS CONTROLLER 3.0 1.4 NAT CC450 COMMUNICATIONS CONTROLLER 2.5 1.1 NAT DTE12-001 DATA ENCODER KEYBOARD 0.8 0.4 NAT TH250-7NN MASTER CONTROL HEAD 0.0 0.0 NAT TH350-2 MASTER CONTROL HEAD 3.0 1.4 PROVISIONS C1000-10 FLEXCOMM CONTROL HEAD 0.0 0.0 PROVISIONS C5000-1 FLEXCOMM CONTROL HEAD 0.0 0.0 TECHNISOFT TFM-403 FM COMM 4.5 2.0 TFM-138 VHF HIGH BAND TRANSCEIVER 3.1 1.4 WULFSBERG C1000-10 FLEX COMM CONTROL HEAD 2.6 1.8 WULFSBERG RT138F-0 TRANSCEIVER 7.5 3.4 WULFSBERG RT30-0 TRANSCEIVER (WIDEBAND) 8.3 3.8 WULFSBERG RT406F-0 TRANSCEIVER 7.5 3.4 WULFSBERG RT5000-01 TRANSCEIVER 27.2 12.3 WULFSBERG C5000-1 FLEX COMM CONTROL HEAD 4.2 1.9

– 82 –

600

OPTIONAL EQUIPMENT

Comm/Nav

lb kg

Emergency LOC TRANS, ARTEX-100HM 6.9 3.1 Emergency LOC transmitter pointer 3000 4.0 1.8 FOXTRONICS 3050 wide band antennna 0.0 0.0 KDF806-00 ADF w/KFS586 freq selector 5.0 2.3 KI202-00 VOR/LOC indicator 1.3 0.6 KI203-00 VOR/LOC indicator 1.0 .5 KI204-02 VOR/LOC/GS indicator 3.0 1.4 KI206-04 VOR/LOC/GS indicator 3.0 1.4 KI208-00 VOR/LOC indicator 2.4 1.0 KI209-01 VOR/LOC/GS indicator 1.2 0.5 KN53-00 NAV receiver w/GLS 3.0 1.4 KN62A-01 DME 2.6 1.2 KN63-04 DME w/KDI 572 indicator 3.6 1.6 KN75-02 glideslope receiver 1.6 0.7 KR22-00 marker beacon receiver 1.6 0.7 KR87-16 ADF 6.8 3.1 KR87-16 ADF W/KI227-00 IND 8.2 3.7 KT70-00 S-MODE TRANSPONDER 5.2 2.4 KT71-00 A AND C-MODE DIGITAL TRANSPONDER 4.0 1.8 KT76A-01 A AND C-MODE TRANSPONDER 4.2 1.9 KX155-39 NAV/COMM TRANSCEIVER 7.9 3.6 KX155-39 NAV/COMM W/KI208 VOR IND 9.7 4.4 KX155-43 NAV/COMM TRANSCEIVER W/GLS 7.9 3.6 KX155-43 NAV/COMM W/GS W/KI209 VOR/GLS IND 9.7 4.4 KX165-25 NAV/COMM W/GS W/KI206 VOR/GLS IND 10.6 4.8

Controls

lb kg

FLIGHT CONTROLS-DUAL, LH COMMAND 10.4 4.7 FLIGHT CONTROLS-DUAL, RH COMMAND 10.4 4.7

Electrical System

lb kg

BATTERY -500E SAFT HEAVY DUTY, 17 AMP 14.1 6.4 BATTERY -500N/530FF HD, SAFT 0.0 0.0 BATTERY -520N NOSE MOUNTED 8.0 3.6 BATTERY -LEAD ACID KIT AND BATTERY 23.0 10.4 FLIGHT TRAILS 28V RECP FRONT AND REAR 0.0 0.0 KA-33 AVIONICS COOLING FAN 2.2 1.0 VOLTMETER-DAVTRON M450 DIGITAL BATTERY 0.0 0.0 WECO GENERATOR COOLER SCOOP KIT 0.0 0.0 WECO 165 AMP STARGER GENERATOR 0.0 0.0

– 83 –

600

OPTIONAL EQUIPMENT

Engine

lb kg

ENGINE COMPRESSOR ANTI-ICE 0.0 0.0 ENGINE OIL EXHAUST BREATHER 0.0 0.0 FACET OIL FILTER - MD530FF 3.7 1.7 HOBBS COLLECTIVE RUNNING TIME METER 0.5 0.2 MIST ELIMINATOR 4.2 1.9 PARTICLE SEPARATOR 13.0 5.9 SYSTRON DONNER FIRE DETECTION SYSTEM 0.0 0.0

Environmental

lb kg

AERO-AIRE BOOST FAN 0.0 0.0 AIR CONDITIONING, INTEGRATED FLIGHT SYSTEMS 88.8 40.3 HEATER/DEFOGGER 8.1 3.7

Exterior Accessories

lb kg

BREEZE CARGO HOOK, MD 500 SERIES 6.3 2.9 ONBOARD SYSTEMS CARGO HOOK 7.0 3.2 ONBOARD SYSTEMS CARGO HOOK LOAD WEIGHT SYSTEM 5.0 2.3 PROVISIONS FLIR 4000-SAFIRE BELLY MOUNT 20.0 9.1 PROVISIONS FLIR REAR MONITOR MOUNT 0.0 0.0 PROVISIONS ULTRA 7000 FLIR -NOSE MOUNTED 10.0 4.5 PROVISIONS ULTRA 7000 FLIR -LEFT SIDE MOUNTED 10.0 4.5 PROVISIONS ULTRA 7000 FLIR -NOSE MOUNT 20.0 9.1 PROVISIONS ULTRA 7000 FLIR -RIGHT SIDE MOUNTED 10.0 4.5 WATER PROOF COVER 0.0 0.0 WIRE STRIKE KIT, MD 500 SERIES 17.0 7.7 FLOAT LIGHT KIT 4.8 2.2 NIGHTSCANNER 400K CPWR SEARCHLIGHT 23.0 10.4 NIGHTSCANNER, IR LENS KIT 0.8 0.4 NIGHTSCANNER, SUPER 800K CPWR 24.1 10.9 NIGHTSCANNER, SUPER, IR LENS KIT 0.8 0.4 PROVISIONS SX16 SEARCHLIGHT LEFT SIDE MOUNTED 30.0 13.6 PROVISIONS SX16 SEARCHLIGHT NOSE MOUNTED 30.0 13.6 PROVISIONS SX16 SEARCHLIGHT RIGHT SIDE MOUNTED 30.0 13.6 PROVISIONS SX5 SEARCHLIGHT LEFT SIDE MOUNTED 23.5 10.7 PROVISIONS SX5 SEARCHLIGHT NOSE MOUNTED 23.3 10.6 PROVISIONS SX5 SEARCHLIGHT RIGHT SIDE MOUNTED 23.5 10.7 SX16 SEARCHLIGHT LEFT SIDE MOUNTED 65.0 29.5 SX16 SEARCHLIGHT NOSE MOUNTED 65.0 29.5 SX16 SEARCHLIGHT RIGHT SIDE MOUNTED 65.0 29.5 SX5 SEARCHLIGHT LEFT SIDE MOUNTED 14.8 6.7 SX5 SEARCHLIGHT NOSE MOUNTED 14.8 6.7 SX5 SEARCHLIGHT RIGHT SIDE MOUNTED 14.8 6.7

– 84 –

600

OPTIONAL EQUIPMENT

Fuel System

lb kg

AIRFRAME FUEL FILTER 5.3 2.4 FARGO 21 GAL (79L) AUX FUEL TANK 44.5 20.2 POVISIONS FARGO 21 GAL (79L) AUX FUEL TANK 8.0 3.6 ROBERTSON 38.5 GAL (146L) AUX FUEL TANK 56.0 25.4 PROVISIONS ROBERTSON 38.5 GAL (146L) AUX FUEL TANK 9.0 4.1 SELF SEALING FUEL CELLS 21.2 9.6 SHADIN DIGIDATA FUEL AIR DATA SYSTEM 2.4 1.1

Gear/Handling

lb kg

EMERGENCY FLOATS, AIR CRUISERS 152.0 68.9 EMERGENCY FLOATS, APICAL INDUSTRIES 115.0 52.2 EXTENDED LANDING GEAR 9.5 4.3 FLIGHT TRAILS CREW HANDLES (4) 5.0 2.3 FLIGHT TRAILS SKID MIRROR 2.0 0.9 WINTERIZED H/D DAMPERS SET (4) 0.0 0.0

Interior Trim/Lights/Seats

lb kg

D BENCH SEAT WITH CUSHIONS -1.0 -0.5 D BENCH SEAT WITH MESH -9.0 -4.1 FLIGHT TRAILS CONSOLE FACE PLATE 0.0 0.0 FLIGHT TRAILS NVG LIGHTING COMPATABILITY 6.0 2.7 FLIGHT TRAILS OAT GAUGE LIGHT 0.0 0.0 FLIGHT TRAILS POST LIGHT MODIFICATION 0.0 0.0 FLIGHT TRAILS SLANT PANEL 3.0 1.4 INTERIOR -SOUNDPROOF IN SPECIAL COLOR 119.9 54.4 INTERIOR -LEATHER SEATS, PANELS, TRIM, MD 500 20.0 9.1 INTERIOR -BASIC MILITARY BLACK 30.0 13.6 INTERIOR -BASIC MILITARY GRAY 30.0 13.6 INTERIOR -SOUNDPROOF IN BEIGE 119.9 54.4 INTERIOR -SOUNDPROOF IN GRAY 119.9 54.4 INTERIOR -SOUNDPROOF IN OPTIONAL COLORS 0.0 0.0 INTERIOR -VELOUR PANELS IN BEIGE 36.0 16.3 INTERIOR -VELOUR PANELS IN GRAY 36.0 16.3 SEATS -BLACK MESH 2+1 -22.2 -10.1 SEATS -BLACK MESH 2+2 -23.7 -10.8 VINYL INTERIOR TRIM PANELS 0.0 0.0

– 85 –

OPTIONAL EQUIPMENT

Interior Accessories

lb kg

CABIN LIGHTER/28-VOLT UTILITY OUTLET 0.0 0.0 COCKPIT UTILITY-MAP GOOSENECK LIGHT - NVG 3.1 1.4 COCKPIT UTILITY-MAP LUMINATOR LIGHT - NON-NVG 3.1 1.4 COCKPIT UTILITY-MAP LUMINATOR LIGHT - NVG 3.1 1.4 FLIGHT TRAILS INSTRUMENT PANEL MAP CASE 0.5 0.2 FLIGHT TRAILS LH FWD MAP CASE 0.3 0.1 LITTER KIT RIGHT HAND 66.0 29.9 ROTOR BRAKE LH COMMAND 6.7 3.0 ROTOR BRAKE RH COMMAND 6.7 3.0

Nav Special

lb kg

ARGUS 5000 MOVING MAP DISPLAY 3.5 1.6 ARGUS 7000 MOVING MAP DISPLAY 0.0 0.0 FLIGHT TRAILS GPS-VOR SWITCH 0.3 0.1 GARMIN 155 XL GPS 4.3 2.0 GARMIN 250 XL GPS/COMM 5.3 2.4 GARMIN GNS-430 MAP/COMM/VOR/GPS 7.8 3.5 GARMIN GNS-530 MAP/COMM/VOR/GPS 9.8 4.4 KLN90B-01 GPS NORTH AMERICA 8.4 3.8 KLN90B-01 GPS INTERNATIONAL 8.4 3.8 KLX135-00 GPS NORTH AMERICA 0.0 0.0 KLX135-01 INTERNATIONAL 0.0 0.0 MAGELLAN 5000 SKY-NAV GPS 3.0 1.4 RYAN ATS-7000 TCAD 4.0 1.8 RYAN ATS-9900 TCAD 5.0 2.3

– 86 –

OPTIONAL EQUIPMENT

Paint

lb kg

HIGH VISIBILITY MAIN ROTOR BLADE PAINT 0.4 0.2 PAINT 0 COLOR PRIMER ONLY 500 SERIES -20.0 -9.1 PAINT 2 COLOR AMBASSADOR 0.0 0.0 PAINT 2 COLOR CUSTOM 2 0.0 0.0 PAINT 2 COLOR DIPLOMAT 0.0 0.0 PAINT 2 COLOR ENVOY 0.0 0.0 PAINT 2 COLOR STATESMAN 0.0 0.0 PAINT 2 COLOR VICEROY 0.0 0.0 PAINT 3 COLOR AMBASSADOR 0.0 0.0 PAINT 3 COLOR CUSTOM 3 0.0 0.0 PAINT 3 COLOR DIPLOMAT 0.0 0.0 PAINT 3 COLOR ENVOY 0.0 0.0 PAINT 3 COLOR STATESMAN 0.0 0.0 PAINT 3 COLOR VICEROY 0.0 0.0 PAINT 4 COLOR AMBASSADOR 0.0 0.0 PAINT 4 COLOR CUSTOM 4 0.0 0.0 PAINT 4 COLOR DIPLOMAT 0.0 0.0 PAINT 4 COLOR ENVOY 0.0 0.0 PAINT 4 COLOR STATESMAN 0.0 0.0 PAINT 4 COLOR VICEROY 0.0 0.0 PAINT 5 COLOR AMBASSADOR 0.0 0.0 PAINT 5 COLOR CUSTOM 5 0.0 0.0 PAINT 5 COLOR DIPLOMAT 0.0 0.0 PAINT 5 COLOR ENVOY 0.0 0.0 PAINT 5 COLOR STATESMAN 0.0 0.0 PAINT 5 COLOR VICEROY 0.0 0.0

Windows/Canopy

MEEKER QUICK RELEASE ENGINE BAY DOORS 2.1 1.0 MEEKER QUICK RELEASE DOOR HINGES (4) MD 500 7.0 3.2 PARAVION LEFT FRONT DOOR OPENER 1.2 0.5 PARAVION LEFT REAR DOOR OPENER 1.2 0.5 PARAVION RIGHT FRONT DOOR OPENER 1.5 0.7 PARAVION RIGHT REAR DOOR OPENER 1.5 0.7 TECH TOOL LF COMFORT W/POP OUT VENTS 0.0 0.0 TECH TOOL LF COMFORT W/SLIDE 0.0 0.0 TECH TOOL LR COMFORT W/POP OUT VENTS 0.0 0.0 TECH TOOL LR COMFORT W/SLIDE 0.0 0.0 TECH TOOL RF COMFORT W/POP OUT VENTS 0.0 0.0 TECH TOOL RF COMFORT W/SLIDE 0.0 0.0 TECH TOOL RR COMFORT W/POP OUT VENTS 0.0 0.0 TECH TOOL RR COMFORT W/SLIDE 0.0 0.0

lb kg

– 87 –

MDHELICOPTERS,INC. ~ phone1-480-346-6300 ~ fax1-480-346-6339 ~ helicoptersales@mdhelicopters.com ~ www.mdhelicopters.com

MD Helicopters MD500, MD500E, MD530F, MD520N Technical Description

Specifications and Main Features

Frequently Asked Questions

User Manual